<CHAPTER> <SUBCHAP TYPE="N"> <PRTPAGE P="5"/> <HD SOURCE="HED">SUBCHAPTER A—DEFINITIONS</HD> <PART> <EAR>Pt. 1</EAR> <HD SOURCE="HED">PART 1—DEFINITIONS AND ABBREVIATIONS</HD> <CONTENTS> <SECHD>Sec.</SECHD> <SECTNO>1.1</SECTNO> <SUBJECT>General definitions.</SUBJECT> <SECTNO>1.2</SECTNO> <SUBJECT>Abbreviations and symbols.</SUBJECT> <SECTNO>1.3</SECTNO> <SUBJECT>Rules of construction.</SUBJECT> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 49 U.S.C. 106(g), 40113, 44701. </AUTH> <SECTION> <SECTNO>§ 1.1</SECTNO> <SUBJECT>General definitions.</SUBJECT> As used in Subchapters A through K of this chapter, unless the context requires otherwise: <E T="03">Administrator</E> means the Federal Aviation Administrator or any person to whom he has delegated his authority in the matter concerned. <E T="03">Aerodynamic coefficients</E> means non-dimensional coefficients for aerodynamic forces and moments. <E T="03">Air carrier</E> means a person who undertakes directly by lease, or other arrangement, to engage in air transportation. <E T="03">Air commerce</E> means interstate, overseas, or foreign air commerce or the transportation of mail by aircraft or any operation or navigation of aircraft within the limits of any Federal airway or any operation or navigation of aircraft which directly affects, or which may endanger safety in, interstate, overseas, or foreign air commerce. <E T="03">Aircraft</E> means a device that is used or intended to be used for flight in the air. <E T="03">Aircraft engine</E> means an engine that is used or intended to be used for propelling aircraft. It includes turbosuperchargers, appurtenances, and accessories necessary for its functioning, but does not include propellers. <E T="03">Airframe</E> means the fuselage, booms, nacelles, cowlings, fairings, airfoil surfaces (including rotors but excluding propellers and rotating airfoils of engines), and landing gear of an aircraft and their accessories and controls. <E T="03">Airplane</E> means an engine-driven fixed-wing aircraft heavier than air, that is supported in flight by the dynamic reaction of the air against its wings. <E T="03">Airport</E> means an area of land or water that is used or intended to be used for the landing and takeoff of aircraft, and includes its buildings and facilities, if any. <E T="03">Airship</E> means an engine-driven lighter-than-air aircraft that can be steered. <E T="03">Air traffic</E> means aircraft operating in the air or on an airport surface, exclusive of loading ramps and parking areas. <E T="03">Air traffic clearance</E> means an authorization by air traffic control, for the purpose of preventing collision between known aircraft, for an aircraft to proceed under specified traffic conditions within controlled airspace. <E T="03">Air traffic control</E> means a service operated by appropriate authority to promote the safe, orderly, and expeditious flow of air traffic. <E T="03">Air transportation</E> means interstate, overseas, or foreign air transportation or the transportation of mail by aircraft. <E T="03">Alert Area.</E> An alert area is established to inform pilots of a specific area wherein a high volume of pilot training or an unusual type of aeronautical activity is conducted. <E T="03">Alternate airport</E> means an airport at which an aircraft may land if a landing at the intended airport becomes inadvisable. <E T="03">Altitude engine</E> means a reciprocating aircraft engine having a rated takeoff power that is producible from sea level to an established higher altitude. <E T="03">Appliance</E> means any instrument, mechanism, equipment, part, apparatus, appurtenance, or accessory, including communications equipment, that is used or intended to be used in operating or controlling an aircraft in flight, is installed in or attached to the aircraft, and is not part of an airframe, engine, or propeller. <E T="03">Approved</E>, unless used with reference to another person, means approved by the Administrator. <E T="03">Area navigation (RNAV)</E> means a method of navigation that permits aircraft operations on any desired course within the coverage of station-referenced navigation signals or within the limits of self-contained system capability.<PRTPAGE P="6"/> <E T="03">Area navigation low route</E> means an area navigation route within the airspace extending upward from 1,200 feet above the surface of the earth to, but not including, 18,000 feet MSL. <E T="03">Area navigation high route</E> means an area navigation route within the airspace extending upward from, and including, 18,000 feet MSL to flight level 450. <E T="03">Armed Forces</E> means the Army, Navy, Air Force, Marine Corps, and Coast Guard, including their regular and reserve components and members serving without component status. <E T="03">Autorotation</E> means a rotorcraft flight condition in which the lifting rotor is driven entirely by action of the air when the rotorcraft is in motion. <E T="03">Auxiliary rotor</E> means a rotor that serves either to counteract the effect of the main rotor torque on a rotorcraft or to maneuver the rotorcraft about one or more of its three principal axes. <E T="03">Balloon</E> means a lighter-than-air aircraft that is not engine driven, and that sustains flight through the use of either gas buoyancy or an airborne heater. <E T="03">Brake horsepower</E> means the power delivered at the propeller shaft (main drive or main output) of an aircraft engine. <E T="03">Calibrated airspeed</E> means the indicated airspeed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. <E T="03">Canard</E> means the forward wing of a canard configuration and may be a fixed, movable, or variable geometry surface, with or without control surfaces. <E T="03">Canard configuration</E> means a configuration in which the span of the forward wing is substantially less than that of the main wing. <E T="03">Category:</E> (1) As used with respect to the certification, ratings, privileges, and limitations of airmen, means a broad classification of aircraft. Examples include: airplane; rotorcraft; glider; and lighter-than-air; and (2) As used with respect to the certification of aircraft, means a grouping of aircraft based upon intended use or operating limitations. Examples include: transport, normal, utility, acrobatic, limited, restricted, and provisional. <E T="03">Category A,</E> with respect to transport category rotorcraft, means multiengine rotorcraft designed with engine and system isolation features specified in Part 29 and utilizing scheduled takeoff and landing operations under a critical engine failure concept which assures adequate designated surface area and adequate performance capability for continued safe flight in the event of engine failure. <E T="03">Category B,</E> with respect to transport category rotorcraft, means single-engine or multiengine rotorcraft which do not fully meet all Category A standards. Category B rotorcraft have no guaranteed stay-up ability in the event of engine failure and unscheduled landing is assumed. <E T="03">Category II operations</E>, with respect to the operation of aircraft, means a straight-in ILS approach to the runway of an airport under a Category II ILS instrument approach procedure issued by the Administrator or other appropriate authority. <E T="03">Category III operations,</E> with respect to the operation of aircraft, means an ILS approach to, and landing on, the runway of an airport using a Category III ILS instrument approach procedure issued by the Administrator or other appropriate authority. <E T="03">Category IIIa operations,</E> an ILS approach and landing with no decision height (DH), or a DH below 100 feet (30 meters), and controlling runway visual range not less than 700 feet (200 meters). <E T="03">Category IIIb operations,</E> an ILS approach and landing with no DH, or with a DH below 50 feet (15 meters), and controlling runway visual range less than 700 feet (200 meters), but not less than 150 feet (50 meters). <E T="03">Category IIIc operations,</E> an ILS approach and landing with no DH and no runway visual range limitation. <E T="03">Ceiling</E> means the height above the earth's surface of the lowest layer of clouds or obscuring phenomena that is reported as “broken”, “overcast”, or “obscuration”, and not classified as “thin” or “partial”. <E T="03">Civil aircraft</E> means aircraft other than public aircraft.<PRTPAGE P="7"/> <E T="03">Class:</E> (1) As used with respect to the certification, ratings, privileges, and limitations of airmen, means a classification of aircraft within a category having similar operating characteristics. Examples include: single engine; multiengine; land; water; gyroplane; helicopter; airship; and free balloon; and (2) As used with respect to the certification of aircraft, means a broad grouping of aircraft having similar characteristics of propulsion, flight, or landing. Examples include: airplane; rotorcraft; glider; balloon; landplane; and seaplane. <E T="03">Clearway</E> means: (1) For turbine engine powered airplanes certificated after August 29, 1959, an area beyond the runway, not less than 500 feet wide, centrally located about the extended centerline of the runway, and under the control of the airport authorities. The clearway is expressed in terms of a clearway plane, extending from the end of the runway with an upward slope not exceeding 1.25 percent, above which no object nor any terrain protrudes. However, threshold lights may protrude above the plane if their height above the end of the runway is 26 inches or less and if they are located to each side of the runway. (2) For turbine engine powered airplanes certificated after September 30, 1958, but before August 30, 1959, an area beyond the takeoff runway extending no less than 300 feet on either side of the extended centerline of the runway, at an elevation no higher than the elevation of the end of the runway, clear of all fixed obstacles, and under the control of the airport authorities. <E T="03">Climbout speed,</E> with respect to rotorcraft, means a referenced airspeed which results in a flight path clear of the height-velocity envelope during initial climbout. <E T="03">Commercial operator</E> means a person who, for compensation or hire, engages in the carriage by aircraft in air commerce of persons or property, other than as an air carrier or foreign air carrier or under the authority of Part 375 of this title. Where it is doubtful that an operation is for “compensation or hire”, the test applied is whether the carriage by air is merely incidental to the person's other business or is, in itself, a major enterprise for profit. <E T="03">Controlled airspace</E> means an airspace of defined dimensions within which air traffic control service is provided to IFR flights and to VFR flights in accordance with the airspace classification. <NOTE> <HD SOURCE="HED">Note:</HD> Controlled airspace is a generic term that covers Class A, Class B, Class C, Class D, and Class E airspace. </NOTE> <E T="03">Controlled Firing Area.</E> A controlled firing area is established to contain activities, which if not conducted in a controlled environment, would be hazardous to nonparticipating aircraft. <E T="03">Crewmember</E> means a person assigned to perform duty in an aircraft during flight time. <E T="03">Critical altitude</E> means the maximum altitude at which, in standard atmosphere, it is possible to maintain, at a specified rotational speed, a specified power or a specified manifold pressure. Unless otherwise stated, the critical altitude is the maximum altitude at which it is possible to maintain, at the maximum continuous rotational speed, one of the following: (1) The maximum continuous power, in the case of engines for which this power rating is the same at sea level and at the rated altitude. (2) The maximum continuous rated manifold pressure, in the case of engines, the maximum continuous power of which is governed by a constant manifold pressure. <E T="03">Critical engine</E> means the engine whose failure would most adversely affect the performance or handling qualities of an aircraft. <E T="03">Decision height,</E> with respect to the operation of aircraft, means the height at which a decision must be made, during an ILS or PAR instrument approach, to either continue the approach or to execute a missed approach. <E T="03">Equivalent airspeed</E> means the calibrated airspeed of an aircraft corrected for adiabatic compressible flow for the particular altitude. Equivalent airspeed is equal to calibrated airspeed in standard atmosphere at sea level. <E T="03">Extended over-water operation</E> means— (1) With respect to aircraft other than helicopters, an operation over water at a horizontal distance of more <PRTPAGE P="8"/>than 50 nautical miles from the nearest shoreline; and (2) With respect to helicopters, an operation over water at a horizontal distance of more than 50 nautical miles from the nearest shoreline and more than 50 nautical miles from an off-shore heliport structure. <E T="03">External load</E> means a load that is carried, or extends, outside of the aircraft fuselage. <E T="03">External-load attaching means</E> means the structural components used to attach an external load to an aircraft, including external-load containers, the backup structure at the attachment points, and any quick-release device used to jettison the external load. <E T="03">Fireproof</E>— (1) With respect to materials and parts used to confine fire in a designated fire zone, means the capacity to withstand at least as well as steel in dimensions appropriate for the purpose for which they are used, the heat produced when there is a severe fire of extended duration in that zone; and (2) With respect to other materials and parts, means the capacity to withstand the heat associated with fire at least as well as steel in dimensions appropriate for the purpose for which they are used. <E T="03">Fire resistant</E>— (1) With respect to sheet or structural members means the capacity to withstand the heat associated with fire at least as well as aluminum alloy in dimensions appropriate for the purpose for which they are used; and (2) With respect to fluid-carrying lines, fluid system parts, wiring, air ducts, fittings, and powerplant controls, means the capacity to perform the intended functions under the heat and other conditions likely to occur when there is a fire at the place concerned. <E T="03">Flame resistant</E> means not susceptible to combustion to the point of propagating a flame, beyond safe limits, after the ignition source is removed. <E T="03">Flammable</E>, with respect to a fluid or gas, means susceptible to igniting readily or to exploding. <E T="03">Flap extended speed</E> means the highest speed permissible with wing flaps in a prescribed extended position. <E T="03">Flash resistant</E> means not susceptible to burning violently when ignited. <E T="03">Flightcrew member</E> means a pilot, flight engineer, or flight navigator assigned to duty in an aircraft during flight time. <E T="03">Flight level</E> means a level of constant atmospheric pressure related to a reference datum of 29.92 inches of mercury. Each is stated in three digits that represent hundreds of feet. For example, flight level 250 represents a barometric altimeter indication of 25,000 feet; flight level 255, an indication of 25,500 feet. <E T="03">Flight plan</E> means specified information, relating to the intended flight of an aircraft, that is filed orally or in writing with air traffic control. <E T="03">Flight time</E> means: (1) Pilot time that commences when an aircraft moves under its own power for the purpose of flight and ends when the aircraft comes to rest after landing; or (2) For a glider without self-launch capability, pilot time that commences when the glider is towed for the purpose of flight and ends when the glider comes to rest after landing. <E T="03">Flight visibility</E> means the average forward horizontal distance, from the cockpit of an aircraft in flight, at which prominent unlighted objects may be seen and identified by day and prominent lighted objects may be seen and identified by night. <E T="03">Foreign air carrier</E> means any person other than a citizen of the United States, who undertakes directly, by lease or other arrangement, to engage in air transportation. <E T="03">Foreign air commerce</E> means the carriage by aircraft of persons or property for compensation or hire, or the carriage of mail by aircraft, or the operation or navigation of aircraft in the conduct or furtherance of a business or vocation, in commerce between a place in the United States and any place outside thereof; whether such commerce moves wholly by aircraft or partly by aircraft and partly by other forms of transportation. <E T="03">Foreign air transportation</E> means the carriage by aircraft of persons or property as a common carrier for compensation or hire, or the carriage of mail by aircraft, in commerce between <PRTPAGE P="9"/>a place in the United States and any place outside of the United States, whether that commerce moves wholly by aircraft or partly by aircraft and partly by other forms of transportation. <E T="03">Forward wing</E> means a forward lifting surface of a canard configuration or tandem-wing configuration airplane. The surface may be a fixed, movable, or variable geometry surface, with or without control surfaces. <E T="03">Glider</E> means a heavier-than-air aircraft, that is supported in flight by the dynamic reaction of the air against its lifting surfaces and whose free flight does not depend principally on an engine. <E T="03">Ground visibility</E> means prevailing horizontal visibility near the earth's surface as reported by the United States National Weather Service or an accredited observer. <E T="03">Go-around power or thrust setting</E> means the maximum allowable in-flight power or thrust setting identified in the performance data. <E T="03">Gyrodyne</E> means a rotorcraft whose rotors are normally engine-driven for takeoff, hovering, and landing, and for forward flight through part of its speed range, and whose means of propulsion, consisting usually of conventional propellers, is independent of the rotor system. <E T="03">Gyroplane</E> means a rotorcraft whose rotors are not engine-driven, except for initial starting, but are made to rotate by action of the air when the rotorcraft is moving; and whose means of propulsion, consisting usually of conventional propellers, is independent of the rotor system. <E T="03">Helicopter</E> means a rotorcraft that, for its horizontal motion, depends principally on its engine-driven rotors. <E T="03">Heliport</E> means an area of land, water, or structure used or intended to be used for the landing and takeoff of helicopters. <E T="03">Idle thrust</E> means the jet thrust obtained with the engine power control level set at the stop for the least thrust position at which it can be placed. <E T="03">IFR conditions</E> means weather conditions below the minimum for flight under visual flight rules. <E T="03">IFR over-the-top</E>, with respect to the operation of aircraft, means the operation of an aircraft over-the-top on an IFR flight plan when cleared by air traffic control to maintain “VFR conditions” or “VFR conditions on top”. <E T="03">Indicated airspeed</E> means the speed of an aircraft as shown on its pitot static airspeed indicator calibrated to reflect standard atmosphere adiabatic compressible flow at sea level uncorrected for airspeed system errors. <E T="03">Instrument</E> means a device using an internal mechanism to show visually or aurally the attitude, altitude, or operation of an aircraft or aircraft part. It includes electronic devices for automatically controlling an aircraft in flight. <E T="03">Interstate air commerce</E> means the carriage by aircraft of persons or property for compensation or hire, or the carriage of mail by aircraft, or the operation or navigation of aircraft in the conduct or furtherance of a business or vocation, in commerce between a place in any State of the United States, or the District of Columbia, and a place in any other State of the United States, or the District of Columbia; or between places in the same State of the United States through the airspace over any place outside thereof; or between places in the same territory or possession of the United States, or the District of Columbia. <E T="03">Interstate air transportation</E> means the carriage by aircraft of persons or property as a common carrier for compensation or hire, or the carriage of mail by aircraft in commerce: (1) Between a place in a State or the District of Columbia and another place in another State or the District of Columbia; (2) Between places in the same State through the airspace over any place outside that State; or (3) Between places in the same possession of the United States; <FP>Whether that commerce moves wholly by aircraft of partly by aircraft and partly by other forms of transportation.</FP> <E T="03">Intrastate air transportation</E> means the carriage of persons or property as a common carrier for compensation or hire, by turbojet-powered aircraft capable of carrying thirty or more persons, wholly within the same State of the United States.<PRTPAGE P="10"/> <E T="03">Kite</E> means a framework, covered with paper, cloth, metal, or other material, intended to be flown at the end of a rope or cable, and having as its only support the force of the wind moving past its surfaces. <E T="03">Landing gear extended speed</E> means the maximum speed at which an aircraft can be safely flown with the landing gear extended. <E T="03">Landing gear operating speed</E> means the maximum speed at which the landing gear can be safely extended or retracted. <E T="03">Large aircraft</E> means aircraft of more than 12,500 pounds, maximum certificated takeoff weight. <E T="03">Lighter-than-air aircraft</E> means aircraft that can rise and remain suspended by using contained gas weighing less than the air that is displaced by the gas. <E T="03">Load factor</E> means the ratio of a specified load to the total weight of the aircraft. The specified load is expressed in terms of any of the following: aerodynamic forces, inertia forces, or ground or water reactions. <E T="03">Long-range communication system (LRCS).</E> A system that uses satellite relay, data link, high frequency, or another approved communication system which extends beyond line of sight. <E T="03">Long-range navigation system (LRNS).</E> An electronic navigation unit that is approved for use under instrument flight rules as a primary means of navigation, and has at least one source of navigational input, such as inertial navigation system, global positioning system, Omega/very low frequency, or Loran C. <E T="03">Mach number</E> means the ratio of true airspeed to the speed of sound. <E T="03">Main rotor</E> means the rotor that supplies the principal lift to a rotorcraft. <E T="03">Maintenance</E> means inspection, overhaul, repair, preservation, and the replacement of parts, but excludes preventive maintenance. <E T="03">Major alteration</E> means an alteration not listed in the aircraft, aircraft engine, or propeller specifications— (1) That might appreciably affect weight, balance, structural strength, performance, powerplant operation, flight characteristics, or other qualities affecting airworthiness; or (2) That is not done according to accepted practices or cannot be done by elementary operations. <E T="03">Major repair</E> means a repair: (1) That, if improperly done, might appreciably affect weight, balance, structural strength, performance, powerplant operation, flight characteristics, or other qualities affecting airworthiness; or (2) That is not done according to accepted practices or cannot be done by elementary operations. <E T="03">Manifold pressure</E> means absolute pressure as measured at the appropriate point in the induction system and usually expressed in inches of mercury. <E T="03">Maximum speed for stability characteristics, V</E> <E T="52">FC</E>/M<E T="52">FC</E> means a speed that may not be less than a speed midway between maximum operating limit speed (V<E T="52">MO</E>/M<E T="52">MO</E>) and demonstrated flight diving speed (V<E T="52">DF</E>/M<E T="52">DF</E>), except that, for altitudes where the Mach number is the limiting factor, M<E T="52">FC</E> need not exceed the Mach number at which effective speed warning occurs. <E T="03">Medical certificate</E> means acceptable evidence of physical fitness on a form prescribed by the Administrator. <E T="03">Military operations area.</E> A military operations area (MOA) is airspace established outside Class A airspace to separate or segregate certain nonhazardous military activities from IFR Traffic and to identify for VFR traffic where theses activities are conducted. <E T="03">Minimum descent altitude</E> means the lowest altitude, expressed in feet above mean sea level, to which descent is authorized on final approach or during circle-to-land maneuvering in execution of a standard instrument approach procedure, where no electronic glide slope is provided. <E T="03">Minor alteration</E> means an alteration other than a major alteration. <E T="03">Minor repair</E> means a repair other than a major repair. <E T="03">Navigable airspace</E> means airspace at and above the minimum flight altitudes prescribed by or under this chapter, including airspace needed for safe takeoff and landing. <E T="03">Night</E> means the time between the end of evening civil twilight and the beginning of morning civil twilight, as <PRTPAGE P="11"/>published in the American Air Almanac, converted to local time. <E T="03">Nonprecision approach procedure</E> means a standard instrument approach procedure in which no electronic glide slope is provided. <E T="03">Operate,</E> with respect to aircraft, means use, cause to use or authorize to use aircraft, for the purpose (except as provided in § 91.13 of this chapter) of air navigation including the piloting of aircraft, with or without the right of legal control (as owner, lessee, or otherwise). <E T="03">Operational control</E>, with respect to a flight, means the exercise of authority over initiating, conducting or terminating a flight. <E T="03">Overseas air commerce</E> means the carriage by aircraft of persons or property for compensation or hire, or the carriage of mail by aircraft, or the operation or navigation of aircraft in the conduct or furtherance of a business or vocation, in commerce between a place in any State of the United States, or the District of Columbia, and any place in a territory or possession of the United States; or between a place in a territory or possession of the United States, and a place in any other territory or possession of the United States. <E T="03">Overseas air transportation</E> means the carriage by aircraft of persons or property as a common carrier for compensation or hire, or the carriage of mail by aircraft, in commerce: (1) Between a place in a State or the District of Columbia and a place in a possession of the United States; or (2) Between a place in a possession of the United States and a place in another possession of the United States; whether that commerce moves wholly by aircraft or partly by aircraft and partly by other forms of transportation. <E T="03">Over-the-top</E> means above the layer of clouds or other obscuring phenomena forming the ceiling. <E T="03">Parachute</E> means a device used or intended to be used to retard the fall of a body or object through the air. <E T="03">Person</E> means an individual, firm, partnership, corporation, company, association, joint-stock association, or governmental entity. It includes a trustee, receiver, assignee, or similar representative of any of them. <E T="03">Pilotage</E> means navigation by visual reference to landmarks. <E T="03">Pilot in command</E> means the person who: (1) Has final authority and responsibility for the operation and safety of the flight; (2) Has been designated as pilot in command before or during the flight; and (3) Holds the appropriate category, class, and type rating, if appropriate, for the conduct of the flight. <E T="03">Pitch setting</E> means the propeller blade setting as determined by the blade angle measured in a manner, and at a radius, specified by the instruction manual for the propeller. <E T="03">Positive control</E> means control of all air traffic, within designated airspace, by air traffic control. <E T="03">Powered-lift</E> means a heavier-than-air aircraft capable of vertical takeoff, vertical landing, and low speed flight that depends principally on engine-driven lift devices or engine thrust for lift during these flight regimes and on nonrotating airfoil(s) for lift during horizontal flight. <E T="03">Precision approach procedure</E> means a standard instrument approach procedure in which an electronic glide slope is provided, such as ILS and PAR. <E T="03">Preventive maintenance</E> means simple or minor preservation operations and the replacement of small standard parts not involving complex assembly operations. <E T="03">Prohibited area.</E> A prohibited area is airspace designated under part 73 within which no person may operate an aircraft without the permission of the using agency. <E T="03">Propeller</E> means a device for propelling an aircraft that has blades on an engine-driven shaft and that, when rotated, produces by its action on the air, a thrust approximately perpendicular to its plane of rotation. It includes control components normally supplied by its manufacturer, but does not include main and auxiliary rotors or rotating airfoils of engines. <E T="03">Public aircraft</E> means an aircraft used only for the United States Government, or owned and operated (except for commercial purposes), or exclusively leased for at least 90 continuous days, by a government (except the <PRTPAGE P="12"/>United States Government), including a State, the District of Columbia, or a territory or possession of the United States, or political subdivision of that government; but does not include a government-owned aircraft transporting property for commercial purposes, or transporting passengers other than transporting (for other than commercial purposes) crewmembers or other persons aboard the aircraft whose presence is required to perform, or is associated with the performance of, a governmental function such as firefighting, search and rescue, law enforcement, aeronautical research, or biological or geological resource management; or transporting (for other than commercial purposes) persons aboard the aircraft if the aircraft is operated by the Armed Forces or an intelligence agency of the United States. An aircraft described in the preceding sentence shall, notwithstanding any limitation relating to use of the aircraft for commercial purposes, be considered to be a public aircraft for the purposes of this Chapter without regard to whether the aircraft is operated by a unit of government on behalf of another unit of government, pursuant to a cost reimbursement agreement between such units of government, if the unit of government on whose behalf the operation is conducted certifies to the Administrator of the Federal Aviation Administration that the operation was necessary to respond to a significant and imminent threat to life or property (including natural resources) and that no service by a private operator was reasonably available to meet the threat. <E T="03">Rated 30-second OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under part 33 of this chapter, for continued one-flight operation after the failure of one engine in multiengine rotorcraft, limited to three periods of use no longer than 30 seconds each in any one flight, and followed by mandatory inspection and prescribed maintenance action. <E T="03">Rated 2-minute OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under part 33 of this chapter, for continued one-flight operation after the failure of one engine in multiengine rotorcraft, limited to three periods of use no longer than 2 minutes each in any one flight, and followed by mandatory inspection and prescribed maintenance action. <E T="03">Rated continuous OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Part 33 of this chapter, and limited in use to the time required to complete the flight after the failure of one engine of a multiengine rotorcraft. <E T="03">Rated maximum continuous augmented thrust</E>, with respect to turbojet engine type certification, means the approved jet thrust that is developed statically or in flight, in standard atmosphere at a specified altitude, with fluid injection or with the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Part 33 of this chapter, and approved for unrestricted periods of use. <E T="03">Rated maximum continuous power,</E> with respect to reciprocating, turbopropeller, and turboshaft engines, means the approved brake horsepower that is developed statically or in flight, in standard atmosphere at a specified altitude, within the engine operating limitations established under Part 33, and approved for unrestricted periods of use. <E T="03">Rated maximum continuous thrust</E>, with respect to turbojet engine type certification, means the approved jet thrust that is developed statically or in flight, in standard atmosphere at a specified altitude, without fluid injection and without the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Part 33 of this chapter, and approved for unrestricted periods of use.<PRTPAGE P="13"/> <E T="03">Rated takeoff augmented thrust</E>, with respect to turbojet engine type certification, means the approved jet thrust that is developed statically under standard sea level conditions, with fluid injection or with the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Part 33 of this chapter, and limited in use to periods of not over 5 minutes for -takeoff operation. <E T="03">Rated takeoff power</E>, with respect to reciprocating, turbopropeller, and turboshaft engine type certification, means the approved brake horsepower that is developed statically under standard sea level conditions, within the engine operating limitations established under Part 33, and limited in use to periods of not over 5 minutes for takeoff operation. <E T="03">Rated takeoff thrust</E>, with respect to turbojet engine type certification, means the approved jet thrust that is developed statically under standard sea level conditions, without fluid injection and without the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Part 33 of this chapter, and limited in use to periods of not over 5 minutes for takeoff operation. <E T="03">Rated 30-minute OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Part 33 of this chapter, and limited in use to a period of not more than 30 minutes after the failure of one engine of a multiengine rotorcraft. <E T="03">Rated 2\1/2\-minute OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Part 33 of this chapter, and limited in use to a period of not more than 2<FR>1/2</FR> minutes after the failure of one engine of a multiengine rotorcraft. <E T="03">Rating</E> means a statement that, as a part of a certificate, sets forth special conditions, privileges, or limitations. <E T="03">Reporting point</E> means a geographical location in relation to which the position of an aircraft is reported. <E T="03">Restricted area.</E> A restricted area is airspace designated under Part 73 within which the flight of aircraft, while not wholly prohibited, is subject to restriction. <E T="03">RNAV way point (W/P)</E> means a predetermined geographical position used for route or instrument approach definition or progress reporting purposes that is defined relative to a VORTAC station position. <E T="03">Rocket</E> means an aircraft propelled by ejected expanding gases generated in the engine from self-contained propellants and not dependent on the intake of outside substances. It includes any part which becomes separated during the operation. <E T="03">Rotorcraft</E> means a heavier-than-air aircraft that depends principally for its support in flight on the lift generated by one or more rotors. <E T="03">Rotorcraft-load combination</E> means the combination of a rotorcraft and an external-load, including the external-load attaching means. Rotorcraft-load combinations are designated as Class A, Class B, Class C, and Class D, as follows: (1) <E T="03">Class A rotorcraft-load combination</E> means one in which the external load cannot move freely, cannot be jettisoned, and does not extend below the landing gear. (2) <E T="03">Class B rotorcraft-load combination</E> means one in which the external load is jettisonable and is lifted free of land or water during the rotorcraft operation. (3) <E T="03">Class C rotorcraft-load combination</E> means one in which the external load is jettisonable and remains in contact with land or water during the rotorcraft operation. (4) <E T="03">Class D rotorcraft-load combination</E> means one in which the external-load is other than a Class A, B, or C and has been specifically approved by the Administrator for that operation. <E T="03">Route segment</E> means a part of a route. Each end of that part is identified by: (1) A continental or insular geographical location; or (2) A point at which a definite radio fix can be established.<PRTPAGE P="14"/> <E T="03">Sea level engine</E> means a reciprocating aircraft engine having a rated takeoff power that is producible only at sea level. <E T="03">Second in command</E> means a pilot who is designated to be second in command of an aircraft during flight time. <E T="03">Show</E>, unless the context otherwise requires, means to show to the satisfaction of the Administrator. <E T="03">Small aircraft</E> means aircraft of 12,500 pounds or less, maximum certificated takeoff weight. <E T="03">Special VFR conditions</E> mean meteorological conditions that are less than those required for basic VFR flight in controlled airspace and in which some aircraft are permitted flight under visual flight rules. <E T="03">Special VFR operations</E> means aircraft operating in accordance with clearances within controlled airspace in meteorological conditions less than the basic VFR weather minima. Such operations must be requested by the pilot and approved by ATC. <E T="03">Standard atmosphere</E> means the atmosphere defined in U.S. Standard Atmosphere, 1962 (Geopotential altitude tables). <E T="03">Stopway</E> means an area beyond the takeoff runway, no less wide than the runway and centered upon the extended centerline of the runway, able to support the airplane during an aborted takeoff, without causing structural damage to the airplane, and designated by the airport authorities for use in decelerating the airplane during an aborted takeoff. <E T="03">Takeoff power:</E> (1) With respect to reciprocating engines, means the brake horsepower that is developed under standard sea level conditions, and under the maximum conditions of crankshaft rotational speed and engine manifold pressure approved for the normal takeoff, and limited in continuous use to the period of time shown in the approved engine specification; and (2) With respect to turbine engines, means the brake horsepower that is developed under static conditions at a specified altitude and atmospheric temperature, and under the maximum conditions of rotor shaft rotational speed and gas temperature approved for the normal takeoff, and limited in continuous use to the period of time shown in the approved engine specification. <E T="03">Takeoff safety speed</E> means a referenced airspeed obtained after lift-off at which the required one-engine-inoperative climb performance can be achieved. <E T="03">Takeoff thrust</E>, with respect to turbine engines, means the jet thrust that is developed under static conditions at a specific altitude and atmospheric temperature under the maximum conditions of rotorshaft rotational speed and gas temperature approved for the normal takeoff, and limited in continuous use to the period of time shown in the approved engine specification. <E T="03">Tandem wing configuration</E> means a configuration having two wings of similar span, mounted in tandem. <E T="03">TCAS I</E> means a TCAS that utilizes interrogations of, and replies from, airborne radar beacon transponders and provides traffic advisories to the pilot. <E T="03">TCAS II</E> means a TCAS that utilizes interrogations of, and replies from airborne radar beacon transponders and provides traffic advisories and resolution advisories in the vertical plane. <E T="03">TCAS III</E> means a TCAS that utilizes interrogation of, and replies from, airborne radar beacon transponders and provides traffic advisories and resolution advisories in the vertical and horizontal planes to the pilot. <E T="03">Time in service</E>, with respect to maintenance time records, means the time from the moment an aircraft leaves the surface of the earth until it touches it at the next point of landing. <E T="03">True airspeed</E> means the airspeed of an aircraft relative to undisturbed air. True airspeed is equal to equivalent airspeed multiplied by (<E T="22">ρ</E>0/<E T="22">ρ</E>)<E T="21">1/2</E>. <E T="03">Traffic pattern</E> means the traffic flow that is prescribed for aircraft landing at, taxiing on, or taking off from, an airport. <E T="03">Type:</E> (1) As used with respect to the certification, ratings, privileges, and limitations of airmen, means a specific make and basic model of aircraft, including modifications thereto that do not change its handling or flight characteristics. Examples include: DC-7, 1049, and F-27; and<PRTPAGE P="15"/> (2) As used with respect to the certification of aircraft, means those aircraft which are similar in design. Examples include: DC-7 and DC-7C; 1049G and 1049H; and F-27 and F-27F. (3) As used with respect to the certification of aircraft engines means those engines which are similar in design. For example, JT8D and JT8D-7 are engines of the same type, and JT9D-3A and JT9D-7 are engines of the same type. <E T="03">United States</E>, in a geographical sense, means (1) the States, the District of Columbia, Puerto Rico, and the possessions, including the territorial waters, and (2) the airspace of those areas. <E T="03">United States air carrier</E> means a citizen of the United States who undertakes directly by lease, or other arrangement, to engage in air transportation. <E T="03">VFR over-the-top</E>, with respect to the operation of aircraft, means the operation of an aircraft over-the-top under VFR when it is not being operated on an IFR flight plan. <E T="03">Warning area.</E> A warning area is airspace of defined dimensions, extending from 3 nautical miles outward from the coast of the United States, that contains activity that may be hazardous to nonparticipating aircraft. The purpose of such warning areas is to warn nonparticipating pilots of the potential danger. A warning area may be located over domestic or international waters or both. <E T="03">Winglet or tip fin</E> means an out-of-plane surface extending from a lifting surface. The surface may or may not have control surfaces. <CITA>[Doc. No. 1150, 27 FR 4588, May 15, 1962]</CITA> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For <E T="04">Federal Register</E> citations affecting § 1.1, see the List of CFR Sections Affected appearing in the Finding Aids section of this volume. </EDNOTE> </SECTION> <SECTION> <SECTNO>§ 1.2</SECTNO> <SUBJECT>Abbreviations and symbols.</SUBJECT> In Subchapters A through K of this chapter: <E T="03">AGL</E> means above ground level. <E T="03">ALS</E> means approach light system. <E T="03">ASR</E> means airport surveillance radar. <E T="03">ATC</E> means air traffic control. <E T="03">CAS</E> means calibrated airspeed. <E T="03">CAT II</E> means Category II. <E T="03">CONSOL</E> or <E T="03">CONSOLAN</E> means a kind of low or medium frequency long range navigational aid. <E T="03">DH</E> means decision height. <E T="03">DME</E> means distance measuring equipment compatible with TACAN. <E T="03">EAS</E> means equivalent airspeed. <E T="03">FAA</E> means Federal Aviation Administration. <E T="03">FM</E> means fan marker. <E T="03">GS</E> means glide slope. <E T="03">HIRL</E> means high-intensity runway light system. <E T="03">IAS</E> means indicated airspeed. <E T="03">ICAO</E> means International Civil Aviation Organization. <E T="03">IFR</E> means instrument flight rules. <E T="03">ILS</E> means instrument landing system. <E T="03">IM</E> means ILS inner marker. <E T="03">INT</E> means intersection. <E T="03">LDA</E> means localizer-type directional aid. <E T="03">LFR</E> means low-frequency radio range. <E T="03">LMM</E> means compass locator at middle marker. <E T="03">LOC</E> means ILS localizer. <E T="03">LOM</E> means compass locator at outer marker. <E T="03">M</E> means mach number. <E T="03">MAA</E> means maximum authorized IFR altitude. <E T="03">MALS</E> means medium intensity approach light system. <E T="03">MALSR</E> means medium intensity approach light system with runway alignment indicator lights. <E T="03">MCA</E> means minimum crossing altitude. <E T="03">MDA</E> means minimum descent altitude. <E T="03">MEA</E> means minimum en route IFR altitude. <E T="03">MM</E> means ILS middle marker. <E T="03">MOCA</E> means minimum obstruction clearance altitude. <E T="03">MRA</E> means minimum reception altitude. <E T="03">MSL</E> means mean sea level. <E T="03">NDB(ADF)</E> means nondirectional beacon (automatic direction finder). <E T="03">NOPT</E> means no procedure turn required. <E T="03">OEI</E> means one engine inoperative. <E T="03">OM</E> means ILS outer marker. <E T="03">PAR</E> means precision approach radar. <E T="03">RAIL</E> means runway alignment indicator light system.<PRTPAGE P="16"/> <E T="03">RBN</E> means radio beacon. <E T="03">RCLM</E> means runway centerline marking. <E T="03">RCLS</E> means runway centerline light system. <E T="03">REIL</E> means runway end identification lights. ‘<E T="03">RR</E>” means low or medium frequency radio range station. <E T="03">RVR</E> means runway visual range as measured in the touchdown zone area. <E T="03">SALS</E> means short approach light system. <E T="03">SSALS</E> means simplified short approach light system. <E T="03">SSALSR</E> means simplified short approach light system with runway alignment indicator lights. <E T="03">TACAN</E> means ultra-high frequency tactical air navigational aid. <E T="03">TAS</E> means true airspeed. <E T="03">TCAS</E> means a traffic alert and collision avoidance system. <E T="03">TDZL</E> means touchdown zone lights. <E T="03">TVOR</E> means very high frequency terminal omnirange station. <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">A</E> means design maneuvering speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">B</E> means design speed for maximum gust intensity.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">C</E> means design cruising speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">D</E> means design diving speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">DF</E>/<E T="03">M</E> <E T="24">DF</E> means demonstrated flight diving speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">EF</E> means the speed at which the critical engine is assumed to fail during takeoff.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">F</E> means design flap speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">FC</E>/<E T="03">M</E> <E T="24">FC</E> means maximum speed for stability characteristics.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">FE</E> means maximum flap extended speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">H</E> means maximum speed in level flight with maximum continuous power.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">LE</E> means maximum landing gear extended speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">LO</E> means maximum landing gear operating speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">LOF</E> means lift-off speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">MC</E> means minimum control speed with the critical engine inoperative.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> means maximum operating limit speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">MU</E> means minimum unstick speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">NE</E> means never-exceed speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">NO</E> means maximum structural cruising speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">R</E> means rotation speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">S</E> means the stalling speed or the minimum steady flight speed at which the airplane is controllable.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">S</E> <E T="22">0</E> means the stalling speed or the minimum steady flight speed in the landing configuration.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">S</E> <E T="22">1</E> means the stalling speed or the minimum steady flight speed obtained in a specific configuration.</FP> <FP SOURCE="FP-1">V<E T="54">TOSS</E> means takeoff safety speed for Category A rotorcraft.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">X</E> means speed for best angle of climb.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">Y</E> means speed for best rate of climb.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="22">1</E> means the maximum speed in the takeoff at which the pilot must take the first action (e.g., apply brakes, reduce thrust, deploy speed brakes) to stop the airplane within the accelerate-stop distance. V<E T="52">1</E> also means the minimum speed in the takeoff, following a failure of the critical engine at V<E T="52">EF</E>, at which the pilot can continue the takeoff and achieve the required height above the takeoff surface within the takeoff distance.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="22">2</E> means takeoff safety speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="22">2</E> min means minimum takeoff safety speed.</FP> <E T="03">VFR</E> means visual flight rules. <E T="03">VHF</E> means very high frequency. <E T="03">VOR</E> means very high frequency omnirange station. ‘<E T="03">ORTAC</E> means collocated VOR and TACAN. <CITA>[Doc. No. 1150, 27 FR 4590, May 15, 1962]</CITA> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For <E T="04">Federal Register</E> citations affecting § 1.2, see the List of CFR Sections Affected appearing in the Finding Aids, section of this volume. </EDNOTE> </SECTION> <SECTION> <SECTNO>§ 1.3</SECTNO> <SUBJECT>Rules of construction.</SUBJECT> (a) In Subchapters A through K of this chapter, unless the context requires otherwise: (1) Words importing the singular include the plural; (2) Words importing the plural include the singular; and (3) Words importing the masculine gender include the feminine. (b) In Subchapters A through K of this chapter, the word: (1) <E T="03">Shall</E> is used in an imperative sense; (2) <E T="03">May</E> is used in a permissive sense to state authority or permission to do the act prescribed, and the words “no person may * * *” or “a person may <PRTPAGE P="17"/>not * * *” mean that no person is required, authorized, or permitted to do the act prescribed; and (3) <E T="03">Includes</E> means “includes but is not limited to”. <CITA>[Doc. No. 1150, 27 FR 4590, May 15, 1962, as amended by Amdt. 1-10, 31 FR 5055, Mar. 29, 1966]</CITA> </SECTION> </PART> </SUBCHAP> <SUBCHAP TYPE="P"> <PRTPAGE P="18"/> <HD SOURCE="HED">SUBCHAPTER B—PROCEDURAL RULES</HD> <PART> <EAR>Pt. 11</EAR> <HD SOURCE="HED">PART 11—GENERAL RULEMAKING PROCEDURES</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECHD>Sec.</SECHD> <SECTNO>11.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>11.11</SECTNO> <SUBJECT>Docket.</SUBJECT> <SECTNO>11.13</SECTNO> <SUBJECT>Delegation of authority.</SUBJECT> <SECTNO>11.15</SECTNO> <SUBJECT>Emergency exemptions.</SUBJECT> <SECTNO>11.17</SECTNO> <SUBJECT>Direct final rule.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Rules Other Than Airspace Assignment and Use</HD> <SECTNO>11.21</SECTNO> <SUBJECT>Scope.</SUBJECT> <SECTNO>11.23</SECTNO> <SUBJECT>Initiating rulemaking procedures.</SUBJECT> <SECTNO>11.25</SECTNO> <SUBJECT>Petitions for rulemaking or exemptions.</SUBJECT> <SECTNO>11.27</SECTNO> <SUBJECT>Action on petitions for rulemaking or exemptions.</SUBJECT> <SECTNO>11.28</SECTNO> <SUBJECT>Action on special conditions.</SUBJECT> <SECTNO>11.29</SECTNO> <SUBJECT>Notice of proposed rulemaking.</SUBJECT> <SECTNO>11.31</SECTNO> <SUBJECT>Participation of interested persons in rulemaking procedures.</SUBJECT> <SECTNO>11.33</SECTNO> <SUBJECT>Additional rulemaking proceedings.</SUBJECT> <SECTNO>11.35</SECTNO> <SUBJECT>Participation by Civil Aeronautics Board in rulemaking proceedings.</SUBJECT> <SECTNO>11.37</SECTNO> <SUBJECT>Requests for informal appearances.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Processing of Rules Other Than Airworthiness Directives and Airspace Assignment and Use</HD> <SECTNO>11.41</SECTNO> <SUBJECT>Scope.</SUBJECT> <SECTNO>11.43</SECTNO> <SUBJECT>Processing of petitions for rulemaking or exemption from parts of this chapter.</SUBJECT> <SECTNO>11.45</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> <SECTNO>11.47</SECTNO> <SUBJECT>Proceedings after notice of proposed rulemaking.</SUBJECT> <SECTNO>11.49</SECTNO> <SUBJECT>Adoption of final rules.</SUBJECT> <SECTNO>11.51</SECTNO> <SUBJECT>Denial of petition for rulemaking.</SUBJECT> <SECTNO>11.53</SECTNO> <SUBJECT>Grant or denial of exemption.</SUBJECT> <SECTNO>11.55</SECTNO> <SUBJECT>Reconsideration of a denial or grant of exemption.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Rules and Procedures for Airspace Assignment and Use</HD> <SECTNO>11.61</SECTNO> <SUBJECT>Scope.</SUBJECT> <SECTNO>11.63</SECTNO> <SUBJECT>Filing of proposals.</SUBJECT> <SECTNO>11.65</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> <SECTNO>11.67</SECTNO> <SUBJECT>Hearings.</SUBJECT> <SECTNO>11.69</SECTNO> <SUBJECT>Adoption of rules or orders.</SUBJECT> <SECTNO>11.71</SECTNO> <SUBJECT>Exemptions.</SUBJECT> <SECTNO>11.73</SECTNO> <SUBJECT>Petitions for rehearing or reconsideration of rules or orders.</SUBJECT> <SECTNO>11.75</SECTNO> <SUBJECT>Petitions for revoking or modifying rules or orders.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Processing of Airworthiness Directives</HD> <SECTNO>11.81</SECTNO> <SUBJECT>Scope.</SUBJECT> <SECTNO>11.83</SECTNO> <SUBJECT>Processing of petitions for rulemaking or exemption.</SUBJECT> <SECTNO>11.85</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> <SECTNO>11.87</SECTNO> <SUBJECT>Proceedings after notice of proposed rulemaking.</SUBJECT> <SECTNO>11.89</SECTNO> <SUBJECT>Adoption of final rules.</SUBJECT> <SECTNO>11.91</SECTNO> <SUBJECT>Grant or denial of exemption.</SUBJECT> <SECTNO>11.93</SECTNO> <SUBJECT>Petitions for reconsideration of rules.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Agency Information Collection Requirements Under the Paperwork Reduction Act</HD> <SECTNO>11.101</SECTNO> <SUBJECT>OMB control numbers assigned pursuant to the Paperwork Reduction Act.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 49 U.S.C. 106(g), 40101, 40103, 40105, 40109, 40113, 44110, 44502, 44701-44702, 44711, 46102. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 1242, 27 FR 9586, Sept. 28, 1962, unless otherwise noted. </SOURCE> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> Nomenclature changes to part 11 appear at 61 FR 18052, April 24, 1996. </EDNOTE> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECTION> <SECTNO>§ 11.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> This part applies to the issue, amendment, and repeal of— (a) Rules and orders for airspace assignment and use issued under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)); and (b) Other substantive rules, including those applicable to a class of persons, and those addressed to and served on named persons whenever the Administrator decides to use public rulemaking procedures in such a case. </SECTION> <SECTION> <SECTNO>§ 11.11</SECTNO> <SUBJECT>Docket.</SUBJECT> Official FAA records relating to rulemaking actions, including: (a) Proposals, (b) notices of proposed rulemaking, (c) written material received in response to notices, (d) petitions for rulemaking and exemptions, (e) written material received in response to summaries of petitions for rulemaking and exemptions, (f) petitions for rehearing or reconsideration, (g) petitions for modification or revocation, (h) notices denying petitions for rulemaking, (i) <PRTPAGE P="19"/>notices granting or denying exemptions, (j) summaries required to be published under § 11.27, (k) special conditions required, as prescribed under § 21.16 or § 21.101(b)(2), (l) written material received in response to published special conditions, (m) reports of proceedings conducted under § 11.47 (n) notices denying proposals, and (o) final rules or orders are maintained in current docket form in the Office of the Chief Counsel. A public docket relating to rulemaking actions taken by each Regional Administrator on petitions for exemption filed under Part 139 of this chapter is maintained in the Regional Counsel's Office for that region. Unless a request for comment indicates otherwise, a public docket relating to rulemaking actions taken by Regional Administrators under Subparts D and E of this part is maintained in the Regional Counsel's Office. Any interested person may examine any docketed material at that office, at any time after the docket is established, except material that is ordered withheld from the public under section 1104 of the Federal Aviation Act of 1958 (49 U.S.C. 1504), and may obtain a photostatic or duplicate copy of it upon paying the cost of the copy. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-4, 29 FR 15074, Nov. 7, 1964; Amdt. 11-6, 31 FR 13697, Oct. 25, 1966; Amdt. 11-12, 37 FR 19354, Sept. 20, 1972; Amdt. 11-16, 44 FR 6900, Feb. 5, 1979; Amdt. 11-20, 45 FR 60170, Sept. 11, 1980; Amdt. 11-32, 54 FR 39289, Sept. 29, 1989; Amdt. 11-42, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.13</SECTNO> <SUBJECT>Delegation of authority.</SUBJECT> All agency officials, with regulatory issuance authority, may exercise the authority of the Administrator to make certifications, findings and determinations under the Regulatory Flexibility Act (Pub. L. 96-354) with regard to any rulemaking document for which issuance authority is delegated by other sections in this part. <CITA>[Doc. No. 22081, 46 FR 41488, Aug. 17, 1981]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.15</SECTNO> <SUBJECT>Emergency exemptions.</SUBJECT> If, as a result of enemy attack on the United States, communication with Washington headquarters of FAA is or may be disrupted or materially impaired, petitions for exemptions from any rule issued under Titles III or VI of the Federal Aviation Act of 1958 (air safety rules and air traffic and airspace rules) may also be filed at the nearest FAA Regional Office, air traffic control facility or office, Flight Standards District Office, Aircraft Certification Directorate, Aircraft Certification Office, International Field Office or FAA Representative in the Europe, Africa, and Middle East Region, or in the Pacific Region. The procedural requirements of §§ 11.53, 11.71, and 11.91, and the publication and comment procedures of § 11.27 need not be followed. Under these emergency conditions, the FAA inspectors or officers in charge of these offices may grant, in whole or in part and subject to reasonable conditions or limitations, such exemptions or may deny petitions for such exemptions; may issue such exemptions to named persons or in blanket form on their own initiative; and may limit or terminate exemptions so issued by them or by offices whose jurisdiction they may have assumed. Exemptions issued under these circumstances are at all times subject to modification and termination by the Regional Administrator or Acting Regional Administrator or officer in charge of the Region concerned, subject to ultimate action by the Director or Acting Director of the Service concerned. <CITA>[Amdt. 11-2, 29 FR 7091, May 29, 1964, as amended by Amdt. 11-5, 31 FR 11091, Aug. 20, 1966; Amdt. 11-10, 33 FR 17850, Nov. 30, 1968; Amdt. 11-11, 36 FR 3463, Feb. 25, 1971; Amdt. 11-16, 44 FR 6901, Feb. 5, 1979; Amdt. 11-32, 54 FR 39289, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.17</SECTNO> <SUBJECT>Direct final rule.</SUBJECT> Whenever the FAA anticipates that a proposed regulation is unlikely to result in adverse comment, it may choose to issue a direct final rule. The direct final rule will advise the public that no adverse or negative comments are anticipated, and that unless a written adverse or negative comment, or a written notice of intent to submit an adverse or negative comment is received within the comment period, the regulation will become effective on the date specified in the direct final rule. If no written adverse or negative comment, or notice of intent to submit such a comment is received within the <PRTPAGE P="20"/>comment period, the direct final rule will become effective on the date indicated in the direct final rule. The FAA will publish a document in the <E T="04">Federal Register</E> indicating that no adverse or negative comments were received and confirming the date on which the final rule will become effective. If the FAA does receive, within the comment period, an adverse or negative comment, or written notice of intent to submit such a comment, a document withdrawing the direct final rule will be published in the <E T="04">Federal Register</E>, and a notice of proposed rulemaking may be published with a new comment period. Normal procedures for the agency's receipt and consideration of comments will then apply. <CITA>[Doc. No. 27925, 61 FR 11282, Mar. 19, 1996]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Rules Other Than Airspace Assignment and Use</HD> <SECTION> <SECTNO>§ 11.21</SECTNO> <SUBJECT>Scope.</SUBJECT> (a) This subpart applies to substantive rules, other than those relating to airspace assignment and use. (b) Unless the Administrator, for good cause, finds that notice is impracticable, unnecessary, or contrary to the public interest, and incorporates that finding and a brief statement of the reasons for it in the rule, the FAA issues notices of proposed rulemaking and allows interested persons to participate in rulemaking procedings involving a substantive rule. (c) Unless the Administrator determines that notice and rulemaking procedures are to be followed, interpretive rules, general statements of policy, and rules of FAA organization, procedure, or practice are prescribed as final without notice or rulemaking procedures. (d) Whenever the Administrator so determines, the procedures prescribed in this subpart apply to exempting persons and classes from the requirements of a substantive rule. </SECTION> <SECTION> <SECTNO>§ 11.23</SECTNO> <SUBJECT>Initiating rulemaking procedures.</SUBJECT> The Administrator initiates rulemaking procedures upon his own motion. However, in doing so, he considers the recommendations of other agencies of the United States and the petitions of other interested persons. </SECTION> <SECTION> <SECTNO>§ 11.25</SECTNO> <SUBJECT>Petitions for rulemaking or exemptions.</SUBJECT> (a) Any interested person may petition the Administrator to issue, amend, or repeal a rule whether or not it is a substantive rule within the meaning of § 11.21, or for a temporary or permanent exemption from any rule issued by the Federal Aviation Administration under statutory authority. (b) Each petition filed under this section must— (1) In the case of a petition for exemption, unless good cause is shown in that petition, be submitted at least 120 days before the proposed effective date of the exemption; (2) Be submitted in duplicate— (i) To the appropriate FAA airport field office in whose area the petitioner proposes to establish or has established its airport, in the case of any petition for exemption filed under Part 139 of this chapter; (ii) To the Director having Airworthiness Directive responsibility for the product involved in the case of petitions filed in accordance with Subpart D of this part. (iii) To the Federal Air Surgeon (AAM-1), Federal Aviation Administration, 800 Independence Avenue, SW., Washington, D.C. 20591, in the case of a petition for exemption filed under Part 67 of this chapter; and (iv) To the Rules Docket (AGC-10), Federal Aviation Administration, 800 Independence Avenue, Washington, D.C. 20591, in all other cases. (3) Set forth the text or substance of the rule or amendment proposed, or of the rule or statute from which the exemption is sought, or specify the rule that the petitioner seeks to have repealed, as the case may be; (4) Explain the interests of the petitioner in the action requested including, in the case of a petition for an exemption, the nature and extent of the relief sought and a description of each aircraft or person to be covered by the exemption; (5) Contain any information, views, or arguments available to the petitioner to support the action sought, <PRTPAGE P="21"/>the reasons why the granting of the request would be in the public interest and, if appropriate, in the case of an exemption, the reason why the exemption would not adversely affect safety or the action to be taken by the petitioner to provide a level of safety equal to that provided by the rule from which the exemption is sought; and (6)(i) In the case of a unit of Federal, state, or local government that is applying for an exemption from any requirement of part A of subtitle VII of title 49, United States Code, that would otherwise be applicable to current or future aircraft of such unit of government as a result of the statutory change in the definition of public aircraft made by the Independent Safety Board Act Amendments of 1994, Public Law 103-411, the petition for exemption must contain any information, views, analysis, or arguments available to the petitioner to show that: (A) The exemption is necessary to prevent an undue economic burden on the unit of government; and (B) The aviation safety program of the unit of government is effective and appropriate to ensure safe operations of the type of aircraft operated by the unit of government. (ii) The authority of the Administrator, under the Independent Safety Board Amendments of 1994, Pub. L. 103-411, to grant exemptions to units of government is delegated to the Director, Flight Standards Service, and the Director, Aircraft Certification Service. (c) A petition for rulemaking filed under this section must contain a summary, which may be published in the <E T="04">Federal Register</E> as provided in § 11.27(b), which includes— (1) A brief description of the general nature of the rule requested; and (2) A brief description of the pertinent reasons presented in the petition for instituting rulemaking procedures. (d) A petition for exemption filed under this section must contain a summary, which may be published in the <E T="04">Federal Register</E> as provided in § 11.27(c), which includes— (1) A citation of each rule from which relief is requested; and (2) A brief description of the general nature of the relief requested. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962]</CITA> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For <E T="04">Federal Register</E> citations affecting § 11.25, see the List of CFR Sections Affected appearing in the Finding Aids section of this volume. </EDNOTE> </SECTION> <SECTION> <SECTNO>§ 11.27</SECTNO> <SUBJECT>Action on petitions for rulemaking or exemptions.</SUBJECT> (a) <E T="03">General.</E> Except for the publication and comment procedures provided for in this section, no public hearing, argument, or other formal proceeding is held directly on a petition, filed under § 11.25, before its disposition by the FAA. (b) <E T="03">Publication of summary of petition for rulemaking.</E> After receipt of a petition for rulemaking, except as otherwise provided in paragraph (i) of this section, the FAA publishes a summary of the petition in the <E T="04">Federal Register</E> which includes— (1) The docket number of the petition; (2) The name of the petitioner; (3) A brief description of the general nature of the rule requested; (4) A brief description of the pertinent reasons presented in the petition for instituting rulemaking procedures; and (5) In appropriate situations, a list of questions to assist the FAA in obtaining comment on the petition. <FP>Comments on the petition for rulemaking must be filed, in triplicate, within 60 days after the summary is published in the <E T="04">Federal Register</E> unless the Administrator, for good cause, finds a different time period appropriate. Timely comments received will be considered by the Administrator before taking action on the petition.</FP> (c) <E T="03">Publication of summary of petition for exemption.</E> After receipt of a petition for exemption, except as otherwise provided in paragraphs (i) and (j) of this section, the FAA publishes a summary of the petition in the <E T="04">Federal Register</E> which includes— (1) The docket number of the petition; (2) The name of the petitioner; (3) A citation of each rule from which relief is requested; and (4) A brief description of the general nature of the relief requested.<PRTPAGE P="22"/> <FP>Comments on the petition for exemption must be filed, in triplicate, within 20 days after the summary is published in the <E T="04">Federal Register</E> unless the Administrator, for good cause, finds a different time period appropriate. Timely comments received will be considered by the Administrator before taking action on the petition.</FP> (d) <E T="03">Instituting rulemaking procedures based on a petition.</E> If the Administrator determines, after consideration of any comments received in response to a summary of a petition for rulemaking, that the petition discloses adequate reasons, the FAA institutes rulemaking procedures. (e) <E T="03">Grant of petition for exemption—summary.</E> If the Administrator determines, after consideration of any comments received in response to a summary of a petition for exemption, that the petition is in the public interest, the Administrator grants the exemption and, except as otherwise provided in paragraph (i) of this section, the FAA publishes a summary of the grant of the petition for exemption in the <E T="04">Federal Register.</E> A summary of a grant of a petition for exemption includes— (1) The docket number of the petition; (2) The name of the petitioner; (3) A citation of each rule from which relief is requested; (4) A brief description of the general nature of the relief granted; and (5) The disposition of the petition. (f) <E T="03">Denial of petition for rulemaking.</E> If the Administrator determines, after consideration of any comments received in response to a summary of a petition for rulemaking, that the petition does not justify instituting rulemaking procedures, the FAA notifies the petitioner to that effect. Except as otherwise provided in paragraph (i) of this section, the FAA publishes a summary of the denial of the petition for rulemaking in the <E T="04">Federal Register</E> in accordance with paragraph (h) of this section. (g) <E T="03">Denial of petition for exemption.</E> If the Administrator determines, after consideration of any comments received in response to a summary of a petition for exemption, that the petition does not justify granting the requested exemption, the FAA notifies the petitioner to that effect. Except as otherwise provided in paragraph (i) of this section, the FAA publishes a summary of the denial of the petition for exemption in the <E T="04">Federal Register</E> in accordance with paragraph (h) of this section. (h) <E T="03">Summary of denial of petition for rulemaking or exemption.</E> A summary of a denial of a petition for rulemaking or exemption includes— (1) The docket number of the petition; (2) The name of the petitioner; (3) In the case of a denial of a petition for exemption, a citation of each rule from which relief is requested; (4) A brief description of the general nature of the rule or relief requested; and (5) The disposition of the petition. (i) <E T="03">General exceptions.</E> The publication and comment procedures of paragraphs (b) through (h) of this section do not apply to the following: (1) To petitions for rulemakings or exemptions processed under § 11.83. (2) To petitions for exemptions from the requirements of Part 67 of this chapter. (j) <E T="03">Exceptions to publication of summary of petition for exemption.</E> The publication and comment procedures of paragraph (c) of this section do not apply to the following: (1) To petitions for emergency exemptions processed under § 11.15. (2) To petitions for exemptions processed under Part 139 of this chapter. (3) Whenever the head of the Office or Service concerned, subject to the approval of the Chief Counsel with respect to form and legality, finds for good cause shown in a petition for exemption that action on the petition should not be delayed by the publication and comment procedures. Factors that may be considered in determining whether good cause exists, include— (i) Whether a grant of exemption would set a precedent or whether the petition for exemption and the reasons presented in it are identical to exemptions previously granted; (ii) Whether the delay in acting on the petition for exemption that would result from publication would be detrimental to the petitioner; and<PRTPAGE P="23"/> (iii) Whether petitioner acted in a timely manner in filing the petition for exemption. (k) <E T="03">Status of petition for rulemaking.</E> Within 120 days after publication in the <E T="04">Federal Register</E> of a summary of petition for rulemaking and every 120 days thereafter, unless sooner denied under § 11.51 or issued as a notice of proposed rulemaking under § 11.65, the Office or Service concerned shall advise petitioner in writing of the status of the petition. (l) <E T="03">Additional specific provisions.</E> Specific provisions covering actions on petitions are set forth in Subpart C of this part. <CITA>[Amdt. 11-20, 44 FR 6901, Feb. 5, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.28</SECTNO> <SUBJECT>Action on special conditions.</SUBJECT> (a) <E T="03">General.</E> Except for the publication and comment procedures provided for in this section, no public hearing, argument, or other formal proceeding is held directly on a special condition established by the Administrator. (b) <E T="03">Procedures.</E> This subpart and Subpart C apply to the issue, amendment, and repeal of special conditions under Part 21. In addition to the information required by § 11.29(b), each notice will include— (1) The name and address of the applicant; (2) The model designation and a summary description of the affected product; (3) The applicable type design approval regulations designated in accordance with § 21.17 or § 21.101 of Part 21; and (4) A summary description of the novel or unusual design features that make the issue or amendment of special conditions necessary. <CITA>[Amdt. 11-17, 45 FR 60170, Sept. 11, 1980]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.29</SECTNO> <SUBJECT>Notice of proposed rulemaking.</SUBJECT> (a) Each general notice of proposed rulemaking is published in the <E T="04">Federal Register,</E> unless all persons subject to it are named and are personally served with a copy of it. (b) Each notice, whether published in the <E T="04">Federal Register</E> or personally served, includes— (1) A statement of the time, place, and nature of the proposed rulemaking proceeding; (2) A reference to the authority under which it is issued; (3) A description of the subjects and issues involved or the substance and terms of the proposed rule; (4) A statement of the time within which written comments must be submitted and the required number of copies; and (5) A statement of how and to what extent interested persons may participate in the proceedings, as prescribed by §§ 11.31 and 11.33. (c) A petition for extension of the time for comments must be submitted in duplicate not later than two days before expiration of the time stated in the notice. The filing of the petition does not automatically extend the time for petitioner's comments. Such a petition is granted only if the petitioner shows a substantive interest in the proposed rule and good cause for the extension, and if the extension is consistent with the public interest. If an extension is granted it is published in the <E T="04">Federal Register</E>. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-1, 28 FR 2897, Mar. 23, 1963]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.31</SECTNO> <SUBJECT>Participation of interested persons in rulemaking procedures.</SUBJECT> (a) Each interested person is entitled to participate in rulemaking proceedings by submitting written in-for-ma-tion, views, or arguments. In addition, he may comment on the original information, views, and arguments submitted by other persons, if, after receiving them, the Administrator considers it desirable. (b) In any appropriate case, the Administrator also allows interested persons to participate in the rulemaking procedures described in § 11.33. </SECTION> <SECTION> <SECTNO>§ 11.33</SECTNO> <SUBJECT>Additional rulemaking proceedings.</SUBJECT> (a) The rulemaking procedure also includes any further procedural steps that best serve the purposes of a particular proceeding. For example, interested persons may be allowed to make oral arguments, participate in conferences between the Administrator or <PRTPAGE P="24"/>his representative and interested persons and organizations, appear at informal hearings presided over by a designated FAA official at which a stenographic transcript is made, or participate in any other procedure whenever it is desirable and appropriate to assure informed administrative action and adequate protection of private interests. (b) Any appropriate combination of the procedures described in paragraph (a) of this section may be used in addition to the basic procedure of allowing interested persons to participate in rulemaking proceedings by submitting written information, views, or arguments. </SECTION> <SECTION> <SECTNO>§ 11.35</SECTNO> <SUBJECT>Participation by Civil Aeronautics Board in rulemaking proceedings.</SUBJECT> (a) Under section 1001 of the Federal Aviation Act of 1958 (49 U.S.C. 1481), the Civil Aeronautics Board may appear and participate as an interested party in any proceeding conducted by the Administrator under Title III of that Act, and in any proceeding under Title VI of that Act that cannot be appealed to the National Transportation Safety Board. (b) To indicate its intention to participate in any proceeding described in paragraph (a) of this section, the Civil Aeronautics Board may file written information, views, or arguments in response to a notice of proposed rulemaking issued by the Administrator. The Civil Aeronautics Board is entitled to the procedural privileges accorded other parties and is equally free to participate. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.37</SECTNO> <SUBJECT>Requests for informal appearances.</SUBJECT> (a) Upon his request, any interested person may appear informally before an appropriate official of the FAA to present, adjust, or determine a question or controversy relating to a rulemaking function of the FAA. (b) A request for an appearance under this section must be sent in writing to the Federal Aviation Administration, Washington, D.C. 20590, or to the Regional or District Office nearest to the person making the request. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967; Amdt. 11-8, 32 FR 6390, Apr. 25, 1967]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Processing of Rules Other Than Airworthiness Directives and Airspace Assignment and Use</HD> <SECTION> <SECTNO>§ 11.41</SECTNO> <SUBJECT>Scope.</SUBJECT> (a) This subpart prescribes the supplemental procedures to be followed by the Offices and Services of the FAA in rulemaking proceedings and in granting or denying exemptions from rules. It also designates the Office or Service that is authorized to act for the Administrator in connection with those proceedings and exemptions. Any authority conferred by this subpart on the head of any Office or Service is also conferred on the Associate Administrator (if any) who exercises executive direction over that official. (b) This subpart applies to rulemaking procedures other than for Airworthiness Directives and rules relating to Airspace Assignment and Use. (c) For the purposes of this subpart— (1) The words “Office or Service” include the Technical Center, and include Regional Administrators with respect to petitions for exemptions from the requirements of Part 139 of this chapter; and (2) “Chief Counsel” means— (i) The Chief Counsel; (ii) A Regional Counsel or the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office with respect to petitions for exemptions from the requirements of Part 139 of this chapter; (iii) The Assistant Chief Counsel for Regulations for all other exemptions processed under this subpart; or (iv) Any person to whom the Chief Counsel has delegated authority in the matter concerned. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-5, 31 FR 11091, Aug. 20, 1966; Amdt. 11-16, 31 FR 13697, Oct. 25, 1966; Amdt. 11-12, 37 FR 19354, Sept. 20, 1972; Amdt. 11-15, 43 FR 52205, Nov. 9, 1978; Amdt. 11-32, 54 FR 39290, Sept. 25, 1989; Amdt. 11-42, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <PRTPAGE P="25"/> <SECTNO>§ 11.43</SECTNO> <SUBJECT>Processing of petitions for rulemaking or exemption from parts of this chapter.</SUBJECT> Whenever the FAA receives a petition for rulemaking or for an exemption, a copy of the petition is referred for action, as provided in § 11.27, to the Office or Service having substantive responsibility for the subject involved. <CITA>[Doc. No. 15457, 41 FR 11271, Mar. 18, 1976]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.45</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> Whenever he determines that a notice of proposed rulemaking is necessary or desirable, the head of the Office or Service concerned may, subject to the approval of the Chief Counsel with respect to form and legality, issue the notice provided for in § 11.29. In addition, he may grant or deny petitions for extension of the time for comments on the notice, filed under § 11.29(c). <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-1, 28 FR 2897, Mar. 23, 1963]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.47</SECTNO> <SUBJECT>Proceedings after notice of proposed rulemaking.</SUBJECT> (a) Each person who submits written information, views, or arguments in response to a notice of proposed rulemaking, or during additional rulemaking proceedings in connection with such a notice, must file the number of copies specified in the notice. All timely comments are considered before final action on the rulemaking proposal is taken. Late filed comments are considered so far as possible without incurring expense or delay. (b) Whenever the head of the Office or Service concerned determines that additional rulemaking proceedings of the kind described in § 11.33 are necessary or desirable, he may designate representatives to conduct those proceedings. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-5, 31 FR 11091, Aug. 20, 1966]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.49</SECTNO> <SUBJECT>Adoption of final rules.</SUBJECT> (a) After the Office or Service concerned has completed its analysis and evaluation of the information, views, and arguments submitted with respect to a proposed rule, representatives of that Office or Service and the Office of the Chief Counsel prepare an appropriate rule, subject to the approval of the Chief Counsel as to form and legality. Except as provided in paragraph (b) of this section, the rule is then submitted, with the recommendations of the head of the Office or Service concerned and the Chief Counsel, to the Administrator for consideration. If a rule is adopted, it is published in the <E T="04">Federal Register.</E> (b) Final authority to issue, amend, and repeal— (1) An appendix to a part is delegated to the head of the Office or Service concerned; (2) Minimum en route IFR altitudes and associated flight data under Part 95 of this chapter, and standard instrument approach procedures under Part 97 of this chapter is delegated to the Manager, Technical Programs Division, Flight Standards Service; and (3) Special conditions under Part 21 of this chapter is delegated to the Director, Aircraft Certification Service. <CITA>[Amdt. 11-15, 43 FR 52205, Nov. 9, 1978 as amended by Amdt. 11-19, 45 FR 47838, July 17, 1980; Amdt. 11-18, 45 FR 38346, June 9, 1980; Amdt. 11-20, 45 FR 60170, Sept. 11, 1980; Amdt. 11-20A, 45 FR 85597, Dec. 29, 1980; Amdt. 11-32, 54 FR 39290, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.51</SECTNO> <SUBJECT>Denial of petition for rulemaking.</SUBJECT> Whenever it is determined that a petition for rulemaking filed under § 11.25 should be denied, the Office or Service concerned prepares, subject to the approval of the Chief Counsel with respect to form and legality, a notice of denial for the Administrator's signature. </SECTION> <SECTION> <SECTNO>§ 11.53</SECTNO> <SUBJECT>Grant or denial of exemption.</SUBJECT> (a) The head of the Office or Service concerned may, subject to the approval of the Chief Counsel with respect to form and legality, grant or deny any petition for an exemption. However, if the head of the Office or Service concerned finds that the grant or denial involves a technical or policy determination that should be made by the Administrator, he refers the petition and his recommendations and those of the Chief Counsel to the Administrator for final action.<PRTPAGE P="26"/> (b) Whenever a petition is granted or denied under this section, the Office or Service concerned prepares, subject to the approval of the Chief Counsel with respect to form and legality, a notice to the petitioner informing him of the action taken. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-11, 36 FR 3463, Feb. 25, 1971; Amdt. 11-15, 43 FR 52205, Nov. 9, 1978]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.55</SECTNO> <SUBJECT>Reconsideration of a denial or grant of exemption.</SUBJECT> (a) Except as provided in paragraph (c) of this section, if a petition for exemption is denied, the petitioner may file a petition for reconsideration with the Administrator. The petition must be filed, in duplicate, within 30 days after the petitioner is notified of the denial of the exemption. (b) If a petition for exemption is granted, a person other than the initial petitioner may file a petition for reconsideration with the Administrator. The petition must be filed, in duplicate, within 45 days after the grant of exemption is issued. (c) If a petition for exemption from the requirements of Part 67 of this chapter is denied, the petitioner may file a petition for reconsideration with the Federal Air Surgeon. The petition must be filed in duplicate, within 30 days after the petitioner is notified of the denial of the exemption. However, if the final action on the initial petition was by the Administrator in accordance with the second sentence of § 11.53(a), the Federal Air Surgeon refers the petition for reconsideration and recommendations and those of the Chief Counsel to the Administrator for final action. (d) A petition for reconsideration under this section must be based on the existence of one or more of the following: (1) A finding of a material fact that is erroneous. (2) A necessary legal conclusion that is without governing precedent or is a departure from or contrary to law, FAA rules, or precedent. (3) An additional fact relevant to the decision that was not presented in the initial petition for exemption. In order for a petition under paragraph (a) or (c) of this section to be based on this ground, the petition for reconsideration must state the reason the additional fact was not presented in the initial petition. <CITA>[Amdt. 11-15, 43 FR 52205, Nov. 9, 1978]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Rules and Procedures for Airspace Assignment and Use</HD> <SECTION> <SECTNO>§ 11.61</SECTNO> <SUBJECT>Scope.</SUBJECT> (a) This subpart establishes procedures for initiating, processing, issuing, and publishing rules and orders issued under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)), including— (1) Designations of controlled airspace under part 71 of this chapter; (2) Assignments of segments or parts of the navigable airspace for special use purposes, such as restricted areas, military climb corridors, and experimental flight test areas; and (3) Special rules or orders relating to the assignment or use of navigable airspace. (b) This subpart does not apply to emergency cases and cases in which the procedures described in paragraph (a) of this section are found to be impractical, unnecessary, or contrary to the public interest. (c) For the purposes of this subpart, “Director” means the Executive Director of System Operations, the Associate Administrator for Air Traffic or the Director, Air Traffic Rules and Procedures Service, or any person to whom the Director has delegated authority in the matter concerned. (d) For the purposes of this subpart, “Chief Counsel” means the Chief Counsel, or a Regional Counsel, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office or the Assistant Chief Counsel for Regulations or any person to whom the Chief Counsel, Assistant Chief Counsel, or Regional Counsel has delegated authority in the matter concerned. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-3, 29 FR 9662, July 17, 1964; Amdt. 11-4, 29 FR 15074, Nov. 7, 1964; Amdt. 11-5; 31 FR 11091, Aug. 20, 1966; Amdt. 11-15, 43 FR 52205, Nov. 9, 1978; Amdt. 11-30, 51 FR 2348, Jan. 16, 1986; Amdt. 11-32, 54 FR 39290, Sept. 25, 1989; Amdt. 11-35, 56 FR 65638, 65653, Dec. 17, 1991; Amdt. 11-42, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <PRTPAGE P="27"/> <SECTNO>§ 11.63</SECTNO> <SUBJECT>Filing of proposals.</SUBJECT> (a) Each proposal, except one arising in the FAA, for the designation of Federal airways or other areas for normal air traffic use, the assignment of navigable airspace for special use purposes, or the issue of a special rule or order relating to the use of navigable airspace, must be filed in writing, in triplicate, with the Director. (b) The director may, on his own motion, initiate the procedures prescribed in this subpart for proposals arising within the FAA. (c) A proposal requesting the assignment of navigable airspace for special use purposes, or for the designation of an area for air traffic purposes, must include at least the following: (1) The location and a description of the airspace desired for assignment or designation. (2) A complete description of the activity or use to be made of that airspace, including a detailed description of the type, volume, duration, time, and place of the operations to be conducted in the assigned or designated area. (3) A description of the air navigation, air traffic control, surveillance, and communication facilities available and to be provided if the assignment or designation is made. (4) The name and location of the agency, office, facility, or person to whom authority would be delegated to permit the use of the airspace during those times it would not be used for the purpose to which it would be assigned. (d) Subject to the approval of the Chief Counsel with respect to form and legality, the Director issues a notice of any rejected proposal. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-3, 29 FR 9662, July 17, 1964]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.65</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> (a) If it is determined that the subject matter of a proposal should be submitted to the rulemaking process, or if rulemaking action is to be taken on his own motion, the Director, subject to the approval of the Chief Counsel with respect to form and legality, issues a notice of proposed rulemaking. (b) Normally, a notice of proposed rulemaking is issued within approximately 30 days after receipt of a proposal with respect to which it has been determined that action might be taken. (c) Each notice of proposed rulemaking is published in the <E T="04">Federal Register</E> and includes at least the following: (1) A statement of the time, place, and nature of the public rulemaking proceedings. (2) A reference to the authority under which it is proposed. (3) Either the terms or substance of the proposed action or a description of the subjects and issues involved. (d) Approximately 30 days are allowed for submitting written information, views, or arguments on the notice. Petitions for extension of the time for such comments are governed by the provisions of § 11.29(c). If a public hearing is to be held, either the original notice of proposed rulemaking or a revised notice gives approximately 30 days’ notice. The Director may grant or deny petitions for extension of the time for comments on the notice and may change the date of any hearing previously noticed. (e) Written information, views, and arguments submitted in response to a notice of proposed rulemaking, or that are requested after the notice, must be submitted in triplicate. (f) Each interested person is entitled to discuss or confer informally with appropriate FAA officials concerning a proposed action. However, to become a part of the formal record for consideration, any information, views, or arguments presented during the conference must also be submitted in writing in accordance with the notice. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-1, 28 FR 2897, Mar. 23, 1963]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.67</SECTNO> <SUBJECT>Hearings.</SUBJECT> (a) Sections 7 and 8 of the Administrative Procedure Act do not apply to proceedings used to formulate rules under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)). <PRTPAGE P="28"/>Whenever the Director, in his discretion, considers that a hearing is necessary to provide informed Administrative action and assure adequate protection of private or public interests, he may hold an informal public hearing. However, any rule or order issued in a case in which such a hearing is held is not based exclusively on the record of the hearing. (b) The Director designates a presiding officer for each hearing and the Chief Counsel designates a legal adviser. (c) Normally, hearings held under this section are held in the vicinity of the affected airspace. Interested persons are allotted time to make an oral presentation without interruption and a verbatim transcript is made of the proceedings by a certified court reporter. (d) The procedure in hearings held under this section is as follows: (1) The presiding officer makes an opening statement with particular reference to the notice of proposed rulemaking. (2) The presiding officer designates interested persons or their authorized representatives to speak at the hearing. (3) The presiding officer allots enough time to each interested person on an equal basis so that his position may be expressed fully and placed on the record, with those who favor it speaking first followed by those who oppose it, initial statements being made as far as possible without interruption, and questions permitted after initial statements have been made by all designated persons. (4) Arguments and oral statements are limited to the subject named in the notice of proposed rulemaking. (5) Written information, views, arguments, or briefs may be offered for the record, but may not be accepted after the hearing unless good cause is shown or the submission is requested by the presiding officer or the Director. (e) The presiding officer of a hearing may deviate from the procedures prescribed in this section to assure a more complete and informative record. </SECTION> <SECTION> <SECTNO>§ 11.69</SECTNO> <SUBJECT>Adoption of rules or orders.</SUBJECT> (a) After the closing date for submitting written comments on a notice or, if a hearing is held; after the hearing, the Office having substantive responsibility for the subject involved studies the entire matter of a proposed rule or order. The Chief Counsel determines whether legal justification exists for the proposed action, and thereafter prepares an appropriate rule, order, or notice of denial. The rule, order, or notice of denial is then submitted to the Director for his action. (b) Each rule or order issued by the Director is published in the <E T="04">Federal Register</E> and in such other publications as the Director considers desirable. Each notice of denial is sent to the person who made the proposal and to such other interested persons as the Director considers desirable. (c) Each rule or order issued under this subpart becomes effective not less than 30 days after it is published, except in an emergency, or when it is impractical, unnecessary, or contrary to the public interest. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-3, 29 FR 9662, July 17, 1964]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.71</SECTNO> <SUBJECT>Exemptions.</SUBJECT> (a) A petition for an exemption from any rule or order issued under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)) may be filed with the Director. Such a petition must be in triplicate and state clearly the nature of the requested exemption and the reasons why it should be granted. (b) The Director may, subject to the approval of the Chief Counsel with respect to form and legality, grant or deny any petition filed under this section and shall notify the petitioner of his action. </SECTION> <SECTION> <SECTNO>§ 11.73</SECTNO> <SUBJECT>Petitions for rehearing or reconsideration of rules or orders.</SUBJECT> (a) Any interested person may petition the Administrator for a rehearing on, or for reconsideration of, any rule or order issued under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)). Such a petition must be filed, in triplicate, within 30 days after <PRTPAGE P="29"/>the rule or order is published in the <E T="04">Federal Register.</E> It must contain a brief statement of the complaint and an explanation as to how the rule or order is contrary to the public interest. (b) If the petitioner requests the consideration of additional facts, he must state their nature and purpose, and the reason they were not presented at the hearing or in writing within the allotted time. (c) The Administrator does not consider repetitious petitions. (d) Unless the Administrator orders otherwise, the filing of a petition under this section does not stay the effect of a rule or order. </SECTION> <SECTION> <SECTNO>§ 11.75</SECTNO> <SUBJECT>Petitions for revoking or modifying rules or orders.</SUBJECT> (a) Any interested person may petition to revoke or modify any rule or order covered by this subpart. Such a petition must be filed, in triplicate, with the Director and must clearly state the information, views, and arguments the petitioner considers necessary to support the requested action and must clearly indicate the effect the action would have on the use of navigable airspace. (b) A petition filed under this section is processed in the same manner as an original proposal, or in any other manner that the Director considers necessary or desirable. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-3, 29 FR 9662, July 17, 1964]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Processing of Airworthiness Directives</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 7162, 31 FR 13697, Oct. 25, 1966, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 11.81</SECTNO> <SUBJECT>Scope.</SUBJECT> (a) This subpart prescribes the procedures to be followed in rulemaking proceedings for Airworthiness Directives issued pursuant to Part 39 and in granting or denying exemptions from Airworthiness Directives. It also designates the persons that are authorized to act for the Administrator in connection with those proceedings and exemptions. (b) For the purposes of this subpart, “Director” means the Director, Aircraft Certification Service, or a Manager of an Aircraft Certification Directorate (Directorate Manager). (c) The authority for issuing Airworthiness Directives is limited to the following persons: (1) The Director, Aircraft Certification Service; and (2) Managers of the Aircraft Certification Directorates for products under the authority of those directorates, as determined by the Administrator. (d) For the purposes of this subpart, “Chief Counsel” means the Chief Counsel or a Regional Counsel or a Directorate Counsel, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office or the Assistant Chief Counsel for Regulations, or any person to whom the Chief Counsel, Assistant Chief Counsel, Regional Counsel, or Directorate Counsel has delegated authority in the matter concerned. <CITA>[Doc. No. 7162, 31 FR 13697, Oct. 25, 1966, as amended by Amdt. 11-15, 43 FR 52205, Nov. 9, 1978; Amdt. 11-21, 45 FR 80815, Dec. 8, 1980; Amdt. 11-32, 54 FR 39290, Sept. 25, 1989; Amdt. 11-42, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.83</SECTNO> <SUBJECT>Processing of petitions for rulemaking or exemption.</SUBJECT> Whenever the FAA receives a petition for rulemaking or for an exemption, a copy of the petition is referred for action, as provided in § 11.27, to the Director having Airworthiness Directive responsibility for the product involved. </SECTION> <SECTION> <SECTNO>§ 11.85</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> Whenever he determines that a notice of proposed rulemaking is necessary or desirable, the Director may, subject to the approval of the Chief Counsel with respect to form and legality issue the notice provided for in § 11.29. In addition, he may grant or deny petitions for extension of the time for comments on the notice, filed under § 11.29(c). </SECTION> <SECTION> <PRTPAGE P="30"/> <SECTNO>§ 11.87</SECTNO> <SUBJECT>Proceedings after notice of proposed rulemaking.</SUBJECT> (a) Each person who submits written information, views, or arguments in response to a notice of proposed rulemaking, or during additional rulemaking proceedings in connection with such a notice, must file the number of copies specified in the notice. (b) Whenever the Director determines that additional rulemaking proceedings of the kind described in § 11.33 are necessary or desirable, he may designate representatives to conduct those proceedings. </SECTION> <SECTION> <SECTNO>§ 11.89</SECTNO> <SUBJECT>Adoption of final rules.</SUBJECT> In any case in which a notice of proposed rulemaking was issued, the Director completes his analysis and evaluation of the information, views, and arguments submitted with respect to the proposed rule and studies the entire matter. In any case in which the subject matter is, for good cause, submitted to the rulemaking process without notice, the Director initiates the procedure. The Chief Counsel determines whether legal justification exists for the action proposed, and thereafter prepares an appropriate rule or notice of denial. The rule or notice of denial is then submitted to the Director for his action. </SECTION> <SECTION> <SECTNO>§ 11.91</SECTNO> <SUBJECT>Grant or denial of exemption.</SUBJECT> (a) The Director may, subject to the approval of the Chief Counsel with respect to form and legality, grant or deny any petition for an exemption from an Airworthiness Directive. (b) Whenever a petition is granted or denied under this section, the Director prepares, subject to the approval of the Chief Counsel with respect to form and legality, a notice to the petitioner informing him of the action taken. </SECTION> <SECTION> <SECTNO>§ 11.93</SECTNO> <SUBJECT>Petitions for reconsideration of rules.</SUBJECT> (a) Any interested person may petition the Administrator for a rehearing on, or for reconsideration of, any Airworthiness Directive. Such a petition must be filed, in duplicate, within 30 days after the rule is published in the <E T="04">Federal Register.</E> It must contain a brief statement of the complaint and an explanation as to how the rule is contrary to the public interest. (b) If the petitioner requests the consideration of additional facts, he must state their nature and purpose and the reason they were not presented at the hearing or in writing within the allotted time. (c) The Administrator does not consider repetitious petitions. (d) Unless the Administrator orders otherwise, the filing of a petition under this section does not stay the effect of a rule or order. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Agency Information Collection Requirements Under the Paperwork Reduction Act</HD> <SECTION> <SECTNO>§ 11.101</SECTNO> <SUBJECT>OMB control numbers assigned pursuant to the Paperwork Reduction Act.</SUBJECT> (a) <E T="03">Purpose.</E> This subpart consolidates and displays the OMB assigned control numbers for the information collection requirements of the Federal Aviation Administration pursuant to the Paperwork Reduction Act of 1980 (Title 44, U.S.C. Chapter 35) which mandates that every collection requirement have a control number displayed in the Code of Federal Regulations. (b) <E T="03">Display.</E> <GPOTABLE CDEF="s10,r10" COLS="2" OPTS="L2"> <BOXHD> <CHED H="1">14 CFR part or section identified and described</CHED> <CHED H="1">Current OMB control No.</CHED> </BOXHD> <ROW> <ENT I="01">Part 21 </ENT> <ENT>2120-0018</ENT> </ROW> <ROW> <ENT I="01">§ 34.7 </ENT> <ENT>2120-0508</ENT> </ROW> <ROW> <ENT I="01">Part 39 </ENT> <ENT>2120-0056</ENT> </ROW> <ROW> <ENT I="01">Part 43 </ENT> <ENT>2120-0020</ENT> </ROW> <ROW> <ENT I="01">§ 45.13 </ENT> <ENT>2120-0508</ENT> </ROW> <ROW> <ENT I="01">§§ 47.3, 47.5</ENT> <ENT>2120-0029</ENT> </ROW> <ROW> <ENT I="01">§ 47.7 </ENT> <ENT>2120-0029, 2120-0042</ENT> </ROW> <ROW> <ENT I="01">§ 47.8 </ENT> <ENT>2120-0042</ENT> </ROW> <ROW> <ENT I="01">§ 47.9 </ENT> <ENT>2120-0029, 2120-0042</ENT> </ROW> <ROW> <ENT I="01">§§ 47.11 thru 47.47 </ENT> <ENT>2120-0042</ENT> </ROW> <ROW> <ENT I="01">§ 47.63 </ENT> <ENT>2120-0024</ENT> </ROW> <ROW> <ENT I="01">Part 49 </ENT> <ENT>2120-0043</ENT> </ROW> <ROW> <ENT I="01">§ 61.3</ENT> <ENT>2120-0034</ENT> </ROW> <ROW> <ENT I="01">§§ 61.13 thru 61.197 </ENT> <ENT>2120-0021</ENT> </ROW> <ROW> <ENT I="01">Part 63 </ENT> <ENT>2120-0007</ENT> </ROW> <ROW> <ENT I="01">Part 65 </ENT> <ENT>2120-0022</ENT> </ROW> <ROW> <ENT I="01">§ 67.11 </ENT> <ENT>2120-0034,2120-0052, 2120-0059, 2120-0069</ENT> </ROW> <ROW> <ENT I="01">§ 67.19 </ENT> <ENT>2120-0052,2120-0059, 2120-0069</ENT> </ROW> <ROW> <ENT I="01">§ 67.23 </ENT> <ENT>2120-0002</ENT> </ROW> <ROW> <ENT I="01">Part 77 </ENT> <ENT>2120-0001</ENT> </ROW> <ROW> <ENT I="01">§ 91.1 </ENT> <ENT>2120-0026</ENT> </ROW> <ROW> <ENT I="01">§ 91.3 </ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">§ 91.18 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">§§ 91.24 thru 91.34 (except § 91.30)</ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">§ 91.30</ENT> <ENT>2120-0522</ENT> </ROW> <ROW> <PRTPAGE P="31"/> <ENT I="01">§ 91.39 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">§§ 91.41 thru 91.55 </ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">§ 91.63 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">§ 91.75 </ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">§ 91.83 </ENT> <ENT>2120-0026</ENT> </ROW> <ROW> <ENT I="01">§§ 91.97 thru 91.217 </ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">Part 91, Subpart E </ENT> <ENT>2120-0082</ENT> </ROW> <ROW> <ENT I="01">§§ 91.851 thru 91.875 </ENT> <ENT>2120-0553</ENT> </ROW> <ROW> <ENT I="01">Part 93, Subpart S </ENT> <ENT>2120-0524</ENT> </ROW> <ROW> <ENT I="01">Part 101 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">Part 105 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">Part 107 </ENT> <ENT>2120-0075</ENT> </ROW> <ROW> <ENT I="01">Part 108 </ENT> <ENT>2120-0098</ENT> </ROW> <ROW> <ENT I="01">Part 121 (except as below) </ENT> <ENT>2120-0008</ENT> </ROW> <ROW> <ENT I="02">§§ 121.3 thru 121.155 </ENT> <ENT>2120-0008, 2120-0028</ENT> </ROW> <ROW> <ENT I="02">§ 121.344 </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="02">§ 121.344a </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="02">§ 121.585 </ENT> <ENT>2120-0542</ENT> </ROW> <ROW> <ENT I="02">§ 121.683 </ENT> <ENT>2120-0585</ENT> </ROW> <ROW> <ENT I="02">§ 121.715 </ENT> <ENT>2120-0523</ENT> </ROW> <ROW> <ENT I="02">§ 121.723 </ENT> <ENT>2120-0008, 2120-0025</ENT> </ROW> <ROW> <ENT I="01">Part 123 </ENT> <ENT>2120-0028</ENT> </ROW> <ROW> <ENT I="01">Part 125 (except as below) </ENT> <ENT>2120-0085</ENT> </ROW> <ROW> <ENT I="02">§ 125.226 </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="01">Part 127 </ENT> <ENT>2120-0028</ENT> </ROW> <ROW> <ENT I="01">§ 129.20 </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="01">Part 133</ENT> <ENT>2120-0044</ENT> </ROW> <ROW> <ENT I="01">Part 135 (except as below) </ENT> <ENT>2120-0039</ENT> </ROW> <ROW> <ENT I="02">§§ 135.11 thru 135.17 </ENT> <ENT>2120-0008, 2120-0039</ENT> </ROW> <ROW> <ENT I="02">§ 135.43 </ENT> <ENT>2120-0025, 2120-0039</ENT> </ROW> <ROW> <ENT I="02">§ 135.63 </ENT> <ENT>2120-0585</ENT> </ROW> <ROW> <ENT I="02">§ 135.129 </ENT> <ENT>2120-0542</ENT> </ROW> <ROW> <ENT I="02">§ 135.152 </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="02">§ 135.163 </ENT> <ENT>2120-0619</ENT> </ROW> <ROW> <ENT I="02">§ 135.411 </ENT> <ENT>2120-0619</ENT> </ROW> <ROW> <ENT I="02">§ 135.415 </ENT> <ENT>2120-0003, 2120-0039</ENT> </ROW> <ROW> <ENT I="02">§ 135.421 </ENT> <ENT>2120-0619</ENT> </ROW> <ROW> <ENT I="01">Part 137 </ENT> <ENT>2120-0049</ENT> </ROW> <ROW> <ENT I="01">Part 139 </ENT> <ENT>2120-0063</ENT> </ROW> <ROW> <ENT I="01">Part 141 </ENT> <ENT>2120-0009</ENT> </ROW> <ROW> <ENT I="01">Part 143 </ENT> <ENT>2120-0021</ENT> </ROW> <ROW> <ENT I="01">Part 145 (except as below) </ENT> <ENT>2120-0010</ENT> </ROW> <ROW> <ENT I="02">§ 145.63 </ENT> <ENT>2120-0003, 2120-0010</ENT> </ROW> <ROW> <ENT I="01">Part 147 </ENT> <ENT>2120-0040</ENT> </ROW> <ROW> <ENT I="01">Part 149 </ENT> <ENT>2120-0012</ENT> </ROW> <ROW> <ENT I="01">§§ 150.21 and 150.23</ENT> <ENT>2120-0517</ENT> </ROW> <ROW> <ENT I="01">Part 152 </ENT> <ENT>2120-0065, 2120-0080</ENT> </ROW> <ROW> <ENT I="01">Part 157 </ENT> <ENT>2120-0036</ENT> </ROW> <ROW> <ENT I="01">§ 159.13 </ENT> <ENT>2120-0061</ENT> </ROW> <ROW> <ENT I="01">§ 159.93 </ENT> <ENT>2120-0084</ENT> </ROW> <ROW> <ENT I="01">Part 171 </ENT> <ENT>2120-0014</ENT> </ROW> <ROW> <ENT I="01">§ 183.11</ENT> <ENT>2120-0002,2120-0033, 2120-0035</ENT> </ROW> <ROW> <ENT I="01">§§ 183.15 thru 183.17 </ENT> <ENT>2120-0033</ENT> </ROW> <ROW> <ENT I="01">§§ 183-25 thru 183.31 </ENT> <ENT>2120-0035</ENT> </ROW> <ROW> <ENT I="01">Part 198 </ENT> <ENT>2120-0514</ENT> </ROW> <ROW> <ENT I="01">Part 199 </ENT> <ENT>2120-0081</ENT> </ROW> <ROW> <ENT I="01">SFAR 44-5 Appendix </ENT> <ENT>2120-0502</ENT> </ROW> <ROW> <ENT I="01">SFAR 36 </ENT> <ENT>2120-0507</ENT> </ROW> </GPOTABLE> <CITA>[Doc. No. 23738, 48 FR 39449, Aug. 31, 1983]</CITA> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For <E T="04">Federal Register</E> citations affecting § 11.101, see the List of CFR Sections Affected in the Finding Aids section of this volume. </EDNOTE> </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 13</EAR> <HD SOURCE="HED">PART 13—INVESTIGATIVE AND ENFORCEMENT PROCEDURES</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—Investigative Procedures</HD> <SECHD>Sec.</SECHD> <SECTNO>13.1</SECTNO> <SUBJECT>Reports of violations.</SUBJECT> <SECTNO>13.3</SECTNO> <SUBJECT>Investigations (general).</SUBJECT> <SECTNO>13.5</SECTNO> <SUBJECT>Formal complaints.</SUBJECT> <SECTNO>13.7</SECTNO> <SUBJECT>Records, documents and reports.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Administrative Actions</HD> <SECTNO>13.11</SECTNO> <SUBJECT>Administrative disposition of certain violations.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Legal Enforcement Actions</HD> <SECTNO>13.13</SECTNO> <SUBJECT>Consent orders.</SUBJECT> <SECTNO>13.15</SECTNO> <SUBJECT>Civil penalties: Federal Aviation Act of 1958, as amended, involving an amount in controversy in excess of $50,000; an in rem action; seizure of aircraft; or injunctive relief.</SUBJECT> <SECTNO>13.16</SECTNO> <SUBJECT>Civil penalties: Federal Aviation Act of 1958, involving an amount in controversy not exceeding $50,000; Hazardous Materials Transportation Act.</SUBJECT> <SECTNO>13.17</SECTNO> <SUBJECT>Seizure of aircraft.</SUBJECT> <SECTNO>13.19</SECTNO> <SUBJECT>Certificate action.</SUBJECT> <SECTNO>13.20</SECTNO> <SUBJECT>Orders of compliance, cease and desist orders, orders of denial, and other orders.</SUBJECT> <SECTNO>13.21</SECTNO> <SUBJECT>Military personnel.</SUBJECT> <SECTNO>13.23</SECTNO> <SUBJECT>Criminal penalties.</SUBJECT> <SECTNO>13.25</SECTNO> <SUBJECT>Injunctions.</SUBJECT> <SECTNO>13.27</SECTNO> <SUBJECT>Final order of Hearing Officer in certificate of aircraft registration proceedings.</SUBJECT> <SECTNO>13.29</SECTNO> <SUBJECT>Civil penalties: Streamlined enforcement procedures for certain security violations.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Rules of Practice for FAA Hearings</HD> <SECTNO>13.31</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>13.33</SECTNO> <SUBJECT>Appearances.</SUBJECT> <SECTNO>13.35</SECTNO> <SUBJECT>Request for hearing.</SUBJECT> <SECTNO>13.37</SECTNO> <SUBJECT>Hearing Officer's powers.</SUBJECT> <SECTNO>13.39</SECTNO> <SUBJECT>Disqualification of Hearing Officer.</SUBJECT> <SECTNO>13.41</SECTNO> <SUBJECT>[Reserved]</SUBJECT> <SECTNO>13.43</SECTNO> <SUBJECT>Service and filing of pleadings, motions, and documents.</SUBJECT> <SECTNO>13.44</SECTNO> <SUBJECT>Computation of time and extension of time.</SUBJECT> <SECTNO>13.45</SECTNO> <SUBJECT>Amendment of notice and answer.</SUBJECT> <SECTNO>13.47</SECTNO> <SUBJECT>Withdrawal of notice or request for hearing.</SUBJECT> <SECTNO>13.49</SECTNO> <SUBJECT>Motions.</SUBJECT> <SECTNO>13.51</SECTNO> <SUBJECT>Intervention.</SUBJECT> <SECTNO>13.53</SECTNO> <SUBJECT>Depositions.</SUBJECT> <SECTNO>13.55</SECTNO> <SUBJECT>Notice of hearing.</SUBJECT> <SECTNO>13.57</SECTNO> <SUBJECT>Subpoenas and witness fees.</SUBJECT> <SECTNO>13.59</SECTNO> <SUBJECT>Evidence.</SUBJECT> <SECTNO>13.61</SECTNO> <SUBJECT>Argument and submittals.</SUBJECT> <SECTNO>13.63</SECTNO> <SUBJECT>Record.</SUBJECT> </SUBPART> <SUBPART> <PRTPAGE P="32"/> <HD SOURCE="HED">Subpart E—Orders of Compliance Under the Hazardous Materials Transportation Act</HD> <SECTNO>13.71</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>13.73</SECTNO> <SUBJECT>Notice of proposed order of compliance.</SUBJECT> <SECTNO>13.75</SECTNO> <SUBJECT>Reply or request for hearing.</SUBJECT> <SECTNO>13.77</SECTNO> <SUBJECT>Consent order of compliance.</SUBJECT> <SECTNO>13.79</SECTNO> <SUBJECT>Hearing.</SUBJECT> <SECTNO>13.81</SECTNO> <SUBJECT>Order of immediate compliance.</SUBJECT> <SECTNO>13.83</SECTNO> <SUBJECT>Appeal.</SUBJECT> <SECTNO>13.85</SECTNO> <SUBJECT>Filing, service and computation of time.</SUBJECT> <SECTNO>13.87</SECTNO> <SUBJECT>Extension of time.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Formal Fact-Finding Investigation Under an Order of Investigation</HD> <SECTNO>13.101</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>13.103</SECTNO> <SUBJECT>Order of investigation.</SUBJECT> <SECTNO>13.105</SECTNO> <SUBJECT>Notification.</SUBJECT> <SECTNO>13.107</SECTNO> <SUBJECT>Designation of additional parties.</SUBJECT> <SECTNO>13.109</SECTNO> <SUBJECT>Convening the investigation.</SUBJECT> <SECTNO>13.111</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> <SECTNO>13.113</SECTNO> <SUBJECT>Noncompliance with the investigative process.</SUBJECT> <SECTNO>13.115</SECTNO> <SUBJECT>Public proceedings.</SUBJECT> <SECTNO>13.117</SECTNO> <SUBJECT>Conduct of investigative proceeding or deposition.</SUBJECT> <SECTNO>13.119</SECTNO> <SUBJECT>Rights of persons against self-incrimination.</SUBJECT> <SECTNO>13.121</SECTNO> <SUBJECT>Witness fees.</SUBJECT> <SECTNO>13.123</SECTNO> <SUBJECT>Submission by party to the investigation.</SUBJECT> <SECTNO>13.125</SECTNO> <SUBJECT>Depositions.</SUBJECT> <SECTNO>13.127</SECTNO> <SUBJECT>Reports, decisions and orders.</SUBJECT> <SECTNO>13.129</SECTNO> <SUBJECT>Post-investigation action.</SUBJECT> <SECTNO>13.131</SECTNO> <SUBJECT>Other procedures.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Rules of Practice in FAA Civil Penalty Actions</HD> <SECTNO>13.201</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>13.202</SECTNO> <SUBJECT>Definitions.</SUBJECT> <SECTNO>13.203</SECTNO> <SUBJECT>Separation of functions.</SUBJECT> <SECTNO>13.204</SECTNO> <SUBJECT>Appearances and rights of parties.</SUBJECT> <SECTNO>13.205</SECTNO> <SUBJECT>Administrative law judges.</SUBJECT> <SECTNO>13.206</SECTNO> <SUBJECT>Intervention.</SUBJECT> <SECTNO>13.207</SECTNO> <SUBJECT>Certification of documents.</SUBJECT> <SECTNO>13.208</SECTNO> <SUBJECT>Complaint.</SUBJECT> <SECTNO>13.209</SECTNO> <SUBJECT>Answer.</SUBJECT> <SECTNO>13.210</SECTNO> <SUBJECT>Filing of documents.</SUBJECT> <SECTNO>13.211</SECTNO> <SUBJECT>Service of documents.</SUBJECT> <SECTNO>13.212</SECTNO> <SUBJECT>Computation of time.</SUBJECT> <SECTNO>13.213</SECTNO> <SUBJECT>Extension of time.</SUBJECT> <SECTNO>13.214</SECTNO> <SUBJECT>Amendment of pleadings.</SUBJECT> <SECTNO>13.215</SECTNO> <SUBJECT>Withdrawal of complaint or request for hearing.</SUBJECT> <SECTNO>13.216</SECTNO> <SUBJECT>Waivers.</SUBJECT> <SECTNO>13.217</SECTNO> <SUBJECT>Joint procedural or discovery schedule.</SUBJECT> <SECTNO>13.218</SECTNO> <SUBJECT>Motions.</SUBJECT> <SECTNO>13.219</SECTNO> <SUBJECT>Interlocutory appeals.</SUBJECT> <SECTNO>13.220</SECTNO> <SUBJECT>Discovery.</SUBJECT> <SECTNO>13.221</SECTNO> <SUBJECT>Notice of hearing.</SUBJECT> <SECTNO>13.222</SECTNO> <SUBJECT>Evidence.</SUBJECT> <SECTNO>13.223</SECTNO> <SUBJECT>Standard of proof.</SUBJECT> <SECTNO>13.224</SECTNO> <SUBJECT>Burden of proof.</SUBJECT> <SECTNO>13.225</SECTNO> <SUBJECT>Offer of proof.</SUBJECT> <SECTNO>13.226</SECTNO> <SUBJECT>Public disclosure of evidence.</SUBJECT> <SECTNO>13.227</SECTNO> <SUBJECT>Expert or opinion witnesses.</SUBJECT> <SECTNO>13.228</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> <SECTNO>13.229</SECTNO> <SUBJECT>Witness fees.</SUBJECT> <SECTNO>13.230</SECTNO> <SUBJECT>Record.</SUBJECT> <SECTNO>13.231</SECTNO> <SUBJECT>Argument before the administrative law judge.</SUBJECT> <SECTNO>13.232</SECTNO> <SUBJECT>Initial decision.</SUBJECT> <SECTNO>13.233</SECTNO> <SUBJECT>Appeal from initial decision.</SUBJECT> <SECTNO>13.234</SECTNO> <SUBJECT>Petition to reconsider or modify a final decision and order of the FAA decisionmaker on appeal.</SUBJECT> <SECTNO>13.235</SECTNO> <SUBJECT>Judicial review of a final decision and order.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Civil Monetary Penalty Inflation Adjustment</HD> <SECTNO>13.301</SECTNO> <SUBJECT>Scope and purpose.</SUBJECT> <SECTNO>13.303</SECTNO> <SUBJECT>Definitions.</SUBJECT> <SECTNO>13.305</SECTNO> <SUBJECT>Cost of living adjustments of civil monetary penalties.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 18 U.S.C. 6002; 28 U.S.C. 2461 (note); 49 U.S.C. 106(g), 5121-5124, 40113-40114, 44103-44106, 44702-44703, 44709-44710, 44713, 46101-46110, 46301-46316, 46501-46502, 46504-46507, 47106, 47111, 47122, 47306, 47531-47532. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 18884, 44 FR 63723, Nov. 5, 1979, unless otherwise noted. </SOURCE> <SUBPART> <HD SOURCE="HED">Subpart A—Investigative Procedures</HD> <SECTION> <SECTNO>§ 13.1</SECTNO> <SUBJECT>Reports of violations.</SUBJECT> (a) Any person who knows of a violation of the Federal Aviation Act of 1958, as amended, the Hazardous Materials Transportation Act relating to the transportation or shipment by air of hazardous materials, the Airport and Airway Development Act of 1970, the Airport and Airway Improvement Act of 1982, the Airport and Airway Improvement Act of 1982 as amended by the Airport and Airway Safety and Capacity Expansion Act of 1987, or any rule, regulation, or order issued thereunder, should report it to appropriate personnel of any FAA regional or district office. (b) Each report made under this section, together with any other information the FAA may have that is relevant to the matter reported, will be <PRTPAGE P="33"/>reviewed by FAA personnel to determine the nature and type of any additional investigation or enforcement action the FAA will take. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-17, 53 FR 33783, Aug. 31, 1988]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.3</SECTNO> <SUBJECT>Investigations (general).</SUBJECT> (a) Under the Federal Aviation Act of 1958, as amended, (49 U.S.C. 1301 <E T="03">et seq.</E>), the Hazardous Materials Transportation Act (49 U.S.C. 1801 <E T="03">et seq.</E>), the Airport and Airway Development Act of 1970 (49 U.S.C. 1701 <E T="03">et seq.</E>), the Airport and Airway Improvement Act of 1982 (49 U.S.C. 2201 <E T="03">et seq.</E>), the Airport and Airway Improvement Act of 1982 (as amended, 49 U.S.C. App. 2201 <E T="03">et seq., </E> Airport and Airway Safety and Capacity Expansion Act of 1987), and the Regulations of the Office of the Secretary of Transportation (49 CFR 1 <E T="03">et seq.</E>), the Administrator may conduct investigations, hold hearings, issue subpoenas, require the production of relevant documents, records, and property, and take evidence and depositions. (b) For the purpose of investigating alleged violations of the Federal Aviation Act of 1958, as amended the Hazardous Materials Transportation Act, the Airport and Airway Development Act of 1970, the Airport and Airway Improvement Act of 1982, the Airport and Airway Improvement Act of 1982 as amended by the Airport and Airway Safety and Capacity Expansion Act of 1987, or any rule, regulation, or order issued thereunder, the Administrator's authority has been delegated to the various services and or offices for matters within their respective areas for all routine investigations. When the compulsory processes of sections 313 and 1004 (49 U.S.C. 1354 and 1484) of the Federal Aviation Act, or section 109 of the Hazardous Materials Transportation Act (49 U.S.C. 1808) are invoked, the Administrator's authority has been delegated to the Chief Counsel, the Deputy Chief Counsel, each Assistant Chief Counsel, each Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel. (c) In conducting formal investigations, the Chief Counsel, the Deputy Chief Counsel, each Assistant Chief Counsel, each Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel may issue an order of investigation in accordance with Subpart F of this part. (d) A complaint against the sponsor, proprietor, or operator of a Federally-assisted airport involving violations of the legal authorities listed in § 16.1 of this chapter shall be filed in accordance with the provisions of part 16 of this chapter, except in the case of complaints, investigations, and proceedings initiated before December 16, 1996, the effective date of part 16 of this chapter. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-17, 53 FR 33783, Aug. 31, 1988; 53 FR 35255, Sept. 12, 1988; Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-27, 61 FR 54004, Oct. 16, 1996; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.5</SECTNO> <SUBJECT>Formal complaints.</SUBJECT> (a) Any person may file a complaint with the Administrator with respect to anything done or omitted to be done by any person in contravention of any provision of any Act or of any regulation or order issued under it, as to matters within the jurisdiction of the Administrator. This section does not apply to complaints against the Administrator or employees of the FAA acting within the scope of their employment. (b) Complaints filed under this section must— (1) Be submitted in writing and identified as a complaint filed for the purpose of seeking an appropriate order or other enforcement action; (2) Be submitted to the Federal Aviation Administration, Office of the Chief Counsel, Attention: Enforcement Docket (AGC-10), 800 Independence Avenue, S.W., Washington, DC 20591; (3) Set forth the name and address, if known, of each person who is the subject of the complaint and, with respect to each person, the specific provisions of the Act or regulation or order that the complainant believes were violated; (4) Contain a concise but complete statement of the facts relied upon to substantiate each allegation; (5) State the name, address and telephone number of the person filing the complaint; and<PRTPAGE P="34"/> (6) Be signed by the person filing the complaint or a duly authorized representative. (c) Complaints which do not meet the requirements of paragraph (b) of this section will be considered reports under § 13.1. (d) Complaints which meet the requirements of paragraph (b) of this section will be docketed and a copy mailed to each person named in the complaint. (e) Any complaint filed against a member of the Armed Forces of the United States acting in the performance of official duties shall be referred to the Secretary of the Department concerned for action in accordance with the procedures set forth in § 13.21 of this part. (f) The person named in the complaint shall file an answer within 20 days after service of a copy of the complaint. (g) After the complaint has been answered or after the allotted time in which to file an answer has expired, the Administrator shall determine if there are reasonable grounds for investigating the complaint. (h) If the Administrator determines that a complaint does not state facts which warrant an investigation or action, the complaint may be dismissed without a hearing and the reason for the dismissal shall be given, in writing, to the person who filed the complaint and the person named in the complaint. (i) If the Administrator determines that reasonable grounds exist, an informal investigation may be initiated or an order of investigation may be issued in accordance with Subpart F of this part, or both. Each person named in the complaint shall be advised which official has been delegated the responsibility under § 13.3(b) or (c) for conducting the investigation. (j) If the investigation substantiates the allegations set forth in the complaint, a notice of proposed order may be issued or other enforcement action taken in accordance with this part. (k) The complaint and other pleadings and official FAA records relating to the disposition of the complaint are maintained in current docket form in the Enforcement Docket (AGC-10), Office of the Chief Counsel, Federal Aviation Administration, 800 Independence Avenue, S.W., Washington, D. C. 20591. Any interested person may examine any docketed material at that office, at any time after the docket is established, except material that is ordered withheld from the public under applicable law or regulations, and may obtain a photostatic or duplicate copy upon paying the cost of the copy. <SECAUTH>(Secs. 313(a), 314(a), 601 through 610, and 1102 of the Federal Aviation Act of 1958 (49 U.S.C. 1354(a), 1421 through 1430, 1502); sec. 6(c), Dept. of Transportation Act (49 U.S.C. 1655(c)))</SECAUTH> <CITA>[Doc. No 13-14, 44 FR 63723, Nov. 5, 1979; as amended by Amdt. 13-16, 45 FR 35307, May 27, 1980; Amdt. 13-19, 54 FR 39290, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.7</SECTNO> <SUBJECT>Records, documents and reports.</SUBJECT> Each record, document and report that the Federal Aviation Regulations require to be maintained, exhibited or submitted to the Administrator may be used in any investigation conducted by the Administrator; and, except to the extent the use may be specifically limited or prohibited by the section which imposes the requirement, the records, documents and reports may be used in any civil penalty action, certificate action, or other legal proceeding. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Administrative Actions</HD> <SECTION> <SECTNO>§ 13.11</SECTNO> <SUBJECT>Administrative disposition of certain violations.</SUBJECT> (a) If it is determined that a violation or an alleged violation of the Federal Aviation Act of 1958, or an order or regulation issued under it, or of the Hazardous Materials Transportation Act, or an order or regulation issued under it, does not require legal enforcement action, an appropriate official of the FAA field office responsible for processing the enforcement case or other appropriate FAA official may take administrative action in disposition of the case. (b) An administrative action under this section does not constitute a formal adjudication of the matter, and may be taken by issuing the alleged violator— (1) A “Warning Notice” which recites available facts and information about <PRTPAGE P="35"/>the incident or condition and indicates that it may have been a violation; or (2) A “Letter of Correction” which confirms the FAA decision in the matter and states the necessary corrective action the alleged violator has taken or agrees to take. If the agreed corrective action is not fully completed, legal enforcement action may be taken. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Legal Enforcement Actions</HD> <SECTION> <SECTNO>§ 13.13</SECTNO> <SUBJECT>Consent orders.</SUBJECT> (a) At any time before the issuance of an order under this subpart, the official who issued the notice and the person subject to the notice may agree to dispose of the case by the issuance of a consent order by the official. (b) A proposal for a consent order, submitted to the official who issued the notice, under this section must include— (1) A proposed order; (2) An admission of all jurisdictional facts; (3) An express waiver of the right to further procedural steps and of all rights to judicial review; and (4) An incorporation by reference of the notice and an acknowledgment that the notice may be used to construe the terms of the order. (c) If the issuance of a consent order has been agreed upon after the filing of a request for hearing in accordance with Subpart D of this part, the proposal for a consent order shall include a request to be filed with the Hearing Officer withdrawing the request for a hearing and requesting that the case be dismissed. </SECTION> <SECTION> <SECTNO>§ 13.15</SECTNO> <SUBJECT>Civil penalties: Federal Aviation Act of 1958, as amended, involving an amount in controversy in excess of $50,000; an in rem action; seizure of aircraft; or injunctive relief.</SUBJECT> (a) The following penalties apply to persons who violate the Federal Aviation Act of l958, as amended: (1) Any person who violates any provision of Title III, V, VI, or XII of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than the amount specified in the Act for each violation in accordance with section 901 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1471, <E T="03">et seq.</E>). (2) Any person who violates section 404(d) of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than the amount specified in the Act for each violation in accordance with section 404(d) or section 901 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1374, 1471, <E T="03">et seq.</E>). (3) Any person who operates aircraft for the carriage of persons or property for compensation or hire (other than an airman serving in the capacity of an airman) is subject to a civil penalty of not more than $10,000 for each violation of Title III, VI, or XII of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, occurring after December 30, 1987, in accordance with section 901 of the Federal Aviation Act of l958, as amended (49 U.S.C. 1471 <E T="03">et seq.</E>). (b) The authority of the Administrator, under section 901 of the Federal Aviation Act of 1958, as amended, to propose a civil penalty for a violation of that Act, or a rule, regulation, or order issued thereunder, and the ability to refer cases to the United States Attorney General, or the delegate of the Attorney General, for prosecution of civil penalty actions proposed by the Administrator, involving an amount in controversy in excess of $50,000, an <E T="03">in rem</E> action, seizure of aircraft subject to lien, or suit for injunctive relief, or for collection of an assessed civil penalty, is delegated to the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, the Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel. (c) The Administrator may compromise any civil penalty, proposed in accordance with section 901 of the Federal Aviation Act of 1958, as amended, involving an amount in controversy in excess of $50,000, an <E T="03">in rem</E> action, seizure of aircraft subject to lien, or suit for injunctive relief, prior to referral of the civil penalty action to the United <PRTPAGE P="36"/>States Attorney General, or the delegate of the Attorney General, for prosecution. (1) The Administrator, through the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, the Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel sends a civil penalty letter to the person charged with a violation of the Federal Aviation Act of 1958, as amended, or a rule, regulation, or order issued thereunder. The civil penalty letter contains a statement of the charges, the applicable law, rule, regulation, or order, the amount of civil penalty that the Administrator will accept in full settlement of the action or an offer to compromise the civil penalty. (2) Not later than 30 days after receipt of the civil penalty letter, the person charged with a violation may present any material or information in answer to the charges to the agency attorney, either orally or in writing, that may explain, mitigate, or deny the violation or that may show extenuating circumstances. The Administrator will consider any material or information submitted in accordance with this paragraph to determine whether the person is subject to a civil penalty or to determine the amount for which the Administrator will compromise the action. (3) If the person charged with the violation offers to compromise for a specific amount, that person shall send a certified check or money order for that amount, payable to the Federal Aviation Administration, to the agency attorney. The Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, the Regional Counsel, the Aeronautical Center Counsel, or the Technical Center Counsel may accept the certified check or money order or may refuse and return the certified check or money order. (4) If the offer to compromise is accepted by the Administrator, the agency attorney will send a letter to the person charged with the violation stating that the certified check or money order is accepted in full settlement of the civil penalty action. (5) If the parties cannot agree to compromise the civil penalty action or the offer to compromise is rejected and the certified check or money order submitted in compromise is returned, the Administrator may refer the civil penalty action to the United States Attorney General, or the delegate of the Attorney General, to begin proceedings in a United States District Court, pursuant to the authority in section 903 of the Federal Aviation Act, as amended (49 U.S.C. 1473), to prosecute and collect the civil penalty. <CITA>[Amdt. 13-18, 53 FR 34653, Sept. 7, 1988, as amended by Amdt. 13-20, 55 FR 15128, Apr. 20, 1990; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.16</SECTNO> <SUBJECT>Civil penalties: Federal Aviation Act of 1958, involving an amount in controversy not exceeding $50,000; Hazardous Materials Transportation Act.</SUBJECT> (a) <E T="03">General.</E> The following penalties apply to persons who violate the Federal Aviation Act of 1958, as amended, and the Hazardous Materials Transportation Act: (1) Any person who violates any provision of title III, V, VI, or XII of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than the amount specified in the Act for each violation in accordance with section 901 of the Federal Aviation Act, of 1958, as amended (49 U.S.C. 1471, <E T="03">et seq</E>.). (2) Any person who violates section 404(d) of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than the amount specified in the Act for each violation in accordance with section 404(d) or section 901 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1374, 1471, <E T="03">et seq</E>.). (3) Any person who operates aircraft for the carriage of persons or property for compensation or hire (other than an airman serving in the capacity of an airman) is subject to a civil penalty of not more than $10,000 for each violation of title III, VI, or XII of the Federal <PRTPAGE P="37"/>Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, occurring after December 30, 1987, in accordance with section 901 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1471, <E T="03">et seq</E>.). (4) Any person who knowingly commits an act in violation of the Hazardous Materials Transportation Act, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than $10,000 for each violation in accordance with section 901 of the Federal Aviation Act of 1958, as amended, and section 110 of the Hazardous Materials Transportation Act (49 U.S.C. 1471 and 1809, <E T="03">et seq</E>.). An order assessing civil penalty for a violation under the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder, will be issued only after consideration of— (i) The nature and circumstances of the violation; (ii) The extent and gravity of the violation; (iii) The person's degree of culpability; (iv) The person's history of prior violations; (v) The person's ability to pay the civil penalty; (vi) The effect on the person's ability to continue in business; and (vii) Such other matters as justice may require. (b) <E T="03">Order assessing civil penalty</E>. An order assessing civil penalty may be issued for a violation described in paragraph (a) of this section, or as otherwise provided by statute, after notice and opportunity for a hearing. A person charged with a violation may be subject to an order assessing civil penalty in the following circumstances: (1) An order assessing civil penalty may be issued if a person charged with a violation submits or agrees to submit a civil penalty for a violation. (2) An order assessing civil penalty may be issued if a person charged with a violation does not request a hearing under paragraph (e)(2)(ii) of this section within 15 days after receipt of a final notice of proposed civil penalty. (3) Unless an appeal is filed with the FAA decisionmaker in a timely manner, an initial decision or order of an administrative law judge shall be considered an order assessing civil penalty if an administrative law judge finds that an alleged violation occurred and determines that a civil penalty, in an amount found appropriate by the administrative law judge, is warranted. (4) Unless a petition for review is filed with a U.S. Court of Appeals in a timely manner, a final decision and order of the Administrator shall be considered an order assessing civil penalty if the FAA decisionmaker finds that an alleged violation occurred and a civil penalty is warranted. (c) <E T="03">Delegation of authority</E>. The authority of the Administrator, under section 901 and section 905 of the Federal Aviation Act of 1958, as amended, and section 110 of the Hazardous Materials Transportation Act, to initiate and assess civil penalties for a violation of those Acts, or a rule, regulation, or order issued thereunder, is delegated to the Deputy Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel. The authority of the Administrator to refer cases to the Attorney General of the United States, or the delegate of the Attorney General, for the collection of civil penalties, is delegated to the Chief Counsel, the Deputy Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel. (d) <E T="03">Notice of proposed civil penalty</E>. A civil penalty action is initiated by sending a notice of proposed civil penalty to the person charged with a violation of the Federal Aviation Act of 1958, as amended, the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder. A notice of proposed civil penalty will be sent to the individual charged with a violation or to the president of the corporation or company charged with a violation. In response to a notice of proposed civil penalty, a corporation or <PRTPAGE P="38"/>company may designate in writing another person to receive documents in that civil penalty action. The notice of proposed civil penalty contains a statement of the charges and the amount of the proposed civil penalty. Not later than 30 days after receipt of the notice of proposed civil penalty, the person charged with a violation shall— (1) Submit the amount of the proposed civil penalty or an agreed-upon amount, in which case either an order assessing civil penalty or compromise order shall be issued in that amount; (2) Submit to the agency attorney one of the following: (i) Written information, including documents and witness statements, demonstrating that a violation of the regulations did not occur or that a penalty or the amount of the penalty is not warranted by the circumstances. (ii) A written request to reduce the proposed civil penalty, the amount of reduction, and the reasons and any documents supporting a reduction of the proposed civil penalty, including records indicating a financial inability to pay or records showing that payment of the proposed civil penalty would prevent the person from continuing in business. (iii) A written request for an informal conference to discuss the matter with the agency attorney and to submit relevant information or documents; or (3) Request a hearing in which case a complaint shall be filed with the hearing docket clerk. (e) <E T="03">Final notice of proposed civil penalty</E>. A final notice of proposed civil penalty may be issued after participation in informal procedures provided in paragraph (d)(2) of this section or failure to respond in a time1y manner to a notice of proposed civil penalty. A final notice of proposed civil penalty will be sent to the individual charged with a violation, to the president of the corporation or company charged with a violation, or a person previously designated in writing by the individual, corporation, or company to receive documents in that civil penalty action. If not previously done in response to a notice of proposed civil penalty, a corporation or company may designate in writing another person to receive documents in that civil penalty action. The final notice of proposed civil penalty contains a statement of the charges and the amount of the proposed civil penalty and, as a result of information submitted to the agency attorney during informal procedures, may modify an allegation or a proposed civil penalty contained in a notice of proposed civil penalty. (1) A final notice of proposed civil penalty may be issued— (i) If the person charged with a violation fails to respond to the notice of proposed civil penalty within 30 days after receipt of that notice; or (ii) If the parties participated in any informal procedures under paragraph (d)(2) of this section and the parties have not agreed to compromise the action or the agency attorney has not agreed to withdraw the notice of proposed civil penalty. (2) Not later than 15 days after receipt of the final notice of proposed civil penalty, the person charged with a violation shall do one of the following— (i) Submit the amount of the proposed civil penalty or an agreed-upon amount, in which case either an order assessing civil penalty or a compromise order shall be issued in that amount; or (ii) Request a hearing in which case a complaint shall be filed with the hearing docket clerk. (f) <E T="03">Request for a hearing.</E> Any person charged with a violation may request a hearing, pursuant to paragraph (d)(3) or paragraph (e)(2)(ii) of this section, to be conducted in accordance with the procedures in subpart G of this part. A person requesting a hearing shall file a written request for a hearing with the hearing docket clerk (Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591, Attention: Hearing Docket Clerk) and shall mail a copy of the request to the agency attorney. The request for a hearing may be in the form of a letter but must be dated and signed by the person requesting a hearing. The request for a hearing may be typewritten or may be legibly handwritten. (g) <E T="03">Hearing.</E> If the person charged with a violation requests a hearing <PRTPAGE P="39"/>pursuant to paragraph (d)(3) or paragraph (e)(2)(ii) of this section, the original complaint shall be filed with the hearing docket clerk and a copy shall be sent to the person requesting the hearing. The procedural rules in subpart G of this part apply to the hearing and any appeal. At the close of the hearing, the administrative law judge shall issue, either orally on the record or in writing, an initial decision, including the reasons for the decision, that contains findings or conclusions on the allegations contained, and the civil penalty sought, in the complaint. (h) <E T="03">Appeal.</E> Either party may appeal the administrative law judge's initial decision to the FAA decisionmaker pursuant to the procedures in subpart G of this part. If a party files a notice of appeal pursuant to § 13.233 of subpart G, the effectiveness of the initial decision is stayed until a final decision and order of the Administrator have been entered on the record. The FAA decisionmaker shall review the record and issue a final decision and order of the Administrator that affirm, modify, or reverse the initial decision. The FAA decisionmaker may assess a civil penalty but shall not assess a civil penalty in an amount greater than that sought in the complaint. (i) <E T="03">Payment.</E> A person shall pay a civil penalty by sending a certified check or money order, payable to the Federal Aviation Administration, to the agency attorney. (j) <E T="03">Collection of civil penalties.</E> If a person does not pay a civil penalty imposed by an order assessing civil penalty or a compromise order within 60 days after service of the order, the Administrator may refer the order to the United States Attorney General, or the delegate of the Attorney General, to begin proceedings to collect the civil penalty. The action shall be brought in a United States District Court, pursuant to the authority in section 903 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1473), or section 110 of the Hazardous Materials Transportation Act (49 U.S.C. 1809). (k) <E T="03">Exhaustion of administrative remedies.</E> A party may only petition for review of a final decision and order of the Administrator to the courts of appeals of the United States or the United States Court of Appeals for the District of Columbia pursuant to section 1006 of the Federal Aviation Act of 1958, as amended. Neither an initial decision or order issued by an administrative law judge, that has not been appealed to the FAA decisionmaker, nor an order compromising a civil penalty action constitutes a final order of the Administrator for the purposes of judicial appellate review under section 1006 of the Federal Aviation Act of 1958, as amended. (l) <E T="03">Compromise.</E> The FAA may compromise any civil penalty action initiated in accordance with section 901 and section 905 of the Federal Aviation Act of 1958, as amended, involving an amount in controversy not exceeding $50,000, or any civil penalty action initiated in accordance with section 901 of the Federal Aviation Act of 1958, as amended, and section 110 of the Hazardous Materials Transportation Act, at any time before referring the action to the United States Attorney for collection. (1) An agency attorney may compromise any civil penalty action where a person charged with a violation agrees to pay a civil penalty and the FAA agrees to make no finding of violation. Pursuant to such agreement, a compromise order shall be issued, stating: (i) The person agrees to pay a civil penalty. (ii) The FAA makes no finding of a violation. (iii) The compromise order shall not be used as evidence of a prior violation in any subsequent civil penalty proceeding or certificate action proceeding. (2) An agency attorney may compromise the amount of any civil penalty proposed in a notice, assessed in an order, or imposed in a compromise order. <CITA>[Amdt. 13-21, 55 FR 27574, July 3, 1990; 55 FR 29293, July 18, 1990; 55 FR 31027, July 30, 1990; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.17</SECTNO> <SUBJECT>Seizure of aircraft.</SUBJECT> (a) Under section 903 of the Federal Aviation Act of 1958 (49 U.S.C. 1473), a <PRTPAGE P="40"/>State or Federal law enforcement officer, or a Federal Aviation Administration safety inspector, authorized in an order of seizure issued by the Regional Administrator of the region, or by the Chief Counsel, may summarily seize an aircraft that is involved in a violation for which a civil penalty may be imposed on its owner or operator. (b) Each person seizing an aircraft under this section shall place it in the nearest available and adequate public storage facility in the judicial district in which it was seized. (c) The Regional Administrator or Chief Counsel, without delay, sends a written notice and a copy of this section, to the registered owner of the seized aircraft, and to each other persons shown by FAA records to have an interest in it, stating the— (1) Time, date, and place of seizure; (2) Name and address of the custodian of the aircraft; (3) Reasons for the seizure, including the violations believed, or judicially determined, to have been committed; and (4) Amount that may be tendered as— (i) A compromise of a civil penalty for the alleged violation; or (ii) Payment for a civil penalty imposed by a Federal court for a proven violation. (d) The Chief Counsel, or the Regional Counsel or Assistant Chief Counsel for the region or area in which an aircraft is seized under this section, immediately sends a report to the United States District Attorney for the judicial district in which it was seized, requesting the District Attorney to institute proceedings to enforce a lien against the aircraft. (e) The Regional Administrator or Chief Counsel directs the release of a seized aircraft whenever— (1) The alleged violator pays a civil penalty or an amount agreed upon in compromise, and the costs of seizing, storing, and maintaining the aircraft; (2) The aircraft is seized under an order of a Federal Court in proceedings in rem to enforce a lien against the aircraft, or the United States District Attorney for the judicial district concerned notifies the FAA that the District Attorney refuses to institute those proceedings; or (3) A bond in the amount and with the sureties prescribed by the Chief Counsel, the Regional Counsel, or the Assistant Chief Counsel is deposited, conditioned on payment of the penalty, or the compromise amount, and the costs of seizing, storing, and maintaining the aircraft. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.19</SECTNO> <SUBJECT>Certificate action.</SUBJECT> (a) Under section 609 of the Federal Aviation Act of 1958 (49 U.S.C. 1429), the Administrator may reinspect any civil aircraft, aircraft engine, propeller, appliance, air navigation facility, or air agency, and may re-examine any civil airman. Under section 501(e) of the FA Act, any Certificate of Aircraft Registration may be suspended or revoked by the Administrator for any cause that renders the aircraft ineligible for registration. (b) If, as a result of such a reinspection re-examination, or other investigation made by the Administrator under section 609 of the FA Act, the Administrator determines that the public interest and safety in air commerce requires it, the Administrator may issue an order amending, suspending, or revoking, all or part of any type certificate, production certificate, airworthiness certificate, airman certificate, air carrier operating certificate, air navigation facility certificate, or air agency certificate. This authority may be exercised for remedial purposes in cases involving the Hazardous Materials Transportation Act (49 U.S.C. 1801 et seq.) or regulations issued under that Act. This authority is also exercised by the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, and the Aeronautical Center Counsel. If the Administrator finds that any aircraft registered under Part 47 of this chapter is ineligible for registration or if the <PRTPAGE P="41"/>holder of a Certificate of Aircraft Registration has refused or failed to submit AC Form 8050-73, as required by § 47.51 of this chapter, the Administrator issues an order suspending or revoking that certificate. This authority as to aircraft found ineligible for registration is also exercised by each Regional Counsel, the Aeronautical Center Counsel, and the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office. (c) Before issuing an order under paragraph (b) of this section, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, or the Aeronautical Center Counsel advises the certificate holder of the charges or other reasons upon which the Administrator bases the proposed action and, except in an emergency, allows the holder to answer any charges and to be heard as to why the certificate should not be amended, suspended, or revoked. The holder may, by checking the appropriate box on the form that is sent to the holder with the notice of proposed certificate action, elect to— (1) Admit the charges and surrender his or her certificate; (2) Answer the charges in writing; (3) Request that an order be issued in accordance with the notice of proposed certificate action so that the certificate holder may appeal to the National Transportation Safety Board, if the charges concerning a matter under Title VI of the FA Act; (4) Request an opportunity to be heard in an informal conference with the FAA counsel; or (5) Request a hearing in accordance with Subpart D of this part if the charges concern a matter under Title V of the FA Act. <FP>Except as provided in § 13.35(b), unless the certificate holder returns the form and, where required, an answer or motion, with a postmark of not later than 15 days after the date of receipt of the notice, the order of the Administrator is issued as proposed. If the certificate holder has requested an informal conference with the FAA counsel and the charges concern a matter under Title V of the FA Act, the holder may after that conference also request a formal hearing in writing with a postmark of not later than 10 days after the close of the conference. After considering any information submitted by the certificate holder, the Chief Counsel, the Assistant Chief Counsel for Regulations and Enforcement, the Regional Counsel concerned, or the Aeronautical Center Counsel (as to matters under Title V of the FA Act) issues the order of the Administrator, except that if the holder has made a valid request for a formal hearing on a matter under Title V of the FA Act initially or after an informal conference, Subpart D of this part governs further proceedings.</FP> (d) Any person whose certificate is affected by an order issued under this section may appeal to the National Transportation Safety Board. If the certificate holder files an appeal with the Board, the Administrator's order is stayed unless the Administrator advises the Board that an emergency exists and safety in air commerce requires that the order become effective immediately. If the Board is so advised, the order remains effective and the Board shall finally dispose of the appeal within 60 days after the date of the advice. This paragraph does not apply to any person whose Certificate of Aircraft Registration is affected by an order issued under this section. <CITA>[Doc. No. 13-14, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-15, 45 FR 20773, Mar. 31, 1980; Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.20</SECTNO> <SUBJECT>Orders of compliance, cease and desist orders, orders of denial, and other orders.</SUBJECT> (a) This section applies to orders of compliance, cease and desist orders, orders of denial, and other orders issued by the Administrator to carry out the provisions of the Federal Aviation Act of 1958, as amended, the Hazardous Materials Transportation Act, the Airport and Airway Development Act of 1970, and the Airport and Airway Improvement Act of 1982, or the Airport and Airway Improvement Act of 1982 as amended by the Airport and Airway Safety and Capacity Expansion Act of 1987. This section does not apply to orders issued pursuant to section 602 or <PRTPAGE P="42"/>section 609 of the Federal Aviation Act of 1958, as amended. (b) Unless the Administrator determines that an emergency exists and safety in air commerce requires the immediate issuance of an order under this section, the person subject to the order shall be provided with notice prior to issuance. (c) Within 30 days after service of the notice, the person subject to the order may reply in writing or request a hearing in accordance with Subpart D of this part. (d) If a reply is filed, as to any charges not dismissed or not subject to a consent order, the person subject to the order may, within 10 days after receipt of notice that the remaining charges are not dismissed, request a hearing in accordance with Subpart D of this part. (e) Failure to request a hearing within the period provided in paragraphs (c) or (d) of this section— (1) Constitutes a waiver of the right to appeal and the right to a hearing, and (2) Authorizes the official who issued the notice to find the facts to be as alleged in the notice, or as modified as the official may determine necessary based on any written response, and to issue an appropriate order, without further notice or proceedings. (f) If a hearing is requested in accordance with paragraph (c) or (d) of this section, the procedure of Subpart D of this part applies. At the close of the hearing, the Hearing Officer, on the record or subsequently in writing, shall set forth findings and conclusions and the reasons therefor, and either— (1) Dismiss the notice; or (2) Issue an order. (g) Any party to the hearing may appeal from the order of the Hearing Officer by filing a notice of appeal with the Administrator within 20 days after the date of issuance of the order. (h) If a notice of appeal is not filed from the order issued by a Hearing Officer, such order is the final agency order. (i) Any person filing an appeal authorized by paragraph (g) of this section shall file an appeal brief with the Administrator within 40 days after the date of issuance of the order, and serve a copy on the other party. A reply brief must be filed within 20 days after service of the appeal brief and a copy served on the appellant. (j) On appeal the Administrator reviews the available record of the proceeding, and issues an order dismissing, reversing, modifying or affirming the order. The Administrator's order includes the reasons for the Administrator's action. (k) For good cause shown, requests for extensions of time to file any document under this section may be granted by— (1) The official who issued the order, if the request is filed prior to the designation of a Hearing Officer; or (2) The Hearing Officer, if the request is filed prior to the filing of a notice of appeal; or (3) The Administrator, if the request is filed after the filing of a notice of appeal. (l) Except in the case of an appeal from the decision of a Hearing Officer, the authority of the Administrator under this section is also exercised by the Chief Counsel, Deputy Chief Counsel, each Assistant Chief Counsel, each Regional Counsel, and the Aeronautical Center Counsel (as to matters under Title V of the Federal Aviation Act of 1958). (m) Filing and service of documents under this section shall be accomplished in accordance with § 13.43; and the periods of time specified in this section shall be computed in accordance with § 13.44. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-17, 53 FR 33783, Aug. 31, 1988; Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.21</SECTNO> <SUBJECT>Military personnel.</SUBJECT> If a report made under this part indicates that, while performing official duties, a member of the Armed Forces, or a civilian employee of the Department of Defense who is subject to the Uniform Code of Military Justice (10 U.S.C. Ch. 47), has violated the Federal Aviation Act of 1958, or a regulation or order issued under it, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East <PRTPAGE P="43"/>Area Office, each Regional Counsel, and the Aeronautical Center Counsel send a copy of the report to the appropriate military authority for such disciplinary action as that authority considers appropriate and a report to the Administrator thereon. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.23</SECTNO> <SUBJECT>Criminal penalties.</SUBJECT> (a) Sections 902 and 1203 of the Federal Aviation Act of 1958 (49 U.S.C. 1472 and 1523), provide criminal penalties for any person who knowingly and willfully violates specified provisions of that Act, or any regulation or order issued under those provisions. Section 110(b) of the Hazardous Materials Transportation Act (49 U.S.C. 1809(b)) provides for a criminal penalty of a fine of not more than $25,000, imprisonment for not more than five years, or both, for any person who willfully violates a provision of that Act or a regulation or order issued under it. (b) If an inspector or other employee of the FAA becomes aware of a possible violation of any criminal provision of the Federal Aviation Act of 1958 (except a violation of section 902 (i) through (m) which is reported directly to the Federal Bureau of Investigation), or of the Hazardous Materials Transportation Act, relating to the transportation or shipment by air of hazardous materials, he or she shall report it to the Office of the Chief Counsel or the Regional Counsel or Assistant Chief Counsel for the region or area concerned. If appropriate, that office refers the report to the Department of Justice for criminal prosecution of the offender. If such an inspector or other employee becomes aware of a possible violation of a Federal statute that is within the investigatory jurisdiction of another Federal agency, he or she shall immediately report it to that agency according to standard FAA practices. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.25</SECTNO> <SUBJECT>Injunctions.</SUBJECT> (a) Whenever it is determined that a person has engaged, or is about to engage, in any act or practice constituting a violation of the Federal Aviation Act of 1958, or any regulation or order issued under it for which the FAA exercises enforcement responsibility, or, with respect to the transportation or shipment by air of any hazardous materials, in any act or practice constituting a violation of the Hazardous Materials Transportation Act, or any regulation or order issued under it for which the FAA exercises enforcement responsibility, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, and the Aeronautical Center Counsel may request the United States Attorney General, or the delegate of the Attorney General, to bring an action in the appropriate United States District Court for such relief as is necessary or appropriate, including mandatory or prohibitive injunctive relief, interim equitable relief, and punitive damages, as provided by section 1007 of the Federal Aviation Act of 1958 (49 U.S.C. 1487) and section 111(a) of the Hazardous Materials Transportation Act (49 U.S.C. 1810). (b) Whenever it is determined that there is substantial likelihood that death, serious illness, or severe personal injury, will result from the transportation by air of a particular hazardous material before an order of compliance proceeding, or other administrative hearing or formal proceeding to abate the risk of the harm can be completed, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, and the Aeronautical Center Counsel may bring, or request the United States Attorney General to bring, an action in the appropriate United States District Court for an order suspending or restricting the transportation by air of the hazardous material or for such other order as is necessary to eliminate or ameliorate the imminent hazard, as provided by <PRTPAGE P="44"/>section 111(b) of the Hazardous Materials Transportation Act (49 U.S.C. 1810). <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.27</SECTNO> <SUBJECT>Final order of Hearing Officer in certificate of aircraft registration proceedings.</SUBJECT> (a) If, in proceedings under section 501(b) of the Federal Aviation Act of 1958 (49 USC 1401), the Hearing Officer determines that the holder of the Certificate of Aircraft Registration has refused or failed to submit AC Form 8050-73, as required by § 47.51 of this chapter, or that the aircraft is ineligible for a Certificate of Aircraft Registration, the Hearing Officer shall suspend or revoke the respondent's certificate, as proposed in the notice of proposed certificate action. (b) If the final order of the Hearing Officer makes a decision on the merits, it shall contain a statement of the findings and conclusions of law on all material issues of fact and law. If the Hearing Officer finds that the allegations of the notice have been proven, but that no sanction is required, the Hearing Officer shall make appropriate findings and issue an order terminating the notice. If the Hearing Officer finds that the allegations of the notice have not been proven, the Hearing Officer shall issue an order dismissing the notice. If the Hearing Officer finds it to be equitable and in the public interest, the Hearing Officer shall issue an order terminating the proceeding upon payment by the respondent of a civil penalty in an amount agreed upon by the parties. (c) If the order is issued in writing, it shall be served upon the parties. <CITA>[Doc. No. 13-14, 44 FR 63723, Nov. 5, 1979; as amended by Amdt. 13-15, 45 FR 20773, Mar. 31, 1980]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.29</SECTNO> <SUBJECT>Civil penalties: Streamlined enforcement procedures for certain security violations.</SUBJECT> This section may be used, at the agency's discretion, in enforcement actions involving individuals presenting dangerous or deadly weapons for screening at airports or in checked baggage where the amount of the proposed civil penalty is less than $5,000. In these cases, sections 13.16(a), 13.16(c), and 13.16 (f) through (l) of this chapter are used, as well as paragraphs (a) through (d) of this section: (a) <E T="03">Delegation of authority.</E> The authority of the Administrator, under 49 U.S.C. 46301, to initiate the assessment of civil penalties for a violation of 49 U.S.C. Subtitle VII, or a rule, regulation, or order issued thereunder, is delegated to the regional Civil Aviation Security Division Manager and the regional Civil Aviation Security Deputy Division Manager for the purpose of issuing notices of violation in cases involving violations of 49 U.S.C. Subtitle VII and the FAA's regulations by individuals presenting dangerous or deadly weapons for screening at airport checkpoints or in checked baggage. This authority may not be delegated below the level of the regional Civil Aviation Security Deputy Division Manager. (b) <E T="03">Notice of violation.</E> A civil penalty action is initiated by sending a notice of violation to the person charged with the violation. The notice of violation contains a statement of the charges and the amount of the proposed civil penalty. Not later than 30 days after receipt of the notice of violation, the person charged with a violation shall: (1) Submit the amount of the proposed civil penalty or an agreed-upon amount, in which case either an order assessing a civil penalty or a compromise order shall be issued in that amount; or (2) Submit to the agency attorney identified in the material accompanying the notice any of the following: (i) Written information, including documents and witness statements, demonstrating that a violation of the regulations did not occur or that a penalty or the penalty amount is not warranted by the circumstances; or (ii) A written request to reduce the proposed civil penalty, the amount of reduction, and the reasons and any documents supporting a reduction of the proposed civil penalty, including records indicating a financial inability to pay or records showing that payment of the proposed civil penalty would prevent the person from continuing in business; or<PRTPAGE P="45"/> (iii) A written request for an informal conference to discuss the matter with an agency attorney and submit relevant information or documents; or (3) Request a hearing in which case a complaint shall be filed with the hearing docket clerk. (c) <E T="03">Final notice of violation and civil penalty assessment order.</E> A final notice of violation and civil penalty assessment order (“final notice and order”) may be issued after participation in any informal proceedings as provided in paragraph (b)(2) of this section, or after failure of the respondent to respond in a timely manner to a notice of violation. A final notice and order will be sent to the individual charged with a violation. The final notice and order will contain a statement of the charges and the amount of the proposed civil penalty and, as a result of information submitted to the agency attorney during any informal procedures, may reflect a modified allegation or proposed civil penalty. A final notice and order may be issued— (1) If the person charged with a violation fails to respond to the notice of violation within 30 days after receipt of that notice; or (2) If the parties participated in any informal procedures under paragraph (b)(2) of this section and the parties have not agreed to compromise the action or the agency attorney has not agreed to withdraw the notice of violation. (d) <E T="03">Order assessing civil penalty.</E> An order assessing civil penalty may be issued after notice and opportunity for a hearing. A person charged with a violation may be subject to an order assessing civil penalty in the following circumstances: (1) An order assessing civil penalty may be issued if a person charged with a violation submits, or agrees to submit, the amount of civil penalty proposed in the notice of violation. (2) An order assessing civil penalty may be issued if a person charged with a violation submits, or agrees to submit, an agreed-upon amount of civil penalty that is not reflected in either the notice of violation or the final notice and order. (3) The final notice and order becomes (and contains a statement so indicating) an order assessing a civil penalty when the person charged with a violation submits the amount of the proposed civil penalty that is reflected in the final notice and order. (4) The final notice and order becomes (and contains a statement so indicating) an order assessing a civil penalty 16 days after receipt of the final notice and order, <E T="03">unless</E> not later than 15 days after receipt of the final notice and order, the person charged with a violation does one of the following— (i) Submits an agreed-upon amount of civil penalty that is not reflected in the final notice and order, in which case an order assessing civil penalty or a compromise order shall be issued in that amount; or (ii) Requests a hearing in which case a complaint shall be filed with the hearing docket clerk. (5) Unless an appeal is filed with the FAA decisionmaker in a timely manner, an initial decision or order of an administrative law judge shall be considered an order assessing civil penalty if an administrative law judge finds that an alleged violation occurred and determines that a civil penalty, in an amount found to be appropriate by the administrative law judge, is warranted. (6) Unless a petition for review is filed with a U.S. Court of Appeals in a timely manner, a final decision and order of the Administrator shall be considered an order assessing civil penalty if the FAA decisionmaker finds that an alleged violation occurred and a civil penalty is warranted. <CITA>[Doc. No. 27873, 61 FR 44155, Aug. 28, 1996]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Rules of Practice for FAA Hearings</HD> <SECTION> <SECTNO>§ 13.31</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart applies to proceedings in which a hearing has been requested in accordance with §§ 13.19(c)(5), 13.20(c), 13.20(d), 13.75(a)(2), 13.75(b), or 13.81(e). <CITA>[Amdt. 13-18, 53 FR 34655, Sept. 7, 1988]</CITA> </SECTION> <SECTION> <PRTPAGE P="46"/> <SECTNO>§ 13.33</SECTNO> <SUBJECT>Appearances.</SUBJECT> Any party to a proceeding under this subpart may appear and be heard in person or by attorney. </SECTION> <SECTION> <SECTNO>§ 13.35</SECTNO> <SUBJECT>Request for hearing.</SUBJECT> (a) A request for hearing must be made in writing to the Hearing Docket, Room 924A, Federal Aviation Administration, 800 Independence Avenue, S.W., Washington, D.C. 20591. It must describe briefly the action proposed by the FAA, and must contain a statement that a hearing is requested. A copy of the request for hearing and a copy of the answer required by paragraph (b) of this section must be served on the official who issued the notice of proposed action. (b) An answer to the notice of proposed action must be filed with the request for hearing. All allegations in the notice not specifically denied in the answer are deemed admitted. (c) Within 15 days after service of the copy of the request for hearing, the official who issued the notice of proposed action forwards a copy of that notice, which serves as the complaint, to the Hearing Docket. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.37</SECTNO> <SUBJECT>Hearing Officer's powers.</SUBJECT> Any Hearing Officer may— (a) Give notice concerning, and hold, prehearing conferences and hearings; (b) Administrator oaths and affirmations; (c) Examine witnesses; (d) Adopt procedures for the submission of evidence in written form; (e) Issue subpoenas and take depositions or cause them to be taken; (f) Rule on offers of proof; (g) Receive evidence; (h) Regulate the course of the hearing; (i) Hold conferences, before and during the hearing, to settle and simplify issues by consent of the parties; (j) Dispose of procedural requests and similar matters; and (k) Issue decisions, make findings of fact, make assessments, and issue orders, as appropriate. </SECTION> <SECTION> <SECTNO>§ 13.39</SECTNO> <SUBJECT>Disqualification of Hearing Officer.</SUBJECT> If disqualified for any reason, the Hearing Officer shall withdraw from the case. </SECTION> <SECTION> <SECTNO>§ 13.41</SECTNO> <RESERVED>[Reserved]</RESERVED> </SECTION> <SECTION> <SECTNO>§ 13.43</SECTNO> <SUBJECT>Service and filing of pleadings, motions, and documents.</SUBJECT> (a) Copies of all pleadings, motions, and documents filed with the Hearing Docket must be served upon all parties to the proceedings by the person filing them. (b) Service may be made by personal delivery or by mail. (c) A certificate of service shall accompany all documents when they are tendered for filing and shall consist of a certificate of personal delivery or a certificate of mailing, executed by the person making the personal delivery or mailing the document. (d) Whenever proof of service by mail is made, the date of mailing or the date as shown on the postmark shall be the date of service, and where personal service is made, the date of personal delivery shall be the date of service. (e) The date of filing is the date the document is actually received. </SECTION> <SECTION> <SECTNO>§ 13.44</SECTNO> <SUBJECT>Computation of time and extension of time.</SUBJECT> (a) In computing any period of time prescribed or allowed by this subpart, the date of the act, event, default, notice or order after which the designated period of time begins to run is not to be included in the computation. The last day of the period so computed is to be included unless it is a Saturday, Sunday, or legal holiday for the FAA, in which event the period runs until the end of the next day which is neither a Saturday, Sunday nor a legal holiday. (b) Upon written request filed with the Hearing Docket and served upon all parties, and for good cause shown, a Hearing Officer may grant an extension of time to file any documents specified in this subpart. </SECTION> <SECTION> <SECTNO>§ 13.45</SECTNO> <SUBJECT>Amendment of notice and answer.</SUBJECT> At any time more than 10 days before the date of hearing, any party may <PRTPAGE P="47"/>amend his or her notice, answer, or other pleading, by filing the amendment with the Hearing Officer and serving a copy of it on each other party. After that time, amendments may be allowed only in the discretion of the Hearing Officer. If an amendment to an initial pleading has been allowed, the Hearing Officer shall allow the other parties a reasonable opportunity to answer. </SECTION> <SECTION> <SECTNO>§ 13.47</SECTNO> <SUBJECT>Withdrawal of notice or request for hearing.</SUBJECT> At any time before the hearing, the FAA counsel may withdraw the notice of proposed action, and the party requesting the hearing may withdraw the request for hearing. </SECTION> <SECTION> <SECTNO>§ 13.49</SECTNO> <SUBJECT>Motions.</SUBJECT> (a) <E T="03">Motion to dismiss for insufficiency.</E> A respondent who requests a formal hearing may, in place of an answer, file a motion to dismiss for failure of the allegations in the notice of proposed action to state a violation of the FA Act or of this chapter or to show lack of qualification of the respondent. If the Hearing Officer denies the motion, the respondent shall file an answer within 10 days. (b) [Reserved] (c) <E T="03">Motion for more definite statement.</E> The certificate holder may, in place of an answer, file a motion that the allegations in the notice be made more definite and certain. If the Hearing Officer grants the motion, the FAA counsel shall comply within 10 days after the date it is granted. If the Hearing Officer denies the motion the certificate holder shall file an answer within 10 days after the date it is denied. (d) <E T="03">Motion for judgment on the pleadings.</E> After the pleadings are closed, either party may move for a judgment on the pleadings. (e) <E T="03">Motion to strike.</E> Upon motion of either party, the Hearing Officer may order stricken, from any pleadings, any insufficient allegation or defense, or any immaterial, impertinent, or scandalous matter. (f) <E T="03">Motion for production of documents.</E> Upon motion of any party showing good cause, the Hearing Officer may, in the manner provided by Rule 34, Federal Rules of Civil Procedure, order any party to produce any designated document, paper, book, account, letter, photograph, object, or other tangible thing, that is not privileged, that constitutes or contains evidence relevant to the subject matter of the hearings, and that is in the party's possession, custody, or control. (g) <E T="03">Consolidation of motions.</E> A party who makes a motion under this section shall join with it all other motions that are then available to the party. Any objection that is not so raised is considered to be waived. (h) <E T="03">Answers to motions.</E> Any party may file an answer to any motion under this section within 5 days after service of the motion. </SECTION> <SECTION> <SECTNO>§ 13.51</SECTNO> <SUBJECT>Intervention.</SUBJECT> Any person may move for leave to intervene in a proceeding and may become a party thereto, if the Hearing Officer, after the case is sent to the Hearing Officer for hearing, finds that the person may be bound by the order to be issued in the proceedings or has a property or financial interest that may not be adequately represented by existing parties, and that the intervention will not unduly broaden the issues or delay the proceedings. Except for good cause shown, a motion for leave to intervene may not be considered if it is filed less than 10 days before the hearing. </SECTION> <SECTION> <SECTNO>§ 13.53</SECTNO> <SUBJECT>Depositions.</SUBJECT> After the respondent has filed a request for hearing and an answer, either party may take testimony by deposition in accordance with section 1004 of the Federal Aviation Act of 1958 (49 U.S.C. 1484) or Rule 26, Federal Rules of Civil Procedure. </SECTION> <SECTION> <SECTNO>§ 13.55</SECTNO> <SUBJECT>Notice of hearing.</SUBJECT> The Hearing Officer shall set a reasonable date, time, and place for the hearing, and shall give the parties adequate notice thereof and of the nature of the hearing. Due regard shall be given to the convenience of the parties with respect to the place of the hearing. </SECTION> <SECTION> <SECTNO>§ 13.57</SECTNO> <SUBJECT>Subpoenas and witness fees.</SUBJECT> (a) The Hearing Officer to whom a case is assigned may, upon application <PRTPAGE P="48"/>by any party to the proceeding, issue subpoenas requiring the attendance of witnesses or the production of documentary or tangible evidence at a hearing or for the purpose of taking depositions. However, the application for producing evidence must show its general relevance and reasonable scope. This paragraph does not apply to the attendance of FAA employees or to the production of documentary evidence in the custody of such an employee at a hearing. (b) A person who applies for the production of a document in the custody of an FAA employee must follow the procedure in § 13.49(f). A person who applies for the attendance of an FAA employee must send the application, in writing, to the Hearing Officer setting forth the need for that employee's attendance. (c) A witness in a proceeding under this subpart is entitled to the same fees and mileage as is paid to a witness in a court of the United States under comparable circumstances. The party at whose instance the witness is subpoenaed or appears shall pay the witness fees. (d) Notwithstanding the provisions of paragraph (c) of this section, the FAA pays the witness fees and mileage if the Hearing Officer who issued the subpoena determines, on the basis of a written request and good cause shown, that— (1) The presence of the witness will materially advance the proceeding; and (2) The party at whose instance the witness is subpoenaed would suffer a serious hardship if required to pay the witness fees and mileage. </SECTION> <SECTION> <SECTNO>§ 13.59</SECTNO> <SUBJECT>Evidence.</SUBJECT> (a) Each party to a hearing may present the party's case or defense by oral or documentary evidence, submit evidence in rebuttal, and conduct such cross-examination as may be needed for a full disclosure of the facts. (b) Except with respect to affirmative defenses and orders of denial, the burden of proof is upon the FAA counsel. (c) The Hearing Officer may order information contained in any report or document filed or in any testimony given pursuant to this subpart withheld from public disclosure when, in the judgment of the Hearing Officer, disclosure would adversely affect the interests of any person and is not required in the public interest or is not otherwise required by statute to be made available to the public. Any person may make written objection to the public disclosure of such information, stating the ground for such objection. </SECTION> <SECTION> <SECTNO>§ 13.61</SECTNO> <SUBJECT>Argument and submittals.</SUBJECT> The Hearing Officer shall give the parties adequate opportunity to present arguments in support of motions, objections, and the final order. The Hearing Officer may determine whether arguments are to be oral or written. At the end of the hearing the Hearing Officer may, in the discretion of the Hearing Officer, allow each party to submit written proposed findings and conclusions and supporting reasons for them. </SECTION> <SECTION> <SECTNO>§ 13.63</SECTNO> <SUBJECT>Record.</SUBJECT> The testimony and exhibits presented at a hearing, together with all papers, requests, and rulings filed in the proceedings are the exclusive basis for the issuance of an order. Either party may obtain a transcript from the official reporter upon payment of the fees fixed therefor. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Orders of Compliance Under the Hazardous Materials Transportation Act</HD> <SECTION> <SECTNO>§ 13.71</SECTNO> <SUBJECT>Applicability.</SUBJECT> Whenever the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, or a Regional Counsel has reason to believe that a person is engaging in the transportation or shipment by air of hazardous materials in violation of the Hazardous Materials Transportation Act, or any regulation or order issued under it for which the FAA exercises enforcement responsibility, and the circumstances do not require the issuance of an order of immediate compliance, he may conduct proceedings pursuant to section 109 of that Act (49 U.S.C. 1808) to determine the nature and extent of the violation, and may <PRTPAGE P="49"/>thereafter issue an order directing compliance. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.73</SECTNO> <SUBJECT>Notice of proposed order of compliance.</SUBJECT> A compliance order proceeding commences when the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, or a Regional Counsel sends the alleged violator a notice of proposed order of compliance advising the alleged violator of the charges and setting forth the remedial action sought in the form of a proposed order of compliance. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.75</SECTNO> <SUBJECT>Reply or request for hearing.</SUBJECT> (a) Within 30 days after service upon the alleged violator of a notice of proposed order of compliance, the alleged violator may— (1) File a reply in writing with the official who issued the notice; or (2) Request a hearing in accordance with Subpart D of this part. (b) If a reply is filed, as to any charges not dismissed or not subject to a consent order of compliance, the alleged violator may, within 10 days after receipt of notice that the remaining charges are not dismissed, request a hearing in accordance with Subpart D of this part. (c) Failure of the alleged violator to file a reply or request a hearing within the period provided in paragraph (a) or (b) of this section— (1) Constitutes a waiver of the right to a hearing and the right to an appeal, and (2) Authorizes the official who issued the notice to find the facts to be as alleged in the notice and to issue an appropriate order directing compliance, without further notice or proceedings. </SECTION> <SECTION> <SECTNO>§ 13.77</SECTNO> <SUBJECT>Consent order of compliance.</SUBJECT> (a) At any time before the issuance of an order of compliance, the official who issued the notice and the alleged violator may agree to dispose of the case by the issuance of a consent order of compliance by the official. (b) A proposal for a consent order submitted to the official who issued the notice under this section must include— (1) A proposed order of compliance; (2) An admission of all jurisdictional facts; (3) An express waiver of right to further procedural steps and of all rights to judicial review; (4) An incorporation by reference of the notice and an acknowledgement that the notice may be used to construe the terms of the order of compliance; and (5) If the issuance of a consent order has been agreed upon after the filing of a request for hearing in accordance with Subpart D of this part, the proposal for a consent order shall include a request to be filed with the Hearing Officer withdrawing the request for a hearing and requesting that the case be dismissed. </SECTION> <SECTION> <SECTNO>§ 13.79</SECTNO> <SUBJECT>Hearing.</SUBJECT> If an alleged violator requests a hearing in accordance with § 13.75, the procedure of Subpart D of this part applies. At the close of the hearing, the Hearing Officer, on the record or subsequently in writing, sets forth the Hearing Officer's findings and conclusion and the reasons therefor, and either— (a) Dismisses the notice of proposed order of compliance; or (b) Issues an order of compliance. </SECTION> <SECTION> <SECTNO>§ 13.81</SECTNO> <SUBJECT>Order of immediate compliance.</SUBJECT> (a) Notwithstanding §§ 13.73 through 13.79, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, or a Regional Counsel may issue an order of immediate compliance, which is effective upon issuance, if the person who issues the order finds that— (1) There is strong probability that a violation is occurring or is about to occur; (2) The violation poses a substantial risk to health or to safety of life or property; and<PRTPAGE P="50"/> (3) The public interest requires the avoidance or amelioration of that risk through immediate compliance and waiver of the procedures afforded under §§ 13.73 through 13.79. (b) An order of immediate compliance is served promptly upon the person against whom the order is issued by telephone or telegram, and a written statement of the relevant facts and the legal basis for the order, including the findings required by paragraph (a) of this section, is served promptly by personal service or by mail. (c) The official who issued the order of immediate compliance may rescind or suspend the order if it appears that the criteria set forth in paragraph (a) of this section are no longer satisfied, and, when appropriate, may issue a notice of proposed order of compliance under § 13.73 in lieu thereof. (d) If at any time in the course of a proceeding commenced in accordance with § 13.73 the criteria set forth in paragraph (a) of this section are satisfied, the official who issued the notice may issue an order of immediate compliance, even if the period for filing a reply or requesting a hearing specified in § 13.75 has not expired. (e) Within three days after receipt of service of an order of immediate compliance, the alleged violator may request a hearing in accordance with Subpart D of this part and the procedure in that subpart will apply except that— (1) The case will be heard within fifteen days after the date of the order of immediate compliance unless the alleged violator requests a later date; (2) The order will serve as the complaint; and (3) The Hearing Officer shall issue his decision and order dismissing, reversing, modifying, or affirming the order of immediate compliance on the record at the close of the hearing. (f) The filing of a request for hearing in accordance with paragraph (e) of this section does not stay the effectiveness of an order of immediate compliance. (g) At any time after an order of immediate compliance has become effective, the official who issued the order may request the United States Attorney General, or the delegate of the Attorney General, to bring an action for appropriate relief in accordance with § 13.25. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.83</SECTNO> <SUBJECT>Appeal.</SUBJECT> (a) Any party to the hearing may appeal from the order of the Hearing Officer by filing a notice of appeal with the Administrator within 20 days after the date of issuance of the order. (b) Any person against whom an order of immediate compliance has been issued in accordance with § 13.81 or the official who issued the order of immediate compliance may appeal from the order of the Hearing Officer by filing a notice of appeal with the Administrator within three days after the date of issuance of the order by the Hearing Officer. (c) Unless the Administrator expressly so provides, the filing of a notice of appeal does not stay the effectiveness of an order of immediate compliance. (d) If a notice of appeal is not filed from the order of compliance issued by a Hearing Officer, such order is the final agency order of compliance. (e) Any person filing an appeal authorized by paragraph (a) of this section shall file an appeal brief with the Administrator within 40 days after the date of the issuance of the order, and serve a copy on the other party. Any reply brief must be filed within 20 days after service of the appeal brief. A copy of the reply brief must be served on the appellant. (f) Any person filing an appeal authorized by paragraph (b) of this section shall file an appeal brief with the Administrator with the notice of appeal and serve a copy on the other party. Any reply brief must be filed within 3 days after receipt of the appeal brief. A copy of the reply brief must be served on the appellant. (g) On appeal the Administrator reviews the available record of the proceeding, and issues an order dismissing, reversing, modifying or affirming the <PRTPAGE P="51"/>order of compliance or the order of immediate compliance. The Administrator's order includes the reasons for the action. (h) In cases involving an order of immediate compliance, the Administrator's order on appeal is issued within ten days after the filing of the notice of appeal. </SECTION> <SECTION> <SECTNO>§ 13.85</SECTNO> <SUBJECT>Filing, service and computation of time.</SUBJECT> Filing and service of documents under this subpart shall be accomplished in accordance with § 13.43 except service of orders of immediate compliance under § 13.81(b); and the periods of time specified in this subpart shall be computed in accordance with § 13.44. </SECTION> <SECTION> <SECTNO>§ 13.87</SECTNO> <SUBJECT>Extension of time.</SUBJECT> (a) The official who issued the notice of proposed order of compliance, for good cause shown, may grant an extension of time to file any document specified in this subpart, except documents to be filed with the Administrator. (b) Extensions of time to file documents with the Administrator may be granted by the Administrator upon written request, served upon all parties, and for good cause shown. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Formal Fact-Finding Investigation Under an Order of Investigation</HD> <SECTION> <SECTNO>§ 13.101</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart applies to fact-finding investigations in which an order of investigation has been issued under § 13.3(c) or § 13.5(i) of this part. (b) This subpart does not limit the authority of duly designated persons to issue subpoenas, administer oaths, examine witnesses and receive evidence in any informal investigation as provided for in sections 313 and 1004(a) of the Federal Aviation Act (49 U.S.C. 1354 and 1484(a)) and section 109(a) of the Hazardous Materials Transportation Act (49 U.S.C. 1808(a)). </SECTION> <SECTION> <SECTNO>§ 13.103</SECTNO> <SUBJECT>Order of investigation.</SUBJECT> The order of investigation— (a) Defines the scope of the investigation by describing the information sought in terms of its subject matter or its relevancy to specified FAA functions; (b) Sets forth the form of the investigation which may be either by individual deposition or investigative proceeding or both; and (c) Names the official who is authorized to conduct the investigation and serve as the Presiding Officer. </SECTION> <SECTION> <SECTNO>§ 13.105</SECTNO> <SUBJECT>Notification.</SUBJECT> Any person under investigation and any person required to testify and produce documentary or physical evidence during the investigation will be advised of the purpose of the investigation, and of the place where the investigative proceeding or deposition will be convened. This may be accomplished by a notice of investigation or by a subpoena. A copy of the order of investigation may be sent to such persons, when appropriate. </SECTION> <SECTION> <SECTNO>§ 13.107</SECTNO> <SUBJECT>Designation of additional parties.</SUBJECT> (a) The Presiding Officer may designate additional persons as parties to the investigation, if in the discretion of the Presiding Officer, it will aid in the conduct of the investigation. (b) The Presiding Officer may designate any person as a party to the investigation if that person— (1) Petitions the Presiding Officer to participate as a party; and (2) Is so situated that the disposition of the investigation may as a practical matter impair the ability to protect that person's interest unless allowed to participate as a party, and (3) Is not adequately represented by existing parties. </SECTION> <SECTION> <SECTNO>§ 13.109</SECTNO> <SUBJECT>Convening the investigation.</SUBJECT> The investigation shall be conducted at such place or places designated by the Presiding Officer, and as convenient to the parties involved as expeditious and efficient handling of the investigation permits. </SECTION> <SECTION> <SECTNO>§ 13.111</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> (a) Upon motion of the Presiding Officer, or upon the request of a party to the investigation, the Presiding Officer may issue a subpoena directing any person to appear at a designated time <PRTPAGE P="52"/>and place to testify or to produce documentary or physical evidence relating to any matter under investigation. (b) Subpoenas shall be served by personal service, or upon an agent designated in writing for the purpose, or by registered or certified mail addressed to such person or agent. Whenever service is made by registered or certified mail, the date of mailing shall be considered as the time when service is made. (c) Subpoenas shall extend in jurisdiction throughout the United States or any territory or possession thereof. </SECTION> <SECTION> <SECTNO>§ 13.113</SECTNO> <SUBJECT>Noncompliance with the investigative process.</SUBJECT> If any person fails to comply with the provisions of this subpart or with any subpoena or order issued by the Presiding Officer or the designee of the Presiding Officer, judicial enforcement may be initiated against that person under applicable statutes. </SECTION> <SECTION> <SECTNO>§ 13.115</SECTNO> <SUBJECT>Public proceedings.</SUBJECT> (a) All investigative proceedings and depositions shall be public unless the Presiding Officer determines that the public interest requires otherwise. (b) The Presiding Officer may order information contained in any report or document filed or in any testimony given pursuant to this subpart withheld from public disclosure when, in the judgment of the Presiding Officer, disclosure would adversely affect the interests of any person and is not required in the public interest or is not otherwise required by statute to be made available to the public. Any person may make written objection to the public disclosure of such information, stating the grounds for such objection. </SECTION> <SECTION> <SECTNO>§ 13.117</SECTNO> <SUBJECT>Conduct of investigative proceeding or deposition.</SUBJECT> (a) The Presiding Officer or the designee of the Presiding Officer may question witnesses. (b) Any witness may be accompanied by counsel. (c) Any party may be accompanied by counsel and either the party or counsel may— (1) Question witnesses, provided the questions are relevant and material to the matters under investigation and would not unduly impede the progress of the investigation; and (2) Make objections on the record and argue the basis for such objections. (d) Copies of all notices or written communications sent to a party or witness shall upon request be sent to that person's attorney of record. </SECTION> <SECTION> <SECTNO>§ 13.119</SECTNO> <SUBJECT>Rights of persons against self-incrimination.</SUBJECT> (a) Whenever a person refuses, on the basis of a privilege against self-incrimination, to testify or provide other information during the course of any investigation conducted under this subpart, the Presiding Officer may, with the approval of the Attorney General of the United States, issue an order requiring the person to give testimony or provide other information. However, no testimony or other information so compelled (or any information directly or indirectly derived from such testimony or other information) may be used against the person in any criminal case, except in a prosecution for perjury, giving a false statement, or otherwise failing to comply with the order. (b) The Presiding Officer may issue an order under this section if— (1) The testimony or other information from the witness may be necessary to the public interest; and (2) The witness has refused or is likely to refuse to testify or provide other information on the basis of a privilege against self-incrimination. (c) Immunity provided by this section will not become effective until the person has refused to testify or provide other information on the basis of a privilege against self-incrimination, and an order under this section has been issued. An order, however, may be issued prospectively to become effective in the event of a claim of the privilege. </SECTION> <SECTION> <SECTNO>§ 13.121</SECTNO> <SUBJECT>Witness fees.</SUBJECT> All witnesses appearing shall be compensated at the same rate as a witness appearing before a United States District Court. </SECTION> <SECTION> <PRTPAGE P="53"/> <SECTNO>§ 13.123</SECTNO> <SUBJECT>Submission by party to the investigation.</SUBJECT> (a) During an investigation conducted under this subpart, a party may submit to the Presiding Officer— (1) A list of witnesses to be called, specifying the subject matter of the expected testimony of each witness, and (2) A list of exhibits to be considered for inclusion in the record. (b) If the Presiding Officer determines that the testimony of a witness or the receipt of an exhibit in accordance with paragraph (a) of this section will be relevant, competent and material to the investigation, the Presiding Officer may subpoena the witness or use the exhibit during the investigation. </SECTION> <SECTION> <SECTNO>§ 13.125</SECTNO> <SUBJECT>Depositions.</SUBJECT> Depositions for investigative purposes may be taken at the discretion of the Presiding Officer with reasonable notice to the party under investigation. Such depositions shall be taken before the Presiding Officer or other person authorized to administer oaths and designated by the Presiding Officer. The testimony shall be reduced to writing by the person taking the deposition, or under the direction of that person, and where possible shall then be subscribed by the deponent. Any person may be compelled to appear and testify and to produce physical and documentary evidence. </SECTION> <SECTION> <SECTNO>§ 13.127</SECTNO> <SUBJECT>Reports, decisions and orders.</SUBJECT> The Presiding Officer shall issue a written report based on the record developed during the formal investigation, including a summary of principal conclusions. A summary of principal conclusions shall be prepared by the official who issued the order of investigation in every case which results in no action, or no action as to a particular party to the investigation. All such reports shall be furnished to the parties to the investigation and filed in the public docket. Insertion of the report in the Public Docket shall constitute “entering of record” and publication as prescribed by section 313(b) of the Federal Aviation Act. </SECTION> <SECTION> <SECTNO>§ 13.129</SECTNO> <SUBJECT>Post-investigation action.</SUBJECT> A decision on whether to initiate subsequent action shall be made on the basis of the record developed during the formal investigation and any other information in the possession of the Administrator. </SECTION> <SECTION> <SECTNO>§ 13.131</SECTNO> <SUBJECT>Other procedures.</SUBJECT> Any question concerning the scope or conduct of a formal investigation not covered in this subpart may be ruled on by the Presiding Officer on motion of the Presiding Officer, or on the motion of a party or a person testifying or producing evidence. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Rules of Practice in FAA Civil Penalty Actions</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 13-21, 55 FR 27575, July 3, 1990, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 13.201</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart applies to the following actions: (1) A civil penalty action in which a complaint has been issued for an amount not exceeding $50,000 for a violation arising under the Federal Aviation Act of 1958, as amended (49 U.S.C. 1301, <E T="03">et seq</E>.), or a rule, regulation, or order issued thereunder. (2) A civil penalty action in which a complaint has been issued for a violation arising under the Federal Aviation Act of 1958, as amended (49 U.S.C. 1471, <E T="03">et seq</E>.) and the Hazardous Materials Transportation Act (49 U.S.C. 1801 <E T="03">et seq</E>.), or a rule, regulation, or order issued thereunder. (b) This subpart applies only to proceedings initiated after September 7, 1988. All other cases, hearings, or other proceedings pending or in progress before September 7, 1988, are not affected by the rules in this subpart. (c) Notwithstanding the provisions of paragraph (a) of this section, the United States district courts shall have exclusive jurisdiction of any civil penalty action initiated by the Administrator: (1) Which involves an amount in controversy in excess of $50,000; (2) Which is an <E T="03">in rem</E> action or in which an <E T="03">in rem</E> action based on the same violation has been brought;<PRTPAGE P="54"/> (3) Regarding which an aircraft subject to lien has been seized by the United States; and (4) In which a suit for injunctive relief based on the violation giving rise to the civil penalty has also been brought. </SECTION> <SECTION> <SECTNO>§ 13.202</SECTNO> <SUBJECT>Definitions.</SUBJECT> <E T="03">Administrative law judge</E> means an administrative law judge appointed pursuant to the provisions of 5 U.S.C. 3105. <E T="03">Agency attorney</E> means the Deputy Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, the Aeronautical Center Counsel, or the Technical Center Counsel, or an attorney on the staff of the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, the Aeronautical Center Counsel, or the Technical Center Counsel who prosecutes a civil penalty action. An agency attorney shall not include: (1) The Chief Counsel, the Assistant Chief Counsel for Litigation, or the Special Counsel and Director of Civil Penalty Adjudications; or (2) Any attorney on the staff of either the Assistant Chief Counsel for Litigation or the Special Counsel and Director of Civil Penalty Adjudications who advises the FAA decisionmaker regarding an initial decision or any appeal to the FAA decisionmaker; or (3) Any attorney who is supervised in a civil penalty action by a person who provides such advice to the FAA decisionmaker in that action or a factually-related action. <E T="03">Attorney</E> means a person licensed by a state, the District of Columbia, or a territory of the United States to practice law or appear before the courts of that state or territory. <E T="03">Complaint</E> means a document issued by an agency attorney alleging a violation of the Federal Aviation Act of 1958, as amended, or a rule, regulation, or order issued thereunder, or the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder that has been filed with the hearing docket after a hearing has been requested pursuant to § 13.16(d)(3) or § 13.16(e)(2)(ii) of this part. <E T="03">FAA decisionmaker</E> means the Administrator of the Federal Aviation Administration, acting in the capacity of the decisionmaker on appeal, or any person to whom the Administrator has delegated the Administrator's decisionmaking authority in a civil penalty action. As used in this subpart, the FAA decisionmaker is the official authorized to issue a final decision and order of the Administrator in a civil penalty action. <E T="03">Mail</E> includes U.S. certified mail, U.S. registered mail, or use of an overnight express courier service. <E T="03">Order assessing civil penalty</E> means a document that contains a finding of violation of the Federal Aviation Act of 1958, as amended, or a rule, regulation, or order issued thereunder, or the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder and may direct payment of a civil penalty. Unless an appeal is filed with the FAA decisionmaker in a timely manner, an initial decision or order of an administrative law judge shall be considered an order assessing civil penalty if an administrative law judge finds that an alleged violation occurred and determines that a civil penalty, in an amount found appropriate by the administrative law judge, is warranted. Unless a petition for review is filed with a U.S. Court of Appeals in a timely manner, a final decision and order of the Administrator shall be considered an order assessing civil penalty if the FAA decisionmaker finds that an alleged violation occurred and a civil penalty is warranted. <E T="03">Party</E> means the respondent or the Federal Aviation Administration (FAA). <E T="03">Personal delivery</E> includes hand-delivery or use of a contract or express messenger service. “Personal delivery” does not include the use of Government interoffice mail service. <E T="03">Pleading</E> means a complaint, an answer, and any amendment of these documents permitted under this subpart. <E T="03">Properly addressed</E> means a document that shows an address contained in agency records, a residential, business, or other address submitted by a person <PRTPAGE P="55"/>on any document provided under this subpart, or any other address shown by other reasonable and available means. <E T="03">Respondent</E> means a person, corporation, or company named in a complaint. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990, as amended by Amdt. 13-24, 58 FR 50241, Sept. 24, 1993; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.203</SECTNO> <SUBJECT>Separation of functions.</SUBJECT> (a) Civil penalty proceedings, including hearings, shall be prosecuted by an agency attorney. (b) An agency employee engaged in the performance of investigative or prosecutorial functions in a civil penalty action shall not, in that case or a factually-related case, participate or give advice in a decision by the administrative law judge or by the FAA decisionmaker on appeal, except as counsel or a witness in the public proceedings. (c) The Chief Counsel, the Assistant Chief Counsel for Litigation, the Special Counsel and Director of Civil Penalty Adjudications, or an attorney on the staff of either the Assistant Chief Counsel for Litigation or the Special Counsel and Director of Civil Penalty Adjudications, will advise the FAA decisionmaker regarding an initial decision or any appeal of a civil penalty action to the FAA decisionmaker. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990, as amended by Amdt. 13-24, 58 FR 50241, Sept. 24, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.204</SECTNO> <SUBJECT>Appearances and rights of parties.</SUBJECT> (a) Any party may appear and be heard in person. (b) Any party may be accompanied, represented, or advised by an attorney or representative designated by the party and may be examined by that attorney or representative in any proceeding governed by this subpart. An attorney or representative who represents a party may file a notice of appearance in the action, in the manner provided in § 13.210 of this subpart, and shall serve a copy of the notice of appearance on each party, in the manner provided in § 13.211 of this subpart, before participating in any proceeding governed by this subpart. The attorney or representative shall include the name, address, and telephone number of the attorney or representative in the notice of appearance. (c) Any person may request a copy of a document upon payment of reasonable costs. A person may keep an original document, data, or evidence, with the consent of the administrative law judge, by substituting a legible copy of the document for the record. </SECTION> <SECTION> <SECTNO>§ 13.205</SECTNO> <SUBJECT>Administrative law judges.</SUBJECT> (a) <E T="03">Powers of an administrative law judge.</E> In accordance with the rules of this subpart, an administrative law judge may: (1) Give notice of, and hold, prehearing conferences and hearings; (2) Administer oaths and affirmations; (3) Issue subpoenas authorized by law and issue notices of deposition requested by the parties; (4) Rule on offers of proof; (5) Receive relevant and material evidence; (6) Regulate the course of the hearing in accordance with the rules of this subpart; (7) Hold conferences to settle or to simplify the issues by consent of the parties; (8) Dispose of procedural motions and requests; and (9) Make findings of fact and conclusions of law, and issue an initial decision. (b) <E T="03">Limitations on the power of the administrative law judge.</E> The administrative law judge shall not issue an order of contempt, award costs to any party, or impose any sanction not specified in this subpart. If the administrative law judge imposes any sanction not specified in this subpart, a party may file an interlocutory appeal of right with the FAA decisionmaker pursuant to § 13.219(c)(4) of this subpart. This section does not preclude an administrative law judge from issuing an order that bars a person from a specific proceeding based on a finding of obstreperous or disruptive behavior in that specific proceeding. (c) <E T="03">Disqualification.</E> The administrative law judge may disqualify himself or herself at any time. A party may file a motion, pursuant to § 13.218(f)(6), requesting that an administrative law <PRTPAGE P="56"/>judge be disqualified from the proceedings. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990; 55 FR 29293, July 18, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.206</SECTNO> <SUBJECT>Intervention.</SUBJECT> (a) A person may submit a motion for leave to intervene as a party in a civil penalty action. Except for good cause shown, a motion for leave to intervene shall be submitted not later than 10 days before the hearing. (b) If the administrative law judge finds that intervention will not unduly broaden the issues or delay the proceedings, the administrative law judge may grant a motion for leave to intervene if the person will be bound by any order or decision entered in the action or the person has a property, financial, or other legitimate interest that may not be addressed adequately by the parties. The administrative law judge may determine the extent to which an intervenor may participate in the proceedings. </SECTION> <SECTION> <SECTNO>§ 13.207</SECTNO> <SUBJECT>Certification of documents.</SUBJECT> (a) <E T="03">Signature required.</E> The attorney of record, the party, or the party's representative shall sign each document tendered for filing with the hearing docket clerk, the administrative law judge, the FAA decisionmaker on appeal, or served on each party. (b) <E T="03">Effect of signing a document.</E> By signing a document, the attorney of record, the party, or the party's representative certifies that the attorney, the party, or the party's representative has read the document and, based on reasonable inquiry and to the best of that person's knowledge, information, and belief, the document is— (1) Consistent with these rules; (2) Warranted by existing law or that a good faith argument exists for extension, modification, or reversal of existing law; and (3) Not unreasonable or unduly burdensome or expensive, not made to harass any person, not made to cause unnecessary delay, not made to cause needless increase in the cost of the proceedings, or for any other improper purpose. (c) <E T="03">Sanctions</E>. If the attorney of record, the party, or the party's representative signs a document in violation of this section, the administrative law judge or the FAA decisionmaker shall: (1) Strike the pleading signed in violation of this section; (2) Strike the request for discovery or the discovery response signed in violation of this section and preclude further discovery by the party; (3) Deny the motion or request signed in violation of this section; (4) Exclude the document signed in violation of this section from the record; (5) Dismiss the interlocutory appeal and preclude further appeal on that issue by the party who filed the appeal until an initial decision has been entered on the record; or (6) Dismiss the appeal of the administrative law judge's initial decision to the FAA decisionmaker. </SECTION> <SECTION> <SECTNO>§ 13.208</SECTNO> <SUBJECT>Complaint.</SUBJECT> (a) <E T="03">Filing</E>. The agency attorney shall file the original and one copy of the complaint with the hearing docket clerk, or may file a written motion pursuant to § l3.218(f)(2)(i) of this subpart instead of filing a complaint, not later than 20 days after receipt by the agency attorney of a request for hearing. The agency attorney should suggest a location for the hearing when filing the complaint. (b) <E T="03">Service</E>. An agency attorney shall personally deliver or mail a copy of the complaint on the respondent, the president of the corporation or company named as a respondent, or a person designated by the respondent to accept service of documents in the civil penalty action. (c) <E T="03">Contents</E>. A complaint shall set forth the facts alleged, any regulation allegedly violated by the respondent, and the proposed civil penalty in sufficient detail to provide notice of any factual or legal allegation and proposed civil penalty. (d) <E T="03">Motion to dismiss allegations or complaint.</E> Instead of filing an answer to the complaint, a respondent may move to dismiss the complaint, or that part of the complaint, alleging a violation that occurred on or after August 2, 1990, and more than 2 years before an <PRTPAGE P="57"/>agency attorney issued a notice of proposed civil penalty to the respondent. (1) An administrative law judge may not grant the motion and dismiss the complaint or part of the complaint if the administrative law judge finds that the agency has shown good cause for any delay in issuing the notice of proposed civil penalty. (2) If the agency fails to show good cause for any delay, an administrative law judge may dismiss the complaint, or that part of the complaint, alleging a violation that occurred more than 2 years before an agency attorney issued the notice of proposed civil penalty to the respondent. (3) A party may appeal the administrative law judge's ruling on the motion to dismiss the complaint or any part of the complaint in accordance with § 13.219(b) of this subpart. <CITA>[Admt. 13-21, 55 FR 27575, July 3, 1990, as amended by Admt. 13-22, 55 FR 31176, Aug. 1, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.209</SECTNO> <SUBJECT>Answer.</SUBJECT> (a) <E T="03">Writing required</E>. A respondent shall file a written answer to the complaint, or may file a written motion pursuant to § 13.208(d) or § 13.218(f)(1-4) of this subpart instead of filing an answer, not later than 30 days after service of the complaint. The answer may be in the form of a letter but must be dated and signed by the person responding to the complaint. An answer may be typewritten or may be legibly handwritten. (b) <E T="03">Filing and address</E>. A person filing an answer shall personally deliver or mail the original and one copy of the answer for filing with the hearing docket clerk, not later than 30 days after service of the complaint, to the Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591, Attention: Hearing Docket Clerk. The person filing an answer should suggest a location for the hearing when filing the answer. (c) <E T="03">Service</E>. A person filing an answer shall serve a copy of the answer on the agency attorney who filed the complaint. (d) <E T="03">Contents</E>. An answer shall specifically state any affirmative defense that the respondent intends to assert at the hearing. A person filing an answer may include a brief statement of any relief requested in the answer. (e) <E T="03">Specific denial of allegations required</E>. A person filing an answer shall admit, deny, or state that the person is without sufficient knowledge or information to admit or deny, each numbered paragraph of the complaint. Any statement or allegation contained in the complaint that is not specifically denied in the answer may be deemed an admission of the truth of that allegation. A general denial of the complaint is deemed a failure to file an answer. (f) <E T="03">Failure to file answer</E>. A person's failure to file an answer without good cause shall be deemed an admission of the truth of each allegation contained in the complaint. </SECTION> <SECTION> <SECTNO>§ 13.210</SECTNO> <SUBJECT>Filing of documents.</SUBJECT> (a) <E T="03">Address and method of filing</E>. A person tendering a document for filing shall personally deliver or mail the signed original and one copy of each document to the Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591, Attention: Hearing Docket Clerk. A person shall serve a copy of each document on each party in accordance with § 13.211 of this subpart. (b) <E T="03">Date of filing.</E> A document shall be considered to be filed on the date of personal delivery; or if mailed, the mailing date shown on the certificate of service, the date shown on the postmark if there is no certificate of service, or other mailing date shown by other evidence if there is no certificate of service or postmark. (c) <E T="03">Form.</E> Each document shall be typewritten or legibly handwritten. (d) <E T="03">Contents.</E> Unless otherwise specified in this subpart, each document must contain a short, plain statement of the facts on which the person's case rests and a brief statement of the action requested in the document. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990; 55 FR 29293, July 18, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.211</SECTNO> <SUBJECT>Service of documents.</SUBJECT> (a) <E T="03">General.</E> A person shall serve a copy of any document filed with the Hearing Docket on each party at the <PRTPAGE P="58"/>time of filing. Service on a party's attorney of record or a party's designated representative may be considered adequate service on the party. (b) <E T="03">Type of service.</E> A person may serve documents by personal delivery or by mail. (c) <E T="03">Certificate of service.</E> A person may attach a certificate of service to a document tendered for filing with the hearing docket clerk. A certificate of service shall consist of a statement, dated and signed by the person filing the document, that the document was personally delivered or mailed to each party on a specific date. (d) <E T="03">Date of service.</E> The date of service shall be the date of personal delivery; or if mailed, the mailing date shown on the certificate of service, the date shown on the postmark if there is no certificate of service, or other mailing date shown by other evidence if there is no certificate of service or postmark. (e) <E T="03">Additional time after service by mail.</E> Whenever a party has a right or a duty to act or to make any response within a prescribed period after service by mail, or on a date certain after service by mail, 5 days shall be added to the prescribed period. (f) <E T="03">Service by the administrative law judge.</E> The administrative law judge shall serve a copy of each document including, but not limited to, notices of prehearing conferences and hearings, rulings on motions, decisions, and orders, upon each party to the proceedings by personal delivery or by mail. (g) <E T="03">Valid service.</E> A document that was properly addressed, was sent in accordance with this subpart, and that was returned, that was not claimed, or that was refused, is deemed to have been served in accordance with this subpart. The service shall be considered valid as of the date and the time that the document was deposited with a contract or express messenger, the document was mailed, or personal delivery of the document was refused. (h) <E T="03">Presumption of service.</E> There shall be a presumption of service where a party or a person, who customarily receives mail, or receives it in the ordinary course of business, at either the person's residence or the person's principal place of business, acknowledges receipt of the document. </SECTION> <SECTION> <SECTNO>§ 13.212</SECTNO> <SUBJECT>Computation of time.</SUBJECT> (a) This section applies to any period of time prescribed or allowed by this subpart, by notice or order of the administrative law judge, or by any applicable statute. (b) The date of an act, event, or default, after which a designated time period begins to run, is not included in a computation of time under this subpart. (c) The last day of a time period is included in a computation of time unless it is a Saturday, Sunday, or a legal holiday. If the last day of the time period is a Saturday, Sunday, or legal holiday, the time period runs until the end of the next day that is not a Saturday, Sunday, or legal holiday. </SECTION> <SECTION> <SECTNO>§ 13.213</SECTNO> <SUBJECT>Extension of time.</SUBJECT> (a) <E T="03">Oral requests.</E> The parties may agree to extend for a reasonable period the time for filing a document under this subpart. If the parties agree, the administrative law judge shall grant one extension of time to each party. The party seeking the extension of time shall submit a draft order to the administrative law judge to be signed by the administrative law judge and filed with the hearing docket clerk. The administrative law judge may grant additional oral requests for an extension of time where the parties agree to the extension. (b) <E T="03">Written motion.</E> A party shall file a written motion for an extension of time with the administrative law judge not later than 7 days before the document is due unless good cause for the late filing is shown. A party filing a written motion for an extension of time shall serve a copy of the motion on each party. The administrative law judge may grant the extension of time if good cause for the extension is shown. (c) <E T="03">Failure to rule.</E> If the administrative law judge fails to rule on a written motion for an extension of time by the date the document was due, the motion for an extension of time is deemed granted for no more than 20 days after the original date the document was to be filed. </SECTION> <SECTION> <PRTPAGE P="59"/> <SECTNO>§ 13.214</SECTNO> <SUBJECT>Amendment of pleadings.</SUBJECT> (a) <E T="03">Filing and service.</E> A party shall file the amendment with the administrative law judge and shall serve a copy of the amendment on all parties to the proceeding. (b) <E T="03">Time.</E> A party shall file an amendment to a complaint or an answer within the following: (1) Not later than 15 days before the scheduled date of a hearing, a party may amend a complaint or an answer without the consent of the administrative law judge. (2) Less than 15 days before the scheduled date of a hearing, the administrative law judge may allow amendment of a complaint or an answer only for good cause shown in a motion to amend. (c) <E T="03">Responses.</E> The administrative law judge shall allow a reasonable time, but not more than 20 days from the date of filing, for other parties to respond if an amendment to a complaint, answer, or other pleading has been filed with the administrative law judge. </SECTION> <SECTION> <SECTNO>§ 13.215</SECTNO> <SUBJECT>Withdrawal of complaint or request for hearing.</SUBJECT> At any time before or during a hearing, an agency attorney may withdraw a complaint or a party may withdraw a request for a hearing without the consent of the administrative law judge. If an agency attorney withdraws the complaint or a party withdraws the request for a hearing and the answer, the administrative law judge shall dismiss the proceedings under this subpart with prejudice. </SECTION> <SECTION> <SECTNO>§ 13.216</SECTNO> <SUBJECT>Waivers.</SUBJECT> Waivers of any rights provided by statute or regulation shall be in writing or by stipulation made at a hearing and entered into the record. The parties shall set forth the precise terms of the waiver and any conditions. </SECTION> <SECTION> <SECTNO>§ 13.217</SECTNO> <SUBJECT>Joint procedural or discovery schedule.</SUBJECT> (a) <E T="03">General.</E> The parties may agree to submit a schedule for filing all prehearing motions, a schedule for conducting discovery in the proceedings, or a schedule that will govern all prehearing motions and discovery in the proceedings. (b) <E T="03">Form and content of schedule.</E> If the parties agree to a joint procedural or discovery schedule, one of the parties shall file the joint schedule with the administrative law judge, setting forth the dates to which the parties have agreed, and shall serve a copy of the joint schedule on each party. (1) The joint schedule may include, but need not be limited to, requests for discovery, any objections to discovery requests, responses to discovery requests to which there are no objections, submission of prehearing motions, responses to prehearing motions, exchange of exhibits to be introduced at the hearing, and a list of witnesses that may be called at the hearing. (2) Each party shall sign the original joint schedule to be filed with the administrative law judge. (c) <E T="03">Time.</E> The parties may agree to submit all prehearing motions and responses and may agree to close discovery in the proceedings under the joint schedule within a reasonable time before the date of the hearing, but not later than 15 days before the hearing. (d) <E T="03">Order establishing joint schedule.</E> The administrative law judge shall approve the joint schedule filed by the parties. One party shall submit a draft order establishing a joint schedule to the administrative law judge to be signed by the administrative law judge and filed with the hearing docket clerk. (e) <E T="03">Disputes.</E> The administrative law judge shall resolve disputes regarding discovery or disputes regarding compliance with the joint schedule as soon as possible so that the parties may continue to comply with the joint schedule. (f) <E T="03">Sanctions for failure to comply with joint schedule.</E> If a party fails to comply with the administrative law judge's order establishing a joint schedule, the administrative law judge may direct that party to comply with a motion to discovery request or, limited to the extent of the party's failure to comply with a motion or discovery request, the administrative law judge may: (1) Strike that portion of a party's pleadings; (2) Preclude prehearing or discovery motions by that party;<PRTPAGE P="60"/> (3) Preclude admission of that portion of a party's evidence at the hearing, or (4) Preclude that portion of the testimony of that party's witnesses at the hearing. </SECTION> <SECTION> <SECTNO>§ 13.218</SECTNO> <SUBJECT>Motions.</SUBJECT> (a) <E T="03">General.</E> A party applying for an order or ruling not specifically provided in this subpart shall do so by motion. A party shall comply with the requirements of this section when filing a motion with the administrative law judge. A party shall serve a copy of each motion on each party. (b) <E T="03">Form and contents.</E> A party shall state the relief sought by the motion and the particular grounds supporting that relief. If a party has evidence in support of a motion, the party shall attach any supporting evidence, including affidavits, to the motion. (c) <E T="03">Filing of motions.</E> A motion made prior to the hearing must be in writing. Unless otherwise agreed by the parties or for good cause shown, a party shall file any prehearing motion, and shall serve a copy on each party, not later than 30 days before the hearing. Motions introduced during a hearing may be made orally on the record unless the administrative law judge directs otherwise. (d) <E T="03">Answers to motions.</E> Any party may file an answer, with affidavits or other evidence in support of the answer, not later than 10 days after service of a written motion on that party. When a motion is made during a hearing, the answer may be made at the hearing on the record, orally or in writing, within a reasonable time determined by the administrative law judge. (e) <E T="03">Rulings on motions.</E> The administrative law judge shall rule on all motions as follows: (1) <E T="03">Discovery motions.</E> The administrative law judge shall resolve all pending discovery motions not later than 10 days before the hearing. (2) <E T="03">Prehearing motions.</E> The administrative law judge shall resolve all pending prehearing motions not later than 7 days before the hearing. If the administrative law judge issues a ruling or order orally, the administrative law judge shall serve a written copy of the ruling or order, within 3 days, on each party. In all other cases, the administrative law judge shall issue rulings and orders in writing and shall serve a copy of the ruling or order on each party. (3) <E T="03">Motions made during the hearing.</E> The administrative law judge may issue rulings and orders on motions made during the hearing orally. Oral rulings or orders on motions must be made on the record. (f) <E T="03">Specific motions.</E> A party may file the following motions with the administrative law judge: (1) <E T="03">Motion to dismiss for insufficiency.</E> A respondent may file a motion to dismiss the complaint for insufficiency instead of filing an answer. If the administrative law judge denies the motion to dismiss the complaint for insufficiency, the respondent shall file an answer not later than 10 days after service of the administrative law judge's denial of the motion. A motion to dismiss the complaint for insufficiency must show that the complaint fails to state a violation of the Federal Aviation Act of 1958, as amended, or a rule, regulation, or order issued thereunder, or a violation of the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder. (2) <E T="03">Motion to dismiss.</E> A party may file a motion to dismiss, specifying the grounds for dismissal. If an administrative law judge grants a motion to dismiss in part, a party may appeal the administrative law judge's ruling on the motion to dismiss under § 13.219(b) of this subpart. (i) <E T="03">Motion to dismiss a request for a hearing.</E> An agency attorney may file a motion to dismiss a request for a hearing instead of filing a complaint. If the motion to dismiss is not granted, the agency attorney shall file the complaint and shall serve a copy of the complaint on each party not later than 10 days after service of the administrative law judge's ruling or order on the motion to dismiss. If the motion to dismiss is granted and the proceedings are terminated without a hearing, the respondent may file an appeal pursuant to § 13.233 of this subpart. If required by the decision on appeal, the agency attorney shall file a complaint and shall serve a copy of the complaint on each <PRTPAGE P="61"/>party not later than 10 days after service of the decision on appeal. (ii) <E T="03">Motion to dismiss a complaint.</E> A respondent may file a motion to dismiss a complaint instead of filing an answer. If the motion to dismiss is not granted, the respondent shall file an answer and shall serve a copy of the answer on each party not later than 10 days after service of the administrative law judge's ruling or order on the motion to dismiss. If the motion to dismiss is granted and the proceedings are terminated without a hearing, the agency attorney may file an appeal pursuant to § 13.233 of this subpart. If required by the decision on appeal, the respondent shall file an answer and shall serve a copy of the answer on each party not later than 10 days after service of the decision on appeal. (3) <E T="03">Motion for more definite statement.</E> A party may file a motion for more definite statement of any pleading which requires a response under this subpart. A party shall set forth, in detail, the indefinite or uncertain allegations contained in a complaint or response to any pleading and shall submit the details that the party believes would make the allegation or response definite and certain. (i) <E T="03">Complaint.</E> A respondent may file a motion requesting a more definite statement of the allegations contained in the complaint instead of filing an answer. If the administrative law judge grants the motion, the agency attorney shall supply a more definite statement not later than 15 days after service of the ruling granting the motion. If the agency attorney fails to supply a more definite statement, the administrative law judge shall strike the allegations in the complaint to which the motion is directed. If the administrative law judge denies the motion, the respondent shall file an answer and shall serve a copy of the answer on each party not later than 10 days after service of the order of denial. (ii) <E T="03">Answer.</E> An agency attorney may file a motion requesting a more definite statement if an answer fails to respond clearly to the allegations in the complaint. If the administrative law judge grants the motion, the respondent shall supply a more definite statement not later than 15 days after service of the ruling on the motion. If the respondent fails to supply a more definite statement, the administrative law judge shall strike those statements in the answer to which the motion is directed. The respondent's failure to supply a more definite statement may be deemed an admission of unanswered allegations in the complaint. (4) <E T="03">Motion to strike.</E> Any party may make a motion to strike any insufficient allegation or defense, or any redundant, immaterial, or irrelevant matter in a pleading. A party shall file a motion to strike with the administrative law judge and shall serve a copy on each party before a response is required under this subpart or, if a response is not required, not later than 10 days after service of the pleading. (5) <E T="03">Motion for decision.</E> A party may make a motion for decision, regarding all or any part of the proceedings, at any time before the administrative law judge has issued an initial decision in the proceedings. The administrative law judge shall grant a party's motion for decision if the pleadings, depositions, answers to interrogatories, admissions, matters that the administrative law judge has officially noticed, or evidence introduced during the hearing show that there is no genuine issue of material fact and that the party making the motion is entitled to a decision as a matter of law. The party making the motion for decision has the burden of showing that there is no genuine issue of material fact disputed by the parties. (6) <E T="03">Motion for disqualification.</E> A party may file a motion for disqualification with the administrative law judge and shall serve a copy on each party. A party may file the motion at any time after the administrative law judge has been assigned to the proceedings but shall make the motion before the administrative law judge files an initial decision in the proceedings. (i) <E T="03">Motion and supporting affidavit.</E> A party shall state the grounds for disqualification, including, but not limited to, personal bias, pecuniary interest, or other factors showing disqualification, in the motion for disqualification. A party shall submit an affidavit with the motion for disqualification that sets forth, in detail, the matters <PRTPAGE P="62"/>alleged to constitute grounds for disqualification. (ii) <E T="03">Answer.</E> A party shall respond to the motion for disqualification not later than 5 days after service of the motion for disqualification. (iii) <E T="03">Decision on motion for disqualification.</E> The administrative law judge shall render a decision on the motion for disqualification not later than 15 days after the motion has been filed. If the administrative law judge finds that the motion for disqualification and supporting affidavit show a basis for disqualification, the administrative law judge shall withdraw from the proceedings immediately. If the administrative law judge finds that disqualification is not warranted, the administrative law judge shall deny the motion and state the grounds for the denial on the record. If the administrative law judge fails to rule on a party's motion for disqualification within 15 days after the motion has been filed, the motion is deemed granted. (iv) <E T="03">Appeal.</E> A party may appeal the administrative law judge's denial of the motion for disqualification in accordance with § 13.219(b) of this subpart. </SECTION> <SECTION> <SECTNO>§ 13.219</SECTNO> <SUBJECT>Interlocutory appeals.</SUBJECT> (a) <E T="03">General.</E> Unless otherwise provided in this subpart, a party may not appeal a ruling or decision of the administrative law judge to the FAA decisionmaker until the initial decision has been entered on the record. A decision or order of the FAA decisionmaker on the interlocutory appeal does not constitute a final order of the Administrator for the purposes of judicial appellate review under section 1006 of the Federal Aviation Act of 1958, as amended. (b) <E T="03">Interlocutory appeal for cause.</E> If a party files a written request for an interlocutory appeal for cause with the administrative law judge, or orally requests an interlocutory appeal for cause, the proceedings are stayed until the administrative law judge issues a decision on the request. If the administrative law judge grants the request, the proceedings are stayed until the FAA decisionmaker issues a decision on the interlocutory appeal. The administrative law judge shall grant an interlocutory appeal for cause if a party shows that delay of the appeal would be detrimental to the public interest or would result in undue prejudice to any party. (c) <E T="03">Interlocutory appeals of right.</E> If a party notifies the administrative law judge of an interlocutory appeal of right, the proceedings are stayed until the FAA decisionmaker issues a decision on the interlocutory appeal. A party may file an interlocutory appeal with the FAA decisionmaker, without the consent of the administrative law judge, before an initial decision has been entered in the case of: (1) A ruling or order by the administrative law judge barring a person from the proceedings. (2) Failure of the administrative law judge to dismiss the proceedings in accordance with § 13.215 of this subpart. (3) A ruling or order by the administrative law judge in violation of § 13.205(b) of this subpart. (d) <E T="03">Procedure.</E> A party shall file a notice of interlocutory appeal, with supporting documents, with the FAA decisionmaker and the hearing docket clerk, and shall serve a copy of the notice and supporting documents on each party and the administrative law judge, not later than 10 days after the administrative law judge's decision forming the basis of an interlocutory appeal of right or not later than 10 days after the administrative law judge's decision granting an interlocutory appeal for cause, whichever is appropriate. A party shall file a reply brief, if any, with the FAA decisionmaker and serve a copy of the reply brief on each party, not later than 10 days after service of the appeal brief. The FAA decisionmaker shall render a decision on the interlocutory appeal, on the record and as a part of the decision in the proceedings, within a reasonable time after receipt of the interlocutory appeal. (e) The FAA decisionmaker may reject frivolous, repetitive, or dilatory appeals, and may issue an order precluding one or more parties from making further interlocutory appeals in a proceeding in which there have been <PRTPAGE P="63"/>frivolous, repetitive, or dilatory interlocutory appeals. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990, as amended by Amdt. 13-23, 55 FR 45983, Oct. 31, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.220</SECTNO> <SUBJECT>Discovery.</SUBJECT> (a) <E T="03">Initiation of discovery.</E> Any party may initiate discovery described in this section, without the consent or approval of the administrative law judge, at any time after a complaint has been filed in the proceedings. (b) <E T="03">Methods of discovery.</E> The following methods of discovery are permitted under this section: depositions on oral examination or written questions of any person; written interrogatories directed to a party; requests for production of documents or tangible items to any person; and requests for admission by a party. A party is not required to file written interrogatories and responses, requests for production of documents or tangible items and responses, and requests for admission and response with the administrative law judge or the hearing docket clerk. In the event of a discovery dispute, a party shall attach a copy of these documents in support of a motion made under this section. (c) <E T="03">Service on the agency.</E> A party shall serve each discovery request directed to the agency or any agency employee on the agency attorney of record. (d) <E T="03">Time for response to discovery requests.</E> Unless otherwise directed by this subpart or agreed by the parties, a party shall respond to a request for discovery, including filing objections to a request for discovery, not later than 30 days of service of the request. (e) <E T="03">Scope of discovery.</E> Subject to the limits on discovery set forth in paragraph (f) of this section, a party may discover any matter that is not privileged and that is relevant to the subject matter of the proceeding. A party may discover information that relates to the claim or defense of any party including the existence, description, nature, custody, condition, and location of any document or other tangible item and the identity and location of any person having knowledge of discoverable matter. A party may discover facts known, or opinions held, by an expert who any other party expects to call to testify at the hearing. A party has no ground to object to a discovery request on the basis that the information sought would not be admissible at the hearing if the information sought during discovery is reasonably calculated to lead to the discovery of admissible evidence. (f) <E T="03">Limiting discovery.</E> The administrative law judge shall limit the frequency and extent of discovery permitted by this section if a party shows that— (1) The information requested is cumulative or repetitious; (2) The information requested can be obtained from another less burdensome and more convenient source; (3) The party requesting the information has had ample opportunity to obtain the information through other discovery methods permitted under this section; or (4) The method or scope of discovery requested by the party is unduly burdensome or expensive. (g) <E T="03">Confidential orders.</E> A party or person who has received a discovery request for information that is related to a trade secret, confidential or sensitive material, competitive or commercial information, proprietary data, or information on research and development, may file a motion for a confidential order with the administrative law judge and shall serve a copy of the motion for a confidential order on each party. (1) The party or person making the motion must show that the confidential order is necessary to protect the information from disclosure to the public. (2) If the administrative law judge determines that the requested material is not necessary to decide the case, the administrative law judge shall preclude any inquiry into the matter by any party. (3) If the administrative law judge determines that the requested material may be disclosed during discovery, the administrative law judge may order that the material may be discovered and disclosed under limited conditions or may be used only under certain terms and conditions. (4) If the administrative law judge determines that the requested material is <PRTPAGE P="64"/>necessary to decide the case and that a confidential order is warranted, the administrative law judge shall provide: (i) An opportunity for review of the document by the parties off the record; (ii) Procedures for excluding the information from the record; and (iii) Order that the parties shall not disclose the information in any manner and the parties shall not use the information in any other proceeding. (h) <E T="03">Protective orders.</E> A party or a person who has received a request for discovery may file a motion for protective order with the administrative law judge and shall serve a copy of the motion for protective order on each party. The party or person making the motion must show that the protective order is necessary to protect the party or the person from annoyance, embarrassment, oppression, or undue burden or expense. As part of the protective order, the administrative law judge may: (1) Deny the discovery request; (2) Order that discovery be conducted only on specified terms and conditions, including a designation of the time or place for discovery or a determination of the method of discovery; or (3) Limit the scope of discovery or preclude any inquiry into certain matters during discovery. (i) <E T="03">Duty to supplement or amend responses.</E> A party who has responded to a discovery request has a duty to supplement or amend the response, as soon as the information is known, as follows: (1) A party shall supplement or amend any response to a question requesting the identity and location of any person having knowledge of discoverable matters. (2) A party shall supplement or amend any response to a question requesting the identity of each person who will be called to testify at the hearing as an expert witness and the subject matter and substance of that witness’ testimony. (3) A party shall supplement or amend any response that was incorrect when made or any response that was correct when made but is no longer correct, accurate, or complete. (j) <E T="03">Depositions.</E> The following rules apply to depositions taken pursuant to this section: (1) <E T="03">Form.</E> A deposition shall be taken on the record and reduced to writing. The person being deposed shall sign the deposition unless the parties agree to waive the requirement of a signature. (2) <E T="03">Administration of oaths.</E> Within the United States, or a territory or possession subject to the jurisdiction of the United States, a party shall take a deposition before a person authorized to administer oaths by the laws of the United States or authorized by the law of the place where the examination is held. In foreign countries, a party shall take a deposition in any manner allowed by the Federal Rules of Civil Procedure. (3) <E T="03">Notice of deposition.</E> A party shall serve a notice of deposition, stating the time and place of the deposition and the name and address of each person to be examined, on the person to be deposed, on the administrative law judge, on the hearing docket clerk, and on each party not later than 7 days before the deposition. A party may serve a notice of deposition less than 7 days before the deposition only with consent of the administrative law judge. If a subpoena <E T="03">duces tecum</E> is to be served on the person to be examined, the party shall attach a copy of the subpoena <E T="03">duces tecum</E> that describes the materials to be produced at the deposition to the notice of deposition. (4) <E T="03">Use of depositions.</E> A party may use any part or all of a deposition at a hearing authorized under this subpart only upon a showing of good cause. The deposition may be used against any party who was present or represented at the deposition or who had reasonable notice of the deposition. (k) <E T="03">Interrogatories.</E> A party, the party's attorney, or the party's representative may sign the party's responses to interrogatories. A party shall answer each interrogatory separately and completely in writing.If a party objects to an interrogatory, the party shall state the objection and the reasons for the objection. An opposing party may use any part or all of a party's responses to interrogatories at a hearing authorized under this subpart to the extent that the response is relevant, material, and not repetitious. (1) A party shall not serve more than 30 interrogatories to each other party. <PRTPAGE P="65"/>Each subpart of an interrogatory shall be counted as a separate interrogatory. (2) A party shall file a motion for leave to serve additional interrogatories on a party with the administrative law judge before serving additional interrogatories on a party. The administrative law judge shall grant the motion only if the party shows good cause for the party's failure to inquire about the information previously and that the information cannot reasonably be obtained using less burdensome discovery methods or be obtained from other sources. (l) <E T="03">Requests for admission.</E> A party may serve a written request for admission of the truth of any matter within the scope of discovery under this section or the authenticity of any document described in the request. A party shall set forth each request for admission separately. A party shall serve copies of documents referenced in the request for admission unless the documents have been provided or are reasonably available for inspection and copying. (1) <E T="03">Time</E>. A party's failure to respond to a request for admission, in writing and signed by the attorney or the party, not later than 30 days after service of the request, is deemed an admission of the truth of the statement or statements contained in the request for admission. The administrative law judge may determine that a failure to respond to a request for admission is not deemed an admission of the truth if a party shows that the failure was due to circumstances beyond the control of the party or the party's attorney. (2) <E T="03">Response.</E> A party may object to a request for admission and shall state the reasons for objection. A party may specifically deny the truth of the matter or describe the reasons why the party is unable to truthfully deny or admit the matter. If a party is unable to deny or admit the truth of the matter, the party shall show that the party has made reasonable inquiry into the matter or that the information known to, or readily obtainable by, the party is insufficient to enable the party to admit or deny the matter. A party may admit or deny any part of the request for admission. If the administrative law judge determines that a response does not comply with the requirements of this rule or that the response is insufficient, the matter is deemed admitted. (3) <E T="03">Effect of admission.</E> Any matter admitted or deemed admitted under this section is conclusively established for the purpose of the hearing and appeal. (m) <E T="03">Motion to compel discovery</E>. A party may make a motion to compel discovery if a person refuses to answer a question during a deposition, a party fails or refuses to answer an interrogatory, if a person gives an evasive or incomplete answer during a deposition or when responding to an interrogatory, or a party fails or refuses to produce documents or tangible items. During a deposition, the proponent of a question may complete the deposition or may adjourn the examination before making a motion to compel if a person refuses to answer. (n) <E T="03">Failure to comply with a discovery order or order to compel.</E> If a party fails to comply with a discovery order or an order to compel, the administrative law judge, limited to the extent of the party's failure to comply with the discovery order or motion to compel, may: (1) Strike that portion of a party's pleadings; (2) Preclude prehearing or discovery motions by that party; (3) Preclude admission of that portion of a party's evidence at the hearing; or (4) Preclude that portion of the testimony of that party's witnesses at the hearing. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990, as amended by Amdt. 13-23, 55 FR 45983, Oct. 31, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.221</SECTNO> <SUBJECT>Notice of hearing.</SUBJECT> (a) <E T="03">Notice.</E> The administrative law judge shall give each party at least 60 days notice of the date, time, and location of the hearing. (b) <E T="03">Date, time, and location of the hearing.</E> The administrative law judge to whom the proceedings have been assigned shall set a reasonable date, time, and location for the hearing. The administrative law judge shall consider the need for discovery and any joint <PRTPAGE P="66"/>procedural or discovery schedule submitted by the parties when determining the hearing date. The administrative law judge shall give due regard to the convenience of the parties, the location where the majority of the witnesses reside or work, and whether the location is served by a scheduled air carrier. (c) <E T="03">Earlier hearing.</E> With the consent of the administrative law judge, the parties may agree to hold the hearing on an earlier date than the date specified in the notice of hearing. </SECTION> <SECTION> <SECTNO>§ 13.222</SECTNO> <SUBJECT>Evidence.</SUBJECT> (a) <E T="03">General.</E> A party is entitled to present the party's case or defense by oral, documentary, or demonstrative evidence, to submit rebuttal evidence, and to conduct any cross-examination that may be required for a full and true disclosure of the facts. (b) <E T="03">Admissibility.</E> A party may introduce any oral, documentary, or demonstrative evidence in support of the party's case or defense. The administrative law judge shall admit any oral, documentary, or demonstrative evidence introduced by a party but shall exclude irrelevant, immaterial, or unduly repetitious evidence. (c) <E T="03">Hearsay evidence.</E> Hearsay evidence is admissible in proceedings governed by this subpart. The fact that evidence submitted by a party is hearsay goes only to the weight of the evidence and does not affect its admissibility. </SECTION> <SECTION> <SECTNO>§ 13.223</SECTNO> <SUBJECT>Standard of proof.</SUBJECT> The administrative law judge shall issue an initial decision or shall rule in a party's favor only if the decision or ruling is supported by, and in accordance with, the reliable, probative, and substantial evidence contained in the record. In order to prevail, the party with the burden of proof shall prove the party's case or defense by a preponderance of reliable, probative, and substantial evidence. </SECTION> <SECTION> <SECTNO>§ 13.224</SECTNO> <SUBJECT>Burden of proof.</SUBJECT> (a) Except in the case of an affirmative defense, the burden of proof is on the agency. (b) Except as otherwise provided by statute or rule, the proponent of a motion, request, or order has the burden of proof. (c) A party who has asserted an affirmative defense has the burden of proving the affirmative defense. </SECTION> <SECTION> <SECTNO>§ 13.225</SECTNO> <SUBJECT>Offer of proof.</SUBJECT> A party whose evidence has been excluded by a ruling of the administrative law judge may offer the evidence for the record on appeal. </SECTION> <SECTION> <SECTNO>§ 13.226</SECTNO> <SUBJECT>Public disclosure of evidence.</SUBJECT> (a) The administrative law judge may order that any information contained in the record be withheld from public disclosure. Any person may object to disclosure of information in the record by filing a written motion to withhold specific information with the administrative law judge and serving a copy of the motion on each party. The party shall state the specific grounds for nondisclosure in the motion. (b) The administrative law judge shall grant the motion to withhold information in the record if, based on the motion and any response to the motion, the administrative law judge determines that disclosure would be detrimental to aviation safety, disclosure would not be in the public interest, or that the information is not otherwise required to be made available to the public. </SECTION> <SECTION> <SECTNO>§ 13.227</SECTNO> <SUBJECT>Expert or opinion witnesses.</SUBJECT> An employee of the agency may not be called as an expert or opinion witness, for any party other than the FAA, in any proceeding governed by this subpart. An employee of a respondent may not be called by an agency attorney as an expert or opinion witness for the FAA in any proceeding governed by this subpart to which the respondent is a party. </SECTION> <SECTION> <SECTNO>§ 13.228</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> (a) <E T="03">Request for subpoena.</E> A party may obtain a subpoena to compel the attendance of a witness at a deposition or hearing or to require the production of documents or tangible items from the hearing docket clerk. The hearing docket clerk shall deliver the subpoena, signed by the hearing docket clerk or an administrative law judge but otherwise in blank, to the party. <PRTPAGE P="67"/>The party shall complete the subpoena, stating the title of the action and the date and time for the witness’ attendance or production of documents or items. The party who obtained the subpoena shall serve the subpoena on the witness. (b) <E T="03">Motion to quash or modify the subpoena.</E> A party, or any person upon whom a subpoena has been served, may file a motion to quash or modify the subpoena with the administrative law judge at or before the time specified in the subpoena for compliance. The applicant shall describe, in detail, the basis for the application to quash or modify the supoena including, but not limited to, a statement that the testimony, document, or tangible evidence is not relevant to the proceeding, that the subpoena is not reasonably tailored to the scope of the proceeding, or that the subpoena is unreasonable and oppressive. A motion to quash or modify the subpoena will stay the effect of the subpoena pending a decision by the administrative law judge on the motion. (c) <E T="03">Enforcement of subpoena.</E> Upon a showing that a person has failed or refused to comply with a subpoena, a party may apply to the local Federal district court to seek judicial enforcement of the subpoena in accordance with section 1004 of the Federal Aviation Act of 1958, as amended. </SECTION> <SECTION> <SECTNO>§ 13.229</SECTNO> <SUBJECT>Witness fees.</SUBJECT> (a) <E T="03">General.</E> Unless otherwise authorized by the administrative law judge, the party who applies for a subpoena to compel the attendance of a witness at a deposition or hearing, or the party at whose request a witness appears at a deposition or hearing, shall pay the witness fees described in this section. (b) <E T="03">Amount.</E> Except for an employee of the agency who appears at the direction of the agency, a witness who appears at a deposition or hearing is entitled to the same fees and mileage expenses as are paid to a witness in a court of the United States in comparable circumstances. </SECTION> <SECTION> <SECTNO>§ 13.230</SECTNO> <SUBJECT>Record.</SUBJECT> (a) <E T="03">Exclusive record.</E> The transcript of all testimony in the hearing, all exhibits received into evidence, and all motions, applications, requests, and rulings shall constitute the exclusive record for decision of the proceedings and the basis for the issuance of any orders in the proceeding. Any proceedings regarding the disqualification of an administrative law judge shall be included in the record. (b) <E T="03">Examination and copying of record.</E> Any person may examine the record at the Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591. Any person may have a copy of the record after payment of reasonable costs to copy the record. </SECTION> <SECTION> <SECTNO>§ 13.231</SECTNO> <SUBJECT>Argument before the administrative law judge.</SUBJECT> (a) <E T="03">Arguments during the hearing.</E> During the hearing, the administrative law judge shall give the parties a reasonable opportunity to present arguments on the record supporting or opposing motions, objections, and rulings if the parties request an opportunity for argument. The administrative law judge may request written arguments during the hearing if the administrative law judge finds that submission of written arguments would be reasonable. (b) <E T="03">Final oral argument.</E> At the conclusion of the hearing and before the administrative law judge issues an initial decision in the proceedings, the parties are entitled to submit oral proposed findings of fact and conclusions of law, exceptions to rulings of the administrative law judge, and supporting arguments for the findings, conclusions, or exceptions. At the conclusion of the hearing, a party may waive final oral argument. (c) <E T="03">Posthearing briefs.</E> The administrative law judge may request written posthearing briefs before the administrative law judge issues an initial decision in the proceedings if the administrative law judge finds that submission of written arguments would be reasonable. If a party files a written posthearing brief, the party shall include proposed findings of fact and conclusions of law, exceptions to rulings of the administrative law judge, and supporting arguments for the findings, conclusions, or exceptions. The administrative law judge shall give the parties a reasonable opportunity, not more than 30 days after receipt of the <PRTPAGE P="68"/>transcript, to prepare and submit the briefs. </SECTION> <SECTION> <SECTNO>§ 13.232</SECTNO> <SUBJECT>Initial decision.</SUBJECT> (a) <E T="03">Contents.</E> The administrative law judge shall issue an initial decision at the conclusion of the hearing. In each oral or written decision, the administrative law judge shall include findings of fact and conclusions of law, and the grounds supporting those findings and conclusions, upon all material issues of fact, the credibility of witnesses, the applicable law, any exercise of the administrative law judge's discretion, the amount of any civil penalty found appropriate by the administrative law judge, and a discussion of the basis for any order issued in the proceedings. The administrative law judge is not required to provide a written explanation for rulings on objections, procedural motions, and other matters not directly relevant to the substance of the initial decision. If the administrative law judge refers to any previous unreported or unpublished initial decision, the administrative law judge shall make copies of that initial decision available to all parties and the FAA decisionmaker. (b) <E T="03">Oral decision.</E> Except as provided in paragraph (c) of this section, at the conclusion of the hearing, the administrative law judge shall issue the initial decision and order orally on the record. (c) <E T="03">Written decision.</E> The administrative law judge may issue a written initial decision not later than 30 days after the conclusion of the hearing or submission of the last posthearing brief if the administrative law judge finds that issuing a written initial decision is reasonable. The administrative law judge shall serve a copy of any written initial decision on each party. (d) <E T="03">Order assessing civil penalty.</E> Unless appealed pursuant to § 13.233 of this subpart, the initial decision issued by the administrative law judge shall be considered an order assessing civil penalty if the administrative law judge finds that an alleged violation occurred and determines that a civil penalty, in an amount found appropriate by the administrative law judge, is warranted. </SECTION> <SECTION> <SECTNO>§ 13.233</SECTNO> <SUBJECT>Appeal from initial decision.</SUBJECT> (a) <E T="03">Notice of appeal.</E> A party may appeal the initial decision, and any decision not previously appealed pursuant to § 13.219, by filing a notice of appeal with the FAA decisionmaker. A party shall file the notice of appeal with the Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591, Attention: Appellate Docket Clerk. A party shall file the notice of appeal not later than 10 days after entry of the oral initial decision on the record or service of the written initial decision on the parties and shall serve a copy of the notice of appeal on each party. (b) <E T="03">Issues on appeal.</E> A party may appeal only the following issues: (1) Whether each filing of fact is supported by a preponderance of reliable, probative, and substantial evidence; (2) Whether each conclusion of law is made in accordance with applicable law, precedent, and public policy; and (3) Whether the administrative law judge committed any prejudicial errors during the hearing that support the appeal. (c) <E T="03">Perfecting an appeal.</E> Unless otherwise agreed by the parties, a party shall perfect an appeal, not later than 50 days after entry of the oral initial decision on the record or service of the written initial decision on the party, by filing an appeal brief with the FAA decisionmaker. (1) <E T="03">Extension of time by agreement of the parties.</E> The parties may agree to extend the time for perfecting the appeal with the consent of the FAA decisionmaker. If the FAA decisionmaker grants an extension of time to perfect the appeal, the appellate docket clerk shall serve a letter confirming the extension of time on each party. (2) <E T="03">Written motion for extension.</E> If the parties do not agree to an extension of time for perfecting an appeal, a party desiring an extension of time may file a written motion for an extension with the FAA decisionmaker and shall serve a copy of the motion on each party. The FAA decisionmaker may grant an extension if good cause for the extension is shown in the motion.<PRTPAGE P="69"/> (d) <E T="03">Appeal briefs.</E> A party shall file the appeal brief with the FAA decisionmaker and shall serve a copy of the appeal brief on each party. (1) A party shall set forth, in detail, the party's specific objections to the initial decision or rulings in the appeal brief. A party also shall set forth, in detail, the basis for the appeal, the reasons supporting the appeal, and the relief requested in the appeal. If the party relies on evidence contained in the record for the appeal, the party shall specifically refer to the pertinent evidence contained in the transcript in the appeal brief. (2) The FAA decisionmaker may dismiss an appeal, on the FAA decisionmaker's own initiative or upon motion of any other party, where a party has filed a notice of appeal but fails to perfect the appeal by timely filing an appeal brief with the FAA decisionmaker. (e) <E T="03">Reply brief.</E> Unless otherwise agreed by the parties, any party may file a reply brief with the FAA decisionmaker not later than 35 days after the appeal brief has been served on that party. The party filing the reply brief shall serve a copy of the reply brief on each party. If the party relies on evidence contained in the record for the reply, the party shall specifically refer to the pertinent evidence contained in the transcript in the reply brief. (1) <E T="03">Extension of time by agreement of the parties.</E> The parties may agree to extend the time for filing a reply brief with the consent of the FAA decisionmaker. If the FAA decisionmaker grants an extension of time to file the reply brief, the appellate docket clerk shall serve a letter confirming the extension of time on each party. (2) <E T="03">Written motion for extension.</E> If the parties do not agree to an extension of time for filing a reply brief, a party desiring an extension of time may file a written motion for an extension with the FAA decisionmaker and shall serve a copy of the motion on each party. The FAA decisionmaker may grant an extension if good cause for the extension is shown in the motion. (f) <E T="03">Other briefs.</E> The FAA decisionmaker may allow any person to submit an <E T="03">amicus curiae</E> brief in an appeal of an initial decision. A party may not file more than one appeal brief or reply brief. A party may petition the FAA decisionmaker, in writing, for leave to file an additional brief and shall serve a copy of the petition on each party. The party may not file the additional brief with the petition. The FAA decisionmaker may grant leave to file an additional brief if the party demonstrates good cause for allowing additional argument on the appeal. The FAA decisionmaker will allow a reasonable time for the party to file the additional brief. (g) <E T="03">Number of copies.</E> A party shall file the original appeal brief or the original reply brief, and two copies of the brief, with the FAA decisionmaker. (h) <E T="03">Oral argument.</E> The FAA decisionmaker has sole discretion to permit oral argument on the appeal. On the FAA decisionmaker's own initiative or upon written motion by any party, the FAA decisionmaker may find that oral argument will contribute substantially to the development of the issues on appeal and may grant the parties an opportunity for oral argument. (i) <E T="03">Waiver of objections on appeal.</E> If a party fails to object to any alleged error regarding the proceedings in an appeal or a reply brief, the party waives any objection to the alleged error. The FAA decisionmaker is not required to consider any objection in an appeal brief or any argument in the reply brief if a party's objection is based on evidence contained on the record and the party does not specifically refer to the pertinent evidence from the record in the brief. (j) <E T="03">FAA decisionmaker's decision on appeal.</E> The FAA decisionmaker will review the briefs on appeal and the oral argument, if any, to determine if the administrative law judge committed prejudicial error in the proceedings or that the initial decision should be affirmed, modified, or reversed. The FAA decisionmaker may affirm, modify, or reverse the initial decision, make any necessary findings, or may remand the case for any proceedings that the FAA decisionmaker determines may be necessary. (1) The FAA decisionmaker may raise any issue, on the FAA decisionmaker's own initiative, that is required for proper disposition of the proceedings. <PRTPAGE P="70"/>The FAA decisionmaker will give the parties a reasonable opportunity to submit arguments on the new issues before making a decision on appeal. If an issue raised by the FAA decisionmaker requires the consideration of additional testimony or evidence, the FAA decisionmaker will remand the case to the administrative law judge for further proceedings and an initial decision related to that issue. If an issue raised by the FAA decisionmaker is solely an issue of law or the issue was addressed at the hearing but was not raised by a party in the briefs on appeal, a remand of the case to the administrative law judge for further proceedings is not required but may be provided in the discretion of the FAA decisionmaker. (2) The FAA decisionmaker will issue the final decision and order of the Administrator on appeal in writing and will serve a copy of the decision and order on each party. Unless a petition for review is filed pursuant to § 13.235, a final decision and order of the Administrator shall be considered an order assessing civil penalty if the FAA decisionmaker finds that an alleged violation occurred and a civil penalty is warranted. (3) A final decision and order of the Administrator after appeal is precedent in any other civil penalty action. Any issue, finding or conclusion, order, ruling, or initial decision of an administrative law judge that has not been appealed to the FAA decisionmaker is not precedent in any other civil penalty action. </SECTION> <SECTION> <SECTNO>§ 13.234</SECTNO> <SUBJECT>Petition to reconsider or modify a final decision and order of the FAA decisionmaker on appeal.</SUBJECT> (a) <E T="03">General.</E> Any party may petition the FAA decisionmaker to reconsider or modify a final decision and order issued by the FAA decisionmaker on appeal from an initial decision. A party shall file a petition to reconsider or modify with the FAA decisionmaker not later than 30 days after service of the FAA decisionmaker's final decision and order on appeal and shall serve a copy of the petition on each party. The FAA decisionmaker will not reconsider or modify an initial decision and order issued by an administrative law judge that has not been appealed by any party to the FAA decisionmaker. (b) <E T="03">Form and number of copies.</E> A party shall file a petition to reconsider or modify, in writing, with the FAA decisionmaker. The party shall file the original petition with the FAA decisionmaker and shall serve a copy of the petition on each party. (c) <E T="03">Contents.</E> A party shall state briefly and specifically the alleged errors in the final decision and order on appeal, the relief sought by the party, and the grounds that support, the petition to reconsider or modify. (1) If the petition is based, in whole or in part, on allegations regarding the consequences of the FAA decisionmaker's decision, the party shall describe these allegations and shall describe, and support, the basis for the allegations. (2) If the petition is based, in whole or in part, on new material not previously raised in the proceedings, the party shall set forth the new material and include affidavits of prospective witnesses and authenticated documents that would be introduced in support of the new material. The party shall explain, in detail, why the new material was not discovered through due diligence prior to the hearing. (d) <E T="03">Repetitious and frivolous petitions.</E> The FAA decisionmaker will not consider repetitious or frivolous petitions. The FAA decisionmaker may summarily dismiss repetitious or frivolous petitions to reconsider or modify. (e) <E T="03">Reply petitions.</E> Any other party may reply to a petition to reconsider or modify, not later than 10 days after service of the petition on that party, by filing a reply with the FAA decisionmaker. A party shall serve a copy of the reply on each party. (f) <E T="03">Effect of filing petition.</E> Unless otherwise ordered by the FAA decisionmaker, filing of a petition pursuant to this section will not stay or delay the effective date of the FAA decisionmaker's final decision and order on appeal and shall not toll the time allowed for judicial review. (g) <E T="03">FAA decisionmaker's decision on petition.</E> The FAA decisionmaker has sole discretion to grant or deny a petition to reconsider or modify. The FAA decisionmaker will grant or deny a petition <PRTPAGE P="71"/>to reconsider or modify within a reasonable time after receipt of the petition or receipt of the reply petition, if any. The FAA decisionmaker may affirm, modify, or reverse the final decision and order on appeal, or may remand the case for any proceedings that the FAA decisionmaker determines may be necessary. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990; 55 FR 29293, July 18, 1990; Amdt. 13-23, 55 FR 45983, Oct. 31, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.235</SECTNO> <SUBJECT>Judicial review of a final decision and order.</SUBJECT> A person may seek judicial review of a final decision and order of the Administrator as provided in section 1006 of the Federal Aviation Act of 1958, as amended. A party seeking judicial review of a final decision and order shall file a petition for review not later than 60 days after the final decision and order has been served on the party. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Civil Monetary Penalty Inflation Adjustment</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 28762, 61 FR 67445, Dec. 20, 1996, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 13.301</SECTNO> <SUBJECT>Scope and purpose.</SUBJECT> (a) This subpart provides a mechanism for the regular adjustment for inflation of civil monetary penalties in conformity with the Federal Civil Penalties Inflation Adjustment Act of 1990, 28 U.S.C. 2461 (note), as amended by the Debt Collection Improvement Act of 1996, Public Law 104-134, April 26, 1996, in order to maintain the deterrent effect of civil monetary penalties and to promote compliance with the law. This subpart also sets out the current adjusted maximum civil monetary penalties or range of minimum and maximum civil monetary penalties for each statutory civil penalty subject to the FAA's jurisdiction. (b) Each adjustment to the maximum civil monetary penalty or the range of minimum and maximum civil monetary penalties, as applicable, made in accordance with this subpart applies prospectively from the date it becomes effective to actions initiated under this part, notwithstanding references to a specific maximum civil monetary penalty or range of minimum and maximum civil monetary penalties contained elsewhere in this part. </SECTION> <SECTION> <SECTNO>§ 13.303</SECTNO> <SUBJECT>Definitions.</SUBJECT> (a) <E T="03">Civil Monetary Penalty</E> means any penalty, fine, or other sanction that: (1) Is for a specific monetary amount as provided by Federal law or has a maximum amount provided by Federal law; (2) Is assessed or enforced by the FAA pursuant to Federal law; and (3) Is assessed or enforced pursuant to an administrative proceeding or a civil action in the Federal courts. (b) <E T="03">Consumer Price Index</E> means the Consumer Price Index for all urban consumers published by the Department of Labor. </SECTION> <SECTION> <SECTNO>§ 13.305</SECTNO> <SUBJECT>Cost of living adjustments of civil monetary penalties.</SUBJECT> (a) Except for the limitation to the initial adjustment to statutory maximum civil monetary penalties or range of minimum and maximum civil monetary penalties set forth in paragraph (c) of this section, the inflation adjustment under this subpart is determined by increasing the maximum civil monetary penalty or range of minimum and maximum civil monetary penalty for each civil monetary penalty by the cost-of-living adjustment. Any increase determined under paragraph (a) of this section is rounded to the nearest: (1) Multiple of $10 in the case of penalties less than or equal to $100; (2) Multiple of $100 in the case of penalties greater than $100 but less than or equal to $1,000; (3) Multiple of $1,000 in the case of penalties greater than $1,000 but less than or equal to $10,000; (4) Multiple of $5,000 in the case of penalties greater than $10,000 but less than or equal to $100,000; (5) Multiple of $10,000 in the case of penalties greater than $100,000 but less than or equal to $200,000; and (6) Multiple of $25,000 in the case of penalties greater than $200,000. (b) For purposes of paragraph (a) of this section, the term “cost-of-living adjustment” means the percentage (if any) for each civil monetary penalty by which the Consumer Price Index for the month of June of the calendar year <PRTPAGE P="72"/>preceding the adjustment exceeds the Consumer Price Index for the month of June of the calendar year in which the amount of such civil monetary penalty was last set or adjusted pursuant to law. (c) Limitation on initial adjustment. The initial adjustment of maximum civil penalty or range of minimum and maximum civil monetary penalties made pursuant to this subpart does not exceed 10 percent of the statutory maximum civil penalty before an adjustment under this subpart is made. This limitation applies only to the initial adjustment, effective on January 21, 1997. (d) <E T="03">Inflation adjustment.</E> Minimum and maximum civil monetary penalties within the jurisdiction of the FAA are adjusted for inflation as follows: <GPOTABLE CDEF="s50,r75,xls40,xls40,r50,r50" COLS="6" OPTS="L2,i1"> <TTITLE> <E T="04">Minimum and Maximum Civil Penalties—Adjusted for Inflation, Effective January 21, 1997</E> </TTITLE> <BOXHD> <CHED H="1">United States Code<LI>citation</LI> </CHED> <CHED H="1">Civil monetary penalty<LI>description</LI> </CHED> <CHED H="1">Minimum penalty amount as of<LI>10/23/96</LI> </CHED> <CHED H="1">New adjusted minimum penalty amount</CHED> <CHED H="1">Maximum penalty amount as of 10/26/96</CHED> <CHED H="1">New adjusted maximum penalty amount</CHED> </BOXHD> <ROW> <ENT I="01">49 U.S.C. 5123(a) (changed 1990) </ENT> <ENT>Violations of hazardous materials transportation law or regulations </ENT> <ENT>$250 per violation per day </ENT> <ENT>$250 per violation per day </ENT> <ENT>$25,000 per violation per day </ENT> <ENT>$27,500 per violation per day.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46301(a)(1) (1958) </ENT> <ENT>Violations of FAA statute or regulations by a person </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$1,000 per violation per day or per flight </ENT> <ENT>$1,100 per violation per day or per flight.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46301(a)(2) (changed 1987) </ENT> <ENT>Violations of FAA statute or regulations by a person operating an aircraft for the transportation of passengers or property for compensation </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation per day or per flight </ENT> <ENT>$11,000 per violation per day or per flight.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46301(a)(3)(A) (1974) </ENT> <ENT>Violations of FAA statute or regulations involving the transportation of hazardous materials by air </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation per day or per flight </ENT> <ENT>$11,000 per violation per day or per flight.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 463(a)(3)(B) (1988) </ENT> <ENT>Violations of FAA statute or regulations involving the registration or recordation under chapter 441 of aircraft not used to provide air transportation </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation per day or per flight </ENT> <ENT>$11,000 per violation per day or per flight.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46301(b) (1987) </ENT> <ENT>Tampering with a smoke alarm device </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$2,000 per violation </ENT> <ENT>$2,200 per violation.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46302 (1984) </ENT> <ENT>Knowingly providing false information about alleged violations involving the special aircraft jurisdiction of the United States </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation </ENT> <ENT>$11,000 per violation.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46303 (1984) </ENT> <ENT>Carrying a concealed deadly or dangerous weapon </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation </ENT> <ENT>$11,000 per violation.</ENT> </ROW> </GPOTABLE> <CITA TYPE="W">[61 FR 67445, Dec. 20, 1996, as amended by Amdt. 13-28, 62 FR 4134, Jan. 29, 1997]</CITA> </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 14</EAR> <HD SOURCE="HED">PART 14—RULES IMPLEMENTING THE EQUAL ACCESS TO JUSTICE ACT OF 1980</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—General Provisions</HD> <SECHD>Sec.</SECHD> <SECTNO>14.01</SECTNO> <SUBJECT>Purpose of these rules.</SUBJECT> <SECTNO>14.02</SECTNO> <SUBJECT>Proceedings covered.</SUBJECT> <SECTNO>14.03</SECTNO> <SUBJECT>Eligibility of applicants.</SUBJECT> <SECTNO>14.04</SECTNO> <SUBJECT>Standards for awards.</SUBJECT> <SECTNO>14.05</SECTNO> <SUBJECT>Allowance fees and expenses.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Information Required From Applicants</HD> <SECTNO>14.10</SECTNO> <SUBJECT>Contents of application.</SUBJECT> <SECTNO>14.11</SECTNO> <SUBJECT>Net worth exhibit.</SUBJECT> <SECTNO>14.12</SECTNO> <SUBJECT>Documentation of fees and expenses.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Procedures for Considering Applications</HD> <SECTNO>14.20</SECTNO> <SUBJECT>When an application may be filed.</SUBJECT> <SECTNO>14.21</SECTNO> <SUBJECT>Filing and service of documents.</SUBJECT> <SECTNO>14.22</SECTNO> <SUBJECT>Answer to application.</SUBJECT> <SECTNO>14.23</SECTNO> <SUBJECT>Reply.</SUBJECT> <SECTNO>14.24</SECTNO> <SUBJECT>Comments by other parties.</SUBJECT> <SECTNO>14.25</SECTNO> <SUBJECT>Settlement.<PRTPAGE P="73"/> </SUBJECT> <SECTNO>14.26</SECTNO> <SUBJECT>Further proceedings.</SUBJECT> <SECTNO>14.27</SECTNO> <SUBJECT>Decision.</SUBJECT> <SECTNO>14.28</SECTNO> <SUBJECT>Review by FAA Decisionmaker.</SUBJECT> <SECTNO>14.29</SECTNO> <SUBJECT>Judicial review.</SUBJECT> <SECTNO>14.30</SECTNO> <SUBJECT>Payment of award.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 5 U.S.C. 504; 49 U.S.C. 106(g), 40113, 46104. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> 54 FR 46199, Nov. 1, 1989, unless otherwise noted. </SOURCE> <SUBPART> <HD SOURCE="HED">Subpart A—General Provisions</HD> <SECTION> <SECTNO>§ 14.01</SECTNO> <SUBJECT>Purpose of these rules.</SUBJECT> The Equal Access to Justice Act, 5 U.S.C. 504 (the Act), provides for the award of attorney fees and other expenses to eligible individuals and entities who are parties to certain administrative proceedings (adversary adjudications) before the Federal Aviation Administration (FAA). An eligible party may receive an award when it prevails over the FAA, unless the agency's position in the proceeding was substantially justified or special circumstances make an award unjust. The rules in this part describe the parties eligible for awards and the proceedings that are covered. They also explain how to apply for awards, and the procedures and standards that the FAA Decisionmaker will use to make them. As used hereinafter, the term “agency” applies to the FAA. </SECTION> <SECTION> <SECTNO>§ 14.02</SECTNO> <SUBJECT>Proceedings covered.</SUBJECT> (a) The Act applies to certain adversary adjudications conducted by the FAA. These are adjudications under 5 U.S.C. 554 in which the position of the FAA is represented by an attorney or other representative who enters an appearance and participates in the proceeding. This subpart applies to proceedings under 49 U.S.C. App. 1475 and 49 U.S.C. App. 1471(a). (b) If a proceeding includes both matters covered by the Act and matters specifically excluded from coverage, any award made will include only fees and expenses related to covered issues. (c) Fees and other expenses may not be awarded to a party for any portion of the adversary adjudication in which such party has unreasonably protracted the proceedings. </SECTION> <SECTION> <SECTNO>§ 14.03</SECTNO> <SUBJECT>Eligibility of applicants.</SUBJECT> (a) To be eligible for an award of attorney fees and other expenses under the Act, the applicant must be a party to the adversary adjudication for which it seeks an award. The term “party” is defined in 5 U.S.C. 551(3). The applicant must show that it meets all conditions or eligibility set out in this subpart and in subpart B of this part. (b) The types of eligible applicants are as follows: (1) An individual with a net worth of not more than $2 million at the time the adversary adjudication was initiated; (2) The sole owner of an unincorporated business who has a net worth of not more than $7 million, including both personal and business interests, and not more than 500 employees at the time the adversary adjudication was initiated; (3) A charitable or other tax-exempt organization described in section 501(c)(3) of the Internal Revenue Code (26 U.S.C. 501(c)(3)) with not more than 500 employees at the time the adversary adjudication was initiated; and (4) A cooperative association as defined in section 15(a) of the Agricultural Marketing Act (12 U.S.C. 1141j(a)) with not more than 500 employees at the time the adversary adjudication was initiated; and (5) Any other partnership, corporation, association, or public or private organization with a net worth of not more than $7 million and not more than 500 employees at the time the adversary adjudication was initiated. (c) For the purpose of eligibility, the net worth and number of employees of an applicant shall be determined as of the date the proceeding was initiated. (d) An applicant who owns an unincorporated business will be considered an “individual” rather than a “sole owner of an unincorporated business” if the issues on which the applicant prevails are related primarily to personal interests rather than to business interest. (e) The employees of an applicant include all persons who regularly perform services for remuneration for the applicant, under the applicant's direction and control. Part-time employees <PRTPAGE P="74"/>shall be included on a proportional basis. (f) The net worth and number of employees of the applicant and all of its affiliates shall be aggregated to determine eligibility. Any individual, corporation, or other entity that directly or indirectly controls or owns a majority of the voting shares or other interest of the applicant, or any corporation or other entity of which the applicant directly or indirectly owns or controls a majority of the voting shares or other interest, will be considered an affiliate for purposes of this part, unless the administrative law judge determines that such treatment would be unjust and contrary to the purposes of the Act in light of the actual relationship between the affiliated entities. In addition, the administrative law judge may determine that financial relationships of the applicant, other than those described in this paragraph, constitute special circumstances that would make an award unjust. (g) An applicant that participates in a proceeding primarily on behalf of one or more other persons or entities that would be ineligible if not itself eligible for an award. </SECTION> <SECTION> <SECTNO>§ 14.04</SECTNO> <SUBJECT>Standards for awards.</SUBJECT> (a) A prevailing applicant may receive an award for attorney fees and other expenses incurred in connection with a proceeding, or in a significant and discrete substantive portion of the proceeding, unless the position of the agency over which the applicant has prevailed was substantially justified. Whether or not the position of the FAA was substantially justified shall be determined on the basis of the record (including the record with respect to the action or failure to act by the agency upon which the civil action is based) which was made in the civil action for which fees and other expenses are sought. The burden of proof that an award should not be made to an eligible prevailing applicant is on the agency counsel, who may avoid an award by showing that the agency's position was reasonable in law and fact. (b) An award will be reduced or denied if the applicant has unduly or unreasonably protracted the proceeding or if special circumstances make the award sought unjust. </SECTION> <SECTION> <SECTNO>§ 14.05</SECTNO> <SUBJECT>Allowance fees and expenses.</SUBJECT> (a) Awards will be based on rates customarily charged by persons engaged in the business of acting as attorneys, agents, and expert witnesses, even if the services were made available without charge or at a reduced rate to the applicant. (b) No award for the fee of an attorney or agent under these rules may exceed $75 per hour. No award to compensate an expert witness may exceed the highest rate at which the agency pays expert witnesses. However, an award may also include the reasonable expenses of the attorney, agent, or witness as a separate item, if the attorney, agent, or witness ordinarily charges clients separately for such expenses. (c) In determining the reasonableness of the fee sought for an attorney, agent, or expert witness, the administrative law judge shall consider the following: (1) If the attorney, agent, or witness is in private practice, his or her customary fee for similar services, or if an employee of the applicant, the fully allocated cost of the services; (2) The prevailing rate for similar services in the community in which the attorney, agent, or witness ordinarily performs services; (3) The time actually spent in the representation of the applicant; (4) The time reasonably spent in light of the difficulty or complexity of the issues in the proceeding; and (5) Such other factors as may bear on the value of the services provided. (d) The reasonable cost of any study, analysis, engineering report, test, project, or similar matter prepared on behalf of a party may be awarded, to the extent that the charge for the service does not exceed the prevailing rate for similar services, and the study or other matter was necessary for preparation of the applicant's case. (e) Fees may be awarded only for work performed after the issuance of a complaint. <CITA>[Amdt. 13-18, 53 FR 34655, Sept. 7, 1988, as amended by Amdt. 14-1, 55 FR 15131, Apr. 20, 1990]</CITA> </SECTION> </SUBPART> <SUBPART> <PRTPAGE P="75"/> <HD SOURCE="HED">Subpart B—Information Required From Applicants</HD> <SECTION> <SECTNO>§ 14.10</SECTNO> <SUBJECT>Contents of application.</SUBJECT> (a) An application for an award of fees and expenses under the Act shall identify the applicant and the proceeding for which an award is sought. The application shall show that the applicant has prevailed and identify the position of the agency in the proceeding that the applicant alleges was not substantially justified. Unless the applicant is an individual, the application shall also state the number of employees of the applicant and describe briefly the type and purpose of its organization or business. (b) The application shall also include a statement that the applicant's net worth does not exceed $2 million (if an individual) or $7 million (for all other applicants, including their affiliates) at the time the adversary adjudication was initiated. However, an applicant may omit this statement if: (1) It attaches a copy of a ruling by the Internal Revenue Service that it qualifies as an organization described in section 501(c)(3) of the Internal Revenue Code (26 U.S.C. 501(c)(3)), or in the case of a tax-exempt organization not required to obtain a ruling from the Internal Revenue Service on its exempt status, a statement that describes the basis for the applicant's belief that it qualifies under such section; or (2) It states that it is a cooperative association as defined in section 15(a) of the Agricultural Marketing Act (12 U.S.C. 1141j(a)). (c) The application shall state the amount of fees and expenses for which an award is sought. (d) The application may also include any other matters that the applicant wishes this agency to consider in determining whether and in what amount an award should be made. (e) The application shall be signed by the applicant or an authorized officer or attorney for the applicant. It shall also contain or be accompanied by a written verification under oath or under penalty of perjury that the information provided in the application is true and correct. (f) If the applicant is a partnership, corporation, association, organization, or sole owner of an unincorporated business, the application shall state that the applicant did not have more than 500 employees at the time the adversary adjudication was initiated, giving the number of its employees and describing briefly the type and purpose of its organization or business. </SECTION> <SECTION> <SECTNO>§ 14.11</SECTNO> <SUBJECT>Net worth exhibit.</SUBJECT> (a) Each applicant except a qualified tax-exempt organization or cooperative association must provide with its application a detailed exhibit showing the net worth of the applicant and any affiliates when the proceeding was initiated. If any individual, corporation, or other entity directly or indirectly controls or owns a majority of the voting shares or other interest of the applicant, or if the applicant directly or indirectly owns or controls a majority of the voting shares or other interest of any corporation or other entity, the exhibit must include a showing of the net worth of all such affiliates or of the applicant including the affiliates. The exhibit may be in any form convenient to the applicant that provides full disclosure of the applicant's and its affiliates’ assets and liabilities and is sufficient to determine whether the applicant qualifies under the standards in this part. The administrative law judge may require an applicant to file additional information to determine the eligibility for an award. (b) The net worth exhibit shall describe any transfers of assets from, or obligations incurred by, the applicant or any affiliate, occurring in the one-year period prior to the date on which the proceeding was initiated, that reduced the net worth of the applicant and its affiliates below the applicable net worth ceiling. If there were no such transactions, the applicant shall so state. (c) Ordinarily, the net worth exhibit will be included in the public record of the proceeding. However, an applicant that objects to public disclosure of information in any portion of the exhibit and believes there are legal grounds for withholding it from disclosure may submit that portion of the exhibit directly to the administrative law judge <PRTPAGE P="76"/>in a sealed envelope labeled “Confidential Financial Information,” accompanied by a motion to withhold the information from public disclosure. The motion shall describe the information sought to be withheld and explain, in detail, why it falls within one or more of the specific exemptions from mandatory disclosure under the Freedom of Information Act, 5 U.S.C. 552(b)(1)-(9), why public disclosure of the information would adversely affect the applicant, and why disclosure is not required in the public interest. The material in question shall be served on counsel representing the agency against which the applicant seeks an award, but need not be served on any other party to the proceeding. If the administrative law judge finds that the information should not be withheld from disclosure, it shall be placed in the public record of the proceeding. Otherwise, any request to inspect or copy the exhibit shall be disposed of in accordance with the FAA's established procedures under the Freedom of Information Act as implemented by 49 CFR part 7, appendix C of the FAA's rules. </SECTION> <SECTION> <SECTNO>§ 14.12</SECTNO> <SUBJECT>Documentation of fees and expenses.</SUBJECT> The application shall be accompanied by full documentation of the fees and expenses, including the cost of any study, analysis, engineering report, test, project or similar matter, for which an award is sought. A separate itemized statement shall be submitted for each professional firm or individual whose services are covered by the application, showing the hours spent in connection with the proceedings by each individual, a description of the specific services performed, the rate at which each fee has been computed, any expenses for which reimbursement is sought, the total amount claimed, and the total amount paid or payable by the applicant or by any other person or entity for the services provided. The administrative law judge may require the applicant to provide vouchers, receipts, or other substantiation for any expenses claimed. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Procedures for Considering Applications</HD> <SECTION> <SECTNO>§ 14.20</SECTNO> <SUBJECT>When an application may be filed.</SUBJECT> (a) An application may be filed whenever the applicant has prevailed in the proceeding, but in no case later than 30 days after the FAA Decisionmaker's final disposition of the proceeding. (b) If review or reconsideration is sought or taken of a decision to which an applicant believes it has prevailed, proceedings for the award of fees shall be stayed pending final disposition of the underlying controversy. (c) For purposes of this rule, final disposition means the later of: (1) The date on which an unappealed initial decision becomes administratively final; (2) Issuance of an order disposing of any petitions for reconsideration of the FAA Decisionmaker's Final order in the proceeding; (3) If no petition for reconsideration is filed, the last date on which such a petition could have been filed; or (4) Issuance of a final order or any other final resolution of a proceeding, such as a settlement or voluntary dismissal, which is not subject to a petition for reconsideration. </SECTION> <SECTION> <SECTNO>§ 14.21</SECTNO> <SUBJECT>Filing and service of documents.</SUBJECT> Any application for an award or other pleading or document related to an application shall be filed and served on all parties to the proceeding in the same manner as other pleadings in the proceeding, except as provided in § 14.11(b) for confidential financial information. </SECTION> <SECTION> <SECTNO>§ 14.22</SECTNO> <SUBJECT>Answer to application.</SUBJECT> (a) Within 30 days after service of an application, counsel representing the agency against which an award is sought may file an answer to the application. Unless agency counsel requests an extension of time for filing or files a statement of intent to negotiate under paragraph (b) of the section, failure to file an answer within the 30-day period may be treated as a consent to the award requested.<PRTPAGE P="77"/> (b) If agency counsel and the applicant believe that the issues in the fee application can be settled, they may jointly file a statement of their intent to negotiate a settlement. The filing of this statement shall extend the time for filing an answer for an additional 30 days, and further extensions may be granted by the administrative law judge upon request by agency counsel and the applicant. (c) The answer shall explain in detail any objections to the award requested and identify the facts relied on in support of agency counsel's position. If the answer is based on any alleged facts not already in the record of the proceeding, agency counsel shall include with the answer either supporting affidavits or a request for further proceedings under § 14.26. </SECTION> <SECTION> <SECTNO>§ 14.23</SECTNO> <SUBJECT>Reply.</SUBJECT> Within 15 days after service of an answer, the applicant may file a reply. If the reply is based on any alleged facts not already in the record of the proceeding, the applicant shall include with the reply either supporting affidavits or a request for further proceedings under § 14.26. </SECTION> <SECTION> <SECTNO>§ 14.24</SECTNO> <SUBJECT>Comments by other parties.</SUBJECT> Any party to a proceeding other than the applicant and agency counsel may file comments on an application within 30 days after it is served or on an answer within 15 days after it is served. A commenting party may not participate further in proceedings on the application unless the administrative law judge determines that the public interest requires such participation in order to permit full exploration of matters raised in the comments. </SECTION> <SECTION> <SECTNO>§ 14.25</SECTNO> <SUBJECT>Settlement.</SUBJECT> The applicant and agency counsel may agree on a proposed settlement of the award before final action on the application, either in connection with a settlement of the underlying proceeding, or after the underlying proceeding has been concluded. If a prevailing party and agency counsel agree on a proposed settlement of an award before an application has been filed, the application shall be filed with the proposed settlement. </SECTION> <SECTION> <SECTNO>§ 14.26</SECTNO> <SUBJECT>Further proceedings.</SUBJECT> (a) Ordinarily the determination of an award will be made on the basis of the written record; however, on request of either the applicant or agency counsel, or on his or her own initiative, the administrative law judge assigned to the matter may order further proceedings, such as an informal conference, oral argument, additional written submissions, or an evidentiary hearing. Such further proceedings shall be held only when necessary for full and fair resolution of the issues arising from the application and shall be conducted as promptly as possible. (b) A request that the administrative law judge order further proceedings under this section shall specifically identify the information sought or the disputed issues and shall explain why the additional proceedings are necessary to resolve the issues. </SECTION> <SECTION> <SECTNO>§ 14.27</SECTNO> <SUBJECT>Decision.</SUBJECT> The administrative law judge shall issue an initial decision on the application within 60 days after completion of proceedings on the application. The decision shall include written findings and conclusions on the applicant's eligibility and status as a prevailing party and an explanation of the reasons for any difference between the amount requested and the amount awarded. The decision shall also include, if at issue, findings on whether the agency's position was substantially justified, whether the applicant unduly protracted the proceedings, or whether special circumstances make an award unjust. </SECTION> <SECTION> <SECTNO>§ 14.28</SECTNO> <SUBJECT>Review by FAA Decisionmaker.</SUBJECT> Either the applicant or the FAA counsel may seek review of the initial decision on the fee application in accordance with subpart G of part 13 of the Federal Aviation Regulations, specifically 14 CFR 13.233. Additionally, the FAA Decisionmaker may decide to review the decision on its own initiative. If neither the applicant nor the agency counsel seeks review within 30 days after the decision is issued, it shall become final. Whether to review a decision is a matter within the discretion of the FAA Decisionmaker. If review is taken, the FAA Decisionmaker <PRTPAGE P="78"/>will issue a final decision on the application or remand the application to the administrative law judge who issued the initial fee award determination for further proceedings. </SECTION> <SECTION> <SECTNO>§ 14.29</SECTNO> <SUBJECT>Judicial review.</SUBJECT> If an applicant is dissatisfied with the determination of fees and other expenses made under this subsection, pursuant 5 U.S.C. 504(c)(2), that applicant may, within thirty (30) days after the determination is made, appeal the determination to the court of the United States having jurisdiction to review the merits of the underlying decision of the FAA adversary adjudication. The court's determination on any appeal heard under this paragraph shall be based solely on the factual record made before the FAA. The court may modify the determination of fees and other expenses only if the court finds that the failure to make an award of fees and other expenses, or the calculation of the amount of the award, was unsupported by substantial evidence. </SECTION> <SECTION> <SECTNO>§ 14.30</SECTNO> <SUBJECT>Payment of award.</SUBJECT> An applicant seeking payment of an award shall submit to the disbursing official of the FAA a copy of the FAA Decisionmaker's final decision granting the award, accompanied by a statement that the applicant will not seek review of the decision in the United States courts. Applications for award grants in cases involving the FAA shall be sent to: The Office of Accounting and Audit, AAA-1, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591. The agency will pay the amount awarded to the applicant within 60 days, unless judicial review of the award or of the underlying decision of the adversary adjudication has been sought by the applicant or any other party to the proceeding. </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 15</EAR> <HD SOURCE="HED">PART 15—ADMINISTRATIVE CLAIMS UNDER FEDERAL TORT CLAIMS ACT</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—General Procedures</HD> <SECHD>Sec.</SECHD> <SECTNO>15.1</SECTNO> <SUBJECT>Scope of regulations.</SUBJECT> <SECTNO>15.3</SECTNO> <SUBJECT>Administrative claim, when presented; appropriate office.</SUBJECT> <SECTNO>15.5</SECTNO> <SUBJECT>Administrative claim, who may file.</SUBJECT> <SECTNO>15.7</SECTNO> <SUBJECT>Administrative claims; evidence and information to be submitted.</SUBJECT> <SECTNO>15.9</SECTNO> <SUBJECT>Investigation and examination.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Indemnification Under Section 1118 of the Federal Aviation Act of 1958</HD> <SECTNO>15.101</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>15.103</SECTNO> <SUBJECT>Exclusions.</SUBJECT> <SECTNO>15.105</SECTNO> <SUBJECT>Filing of requests for indemnification.</SUBJECT> <SECTNO>15.107</SECTNO> <SUBJECT>Notification requirements.</SUBJECT> <SECTNO>15.109</SECTNO> <SUBJECT>Settlements.</SUBJECT> <SECTNO>15.111</SECTNO> <SUBJECT>Conduct of litigation.</SUBJECT> <SECTNO>15.113</SECTNO> <SUBJECT>Indemnification agreements.</SUBJECT> <SECTNO>15.115</SECTNO> <SUBJECT>Payment.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 5 U.S.C. 301; 28 U.S.C. 2672, 2675; 49 U.S.C. 106(g), 40113, 44721. </AUTH> <SUBPART> <HD SOURCE="HED">Subpart A—General Procedures</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 25264, 52 FR 18171, May 13, 1987, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 15.1</SECTNO> <SUBJECT>Scope of regulations.</SUBJECT> (a) These regulations apply to claims asserted under the Federal Tort Claims Act, as amended, for money damages against the United States for injury to, or loss of property, or for personal injury or death, caused by the negligent or wrongful act or omission of an employee of the FAA acting within the scope of office or employment. The regulations in this part supplement the Attorney General's regulations in 28 CFR Part 14, as amended. The regulations in 28 CFR Part 14, as amended, and the regulations in this part apply to consideration by the FAA of administrative claims under the Federal Tort Claims Act. </SECTION> <SECTION> <SECTNO>§ 15.3</SECTNO> <SUBJECT>Administrative claim, when presented; appropriate office.</SUBJECT> (a) A claim is deemed to have been presented when the FAA receives, at a place designated in paragraph (b) of this section, an executed Standard Form 95 or other written notification of an incident, accompanied by a claim for money damages in a sum certain for injury to, or loss of, property or for personal injury or death, alleged to have occurred by reason of the incident. A claim which should have been presented to the FAA but which was mistakenly filed with another Federal <PRTPAGE P="79"/>agency, is deemed presented to the FAA on the date the claim is received by the FAA at a place designated in paragraph (b) of this section. A claim addressed to, or filed with, the FAA by mistake will be transferred to the appropriate Federal agency, if that agency can be determined, or returned to the claimant. (b) Claims shall be delivered or mailed to the Assistant Chief Counsel, Litigation Division, AGC-400, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591, or alternatively, may be mailed or delivered to the Regional Counsel in any of the FAA Regional Offices or the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office. (d) A claim presented in accordance with this section may be amended by the claimant at any time prior to final FAA action or prior to the exercise of the claimant's option, under 28 U.S.C. 2675(a), to deem the agency's failure to make a final disposition of his or her claim within 6 months after it was filed as a final denial. Each amendment to a claim shall be submitted in writing and signed by the claimant or the claimant's duly authorized agent or legal representative. Upon the timely filing of an amendment to a pending claim, the FAA has 6 months thereafter in which to make a final disposition of the claim as amended, and the claimant's option under 28 U.S.C. 2675(a) does not accrue until 6 months after the filing of the amendment. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 15-1, 54 FR 39290, Sept. 25, 1989; Amdt. 15-4, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 15.5</SECTNO> <SUBJECT>Administrative claim, who may file.</SUBJECT> (a) A claim for injury to, or loss of, property may be presented by the owner of the property interest which is the subject of the claim or by the owner's duly authorized agent or legal representative. (b) A claim for personal injury may be presented by the injured person or that person's duly authorized agent or legal representative. (c) A claim based on death may be presented by the executor or administrator of the decedent's estate or by any other person legally entitled to assert such a claim under applicable State law. (d) A claim for loss wholly compensated by an insurer with the rights of a subrogee may be presented by the insurer. A claim for loss partially compensated by an insurer with the rights of a subrogee may be presented by the insurer or the insured individually, as their respective interest appear, or jointly. Whenever an insurer presents a claim asserting the rights of a subrogee, it shall present with its claim appropriate evidence that it has the rights of a subrogee. (e) A claim presented by an agent or legal representative shall be presented in the name of the claimant, be signed by the agent or legal representative, show the title or legal capacity of the person signing, and be accompanied by evidence of authority to present a claim on behalf of the claimant as agent, executor, administrator, parent, guardian, or other representative. </SECTION> <SECTION> <SECTNO>§ 15.7</SECTNO> <SUBJECT>Administrative claims; evidence and information to be submitted.</SUBJECT> (a) <E T="03">Death.</E> In support of a claim based on death, the claimant may be required to submit the following evidence or information: (1) An authenticated death certificate or other competent evidence showing cause of death, date of death, and age of the decedent. (2) The decedent's employment or occupation at time of death, including monthly or yearly salary or earnings (if any), and the duration of last employment or occupation. (3) Full names, addresses, birth dates, kinship, and marital status of the decedent's survivors, including identification of those survivors who were dependent for support upon the decedent at the time of death. (4) Degree of support afforded by the decedent to each survivor dependent upon decedent for support at the time of death. (5) Decedent's general, physical, and mental conditions before death. (6) Itemized bills for medical and burial expenses incurred by reason of the incident causing death or itemized receipts of payment for such expenses.<PRTPAGE P="80"/> (7) If damages for pain and suffering prior to death are claimed, a physician's detailed statement specifying the injuries suffered, duration of pain and suffering, any drugs administered for pain, and the decedent's physical condition in the interval between injury and death. (8) Any other evidence or information which may have a bearing on either the responsibility of the United States for the death or the amount of damages claimed. (b) <E T="03">Personal injury.</E> In support of a claim for personal injury, including pain and suffering, the claimant may be required to submit the following evidence or information: (1) A written report by the attending physician or dentist setting forth the nature and extent of the injuries, nature and extent of treatment, any degree of temporary or permanent disability, the prognosis, period of hospitalization, and any diminished earning capacity. (2) In addition to the report required by paragraph (b)(1) of this section, the claimant may be required to submit to a physical or mental examination by a physician employed by the FAA or another Federal agency. A copy of the report of the examining physician is made available to the claimant upon the claimant's written request if the claimant has, upon request, furnished the report required by paragraph (b)(1), and has made or agrees to make available to the FAA any other physician's reports previously or thereafter made on the physical or mental condition which is the subject matter of the claim. (3) Itemized bills for medical, dental, and hospital expenses incurred or itemized receipts of payment for such expenses. (4) If the prognosis reveals the necessity for future treatment, a statement of expected expenses for such treatment. (5) If a claim is made for loss of time from employment, a written statement from the claimant's employer showing actual time lost from employment, whether the claimant is a full or part-time employee, and wages or salary actually lost. (6) If a claim is made for loss of income and the claimant is self-employed, documentary evidence showing the amount of earnings actually lost. (7) Any other evidence or information which may have a bearing on the responsibility of the United States for the personal injury or the damages claimed. (c) <E T="03">Property damage.</E> In support of a claim for injury to or loss of property, real or personal, the claimant may be required to submit the following evidence or information: (1) Proof of ownership of the property interest which is the subject of the claim. (2) A detailed statement of the amount claimed with respect to each item of property. (3) An itemized receipt of payment for necessary repairs or itemized written estimates of the cost of such repairs. (4) A statement listing date of purchase, purchase price, and salvage value, where repair is not economical. (5) Any other evidence or information which may have a bearing on either the responsibility of the United States for the injury to or loss of property or the damages claimed. </SECTION> <SECTION> <SECTNO>§ 15.9</SECTNO> <SUBJECT>Investigation and examination.</SUBJECT> The FAA may investigate a claim or conduct a physical examination of a claimant. The FAA may request any other Federal agency to investigate a claim or conduct a physical examination of a claimant and provide a report of the investigation or examination to the FAA. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Indemnification Under Section 1118 of the Federal Aviation Act of 1958</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 15-2, 55 FR 18710, May 3, 1990, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 15.101</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the indemnification of a publisher of aeronautical charts or maps under section 1118 of the Federal Aviation Act of 1958, as amended, when the publisher incurs liability as a result of publishing—<PRTPAGE P="81"/> (a) A chart or map accurately depicting a defective or deficient flight procedure or airway that was promulgated by the FAA; or (b) Aeronautical data that— (1) Is visually displayed in the cockpit of an aircraft; and (2) When visually displayed, accurately depicts a defective or deficient flight procedure or airway promulgated by the FAA. </SECTION> <SECTION> <SECTNO>§ 15.103</SECTNO> <SUBJECT>Exclusions.</SUBJECT> A publisher that requests indemnification under this part will not be indemnified if— (a) The complaint filed against the publisher, or demand for payment against the publisher, first occurred before December 19, 1985; (b) The publisher does not negotiate a good faith settlement; (c) The publisher does not conduct a good faith defense; (d) The defective or deficient flight procedure or airway— (1) Was not promulgated by the FAA; (2) Was not accurately depicted on the publisher's chart or map; (3) Was not accurately displayed on a visual display in the cockpit, or (4) Was obviously defective or deficient; (e) The publisher does not give notice as required by § 15.107 of this part and that failure is prejudicial to the Government; or (f) The publisher does not appeal a lower court's decision pursuant to a request by the Administrator under § 15.111(d)(2) of this part. </SECTION> <SECTION> <SECTNO>§ 15.105</SECTNO> <SUBJECT>Filing of requests for indemnification.</SUBJECT> A request for indemnification under this part— (a) May be filed by— (1) A publisher described in § 15.101 of this part; or (2) The publisher's duly authorized agent or legal representative; (b) Shall be filed with the Chief Counsel, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; and (c) Shall state the basis for the publisher's assertion that indemnification under this part is required. </SECTION> <SECTION> <SECTNO>§ 15.107</SECTNO> <SUBJECT>Notification requirements.</SUBJECT> A request for indemnification will not be considered by the FAA unless the following conditions are met: (a) The publisher must notify the Chief Counsel of the FAA, within the time limits prescribed in paragraph (b) or (c) of this section, of the publisher's first receipt of a demand for payment, or service of a complaint in any proceeding, federal or state, in which it appears that indemnification under this part may be required. (b) For each complaint filed, or demand for payment made, on or after December 19, 1985, and before June 4, 1990, the notice required by paragraph (a) of this section must be received by the FAA on or before July 2, 1990. (c) For each complaint filed, or demand for payment made, on or after June 4, 1990, the notice required by paragraph (a) of this section must be received by the FAA within 60 days after the day the publisher first receives the demand for payment or service of the complaint. (d) Within 5 days after the day a judgment is rendered against the publisher in any proceeding, or within 30 days of the denial of an appeal, whichever is later, the publisher must notify the FAA Chief Counsel that— (1) There is an adverse judgment against the publisher; and (2) The publisher has a claim for indemnification against the FAA arising out of that judgment. </SECTION> <SECTION> <SECTNO>§ 15.109</SECTNO> <SUBJECT>Settlements.</SUBJECT> (a) A publisher may not settle a claim with another party, for which the publisher has sought, or intends to seek, indemnification under this part, unless— (1) The publisher submits a copy of the proposed settlement, and a statement justifying the settlement, to the Chief Counsel of the FAA; and (2) The Administrator and where necessary, the appropriate official of the Department of Justice, approves the proposed settlement. (3) The publisher submits a signed release that clearly releases the United States from any further liability to the publisher and the claimant.<PRTPAGE P="82"/> (b) If the Administrator does not approve the proposed settlement, the Administrator will— (1) So notify the publisher by registered mail within 60 days of receipt of the proposed settlement; and (2) Explain why the request for indemnification was not approved. (c) If the Administrator approves the proposed settlement, the Administrator will so notify the publisher by registered mail within 60 days after the FAA's receipt of the proposed settlement. (d) If the Administrator does not have sufficient information to approve or disapprove the proposed settlement, the Administrator will request, within 60 days after receipt of the proposed settlement, the additional information needed to make a determination. </SECTION> <SECTION> <SECTNO>§ 15.111</SECTNO> <SUBJECT>Conduct of litigation.</SUBJECT> (a) If a lawsuit is filed against the publisher and the publisher has sought, or intends to seek, indemnification under this part, the publisher shall— (1) Give notice as required by § 15.107 of this part; (2) If requested by the United States— (i) Implead the United States as a third-party defendant in the action; and (ii) Arrange for the removal of the action to Federal Court; (3) Promptly provide any additional information requested by the United States; and (4) Cooperate with the United States in the defense of the lawsuit. (b) If the lawsuit filed against the publisher results in a proposed settlement, the publisher shall submit that proposed settlement to the FAA for approval in accordance with § 15.109 of this part. (c) If the lawsuit filed against the publisher results in a judgment against the publisher and the publisher has sought, or intends to seek, indemnification under this part as a result of the adverse judgment, the publisher shall— (1) Give notice to the FAA as required by § 15.107(d) of this part; (2) Submit a copy of the trial court's decision to the FAA Chief Counsel not more than 5 business days after the adverse judgment is rendered; and (3) If an appeal is taken from the adverse judgment, submit a copy of the appellate decision to the FAA Chief Counsel not more than 30 days after that decision is rendered. (d) Within 60 days after receipt of the trial court's decision, the Administrator by registered mail will— (1) Notify the publisher that indemnification is required under this part; (2) Request that the publisher appeal the trial court's adverse decision; or (3) Notify the publisher that it is not entitled to indemnification under this part and briefly state the basis for the denial. </SECTION> <SECTION> <SECTNO>§ 15.113</SECTNO> <SUBJECT>Indemnification agreements.</SUBJECT> (a) Upon a finding of the Administrator that indemnification is required under this part, and after obtaining the concurrence of the United States Department of Justice, the FAA will promptly enter into an indemnification agreement providing for the payment of the costs specified in paragraph (c) of this section. (b) The indemnification agreement will be signed by the Chief Counsel and the publisher. (c) The FAA will indemnify the publisher for— (1) Compensatory damages awarded by the court against the publisher; (2) Reasonable costs and fees, including reasonable attorney fees at a rate not to exceed that permitted under the Equal Access to Justice Act (5 U.S.C. 504), and any postjudgment interest, if the publisher conducts a good faith defense, or pursues a good faith appeal, at the request, or with the concurrence, of the FAA. (d) Except as otherwise provided in this section, the FAA will not indemnify the publisher for— (1) Punitive or exemplary damages; (2) Civil or criminal fines or any other litigation sanctions; (3) Postjudgment interest; (4) Costs; (5) Attorney fees; or (6) Other incidental expenses. (e) The indemnification agreement must provide that the Government will be subrogated to all claims or rights of the publisher, including third-party <PRTPAGE P="83"/>claims, cross-claims, and counterclaims. </SECTION> <SECTION> <SECTNO>§ 15.115</SECTNO> <SUBJECT>Payment.</SUBJECT> After execution of the indemnification agreement, the FAA will submit the agreement to the United States Department of Justice and request payment, in accordance with the agreement, from the Judgment Fund. </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 16</EAR> <HD SOURCE="HED">PART 16—RULES OF PRACTICE FOR FEDERALLY-ASSISTED AIRPORT ENFORCEMENT PROCEEDINGS</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—General Provisions</HD> <SECHD>Sec.</SECHD> <SECTNO>16.1</SECTNO> <SUBJECT>Applicability and description of part.</SUBJECT> <SECTNO>16.3</SECTNO> <SUBJECT>Definitions.</SUBJECT> <SECTNO>16.5</SECTNO> <SUBJECT>Separation of functions.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—General Rules Applicable to Complaints, Proceedings Initiated by the FAA, and Appeals</HD> <SECTNO>16.11</SECTNO> <SUBJECT>Expedition and other modification of process.</SUBJECT> <SECTNO>16.13</SECTNO> <SUBJECT>Filing of documents.</SUBJECT> <SECTNO>16.15</SECTNO> <SUBJECT>Service of documents on the parties and the agency.</SUBJECT> <SECTNO>16.17</SECTNO> <SUBJECT>Computation of time.</SUBJECT> <SECTNO>16.19</SECTNO> <SUBJECT>Motions.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Special Rules Applicable to Complaints</HD> <SECTNO>16.21</SECTNO> <SUBJECT>Pre-complaint resolution.</SUBJECT> <SECTNO>16.23</SECTNO> <SUBJECT>Complaints, answers, replies, rebuttals, and other documents.</SUBJECT> <SECTNO>16.25</SECTNO> <SUBJECT>Dismissals.</SUBJECT> <SECTNO>16.27</SECTNO> <SUBJECT>Incomplete complaints.</SUBJECT> <SECTNO>16.29</SECTNO> <SUBJECT>Investigations.</SUBJECT> <SECTNO>16.31</SECTNO> <SUBJECT>Director's determinations after investigations.</SUBJECT> <SECTNO>16.33</SECTNO> <SUBJECT>Final decisions without hearing.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Special Rules Applicable to Proceedings Initiated by the FAA</HD> <SECTNO>16.101</SECTNO> <SUBJECT>Basis for the initiation of agency action.</SUBJECT> <SECTNO>16.103</SECTNO> <SUBJECT>Notice of investigation.</SUBJECT> <SECTNO>16.105</SECTNO> <SUBJECT>Failure to resolve informally.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Proposed Orders of Compliance</HD> <SECTNO>16.109</SECTNO> <SUBJECT>Orders terminating eligibility for grants, cease and desist orders, and other compliance orders.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Hearings</HD> <SECTNO>16.201</SECTNO> <SUBJECT>Notice and order of hearing.</SUBJECT> <SECTNO>16.202</SECTNO> <SUBJECT>Powers of a hearing officer.</SUBJECT> <SECTNO>16.203</SECTNO> <SUBJECT>Appearances, parties, and rights of parties.</SUBJECT> <SECTNO>16.207</SECTNO> <SUBJECT>Intervention and other participation.</SUBJECT> <SECTNO>16.209</SECTNO> <SUBJECT>Extension of time.</SUBJECT> <SECTNO>16.211</SECTNO> <SUBJECT>Prehearing conference.</SUBJECT> <SECTNO>16.213</SECTNO> <SUBJECT>Discovery.</SUBJECT> <SECTNO>16.215</SECTNO> <SUBJECT>Depositions.</SUBJECT> <SECTNO>16.217</SECTNO> <SUBJECT>Witnesses.</SUBJECT> <SECTNO>16.219</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> <SECTNO>16.221</SECTNO> <SUBJECT>Witness fees.</SUBJECT> <SECTNO>16.223</SECTNO> <SUBJECT>Evidence.</SUBJECT> <SECTNO>16.225</SECTNO> <SUBJECT>Public disclosure of evidence.</SUBJECT> <SECTNO>16.227</SECTNO> <SUBJECT>Standard of proof.</SUBJECT> <SECTNO>16.229</SECTNO> <SUBJECT>Burden of proof.</SUBJECT> <SECTNO>16.231</SECTNO> <SUBJECT>Offer of proof.</SUBJECT> <SECTNO>16.233</SECTNO> <SUBJECT>Record.</SUBJECT> <SECTNO>16.235</SECTNO> <SUBJECT>Argument before the hearing officer.</SUBJECT> <SECTNO>16.237</SECTNO> <SUBJECT>Waiver of procedures.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Initial Decisions, Orders and Appeals</HD> <SECTNO>16.241</SECTNO> <SUBJECT>Initial decisions, orders, and appeals.</SUBJECT> <SECTNO>16.243</SECTNO> <SUBJECT>Consent orders.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Judicial Review</HD> <SECTNO>16.247</SECTNO> <SUBJECT>Judicial review of a final decision and order.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart I—Ex Parte Communications</HD> <SECTNO>16.301</SECTNO> <SUBJECT>Definitions.</SUBJECT> <SECTNO>16.303</SECTNO> <SUBJECT>Prohibited ex parte communications.</SUBJECT> <SECTNO>16.305</SECTNO> <SUBJECT>Procedures for handling ex parte communications.</SUBJECT> <SECTNO>16.307</SECTNO> <SUBJECT>Requirement to show cause and imposition of sanction.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 49 U.S.C. 106(g), 322, 1110, 1111, 1115, 1116, 1718 (a) and (b), 1719, 1723, 1726, 1727, 40103(e), 40113, 40116, 44502(b), 46101, 46104, 46110, 47104, 47106(e), 47107, 47108, 47111(d), 47122, 47123-47125, 47151-47153, 48103. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 27783, 61 FR 54004, October 16, 1996, unless otherwise noted. </SOURCE> <SUBPART> <HD SOURCE="HED">Subpart A—General Provisions</HD> <SECTION> <SECTNO>§ 16.1</SECTNO> <SUBJECT>Applicability and description of part.</SUBJECT> (a) <E T="03">General.</E> The provisions of this part govern all proceedings involving Federally-assisted airports, except for disputes between U.S. and foreign air carriers and airport proprietors concerning the reasonableness of airport fees covered by 14 CFR part 302, whether the proceedings are instituted by order of the FAA or by filing with the FAA a complaint, under the following authorities: (1) 49 U.S.C. 40103(e), prohibiting the grant of exclusive rights for the use of <PRTPAGE P="84"/>any landing area or air navigation facility on which Federal funds have been expended (formerly section 308 of the Federal Aviation Act of 1958, as amended). (2) Requirements of the Anti-Head Tax Act, 49 U.S.C. 40116. (3) The assurances contained in grant-in-aid agreements issued under the Federal Airport Act of 1946, 49 U.S.C. 1101 <E T="03">et seq</E> (repealed 1970). (4) The assurances contained in grant-in-aid agreements issued under the Airport and Airway Development Act of 1970, as amended, 49 U.S.C. 1701 <E T="03">et seq.</E> (5) The assurances contained in grant-in-aid agreements issued under the Airport and Airway Improvement Act of 1982 (AAIA), as amended, 49 U.S.C. 47101 <E T="03">et seq.,</E> specifically section 511(a), 49 U.S.C. 47107(a) and (b). (6) Section 505(d) of the Airport and Airway Improvement Act of 1982, as amended, 49 U.S.C. 47113. (7) Obligations contained in property deeds for property transferred pursuant to section 16 of the Federal Airport Act (49 U.S.C. 1115), section 23 of the Airport and Airway Development Act (49 U.S.C. 1723), or section 516 of the Airport and Airway Improvement Act (49 U.S.C. 47125). (8) Obligations contained in property deeds for property transferred under the Surplus Property Act (49 U.S.C. 47151-47153). (b) <E T="03">Other agencies.</E> Where a grant assurance concerns a statute, executive order, regulation, or other authority that provides an administrative process for the investigation or adjudication of complaints by a Federal agency other than the FAA, persons shall use the administrative process established by those authorities. Where a grant assurance concerns a statute, executive order, regulation, or other authority that enables a Federal agency other than the FAA to investigate, adjudicate, and enforce compliance under those authorities on its own initiative, the FAA may defer to that Federal agency. (c) <E T="03">Other enforcement.</E> If a complaint or action initiated by the FAA involves a violation of the 49 U.S.C. subtitle VII or FAA regulations, except as specified in paragraphs (a)(1) and (a)(2) of this section, the FAA may take investigative and enforcement action under 14 CFR part 13, “Investigative and Enforcement Procedures.” (d) <E T="03">Effective date.</E> This part applies to a complaint filed with the FAA and to an investigation initiated by the FAA on or after December 16, 1996. </SECTION> <SECTION> <SECTNO>§ 16.3</SECTNO> <SUBJECT>Definitions.</SUBJECT> Terms defined in the Acts are used as so defined. As used in this part: <E T="03">Act</E> means a statute listed in § 16.1 and any regulation, agreement, or document of conveyance issued or made under that statute. <E T="03">Agency attorney</E> means the Deputy Chief Counsel; the Assistant Chief Counsel and attorneys in the Airports/Environmental Law Division of the Office of the Chief Counsel; the Assistant Chief Counsel and attorneys in an FAA region or center who represent the FAA during the investigation of a complaint or at a hearing on a complaint, and who prosecute on behalf of the FAA, as appropriate. An agency attorney shall not include the Chief Counsel; the Assistant Chief Counsel for Litigation, or any attorney on the staff of the Assistant Chief Counsel for Litigation, who advises the Associate Administrator regarding an initial decision of the hearing officer or any appeal to the Associate Administrator or who is supervised in that action by a person who provides such advice in an action covered by this part. <E T="03">Agency employee</E> means any employee of the U.S. Department of Transportation. <E T="03">Associate Administrator</E> means the Associate Administrator for Airports or a designee. <E T="03">Complainant</E> means the person submitting a complaint. <E T="03">Complaint</E> means a written document meeting the requirements of this part filed with the FAA by a person directly and substantially affected by anything allegedly done or omitted to be done by any person in contravention of any provision of any Act, as defined in this section, as to matters within the jurisdiction of the Administrator. <E T="03">Director</E> means the Director of the Office of Airport Safety and Standards.<PRTPAGE P="85"/> <E T="03">Director's determination</E> means the initial determination made by the Director following an investigation, which is a non-final agency decision. <E T="03">File</E> means to submit written documents to the FAA for inclusion in the Part 16 Airport Proceedings Docket or to a hearing officer. <E T="03">Final decision and order</E> means a final agency decision that disposes of a complaint or determines a respondent's compliance with any Act, as defined in this section, and directs appropriate action. <E T="03">Hearing officer</E> means an attorney designated by the FAA in a hearing order to serve as a hearing officer in a hearing under this part. The following are not designated as hearing officers: the Chief Counsel and Deputy Chief Counsel; the Assistant Chief Counsel and attorneys in the FAA region or center in which the noncompliance has allegedly occurred or is occurring; the Assistant Chief Counsel and attorneys in the Airports and Environmental Law Division of the FAA Office of the Chief Counsel; and the Assistant Chief Counsel and attorneys in the Litigation Division of the FAA Office of Chief Counsel. <E T="03">Initial decision</E> means a decision made by the hearing officer in a hearing under subpart F of this part. <E T="03">Mail</E> means U.S. first class mail; U.S. certified mail; and U.S. express mail. <E T="03">Noncompliance</E> means anything done or omitted to be done by any person in contravention of any provision of any Act, as defined in this section, as to matters within the jurisdiction of the Administrator. <E T="03">Party</E> means the complainant(s) and the respondent(s) named in the complaint and, after an initial determination providing an opportunity for hearing is issued under § 16.31 and subpart E of this part, the agency. <E T="03">Person</E> in addition to its meaning under 49 U.S.C. 40102(a)(33), includes a public agency as defined in 49 U.S.C. 47102(a)(15). <E T="03">Personal delivery</E> means hand delivery or overnight express delivery service. <E T="03">Respondent</E> means any person named in a complaint as a person responsible for noncompliance. <E T="03">Sponsor</E> means: (1) Any public agency which, either individually or jointly with one or more other public agencies, has received Federal financial assistance for airport development or planning under the Federal Airport Act, Airport and Airway Development Act or Airport and Airway Improvement Act; (2) Any private owner of a public-use airport that has received financial assistance from the FAA for such airport; and (3) Any person to whom the Federal Government has conveyed property for airport purposes under section 13(g) of the Surplus Property Act of 1944, as amended. </SECTION> <SECTION> <SECTNO>§ 16.5</SECTNO> <SUBJECT>Separation of functions.</SUBJECT> (a) Proceedings under this part, including hearings under subpart F of this part, will be prosecuted by an agency attorney. (b) After issuance of an initial determination in which the FAA provides the opportunity for a hearing, an agency employee engaged in the performance of investigative or prosecutorial functions in a proceeding under this part will not, in that case or a factually related case, participate or give advice in an initial decision by the hearing officer, or a final decision by the Associate Administrator or designee on written appeal, and will not, except as counsel or as witness in the public proceedings, engage in any substantive communication regarding that case or a related case with the hearing officer, the Associate Administrator on written appeal, or agency employees advising those officials in that capacity. (c) The Chief Counsel, the Assistant Chief Counsel for Litigation, or an attorney on the staff of the Assistant Chief Counsel for Litigation advises the Associate Administrator regarding an initial decision, an appeal, or a final decision regarding any case brought under this part. </SECTION> </SUBPART> <SUBPART> <PRTPAGE P="86"/> <HD SOURCE="HED">Subpart B—General Rules Applicable to Complaints, Proceedings Initiated by the FAA, and Appeals</HD> <SECTION> <SECTNO>§ 16.11</SECTNO> <SUBJECT>Expedition and other modification of process.</SUBJECT> (a) Under the authority of 49 U.S.C. 40113 and 47121, the Director may conduct investigations, issue orders, and take such other actions as are necessary to fulfill the purposes of this part, including the extension of any time period prescribed where necessary or appropriate for a fair and complete hearing of matters before the agency. (b) Notwithstanding any other provision of this part, upon finding that circumstances require expedited handling of a particular case or controversy, the Director may issue an order directing any of the following prior to the issuance of the Director's determination: (1) Shortening the time period for any action under this part consistent with due process; (2) If other adequate opportunity to respond to pleadings is available, eliminating the reply, rebuttal, or other actions prescribed by this part; (3) Designating alternative methods of service; or (4) Directing such other measures as may be required. </SECTION> <SECTION> <SECTNO>§ 16.13</SECTNO> <SUBJECT>Filing of documents.</SUBJECT> Except as otherwise provided in this part, documents shall be filed with the FAA during a proceeding under this part as follows: (a) <E T="03">Filing address.</E> Documents to be filed with the FAA shall be filed with the Office of the Chief Counsel, Attention: FAA Part 16 Airport Proceedings Docket, AGC-610, Federal Aviation Administration, 800 Independence Ave., SW., Washington, DC, 20591. Documents to be filed with a hearing officer shall be filed at the address stated in the hearing order. (b) <E T="03">Date and method of filing.</E> Filing of any document shall be by personal delivery or mail as defined in this part, or by facsimile (when confirmed by filing on the same date by one of the foregoing methods). Unless the date is shown to be inaccurate, documents to be filed with the FAA shall be deemed to be filed on the date of personal delivery, on the mailing date shown on the certificate of service, on the date shown on the postmark if there is no certificate of service, on the send date shown on the facsimile (provided filing has been confirmed through one of the foregoing methods), or on the mailing date shown by other evidence if there is no certificate of service and no postmark. (c) <E T="03">Number of copies.</E> Unless otherwise specified, an executed original and three copies of each document shall be filed with the FAA Part 16 Airport Proceedings Docket. Copies need not be signed, but the name of the person signing the original shall be shown. If a hearing order has been issued in the case, one of the three copies shall be filed with the hearing officer. If filing by facsimile, the facsimile copy does not constitute one of the copies required under this section. (d) <E T="03">Form.</E> Documents filed with the FAA shall be typewritten or legibly printed. In the case of docketed proceedings, the document shall include the docket number of the proceeding on the front page. (e) <E T="03">Signing of documents and other papers.</E> The original of every document filed shall be signed by the person filing it or the person's duly authorized representative. The signature shall serve as a certification that the signer has read the document and, based on reasonable inquiry and to the best of the signer's knowledge, information, and belief, the document is— (1) Consistent with this part; (2) Warranted by existing law or that a good faith argument exists for extension, modification, or reversal of existing law; and (3) Not interposed for any improper purpose, such as to harass or to cause unnecessary delay or needless increase in the cost of the administrative process. (f) <E T="03">Designation of person to receive service.</E> The initial document filed by any person shall state on the first page the name, post office address, telephone number, and facsimile number, if any, of the person(s) to be served with documents in the proceeding. If any of these items change during the proceeding, the person shall promptly file notice of <PRTPAGE P="87"/>the change with the FAA Part 16 Airport Proceedings Docket and the hearing officer and shall serve the notice on all parties. (g) <E T="03">Docket numbers.</E> Each submission identified as a complaint under this part by the submitting person will be assigned a docket number. </SECTION> <SECTION> <SECTNO>§ 16.15</SECTNO> <SUBJECT>Service of documents on the parties and the agency.</SUBJECT> Except as otherwise provided in this part, documents shall be served as follows: (a) <E T="03">Who must be served.</E> Copies of all documents filed with the FAA Part 16 Airport Proceedings Docket shall be served by the persons filing them on all parties to the proceeding. A certificate of service shall accompany all documents when they are tendered for filing and shall certify concurrent service on the FAA and all parties. Certificates of service shall be in substantially the following form: <EXTRACT> I hereby certify that I have this day served the foregoing [name of document] on the following persons at the following addresses and facsimile numbers (if also served by facsimile) by [specify method of service]: <FP>[list persons, addresses, facsimile numbers]</FP> Dated this <E T="72">___</E> day of <E T="72">___</E>, 19<E T="72">__</E>. <FP>[signature], for [party]</FP> </EXTRACT> (b) <E T="03">Method of service.</E> Except as otherwise agreed by the parties and the hearing officer, the method of service is the same as set forth in § 16.13(b) for filing documents. (c) <E T="03">Where service shall be made.</E> Service shall be made to the persons identified in accordance with § 16.13(f). If no such person has been designated, service shall be made on the party. (d) <E T="03">Presumption of service.</E> There shall be a presumption of lawful service— (1) When acknowledgment of receipt is by a person who customarily or in the ordinary course of business receives mail at the address of the party or of the person designated under § 16.13(f); or (2) When a properly addressed envelope, sent to the most current address submitted under § 16.13(f), has been returned as undeliverable, unclaimed, or refused. (e) <E T="03">Date of service.</E> The date of service shall be determined in the same manner as the filing date under § 16.13(b). </SECTION> <SECTION> <SECTNO>§ 16.17</SECTNO> <SUBJECT>Computation of time.</SUBJECT> This section applies to any period of time prescribed or allowed by this part, by notice or order of the hearing officer, or by an applicable statute. (a) The date of an act, event, or default, after which a designated time period begins to run, is not included in a computation of time under this part. (b) The last day of a time period is included in a computation of time unless it is a Saturday, Sunday, or legal holiday for the FAA, in which case, the time period runs until the end of the next day that is not a Saturday, Sunday, or legal holiday. (c) Whenever a party has the right or is required to do some act within a prescribed period after service of a document upon the party, and the document is served on the party by mail, 3 days shall be added to the prescribed period. </SECTION> <SECTION> <SECTNO>§ 16.19</SECTNO> <SUBJECT>Motions.</SUBJECT> (a) <E T="03">General.</E> An application for an order or ruling not otherwise specifically provided for in this part shall be by motion. Unless otherwise ordered by the agency, the filing of a motion will not stay the date that any action is permitted or required by this part. (b) <E T="03">Form and contents.</E> Unless made during a hearing, motions shall be made in writing, shall state with particularity the relief sought and the grounds for the relief sought, and shall be accompanied by affidavits or other evidence relied upon. Motions introduced during hearings may be made orally on the record, unless the hearing officer directs otherwise. (c) <E T="03">Answers to motions.</E> Except as otherwise provided in this part, or except when a motion is made during a hearing, any party may file an answer in support of or in opposition to a motion, accompanied by affidavits or other evidence relied upon, provided that the answer to the motion is filed within 10 days after the motion has been served upon the person answering, or any other period set by the hearing officer. Where a motion is made during a hearing, the answer and the ruling thereon may be made at the hearing, or orally or in writing within the time set by the hearing officer. </SECTION> </SUBPART> <SUBPART> <PRTPAGE P="88"/> <HD SOURCE="HED">Subpart C—Special Rules Applicable to Complaints</HD> <SECTION> <SECTNO>§ 16.21</SECTNO> <SUBJECT>Pre-complaint resolution.</SUBJECT> (a) Prior to filing a complaint under this part, a person directly and substantially affected by the alleged noncompliance shall initiate and engage in good faith efforts to resolve the disputed matter informally with those individuals or entities believed responsible for the noncompliance. These efforts at informal resolution may include, without limitation, at the parties’ expense, mediation, arbitration, or the use of a dispute resolution board, or other form of third party assistance. The FAA Airports District Office, FAA Airports Field Office, or FAA Regional Airports Division responsible for administrating financial assistance to the respondent airport proprietor, will be available upon request to assist the parties with informal resolution. (b) A complaint under this part will not be considered unless the person or authorized representative filing the complaint certifies that substantial and reasonable good faith efforts to resolve the disputed matter informally prior to filing the complaint have been made and that there appears no reasonable prospect for timely resolution of the dispute. This certification shall include a brief description of the party's efforts to obtain informal resolution but shall not include information on monetary or other settlement offers made but not agreed upon in writing by all parties. </SECTION> <SECTION> <SECTNO>§ 16.23</SECTNO> <SUBJECT>Complaints, answers, replies, rebuttals, and other documents.</SUBJECT> (a) A person directly and substantially affected by any alleged noncompliance may file a complaint with the Administrator. A person doing business with an airport and paying fees or rentals to the airport shall be considered directly and substantially affected by alleged revenue diversion as defined in 49 U.S.C. 47107(b). (b) Complaints filed under this part shall— (1) State the name and address of each person who is the subject of the complaint and, with respect to each person, the specific provisions of each Act that the complainant believes were violated; (2) Be served, in accordance with § 16.15, along with all documents then available in the exercise of reasonable diligence, offered in support of the complaint, upon all persons named in the complaint as persons responsible for the alleged action(s) or omission(s) upon which the complaint is based; (3) Provide a concise but complete statement of the facts relied upon to substantiate each allegation; and (4) Describe how the complainant was directly and substantially affected by the things done or omitted to be done by the respondents. (c) Unless the complaint is dismissed pursuant to § 16.25 or § 16.27, the FAA notifies the complainant and respondents in writing within 20 days after the date the FAA receives the complaint that the complaint has been docketed and that respondents are required to file an answer within 20 days of the date of service of the notification. (d) The respondent shall file an answer within 20 days of the date of service of the FAA notification. (e) The complainant may file a reply within 10 days of the date of service of the answer. (f) The respondent may file a rebuttal within 10 days of the date of service of the complainant's reply. (g) The answer, reply, and rebuttal shall, like the complaint, be accompanied by supporting documentation upon which the parties rely. (h) The answer shall deny or admit the allegations made in the complaint or state that the person filing the document is without sufficient knowledge or information to admit or deny an allegation, and shall assert any affirmative defense. (i) The answer, reply, and rebuttal shall each contain a concise but complete statement of the facts relied upon to substantiate the answers, admissions, denials, or averments made. (j) The respondent's answer may include a motion to dismiss the complaint, or any portion thereof, with a supporting memorandum of points and authorities. If a motion to dismiss is filed, the complainant may respond as part of its reply notwithstanding the <PRTPAGE P="89"/>10-day time limit for answers to motions in § 16.19(c). </SECTION> <SECTION> <SECTNO>§ 16.25</SECTNO> <SUBJECT>Dismissals.</SUBJECT> Within 20 days after the receipt of the complaint, the Director will dismiss a complaint, or any claim made in a complaint, with prejudice if: (a) It appears on its face to be outside the jurisdiction of the Administrator under the Acts listed in § 16.1; (b) On its face it does not state a claim that warrants an investigation or further action by the FAA; or (c) The complainant lacks standing to file a complaint under §§ 16.3 and 16.23. The Director's dismissal will include the reasons for the dismissal. </SECTION> <SECTION> <SECTNO>§ 16.27</SECTNO> <SUBJECT>Incomplete complaints.</SUBJECT> If a complaint is not dismissed pursuant to § 16.25 of this part, but is deficient as to one or more of the requirements set forth in § 16.21 or § 16.23(b), the Director will dismiss the complaint within 20 days after receiving it. Dismissal will be without prejudice to the refiling of the complaint after amendment to correct the deficiency. The Director's dismissal will include the reasons for the dismissal. </SECTION> <SECTION> <SECTNO>§ 16.29</SECTNO> <SUBJECT>Investigations.</SUBJECT> (a) If, based on the pleadings, there appears to be a reasonable basis for further investigation, the FAA investigates the subject matter of the complaint. (b) The investigation may include one or more of the following, at the sole discretion of the FAA: (1) A review of the written submissions or pleadings of the parties, as supplemented by any informal investigation the FAA considers necessary and by additional information furnished by the parties at FAA request. In rendering its initial determination, the FAA may rely entirely on the complaint and the responsive pleadings provided under this subpart. Each party shall file documents that it considers sufficient to present all relevant facts and argument necessary for the FAA to determine whether the sponsor is in compliance. (2) Obtaining additional oral and documentary evidence by use of the agency's authority to compel production of such evidence under section 313 Aviation Act, 49 U.S.C. 40113 and 46104, and section 519 of the Airport and Airway Improvement Act, 49 U.S.C. 47122. The Administrator's statutory authority to issue compulsory process has been delegated to the Chief Counsel, the Deputy Chief Counsel, the Assistant Chief Counsel for Airports and Environmental Law, and each Assistant Chief Counsel for a region or center. (3) Conducting or requiring that a sponsor conduct an audit of airport financial records and transactions as provided in 49 U.S.C. 47107 and 47121. </SECTION> <SECTION> <SECTNO>§ 16.31</SECTNO> <SUBJECT>Director's determinations after investigations.</SUBJECT> (a) After consideration of the pleadings and other information obtained by the FAA after investigation, the Director will render an initial determination and provide it to each party by certified mail within 120 days of the date the last pleading specified in § 16.23 was due. (b) The Director's determination will set forth a concise explanation of the factual and legal basis for the Director's determination on each claim made by the complainant. (c) A party adversely affected by the Director's determination may appeal the initial determination to the Associate Administrator as provided in § 16.33. (d) If the Director's determination finds the respondent in noncompliance and proposes the issuance of a compliance order, the initial determination will include notice of opportunity for a hearing under subpart F of this part, if such an opportunity is provided by the FAA. The respondent may elect or waive a hearing as provided in subpart E of this part. </SECTION> <SECTION> <SECTNO>§ 16.33</SECTNO> <SUBJECT>Final decisions without hearing.</SUBJECT> (a) The Associate Administrator will issue a final decision on appeal from the Director's determination, without a hearing, where— (1) The complaint is dismissed after investigation; (2) A hearing is not required by statute and is not otherwise made available by the FAA; or<PRTPAGE P="90"/> (3) The FAA provides opportunity for a hearing to the respondent and the respondent waives the opportunity for a hearing as provided in subpart E of this part. (b) In the cases described in paragraph (a) of this section, a party adversely affected by the Director's determination may file an appeal with the Associate Administrator within 30 days after the date of service of the initial determination. (c) A reply to an appeal may be filed with the Associate Administrator within 20 days after the date of service of the appeal. (d) The Associate Administrator will issue a final decision and order within 60 days after the due date of the reply. (e) If no appeal is filed within the time period specified in paragraph (b) of this section, the Director's determination becomes the final decision and order of the FAA without further action. A Director's determination that becomes final because there is no administrative appeal is not judicially reviewable. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Special Rules Applicable to Proceedings Initiated by the FAA</HD> <SECTION> <SECTNO>§ 16.101</SECTNO> <SUBJECT>Basis for the initiation of agency action.</SUBJECT> The FAA may initiate its own investigation of any matter within the applicability of this part without having received a complaint. The investigation may include, without limitation, any of the actions described in § 16.29(b). </SECTION> <SECTION> <SECTNO>§ 16.103</SECTNO> <SUBJECT>Notice of investigation.</SUBJECT> Following the initiation of an investigation under § 16.101, the FAA sends a notice to the person(s) subject to investigation. The notice will set forth the areas of the agency's concern and the reasons therefor; request a response to the notice within 30 days of the date of service; and inform the respondent that the FAA will, in its discretion, invite good faith efforts to resolve the matter. </SECTION> <SECTION> <SECTNO>§ 16.105</SECTNO> <SUBJECT>Failure to resolve informally.</SUBJECT> If the matters addressed in the FAA notices are not resolved informally, the FAA may issue a Director's determination under § 16.31. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Proposed Orders of Compliance</HD> <SECTION> <SECTNO>§ 16.109</SECTNO> <SUBJECT>Orders terminating eligibility for grants, cease and desist orders, and other compliance orders.</SUBJECT> This section applies to initial determinations issued under § 16.31 that provide the opportunity for a hearing. (a) The agency will provide the opportunity for a hearing if, in the Director's determination, the agency proposes to issue an order terminating eligibility for grants pursuant to 49 U.S.C. 47106(e) and 47111(d), an order suspending the payment of grant funds, an order withholding approval of any new application to impose a passenger facility charge pursuant to section 112 of the Federal Aviation Administration Act of 1994, 49 U.S.C. 47111(e), a cease and desist order, an order directing the refund of fees unlawfully collected, or any other compliance order issued by the Administrator to carry out the provisions of the Acts, and required to be issued after notice and opportunity for a hearing. In cases in which a hearing is not required by statute, the FAA may provide opportunity for a hearing at its discretion. (b) In a case in which the agency provides the opportunity for a hearing, the Director's determination issued under § 16.31 will include a statement of the availability of a hearing under subpart F of this part. (c) Within 20 days after service of a Director's determination under § 16.31 and paragraph (b) of this section, a person subject to the proposed compliance order may— (1) Request a hearing under subpart F of this part; (2) Waive hearing and appeal the Director's determination in writing to the Associate Administrator, as provided in § 16.33; (3) File, jointly with a complainant, a motion to withdraw the complaint and to dismiss the proposed compliance action; or (4) Submit, jointly with the agency attorney, a proposed consent order under § 16.243(e).<PRTPAGE P="91"/> (d) If the respondent fails to request a hearing or to file an appeal in writing within the time periods provided in paragraph (c) of this section, the Director's determination becomes final. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Hearings</HD> <SECTION> <SECTNO>§ 16.201</SECTNO> <SUBJECT>Notice and order of hearing.</SUBJECT> (a) If a respondent is provided the opportunity for hearing in an initial determination and does not waive hearing, the Deputy Chief Counsel within 10 days after the respondent elects a hearing will issue and serve on the respondent and complainant a hearing order. The hearing order will set forth: (1) The allegations in the complaint, or notice of investigation, and the chronology and results of the investigation preliminary to the hearing; (2) The relevant statutory, judicial, regulatory, and other authorities; (3) The issues to be decided; (4) Such rules of procedure as may be necessary to supplement the provisions of this part; (5) The name and address of the person designated as hearing officer, and the assignment of authority to the hearing officer to conduct the hearing in accordance with the procedures set forth in this part; and (6) The date by which the hearing officer is directed to issue an initial decision. (b) Where there are no genuine issues of material fact requiring oral examination of witnesses, the hearing order may contain a direction to the hearing officer to conduct a hearing by submission of briefs and oral argument without the presentation of testimony or other evidence. </SECTION> <SECTION> <SECTNO>§ 16.202</SECTNO> <SUBJECT>Powers of a hearing officer.</SUBJECT> In accordance with the rules of this subpart, a hearing officer may: (a) Give notice of, and hold, prehearing conferences and hearings; (b) Administer oaths and affirmations; (c) Issue subpoenas authorized by law and issue notices of deposition requested by the parties; (d) Limit the frequency and extent of discovery; (e) Rule on offers of proof; (f) Receive relevant and material evidence; (g) Regulate the course of the hearing in accordance with the rules of this part to avoid unnecessary and duplicative proceedings in the interest of prompt and fair resolution of the matters at issue; (h) Hold conferences to settle or to simplify the issues by consent of the parties; (i) Dispose of procedural motions and requests; (j) Examine witnesses; and (k) Make findings of fact and conclusions of law, and issue an initial decision. </SECTION> <SECTION> <SECTNO>§ 16.203</SECTNO> <SUBJECT>Appearances, parties, and rights of parties.</SUBJECT> (a) <E T="03">Appearances.</E> Any party may appear and be heard in person. (1) Any party may be accompanied, represented, or advised by an attorney licensed by a State, the District of Columbia, or a territory of the United States to practice law or appear before the courts of that State or territory, or by another duly authorized representative. (2) An attorney, or other duly authorized representative, who represents a party shall file a notice of appearance in accordance with § 16.13. (b) <E T="03">Parties and agency participation.</E> (1) The parties to the hearing are the respondent (s) named in the hearing order, the complainant(s), and the agency. (2) Unless otherwise specified in the hearing order, the agency attorney will serve as prosecutor for the agency from the date of issuance of the Director's determination providing an opportunity for hearing. </SECTION> <SECTION> <SECTNO>§ 16.207</SECTNO> <SUBJECT>Intervention and other participation.</SUBJECT> (a) A person may submit a motion for leave to intervene as a party. Except for good cause shown, a motion for leave to intervene shall be submitted not later than 10 days after the notice of hearing and hearing order. (b) If the hearing officer finds that intervention will not unduly broaden the issues or delay the proceedings and, if the person has a property or financial interest that may not be addressed <PRTPAGE P="92"/>adequately by the parties, the hearing officer may grant a motion for leave to intervene. The hearing officer may determine the extent to which an intervenor may participate in the proceedings. (c) Other persons may petition the hearing officer for leave to participate in the hearing. Participation is limited to the filing of post-hearing briefs and reply to the hearing officer and the Associate Administrator. Such briefs shall be filed and served on all parties in the same manner as the parties’ post hearing briefs are filed. (d) Participation under this section is at the discretion of the FAA, and no decision permitting participation shall be deemed to constitute an expression by the FAA that the participant has such a substantial interest in the proceeding as would entitle it to judicial review of such decision. </SECTION> <SECTION> <SECTNO>§ 16.209</SECTNO> <SUBJECT>Extension of time.</SUBJECT> (a) <E T="03">Extension by oral agreement.</E> The parties may agree to extend for a reasonable period of time for filing a document under this part. If the parties agree, the hearing officer shall grant one extension of time to each party. The party seeking the extension of time shall submit a draft order to the hearing officer to be signed by the hearing officer and filed with the hearing docket. The hearing officer may grant additional oral requests for an extension of time where the parties agree to the extension. (b) <E T="03">Extension by motion.</E> A party shall file a written motion for an extension of time with the hearing officer not later than 7 days before the document is due unless good cause for the late filing is shown. A party filing a written motion for an extension of time shall serve a copy of the motion on each party. (c) <E T="03">Failure to rule.</E> If the hearing officer fails to rule on a written motion for an extension of time by the date the document was due, the motion for an extension of time is deemed denied. (d) <E T="03">Effect on time limits.</E> In a hearing required by section 519(b) of the Airport and Airways Improvement Act, as amended in 1987, 49 U.S.C. 47106(e) and 47111(d), the due date for the hearing officer's initial decision and for the final agency decision are extended by the length of the extension granted by the hearing officer only if the hearing officer grants an extension of time as a result of an agreement by the parties as specified in paragraph (a) of this section or, if the hearing officer grants an extension of time as a result of the sponsor's failure to adhere to the hearing schedule. In any other hearing, an extension of time granted by the hearing officer for any reason extends the due date for the hearing officer's initial decision and for the final agency decision by the length of time of the hearing officer's decision. </SECTION> <SECTION> <SECTNO>§ 16.211</SECTNO> <SUBJECT>Prehearing conference.</SUBJECT> (a) <E T="03">Prehearing conference notice.</E> The hearing officer schedules a prehearing conference and serves a prehearing conference notice on the parties promptly after being designated as a hearing officer. (1) The prehearing conference notice specifies the date, time, place, and manner (in person or by telephone) of the prehearing conference. (2) The prehearing conference notice may direct the parties to exchange proposed witness lists, requests for evidence and the production of documents in the possession of another party, responses to interrogatories, admissions, proposed procedural schedules, and proposed stipulations before the date of the prehearing conference. (b) <E T="03">The prehearing conference.</E> The prehearing conference is conducted by telephone or in person, at the hearing officer's discretion. The prehearing conference addresses matters raised in the prehearing conference notice and such other matters as the hearing officer determines will assist in a prompt, full and fair hearing of the issues. (c) <E T="03">Prehearing conference report.</E> At the close of the prehearing conference, the hearing officer rules on any requests for evidence and the production of documents in the possession of other parties, responses to interrogatories, and admissions; on any requests for depositions; on any proposed stipulations; and on any pending applications for subpoenas as permitted by § 16.219. In addition, the hearing officer establishes the schedule, which shall provide for the issuance of an initial decision <PRTPAGE P="93"/>not later than 110 days after issuance of the Director's determination order unless otherwise provided in the hearing order. </SECTION> <SECTION> <SECTNO>§ 16.213</SECTNO> <SUBJECT>Discovery.</SUBJECT> (a) Discovery is limited to requests for admissions, requests for production of documents, interrogatories, and depositions as authorized by § 16.215. (b) The hearing officer shall limit the frequency and extent of discovery permitted by this section if a party shows that— (1) The information requested is cumulative or repetitious; (2) The information requested may be obtained from another less burdensome and more convenient source; (3) The party requesting the information has had ample opportunity to obtain the information through other discovery methods permitted under this section; or (4) The method or scope of discovery requested by the party is unduly burdensome or expensive. </SECTION> <SECTION> <SECTNO>§ 16.215</SECTNO> <SUBJECT>Depositions.</SUBJECT> (a) <E T="03">General.</E> For good cause shown, the hearing officer may order that the testimony of a witness may be taken by deposition and that the witness produce documentary evidence in connection with such testimony. Generally, an order to take the deposition of a witness is entered only if: (1) The person whose deposition is to be taken would be unavailable at the hearing; (2) The deposition is deemed necessary to perpetuate the testimony of the witness; or (3) The taking of the deposition is necessary to prevent undue and excessive expense to a party and will not result in undue burden to other parties or in undue delay. (b) <E T="03">Application for deposition</E>. Any party desiring to take the deposition of a witness shall make application therefor to the hearing officer in writing, with a copy of the application served on each party. The application shall include: (1) The name and residence of the witness; (2) The time and place for the taking of the proposed deposition; (3) The reasons why such deposition should be taken; and (4) A general description of the matters concerning which the witness will be asked to testify. (c) <E T="03">Order authorizing deposition</E>. If good cause is shown, the hearing officer, in his or her discretion, issues an order authorizing the deposition and specifying the name of the witness to be deposed, the location and time of the deposition and the general scope and subject matter of the testimony to be taken. (d) <E T="03">Procedures for deposition.</E> (1) Witnesses whose testimony is taken by deposition shall be sworn or shall affirm before any questions are put to them. Each question propounded shall be recorded and the answers of the witness transcribed verbatim. (2) Objections to questions or evidence shall be recorded in the transcript of the deposition. The interposing of an objection shall not relieve the witness of the obligation to answer questions, except where the answer would violate a privilege. (3) The written transcript shall be subscribed by the witness, unless the parties by stipulation waive the signing, or the witness is ill, cannot be found, or refuses to sign. The reporter shall note the reason for failure to sign. </SECTION> <SECTION> <SECTNO>§ 16.217</SECTNO> <SUBJECT>Witnesses.</SUBJECT> (a) Each party may designate as a witness any person who is able and willing to give testimony that is relevant and material to the issues in the hearing case, subject to the limitation set forth in paragraph (b) of this section. (b) The hearing officer may exclude testimony of witnesses that would be irrelevant, immaterial, or unduly repetitious. (c) Any witness may be accompanied by counsel. Counsel representing a nonparty witness has no right to examine the witness or otherwise participate in the development of testimony. </SECTION> <SECTION> <SECTNO>§ 16.219</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> (a) <E T="03">Request for subpoena</E>. A party may apply to the hearing officer, within the time specified for such applications in the prehearing conference report, for a <PRTPAGE P="94"/>subpoena to compel testimony at a hearing or to require the production of documents only from the following persons: (1) Another party; (2) An officer, employee, or agent of another party; (3) Any other person named in the complaint as participating in or benefiting from the actions of the respondent alleged to have violated any Act; (4) An officer, employee, or agent of any other person named in the complaint as participating in or benefiting from the actions of the respondent alleged to have violated any Act. (b) <E T="03">Issuance and service of subpoena.</E> (1) The hearing officer issues the subpoena if the hearing officer determines that the evidence to be obtained by the subpoena is relevant and material to the resolution of the issues in the case. (2) Subpoenas shall be served by personal service, or upon an agent designated in writing for the purpose, or by certified mail, return receipt addressed to such person or agent. Whenever service is made by registered or certified mail, the date of mailing shall be considered as the time when service is made. (3) A subpoena issued under this part is effective throughout the United States or any territory or possession thereof. (c) <E T="03">Motions to quash or modify subpoena.</E> (1) A party or any person upon whom a subpoena has been served may file a motion to quash or modify the subpoena with the hearing officer at or before the time specified in the subpoena for the filing of such motions. The applicant shall describe in detail the basis for the application to quash or modify the subpoena including, but not limited to, a statement that the testimony, document, or tangible evidence is not relevant to the proceeding, that the subpoena is not reasonably tailored to the scope of the proceeding, or that the subpoena is unreasonable and oppressive. (2) A motion to quash or modify the subpoena stays the effect of the subpoena pending a decision by the hearing officer on the motion. </SECTION> <SECTION> <SECTNO>§ 16.221</SECTNO> <SUBJECT>Witness fees.</SUBJECT> (a) The party on whose behalf a witness appears is responsible for paying any witness fees and mileage expenses. (b) Except for employees of the United States summoned to testify as to matters related to their public employment, witnesses summoned by subpoena shall be paid the same fees and mileage expenses as are paid to a witness in a court of the United States in comparable circumstances. </SECTION> <SECTION> <SECTNO>§ 16.223</SECTNO> <SUBJECT>Evidence.</SUBJECT> (a) <E T="03">General.</E> A party may submit direct and rebuttal evidence in accordance with this section. (b) <E T="03">Requirement for written testimony and evidence.</E> Except in the case of evidence obtained by subpoena, or in the case of a special ruling by the hearing officer to admit oral testimony, a party's direct and rebuttal evidence shall be submitted in written form in advance of the oral hearing pursuant to the schedule established in the hearing officer's prehearing conference report. Written direct and rebuttal fact testimony shall be certified by the witness as true and correct. Subject to the same exception (for evidence obtained by subpoena or subject to a special ruling by the hearing officer), oral examination of a party's own witness is limited to certification of the accuracy of written evidence, including correction and updating, if necessary, and reexamination following cross-examination by other parties. (c) <E T="03">Subpoenaed testimony.</E> Testimony of witnesses appearing under subpoena may be obtained orally. (d) <E T="03">Cross-examination.</E> A party may conduct cross-examination that may be required for disclosure of the facts, subject to control by the hearing officer for fairness, expedition and exclusion of extraneous matters. (e) <E T="03">Hearsay evidence.</E> Hearsay evidence is admissible in proceedings governed by this part. The fact that evidence is hearsay goes to the weight of evidence and does not affect its admissibility. (f) <E T="03">Admission of evidence.</E> The hearing officer admits evidence introduced by a <PRTPAGE P="95"/>party in support of its case in accordance with this section, but may exclude irrelevant, immaterial, or unduly repetitious evidence. (g) <E T="03">Expert or opinion witnesses.</E> An employee of the FAA or DOT may not be called as an expert or opinion witness for any party other than the agency except as provided in Department of Transportation regulations at 49 CFR part 9. </SECTION> <SECTION> <SECTNO>§ 16.225</SECTNO> <SUBJECT>Public disclosure of evidence.</SUBJECT> (a) Except as provided in this section, the hearing shall be open to the public. (b) The hearing officer may order that any information contained in the record be withheld from public disclosure. Any person may object to disclosure of information in the record by filing a written motion to withhold specific information with the hearing officer. The person shall state specific grounds for nondisclosure in the motion. (c) The hearing officer shall grant the motion to withhold information from public disclosure if the hearing officer determines that disclosure would be in violation of the Privacy Act, would reveal trade secrets or privileged or confidential commercial or financial information, or is otherwise prohibited by law. </SECTION> <SECTION> <SECTNO>§ 16.227</SECTNO> <SUBJECT>Standard of proof.</SUBJECT> The hearing officer shall issue an initial decision or shall rule in a party's favor only if the decision or ruling is supported by, and in accordance with, reliable, probative, and substantial evidence contained in the record and is in accordance with law. </SECTION> <SECTION> <SECTNO>§ 16.229</SECTNO> <SUBJECT>Burden of proof.</SUBJECT> (a) The burden of proof of noncompliance with an Act or any regulation, order, agreement or document of conveyance issued under the authority of an Act is on the agency. (b) Except as otherwise provided by statute or rule, the proponent of a motion, request, or order has the burden of proof. (c) A party who has asserted an affirmative defense has the burden of proving the affirmative defense. </SECTION> <SECTION> <SECTNO>§ 16.231</SECTNO> <SUBJECT>Offer of proof.</SUBJECT> A party whose evidence has been excluded by a ruling of the hearing officer may offer the evidence on the record when filing an appeal. </SECTION> <SECTION> <SECTNO>§ 16.233</SECTNO> <SUBJECT>Record.</SUBJECT> (a) <E T="03">Exclusive record</E>. The transcript of all testimony in the hearing, all exhibits received into evidence, all motions, applications requests and rulings, and all documents included in the hearing record shall constitute the exclusive record for decision in the proceedings and the basis for the issuance of any orders. (b) <E T="03">Examination and copy of record</E>. Any interested person may examine the record at the Part 16 Airport Proceedings Docket, AGC-600, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591. Any person may have a copy of the record after payment of reasonable costs for search and reproduction of the record. </SECTION> <SECTION> <SECTNO>§ 16.235</SECTNO> <SUBJECT>Argument before the hearing officer.</SUBJECT> (a) <E T="03">Argument during the hearing</E>. During the hearing, the hearing officer shall give the parties reasonable opportunity to present oral argument on the record supporting or opposing motions, objections, and rulings if the parties request an opportunity for argument. The hearing officer may direct written argument during the hearing if the hearing officer finds that submission of written arguments would not delay the hearing. (b) <E T="03">Posthearing briefs.</E> The hearing officer may request or permit the parties to submit posthearing briefs. The hearing officer may provide for the filing of simultaneous reply briefs as well, if such filing will not unduly delay the issuance of the hearing officer's initial decision. Posthearing briefs shall include proposed findings of fact and conclusions of law; exceptions to rulings of the hearing officer; references to the record in support of the findings of fact; and supporting arguments for the proposed findings, proposed conclusions, and exceptions. </SECTION> <SECTION> <PRTPAGE P="96"/> <SECTNO>§ 16.237</SECTNO> <SUBJECT>Waiver of procedures.</SUBJECT> (a) The hearing officer shall waive such procedural steps as all parties to the hearing agree to waive before issuance of an initial decision. (b) Consent to a waiver of any procedural step bars the raising of this issue on appeal. (c) The parties may not by consent waive the obligation of the hearing officer to enter an initial decision on the record. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Initial Decisions, Orders and Appeals</HD> <SECTION> <SECTNO>§ 16.241</SECTNO> <SUBJECT>Initial decisions, order, and appeals.</SUBJECT> (a) The hearing officer shall issue an initial decision based on the record developed during the proceeding and shall send the initial decision to the parties not later than 110 days after the Director's determination unless otherwise provided in the hearing order. (b) Each party adversely affected by the hearing officer's initial decision may file an appeal with the Associate Administrator within 15 days of the date the initial decision is issued. Each party may file a reply to an appeal within 10 days after it is served on the party. Filing and service of appeals and replies shall be by personal delivery. (c) If an appeal is filed, the Associate Administrator reviews the entire record and issues a final agency decision and order within 30 days of the due date of the reply. If no appeal is filed, the Associate Administrator may take review of the case on his or her own motion. If the Associate Administrator finds that the respondent is not in compliance with any Act or any regulation, agreement, or document of conveyance issued or made under such Act, the final agency order includes a statement of corrective action, if appropriate, and identifies sanctions for continued noncompliance. (d) If no appeal is filed, and the Associate Administrator does not take review of the initial decision on the Associate Administrator's own motion, the initial decision shall take effect as the final agency decision and order on the sixteenth day after the actual date the initial decision is issued. (e) The failure to file an appeal is deemed a waiver of any rights to seek judicial review of an initial decision that becomes a final agency decision by operation of paragraph (d) of this section. (f) If the Associate Administrator takes review on the Associate Administrator's own motion, the Associate Administrator issues a notice of review by the sixteenth day after the actual date the initial decision is issued. (1) The notice sets forth the specific findings of fact and conclusions of law in the initial decision that are subject to review by the Associate Administrator. (2) Parties may file one brief on review to the Associate Administrator or rely on their posthearing briefs to the hearing officer. Briefs on review shall be filed not later than 10 days after service of the notice of review. Filing and service of briefs on review shall be by personal delivery. (3) The Associate Administrator issues a final agency decision and order within 30 days of the due date of the briefs on review. If the Associate Administrator finds that the respondent is not in compliance with any Act or any regulation, agreement or document of conveyance issued under such Act, the final agency order includes a statement of corrective action, if appropriate, and identifies sanctions for continued noncompliance. </SECTION> <SECTION> <SECTNO>§ 16.243</SECTNO> <SUBJECT>Consent orders.</SUBJECT> (a) The agency attorney and the respondents may agree at any time before the issuance of a final decision and order to dispose of the case by issuance of a consent order. Good faith efforts to resolve a complaint through issuance of a consent order may continue throughout the administrative process. Except as provided in § 16.209, such efforts may not serve as the basis for extensions of the times set forth in this part. (b) A proposal for a consent order, specified in paragraph (a) of this section, shall include: (1) A proposed consent order; (2) An admission of all jurisdictional facts;<PRTPAGE P="97"/> (3) An express waiver of the right to further procedural steps and of all rights of judicial review; and (4) The hearing order, if issued, and an acknowledgment that the hearing order may be used to construe the terms of the consent order. (c) If the issuance of a consent order has been agreed upon by all parties to the hearing, the proposed consent order shall be filed with the hearing officer, along with a draft order adopting the consent decree and dismissing the case, for the hearing officer's adoption. (d) The deadline for the hearing officer's initial decision and the final agency decision is extended by the amount of days elapsed between the filing of the proposed consent order with the hearing officer and the issuance of the hearing officer's order continuing the hearing. (e) If the agency attorney and sponsor agree to dispose of a case by issuance of a consent order before the FAA issues a hearing order, the proposal for a consent order is submitted jointly to the official authorized to issue a hearing order, together with a request to adopt the consent order and dismiss the case. The official authorized to issue the hearing order issues the consent order as an order of the FAA and terminates the proceeding. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Judicial Review</HD> <SECTION> <SECTNO>§ 16.247</SECTNO> <SUBJECT>Judicial review of a final decision and order.</SUBJECT> (a) A person may seek judicial review, in a United States Court of Appeals, of a final decision and order of the Associate Administrator as provided in 49 U.S.C. 46110 or section 519(b)(4) of the Airport and Airway Improvement Act of 1982, as amended, (AAIA), 49 U.S.C. 47106(d) and 47111(d). A party seeking judicial review of a final decision and order shall file a petition for review with the Court not later than 60 days after a final decision and order under the AAIA has been served on the party or within 60 days after the entry of an order under 49 U.S.C. 40101 <E T="03">et seq.</E> (b) The following do not constitute final decisions and orders subject to judicial review: (1) An FAA decision to dismiss a complaint without prejudice, as set forth in § 16.27; (2) A Director's determination; (3) An initial decision issued by a hearing officer at the conclusion of a hearing; (4) A Director's determination or an initial decision of a hearing officer that becomes the final decision of the Associate Administrator because it was not appealed within the applicable time periods provided under §§ 16.33(b) and 16.241(b). </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart I—Ex Parte Communications</HD> <SECTION> <SECTNO>§ 16.301</SECTNO> <SUBJECT>Definitions.</SUBJECT> As used in this subpart: <E T="03">Decisional employee</E> means the Administrator, Deputy Administrator, Associate Administrator, Director, hearing officer, or other FAA employee who is or who may reasonably be expected to be involved in the decisional process of the proceeding. <E T="03">Ex parte communication</E> means an oral or written communication not on the public record with respect to which reasonable prior notice to all parties is not given, but it shall not include requests for status reports on any matter or proceeding covered by this part, or communications between FAA employees who participate as parties to a hearing pursuant to 16.203(b) of this part and other parties to a hearing. </SECTION> <SECTION> <SECTNO>§ 16.303</SECTNO> <SUBJECT>Prohibited ex parte communications.</SUBJECT> (a) The prohibitions of this section shall apply from the time a proceeding is noticed for hearing unless the person responsible for the communication has knowledge that it will be noticed, in which case the prohibitions shall apply at the time of the acquisition of such knowledge. (b) Except to the extent required for the disposition of ex parte matters as authorized by law: (1) No interested person outside the FAA and no FAA employee participating as a party shall make or knowingly cause to be made to any decisional employee an ex parte communication relevant to the merits of the proceeding;<PRTPAGE P="98"/> (2) No FAA employee shall make or knowingly cause to be made to any interested person outside the FAA an ex parte communication relevant to the merits of the proceeding; or (3) Ex parte communications regarding solely matters of agency procedure or practice are not prohibited by this section. </SECTION> <SECTION> <SECTNO>§ 16.305</SECTNO> <SUBJECT>Procedures for handling ex parte communications.</SUBJECT> A decisional employee who receives or who makes or knowingly causes to be made a communication prohibited by § 16.303 shall place in the public record of the proceeding: (a) All such written communications; (b) Memoranda stating the substance of all such oral communications; and (c) All written responses, and memoranda stating the substance of all oral responses, to the materials described in paragraphs (a) and (b) of this section. </SECTION> <SECTION> <SECTNO>§ 16.307</SECTNO> <SUBJECT>Requirement to show cause and imposition of sanction.</SUBJECT> (a) Upon receipt of a communication knowingly made or knowingly caused to be made by a party in violation of § 16.303, the Associate Administrator or his designee or the hearing officer may, to the extent consistent with the interests of justice and the policy of the underlying statutes, require the party to show cause why his or her claim or interest in the proceeding should not be dismissed, denied, disregarded, or otherwise adversely affected on account of such violation. (b) The Associate Administrator may, to the extent consistent with the interests of justice and the policy of the underlying statutes administered by the FAA, consider a violation of this subpart sufficient grounds for a decision adverse to a party who has knowingly committed such violation or knowingly caused such violation to occur. </SECTION> </SUBPART> </PART> </SUBCHAP> <SUBCHAP TYPE="P"> <PRTPAGE P="99"/> <HD SOURCE="HED">SUBCHAPTER C—AIRCRAFT</HD> <PART> <EAR>Pt. 21</EAR> <HD SOURCE="HED">PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS</HD> <CONTENTS> <SUBJGRP> <HD SOURCE="HED">Special Federal Aviation Regulations</HD> </SUBJGRP> <FP SOURCE="FP-2"> <E T="04">SFAR No.</E> 26</FP> <FP SOURCE="FP-2"> <E T="04">SFAR No.</E> 29-4</FP> <FP SOURCE="FP-2"> <E T="04">SFAR No.</E> 41</FP> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECHD>Sec.</SECHD> <SECTNO>21.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.2</SECTNO> <SUBJECT>Falsification of applications, reports, or records.</SUBJECT> <SECTNO>21.3</SECTNO> <SUBJECT>Reporting of failures, malfunctions, and defects.</SUBJECT> <SECTNO>21.5</SECTNO> <SUBJECT>Airplane or Rotorcraft Flight Manual.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Type Certificates</HD> <SECTNO>21.11</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.13</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.15</SECTNO> <SUBJECT>Application for type certificate.</SUBJECT> <SECTNO>21.16</SECTNO> <SUBJECT>Special conditions.</SUBJECT> <SECTNO>21.17</SECTNO> <SUBJECT>Designation of applicable regulations.</SUBJECT> <SECTNO>21.19</SECTNO> <SUBJECT>Changes requiring a new type certificate.</SUBJECT> <SECTNO>21.21</SECTNO> <SUBJECT>Issue of type certificate: normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; special classes of aircraft; aircraft engines; propellers.</SUBJECT> <SECTNO>21.23</SECTNO> <SUBJECT>[Reserved]</SUBJECT> <SECTNO>21.24</SECTNO> <SUBJECT>Issuance of type certificate: primary category aircraft.</SUBJECT> <SECTNO>21.25</SECTNO> <SUBJECT>Issue of type certificate: Restricted category aircraft.</SUBJECT> <SECTNO>21.27</SECTNO> <SUBJECT>Issue of type certificate: surplus aircraft of the Armed Forces.</SUBJECT> <SECTNO>21.29</SECTNO> <SUBJECT>Issue of type certificate: import products.</SUBJECT> <SECTNO>21.31</SECTNO> <SUBJECT>Type design.</SUBJECT> <SECTNO>21.33</SECTNO> <SUBJECT>Inspection and tests.</SUBJECT> <SECTNO>21.35</SECTNO> <SUBJECT>Flight tests.</SUBJECT> <SECTNO>21.37</SECTNO> <SUBJECT>Flight test pilot.</SUBJECT> <SECTNO>21.39</SECTNO> <SUBJECT>Flight test instrument calibration and correction report.</SUBJECT> <SECTNO>21.41</SECTNO> <SUBJECT>Type certificate.</SUBJECT> <SECTNO>21.43</SECTNO> <SUBJECT>Location of manufacturing facilities.</SUBJECT> <SECTNO>21.45</SECTNO> <SUBJECT>Privileges.</SUBJECT> <SECTNO>21.47</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.49</SECTNO> <SUBJECT>Availability.</SUBJECT> <SECTNO>21.50</SECTNO> <SUBJECT>Instructions for continued airworthiness and manufacturer's maintenance manuals having airworthiness limitations sections.</SUBJECT> <SECTNO>21.51</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.53</SECTNO> <SUBJECT>Statement of conformity.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Provisional Type Certificates</HD> <SECTNO>21.71</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.73</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.75</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.77</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.79</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.81</SECTNO> <SUBJECT>Requirements for issue and amendment of Class I provisional type certificates.</SUBJECT> <SECTNO>21.83</SECTNO> <SUBJECT>Requirements for issue and amendment of Class II provisional type certificates.</SUBJECT> <SECTNO>21.85</SECTNO> <SUBJECT>Provisional amendments to type certificates.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Changes to Type Certificates</HD> <SECTNO>21.91</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.93</SECTNO> <SUBJECT>Classification of changes in type design.</SUBJECT> <SECTNO>21.95</SECTNO> <SUBJECT>Approval of minor changes in type design.</SUBJECT> <SECTNO>21.97</SECTNO> <SUBJECT>Approval of major changes in type design.</SUBJECT> <SECTNO>21.99</SECTNO> <SUBJECT>Required design changes.</SUBJECT> <SECTNO>21.101</SECTNO> <SUBJECT>Designation of applicable regulations.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Supplemental Type Certificates</HD> <SECTNO>21.111</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.113</SECTNO> <SUBJECT>Requirement of supplemental type certificate.</SUBJECT> <SECTNO>21.115</SECTNO> <SUBJECT>Applicable requirements.</SUBJECT> <SECTNO>21.117</SECTNO> <SUBJECT>Issue of supplemental type certificates.</SUBJECT> <SECTNO>21.119</SECTNO> <SUBJECT>Privileges.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Production Under Type Certificate Only</HD> <SECTNO>21.121</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.123</SECTNO> <SUBJECT>Production under type certificate.</SUBJECT> <SECTNO>21.125</SECTNO> <SUBJECT>Production inspection system: Materials Review Board.</SUBJECT> <SECTNO>21.127</SECTNO> <SUBJECT>Tests: aircraft.</SUBJECT> <SECTNO>21.128</SECTNO> <SUBJECT>Tests: aircraft engines.</SUBJECT> <SECTNO>21.129</SECTNO> <SUBJECT>Tests: propellers.</SUBJECT> <SECTNO>21.130</SECTNO> <SUBJECT>Statement of conformity.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Production Certificates</HD> <SECTNO>21.131</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.133</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.135</SECTNO> <SUBJECT>Requirements for issuance.</SUBJECT> <SECTNO>21.137</SECTNO> <SUBJECT>Location of manufacturing facilities.</SUBJECT> <SECTNO>21.139</SECTNO> <SUBJECT>Quality control.</SUBJECT> <SECTNO>21.143</SECTNO> <SUBJECT>Quality control data requirements; prime manufacturer.</SUBJECT> <SECTNO>21.147</SECTNO> <SUBJECT>Changes in quality control system.</SUBJECT> <SECTNO>21.149</SECTNO> <SUBJECT>Multiple products.</SUBJECT> <SECTNO>21.151</SECTNO> <SUBJECT>Production limitation record.</SUBJECT> <SECTNO>21.153</SECTNO> <SUBJECT>Amendment of the production certificates.<PRTPAGE P="100"/> </SUBJECT> <SECTNO>21.155</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.157</SECTNO> <SUBJECT>Inspections and tests.</SUBJECT> <SECTNO>21.159</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.161</SECTNO> <SUBJECT>Display.</SUBJECT> <SECTNO>21.163</SECTNO> <SUBJECT>Privileges.</SUBJECT> <SECTNO>21.165</SECTNO> <SUBJECT>Responsibility of holder.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Airworthiness Certificates</HD> <SECTNO>21.171</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.173</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.175</SECTNO> <SUBJECT>Airworthiness certificates: classification.</SUBJECT> <SECTNO>21.177</SECTNO> <SUBJECT>Amendment or modification.</SUBJECT> <SECTNO>21.179</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.181</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.182</SECTNO> <SUBJECT>Aircraft identification.</SUBJECT> <SECTNO>21.183</SECTNO> <SUBJECT>Issue of standard airworthiness certificates for normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; and special classes of aircraft.</SUBJECT> <SECTNO>21.184</SECTNO> <SUBJECT>Issue of special airworthiness certificates for primary category aircraft.</SUBJECT> <SECTNO>21.185</SECTNO> <SUBJECT>Issue of airworthiness certificates for restricted category aircraft.</SUBJECT> <SECTNO>21.187</SECTNO> <SUBJECT>Issue of multiple airworthiness certification.</SUBJECT> <SECTNO>21.189</SECTNO> <SUBJECT>Issue of airworthiness certificate for limited category aircraft.</SUBJECT> <SECTNO>21.191</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> <SECTNO>21.193</SECTNO> <SUBJECT>Experimental certificates: general.</SUBJECT> <SECTNO>21.195</SECTNO> <SUBJECT>Experimental certificates: Aircraft to be used for market surveys, sales demonstrations, and customer crew training.</SUBJECT> <SECTNO>21.197</SECTNO> <SUBJECT>Special flight permits.</SUBJECT> <SECTNO>21.199</SECTNO> <SUBJECT>Issue of special flight permits.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart I—Provisional Airworthiness Certificates</HD> <SECTNO>21.211</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.213</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.215</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.217</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.219</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.221</SECTNO> <SUBJECT>Class I provisional airworthiness certificates.</SUBJECT> <SECTNO>21.223</SECTNO> <SUBJECT>Class II provisional airworthiness certificates.</SUBJECT> <SECTNO>21.225</SECTNO> <SUBJECT>Provisional airworthiness certificates corresponding with provisional amendments to type certificates.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart J—Delegation Option Authorization Procedures</HD> <SECTNO>21.231</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.235</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.239</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.243</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.245</SECTNO> <SUBJECT>Maintenance of eligibility.</SUBJECT> <SECTNO>21.247</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.249</SECTNO> <SUBJECT>Inspections.</SUBJECT> <SECTNO>21.251</SECTNO> <SUBJECT>Limits of applicability.</SUBJECT> <SECTNO>21.253</SECTNO> <SUBJECT>Type certificates: application.</SUBJECT> <SECTNO>21.257</SECTNO> <SUBJECT>Type certificates: issue.</SUBJECT> <SECTNO>21.261</SECTNO> <SUBJECT>Equivalent safety provisions.</SUBJECT> <SECTNO>21.267</SECTNO> <SUBJECT>Production certificates.</SUBJECT> <SECTNO>21.269</SECTNO> <SUBJECT>Export airworthiness approvals.</SUBJECT> <SECTNO>21.271</SECTNO> <SUBJECT>Airworthiness approval tags.</SUBJECT> <SECTNO>21.273</SECTNO> <SUBJECT>Airworthiness certificates other than experimental.</SUBJECT> <SECTNO>21.275</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> <SECTNO>21.277</SECTNO> <SUBJECT>Data review and service experience.</SUBJECT> <SECTNO>21.289</SECTNO> <SUBJECT>Major repairs, rebuilding and alteration.</SUBJECT> <SECTNO>21.293</SECTNO> <SUBJECT>Current records.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart K—Approval of Materials, Parts, Processes, and Appliances</HD> <SECTNO>21.301</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.303</SECTNO> <SUBJECT>Replacement and modification parts.</SUBJECT> <SECTNO>21.305</SECTNO> <SUBJECT>Approval of materials, parts, processes, and appliances.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart L—Export Airworthiness Approvals</HD> <SECTNO>21.321</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.323</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.325</SECTNO> <SUBJECT>Export airworthiness approvals.</SUBJECT> <SECTNO>21.327</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.329</SECTNO> <SUBJECT>Issue of export certificates of airworthiness for Class I products.</SUBJECT> <SECTNO>21.331</SECTNO> <SUBJECT>Issue of airworthiness approval tags for Class II products.</SUBJECT> <SECTNO>21.333</SECTNO> <SUBJECT>Issue of export airworthiness approval tags for Class III products.</SUBJECT> <SECTNO>21.335</SECTNO> <SUBJECT>Responsibilities of exporters.</SUBJECT> <SECTNO>21.337</SECTNO> <SUBJECT>Performance of inspections and overhauls.</SUBJECT> <SECTNO>21.339</SECTNO> <SUBJECT>Special export airworthiness approval for aircraft.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart M—Designated Alteration Station Authorization Procedures</HD> <SECTNO>21.431</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.435</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.439</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.441</SECTNO> <SUBJECT>Procedure manual.</SUBJECT> <SECTNO>21.443</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.445</SECTNO> <SUBJECT>Maintenance of eligibility.</SUBJECT> <SECTNO>21.447</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.449</SECTNO> <SUBJECT>Inspections.</SUBJECT> <SECTNO>21.451</SECTNO> <SUBJECT>Limits of applicability.</SUBJECT> <SECTNO>21.461</SECTNO> <SUBJECT>Equivalent safety provisions.</SUBJECT> <SECTNO>21.463</SECTNO> <SUBJECT>Supplemental type certificates.</SUBJECT> <SECTNO>21.473</SECTNO> <SUBJECT>Airworthiness certificates other than experimental.</SUBJECT> <SECTNO>21.475</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> <SECTNO>21.477</SECTNO> <SUBJECT>Data review and service experience.</SUBJECT> <SECTNO>21.493</SECTNO> <SUBJECT>Current records.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart N—Approval of Engines, Propellers, Materials, Parts, and Appliances: Import</HD> <SECTNO>21.500</SECTNO> <SUBJECT>Approval of engines and propellers.</SUBJECT> <SECTNO>21.502</SECTNO> <SUBJECT>Approval of materials, parts, and appliances.</SUBJECT> </SUBPART> <SUBPART> <PRTPAGE P="101"/> <HD SOURCE="HED">Subpart O—Technical Standard Order Authorizations</HD> <SECTNO>21.601</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.603</SECTNO> <SUBJECT>TSO marking and privileges.</SUBJECT> <SECTNO>21.605</SECTNO> <SUBJECT>Application and issue.</SUBJECT> <SECTNO>21.607</SECTNO> <SUBJECT>General rules governing holders of TSO authorizations.</SUBJECT> <SECTNO>21.609</SECTNO> <SUBJECT>Approval for deviation.</SUBJECT> <SECTNO>21.611</SECTNO> <SUBJECT>Design changes.</SUBJECT> <SECTNO>21.613</SECTNO> <SUBJECT>Recordkeeping requirements.</SUBJECT> <SECTNO>21.615</SECTNO> <SUBJECT>FAA inspection.</SUBJECT> <SECTNO>21.617</SECTNO> <SUBJECT>Issue of letters of TSO design approval: import appliances.</SUBJECT> <SECTNO>21.619</SECTNO> <SUBJECT>Noncompliance.</SUBJECT> <SECTNO>21.621</SECTNO> <SUBJECT>Transferability and duration.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 42 U.S.C. 7572; 49 U.S.C. 106(g), 40105, 40113, 44701-44702, 44707, 44709, 44711, 44713, 44715, 45303. </AUTH> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For miscellaneous amendments to cross references in this Part 21 see Amdt. 21-10, 31 FR 9211, July 6, 1966. </EDNOTE> <SUBJGRP> <HD SOURCE="HED">Special Federal Aviation Regulations</HD> </SUBJGRP> <EAR>Pt. 21, SFAR No. 26</EAR> <SUBJGRP> <HD SOURCE="HED">SFAR No. <E T="01">26</E> </HD> </SUBJGRP> <EXTRACT> Contrary provisions of §§ 21.29, 21.500, and 21.502 of the Federal Aviation Regulations notwithstanding— 1. A type certificate may be issued under § 21.29 for an aircraft engine or propeller manufactured in a foreign country with which the United States has a currently effective bilateral agreement for the acceptance of powered aircraft for export and import and that is to be imported into the United States if (i) a type certificate has previously been issued by the Administrator for a product manufactured in that country which is of the same kind as the product for which a type certificate is requested; and (ii) the Administrator determines that the design standards and practices, the quality control standards, and the certification procedures utilized by such country for the particular product being imported are the equivalent of those required in the United States. 2. Aircraft engines, propellers, materials, parts (including subassemblies), or appliances (hereinafter referred to as aircraft components), manufactured in a foreign country with which the United States has a currently effective bilateral agreement for the acceptance of powered aircraft may be approved under § 21.500 or § 21.502, as applicable, if (i) an approval has previously been issued by the Administrator for an aircraft component manufactured in that country which is of the same kind as the aircraft component for which approval is requested; and (ii) the Administrator determines that the quality control standards and the certification and approval procedures utilized by such country for the particular aircraft component being imported are the equivalent of those required in the United States. 3. Aircraft subassemblies not covered under paragraph 2 that are to be incorporated on aircraft designed and manufactured in the United States, and that are manufactured in a foreign country with which the United States has a currently effective bilateral agreement for the acceptance of powered aircraft may be approved if (i) an approval has previously been issued by the Administrator for any other subassembly manufactured in that country; (ii) the Administrator determines that the quality control standards and the certification and approval procedures utilized by that country for the particular subassembly being imported are equivalent to those required in the United States; and (iii) the competent aeronautical authorities of the country certify that the subassembly meets the applicable design requirements. 4. Appropriate procedures for the execution of the provisions contained in paragraphs 1, 2, and 3 of the regulation may be embodied in agreements between the Administrator and the competent aeronautical authorities of the country of manufacture of the aircraft component. 5. In the event that the Administrator determines that the quality control standards and certification and approval procedures being utilized in the foreign countries to which this regulation is applicable no longer meet the quality control and certification and approval requirements equivalent to those required in the United States, the approval given under this regulation for the import into the United States of those aeronautical products covered by the regulation will be terminated. 6. After October 1, 1977, this special regulation applies only to aircraft components and subassemblies produced in Japan pursuant to contracts between Japanese manufacturers and United States product manufacturers entered into prior to October 1, 1977. This special regulation shall terminate December 1, 1977, unless sooner rescinded or superseded. </EXTRACT> <CITA>[35 FR 12749, Aug. 12, 1970, as amended at 40 FR 28604, July 8, 1975; 41 FR 27954, July 8, 1976; Doc. No. 10492, 42 FR 35634, July 11, 1977; Amdt. 26-11, 42 FR 54408, Oct. 6, 1977]</CITA> <EAR>Pt. 21, SFAR No. 29-4</EAR> <SUBJGRP> <HD SOURCE="HED">SFAR No. <E T="01">29-4</E> </HD> </SUBJGRP> <EXTRACT> <HD SOURCE="HD1">Limited IFR Operations of Rotorcraft</HD> 1. Contrary provisions of Parts 21, 27, and 29 of the Federal Aviation Regulations notwithstanding, an operator of a rotorcraft that is not otherwise certificated for IFR operations may conduct an approved limited IFR operation in the rotorcraft when— (a) FAA approval for the operation has been issued under paragraph 2 of this SFAR;<PRTPAGE P="102"/> (b) The operator complies with all conditions and limitations established by this SFAR and the approval; and (c) A copy of the approval and this SFAR are set forth as a supplement to the Rotorcraft Flight Manual. 2. FAA approval for the operation of a rotorcraft in limited IFR operations may be issued when the following conditions are met: (a) The operation is approved as part of the FAA study of limited rotorcraft IFR operations. (b) Specific FAA approval has been obtained for the following: (i) The rotorcraft (make, model, and serial number). (ii) The flightcrew. (iii) The procedures to be followed in the operation of the rotorcraft under IFR and the equipment that must be operable during such operations. (c) The conditions and limitations necessary for the safe operation of the rotorcraft in limited IFR operations have been established, approved, and incorporated into the operating limitations section of the Rotorcraft Flight Manual. 3. An approval issued under paragraph 2 of this Special Federal Aviation Regulation and the change to the Rotorcraft Flight Manual specified in paragraph 2(c) of this Special Federal Aviation Regulation constitute a supplemental type certificate for each rotorcraft approved under paragraph 2 of this SFAR. The supplemental type certificate will remain in effect until the approval to operate issued under the Special Federal Aviation Regulation is surrendered, revoked, or otherwise terminated. 4. Notwithstanding § 91.167(a)(3) of the Federal Aviation Regulations, a person may operate a rotorcraft in a limited IFR operation approved under paragraph 2(a) of the Special Federal Aviation Regulation with enough fuel to fly, after reaching the alternate airport, for not less than 30 minutes, when that period of time has been approved. 5. Expiration. (a) New applications for limited IFR rotorcraft operations under SFAR No. 29 may be submitted for approval until, but not including, the effective date of Amendment No. 1 of the Rotorcraft Regulatory Review Program. On and after the effective date of Amendment No. 1 of the Rotorcraft Regulatory Review Program, all applicants for certification of IFR rotorcraft operations must comply with the applicable provisions of the Federal Aviation Regulations. (b) This Special Federal Aviation Regulation will terminate when all approvals issued under Special Federal Aviation Regulation No. 29 are surrendered, revoked, or otherwise terminated. </EXTRACT> <CITA>[Doc. No. 14237, 48 FR 632, Jan. 6, 1983, as amended at 54 FR 34329, Aug. 18, 1989]</CITA> <EAR>Pt. 21, SFAR No. 41</EAR> <SUBJGRP> <HD SOURCE="HED">SFAR No. <E T="01">41</E> </HD> </SUBJGRP> <EXTRACT> 1. <E T="03">Applicability.</E> (a) Contrary provisions of Parts 21 and 23 of the Federal Aviation Regulations notwithstanding, an applicant is entitled to an amended or supplemental type certificate in the normal category for a reciprocating or turbopropeller-powered multiengine small airplane originally type certificated prior to October 17, 1979 in accordance with Part 23 of the Federal Aviation Regulations in effect on March 13, 1971, or later, that is to be certificated with a passenger seating configuration, excluding pilot seats, of 10 seats or more (but not more than 19 seats) at a maximum certificated takeoff weight of 12,500 pounds or less, if the applicant complies with— (1) The regulations incorporated in the type certificate; and (2) The requirements of appendix A of Part 135 of the Federal Aviation Regulations in effect on September 26, 1978, except that the landing distance must be determined for standard atmosphere at each weight, altitude, and wind within the operating limits established by the applicant in accordance with § 23.75(a) of this chapter in effect on September 26, 1978. Instead of a gliding approach specified in § 23.75(a), the landing may be preceded by a steady approach down to the 50-foot height at a gradient of descent not greater than 5.2 percent (3°) at a calibrated airspeed not less than 1.3V<E T="22">s1</E>. (b) Contrary provisions of Parts 1, 21, 23, 91, 121, and 135 of the Federal Aviation Regulations notwithstanding, an applicant is entitled to an amended or supplemental type certificate in the normal category for a reciprocating or turbopropeller powered multiengine airplane originally type certified prior to October 17, 1979 that is to be certificated with a maximum takeoff weight in excess of 12,500 pounds, a specified maximum zero fuel weight to be established by the applicant, and, where requested by the applicant, an increase in passenger seating configuration, (but not more than 19 passenger seats), if the applicant complies with— (1) The regulations incorporated in the type certificate; (2) The requirements of appendix A of Part 135 of the Federal Aviation Regulations in effect on September 26, 1978 with the exceptions specified in section 5 of this Special Federal Aviation Regulation; and (3) The additional requirements specified in sections 7 through 14 of this Special Federal Aviation Regulation applicable to -takeoff weights in excess of 12,500 pounds.<PRTPAGE P="103"/> (c) Contrary provisions of Part 1 of the Federal Aviation Regulations notwithstanding, an airplane certificated under paragraph (b) of this section is considered to be a small airplane for purposes of Parts 21, 23, 36, 121, 135, and 139 of the Federal Aviation Regulations, and a large airplane for purposes of Parts 61 and 91. Compliance with the small airplane provisions of Part 36 of the Federal Aviation Regulations must be shown at the maximum certificated takeoff weight approved under this Special Federal Aviation Regulation. 2. <E T="03">Eligibility.</E> Any person may apply for a supplemental type certificate (or an amended type certificate in the case of a type certificate holder) under this Special Federal Aviation Regulation. 3. <E T="03">Production limitation.</E> An amended or supplemental type certificate issued pursuant to section 1.(b) of this Special Federal Aviation Regulation is effective for the purpose of obtaining an original or an amended airworthiness certificate, until October 17, 1991 unless the type certificate is sooner surrendered, suspended, revoked, or terminated. 4. <E T="03">Restrictions.</E> For airplanes certificated under section 1.(b) of this Special Federal Aviation Regulation— (a) The maximum zero fuel weight of the airplane must be established as an operating limitation; and (b) Except as provided in paragraph (c) of this section the airworthiness certificate shall be endorsed “This airplane at weights in excess of 5,700 kg does not meet the airworthiness requirements of ICAO, as prescribed by Annex 8 of the Convention on International Civil Aviation.” (c) An applicant is entitled to type certificate amendment or a supplemental type certificate that shows compliance with ICAO Annex 8 if the airplane meets SFAR 41 and the following requirements prescribed by the Administrator in effect on October 17, 1979: (1) At each weight, altitude, and temperature within the operational limits selected by the applicant— (i) For approach climb performance, comply with §§ 25.121(d) and 25.1533(a)(2). (ii) For takeoff performance, comply with §§ 25.105(d), 25.111, 25.113(a), and 25.115. (2) For gust loads design at rough air gust speed V<E T="22">B</E>, comply with §§ 25.335(d), 25.341(a)(1), and 25.351(b). (3) For smoke evacuation design, comply with § 25.831(d). (4) For engine rotation and restarting design, comply with § 25.903 (c) and (e). (5) For engine cooling design, comply with § 25.1521(e). 5. <E T="03">Exceptions.</E> For purposes of obtaining an amended or supplemental type certificate under section 1.(b) of this Special Federal Aviation Regulation, the following exceptions apply. All references in this section to specific sections of Parts 23 and 25 of this chapter are to those in effect on September 26, 1978 if no other date is given: (a) Compliance with section 1 of appendix A of Part 135 of the Federal Aviation Regulations is not required. (b) Compliance may be shown with the applicable regulations incorporated in the type certificate in lieu of the requirements of appendix A of Part 135 of the Federal Aviation Regulations for takeoff weights of 12,500 pounds or less, if the airplane was type certificated— (1) Under FAR Part 23 in effect prior to Amendment 23-10 and the airplane is to be used only in FAR Part 91 operations; (2) Before July 19, 1970, in the normal category with a passenger seating configuration, excluding any pilot seat, of 10 seats or more, (but not to exceed 19 passenger seats), and meets special conditions issued by the Administrator for airplanes intended for use in operations under FAR Part 135; or (3) Before July 19, 1970, in the normal category with a passenger seating configuration, excluding any pilot seat, of 10 seats or more, (but not to exceed 19 passenger seats), and meets the additional airworthiness standards in Special Federal Aviation Regulation No. 23. (c) In lieu of compliance with sections 7., and 19.(c) of appendix A of Part 135 of the Federal Aviation Regulations, comply with the following at takeoff weights in excess of 12,500 pounds: <HD SOURCE="HD1"> <E T="03">Landing</E> </HD> (<E T="03">a</E>) The landing distance must be determined for standard atmosphere at each weight, altitude, and wind within the operational limits established by the applicant in accordance with § 23.75(a) of this chapter. Instead of a gliding approach specified in § 23.75(a), the landing may be preceded by a steady approach down to the 50-foot height at a gradient of descent not greater than 5.2 percent (3°) at a calibrated airspeed not less than 1.3 V<E T="22">S1</E>. (<E T="03">b</E>) The landing distance data must include correction factors for not more than 50 percent of the nominal wind components along the landing path opposite to the direction of landing, and not less than 150 percent of the nominal wind components along the landing path in the direction of landing. (d) In lieu of compliance with section 28 of appendix A of Part 135 of the Federal Aviation Regulations, comply with the following: <E T="03">Fatigue evaluation of flight structure.</E> Unless it is shown that the structure, operating stress levels, materials, and expected use are comparable from a fatigue standpoint to a similar design which has had substantial satifactory service experience, the strength, detail design, and the fabrication of those parts of the wing, wing carrythrough, vertical fin, horizortal stabilizer, and attaching <PRTPAGE P="104"/>structure whose failure would be catastrophic must be evaluted under either— (<E T="03">a</E>) A fatigue strength investigation in which the structure is shown by analysis, tests, or both, to be able to withstand the repeated loads of variable magnitude expected in service. Analysis alone is acceptable only when it is conservative and applied to simple structures; or (<E T="03">b</E>) A fail-safe strength investigation in which it is shown by analysis, tests, or both, that catastrophic failure of the structure is not probable after fatigue, or obvious partial failure, of a principal structural element, and that the remaining structure is able to withstand a static ultimate load factor of 75 percent of the critical limit load factor at V<E T="22">C</E>. These loads must be multiplied by a factor of 1.15 unless the dynamic effects of failure under static load are otherwise considered. (e) In lieu of compliance with section 32 of appendix A of Part 135 of the Federal Aviation Regulations, comply with the following: <E T="03">Doors and exits.</E> The airplane must meet the requirements of §§23.783 and 23.807 (a)(3), (b), and (c) of this chapter, and in addition the following requirements: (<E T="03">a</E>) Each cabin must have at least one easily accessible external door. (<E T="03">b</E>) There must be a means to lock and safeguard each external door against opening in flight (either inadvertently by persons or as a result of mechanical failure or failure of a single structural element). Each external door must be operable from both the inside and the outside, even though persons may be crowded against the door on the inside of the airplane. Inward opening doors may be used if there are means to prevent occupants from crowding against the door to an extent that would interfere with the opening of the door. The means of opening must be simple and obvious and must be arranged and marked so that it can be readily located and operated, even in darkness. Auxiliary locking devices may be used. (<E T="03">c</E>) Each external door must be reasonably free from jamming as a result of fuselage deformation in a minor crash. (<E T="03">d</E>) Each external door must be located where persons using it will not be endangered by the propellers when appropriate operating procedures are used. (<E T="03">e</E>) There must be a provision for direct visual inspection of the locking mechanism by crewmembers to determine whether external doors, for which the initial opening movement is outward (including passenger, crew, service, and cargo doors), are fully locked. In addition, there must be a visual means to signal to appropriate crewmembers when normally used external doors are closed and fully locked. (<E T="03">f</E>) Cargo and service doors not suitable for use as exits in an emergency need only meet paragraph (<E T="03">e</E>) of section 5(<E T="03">e</E>) of this regulation and be safeguarded against opening in flight as a result of mechanical failure or failure of a single structural element. (<E T="03">g</E>) The passenger entrance door must qualify as a floor level emergency exit. If an integral stair is installed at such a passenger entry door, the stair must be designed so that when subjected to the inertia forces specified in § 23.561 of this chapter, and following the collapse of one or more legs of the landing gear, it will not interfere to an extent that will reduce the effectiveness of emergency egress through the passenger entry door. Each additional required emergency exit except floor level exits must be located over the wing or must be provided with acceptable means to assist the occupants in descending to the ground. In addition to the passenger entrance door— (1) For a total passenger seating capacity of 15 or less, an emergency exit, as defined in § 23.807(b) of this chapter, is required on each side of the cabin; and (2) For a total passenger seating capacity of 16 through 19, three emergency exits, as defined in § 23.807(b) of this chapter, are required with one on the same side as the door and two on the side opposite the door. (<E T="03">h</E>) An evacuation demonstration must be conducted utilizing the maximum number of occupants for which certification is desired. It must be conducted under simulated night conditions utilizing only the emergency exits on the most critical side of the aircraft. The participants must be representative of average airline passengers with no prior practice or rehearsal for the demonstration. Evacuation must be completed within 90 seconds. (<E T="03">i</E>) Each emergency exit must be marked with the word “Exit” by a sign which has white letters 1 inch high on a red background 2 inches high, be self-illuminated or independently internally electrically illuminated, and have a minimum luminescence (brightness) of at least 160 microlamberts. The colors may be reversed if the passenger compartment illumination is essentially the same. (<E T="03">j</E>) Access to window type emergency exits may not be obstructed by seats or seat backs. (<E T="03">k</E>) The width of the main passenger aisle at any point between seats must equal or exceed the values in the following table: <GPOTABLE CDEF="s50,r36,r36" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Number of passenger seats</CHED> <CHED H="1">Minimum main passenger aisle width</CHED> <CHED H="2">Less than 25 inches from floor</CHED> <CHED H="2">25 inches and more from floor</CHED> </BOXHD> <ROW> <ENT I="01">10 through 19</ENT> <ENT>9 inches</ENT> <ENT>15 inches.</ENT> </ROW> </GPOTABLE> (f) In lieu of compliance with Section 45 of appendix A of Part 135 of the Federal Aviation Regulations, comply with § 23.954 of this chapter.<PRTPAGE P="105"/> (g) In lieu of compliance with Section 56 of appendix A of Part 135 of the Federal Aviation Regulations, comply with the following: <E T="03">Cowlings.</E> The airplane must be designed and constructed so that no fire originating in any engine compartment can enter, either through openings or by burn through, any other region where it would create additional hazards. (h) In lieu of complaince with Section 57 of appendix A of Part 135 of the Federal Aviation Regulations, comply with § 25.863 of this chapter. 6. <E T="03">Additional requirements—general.</E> The additional requirements specified in sections 7 through 14 apply to the certification of airplanes pursuant to section 1.(b) of this Special Federal Aviation Regulation. 7. <E T="03">Compartment interiors.</E> (a) If smoking is to be prohibited, there must be a placard so stating, and if smoking is to be allowed— (1) There must be an adequate number of self-contained removable ashtrays; and (2) Where the crew compartment is separated from the passenger compartment, there must be at least one sign (using either letters or symbols) notifying all passengers when smoking is prohibited. Signs which notify when smoking is prohibited must— (i) Be legible to each passenger seated in the passenger cabin under all probable lighting conditions; and (ii) When illuminated, be so constructed that the crew can turn them on and off. (b) Each disposal receptacle for towels, paper, or waste must be fully enclosed and constructed of at least fire resistant materials, and must contain fires likely to occur in it under normal use. The ability of the disposal receptacle to contain those fires under all probable conditions of wear, misalignment, and ventilation expected in service must be demonstrated by test. A placard containing the legible words “No Cigarette Disposal” must be located on or near each disposal receptacle door. (c) Lavatories must have “No Smoking” or “No Smoking in Lavatory” placards located conspicuously on each side of the entry door, and self-contained removable ashtrays located conspicuously on or near the entry side of each lavatory door, except that one ashtray may serve more than one lavatory door if it can be seen from the cabin side of each lavatory door served. The placards must have red letters at least one-half inch high on a white background at least one inch high. (A “No smoking” symbol may be included on the placard). (d) There must be at least one hand fire extinguisher conventiently located in the pilot compartment. (e) There must be at least one hand fire extinguisher conventiently located in the passenger compartment. 8. <E T="03">Landing gear.</E> Comply with § 25.721(a)(2), (b), and (c) of this chapter in effect on September 26, 1978. 9. <E T="03">Fuel system components crashworthiness.</E> Comply with §§ 25.963(d) and 25.994 of this chapter in effect on September 26, 1978. 10. <E T="03">Shutoff means.</E> Comply with § 23.1189 of this chapter in effect on September 26, 1978. 11. <E T="03">Fire detector and extinguishing systems—</E>(a) <E T="03">Fire detector systems.</E> (1) There must be a means which ensures the prompt detection of a fire in an engine compartment. (2) Each fire detector must be constructed and installed to withstand the vibration, inertia, and other loads to which it may be subjected in operation. (3) No fire detector may be affected by any oil, water, other fluids, or fumes that might be present. (4) There must be means to allow the crew to check, in flight, the function of each fire detector electric circuit. (5) Wiring and other components of each fire detector system in an engine compartment must be at least fire resistant. (b) <E T="03">Fire extinguishing systems.</E> (1) Except for combustor, turbine, and tail pipe sections of turbine engine installations that contain lines or components carrying flammable fluids or gases for which it is shown that a fire originating in these sections can be controlled, there must be a fire extinguisher system serving each engine compartment. (2) The fire extinguishing system, the quantity of the extinguishing agent, the rate of discharge, and the discharge distribution must be adequate to extinguish fires. An individual “one shot” system may be used. (3) The fire-extinguishing system for a nacelle must be able to simultaneously protect each compartment of the nacelle for which protection is provided. 12. <E T="03">Fire extinguishing agents.</E> Comply with § 25.1197 of this chapter in effect on September 26, 1978. 13. <E T="03">Extinguishing agent containers.</E> Comply with § 25.1199 of this chapter in effect on September 26, 1978. 14. <E T="03">Fire extinguishing system materials.</E> Comply with § 25.1201 of this chapter in effect on September 26, 1978. 15. <E T="03">Expiration.</E> This Special Federal Aviation Regulation terminates on September 13, 1983, unless sooner rescinded or superseded. </EXTRACT> <CITA>[Doc. No. 18315, 44 FR 53729, Sept. 17, 1979; 45 FR 25047, Apr. 14, 1980; 45 FR 80973, Dec. 8, 1980, as amended by Doc. No. 21716, 47 FR 35153, Aug. 12, 1982]</CITA> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECTION> <SECTNO>§ 21.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This part prescribes— (1) Procedural requirements for the issue of type certificates and changes <PRTPAGE P="106"/>to those certificates; the issue of production certificates; the issue of airworthiness certificates; and the issue of export airworthiness approvals. (2) Rules governing the holders of any certificate specified in paragraph (a)(1) of this section; and (3) Procedural requirements for the approval of certain materials, parts, processes, and appliances. (b) For the purposes of this part, the word “product” means an aircraft, aircraft engine, or propeller. In addition, for the purposes of Subpart L only, it includes components and parts of aircraft, of aircraft engines, and of propellers; also parts, materials, and appliances, approved under the Technical Standard Order system. <CITA>[Doc. No. 5085, 29 FR 14563, Oct. 24, 1964, as amended by Amdt. 21-2, 30 FR 8465, July 2, 1965; Amdt. 21-6, 30 FR 11379, Sept. 8, 1965]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.2</SECTNO> <SUBJECT>Falsification of applications, reports, or records.</SUBJECT> (a) No person shall make or cause to be made— (1) Any fraudulent or intentionally false statement on any application for a certificate or approval under this part; (2) Any fraudulent or intentionally false entry in any record or report that is required to be kept, made, or used to show compliance with any requirement for the issuance or the exercise of the privileges of any certificate or approval issued under this part; (3) Any reproduction for a fraudulent purpose of any certificate or approval issued under this part. (4) Any alteration of any certificate or approval issued under this part. (b) The commission by any person of an act prohibited under paragraph (a) of this section is a basis for suspending or revoking any certificate or approval issued under this part and held by that person. <CITA>[Doc. No. 23345, 57 FR 41367, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.3</SECTNO> <SUBJECT>Reporting of failures, malfunctions, and defects.</SUBJECT> (a) Except as provided in paragraph (d) of this section, the holder of a Type Certificate (including a Supplemental Type Certificate), a Parts Manufacturer Approval (PMA), or a TSO authorization, or the licensee of a Type Certificate shall report any failure, malfunction, or defect in any product, part, process, or article manufactured by it that it determines has resulted in any of the occurrences listed in paragraph (c) of this section. (b) The holder of a Type Certificate (including a Supplemental Type Certificate), a Parts Manufacturer Approval (PMA), or a TSO authorization, or the licensee of a Type of Certificate shall report any defect in any product, part, or article manufactured by it that has left its quality control system and that it determines could result in any of the occurrences listed in paragraph (c) of this section. (c) The following occurrences must be reported as provided in paragraphs (a) and (b) of this section: (1) Fires caused by a system or equipment failure, malfunction, or defect. (2) An engine exhaust system failure, malfunction, or defect which causes damage to the engine, adjacent aircraft structure, equipment, or components. (3) The accumulation or circulation of toxic or noxious gases in the crew compartment or passenger cabin. (4) A malfunction, failure, or defect of a propeller control system. (5) A propeller or rotorcraft hub or blade structural failure. (6) Flammable fluid leakage in areas where an ignition source normally exists. (7) A brake system failure caused by structural or material failure during operation. (8) A significant aircraft primary structural defect or failure caused by any autogenous condition (fatigue, understrength, corrosion, etc.). (9) Any abnormal vibration or buffeting caused by a structural or system malfunction, defect, or failure. (10) An engine failure. (11) Any structural or flight control system malfunction, defect, or failure which causes an interference with normal control of the aircraft for which derogates the flying qualities. (12) A complete loss of more than one electrical power generating system or hydraulic power system during a given operation of the aircraft. (13) A failure or malfunction of more than one attitude, airspeed, or altitude <PRTPAGE P="107"/>instrument during a given operation of the aircraft. (d) The requirements of paragraph (a) of this section do not apply to— (1) Failures, malfunctions, or defects that the holder of a Type Certificate (including a Supplemental Type Certificate), Parts Manufacturer Approval (PMA), or TSO authorization, or the licensee of a Type Certificate— (i) Determines were caused by improper maintenance, or improper usage; (ii) Knows were reported to the FAA by another person under the Federal Aviation Regulations; or (iii) Has already reported under the accident reporting provisions of Part 430 of the regulations of the National Transportation Safety Board. (2) Failures, malfunctions, or defects in products, parts, or articles manufactured by a foreign manufacturer under a U.S. Type Certificate issued under § 21.29 or § 21.617, or exported to the United States under § 21.502. (e) Each report required by this section— (1) Shall be made to the Aircraft Certification Office in the region in which the person required to make the report is located within 24 hours after it has determined that the failure, malfunction, or defect required to be reported has occurred. However, a report that is due on a Saturday or a Sunday may be delivered on the following Monday and one that is due on a holiday may be delivered on the next workday; (2) Shall be transmitted in a manner and form acceptable to the Administrator and by the most expeditious method available; and (3) Shall include as much of the following information as is available and applicable: (i) Aircraft serial number. (ii) When the failure, malfunction, or defect is associated with an article approved under a TSO authorization, the article serial number and model designation, as appropriate. (iii) When the failure, malfunction, or defect is associated with an engine or propeller, the engine or propeller serial number, as appropriate. (iv) Product model. (v) Identification of the part, component, or system involved. The identification must include the part number. (vi) Nature of the failure, malfunction, or defect. (f) Whenever the investigation of an accident or service difficulty report shows that an article manufactured under a TSO authorization is unsafe because of a manufacturing or design defect, the manufacturer shall, upon request of the Administrator, report to the Administrator the results of its investigation and any action taken or proposed by the manufacturer to correct that defect. If action is required to correct the defect in existing articles, the manufacturer shall submit the data necessary for the issuance of an appropriate airworthiness directive to the Manager of the Aircraft Certification Office for the geographic area of the FAA regional office in the region in which it is located. <CITA>[Amdt. 21-36, 35 FR 18187, Nov. 28, 1970, as amended by Amdt. 21-37, 35 FR 18450, Dec. 4, 1970; Amdt. 21-50, 45 FR 38346, June 9, 1980; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.5</SECTNO> <SUBJECT>Airplane or Rotorcraft Flight Manual.</SUBJECT> (a) With each airplane or rotorcraft that was not type certificated with an Airplane or Rotorcraft Flight Manual and that has had no flight time prior to March 1, 1979, the holder of a Type Certificate (including a Supplemental Type Certificate) or the licensee of a Type Certificate shall make available to the owner at the time of delivery of the aircraft a current approved Airplane or Rotorcraft Flight Manual. (b) The Airplane or Rotorcraft Flight Manual required by paragraph (a) of this section must contain the following information: (1) The operating limitations and information required to be furnished in an Airplane or Rotorcraft Flight Manual or in manual material, markings, and placards, by the applicable regulations under which the airplane or rotorcraft was type certificated. (2) The maximum ambient atmospheric temperature for which engine cooling was demonstrated must be stated in the performance information section of the Flight Manual, if the applicable regulations under which the <PRTPAGE P="108"/>aircraft was type certificated do not require ambient temperature on engine cooling operating limitations in the Flight Manual. <CITA>[Amdt. 21-46, 43 FR 2316, Jan. 16, 1978]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Type Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14564, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.11</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes— (a) Procedural requirements for the issue of type certificates for aircraft, aircraft engines, and propellers; and (b) Rules governing the holders of those certificates. </SECTION> <SECTION> <SECTNO>§ 21.13</SECTNO> <SUBJECT>Eligibility.</SUBJECT> Any interested person may apply for a type certificate. <CITA>[Amdt. 21-25, 34 FR 14068, Sept. 5, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.15</SECTNO> <SUBJECT>Application for type certificate.</SUBJECT> (a) An application for a type certificate is made on a form and in a manner prescribed by the Administrator and is submitted to the appropriate Aircraft Certification Office. (b) An application for an aircraft type certificate must be accompanied by a three-view drawing of that aircraft and available preliminary basic data. (c) An application for an aircraft engine type certificate must be accompanied by a description of the engine design features, the engine operating characteristics, and the proposed engine operating limitations. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-40, 39 FR 35459, Oct. 1, 1974; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.16</SECTNO> <SUBJECT>Special conditions.</SUBJECT> If the Administrator finds that the airworthiness regulations of this subchapter do not contain adequate or appropriate safety standards for an aircraft, aircraft engine, or propeller because of a novel or unusual design feature of the aircraft, aircraft engine or propeller, he prescribes special conditions and amendments thereto for the product. The special conditions are issued in accordance with Part 11 of this chapter and contain such safety standards for the aircraft, aircraft engine or propeller as the Administrator finds necessary to establish a level of safety equivalent to that established in the regulations. <CITA>[Amdt. 21-19, 32 FR 17851, Dec. 13, 1967; as amended by Amdt. 21-51, 45 FR 60170, Sept. 11, 1980]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.17</SECTNO> <SUBJECT>Designation of applicable regulations.</SUBJECT> (a) Except as provided in § 23.2, § 25.2, § 27.2, § 29.2 and in parts 34 and 36 of this chapter, an applicant for a type certificate must show that the aircraft, aircraft engine, or propeller concerned meets— (1) The applicable requirements of this subchapter that are effective on the date of application for that certificate unless— (i) Otherwise specified by the Administrator; or (ii) Compliance with later effective amendments is elected or required under this section; and (2) Any special conditions prescribed by the Administrator. (b) For special classes of aircraft, including the engines and propellers installed thereon (e.g., gliders, airships, and other nonconventional aircraft), for which airworthiness standards have not been issued under this subchapter, the applicable requirements will be the portions of those other airworthiness requirements contained in Parts 23, 25, 27, 29, 31, 33, and 35 found by the Administrator to be appropriate for the aircraft and applicable to a specific type design, or such airworthiness criteria as the Administrator may find provide an equivalent level of safety to those parts. (c) An application for type certification of a transport category aircraft is effective for 5 years and an application for any other type certificate is effective for 3 years, unless an applicant shows at the time of application that his product requires a longer period of time for design, development, and testing, and the Administrator approves a longer period. (d) In a case where a type certificate has not been issued, or it is clear that a type certificate will not be issued, within the time limit established under <PRTPAGE P="109"/>paragraph (c) of this section, the applicant may— (1) File a new application for a type certificate and comply with all the provisions of paragraph (a) of this section applicable to an original application; or (2) File for an extension of the original application and comply with the applicable airworthiness requirements of this subchapter that were effective on a date, to be selected by the applicant, not earlier than the date which precedes the date of issue of the type certificate by the time limit established under paragraph (c) of this section for the original application. (e) If an applicant elects to comply with an amendment to this subchapter that is effective after the filing of the application for a type certificate, he must also comply with any other amendment that the Administrator finds is directly related. (f) For primary category aircraft, the requirements are: (1) The applicable airworthiness requirements contained in parts 23, 27, 31, 33, and 35 of this subchapter, or such other airworthiness criteria as the Administrator may find appropriate and applicable to the specific design and intended use and provide a level of safety acceptable to the Administrator. (2) The noise standards of part 36 applicable to primary category aircraft. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-19, 32 FR 17851, Dec. 13, 1967; Amdt. 21-24, 34 FR 364, Jan. 10, 1969; Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-58, 50 FR 46877, Nov. 13, 1985; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-69, 56 FR 41051, Aug. 16, 1991; Amdt. 21-70, 57 FR 41367, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.19</SECTNO> <SUBJECT>Changes requiring a new type certificate.</SUBJECT> Any person who proposes to change a product must make a new application for a type certificate if— (a) The Administrator finds that the proposed change in design, configuration, power, power limitations (engines), speed limitations (engines), or weight is so extensive that a substantially complete investigation of compliance with the applicable regulations is required; (b) In the case of a normal, utility, acrobatic, commuter or transport category aircraft, the proposed change is— (1) In the number of engines or rotors; or (2) To engines or rotors using different principles of propulsion or to rotors using different principles of operation; (c) In the case of an aircraft engine, the proposed change is in the principle of operation; or (d) In the case of propellers, the proposed change is in the number of blades or principle of pitch change operation. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.21</SECTNO> <SUBJECT>Issue of type certificate: normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; special classes of aircraft; aircraft engines; propellers.</SUBJECT> An applicant is entitled to a type certificate for an aircraft in the normal, utility, acrobatic, commuter, or transport category, or for a manned free balloon, special class of aircraft, or an aircraft engine or propeller, if— (a) The product qualifies under § 21.27; or (b) The applicant submits the type design, test reports, and computations necessary to show that the product to be certificated meets the applicable airworthiness, aircraft noise, fuel venting, and exhaust emission requirements of the Federal Aviation Regulations and any special conditions prescribed by the Administrator, and the Administrator finds— (1) Upon examination of the type design, and after completing all tests and inspections, that the type design and the product meet the applicable noise, fuel venting, and emissions requirements of the Federal Aviation Regulations, and further finds that they meet the applicable airworthiness requirements of the Federal Aviation Regulations or that any airworthiness provisions not complied with are compensated for by factors that provide an equivalent level of safety; and (2) For an aircraft, that no feature or characteristic makes it unsafe for the <PRTPAGE P="110"/>category in which certification is requested. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-15, 32 FR 3735, Mar. 4, 1967; Amdt. 21-27, 34 FR 18368, Nov. 18, 1969; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.23</SECTNO> <RESERVED>[Reserved]</RESERVED> </SECTION> <SECTION> <SECTNO>§ 21.24</SECTNO> <SUBJECT>Issuance of type certificate: primary category aircraft.</SUBJECT> (a) The applicant is entitled to a type certificate for an aircraft in the primary category if— (1) The aircraft— (i) Is unpowered; is an airplane powered by a single, naturally aspirated engine with a 61-knot or less V<E T="52">so</E> stall speed as defined in § 23.49; or is a rotorcraft with a 6-pound per square foot main rotor disc loading limitation, under sea level standard day conditions; (ii) Weighs not more than 2,700 pounds; or, for seaplanes, not more than 3,375 pounds; (iii) Has a maximum seating capacity of not more than four persons, including the pilot; and (iv) Has an unpressurized cabin. (2) The applicant has submitted— (i) Except as provided by paragraph (c) of this section, a statement, in a form and manner acceptable to the Administrator, certifying that: the applicant has completed the engineering analysis necessary to demonstrate compliance with the applicable airworthiness requirements; the applicant has conducted appropriate flight, structural, propulsion, and systems tests necessary to show that the aircraft, its components, and its equipment are reliable and function properly; the type design complies with the airworthiness standards and noise requirements established for the aircraft under § 21.17(f); and no feature or characteristic makes it unsafe for its intended use; (ii) The flight manual required by § 21.5(b), including any information required to be furnished by the applicable airworthiness standards; (iii) Instructions for continued airworthiness in accordance with § 21.50(b); and (iv) A report that: summarizes how compliance with each provision of the type certification basis was determined; lists the specific documents in which the type certification data information is provided; lists all necessary drawings and documents used to define the type design; and lists all the engineering reports on tests and computations that the applicant must retain and make available under § 21.49 to substantiate compliance with the applicable airworthiness standards. (3) The Administrator finds that— (i) The aircraft complies with those applicable airworthiness requirements approved under § 21.17(f) of this part; and (ii) The aircraft has no feature or characteristic that makes it unsafe for its intended use. (b) An applicant may include a special inspection and preventive maintenance program as part of the aircraft's type design or supplemental type design. (c) For aircraft manufactured outside of the United States in a country with which the United States has a bilateral airworthiness agreement for the acceptance of these aircraft, and from which the aircraft is to be imported into the United States— (1) The statement required by paragraph (a)(2)(i) of this section must be made by the civil airworthiness authority of the exporting country; and (2) The required manuals, placards, listings, instrument markings, and documents required by paragraphs (a) and (b) of this section must be submitted in English. <CITA>[Doc. No. 23345, 57 FR 41367, Sept. 9, 1992; as amended by Amdt. 21-75, 62 FR 62808, Nov. 25, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.25</SECTNO> <SUBJECT>Issue of type certificate: Restricted category aircraft.</SUBJECT> (a) An applicant is entitled to a type certificate for an aircraft in the restricted category for special purpose operations if he shows compliance with the applicable noise requirements of Part 36 of this chapter, and if he shows that no feature or characteristic of the aircraft makes it unsafe when it is operated under the limitations prescribed for its intended use, and that the aircraft— (1) Meets the airworthiness requirements of an aircraft category except <PRTPAGE P="111"/>those requirements that the Administrator finds inappropriate for the special purpose for which the aircraft is to be used; or (2) Is of a type that has been manufactured in accordance with the requirements of and accepted for use by, an Armed Force of the United States and has been later modified for a special purpose. (b) For the purposes of this section, “special purpose operations” includes— (1) Agricultural (spraying, dusting, and seeding, and livestock and predatory animal control); (2) Forest and wildlife conservation; (3) Aerial surveying (photography, mapping, and oil and mineral exploration); (4) Patrolling (pipelines, power lines, and canals); (5) Weather control (cloud seeding); (6) Aerial advertising (skywriting, banner towing, airborne signs and public address systems); and (7) Any other operation specified by the Administrator. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-42, 40 FR 1033, Jan. 6, 1975]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.27</SECTNO> <SUBJECT>Issue of type certificate: surplus aircraft of the Armed Forces.</SUBJECT> (a) Except as provided in paragraph (b) of this section an applicant is entitled to a type certificate for an aircraft in the normal, utility, acrobatic, commuter, or transport category that was designed and constructed in the United States, accepted for operational use, and declared surplus by, an Armed Force of the United States, and that is shown to comply with the applicable certification requirements in paragraph (f) of this section. (b) An applicant is entitled to a type certificate for a surplus aircraft of the Armed Forces of the United States that is a counterpart of a previously type certificated civil aircraft, if he shows compliance with the regulations governing the original civil aircraft type certificate. (c) Aircraft engines, propellers, and their related accessories installed in surplus Armed Forces aircraft, for which a type certificate is sought under this section, will be approved for use on those aircraft if the applicant shows that on the basis of the previous military qualifications, acceptance, and service record, the product provides substantially the same level of airworthiness as would be provided if the engines or propellers were type certificated under Part 33 or 35 of the Federal Aviation Regulations. (d) The Administrator may relieve an applicant from strict compliance with a specific provision of the applicable requirements in paragraph (f) of this section, if the Administrator finds that the method of compliance proposed by the applicant provides substantially the same level of airworthiness and that strict compliance with those regulations would impose a severe burden on the applicant. The Administrator may use experience that was satisfactory to an Armed Force of the United States in making such a determination. (e) The Administrator may require an applicant to comply with special conditions and later requirements than those in paragraphs (c) and (f) of this section, if the Administrator finds that compliance with the listed regulations would not ensure an adequate level of airworthiness for the aircraft. (f) Except as provided in paragraphs (b) through (e) of this section, an applicant for a type certificate under this section must comply with the appropriate regulations listed in the following table: <GPOTABLE CDEF="s120,r65,r95" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Type of aircraft</CHED> <CHED H="1">Date accepted for operational use by the Armed Forces of the United States</CHED> <CHED H="1">Regulations that apply <SU>1</SU> </CHED> </BOXHD> <ROW> <ENT I="01">Small reciprocating-engine powered airplanes</ENT> <ENT>Before May 16, 1956<LI>After May 15, 1956</LI> </ENT> <ENT>CAR Part 3, as effective May 15, 1956.<LI>CAR Part 3, or FAR Part 23.</LI> </ENT> </ROW> <ROW> <ENT I="01">Small turbine engine-powered airplanes</ENT> <ENT>Before Oct. 2, 1959<LI>After Oct. 1, 1959</LI> </ENT> <ENT>CAR Part 3, as effective Oct. 1, 1959. <LI>CAR Part 3 or FAR Part 23.</LI> </ENT> </ROW> <ROW> <ENT I="01">Commuter category airplanes</ENT> <ENT>After (Feb. 17, 1987) <LI>FAR Part 23 as of (Feb. 17, 1987).</LI> </ENT> </ROW> <ROW> <ENT I="01">Large reciprocating-engine powered airplanes</ENT> <ENT>Before Aug. 26, 1955<LI>After Aug. 25, 1959</LI> </ENT> <ENT>CAR Part 4b, as effective Aug. 25, 1955. <LI>CAR Part 4b or FAR Part 25.</LI> </ENT> </ROW> <ROW> <PRTPAGE P="112"/> <ENT I="01">Large turbine engine-powered airplanes</ENT> <ENT>Before Oct. 2, 1959<LI>After Oct. 1, 1959</LI> </ENT> <ENT>CAR Part 4b, as effective Oct. 1, 1959. <LI>CAR Part 4b or FAR Part 25.</LI> </ENT> </ROW> <ROW> <ENT I="11">Rotorcraft with maximum certificated takeoff weight of:</ENT> </ROW> <ROW> <ENT I="02">6,000 pounds or less</ENT> <ENT>Before Oct. 2, 1959<LI>After Oct. 1, 1959</LI> </ENT> <ENT>CAR Part 6, as effective Oct. 1, 1959. <LI>CAR Part 6, or FAR Part 27.</LI> </ENT> </ROW> <ROW> <ENT I="02">Over 6,000 pounds</ENT> <ENT>Before Oct. 2, 1959<LI>After Oct. 1, 1959</LI> </ENT> <ENT>CAR Part 7, as effective Oct. 1, 1959. <LI>CAR Part 7, or FAR Part 29.</LI> </ENT> </ROW> <TNOTE> <SU>1</SU> Where no specific date is listed, the applicable regulations are those in effect on the date that the first aircraft of the particular model was accepted for operational use by the Armed Forces.</TNOTE> </GPOTABLE> <CITA TYPE="W">[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987; 52 FR 7262, Mar. 9, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.29</SECTNO> <SUBJECT>Issue of type certificate: import products.</SUBJECT> (a) A type certificate may be issued for a product that is manufactured in a foreign country with which the United States has an agreement for the acceptance of these products for export and import and that is to be imported into the United States if— (1) The country in which the product was manufactured certifies that the product has been examined, tested, and found to meet— (i) The applicable aircraft noise, fuel venting and exhaust emissions requirements of this subchapter as designated in § 21.17, or the applicable aircraft noise, fuel venting and exhaust emissions requirements of the country in which the product was manufactured, and any other requirements the Administrator may prescribe to provide noise, fuel venting and exhaust emission levels no greater than those provided by the applicable aircraft noise, fuel venting, and exhaust emission requirements of this subchapter as designated in § 21.17; and (ii) The applicable airworthiness requirements of this subchapter as designated in § 21.17, or the applicable airworthiness requirements of the country in which the product was manufactured and any other requirements the Administrator may prescribe to provide a level of safety equivalent to that provided by the applicable airworthiness requirements of this subchapter as designated in § 21.17; (2) The applicant has submitted the technical data, concerning aircraft noise and airworthiness, respecting the product required by the Administrator; and (3) The manuals, placards, listings, and instrument markings required by the applicable airworthiness (and noise, where applicable) requirements are presented in the English language. (b) A product type certificated under this section is considered to be type certificated under the noise standards of part 36, and the fuel venting and exhaust emission standards of part 34, of the Federal Aviation Regulations where compliance therewith is certified under paragraph (a)(1)(i) of this section, and under the airworthiness standards of that part of the Federal Aviation Regulations with which compliance is certified under paragraph (a)(1)(ii) of this section or to which an equivalent level of safety is certified under paragraph (a)(1)(ii) of this section. <CITA>[Amdt. 21-27, 34 FR 18363, Nov. 18, 1969, as amended by Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; 55 FR 37287, Sept. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.31</SECTNO> <SUBJECT>Type design.</SUBJECT> The type design consists of— (a) The drawings and specifications, and a listing of those drawings and specifications, necessary to define the configuration and the design features of the product shown to comply with the requirements of that part of this subchapter applicable to the product; (b) Information on dimensions, materials, and processes necessary to define the structural strength of the product; (c) The Airworthiness Limitations section of the Instructions for Continued Airworthiness as required by Parts <PRTPAGE P="113"/>23, 25, 27, 29, 31, 33, and 35 of this chapter or as otherwise required by the Administrator; and as specified in the applicable airworthiness criteria for special classes of aircraft defined in § 21.17(b); and (d) For primary category aircraft, if desired, a special inspection and preventive maintenance program designed to be accomplished by an appropriately rated and trained pilot-owner. (e) Any other data necessary to allow, by comparison, the determination of the airworthiness, noise characteristics, fuel venting, and exhaust emissions (where applicable) of later products of the same type. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-27, 34 FR 18363, Nov. 18, 1969; Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.33</SECTNO> <SUBJECT>Inspection and tests.</SUBJECT> (a) Each applicant must allow the Administrator to make any inspection and any flight and ground test necessary to determine compliance with the applicable requirements of the Federal Aviation Regulations. However, unless otherwise authorized by the Administrator— (1) No aircraft, aircraft engine, propeller, or part thereof may be presented to the Administrator for test unless compliance with paragraphs (b)(2) through (b)(4) of this section has been shown for that aircraft, aircraft engine, propeller, or part thereof; and (2) No change may be made to an aircraft, aircraft engine, propeller, or part thereof between the time that compliance with paragraphs (b)(2) through (b)(4) of this section is shown for that aircraft, aircraft engine, propeller, or part thereof and the time that it is presented to the Administrator for test. (b) Each applicant must make all inspections and tests necessary to determine— (1) Compliance with the applicable airworthiness, aircraft noise, fuel venting, and exhaust emission requirements; (2) That materials and products conform to the specifications in the type design; (3) That parts of the products conform to the drawings in the type design; and (4) That the manufacturing processes, construction and assembly conform to those specified in the type design. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-17, 32 FR 14926, Oct. 28, 1967; Amdt. 21-27, 34 FR 18363, Nov. 18, 1969; Amdt. 21-44, 41 FR 55463, Dec. 20, 1976; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.35</SECTNO> <SUBJECT>Flight tests.</SUBJECT> (a) Each applicant for an aircraft type certificate (other than under §§ 21.24 through 21.29) must make the tests listed in paragraph (b) of this section. Before making the tests the applicant must show— (1) Compliance with the applicable structural requirements of this subchapter; (2) Completion of necessary ground inspections and tests; (3) That the aircraft conforms with the type design; and (4) That the Administrator received a flight test report from the applicant (signed, in the case of aircraft to be certificated under Part 25 [New] of this chapter, by the applicant's test pilot) containing the results of his tests. (b) Upon showing compliance with paragraph (a) of this section, the applicant must make all flight tests that the Administrator finds necessary— (1) To determine compliance with the applicable requirements of this subchapter; and (2) For aircraft to be certificated under this subchapter, except gliders and except airplanes of 6,000 lbs. or less maximum certificated weight that are to be certificated under Part 23 of this chapter, to determine whether there is reasonable assurance that the aircraft, its components, and its equipment are reliable and function properly. (c) Each applicant must, if practicable, make the tests prescribed in paragraph (b)(2) of this section upon the aircraft that was used to show compliance with— (1) Paragraph (b)(1) of this section; and<PRTPAGE P="114"/> (2) For rotorcraft, the rotor drive endurance tests prescribed in § 27.923 or § 29.923 of this chapter, as applicable. (d) Each applicant must show for each flight test (except in a glider or a manned free balloon) that adequate provision is made for the flight test crew for emergency egress and the use of parachutes. (e) Except in gliders and manned free balloons, an applicant must discontinue flight tests under this section until he shows that corrective action has been taken, whenever— (1) The applicant's test pilot is unable or unwilling to make any of the required flight tests; or (2) Items of noncompliance with requirements are found that may make additional test data meaningless or that would make further testing unduly hazardous. (f) The flight tests prescribed in paragraph (b)(2) of this section must include— (1) For aircraft incorporating turbine engines of a type not previously used in a type certificated aircraft, at least 300 hours of operation with a full complement of engines that conform to a type certificate; and (2) For all other aircraft, at least 150 hours of operation. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-40, 39 FR 35459, Oct. 1, 1974; Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.37</SECTNO> <SUBJECT>Flight test pilot.</SUBJECT> Each applicant for a normal, utility, acrobatic, commuter, or transport category aircraft type certificate must provide a person holding an appropriate pilot certificate to make the flight tests required by this part. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.39</SECTNO> <SUBJECT>Flight test instrument calibration and correction report.</SUBJECT> (a) Each applicant for a normal, utility, acrobatic, commuter, or transport category aircraft type certificate must submit a report to the Administrator showing the computations and tests required in connection with the calibration of instruments used for test purposes and in the correction of test results to standard atmospheric conditions. (b) Each applicant must allow the Administrator to conduct any flight tests that he finds necessary to check the accuracy of the report submitted under paragraph (a) of this section. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.41</SECTNO> <SUBJECT>Type certificate.</SUBJECT> Each type certificate is considered to include the type design, the operating limitations, the certificate data sheet, the applicable regulations of this subchapter with which the Administrator records compliance, and any other conditions or limitations prescribed for the product in this subchapter. </SECTION> <SECTION> <SECTNO>§ 21.43</SECTNO> <SUBJECT>Location of manufacturing facilities.</SUBJECT> Except as provided in § 21.29, the Administrator does not issue a type certificate if the manufacturing facilities for the product are located outside of the United States, unless the Administrator finds that the location of the manufacturer's facilities places no undue burden on the FAA in administering applicable airworthiness requirements. </SECTION> <SECTION> <SECTNO>§ 21.45</SECTNO> <SUBJECT>Privileges.</SUBJECT> The holder or licensee of a type certificate for a product may— (a) In the case of aircraft, upon compliance with §§ 21.173 through 21.189, obtain airworthiness certificates; (b) In the case of aircraft engines or propellers, obtain approval for installation or certified aircraft; (c) In the case of any product, upon compliance with §§ 21.133 through 21.163, obtain a production certificate for the type certificated product; (d) Obtain approval of replacement parts for that product. </SECTION> <SECTION> <SECTNO>§ 21.47</SECTNO> <SUBJECT>Transferability.</SUBJECT> A type certificate may be transferred to or made available to third persons by licensing agreements. Each grantor shall, within 30 days after the transfer of a certificate or execution or termination of a licensing agreement, notify in writing the appropriate Aircraft Certification Office. The notification must <PRTPAGE P="115"/>state the name and address of the transferee or licensee, date of the transaction, and in the case of a licensing agreement, the extent of authority granted the licensee. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.49</SECTNO> <SUBJECT>Availability.</SUBJECT> The holder of a type certificate shall make the certificate available for examination upon the request of the Administrator or the National Transportation Safety Board. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.50</SECTNO> <SUBJECT>Instructions for continued airworthiness and manufacturer's maintenance manuals having airworthiness limitations sections.</SUBJECT> (a) The holder of a type certificate for a rotorcraft for which a Rotorcraft Maintenance Manual containing an “Airworthiness Limitations” section has been issued under § 27.1529 (a)(2) or § 29.1529 (a)(2) of this chapter, and who obtains approval of changes to any replacement time, inspection interval, or related procedure in that section of the manual, shall make those changes available upon request to any operator of the same type of rotorcraft. (b) The holder of a design approval, including either the type certificate or supplemental type certificate for an aircraft, aircraft engine, or propeller for which application was made after January 28, 1981, shall furnish at least one set of complete Instructions for Continued Airworthiness, prepared in accordance with §§ 23.1529, 25.1529, 27.1529, 29.1529, 31.82, 33.4, or 35.4 of this chapter, or as specified in the applicable airworthiness criteria for special classes of aircraft defined in § 21.17(b), as applicable, to the owner of each type of aircraft, aircraft engine, or propeller upon its delivery, or upon issuance of the first standard airworthiness certificate for the affected aircraft, whichever occurs later, and thereafter make those instructions available to any other person required by this chapter to comply with any of the terms of these instructions. In addition, changes to the Instructions for Continued Airworthiness shall be made available to any person required by this chapter to comply with any of those instructions. <CITA>[Amdt. No. 21-23, 33 FR 14105, Sept. 18, 1968, as amended by Amdt. No 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.51</SECTNO> <SUBJECT>Duration.</SUBJECT> A type certificate is effective until surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.53</SECTNO> <SUBJECT>Statement of conformity.</SUBJECT> (a) Each applicant must submit a statement of conformity (FAA Form 317) to the Administrator for each aircraft engine and propeller presented to the Administrator for type certification. This statement of conformity must include a statement that the aircraft engine or propeller conforms to the type design therefor. (b) Each applicant must submit a statement of conformity to the Administrator for each aircraft or part thereof presented to the Administrator for tests. This statement of conformity must include a statement that the applicant has complied with § 21.33(a) (unless otherwise authorized under that paragraph). <CITA>[Amdt. 21-17, 32 FR 14926, Oct. 28, 1967]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Provisional Type Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14566, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.71</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes— (a) Procedural requirements for the issue of provisional type certificates, amendments to provisional type certificates, and provisional amendments to type certificates; and (b) Rules governing the holders of those certificates. </SECTION> <SECTION> <SECTNO>§ 21.73</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) Any manufacturer of aircraft manufactured within the United States who is a United States citizen may apply for Class I or Class II provisional type certificates, for amendments to provisional type certificates held by <PRTPAGE P="116"/>him, and for provisional amendments to type certificates held by him. (b) Any manufacturer of aircraft manufactured in a foreign country with which the United States has an agreement for the acceptance of those aircraft for export and import may apply for a Class II provisional type certificate, for amendments to provisional type certificates held by him, and for provisional amendments to type certificates held by him. (c) An aircraft engine manufacturer who is a United States citizen and who has altered a type certificated aircraft by installing different type certificated aircraft engines manufactured by him within the United States may apply for a Class I provisional type certificate for the aircraft, and for amendments to Class I provisional type certificates held by him, if the basic aircraft, before alteration, was type certificated in the normal, utility, acrobatic, commuter, or transport category. <CITA>[Doc. No. 5085, 29 FR 14566, Oct. 24, 1964, as amended by Amdt. 21-12, 31 FR 13380, Oct. 15, 1966; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.75</SECTNO> <SUBJECT>Application.</SUBJECT> Applications for provisional type certificates, for amendments thereto, and for provisional amendments to type certificates must be submitted to the Manager of the Aircraft Certification Office for the geographic area in which the applicant is located (or in the case of European, African, Middle East Region, the Manager, Aircraft Engineering Division), and must be accompanied by the pertinent information specified in this subpart. <CITA>[Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.77</SECTNO> <SUBJECT>Duration.</SUBJECT> (a) Unless sooner surrendered, superseded, revoked, or otherwise terminated, provisional type certificates and amendments thereto are effective for the periods specified in this section. (b) A Class I provisional type certificate is effective for 24 months after the date of issue. (c) A Class II provisional type certificate is effective for twelve months after the date of issue. (d) An amendment to a Class I or Class II provisional type certificate is effective for the duration of the amended certificate. (e) A provisional amendment to a type certificate is effective for six months after its approval or until the amendment of the type certificate is approved, whichever is first. <CITA>[Doc. No. 5085, 29 FR 14566, Oct. 24, 1964 as amended by Amdt. 21-7, 30 FR 14311, Nov. 16, 1965]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.79</SECTNO> <SUBJECT>Transferability.</SUBJECT> Provisional type certificates are not transferable. </SECTION> <SECTION> <SECTNO>§ 21.81</SECTNO> <SUBJECT>Requirements for issue and amendment of Class I provisional type certificates.</SUBJECT> (a) An applicant is entitled to the issue or amendment of a Class I provisional type certificate if he shows compliance with this section and the Administrator finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations established in paragraph (e) of this section and in § 91.317 of this chapter. (b) The applicant must apply for the issue of a type or supplemental type certificate for the aircraft. (c) The applicant must certify that— (1) The aircraft has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type or supplemental type certificate applied for; (2) The aircraft substantially meets the applicable flight characteristic requirements for the type or supplemental type certificate applied for; and (3) The aircraft can be operated safely under the appropriate operating limitations specified in paragraph (a) of this section. (d) The applicant must submit a report showing that the aircraft had been flown in all maneuvers necessary to show compliance with the flight requirements for the issue of the type or supplemental type certificate applied for, and to establish that the aircraft can be operated safely in accordance with the limitations contained in this subchapter. (e) The applicant must establish all limitations required for the issue of the type or supplemental type certificate <PRTPAGE P="117"/>applied for, including limitations on weights, speeds, flight maneuvers, loading, and operation of controls and equipment unless, for each limitation not so established, appropriate operating restrictions are established for the aircraft. (f) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (g) The applicant must show that a prototype aircraft has been flown for at least 50 hours under an experimental certificate issued under §§ 21.191 through 21.195, or under the auspices of an Armed Force of the United States. However, in the case of an amendment to a provisional type certificate, the Administrator may reduce the number of required flight hours. <CITA>[Doc. No. 5085, 29 FR 14566, Oct. 24, 1964, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.83</SECTNO> <SUBJECT>Requirements for issue and amendment of Class II provisional type certificates.</SUBJECT> (a) An applicant who manufactures aircraft within the United States is entitled to the issue or amendment of a Class II provisional type certificate if he shows compliance with this section and the Administrator finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations in paragraph (h) of this section, and §§ 91.317 and 121.207 of this chapter. (b) An applicant who manufactures aircraft in a country with which the United States has an agreement for the acceptance of those aircraft for export and import is entitled to the issue or amendment of a Class II provisional type certificate if the country in which the aircraft was manufactured certifies that the applicant has shown compliance with this section, that the aircraft meets the requirements of paragraph (f) of this section and that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations in paragraph (h) of this section and §§ 91.317 and 121.207 of this chapter. (c) The applicant must apply for a type certificate, in the transport category, for the aircraft. (d) The applicant must hold a U.S. type certificate for at least one other aircraft in the same transport category as the subject aircraft. (e) The FAA's official flight test program or the flight test program conducted by the authorities of the country in which the aircraft was manufactured, with respect to the issue of a type certificate for that aircraft, must be in progress. (f) The applicant or, in the case of a foreign manufactured aircraft, the country in which the aircraft was manufactured, must certify that— (1) The aircraft has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type certificate applied for; (2) The aircraft substantially complies with the applicable flight characteristic requirements for the type certificate applied for; and (3) The aircraft can be operated safely under the appropriate operating limitations in this subchapter. (g) The applicant must submit a report showing that the aircraft has been flown in all maneuvers necessary to show compliance with the flight requirements for the issue of the type certificate and to establish that the aircraft can be operated safely in accordance with the limitations in this subchapter. (h) The applicant must prepare a provisional aircraft flight manual containing all limitations required for the issue of the type certificate applied for, including limitations on weights, speeds, flight maneuvers, loading, and operation of controls and equipment unless, for each limitation not so established, appropriate operating restrictions are established for the aircraft. (i) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (j) The applicant must show that a prototype aircraft has been flown for at least 100 hours. In the case of an <PRTPAGE P="118"/>amendment to a provisional type certificate, the Administrator may reduce the number of required flight hours. <CITA>[Amdt. 21-12, 31 FR 13386, Oct. 15, 1966, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.85</SECTNO> <SUBJECT>Provisional amendments to type certificates.</SUBJECT> (a) An applicant who manufactures aircraft within the United States is entitled to a provisional amendment to a type certificate if he shows compliance with this section and the Administrator finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated under the appropriate limitations contained in this subchapter. (b) An applicant who manufactures aircraft in a foreign country with which the United States has an agreement for the acceptance of those aircraft for export and import is entitled to a provisional amendment to a type certificate if the country in which the aircraft was manufactured certifies that the applicant has shown compliance with this section, that the aircraft meets the requirements of paragraph (e) of this section and that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated under the appropriate limitations contained in this subchapter. (c) The applicant must apply for an amendment to the type certificate. (d) The FAA's official flight test program or the flight test program conducted by the authorities of the country in which the aircraft was manufactured, with respect to the amendment of the type certificate, must be in progress. (e) The applicant or, in the case of foreign manufactured aircraft, the country in which the aircraft was manufactured, must certify that— (1) The modification involved in the amendment to the type certificate has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type certificate for the aircraft; (2) The aircraft substantially complies with the applicable flight characteristic requirements for the type certificate; and (3) The aircraft can be operated safely under the appropriate operating limitations in this subchapter. (f) The applicant must submit a report showing that the aircraft incorporating the modifications involved has been flown in all maneuvers necessary to show compliance with the flight requirements applicable to those modifications and to establish that the aircraft can be operated safely in accordance with the limitations specified in §§ 91.317 and 121.207 of this chapter. (g) The applicant must establish and publish, in a provisional aircraft flight manual or other document and on appropriate placards, all limitations required for the issue of the type certificate applied for, including weight, speed, flight maneuvers, loading, and operation of controls and equipment, unless, for each limitation not so established, appropriate operating restrictions are established for the aircraft. (h) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (i) The applicant must operate a prototype aircraft modified in accordance with the corresponding amendment to the type certificate for the number of hours found necessary by the Administrator. <CITA>[Amdt. 21-12, 31 FR 13388, Oct. 15, 1966, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Changes to Type Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14567, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.91</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the approval of changes to type certificates. </SECTION> <SECTION> <SECTNO>§ 21.93</SECTNO> <SUBJECT>Classification of changes in type design.</SUBJECT> (a) In addition to changes in type design specified in paragraph (b) of this section, changes in type design are classified as minor and major. A “minor change” is one that has no appreciable effect on the weight, balance, <PRTPAGE P="119"/>structural strength, reliability, operational characteristics, or other characteristics affecting the airworthiness of the product. All other changes are “major changes” (except as provided in paragraph (b) of this section). (b) For the purpose of complying with Part 36 of this chapter, and except as provided in paragraphs (b)(2), (b)(3), and (b)(4) of this section, any voluntary change in the type design of an aircraft that may increase the noise levels of that aircraft is an “acoustical change” (in addition to being a minor or major change as classified in paragraph (a) of this section) for the following aircraft: (1) Transport category large airplanes. (2) Turbojet powered airplanes (regardless of category). For airplanes to which this paragraph applies, “acoustical changes” do not include changes in type design that are limited to one of the following— (i) Gear down flight with one or more retractable landing gear down during the entire flight, or (ii) Spare engine and nacelle carriage external to the skin of the airplane (and return of the pylon or other external mount), or (iii) Time-limited engine and/or nacelle changes, where the change in type design specifies that the airplane may not be operated for a period of more than 90 days unless compliance with the applicable acoustical change provisions of Part 36 of this chapter is shown for that change in type design. (3) Propeller driven commuter category and small airplanes in the primary, normal, utility, acrobatic, transport, and restricted categories, except for airplanes that are: (i) Designated for “agricultural aircraft operations” (as defined in § 137.3 of this chapter, effective January 1, 1966) to which § 36.1583 of this chapter does not apply, or (ii) Designated for dispensing fire fighting materials to which § 36.1583 of this chapter does not apply, or (iii) U.S. registered, and that had flight time prior to January 1, 1955 or (iv) Land configured aircraft reconfigured with floats or skis. This reconfiguration does not permit further exception from the requirements of this section upon any acoustical change not enumerated in § 21.93(b). (4) Helicopters except: (i) Those helicopters that are designated exclusively: (A) For “agricultural aircraft operations”, as defined in § 137.3 of this chapter, as effective on January 1, 1966; (B) For dispensing fire fighting materials; or (C) For carrying external loads, as defined in § 133.1(b) of this chapter, as effective on December 20, 1976. (ii) Those helicopters modified by installation or removal of external equipment. For purposes of this paragraph, “external equipment” means any instrument, mechanism, part, apparatus, appurtenance, or accessory that is attached to, or extends from, the helicopter exterior but is not used nor is intended to be used in operating or controlling a helicopter in flight and is not part of an airframe or engine. An “acoustical change” does not include: (A) Addition or removal of external equipment; (B) Changes in the airframe made to accommodate the addition or removal of external equipment, to provide for an external load attaching means, to facilitate the use of external equipment or external loads, or to facilitate the safe operation of the helicopter with external equipment mounted to, or external loads carried by, the helicopter; (C) Reconfiguration of the helicopter by the addition or removal of floats and skis; (D) Flight with one or more doors and/or windows removed or in an open position; or (E) Any changes in the operational limitations placed on the helicopter as a consequence of the addition or removal of external equipment, floats, and skis, or flight operations with doors and/or windows removed or in an open position. (c) For purposes of complying with part 34 of this chapter, any voluntary change in the type design of the airplane or engine which may increase <PRTPAGE P="120"/>fuel venting or exhaust emissions is an “emissions change.” <CITA>[Amdt. 21-27, 34 FR 18363, Nov. 18, 1969, as amended by Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-47, 43 FR 28419, June 29, 1978; Amdt. 21-56, 47 FR 758, Jan. 7, 1982; Amdt. 21-61, 53 FR 3539, Feb. 5, 1988; Amdt. 21-62, 53 FR 16365, May 6, 1988; Amdt. 21-63, 53 FR 47399, Nov. 22, 1988; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992; Amdt. 21-73, 61 FR 20699, May 7, 1996; 61 FR 57002, Nov. 5, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.95</SECTNO> <SUBJECT>Approval of minor changes in type design.</SUBJECT> Minor changes in a type design may be approved under a method acceptable to the Administrator before submitting to the Administrator any substantiating or descriptive data. </SECTION> <SECTION> <SECTNO>§ 21.97</SECTNO> <SUBJECT>Approval of major changes in type design.</SUBJECT> (a) In the case of a major change in type design, the applicant must submit substantiating data and necessary descriptive data for inclusion in the type design. (b) Approval of a major change in the type design of an aircraft engine is limited to the specific engine configuration upon which the change is made unless the applicant identifies in the necessary descriptive data for inclusion in the type design the other configurations of the same engine type for which approval is requested and shows that the change is compatible with the other configurations. <CITA>[Amdt. 21-40, 39 FR 35459, Oct. 1, 1974]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.99</SECTNO> <SUBJECT>Required design changes.</SUBJECT> (a) When an Airworthiness Directive is issued under Part 39 the holder of the type certificate for the product concerned must— (1) If the Administrator finds that design changes are necessary to correct the unsafe condition of the product, and upon his request, submit appropriate design changes for approval; and (2) Upon approval of the design changes, make available the descriptive data covering the changes to all operators of products previously certif-icated under the type certificate. (b) In a case where there are no current unsafe conditions, but the Administrator or the holder of the type certificate finds through service experience that changes in type design will contribute to the safety of the product, the holder of the type certificate may submit appropriate design changes for approval. Upon approval of the changes, the manufacturer shall make information on the design changes available to all operators of the same type of product. <CITA>[Doc. No. 5085, 29 FR 14567, Oct. 24, 1964, as amended by Amdt. 21-3, 30 FR 8826, July 24, 1965]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.101</SECTNO> <SUBJECT>Designation of applicable regulations.</SUBJECT> (a) Except as provided in §§ 23.2, § 25.2, 27.2 and 29.2 and parts 34 and 36 of this chapter, an applicant for a change to a type certificate must comply with either— (1) The regulations incorporated by reference in the type certificate; or (2) The applicable regulations in effect on the date of the application, plus any other amendments the Administrator finds to be directly related. (b) If the Administrator finds that a proposed change consists of a new design or a substantially complete redesign of a component, equipment installation, or system installation, and that the regulations incorporated by reference in the type certificate for the product do not provide adequate standards with respect to the proposed change, the applicant must comply with— (1) The applicable provisions of this subchapter, in effect on the date of the application for the change, that the Administrator finds necessary to provide a level of safety equal to that established by the regulations incorporated by reference in the type certificate for the product; and (2) Any special conditions, and amendments to those special conditions, prescribed by the Administrator to provide a level of safety equal to that established by the regulations incorporated by reference in the type certificate for the product. (c) Unless otherwise required by § 21.19(a), an applicant for a change to a type certificate for a transport category airplane involving the replacement of reciprocating engines with the <PRTPAGE P="121"/>same number of turbopropeller powerplants must comply with the requirements of Part 25 of this chapter applicable to the airplane as type certificated with reciprocating engines, and with the following: (1) The certification performance requirements prescribed in §§ 25.101 through 25.125 and 25.149, 25.1533, 25.1583, and 25.1587. (2) The powerplant requirements of Part 25 of this chapter applicable to turbopropeller engine-powered airplanes. (3) The requirements of Part 25 of this chapter for the standardization of cockpit controls and instruments, unless the Administrator finds that compliance with a particular detailed requirement would be impractical and would not contribute materially to standardization. (4) Any other requirement of Part 25 of this chapter applicable to turbopropeller engine-powered airplanes that the Administrator finds to be related to the changes in engines and that are necessary to ensure a level of safety equal to that of the airplane certificated with reciprocating engines. <FP>For each new limitation established with respect to weight, speed, or altitude that is significantly altered from those approved for the airplane with reciprocating engines, the applicant must show compliance with the requirements of Part 25 of this chapter applicable to the limitations being changed.</FP> <CITA>[Doc. No. 5085, 29 FR 14567, Oct. 24, 1964, as amended by Amdt. 21-16, 32 FR 13262, Sept. 20, 1967; Amdt. 21-19, 32 FR 17851, Dec. 13, 1967; Amdt. 21-27, 34 FR 18363, Nov. 18, 1969; Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-58, 50 FR 46877, Nov. 13, 1985; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-69, 56 FR 41051, Aug. 16, 1991]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Supplemental Type Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14568, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.111</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the issue of supplemental type certificates. </SECTION> <SECTION> <SECTNO>§ 21.113</SECTNO> <SUBJECT>Requirement of supplemental type certificate.</SUBJECT> Any person who alters a product by introducing a major change in type design, not great enough to require a new application for a type certificate under § 21.19, shall apply to the Administrator for a supplemental type certificate, except that the holder of a type certificate for the product may apply for amendment of the original type certificate. The application must be made in a form and manner prescribed by the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.115</SECTNO> <SUBJECT>Applicable requirements.</SUBJECT> (a) Each applicant for a supplemental type certificate must show that the altered product meets applicable airworthiness requirements as specified in paragraphs (a) and (b) of § 21.101 and, in the case of an acoustical change described in § 21.93(b), show compliance with the applicable noise requirements of part 36 of this chapter and, in the case of an emissions change described in § 21.93(c), show compliance with the applicable fuel venting and exhaust emissions requirements of part 34 of this chapter. (b) Each applicant for a supplemental type certificate must meet §§ 21.33 and 21.53 with respect to each change in the type design. <CITA>[Amdt. 21-17, 32 FR 14927, Oct. 28, 1967, as amended by Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-52A, 45 FR 79009, Nov. 28, 1980; Amdt. 21-61, 53 FR 3540, Feb. 5, 1988; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-71, 57 FR 42854, Sept. 16, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.117</SECTNO> <SUBJECT>Issue of supplemental type certificates.</SUBJECT> (a) An applicant is entitled to a supplemental type certificate if he meets the requirements of §§ 21.113 and 21.115. (b) A supplemental type certificate consists of— (1) The approval by the Administrator of a change in the type design of the product; and (2) The type certificate previously issued for the product. </SECTION> <SECTION> <SECTNO>§ 21.119</SECTNO> <SUBJECT>Privileges.</SUBJECT> The holder of a supplemental type certificate may— (a) In the case of aircraft, obtain airworthiness certificates;<PRTPAGE P="122"/> (b) In the case of other products, obtain approval for installation on certificated aircraft; and (c) Obtain a production certificate for the change in the type design that was approved by that supplemental type certificate. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Production Under Type Certificate Only</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14568, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.121</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes rules for production under a type certificate only. </SECTION> <SECTION> <SECTNO>§ 21.123</SECTNO> <SUBJECT>Production under type certificate.</SUBJECT> Each manufacturer of a product being manufactured under a type certificate only shall— (a) Make each product available for inspection by the Administrator; (b) Maintain at the place of manufacture the technical data and drawings necessary for the Administrator to determine whether the product and its parts conform to the type design; (c) Except as otherwise authorized by the Aircraft Certification Directorate Manager for the geographic area which the manufacturer is located, for products manufactured more than 6 months after the date of issue of the type certificate, establish and maintain an approved production inspection system that insures that each product conforms to the type design and is in condition for safe operation; and (d) Upon the establishment of the approved production inspection system (as required by paragraph (c) of this section) submit to the Administrator a manual that describes that system and the means for making the determinations required by § 21.125(b). <CITA>[Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21-34, 35 FR 13008, Aug. 15, 1970; Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.125</SECTNO> <SUBJECT>Production inspection system: Materials Review Board.</SUBJECT> (a) Each manufacturer required to establish a production inspection system by § 21.123(c) shall— (1) Establish a Materials Review Board (to include representatives from the inspection and engineering departments) and materials review procedures; and (2) Maintain complete records of Materials Review Board action for at least two years. (b) The production inspection system required in § 21.123(c) must provide a means for determining at least the following: (1) Incoming materials, and bought or subcontracted parts, used in the finished product must be as specified in the type design data, or must be suitable equivalents. (2) Incoming materials, and bought or subcontracted parts, must be properly identified if their physical or chemical properties cannot be readily and accurately determined. (3) Materials subject to damage and deterioration must be suitably stored and adequately protected. (4) Processes affecting the quality and safety of the finished product must be accomplished in accordance with acceptable industry or United States specifications. (5) Parts and components in process must be inspected for conformity with the type design data at points in production where accurate determinations can be made. (6) Current design drawings must be readily available to manufacturing and inspection personnel, and used when necessary. (7) Design changes, including material substitutions, must be controlled and approved before being incorporated in the finished product. (8) Rejected materials and parts must be segregated and identified in a manner that precludes installation in the finished product. (9) Materials and parts that are withheld because of departures from design data or specifications, and that are to be considered for installation in the finished product, must be processed through the Materials Review Board. Those materials and parts determined by the Board to be serviceable must be properly identified and reinspected if rework or repair is necessary. Materials and parts rejected by the Board <PRTPAGE P="123"/>must be marked and disposed of to ensure that they are not incorporated in the final product. (10) Inspection records must be maintained, identified with the completed product where practicable, and retained by the manufacturer for at least two years. </SECTION> <SECTION> <SECTNO>§ 21.127</SECTNO> <SUBJECT>Tests: aircraft.</SUBJECT> (a) Each person manufacturing aircraft under a type certificate only shall establish an approved production flight test procedure and flight check-off form, and in accordance with that form, flight test each aircraft produced. (b) Each production flight test procedure must include the following: (1) An operational check of the trim, controllability, or other flight characteristics to establish that the production aircraft has the same range and degree of control as the prototype aircraft. (2) An operational check of each part or system operated by the crew while in flight to establish that, during flight, instrument readings are within normal range. (3) A determination that all instruments are properly marked, and that all placards and required flight manuals are installed after flight test. (4) A check of the operational characteristics of the aircraft on the ground. (5) A check on any other items peculiar to the aircraft being tested that can best be done during the ground or flight operation of the aircraft. </SECTION> <SECTION> <SECTNO>§ 21.128</SECTNO> <SUBJECT>Tests: aircraft engines.</SUBJECT> (a) Each person manufacturing aircraft engines under a type certificate only shall subject each engine (except rocket engines for which the manufacturer must establish a sampling technique) to an acceptable test run that includes the following: (1) Break-in runs that include a determination of fuel and oil consumption and a determination of power characteristics at rated maximum continuous power or thrust and, if applicable, at rated takeoff power or thrust. (2) At least five hours of operation at rated maximum continuous power or thrust. For engines having a rated takeoff power or thrust higher than rated maximum continuous power or thrust, the five-hour run must include 30 minutes at rated takeoff power or thrust. (b) The test runs required by paragraph (a) of this section may be made with the engine appropriately mounted and using current types of power and thrust measuring equipment. <CITA>[Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21-5, 32 FR 3735, Mar. 4, 1967]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.129</SECTNO> <SUBJECT>Tests: propellers.</SUBJECT> Each person manufacturing propellers under a type certificate only shall give each variable pitch propeller an acceptable functional test to determine if it operates properly throughout the normal range of operation. </SECTION> <SECTION> <SECTNO>§ 21.130</SECTNO> <SUBJECT>Statement of conformity.</SUBJECT> Each holder or licensee of a type certificate only, for a product manufactured in the United States, shall, upon the initial transfer by him of the ownership of such product manufactured under that type certificate, or upon application for the original issue of an aircraft airworthiness certificate or an aircraft engine or propeller airworthiness approval tag (FAA Form 8130-3), give the Administrator a statement of conformity (FAA Form 317). This statement must be signed by an authorized person who holds a responsible position in the manufacturing organization, and must include— (a) For each product, a statement that the product conforms to its type certificate and is in condition for safe operation; (b) For each aircraft, a statement that the aircraft has been flight checked; and (c) For each aircraft engine or variable pitch propeller, a statement that the engine or propeller has been subjected by the manufacturer to a final operational check. <FP>However, in the case of a product manufactured for an Armed Force of the United States, a statement of conformity is not required if the product has been accepted by that Armed Force.</FP> <CITA>[Amdt. 21-25, 34 FR 14068, Sept. 5, 1969]</CITA> </SECTION> </SUBPART> <SUBPART> <PRTPAGE P="124"/> <HD SOURCE="HED">Subpart G—Production Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14569, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.131</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the issue of production certificates and rules governing the holders of those certificates. </SECTION> <SECTION> <SECTNO>§ 21.133</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) Any person may apply for a production certificate if he holds, for the product concerned, a— (1) Current type certificate; (2) Right to the benefits of that type certificate under a licensing agreement; or (3) Supplemental type certificate. (b) Each application for a production certificate must be made in a form and manner prescribed by the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.135</SECTNO> <SUBJECT>Requirements for issuance.</SUBJECT> An applicant is entitled to a production certificate if the Administrator finds, after examination of the supporting data and after inspection of the organization and production facilities, that the applicant has complied with §§ 21.139 and 21.143. </SECTION> <SECTION> <SECTNO>§ 21.137</SECTNO> <SUBJECT>Location of manufacturing facilities.</SUBJECT> The Administrator does not issue a production certificate if the manufacturing facilities concerned are located outside the United States, unless the Administrator finds no undue burden on the United States in administering the applicable requirements of the Federal Aviation Act of 1958 or of the Federal Aviation Regulations. </SECTION> <SECTION> <SECTNO>§ 21.139</SECTNO> <SUBJECT>Quality control.</SUBJECT> The applicant must show that he has established and can maintain a quality control system for any product, for which he requests a production certificate, so that each article will meet the design provisions of the pertinent type certificate. </SECTION> <SECTION> <SECTNO>§ 21.143</SECTNO> <SUBJECT>Quality control data requirements; prime manufacturer.</SUBJECT> (a) Each applicant must submit, for approval, data describing the inspection and test procedures necessary to ensure that each article produced conforms to the type design and is in a condition for safe operation, including as applicable— (1) A statement describing assigned responsibilities and delegated authority of the quality control organization, together with a chart indicating the functional relationship of the quality control organization to management and to other organizational components, and indicating the chain of authority and responsibility within the quality control organization; (2) A description of inspection procedures for raw materials, purchased items, and parts and assemblies produced by manufacturers’ suppliers including methods used to ensure acceptable quality of parts and assemblies that cannot be completely inspected for conformity and quality when delivered to the prime manufacturer's plant; (3) A description of the methods used for production inspection of individual parts and complete assemblies, including the identification of any special manufacturing processes involved, the means used to control the processes, the final test procedure for the complete product, and, in the case of aircraft, a copy of the manufacturer's production flight test procedures and checkoff list; (4) An outline of the materials review system, including the procedure for recording review board decisions and disposing of rejected parts; (5) An outline of a system for informing company inspectors of current changes in engineering drawings, specifications, and quality control procedures; and (6) A list or chart showing the location and type of inspection stations. (b) Each prime manufacturer shall make available to the Administrator information regarding all delegation of authority to suppliers to make major inspections of parts or assemblies for <PRTPAGE P="125"/>which the prime manufacturer is responsible. <CITA>[Doc. No. 5085, 29 FR 14569, Oct. 24, 1964, as amended by Amdt. 21-51, 45 FR 60170, Sept. 11, 1980]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.147</SECTNO> <SUBJECT>Changes in quality control system.</SUBJECT> After the issue of a production certificate, each change to the quality control system is subject to review by the Administrator. The holder of a production certificate shall immediately notify the Administrator, in writing of any change that may affect the inspection, conformity, or airworthiness of the product. </SECTION> <SECTION> <SECTNO>§ 21.149</SECTNO> <SUBJECT>Multiple products.</SUBJECT> The Administrator may authorize more than one type certificated product to be manufactured under the terms of one production certificate, if the products have similar production characteristics. </SECTION> <SECTION> <SECTNO>§ 21.151</SECTNO> <SUBJECT>Production limitation record.</SUBJECT> A production limitation record is issued as part of a production certificate. The record lists the type certificate of every product that the applicant is authorized to manufacture under the terms of the production certificate. </SECTION> <SECTION> <SECTNO>§ 21.153</SECTNO> <SUBJECT>Amendment of the production certificates.</SUBJECT> The holder of a production certificate desiring to amend it to add a type certificate or model, or both, must apply therefor in a form and manner prescribed by the Administrator. The applicant must comply with the applicable requirements of §§ 21.139, 21.143, and 21.147. </SECTION> <SECTION> <SECTNO>§ 21.155</SECTNO> <SUBJECT>Transferability.</SUBJECT> A production certificate is not transferable. </SECTION> <SECTION> <SECTNO>§ 21.157</SECTNO> <SUBJECT>Inspections and tests.</SUBJECT> Each holder of a production certificate shall allow the Administrator to make any inspections and tests necessary to determine compliance with the applicable regulations in this subchapter. </SECTION> <SECTION> <SECTNO>§ 21.159</SECTNO> <SUBJECT>Duration.</SUBJECT> A production certificate is effective until surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, or the location of the manufacturing facility is changed. </SECTION> <SECTION> <SECTNO>§ 21.161</SECTNO> <SUBJECT>Display.</SUBJECT> The holder of a production certificate shall display it prominently in the main office of the factory in which the product concerned is manufactured. </SECTION> <SECTION> <SECTNO>§ 21.163</SECTNO> <SUBJECT>Privileges.</SUBJECT> (a) The holder of a production certificate may— (1) Obtain an aircraft airworthiness certificate without further showing, except that the Administrator may inspect the aircraft for conformity with the type design; or (2) In the case of other products, obtain approval for installation on type certificated aircraft. (b) Notwithstanding the provisions of § 147.3 of this chapter, the holder of a production certificate for a primary category aircraft, or for a normal, utility, or acrobatic category aircraft of a type design that is eligible for a special airworthiness certificate in the primary category under § 21.184(c), may— (1) Conduct training for persons in the performance of a special inspection and preventive maintenance program approved as a part of the aircraft's type design under § 21.24(b), provided the training is given by a person holding a mechanic certificate with appropriate airframe and powerplant ratings issued under part 65 of this chapter; and (2) Issue a certificate of competency to persons successfully completing the approved training program, provided the certificate specifies the aircraft make and model to which the certificate applies. <CITA>[Doc. No. 23345, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.165</SECTNO> <SUBJECT>Responsibility of holder.</SUBJECT> The holder of a production certificate shall— (a) Maintain the quality control system in conformity with the data and procedures approved for the production certificate; and<PRTPAGE P="126"/> (b) Determine that each part and each completed product, including primary category aircraft assembled under a production certificate by another person from a kit provided by the holder of the production certificate, submitted for airworthiness certification or approval conforms to the approved design and is in a condition for safe operation. <CITA>[Doc. No. 5085, 29 FR 14569, Oct. 24, 1964, as amended by Amdt. 21-64, 53 FR 48521, Dec. 1, 1988; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Airworthiness Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14569, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.171</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the issue of airworthiness certificates. </SECTION> <SECTION> <SECTNO>§ 21.173</SECTNO> <SUBJECT>Eligibility.</SUBJECT> Any registered owner of a U.S.-registered aircraft (or the agent of the owner) may apply for an airworthiness certificate for that aircraft. An application for an airworthiness certificate must be made in a form and manner acceptable to the Administrator, and may be submitted to any FAA office. <CITA>[Amdt. 21-26, 34 FR 15244, Sept. 30, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.175</SECTNO> <SUBJECT>Airworthiness certificates: classification.</SUBJECT> (a) Standard airworthiness certificates are airworthiness certificates issued for aircraft type certificated in the normal, utility, acrobatic, commuter, or transport category, and for manned free balloons, and for aircraft designated by the Administrator as special classes of aircraft. (b) Special airworthiness certificates are primary, restricted, limited, and provisional airworthiness certificates, special flight permits, and experimental certificates. <CITA>[Amdt. 21-21, 33 FR 6858, May 7, 1968, as amended by Amdt. 21-60, 52 FR 8043, Mar. 13, 1987; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.177</SECTNO> <SUBJECT>Amendment or modification.</SUBJECT> An airworthiness certificate may be amended or modified only upon application to the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.179</SECTNO> <SUBJECT>Transferability.</SUBJECT> An airworthiness certificate is transferred with the aircraft. </SECTION> <SECTION> <SECTNO>§ 21.181</SECTNO> <SUBJECT>Duration.</SUBJECT> (a) Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, airworthiness certificates are effective as follows: (1) Standard airworthiness certificates, special airworthiness certificates—primary category, and airworthiness certificates issued for restricted or limited category aircraft are effective as long as the maintenance, preventive maintenance, and alterations are performed in accordance with Parts 43 and 91 of this chapter and the aircraft are registered in the United States. (2) A special flight permit is effective for the period of time specified in the permit. (3) An experimental certificate for research and development, showing compliance with regulations, crew training, or market surveys is effective for one year after the date of issue or renewal unless a shorter period is prescribed by the Administrator. The duration of amateur-built, exhibition, and air-racing experimental certificates will be unlimited unless the Administrator finds for good cause that a specific period should be established. (b) The owner, operator, or bailee of the aircraft shall, upon request, make it available for inspection by the Administrator. (c) Upon suspension, revocation, or termination by order of the Administrator of an airworthiness certificate, the owner, operator, or bailee of an aircraft shall, upon request, surrender the certificate to the Administrator. <CITA>[Amdt. 21-21, 33 FR 6858, May 7, 1968, as amended by Amdt. 21-49, 44 FR 46781, Aug. 9, 1979; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.182</SECTNO> <SUBJECT>Aircraft identification.</SUBJECT> (a) Except as provided in paragraph (b) of this section, each applicant for <PRTPAGE P="127"/>an airworthiness certificate under this subpart must show that his aircraft is identified as prescribed in § 45.11. (b) Paragraph (a) of this section does not apply to applicants for the following: (1) A special flight permit. (2) An experimental certificate for an aircraft that is not amateur-built or kit-built. (3) A change from one airworthiness classification to another, for an aircraft already identified as prescribed in § 45.11. <CITA>[Amdt. 21-13, 32 FR 188, Jan. 10, 1967, as amended by Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.183</SECTNO> <SUBJECT>Issue of standard airworthiness certificates for normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; and special classes of aircraft.</SUBJECT> (a) <E T="03">New aircraft manufactured under a production certificate.</E> An applicant for a standard airworthiness certificate for a new aircraft manufactured under a production certificate is entitled to a standard airworthiness certificate without further showing, except that the Administrator may inspect the aircraft to determine conformity to the type design and condition for safe operation. (b) <E T="03">New aircraft manufactured under type certificate only.</E> An applicant for a standard airworthiness certificate for a new aircraft manufactured under a type certificate only is entitled to a standard airworthiness certificate upon presentation, by the holder or licensee of the type certificate, of the statement of conformity prescribed in § 21.130 if the Administrator finds after inspection that the aircraft conforms to the type design and is in condition for safe operation. (c) <E T="03">Import aircraft.</E> An applicant for a standard airworthiness certificate for an import aircraft type certificated in accordance with § 21.29 is entitled to an airworthiness certificate if the country in which the aircraft was manufactured certifies, and the Administrator finds, that the aircraft conforms to the type design and is in condition for safe operation. (d) <E T="03">Other aircraft.</E> An applicant for a standard airworthiness certificate for aircraft not covered by paragraphs (a) through (c) of this section is entitled to a standard airworthiness certificate if— (1) He presents evidence to the Administrator that the aircraft conforms to a type design approved under a type certificate or a supplemental type certificate and to applicable Airworthiness Directives; (2) The aircraft (except an experimentally certificated aircraft that previously had been issued a different airworthiness certificate under this section) has been inspected in accordance with the performance rules for 100-hour inspections set forth in § 43.15 of this chapter and found airworthy by— (i) The manufacturer; (ii) The holder of a repair station certificate as provided in Part 145 of this chapter; (iii) The holder of a mechanic certificate as authorized in Part 65 of this chapter; or (iv) The holder of a certificate issued under Part 121 or 127 of this chapter, and having a maintenance and inspection organization appropriate to the aircraft type; and (3) The Administrator finds after inspection, that the aircraft conforms to the type design, and is in condition for safe operation. (e) <E T="03">Noise requirements.</E> Notwithstanding all other provisions of this section, the following must be complied with for the original issuance of a standard airworthiness certificate: (1) For transport category large airplanes and turbojet powered airplanes that have not had any flight time before the dates specified in § 36.1(d), no standard airworthiness certificate is originally issued under this section unless the Administrator finds that the type design complies with the noise requirements in § 36.1(d) in addition to the applicable airworthiness requirements in this section. For import airplanes, compliance with this paragraph is shown if the country in which the airplane was manufactured certifies, and the Administrator finds, that § 36.1(d) (or the applicable airplane noise requirements of the country in which the airplane was manufactured <PRTPAGE P="128"/>and any other requirements the Administrator may prescribe to provide noise levels no greater than those provided by compliance with § 36.1(d)) and paragraph (c) of this section are complied with. (2) For normal, utility, acrobatic, commuter, or transport category propeller driven small airplanes (except for those airplanes that are designed for “agricultural aircraft operations” (as defined in § 137.3 of this chapter, as effective on January 1, 1966) or for dispensing fire fighting materials to which § 36.1583 of this chapter does not apply) that have not had any flight time before the applicable date specified in Part 36 of this chapter, no standard airworthiness certificate is originally issued under this section unless the applicant shows that the type design complies with the applicable noise requirements of Part 36 of this chapter in addition to the applicable airworthiness requirements in this section. For import airplanes, compliance with this paragraph is shown if the country in which the airplane was manufactured certifies, and the Administrator finds, that the applicable requirements of Part 36 of this chapter (or the applicable airplane noise requirements of the country in which the airplane was manufactured and any other requirements the Administrator may prescribe to provide noise levels no greater than those provided by compliance with the applicable requirements of Part 36 of this chapter) and paragraph (c) of this section are complied with. (f) <E T="03">Passenger emergency exit requirements.</E> Notwithstanding all other provisions of this section, each applicant for issuance of a standard airworthiness certificate for a transport category airplane manufactured after October 16, 1987, must show that the airplane meets the requirements of § 25.807(c)(7) in effect on July 24, 1989. For the purposes of this paragraph, the date of manufacture of an airplane is the date the inspection acceptance records reflect that the airplane is complete and meets the FAA-approved type design data. (g) <E T="03">Fuel venting and exhaust emission requirements.</E> Notwithstanding all other provisions of this section, and irrespective of the date of application, no airworthiness certificate is issued, on and after the dates specified in part 34 for the airplanes specified therein, unless the airplane complies with the applicable requirements of that part. <CITA>[Amdt. 21-17, 32 FR 14927, Oct. 28, 1967, as amended by Amdt. 21-20, 33 FR 3055, Feb. 16, 1968; Amdt. 21-25, 34 FR 14068, Sept. 5, 1969; Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-47, 43 FR 28419, June 29, 1978; Amdt. 21-52, 45 FR 67066, Oct. 9, 1980; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987; Amdt. 21-60, 52 FR 8043, Mar. 13, 1987; Amdt. 21-65, 54 FR 26695, June 23, 1989; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.184</SECTNO> <SUBJECT>Issue of special airworthiness certificates for primary category aircraft.</SUBJECT> (a) <E T="03">New primary category aircraft manufactured under a production certificate.</E> An applicant for an original, special airworthiness certificate-primary category for a new aircraft that meets the criteria of § 21.24(a)(1), manufactured under a production certificate, including aircraft assembled by another person from a kit provided by the holder of the production certificate and under the supervision and quality control of that holder, is entitled to a special airworthiness certificate without further showing, except that the Administrator may inspect the aircraft to determine conformity to the type design and condition for safe operation. (b) <E T="03">Imported aircraft.</E> An applicant for a special airworthiness certificate-primary category for an imported aircraft type certificated under § 21.29 is entitled to a special airworthiness certificate if the civil airworthiness authority of the country in which the aircraft was manufactured certifies, and the Administrator finds after inspection, that the aircraft conforms to an approved type design that meets the criteria of § 21.24(a)(1) and is in a condition for safe operation. (c) <E T="03">Aircraft having a current standard airworthiness certificate.</E> An applicant for a special airworthiness certificate-primary category, for an aircraft having a current standard airworthiness certificate that meets the criteria of § 21.24(a)(1), may obtain the primary category certificate in exchange for its standard airworthiness certificate <PRTPAGE P="129"/>through the supplemental type certification process. For the purposes of this paragraph, a current standard airworthiness certificate means that the aircraft conforms to its approved normal, utility, or acrobatic type design, complies with all applicable airworthiness directives, has been inspected and found airworthy within the last 12 calendar months in accordance with § 91.409(a)(1) of this chapter, and is found to be in a condition for safe operation by the Administrator. (d) <E T="03">Other aircraft.</E> An applicant for a special airworthiness certificate-primary category for an aircraft that meets the criteria of § 21.24(a)(1), and is not covered by paragraph (a), (b), or (c) of this section, is entitled to a special airworthiness certificate if— (1) The applicant presents evidence to the Administrator that the aircraft conforms to an approved primary, normal, utility, or acrobatic type design, including compliance with all applicable airworthiness directives; (2) The aircraft has been inspected and found airworthy within the past 12 calendar months in accordance with § 91.409(a)(1) of this chapter and; (3) The aircraft is found by the Administrator to conform to an approved type design and to be in a condition for safe operation. (e) <E T="03">Multiple-category airworthiness certificates</E> in the primary category and any other category will not be issued; a primary category aircraft may hold only one airworthiness certificate. <CITA>[Doc. No. 23345, 57 FR 41368, Sept. 9, 1992, as amended by Amdt. 21-70, 57 FR 43776, Sept. 22, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.185</SECTNO> <SUBJECT>Issue of airworthiness certificates for restricted category aircraft.</SUBJECT> (a) <E T="03">Aircraft manufactured under a production certificate or type certificate only.</E> An applicant for the original issue of a restricted category airworthiness certificate for an aircraft type certificated in the restricted category, that was not previously type certificated in any other category, must comply with the appropriate provisions of § 21.183. (b) <E T="03">Other aircraft.</E> An applicant for a restricted category airworthiness certificate for an aircraft type certificated in the restricted category, that was either a surplus aircraft of the Armed Forces or previously type certificated in another category, is entitled to an airworthiness certificate if the aircraft has been inspected by the Administrator and found by him to be in a good state of preservation and repair and in a condition for safe operation. (c) <E T="03">Import aircraft.</E> An applicant for the original issue of a restricted category airworthiness certificate for an import aircraft type certificated in the restricted category only in accordance with § 21.29 is entitled to an airworthiness certificate if the country in which the aircraft was manufactured certifies, and the Administrator finds, that the aircraft conforms to the type design and is in a condition for safe operation. (d) <E T="03">Noise requirements.</E> For propeller-driven small airplanes (except airplanes designed for “agricultural aircraft operations,” as defined in § 137.3 of this chapter, as effective on January 1, 1966, or for dispensing fire fighting materials) that have not had any flight time before the applicable date specified in Part 36 of this chapter, and notwithstanding the other provisions of this section, no original restricted category airworthiness certificate is issued under this section unless the Administrator finds that the type design complies with the applicable noise requirements of Part 36 of this chapter in addition to the applicable airworthiness requirements of this section. For import airplanes, compliance with this paragraph is shown if the country in which the airplane was manufactured certifies, and the Administrator finds, that the applicable requirements of Part 36 of this chapter (or the applicable airplane noise requirements of the country in which the airplane was manufactured and any other requirements the Administrator may prescribe to provide noise levels no greater than those provided by compliance with the applicable requirements of Part 36 of this chapter) and paragraph (c) of this section are complied with. <CITA>[Amdt. 21-10, 31 FR 9211, July 6, 1966; as amended by Amdt. 21-32, 35 FR 10202, June 23, 1970; Amdt. 21-42, 40 FR 1034, Jan. 6, 1975]</CITA> </SECTION> <SECTION> <PRTPAGE P="130"/> <SECTNO>§ 21.187</SECTNO> <SUBJECT>Issue of multiple airworthiness certification.</SUBJECT> (a) An applicant for an airworthiness certificate in the restricted category, and in one or more other categories except primary category, is entitled to the certificate, if— (1) He shows compliance with the requirements for each category, when the aircraft is in the configuration for that category; and (2) He shows that the aircraft can be converted from one category to another by removing or adding equipment by simple mechanical means. (b) The operator of an aircraft certif-icated under this section shall have the aircraft inspected by the Administrator, or by a certificated mechanic with an appropriate airframe rating, to determine airworthiness each time the aircraft is converted from the restricted category to another category for the carriage of passengers for compensation or hire, unless the Administrator finds this unnecessary for safety in a particular case. (c) The aircraft complies with the applicable requirements of part 34. <CITA>[Doc. No. 5085, 29 FR 14569, Oct. 24, 1964, as amended by Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-70, 57 FR 41369, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.189</SECTNO> <SUBJECT>Issue of airworthiness certificate for limited category aircraft.</SUBJECT> (a) An applicant for an airworthiness certificate for an aircraft in the limited category is entitled to the certificate when— (1) He shows that the aircraft has been previously issued a limited category type certificate and that the aircraft conforms to that type certificate; and (2) The Administrator finds, after inspection (including a flight check by the applicant), that the aircraft is in a good state of preservation and repair and is in a condition for safe operation. (b) The Administrator prescribes limitations and conditions necessary for safe operation. <CITA>[Doc. No. 5085, 29 FR 14570, Oct. 24, 1964, as amended by Amdt. 21-4, 30 FR 9437, July 29, 1965]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.191</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> Experimental certificates are issued for the following purposes: (a) <E T="03">Research and development.</E> Testing new aircraft design concepts, new aircraft equipment, new aircraft installations, new aircraft operating techniques, or new uses for aircraft. (b) <E T="03">Showing compliance with regulations.</E> Conducting flight tests and other operations to show compliance with the airworthiness regulations including flights to show compliance for issuance of type and supplemental type certificates, flights to substantiate major design changes, and flights to show compliance with the function and reliability requirements of the regulations. (c) <E T="03">Crew training.</E> Training of the applicant's flight crews. (d) <E T="03">Exhibition.</E> Exhibiting the aircraft's flight capabilities, performance, or unusual characteristics at air shows, motion picture, television, and similar productions, and the maintenance of exhibition flight proficiency, including (for persons exhibiting aircraft) flying to and from such air shows and productions. (e) <E T="03">Air racing.</E> Participating in air races, including (for such participants) practicing for such air races and flying to and from racing events. (f) <E T="03">Market surveys.</E> Use of aircraft for purposes of conducting market surveys, sales demonstrations, and customer crew training only as provided in § 21.195. (g) <E T="03">Operating amateur-built aircraft.</E> Operating an aircraft the major portion of which has been fabricated and assembled by persons who undertook the construction project solely for their own education or recreation. (h) <E T="03">Operating kit-built aircraft.</E> Operating a primary category aircraft that meets the criteria of § 21.24(a)(1) that was assembled by a person from a kit manufactured by the holder of a production certificate for that kit, without the supervision and quality control of the production certificate holder under § 21.184(a). <CITA>[Amdt. 21-21, 38 FR 6858, May 7, 1968, as amended by Amdt. 21-57, 49 FR 39651, Oct. 9, 1984; Amdt. 21-70, 57 FR 41369, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <PRTPAGE P="131"/> <SECTNO>§ 21.193</SECTNO> <SUBJECT>Experimental certificates: general.</SUBJECT> An applicant for an experimental certificate must submit the following information: (a) A statement, in a form and manner prescribed by the Administrator setting forth the purpose for which the aircraft is to be used. (b) Enough data (such as photographs) to identify the aircraft. (c) Upon inspection of the aircraft, any pertinent information found necessary by the Administrator to safeguard the general public. (d) In the case of an aircraft to be used for experimental purposes— (1) The purpose of the experiment; (2) The estimated time or number of flights required for the experiment; (3) The areas over which the experiment will be conducted; and (4) Except for aircraft converted from a previously certificated type without appreciable change in the external configuration, three-view drawings or three-view dimensioned photographs of the aircraft. </SECTION> <SECTION> <SECTNO>§ 21.195</SECTNO> <SUBJECT>Experimental certificates: Aircraft to be used for market surveys, sales demonstrations, and customer crew training.</SUBJECT> (a) A manufacturer of aircraft manufactured within the United States may apply for an experimental certificate for an aircraft that is to be used for market surveys, sales demonstrations, or customer crew training. (b) A manufacturer of aircraft engines who has altered a type certificated aircraft by installing different engines, manufactured by him within the United States, may apply for an experimental certificate for that aircraft to be used for market surveys, sales demonstrations, or customer crew training, if the basic aircraft, before alteration, was type certificated in the normal, acrobatic, commuter, or transport category. (c) A person who has altered the design of a type certificated aircraft may apply for an experimental certificate for the altered aircraft to be used for market surveys, sales demonstrations, or customer crew training if the basic aircraft, before alteration, was type certificated in the normal, utility, acrobatic, or transport category. (d) An applicant for an experimental certificate under this section is entitled to that certificate if, in addition to meeting the requirements of § 21.193— (1) He has established an inspection and maintenance program for the continued airworthiness of the aircraft; and (2) He shows that the aircraft has been flown for at least 50 hours, or for at least 5 hours if it is a type certificated aircraft which has been modified. <CITA>[Amdt. 21-21, 33 FR 6858, May 7, 1968, as amended by Amdt. 21-28, 35 FR 2818, Feb. 11, 1970; Amdt. 21-57, 49 FR 39651, Oct. 9, 1984; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.197</SECTNO> <SUBJECT>Special flight permits.</SUBJECT> (a) A special flight permit may be issued for an aircraft that may not currently meet applicable airworthiness requirements but is capable of safe flight, for the following purposes: (1) Flying the aircraft to a base where repairs, alterations, or maintenance are to be performed, or to a point of storage. (2) Delivering or exporting the aircraft. (3) Production flight testing new production aircraft. (4) Evacuating aircraft from areas of impending danger. (5) Conducting customer demonstration flights in new production aircraft that have satisfactorily completed production flight tests. (b) A special flight permit may also be issued to authorize the operation of an aircraft at a weight in excess of its maximum certificated takeoff weight for flight beyond the normal range over water, or over land areas where adequate landing facilities or appropriate fuel is not available. The excess weight that may be authorized under this paragraph is limited to the additional fuel, fuel-carrying facilities, and navigation equipment necessary for the flight. (c) Upon application, as prescribed in §§ 121.79, 127.27, and 135.17 of this chapter, a special flight permit with a continuing authorization may be issued for aircraft that may not meet applicable airworthiness requirements but are <PRTPAGE P="132"/>capable of safe flight for the purpose of flying aircraft to a base where maintenance or alterations are to be performed. The permit issued under this paragraph is an authorization, including conditions and limitations for flight, which is set forth in the certificate holder's operations specifications. The permit issued under this paragraph may be issued to— (1) Certificate holders authorized to conduct operations under Part 121 or Part 127 of this chapter; or (2) Certificate holders authorized to conduct operations under Part 135 for those aircraft they operate and maintain under a continuous airworthiness maintenance program prescribed by § 135.411 (a)(2) or (b) of that part. <FP>The permit issued under this paragraph is an authorization, including any conditions and limitations for flight, which is set forth in the certificate holder's operations specifications.</FP> <CITA>[Doc. No. 5085, 29 FR 14570, Oct. 24, 1964, as amended by Amdt. 21-21, 33 FR 6859, May 7, 1968; Amdt. 21—51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-54, 46 FR 37878, July 23, 1981]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.199</SECTNO> <SUBJECT>Issue of special flight permits.</SUBJECT> (a) Except as provided in § 21.197(c), an applicant for a special flight permit must submit a statement in a form and manner prescribed by the Administrator, indicating— (1) The purpose of the flight. (2) The proposed itinerary. (3) The crew required to operate the aircraft and its equipment, e.g., pilot, co-pilot, navigator, etc. (4) The ways, if any, in which the aircraft does not comply with the applicable airworthiness requirements. (5) Any restriction the applicant considers necessary for safe operation of the aircraft. (6) Any other information considered necessary by the Administrator for the purpose of prescribing operating limitations. (b) The Administrator may make, or require the applicant to make appropriate inspections or tests necessary for safety. <CITA>[Doc. No. 5085, 29 FR 14570, Oct. 24, 1964, as amended by Amdt. 21-21, 33 FR 6859, May 7, 1968; Amdt. 21-22, 33 FR 11901, Aug. 22, 1968]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart I—Provisional Airworthiness Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14571, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.211</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the issue of provisional airworthiness certificates. </SECTION> <SECTION> <SECTNO>§ 21.213</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) A manufacturer who is a United States citizen may apply for a Class I or Class II provisional airworthiness certificate for aircraft manufactured by him within the U.S. (b) Any holder of an air carrier operating certificate under Part 121 or Part 127 of this chapter who is a United States citizen may apply for a Class II provisional airworthiness certificate for transport category aircraft that meet either of the following: (1) The aircraft has a current Class II provisional type certificate or an amendment thereto. (2) The aircraft has a current provisional amendment to a type certificate that was preceded by a corresponding Class II provisional type certificate. (c) An aircraft engine manufacturer who is a United States citizen and who has altered a type certificated aircraft by installing different type certificated engines, manufactured by him within the United States, may apply for a Class I provisional airworthiness certificate for that aircraft, if the basic aircraft, before alteration, was type certificated in the normal, utility, acrobatic, commuter, or transport category. <CITA>[Doc. No. 5085, 29 FR 14571, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.215</SECTNO> <SUBJECT>Application.</SUBJECT> Applications for provisional airworthiness certificates must be submitted to the Manufacturing Inspection District Office in the geographic area in which the manufacturer or air carrier is located. The application must be accompanied by the pertinent information specified in this subpart. <CITA>[Amdt. 21-67, 54 FR 39291, Sept. 25, 1989; 54 FR 52872, Dec. 22, 1989]</CITA> </SECTION> <SECTION> <PRTPAGE P="133"/> <SECTNO>§ 21.217</SECTNO> <SUBJECT>Duration.</SUBJECT> Unless sooner surrendered, superseded, revoked, or otherwise terminated, provisional airworthiness certificates are effective for the duration of the corresponding provisional type certificate, amendment to a provisional type certificate, or provisional amendment to the type certificate. </SECTION> <SECTION> <SECTNO>§ 21.219</SECTNO> <SUBJECT>Transferability.</SUBJECT> Class I provisional airworthiness certificates are not transferable. Class II provisional airworthiness certificates may be transferred to an air carrier eligible to apply for a certificate under § 21.213(b). </SECTION> <SECTION> <SECTNO>§ 21.221</SECTNO> <SUBJECT>Class I provisional airworthiness certificates.</SUBJECT> (a) Except as provided in § 21.225, an applicant is entitled to a Class I provisional airworthiness certificate for an aircraft for which a Class I provisional type certificate has been issued if— (1) He meets the eligibility requirements of § 21.213 and he complies with this section; and (2) The Administrator finds that there is no feature, characteristic or condition of the aircraft that would make the aircraft unsafe when operated in accordance with the limitations established in §§ 21.81(e) and 91.317 of this subchapter. (b) The manufacturer must hold a provisional type certificate for the aircraft. (c) The manufacturer must submit a statement that the aircraft conforms to the type design corresponding to the provisional type certificate and has been found by him to be in safe operating condition under all applicable limitations. (d) The aircraft must be flown at least five hours by the manufacturer. (e) The aircraft must be supplied with a provisional aircraft flight manual or other document and appropriate placards containing the limitations established by §§ 21.81(e) and 91.317. <CITA>[Doc. No. 5085, 29 FR 14571, Oct. 24, 1964, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]s</CITA> </SECTION> <SECTION> <SECTNO>§ 21.223</SECTNO> <SUBJECT>Class II provisional airworthiness certificates.</SUBJECT> (a) Except as provided in § 21.225, an applicant is entitled to a Class II provisional airworthiness certificate for an aircraft for which a Class II provisional type certificate has been issued if— (1) He meets the eligibility requirements of § 21.213 and he complies with this section; and (2) The Administrator finds that there is no feature, characteristic, or condition of the aircraft that would make the aircraft unsafe when operated in accordance with the limitations established in §§ 21.83(h), 91.317, and 121.207 of this chapter. (b) The applicant must show that a Class II provisional type certificate for the aircraft has been issued to the manufacturer. (c) The applicant must submit a statement by the manufacturer that the aircraft has been manufactured under a quality control system adequate to ensure that the aircraft conforms to the type design corresponding with the provisional type certificate. (d) The applicant must submit a statement that the aircraft has been found by him to be in a safe operating condition under the applicable limitations. (e) The aircraft must be flown at least five hours by the manufacturer. (f) The aircraft must be supplied with a provisional aircraft flight manual containing the limitations established by §§ 21.83(h), 91.317, and 121.207 of this chapter. <CITA>[Doc. No. 5085, 29 FR 14571, Oct. 24, 1964, as amended by Amdt. 21-12, 31 FR 13389, Oct. 15, 1966; Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.225</SECTNO> <SUBJECT>Provisional airworthiness certificates corresponding with provisional amendments to type certificates.</SUBJECT> (a) An applicant is entitled to a Class I or a Class II provisional airworthiness certificate, for an aircraft, for which a provisional amendment to the type certificate has been issued, if— (1) He meets the eligibility requirements of § 21.213 and he complies with this section; and (2) The Administrator finds that there is no feature, characteristic, or condition of the aircraft, as modified in <PRTPAGE P="134"/>accordance with the provisionally amended type certificate, that would make the aircraft unsafe when operated in accordance with the applicable limitations established in §§ 21.85(g), 91.317, and 121.207 of this chapter. (b) The applicant must show that the modification was made under a quality control system adequate to ensure that the modification conforms to the provisionally amended type certificate. (c) The applicant must submit a statement that the aircraft has been found by him to be in a safe operating condition under the applicable limitations. (d) The aircraft must be flown at least five hours by the manufacturer. (e) The aircraft must be supplied with a provisional aircraft flight manual or other document and appropriate placards containing the limitations required by §§ 21.85(g), 91.317, and 121.207 of this chapter. <CITA>[Doc. No. 5085, 29 FR 14571, Oct. 24, 1964, as amended by Amdt. 21-12, 31 FR 13389, Oct. 15, 1966; Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart J—Delegation Option Authorization Procedures</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.231</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedures for— (a) Obtaining and using a delegation option authorization for type, production, and airworthiness certification (as applicable) of— (1) Small airplanes and small gliders; (2) Commuter category airplanes; (3) Normal category rotorcraft; (4) Turbojet engines of not more than 1,000 pounds thrust; (5) Turbopropeller and reciprocating engines of not more than 500 brake horsepower; and (6) Propellers manufactured for use on engines covered by paragraph (a)(4) of this section; and (b) Issuing airworthiness approval tags for engines, propellers, and parts of products covered by paragraph (a) of this section. <CITA>[Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, as amended by Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.235</SECTNO> <SUBJECT>Application.</SUBJECT> (a) An application for a delegation option authorization must be submitted, in a form and manner prescribed by the Administrator, to the Aircraft Certification Office for the area in which the manufacturer is located. (b) The application must include the names, signatures, and titles of the persons for whom authorization to sign airworthiness certificates, repair and alteration forms, and inspection forms is requested. <CITA>[Doc. No. 5085, 29 FR 14574, Oct. 24, 1964, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.239</SECTNO> <SUBJECT>Eligibility.</SUBJECT> To be eligible for a delegation option authorization, the applicant must— (a) Hold a current type certificate, issued to him under the standard procedures, for a product type certificated under the same part as the products for which the delegation option authorization is sought; (b) Hold a current production certificate issued under the standard procedures; (c) Employ a staff of engineering, flight test, production and inspection personnel who can determine compliance with the applicable airworthiness requirements of this chapter; and (d) Meet the requirements of this subpart. </SECTION> <SECTION> <SECTNO>§ 21.243</SECTNO> <SUBJECT>Duration.</SUBJECT> A delegation option authorization is effective until it is surrendered or the Administrator suspends, revokes, or otherwise terminates it. </SECTION> <SECTION> <SECTNO>§ 21.245</SECTNO> <SUBJECT>Maintenance of eligibility.</SUBJECT> The holder of a delegation option authorization shall continue to meet the requirements for issue of the authorization or shall notify the Administrator within 48 hours of any change (including a change of personnel) that <PRTPAGE P="135"/>could affect the ability of the holder to meet those requirements. </SECTION> <SECTION> <SECTNO>§ 21.247</SECTNO> <SUBJECT>Transferability.</SUBJECT> A delegation option authorization is not transferable. </SECTION> <SECTION> <SECTNO>§ 21.249</SECTNO> <SUBJECT>Inspections.</SUBJECT> Upon request, each holder of a delegation option authorization and each applicant shall let the Administrator inspect his organization, facilities, product, and records. </SECTION> <SECTION> <SECTNO>§ 21.251</SECTNO> <SUBJECT>Limits of applicability.</SUBJECT> (a) Delegation option authorizations apply only to products that are manufactured by the holder of the authorization. (b) Delegation option authorizations may be used for— (1) Type certification; (2) Changes in the type design of products for which the manufacturer holds, or obtains, a type certificate; (3) The amendment of a production certificate held by the manufacturer to include additional models or additional types for which he holds or obtains a type certificate; and (4) The issue of— (i) Experimental certificates for aircraft for which the manufacturer has applied for a type certificate or amended type certificate under § 21.253, to permit the operation of those aircraft for the purpose of research and development, crew training, market surveys, or the showing of compliance with the applicable airworthiness requirements; (ii) Airworthiness certificates (other than experimental certificates) for aircraft for which the manufacturer holds a type certificate and holds or is in the process of obtaining a production certificate; (iii) Airworthiness approval tags (FAA Form 8130-3) for engines and propellers for which the manufacturer holds a type certificate and holds or is in the process of obtaining a production certificate; and (iv) Airworthiness approval tags (FAA Form 8130-3) for parts of products covered by this section. (c) Delegation option procedures may be applied to one or more types selected by the manufacturer, who must notify the FAA of each model, and of the first serial number of each model manufactured by him under the delegation option procedures. Other types or models may remain under the standard procedures. (d) Delegation option authorizations are subject to any additional limitations prescribed by the Administrator after inspection of the applicant's facilities or review of the staff qualifications. <CITA>[Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, as amended by Amdt. 21-31, 35 FR 7292, May 9, 1970; Amdt. 21-43, 40 FR 2576, Jan. 14, 1975]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.253</SECTNO> <SUBJECT>Type certificates: application.</SUBJECT> (a) To obtain, under the delegation option authorization, a type certificate for a new product or an amended type certificate, the manufacturer must submit to the Administrator— (1) An application for a type certificate (FAA Form 312); (2) A statement listing the airworthiness requirements of this chapter (by part number and effective date) that the manufacturer considers applicable; (3) After determining that the type design meets the applicable requirements, a statement certifying that this determination has been made; (4) After placing the required technical data and type inspection report in the technical data file required by § 21.293(a)(1)(i), a statement certifying that this has been done; (5) A proposed type certificate data sheet; and (6) An Aircraft Flight Manual (if required) or a summary of required operating limitations and other information necessary for safe operation of the product. </SECTION> <SECTION> <SECTNO>§ 21.257</SECTNO> <SUBJECT>Type certificates: issue.</SUBJECT> An applicant is entitled to a type certificate for a product manufactured under a delegation option authorization if the Administrator finds that the product meets the applicable airworthiness, noise, fuel venting, and exhaust emission requirements (including applicable acoustical change or emissions change requirements in the case of changes in type design). <CITA>[Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <PRTPAGE P="136"/> <SECTNO>§ 21.261</SECTNO> <SUBJECT>Equivalent safety provisions.</SUBJECT> The manufacturer shall obtain the Administrator's concurrence on the application of all equivalent safety provisions applied under § 21.21. </SECTION> <SECTION> <SECTNO>§ 21.267</SECTNO> <SUBJECT>Production certificates.</SUBJECT> To have a new model or new type certificate listed on his production certificate (issued under Subpart G of this part), the manufacturer must submit to the Administrator— (a) An application for an amendment to the production certificate; (b) After determining that the production certification requirements of Subpart G, with respect to the new model or type, are met, a statement certifying that this determination has been made; (c) A statement identifying the type certificate number under which the product is being manufactured; and (d) After placing the manufacturing and quality control data required by § 21.143 with the data required by § 21.293(a)(1)(ii), a statement certifying that this has been done. </SECTION> <SECTION> <SECTNO>§ 21.269</SECTNO> <SUBJECT>Export airworthiness approvals.</SUBJECT> The manufacturer may issue export airworthiness approvals. </SECTION> <SECTION> <SECTNO>§ 21.271</SECTNO> <SUBJECT>Airworthiness approval tags.</SUBJECT> (a) A manufacturer may issue an airworthiness approval tag (FAA Form 8130-3) for each engine and propeller covered by § 21.251(b)(4), and may issue an airworthiness approval tag for parts of each product covered by that section, if he finds, on the basis of inspection and operation tests, that those products conform to a type design for which he holds a type certificate and are in condition for safe operation. (b) When a new model has been included on the Production Limitation Record, the production certification number shall be stamped on the engine or propeller identification data place instead of issuing an airworthiness approval tag. <CITA>[Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, as amended by Amdt. 21-43, 40 FR 2577, Jan. 14, 1975]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.273</SECTNO> <SUBJECT>Airworthiness certificates other than experimental.</SUBJECT> (a) The manufacturer may issue an airworthiness certificate for aircraft manufactured under a delegation option authorization if he finds, on the basis of the inspection and production flight check, that each aircraft conforms to a type design for which he holds a type certificate and is in a condition for safe operation. (b) The manufacturer may authorize any employee to sign airworthiness certificates if that employee— (1) Performs, or is in direct charge of, the inspection specified in paragraph (a) of this section; and (2) Is listed on the manufacturer's application for the delegation option authorization, or on amendments thereof. <CITA>[Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, as amended by Amdt. 21-18, 32 FR 15472, Nov. 7, 1967]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.275</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> (a) The manufacturer shall, before issuing an experimental certificate, obtain from the Administration any limitations and conditions that the Administrator considers necessary for safety. (b) For experimental certificates issued by the manufacturer, under this subpart, for aircraft for which the manufacturer holds the type certificate and which have undergone changes to the type design requiring flight test, the manufacturer may prescribe any operating limitations that he considers necessary. </SECTION> <SECTION> <SECTNO>§ 21.277</SECTNO> <SUBJECT>Data review and service experience.</SUBJECT> (a) If the Administrator finds that a product for which a type certificate was issued under this subpart does not meet the applicable airworthiness requirements, or that an unsafe feature or characteristic caused by a defect in design or manufacture exists, the manufacturer, upon notification by the Administrator, shall investigate the matter and report to the Administrator the results of the investigation and the action, if any, taken or proposed. (b) If corrective action by the user of the product is necessary for safety because of any noncompliance or defect specified in paragraph (a) of this section, the manufacturer shall submit <PRTPAGE P="137"/>the information necessary for the issue of an Airworthiness Directive under Part 39. </SECTION> <SECTION> <SECTNO>§ 21.289</SECTNO> <SUBJECT>Major repairs, rebuilding and alteration.</SUBJECT> For types covered by a delegation option authorization, a manufacturer may— (a) After finding that a major repair or major alteration meets the applicable airworthiness requirements of this chapter, approve that repair or alteration; and (b) Authorize any employee to execute and sign FAA Form 337 and make required log book entries if that employee— (1) Inspects, or is in direct charge of inspecting, the repair, rebuilding, or alteration; and (2) Is listed on the application for the delegation option authorization, or on amendments thereof. </SECTION> <SECTION> <SECTNO>§ 21.293</SECTNO> <SUBJECT>Current records.</SUBJECT> (a) The manufacturer shall maintain at his factory, for each product type certificated under a delegation option authorization, current records containing the following: (1) For the duration of the manufacturing operating under the delegation option authorization— (i) A technical data file that includes the type design drawings, specifications, reports on tests prescribed by this part, and the original type inspection report and amendments to that report; (ii) The data (including amendments) required to be submitted with the original application for each production certificate; and (iii) A record of any rebuilding and alteration performed by the manufacturer on products manufactured under the delegation option authorization. (2) For 2 years— (i) A complete inspection record for each product manufactured, by serial number, and data covering the processes and tests to which materials and parts are subjected; and (ii) A record of reported service difficulties. (b) The records and data specified in paragraph (a) of this section shall be— (1) Made available, upon the Administrator's request, for examination by the Administrator at any time; and (2) Identified and sent to the Administrator as soon as the manufacturer no longer operates under the delegation option procedures. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart K—Approval of Materials, Parts, Processes, and Appliances</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14574, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.301</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the approval of certain materials, parts, processes, and appliances. </SECTION> <SECTION> <SECTNO>§ 21.303</SECTNO> <SUBJECT>Replacement and modification parts.</SUBJECT> (a) Except as provided in paragraph (b) of this section, no person may produce a modification or replacement part for sale for installation on a type certificated product unless it is produced pursuant to a Parts Manufacturer Approval issued under this subpart. (b) This section does not apply to the following: (1) Parts produced under a type or production certificate. (2) Parts produced by an owner or operator for maintaining or altering his own product. (3) Parts produced under an FAA Technical Standard Order. (4) Standard parts (such as bolts and nuts) conforming to established industry or U.S. specifications. (c) An application for a Parts Manufacturer Approval is made to the Manager of the Aircraft Certification Office for the geographic area in which the manufacturing facility is located and must include the following: (1) The identity of the product on which the part is to be installed. (2) The name and address of the manufacturing facilities at which these parts are to be manufactured. (3) The design of the part, which consists of— (i) Drawings and specifications necessary to show the configuration of the part; and<PRTPAGE P="138"/> (ii) Information on dimensions, materials, and processes necessary to define the structural strength of the part. (4) Test reports and computations necessary to show that the design of the part meets the airworthiness requirements of the Federal Aviation Regulations applicable to the product on which the part is to be installed, unless the applicant shows that the design of the part is identical to the design of a part that is covered under a type certificate. If the design of the part was obtained by a licensing agreement, evidence of that agreement must be furnished. (d) An applicant is entitled to a Parts Manufacturer Approval for a replacement or modification part if— (1) The Administrator finds, upon examination of the design and after completing all tests and inspections, that the design meets the airworthiness requirements of the Federal Aviation Regulations applicable to the product on which the part is to be installed; and (2) He submits a statement certifying that he has established the fabrication inspection system required by paragraph (h) of this section. (e) Each applicant for a Parts Manufacturer Approval must allow the Administrator to make any inspection or test necessary to determine compliance with the applicable Federal Aviation Regulations. However, unless otherwise authorized by the Administrator— (1) No part may be presented to the Administrator for an inspection or test unless compliance with paragraphs (f)(2) through (4) of this section has been shown for that part; and (2) No change may be made to a part between the time that compliance with paragraphs (f)(2) through (4) of this section is shown for that part and the time that the part is presented to the Administrator for the inspection or test. (f) Each applicant for a Parts Manufacturer Approval must make all inspections and tests necessary to determine— (1) Compliance with the applicable airworthiness requirements; (2) That materials conform to the specifications in the design; (3) That the part conforms to the drawings in the design; and (4) That the fabrication processes, construction, and assembly conform to those specified in the design. (g) The Administrator does not issue a Parts Manufacturer Approval if the manufacturing facilities for the part are located outside of the United States, unless the Administrator finds that the location of the manufacturing facilities places no burden on the FAA in administering applicable airworthiness requirements. (h) Each holder of a Parts Manufacturer Approval shall establish and maintain a fabrication inspection system that ensures that each completed part conforms to its design data and is safe for installation on applicable type certificated products. The system shall include the following: (1) Incoming materials used in the finished part must be as specified in the design data. (2) Incoming materials must be properly identified if their physical and chemical properties cannot otherwise be readily and accurately determined. (3) Materials subject to damage and deterioration must be suitably stored and adequately protected. (4) Processes affecting the quality and safety of the finished product must be accomplished in accordance with acceptable specifications. (5) Parts in process must be inspected for conformity with the design data at points in production where accurate determination can be made. Statistical quality control procedures may be employed where it is shown that a satisfactory level of quality will be maintained for the particular part involved. (6) Current design drawings must be readily available to manufacturing and inspection personnel, and used when necessary. (7) Major changes to the basic design must be adequately controlled and approved before being incorporated in the finished part. (8) Rejected materials and components must be segregated and identified in such a manner as to preclude their use in the finished part. (9) Inspection records must be maintained, identified with the completed part, where practicable, and retained in <PRTPAGE P="139"/>the manufacturer's file for a period of at least 2 years after the part has been completed. (i) A Parts Manufacturer Approval issued under this section is not transferable and is effective until surrendered or withdrawn or otherwise terminated by the Administrator. (j) The holder of a Parts Manufacturer Approval shall notify the FAA in writing within 10 days from the date the manufacturing facility at which the parts are manufactured is relocated or expanded to include additional facilities at other locations. (k) Each holder of a Parts Manufacturer Approval shall determine that each completed part conforms to the design data and is safe for installation on type certificated products. <CITA>[Amdt. 21-38, 37 FR 10659, May 26, 1972, as amended by Amdt. 21-41, 39 FR 41965, Dec. 4, 1974; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.305</SECTNO> <SUBJECT>Approval of materials, parts, processes, and appliances.</SUBJECT> Whenever a material, part, process, or appliance is required to be approved under this chapter, it may be approved— (a) Under a Parts Manufacturer Approval issued under § 21.303; (b) Under a Technical Standard Order issued by the Administrator. Advisory Circular 20-110 contains a list of Technical Standard Orders that may be used to obtain approval. Copies of the Advisory Circular may be obtained from the U.S. Department of Transportation, Publication Section (M-443.1), Washington, D.C. 20590; (c) In conjunction with type certification procedures for a product; or (d) In any other manner approved by the Administrator. <CITA>[Amdt. 21-38, 37 FR 10659, May 26, 1972, as amended by Amdt. 21-50, 45 FR 38346, June 9, 1980]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart L—Export Airworthiness Approvals</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 21-2, 30 FR 8465, July 2, 1965, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.321</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart prescribes— (1) Procedural requirements for the issue of export airworthiness approv-als; and (2) Rules governing the holders of those approvals. (b) For the purposes of this subpart— (1) A Class I product is a complete aircraft, aircraft engine, or propeller, which— (i) Has been type certificated in accordance with the applicable Federal Aviation Regulations and for which Federal Aviation Specifications or type certificate data sheets have been issued; or (ii) Is identical to a type certificated product specified in paragraph (b)(1)(i) of this section in all respects except as is otherwise acceptable to the civil aviation authority of the importing state. (2) A Class II product is a major component of a Class I product (e.g., wings, fuselages, empennage assemblies, landing gears, power transmissions, control surfaces, etc), the failure of which would jeopardize the safety of a Class I product; or any part, material, or appliance, approved and manufactured under the Technical Standard Order (TSO) system in the “C” series. (3) A Class III product is any part or component which is not a Class I or Class II product and includes standard parts, i.e., those designated as AN, NAS, SAE, etc. (4) The words “newly overhauled” when used to describe a product means that the product has not been operated or placed in service, except for functional testing, since having been overhauled, inspected and approved for return to service in accordance with the applicable Federal Aviation Regulations. <CITA>[Amdt. 21-2, 30 FR 11375, July 2, 1965, as amended by Amdt. 21-48, 44 FR 15649, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.323</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) Any exporter or his authorized representative may obtain an export airworthiness approval for a Class I or Class II product. (b) Any manufacturer may obtain an export airworthiness approval for a Class III product if the manufacturer— (1) Has in his employ a designated representative of the Administrator <PRTPAGE P="140"/>who has been authorized to issue that approval; and (2) Holds for that product— (i) A production certificate; (ii) An approved production inspection system; (iii) An FAA Parts Manufacturer Approval (PMA); or (iv) A Technical Standard Order authorization. </SECTION> <SECTION> <SECTNO>§ 21.325</SECTNO> <SUBJECT>Export airworthiness approvals.</SUBJECT> (a) <E T="03">Kinds of approvals.</E> (1) Export airworthiness approval of Class I products is issued in the form of Export Certificates of Airworthiness, FAA Form 8130-4. Such a certificate does not authorize the operation of aircraft. (2) Export airworthiness approval of Class II and III products is issued in the form of Airworthiness Approval Tags, FAA Form 8130-3. (b) <E T="03">Products which may be approved.</E> Export airworthiness approvals are issued for— (1) New aircraft that are assembled and that have been flight-tested, and other Class I products located in the United States, except that export airworthiness approval may be issued for any of the following without assembly or flight-test: (i) A small airplane type certificated under Part 3 or 4a of the Civil Air Regulations, or Part 23 of the Federal Aviation Regulations, and manufactured under a production certificate; (ii) A glider type certificated under § 21.23 of this part and manufactured under a production certificate; or (iii) A normal category rotorcraft type certificated under Part 6 of the Civil Air Regulations or Part 27 of the Federal Aviation Regulations and manufactured under a production certificate. (2) Used aircraft possessing a valid U.S. airworthiness certificate, or other used Class I products that have been maintained in accordance with the applicable CAR's or FAR's and are located in a foreign country, if the Administrator finds that the location places no undue burden upon the FAA in administering the provisions of this regulation. (3) Class II and III products that are manufactured and located in the United States. (c) <E T="03">Export airworthiness approval exceptions.</E> If the export airworthiness approval is issued on the basis of a written statement by the importing state as provided for in § 21.327(e)(4), the requirements that are not met and the differences in configuration, if any, between the product to be exported and the related type certificated product, are listed on the export airworthiness approval as exceptions. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Amdt. 21-14, 32 FR 2999, Feb. 17, 1967; Amdt. 21-43, 40 FR 2577, Jan. 14, 1975; Amdt. 21-48, 44 FR 15649, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.327</SECTNO> <SUBJECT>Application.</SUBJECT> (a) Except as provided in paragraph (b) of this section, an application for export airworthiness approval for a Class I or Class II product is made on a form and in a manner prescribed by the Administrator and is submitted to the appropriate Flight Standards District Office or to the nearest international field office. (b) A manufacturer holding a production certificate may apply orally to the appropriate Flight Standards District Office or the nearest international field office for export airworthiness approval of a Class II product approved under his production certificate. (c) Application for export airworthiness approval of Class III products is made to the designated representative of the Administrator authorized to issue those approvals. (d) A separate application must be made for— (1) Each aircraft; (2) Each engine and propeller, except that one application may be made for more than one engine or propeller, if all are of the same type and model and are exported to the same purchaser and country; and (3) Each type of Class II product, except that one application may be used for more than one type of Class II product when— (i) They are separated and identified in the application as to the type and model of the related Class I product; and<PRTPAGE P="141"/> (ii) They are to be exported to the same purchaser and country. (e) Each application must be accompanied by a written statement from the importing country that will validate the export airworthiness approval if the product being exported is— (1) An aircraft manufactured outside the United States and being exported to a country with which the United States has a reciprocal agreement concerning the validation of export certificates; (2) An unassembled aircraft which has not been flight-tested; (3) A product that does not meet the special requirement of the importing country; or (4) A product that does not meet a requirement specified in §§ 21.329, 21.331, or 21.333, as applicable, for the issuance of an export airworthiness approval. The written statement must list the requirements not met. (f) Each application for export airworthiness approval of a Class I product must include, as applicable: (1) A Statement of Conformity, FAA Form 8130-9, for each new product that has not been manufactured under a production certificate. (2) A weight and balance report, with a loading schedule when applicable, for each aircraft in accordance with Part 43 of this chapter. For transport aircraft and commuter category airplanes this report must be based on an actual weighing of the aircraft within the preceding twelve months, but after any major repairs or alterations to the aircraft. Changes in equipment not classed as major changes that are made after the actual weighing may be accounted for on a “computed” basis and the report revised accordingly. Manufacturers of new nontransport category air-planes, normal category rotorcraft, and gliders may submit reports having computed weight and balance data, in place of an actual weighing of the aircraft, if fleet weight control procedures approved by the FAA have been established for such aircraft. In such a case, the following statement must be entered in each report: “The weight and balance data shown in this report are computed on the basis of Federal Aviation Administration approved procedures for establishing fleet weight averages.” The weight and balance report must include an equipment list showing weights and moment arms of all required and optional items of equipment that are included in the certificated empty weight. (3) A maintenance manual for each new product when such a manual is required by the applicable airworthiness rules. (4) Evidence of compliance with the applicable airworthiness directives. A suitable notation must be made when such directives are not complied with. (5) When temporary installations are incorporated in an aircraft for the purpose of export delivery, the application form must include a general description of the installations together with a statement that the installation will be removed and the aircraft restored to the approved configuration upon completion of the delivery flight. (6) Historical records such as aircraft and engine log books, repair and alteration forms, etc., for used aircraft and newly overhauled products. (7) For products intended for overseas shipment, the application form must describe the methods used, if any, for the preservation and packaging of such products to protect them against corrosion and damage while in transit or storage. The description must also indicate the duration of the effectiveness of such methods. (8) The Airplane or Rotorcraft Flight Manual when such material is required by the applicable airworthiness regulations for the particular aircraft. (9) A statement as to the date when title passed or is expected to pass to a foreign purchaser. (10) The data required by the special requirements of the importing country. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967; Amdt. 21-48, 44 FR 15650, Mar. 15, 1979; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.329</SECTNO> <SUBJECT>Issue of export certificates of airworthiness for Class I products.</SUBJECT> An applicant is entitled to an export certificate of airworthiness for a Class I product if that applicant shows at the time the product is submitted to the Administrator for export airworthiness approval that it meets the requirements of paragraphs (a) through (f) of <PRTPAGE P="142"/>this section, as applicable, except as provided in paragraph (g) of this section: (a) New or used aircraft manufactured in the United States must meet the airworthiness requirement for a standard U.S. airworthiness certificate under § 21.183, or meet the airworthiness certification requirements for a “restricted” airworthiness certificate under § 21.185. (b) New or used aircraft manufactured outside the United States must have a valid U.S. standard airworthiness certificate. (c) Used aircraft must have undergone an annual type inspection and be approved for return to service in accordance with Part 43 of this chapter. The inspection must have been performed and properly documented within 30 days before the date the application is made for an export certificate of airworthiness. In complying with this paragraph, consideration may be given to the inspections performed on an aircraft maintained in accordance with a continuous airworthiness maintenance program under Part 121 or 127 of this chapter or a progressive inspection program under Part 91 of this chapter, within the 30 days prior to the date the application is made for an export certificate of airworthiness. (d) New engines and propellers must conform to the type design and must be in a condition for safe operation. (e) Used engines and propellers which are not being exported as part of a certificated aircraft must have been newly overhauled. (f) The special requirements of the importing country must have been met. (g) A product need not meet a requirement specified in paragraphs (a) through (f) of this section, as applicable, if acceptable to the importing country and the importing country indicates that acceptability in accordance with § 21.327(e)(4) of this part. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Amdt. 21-8, 31 FR 2421, Feb. 5, 1966; Amdt. 21-9, 31 FR 3336, Mar. 3, 1966; Amdt. 21-48, 44 FR 15650, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.331</SECTNO> <SUBJECT>Issue of airworthiness approval tags for Class II products.</SUBJECT> (a) An applicant is entitled to an export airworthiness approval tag for Class II products if that applicant shows, except as provided in paragraph (b) of this section, that-- (1) The products are new or have been newly overhauled and conform to the approved design data; (2) The products are in a condition for safe operation; (3) The products are identified with at least the manufacturer's name, part number, model designation (when applicable), and serial number or equivalent; and (4) The products meet the special requirements of the importing country. (b) A product need not meet a requirement specified in paragraph (a) of this section if acceptable to the importing country and the importing country indicates that acceptability in accordance with § 21.327(e)(4) of this part. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, l965, as amended by Amdt. 21-48, 44 FR 15650, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.333</SECTNO> <SUBJECT>Issue of export airworthiness approval tags for Class III products.</SUBJECT> (a) An applicant is entitled to an export airworthiness approval tag for Class III products if that applicant shows, except as provided in paragraph (b) of this section, that— (1) The products conform to the approved design data applicable to the Class I or Class II product of which they are a part; (2) The products are in a condition for safe operation; and (3) The products comply with the special requirements of the importing country. (b) A product need not meet a requirement specified in paragraph (a) of this section if acceptable to the importing country and the importing country indicates that acceptability in accordance with § 21.327(e)(4) of this part. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, l965, as amended by Amdt. 21-48, 44 FR 15650, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <PRTPAGE P="143"/> <SECTNO>§ 21.335</SECTNO> <SUBJECT>Responsibilities of exporters.</SUBJECT> Each exporter receiving an export airworthiness approval for a product shall— (a) Forward to the air authority of the importing country all documents and information necessary for the proper operation of the products being exported, e.g., Flight Manuals, Maintenance Manuals, Service Bulletins, and assembly instructions, and such other material as is stipulated in the special requirements of the importing country. The documents, information, and material may be forwarded by any means consistent with the special requirements of the importing country; (b) Forward the manufacturer's assembly instructions and an FAA-approved flight test checkoff form to the air authority of the importing country when unassembled aircraft are being exported. These instructions must be in sufficient detail to permit whatever rigging, alignment, and ground testing is necessary to ensure that the aircraft will conform to the approved configuration when assembled; (c) Remove or cause to be removed any temporary installation incorporated on an aircraft for the purpose of export delivery and restore the aircraft to the approved configuration upon completion of the delivery flight; (d) Secure all proper foreign entry clearances from all the countries involved when conducting sales demonstrations or delivery flights; and (e) When title to an aircraft passes or has passed to a foreign purchaser— (1) Request cancellation of the U.S. registration and airworthiness certificates, giving the date of transfer of title, and the name and address of the foreign owner; (2) Return the Registration and Airworthiness Certificates, AC Form 8050.3 and FAA Form 8100-2, to the FAA; and (3) Submit a statement certifying that the United States’ identification and registration numbers have been removed from the aircraft in compliance with § 45.33. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Amdt. 21-48, 44 FR 15650, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.337</SECTNO> <SUBJECT>Performance of inspections and overhauls.</SUBJECT> Unless otherwise provided for in this subpart, each inspection and overhaul required for export airworthiness approval of Class I and Class II products must be performed and approved by one of the following: (a) The manufacturer of the product. (b) An appropriately certificated domestic repair station. (c) An appropriately certificated foreign repair station having adequate overhaul facilities, and maintenance organization appropriate to the product involved, when the product is a Class I product located in a foreign country and an international office of Flight Standards Service has approved the use of such foreign repair station. (d) The holder of an inspection authorization as provided in Part 65 of this chapter. (e) An air carrier, when the product is one that the carrier has maintained under its own or another air carrier's continuous airworthiness maintenance program and maintenance manuals as provided in Part 121 or 127 of this chapter. (f) A commercial operator, when the product is one that the operator has maintained under its continuous airworthiness maintenance program and maintenance manual as provided in Part 121 of this chapter. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Amdt. 21-8, 31 FR 2421, Feb. 5, 1966]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.339</SECTNO> <SUBJECT>Special export airworthiness approval for aircraft.</SUBJECT> A special export certificate of airworthiness may be issued for an aircraft located in the United States that is to be flown to several foreign countries for the purpose of sale, without returning the aircraft to the United States for the certificate if— (a) The aircraft possesses either— (1) A standard U.S. certificate of airworthiness; or (2) A special U.S. certificate of airworthiness in the restricted category issued under § 21.185; (b) The owner files an application as required by § 21.327 except that items 3 and 4 of the application (FAA Form 8130-1) need not be completed;<PRTPAGE P="144"/> (c) The aircraft is inspected by the Administrator before leaving the United States and is found to comply with all the applicable requirements; (d) A list of foreign countries in which it is intended to conduct sales demonstrations, together with the expected dates and duration of such demonstration, is included in the application; (e) For each prospective importing country, the applicant shows that— (1) He has met that country's special requirements, other than those requiring that documents, information, and materials be furnished; and (2) He has the documents, information, and materials necessary to meet the special requirements of that country; and (f) All other requirements for the issuance of a Class I export certificate of airworthiness are met. <CITA>[Amdt. 21-12, 31 FR 12565, Sept. 23, 1966, as amended by Amdt. 21-43, 40 FR 2577, Jan. 14, 1975; Amdt. 21-55, 46 FR 44737, Sept. 8, 1981]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart M—Designated Alteration Station Authorization Procedures</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 21-6, 30 FR 11379, Sept. 8, 1965; 30 FR 11849, Sept. 16, 1965, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.431</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart prescribes Designated Alteration Station (DAS) authorization procedures for— (1) Issuing supplemental type certificates; (2) Issuing experimental certificates; and (3) Amending standard airworthiness certificates. (b) This subpart applies to domestic repair stations, air carriers, commercial operators of large aircraft, and manufacturers of products. <CITA>[Amdt. 21-6, 30 FR 11379, Sept. 8, 1965; 30 FR 11849, Sept. 16, 1965, as amended by Amdt. 21-74, 62 FR 13253, Mar. 19, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.435</SECTNO> <SUBJECT>Application.</SUBJECT> The applicant for a DAS authorization must submit an application, in writing and signed by an official of the applicant, to the Aircraft Certification Office responsible for the geographic area in which the applicant is located. The application must contain— (a) The repair station certificate number held by the repair station applicant, and the current ratings covered by the certificate; (b) The air carrier or commercial operator operating certificate number held by the air carrier or commercial operator applicant, and the products that it may operate and maintain under the certificate; (c) A statement by the manufacturer applicant of the products for which he holds the type certificate; (d) The names, signatures, and titles of the persons for whom authorization to issue supplemental type certificates or experimental certificates, or amend airworthiness certificates, is requested; and (e) A description of the applicant's facilities, and of the staff with which compliance with § 21.439(a)(4) is to be shown. <CITA>[Amdt. 21-6, 30 FR 11379, Sept. 8, 1965; 30 FR 11849, Sept. 16, 1965, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.439</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) To be eligible for a DAS authorization, the applicant must— (1) Hold a current domestic repair station certificate under Part 145, or air carrier or commercial operator operating certificate under Part 121; (2) Be a manufacturer of a product for which it has alteration authority under § 43.3(i) of this subchapter; (3) Have adequate maintenance facilities and personnel, in the United States, appropriate to the products that it may operate and maintain under its certificate; and (4) Employ, or have available, a staff of engineering, flight test, and inspection personnel who can determine compliance with the applicable airworthiness requirements of this chapter. (b) At least one member of the staff required by paragraph (a)(4) of this section must have all of the following qualifications: (1) A thorough working knowledge of the applicable requirements of this chapter.<PRTPAGE P="145"/> (2) A position, on the applicant's staff, with authority to establish alteration programs that ensure that altered products meet the applicable requirements of this chapter. (3) At least one year of satisfactory experience in direct contact with the FAA (or its predecessor agency (CAA)) while processing engineering work for type certification or alteration projects. (4) At least eight years of aeronautical engineering experience (which may include the one year required by paragraph (b)(3) of this section). (5) The general technical knowledge and experience necessary to determine that altered products, of the types for which a DAS authorization is requested, are in condition for safe operation. </SECTION> <SECTION> <SECTNO>§ 21.441</SECTNO> <SUBJECT>Procedure manual.</SUBJECT> (a) No DAS may exercise any authority under this subpart unless it submits, and obtains approval of, a procedure manual containing— (1) The procedures for issuing STCs; and (2) The names, signatures, and responsibilities of officials and of each staff member required by § 21.439(a)(4), identifying those persons who— (i) Have authority to make changes in procedures that require a revision to the procedure manual; and (ii) Are to conduct inspections (including conformity and compliance inspections) or approve inspection reports, prepare or approve data, plan or conduct tests, approve the results of tests, amend airworthiness certificates, issue experimental certificates, approve changes to operating limitations or Aircraft Flight Manuals, and sign supplemental type certificates. (b) No DAS may continue to perform any DAS function affected by any change in facilities or staff necessary to continue to meet the requirements of § 21.439, or affected by any change in procedures from those approved under paragraph (a) of this section, unless that change is approved and entered in the manual. For this purpose, the manual shall contain a log-of-revisions page with space for the identification of each revised item, page, or date, and the signature of the person approving the change for the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.443</SECTNO> <SUBJECT>Duration.</SUBJECT> (a) A DAS authorization is effective until it is surrendered or the Administrator suspends, revokes, or otherwise terminates it. (b) The DAS shall return the authorization certificate to the Administrator when it is no longer effective. </SECTION> <SECTION> <SECTNO>§ 21.445</SECTNO> <SUBJECT>Maintenance of eligibility.</SUBJECT> The DAS shall continue to meet the requirements for issue of the authorization or shall notify the Administrator within 48 hours of any change (including a change of personnel) that could affect the ability of the DAS to meet those requirements. </SECTION> <SECTION> <SECTNO>§ 21.447</SECTNO> <SUBJECT>Transferability.</SUBJECT> A DAS authorization is not transferable. </SECTION> <SECTION> <SECTNO>§ 21.449</SECTNO> <SUBJECT>Inspections.</SUBJECT> Upon request, each DAS and each applicant shall let the Administrator inspect his facilities, products, and rec-ords. </SECTION> <SECTION> <SECTNO>§ 21.451</SECTNO> <SUBJECT>Limits of applicability.</SUBJECT> (a) DAS authorizations apply only to products— (1) Covered by the ratings of the repair station applicant; (2) Covered by the operating certificate and maintenance manual of the air carrier or commercial operator applicant; and (3) For which the manufacturer applicant has alteration authority under § 43.3(i) of this subchapter. (b) DAS authorizations may be used for— (1) The issue of supplemental type certificates; (2) The issue of experimental certificates for aircraft that— (i) Are altered by the DAS under a supplemental type certificate issued by the DAS; and (ii) Require flight tests in order to show compliance with the applicable airworthiness requirements of this chapter; and (3) The amendment of standard airworthiness certificates for aircraft altered under this subpart.<PRTPAGE P="146"/> (c) DAS authorizations are subject to any additional limitations prescribed by the Administrator after inspection of the applicant's facilities or review of the staff qualifications. (d) Notwithstanding any other provision of this subpart, a DAS may not issue a supplemental type certificate involving the exhaust emissions change requirements of part 34 or the acoustical change requirements of part 36 of this chapter until the Administrator finds that those requirements are met. <CITA>[Amdt. 21-6, 30 FR 11379, Sept. 8, 1965; 30 FR 11849, Sept. 16, 1965, as amended by Amdt. 21-42, 40 FR 1034, Jan. 6, 1975; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.461</SECTNO> <SUBJECT>Equivalent safety provisions.</SUBJECT> The DAS shall obtain the Administrator's concurrence on the application of all equivalent safety provisions applied under § 21.21. </SECTION> <SECTION> <SECTNO>§ 21.463</SECTNO> <SUBJECT>Supplemental type certificates.</SUBJECT> (a) For each supplemental type certificate issued under this subpart, the DAS shall follow the procedure manual prescribed in § 21.441 and shall, before issuing the certificate— (1) Submit to the Administrator a statement describing— (i) The type design change; (ii) The airworthiness requirements of this chapter (by part and effective date) that the DAS considers applicable; and (iii) The proposed program for meeting the applicable airworthiness requirements; (2) Find that each applicable airworthiness requirement is met; and (3) Find that the type of product for which the STC is to be issued, as modified by the supplemental type design data upon which the STC is based, is of proper design for safe operation. (b) Within 30 days after the date of issue of the STC, the DAS shall submit to the Administrator— (1) Two copies of the STC; (2) One copy of the design data approved by the DAS and referred to in the STC; (3) One copy of each inspection and test report; and (4) Two copies of each revision to the Aircraft Flight Manual or to the operating limitations, and any other information necessary for safe operation of the product. </SECTION> <SECTION> <SECTNO>§ 21.473</SECTNO> <SUBJECT>Airworthiness certificates other than experimental.</SUBJECT> For each amendment made to a standard airworthiness certificate under this subpart, the DAS shall follow the procedure manual prescribed in § 21.441 and shall, before making that amendment— (a) Complete each flight test necessary to meet the applicable airworthiness requirements of this chapter; (b) Find that each applicable airworthiness requirement of this chapter is met; and (c) Find that the aircraft is in condition for safe operation. </SECTION> <SECTION> <SECTNO>§ 21.475</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> The DAS shall, before issuing an experimental certificate, obtain from the Administrator any limitations and conditions that the Administrator considers necessary for safety. </SECTION> <SECTION> <SECTNO>§ 21.477</SECTNO> <SUBJECT>Data review and service experience.</SUBJECT> (a) If the Administrator finds that a product for which an STC was issued under this subpart does not meet the applicable airworthiness requirements, or that an unsafe feature or characteristic caused by a defect in design or manufacture exists, the DAS, upon notification by the Administrator, shall investigate the matter and report to the Administrator the results of the investigation and the action, if any, taken or proposed. (b) If corrective action by the user of the product is necessary for safety because of any noncompliance or defect specified in paragraph (a) of this section, the DAS shall submit the information necessary for the issue of an Airworthiness Directive under Part 39. </SECTION> <SECTION> <SECTNO>§ 21.493</SECTNO> <SUBJECT>Current records.</SUBJECT> (a) The DAS shall maintain, at its facility, current records containing— (1) For each product for which it has issued an STC under this subpart, a technical data file that includes any <PRTPAGE P="147"/>data and amendments thereto (including drawings, photographs, specifications, instructions, and reports) necessary for the STC; (2) A list of products by make, model, manufacturer's serial number and, if applicable, any FAA identification, that have been altered under the DAS authorization; and (3) A file of information from all available sources on alteration difficulties of products altered under the DAS authorization. (b) The records prescribed in paragraph (a) of this section shall be— (1) Made available by the DAS, upon the Administrator's request, for examination by the Administrator at any time; and (2) In the case of the data file prescribed in paragraph (a)(1) of this section, identified by the DAS and sent to the Administrator as soon as the DAS no longer operates under this subpart. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart N—Approval of Engines, Propellers, Materials, Parts, and Appliances: Import</HD> <SECTION> <SECTNO>§ 21.500</SECTNO> <SUBJECT>Approval of engines and propellers.</SUBJECT> Each holder or licensee of a U.S. type certificate for an aircraft engine or propeller manufactured in a foreign country with which the United States has an agreement for the acceptance of those products for export and import, shall furnish with each such aircraft engine or propeller imported into this country, a certificate of airworthiness for export issued by the country of manufacture certifying that the individual aircraft engine or propeller— (a) Conforms to its U.S. type certificate and is in condition for safe operation; and (b) Has been subjected by the manufacturer to a final operational check. <CITA>[Amdt. 21-25, 34 FR 14068, Sept. 5, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.502</SECTNO> <SUBJECT>Approval of materials, parts, and appliances.</SUBJECT> (a) A material, part, or appliance, manufactured in a foreign country with which the United States has an agreement for the acceptance of those materials, parts, or appliances for export and import, is considered to meet the requirements for approval in the Federal Aviation Regulations when the country of manufacture issues a certificate of airworthiness for export certifying that the individual material, part, or appliance meets those requirements, unless the Administrator finds, based on the technical data submitted under paragraph (b) of this section, that the material, part, or appliance is otherwise not consistent with the intent of the Federal Aviation Regulations. (b) An applicant for approval of a material, part, or appliance must, upon request, submit to the Administrator any technical data respecting that material, part, or appliance. <CITA>[Amdt. 21-25, 34 FR 14068, Sept. 5, 1969]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart O—Technical Standard Order Authorizations</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 19589, 45 FR 38346, June 9, 1980, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.601</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart prescribes— (1) Procedural requirements for the issue of Technical Standard Order authorizations; (2) Rules governing the holders of Technical Standard Order authorizations; and (3) Procedural requirements for the issuance of a letter of Technical Standard Order design approval. (b) For the purpose of this subpart— (1) A Technical Standard Order (referred to in this subpart as “TSO”) is issued by the Administrator and is a minimum performance standard for specified articles (for the purpose of this subpart, articles means materials, parts, processes, or appliances) used on civil aircraft. (2) A TSO authorization is an FAA design and production approval issued to the manufacturer of an article which has been found to meet a specific TSO. (3) A letter of TSO design approval is an FAA design approval for a foreign-manufactured article which has been found to meet a specific TSO in accordance with the procedures of § 21.617. (4) An article manufactured under a TSO authorization, an FAA letter of <PRTPAGE P="148"/>acceptance as described in § 21.603(b), or an appliance manufactured under a letter of TSO design approval described in § 21.617 is an approved article or appliance for the purpose of meeting the regulations of this chapter that require the article to be approved. (5) An article manufacturer is the person who controls the design and quality of the article produced (or to be produced, in the case of an application), including the parts of them and any processes or services related to them that are procured from an outside source. (c) The Administrator does not issue a TSO authorization if the manufacturing facilities for the product are located outside of the United States, unless the Administrator finds that the location of the manufacturer's facilities places no undue burden on the FAA in administering applicable airworthiness requirements. </SECTION> <SECTION> <SECTNO>§ 21.603</SECTNO> <SUBJECT>TSO marking and privileges.</SUBJECT> (a) Except as provided in paragraph (b) of this section and § 21.617(c), no person may identify an article with a TSO marking unless that person holds a TSO authorization and the article meets applicable TSO performance standards. (b) The holder of an FAA letter of acceptance of a statement of conformance issued for an article before July 1, 1962, or any TSO authorization issued after July 1, 1962, may continue to manufacture that article without obtaining a new TSO authorization but shall comply with the requirements of §§ 21.3, 21.607 through 21.615, 21.619, and 21.621. (c) Notwithstanding paragraphs (a) and (b) of this section, after August 6, 1976, no person may identify or mark an article with any of the following TSO numbers: (1) TSO-C18, -C18a, -C18b, -C18c. (2) TSO-C24. (3) TSO-C33. (4) TSO-C61 or C61a. </SECTION> <SECTION> <SECTNO>§ 21.605</SECTNO> <SUBJECT>Application and issue.</SUBJECT> (a) The manufacturer (or an authorized agent) shall submit an application for a TSO authorization, together with the following documents, to the Manager of the Aircraft Certification Office for the geographic area in which the applicant is located: (1) A statement of conformance certifying that the applicant has met the requirements of this subpart and that the article concerned meets the applicable TSO that is effective on the date of application for that article. (2) One copy of the technical data required in the applicable TSO. (3) A description of its quality control system in the detail specified in § 21.143. In complying with this section, the applicant may refer to current quality control data filed with the FAA as part of a previous TSO authorization application. (b) When a series of minor changes in accordance with § 21.611 is anticipated, the applicant may set forth in its application the basic model number of the article and the part number of the components with open brackets after it to denote that suffix change letters or numbers (or combinations of them) will be added from time to time. (c) After receiving the application and other documents required by paragraph (a) of this section to substantiate compliance with this part, and after a determination has been made of its ability to produce duplicate articles under this part, the Administrator issues a TSO authorization (including all TSO deviations granted to the applicant) to the applicant to identify the article with the applicable TSO marking. (d) If the application is deficient, the applicant must, when requested by the Administrator, submit any additional information necessary to show compliance with this part. If the applicant fails to submit the additional information within 30 days after the Administrator's request, the application is denied and the applicant is so notified. (e) The Administrator issues or denies the application within 30 days after its receipt or, if additional information has been requested, within 30 days after receiving that information. <CITA>[Doc. No. 19589, 45 FR 38346, June 9, 1980, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <PRTPAGE P="149"/> <SECTNO>§ 21.607</SECTNO> <SUBJECT>General rules governing holders of TSO authorizations.</SUBJECT> Each manufacturer of an article for which a TSO authorization has been issued under this part shall— (a) Manufacture the article in accordance with this part and the applicable TSO; (b) Conduct all required tests and inspections and establish and maintain a quality control system adequate to ensure that the article meets the requirements of paragraph (a) of this section and is in condition for safe operation; (c) Prepare and maintain, for each model of each article for which a TSO authorization has been issued, a current file of complete technical data and records in accordance with § 21.613; and (d) Permanently and legibly mark each article to which this section applies with the following information: (1) The name and address of the manufacturer. (2) The name, type, part number, or model designation of the article. (3) The serial number or the date of manufacture of the article or both. (4) The applicable TSO number. </SECTION> <SECTION> <SECTNO>§ 21.609</SECTNO> <SUBJECT>Approval for deviation.</SUBJECT> (a) Each manufacturer who requests approval to deviate from any performance standard of a TSO shall show that the standards from which a deviation is requested are compensated for by factors or design features providing an equivalent level of safety. (b) The request for approval to deviate, together with all pertinent data, must be submitted to the Manager of the Aircraft Certification Office for the geographic area in which the manufacturer is located. If the article is manufactured in another country, the request for approval to deviate, together with all pertinent data, must be submitted through the civil aviation authority in that country to the FAA. <CITA>[Doc. No. 19589, 45 FR 38346, June 9, 1980, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.611</SECTNO> <SUBJECT>Design changes.</SUBJECT> (a) <E T="03">Minor changes by the manufacturer holding a TSO authorization.</E> The manufacturer of an article under an authorization issued under this part may make minor design changes (any change other than a major change) without further approval by the Administrator. In this case, the changed article keeps the original model number (part numbers may be used to identify minor changes) and the manufacturer shall forward to the appropriate Aircraft Certification Office for the geographic area, any revised data that are necessary for compliance with § 21.605(b). (b) <E T="03">Major changes by manufacturer holding a TSO authorization.</E> Any design change by the manufacturer that is extensive enough to require a substantially complete investigation to determine compliance with a TSO is a major change. Before making such a change, the manufacturer shall assign a new type or model designation to the article and apply for an authorization under § 21.605. (c) <E T="03">Changes by person other than manufacturer.</E> No design change by any person (other than the manufacturer who submitted the statement of conformance for the article) is eligible for approval under this part unless the person seeking the approval is a manufacturer and applies under § 21.605(a) for a separate TSO authorization. Persons other than a manufacturer may obtain approval for design changes under Part 43 or under the applicable airworthiness regulations. <CITA>[Doc. No. 19589, 45 FR 38346, June 9, 1980, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.613</SECTNO> <SUBJECT>Recordkeeping requirements.</SUBJECT> (a) <E T="03">Keeping the records.</E> Each manufacturer holding a TSO authorization under this part shall, for each article manufactured under that authorization, keep the following records at its factory: (1) A complete and current technical data file for each type or model article, including design drawings and specifications. (2) Complete and current inspection records showing that all inspections and tests required to ensure compliance with this part have been properly completed and documented. (b) <E T="03">Retention of records.</E> The manufacturer shall retain the records described in paragraph (a)(1) of this section until it no longer manufactures the article. <PRTPAGE P="150"/>At that time, copies of these records shall be sent to the Administrator. The manufacturer shall retain the records described in paragraph (a)(2) of this section for a period of at least 2 years. </SECTION> <SECTION> <SECTNO>§ 21.615</SECTNO> <SUBJECT>FAA inspection.</SUBJECT> Upon the request of the Administrator, each manufacturer of an article under a TSO authorization shall allow the Administrator to— (a) Inspect any article manufactured under that authorization; (b) Inspect the manufacturer's quality control system; (c) Witness any tests; (d) Inspect the manufacturing facilities; and (e) Inspect the technical data files on that article. </SECTION> <SECTION> <SECTNO>§ 21.617</SECTNO> <SUBJECT>Issue of letters of TSO design approval: import appliances.</SUBJECT> (a) A letter of TSO design approval may be issued for an appliance that is manufactured in a foreign country with which the United States has an agreement for the acceptance of these appliances for export and import and that is to be imported into the United States if— (1) The country in which the appliance was manufactured certifies that the appliance has been examined, tested, and found to meet the applicable TSO designated in § 21.305(b) or the applicable performance standards of the country in which the appliance was manufactured and any other performance standards the Administrator may prescribe to provide a level of safety equivalent to that provided by the TSO designated in § 21.305(b); and (2) The manufacturer has submitted one copy of the technical data required in the applicable performance standard through its civil aviation authority. (b) The letter of TSO design approval will be issued by the Administrator and must list any deviation granted to the manufacturer under § 21.609. (c) After the Administrator has issued a letter of TSO design approval and the country of manufacture issues a Certificate of Airworthiness for Export as specified in § 21.502(a), the manufacturer shall be authorized to identify the appliance with the TSO marking requirements described in § 21.607(d) and in the applicable TSO. Each appliance must be accompanied by a Certificate of Airworthiness for Export as specified in § 21.502(a) issued by the country of manufacture. </SECTION> <SECTION> <SECTNO>§ 21.619</SECTNO> <SUBJECT>Noncompliance.</SUBJECT> The Administrator may, upon notice, withdraw the TSO authorization or letter of TSO design approval of any manufacturer who identifies with a TSO marking an article not meeting the performance standards of the applicable TSO. </SECTION> <SECTION> <SECTNO>§ 21.621</SECTNO> <SUBJECT>Transferability and duration.</SUBJECT> A TSO authorization or letter of TSO design approval issued under this part is not transferable and is effective until surrendered, withdrawn, or otherwise terminated by the Administrator. </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 23</EAR> <HD SOURCE="HED">PART 23—AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES</HD> <CONTENTS> <SUBJGRP> <HD SOURCE="HED">Special Federal Aviation Regulations</HD> </SUBJGRP> <FP SOURCE="FP-2"> <E T="04">SFAR</E> No. 23</FP> <FP SOURCE="FP-2"> <E T="04">SFAR</E> No. 41 [Note]</FP> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECHD>Sec.</SECHD> <SECTNO>23.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>23.2</SECTNO> <SUBJECT>Special retroactive requirements.</SUBJECT> <SECTNO>23.3</SECTNO> <SUBJECT>Airplane categories.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Flight</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTNO>23.21</SECTNO> <SUBJECT>Proof of compliance.</SUBJECT> <SECTNO>23.23</SECTNO> <SUBJECT>Load distribution limits.</SUBJECT> <SECTNO>23.25</SECTNO> <SUBJECT>Weight limits.</SUBJECT> <SECTNO>23.29</SECTNO> <SUBJECT>Empty weight and corresponding center of gravity.</SUBJECT> <SECTNO>23.31</SECTNO> <SUBJECT>Removable ballast.</SUBJECT> <SECTNO>23.33</SECTNO> <SUBJECT>Propeller speed and pitch limits.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Performance</HD> <SECTNO>23.45</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.49</SECTNO> <SUBJECT>Stalling period.</SUBJECT> <SECTNO>23.51</SECTNO> <SUBJECT>Takeoff speeds.</SUBJECT> <SECTNO>23.53</SECTNO> <SUBJECT>Takeoff performance.</SUBJECT> <SECTNO>23.55</SECTNO> <SUBJECT>Accelerate-stop distance.</SUBJECT> <SECTNO>23.57</SECTNO> <SUBJECT>Takeoff path.</SUBJECT> <SECTNO>23.59</SECTNO> <SUBJECT>Takeoff distance and takeoff run.</SUBJECT> <SECTNO>23.61</SECTNO> <SUBJECT>Takeoff flight path.</SUBJECT> <SECTNO>23.63</SECTNO> <SUBJECT>Climb: general.</SUBJECT> <SECTNO>23.65</SECTNO> <SUBJECT>Climb: All engines operating.</SUBJECT> <SECTNO>23.66</SECTNO> <SUBJECT>Takeoff climb: One-engine inoperative.</SUBJECT> <SECTNO>23.67</SECTNO> <SUBJECT>Climb: one engine inoperative.<PRTPAGE P="151"/> </SUBJECT> <SECTNO>23.69</SECTNO> <SUBJECT>Enroute climb/descent.</SUBJECT> <SECTNO>23.71</SECTNO> <SUBJECT>Glide: Single-engine airplanes.</SUBJECT> <SECTNO>23.73</SECTNO> <SUBJECT>Reference landing approach speed.</SUBJECT> <SECTNO>23.75</SECTNO> <SUBJECT>Landing distance.</SUBJECT> <SECTNO>23.77</SECTNO> <SUBJECT>Balked landing.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Flight Characteristics</HD> <SECTNO>23.141</SECTNO> <SUBJECT>General.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Controllability and Maneuverability</HD> <SECTNO>23.143</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.145</SECTNO> <SUBJECT>Longitudinal control.</SUBJECT> <SECTNO>23.147</SECTNO> <SUBJECT>Directional and lateral control.</SUBJECT> <SECTNO>23.149</SECTNO> <SUBJECT>Minimum control speed.</SUBJECT> <SECTNO>23.151</SECTNO> <SUBJECT>Acrobatic maneuvers.</SUBJECT> <SECTNO>23.153</SECTNO> <SUBJECT>Control during landings.</SUBJECT> <SECTNO>23.155</SECTNO> <SUBJECT>Elevator control force in maneuvers.</SUBJECT> <SECTNO>23.157</SECTNO> <SUBJECT>Rate of roll.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Trim</HD> <SECTNO>23.161</SECTNO> <SUBJECT>Trim.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Stability</HD> <SECTNO>23.171</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.173</SECTNO> <SUBJECT>Static longitudinal stability.</SUBJECT> <SECTNO>23.175</SECTNO> <SUBJECT>Demonstration of static longitudinal stability.</SUBJECT> <SECTNO>23.177</SECTNO> <SUBJECT>Static directional and lateral stability.</SUBJECT> <SECTNO>23.181</SECTNO> <SUBJECT>Dynamic stability.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Stalls</HD> <SECTNO>23.201</SECTNO> <SUBJECT>Wings level stall.</SUBJECT> <SECTNO>23.203</SECTNO> <SUBJECT>Turning flight and accelerated turning stalls.</SUBJECT> <SECTNO>23.207</SECTNO> <SUBJECT>Stall warning.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Spinning</HD> <SECTNO>23.221</SECTNO> <SUBJECT>Spinning.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ground and Water Handling Characteristics</HD> <SECTNO>23.231</SECTNO> <SUBJECT>Longitudinal stability and control.</SUBJECT> <SECTNO>23.233</SECTNO> <SUBJECT>Directional stability and control.</SUBJECT> <SECTNO>23.235</SECTNO> <SUBJECT>Operation on unpaved surfaces.</SUBJECT> <SECTNO>23.237</SECTNO> <SUBJECT>Operation on water.</SUBJECT> <SECTNO>23.239</SECTNO> <SUBJECT>Spray characteristics.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Miscellaneous Flight Requirements</HD> <SECTNO>23.251</SECTNO> <SUBJECT>Vibration and buffeting.</SUBJECT> <SECTNO>23.253</SECTNO> <SUBJECT>High speed characteristics.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Structure</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTNO>23.301</SECTNO> <SUBJECT>Loads.</SUBJECT> <SECTNO>23.302</SECTNO> <SUBJECT>Canard or tandem wing configurations.</SUBJECT> <SECTNO>23.303</SECTNO> <SUBJECT>Factor of safety.</SUBJECT> <SECTNO>23.305</SECTNO> <SUBJECT>Strength and deformation.</SUBJECT> <SECTNO>23.307</SECTNO> <SUBJECT>Proof of structure.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Flight Loads</HD> <SECTNO>23.321</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.331</SECTNO> <SUBJECT>Symmetrical flight conditions.</SUBJECT> <SECTNO>23.333</SECTNO> <SUBJECT>Flight envelope.</SUBJECT> <SECTNO>23.335</SECTNO> <SUBJECT>Design airspeeds.</SUBJECT> <SECTNO>23.337</SECTNO> <SUBJECT>Limit maneuvering load factors.</SUBJECT> <SECTNO>23.341</SECTNO> <SUBJECT>Gust loads factors.</SUBJECT> <SECTNO>23.343</SECTNO> <SUBJECT>Design fuel loads.</SUBJECT> <SECTNO>23.345</SECTNO> <SUBJECT>High lift devices.</SUBJECT> <SECTNO>23.347</SECTNO> <SUBJECT>Unsymmetrical flight conditions.</SUBJECT> <SECTNO>23.349</SECTNO> <SUBJECT>Rolling conditions.</SUBJECT> <SECTNO>23.351</SECTNO> <SUBJECT>Yawing conditions.</SUBJECT> <SECTNO>23.361</SECTNO> <SUBJECT>Engine torque.</SUBJECT> <SECTNO>23.363</SECTNO> <SUBJECT>Side load on engine mount.</SUBJECT> <SECTNO>23.365</SECTNO> <SUBJECT>Pressurized cabin loads.</SUBJECT> <SECTNO>23.367</SECTNO> <SUBJECT>Unsymmetrical loads due to engine failure.</SUBJECT> <SECTNO>23.369</SECTNO> <SUBJECT>Rear lift truss.</SUBJECT> <SECTNO>23.371</SECTNO> <SUBJECT>Gyroscopic and aerodynamic loads.</SUBJECT> <SECTNO>23.373</SECTNO> <SUBJECT>Speed control devices.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Control Surface and System Loads</HD> <SECTNO>23.391</SECTNO> <SUBJECT>Control surface loads.</SUBJECT> <SECTNO>23.393</SECTNO> <SUBJECT>Loads parallel to hinge line.</SUBJECT> <SECTNO>23.395</SECTNO> <SUBJECT>Control system loads.</SUBJECT> <SECTNO>23.397</SECTNO> <SUBJECT>Limit control forces and torques.</SUBJECT> <SECTNO>23.399</SECTNO> <SUBJECT>Dual control system.</SUBJECT> <SECTNO>23.405</SECTNO> <SUBJECT>Secondary control system.</SUBJECT> <SECTNO>23.407</SECTNO> <SUBJECT>Trim tab effects.</SUBJECT> <SECTNO>23.409</SECTNO> <SUBJECT>Tabs.</SUBJECT> <SECTNO>23.415</SECTNO> <SUBJECT>Ground gust conditions.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Horizontal Stabilizing and Balancing Surfaces</HD> <SECTNO>23.421</SECTNO> <SUBJECT>Balancing loads.</SUBJECT> <SECTNO>23.423</SECTNO> <SUBJECT>Maneuvering loads.</SUBJECT> <SECTNO>23.425</SECTNO> <SUBJECT>Gust loads.</SUBJECT> <SECTNO>23.427</SECTNO> <SUBJECT>Unsymmetrical loads.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Vertical Surfaces</HD> <SECTNO>23.441</SECTNO> <SUBJECT>Maneuvering loads.</SUBJECT> <SECTNO>23.443</SECTNO> <SUBJECT>Gust loads.</SUBJECT> <SECTNO>23.445</SECTNO> <SUBJECT>Outboard fins or winglets.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ailerons and Special Devices</HD> <SECTNO>23.455</SECTNO> <SUBJECT>Ailerons.</SUBJECT> <SECTNO>23.459</SECTNO> <SUBJECT>Special devices.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ground Loads</HD> <SECTNO>23.471</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.473</SECTNO> <SUBJECT>Ground load conditions and assumptions.</SUBJECT> <SECTNO>23.477</SECTNO> <SUBJECT>Landing gear arrangement.</SUBJECT> <SECTNO>23.479</SECTNO> <SUBJECT>Level landing conditions.</SUBJECT> <SECTNO>23.481</SECTNO> <SUBJECT>Tail down landing conditions.</SUBJECT> <SECTNO>23.483</SECTNO> <SUBJECT>One-wheel landing conditions.</SUBJECT> <SECTNO>23.485</SECTNO> <SUBJECT>Side load conditions.</SUBJECT> <SECTNO>23.493</SECTNO> <SUBJECT>Braked roll conditions.</SUBJECT> <SECTNO>23.497</SECTNO> <SUBJECT>Supplementary conditions for tail wheels.</SUBJECT> <SECTNO>23.499</SECTNO> <SUBJECT>Supplementary conditions for nose wheels.</SUBJECT> <SECTNO>23.505</SECTNO> <SUBJECT>Supplementary conditions for ski-planes.</SUBJECT> <SECTNO>23.507</SECTNO> <SUBJECT>Jacking loads.</SUBJECT> <SECTNO>23.509</SECTNO> <SUBJECT>Towing loads.</SUBJECT> <SECTNO>23.511</SECTNO> <SUBJECT>Ground load; unsymmetrical loads on multiple-wheel units.</SUBJECT> </SUBJGRP> <SUBJGRP> <PRTPAGE P="152"/> <HD SOURCE="HED">Water Loads</HD> <SECTNO>23.521</SECTNO> <SUBJECT>Water load conditions.</SUBJECT> <SECTNO>23.523</SECTNO> <SUBJECT>Design weights and center of gravity positions.</SUBJECT> <SECTNO>23.525</SECTNO> <SUBJECT>Application of loads.</SUBJECT> <SECTNO>23.527</SECTNO> <SUBJECT>Hull and main float load factors.</SUBJECT> <SECTNO>23.529</SECTNO> <SUBJECT>Hull and main float landing conditions.</SUBJECT> <SECTNO>23.531</SECTNO> <SUBJECT>Hull and main float takeoff condition.</SUBJECT> <SECTNO>23.533</SECTNO> <SUBJECT>Hull and main float bottom pressures.</SUBJECT> <SECTNO>23.535</SECTNO> <SUBJECT>Auxiliary float loads.</SUBJECT> <SECTNO>23.537</SECTNO> <SUBJECT>Seawing loads.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Emergency Landing Conditions</HD> <SECTNO>23.561</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.562</SECTNO> <SUBJECT>Emergency landing dynamic conditions.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Fatigue Evaluation</HD> <SECTNO>23.571</SECTNO> <SUBJECT>Metallic pressurized cabin structures.</SUBJECT> <SECTNO>23.572</SECTNO> <SUBJECT>Metallic wing, empennage, and associated structures.</SUBJECT> <SECTNO>23.573</SECTNO> <SUBJECT>Damage tolerance and fatigue evaluation of structure.</SUBJECT> <SECTNO>23.574</SECTNO> <SUBJECT>Metallic damage tolerance and fatigue evaluation of commuter category airplanes.</SUBJECT> <SECTNO>23.575</SECTNO> <SUBJECT>Inspections and other procedures.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Design and Construction</HD> <SECTNO>23.601</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.603</SECTNO> <SUBJECT>Materials and workmanship.</SUBJECT> <SECTNO>23.605</SECTNO> <SUBJECT>Fabrication methods.</SUBJECT> <SECTNO>23.607</SECTNO> <SUBJECT>Fasteners.</SUBJECT> <SECTNO>23.609</SECTNO> <SUBJECT>Protection of structure.</SUBJECT> <SECTNO>23.611</SECTNO> <SUBJECT>Accessibility provisions.</SUBJECT> <SECTNO>23.613</SECTNO> <SUBJECT>Material strength properties and design values.</SUBJECT> <SECTNO>23.619</SECTNO> <SUBJECT>Special factors.</SUBJECT> <SECTNO>23.621</SECTNO> <SUBJECT>Casting factors.</SUBJECT> <SECTNO>23.623</SECTNO> <SUBJECT>Bearing factors.</SUBJECT> <SECTNO>23.625</SECTNO> <SUBJECT>Fitting factors.</SUBJECT> <SECTNO>23.627</SECTNO> <SUBJECT>Fatigue strength.</SUBJECT> <SECTNO>23.629</SECTNO> <SUBJECT>Flutter.</SUBJECT> <SUBJGRP> <HD SOURCE="HED">Wings</HD> <SECTNO>23.641</SECTNO> <SUBJECT>Proof of strength.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Control Surfaces</HD> <SECTNO>23.651</SECTNO> <SUBJECT>Proof of strength.</SUBJECT> <SECTNO>23.655</SECTNO> <SUBJECT>Installation.</SUBJECT> <SECTNO>23.657</SECTNO> <SUBJECT>Hinges.</SUBJECT> <SECTNO>23.659</SECTNO> <SUBJECT>Mass balance.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Control Systems</HD> <SECTNO>23.671</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.672</SECTNO> <SUBJECT>Stability augmentation and automatic and power-operated systems.</SUBJECT> <SECTNO>23.673</SECTNO> <SUBJECT>Primary flight controls.</SUBJECT> <SECTNO>23.675</SECTNO> <SUBJECT>Stops.</SUBJECT> <SECTNO>23.677</SECTNO> <SUBJECT>Trim systems.</SUBJECT> <SECTNO>23.679</SECTNO> <SUBJECT>Control system locks.</SUBJECT> <SECTNO>23.681</SECTNO> <SUBJECT>Limit load static tests.</SUBJECT> <SECTNO>23.683</SECTNO> <SUBJECT>Operation tests.</SUBJECT> <SECTNO>23.685</SECTNO> <SUBJECT>Control system details.</SUBJECT> <SECTNO>23.687</SECTNO> <SUBJECT>Spring devices.</SUBJECT> <SECTNO>23.689</SECTNO> <SUBJECT>Cable systems.</SUBJECT> <SECTNO>23.691</SECTNO> <SUBJECT>Artificial stall barrier system.</SUBJECT> <SECTNO>23.693</SECTNO> <SUBJECT>Joints.</SUBJECT> <SECTNO>23.697</SECTNO> <SUBJECT>Wing flap controls.</SUBJECT> <SECTNO>23.699</SECTNO> <SUBJECT>Wing flap position indicator.</SUBJECT> <SECTNO>23.701</SECTNO> <SUBJECT>Flap interconnection.</SUBJECT> <SECTNO>23.703</SECTNO> <SUBJECT>Takeoff warning system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Landing Gear</HD> <SECTNO>23.721</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.723</SECTNO> <SUBJECT>Shock absorption tests.</SUBJECT> <SECTNO>23.725</SECTNO> <SUBJECT>Limit drop tests.</SUBJECT> <SECTNO>23.726</SECTNO> <SUBJECT>Ground load dynamic tests.</SUBJECT> <SECTNO>23.727</SECTNO> <SUBJECT>Reserve energy absorption drop test.</SUBJECT> <SECTNO>23.729</SECTNO> <SUBJECT>Landing gear extension and retraction system.</SUBJECT> <SECTNO>23.731</SECTNO> <SUBJECT>Wheels.</SUBJECT> <SECTNO>23.733</SECTNO> <SUBJECT>Tires.</SUBJECT> <SECTNO>23.735</SECTNO> <SUBJECT>Brakes.</SUBJECT> <SECTNO>23.737</SECTNO> <SUBJECT>Skis.</SUBJECT> <SECTNO>23.745</SECTNO> <SUBJECT>Nose/tail wheel steering.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Floats and Hulls</HD> <SECTNO>23.751</SECTNO> <SUBJECT>Main float buoyancy.</SUBJECT> <SECTNO>23.753</SECTNO> <SUBJECT>Main float design.</SUBJECT> <SECTNO>23.755</SECTNO> <SUBJECT>Hulls.</SUBJECT> <SECTNO>23.757</SECTNO> <SUBJECT>Auxiliary floats.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Personnel and Cargo Accommodations</HD> <SECTNO>23.771</SECTNO> <SUBJECT>Pilot compartment.</SUBJECT> <SECTNO>23.773</SECTNO> <SUBJECT>Pilot compartment view.</SUBJECT> <SECTNO>23.775</SECTNO> <SUBJECT>Windshields and windows.</SUBJECT> <SECTNO>23.777</SECTNO> <SUBJECT>Cockpit controls.</SUBJECT> <SECTNO>23.779</SECTNO> <SUBJECT>Motion and effect of cockpit controls.</SUBJECT> <SECTNO>23.781</SECTNO> <SUBJECT>Cockpit control knob shape.</SUBJECT> <SECTNO>23.783</SECTNO> <SUBJECT>Doors.</SUBJECT> <SECTNO>23.785</SECTNO> <SUBJECT>Seats, berths, litters, safety belts, and shoulder harnesses.</SUBJECT> <SECTNO>23.787</SECTNO> <SUBJECT>Baggage and cargo compartments.</SUBJECT> <SECTNO>23.791</SECTNO> <SUBJECT>Passenger information signs.</SUBJECT> <SECTNO>23.803</SECTNO> <SUBJECT>Emergency evacuation.</SUBJECT> <SECTNO>23.805</SECTNO> <SUBJECT>Flightcrew emergency exits.</SUBJECT> <SECTNO>23.807</SECTNO> <SUBJECT>Emergency exits.</SUBJECT> <SECTNO>23.811</SECTNO> <SUBJECT>Emergency exit marking.</SUBJECT> <SECTNO>23.812</SECTNO> <SUBJECT>Emergency lighting.</SUBJECT> <SECTNO>23.813</SECTNO> <SUBJECT>Emergency exit access.</SUBJECT> <SECTNO>23.815</SECTNO> <SUBJECT>Width of aisle.</SUBJECT> <SECTNO>23.831</SECTNO> <SUBJECT>Ventilation.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Pressurization</HD> <SECTNO>23.841</SECTNO> <SUBJECT>Pressurized cabins.</SUBJECT> <SECTNO>23.843</SECTNO> <SUBJECT>Pressurization tests.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Fire Protection</HD> <SECTNO>23.851</SECTNO> <SUBJECT>Fire extinguishers.</SUBJECT> <SECTNO>23.853</SECTNO> <SUBJECT>Passenger and crew compartment interiors.</SUBJECT> <SECTNO>23.855</SECTNO> <SUBJECT>Cargo and baggage compartment fire protection.</SUBJECT> <SECTNO>23.859</SECTNO> <SUBJECT>Combustion heater fire protection.</SUBJECT> <SECTNO>23.863</SECTNO> <SUBJECT>Flammable fluid fire protection.</SUBJECT> <SECTNO>23.865</SECTNO> <SUBJECT>Fire protection of flight controls, engine mounts, and other flight structure.</SUBJECT> </SUBJGRP> <SUBJGRP> <PRTPAGE P="153"/> <HD SOURCE="HED">Electrical Bonding and Lightning Protection</HD> <SECTNO>23.867</SECTNO> <SUBJECT>Electrical bonding and protection against lightning and static electricity.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Miscellaneous</HD> <SECTNO>23.871</SECTNO> <SUBJECT>Leveling means.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Powerplant</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTNO>23.901</SECTNO> <SUBJECT>Installation.</SUBJECT> <SECTNO>23.903</SECTNO> <SUBJECT>Engines.</SUBJECT> <SECTNO>23.904</SECTNO> <SUBJECT>Automatic power reserve system.</SUBJECT> <SECTNO>23.905</SECTNO> <SUBJECT>Propellers.</SUBJECT> <SECTNO>23.907</SECTNO> <SUBJECT>Propeller vibration.</SUBJECT> <SECTNO>23.909</SECTNO> <SUBJECT>Turbocharger systems.</SUBJECT> <SECTNO>23.925</SECTNO> <SUBJECT>Propeller clearance.</SUBJECT> <SECTNO>23.929</SECTNO> <SUBJECT>Engine installation ice protection.</SUBJECT> <SECTNO>23.933</SECTNO> <SUBJECT>Reversing systems.</SUBJECT> <SECTNO>23.934</SECTNO> <SUBJECT>Turbojet and turbofan engine thrust reverser systems tests.</SUBJECT> <SECTNO>23.937</SECTNO> <SUBJECT>Turbopropeller-drag limiting systems.</SUBJECT> <SECTNO>23.939</SECTNO> <SUBJECT>Powerplant operating characteristics.</SUBJECT> <SECTNO>23.943</SECTNO> <SUBJECT>Negative acceleration.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Fuel System</HD> <SECTNO>23.951</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.953</SECTNO> <SUBJECT>Fuel system independence.</SUBJECT> <SECTNO>23.954</SECTNO> <SUBJECT>Fuel system lightning protection.</SUBJECT> <SECTNO>23.955</SECTNO> <SUBJECT>Fuel flow.</SUBJECT> <SECTNO>23.957</SECTNO> <SUBJECT>Flow between interconnected tanks.</SUBJECT> <SECTNO>23.959</SECTNO> <SUBJECT>Unusable fuel supply.</SUBJECT> <SECTNO>23.961</SECTNO> <SUBJECT>Fuel system hot weather operation.</SUBJECT> <SECTNO>23.963</SECTNO> <SUBJECT>Fuel tanks: General.</SUBJECT> <SECTNO>23.965</SECTNO> <SUBJECT>Fuel tank tests.</SUBJECT> <SECTNO>23.967</SECTNO> <SUBJECT>Fuel tank installation.</SUBJECT> <SECTNO>23.969</SECTNO> <SUBJECT>Fuel tank expansion space.</SUBJECT> <SECTNO>23.971</SECTNO> <SUBJECT>Fuel tank sump.</SUBJECT> <SECTNO>23.973</SECTNO> <SUBJECT>Fuel tank filler connection.</SUBJECT> <SECTNO>23.975</SECTNO> <SUBJECT>Fuel tank vents and carburetor vapor vents.</SUBJECT> <SECTNO>23.977</SECTNO> <SUBJECT>Fuel tank outlet.</SUBJECT> <SECTNO>23.979</SECTNO> <SUBJECT>Pressure fueling systems.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Fuel System Components</HD> <SECTNO>23.991</SECTNO> <SUBJECT>Fuel pumps.</SUBJECT> <SECTNO>23.993</SECTNO> <SUBJECT>Fuel system lines and fittings.</SUBJECT> <SECTNO>23.994</SECTNO> <SUBJECT>Fuel system components.</SUBJECT> <SECTNO>23.995</SECTNO> <SUBJECT>Fuel valves and controls.</SUBJECT> <SECTNO>23.997</SECTNO> <SUBJECT>Fuel strainer or filter.</SUBJECT> <SECTNO>23.999</SECTNO> <SUBJECT>Fuel system drains.</SUBJECT> <SECTNO>23.1001</SECTNO> <SUBJECT>Fuel jettisoning system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Oil System</HD> <SECTNO>23.1011</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1013</SECTNO> <SUBJECT>Oil tanks.</SUBJECT> <SECTNO>23.1015</SECTNO> <SUBJECT>Oil tank tests.</SUBJECT> <SECTNO>23.1017</SECTNO> <SUBJECT>Oil lines and fittings.</SUBJECT> <SECTNO>23.1019</SECTNO> <SUBJECT>Oil strainer or filter.</SUBJECT> <SECTNO>23.1021</SECTNO> <SUBJECT>Oil system drains.</SUBJECT> <SECTNO>23.1023</SECTNO> <SUBJECT>Oil radiators.</SUBJECT> <SECTNO>23.1027</SECTNO> <SUBJECT>Propeller feathering system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Cooling</HD> <SECTNO>23.1041</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1043</SECTNO> <SUBJECT>Cooling tests.</SUBJECT> <SECTNO>23.1045</SECTNO> <SUBJECT>Cooling test procedures for turbine engine powered airplanes.</SUBJECT> <SECTNO>23.1047</SECTNO> <SUBJECT>Cooling test procedures for reciprocating engine powered airplanes.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Liquid Cooling</HD> <SECTNO>23.1061</SECTNO> <SUBJECT>Installation.</SUBJECT> <SECTNO>23.1063</SECTNO> <SUBJECT>Coolant tank tests.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Induction System</HD> <SECTNO>23.1091</SECTNO> <SUBJECT>Air induction system.</SUBJECT> <SECTNO>23.1093</SECTNO> <SUBJECT>Induction system icing protection.</SUBJECT> <SECTNO>23.1095</SECTNO> <SUBJECT>Carburetor deicing fluid flow rate.</SUBJECT> <SECTNO>23.1097</SECTNO> <SUBJECT>Carburetor deicing fluid system capacity.</SUBJECT> <SECTNO>23.1099</SECTNO> <SUBJECT>Carburetor deicing fluid system detail design.</SUBJECT> <SECTNO>23.1101</SECTNO> <SUBJECT>Induction air preheater design.</SUBJECT> <SECTNO>23.1103</SECTNO> <SUBJECT>Induction system ducts.</SUBJECT> <SECTNO>23.1105</SECTNO> <SUBJECT>Induction system screens.</SUBJECT> <SECTNO>23.1107</SECTNO> <SUBJECT>Induction system filters.</SUBJECT> <SECTNO>23.1109</SECTNO> <SUBJECT>Turbocharger bleed air system.</SUBJECT> <SECTNO>23.1111</SECTNO> <SUBJECT>Turbine engine bleed air system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Exhaust System</HD> <SECTNO>23.1121</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1123</SECTNO> <SUBJECT>Exhaust system.</SUBJECT> <SECTNO>23.1125</SECTNO> <SUBJECT>Exhaust heat exchangers.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Powerplant Controls and Accessories</HD> <SECTNO>23.1141</SECTNO> <SUBJECT>Powerplant controls: General.</SUBJECT> <SECTNO>23.1142</SECTNO> <SUBJECT>Auxiliary power unit controls.</SUBJECT> <SECTNO>23.1143</SECTNO> <SUBJECT>Engine controls.</SUBJECT> <SECTNO>23.1145</SECTNO> <SUBJECT>Ignition switches.</SUBJECT> <SECTNO>23.1147</SECTNO> <SUBJECT>Mixture controls.</SUBJECT> <SECTNO>23.1149</SECTNO> <SUBJECT>Propeller speed and pitch controls.</SUBJECT> <SECTNO>23.1153</SECTNO> <SUBJECT>Propeller feathering controls.</SUBJECT> <SECTNO>23.1155</SECTNO> <SUBJECT>Turbine engine reverse thrust and propeller pitch settings below the flight regime.</SUBJECT> <SECTNO>23.1157</SECTNO> <SUBJECT>Carburetor air temperature controls.</SUBJECT> <SECTNO>23.1163</SECTNO> <SUBJECT>Powerplant accessories.</SUBJECT> <SECTNO>23.1165</SECTNO> <SUBJECT>Engine ignition systems.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Powerplant Fire Protection</HD> <SECTNO>23.1181</SECTNO> <SUBJECT>Designated fire zones; regions included.</SUBJECT> <SECTNO>23.1182</SECTNO> <SUBJECT>Nacelle areas behind firewalls.</SUBJECT> <SECTNO>23.1183</SECTNO> <SUBJECT>Lines, fittings, and components.</SUBJECT> <SECTNO>23.1189</SECTNO> <SUBJECT>Shutoff means.</SUBJECT> <SECTNO>23.1191</SECTNO> <SUBJECT>Firewalls.</SUBJECT> <SECTNO>23.1192</SECTNO> <SUBJECT>Engine accessory compartment diaphragm.</SUBJECT> <SECTNO>23.1193</SECTNO> <SUBJECT>Cowling and nacelle.</SUBJECT> <SECTNO>23.1195</SECTNO> <SUBJECT>Fire extinguishing systems.</SUBJECT> <SECTNO>23.1197</SECTNO> <SUBJECT>Fire extinguishing agents.</SUBJECT> <SECTNO>23.1199</SECTNO> <SUBJECT>Extinguishing agent containers.</SUBJECT> <SECTNO>23.1201</SECTNO> <SUBJECT>Fire extinguishing systems materials.</SUBJECT> <SECTNO>23.1203</SECTNO> <SUBJECT>Fire detector system.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <PRTPAGE P="154"/> <HD SOURCE="HED">Subpart F—Equipment</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTNO>23.1301</SECTNO> <SUBJECT>Function and installation.</SUBJECT> <SECTNO>23.1303</SECTNO> <SUBJECT>Flight and navigation instruments.</SUBJECT> <SECTNO>23.1305</SECTNO> <SUBJECT>Powerplant instruments.</SUBJECT> <SECTNO>23.1307</SECTNO> <SUBJECT>Miscellaneous equipment.</SUBJECT> <SECTNO>23.1309</SECTNO> <SUBJECT>Equipment, systems, and installations.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Instruments: Installation</HD> <SECTNO>23.1311</SECTNO> <SUBJECT>Electronic display instrument systems.</SUBJECT> <SECTNO>23.1321</SECTNO> <SUBJECT>Arrangement and visibility.</SUBJECT> <SECTNO>23.1322</SECTNO> <SUBJECT>Warning, caution, and advisory lights.</SUBJECT> <SECTNO>23.1323</SECTNO> <SUBJECT>Airspeed indicating system.</SUBJECT> <SECTNO>23.1325</SECTNO> <SUBJECT>Static pressure system.</SUBJECT> <SECTNO>23.1326</SECTNO> <SUBJECT>Pitot heat indication systems.</SUBJECT> <SECTNO>23.1327</SECTNO> <SUBJECT>Magnetic direction indicator.</SUBJECT> <SECTNO>23.1329</SECTNO> <SUBJECT>Automatic pilot system.</SUBJECT> <SECTNO>23.1331</SECTNO> <SUBJECT>Instruments using a power source.</SUBJECT> <SECTNO>23.1335</SECTNO> <SUBJECT>Flight director systems.</SUBJECT> <SECTNO>23.1337</SECTNO> <SUBJECT>Powerplant instruments installation.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Electrical Systems and Equipment</HD> <SECTNO>23.1351</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1353</SECTNO> <SUBJECT>Storage battery design and installation.</SUBJECT> <SECTNO>23.1357</SECTNO> <SUBJECT>Circuit protective devices.</SUBJECT> <SECTNO>23.1359</SECTNO> <SUBJECT>Electrical system fire protection.</SUBJECT> <SECTNO>23.1361</SECTNO> <SUBJECT>Master switch arrangement.</SUBJECT> <SECTNO>23.1365</SECTNO> <SUBJECT>Electric cables and equipment.</SUBJECT> <SECTNO>23.1367</SECTNO> <SUBJECT>Switches.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Lights</HD> <SECTNO>23.1381</SECTNO> <SUBJECT>Instrument lights.</SUBJECT> <SECTNO>23.1383</SECTNO> <SUBJECT>Taxi and landing lights.</SUBJECT> <SECTNO>23.1385</SECTNO> <SUBJECT>Position light system installation.</SUBJECT> <SECTNO>23.1387</SECTNO> <SUBJECT>Position light system dihedral angles.</SUBJECT> <SECTNO>23.1389</SECTNO> <SUBJECT>Position light distribution and intensities.</SUBJECT> <SECTNO>23.1391</SECTNO> <SUBJECT>Minimum intensities in the horizontal plane of position lights.</SUBJECT> <SECTNO>23.1393</SECTNO> <SUBJECT>Minimum intensities in any vertical plane of position lights.</SUBJECT> <SECTNO>23.1395</SECTNO> <SUBJECT>Maximum intensities in overlapping beams of position lights.</SUBJECT> <SECTNO>23.1397</SECTNO> <SUBJECT>Color specifications.</SUBJECT> <SECTNO>23.1399</SECTNO> <SUBJECT>Riding light.</SUBJECT> <SECTNO>23.1401</SECTNO> <SUBJECT>Anticollision light system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Safety Equipment</HD> <SECTNO>23.1411</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1415</SECTNO> <SUBJECT>Ditching equipment.</SUBJECT> <SECTNO>23.1416</SECTNO> <SUBJECT>Pneumatic de-icer boot system.</SUBJECT> <SECTNO>23.1419</SECTNO> <SUBJECT>Ice protection.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Miscellaneous Equipment</HD> <SECTNO>23.1431</SECTNO> <SUBJECT>Electronic equipment.</SUBJECT> <SECTNO>23.1435</SECTNO> <SUBJECT>Hydraulic systems.</SUBJECT> <SECTNO>23.1437</SECTNO> <SUBJECT>Accessories for multiengine airplanes.</SUBJECT> <SECTNO>23.1438</SECTNO> <SUBJECT>Pressurization and pneumatic systems.</SUBJECT> <SECTNO>23.1441</SECTNO> <SUBJECT>Oxygen equipment and supply.</SUBJECT> <SECTNO>23.1443</SECTNO> <SUBJECT>Minimum mass flow of supplemental oxygen.</SUBJECT> <SECTNO>23.1445</SECTNO> <SUBJECT>Oxygen distribution system.</SUBJECT> <SECTNO>23.1447</SECTNO> <SUBJECT>Equipment standards for oxygen dispensing units.</SUBJECT> <SECTNO>23.1449</SECTNO> <SUBJECT>Means for determining use of oxygen.</SUBJECT> <SECTNO>23.1450</SECTNO> <SUBJECT>Chemical oxygen generators.</SUBJECT> <SECTNO>23.1451</SECTNO> <SUBJECT>Fire protection for oxygen equipment.</SUBJECT> <SECTNO>23.1453</SECTNO> <SUBJECT>Protection of oxygen equipment from rupture.</SUBJECT> <SECTNO>23.1457</SECTNO> <SUBJECT>Cockpit voice recorders.</SUBJECT> <SECTNO>23.1459</SECTNO> <SUBJECT>Flight recorders.</SUBJECT> <SECTNO>23.1461</SECTNO> <SUBJECT>Equipment containing high energy rotors.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Operating Limitations and Information</HD> <SECTNO>23.1501</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1505</SECTNO> <SUBJECT>Airspeed limitations.</SUBJECT> <SECTNO>23.1507</SECTNO> <SUBJECT>Operating maneuvering speed.</SUBJECT> <SECTNO>23.1511</SECTNO> <SUBJECT>Flap extended speed.</SUBJECT> <SECTNO>23.1513</SECTNO> <SUBJECT>Minimum control speed.</SUBJECT> <SECTNO>23.1519</SECTNO> <SUBJECT>Weight and center of gravity.</SUBJECT> <SECTNO>23.1521</SECTNO> <SUBJECT>Powerplant limitations.</SUBJECT> <SECTNO>23.1522</SECTNO> <SUBJECT>Auxiliary power unit limitations.</SUBJECT> <SECTNO>23.1523</SECTNO> <SUBJECT>Minimum flight crew.</SUBJECT> <SECTNO>23.1524</SECTNO> <SUBJECT>Maximum passenger seating configuration.</SUBJECT> <SECTNO>23.1525</SECTNO> <SUBJECT>Kinds of operation.</SUBJECT> <SECTNO>23.1527</SECTNO> <SUBJECT>Maximum operating altitude.</SUBJECT> <SECTNO>23.1529</SECTNO> <SUBJECT>Instructions for Continued Airworthiness.</SUBJECT> <SUBJGRP> <HD SOURCE="HED">Markings and Placards</HD> <SECTNO>23.1541</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1543</SECTNO> <SUBJECT>Instrument markings: General.</SUBJECT> <SECTNO>23.1545</SECTNO> <SUBJECT>Airspeed indicator.</SUBJECT> <SECTNO>23.1547</SECTNO> <SUBJECT>Magnetic direction indicator.</SUBJECT> <SECTNO>23.1549</SECTNO> <SUBJECT>Powerplant and auxiliary power unit instruments.</SUBJECT> <SECTNO>23.1551</SECTNO> <SUBJECT>Oil quantity indicator.</SUBJECT> <SECTNO>23.1553</SECTNO> <SUBJECT>Fuel quantity indicator.</SUBJECT> <SECTNO>23.1555</SECTNO> <SUBJECT>Control markings.</SUBJECT> <SECTNO>23.1557</SECTNO> <SUBJECT>Miscellaneous markings and placards.</SUBJECT> <SECTNO>23.1559</SECTNO> <SUBJECT>Operating limitations placard.</SUBJECT> <SECTNO>23.1561</SECTNO> <SUBJECT>Safety equipment.</SUBJECT> <SECTNO>23.1563</SECTNO> <SUBJECT>Airspeed placards.</SUBJECT> <SECTNO>23.1567</SECTNO> <SUBJECT>Flight maneuver placard.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Airplane Flight Manual and Approved Manual Material</HD> <SECTNO>23.1581</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1583</SECTNO> <SUBJECT>Operating limitations.</SUBJECT> <SECTNO>23.1585</SECTNO> <SUBJECT>Operating procedures.</SUBJECT> <SECTNO>23.1587</SECTNO> <SUBJECT>Performance information.</SUBJECT> <SECTNO>23.1589</SECTNO> <SUBJECT>Loading information.</SUBJECT> <APP> <E T="04">Appendix A to Part</E> 23<E T="04">—Simplified Design Load Criteria</E> </APP> <APP> <E T="04">Appendix B to Part</E> 23<E T="04"> [Reserved]</E> <PRTPAGE P="155"/> </APP> <APP> <E T="04">Appendix C to Part</E> 23<E T="04">—Basic Landing Conditions</E> </APP> <APP> <E T="04">Appendix D to Part</E> 23<E T="04">—Wheel Spin-Up and Spring-Back Loads</E> </APP> <APP> <E T="04">Appendix E to Part</E> 23<E T="04"> [Reserved]</E> </APP> <APP> <E T="04">Appendix F to Part</E> 23<E T="04">—Test Procedure</E> </APP> <APP> <E T="04">Appendix G to Part</E> 23<E T="04">—Instructions for Continued Airworthiness</E> </APP> <APP> <E T="04">Appendix H to Part</E> 23<E T="04">—Installation of An Automatic Power Reserve (APR) System</E> </APP> <APP> <E T="04">Appendix I to Part</E> 23<E T="04">—Seaplane Loads</E> </APP> </SUBJGRP> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 49 U.S.C. 106(g), 40113, 44701-44702, 44704. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 4080, 29 FR 17955, Dec. 18. 1964; 30 FR 258, Jan. 9, 1965, unless otherwise noted. </SOURCE> <EAR>Pt. 23, SFAR No. 23</EAR> <SUBJGRP> <HD SOURCE="HED">Special Federal Aviation Regulations SFAR No. <E T="01">23</E> </HD> </SUBJGRP> <EXTRACT> 1. <E T="03">Applicability.</E> An applicant is entitled to a type certificate in the normal category for a reciprocating or turbopropeller multiengine powered small airplane that is to be certificated to carry more than 10 occupants and that is intended for use in operations under Part 135 of the Federal Aviation Regulations if he shows compliance with the applicable requirements of Part 23 of the Federal Aviation Regulations, as supplemented or modified by the additional airworthiness requirements of this regulation. 2. <E T="03">References.</E> Unless otherwise provided, all references in this regulation to specific sections of Part 23 of the Federal Aviation Regulations are those sections of Part 23 in effect on March 30, 1967. <HD SOURCE="HD1">Flight Requirements</HD> 3. <E T="03">General.</E> Compliance must be shown with the applicable requirements of Subpart B of Part 23 of the Federal Aviation Regulations in effect on March 30, 1967, as supplemented or modified in sections 4 through 10 of this regulation. <HD SOURCE="HD1">Performance</HD> 4. <E T="03">General.</E> (a) Unless otherwise prescribed in this regulation, compliance with each applicable performance requirement in sections 4 through 7 of this regulation must be shown for ambient atmospheric conditions and still air. (b) The performance must correspond to the propulsive thrust available under the particular ambient atmospheric conditions and the particular flight condition. The available propulsive thrust must correspond to engine power or thrust, not exceeding the approved power or thrust less— (1) Installation losses; and (2) The power or equivalent thrust absorbed by the accessories and services appropriate to the particular ambient atmospheric conditions and the particular flight condition. (c) Unless otherwise prescribed in this regulation, the applicant must select the take-off, en route, and landing configurations for the airplane. (d) The airplane configuration may vary with weight, altitude, and temperature, to the extent they are compatible with the operating procedures required by paragraph (e) of this section. (e) Unless otherwise prescribed in this regulation, in determining the critical engine inoperative takeoff performance, the accelerate-stop distance, takeoff distance, changes in the airplane's configuration, speed, power, and thrust, must be made in accordance with procedures established by the applicant for operation in service. (f) Procedures for the execution of balked landings must be established by the applicant and included in the Airplane Flight Manual. (g) The procedures established under paragraphs (e) and (f) of this section must— (1) Be able to be consistently executed in service by a crew of average skill; (2) Use methods or devices that are safe and reliable; and (3) Include allowance for any time delays, in the execution of the procedures, that may reasonably be expected in service. 5. <E T="03">Takeoff</E>—(a) <E T="03">General.</E> The takeoff speeds described in paragraph (b), the accelerate-stop distance described in paragraph (c), and the takeoff distance described in paragraph (d), must be determined for— (1) Each weight, altitude, and ambient temperature within the operational limits selected by the applicant; (2) The selected configuration for takeoff; (3) The center of gravity in the most unfavorable position; (4) The operating engine within approved operating limitation; and (5) Takeoff data based on smooth, dry, hard-surface runway. (b) <E T="03">Takeoff speeds.</E> (1) The decision speed <E T="03">V</E> <E T="22">1</E> is the calibrated airspeed on the ground at which, as a result of engine failure or other reasons, the pilot is assumed to have made a decision to continue or discontinue the takeoff. The speed <E T="03">V</E> <E T="22">1</E> must be selected by the applicant but may not be less than— (i) 1.10 <E T="03">V</E> <E T="24">s1</E>; (ii) 1.10 <E T="03">V</E> <E T="24">MC</E>; (iii) A speed that permits acceleration to <E T="03">V</E> <E T="22">1</E> and stop in accordance with paragraph (c) allowing credit for an overrun distance equal to that required to stop the airplane from a ground speed of 35 knots utilizing maximum braking; or (iv) A speed at which the airplane can be rotated for takeoff and shown to be adequate to safely continue the takeoff, using normal piloting skill, when the critical engine is suddenly made inoperative.<PRTPAGE P="156"/> (2) Other essential takeoff speeds necessary for safe operation of the airplane must be determined and shown in the Airplane Flight Manual. (c) <E T="03">Accelerate-stop distance.</E> (1) The accelerate-stop distance is the sum of the distances necessary to— (i) Accelerate the airplane from a standing start to <E T="03">V</E> <E T="22">1</E>; and (ii) Decelerate the airplane from <E T="03">V</E> <E T="22">1</E> to a speed not greater than 35 knots, assuming that in the case of engine failure, failure of the critical engine is recognized by the pilot at the speed <E T="03">V</E> <E T="22">1</E>. The landing gear must remain in the extended position and maximum braking may be utilized during deceleration. (2) Means other than wheel brakes may be used to determine the accelerate-stop distance if that means is available with the critical engine inoperative and— (i) Is safe and reliable; (ii) Is used so that consistent results can be expected under normal operating conditions; and (iii) Is such that exceptional skill is not required to control the airplane. (d) <E T="03">All engines operating takeoff distance.</E> The all engine operating takeoff distance is the horizontal distance required to takeoff and climb to a height of 50 feet above the takeoff surface according to procedures in FAR 23.51(a). (e) <E T="03">One-engine-inoperative takeoff.</E> The maximum weight must be determined for each altitude and temperature within the operational limits established for the airplane, at which the airplane has takeoff capability after failure of the critical engine at or above <E T="03">V</E> <E T="22">1</E> determined in accordance with paragraph (b) of this section. This capability may be established— (1) By demonstrating a measurably positive rate of climb with the airplane in the takeoff configuration, landing gear extended; or (2) By demonstrating the capability of maintaining flight after engine failure utilizing procedures prescribed by the applicant. 6. <E T="03">Climb</E>—(a) <E T="03">Landing climb: All-engines-operating.</E> The maximum weight must be determined with the airplane in the landing configuration, for each altitude, and ambient temperature within the operational limits established for the airplane and with the most unfavorable center of gravity and out-of-ground effect in free air, at which the steady gradient of climb will not be less than 3.3 percent, with: (1) The engines at the power that is available 8 seconds after initiation of movement of the power or thrust controls from the mimimum flight idle to the takeoff position. (2) A climb speed not greater than the approach speed established under section 7 of this regulation and not less than the greater of 1.05<E T="24">MC</E> or 1.10V<E T="24">S</E> <E T="22">1</E>. (b) <E T="03">En route climb, one-engine-inoperative.</E> (1) the maximum weight must be determined with the airplane in the en route configuration, the critical engine inoperative, the remaining engine at not more than maximum continuous power or thrust, and the most unfavorable center of gravity, at which the gradient at climb will be not less than— (i) 1.2 percent (or a gradient equivalent to 0.20 <E T="03">V</E> <E T="24">so</E> 2<E T="11">, if greater) at 5,000 feet and an ambient temperature of 41° F. or</E> (ii) 0.6 percent (or a gradient equivalent to 0.01 <E T="03">V</E> <E T="24">so</E> 2<E T="11">, if greater) at 5,000 feet and ambient temperature of 81° F.</E> (2) The minimum climb gradient specified in subdivisions (i) and (ii) of subparagraph (1) of this paragraph must vary linearly between 41° F. and 81° F. and must change at the same rate up to the maximum operational temperature approved for the airplane. 7. <E T="03">Landing.</E> The landing distance must be determined for standard atmosphere at each weight and altitude in accordance with FAR 23.75(a), except that instead of the gliding approach specified in FAR 23.75(a)(1), the landing may be preceded by a steady approach down to the 50-foot height at a gradient of descent not greater than 5.2 percent (3°) at a calibrated airspeed not less than 1.3<E T="24">s</E> <E T="22">1</E>. <HD SOURCE="HD1">Trim</HD> 8. <E T="03">Trim</E>—(a) <E T="03">Lateral and directional trim.</E> The airplane must maintain lateral and directional trim in level flight at a speed of <E T="03">V</E> <E T="24">h</E> or <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO,</E> whichever is lower, with landing gear and wing flaps retracted. (b) <E T="03">Longitudinal trim.</E> The airplane must maintain longitudinal trim during the following conditions, except that it need not maintain trim at a speed greater than <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO:</E> (1) In the approach conditions specified in FAR 23.161(c)(3) through (5), except that instead of the speeds specified therein, trim must be maintained with a stick force of not more than 10 pounds down to a speed used in showing compliance with section 7 of this regulation or 1.4 <E T="03">V</E> <E T="23">s</E> <E T="22">1</E> whichever is lower. (2) In level flight at any speed from <E T="03">V</E> <E T="24">H</E> or <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E>, whichever is lower, to either <E T="03">Vx</E> or 1.4 <E T="03">V</E> <E T="24">s</E> <E T="22">1</E>, with the landing gear and wing flaps retracted. <HD SOURCE="HD1">Stability</HD> 9. <E T="03">Static longitudinal stability.</E> (a) In showing compliance with the provisions of FAR 23.175(b) and with paragraph (b) of this section, the airspeed must return to within <E T="21">±</E>7<FR>1/2</FR> percent of the trim speed. (b) <E T="03">Cruise stability.</E> The stick force curve must have a stable slope for a speed range of <E T="21">±</E>50 knots from the trim speed except that the speeds need not exceed <E T="03">V</E> <E T="24">FC</E>/<E T="03">M</E> <E T="24">FC</E> or be less than 1.4 <E T="03">V</E> <E T="24">s</E> <E T="22">1</E>. This speed range will be considered to begin at the outer extremes of the <PRTPAGE P="157"/>friction band and the stick force may not exceed 50 pounds with— (i) Landing gear retracted; (ii) Wing flaps retracted; (iii) The maximum cruising power as selected by the applicant as an operating limitation for turbine engines or 75 percent of maximum continuous power for reciprocating engines except that the power need not exceed that required at <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO:</E> (iv) Maximum takeoff weight; and (v) The airplane trimmed for level flight with the power specified in subparagraph (iii) of this paragraph. <E T="03">V</E> <E T="24">FC</E>/<E T="03">M</E> <E T="24">FC</E> may not be less than a speed midway between <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> and <E T="03">V</E> <E T="24">DF</E>/<E T="03">M</E> <E T="24">DF</E>, except that, for altitudes where Mach number is the limiting factor, <E T="03">M</E> <E T="24">FC</E> need not exceed the Mach number at which effective speed warning occurs. (c) <E T="03">Climb stability. For turbopropeller powered airplanes only.</E> In showing compliance with FAR 23.175(a), an applicant must in lieu of the power specified in FAR 23.175(a)(4), use the maximum power or thrust selected by the applicant as an operating limitation for use during climb at the best rate of climb speed except that the speed need not be less than 1.4 <E T="03">V</E> <E T="24">s</E> <E T="22">1</E>. <HD SOURCE="HD1">Stalls</HD> 10. <E T="03">Stall warning.</E> If artificial stall warning is required to comply with the requirements of FAR 23.207, the warning device must give clearly distinguishable indications under expected conditions of flight. The use of a visual warning device that requires the attention of the crew within the cockpit is not acceptable by itself. <HD SOURCE="HD1">Control Systems</HD> 11. <E T="03">Electric trim tabs.</E> The airplane must meet the requirements of FAR 23.677 and in addition it must be shown that the airplane is safely controllable and that a pilot can perform all the maneuvers and operations necessary to effect a safe landing following any probable electric trim tab runaway which might be reasonably expected in service allowing for appropriate time delay after pilot recognition of the runaway. This demonstration must be conducted at the critical airplane weights and center of gravity positions. <HD SOURCE="HD1">Instruments: Installation</HD> 12. <E T="03">Arrangement and visibility.</E> Each instrument must meet the requirements of FAR 23.1321 and in addition— (a) Each flight, navigation, and powerplant instrument for use by any pilot must be plainly visible to him from his station with the minimum practicable deviation from his normal position and line of vision when he is looking forward along the flight path. (b) The flight instruments required by FAR 23.1303 and by the applicable operating rules must be grouped on the instrument panel and centered as nearly as practicable about the vertical plane of each pilot's forward vision. In addition— (1) The instrument that most effectively indicates the attitude must be on the panel in the top center position; (2) The instrument that most effectively indicates airspeed must be adjacent to and directly to the left of the instrument in the top center position; (3) The instrument that most effectively indicates altitude must be adjacent to and directly to the right of the instrument in the top center position; and (4) The instrument that most effectively indicates direction of flight must be adjacent to and directly below the instrument in the top center position. 13. <E T="03">Airspeed indicating system.</E> Each airspeed indicating system must meet the requirements of FAR 23.1323 and in addition— (a) Airspeed indicating instruments must be of an approved type and must be calibrated to indicate true airspeed at sea level in the standard atmosphere with a mimimum practicable instrument calibration error when the corresponding pilot and static pressures are supplied to the instruments. (b) The airspeed indicating system must be calibrated to determine the system error, i.e., the relation between IAS and CAS, in flight and during the accelerate takeoff ground run. The ground run calibration must be obtained between 0.8 of the mimimum value of <E T="03">V</E> <E T="22">1</E> and 1.2 times the maximum value of <E T="03">V</E> <E T="22">1</E>, considering the approved ranges of altitude and weight. The ground run calibration will be determined assuming an engine failure at the mimimum value of <E T="03">V</E> <E T="22">1</E>. (c) The airspeed error of the installation excluding the instrument calibration error, must not exceed 3 percent or 5 knots whichever is greater, throughout the speed range from <E T="03">V</E> <E T="24">MO</E> to 1.3<E T="03">S</E> <E T="22">1</E> with flaps retracted and from 1.3 <E T="03">VS</E> <E T="24">O</E> to <E T="03">V</E> <E T="24">FE</E> with flaps in the landing position. (d) Information showing the relationship between IAS and CAS must be shown in the Airplane Flight Manual. 14. <E T="03">Static air vent system.</E> The static air vent system must meet the requirements of FAR 23.1325. The altimeter system calibration must be determined and shown in the Airplane Flight Manual. <HD SOURCE="HD1">Operating Limitations and Information</HD> 15. <E T="03">Maximum operating limit speed V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO.</E> Instead of establishing operating limitations based on <E T="03">V</E> <E T="24">ME</E> and <E T="03">V</E> <E T="24">NO</E>, the applicant must establish a maximum operating limit speed <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> in accordance with the following: (a) The maximum operating limit speed must not exceed the design cruising speed <E T="03">Vc</E> <PRTPAGE P="158"/>and must be sufficiently below <E T="03">V</E> <E T="24">D</E>/<E T="03">M</E> <E T="24">D</E> or <E T="03">V</E> <E T="24">DF</E>/<E T="03">M</E> <E T="24">DF</E> to make it highly improbable that the latter speeds will be inadvertently exceeded in flight. (b) The speed <E T="03">Vmo</E> must not exceed 0.8 <E T="03">V</E> <E T="24">D</E>/<E T="03">M</E> <E T="24">D</E> or 0.8 <E T="03">V</E> <E T="24">DF</E>/<E T="03">M</E> <E T="24">DF</E> unless flight demonstrations involving upsets as specified by the Administrator indicates a lower speed margin will not result in speeds exceeding <E T="03">V</E> <E T="24">D</E>/<E T="03">M</E> <E T="24">D</E> or <E T="03">V</E> <E T="24">DF</E>. Atmospheric variations, horizontal gusts, and equipment errors, and airframe production variations will be taken into account. 16. <E T="03">Minimum flight crew.</E> In addition to meeting the requirements of FAR 23.1523, the applicant must establish the minimum number and type of qualified flight crew personnel sufficient for safe operation of the airplane considering— (a) Each kind of operation for which the applicant desires approval; (b) The workload on each crewmember considering the following: (1) Flight path control. (2) Collision avoidance. (3) Navigation. (4) Communications. (5) Operation and monitoring of all essential aircraft systems. (6) Command decisions; and (c) The accessibility and ease of operation of necessary controls by the appropriate crewmember during all normal and emergency operations when at his flight station. 17. <E T="03">Airspeed indicator.</E> The airspeed indicator must meet the requirements of FAR 23.1545 except that, the airspeed notations and markings in terms of <E T="03">V</E> <E T="24">NO</E> and <E T="03">V</E> <E T="24">NE</E> must be replaced by the <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> notations. The airspeed indicator markings must be easily read and understood by the pilot. A placard adjacent to the airspeed indicator is an acceptable means of showing compliance with the requirements of FAR 23.1545(c). <HD SOURCE="HD1">Airplane Flight Manual</HD> 18. <E T="03">General.</E> The Airplane Flight Manual must be prepared in accordance with the requirements of FARs 23.1583 and 23.1587, and in addition the operating limitations and performance information set forth in sections 19 and 20 must be included. 19. <E T="03">Operating limitations.</E> The Airplane Flight Manual must include the following limitations— (a) <E T="03">Airspeed limitations.</E> (1) The maximum operating limit speed <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> and a statement that this speed limit may not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training; (2) If an airspeed limitation is based upon compressibility effects, a statement to this effect and information as to any symptoms, the probable behavior of the airplane, and the recommended recovery procedures; and (3) The airspeed limits, shown in terms of <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> instead of <E T="03">V</E> <E T="24">NO</E> and <E T="03">V</E> <E T="24">NE</E>. (b) <E T="03">Takeoff weight limitations.</E> The maximum takeoff weight for each airport elevation, ambient temperature, and available takeoff runway length within the range selected by the applicant. This weight may not exceed the weight at which: (1) The all-engine operating takeoff distance determined in accordance with section 5(d) or the accelerate-stop distance determined in accordance with section 5(c), which ever is greater, is equal to the available runway length; (2) The airplane complies with the one-engine-inoperative takeoff requirements specified in section 5(e); and (3) The airplane complies with the one-engine-inoperative en route climb requirements specified in section 6(b), assuming that a standard temperature lapse rate exists from the airport elevation to the altitude of 5,000 feet, except that the weight may not exceed that corresponding to a temperature of 41° F at 5,000 feet. 20. <E T="03">Performance information.</E> The Airplane Flight Manual must contain the performance information determined in accordance with the provisions of the performance requirements of this regulation. The information must include the following: (a) Sufficient information so that the take-off weight limits specified in section 19(b) can be determined for all temperatures and altitudes within the operation limitations selected by the applicant. (b) The conditions under which the performance information was obtained, including the airspeed at the 50-foot height used to determine landing distances. (c) The performance information (determined by extrapolation and computed for the range of weights between the maximum landing and takeoff weights) for— (1) Climb in the landing configuration; and (2) Landing distance. (d) Procedure established under section 4 of this regulation related to the limitations and information required by this section in the form of guidance material including any relevant limitations or information. (e) An explanation of significant or unusual flight or ground handling characteristics of the airplane. (f) Airspeeds, as indicated airspeeds, corresponding to those determined for takeoff in accordance with section 5(b). 21. <E T="03">Maximum operating altitudes.</E> The maximum operating altitude to which operation is permitted, as limited by flight, structural, powerplant, functional, or equipment characteristics, must be specified in the Airplane Flight Manual. 22. <E T="03">Stowage provision for Airplane Flight Manual.</E> Provision must be made for stowing the Airplane Flight Manual in a suitable <PRTPAGE P="159"/>fixed container which is readily accessible to the pilot. 23. <E T="03">Operating procedures.</E> Procedures for restarting turbine engines in flight (including the effects of altitude) must be set forth in the Airplane Flight Manual. <HD SOURCE="HD1">Airframe Requirements</HD> <HD SOURCE="HD1">flight loads</HD> 24. <E T="03">Engine torque.</E> (a) Each turbopropeller engine mount and its supporting structure must be designed for the torque effects of— (1) The conditions set forth in FAR 23.361(a). (2) The limit engine torque corresponding to takeoff power and propeller speed, multiplied by a factor accounting for propeller control system malfunction, including quick feathering action, simultaneously with 1 <E T="03">g</E> level flight loads. In the absence of a rational analysis, a factor of 1.6 must be used. (b) The limit torque is obtained by multiplying the mean torque by a factor of 1.25. 25. <E T="03">Turbine engine gyroscopic loads.</E> Each turbopropeller engine mount and its supporting structure must be designed for the gyroscopic loads that result, with the engines at maximum continuous r.p.m., under either— (a) The conditions prescribed in FARs 23.351 and 23.423; or (b) All possible combinations of the following: (1) A yaw velocity of 2.5 radius per second. (2) A pitch velocity of 1.0 radians per second. (3) A normal load factor of 2.5. (4) Maximum continuous thrust. 26. <E T="03">Unsymmetrical loads due to engine failure.</E> (a) Turbopropeller powered airplanes must be designed for the unsymmetrical loads resulting from the failure of the critical engine including the following conditions in combination with a single malfunction of the propeller drag limiting system, considering the probable pilot corrective action on the flight controls. (1) At speeds between <E T="03">V</E> <E T="24">MC</E> and V<E T="24">D</E>, the loads resulting from power failure because of fuel flow interruption are considered to be limit loads. (2) At speeds between <E T="03">V</E> <E T="24">MC</E> and <E T="03">V</E> <E T="24">C</E>, the loads resulting from the disconnection of the engine compressor from the turbine or from loss of the turbine blades are considered to be ultimate loads. (3) The time history of the thrust decay and drag buildup occurring as a result of the prescribed engine failures must be substantiated by test or other data applicable to the particular engine-propeller combination. (4) The timing and magnitude of the probable pilot corrective action must be conservatively estimated, considering the characteristics of the particular engine-propeller-airplane combination. (b) Pilot corrective action may be assumed to be initiated at the time maximum yawing velocity is reached, but not earlier than two seconds after the engine failure. The magnitude of the corrective action may be based on the control forces specified in FAR 23.397 except that lower forces may be assumed where it is shown by analysis or test that these forces can control the yaw and roll resulting from the prescribed engine failure conditions. <HD SOURCE="HD1">Ground Loads</HD> 27. <E T="03">Dual wheel landing gear units.</E> Each dual wheel landing gear unit and its supporting structure must be shown to comply with the following: (a) <E T="03">Pivoting.</E> The airplane must be assumed to pivot about one side of the main gear with the brakes on that side locked. The limit vertical load factor must be 1.0 and the coefficient of friction 0.8. This condition need apply only to the main gear and its supporting structure. (b) <E T="03">Unequal tire inflation.</E> A 60-40 percent distribution of the loads established in accordance with FAR 23.471 through FAR 23.483 must be applied to the dual wheels. (c) <E T="03">Flat tire.</E> (1) Sixty percent of the loads specified in FAR 23.471 through FAR 23.483 must be applied to either wheel in a unit. (2) Sixty percent of the limit drag and side loads and 100 percent of the limit vertical load established in accordance with FARs 23.493 and 23.485 must be applied to either wheel in a unit except that the vertical load need not exceed the maximum vertical load in paragraph (c)(1) of this section. <HD SOURCE="HD1">Fatigue Evaluation</HD> 28. <E T="03">Fatigue evaluation of wing and associated structure.</E> Unless it is shown that the structure, operating stress levels, materials, and expected use are comparable from a fatigue standpoint to a similar design which has had substantial satisfactory service experience, the strength, detail design, and the fabrication of those parts of the wing, wing carrythrough, and attaching structure whose failure would be catastrophic must be evaluated under either— (a) A fatigue strength investigation in which the structure is shown by analysis, tests, or both to be able to withstand the repeated loads of variable magnitude expected in service; or (b) A fail-safe strength investigation in which it is shown by analysis, tests, or both that catastrophic failure of the structure is not probable after fatigue, or obvious partial failure, of a principal structural element, and that the remaining structure is able to withstand a static ultimate load factor of 75 percent of the critical limit load factor at <PRTPAGE P="160"/> <E T="03">V</E> <E T="24">c</E>. These loads must be multiplied by a factor of 1.15 unless the dynamic effects of failure under static load are otherwise considered. <HD SOURCE="HD1">Design and Construction</HD> 29. <E T="03">Flutter.</E> For Multiengine turbopropeller powered airplanes, a dynamic evaluation must be made and must include— (a) The significant elastic, inertia, and aerodynamic forces associated with the rotations and displacements of the plane of the propeller; and (b) Engine-propeller-nacelle stiffness and damping variations appropriate to the particular configuration. <HD SOURCE="HD1">Landing Gear</HD> 30. <E T="03">Flap operated landing gear warning device.</E> Airplanes having retractable landing gear and wing flaps must be equipped with a warning device that functions continuously when the wing flaps are extended to a flap position that activates the warning device to give adequate warning before landing, using normal landing procedures, if the landing gear is not fully extended and locked. There may not be a manual shut off for this warning device. The flap position sensing unit may be installed at any suitable location. The system for this device may use any part of the system (including the aural warning device) provided for other landing gear warning devices. <HD SOURCE="HD1">Personnel and Cargo Accommodations</HD> 31. <E T="03">Cargo and baggage compartments.</E> Cargo and baggage compartments must be designed to meet the requirements of FAR 23.787 (a) and (b), and in addition means must be provided to protect passengers from injury by the contents of any cargo or baggage compartment when the ultimate forward inertia force is 9<E T="03">g.</E> 32. <E T="03">Doors and exits.</E> The airplane must meet the requirements of FAR 23.783 and FAR 23.807 (a)(3), (b), and (c), and in addition: (a) There must be a means to lock and safeguard each external door and exit against opening in flight either inadvertently by persons, or as a result of mechanical failure. Each external door must be operable from both the inside and the outside. (b) There must be means for direct visual inspection of the locking mechanism by crewmembers to determine whether external doors and exits, for which the initial opening movement is outward, are fully locked. In addition, there must be a visual means to signal to crewmembers when normally used external doors are closed and fully locked. (c) The passenger entrance door must qualify as a floor level emergency exit. Each additional required emergency exit except floor level exits must be located over the wing or must be provided with acceptable means to assist the occupants in descending to the ground. In addition to the passenger entrance door: (1) For a total seating capacity of 15 or less, an emergency exit as defined in FAR 23.807(b) is required on each side of the cabin. (2) For a total seating capacity of 16 through 23, three emergency exits as defined in 23.807(b) are required with one on the same side as the door and two on the side opposite the door. (d) An evacuation demonstration must be conducted utilizing the maximum number of occupants for which certification is desired. It must be conducted under simulated night conditions utilizing only the emergency exits on the most critical side of the aircraft. The participants must be representative of average airline passengers with no prior practice or rehearsal for the demonstration. Evacuation must be completed within 90 seconds. (e) Each emergency exit must be marked with the word “Exit” by a sign which has white letters 1 inch high on a red background 2 inches high, be self-illuminated or independently internally electrically illuminated, and have a minimum luminescence (brightness) of at least 160 microlamberts. The colors may be reversed if the passenger compartment illumination is essentially the same. (f) Access to window type emergency exits must not be obstructed by seats or seat backs. (g) The width of the main passenger aisle at any point between seats must equal or exceed the values in the following table. <GPOTABLE CDEF="s50,r40,r40" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Total seating capacity</CHED> <CHED H="1">Minimum main passenger aisle width</CHED> <CHED H="2">Less than 25 inches from floor</CHED> <CHED H="2">25 inches and more from floor</CHED> </BOXHD> <ROW> <ENT I="01">10 through 23</ENT> <ENT>9 inches</ENT> <ENT>15 inches.</ENT> </ROW> </GPOTABLE> <HD SOURCE="HD1">Miscellaneous</HD> 33. <E T="03">Lightning strike protection.</E> Parts that are electrically insulated from the basic airframe must be connected to it through lightning arrestors unless a lightning strike on the insulated part— (a) Is improbable because of shielding by other parts; or (b) Is not hazardous. 34. <E T="03">Ice protection.</E> If certification with ice protection provisions is desired, compliance with the following requirements must be shown: (a) The recommended procedures for the use of the ice protection equipment must be set forth in the Airplane Flight Manual. (b) An analysis must be performed to establish, on the basis of the airplane's operational needs, the adequacy of the ice protection system for the various components of <PRTPAGE P="161"/>the airplane. In addition, tests of the ice protection system must be conducted to demonstrate that the airplane is capable of operating safely in continuous maximum and intermittent maximum icing conditions as described in FAR 25, appendix C. (c) Compliance with all or portions of this section may be accomplished by reference, where applicable because of similarity of the designs, to analysis and tests performed by the applicant for a type certificated model. 35. <E T="03">Maintenance information.</E> The applicant must make available to the owner at the time of delivery of the airplane the information he considers essential for the proper maintenance of the airplane. That information must include the following: (a) Description of systems, including electrical, hydraulic, and fuel controls. (b) Lubrication instructions setting forth the frequency and the lubricants and fluids which are to be used in the various systems. (c) Pressures and electrical loads applicable to the various systems. (d) Tolerances and adjustments necessary for proper functioning. (e) Methods of leveling, raising, and towing. (f) Methods of balancing control surfaces. (g) Identification of primary and secondary structures. (h) Frequency and extent of inspections necessary to the proper operation of the airplane. (i) Special repair methods applicable to the airplane. (j) Special inspection techniques, including those that require X-ray, ultrasonic, and magnetic particle inspection. (k) List of special tools. <HD SOURCE="HD1">Propulsion</HD> <HD SOURCE="HD1">general</HD> 36. <E T="03">Vibration characteristics.</E> For turbopropeller powered airplanes, the engine installation must not result in vibration characteristics of the engine exceeding those established during the type certification of the engine. 37. <E T="03">In-flight restarting of engine.</E> If the engine on turbopropeller powered airplanes cannot be restarted at the maximum cruise altitude, a determination must be made of the altitude below which restarts can be consistently accomplished. Restart information must be provided in the Airplane Flight Manual. 38. <E T="03">Engines</E>—(a) <E T="03">For turbopropeller powered airplanes.</E> The engine installation must comply with the following requirements: (1) <E T="03">Engine isolation.</E> The powerplants must be arranged and isolated from each other to allow operation, in at least one configuration, so that the failure or malfunction of any engine, or of any system that can affect the engine, will not— (i) Prevent the continued safe operation of the remaining engines; or (ii) Require immediate action by any crewmember for continued safe operation. (2) <E T="03">Control of engine rotation.</E> There must be a means to individually stop and restart the rotation of any engine in flight except that engine rotation need not be stopped if continued rotation could not jeopardize the safety of the airplane. Each component of the stopping and restarting system on the engine side of the firewall, and that might be exposed to fire, must be at least fire resistant. If hydraulic propeller feathering systems are used for this purpose, the feathering lines must be at least fire resistant under the operating conditions that may be expected to exist during feathering. (3) <E T="03">Engine speed and gas temperature control devices.</E> The powerplant systems associated with engine control devices, systems, and instrumentation must provide reasonable assurance that those engine operating limitations that adversely affect turbine rotor structural integrity will not be exceeded in service. (b) <E T="03">For reciprocating-engine powered airplanes.</E> To provide engine isolation, the powerplants must be arranged and isolated from each other to allow operation, in at least one configuration, so that the failure or malfunction of any engine, or of any system that can affect that engine, will not— (1) Prevent the continued safe operation of the remaining engines; or (2) Require immediate action by any crewmember for continued safe operation. 39. <E T="03">Turbopropeller reversing systems.</E> (a) Turbopropeller reversing systems intended for ground operation must be designed so that no single failure or malfunction of the system will result in unwanted reverse thrust under any expected operating condition. Failure of structural elements need not be considered if the probability of this kind of failure is extremely remote. (b) Turbopropeller reversing systems intended for in-flight use must be designed so that no unsafe condition will result during normal operation of the system, or from any failure (or reasonably likely combination of failures) of the reversing system, under any anticipated condition of operation of the airplane. Failure of structural elements need not be considered if the probability of this kind of failure is extremely remote. (c) Compliance with this section may be shown by failure analysis, testing, or both for propeller systems that allow propeller blades to move from the flight low-pitch position to a position that is substantially less than that at the normal flight low-pitch stop position. The analysis may include or be supported by the analysis made to show compliance with the type certification of the propeller and associated installation components. Credit will be given for pertinent <PRTPAGE P="162"/>analysis and testing completed by the engine and propeller manufacturers. 40. <E T="03">Turbopropeller drag-limiting systems.</E> Turbopropeller drag-limiting systems must be designed so that no single failure or malfunction of any of the systems during normal or emergency operation results in propeller drag in excess of that for which the airplane was designed. Failure of structural elements of the drag-limiting systems need not be considered if the probability of this kind of failure is extremely remote. 41. <E T="03">Turbine engine powerplant operating characteristics.</E> For turbopropeller powered airplanes, the turbine engine powerplant operating characteristics must be investigated in flight to determine that no adverse characteristics (such as stall, surge, or flameout) are present to a hazardous degree, during normal and emergency operation within the range of operating limitations of the airplane and of the engine. 42. <E T="03">Fuel flow.</E> (a) For turbopropeller powered airplanes— (1) The fuel system must provide for continuous supply of fuel to the engines for normal operation without interruption due to depletion of fuel in any tank other than the main tank; and (2) The fuel flow rate for turbopropeller engine fuel pump systems must not be less than 125 percent of the fuel flow required to develop the standard sea level atmospheric conditions takeoff power selected and included as an operating limitation in the Airplane Flight Manual. (b) For reciprocating engine powered airplanes, it is acceptable for the fuel flow rate for each pump system (main and reserve supply) to be 125 percent of the takeoff fuel consumption of the engine. <HD SOURCE="HD1">Fuel System Components</HD> 43. <E T="03">Fuel pumps.</E> For turbopropeller powered airplanes, a reliable and independent power source must be provided for each pump used with turbine engines which do not have provisions for mechanically driving the main pumps. It must be demonstrated that the pump installations provide a reliability and durability equivalent to that provided by FAR 23.991(a). 44. <E T="03">Fuel strainer or filter.</E> For turbopropeller powered airplanes, the following apply: (a) There must be a fuel strainer or filter between the tank outlet and the fuel metering device of the engine. In addition, the fuel strainer or filter must be— (1) Between the tank outlet and the engine-driven positive displacement pump inlet, if there is an engine-driven positive displacement pump; (2) Accessible for drainage and cleaning and, for the strainer screen, easily removable; and (3) Mounted so that its weight is not supported by the connecting lines or by the inlet or outlet connections of the strainer or filter itself. (b) Unless there are means in the fuel system to prevent the accumulation of ice on the filter, there must be means to automatically maintain the fuel flow if ice-clogging of the filter occurs; and (c) The fuel strainer or filter must be of adequate capacity (with respect to operating limitations established to insure proper service) and of appropriate mesh to insure proper engine operation, with the fuel contaminated to a degree (with respect to particle size and density) that can be reasonably expected in service. The degree of fuel filtering may not be less than that established for the engine type certification. 45. <E T="03">Lightning strike protection.</E> Protection must be provided against the ignition of flammable vapors in the fuel vent system due to lightning strikes. <HD SOURCE="HD1">Cooling</HD> 46. <E T="03">Cooling test procedures for turbopropeller powered airplanes.</E> (a) Turbopropeller powered airplanes must be shown to comply with the requirements of FAR 23.1041 during takeoff, climb en route, and landing stages of flight that correspond to the applicable performance requirements. The cooling test must be conducted with the airplane in the configuration and operating under the conditions that are critical relative to cooling during each stage of flight. For the cooling tests a temperature is “stabilized” when its rate of change is less than 2° F. per minute. (b) Temperatures must be stabilized under the conditions from which entry is made into each stage of flight being investigated unless the entry condition is not one during which component and engine fluid temperatures would stabilize, in which case, operation through the full entry condition must be conducted before entry into the stage of flight being investigated in order to allow temperatures to reach their natural levels at the time of entry. The takeoff cooling test must be preceded by a period during which the powerplant component and engine fluid temperatures are stabilized with the engines at ground idle. (c) Cooling tests for each stage of flight must be continued until— (1) The component and engine fluid temperatures stabilize; (2) The stage of flight is completed; or (3) An operating limitation is reached. <HD SOURCE="HD1">Induction System</HD> 47. <E T="03">Air induction.</E> For turbopropeller powered airplanes— (a) There must be means to prevent hazardous quantities of fuel leakage or overflow from drains, vents, or other components of flammable fluid systems from entering the engine intake system; and<PRTPAGE P="163"/> (b) The air inlet ducts must be located or protected so as to minimize the ingestion of foreign matter during takeoff, landing, and taxiing. 48. <E T="03">Induction system icing protection.</E> For turbopropeller powered airplanes, each turbine engine must be able to operate throughout its flight power range without adverse effect on engine operation or serious loss of power or thrust, under the icing conditions specified in appendix C of FAR 25. In addition, there must be means to indicate to appropriate flight crewmembers the functioning of the powerplant ice protection system. 49. <E T="03">Turbine engine bleed air systems.</E> Turbine engine bleed air systems of turbopropeller powered airplanes must be investigated to determine— (a) That no hazard to the airplane will result if a duct rupture occurs. This condition must consider that a failure of the duct can occur anywhere between the engine port and the airplane bleed service; and (b) That if the bleed air system is used for direct cabin pressurization, it is not possible for hazardous contamination of the cabin air system to occur in event of lubrication system failure. <HD SOURCE="HD1">Exhaust System</HD> 50. <E T="03">Exhaust system drains.</E> Turbopropeller engine exhaust systems having low spots or pockets must incorporate drains at such locations. These drains must discharge clear of the airplane in normal and ground attitudes to prevent the accumulation of fuel after the failure of an attempted engine start. <HD SOURCE="HD1">Powerplant Controls and Accessories</HD> 51. <E T="03">Engine controls.</E> If throttles or power levers for turbopropeller powered airplanes are such that any position of these controls will reduce the fuel flow to the engine(s) below that necessary for satisfactory and safe idle operation of the engine while the airplane is in flight, a means must be provided to prevent inadvertent movement of the control into this position. The means provided must incorporate a positive lock or stop at this idle position and must require a separate and distinct operation by the crew to displace the control from the normal engine operating range. 52. <E T="03">Reverse thrust controls.</E> For turbopropeller powered airplanes, the propeller reverse thrust controls must have a means to prevent their inadvertent operation. The means must have a positive lock or stop at the idle position and must require a separate and distinct operation by the crew to displace the control from the flight regime. 53. <E T="03">Engine ignition systems.</E> Each turbopropeller airplane ignition system must be considered an essential electrical load. 54. <E T="03">Powerplant accessories.</E> The powerplant accessories must meet the requirements of FAR 23.1163, and if the continued rotation of any accessory remotely driven by the engine is hazardous when malfunctioning occurs, there must be means to prevent rotation without interfering with the continued operation of the engine. <HD SOURCE="HD1">Powerplant Fire Protection</HD> 55. <E T="03">Fire detector system.</E> For turbopropeller powered airplanes, the following apply: (a) There must be a means that ensures prompt detection of fire in the engine compartment. An overtemperature switch in each engine cooling air exit is an acceptable method of meeting this requirement. (b) Each fire detector must be constructed and installed to withstand the vibration, inertia, and other loads to which it may be subjected in operation. (c) No fire detector may be affected by any oil, water, other fluids, or fumes that might be present. (d) There must be means to allow the flight crew to check, in flight, the functioning of each fire detector electric circuit. (e) Wiring and other components of each fire detector system in a fire zone must be at least fire resistant. 56. <E T="03">Fire protection, cowling and nacelle skin.</E> For reciprocating engine powered airplanes, the engine cowling must be designed and constructed so that no fire originating in the engine compartment can enter, either through openings or by burn through, any other region where it would create additional hazards. 57. <E T="03">Flammable fluid fire protection.</E> If flammable fluids or vapors might be liberated by the leakage of fluid systems in areas other than engine compartments, there must be means to— (a) Prevent the ignition of those fluids or vapors by any other equipment; or (b) Control any fire resulting from that ignition. <HD SOURCE="HD1">Equipment</HD> 58. <E T="03">Powerplant instruments.</E> (a) The following are required for turbopropeller airplanes: (1) The instruments required by FAR 23.1305 (a)(1) through (4), (b)(2) and (4). (2) A gas temperature indicator for each engine. (3) Free air temperature indicator. (4) A fuel flowmeter indicator for each engine. (5) Oil pressure warning means for each engine. (6) A torque indicator or adequate means for indicating power output for each engine. (7) Fire warning indicator for each engine. (8) A means to indicate when the propeller blade angle is below the low-pitch position corresponding to idle operation in flight. (9) A means to indicate the functioning of the ice protection system for each engine.<PRTPAGE P="164"/> (b) For turbopropeller powered airplanes, the turbopropeller blade position indicator must begin indicating when the blade has moved below the flight low-pitch position. (c) The following instruments are required for reciprocating-engine powered airplanes: (1) The instruments required by FAR 23.1305. (2) A cylinder head temperature indicator for each engine. (3) A manifold pressure indicator for each engine. <HD SOURCE="HD1">Systems and Equipments</HD> <HD SOURCE="HD1">general</HD> 59. <E T="03">Function and installation.</E> The systems and equipment of the airplane must meet the requirements of FAR 23.1301, and the following: (a) Each item of additional installed equipment must— (1) Be of a kind and design appropriate to its intended function; (2) Be labeled as to its identification, function, or operating limitations, or any applicable combination of these factors, unless misuse or inadvertent actuation cannot create a hazard; (3) Be installed according to limitations specified for that equipment; and (4) Function properly when installed. (b) Systems and installations must be designed to safeguard against hazards to the aircraft in the event of their malfunction or failure. (c) Where an installation, the functioning of which is necessary in showing compliance with the applicable requirements, requires a power supply, such installation must be considered an essential load on the power supply, and the power sources and the distribution system must be capable of supplying the following power loads in probable operation combinations and for probable durations: (1) All essential loads after failure of any prime mover, power converter, or energy storage device. (2) All essential loads after failure of any one engine on two-engine airplanes. (3) In determining the probable operating combinations and durations of essential loads for the power failure conditions described in subparagraphs (1) and (2) of this paragraph, it is permissible to assume that the power loads are reduced in accordance with a monitoring procedure which is consistent with safety in the types of operations authorized. 60. <E T="03">Ventilation.</E> The ventilation system of the airplane must meet the requirements of FAR 23.831, and in addition, for pressurized aircraft the ventilating air in flight crew and passenger compartments must be free of harmful or hazardous concentrations of gases and vapors in normal operation and in the event of reasonably probable failures or malfunctioning of the ventilating, heating, pressurization, or other systems, and equipment. If accumulation of hazardous quantities of smoke in the cockpit area is reasonably probable, smoke evacuation must be readily accomplished. <HD SOURCE="HD1">Electrical Systems and Equipment</HD> 61. <E T="03">General.</E> The electrical systems and equipment of the airplane must meet the requirements of FAR 23.1351, and the following: (a) <E T="03">Electrical system capacity.</E> The required generating capacity, and number and kinds of power sources must— (1) Be determined by an electrical load analysis, and (2) Meet the requirements of FAR 23.1301. (b) <E T="03">Generating system.</E> The generating system includes electrical power sources, main power busses, transmission cables, and associated control, regulation, and protective devices. It must be designed so that— (1) The system voltage and frequency (as applicable) at the terminals of all essential load equipment can be maintained within the limits for which the equipment is designed, during any probable operating conditions; (2) System transients due to switching, fault clearing, or other causes do not make essential loads inoperative, and do not cause a smoke or fire hazard; (3) There are means, accessible in flight to appropriate crewmembers, for the individual and collective disconnection of the electrical power sources from the system; and (4) There are means to indicate to appropriate crewmembers the generating system quantities essential for the safe operation of the system, including the voltage and current supplied by each generator. 62. <E T="03">Electrical equipment and installation.</E> Electrical equipment controls, and wiring must be installed so that operation of any one unit or system of units will not adversely affect the simultaneous operation of to the safe operation. 63. <E T="03">Distribution system.</E> (a) For the purpose of complying with this section, the distribution system includes the distribution busses, their associated feeders and each control and protective device. (b) Each system must be designed so that essential load circuits can be supplied in the event of reasonably probable faults or open circuits, including faults in heavy current carrying cables. (c) If two independent sources of electrical power for particular equipment or systems are required by this regulation, their electrical energy supply must be insured by means such as duplicate electrical equipment, throwover switching, or multichannel or loop circuits separately routed. 64. <E T="03">Circuit protective devices.</E> The circuit protective devices for the electrical circuits of the airplane must meet the requirements <PRTPAGE P="165"/>of FAR 23.1357, and in addition circuits for loads which are essential to safe operation must have individual and exclusive circuit protection. </EXTRACT> <CITA>[Doc. No. 8070, 34 FR 189, Jan. 7, 1969, as amended by SFAR 23-1, 34 FR 20176, Dec. 24, 1969; 35 FR 1102, Jan. 28, 1970]</CITA> <EAR>Pt. 23, SFAR No. 41</EAR> <SUBJGRP> <HD SOURCE="HED">SFAR No. <E T="01">41</E> </HD> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For the text of SFAR No. 41, see part 21 of this chapter. </EDNOTE> </SUBJGRP> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECTION> <SECTNO>§ 23.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This part prescribes airworthiness standards for the issue of type certificates, and changes to those certificates, for airplanes in the normal, utility, acrobatic, and commuter categories. (b) Each person who applies under Part 21 for such a certificate or change must show compliance with the applicable requirements of this part. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-34, 52 FR 1825, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.2</SECTNO> <SUBJECT>Special retroactive requirements.</SUBJECT> (a) Notwithstanding §§ 21.17 and 21.101 of this chapter and irrespective of the type certification basis, each normal, utility, and acrobatic category airplane having a passenger seating configuration, excluding pilot seats, of nine or less, manufactured after December 12, 1986, or any such foreign airplane for entry into the United States must provide a safety belt and shoulder harness for each forward- or aft-facing seat which will protect the occupant from serious head injury when subjected to the inertia loads resulting from the ultimate static load factors prescribed in § 23.561(b)(2) of this part, or which will provide the occupant protection specified in § 23.562 of this part when that section is applicable to the airplane. For other seat orientations, the seat/restraint system must be designed to provide a level of occupant protection equivalent to that provided for forward- or aft-facing seats with a safety belt and shoulder harness installed. (b) Each shoulder harness installed at a flight crewmember station, as required by this section, must allow the crewmember, when seated with the safety belt and shoulder harness fastened, to perform all functions necessary for flight operations. (c) For the purpose of this section, the date of manufacture is: (1) The date the inspection acceptance records, or equivalent, reflect that the airplane is complete and meets the FAA approved type design data; or (2) In the case of a foreign manufactured airplane, the date the foreign civil airworthiness authority certifies the airplane is complete and issues an original standard airworthiness certificate, or the equivalent in that country. <CITA>[Amdt. 23-36, 53 FR 30812, Aug. 15, 1988]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.3</SECTNO> <SUBJECT>Airplane categories.</SUBJECT> (a) The normal category is limited to airplanes that have a seating configuration, excluding pilot seats, of nine or less, a maximum certificated takeoff weight of 12,500 pounds or less, and intended for nonacrobatic operation. Nonacrobatic operation includes: (1) Any maneuver incident to normal flying; (2) Stalls (except whip stalls); and (3) Lazy eights, chandelles, and steep turns, in which the angle of bank is not more than 60 degrees. (b) The utility category is limited to airplanes that have a seating configuration, excluding pilot seats, of nine or less, a maximum certificated takeoff weight of 12,500 pounds or less, and intended for limited acrobatic operation. Airplanes certificated in the utility category may be used in any of the operations covered under paragraph (a) of this section and in limited acrobatic operations. Limited acrobatic operation includes: (1) Spins (if approved for the particular type of airplane); and (2) Lazy eights, chandelles, and steep turns, or similar maneuvers, in which the angle of bank is more than 60 degrees but not more than 90 degrees. (c) The acrobatic category is limited to airplanes that have a seating configuration, excluding pilot seats, of nine or less, a maximum certificated takeoff weight of 12,500 pounds or less, <PRTPAGE P="166"/>and intended for use without restrictions, other than those shown to be necessary as a result of required flight tests. (d) The commuter category is limited to propeller-driven, multiengine airplanes that have a seating configuration, excluding pilot seats, of 19 or less, and a maximum certificated takeoff weight of 19,000 pounds or less. The commuter category operation is limited to any maneuver incident to normal flying, stalls (except whip stalls), and steep turns, in which the angle of bank is not more than 60 degrees. (e) Except for commuter category, airplanes may be type certificated in more than one category if the requirements of each requested category are met. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-4, 32 FR 5934, Apr. 14, 1967; Amdt. 23-34, 52 FR 1825, Jan. 15, 1987; 52 FR 34745, Sept. 14, 1987; Amdt. 23-50, 61 FR 5183, Feb. 9, 1996]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Flight</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTION> <SECTNO>§ 23.21</SECTNO> <SUBJECT>Proof of compliance.</SUBJECT> (a) Each requirement of this subpart must be met at each appropriate combination of weight and center of gravity within the range of loading conditions for which certification is requested. This must be shown— (1) By tests upon an airplane of the type for which certification is requested, or by calculations based on, and equal in accuracy to, the results of testing; and (2) By systematic investigation of each probable combination of weight and center of gravity, if compliance cannot be reasonably inferred from combinations investigated. (b) The following general tolerances are allowed during flight testing. However, greater tolerances may be allowed in particular tests: <GPOTABLE CDEF="s80,r50" COLS="2" OPTS="L2"> <BOXHD> <CHED H="1">Item</CHED> <CHED H="1">Tolerance</CHED> </BOXHD> <ROW> <ENT I="01">Weight</ENT> <ENT>+5%, -10%.</ENT> </ROW> <ROW> <ENT I="01">Critical items affected by weight</ENT> <ENT>+5%, -1%.</ENT> </ROW> <ROW> <ENT I="01">C.G</ENT> <ENT> <E T="21">±</E>7% total travel.</ENT> </ROW> </GPOTABLE> </SECTION> <SECTION> <SECTNO>§ 23.23</SECTNO> <SUBJECT>Load distribution limits.</SUBJECT> (a) Ranges of weights and centers of gravity within which the airplane may be safely operated must be established. If a weight and center of gravity combination is allowable only within certain lateral load distribution limits that could be inadvertently exceeded, these limits must be established for the corresponding weight and center of gravity combinations. (b) The load distribution limits may not exceed any of the following: (1) The selected limits; (2) The limits at which the structure is proven; or (3) The limits at which compliance with each applicable flight requirement of this subpart is shown. <CITA>[Doc. No. 26269, 58 FR 42156, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.25</SECTNO> <SUBJECT>Weight limits.</SUBJECT> (a) <E T="03">Maximum weight.</E> The maximum weight is the highest weight at which compliance with each applicable requirement of this part (other than those complied with at the design landing weight) is shown. The maximum weight must be established so that it is— (1) Not more than the least of— (i) The highest weight selected by the applicant; or (ii) The design maximum weight, which is the highest weight at which compliance with each applicable structural loading condition of this part (other than those complied with at the design landing weight) is shown; or (iii) The highest weight at which compliance with each applicable flight requirement is shown, and (2) Not less than the weight with— (i) Each seat occupied, assuming a weight of 170 pounds for each occupant for normal and commuter category airplanes, and 190 pounds for utility and acrobatic category airplanes, except that seats other than pilot seats may be placarded for a lesser weight; and (A) Oil at full capacity, and (B) At least enough fuel for maximum continuous power operation of at least 30 minutes for day-VFR approved airplanes and at least 45 minutes for night-VFR and IFR approved airplanes; or<PRTPAGE P="167"/> (ii) The required minimum crew, and fuel and oil to full tank capacity. (b) <E T="03">Minimum weight.</E> The minimum weight (the lowest weight at which compliance with each applicable requirement of this part is shown) must be established so that it is not more than the sum of— (1) The empty weight determined under § 23.29; (2) The weight of the required minimum crew (assuming a weight of 170 pounds for each crewmember); and (3) The weight of— (i) For turbojet powered airplanes, 5 percent of the total fuel capacity of that particular fuel tank arrangement under investigation, and (ii) For other airplanes, the fuel necessary for one-half hour of operation at maximum continuous power. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13086, Aug. 13, 1969; Amdt. 23-21, 43 FR 2317, Jan. 16, 1978; Amdt. 23-34, 52 FR 1825, Jan. 15, 1987; Amdt. 23-45, 58 FR 42156, Aug. 6, 1993; Amdt. 23-50, 61 FR 5183, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.29</SECTNO> <SUBJECT>Empty weight and corresponding center of gravity.</SUBJECT> (a) The empty weight and corresponding center of gravity must be determined by weighing the airplane with— (1) Fixed ballast; (2) Unusable fuel determined under § 23.959; and (3) Full operating fluids, including— (i) Oil; (ii) Hydraulic fluid; and (iii) Other fluids required for normal operation of airplane systems, except potable water, lavatory precharge water, and water intended for injection in the engines. (b) The condition of the airplane at the time of determining empty weight must be one that is well defined and can be easily repeated. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-21, 43 FR 2317, Jan. 16, 1978]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.31</SECTNO> <SUBJECT>Removable ballast.</SUBJECT> Removable ballast may be used in showing compliance with the flight requirements of this subpart, if— (a) The place for carrying ballast is properly designed and installed, and is marked under § 23.1557; and (b) Instructions are included in the airplane flight manual, approved manual material, or markings and placards, for the proper placement of the removable ballast under each loading condition for which removable ballast is necessary. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-13, 37 FR 20023, Sept. 23, 1972]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.33</SECTNO> <SUBJECT>Propeller speed and pitch limits.</SUBJECT> (a) <E T="03">General.</E> The propeller speed and pitch must be limited to values that will assure safe operation under normal operating conditions. (b) <E T="03">Propellers not controllable in flight.</E> For each propeller whose pitch cannot be controlled in flight— (1) During takeoff and initial climb at the all engine(s) operating climb speed specified in § 23.65, the propeller must limit the engine r.p.m., at full throttle or at maximum allowable takeoff manifold pressure, to a speed not greater than the maximum allowable takeoff r.p.m.; and (2) During a closed throttle glide, at V<E T="52">NE</E>, the propeller may not cause an engine speed above 110 percent of maximum continuous speed. (c) <E T="03">Controllable pitch propellers without constant speed controls.</E> Each propeller that can be controlled in flight, but that does not have constant speed controls, must have a means to limit the pitch range so that— (1) The lowest possible pitch allows compliance with paragraph (b)(1) of this section; and (2) The highest possible pitch allows compliance with paragraph (b)(2) of this section. (d) <E T="03">Controllable pitch propellers with constant speed controls.</E> Each controllable pitch propeller with constant speed controls must have— (1) With the governor in operation, a means at the governor to limit the maximum engine speed to the maximum allowable takeoff r.p.m.; and (2) With the governor inoperative, the propeller blades at the lowest possible pitch, with takeoff power, the airplane stationary, and no wind, either—<PRTPAGE P="168"/> (i) A means to limit the maximum engine speed to 103 percent of the maximum allowable takeoff r.p.m., or (ii) For an engine with an approved overspeed, a means to limit the maximum engine and propeller speed to not more than the maximum approved overspeed. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42156, Aug. 6, 1993; Amdt. 23-50, 61 FR 5183, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Performance</HD> <SECTION> <SECTNO>§ 23.45</SECTNO> <SUBJECT>General.</SUBJECT> (a) Unless otherwise prescribed, the performance requirements of this part must be met for— (1) Still air and standard atmosphere; and (2) Ambient atmospheric conditions, for commuter category airplanes, for reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and for turbine engine-powered airplanes. (b) Performance data must be determined over not less than the following ranges of conditions— (1) Airport altitudes from sea level to 10,000 feet; and (2) For reciprocating engine-powered airplanes of 6,000 pounds, or less, maximum weight, temperature from standard to 30 °C above standard; or (3) For reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight and turbine engine-powered airplanes, temperature from standard to 30 °C above standard, or the maximum ambient atmospheric temperature at which compliance with the cooling provisions of § 23.1041 to § 23.1047 is shown, if lower. (c) Performance data must be determined with the cowl flaps or other means for controlling the engine cooling air supply in the position used in the cooling tests required by § 23.1041 to § 23.1047. (d) The available propulsive thrust must correspond to engine power, not exceeding the approved power, less— (1) Installation losses; and (2) The power absorbed by the accessories and services appropriate to the particular ambient atmospheric conditions and the particular flight condition. (e) The performance, as affected by engine power or thrust, must be based on a relative humidity: (1) Of 80 percent at and below standard temperature; and (2) From 80 percent, at the standard temperature, varying linearly down to 34 percent at the standard temperature plus 50 °F. (f) Unless otherwise prescribed, in determining the takeoff and landing distances, changes in the airplane's configuration, speed, and power must be made in accordance with procedures established by the applicant for operation in service. These procedures must be able to be executed consistently by pilots of average skill in atmospheric conditions reasonably expected to be encountered in service. (g) The following, as applicable, must be determined on a smooth, dry, hard-surfaced runway— (1) Takeoff distance of § 23.53(b); (2) Accelerate-stop distance of § 23.55; (3) Takeoff distance and takeoff run of § 23.59; and (4) Landing distance of § 23.75. <NOTE> <HD SOURCE="HED">Note:</HD> The effect on these distances of operation on other types of surfaces (for example, grass, gravel) when dry, may be determined or derived and these surfaces listed in the Airplane Flight Manual in accordance with § 23.1583(p). </NOTE> (h) For commuter category airplanes, the following also apply: (1) Unless otherwise prescribed, the applicant must select the takeoff, enroute, approach, and landing configurations for the airplane. (2) The airplane configuration may vary with weight, altitude, and temperature, to the extent that they are compatible with the operating procedures required by paragraph (h)(3) of this section. (3) Unless otherwise prescribed, in determining the critical-engine-inoperative takeoff performance, takeoff flight path, and accelerate-stop distance, changes in the airplane's configuration, speed, and power must be made in accordance with procedures established by the applicant for operation in service. (4) Procedures for the execution of discontinued approaches and balked landings associated with the conditions prescribed in § 23.67(c)(4) and § 23.77(c) must be established.<PRTPAGE P="169"/> (5) The procedures established under paragraphs (h)(3) and (h)(4) of this section must— (i) Be able to be consistently executed by a crew of average skill in atmospheric conditions reasonably expected to be encountered in service; (ii) Use methods or devices that are safe and reliable; and (iii) Include allowance for any reasonably expected time delays in the execution of the procedures. <CITA>[Doc. No. 27807, 61 FR 5184, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.49</SECTNO> <SUBJECT>Stalling period.</SUBJECT> (a) V<E T="52">SO</E> and V<E T="52">S1</E> are the stalling speeds or the minimum steady flight speeds, in knots (CAS), at which the airplane is controllable with— (1) For reciprocating engine-powered airplanes, the engine(s) idling, the throttle(s) closed or at not more than the power necessary for zero thrust at a speed not more than 110 percent of the stalling speed; (2) For turbine engine-powered airplanes, the propulsive thrust not greater than zero at the stalling speed, or, if the resultant thrust has no appreciable effect on the stalling speed, with engine(s) idling and throttle(s) closed; (3) The propeller(s) in the takeoff position; (4) The airplane in the condition existing in the test, in which V<E T="52">SO</E> and V<E T="52">S1</E> are being used; (5) The center of gravity in the position that results in the highest value of V<E T="52">SO</E> and V<E T="52">S1</E>; and (6) The weight used when V<E T="52">SO</E> and V<E T="52">S1</E> are being used as a factor to determine compliance with a required performance standard. (b) V<E T="52">SO</E> and V<E T="52">S1</E> must be determined by flight tests, using the procedure and meeting the flight characteristics specified in § 23.201. (c) Except as provided in paragraph (d) of this section, V<E T="52">SO</E> and V<E T="52">S1</E> at maximum weight must not exceed 61 knots for— (1) Single-engine airplanes; and (2) Multiengine airplanes of 6,000 pounds or less maximum weight that cannot meet the minimum rate of climb specified in § 23.67(a) (1) with the critical engine inoperative. (d) All single-engine airplanes, and those multiengine airplanes of 6,000 pounds or less maximum weight with a V<E T="52">SO</E> of more than 61 knots that do not meet the requirements of § 23.67(a)(1), must comply with § 23.562(d). <CITA>[Doc. No. 27807, 61 FR 5184, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.51</SECTNO> <SUBJECT>Takeoff speeds.</SUBJECT> (a) For normal, utility, and acrobatic category airplanes, rotation speed, V<E T="52">R</E>, is the speed at which the pilot makes a control input, with the intention of lifting the airplane out of contact with the runway or water surface. (1) For multiengine landplanes, V<E T="52">R</E>, must not be less than the greater of 1.05 V<E T="52">MC</E>; or 1.10 V<E T="52">S1</E>; (2) For single-engine landplanes, V<E T="52">R</E>, must not be less than V<E T="52">S1</E>; and (3) For seaplanes and amphibians taking off from water, V<E T="52">R</E>, may be any speed that is shown to be safe under all reasonably expected conditions, including turbulence and complete failure of the critical engine. (b) For normal, utility, and acrobatic category airplanes, the speed at 50 feet above the takeoff surface level must not be less than: (1) or multiengine airplanes, the highest of— (i) A speed that is shown to be safe for continued flight (or emergency landing, if applicable) under all reasonably expected conditions, including turbulence and complete failure of the critical engine; (ii) 1.10 V<E T="52">MC</E>; or (iii) 1.20 V<E T="52">S1</E>. (2) For single-engine airplanes, the higher of— (i) A speed that is shown to be safe under all reasonably expected conditions, including turbulence and complete engine failure; or (ii) 1.20 V<E T="52">S1</E>. (c) For commuter category airplanes, the following apply: (l) V<E T="52">1</E> must be established in relation to V<E T="52">EF</E> as follows: (i) V<E T="52">EF</E> is the calibrated airspeed at which the critical engine is assumed to fail. V<E T="52">EF</E> must be selected by the applicant but must not be less than 1.05 V<E T="52">MC</E> determined under § 23.149(b) or, at the option of the applicant, not less than V<E T="52">MCG</E> determined under § 23.149(f). (ii) The takeoff decision speed, V<E T="52">1</E>, is the calibrated airspeed on the ground at which, as a result of engine failure <PRTPAGE P="170"/>or other reasons, the pilot is assumed to have made a decision to continue or discontinue the takeoff. The takeoff decision speed, V<E T="52">1</E>, must be selected by the applicant but must not be less than V<E T="52">EF</E> plus the speed gained with the critical engine inoperative during the time interval between the instant at which the critical engine is failed and the instant at which the pilot recognizes and reacts to the engine failure, as indicated by the pilot's application of the first retarding means during the accelerate-stop determination of § 23.55. (2) The rotation speed, V<E T="52">R</E>, in terms of calibrated airspeed, must be selected by the applicant and must not be less than the greatest of the following: (i) V<E T="52">1</E>; (ii) 1.05 V<E T="52">MC</E> determined under § 23.149(b); (iii) 1.10 V<E T="52">S1</E>; or (iv) The speed that allows attaining the initial climb-out speed, V<E T="52">2</E>, before reaching a height of 35 feet above the takeoff surface in accordance with § 23.57(c)(2). (3) For any given set of conditions, such as weight, altitude, temperature, and configuration, a single value of V<E T="52">R</E> must be used to show compliance with both the one-engine-inoperative takeoff and all-engines-operating takeoff requirements. (4) The takeoff safety speed, V<E T="52">2</E>, in terms of calibrated airspeed, must be selected by the applicant so as to allow the gradient of climb required in § 23.67 (c)(1) and (c)(2) but mut not be less than 1.10 V<E T="52">MC</E> or less than 1.20 V<E T="52">S1</E>. (5) The one-engine-inoperative takeoff distance, using a normal rotation rate at a speed 5 knots less than V<E T="52">R</E>, established in accordance with paragraph (c)(2) of this section, must be shown not to exceed the corresponding one-engine-inoperative takeoff distance, determined in accordance with § 23.57 and § 23.59(a)(1), using the established V<E T="52">R</E>. The takeoff, otherwise performed in accordance with § 23.57, must be continued safely from the point at which the airplane is 35 feet above the takeoff surface and at a speed not less than the established V<E T="52">2</E> minus 5 knots. (6) The applicant must show, with all engines operating, that marked increases in the scheduled takeoff distances, determined in accordance with § 23.59(a)(2), do not result from over-rotation of the airplane or out-of-trim conditions. <CITA>[Doc. No. 27807, 61 FR 5184, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.53</SECTNO> <SUBJECT>Takeoff performance.</SUBJECT> (a) For normal, utility, and acrobatic category airplanes, the takeoff distance must be determined in accordance with paragraph (b) of this section, using speeds determined in accordance with § 23.51 (a) and (b). (b) For normal, utility, and acrobatic category airplanes, the distance required to takeoff and climb to a height of 50 feet above the takeoff surface must be determined for each weight, altitude, and temperature within the operational limits established for takeoff with— (1) Takeoff power on each engine; (2) Wing flaps in the takeoff position(s); and (3) Landing gear extended. (c) For commuter category airplanes, takeoff performance, as required by §§ 23.55 through 23.59, must be determined with the operating engine(s) within approved operating limitations. <CITA>[Doc. No. 27807, 61 FR 5185, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.55</SECTNO> <SUBJECT>Accelerate-stop distance.</SUBJECT> For each commuter category airplane, the accelerate-stop distance must be determined as follows: (a) The accelerate-stop distance is the sum of the distances necessary to— (1) Accelerate the airplane from a standing start to V<E T="52">EF</E> with all engines operating; (2) Accelerate the airplane from V<E T="52">EF</E> to V<E T="52">1</E>, assuming the critical engine fails at V<E T="52">EF</E>; and (3) Come to a full stop from the point at which V<E T="52">1</E> is reached. (b) Means other than wheel brakes may be used to determine the accelerate-stop distances if that means— (1) Is safe and reliable; (2) Is used so that consistent results can be expected under normal operating conditions; and (3) Is such that exceptional skill is not required to control the airplane. <CITA>[Amdt. 23-34, 52 FR 1826, Jan. 15, 1987, as amended by Amdt. 23-50, 61 FR 5185, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <PRTPAGE P="171"/> <SECTNO>§ 23.57</SECTNO> <SUBJECT>Takeoff path.</SUBJECT> For each commuter category airplane, the takeoff path is as follows: (a) The takeoff path extends from a standing start to a point in the takeoff at which the airplane is 1500 feet above the takeoff surface at or below which height the transition from the takeoff to the enroute configuration must be completed; and (1) The takeoff path must be based on the procedures prescribed in § 23.45; (2) The airplane must be accelerated on the ground to V<E T="54">EF</E> at which point the critical engine must be made inoperative and remain inoperative for the rest of the takeoff; and (3) After reaching V<E T="54">EF</E>, the airplane must be accelerated to V<E T="54">2</E>. (b) During the acceleration to speed V<E T="52">2</E>, the nose gear may be raised off the ground at a speed not less than V<E T="52">R</E>. However, landing gear retraction must not be initiated until the airplane is airborne. (c) During the takeoff path determination, in accordance with paragraphs (a) and (b) of this section— (1) The slope of the airborne part of the takeoff path must not be negative at any point; (2) The airplane must reach V<E T="54">2</E> before it is 35 feet above the takeoff surface, and must continue at a speed as close as practical to, but not less than V<E T="54">2</E>, until it is 400 feet above the takeoff surface; (3) At each point along the takeoff path, starting at the point at which the airplane reaches 400 feet above the takeoff surface, the available gradient of climb must not be less than— (i) 1.2 percent for two-engine airplanes; (ii) 1.5 percent for three-engine airplanes; (iii) 1.7 percent for four-engine airplanes; and (4) Except for gear retraction and automatic propeller feathering, the airplane configuration must not be changed, and no change in power that requires action by the pilot may be made, until the airplane is 400 feet above the takeoff surface. (d) The takeoff path to 35 feet above the takeoff surface must be determined by a continuous demonstrated takeoff. (e) The takeoff path to 35 feet above the takeoff surface must be determined by synthesis from segments; and (1) The segments must be clearly defined and must be related to distinct changes in configuration, power, and speed; (2) The weight of the airplane, the configuration, and the power must be assumed constant throughout each segment and must correspond to the most critical condition prevailing in the segment; and (3) The takeoff flight path must be based on the airplane's performance without utilizing ground effect. <CITA>[Amdt. 23-34, 52 FR 1827, Jan. 15, 1987, as amended by Amdt. 23-50, 61 FR 5185, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.59</SECTNO> <SUBJECT>Takeoff distance and takeoff run.</SUBJECT> For each commuter category airplane, the takeoff distance and, at the option of the applicant, the takeoff run, must be determined. (a) Takeoff distance is the greater of— (1) The horizontal distance along the takeoff path from the start of the takeoff to the point at which the airplane is 35 feet above the takeoff surface as determined under § 23.57; or (2) With all engines operating, 115 percent of the horizontal distance from the start of the takeoff to the point at which the airplane is 35 feet above the takeoff surface, determined by a procedure consistent with § 23.57. (b) If the takeoff distance includes a clearway, the takeoff run is the greater of— (1) The horizontal distance along the takeoff path from the start of the takeoff to a point equidistant between the liftoff point and the point at which the airplane is 35 feet above the takeoff surface as determined under § 23.57; or (2) With all engines operating, 115 percent of the horizontal distance from the start of the takeoff to a point equidistant between the liftoff point and the point at which the airplane is 35 feet above the takeoff surface, determined by a procedure consistent with § 23.57. <CITA>[Amdt. 23-34, 52 FR 1827, Jan. 15, 1987, as amended by Amdt. 23-50, 61 FR 5185, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <PRTPAGE P="172"/> <SECTNO>§ 23.61</SECTNO> <SUBJECT>Takeoff flight path.</SUBJECT> For each commuter category airplane, the takeoff flight path must be determined as follows: (a) The takeoff flight path begins 35 feet above the takeoff surface at the end of the takeoff distance determined in accordance with § 23.59. (b) The net takeoff flight path data must be determined so that they represent the actual takeoff flight paths, as determined in accordance with § 23.57 and with paragraph (a) of this section, reduced at each point by a gradient of climb equal to— (1) 0.8 percent for two-engine airplanes; (2) 0.9 percent for three-engine airplanes; and (3) 1.0 percent for four-engine airplanes. (c) The prescribed reduction in climb gradient may be applied as an equivalent reduction in acceleration along that part of the takeoff flight path at which the airplane is accelerated in level flight. <CITA>[Amdt. 23-34, 52 FR 1827, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.63</SECTNO> <SUBJECT>Climb: general.</SUBJECT> (a) Compliance with the requirements of §§ 23.65, 23.66, 23.67, 23.69, and 23.77 must be shown— (1) Out of ground effect; and (2) At speeds that are not less than those at which compliance with the powerplant cooling requirements of §§ 23.1041 to 23.1047 has been demonstrated; and (3) Unless otherwise specified, with one engine inoperative, at a bank angle not exceeding 5 degrees. (b) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, compliance must be shown with § 23.65(a), § 23.67(a), where appropriate, and § 23.77(a) at maximum takeoff or landing weight, as appropriate, in a standard atmosphere. (c) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-powered airplanes in the normal, utility, and acrobatic category, compliance must be shown at weights as a function of airport altitude and ambient temperature, within the operational limits established for takeoff and landing, respectively, with— (1) Sections 23.65(b) and 23.67(b) (1) and (2), where appropriate, for takeoff, and (2) Section 23.67(b)(2), where appropriate, and § 23.77(b), for landing. (d) For commuter category airplanes, compliance must be shown at weights as a function of airport altitude and ambient temperature within the operational limits established for takeoff and landing, respectively, with— (1) Sections 23.67(c)(1), 23.67(c)(2), and 23.67(c)(3) for takeoff; and (2) Sections 23.67(c)(3), 23.67(c)(4), and 23.77(c) for landing. <CITA>[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.65</SECTNO> <SUBJECT>Climb: all engines operating.</SUBJECT> (a) Each normal, utility, and acrobatic category reciprocating engine-powered airplane of 6,000 pounds or less maximum weight must have a steady climb gradient at sea level of at least 8.3 percent for landplanes or 6.7 percet for seaplanes and amphibians with— (1) Not more than maximum continuous power on each engine; (2) The landing gear retracted; (3) The wing flaps in the takeoff position(s); and (4) A climb speed not less than the greater of 1.1 V<E T="52">MC</E> and 1.2 V<E T="52">S1</E> for multiengine airplanes and not less than 1.2 V<E T="52">S1</E> for single—engine airplanes. (b) Each normal, utility, and acrobatic category reciprocating engine-powered airplane of more than 6,000 pounds maximum weight and turbine engine-powered airplanes in the normal, utility, and acrobatic category must have a steady gradient of climb after takeoff of at least 4 percent with (1) Take off power on each engine; (2) The landing gear extended, except that if the landing gear can be retracted in not more than sven seconds, the test may be conducted with the gear retracted; (3) The wing flaps in the takeoff position(s); and (4) A climb speed as specified in § 23.65(a)(4). <CITA>[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <PRTPAGE P="173"/> <SECTNO>§ 23.66</SECTNO> <SUBJECT>Takeoff climb: One-engine inoperative.</SUBJECT> For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-powered airplanes in the normal, utility, and acrobatic category, the steady gradient of climb or descent must be determined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with— (a) The critical engine inoperative and its propeller in the position it rapidly and automatically assumes; (b) The remaining engine(s) at takeoff power; (c) The landing gear extended, except that if the landing gear can be retracted in not more than seven seconds, the test may be conducted with the gear retracted; (d) The wing flaps in the takeoff position(s): (e) The wings level; and (f) A climb speed equal to that achieved at 50 feet in the demonstration of § 23.53. <CITA>[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.67</SECTNO> <SUBJECT>Climb: One engine inoperative.</SUBJECT> (a) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, the following apply: (1) Except for those airplanes that meet the requirements prescribed in § 23.562(d), each airplane with a V<E T="52">SO</E> of more than 61 knots must be able to maintain a steady climb gradient of at least 1.5 percent at a pressure altitude of 5,000 feet with the— (i) Critical engine inoperative and its propeller in the minimum drag position; (ii) Remaining engine(s) at not more than maximum continuous power; (iii) Landing gear retracted; (iv) Wing flaps retracted; and (v) Climb speed not less than 1.2 V<E T="52">S1</E>. (2) For each airplane that meets the requirements prescribed in § 23.562(d), or that has a V<E T="52">SO</E> of 61 knots or less, the steady gradient of climb or descent at a pressure altitude of 5,000 feet must be determined with the— (i) Critical engine inoperative and its propeller in the minimum drag position; (ii) Remaining engine(s) at not more than maximum continuous power; (iii) Landing gear retracted; (iv) Wing flaps retracted; and (v) Climb speed not less than 1.2V<E T="52">S1</E>. (b) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-powered airplanes in the normal, utility, and acrobatic category— (1) The steady gradient of climb at an altitude of 400 feet above the takeoff must be measurably positive with the— (i) Critical engine inoperative and its propeller in the minimum drag position; (ii) Remaining engine(s) at takeoff power; (iii) Landing gear retracted; (iv) Wing flaps in the takeoff position(s); and (v) Climb speed equal to that achieved at 50 feet in the demonstration of § 23.53. (2) The steady gradient of climb must not be less than 0.75 percent at an altitude of 1,500 feet above the takeoff surface, or landing surface, as appropriate, with the— (i) Critical engine inoperative and its propeller in the minimum drag position; (ii) Remaining engine(s) at not more than maximum continuous power; (iii) Landing gear retracted; (iv) Wing flaps retracted; and (v) Climb speed not less than 1.2 V<E T="52">S1</E>. (c) For commuter category airplanes, the following apply: (1) <E T="03">Takeoff; landing gear extended.</E> The steady gradient of climb at the altitude of the takeoff surface must be measurably positive for two-engine airplanes, not less than 0.3 percent for three-engine airplanes, or 0.5 percent for four-engine airplanes with— (i) The critical engine inoperative and its propeller in the position it rapidly and automatically assumes; (ii) The remaining engine(s) at takeoff power; (iii) The landing gear extended, and all landing gear doors open; (iv) The wing flaps in the takeoff position(s);<PRTPAGE P="174"/> (v) The wings level; and (vi) A climb speed equal to V<E T="52">2</E>. (2) <E T="03">Takeoff; landing gear retracted.</E> The steady gradient of climb at an altitude of 400 feet above the takeoff surface must be not less than 2.0 percent of two-engine airplanes, 2.3 percent for three-engine airplanes, and 2.6 percent for four-engine airplanes with— (i) The critical engine inoperative and its propeller in the position it rapidly and automatically assumes; (ii) The remaining engine(s) at takeoff power; (iii) The landing gear retracted; (iv) The wing flaps in the takeoff position(s); (v) A climb speed equal to V<E T="52">2</E>. (3) <E T="03">Enroute.</E> The steady gradient of climb at an altitude of 1,500 feet above the takeoff or landing surface, as appropriate, must be not less than 1.2 percent for two-engine airplanes, 1.5 percent for three-engine airplanes, and 1.7 percent for four-engine airplanes with— (i) The critical engine inoperative and its propeller in the minimum drag position; (ii) The remaining engine(s) at not more than maximum continuous power; (iii) The landing gear retracted; (iv) The wing flaps retracted; and (v) A climb speed not less than 1.2 V<E T="52">S1</E>. (4) <E T="03">Discontinued approach.</E> The steady gradient of climb at an altitude of 400 feet above the landing surface must be not less than 2.1 percent for two-engine airplanes, 2.4 percent for three-engine airplanes, and 2.7 percent for four-engine airplanes, with— (i) The critical engine inoperative and its propeller in the minimum drag position; (ii) The remaining engine(s) at takeoff power; (iii) Landing gear retracted; (iv) Wing flaps in the approach position(s) in which V<E T="52">S1</E> for these position(s) does not exceed 110 percent of the V<E T="52">S1</E> for the related all-engines-operated landing position(s); and (v) A climb speed established in connection with normal landing procedures but not exceeding 1.5 V<E T="52">S1</E>. <CITA>[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.69</SECTNO> <SUBJECT>Enroute climb/descent.</SUBJECT> (a) <E T="03">All engines operating.</E> The steady gradient and rate of climb must be determined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with— (1) Not more than maximum continuous power on each engine; (2) The landing gear retracted; (3) The wing flaps retracted; and (4) A climb speed not less than 1.3 V<E T="52">S1</E>. (b) <E T="03">One engine inoperative.</E> The steady gradient and rate of climb/descent must be determined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with— (1) The critical engine inoperative and its propeller in the minimum drag position; (2) The remaining engine(s) at not more than maximum continuous power; (3) The landing gear retracted; (4) The wing flaps retracted; and (5) A climb speed not less than 1.2 V<E T="52">S1</E>. <CITA>[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.71</SECTNO> <SUBJECT>Glide: Single-engine airplanes.</SUBJECT> The maximum horizontal distance traveled in still air, in nautical miles, per 1,000 feet of altitude lost in a glide, and the speed necessary to achieve this must be determined with the engine inoperative, its propeller in the minimum drag position, and landing gear and wing flaps in the most favorable available position. <CITA>[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.73</SECTNO> <SUBJECT>Reference landing approach speed.</SUBJECT> (a) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, the reference landing approach speed, V<E T="52">REF</E>, must not be less than the greater of V<E T="52">MC</E>, determined in § 23.149(b) with the wing flaps in the most extended takeoff position, and 1.3 V<E T="52">SO</E>. (b) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-<PRTPAGE P="175"/>powered airplanes in the normal, utility, and acrobatic category, the reference landing approach speed, V<E T="52">REF</E>, must not be less than the greater of V<E T="52">MC</E>, determined in § 23.149(c), and 1.3 V<E T="52">SO</E>. (c) For commuter category airplanes, the reference landing approach speed, V<E T="52">REF</E>, must not be less than the greater of 1.05 V<E T="52">MC</E>, determined in § 23.149(c), and 1.3 V<E T="52">SO</E>. <CITA>[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.75</SECTNO> <SUBJECT>Landing distance.</SUBJECT> The horizontal distance necessary to land and come to a complete stop from a point 50 feet above the landing surface must be determined, for standard temperatures at each weight and altitude within the operational limits established for landing, as follows: (a) A steady approach at not less than V<E T="52">REF</E>, determined in accordance with § 23.73 (a), (b), or (c), as appropriate, must be maintained down to the 50 foot height and— (1) The steady approach must be at a gradient of descent not greater than 5.2 percent (3 degrees) down to the 50-foot height. (2) In addition, an applicant may demonstrate by tests that a maximum steady approach gradient steeper than 5.2 percent, down to the 50-foot height, is safe. The gradient must be established as an operating limitation and the information necessary to display the gradient must be available to the pilot by an appropriate instrument. (b) A constant configuration must be maintained throughout the maneuver. (c) The landing must be made without excessive vertical acceleration or tendency to bounce, nose over, ground loop, porpoise, or water loop. (d) It must be shown that a safe transition to the balked landing conditions of § 23.77 can be made from the conditions that exist at the 50 foot height, at maximum landing weight, or at the maximum landing weight for altitude and temperature of § 23.63 (c)(2) or (d)(2), as appropriate. (e) The brakes must be used so as to not cause excessive wear of brakes or tires. (f) Retardation means other than wheel brakes may be used if that means— (1) Is safe and reliable; and (2) Is used so that consistent results can be expected in service. (g) If any device is used that depends on the operation of any engine, and the landing distance would be increased when a landing is made with that engine inoperative, the landing distance must be determined with that engine inoperative unless the use of other compensating means will result in a landing distance not more than that with each engine operating. <CITA>[Amdt. 23-21, 43 FR 2318, Jan. 16, 1978, as amended by Amdt. 23-34, 52 FR 1828, Jan. 15, 1987; Amdt. 23-42, 56 FR 351, Jan. 3, 1991; Amdt. 23-50, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.77</SECTNO> <SUBJECT>Balked landing.</SUBJECT> (a) Each normal, utility, and acrobatic category reciprocating engine-powered airplane at 6,000 pounds or less maximum weight must be able to maintain a steady gradient of climb at sea level of at least 3.3 percent with— (1) Takeoff power on each engine; (2) The landing gear extended; (3) The wing flaps in the landing position, except that if the flaps may safely be retracted in two seconds or less without loss of altitude and without sudden changes of angle of attack, they may be retracted; and (4) A climb speed equal to V<E T="52">REF</E>, as defined in § 23.73(a). (b) Each normal, utility, and acrobatic category reciprocating engine-powered airplane of more than 6,000 pounds maximum weight and each normal, utility, and acrobatic category turbine engine-powered airplane must be able to maintain a steady gradient of climb of at least 2.5 percent with— (1) Not more than the power that is available on each engine eight seconds after initiation of movement of the power controls from minimum flight-idle position; (2) The landing gear extended; (3) The wing flaps in the landing position; and (4) A climb speed equal to V<E T="52">REF</E>, as defined in § 23.73(b). (c) Each commuter category airplane must be able to maintain a steady gradient of climb of at least 3.2 percent with— (1) Not more than the power that is available on each engine eight seconds <PRTPAGE P="176"/>after initiation of movement of the power controls from the minimum flight idle position; (2) Landing gear extended; (3) Wing flaps in the landing position; and (4) A climb speed equal to V<E T="52">REF</E>, as defined in § 23.73(c). <CITA>[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Flight Characteristics</HD> <SECTION> <SECTNO>§ 23.141</SECTNO> <SUBJECT>General.</SUBJECT> The airplane must meet the requirements of §§ 23.143 through 23.253 at all practical loading conditions and operating altitudes for which certification has been requested, not exceeding the maximum operating altitude established under § 23.1527, and without requiring exceptional piloting skill, alertness, or strength. <CITA>[Doc. No. 26269, 58 FR 42156, Aug. 6, 1993]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Controllability and Maneuverability</HD> <SECTION> <SECTNO>§ 23.143</SECTNO> <SUBJECT>General.</SUBJECT> (a) The airplane must be safely controllable and maneuverable during all flight phases including— (1) Takeoff; (2) Climb; (3) Level flight; (4) Descent; (5) Go-around; and (6) Landing (power on and power off) with the wing flaps extended and retracted. (b) It must be possible to make a smooth transition from one flight condition to another (including turns and slips) without danger of exceeding the limit load factor, under any probable operating condition (including, for multiengine airplanes, those conditions normally encountered in the sudden failure of any engine). (c) If marginal conditions exist with regard to required pilot strength, the control forces necessary must be determined by quantitative tests. In no case may the control forces under the conditions specified in paragraphs (a) and (b) of this section exceed those prescribed in the following table: <GPOTABLE CDEF="s25,6,6,6" COLS="4" OPTS="L2,i1"> <BOXHD> <CHED H="1">Values in pounds force applied to the relevant control</CHED> <CHED H="1">Pitch</CHED> <CHED H="1">Roll</CHED> <CHED H="1">Yaw</CHED> </BOXHD> <ROW> <ENT I="22">(a) For temporary application:</ENT> </ROW> <ROW> <ENT I="02">Stick</ENT> <ENT>60</ENT> <ENT>30</ENT> <ENT/> </ROW> <ROW> <ENT I="02">Wheel (Two hands on rim)</ENT> <ENT>75</ENT> <ENT>50</ENT> <ENT/> </ROW> <ROW> <ENT I="02">Wheel (One hand on rim)</ENT> <ENT>50</ENT> <ENT>25</ENT> <ENT/> </ROW> <ROW> <ENT I="02">Rudder Pedal</ENT> <ENT/> <ENT/> <ENT>150</ENT> </ROW> <ROW> <ENT I="01">(b) For prolonged application</ENT> <ENT>10</ENT> <ENT>5</ENT> <ENT>20</ENT> </ROW> </GPOTABLE> <CITA>[Doc. No, 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-14, 38 FR 31819, Nov. 19, 1973; Amdt. 23-17, 41 FR 55464, Dec. 20, 1976; Amdt. 23-45, 58 FR 42156, Aug. 6, 1993; Amdt. 23-50, 61 FR 5188, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.145</SECTNO> <SUBJECT>Longitudinal control.</SUBJECT> (a) With the airplane as nearly as possible in trim at 1.3 V<E T="52">S1</E>, it must be possible, at speeds below the trim speed, to pitch the nose downward so that the rate of increase in airspeed allows prompt acceleration to the trim speed with— (1) Maximum continuous power on each engine; (2) Power off; and (3) Wing flap and landing gear— (i) retracted, and (ii) extended. (b) Unless otherwise required, it must be possible to carry out the following maneuvers without requiring the application of single-handed control forces exceeding those specified in § 23.143(c). The trimming controls must not be adjusted during the maneuvers: (1) With the landing gear extended, the flaps retracted, and the airplanes as nearly as possible in trim at 1.4 V<E T="52">S1</E>, extend the flaps as rapidly as possible and allow the airspeed to transition from 1.4V<E T="52">S1</E> to 1.4 V<E T="52">SO:</E> (i) With power off; and (ii) With the power necessary to maintain level flight in the initial condition. (2) With landing gear and flaps extended, power off, and the airplane as nearly as possible in trim at 1.3 V<E T="52">SO</E>, quickly apply takeoff power and retract the flaps as rapidly as possible to the recommended go around setting and allow the airspeed to transition from 1.3 V<E T="52">SO</E> to 1.3 V<E T="52">S1</E>. Retract the gear when a positive rate of climb is established. (3) With landing gear and flaps extended, in level flight, power necessary to attain level flight at 1.1 V<E T="52">SO</E>, and the airplane as nearly as possible in trim, <PRTPAGE P="177"/>it must be possible to maintain approximately level flight while retracting the flaps as rapidly as possible with simultaneous application of not more than maximum continuous power. If gated flat positions are provided, the flap retraction may be demonstrated in stages with power and trim reset for level flight at 1.1 V<E T="52">S1</E>, in the initial configuration for each stage— (i) From the fully extended position to the most extended gated position; (ii) Between intermediate gated positions, if applicable; and (iii) From the least extended gated position to the fully retracted position. (4) With power off, flaps and landing gear retracted and the airplane as nearly as possible in trim at 1.4 V<E T="52">S1</E>, apply takeoff power rapidly while maintaining the same airspeed. (5) With power off, landing gear and flaps extended, and the airplane as nearly as possible in trim at V<E T="52">REF</E>, obtain and maintain airspeeds between 1.1 V<E T="52">SO</E>, and either 1.7 V<E T="52">SO</E> or V<E T="52">FE</E>, whichever is lower without requiring the application of two-handed control forces exceeding those specified in § 23.143(c). (6) With maximum takeoff power, landing gear retracted, flaps in the takeoff position, and the airplane as nearly as possible in trim at V<E T="52">FE</E> appropriate to the takeoff flap position, retract the flaps as rapidly as possible while maintaining constant speed. (c) At speeds above V<E T="52">MO</E>/M<E T="52">MO</E>, and up to the maximum speed shown under § 23.251, a maneuvering capability of 1.5 g must be demonstrated to provide a margin to recover from upset or inadvertent speed increase. (d) It must be possible, with a pilot control force of not more than 10 pounds, to maintain a speed of not more than V<E T="52">REF</E> during a power-off glide with landing gear and wing flaps extended, for any weight of the airplane, up to and including the maximum weight. (e) By using normal flight and power controls, except as otherwise noted in paragraphs (e)(1) and (e)(2) of this section, it must be possible to establish a zero rate of descent at an attitude suitable for a controlled landing without exceeding the operational and structural limitations of the airplane, as follows: (1) For single-engine and multiengine airplanes, without the use of the primary longitudinal control system. (2) For multiengine airplanes— (i) Without the use of the primary directional control; and (ii) If a single failure of any one connecting or transmitting link would affect both the longitudinal and directional primary control system, without the primary longitudinal and directional control system. <CITA>[Doc. No. 26269, 58 FR 42157, Aug. 6, 1993; Amdt. 23-45, 58 FR 51970, Oct. 5, 1993, as amended by Amdt. 23-50, 61 FR 5188, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.147</SECTNO> <SUBJECT>Directional and lateral control.</SUBJECT> (a) For each multiengine airplane, it must be possible, while holding the wings level within five degrees, to make sudden changes in heading safely in both directions. This ability must be shown at 1.4 V<E T="52">S1</E> with heading changes up to 15 degrees, except that the heading change at which the rudder force corresponds to the limits specified in § 23.143 need not be exceeded, with the— (1) Critical engine inoperative and its propeller in the minimum drag position; (2) Remaining engines at maximum continuous power; (3) Landing gear— (i) Retracted; and (ii) Extended; and (4) Flaps retracted. (b) For each multiengine airplane, it must be possible to regain full control of the airplane without exceeding a bank angle of 45 degrees, reaching a dangerous attitude or encountering dangerous characteristics, in the event of a sudden and complete failure of the critical engine, making allowance for a delay of two seconds in the initiation of recovery action appropriate to the situation, with the airplane initially in trim, in the following condition: (1) Maximum continuous power on each engine; (2) The wing flaps retracted; (3) The landing gear retracted; (4) A speed equal to that at which compliance with § 23.69(a) has been shown; and<PRTPAGE P="178"/> (5) All propeller controls in the position at which compliance with § 23.69(a) has been shown. (c) For all airplanes, it must be shown that the airplane is safely controllable without the use of the primary lateral control system in any all-engine configuration(s) and at any speed or altitude within the approved operating envelope. It must also be shown that the airplane's flight characteristics are not impaired below a level needed to permit continued safe flight and the ability to maintain attitudes suitable for a controlled landing without exceeding the operational and structural limitations of the airplane. If a single failure of any one connecting or transmitting link in the lateral control system would also cause the loss of additional control system(s), compliance with the above requirement must be shown with those additional systems also assumed to be inoperative. <CITA>[Doc. No. 27807, 61 FR 5188, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.149</SECTNO> <SUBJECT>Minimum control speed.</SUBJECT> (a) V<E T="52">MC</E> is the calibrated airspeed at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the airplane with that engine still inoperative, and thereafter maintain straight flight at the same speed with an angle of bank of not more than 5 degrees. The method used to simulate critical engine failure must represent the most critical mode of powerplant failure expected in service with respect to controllability. (b) V<E T="52">MC</E> for takeoff must not exceed 1.2 V<E T="52">S1</E>, where V<E T="52">S1</E> is determined at the maximum takeoff weight. V<E T="52">MC</E> must be determined with the most unfavorable weight and center of gravity position and with the airplane airborne and the ground effect negligible, for the takeoff configuration(s) with— (1) Maximum available takeoff power initially on each engine; (2) The airplane trimmed for takeoff; (3) Flaps in the takeoff position(s); (4) Landing gear retracted; and (5) All propeller controls in the recommended takeoff position throughout. (c) For all airplanes except reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, the conditions of paragraph (a) of this section must also be met for the landing configuration with— (1) Maximum available takeoff power initially on each engine; (2) The airplane trimmed for an approach, with all engines operating, at V<E T="52">REF</E>, at an approach gradient equal to the steepest used in the landing distance demonstration of § 23.75; (3) Flaps in the landing position; (4) Landing gear extended; and (5) All propeller controls in the position recommended for approach with all engines operating. (d) A minimum speed to intentionally render the critical engine inoperative must be established and designated as the safe, intentional, one-engine-inoperative speed, V<E T="52">SSE</E>. (e) At V<E T="52">MC</E>, the rudder pedal force required to maintain control must not exceed 150 pounds and it must not be necessary to reduce power of the operative engine(s). During the maneuver, the airplane must not assume any dangerous attitude and it must be possible to prevent a heading change of more than 20 degrees. (f) At the option of the applicant, to comply with the requirements of § 23.51(c)(1), V<E T="52">MCG</E> may be determined. V<E T="52">MCG</E> is the minimum control speed on the ground, and is the calibrated airspeed during the takeoff run at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the airplane using the rudder control alone (without the use of nosewheel steering), as limited by 150 pounds of force, and using the lateral control to the extent of keeping the wings level to enable the takeoff to be safely continued. In the determination of V<E T="52">MCG</E>, assuming that the path of the airplane accelerating with all engines operating is along the centerline of the runway, its path from the point at which the critical engine is made inoperative to the point at which recovery to a direction parallel to the centerline is completed may not deviate more than 30 feet laterally from the centerline at any point. V<E T="52">MCG</E> must be established with— (1) The airplane in each takeoff configuration or, at the option of the applicant, in the most critical takeoff configuration;<PRTPAGE P="179"/> (2) Maximum available takeoff power on the operating engines; (3) The most unfavorable center of gravity; (4) The airplane trimmed for takeoff; and (5) The most unfavorable weight in the range of takeoff weights. <CITA>[Doc. No. 27807, 61 FR 5189, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.151</SECTNO> <SUBJECT>Acrobatic maneuvers.</SUBJECT> Each acrobatic and utility category airplane must be able to perform safely the acrobatic maneuvers for which certification is requested. Safe entry speeds for these maneuvers must be determined. </SECTION> <SECTION> <SECTNO>§ 23.153</SECTNO> <SUBJECT>Control during landings.</SUBJECT> It must be possible, while in the landing configuration, to safely complete a landing without exceeding the one-hand control force limits specified in § 23.143(c) following an approach to land— (a) At a speed of V<E T="52">REF</E> minus 5 knots; (b) With the airplane in trim, or as nearly as possible in trim and without the trimming control being moved throughout the maneuver; (c) At an approach gradient equal to the steepest used in the landing distance demonstration of § 23.75; and (d) With only those power changes, if any, that would be made when landing normally from an approach at V<E T="52">REF</E>. <CITA>[Doc. No. 27807, 61 FR 5189, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.155</SECTNO> <SUBJECT>Elevator control force in maneuvers.</SUBJECT> (a) The elevator control force needed to achieve the positive limit maneuvering load factor may not be less than: (1) For wheel controls, W/100 (where W is the maximum weight) or 20 pounds, whichever is greater, except that it need not be greater than 50 pounds; or (2) For stick controls, W/140 (where W is the maximum weight) or 15 pounds, whichever is greater, except that it need not be greater than 35 pounds. (b) The requirement of paragraph (a) of this section must be met at 75 percent of maximum continuous power for reciprocating engines, or the maximum continuous power for turbine engines, and with the wing flaps and landing gear retracted— (1) In a turn, with the trim setting used for wings level flight at V<E T="52">O</E>; and (2) In a turn with the trim setting used for the maximum wings level flight speed, except that the speed may not exceed V<E T="52">NE</E> or V<E T="52">MO</E>/M<E T="52">MO</E>, whichever is appropriate. (c) There must be no excessive decrease in the gradient of the curve of stick force versus maneuvering load factor with increasing load factor. <CITA>[Amdt. 23-14, 38 FR 31819, Nov. 19, 1973; 38 FR 32784, Nov. 28, 1973, as amended by Amdt. 23-45, 58 FR 42158, Aug. 6, 1993; Amdt. 23-50, 61 FR 5189 Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.157</SECTNO> <SUBJECT>Rate of roll.</SUBJECT> (a) <E T="03">Takeoff.</E> It must be possible, using a favorable combination of controls, to roll the airplane from a steady 30-degree banked turn through an angle of 60 degrees, so as to reverse the direction of the turn within: (1) For an airplane of 6,000 pounds or less maximum weight, 5 seconds from initiation of roll; and (2) For an airplane of over 6,000 pounds maximum weight, <EXTRACT> <HD SOURCE="HD3">(W+500)/1,300</HD> </EXTRACT> <FP>seconds, but not more than 10 seconds, where W is the weight in pounds.</FP> (b) The requirement of paragraph (a) of this section must be met when rolling the airplane in each direction with— (1) Flaps in the takeoff position; (2) Landing gear retracted; (3) For a single-engine airplane, at maximum takeoff power; and for a multiengine airplane with the critical engine inoperative and the propeller in the minimum drag position, and the other engines at maximum takeoff power; and (4) The airplane trimmed at a speed equal to the greater of 1.2 V<E T="52">S1</E> or 1.1 V<E T="52">MC</E>, or as nearly as possible in trim for straight flight. (c) <E T="03">Approach.</E> It must be possible, using a favorable combination of controls, to roll the airplane from a steady 30-degree banked turn through an angle of 60 degrees, so as to reverse the direction of the turn within:<PRTPAGE P="180"/> (1) For an airplane of 6,000 pounds or less maximum weight, 4 seconds from initiation of roll; and (2) For an airplane of over 6,000 pounds maximum weight, <CTRHD>(W+2,800)/2,200<FP>seconds, but not more than 7 seconds, where W is the weight in pounds.</FP> </CTRHD> (d) The requirement of paragraph (c) of this section must be met when rolling the airplane in each direction in the following conditions— (1) Flaps in the landing position(s); (2) Landing gear extended; (3) All engines operating at the power for a 3 degree approach; and (4) The airplane trimmed at V<E T="52">REF</E>. <CITA>[Amdt. 23-14, 38 FR 31819, Nov. 19, 1973, as amended by Amdt. 23-45, 58 FR 42158, Aug. 6, 1993; Amdt. 23-50, 61 FR 5189, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Trim</HD> <SECTION> <SECTNO>§ 23.161</SECTNO> <SUBJECT>Trim.</SUBJECT> (a) <E T="03">General</E>. Each airplane must meet the trim requirements of this section after being trimmed and without further pressure upon, or movement of, the primary controls or their corresponding trim controls by the pilot or the automatic pilot. In addition, it must be possible, in other conditions of loading, configuration, speed and power to ensure that the pilot will not be unduly fatigued or distracted by the need to apply residual control forces exceeding those for prolonged application of § 23.143(c). This applies in normal operation of the airplane and, if applicable, to those conditions associated with the failure of one engine for which performance characteristics are established. (b) <E T="03">Lateral and directional trim.</E> The airplane must maintain lateral and directional trim in level flight with the landing gear and wing flaps retracted as follows: (1) For normal, utility, and acrobatic category airplanes, at a speed of 0.9 V<E T="52">H</E>, V<E T="52">C</E>, or V<E T="52">MO</E>/M<E T="52">O</E>, whichever is lowest; and (2) For commuter category airplanes, at all speeds from 1.4 V<E T="52">S1</E> to the lesser of V<E T="52">H</E> or V<E T="52">MO</E>/M<E T="52">MO</E>. (c) <E T="03">Longitudinal trim.</E> The airplane must maintain longitudinal trim under each of the following conditions: (1) A climb with— (i) Takeoff power, landing gear retracted, wing flaps in the takeoff position(s), at the speeds used in determining the climb performance required by § 23.65; and (ii) Maximum continuous power at the speeds and in the configuration used in determining the climb performance required by § 23.69(a). (2) Level flight at all speeds from the lesser of V<E T="52">H</E> and either V<E T="52">NO</E> or V<E T="52">MO</E>/M<E T="52">MO</E> (as appropriate), to 1.4 V<E T="52">S1</E>, with the landing gear and flaps retracted. (3) A descent at V<E T="52">NO</E> or V<E T="52">MO</E>/M<E T="52">MO</E>, whichever is applicable, with power off and with the landing gear and flaps retracted. (4) Approach with landing gear extended and with— (i) A 3 degree angle of descent, with flaps retracted and at a speed of 1.4 V<E T="52">S1</E>; (ii) A 3 degree angle of descent, flaps in the landing position(s) at V<E T="52">REF</E>; and (iii) An approach gradient equal to the steepest used in the landing distance demonstrations of § 23.75, flaps in the landing position(s) at V<E T="52">REF</E>. (d) In addition, each multiple airplane must maintain longitudinal and directional trim, and the lateral control force must not exceed 5 pounds at the speed used in complying with § 23.67(a), (b)(2), or (c)(3), as appropriate, with— (1) The critical engine inoperative, and if applicable, its propeller in the minimum drag position; (2) The remaining engines at maximum continuous power; (3) The landing gear retracted; (4) Wing flaps retracted; and (5) An angle of bank of not more than five degrees. (e) In addition, each commuter category airplane for which, in the determination of the takeoff path in accordance with § 23.57, the climb in the takeoff configuration at V<E T="52">2</E> extends beyond 400 feet above the takeoff surface, it must be possible to reduce the longitudinal and lateral control forces to 10 pounds and 5 pounds, respectively, and the directional control force must not exceed 50 pounds at V<E T="52">2</E> with— (1) The critical engine inoperative and its propeller in the minimum drag position; (2) The remaining engine(s) at takeoff power;<PRTPAGE P="181"/> (3) Landing gear retracted; (4) Wing flaps in the takeoff position(s); and (5) An angle of bank not exceeding 5 degrees. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-21, 43 FR 2318, Jan. 16, 1978; Amdt. 23-34, 52 FR 1828, Jan. 15, 1987; Amdt. 23-42, 56 FR 351, Jan. 3, 1991; 56 FR 5455, Feb. 11, 1991; Amdt. 23-50, 61 FR 5189, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Stability</HD> <SECTION> <SECTNO>§ 23.171</SECTNO> <SUBJECT>General.</SUBJECT> The airplane must be longitudinally, directionally, and laterally stable under §§ 23.173 through 23.181. In addition, the airplane must show suitable stability and control “feel” (static stability) in any condition normally encountered in service, if flight tests show it is necessary for safe operation. </SECTION> <SECTION> <SECTNO>§ 23.173</SECTNO> <SUBJECT>Static longitudinal stability.</SUBJECT> Under the conditions specified in § 23.175 and with the airplane trimmed as indicated, the characteristics of the elevator control forces and the friction within the control system must be as follows: (a) A pull must be required to obtain and maintain speeds below the specified trim speed and a push required to obtain and maintain speeds above the specified trim speed. This must be shown at any speed that can be obtained, except that speeds requiring a control force in excess of 40 pounds or speeds above the maximum allowable speed or below the minimum speed for steady unstalled flight, need not be considered. (b) The airspeed must return to within the tolerances specified for applicable categories of airplanes when the control force is slowly released at any speed within the speed range specified in paragraph (a) of this section. The applicable tolerances are— (1) The airspeed must return to within plus or minus 10 percent of the original trim airspeed; and (2) For commuter category airplanes, the airspeed must return to within plus or minus 7.5 percent of the original trim airspeed for the cruising condition specified in § 23.175(b). (c) The stick force must vary with speed so that any substantial speed change results in a stick force clearly perceptible to the pilot. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-14, 38 FR 31820 Nov. 19, 1973; Amdt. 23-34, 52 FR 1828, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.175</SECTNO> <SUBJECT>Demonstration of static longitudinal stability.</SUBJECT> Static longitudinal stability must be shown as follows: (a) <E T="03">Climb.</E> The stick force curve must have a stable slope at speeds between 85 and 115 percent of the trim speed, with— (1) Flaps retracted; (2) Landing gear retracted; (3) Maximum continuous power; and (4) The airplane trimmed at the speed used in determining the climb performance required by § 23.69(a). (b) <E T="03">Cruise.</E> With flaps and landing gear retracted and the airplane in trim with power for level flight at representative cruising speeds at high and low altitudes, including speeds up to V<E T="52">NO</E> or V<E T="52">MO</E>/M<E T="52">MO</E>, as appropriate, except that the speed need not exceed V<E T="52">H</E>— (1) For normal, utility, and acrobatic category airplanes, the stick force curve must have a stable slope at all speeds within a range that is the greater of 15 percent of the trim speed plus the resulting free return speed range, or 40 knots plus the resulting free return speed range, above and below the trim speed, except that the slope need not be stable— (i) At speeds less than 1.3 V<E T="52">S1</E>; or (ii) For airplanes with V<E T="52">NE</E> established under § 23.1505(a), at speeds greater than V<E T="52">NE</E>; or (iii) For airplanes with V<E T="52">MO</E>/M<E T="52">MO</E> established under § 23.1505(c), at speeds greater than V<E T="52">FC</E>/M<E T="52">FC</E>. (2) For commuter category airplanes, the stick force curve must have a stable slope at all speeds within a range of 50 knots plus the resulting free return speed range, above and below the trim speed, except that the slope need not be stable— (i) At speeds less than 1.4 V<E T="52">S1</E>; or (ii) At speeds greater than V<E T="52">FC</E>/M<E T="52">FC</E>; or (iii) At speeds that require a stick force greater than 50 pounds.<PRTPAGE P="182"/> (c) <E T="03">Landing.</E> The stick force curve must have a stable slope at speeds between 1.1 V<E T="52">S1</E> and 1.8 V<E T="52">S1</E> with— (1) Flaps in the landing position; (2) Landing gear extended; and (3) The airplane trimmed at— (i) V<E T="52">REF</E>, or the minimum trim speed if higher, with power off; and (ii) V<E T="52">REF</E> with enough power to maintain a 3 degree angle of descent. <CITA>[Doc. No. 27807, 61 FR 5190, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.177</SECTNO> <SUBJECT>Static directional and lateral stability.</SUBJECT> (a) The static directional stability, as shown by the tendency to recover from a wings level sideslip with the rudder free, must be positive for any landing gear and flap position appropriate to the takeoff, climb, cruise, approach, and landing configurations. This must be shown with symmetrical power up to maximum continuous power, and at speeds from 1.2 V<E T="52">S1</E> up to the maximum allowable speed for the condition being investigated. The angel of sideslip for these tests must be appropriate to the type of airplane. At larger angles of sideslip, up to that at which full rudder is used or a control force limit in § 23.143 is reached, whichever occurs first, and at speeds from 1.2 V<E T="52">S1</E> to V<E T="52">O</E>, the rudder pedal force must not reverse. (b) The static lateral stability, as shown by the tendency to raise the low wing in a sideslip, must be positive for all landing gear and flap positions. This must be shown with symmetrical power up to 75 percent of maximum continuous power at speeds above 1.2 V<E T="52">S1</E> in the take off configuration(s) and at speeds above 1.3 V<E T="52">S1</E> in other configurations, up to the maximum allowable speed for the configuration being investigated, in the takeoff, climb, cruise, and approach configurations. For the landing configuration, the power must be that necessary to maintain a 3 degree angle of descent in coordinated flight. The static lateral stability must not be negative at 1.2 V<E T="52">S1</E> in the takeoff configuration, or at 1.3 V<E T="52">S1</E> in other configurations. The angle of sideslip for these tests must be appropriate to the type of airplane, but in no case may the constant heading sideslip angle be less than that obtainable with a 10 degree bank, or if less, the maximum bank angle obtainable with full rudder deflection or 150 pound rudder force. (c) Paragraph (b) of this section does not apply to acrobatic category airplanes certificated for inverted flight. (d) In straight, steady slips at 1.2 V<E T="52">S1</E> for any landing gear and flap positions, and for any symmetrical power conditions up to 50 percent of maximum continuous power, the aileron and rudder control movements and forces must increase steadily, but not necessarily in constant proportion, as the angle of sideslip is increased up to the maximum appropriate to the type of airplane. At larger slip angles, up to the angle at which full rudder or aileron control is used or a control force limit contained in § 23.143 is reached, the aileron and rudder control movements and forces must not reverse as the angle of sideslip is increased. Rapid entry into, and recovery from, a maximum sideslip considered appropriate for the airplane must not result in uncontrollable flight characteristics. <CITA>[Doc. No. 27807, 61 FR 5190, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.181</SECTNO> <SUBJECT>Dynamic stability.</SUBJECT> (a) Any short period oscillation not including combined lateral-directional oscillations occurring between the stalling speed and the maximum allowable speed appropriate to the configuration of the airplane must be heavily damped with the primary controls— (1) Free; and (2) In a fixed position. (b) Any combined lateral-directional oscillations (“Dutch roll”) occurring between the stalling speed and the maximum allowable speed appropriate to the configuration of the airplane must be damped to 1/10 amplitude in 7 cycles with the primary controls— (1) Free; and (2) In a fixed position. (c) If it is determined that the function of a stability augmentation system, reference § 23.672, is needed to meet the flight characteristic requirements of this part, the primary control requirements of paragraphs (a)(2) and (b)(2) of this section are not applicable to the tests needed to verify the acceptability of that system.<PRTPAGE P="183"/> (d) During the conditions as specified in § 23.175, when the longitudinal control force required to maintain speeds differing from the trim speed by at least plus and minus 15 percent is suddenly released, the response of the airplane must not exhibit any dangerous characteristics nor be excessive in relation to the magnitude of the control force released. Any long-period oscillation of flight path, phugoid oscillation, that results must not be so unstable as to increase the pilot's workload or otherwise endanger the airplane. <CITA>[Amdt. 23-21, 43 FR 2318, Jan. 16, 1978, as amended by Amdt. 23-45, 58 FR 42158, Aug. 6, 1993]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Stalls</HD> <SECTION> <SECTNO>§ 23.201</SECTNO> <SUBJECT>Wings level stall.</SUBJECT> (a) It must be possible to produce and to correct roll by unreversed use of the rolling control and to produce and to correct yaw by unreversed use of the directional control, up to the time the airplane stalls. (b) The wings level stall characteristics must be demonstrated in flight as follows. Starting from a speed at least 10 knots above the stall speed, the elevator control must be pulled back so that the rate of speed reduction will not exceed one knot per second until a stall is produced, as shown by either: (1) An uncontrollable downward pitching motion of the airplane; (2) A downward pitching motion of the airplane that results from the activation of a stall avoidance device (for example, stick pusher); or (3) The control reaching the stop. (c) Normal use of elevator control for recovery is allowed after the downward pitching motion of paragraphs (b)(1) or (b)(2) of this section has unmistakably been produced, or after the control has been held against the stop for not less than the longer of two seconds or the time employed in the minimum steady slight speed determination of § 23.49. (d) During the entry into and the recovery from the maneuver, it must be possible to prevent more than 15 degrees of roll or yaw by the normal use of controls. (e) Compliance with the requirements of this section must be shown under the following conditions: (1) <E T="03">Wing flaps.</E> Retracted, fully extended, and each intermediate normal operating position. (2) <E T="03">Landing gear.</E> Retracted and extended. (3) <E T="03">Cowl flaps.</E> Appropriate to configuration. (4) <E T="03">Power:</E> (i) Power off; and (ii) 75 percent of maximum continuous power. However, if the power-to-weight ratio at 75 percent of maximum continuous power result in extreme nose-up attitudes, the test may be carried out with the power required for level flight in the landing configuration at maximum landing weight and a speed of 1.4 V<E T="52">SO</E>, except that the power may not be less than 50 percent of maximum continuous power. (5) <E T="03">Trim.</E> The airplane trimmed at a speed as near 1.5 V<E T="52">S1</E> as practicable. (6) <E T="03">Propeller.</E> Full increase r.p.m. position for the power off condition. <CITA>[Doc. No. 27807, 61 FR 5191, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.203</SECTNO> <SUBJECT>Turning flight and accelerated turning stalls.</SUBJECT> Turning flight and accelerated turning stalls must be demonstrated in tests as follows: (a) Establish and maintain a coordinated turn in a 30 degree bank. Reduce speed by steadily and progressively tightening the turn with the elevator until the airplane is stalled, as defined in § 23.201(b). The rate of speed reduction must be constant, and— (1) For a turning flight stall, may not exceed one knot per second; and (2) For an accelerated turning stall, be 3 to 5 knots per second with steadily increasing normal acceleration. (b) After the airplane has stalled, as defined in § 23.201(b), it must be possible to regain wings level flight by normal use of the flight controls, but without increasing power and without— (1) Excessive loss of altitude; (2) Undue pitchup; (3) Uncontrollable tendency to spin; (4) Exceeding a bank angle of 60 degrees in the original direction of the turn or 30 degrees in the opposite direction in the case of turning flight stalls; (5) Exceeding a bank angle of 90 degrees in the original direction of the <PRTPAGE P="184"/>turn or 60 degrees in the opposite direction in the case of accelerated turning stalls; and (6) Exceeding the maximum permissible speed or allowable limit load factor. (c) Compliance with the requirements of this section must be shown under the following conditions: (1) <E T="03">Wing flaps:</E> Retracted, fully extended, and each intermediate normal operating position; (2) <E T="03">Landing gear:</E> Retracted and extended; (3) <E T="03">Cowl flaps:</E> Appropriate to configuration; (4) <E T="03">Power:</E> (i) Power off; and (ii) 75 percent of maximum continuous power. However, if the power-to-weight ratio at 75 percent of maximum continuous power results in extreme nose-up attitudes, the test may be carried out with the power required for level flight in the landing configuration at maximum landing weight and a speed of 1.4 V<E T="52">SO</E>, except that the power may not be less than 50 percent of maximum continuous power. (5) <E T="03">Trim:</E> The airplane trimmed at a speed as near 1.5 V<E T="52">S1</E> as practicable. (6) <E T="03">Propeller.</E> Full increase rpm position for the power off condition. <CITA>[Amdt. 23-14, 38 FR 31820, Nov. 19, 1973, as amended by Amdt. 23-45, 58 FR 42159, Aug. 6, 1993; Amdt. 23-50, 61 FR 5191, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.207</SECTNO> <SUBJECT>Stall warning.</SUBJECT> (a) There must be a clear and distinctive stall warning, with the flaps and landing gear in any normal position, in straight and turning flight. (b) The stall warning may be furnished either through the inherent aerodynamic qualities of the airplane or by a device that will give clearly distinguishable indications under expected conditions of flight. However, a visual stall warning device that requires the attention of the crew within the cockpit is not acceptable by itself. (c) During the stall tests required by § 23.201(b) and § 23.203(a)(1), the stall warning must begin at a speed exceeding the stalling speed by a margin of not less than 5 knots and must continue until the stall occurs. (d) When following procedures furnished in accordance with § 23.1585, the stall warning must not occur during a takeoff with all engines operating, a takeoff continued with one engine inoperative, or during an approach to landing. (e) During the stall tests required by § 23.203(a)(2), the stall warning must begin sufficiently in advance of the stall for the stall to be averted by pilot action taken after the stall warning first occurs. (f) For acrobatic category airplanes, an artificial stall warning may be mutable, provided that it is armed automatically during takeoff and rearmed automatically in the approach configuration. <CITA>[Amdt. 23-7, 34 FR 13087, Aug. 13, 1969, as amended by Amdt. 23-45, 58 FR 42159, Aug. 6, 1993; Amdt. 23-50, 61 FR 5191, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Spinning</HD> <SECTION> <SECTNO>§ 23.221</SECTNO> <SUBJECT>Spinning.</SUBJECT> (a) <E T="03">Normal category airplanes.</E> A single-engine, normal category airplane must be able to recover from a one-turn spin or a three-second spin, whichever takes longer, in not more than one additional turn after initiation of the first control action for recovery, or demonstrate compliance with the optional spin resistant requirements of this section. (1) The following apply to one turn or three second spins: (i) For both the flaps-retracted and flaps-extended conditions, the applicable airspeed limit and positive limit maneuvering load factor must not be exceeded; (ii) No control forces or characteristic encountered during the spin or recovery may adversely affect prompt recovery; (iii) It must be impossible to obtain unrecoverable spins with any use of the flight or engine power controls either at the entry into or during the spin; and (iv) For the flaps-extended condition, the flaps may be retracted during the recovery but not before rotation has ceased. (2) At the applicant's option, the airplane may be demonstrated to be spin resistant by the following: (i) During the stall maneuver contained in § 23.201, the pitch control <PRTPAGE P="185"/>must be pulled back and held against the stop. Then, using ailerons and rudders in the proper direction, it must be possible to maintain wings-level flight within 15 degrees of bank and to roll the airplane from a 30 degree bank in one direction to a 30 degree bank in the other direction; (ii) Reduce the airplane speed using pitch control at a rate of approximately one knot per second until the pitch control reaches the stop; then, with the pitch control pulled back and held against the stop, apply full rudder control in a manner to promote spin entry for a period of seven seconds or through a 360 degree heading change, whichever occurs first. If the 360 degree heading change is reached first, it must have taken no fewer than four seconds. This maneuver must be performed first with the ailerons in the neutral position, and then with the ailerons deflected opposite the direction of turn in the most adverse manner. Power and airplane configuration must be set in accordance with § 23.201(e) without change during the maneuver. At the end of seven seconds or a 360 degree heading change, the airplane must respond immediately and normally to primary flight controls applied to regain coordinated, unstalled flight without reversal of control effect and without exceeding the temporary control forces specified by § 23.143(c); and (iii) Compliance with §§ 23.201 and 23.203 must be demonstrated with the airplane in uncoordinated flight, corresponding to one ball width displacement on a slip-skid indicator, unless one ball width displacement cannot be obtained with full rudder, in which case the demonstration must be with full rudder applied. (b) <E T="03">Utility category airplanes.</E> A utility category airplane must meet the requirements of paragraph (a) of this section. In addition, the requirements of paragraph (c) of this section and § 23.807(b)(7) must be met if approval for spinning is requested. (c) <E T="03">Acrobatic category airplanes.</E> An acrobatic category airplane must meet the spin requirements of paragraph (a) of this section and § 23.807(b)(6). In addition, the following requirements must be met in each configuration for which approval for spinning is requested: (1) The airplane must recover from any point in a spin up to and including six turns, or any greater number of turns for which certification is requested, in not more than one and one-half additional turns after initiation of the first control action for recovery. However, beyond three turns, the spin may be discontinued if spiral characteristics appear. (2) The applicable airspeed limits and limit maneuvering load factors must not be exceeded. For flaps-extended configurations for which approval is requested, the flaps must not be retracted during the recovery. (3) It must be impossible to obtain unrecoverable spins with any use of the flight or engine power controls either at the entry into or during the spin. (4) There must be no characteristics during the spin (such as excessive rates of rotation or extreme oscillatory motion) that might prevent a successful recovery due to disorientation or incapacitation of the pilot. <CITA>[Doc. No. 27807, 61 FR 5191, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ground and Water Handling Characteristics</HD> <SECTION> <SECTNO>§ 23.231</SECTNO> <SUBJECT>Longitudinal stability and control.</SUBJECT> (a) A landplane may have no uncontrollable tendency to nose over in any reasonably expected operating condition, including rebound during landing or takeoff. Wheel brakes must operate smoothly and may not induce any undue tendency to nose over. (b) A seaplane or amphibian may not have dangerous or uncontrollable porpoising characteristics at any normal operating speed on the water. </SECTION> <SECTION> <SECTNO>§ 23.233</SECTNO> <SUBJECT>Directional stability and control.</SUBJECT> (a) A 90 degree cross-component of wind velocity, demonstrated to be safe for taxiing, takeoff, and landing must be established and must be not less than 0.2 V<E T="52">SO</E>. (b) The airplane must be satisfactorily controllable in power-off landings at normal landing speed, without using brakes or engine power to maintain a straight path until the speed has decreased to at least 50 percent of the speed at touchdown.<PRTPAGE P="186"/> (c) The airplane must have adequate directional control during taxiing. (d) Seaplanes must demonstrate satisfactory directional stability and control for water operations up to the maximum wind velocity specified in paragraph (a) of this section. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42159, Aug. 6, 1993; Amdt. 23-50, 61 FR 5192, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.235</SECTNO> <SUBJECT>Operation on unpaved surfaces.</SUBJECT> The airplane must be demonstrated to have satisfactory characteristics and the shock-absorbing mechanism must not damage the structure of the airplane when the airplane is taxied on the roughest ground that may reasonably be expected in normal operation and when takeoffs and landings are performed on unpaved runways having the roughest surface that may reasonably be expected in normal operation. <CITA>[Doc. No. 27807, 61 FR 5192, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.237</SECTNO> <SUBJECT>Operation on water.</SUBJECT> A wave height, demonstrated to be safe for operation, and any necessary water handling procedures for seaplanes and amphibians must be established. <CITA>[Doc. No. 27807, 61 FR 5192, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.239</SECTNO> <SUBJECT>Spray characteristics.</SUBJECT> Spray may not dangerously obscure the vision of the pilots or damage the propellers or other parts of a seaplane or amphibian at any time during taxiing, takeoff, and landing. </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Miscellaneous Flight Requirements</HD> <SECTION> <SECTNO>§ 23.251</SECTNO> <SUBJECT>Vibration and buffeting.</SUBJECT> There must be no vibration or buffeting severe enough to result in structural damage, and each part of the airplane must be free from excessive vibration, under any appropriate speed and power conditions up to V<E T="52">D</E>/M<E T="52">D</E>. In addition, there must be no buffeting in any normal flight condition severe enough to interfere with the satisfactory control of the airplane or cause excessive fatigue to the flight crew. Stall warning buffeting within these limits is allowable. <CITA>[Doc. No. 26269, 58 FR 42159, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.253</SECTNO> <SUBJECT>High speed characteristics.</SUBJECT> If a maximum operating speed <E T="03">V</E> <E T="24">MO</E> <E T="03">/M</E> <E T="24">MO</E> is established under § 23.1505(c), the following speed increase and recovery characteristics must be met: (a) Operating conditions and characteristics likely to cause inadvertent speed increases (including upsets in pitch and roll) must be simulated with the airplane trimmed at any likely speed up to V<E T="52">MO</E>/M<E T="52">MO</E>. These conditions and characteristics include gust upsets, inadvertent control movements, low stick force gradients in relation to control friction, passenger movement, leveling off from climb, and descent from Mach to airspeed limit altitude. (b) Allowing for pilot reaction time after occurrence of the effective inherent or artificial speed warning specified in § 23.1303, it must be shown that the airplane can be recovered to a normal attitude and its speed reduced to V<E T="52">MO</E>/M<E T="52">MO</E>, without— (1) Exceeding <E T="03">V</E> <E T="24">D</E> <E T="03">/M</E> <E T="24">D</E>, the maximum speed shown under § 23.251, or the structural limitations; or (2) Buffeting that would impair the pilot's ability to read the instruments or to control the airplane for recovery. (c) There may be no control reversal about any axis at any speed up to the maximum speed shown under § 23.251. Any reversal of elevator control force or tendency of the airplane to pitch, roll, or yaw must be mild and readily controllable, using normal piloting techniques. <CITA>[Amdt. 23-7, 34 FR 13087, Aug. 13, 1969; as amended by Amdt. 23-26, 45 FR 60170, Sept. 11, 1980; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993; Amdt. 23-50, 61 FR 5192, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Structure</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTION> <SECTNO>§ 23.301</SECTNO> <SUBJECT>Loads.</SUBJECT> (a) Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety). Unless otherwise provided, prescribed loads are limit loads. (b) Unless otherwise provided, the air, ground, and water loads must be placed in equilibrium with inertia forces, considering each item of mass <PRTPAGE P="187"/>in the airplane. These loads must be distributed to conservatively approximate or closely represent actual conditions. Methods used to determine load intensities and distribution on canard and tandem wing configurations must be validated by flight test measurement unless the methods used for determining those loading conditions are shown to be reliable or conservative on the configuration under consideration. (c) If deflections under load would significantly change the distribution of external or internal loads, this redistribution must be taken into account. (d) Simplified structural design criteria may be used if they result in design loads not less than those prescribed in §§ 23.331 through 23.521. For airplane configurations described in appendix A, § 23.1, the design criteria of appendix A of this part are an approved equivalent of §§ 23.321 through 23.459. If appendix A of this part is used, the entire appendix must be substituted for the corresponding sections of this part. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-28, 47 FR 13315, Mar. 29, 1982; Amdt. 23-42, 56 FR 352, Jan. 3, 1991; Amdt. 23-48, 61 FR 5143, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.302</SECTNO> <SUBJECT>Canard or tandem wing configurations.</SUBJECT> The forward structure of a canard or tandem wing configuration must: (a) Meet all requirements of subpart C and subpart D of this part applicable to a wing; and (b) Meet all requirements applicable to the function performed by these surfaces. <CITA>[Amdt. 23-42, 56 FR 352, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.303</SECTNO> <SUBJECT>Factor of safety.</SUBJECT> Unless otherwise provided, a factor of safety of 1.5 must be used. </SECTION> <SECTION> <SECTNO>§ 23.305</SECTNO> <SUBJECT>Strength and deformation.</SUBJECT> (a) The structure must be able to support limit loads without detrimental, permanent deformation. At any load up to limit loads, the deformation may not interfere with safe operation. (b) The structure must be able to support ultimate loads without failure for at least three seconds, except local failures or structural instabilities between limit and ultimate load are acceptable only if the structure can sustain the required ultimate load for at least three seconds. However when proof of strength is shown by dynamic tests simulating actual load conditions, the three second limit does not apply. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.307</SECTNO> <SUBJECT>Proof of structure.</SUBJECT> (a) Compliance with the strength and deformation requirements of § 23.305 must be shown for each critical load condition. Structural analysis may be used only if the structure conforms to those for which experience has shown this method to be reliable. In other cases, substantiating load tests must be made. Dynamic tests, including structural flight tests, are acceptable if the design load conditions have been simulated. (b) Certain parts of the structure must be tested as specified in Subpart D of this part. </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Flight Loads</HD> <SECTION> <SECTNO>§ 23.321</SECTNO> <SUBJECT>General.</SUBJECT> (a) Flight load factors represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of the airplane) to the weight of the airplane. A positive flight load factor is one in which the aerodynamic force acts upward, with respect to the airplane. (b) Compliance with the flight load requirements of this subpart must be shown— (1) At each critical altitude within the range in which the airplane may be expected to operate; (2) At each weight from the design minimum weight to the design maximum weight; and (3) For each required altitude and weight, for any practicable distribution of disposable load within the operating limitations specified in §§ 23.1583 through 23.1589. (c) When significant, the effects of compressibility must be taken into account. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <PRTPAGE P="188"/> <SECTNO>§ 23.331</SECTNO> <SUBJECT>Symmetrical flight conditions.</SUBJECT> (a) The appropriate balancing horizontal tail load must be accounted for in a rational or conservative manner when determining the wing loads and linear inertia loads corresponding to any of the symmetrical flight conditions specified in §§ 23.333 through 23.341. (b) The incremental horizontal tail loads due to maneuvering and gusts must be reacted by the angular inertia of the airplane in a rational or conservative manner. (c) Mutual influence of the aerodynamic surfaces must be taken into account when determining flight loads. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-42, 56 FR 352, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.333</SECTNO> <SUBJECT>Flight envelope.</SUBJECT> (a) <E T="03">General.</E> Compliance with the strength requirements of this subpart must be shown at any combination of airspeed and load factor on and within the boundaries of a flight envelope (similar to the one in paragraph (d) of this section) that represents the envelope of the flight loading conditions specified by the maneuvering and gust criteria of paragraphs (b) and (c) of this section respectively. (b) <E T="03">Maneuvering envelope.</E> Except where limited by maximum (static) lift coefficients, the airplane is assumed to be subjected to symmetrical maneuvers resulting in the following limit load factors: (1) The positive maneuvering load factor specified in § 23.337 at speeds up to <E T="03">V</E> <E T="24">D</E>; (2) The negative maneuvering load factor specified in § 23.337 at <E T="03">V</E> <E T="24">C</E>; and (3) Factors varying linearly with speed from the specified value at <E T="03">V</E> <E T="24">C</E> to 0.0 at <E T="03">V</E> <E T="24">D</E> for the normal and commuter category, and —1.0 at <E T="03">V</E> <E T="24">D</E> for the acrobatic and utility categories. (c) <E T="03">Gust envelope.</E> (1) The airplane is assumed to be subjected to symmetrical vertical gusts in level flight. The resulting limit load factors must correspond to the conditions determined as follows: (i) Positive (up) and negative (down) gusts of 50 f.p.s. at <E T="03">V</E> <E T="24">C</E> must be considered at altitudes between sea level and 20,000 feet. The gust velocity may be reduced linearly from 50 f.p.s. at 20,000 feet to 25 f.p.s. at 50,000 feet. (ii) Positive and negative gusts of 25 f.p.s. at <E T="03">V</E> <E T="24">D</E> must be considered at altitudes between sea level and 20,000 feet. The gust velocity may be reduced linearly from 25 f.p.s. at 20,000 feet to 12.5 f.p.s. at 50,000 feet. (iii) In addition, for commuter category airplanes, positive (up) and negative (down) rough air gusts of 66 f.p.s. at V<E T="64">Β</E> must be considered at altitudes between sea level and 20,000 feet. The gust velocity may be reduced linearly from 66 f.p.s. at 20,000 feet to 38 f.p.s. at 50,000 feet. (2) The following assumptions must be made: (i) The shape of the gust is— <MATH DEEP="30" SPAN="1"> <MID>EC28SE91.000</MID> </MATH> <EXTRACT> <FP>Where—</FP> </EXTRACT> <FP SOURCE="FP-2"> <E T="03">s</E> =Distance penetrated into gust (ft.);</FP> <FP SOURCE="FP-2"> <E T="03">C</E> =Mean geometric chord of wing (ft.); and</FP> <FP SOURCE="FP-2"> <E T="03">Ude</E> =Derived gust velocity referred to in subparagraph (1) of this section.</FP> (ii) Gust load factors vary linearly with speed between <E T="03">V</E> <E T="24">C</E> and <E T="03">V</E> <E T="24">D</E> . (d) <E T="03">Flight envelope.</E> <GPH DEEP="196" SPAN="2"> <PRTPAGE P="189"/> <GID>EC28SE91.001</GID> </GPH> <CITA TYPE="W">[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13087, Aug. 13, 1969; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.335</SECTNO> <SUBJECT>Design airspeeds.</SUBJECT> Except as provided in paragraph (a)(4) of this section, the selected design airspeeds are equivalent airspeeds (EAS). (a) <E T="03">Design cruising speed, V</E> <E T="24">C</E> <E T="11">.</E> For <E T="03">V</E> <E T="24">C</E> the following apply: (1) Where W/S′=wing loading at the design maximum takeoff weight, V<E T="52">c</E> (in knots) may not be less than— (i) 33 |(W/S) (for normal, utility, and commuter category airplanes); (ii) 36 |(W/S) (for acrobatic category airplanes). (2) For values of <E T="03">W/S</E> more than 20, the multiplying factors may be decreased linearly with <E T="03">W/S</E> to a value of 28.6 where <E T="03">W/S</E> =100. (3) <E T="03">V</E> <E T="24">C</E> need not be more than 0.9 <E T="03">V</E> <E T="24">H</E> at sea level. (4) At altitudes where an <E T="03">M</E> <E T="24">D</E> is established, a cruising speed <E T="03">M</E> <E T="24">C</E> limited by compressibility may be selected. (b) <E T="03">Design dive speed V</E> <E T="24">D</E>. For <E T="03">V</E> <E T="24">D</E>, the following apply: (1) <E T="03">V</E> <E T="24">D</E>/M<E T="24">D</E> may not be less than 1.25 <E T="03">V</E> <E T="24">C</E>/M<E T="24">C</E>; and (2) With <E T="03">V</E> <E T="24">C min,</E> the required minimum design cruising speed, <E T="03">V</E> <E T="24">D</E> (in knots) may not be less than— (i) 1.40 V<E T="52">c</E> <E T="03">min</E> (for normal and commuter category airplanes); (ii) 1.50 <E T="03">V</E> <E T="24">C min</E> (for utility category airplanes); and (iii) 1.55 <E T="03">V</E> <E T="24">C min</E> (for acrobatic category airplanes). (3) For values of <E T="03">W/S</E> more than 20, the multiplying factors in paragraph (b)(2) of this section may be decreased linearly with <E T="03">W/S</E> to a value of 1.35 where <E T="03">W/S=100.</E> (4) Compliance with paragraphs (b)(1) and (2) of this section need not be shown if <E T="03">V</E> <E T="24">D</E> <E T="03">/M</E> <E T="24">D</E> is selected so that the minimum speed margin between <E T="03">V</E> <E T="24">C</E> <E T="03">/M</E> <E T="24">C</E> and <E T="03">V</E> <E T="24">D</E> <E T="03">/M</E> <E T="24">D</E> is the greater of the following: (i) The speed increase resulting when, from the initial condition of stabilized flight at <E T="03">V</E> <E T="24">C</E> <E T="03">/M</E> <E T="24">C</E>, the airplane is assumed to be upset, flown for 20 seconds along a flight path 7.5° below the initial path, and then pulled up with a load factor of 1.5 (0.5 <E T="03">g.</E> acceleration increment). At least 75 percent maximum continuous power for reciprocating engines, and maximum cruising power for turbines, or, if less, the power required for <E T="03">V</E> <E T="24">C</E>/<E T="03">M</E> <E T="24">C</E> for both kinds of engines, must be assumed until the pullup is initiated, at which point power reduction and pilot-controlled drag devices may be used; and either—<PRTPAGE P="190"/> (ii) Mach 0.05 for normal, utility, and acrobatic category airplanes (at altitudes where M<E T="52">D</E> is established); or (iii) Mach 0.07 for commuter category airplanes (at altitudes where M<E T="52">D</E> is established) unless a rational analysis, including the effects of automatic systems, is used to determine a lower margin. If a rational analysis is used, the minimum speed margin must be enough to provide for atmospheric variations (such as horizontal gusts), and the penetration of jet streams or cold fronts), instrument errors, airframe production variations, and must not be less than Mach 0.05. (c) <E T="03">Design maneuvering speed V</E> <E T="24">A.</E> For <E T="03">V</E> <E T="24">A</E>, the following applies: (1) <E T="03">V</E> <E T="24">A</E> may not be less than <E T="03">V</E> <E T="24">S</E>|<E T="13">n</E> <E T="01">where—</E> (i) <E T="03">V</E> <E T="24">S</E> is a computed stalling speed with flaps retracted at the design weight, normally based on the maximum airplane normal force coefficients, <E T="03">C</E> <E T="24">NA</E> <E T="03">;</E> and (ii) <E T="03">n</E> is the limit maneuvering load factor used in design (2) The value of <E T="03">V</E> <E T="24">A</E> need not exceed the value of <E T="03">V</E> <E T="24">C</E> used in design. (d) <E T="03">Design speed for maximum gust intensity, V</E> <E T="54">B</E>. For V<E T="54">B</E>, the following apply: (1) V<E T="52">B</E> may not be less than the speed determined by the intersection of the line representing the maximum positive lift, C<E T="52">NMAX</E>, and the line representing the rough air gust velocity on the gust V-n diagram, or V<E T="52">S1</E>|n<E T="52">g,</E> whichever is less, where: (i) n<E T="54">g</E> the positive airplane gust load factor due to gust, at speed V<E T="54">C</E> (in accordance with § 23.341), and at the particular weight under consideration; and (ii) V<E T="54">S1</E> is the stalling speed with the flaps retracted at the particular weight under consideration. (2) V<E T="54">B</E> need not be greater than V<E T="54">C</E>. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13088, Aug. 13, 1969; Amdt. 23-16, 40 FR 2577, Jan. 14, 1975; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987; Amdt. 23-24, 52 FR 34745, Sept. 14, 1987; Amdt. 23-48, 61 FR 5143, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.337</SECTNO> <SUBJECT>Limit maneuvering load factors.</SUBJECT> (a) The positive limit maneuvering load factor <E T="03">n</E> may not be less than— (1) 2.1+(24,000÷(W+10,000)) for normal and commuter category airplanes, where W=design maximum takeoff weight, except that n need not be more than 3.8; (2) 4.4 for utility category airplanes; or (3) 6.0 for acrobatic category airplanes. (b) The negative limit maneuvering load factor may not be less than— (1) 0.4 times the positive load factor for the normal utility and commuter categories; or (2) 0.5 times the positive load factor for the acrobatic category. (c) Maneuvering load factors lower than those specified in this section may be used if the airplane has design features that make it impossible to exceed these values in flight. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13088, Aug. 13, 1969; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987; Amdt. 23-48, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.341</SECTNO> <SUBJECT>Gust loads factors.</SUBJECT> (a) Each airplane must be designed to withstand loads on each lifting surface resulting from gusts specified in § 23.333(c). (b) The gust load for a canard or tandem wing configuration must be computed using a rational analysis, or may be computed in accordance with paragraph (c) of this section, provided that the resulting net loads are shown to be conservative with respect to the gust criteria of § 23.333(c). (c) In the absence of a more rational analysis, the gust load factors must be computed as follows— <MATH DEEP="30" SPAN="1"> <MID>ER09FE96.010</MID> </MATH> <EXTRACT> <FP>Where—</FP> <FP SOURCE="FP-2"> <E T="03">K</E> <E T="22">g</E> <E T="03">=0.88</E> <E T="21">μ</E> <E T="22">g</E>/5.3+<E T="21">μ</E> <E T="22">g</E>=gust alleviation factor;</FP> <FP SOURCE="FP-2"> <E T="21">μ</E> <E T="22">g</E>=2(W/S)/<E T="22">ρ</E> Cag=<E T="01">airplane mass ratio;</E> </FP> <FP SOURCE="FP-2"> <E T="03">U</E> <E T="24">de</E>=<E T="01">Derived gust velocities referred to in § 23.333(c) (f.p.s.);</E> </FP> <FP SOURCE="FP-2"> <E T="22">ρ</E>=Density of air (slugs/cu.ft.);</FP> <FP SOURCE="FP-2"> <E T="03">W/S</E> =Wing loading (p.s.f.) due to the applicable weight of the airplane in the particular load case.</FP> <FP SOURCE="FP-2"> <E T="03">W/S</E> =Wing loading (p.s.f.);</FP> <FP SOURCE="FP-2"> <E T="03">C</E> =Mean geometric chord (ft.);</FP> <FP SOURCE="FP-2"> <E T="03">g</E> =Acceleration due to gravity (ft./sec.<E T="21"> 2</E>)</FP> <FP SOURCE="FP-2"> <E T="03">V</E> =Airplane equivalent speed (knots); and</FP> <FP SOURCE="FP-2"> <E T="03">a</E> =Slope of the airplane normal force coefficient curve <E T="03">C</E> <E T="24">NA</E> per radian if the gust <PRTPAGE P="191"/>loads are applied to the wings and horizontal tail surfaces simultaneously by a rational method. The wing lift curve slope <E T="03">C</E> <E T="24">L</E> per radian may be used when the gust load is applied to the wings only and the horizontal tail gust loads are treated as a separate condition. </FP> </EXTRACT> <CITA>[Amdt. 23-7, 34 FR 13088, Aug. 13, 1969, as amended by Amdt. 23-42, 56 FR 352, Jan. 3, 1991; Amdt. 23-48, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.343</SECTNO> <SUBJECT>Design fuel loads.</SUBJECT> (a) The disposable load combinations must include each fuel load in the range from zero fuel to the selected maximum fuel load. (b) If fuel is carried in the wings, the maximum allowable weight of the airplane without any fuel in the wing tank(s) must be established as “maximum zero wing fuel weight,” if it is less than the maximum weight. (c) For commuter category airplanes, a structural reserve fuel condition, not exceeding fuel necessary for 45 minutes of operation at maximum continuous power, may be selected. If a structural reserve fuel condition is selected, it must be used as the minimum fuel weight condition for showing compliance with the flight load requirements prescribed in this part and— (1) The structure must be designed to withstand a condition of zero fuel in the wing at limit loads corresponding to: (i) Ninety percent of the maneuvering load factors defined in § 23.337, and (ii) Gust velocities equal to 85 percent of the values prescribed in § 23.333(c). (2) The fatigue evaluation of the structure must account for any increase in operating stresses resulting from the design condition of paragraph (c)(1) of this section. (3) The flutter, deformation, and vibration requirements must also be met with zero fuel in the wings. <CITA>[Doc. No. 27805, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.345</SECTNO> <SUBJECT>High lift devices.</SUBJECT> (a) If flaps or similar high lift devices are to be used for takeoff, approach or landing, the airplane, with the flaps fully extended at V<E T="52">F</E>, is assumed to be subjected to symmetrical maneuvers and gusts within the range determined by— (1) Maneuvering, to a positive limit load factor of 2.0; and (2) Positive and negative gust of 25 feet per second acting normal to the flight path in level flight. (b) V<E T="52">F</E> must be assumed to be not less than 1.4 V<E T="52">S</E> or 1.8 V<E T="52">SF</E>, whichever is greater, where— (1) V<E T="52">S</E> is the computed stalling speed with flaps retracted at the design weight; and (2) V<E T="52">SF</E> is the computed stalling speed with flaps fully extended at the design weight. (3) If an automatic flap load limiting device is used, the airplane may be designed for the critical combinations of airspeed and flap position allowed by that device. (c) In determining external loads on the airplane as a whole, thrust, slipstream, and pitching acceleration may be assumed to be zero. (d) The flaps, their operating mechanism, and their supporting structures, must be designed to withstand the conditions prescribed in paragraph (a) of this section. In addition, with the flaps fully extended at V<E T="52">F</E>, the following conditions, taken separately, must be accounted for: (1) A head-on gust having a velocity of 25 feet per second (EAS), combined with propeller slipstream corresponding to 75 percent of maximum continuous power; and (2) The effects of propeller slipstream corresponding to maximum takeoff power. <CITA>[Doc. No. 27805, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.347</SECTNO> <SUBJECT>Unsymmetrical flight conditions.</SUBJECT> (a) The airplane is assumed to be subjected to the unsymmetrical flight conditions of §§ 23.349 and 23.351. Unbalanced aerodynamic moments about the center of gravity must be reacted in a rational or conservative manner, considering the principal masses furnishing the reacting inertia forces. (b) Acrobatic category airplanes certified for flick maneuvers (snap roll) must be designed for additional asymmetric loads acting on the wing and the horizontal tail. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-48, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <PRTPAGE P="192"/> <SECTNO>§ 23.349</SECTNO> <SUBJECT>Rolling conditions.</SUBJECT> The wing and wing bracing must be designed for the following loading conditions: (a) Unsymmetrical wing loads appropriate to the category. Unless the following values result in unrealistic loads, the rolling accelerations may be obtained by modifying the symmetrical flight conditions in § 23.333(d) as follows: (1) For the acrobatic category, in conditions A and F, assume that 100 percent of the semispan wing airload acts on one side of the plane of symmetry and 60 percent of this load acts on the other side. (2) For normal, utility, and commuter categories, in Condition A, assume that 100 percent of the semispan wing airload acts on one side of the airplane and 75 percent of this load acts on the other side. (b) The loads resulting from the aileron deflections and speeds specified in § 23.455, in combination with an airplane load factor of at least two thirds of the positive maneuvering load factor used for design. Unless the following values result in unrealistic loads, the effect of aileron displacement on wing torsion may be accounted for by adding the following increment to the basic airfoil moment coefficient over the aileron portion of the span in the critical condition determined in § 23.333(d): <EXTRACT> <E T="21">Δ</E> <E T="03">c</E> <E T="24">m</E>=—0.01<E T="21">δ</E> <FP>where— </FP> </EXTRACT> <EXTRACT> <FP SOURCE="FP-1"> <E T="21">Δ</E> <E T="03">c</E> <E T="24">m</E> is the moment coefficient increment; and</FP> <FP SOURCE="FP-1"> <E T="21">δ</E> is the down aileron deflection in degrees in the critical condition.</FP> </EXTRACT> <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13088, Aug. 13, 1969; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987; Amdt. 23-48, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.351</SECTNO> <SUBJECT>Yawing conditions.</SUBJECT> The airplane must be designed for yawing loads on the vertical surfaces resulting from the loads specified in §§ 23.441 through 23.445. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-42, 56 FR 352, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.361</SECTNO> <SUBJECT>Engine torque.</SUBJECT> (a) Each engine mount and its supporting structure must be designed for the effects of— (1) A limit engine torque corresponding to takeoff power and propeller speed acting simultaneously with 75 percent of the limit loads from flight condition A of § 23.333(d); (2) A limit engine torque corresponding to maximum continuous power and propeller speed acting simultaneously with the limit loads from flight condition A of § 23.333(d); and (3) For turbopropeller installations, in addition to the conditions specified in paragraphs (a)(1) and (a)(2) of this section, a limit engine torque corresponding to takeoff power and propeller speed, multiplied by a factor accounting for propeller control system malfunction, including quick feathering, acting simultaneously with lg level flight loads. In the absence of a rational analysis, a factor of 1.6 must be used. (b) For turbine engine installations, the engine mounts and supporting structure must be designed to withstand each of the following: (1) A limit engine torque load imposed by sudden engine stoppage due to malfunction or structural failure (such as compressor jamming). (2) A limit engine torque load imposed by the maximum acceleration of the engine. (c) The limit engine torque to be considered under paragraph (a) of this section must be obtained by multiplying the mean torque by a factor of— (1) 1.25 for turbopropeller installations; (2) 1.33 for engines with five or more cylinders; and (3) Two, three, or four, for engines with four, three, or two cylinders, respectively. <CITA>[Amdt. 23-26, 45 FR 60171, Sept. 11, 1980, as amended by Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.363</SECTNO> <SUBJECT>Side load on engine mount.</SUBJECT> (a) Each engine mount and its supporting structure must be designed for a limit load factor in a lateral direction, for the side load on the engine mount, of not less than— (1) 1.33, or<PRTPAGE P="193"/> (2) One-third of the limit load factor for flight condition A. (b) The side load prescribed in paragraph (a) of this section may be assumed to be independent of other flight conditions. </SECTION> <SECTION> <SECTNO>§ 23.365</SECTNO> <SUBJECT>Pressurized cabin loads.</SUBJECT> For each pressurized compartment, the following apply: (a) The airplane structure must be strong enough to withstand the flight loads combined with pressure differential loads from zero up to the maximum relief valve setting. (b) The external pressure distribution in flight, and any stress concentrations, must be accounted for. (c) If landings may be made with the cabin pressurized, landing loads must be combined with pressure differential loads from zero up to the maximum allowed during landing. (d) The airplane structure must be strong enough to withstand the pressure differential loads corresponding to the maximum relief valve setting multiplied by a factor of 1.33, omitting other loads. (e) If a pressurized cabin has two or more compartments separated by bulkheads or a floor, the primary structure must be designed for the effects of sudden release of pressure in any compartment with external doors or windows. This condition must be investigated for the effects of failure of the largest opening in the compartment. The effects of intercompartmental venting may be considered. </SECTION> <SECTION> <SECTNO>§ 23.367</SECTNO> <SUBJECT>Unsymmetrical loads due to engine failure.</SUBJECT> (a) Turbopropeller airplanes must be designed for the unsymmetrical loads resulting from the failure of the critical engine including the following conditions in combination with a single malfunction of the propeller drag limiting system, considering the probable pilot corrective action on the flight controls: (1) At speeds between <E T="03">V</E> <E T="24">MC</E> and <E T="03">V</E> <E T="24">D,</E> the loads resulting from power failure because of fuel flow interruption are considered to be limit loads. (2) At speeds between <E T="03">V</E> <E T="24">MC</E> and <E T="03">V</E> <E T="24">C</E>, the loads resulting from the disconnection of the engine compressor from the turbine or from loss of the turbine blades are considered to be ultimate loads. (3) The time history of the thrust decay and drag buildup occurring as a result of the prescribed engine failures must be substantiated by test or other data applicable to the particular engine-propeller combination. (4) The timing and magnitude of the probable pilot corrective action must be conservatively estimated, considering the characteristics of the particular engine-propeller-airplane combination. (b) Pilot corrective action may be assumed to be initiated at the time maximum yawing velocity is reached, but not earlier than 2 seconds after the engine failure. The magnitude of the corrective action may be based on the limit pilot forces specified in § 23.397 except that lower forces may be assumed where it is shown by analysis or test that these forces can control the yaw and roll resulting from the prescribed engine failure conditions. <CITA>[Amdt. 23-7, 34 FR 13089, Aug. 13, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.369</SECTNO> <SUBJECT>Rear lift truss.</SUBJECT> (a) If a rear lift truss is used, it must be designed to withstand conditions of reversed airflow at a design speed of— V = 8.7 |(W/S) + 8.7 (knots), where W/S = wing loading at design maximum takeoff weight. (b) Either aerodynamic data for the particular wing section used, or a value of <E T="03">C</E> <E T="24">L</E> equalling −0.8 with a chordwise distribution that is triangular between a peak at the trailing edge and zero at the leading edge, must be used. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969; 34 FR 17509, Oct. 30, 1969; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993; Amdt. 23-48, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.371</SECTNO> <SUBJECT>Gyroscopic and aerodynamic loads.</SUBJECT> (a) Each engine mount and its supporting structure must be designed for the gyroscopic, inertial, and aerodynamic loads that result, with the engine(s) and propeller(s), if applicable, at maximum continuous r.p.m., under either: (1) The conditions prescribed in § 23.351 and § 23.423; or<PRTPAGE P="194"/> (2) All possible combinations of the following— (i) A yaw velocity of 2.5 radians per second; (ii) A pitch velocity of 1.0 radian per second; (iii) A normal load factor of 2.5; and (iv) Maximum continuous thrust. (b) For airplanes approved for aerobatic maneuvers, each engine mount and its supporting structure must meet the requirements of paragraph (a) of this section and be designed to withstand the load factors expected during combined maximum yaw and pitch velocities. (c) For airplanes certificated in the commuter category, each engine mount and its supporting structure must meet the requirements of paragraph (a) of this section and the gust conditions specified in § 23.341 of this part. <CITA>[Doc. No. 27805, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.373</SECTNO> <SUBJECT>Speed control devices.</SUBJECT> If speed control devices (such as spoilers and drag flaps) are incorporated for use in enroute conditions— (a) The airplane must be designed for the symmetrical maneuvers and gusts prescribed in §§ 23.333, 23.337, and 23.341, and the yawing maneuvers and lateral gusts in §§ 23.441 and 23.443, with the device extended at speeds up to the placard device extended speed; and (b) If the device has automatic operating or load limiting features, the airplane must be designed for the maneuver and gust conditions prescribed in paragraph (a) of this section at the speeds and corresponding device positions that the mechanism allows. <CITA>[Amdt. 23-7, 34 FR 13089, Aug. 13, 1969]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Control Surface and System Loads</HD> <SECTION> <SECTNO>§ 23.391</SECTNO> <SUBJECT>Control surface loads.</SUBJECT> The control surface loads specified in §§ 23.397 through 23.459 are assumed to occur in the conditions described in §§ 23.331 through 23.351. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-48, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.393</SECTNO> <SUBJECT>Loads parallel to hinge line.</SUBJECT> (a) Control surfaces and supporting hinge brackets must be designed to withstand inertial loads acting parallel to the hinge line. (b) In the absence of more rational data, the inertial loads may be assumed to be equal to KW, where— (1) K = 24 for vertical surfaces; (2) K = 12 for horizontal surfaces; and (3) W = weight of the movable surfaces. <CITA>[Doc. No. 27805, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.395</SECTNO> <SUBJECT>Control system loads.</SUBJECT> (a) Each flight control system and its supporting structure must be designed for loads corresponding to at least 125 percent of the computed hinge moments of the movable control surface in the conditions prescribed in §§ 23.391 through 23.459. In addition, the following apply: (1) The system limit loads need not exceed the higher of the loads that can be produced by the pilot and automatic devices operating the controls. However, autopilot forces need not be added to pilot forces. The system must be designed for the maximum effort of the pilot or autopilot, whichever is higher. In addition, if the pilot and the autopilot act in opposition, the part of the system between them may be designed for the maximum effort of the one that imposes the lesser load. Pilot forces used for design need not exceed the maximum forces prescribed in § 23.397(b). (2) The design must, in any case, provide a rugged system for service use, considering jamming, ground gusts, taxiing downwind, control inertia, and friction. Compliance with this subparagraph may be shown by designing for loads resulting from application of the minimum forces prescribed in § 23.397(b). (b) A 125 percent factor on computed hinge moments must be used to design elevator, aileron, and rudder systems. However, a factor as low as 1.0 may be used if hinge moments are based on accurate flight test data, the exact reduction depending upon the accuracy and reliability of the data. (c) Pilot forces used for design are assumed to act at the appropriate control <PRTPAGE P="195"/>grips or pads as they would in flight, and to react at the attachments of the control system to the control surface horns. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.397</SECTNO> <SUBJECT>Limit control forces and -torques.</SUBJECT> (a) In the control surface flight loading condition, the airloads on movable surfaces and the corresponding deflections need not exceed those that would result in flight from the application of any pilot force within the ranges specified in paragraph (b) of this section. In applying this criterion, the effects of control system boost and servo-mechanisms, and the effects of tabs must be considered. The automatic pilot effort must be used for design if it alone can produce higher control surface loads than the human pilot. (b) The limit pilot forces and -torques are as follows: <GPOTABLE CDEF="s65,r40,r30" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Control</CHED> <CHED H="1">Maximum forces or torques for design weight, weight equal to or less than 5,000 pounds <SU>1</SU> </CHED> <CHED H="1">Minimum forces or torques <SU>2</SU> </CHED> </BOXHD> <ROW> <ENT I="11">Aileron:</ENT> </ROW> <ROW> <ENT I="02">Stick</ENT> <ENT>67 lbs</ENT> <ENT>40 lbs.</ENT> </ROW> <ROW> <ENT I="02">Wheel <SU>3</SU> </ENT> <ENT>50 D in.-lbs <SU>4</SU> </ENT> <ENT>40 D in.-lbs.<SU>4</SU> </ENT> </ROW> <ROW> <ENT I="11">Elevator:</ENT> </ROW> <ROW> <ENT I="02">Stick</ENT> <ENT>167 lbs</ENT> <ENT>100 lbs.</ENT> </ROW> <ROW> <ENT I="02">Wheel (symmetrical)</ENT> <ENT>200 lbs </ENT> <ENT>100 lbs.</ENT> </ROW> <ROW> <ENT I="02">Wheel (unsymmetrical) <SU>5</SU> </ENT> <ENT/> <ENT>100 lbs.</ENT> </ROW> <ROW> <ENT I="01">Rudder</ENT> <ENT>200 lbs</ENT> <ENT>150 lbs.</ENT> </ROW> <TNOTE> <SU>1</SU> For design weight <E T="03">(W)</E> more than 5,000 pounds, the specified maximum values must be increased linearly with weight to 1.18 times the specified values at a design weight of 12,500 pounds and for commuter category airplanes, the specified values must be increased linearly with weight to 1.35 times the specified values at a design weight of 19,000 pounds.</TNOTE> <TNOTE> <SU>2</SU> If the design of any individual set of control systems or surfaces makes these specified minimum forces or torques inapplicable, values corresponding to the present hinge moments obtained under § 23.415, but not less than 0.6 of the specified minimum forces or torques, may be used.</TNOTE> <TNOTE> <SU>3</SU> The critical parts of the aileron control system must also be designed for a single tangential force with a limit value of 1.25 times the couple force determined from the above criteria.</TNOTE> <TNOTE> <SU>4</SU> D=wheel diameter (inches).</TNOTE> <TNOTE> <SU>5</SU> The unsymmetrical force must be applied at one of the normal handgrip points on the control wheel.</TNOTE> </GPOTABLE> <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969; Amdt. 23-17, 41 FR 55464, Dec. 20, 1976; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.399</SECTNO> <SUBJECT>Dual control system.</SUBJECT> (a) Each dual control system must be designed to withstand the force of the pilots operating in opposition, using individual pilot forces not less than the greater of— (1) 0.75 times those obtained under § 23.395; or (2) The minimum forces specified in § 23.397(b). (b) Each dual control system must be designed to withstand the force of the pilots applied together, in the same direction, using individual pilot forces not less than 0.75 times those obtained under § 23.395. <CITA>[Doc. No. 27805, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.405</SECTNO> <SUBJECT>Secondary control system.</SUBJECT> Secondary controls, such as wheel brakes, spoilers, and tab controls, must be designed for the maximum forces that a pilot is likely to apply to those controls. </SECTION> <SECTION> <SECTNO>§ 23.407</SECTNO> <SUBJECT>Trim tab effects.</SUBJECT> The effects of trim tabs on the control surface design conditions must be accounted for only where the surface loads are limited by maximum pilot effort. In these cases, the tabs are considered to be deflected in the direction that would assist the pilot. These deflections must correspond to the maximum degree of “out of trim” expected at the speed for the condition under consideration. </SECTION> <SECTION> <SECTNO>§ 23.409</SECTNO> <SUBJECT>Tabs.</SUBJECT> Control surface tabs must be designed for the most severe combination of airspeed and tab deflection likely to be obtained within the flight envelope for any usable loading condition. </SECTION> <SECTION> <SECTNO>§ 23.415</SECTNO> <SUBJECT>Ground gust conditions.</SUBJECT> (a) The control system must be investigated as follows for control surface loads due to ground gusts and taxiing downwind: (1) If an investigation of the control system for ground gust loads is not required by paragraph (a)(2) of this section, but the applicant elects to design a part of the control system of these loads, these loads need only be carried from control surface horns through the <PRTPAGE P="196"/>nearest stops or gust locks and their supporting structures. (2) If pilot forces less than the minimums specified in § 23.397(b) are used for design, the effects of surface loads due to ground gusts and taxiing downwind must be investigated for the entire control system according to the formula: <FP SOURCE="FP-2">H = K c S q</FP> <FP SOURCE="FP-2">where—</FP> <FP SOURCE="FP-2">H = limit hinge moment (ft.-lbs.);</FP> <FP SOURCE="FP-2">c = mean chord of the control surface aft of the hinge line (ft.);</FP> <FP SOURCE="FP-2">S = area of control surface aft of the hinge line (sq. ft.);</FP> <FP SOURCE="FP-2">q = dynamic pressure (p.s.f.) based on a design speed not less than 14.6 |(W/S) + 14.6 (f.p.s.) where W/S = wing loading at design maximum weight, except that the design speed need not exceed 88 (f.p.s.);</FP> <FP SOURCE="FP-2">K = limit hinge moment factor for ground gusts derived in paragraph (b) of this section. (For ailerons and elevators, a positive value of K indicates a moment tending to depress the surface and a negative value of K indicates a moment tending to raise the surface).</FP> (b) The limit hinge moment factor <E T="03">K</E> for ground gusts must be derived as follows: <GPOTABLE CDEF="xs45,6,r50" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Surface</CHED> <CHED H="1"> <E T="03">K</E> </CHED> <CHED H="1">Position of controls</CHED> </BOXHD> <ROW> <ENT I="01">(a) Aileron</ENT> <ENT>0.75 </ENT> <ENT>Control column locked lashed in mid-position.</ENT> </ROW> <ROW> <ENT I="01">(b) Aileron</ENT> <ENT> <E T="21">±</E>0.50</ENT> <ENT>Ailerons at full throw; + moment on one aileron, − moment on the other.</ENT> </ROW> <ROW> <ENT I="01">(c) Elevator</ENT> <ENT> <E T="21">±</E>0.75</ENT> <ENT>(c) Elevator full up (−).</ENT> </ROW> <ROW> <ENT I="01">(d) Elevator</ENT> <ENT/> <ENT>(d) Elevator full down (+).</ENT> </ROW> <ROW> <ENT I="01">(e) Rudder</ENT> <ENT> <E T="21">±</E>0.75</ENT> <ENT>(e) Rudder in neutral.</ENT> </ROW> <ROW> <ENT I="01">(f) Rudder</ENT> <ENT/> <ENT>(f) Rudder at full throw.</ENT> </ROW> </GPOTABLE> (c) At all weights between the empty weight and the maximum weight declared for tie-down stated in the appropriate manual, any declared tie-down points and surrounding structure, control system, surfaces and associated gust locks, must be designed to withstand the limit load conditions that exist when the airplane is tied down and that result from wind speeds of up to 65 knots horizontally from any direction. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993; Amdt. 23-48, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Horizontal Stabilizing and Balancing Surfaces</HD> <SECTION> <SECTNO>§ 23.421</SECTNO> <SUBJECT>Balancing loads.</SUBJECT> (a) A horizontal surface balancing load is a load necessary to maintain equilibrium in any specified flight condition with no pitching acceleration. (b) Horizontal balancing surfaces must be designed for the balancing loads occurring at any point on the limit maneuvering envelope and in the flap conditions specified in § 23.345. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969; Amdt. 23-42, 56 FR 352, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.423</SECTNO> <SUBJECT>Maneuvering loads.</SUBJECT> Each horizontal surface and its supporting structure, and the main wing of a canard or tandem wing configuration, if that surface has pitch control, must be designed for the maneuvering loads imposed by the following conditions: (a) A sudden movement of the pitching control, at the speed V<E T="52">A</E>, to the maximum aft movement, and the maximum forward movement, as limited by the control stops, or pilot effort, whichever is critical. (b) A sudden aft movement of the pitching control at speeds above V<E T="52">A</E>, followed by a forward movement of the pitching control resulting in the following combinations of normal and angular acceleration: <GPOTABLE CDEF="s50,xls28,xls64" COLS="3" OPTS="L2,i1"> <BOXHD> <CHED H="1">Condition</CHED> <CHED H="1">Normal acceleration (n)</CHED> <CHED H="1">Angular acceleration (radian/sec<E T="52">2</E>)</CHED> </BOXHD> <ROW> <ENT I="01">Nose-up pitching</ENT> <ENT>1.0</ENT> <ENT>+39n<E T="52">m</E>÷V×(n<E T="52">m</E>−1.5)</ENT> </ROW> <ROW> <ENT I="01">Nose-down ptiching</ENT> <ENT>n<E T="52">m</E> </ENT> <ENT>−39n<E T="52">m</E>÷V×(n<E T="52">m</E>−1.5)</ENT> </ROW> </GPOTABLE> <FP>where—</FP> (1) n<E T="52">m</E>=positive limit maneuvering load factor used in the design of the airplane; and (2) V=initial speed in knots. The conditions in this paragraph involve loads corresponding to the loads that may occur in a “checked maneuver” (a maneuver in which the pitching control is suddenly displaced in one direction and then suddenly moved in the opposite direction). The deflections and timing of the “checked maneuver” must avoid exceeding the limit maneuvering load factor. The total horizontal <PRTPAGE P="197"/>surface load for both nose-up and nose-down pitching conditions is the sum of the balancing loads at <E T="03">V</E> and the specified value of the normal load factor <E T="03">n</E>, plus the maneuvering load increment due to the specified value of the angular acceleration. <CITA>[Amdt. 23-42, 56 FR 353, Jan. 3, 1991; 56 FR 5455, Feb. 11, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.425</SECTNO> <SUBJECT>Gust loads.</SUBJECT> (a) Each horizontal surface, other than a main wing, must be designed for loads resulting from— (1) Gust velocities specified in § 23.333(c) with flaps retracted; and (2) Positive and negative gusts of 25 f.p.s. nominal intensity at <E T="03">V</E> <E T="24">F</E> corresponding to the flight conditions specified in § 23.345(a)(2). (b) [Reserved] (c) When determining the total load on the horizontal surfaces for the conditions specified in paragraph (a) of this section, the initial balancing loads for steady unaccelerated flight at the pertinent design speeds V<E T="52">F,</E> V<E T="52">C</E>, and V<E T="52">D</E> must first be determined. The incremental load resulting from the gusts must be added to the initial balancing load to obtain the total load. (d) In the absence of a more rational analysis, the incremental load due to the gust must be computed as follows only on airplane configurations with aft-mounted, horizontal surfaces, unless its use elsewhere is shown to be conservative: <MATH DEEP="30" SPAN="1"> <MID>EC28SE91.002</MID> </MATH> <EXTRACT> <FP>where—</FP> <FP SOURCE="FP-2">ΔL<E T="22">ht</E>=Incremental horizontal tailload (lbs.);</FP> <FP SOURCE="FP-2">K<E T="22">g</E>=Gust alleviation factor defined in § 23.341;</FP> <FP SOURCE="FP-2">U<E T="22">de</E>=Derived gust velocity (f.p.s.);</FP> <FP SOURCE="FP-2">V=Airplane equivalent speed (knots);</FP> <FP SOURCE="FP-2">a<E T="22">ht</E>=Slope of aft horizontal lift curve (per radian)</FP> <FP SOURCE="FP-2">S<E T="52">ht</E>=Area of aft horizontal lift surface (ft<E T="51">2</E>); and</FP> </EXTRACT> <MATH DEEP="30" SPAN="1"> <MID>EC28SE91.003</MID> </MATH> <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089 Aug. 13, 1969; Amdt. 23-42, 56 FR 353, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.427</SECTNO> <SUBJECT>Unsymmetrical loads.</SUBJECT> (a) Horizontal surfaces other than main wing and their supporting structure must be designed for unsymmetrical loads arising from yawing and slipstream effects, in combination with the loads prescribed for the flight conditions set forth in §§ 23.421 through 23.425. (b) In the absence of more rational data for airplanes that are conventional in regard to location of engines, wings, horizontal surfaces other than main wing, and fuselage shape: (1) 100 percent of the maximum loading from the symmetrical flight conditions may be assumed on the surface on one side of the plane of symmetry; and (2) The following percentage of that loading must be applied to the opposite side: <EXTRACT> Percent=100−10 (n−1), where n is the specified positive maneuvering load factor, but this value may not be more than 80 percent. </EXTRACT> (c) For airplanes that are not conventional (such as airplanes with horizontal surfaces other than main wing having appreciable dihedral or supported by the vertical tail surfaces) the surfaces and supporting structures must be designed for combined vertical and horizontal surface loads resulting from each prescribed flight condition taken separately. <CITA>[Amdt. 23-14, 38 FR 31820, Nov. 19, 1973, as amended by Amdt. 23-42, 56 FR 353, Jan. 3, 1991]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Vertical Surfaces</HD> <SECTION> <SECTNO>§ 23.441</SECTNO> <SUBJECT>Maneuvering loads.</SUBJECT> (a) At speeds up to <E T="03">V</E> <E T="24">A</E>, the vertical surfaces must be designed to withstand the following conditions. In computing the loads, the yawing velocity may be assumed to be zero: (1) With the airplane in unaccelerated flight at zero yaw, it is assumed that the rudder control is suddenly displaced to the maximum deflection, as limited by the control stops or by limit pilot forces. (2) With the rudder deflected as specified in paragraph (a)(1) of this section, it is assumed that the airplane yaws to the overswing sideslip angle. In lieu of a rational analysis, an overswing angle <PRTPAGE P="198"/>equal to 1.5 times the static sideslip angle of paragraph (a)(3) of this section may be assumed. (3) A yaw angle of 15 degrees with the rudder control maintained in the neutral position (except as limited by pilot strength). (b) For commuter category airplanes, the loads imposed by the following additional maneuver must be substantiated at speeds from V<E T="52">A</E> to V<E T="52">D</E>/M<E T="52">D</E>. When computing the tail loads— (1) The airplane must be yawed to the largest attainable steady state sideslip angle, with the rudder at maximum deflection caused by any one of the following: (i) Control surface stops; (ii) Maximum available booster effort; (iii) Maximum pilot rudder force as shown below: <GPH DEEP="470" SPAN="2"> <PRTPAGE P="199"/> <GID>ER09FE96.006</GID> </GPH> (2) The rudder must be suddenly displaced from the maximum deflection to the neutral position. (c) The yaw angles specified in paragraph (a)(3) of this section may be reduced if the yaw angle chosen for a particular speed cannot be exceeded in—<PRTPAGE P="200"/> (1) Steady slip conditions; (2) Uncoordinated rolls from steep banks; or (3) Sudden failure of the critical engine with delayed corrective action. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13090, Aug. 13, 1969; Amdt. 23-14, 38 FR 31821, Nov. 19, 1973; Amdt. 23-28, 47 FR 13315, Mar. 29, 1982; Amdt. 23-42, 56 FR 353, Jan. 3, 1991; Amdt. 23-48, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.443</SECTNO> <SUBJECT>Gust loads.</SUBJECT> (a) Vertical surfaces must be designed to withstand, in unaccelerated flight at speed <E T="03">V</E> <E T="22">C</E>, lateral gusts of the values prescribed for <E T="03">V</E> <E T="22">C</E> in § 23.333(c). (b) In addition, for commuter category airplanes, the airplane is assumed to encounter derived gusts normal to the plane of symmetry while in unaccelerated flight at V<E T="54">B</E>, V<E T="54">C</E>, V<E T="54">D</E>, and V<E T="54">F</E>. The derived gusts and airplane speeds corresponding to these conditions, as determined by §§ 23.341 and 23.345, must be investigated. The shape of the gust must be as specified in § 23.333(c)(2)(i). (c) In the absence of a more rational analysis, the gust load must be computed as follows: <MATH DEEP="28" SPAN="1"> <MID>ER09FE96.000</MID> </MATH> <FP SOURCE="FP-2">Where—</FP> <FP SOURCE="FP-2">L<E T="52">vt</E>=Vertical surface loads (lbs.);</FP> <MATH DEEP="29" SPAN="1"> <MID>ER09FE96.001</MID> </MATH> <MATH DEEP="31" SPAN="1"> <MID>ER09FE96.002</MID> </MATH> <FP SOURCE="FP-2">U<E T="52">de</E>=Derived gust velocity (f.p.s.);</FP> <FP SOURCE="FP-2"> <E T="61">ρ</E>=Air density (slugs/cu.ft.);</FP> <FP SOURCE="FP-2">W=the applicable weight of the airplane in the particular load case (lbs.);</FP> <FP SOURCE="FP-2">S<E T="52">vt</E>=Area of vertical surface (ft.<E T="51">2</E>);</FP> <FP SOURCE="FP-2">c<AC T="08"/> <E T="52">t</E>=Mean geometric chord of vertical surface (ft.);</FP> <FP SOURCE="FP-2">a<E T="52">vt</E>=Lift curve slope of vertical surface (per radian);</FP> <FP SOURCE="FP-2">K=Radius of gyration in yaw (ft.);</FP> <FP SOURCE="FP-2">l<E T="52">vt</E>=Distance from airplane c.g. to lift center of vertical surface (ft.);</FP> <FP SOURCE="FP-2">g=Acceleration due to gravity (ft./sec.<E T="51">2</E>); and</FP> <FP SOURCE="FP-2">V=Equivalent airspeed (knots).</FP> <CITA>[Amdt. 23-7, 34 FR 13090, Aug. 13, 1969, as amended by Amdt. 23-34, 52 FR 1830, Jan. 15, 1987; 52 FR 7262, Mar. 9, 1987; Amdt. 23-24, 52 FR 34745, Sept. 14, 1987; Amdt. 23-42, 56 FR 353, Jan. 3, 1991; Amdt. 23-48, 61 FR 5147, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.445</SECTNO> <SUBJECT>Outboard fins or winglets.</SUBJECT> (a) If outboard fins or winglets are included on the horizontal surfaces or wings, the horizontal surfaces or wings must be designed for their maximum load in combination with loads induced by the fins or winglets and moments or forces exerted on the horizontal surfaces or wings by the fins or winglets. (b) If outboard fins or winglets extend above and below the horizontal surface, the critical vertical surface loading (the load per unit area as determined under §§ 23.441 and 23.443) must be applied to— (1) The part of the vertical surfaces above the horizontal surface with 80 percent of that loading applied to the part below the horizontal surface; and (2) The part of the vertical surfaces below the horizontal surface with 80 percent of that loading applied to the part above the horizontal surface. (c) The end plate effects of outboard fins or winglets must be taken into account in applying the yawing conditions of §§ 23.441 and 23.443 to the vertical surfaces in paragraph (b) of this section. (d) When rational methods are used for computing loads, the maneuvering loads of § 23.441 on the vertical surfaces and the one-g horizontal surface load, including induced loads on the horizontal surface and moments or forces exerted on the horizontal surfaces by the vertical surfaces, must be applied simultaneously for the structural loading condition. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-14, 38 FR 31821, Nov. 19, 1973; Amdt. 23-42, 56 FR 353, Jan. 3, 1991]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ailerons and Special Devices</HD> <SECTION> <SECTNO>§ 23.455</SECTNO> <SUBJECT>Ailerons.</SUBJECT> (a) The ailerons must be designed for the loads to which they are subjected—<PRTPAGE P="201"/> (1) In the neutral position during symmetrical flight conditions; and (2) By the following deflections (except as limited by pilot effort), during unsymmetrical flight conditions: (i) Sudden maximum displacement of the aileron control at <E T="03">V</E> <E T="24">A</E>. Suitable allowance may be made for control system deflections. (ii) Sufficient deflection at <E T="03">V</E> <E T="24">C</E>, where <E T="03">V</E> <E T="24">C</E> is more than <E T="03">V</E> <E T="24">A</E>, to produce a rate of roll not less than obtained in paragraph (a)(2)(i) of this section. (iii) Sufficient deflection at <E T="03">V</E> <E T="24">D</E> to produce a rate of roll not less than one-third of that obtained in paragraph (a)(2)(i) of this section. (b) [Reserved] <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13090, Aug. 13, 1969; Amdt. 23-42, 56 FR 353, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.459</SECTNO> <SUBJECT>Special devices.</SUBJECT> The loading for special devices using aerodynamic surfaces (such as slots and spoilers) must be determined from test data. </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ground Loads</HD> <SECTION> <SECTNO>§ 23.471</SECTNO> <SUBJECT>General.</SUBJECT> The limit ground loads specified in this subpart are considered to be external loads and inertia forces that act upon an airplane structure. In each specified ground load condition, the external reactions must be placed in equilibrium with the linear and angular inertia forces in a rational or conservative manner. </SECTION> <SECTION> <SECTNO>§ 23.473</SECTNO> <SUBJECT>Ground load conditions and assumptions.</SUBJECT> (a) The ground load requirements of this subpart must be complied with at the design maximum weight except that §§ 23.479, 23.481, and 23.483 may be complied with at a design landing weight (the highest weight for landing conditions at the maximum descent velocity) allowed under paragraphs (b) and (c) of this section. (b) The design landing weight may be as low as— (1) 95 percent of the maximum weight if the minimum fuel capacity is enough for at least one-half hour of operation at maximum continuous power plus a capacity equal to a fuel weight which is the difference between the design maximum weight and the design landing weight; or (2) The design maximum weight less the weight of 25 percent of the total fuel capacity. (c) The design landing weight of a multiengine airplane may be less than that allowed under paragraph (b) of this section if— (1) The airplane meets the one-engine-inoperative climb requirements of § 23.67(b)(1) or (c); and (2) Compliance is shown with the fuel jettisoning system requirements of § 23.1001. (d) The selected limit vertical inertia load factor at the center of gravity of the airplane for the ground load conditions prescribed in this subpart may not be less than that which would be obtained when landing with a descent velocity (<E T="03">V</E>), in feet per second, equal to 4.4 (W/S)<FR>1/4</FR>, except that this velocity need not be more than 10 feet per second and may not be less than seven feet per second. (e) Wing lift not exceeding two-thirds of the weight of the airplane may be assumed to exist throughout the landing impact and to act through the center of gravity. The ground reaction load factor may be equal to the inertia load factor minus the ratio of the above assumed wing lift to the airplane weight. (f) If energy absorption tests are made to determine the limit load factor corresponding to the required limit descent velocities, these tests must be made under § 23.723(a). (g) No inertia load factor used for design purposes may be less than 2.67, nor may the limit ground reaction load factor be less than 2.0 at design maximum weight, unless these lower values will not be exceeded in taxiing at speeds up to takeoff speed over terrain as rough as that expected in service. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13090, Aug. 13, 1969; Amdt. 23-28, 47 FR 13315, Mar. 29, 1982; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993; Amdt. 23-48, 61 FR 5147, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.477</SECTNO> <SUBJECT>Landing gear arrangement.</SUBJECT> Sections 23.479 through 23.483, or the conditions in appendix C, apply to airplanes with conventional arrangements <PRTPAGE P="202"/>of main and nose gear, or main and tail gear. </SECTION> <SECTION> <SECTNO>§ 23.479</SECTNO> <SUBJECT>Level landing conditions.</SUBJECT> (a) For a level landing, the airplane is assumed to be in the following attitudes: (1) For airplanes with tail wheels, a normal level flight attitude. (2) For airplanes with nose wheels, attitudes in which— (i) The nose and main wheels contact the ground simultaneously; and (ii) The main wheels contact the ground and the nose wheel is just clear of the ground. <FP>The attitude used in paragraph (a)(2)(i) of this section may be used in the analysis required under paragraph (a)(2)(ii) of this section.</FP> (b) When investigating landing conditions, the drag components simulating the forces required to accelerate the tires and wheels up to the landing speed (spin-up) must be properly combined with the corresponding instantaneous vertical ground reactions, and the forward-acting horizontal loads resulting from rapid reduction of the spin-up drag loads (spring-back) must be combined with vertical ground reactions at the instant of the peak forward load, assuming wing lift and a tire-sliding coefficient of friction of 0.8. However, the drag loads may not be less than 25 percent of the maximum vertical ground reactions (neglecting wing lift). (c) In the absence of specific tests or a more rational analysis for determining the wheel spin-up and spring-back loads for landing conditions, the method set forth in appendix D of this part must be used. If appendix D of this part is used, the drag components used for design must not be less than those given by appendix C of this part. (d) For airplanes with tip tanks or large overhung masses (such as turbo-propeller or jet engines) supported by the wing, the tip tanks and the structure supporting the tanks or overhung masses must be designed for the effects of dynamic responses under the level landing conditions of either paragraph (a)(1) or (a)(2)(ii) of this section. In evaluating the effects of dynamic response, an airplane lift equal to the weight of the airplane may be assumed. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-17, 41 FR 55464, Dec. 20, 1976; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.481</SECTNO> <SUBJECT>Tail down landing conditions.</SUBJECT> (a) For a tail down landing, the airplane is assumed to be in the following attitudes: (1) For airplanes with tail wheels, an attitude in which the main and tail wheels contact the ground simultaneously. (2) For airplanes with nose wheels, a stalling attitude, or the maximum angle allowing ground clearance by each part of the airplane, whichever is less. (b) For airplanes with either tail or nose wheels, ground reactions are assumed to be vertical, with the wheels up to speed before the maximum vertical load is attained. </SECTION> <SECTION> <SECTNO>§ 23.483</SECTNO> <SUBJECT>One-wheel landing conditions.</SUBJECT> For the one-wheel landing condition, the airplane is assumed to be in the level attitude and to contact the ground on one side of the main landing gear. In this attitude, the ground reactions must be the same as those obtained on that side under § 23.479. </SECTION> <SECTION> <SECTNO>§ 23.485</SECTNO> <SUBJECT>Side load conditions.</SUBJECT> (a) For the side load condition, the airplane is assumed to be in a level attitude with only the main wheels contacting the ground and with the shock absorbers and tires in their static positions. (b) The limit vertical load factor must be 1.33, with the vertical ground reaction divided equally between the main wheels. (c) The limit side inertia factor must be 0.83, with the side ground reaction divided between the main wheels so that— (1) 0.5 (<E T="03">W</E>) is acting inboard on one side; and (2) 0.33 (<E T="03">W</E>) is acting outboard on the other side. (d) The side loads prescribed in paragraph (c) of this section are assumed to be applied at the ground contact point <PRTPAGE P="203"/>and the drag loads may be assumed to be zero. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.493</SECTNO> <SUBJECT>Braked roll conditions.</SUBJECT> Under braked roll conditions, with the shock absorbers and tires in their static positions, the following apply: (a) The limit vertical load factor must be 1.33. (b) The attitudes and ground contacts must be those described in § 23.479 for level landings. (c) A drag reaction equal to the vertical reaction at the wheel multiplied by a coefficient of friction of 0.8 must be applied at the ground contact point of each wheel with brakes, except that the drag reaction need not exceed the maximum value based on limiting brake torque. </SECTION> <SECTION> <SECTNO>§ 23.497</SECTNO> <SUBJECT>Supplementary conditions for tail wheels.</SUBJECT> In determining the ground loads on the tail wheel and affected supporting structures, the following apply: (a) For the obstruction load, the limit ground reaction obtained in the tail down landing condition is assumed to act up and aft through the axle at 45 degrees. The shock absorber and tire may be assumed to be in their static positions. (b) For the side load, a limit vertical ground reaction equal to the static load on the tail wheel, in combination with a side component of equal magnitude, is assumed. In addition— (1) If a swivel is used, the tail wheel is assumed to be swiveled 90 degrees to the airplane longitudinal axis with the resultant ground load passing through the axle; (2) If a lock, steering device, or shimmy damper is used, the tail wheel is also assumed to be in the trailing position with the side load acting at the ground contact point; and (3) The shock absorber and tire are assumed to be in their static positions. (c) If a tail wheel, bumper, or an energy absorption device is provided to show compliance with § 23.925(b), the following apply: (1) Suitable design loads must be established for the tail wheel, bumper, or energy absorption device; and (2) The supporting structure of the tail wheel, bumper, or energy absorption device must be designed to withstand the loads established in paragraph (c)(1) of this section. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-48, 61 FR 5147, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.499</SECTNO> <SUBJECT>Supplementary conditions for nose wheels.</SUBJECT> In determining the ground loads on nose wheels and affected supporting structures, and assuming that the shock absorbers and tires are in their static positions, the following conditions must be met: (a) For aft loads, the limit force components at the axle must be— (1) A vertical component of 2.25 times the static load on the wheel; and (2) A drag component of 0.8 times the vertical load. (b) For forward loads, the limit force components at the axle must be— (1) A vertical component of 2.25 times the static load on the wheel; and (2) A forward component of 0.4 times the vertical load. (c) For side loads, the limit force components at ground contact must be— (1) A vertical component of 2.25 times the static load on the wheel; and (2) A side component of 0.7 times the vertical load. (d) For airplanes with a steerable nose wheel that is controlled by hydraulic or other power, at design takeoff weight with the nose wheel in any steerable position, the application of 1.33 times the full steering torque combined with a vertical reaction equal to 1.33 times the maximum static reaction on the nose gear must be assumed. However, if a torque limiting device is installed, the steering torque can be reduced to the maximum value allowed by that device. (e) For airplanes with a steerable nose wheel that has a direct mechanical connection to the rudder pedals, the mechanism must be designed to withstand the steering torque for the <PRTPAGE P="204"/>maximum pilot forces specified in § 23.397(b). <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-48, 61 FR 5147, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.505</SECTNO> <SUBJECT>Supplementary conditions for skiplanes.</SUBJECT> In determining ground loads for skiplanes, and assuming that the airplane is resting on the ground with one main ski frozen at rest and the other skis free to slide, a limit side force equal to 0.036 times the design maximum weight must be applied near the tail assembly, with a factor of safety of 1. <CITA>[Amdt. 23-7, 34 FR 13090, Aug. 13, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.507</SECTNO> <SUBJECT>Jacking loads.</SUBJECT> (a) The airplane must be designed for the loads developed when the aircraft is supported on jacks at the design maximum weight assuming the following load factors for landing gear jacking points at a three-point attitude and for primary flight structure jacking points in the level attitude: (1) Vertical-load factor of 1.35 times the static reactions. (2) Fore, aft, and lateral load factors of 0.4 ti

CODE OF FEDERAL REGULATIONS14 Aeronautics and Space PARTS 1 TO 59 Revised as of January 1, 1999

CONTAINING

A CODIFICATION OF DOCUMENTS

OF GENERAL APPLICABILITY

AND FUTURE EFFECT

AS OF JANUARY 1, 1999 With Ancillaries

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Table of Contents Page Explanation v Title 14: Chapter I—Federal Aviation Administration, Department of Transportation (parts 1 to 59) 3 Finding Aids: Material Approved for Incorporation by Reference 875 Table of CFR Titles and Chapters 993 Alphabetical List of Agencies Appearing in the CFR 1011 List of CFR Sections Affected 1021

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Properly approved incorporations by reference in this volume are listed in the Finding Aids at the end of this volume.

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Raymond A. Mosley, Director, Office of the Federal Register. January 1, 1999. THIS TITLE

Title 14—Aeronautics and Space is composed of five volumes. The parts in these volumes are arranged in the following order: parts 1-59, 60-139, 140-199, 200-1199, and part 1200-End. The first three volumes containing parts 1-199 are comprised of chapter I—Federal Aviation Administration, Department of Transportation (DOT). The fourth volume containing parts 200-1199 is comprised of chapter II—Office of the Secretary, DOT (Aviation Proceedings) and chapter III—Commercial Space Transportation, Federal Aviation Administration, DOT. The fifth volume containing part 1200-End is comprised of chapter V—National Aeronautics and Space Administration. The contents of these volumes represent all current regulations codified under this title of the CFR as of January 1, 1999.

Redesignation tables appear in the Finding Aids section of the volume containing parts 60-139.

For this volume, Cheryl E. Sirofchuck was Chief Editor. The Code of Federal Regulations publication program is under the direction of Frances D. McDonald, assisted by Alomha S. Morris.

CFRORDR.FRM 14 CFR Ch. I (1-1-99 Edition) Federal Aviation Administration, DOT <CHAPTER> <SUBCHAP TYPE="N"> <PRTPAGE P="5"/> <HD SOURCE="HED">SUBCHAPTER A—DEFINITIONS</HD> <PART> <EAR>Pt. 1</EAR> <HD SOURCE="HED">PART 1—DEFINITIONS AND ABBREVIATIONS</HD> <CONTENTS> <SECHD>Sec.</SECHD> <SECTNO>1.1</SECTNO> <SUBJECT>General definitions.</SUBJECT> <SECTNO>1.2</SECTNO> <SUBJECT>Abbreviations and symbols.</SUBJECT> <SECTNO>1.3</SECTNO> <SUBJECT>Rules of construction.</SUBJECT> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 49 U.S.C. 106(g), 40113, 44701. </AUTH> <SECTION> <SECTNO>§ 1.1</SECTNO> <SUBJECT>General definitions.</SUBJECT> As used in Subchapters A through K of this chapter, unless the context requires otherwise: <E T="03">Administrator</E> means the Federal Aviation Administrator or any person to whom he has delegated his authority in the matter concerned. <E T="03">Aerodynamic coefficients</E> means non-dimensional coefficients for aerodynamic forces and moments. <E T="03">Air carrier</E> means a person who undertakes directly by lease, or other arrangement, to engage in air transportation. <E T="03">Air commerce</E> means interstate, overseas, or foreign air commerce or the transportation of mail by aircraft or any operation or navigation of aircraft within the limits of any Federal airway or any operation or navigation of aircraft which directly affects, or which may endanger safety in, interstate, overseas, or foreign air commerce. <E T="03">Aircraft</E> means a device that is used or intended to be used for flight in the air. <E T="03">Aircraft engine</E> means an engine that is used or intended to be used for propelling aircraft. It includes turbosuperchargers, appurtenances, and accessories necessary for its functioning, but does not include propellers. <E T="03">Airframe</E> means the fuselage, booms, nacelles, cowlings, fairings, airfoil surfaces (including rotors but excluding propellers and rotating airfoils of engines), and landing gear of an aircraft and their accessories and controls. <E T="03">Airplane</E> means an engine-driven fixed-wing aircraft heavier than air, that is supported in flight by the dynamic reaction of the air against its wings. <E T="03">Airport</E> means an area of land or water that is used or intended to be used for the landing and takeoff of aircraft, and includes its buildings and facilities, if any. <E T="03">Airship</E> means an engine-driven lighter-than-air aircraft that can be steered. <E T="03">Air traffic</E> means aircraft operating in the air or on an airport surface, exclusive of loading ramps and parking areas. <E T="03">Air traffic clearance</E> means an authorization by air traffic control, for the purpose of preventing collision between known aircraft, for an aircraft to proceed under specified traffic conditions within controlled airspace. <E T="03">Air traffic control</E> means a service operated by appropriate authority to promote the safe, orderly, and expeditious flow of air traffic. <E T="03">Air transportation</E> means interstate, overseas, or foreign air transportation or the transportation of mail by aircraft. <E T="03">Alert Area.</E> An alert area is established to inform pilots of a specific area wherein a high volume of pilot training or an unusual type of aeronautical activity is conducted. <E T="03">Alternate airport</E> means an airport at which an aircraft may land if a landing at the intended airport becomes inadvisable. <E T="03">Altitude engine</E> means a reciprocating aircraft engine having a rated takeoff power that is producible from sea level to an established higher altitude. <E T="03">Appliance</E> means any instrument, mechanism, equipment, part, apparatus, appurtenance, or accessory, including communications equipment, that is used or intended to be used in operating or controlling an aircraft in flight, is installed in or attached to the aircraft, and is not part of an airframe, engine, or propeller. <E T="03">Approved</E>, unless used with reference to another person, means approved by the Administrator. <E T="03">Area navigation (RNAV)</E> means a method of navigation that permits aircraft operations on any desired course within the coverage of station-referenced navigation signals or within the limits of self-contained system capability.<PRTPAGE P="6"/> <E T="03">Area navigation low route</E> means an area navigation route within the airspace extending upward from 1,200 feet above the surface of the earth to, but not including, 18,000 feet MSL. <E T="03">Area navigation high route</E> means an area navigation route within the airspace extending upward from, and including, 18,000 feet MSL to flight level 450. <E T="03">Armed Forces</E> means the Army, Navy, Air Force, Marine Corps, and Coast Guard, including their regular and reserve components and members serving without component status. <E T="03">Autorotation</E> means a rotorcraft flight condition in which the lifting rotor is driven entirely by action of the air when the rotorcraft is in motion. <E T="03">Auxiliary rotor</E> means a rotor that serves either to counteract the effect of the main rotor torque on a rotorcraft or to maneuver the rotorcraft about one or more of its three principal axes. <E T="03">Balloon</E> means a lighter-than-air aircraft that is not engine driven, and that sustains flight through the use of either gas buoyancy or an airborne heater. <E T="03">Brake horsepower</E> means the power delivered at the propeller shaft (main drive or main output) of an aircraft engine. <E T="03">Calibrated airspeed</E> means the indicated airspeed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. <E T="03">Canard</E> means the forward wing of a canard configuration and may be a fixed, movable, or variable geometry surface, with or without control surfaces. <E T="03">Canard configuration</E> means a configuration in which the span of the forward wing is substantially less than that of the main wing. <E T="03">Category:</E> (1) As used with respect to the certification, ratings, privileges, and limitations of airmen, means a broad classification of aircraft. Examples include: airplane; rotorcraft; glider; and lighter-than-air; and (2) As used with respect to the certification of aircraft, means a grouping of aircraft based upon intended use or operating limitations. Examples include: transport, normal, utility, acrobatic, limited, restricted, and provisional. <E T="03">Category A,</E> with respect to transport category rotorcraft, means multiengine rotorcraft designed with engine and system isolation features specified in Part 29 and utilizing scheduled takeoff and landing operations under a critical engine failure concept which assures adequate designated surface area and adequate performance capability for continued safe flight in the event of engine failure. <E T="03">Category B,</E> with respect to transport category rotorcraft, means single-engine or multiengine rotorcraft which do not fully meet all Category A standards. Category B rotorcraft have no guaranteed stay-up ability in the event of engine failure and unscheduled landing is assumed. <E T="03">Category II operations</E>, with respect to the operation of aircraft, means a straight-in ILS approach to the runway of an airport under a Category II ILS instrument approach procedure issued by the Administrator or other appropriate authority. <E T="03">Category III operations,</E> with respect to the operation of aircraft, means an ILS approach to, and landing on, the runway of an airport using a Category III ILS instrument approach procedure issued by the Administrator or other appropriate authority. <E T="03">Category IIIa operations,</E> an ILS approach and landing with no decision height (DH), or a DH below 100 feet (30 meters), and controlling runway visual range not less than 700 feet (200 meters). <E T="03">Category IIIb operations,</E> an ILS approach and landing with no DH, or with a DH below 50 feet (15 meters), and controlling runway visual range less than 700 feet (200 meters), but not less than 150 feet (50 meters). <E T="03">Category IIIc operations,</E> an ILS approach and landing with no DH and no runway visual range limitation. <E T="03">Ceiling</E> means the height above the earth's surface of the lowest layer of clouds or obscuring phenomena that is reported as “broken”, “overcast”, or “obscuration”, and not classified as “thin” or “partial”. <E T="03">Civil aircraft</E> means aircraft other than public aircraft.<PRTPAGE P="7"/> <E T="03">Class:</E> (1) As used with respect to the certification, ratings, privileges, and limitations of airmen, means a classification of aircraft within a category having similar operating characteristics. Examples include: single engine; multiengine; land; water; gyroplane; helicopter; airship; and free balloon; and (2) As used with respect to the certification of aircraft, means a broad grouping of aircraft having similar characteristics of propulsion, flight, or landing. Examples include: airplane; rotorcraft; glider; balloon; landplane; and seaplane. <E T="03">Clearway</E> means: (1) For turbine engine powered airplanes certificated after August 29, 1959, an area beyond the runway, not less than 500 feet wide, centrally located about the extended centerline of the runway, and under the control of the airport authorities. The clearway is expressed in terms of a clearway plane, extending from the end of the runway with an upward slope not exceeding 1.25 percent, above which no object nor any terrain protrudes. However, threshold lights may protrude above the plane if their height above the end of the runway is 26 inches or less and if they are located to each side of the runway. (2) For turbine engine powered airplanes certificated after September 30, 1958, but before August 30, 1959, an area beyond the takeoff runway extending no less than 300 feet on either side of the extended centerline of the runway, at an elevation no higher than the elevation of the end of the runway, clear of all fixed obstacles, and under the control of the airport authorities. <E T="03">Climbout speed,</E> with respect to rotorcraft, means a referenced airspeed which results in a flight path clear of the height-velocity envelope during initial climbout. <E T="03">Commercial operator</E> means a person who, for compensation or hire, engages in the carriage by aircraft in air commerce of persons or property, other than as an air carrier or foreign air carrier or under the authority of Part 375 of this title. Where it is doubtful that an operation is for “compensation or hire”, the test applied is whether the carriage by air is merely incidental to the person's other business or is, in itself, a major enterprise for profit. <E T="03">Controlled airspace</E> means an airspace of defined dimensions within which air traffic control service is provided to IFR flights and to VFR flights in accordance with the airspace classification. <NOTE> <HD SOURCE="HED">Note:</HD> Controlled airspace is a generic term that covers Class A, Class B, Class C, Class D, and Class E airspace. </NOTE> <E T="03">Controlled Firing Area.</E> A controlled firing area is established to contain activities, which if not conducted in a controlled environment, would be hazardous to nonparticipating aircraft. <E T="03">Crewmember</E> means a person assigned to perform duty in an aircraft during flight time. <E T="03">Critical altitude</E> means the maximum altitude at which, in standard atmosphere, it is possible to maintain, at a specified rotational speed, a specified power or a specified manifold pressure. Unless otherwise stated, the critical altitude is the maximum altitude at which it is possible to maintain, at the maximum continuous rotational speed, one of the following: (1) The maximum continuous power, in the case of engines for which this power rating is the same at sea level and at the rated altitude. (2) The maximum continuous rated manifold pressure, in the case of engines, the maximum continuous power of which is governed by a constant manifold pressure. <E T="03">Critical engine</E> means the engine whose failure would most adversely affect the performance or handling qualities of an aircraft. <E T="03">Decision height,</E> with respect to the operation of aircraft, means the height at which a decision must be made, during an ILS or PAR instrument approach, to either continue the approach or to execute a missed approach. <E T="03">Equivalent airspeed</E> means the calibrated airspeed of an aircraft corrected for adiabatic compressible flow for the particular altitude. Equivalent airspeed is equal to calibrated airspeed in standard atmosphere at sea level. <E T="03">Extended over-water operation</E> means— (1) With respect to aircraft other than helicopters, an operation over water at a horizontal distance of more <PRTPAGE P="8"/>than 50 nautical miles from the nearest shoreline; and (2) With respect to helicopters, an operation over water at a horizontal distance of more than 50 nautical miles from the nearest shoreline and more than 50 nautical miles from an off-shore heliport structure. <E T="03">External load</E> means a load that is carried, or extends, outside of the aircraft fuselage. <E T="03">External-load attaching means</E> means the structural components used to attach an external load to an aircraft, including external-load containers, the backup structure at the attachment points, and any quick-release device used to jettison the external load. <E T="03">Fireproof</E>— (1) With respect to materials and parts used to confine fire in a designated fire zone, means the capacity to withstand at least as well as steel in dimensions appropriate for the purpose for which they are used, the heat produced when there is a severe fire of extended duration in that zone; and (2) With respect to other materials and parts, means the capacity to withstand the heat associated with fire at least as well as steel in dimensions appropriate for the purpose for which they are used. <E T="03">Fire resistant</E>— (1) With respect to sheet or structural members means the capacity to withstand the heat associated with fire at least as well as aluminum alloy in dimensions appropriate for the purpose for which they are used; and (2) With respect to fluid-carrying lines, fluid system parts, wiring, air ducts, fittings, and powerplant controls, means the capacity to perform the intended functions under the heat and other conditions likely to occur when there is a fire at the place concerned. <E T="03">Flame resistant</E> means not susceptible to combustion to the point of propagating a flame, beyond safe limits, after the ignition source is removed. <E T="03">Flammable</E>, with respect to a fluid or gas, means susceptible to igniting readily or to exploding. <E T="03">Flap extended speed</E> means the highest speed permissible with wing flaps in a prescribed extended position. <E T="03">Flash resistant</E> means not susceptible to burning violently when ignited. <E T="03">Flightcrew member</E> means a pilot, flight engineer, or flight navigator assigned to duty in an aircraft during flight time. <E T="03">Flight level</E> means a level of constant atmospheric pressure related to a reference datum of 29.92 inches of mercury. Each is stated in three digits that represent hundreds of feet. For example, flight level 250 represents a barometric altimeter indication of 25,000 feet; flight level 255, an indication of 25,500 feet. <E T="03">Flight plan</E> means specified information, relating to the intended flight of an aircraft, that is filed orally or in writing with air traffic control. <E T="03">Flight time</E> means: (1) Pilot time that commences when an aircraft moves under its own power for the purpose of flight and ends when the aircraft comes to rest after landing; or (2) For a glider without self-launch capability, pilot time that commences when the glider is towed for the purpose of flight and ends when the glider comes to rest after landing. <E T="03">Flight visibility</E> means the average forward horizontal distance, from the cockpit of an aircraft in flight, at which prominent unlighted objects may be seen and identified by day and prominent lighted objects may be seen and identified by night. <E T="03">Foreign air carrier</E> means any person other than a citizen of the United States, who undertakes directly, by lease or other arrangement, to engage in air transportation. <E T="03">Foreign air commerce</E> means the carriage by aircraft of persons or property for compensation or hire, or the carriage of mail by aircraft, or the operation or navigation of aircraft in the conduct or furtherance of a business or vocation, in commerce between a place in the United States and any place outside thereof; whether such commerce moves wholly by aircraft or partly by aircraft and partly by other forms of transportation. <E T="03">Foreign air transportation</E> means the carriage by aircraft of persons or property as a common carrier for compensation or hire, or the carriage of mail by aircraft, in commerce between <PRTPAGE P="9"/>a place in the United States and any place outside of the United States, whether that commerce moves wholly by aircraft or partly by aircraft and partly by other forms of transportation. <E T="03">Forward wing</E> means a forward lifting surface of a canard configuration or tandem-wing configuration airplane. The surface may be a fixed, movable, or variable geometry surface, with or without control surfaces. <E T="03">Glider</E> means a heavier-than-air aircraft, that is supported in flight by the dynamic reaction of the air against its lifting surfaces and whose free flight does not depend principally on an engine. <E T="03">Ground visibility</E> means prevailing horizontal visibility near the earth's surface as reported by the United States National Weather Service or an accredited observer. <E T="03">Go-around power or thrust setting</E> means the maximum allowable in-flight power or thrust setting identified in the performance data. <E T="03">Gyrodyne</E> means a rotorcraft whose rotors are normally engine-driven for takeoff, hovering, and landing, and for forward flight through part of its speed range, and whose means of propulsion, consisting usually of conventional propellers, is independent of the rotor system. <E T="03">Gyroplane</E> means a rotorcraft whose rotors are not engine-driven, except for initial starting, but are made to rotate by action of the air when the rotorcraft is moving; and whose means of propulsion, consisting usually of conventional propellers, is independent of the rotor system. <E T="03">Helicopter</E> means a rotorcraft that, for its horizontal motion, depends principally on its engine-driven rotors. <E T="03">Heliport</E> means an area of land, water, or structure used or intended to be used for the landing and takeoff of helicopters. <E T="03">Idle thrust</E> means the jet thrust obtained with the engine power control level set at the stop for the least thrust position at which it can be placed. <E T="03">IFR conditions</E> means weather conditions below the minimum for flight under visual flight rules. <E T="03">IFR over-the-top</E>, with respect to the operation of aircraft, means the operation of an aircraft over-the-top on an IFR flight plan when cleared by air traffic control to maintain “VFR conditions” or “VFR conditions on top”. <E T="03">Indicated airspeed</E> means the speed of an aircraft as shown on its pitot static airspeed indicator calibrated to reflect standard atmosphere adiabatic compressible flow at sea level uncorrected for airspeed system errors. <E T="03">Instrument</E> means a device using an internal mechanism to show visually or aurally the attitude, altitude, or operation of an aircraft or aircraft part. It includes electronic devices for automatically controlling an aircraft in flight. <E T="03">Interstate air commerce</E> means the carriage by aircraft of persons or property for compensation or hire, or the carriage of mail by aircraft, or the operation or navigation of aircraft in the conduct or furtherance of a business or vocation, in commerce between a place in any State of the United States, or the District of Columbia, and a place in any other State of the United States, or the District of Columbia; or between places in the same State of the United States through the airspace over any place outside thereof; or between places in the same territory or possession of the United States, or the District of Columbia. <E T="03">Interstate air transportation</E> means the carriage by aircraft of persons or property as a common carrier for compensation or hire, or the carriage of mail by aircraft in commerce: (1) Between a place in a State or the District of Columbia and another place in another State or the District of Columbia; (2) Between places in the same State through the airspace over any place outside that State; or (3) Between places in the same possession of the United States; <FP>Whether that commerce moves wholly by aircraft of partly by aircraft and partly by other forms of transportation.</FP> <E T="03">Intrastate air transportation</E> means the carriage of persons or property as a common carrier for compensation or hire, by turbojet-powered aircraft capable of carrying thirty or more persons, wholly within the same State of the United States.<PRTPAGE P="10"/> <E T="03">Kite</E> means a framework, covered with paper, cloth, metal, or other material, intended to be flown at the end of a rope or cable, and having as its only support the force of the wind moving past its surfaces. <E T="03">Landing gear extended speed</E> means the maximum speed at which an aircraft can be safely flown with the landing gear extended. <E T="03">Landing gear operating speed</E> means the maximum speed at which the landing gear can be safely extended or retracted. <E T="03">Large aircraft</E> means aircraft of more than 12,500 pounds, maximum certificated takeoff weight. <E T="03">Lighter-than-air aircraft</E> means aircraft that can rise and remain suspended by using contained gas weighing less than the air that is displaced by the gas. <E T="03">Load factor</E> means the ratio of a specified load to the total weight of the aircraft. The specified load is expressed in terms of any of the following: aerodynamic forces, inertia forces, or ground or water reactions. <E T="03">Long-range communication system (LRCS).</E> A system that uses satellite relay, data link, high frequency, or another approved communication system which extends beyond line of sight. <E T="03">Long-range navigation system (LRNS).</E> An electronic navigation unit that is approved for use under instrument flight rules as a primary means of navigation, and has at least one source of navigational input, such as inertial navigation system, global positioning system, Omega/very low frequency, or Loran C. <E T="03">Mach number</E> means the ratio of true airspeed to the speed of sound. <E T="03">Main rotor</E> means the rotor that supplies the principal lift to a rotorcraft. <E T="03">Maintenance</E> means inspection, overhaul, repair, preservation, and the replacement of parts, but excludes preventive maintenance. <E T="03">Major alteration</E> means an alteration not listed in the aircraft, aircraft engine, or propeller specifications— (1) That might appreciably affect weight, balance, structural strength, performance, powerplant operation, flight characteristics, or other qualities affecting airworthiness; or (2) That is not done according to accepted practices or cannot be done by elementary operations. <E T="03">Major repair</E> means a repair: (1) That, if improperly done, might appreciably affect weight, balance, structural strength, performance, powerplant operation, flight characteristics, or other qualities affecting airworthiness; or (2) That is not done according to accepted practices or cannot be done by elementary operations. <E T="03">Manifold pressure</E> means absolute pressure as measured at the appropriate point in the induction system and usually expressed in inches of mercury. <E T="03">Maximum speed for stability characteristics, V</E> <E T="52">FC</E>/M<E T="52">FC</E> means a speed that may not be less than a speed midway between maximum operating limit speed (V<E T="52">MO</E>/M<E T="52">MO</E>) and demonstrated flight diving speed (V<E T="52">DF</E>/M<E T="52">DF</E>), except that, for altitudes where the Mach number is the limiting factor, M<E T="52">FC</E> need not exceed the Mach number at which effective speed warning occurs. <E T="03">Medical certificate</E> means acceptable evidence of physical fitness on a form prescribed by the Administrator. <E T="03">Military operations area.</E> A military operations area (MOA) is airspace established outside Class A airspace to separate or segregate certain nonhazardous military activities from IFR Traffic and to identify for VFR traffic where theses activities are conducted. <E T="03">Minimum descent altitude</E> means the lowest altitude, expressed in feet above mean sea level, to which descent is authorized on final approach or during circle-to-land maneuvering in execution of a standard instrument approach procedure, where no electronic glide slope is provided. <E T="03">Minor alteration</E> means an alteration other than a major alteration. <E T="03">Minor repair</E> means a repair other than a major repair. <E T="03">Navigable airspace</E> means airspace at and above the minimum flight altitudes prescribed by or under this chapter, including airspace needed for safe takeoff and landing. <E T="03">Night</E> means the time between the end of evening civil twilight and the beginning of morning civil twilight, as <PRTPAGE P="11"/>published in the American Air Almanac, converted to local time. <E T="03">Nonprecision approach procedure</E> means a standard instrument approach procedure in which no electronic glide slope is provided. <E T="03">Operate,</E> with respect to aircraft, means use, cause to use or authorize to use aircraft, for the purpose (except as provided in § 91.13 of this chapter) of air navigation including the piloting of aircraft, with or without the right of legal control (as owner, lessee, or otherwise). <E T="03">Operational control</E>, with respect to a flight, means the exercise of authority over initiating, conducting or terminating a flight. <E T="03">Overseas air commerce</E> means the carriage by aircraft of persons or property for compensation or hire, or the carriage of mail by aircraft, or the operation or navigation of aircraft in the conduct or furtherance of a business or vocation, in commerce between a place in any State of the United States, or the District of Columbia, and any place in a territory or possession of the United States; or between a place in a territory or possession of the United States, and a place in any other territory or possession of the United States. <E T="03">Overseas air transportation</E> means the carriage by aircraft of persons or property as a common carrier for compensation or hire, or the carriage of mail by aircraft, in commerce: (1) Between a place in a State or the District of Columbia and a place in a possession of the United States; or (2) Between a place in a possession of the United States and a place in another possession of the United States; whether that commerce moves wholly by aircraft or partly by aircraft and partly by other forms of transportation. <E T="03">Over-the-top</E> means above the layer of clouds or other obscuring phenomena forming the ceiling. <E T="03">Parachute</E> means a device used or intended to be used to retard the fall of a body or object through the air. <E T="03">Person</E> means an individual, firm, partnership, corporation, company, association, joint-stock association, or governmental entity. It includes a trustee, receiver, assignee, or similar representative of any of them. <E T="03">Pilotage</E> means navigation by visual reference to landmarks. <E T="03">Pilot in command</E> means the person who: (1) Has final authority and responsibility for the operation and safety of the flight; (2) Has been designated as pilot in command before or during the flight; and (3) Holds the appropriate category, class, and type rating, if appropriate, for the conduct of the flight. <E T="03">Pitch setting</E> means the propeller blade setting as determined by the blade angle measured in a manner, and at a radius, specified by the instruction manual for the propeller. <E T="03">Positive control</E> means control of all air traffic, within designated airspace, by air traffic control. <E T="03">Powered-lift</E> means a heavier-than-air aircraft capable of vertical takeoff, vertical landing, and low speed flight that depends principally on engine-driven lift devices or engine thrust for lift during these flight regimes and on nonrotating airfoil(s) for lift during horizontal flight. <E T="03">Precision approach procedure</E> means a standard instrument approach procedure in which an electronic glide slope is provided, such as ILS and PAR. <E T="03">Preventive maintenance</E> means simple or minor preservation operations and the replacement of small standard parts not involving complex assembly operations. <E T="03">Prohibited area.</E> A prohibited area is airspace designated under part 73 within which no person may operate an aircraft without the permission of the using agency. <E T="03">Propeller</E> means a device for propelling an aircraft that has blades on an engine-driven shaft and that, when rotated, produces by its action on the air, a thrust approximately perpendicular to its plane of rotation. It includes control components normally supplied by its manufacturer, but does not include main and auxiliary rotors or rotating airfoils of engines. <E T="03">Public aircraft</E> means an aircraft used only for the United States Government, or owned and operated (except for commercial purposes), or exclusively leased for at least 90 continuous days, by a government (except the <PRTPAGE P="12"/>United States Government), including a State, the District of Columbia, or a territory or possession of the United States, or political subdivision of that government; but does not include a government-owned aircraft transporting property for commercial purposes, or transporting passengers other than transporting (for other than commercial purposes) crewmembers or other persons aboard the aircraft whose presence is required to perform, or is associated with the performance of, a governmental function such as firefighting, search and rescue, law enforcement, aeronautical research, or biological or geological resource management; or transporting (for other than commercial purposes) persons aboard the aircraft if the aircraft is operated by the Armed Forces or an intelligence agency of the United States. An aircraft described in the preceding sentence shall, notwithstanding any limitation relating to use of the aircraft for commercial purposes, be considered to be a public aircraft for the purposes of this Chapter without regard to whether the aircraft is operated by a unit of government on behalf of another unit of government, pursuant to a cost reimbursement agreement between such units of government, if the unit of government on whose behalf the operation is conducted certifies to the Administrator of the Federal Aviation Administration that the operation was necessary to respond to a significant and imminent threat to life or property (including natural resources) and that no service by a private operator was reasonably available to meet the threat. <E T="03">Rated 30-second OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under part 33 of this chapter, for continued one-flight operation after the failure of one engine in multiengine rotorcraft, limited to three periods of use no longer than 30 seconds each in any one flight, and followed by mandatory inspection and prescribed maintenance action. <E T="03">Rated 2-minute OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under part 33 of this chapter, for continued one-flight operation after the failure of one engine in multiengine rotorcraft, limited to three periods of use no longer than 2 minutes each in any one flight, and followed by mandatory inspection and prescribed maintenance action. <E T="03">Rated continuous OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Part 33 of this chapter, and limited in use to the time required to complete the flight after the failure of one engine of a multiengine rotorcraft. <E T="03">Rated maximum continuous augmented thrust</E>, with respect to turbojet engine type certification, means the approved jet thrust that is developed statically or in flight, in standard atmosphere at a specified altitude, with fluid injection or with the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Part 33 of this chapter, and approved for unrestricted periods of use. <E T="03">Rated maximum continuous power,</E> with respect to reciprocating, turbopropeller, and turboshaft engines, means the approved brake horsepower that is developed statically or in flight, in standard atmosphere at a specified altitude, within the engine operating limitations established under Part 33, and approved for unrestricted periods of use. <E T="03">Rated maximum continuous thrust</E>, with respect to turbojet engine type certification, means the approved jet thrust that is developed statically or in flight, in standard atmosphere at a specified altitude, without fluid injection and without the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Part 33 of this chapter, and approved for unrestricted periods of use.<PRTPAGE P="13"/> <E T="03">Rated takeoff augmented thrust</E>, with respect to turbojet engine type certification, means the approved jet thrust that is developed statically under standard sea level conditions, with fluid injection or with the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Part 33 of this chapter, and limited in use to periods of not over 5 minutes for -takeoff operation. <E T="03">Rated takeoff power</E>, with respect to reciprocating, turbopropeller, and turboshaft engine type certification, means the approved brake horsepower that is developed statically under standard sea level conditions, within the engine operating limitations established under Part 33, and limited in use to periods of not over 5 minutes for takeoff operation. <E T="03">Rated takeoff thrust</E>, with respect to turbojet engine type certification, means the approved jet thrust that is developed statically under standard sea level conditions, without fluid injection and without the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Part 33 of this chapter, and limited in use to periods of not over 5 minutes for takeoff operation. <E T="03">Rated 30-minute OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Part 33 of this chapter, and limited in use to a period of not more than 30 minutes after the failure of one engine of a multiengine rotorcraft. <E T="03">Rated 2\1/2\-minute OEI power,</E> with respect to rotorcraft turbine engines, means the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Part 33 of this chapter, and limited in use to a period of not more than 2<FR>1/2</FR> minutes after the failure of one engine of a multiengine rotorcraft. <E T="03">Rating</E> means a statement that, as a part of a certificate, sets forth special conditions, privileges, or limitations. <E T="03">Reporting point</E> means a geographical location in relation to which the position of an aircraft is reported. <E T="03">Restricted area.</E> A restricted area is airspace designated under Part 73 within which the flight of aircraft, while not wholly prohibited, is subject to restriction. <E T="03">RNAV way point (W/P)</E> means a predetermined geographical position used for route or instrument approach definition or progress reporting purposes that is defined relative to a VORTAC station position. <E T="03">Rocket</E> means an aircraft propelled by ejected expanding gases generated in the engine from self-contained propellants and not dependent on the intake of outside substances. It includes any part which becomes separated during the operation. <E T="03">Rotorcraft</E> means a heavier-than-air aircraft that depends principally for its support in flight on the lift generated by one or more rotors. <E T="03">Rotorcraft-load combination</E> means the combination of a rotorcraft and an external-load, including the external-load attaching means. Rotorcraft-load combinations are designated as Class A, Class B, Class C, and Class D, as follows: (1) <E T="03">Class A rotorcraft-load combination</E> means one in which the external load cannot move freely, cannot be jettisoned, and does not extend below the landing gear. (2) <E T="03">Class B rotorcraft-load combination</E> means one in which the external load is jettisonable and is lifted free of land or water during the rotorcraft operation. (3) <E T="03">Class C rotorcraft-load combination</E> means one in which the external load is jettisonable and remains in contact with land or water during the rotorcraft operation. (4) <E T="03">Class D rotorcraft-load combination</E> means one in which the external-load is other than a Class A, B, or C and has been specifically approved by the Administrator for that operation. <E T="03">Route segment</E> means a part of a route. Each end of that part is identified by: (1) A continental or insular geographical location; or (2) A point at which a definite radio fix can be established.<PRTPAGE P="14"/> <E T="03">Sea level engine</E> means a reciprocating aircraft engine having a rated takeoff power that is producible only at sea level. <E T="03">Second in command</E> means a pilot who is designated to be second in command of an aircraft during flight time. <E T="03">Show</E>, unless the context otherwise requires, means to show to the satisfaction of the Administrator. <E T="03">Small aircraft</E> means aircraft of 12,500 pounds or less, maximum certificated takeoff weight. <E T="03">Special VFR conditions</E> mean meteorological conditions that are less than those required for basic VFR flight in controlled airspace and in which some aircraft are permitted flight under visual flight rules. <E T="03">Special VFR operations</E> means aircraft operating in accordance with clearances within controlled airspace in meteorological conditions less than the basic VFR weather minima. Such operations must be requested by the pilot and approved by ATC. <E T="03">Standard atmosphere</E> means the atmosphere defined in U.S. Standard Atmosphere, 1962 (Geopotential altitude tables). <E T="03">Stopway</E> means an area beyond the takeoff runway, no less wide than the runway and centered upon the extended centerline of the runway, able to support the airplane during an aborted takeoff, without causing structural damage to the airplane, and designated by the airport authorities for use in decelerating the airplane during an aborted takeoff. <E T="03">Takeoff power:</E> (1) With respect to reciprocating engines, means the brake horsepower that is developed under standard sea level conditions, and under the maximum conditions of crankshaft rotational speed and engine manifold pressure approved for the normal takeoff, and limited in continuous use to the period of time shown in the approved engine specification; and (2) With respect to turbine engines, means the brake horsepower that is developed under static conditions at a specified altitude and atmospheric temperature, and under the maximum conditions of rotor shaft rotational speed and gas temperature approved for the normal takeoff, and limited in continuous use to the period of time shown in the approved engine specification. <E T="03">Takeoff safety speed</E> means a referenced airspeed obtained after lift-off at which the required one-engine-inoperative climb performance can be achieved. <E T="03">Takeoff thrust</E>, with respect to turbine engines, means the jet thrust that is developed under static conditions at a specific altitude and atmospheric temperature under the maximum conditions of rotorshaft rotational speed and gas temperature approved for the normal takeoff, and limited in continuous use to the period of time shown in the approved engine specification. <E T="03">Tandem wing configuration</E> means a configuration having two wings of similar span, mounted in tandem. <E T="03">TCAS I</E> means a TCAS that utilizes interrogations of, and replies from, airborne radar beacon transponders and provides traffic advisories to the pilot. <E T="03">TCAS II</E> means a TCAS that utilizes interrogations of, and replies from airborne radar beacon transponders and provides traffic advisories and resolution advisories in the vertical plane. <E T="03">TCAS III</E> means a TCAS that utilizes interrogation of, and replies from, airborne radar beacon transponders and provides traffic advisories and resolution advisories in the vertical and horizontal planes to the pilot. <E T="03">Time in service</E>, with respect to maintenance time records, means the time from the moment an aircraft leaves the surface of the earth until it touches it at the next point of landing. <E T="03">True airspeed</E> means the airspeed of an aircraft relative to undisturbed air. True airspeed is equal to equivalent airspeed multiplied by (<E T="22">ρ</E>0/<E T="22">ρ</E>)<E T="21">1/2</E>. <E T="03">Traffic pattern</E> means the traffic flow that is prescribed for aircraft landing at, taxiing on, or taking off from, an airport. <E T="03">Type:</E> (1) As used with respect to the certification, ratings, privileges, and limitations of airmen, means a specific make and basic model of aircraft, including modifications thereto that do not change its handling or flight characteristics. Examples include: DC-7, 1049, and F-27; and<PRTPAGE P="15"/> (2) As used with respect to the certification of aircraft, means those aircraft which are similar in design. Examples include: DC-7 and DC-7C; 1049G and 1049H; and F-27 and F-27F. (3) As used with respect to the certification of aircraft engines means those engines which are similar in design. For example, JT8D and JT8D-7 are engines of the same type, and JT9D-3A and JT9D-7 are engines of the same type. <E T="03">United States</E>, in a geographical sense, means (1) the States, the District of Columbia, Puerto Rico, and the possessions, including the territorial waters, and (2) the airspace of those areas. <E T="03">United States air carrier</E> means a citizen of the United States who undertakes directly by lease, or other arrangement, to engage in air transportation. <E T="03">VFR over-the-top</E>, with respect to the operation of aircraft, means the operation of an aircraft over-the-top under VFR when it is not being operated on an IFR flight plan. <E T="03">Warning area.</E> A warning area is airspace of defined dimensions, extending from 3 nautical miles outward from the coast of the United States, that contains activity that may be hazardous to nonparticipating aircraft. The purpose of such warning areas is to warn nonparticipating pilots of the potential danger. A warning area may be located over domestic or international waters or both. <E T="03">Winglet or tip fin</E> means an out-of-plane surface extending from a lifting surface. The surface may or may not have control surfaces. <CITA>[Doc. No. 1150, 27 FR 4588, May 15, 1962]</CITA> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For <E T="04">Federal Register</E> citations affecting § 1.1, see the List of CFR Sections Affected appearing in the Finding Aids section of this volume. </EDNOTE> </SECTION> <SECTION> <SECTNO>§ 1.2</SECTNO> <SUBJECT>Abbreviations and symbols.</SUBJECT> In Subchapters A through K of this chapter: <E T="03">AGL</E> means above ground level. <E T="03">ALS</E> means approach light system. <E T="03">ASR</E> means airport surveillance radar. <E T="03">ATC</E> means air traffic control. <E T="03">CAS</E> means calibrated airspeed. <E T="03">CAT II</E> means Category II. <E T="03">CONSOL</E> or <E T="03">CONSOLAN</E> means a kind of low or medium frequency long range navigational aid. <E T="03">DH</E> means decision height. <E T="03">DME</E> means distance measuring equipment compatible with TACAN. <E T="03">EAS</E> means equivalent airspeed. <E T="03">FAA</E> means Federal Aviation Administration. <E T="03">FM</E> means fan marker. <E T="03">GS</E> means glide slope. <E T="03">HIRL</E> means high-intensity runway light system. <E T="03">IAS</E> means indicated airspeed. <E T="03">ICAO</E> means International Civil Aviation Organization. <E T="03">IFR</E> means instrument flight rules. <E T="03">ILS</E> means instrument landing system. <E T="03">IM</E> means ILS inner marker. <E T="03">INT</E> means intersection. <E T="03">LDA</E> means localizer-type directional aid. <E T="03">LFR</E> means low-frequency radio range. <E T="03">LMM</E> means compass locator at middle marker. <E T="03">LOC</E> means ILS localizer. <E T="03">LOM</E> means compass locator at outer marker. <E T="03">M</E> means mach number. <E T="03">MAA</E> means maximum authorized IFR altitude. <E T="03">MALS</E> means medium intensity approach light system. <E T="03">MALSR</E> means medium intensity approach light system with runway alignment indicator lights. <E T="03">MCA</E> means minimum crossing altitude. <E T="03">MDA</E> means minimum descent altitude. <E T="03">MEA</E> means minimum en route IFR altitude. <E T="03">MM</E> means ILS middle marker. <E T="03">MOCA</E> means minimum obstruction clearance altitude. <E T="03">MRA</E> means minimum reception altitude. <E T="03">MSL</E> means mean sea level. <E T="03">NDB(ADF)</E> means nondirectional beacon (automatic direction finder). <E T="03">NOPT</E> means no procedure turn required. <E T="03">OEI</E> means one engine inoperative. <E T="03">OM</E> means ILS outer marker. <E T="03">PAR</E> means precision approach radar. <E T="03">RAIL</E> means runway alignment indicator light system.<PRTPAGE P="16"/> <E T="03">RBN</E> means radio beacon. <E T="03">RCLM</E> means runway centerline marking. <E T="03">RCLS</E> means runway centerline light system. <E T="03">REIL</E> means runway end identification lights. ‘<E T="03">RR</E>” means low or medium frequency radio range station. <E T="03">RVR</E> means runway visual range as measured in the touchdown zone area. <E T="03">SALS</E> means short approach light system. <E T="03">SSALS</E> means simplified short approach light system. <E T="03">SSALSR</E> means simplified short approach light system with runway alignment indicator lights. <E T="03">TACAN</E> means ultra-high frequency tactical air navigational aid. <E T="03">TAS</E> means true airspeed. <E T="03">TCAS</E> means a traffic alert and collision avoidance system. <E T="03">TDZL</E> means touchdown zone lights. <E T="03">TVOR</E> means very high frequency terminal omnirange station. <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">A</E> means design maneuvering speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">B</E> means design speed for maximum gust intensity.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">C</E> means design cruising speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">D</E> means design diving speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">DF</E>/<E T="03">M</E> <E T="24">DF</E> means demonstrated flight diving speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">EF</E> means the speed at which the critical engine is assumed to fail during takeoff.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">F</E> means design flap speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">FC</E>/<E T="03">M</E> <E T="24">FC</E> means maximum speed for stability characteristics.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">FE</E> means maximum flap extended speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">H</E> means maximum speed in level flight with maximum continuous power.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">LE</E> means maximum landing gear extended speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">LO</E> means maximum landing gear operating speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">LOF</E> means lift-off speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">MC</E> means minimum control speed with the critical engine inoperative.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> means maximum operating limit speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">MU</E> means minimum unstick speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">NE</E> means never-exceed speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">NO</E> means maximum structural cruising speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">R</E> means rotation speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">S</E> means the stalling speed or the minimum steady flight speed at which the airplane is controllable.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">S</E> <E T="22">0</E> means the stalling speed or the minimum steady flight speed in the landing configuration.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">S</E> <E T="22">1</E> means the stalling speed or the minimum steady flight speed obtained in a specific configuration.</FP> <FP SOURCE="FP-1">V<E T="54">TOSS</E> means takeoff safety speed for Category A rotorcraft.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">X</E> means speed for best angle of climb.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="24">Y</E> means speed for best rate of climb.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="22">1</E> means the maximum speed in the takeoff at which the pilot must take the first action (e.g., apply brakes, reduce thrust, deploy speed brakes) to stop the airplane within the accelerate-stop distance. V<E T="52">1</E> also means the minimum speed in the takeoff, following a failure of the critical engine at V<E T="52">EF</E>, at which the pilot can continue the takeoff and achieve the required height above the takeoff surface within the takeoff distance.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="22">2</E> means takeoff safety speed.</FP> <FP SOURCE="FP-1"> <E T="03">V</E> <E T="22">2</E> min means minimum takeoff safety speed.</FP> <E T="03">VFR</E> means visual flight rules. <E T="03">VHF</E> means very high frequency. <E T="03">VOR</E> means very high frequency omnirange station. ‘<E T="03">ORTAC</E> means collocated VOR and TACAN. <CITA>[Doc. No. 1150, 27 FR 4590, May 15, 1962]</CITA> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For <E T="04">Federal Register</E> citations affecting § 1.2, see the List of CFR Sections Affected appearing in the Finding Aids, section of this volume. </EDNOTE> </SECTION> <SECTION> <SECTNO>§ 1.3</SECTNO> <SUBJECT>Rules of construction.</SUBJECT> (a) In Subchapters A through K of this chapter, unless the context requires otherwise: (1) Words importing the singular include the plural; (2) Words importing the plural include the singular; and (3) Words importing the masculine gender include the feminine. (b) In Subchapters A through K of this chapter, the word: (1) <E T="03">Shall</E> is used in an imperative sense; (2) <E T="03">May</E> is used in a permissive sense to state authority or permission to do the act prescribed, and the words “no person may * * *” or “a person may <PRTPAGE P="17"/>not * * *” mean that no person is required, authorized, or permitted to do the act prescribed; and (3) <E T="03">Includes</E> means “includes but is not limited to”. <CITA>[Doc. No. 1150, 27 FR 4590, May 15, 1962, as amended by Amdt. 1-10, 31 FR 5055, Mar. 29, 1966]</CITA> </SECTION> </PART> </SUBCHAP> <SUBCHAP TYPE="P"> <PRTPAGE P="18"/> <HD SOURCE="HED">SUBCHAPTER B—PROCEDURAL RULES</HD> <PART> <EAR>Pt. 11</EAR> <HD SOURCE="HED">PART 11—GENERAL RULEMAKING PROCEDURES</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECHD>Sec.</SECHD> <SECTNO>11.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>11.11</SECTNO> <SUBJECT>Docket.</SUBJECT> <SECTNO>11.13</SECTNO> <SUBJECT>Delegation of authority.</SUBJECT> <SECTNO>11.15</SECTNO> <SUBJECT>Emergency exemptions.</SUBJECT> <SECTNO>11.17</SECTNO> <SUBJECT>Direct final rule.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Rules Other Than Airspace Assignment and Use</HD> <SECTNO>11.21</SECTNO> <SUBJECT>Scope.</SUBJECT> <SECTNO>11.23</SECTNO> <SUBJECT>Initiating rulemaking procedures.</SUBJECT> <SECTNO>11.25</SECTNO> <SUBJECT>Petitions for rulemaking or exemptions.</SUBJECT> <SECTNO>11.27</SECTNO> <SUBJECT>Action on petitions for rulemaking or exemptions.</SUBJECT> <SECTNO>11.28</SECTNO> <SUBJECT>Action on special conditions.</SUBJECT> <SECTNO>11.29</SECTNO> <SUBJECT>Notice of proposed rulemaking.</SUBJECT> <SECTNO>11.31</SECTNO> <SUBJECT>Participation of interested persons in rulemaking procedures.</SUBJECT> <SECTNO>11.33</SECTNO> <SUBJECT>Additional rulemaking proceedings.</SUBJECT> <SECTNO>11.35</SECTNO> <SUBJECT>Participation by Civil Aeronautics Board in rulemaking proceedings.</SUBJECT> <SECTNO>11.37</SECTNO> <SUBJECT>Requests for informal appearances.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Processing of Rules Other Than Airworthiness Directives and Airspace Assignment and Use</HD> <SECTNO>11.41</SECTNO> <SUBJECT>Scope.</SUBJECT> <SECTNO>11.43</SECTNO> <SUBJECT>Processing of petitions for rulemaking or exemption from parts of this chapter.</SUBJECT> <SECTNO>11.45</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> <SECTNO>11.47</SECTNO> <SUBJECT>Proceedings after notice of proposed rulemaking.</SUBJECT> <SECTNO>11.49</SECTNO> <SUBJECT>Adoption of final rules.</SUBJECT> <SECTNO>11.51</SECTNO> <SUBJECT>Denial of petition for rulemaking.</SUBJECT> <SECTNO>11.53</SECTNO> <SUBJECT>Grant or denial of exemption.</SUBJECT> <SECTNO>11.55</SECTNO> <SUBJECT>Reconsideration of a denial or grant of exemption.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Rules and Procedures for Airspace Assignment and Use</HD> <SECTNO>11.61</SECTNO> <SUBJECT>Scope.</SUBJECT> <SECTNO>11.63</SECTNO> <SUBJECT>Filing of proposals.</SUBJECT> <SECTNO>11.65</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> <SECTNO>11.67</SECTNO> <SUBJECT>Hearings.</SUBJECT> <SECTNO>11.69</SECTNO> <SUBJECT>Adoption of rules or orders.</SUBJECT> <SECTNO>11.71</SECTNO> <SUBJECT>Exemptions.</SUBJECT> <SECTNO>11.73</SECTNO> <SUBJECT>Petitions for rehearing or reconsideration of rules or orders.</SUBJECT> <SECTNO>11.75</SECTNO> <SUBJECT>Petitions for revoking or modifying rules or orders.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Processing of Airworthiness Directives</HD> <SECTNO>11.81</SECTNO> <SUBJECT>Scope.</SUBJECT> <SECTNO>11.83</SECTNO> <SUBJECT>Processing of petitions for rulemaking or exemption.</SUBJECT> <SECTNO>11.85</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> <SECTNO>11.87</SECTNO> <SUBJECT>Proceedings after notice of proposed rulemaking.</SUBJECT> <SECTNO>11.89</SECTNO> <SUBJECT>Adoption of final rules.</SUBJECT> <SECTNO>11.91</SECTNO> <SUBJECT>Grant or denial of exemption.</SUBJECT> <SECTNO>11.93</SECTNO> <SUBJECT>Petitions for reconsideration of rules.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Agency Information Collection Requirements Under the Paperwork Reduction Act</HD> <SECTNO>11.101</SECTNO> <SUBJECT>OMB control numbers assigned pursuant to the Paperwork Reduction Act.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 49 U.S.C. 106(g), 40101, 40103, 40105, 40109, 40113, 44110, 44502, 44701-44702, 44711, 46102. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 1242, 27 FR 9586, Sept. 28, 1962, unless otherwise noted. </SOURCE> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> Nomenclature changes to part 11 appear at 61 FR 18052, April 24, 1996. </EDNOTE> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECTION> <SECTNO>§ 11.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> This part applies to the issue, amendment, and repeal of— (a) Rules and orders for airspace assignment and use issued under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)); and (b) Other substantive rules, including those applicable to a class of persons, and those addressed to and served on named persons whenever the Administrator decides to use public rulemaking procedures in such a case. </SECTION> <SECTION> <SECTNO>§ 11.11</SECTNO> <SUBJECT>Docket.</SUBJECT> Official FAA records relating to rulemaking actions, including: (a) Proposals, (b) notices of proposed rulemaking, (c) written material received in response to notices, (d) petitions for rulemaking and exemptions, (e) written material received in response to summaries of petitions for rulemaking and exemptions, (f) petitions for rehearing or reconsideration, (g) petitions for modification or revocation, (h) notices denying petitions for rulemaking, (i) <PRTPAGE P="19"/>notices granting or denying exemptions, (j) summaries required to be published under § 11.27, (k) special conditions required, as prescribed under § 21.16 or § 21.101(b)(2), (l) written material received in response to published special conditions, (m) reports of proceedings conducted under § 11.47 (n) notices denying proposals, and (o) final rules or orders are maintained in current docket form in the Office of the Chief Counsel. A public docket relating to rulemaking actions taken by each Regional Administrator on petitions for exemption filed under Part 139 of this chapter is maintained in the Regional Counsel's Office for that region. Unless a request for comment indicates otherwise, a public docket relating to rulemaking actions taken by Regional Administrators under Subparts D and E of this part is maintained in the Regional Counsel's Office. Any interested person may examine any docketed material at that office, at any time after the docket is established, except material that is ordered withheld from the public under section 1104 of the Federal Aviation Act of 1958 (49 U.S.C. 1504), and may obtain a photostatic or duplicate copy of it upon paying the cost of the copy. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-4, 29 FR 15074, Nov. 7, 1964; Amdt. 11-6, 31 FR 13697, Oct. 25, 1966; Amdt. 11-12, 37 FR 19354, Sept. 20, 1972; Amdt. 11-16, 44 FR 6900, Feb. 5, 1979; Amdt. 11-20, 45 FR 60170, Sept. 11, 1980; Amdt. 11-32, 54 FR 39289, Sept. 29, 1989; Amdt. 11-42, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.13</SECTNO> <SUBJECT>Delegation of authority.</SUBJECT> All agency officials, with regulatory issuance authority, may exercise the authority of the Administrator to make certifications, findings and determinations under the Regulatory Flexibility Act (Pub. L. 96-354) with regard to any rulemaking document for which issuance authority is delegated by other sections in this part. <CITA>[Doc. No. 22081, 46 FR 41488, Aug. 17, 1981]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.15</SECTNO> <SUBJECT>Emergency exemptions.</SUBJECT> If, as a result of enemy attack on the United States, communication with Washington headquarters of FAA is or may be disrupted or materially impaired, petitions for exemptions from any rule issued under Titles III or VI of the Federal Aviation Act of 1958 (air safety rules and air traffic and airspace rules) may also be filed at the nearest FAA Regional Office, air traffic control facility or office, Flight Standards District Office, Aircraft Certification Directorate, Aircraft Certification Office, International Field Office or FAA Representative in the Europe, Africa, and Middle East Region, or in the Pacific Region. The procedural requirements of §§ 11.53, 11.71, and 11.91, and the publication and comment procedures of § 11.27 need not be followed. Under these emergency conditions, the FAA inspectors or officers in charge of these offices may grant, in whole or in part and subject to reasonable conditions or limitations, such exemptions or may deny petitions for such exemptions; may issue such exemptions to named persons or in blanket form on their own initiative; and may limit or terminate exemptions so issued by them or by offices whose jurisdiction they may have assumed. Exemptions issued under these circumstances are at all times subject to modification and termination by the Regional Administrator or Acting Regional Administrator or officer in charge of the Region concerned, subject to ultimate action by the Director or Acting Director of the Service concerned. <CITA>[Amdt. 11-2, 29 FR 7091, May 29, 1964, as amended by Amdt. 11-5, 31 FR 11091, Aug. 20, 1966; Amdt. 11-10, 33 FR 17850, Nov. 30, 1968; Amdt. 11-11, 36 FR 3463, Feb. 25, 1971; Amdt. 11-16, 44 FR 6901, Feb. 5, 1979; Amdt. 11-32, 54 FR 39289, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.17</SECTNO> <SUBJECT>Direct final rule.</SUBJECT> Whenever the FAA anticipates that a proposed regulation is unlikely to result in adverse comment, it may choose to issue a direct final rule. The direct final rule will advise the public that no adverse or negative comments are anticipated, and that unless a written adverse or negative comment, or a written notice of intent to submit an adverse or negative comment is received within the comment period, the regulation will become effective on the date specified in the direct final rule. If no written adverse or negative comment, or notice of intent to submit such a comment is received within the <PRTPAGE P="20"/>comment period, the direct final rule will become effective on the date indicated in the direct final rule. The FAA will publish a document in the <E T="04">Federal Register</E> indicating that no adverse or negative comments were received and confirming the date on which the final rule will become effective. If the FAA does receive, within the comment period, an adverse or negative comment, or written notice of intent to submit such a comment, a document withdrawing the direct final rule will be published in the <E T="04">Federal Register</E>, and a notice of proposed rulemaking may be published with a new comment period. Normal procedures for the agency's receipt and consideration of comments will then apply. <CITA>[Doc. No. 27925, 61 FR 11282, Mar. 19, 1996]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Rules Other Than Airspace Assignment and Use</HD> <SECTION> <SECTNO>§ 11.21</SECTNO> <SUBJECT>Scope.</SUBJECT> (a) This subpart applies to substantive rules, other than those relating to airspace assignment and use. (b) Unless the Administrator, for good cause, finds that notice is impracticable, unnecessary, or contrary to the public interest, and incorporates that finding and a brief statement of the reasons for it in the rule, the FAA issues notices of proposed rulemaking and allows interested persons to participate in rulemaking procedings involving a substantive rule. (c) Unless the Administrator determines that notice and rulemaking procedures are to be followed, interpretive rules, general statements of policy, and rules of FAA organization, procedure, or practice are prescribed as final without notice or rulemaking procedures. (d) Whenever the Administrator so determines, the procedures prescribed in this subpart apply to exempting persons and classes from the requirements of a substantive rule. </SECTION> <SECTION> <SECTNO>§ 11.23</SECTNO> <SUBJECT>Initiating rulemaking procedures.</SUBJECT> The Administrator initiates rulemaking procedures upon his own motion. However, in doing so, he considers the recommendations of other agencies of the United States and the petitions of other interested persons. </SECTION> <SECTION> <SECTNO>§ 11.25</SECTNO> <SUBJECT>Petitions for rulemaking or exemptions.</SUBJECT> (a) Any interested person may petition the Administrator to issue, amend, or repeal a rule whether or not it is a substantive rule within the meaning of § 11.21, or for a temporary or permanent exemption from any rule issued by the Federal Aviation Administration under statutory authority. (b) Each petition filed under this section must— (1) In the case of a petition for exemption, unless good cause is shown in that petition, be submitted at least 120 days before the proposed effective date of the exemption; (2) Be submitted in duplicate— (i) To the appropriate FAA airport field office in whose area the petitioner proposes to establish or has established its airport, in the case of any petition for exemption filed under Part 139 of this chapter; (ii) To the Director having Airworthiness Directive responsibility for the product involved in the case of petitions filed in accordance with Subpart D of this part. (iii) To the Federal Air Surgeon (AAM-1), Federal Aviation Administration, 800 Independence Avenue, SW., Washington, D.C. 20591, in the case of a petition for exemption filed under Part 67 of this chapter; and (iv) To the Rules Docket (AGC-10), Federal Aviation Administration, 800 Independence Avenue, Washington, D.C. 20591, in all other cases. (3) Set forth the text or substance of the rule or amendment proposed, or of the rule or statute from which the exemption is sought, or specify the rule that the petitioner seeks to have repealed, as the case may be; (4) Explain the interests of the petitioner in the action requested including, in the case of a petition for an exemption, the nature and extent of the relief sought and a description of each aircraft or person to be covered by the exemption; (5) Contain any information, views, or arguments available to the petitioner to support the action sought, <PRTPAGE P="21"/>the reasons why the granting of the request would be in the public interest and, if appropriate, in the case of an exemption, the reason why the exemption would not adversely affect safety or the action to be taken by the petitioner to provide a level of safety equal to that provided by the rule from which the exemption is sought; and (6)(i) In the case of a unit of Federal, state, or local government that is applying for an exemption from any requirement of part A of subtitle VII of title 49, United States Code, that would otherwise be applicable to current or future aircraft of such unit of government as a result of the statutory change in the definition of public aircraft made by the Independent Safety Board Act Amendments of 1994, Public Law 103-411, the petition for exemption must contain any information, views, analysis, or arguments available to the petitioner to show that: (A) The exemption is necessary to prevent an undue economic burden on the unit of government; and (B) The aviation safety program of the unit of government is effective and appropriate to ensure safe operations of the type of aircraft operated by the unit of government. (ii) The authority of the Administrator, under the Independent Safety Board Amendments of 1994, Pub. L. 103-411, to grant exemptions to units of government is delegated to the Director, Flight Standards Service, and the Director, Aircraft Certification Service. (c) A petition for rulemaking filed under this section must contain a summary, which may be published in the <E T="04">Federal Register</E> as provided in § 11.27(b), which includes— (1) A brief description of the general nature of the rule requested; and (2) A brief description of the pertinent reasons presented in the petition for instituting rulemaking procedures. (d) A petition for exemption filed under this section must contain a summary, which may be published in the <E T="04">Federal Register</E> as provided in § 11.27(c), which includes— (1) A citation of each rule from which relief is requested; and (2) A brief description of the general nature of the relief requested. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962]</CITA> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For <E T="04">Federal Register</E> citations affecting § 11.25, see the List of CFR Sections Affected appearing in the Finding Aids section of this volume. </EDNOTE> </SECTION> <SECTION> <SECTNO>§ 11.27</SECTNO> <SUBJECT>Action on petitions for rulemaking or exemptions.</SUBJECT> (a) <E T="03">General.</E> Except for the publication and comment procedures provided for in this section, no public hearing, argument, or other formal proceeding is held directly on a petition, filed under § 11.25, before its disposition by the FAA. (b) <E T="03">Publication of summary of petition for rulemaking.</E> After receipt of a petition for rulemaking, except as otherwise provided in paragraph (i) of this section, the FAA publishes a summary of the petition in the <E T="04">Federal Register</E> which includes— (1) The docket number of the petition; (2) The name of the petitioner; (3) A brief description of the general nature of the rule requested; (4) A brief description of the pertinent reasons presented in the petition for instituting rulemaking procedures; and (5) In appropriate situations, a list of questions to assist the FAA in obtaining comment on the petition. <FP>Comments on the petition for rulemaking must be filed, in triplicate, within 60 days after the summary is published in the <E T="04">Federal Register</E> unless the Administrator, for good cause, finds a different time period appropriate. Timely comments received will be considered by the Administrator before taking action on the petition.</FP> (c) <E T="03">Publication of summary of petition for exemption.</E> After receipt of a petition for exemption, except as otherwise provided in paragraphs (i) and (j) of this section, the FAA publishes a summary of the petition in the <E T="04">Federal Register</E> which includes— (1) The docket number of the petition; (2) The name of the petitioner; (3) A citation of each rule from which relief is requested; and (4) A brief description of the general nature of the relief requested.<PRTPAGE P="22"/> <FP>Comments on the petition for exemption must be filed, in triplicate, within 20 days after the summary is published in the <E T="04">Federal Register</E> unless the Administrator, for good cause, finds a different time period appropriate. Timely comments received will be considered by the Administrator before taking action on the petition.</FP> (d) <E T="03">Instituting rulemaking procedures based on a petition.</E> If the Administrator determines, after consideration of any comments received in response to a summary of a petition for rulemaking, that the petition discloses adequate reasons, the FAA institutes rulemaking procedures. (e) <E T="03">Grant of petition for exemption—summary.</E> If the Administrator determines, after consideration of any comments received in response to a summary of a petition for exemption, that the petition is in the public interest, the Administrator grants the exemption and, except as otherwise provided in paragraph (i) of this section, the FAA publishes a summary of the grant of the petition for exemption in the <E T="04">Federal Register.</E> A summary of a grant of a petition for exemption includes— (1) The docket number of the petition; (2) The name of the petitioner; (3) A citation of each rule from which relief is requested; (4) A brief description of the general nature of the relief granted; and (5) The disposition of the petition. (f) <E T="03">Denial of petition for rulemaking.</E> If the Administrator determines, after consideration of any comments received in response to a summary of a petition for rulemaking, that the petition does not justify instituting rulemaking procedures, the FAA notifies the petitioner to that effect. Except as otherwise provided in paragraph (i) of this section, the FAA publishes a summary of the denial of the petition for rulemaking in the <E T="04">Federal Register</E> in accordance with paragraph (h) of this section. (g) <E T="03">Denial of petition for exemption.</E> If the Administrator determines, after consideration of any comments received in response to a summary of a petition for exemption, that the petition does not justify granting the requested exemption, the FAA notifies the petitioner to that effect. Except as otherwise provided in paragraph (i) of this section, the FAA publishes a summary of the denial of the petition for exemption in the <E T="04">Federal Register</E> in accordance with paragraph (h) of this section. (h) <E T="03">Summary of denial of petition for rulemaking or exemption.</E> A summary of a denial of a petition for rulemaking or exemption includes— (1) The docket number of the petition; (2) The name of the petitioner; (3) In the case of a denial of a petition for exemption, a citation of each rule from which relief is requested; (4) A brief description of the general nature of the rule or relief requested; and (5) The disposition of the petition. (i) <E T="03">General exceptions.</E> The publication and comment procedures of paragraphs (b) through (h) of this section do not apply to the following: (1) To petitions for rulemakings or exemptions processed under § 11.83. (2) To petitions for exemptions from the requirements of Part 67 of this chapter. (j) <E T="03">Exceptions to publication of summary of petition for exemption.</E> The publication and comment procedures of paragraph (c) of this section do not apply to the following: (1) To petitions for emergency exemptions processed under § 11.15. (2) To petitions for exemptions processed under Part 139 of this chapter. (3) Whenever the head of the Office or Service concerned, subject to the approval of the Chief Counsel with respect to form and legality, finds for good cause shown in a petition for exemption that action on the petition should not be delayed by the publication and comment procedures. Factors that may be considered in determining whether good cause exists, include— (i) Whether a grant of exemption would set a precedent or whether the petition for exemption and the reasons presented in it are identical to exemptions previously granted; (ii) Whether the delay in acting on the petition for exemption that would result from publication would be detrimental to the petitioner; and<PRTPAGE P="23"/> (iii) Whether petitioner acted in a timely manner in filing the petition for exemption. (k) <E T="03">Status of petition for rulemaking.</E> Within 120 days after publication in the <E T="04">Federal Register</E> of a summary of petition for rulemaking and every 120 days thereafter, unless sooner denied under § 11.51 or issued as a notice of proposed rulemaking under § 11.65, the Office or Service concerned shall advise petitioner in writing of the status of the petition. (l) <E T="03">Additional specific provisions.</E> Specific provisions covering actions on petitions are set forth in Subpart C of this part. <CITA>[Amdt. 11-20, 44 FR 6901, Feb. 5, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.28</SECTNO> <SUBJECT>Action on special conditions.</SUBJECT> (a) <E T="03">General.</E> Except for the publication and comment procedures provided for in this section, no public hearing, argument, or other formal proceeding is held directly on a special condition established by the Administrator. (b) <E T="03">Procedures.</E> This subpart and Subpart C apply to the issue, amendment, and repeal of special conditions under Part 21. In addition to the information required by § 11.29(b), each notice will include— (1) The name and address of the applicant; (2) The model designation and a summary description of the affected product; (3) The applicable type design approval regulations designated in accordance with § 21.17 or § 21.101 of Part 21; and (4) A summary description of the novel or unusual design features that make the issue or amendment of special conditions necessary. <CITA>[Amdt. 11-17, 45 FR 60170, Sept. 11, 1980]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.29</SECTNO> <SUBJECT>Notice of proposed rulemaking.</SUBJECT> (a) Each general notice of proposed rulemaking is published in the <E T="04">Federal Register,</E> unless all persons subject to it are named and are personally served with a copy of it. (b) Each notice, whether published in the <E T="04">Federal Register</E> or personally served, includes— (1) A statement of the time, place, and nature of the proposed rulemaking proceeding; (2) A reference to the authority under which it is issued; (3) A description of the subjects and issues involved or the substance and terms of the proposed rule; (4) A statement of the time within which written comments must be submitted and the required number of copies; and (5) A statement of how and to what extent interested persons may participate in the proceedings, as prescribed by §§ 11.31 and 11.33. (c) A petition for extension of the time for comments must be submitted in duplicate not later than two days before expiration of the time stated in the notice. The filing of the petition does not automatically extend the time for petitioner's comments. Such a petition is granted only if the petitioner shows a substantive interest in the proposed rule and good cause for the extension, and if the extension is consistent with the public interest. If an extension is granted it is published in the <E T="04">Federal Register</E>. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-1, 28 FR 2897, Mar. 23, 1963]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.31</SECTNO> <SUBJECT>Participation of interested persons in rulemaking procedures.</SUBJECT> (a) Each interested person is entitled to participate in rulemaking proceedings by submitting written in-for-ma-tion, views, or arguments. In addition, he may comment on the original information, views, and arguments submitted by other persons, if, after receiving them, the Administrator considers it desirable. (b) In any appropriate case, the Administrator also allows interested persons to participate in the rulemaking procedures described in § 11.33. </SECTION> <SECTION> <SECTNO>§ 11.33</SECTNO> <SUBJECT>Additional rulemaking proceedings.</SUBJECT> (a) The rulemaking procedure also includes any further procedural steps that best serve the purposes of a particular proceeding. For example, interested persons may be allowed to make oral arguments, participate in conferences between the Administrator or <PRTPAGE P="24"/>his representative and interested persons and organizations, appear at informal hearings presided over by a designated FAA official at which a stenographic transcript is made, or participate in any other procedure whenever it is desirable and appropriate to assure informed administrative action and adequate protection of private interests. (b) Any appropriate combination of the procedures described in paragraph (a) of this section may be used in addition to the basic procedure of allowing interested persons to participate in rulemaking proceedings by submitting written information, views, or arguments. </SECTION> <SECTION> <SECTNO>§ 11.35</SECTNO> <SUBJECT>Participation by Civil Aeronautics Board in rulemaking proceedings.</SUBJECT> (a) Under section 1001 of the Federal Aviation Act of 1958 (49 U.S.C. 1481), the Civil Aeronautics Board may appear and participate as an interested party in any proceeding conducted by the Administrator under Title III of that Act, and in any proceeding under Title VI of that Act that cannot be appealed to the National Transportation Safety Board. (b) To indicate its intention to participate in any proceeding described in paragraph (a) of this section, the Civil Aeronautics Board may file written information, views, or arguments in response to a notice of proposed rulemaking issued by the Administrator. The Civil Aeronautics Board is entitled to the procedural privileges accorded other parties and is equally free to participate. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.37</SECTNO> <SUBJECT>Requests for informal appearances.</SUBJECT> (a) Upon his request, any interested person may appear informally before an appropriate official of the FAA to present, adjust, or determine a question or controversy relating to a rulemaking function of the FAA. (b) A request for an appearance under this section must be sent in writing to the Federal Aviation Administration, Washington, D.C. 20590, or to the Regional or District Office nearest to the person making the request. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967; Amdt. 11-8, 32 FR 6390, Apr. 25, 1967]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Processing of Rules Other Than Airworthiness Directives and Airspace Assignment and Use</HD> <SECTION> <SECTNO>§ 11.41</SECTNO> <SUBJECT>Scope.</SUBJECT> (a) This subpart prescribes the supplemental procedures to be followed by the Offices and Services of the FAA in rulemaking proceedings and in granting or denying exemptions from rules. It also designates the Office or Service that is authorized to act for the Administrator in connection with those proceedings and exemptions. Any authority conferred by this subpart on the head of any Office or Service is also conferred on the Associate Administrator (if any) who exercises executive direction over that official. (b) This subpart applies to rulemaking procedures other than for Airworthiness Directives and rules relating to Airspace Assignment and Use. (c) For the purposes of this subpart— (1) The words “Office or Service” include the Technical Center, and include Regional Administrators with respect to petitions for exemptions from the requirements of Part 139 of this chapter; and (2) “Chief Counsel” means— (i) The Chief Counsel; (ii) A Regional Counsel or the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office with respect to petitions for exemptions from the requirements of Part 139 of this chapter; (iii) The Assistant Chief Counsel for Regulations for all other exemptions processed under this subpart; or (iv) Any person to whom the Chief Counsel has delegated authority in the matter concerned. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-5, 31 FR 11091, Aug. 20, 1966; Amdt. 11-16, 31 FR 13697, Oct. 25, 1966; Amdt. 11-12, 37 FR 19354, Sept. 20, 1972; Amdt. 11-15, 43 FR 52205, Nov. 9, 1978; Amdt. 11-32, 54 FR 39290, Sept. 25, 1989; Amdt. 11-42, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <PRTPAGE P="25"/> <SECTNO>§ 11.43</SECTNO> <SUBJECT>Processing of petitions for rulemaking or exemption from parts of this chapter.</SUBJECT> Whenever the FAA receives a petition for rulemaking or for an exemption, a copy of the petition is referred for action, as provided in § 11.27, to the Office or Service having substantive responsibility for the subject involved. <CITA>[Doc. No. 15457, 41 FR 11271, Mar. 18, 1976]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.45</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> Whenever he determines that a notice of proposed rulemaking is necessary or desirable, the head of the Office or Service concerned may, subject to the approval of the Chief Counsel with respect to form and legality, issue the notice provided for in § 11.29. In addition, he may grant or deny petitions for extension of the time for comments on the notice, filed under § 11.29(c). <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-1, 28 FR 2897, Mar. 23, 1963]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.47</SECTNO> <SUBJECT>Proceedings after notice of proposed rulemaking.</SUBJECT> (a) Each person who submits written information, views, or arguments in response to a notice of proposed rulemaking, or during additional rulemaking proceedings in connection with such a notice, must file the number of copies specified in the notice. All timely comments are considered before final action on the rulemaking proposal is taken. Late filed comments are considered so far as possible without incurring expense or delay. (b) Whenever the head of the Office or Service concerned determines that additional rulemaking proceedings of the kind described in § 11.33 are necessary or desirable, he may designate representatives to conduct those proceedings. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-5, 31 FR 11091, Aug. 20, 1966]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.49</SECTNO> <SUBJECT>Adoption of final rules.</SUBJECT> (a) After the Office or Service concerned has completed its analysis and evaluation of the information, views, and arguments submitted with respect to a proposed rule, representatives of that Office or Service and the Office of the Chief Counsel prepare an appropriate rule, subject to the approval of the Chief Counsel as to form and legality. Except as provided in paragraph (b) of this section, the rule is then submitted, with the recommendations of the head of the Office or Service concerned and the Chief Counsel, to the Administrator for consideration. If a rule is adopted, it is published in the <E T="04">Federal Register.</E> (b) Final authority to issue, amend, and repeal— (1) An appendix to a part is delegated to the head of the Office or Service concerned; (2) Minimum en route IFR altitudes and associated flight data under Part 95 of this chapter, and standard instrument approach procedures under Part 97 of this chapter is delegated to the Manager, Technical Programs Division, Flight Standards Service; and (3) Special conditions under Part 21 of this chapter is delegated to the Director, Aircraft Certification Service. <CITA>[Amdt. 11-15, 43 FR 52205, Nov. 9, 1978 as amended by Amdt. 11-19, 45 FR 47838, July 17, 1980; Amdt. 11-18, 45 FR 38346, June 9, 1980; Amdt. 11-20, 45 FR 60170, Sept. 11, 1980; Amdt. 11-20A, 45 FR 85597, Dec. 29, 1980; Amdt. 11-32, 54 FR 39290, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.51</SECTNO> <SUBJECT>Denial of petition for rulemaking.</SUBJECT> Whenever it is determined that a petition for rulemaking filed under § 11.25 should be denied, the Office or Service concerned prepares, subject to the approval of the Chief Counsel with respect to form and legality, a notice of denial for the Administrator's signature. </SECTION> <SECTION> <SECTNO>§ 11.53</SECTNO> <SUBJECT>Grant or denial of exemption.</SUBJECT> (a) The head of the Office or Service concerned may, subject to the approval of the Chief Counsel with respect to form and legality, grant or deny any petition for an exemption. However, if the head of the Office or Service concerned finds that the grant or denial involves a technical or policy determination that should be made by the Administrator, he refers the petition and his recommendations and those of the Chief Counsel to the Administrator for final action.<PRTPAGE P="26"/> (b) Whenever a petition is granted or denied under this section, the Office or Service concerned prepares, subject to the approval of the Chief Counsel with respect to form and legality, a notice to the petitioner informing him of the action taken. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-11, 36 FR 3463, Feb. 25, 1971; Amdt. 11-15, 43 FR 52205, Nov. 9, 1978]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.55</SECTNO> <SUBJECT>Reconsideration of a denial or grant of exemption.</SUBJECT> (a) Except as provided in paragraph (c) of this section, if a petition for exemption is denied, the petitioner may file a petition for reconsideration with the Administrator. The petition must be filed, in duplicate, within 30 days after the petitioner is notified of the denial of the exemption. (b) If a petition for exemption is granted, a person other than the initial petitioner may file a petition for reconsideration with the Administrator. The petition must be filed, in duplicate, within 45 days after the grant of exemption is issued. (c) If a petition for exemption from the requirements of Part 67 of this chapter is denied, the petitioner may file a petition for reconsideration with the Federal Air Surgeon. The petition must be filed in duplicate, within 30 days after the petitioner is notified of the denial of the exemption. However, if the final action on the initial petition was by the Administrator in accordance with the second sentence of § 11.53(a), the Federal Air Surgeon refers the petition for reconsideration and recommendations and those of the Chief Counsel to the Administrator for final action. (d) A petition for reconsideration under this section must be based on the existence of one or more of the following: (1) A finding of a material fact that is erroneous. (2) A necessary legal conclusion that is without governing precedent or is a departure from or contrary to law, FAA rules, or precedent. (3) An additional fact relevant to the decision that was not presented in the initial petition for exemption. In order for a petition under paragraph (a) or (c) of this section to be based on this ground, the petition for reconsideration must state the reason the additional fact was not presented in the initial petition. <CITA>[Amdt. 11-15, 43 FR 52205, Nov. 9, 1978]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Rules and Procedures for Airspace Assignment and Use</HD> <SECTION> <SECTNO>§ 11.61</SECTNO> <SUBJECT>Scope.</SUBJECT> (a) This subpart establishes procedures for initiating, processing, issuing, and publishing rules and orders issued under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)), including— (1) Designations of controlled airspace under part 71 of this chapter; (2) Assignments of segments or parts of the navigable airspace for special use purposes, such as restricted areas, military climb corridors, and experimental flight test areas; and (3) Special rules or orders relating to the assignment or use of navigable airspace. (b) This subpart does not apply to emergency cases and cases in which the procedures described in paragraph (a) of this section are found to be impractical, unnecessary, or contrary to the public interest. (c) For the purposes of this subpart, “Director” means the Executive Director of System Operations, the Associate Administrator for Air Traffic or the Director, Air Traffic Rules and Procedures Service, or any person to whom the Director has delegated authority in the matter concerned. (d) For the purposes of this subpart, “Chief Counsel” means the Chief Counsel, or a Regional Counsel, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office or the Assistant Chief Counsel for Regulations or any person to whom the Chief Counsel, Assistant Chief Counsel, or Regional Counsel has delegated authority in the matter concerned. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-3, 29 FR 9662, July 17, 1964; Amdt. 11-4, 29 FR 15074, Nov. 7, 1964; Amdt. 11-5; 31 FR 11091, Aug. 20, 1966; Amdt. 11-15, 43 FR 52205, Nov. 9, 1978; Amdt. 11-30, 51 FR 2348, Jan. 16, 1986; Amdt. 11-32, 54 FR 39290, Sept. 25, 1989; Amdt. 11-35, 56 FR 65638, 65653, Dec. 17, 1991; Amdt. 11-42, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <PRTPAGE P="27"/> <SECTNO>§ 11.63</SECTNO> <SUBJECT>Filing of proposals.</SUBJECT> (a) Each proposal, except one arising in the FAA, for the designation of Federal airways or other areas for normal air traffic use, the assignment of navigable airspace for special use purposes, or the issue of a special rule or order relating to the use of navigable airspace, must be filed in writing, in triplicate, with the Director. (b) The director may, on his own motion, initiate the procedures prescribed in this subpart for proposals arising within the FAA. (c) A proposal requesting the assignment of navigable airspace for special use purposes, or for the designation of an area for air traffic purposes, must include at least the following: (1) The location and a description of the airspace desired for assignment or designation. (2) A complete description of the activity or use to be made of that airspace, including a detailed description of the type, volume, duration, time, and place of the operations to be conducted in the assigned or designated area. (3) A description of the air navigation, air traffic control, surveillance, and communication facilities available and to be provided if the assignment or designation is made. (4) The name and location of the agency, office, facility, or person to whom authority would be delegated to permit the use of the airspace during those times it would not be used for the purpose to which it would be assigned. (d) Subject to the approval of the Chief Counsel with respect to form and legality, the Director issues a notice of any rejected proposal. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-3, 29 FR 9662, July 17, 1964]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.65</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> (a) If it is determined that the subject matter of a proposal should be submitted to the rulemaking process, or if rulemaking action is to be taken on his own motion, the Director, subject to the approval of the Chief Counsel with respect to form and legality, issues a notice of proposed rulemaking. (b) Normally, a notice of proposed rulemaking is issued within approximately 30 days after receipt of a proposal with respect to which it has been determined that action might be taken. (c) Each notice of proposed rulemaking is published in the <E T="04">Federal Register</E> and includes at least the following: (1) A statement of the time, place, and nature of the public rulemaking proceedings. (2) A reference to the authority under which it is proposed. (3) Either the terms or substance of the proposed action or a description of the subjects and issues involved. (d) Approximately 30 days are allowed for submitting written information, views, or arguments on the notice. Petitions for extension of the time for such comments are governed by the provisions of § 11.29(c). If a public hearing is to be held, either the original notice of proposed rulemaking or a revised notice gives approximately 30 days’ notice. The Director may grant or deny petitions for extension of the time for comments on the notice and may change the date of any hearing previously noticed. (e) Written information, views, and arguments submitted in response to a notice of proposed rulemaking, or that are requested after the notice, must be submitted in triplicate. (f) Each interested person is entitled to discuss or confer informally with appropriate FAA officials concerning a proposed action. However, to become a part of the formal record for consideration, any information, views, or arguments presented during the conference must also be submitted in writing in accordance with the notice. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-1, 28 FR 2897, Mar. 23, 1963]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.67</SECTNO> <SUBJECT>Hearings.</SUBJECT> (a) Sections 7 and 8 of the Administrative Procedure Act do not apply to proceedings used to formulate rules under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)). <PRTPAGE P="28"/>Whenever the Director, in his discretion, considers that a hearing is necessary to provide informed Administrative action and assure adequate protection of private or public interests, he may hold an informal public hearing. However, any rule or order issued in a case in which such a hearing is held is not based exclusively on the record of the hearing. (b) The Director designates a presiding officer for each hearing and the Chief Counsel designates a legal adviser. (c) Normally, hearings held under this section are held in the vicinity of the affected airspace. Interested persons are allotted time to make an oral presentation without interruption and a verbatim transcript is made of the proceedings by a certified court reporter. (d) The procedure in hearings held under this section is as follows: (1) The presiding officer makes an opening statement with particular reference to the notice of proposed rulemaking. (2) The presiding officer designates interested persons or their authorized representatives to speak at the hearing. (3) The presiding officer allots enough time to each interested person on an equal basis so that his position may be expressed fully and placed on the record, with those who favor it speaking first followed by those who oppose it, initial statements being made as far as possible without interruption, and questions permitted after initial statements have been made by all designated persons. (4) Arguments and oral statements are limited to the subject named in the notice of proposed rulemaking. (5) Written information, views, arguments, or briefs may be offered for the record, but may not be accepted after the hearing unless good cause is shown or the submission is requested by the presiding officer or the Director. (e) The presiding officer of a hearing may deviate from the procedures prescribed in this section to assure a more complete and informative record. </SECTION> <SECTION> <SECTNO>§ 11.69</SECTNO> <SUBJECT>Adoption of rules or orders.</SUBJECT> (a) After the closing date for submitting written comments on a notice or, if a hearing is held; after the hearing, the Office having substantive responsibility for the subject involved studies the entire matter of a proposed rule or order. The Chief Counsel determines whether legal justification exists for the proposed action, and thereafter prepares an appropriate rule, order, or notice of denial. The rule, order, or notice of denial is then submitted to the Director for his action. (b) Each rule or order issued by the Director is published in the <E T="04">Federal Register</E> and in such other publications as the Director considers desirable. Each notice of denial is sent to the person who made the proposal and to such other interested persons as the Director considers desirable. (c) Each rule or order issued under this subpart becomes effective not less than 30 days after it is published, except in an emergency, or when it is impractical, unnecessary, or contrary to the public interest. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-3, 29 FR 9662, July 17, 1964]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.71</SECTNO> <SUBJECT>Exemptions.</SUBJECT> (a) A petition for an exemption from any rule or order issued under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)) may be filed with the Director. Such a petition must be in triplicate and state clearly the nature of the requested exemption and the reasons why it should be granted. (b) The Director may, subject to the approval of the Chief Counsel with respect to form and legality, grant or deny any petition filed under this section and shall notify the petitioner of his action. </SECTION> <SECTION> <SECTNO>§ 11.73</SECTNO> <SUBJECT>Petitions for rehearing or reconsideration of rules or orders.</SUBJECT> (a) Any interested person may petition the Administrator for a rehearing on, or for reconsideration of, any rule or order issued under section 307(a) of the Federal Aviation Act of 1958 (49 U.S.C. 1348(a)). Such a petition must be filed, in triplicate, within 30 days after <PRTPAGE P="29"/>the rule or order is published in the <E T="04">Federal Register.</E> It must contain a brief statement of the complaint and an explanation as to how the rule or order is contrary to the public interest. (b) If the petitioner requests the consideration of additional facts, he must state their nature and purpose, and the reason they were not presented at the hearing or in writing within the allotted time. (c) The Administrator does not consider repetitious petitions. (d) Unless the Administrator orders otherwise, the filing of a petition under this section does not stay the effect of a rule or order. </SECTION> <SECTION> <SECTNO>§ 11.75</SECTNO> <SUBJECT>Petitions for revoking or modifying rules or orders.</SUBJECT> (a) Any interested person may petition to revoke or modify any rule or order covered by this subpart. Such a petition must be filed, in triplicate, with the Director and must clearly state the information, views, and arguments the petitioner considers necessary to support the requested action and must clearly indicate the effect the action would have on the use of navigable airspace. (b) A petition filed under this section is processed in the same manner as an original proposal, or in any other manner that the Director considers necessary or desirable. <CITA>[Doc. No. 1242, 27 FR 9586, Sept. 28, 1962, as amended by Amdt. 11-3, 29 FR 9662, July 17, 1964]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Processing of Airworthiness Directives</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 7162, 31 FR 13697, Oct. 25, 1966, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 11.81</SECTNO> <SUBJECT>Scope.</SUBJECT> (a) This subpart prescribes the procedures to be followed in rulemaking proceedings for Airworthiness Directives issued pursuant to Part 39 and in granting or denying exemptions from Airworthiness Directives. It also designates the persons that are authorized to act for the Administrator in connection with those proceedings and exemptions. (b) For the purposes of this subpart, “Director” means the Director, Aircraft Certification Service, or a Manager of an Aircraft Certification Directorate (Directorate Manager). (c) The authority for issuing Airworthiness Directives is limited to the following persons: (1) The Director, Aircraft Certification Service; and (2) Managers of the Aircraft Certification Directorates for products under the authority of those directorates, as determined by the Administrator. (d) For the purposes of this subpart, “Chief Counsel” means the Chief Counsel or a Regional Counsel or a Directorate Counsel, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office or the Assistant Chief Counsel for Regulations, or any person to whom the Chief Counsel, Assistant Chief Counsel, Regional Counsel, or Directorate Counsel has delegated authority in the matter concerned. <CITA>[Doc. No. 7162, 31 FR 13697, Oct. 25, 1966, as amended by Amdt. 11-15, 43 FR 52205, Nov. 9, 1978; Amdt. 11-21, 45 FR 80815, Dec. 8, 1980; Amdt. 11-32, 54 FR 39290, Sept. 25, 1989; Amdt. 11-42, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 11.83</SECTNO> <SUBJECT>Processing of petitions for rulemaking or exemption.</SUBJECT> Whenever the FAA receives a petition for rulemaking or for an exemption, a copy of the petition is referred for action, as provided in § 11.27, to the Director having Airworthiness Directive responsibility for the product involved. </SECTION> <SECTION> <SECTNO>§ 11.85</SECTNO> <SUBJECT>Issue of notice of proposed rulemaking.</SUBJECT> Whenever he determines that a notice of proposed rulemaking is necessary or desirable, the Director may, subject to the approval of the Chief Counsel with respect to form and legality issue the notice provided for in § 11.29. In addition, he may grant or deny petitions for extension of the time for comments on the notice, filed under § 11.29(c). </SECTION> <SECTION> <PRTPAGE P="30"/> <SECTNO>§ 11.87</SECTNO> <SUBJECT>Proceedings after notice of proposed rulemaking.</SUBJECT> (a) Each person who submits written information, views, or arguments in response to a notice of proposed rulemaking, or during additional rulemaking proceedings in connection with such a notice, must file the number of copies specified in the notice. (b) Whenever the Director determines that additional rulemaking proceedings of the kind described in § 11.33 are necessary or desirable, he may designate representatives to conduct those proceedings. </SECTION> <SECTION> <SECTNO>§ 11.89</SECTNO> <SUBJECT>Adoption of final rules.</SUBJECT> In any case in which a notice of proposed rulemaking was issued, the Director completes his analysis and evaluation of the information, views, and arguments submitted with respect to the proposed rule and studies the entire matter. In any case in which the subject matter is, for good cause, submitted to the rulemaking process without notice, the Director initiates the procedure. The Chief Counsel determines whether legal justification exists for the action proposed, and thereafter prepares an appropriate rule or notice of denial. The rule or notice of denial is then submitted to the Director for his action. </SECTION> <SECTION> <SECTNO>§ 11.91</SECTNO> <SUBJECT>Grant or denial of exemption.</SUBJECT> (a) The Director may, subject to the approval of the Chief Counsel with respect to form and legality, grant or deny any petition for an exemption from an Airworthiness Directive. (b) Whenever a petition is granted or denied under this section, the Director prepares, subject to the approval of the Chief Counsel with respect to form and legality, a notice to the petitioner informing him of the action taken. </SECTION> <SECTION> <SECTNO>§ 11.93</SECTNO> <SUBJECT>Petitions for reconsideration of rules.</SUBJECT> (a) Any interested person may petition the Administrator for a rehearing on, or for reconsideration of, any Airworthiness Directive. Such a petition must be filed, in duplicate, within 30 days after the rule is published in the <E T="04">Federal Register.</E> It must contain a brief statement of the complaint and an explanation as to how the rule is contrary to the public interest. (b) If the petitioner requests the consideration of additional facts, he must state their nature and purpose and the reason they were not presented at the hearing or in writing within the allotted time. (c) The Administrator does not consider repetitious petitions. (d) Unless the Administrator orders otherwise, the filing of a petition under this section does not stay the effect of a rule or order. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Agency Information Collection Requirements Under the Paperwork Reduction Act</HD> <SECTION> <SECTNO>§ 11.101</SECTNO> <SUBJECT>OMB control numbers assigned pursuant to the Paperwork Reduction Act.</SUBJECT> (a) <E T="03">Purpose.</E> This subpart consolidates and displays the OMB assigned control numbers for the information collection requirements of the Federal Aviation Administration pursuant to the Paperwork Reduction Act of 1980 (Title 44, U.S.C. Chapter 35) which mandates that every collection requirement have a control number displayed in the Code of Federal Regulations. (b) <E T="03">Display.</E> <GPOTABLE CDEF="s10,r10" COLS="2" OPTS="L2"> <BOXHD> <CHED H="1">14 CFR part or section identified and described</CHED> <CHED H="1">Current OMB control No.</CHED> </BOXHD> <ROW> <ENT I="01">Part 21 </ENT> <ENT>2120-0018</ENT> </ROW> <ROW> <ENT I="01">§ 34.7 </ENT> <ENT>2120-0508</ENT> </ROW> <ROW> <ENT I="01">Part 39 </ENT> <ENT>2120-0056</ENT> </ROW> <ROW> <ENT I="01">Part 43 </ENT> <ENT>2120-0020</ENT> </ROW> <ROW> <ENT I="01">§ 45.13 </ENT> <ENT>2120-0508</ENT> </ROW> <ROW> <ENT I="01">§§ 47.3, 47.5</ENT> <ENT>2120-0029</ENT> </ROW> <ROW> <ENT I="01">§ 47.7 </ENT> <ENT>2120-0029, 2120-0042</ENT> </ROW> <ROW> <ENT I="01">§ 47.8 </ENT> <ENT>2120-0042</ENT> </ROW> <ROW> <ENT I="01">§ 47.9 </ENT> <ENT>2120-0029, 2120-0042</ENT> </ROW> <ROW> <ENT I="01">§§ 47.11 thru 47.47 </ENT> <ENT>2120-0042</ENT> </ROW> <ROW> <ENT I="01">§ 47.63 </ENT> <ENT>2120-0024</ENT> </ROW> <ROW> <ENT I="01">Part 49 </ENT> <ENT>2120-0043</ENT> </ROW> <ROW> <ENT I="01">§ 61.3</ENT> <ENT>2120-0034</ENT> </ROW> <ROW> <ENT I="01">§§ 61.13 thru 61.197 </ENT> <ENT>2120-0021</ENT> </ROW> <ROW> <ENT I="01">Part 63 </ENT> <ENT>2120-0007</ENT> </ROW> <ROW> <ENT I="01">Part 65 </ENT> <ENT>2120-0022</ENT> </ROW> <ROW> <ENT I="01">§ 67.11 </ENT> <ENT>2120-0034,2120-0052, 2120-0059, 2120-0069</ENT> </ROW> <ROW> <ENT I="01">§ 67.19 </ENT> <ENT>2120-0052,2120-0059, 2120-0069</ENT> </ROW> <ROW> <ENT I="01">§ 67.23 </ENT> <ENT>2120-0002</ENT> </ROW> <ROW> <ENT I="01">Part 77 </ENT> <ENT>2120-0001</ENT> </ROW> <ROW> <ENT I="01">§ 91.1 </ENT> <ENT>2120-0026</ENT> </ROW> <ROW> <ENT I="01">§ 91.3 </ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">§ 91.18 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">§§ 91.24 thru 91.34 (except § 91.30)</ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">§ 91.30</ENT> <ENT>2120-0522</ENT> </ROW> <ROW> <PRTPAGE P="31"/> <ENT I="01">§ 91.39 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">§§ 91.41 thru 91.55 </ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">§ 91.63 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">§ 91.75 </ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">§ 91.83 </ENT> <ENT>2120-0026</ENT> </ROW> <ROW> <ENT I="01">§§ 91.97 thru 91.217 </ENT> <ENT>2120-0005</ENT> </ROW> <ROW> <ENT I="01">Part 91, Subpart E </ENT> <ENT>2120-0082</ENT> </ROW> <ROW> <ENT I="01">§§ 91.851 thru 91.875 </ENT> <ENT>2120-0553</ENT> </ROW> <ROW> <ENT I="01">Part 93, Subpart S </ENT> <ENT>2120-0524</ENT> </ROW> <ROW> <ENT I="01">Part 101 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">Part 105 </ENT> <ENT>2120-0027</ENT> </ROW> <ROW> <ENT I="01">Part 107 </ENT> <ENT>2120-0075</ENT> </ROW> <ROW> <ENT I="01">Part 108 </ENT> <ENT>2120-0098</ENT> </ROW> <ROW> <ENT I="01">Part 121 (except as below) </ENT> <ENT>2120-0008</ENT> </ROW> <ROW> <ENT I="02">§§ 121.3 thru 121.155 </ENT> <ENT>2120-0008, 2120-0028</ENT> </ROW> <ROW> <ENT I="02">§ 121.344 </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="02">§ 121.344a </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="02">§ 121.585 </ENT> <ENT>2120-0542</ENT> </ROW> <ROW> <ENT I="02">§ 121.683 </ENT> <ENT>2120-0585</ENT> </ROW> <ROW> <ENT I="02">§ 121.715 </ENT> <ENT>2120-0523</ENT> </ROW> <ROW> <ENT I="02">§ 121.723 </ENT> <ENT>2120-0008, 2120-0025</ENT> </ROW> <ROW> <ENT I="01">Part 123 </ENT> <ENT>2120-0028</ENT> </ROW> <ROW> <ENT I="01">Part 125 (except as below) </ENT> <ENT>2120-0085</ENT> </ROW> <ROW> <ENT I="02">§ 125.226 </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="01">Part 127 </ENT> <ENT>2120-0028</ENT> </ROW> <ROW> <ENT I="01">§ 129.20 </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="01">Part 133</ENT> <ENT>2120-0044</ENT> </ROW> <ROW> <ENT I="01">Part 135 (except as below) </ENT> <ENT>2120-0039</ENT> </ROW> <ROW> <ENT I="02">§§ 135.11 thru 135.17 </ENT> <ENT>2120-0008, 2120-0039</ENT> </ROW> <ROW> <ENT I="02">§ 135.43 </ENT> <ENT>2120-0025, 2120-0039</ENT> </ROW> <ROW> <ENT I="02">§ 135.63 </ENT> <ENT>2120-0585</ENT> </ROW> <ROW> <ENT I="02">§ 135.129 </ENT> <ENT>2120-0542</ENT> </ROW> <ROW> <ENT I="02">§ 135.152 </ENT> <ENT>2120-0616</ENT> </ROW> <ROW> <ENT I="02">§ 135.163 </ENT> <ENT>2120-0619</ENT> </ROW> <ROW> <ENT I="02">§ 135.411 </ENT> <ENT>2120-0619</ENT> </ROW> <ROW> <ENT I="02">§ 135.415 </ENT> <ENT>2120-0003, 2120-0039</ENT> </ROW> <ROW> <ENT I="02">§ 135.421 </ENT> <ENT>2120-0619</ENT> </ROW> <ROW> <ENT I="01">Part 137 </ENT> <ENT>2120-0049</ENT> </ROW> <ROW> <ENT I="01">Part 139 </ENT> <ENT>2120-0063</ENT> </ROW> <ROW> <ENT I="01">Part 141 </ENT> <ENT>2120-0009</ENT> </ROW> <ROW> <ENT I="01">Part 143 </ENT> <ENT>2120-0021</ENT> </ROW> <ROW> <ENT I="01">Part 145 (except as below) </ENT> <ENT>2120-0010</ENT> </ROW> <ROW> <ENT I="02">§ 145.63 </ENT> <ENT>2120-0003, 2120-0010</ENT> </ROW> <ROW> <ENT I="01">Part 147 </ENT> <ENT>2120-0040</ENT> </ROW> <ROW> <ENT I="01">Part 149 </ENT> <ENT>2120-0012</ENT> </ROW> <ROW> <ENT I="01">§§ 150.21 and 150.23</ENT> <ENT>2120-0517</ENT> </ROW> <ROW> <ENT I="01">Part 152 </ENT> <ENT>2120-0065, 2120-0080</ENT> </ROW> <ROW> <ENT I="01">Part 157 </ENT> <ENT>2120-0036</ENT> </ROW> <ROW> <ENT I="01">§ 159.13 </ENT> <ENT>2120-0061</ENT> </ROW> <ROW> <ENT I="01">§ 159.93 </ENT> <ENT>2120-0084</ENT> </ROW> <ROW> <ENT I="01">Part 171 </ENT> <ENT>2120-0014</ENT> </ROW> <ROW> <ENT I="01">§ 183.11</ENT> <ENT>2120-0002,2120-0033, 2120-0035</ENT> </ROW> <ROW> <ENT I="01">§§ 183.15 thru 183.17 </ENT> <ENT>2120-0033</ENT> </ROW> <ROW> <ENT I="01">§§ 183-25 thru 183.31 </ENT> <ENT>2120-0035</ENT> </ROW> <ROW> <ENT I="01">Part 198 </ENT> <ENT>2120-0514</ENT> </ROW> <ROW> <ENT I="01">Part 199 </ENT> <ENT>2120-0081</ENT> </ROW> <ROW> <ENT I="01">SFAR 44-5 Appendix </ENT> <ENT>2120-0502</ENT> </ROW> <ROW> <ENT I="01">SFAR 36 </ENT> <ENT>2120-0507</ENT> </ROW> </GPOTABLE> <CITA>[Doc. No. 23738, 48 FR 39449, Aug. 31, 1983]</CITA> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For <E T="04">Federal Register</E> citations affecting § 11.101, see the List of CFR Sections Affected in the Finding Aids section of this volume. </EDNOTE> </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 13</EAR> <HD SOURCE="HED">PART 13—INVESTIGATIVE AND ENFORCEMENT PROCEDURES</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—Investigative Procedures</HD> <SECHD>Sec.</SECHD> <SECTNO>13.1</SECTNO> <SUBJECT>Reports of violations.</SUBJECT> <SECTNO>13.3</SECTNO> <SUBJECT>Investigations (general).</SUBJECT> <SECTNO>13.5</SECTNO> <SUBJECT>Formal complaints.</SUBJECT> <SECTNO>13.7</SECTNO> <SUBJECT>Records, documents and reports.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Administrative Actions</HD> <SECTNO>13.11</SECTNO> <SUBJECT>Administrative disposition of certain violations.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Legal Enforcement Actions</HD> <SECTNO>13.13</SECTNO> <SUBJECT>Consent orders.</SUBJECT> <SECTNO>13.15</SECTNO> <SUBJECT>Civil penalties: Federal Aviation Act of 1958, as amended, involving an amount in controversy in excess of $50,000; an in rem action; seizure of aircraft; or injunctive relief.</SUBJECT> <SECTNO>13.16</SECTNO> <SUBJECT>Civil penalties: Federal Aviation Act of 1958, involving an amount in controversy not exceeding $50,000; Hazardous Materials Transportation Act.</SUBJECT> <SECTNO>13.17</SECTNO> <SUBJECT>Seizure of aircraft.</SUBJECT> <SECTNO>13.19</SECTNO> <SUBJECT>Certificate action.</SUBJECT> <SECTNO>13.20</SECTNO> <SUBJECT>Orders of compliance, cease and desist orders, orders of denial, and other orders.</SUBJECT> <SECTNO>13.21</SECTNO> <SUBJECT>Military personnel.</SUBJECT> <SECTNO>13.23</SECTNO> <SUBJECT>Criminal penalties.</SUBJECT> <SECTNO>13.25</SECTNO> <SUBJECT>Injunctions.</SUBJECT> <SECTNO>13.27</SECTNO> <SUBJECT>Final order of Hearing Officer in certificate of aircraft registration proceedings.</SUBJECT> <SECTNO>13.29</SECTNO> <SUBJECT>Civil penalties: Streamlined enforcement procedures for certain security violations.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Rules of Practice for FAA Hearings</HD> <SECTNO>13.31</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>13.33</SECTNO> <SUBJECT>Appearances.</SUBJECT> <SECTNO>13.35</SECTNO> <SUBJECT>Request for hearing.</SUBJECT> <SECTNO>13.37</SECTNO> <SUBJECT>Hearing Officer's powers.</SUBJECT> <SECTNO>13.39</SECTNO> <SUBJECT>Disqualification of Hearing Officer.</SUBJECT> <SECTNO>13.41</SECTNO> <SUBJECT>[Reserved]</SUBJECT> <SECTNO>13.43</SECTNO> <SUBJECT>Service and filing of pleadings, motions, and documents.</SUBJECT> <SECTNO>13.44</SECTNO> <SUBJECT>Computation of time and extension of time.</SUBJECT> <SECTNO>13.45</SECTNO> <SUBJECT>Amendment of notice and answer.</SUBJECT> <SECTNO>13.47</SECTNO> <SUBJECT>Withdrawal of notice or request for hearing.</SUBJECT> <SECTNO>13.49</SECTNO> <SUBJECT>Motions.</SUBJECT> <SECTNO>13.51</SECTNO> <SUBJECT>Intervention.</SUBJECT> <SECTNO>13.53</SECTNO> <SUBJECT>Depositions.</SUBJECT> <SECTNO>13.55</SECTNO> <SUBJECT>Notice of hearing.</SUBJECT> <SECTNO>13.57</SECTNO> <SUBJECT>Subpoenas and witness fees.</SUBJECT> <SECTNO>13.59</SECTNO> <SUBJECT>Evidence.</SUBJECT> <SECTNO>13.61</SECTNO> <SUBJECT>Argument and submittals.</SUBJECT> <SECTNO>13.63</SECTNO> <SUBJECT>Record.</SUBJECT> </SUBPART> <SUBPART> <PRTPAGE P="32"/> <HD SOURCE="HED">Subpart E—Orders of Compliance Under the Hazardous Materials Transportation Act</HD> <SECTNO>13.71</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>13.73</SECTNO> <SUBJECT>Notice of proposed order of compliance.</SUBJECT> <SECTNO>13.75</SECTNO> <SUBJECT>Reply or request for hearing.</SUBJECT> <SECTNO>13.77</SECTNO> <SUBJECT>Consent order of compliance.</SUBJECT> <SECTNO>13.79</SECTNO> <SUBJECT>Hearing.</SUBJECT> <SECTNO>13.81</SECTNO> <SUBJECT>Order of immediate compliance.</SUBJECT> <SECTNO>13.83</SECTNO> <SUBJECT>Appeal.</SUBJECT> <SECTNO>13.85</SECTNO> <SUBJECT>Filing, service and computation of time.</SUBJECT> <SECTNO>13.87</SECTNO> <SUBJECT>Extension of time.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Formal Fact-Finding Investigation Under an Order of Investigation</HD> <SECTNO>13.101</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>13.103</SECTNO> <SUBJECT>Order of investigation.</SUBJECT> <SECTNO>13.105</SECTNO> <SUBJECT>Notification.</SUBJECT> <SECTNO>13.107</SECTNO> <SUBJECT>Designation of additional parties.</SUBJECT> <SECTNO>13.109</SECTNO> <SUBJECT>Convening the investigation.</SUBJECT> <SECTNO>13.111</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> <SECTNO>13.113</SECTNO> <SUBJECT>Noncompliance with the investigative process.</SUBJECT> <SECTNO>13.115</SECTNO> <SUBJECT>Public proceedings.</SUBJECT> <SECTNO>13.117</SECTNO> <SUBJECT>Conduct of investigative proceeding or deposition.</SUBJECT> <SECTNO>13.119</SECTNO> <SUBJECT>Rights of persons against self-incrimination.</SUBJECT> <SECTNO>13.121</SECTNO> <SUBJECT>Witness fees.</SUBJECT> <SECTNO>13.123</SECTNO> <SUBJECT>Submission by party to the investigation.</SUBJECT> <SECTNO>13.125</SECTNO> <SUBJECT>Depositions.</SUBJECT> <SECTNO>13.127</SECTNO> <SUBJECT>Reports, decisions and orders.</SUBJECT> <SECTNO>13.129</SECTNO> <SUBJECT>Post-investigation action.</SUBJECT> <SECTNO>13.131</SECTNO> <SUBJECT>Other procedures.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Rules of Practice in FAA Civil Penalty Actions</HD> <SECTNO>13.201</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>13.202</SECTNO> <SUBJECT>Definitions.</SUBJECT> <SECTNO>13.203</SECTNO> <SUBJECT>Separation of functions.</SUBJECT> <SECTNO>13.204</SECTNO> <SUBJECT>Appearances and rights of parties.</SUBJECT> <SECTNO>13.205</SECTNO> <SUBJECT>Administrative law judges.</SUBJECT> <SECTNO>13.206</SECTNO> <SUBJECT>Intervention.</SUBJECT> <SECTNO>13.207</SECTNO> <SUBJECT>Certification of documents.</SUBJECT> <SECTNO>13.208</SECTNO> <SUBJECT>Complaint.</SUBJECT> <SECTNO>13.209</SECTNO> <SUBJECT>Answer.</SUBJECT> <SECTNO>13.210</SECTNO> <SUBJECT>Filing of documents.</SUBJECT> <SECTNO>13.211</SECTNO> <SUBJECT>Service of documents.</SUBJECT> <SECTNO>13.212</SECTNO> <SUBJECT>Computation of time.</SUBJECT> <SECTNO>13.213</SECTNO> <SUBJECT>Extension of time.</SUBJECT> <SECTNO>13.214</SECTNO> <SUBJECT>Amendment of pleadings.</SUBJECT> <SECTNO>13.215</SECTNO> <SUBJECT>Withdrawal of complaint or request for hearing.</SUBJECT> <SECTNO>13.216</SECTNO> <SUBJECT>Waivers.</SUBJECT> <SECTNO>13.217</SECTNO> <SUBJECT>Joint procedural or discovery schedule.</SUBJECT> <SECTNO>13.218</SECTNO> <SUBJECT>Motions.</SUBJECT> <SECTNO>13.219</SECTNO> <SUBJECT>Interlocutory appeals.</SUBJECT> <SECTNO>13.220</SECTNO> <SUBJECT>Discovery.</SUBJECT> <SECTNO>13.221</SECTNO> <SUBJECT>Notice of hearing.</SUBJECT> <SECTNO>13.222</SECTNO> <SUBJECT>Evidence.</SUBJECT> <SECTNO>13.223</SECTNO> <SUBJECT>Standard of proof.</SUBJECT> <SECTNO>13.224</SECTNO> <SUBJECT>Burden of proof.</SUBJECT> <SECTNO>13.225</SECTNO> <SUBJECT>Offer of proof.</SUBJECT> <SECTNO>13.226</SECTNO> <SUBJECT>Public disclosure of evidence.</SUBJECT> <SECTNO>13.227</SECTNO> <SUBJECT>Expert or opinion witnesses.</SUBJECT> <SECTNO>13.228</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> <SECTNO>13.229</SECTNO> <SUBJECT>Witness fees.</SUBJECT> <SECTNO>13.230</SECTNO> <SUBJECT>Record.</SUBJECT> <SECTNO>13.231</SECTNO> <SUBJECT>Argument before the administrative law judge.</SUBJECT> <SECTNO>13.232</SECTNO> <SUBJECT>Initial decision.</SUBJECT> <SECTNO>13.233</SECTNO> <SUBJECT>Appeal from initial decision.</SUBJECT> <SECTNO>13.234</SECTNO> <SUBJECT>Petition to reconsider or modify a final decision and order of the FAA decisionmaker on appeal.</SUBJECT> <SECTNO>13.235</SECTNO> <SUBJECT>Judicial review of a final decision and order.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Civil Monetary Penalty Inflation Adjustment</HD> <SECTNO>13.301</SECTNO> <SUBJECT>Scope and purpose.</SUBJECT> <SECTNO>13.303</SECTNO> <SUBJECT>Definitions.</SUBJECT> <SECTNO>13.305</SECTNO> <SUBJECT>Cost of living adjustments of civil monetary penalties.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 18 U.S.C. 6002; 28 U.S.C. 2461 (note); 49 U.S.C. 106(g), 5121-5124, 40113-40114, 44103-44106, 44702-44703, 44709-44710, 44713, 46101-46110, 46301-46316, 46501-46502, 46504-46507, 47106, 47111, 47122, 47306, 47531-47532. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 18884, 44 FR 63723, Nov. 5, 1979, unless otherwise noted. </SOURCE> <SUBPART> <HD SOURCE="HED">Subpart A—Investigative Procedures</HD> <SECTION> <SECTNO>§ 13.1</SECTNO> <SUBJECT>Reports of violations.</SUBJECT> (a) Any person who knows of a violation of the Federal Aviation Act of 1958, as amended, the Hazardous Materials Transportation Act relating to the transportation or shipment by air of hazardous materials, the Airport and Airway Development Act of 1970, the Airport and Airway Improvement Act of 1982, the Airport and Airway Improvement Act of 1982 as amended by the Airport and Airway Safety and Capacity Expansion Act of 1987, or any rule, regulation, or order issued thereunder, should report it to appropriate personnel of any FAA regional or district office. (b) Each report made under this section, together with any other information the FAA may have that is relevant to the matter reported, will be <PRTPAGE P="33"/>reviewed by FAA personnel to determine the nature and type of any additional investigation or enforcement action the FAA will take. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-17, 53 FR 33783, Aug. 31, 1988]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.3</SECTNO> <SUBJECT>Investigations (general).</SUBJECT> (a) Under the Federal Aviation Act of 1958, as amended, (49 U.S.C. 1301 <E T="03">et seq.</E>), the Hazardous Materials Transportation Act (49 U.S.C. 1801 <E T="03">et seq.</E>), the Airport and Airway Development Act of 1970 (49 U.S.C. 1701 <E T="03">et seq.</E>), the Airport and Airway Improvement Act of 1982 (49 U.S.C. 2201 <E T="03">et seq.</E>), the Airport and Airway Improvement Act of 1982 (as amended, 49 U.S.C. App. 2201 <E T="03">et seq., </E> Airport and Airway Safety and Capacity Expansion Act of 1987), and the Regulations of the Office of the Secretary of Transportation (49 CFR 1 <E T="03">et seq.</E>), the Administrator may conduct investigations, hold hearings, issue subpoenas, require the production of relevant documents, records, and property, and take evidence and depositions. (b) For the purpose of investigating alleged violations of the Federal Aviation Act of 1958, as amended the Hazardous Materials Transportation Act, the Airport and Airway Development Act of 1970, the Airport and Airway Improvement Act of 1982, the Airport and Airway Improvement Act of 1982 as amended by the Airport and Airway Safety and Capacity Expansion Act of 1987, or any rule, regulation, or order issued thereunder, the Administrator's authority has been delegated to the various services and or offices for matters within their respective areas for all routine investigations. When the compulsory processes of sections 313 and 1004 (49 U.S.C. 1354 and 1484) of the Federal Aviation Act, or section 109 of the Hazardous Materials Transportation Act (49 U.S.C. 1808) are invoked, the Administrator's authority has been delegated to the Chief Counsel, the Deputy Chief Counsel, each Assistant Chief Counsel, each Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel. (c) In conducting formal investigations, the Chief Counsel, the Deputy Chief Counsel, each Assistant Chief Counsel, each Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel may issue an order of investigation in accordance with Subpart F of this part. (d) A complaint against the sponsor, proprietor, or operator of a Federally-assisted airport involving violations of the legal authorities listed in § 16.1 of this chapter shall be filed in accordance with the provisions of part 16 of this chapter, except in the case of complaints, investigations, and proceedings initiated before December 16, 1996, the effective date of part 16 of this chapter. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-17, 53 FR 33783, Aug. 31, 1988; 53 FR 35255, Sept. 12, 1988; Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-27, 61 FR 54004, Oct. 16, 1996; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.5</SECTNO> <SUBJECT>Formal complaints.</SUBJECT> (a) Any person may file a complaint with the Administrator with respect to anything done or omitted to be done by any person in contravention of any provision of any Act or of any regulation or order issued under it, as to matters within the jurisdiction of the Administrator. This section does not apply to complaints against the Administrator or employees of the FAA acting within the scope of their employment. (b) Complaints filed under this section must— (1) Be submitted in writing and identified as a complaint filed for the purpose of seeking an appropriate order or other enforcement action; (2) Be submitted to the Federal Aviation Administration, Office of the Chief Counsel, Attention: Enforcement Docket (AGC-10), 800 Independence Avenue, S.W., Washington, DC 20591; (3) Set forth the name and address, if known, of each person who is the subject of the complaint and, with respect to each person, the specific provisions of the Act or regulation or order that the complainant believes were violated; (4) Contain a concise but complete statement of the facts relied upon to substantiate each allegation; (5) State the name, address and telephone number of the person filing the complaint; and<PRTPAGE P="34"/> (6) Be signed by the person filing the complaint or a duly authorized representative. (c) Complaints which do not meet the requirements of paragraph (b) of this section will be considered reports under § 13.1. (d) Complaints which meet the requirements of paragraph (b) of this section will be docketed and a copy mailed to each person named in the complaint. (e) Any complaint filed against a member of the Armed Forces of the United States acting in the performance of official duties shall be referred to the Secretary of the Department concerned for action in accordance with the procedures set forth in § 13.21 of this part. (f) The person named in the complaint shall file an answer within 20 days after service of a copy of the complaint. (g) After the complaint has been answered or after the allotted time in which to file an answer has expired, the Administrator shall determine if there are reasonable grounds for investigating the complaint. (h) If the Administrator determines that a complaint does not state facts which warrant an investigation or action, the complaint may be dismissed without a hearing and the reason for the dismissal shall be given, in writing, to the person who filed the complaint and the person named in the complaint. (i) If the Administrator determines that reasonable grounds exist, an informal investigation may be initiated or an order of investigation may be issued in accordance with Subpart F of this part, or both. Each person named in the complaint shall be advised which official has been delegated the responsibility under § 13.3(b) or (c) for conducting the investigation. (j) If the investigation substantiates the allegations set forth in the complaint, a notice of proposed order may be issued or other enforcement action taken in accordance with this part. (k) The complaint and other pleadings and official FAA records relating to the disposition of the complaint are maintained in current docket form in the Enforcement Docket (AGC-10), Office of the Chief Counsel, Federal Aviation Administration, 800 Independence Avenue, S.W., Washington, D. C. 20591. Any interested person may examine any docketed material at that office, at any time after the docket is established, except material that is ordered withheld from the public under applicable law or regulations, and may obtain a photostatic or duplicate copy upon paying the cost of the copy. <SECAUTH>(Secs. 313(a), 314(a), 601 through 610, and 1102 of the Federal Aviation Act of 1958 (49 U.S.C. 1354(a), 1421 through 1430, 1502); sec. 6(c), Dept. of Transportation Act (49 U.S.C. 1655(c)))</SECAUTH> <CITA>[Doc. No 13-14, 44 FR 63723, Nov. 5, 1979; as amended by Amdt. 13-16, 45 FR 35307, May 27, 1980; Amdt. 13-19, 54 FR 39290, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.7</SECTNO> <SUBJECT>Records, documents and reports.</SUBJECT> Each record, document and report that the Federal Aviation Regulations require to be maintained, exhibited or submitted to the Administrator may be used in any investigation conducted by the Administrator; and, except to the extent the use may be specifically limited or prohibited by the section which imposes the requirement, the records, documents and reports may be used in any civil penalty action, certificate action, or other legal proceeding. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Administrative Actions</HD> <SECTION> <SECTNO>§ 13.11</SECTNO> <SUBJECT>Administrative disposition of certain violations.</SUBJECT> (a) If it is determined that a violation or an alleged violation of the Federal Aviation Act of 1958, or an order or regulation issued under it, or of the Hazardous Materials Transportation Act, or an order or regulation issued under it, does not require legal enforcement action, an appropriate official of the FAA field office responsible for processing the enforcement case or other appropriate FAA official may take administrative action in disposition of the case. (b) An administrative action under this section does not constitute a formal adjudication of the matter, and may be taken by issuing the alleged violator— (1) A “Warning Notice” which recites available facts and information about <PRTPAGE P="35"/>the incident or condition and indicates that it may have been a violation; or (2) A “Letter of Correction” which confirms the FAA decision in the matter and states the necessary corrective action the alleged violator has taken or agrees to take. If the agreed corrective action is not fully completed, legal enforcement action may be taken. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Legal Enforcement Actions</HD> <SECTION> <SECTNO>§ 13.13</SECTNO> <SUBJECT>Consent orders.</SUBJECT> (a) At any time before the issuance of an order under this subpart, the official who issued the notice and the person subject to the notice may agree to dispose of the case by the issuance of a consent order by the official. (b) A proposal for a consent order, submitted to the official who issued the notice, under this section must include— (1) A proposed order; (2) An admission of all jurisdictional facts; (3) An express waiver of the right to further procedural steps and of all rights to judicial review; and (4) An incorporation by reference of the notice and an acknowledgment that the notice may be used to construe the terms of the order. (c) If the issuance of a consent order has been agreed upon after the filing of a request for hearing in accordance with Subpart D of this part, the proposal for a consent order shall include a request to be filed with the Hearing Officer withdrawing the request for a hearing and requesting that the case be dismissed. </SECTION> <SECTION> <SECTNO>§ 13.15</SECTNO> <SUBJECT>Civil penalties: Federal Aviation Act of 1958, as amended, involving an amount in controversy in excess of $50,000; an in rem action; seizure of aircraft; or injunctive relief.</SUBJECT> (a) The following penalties apply to persons who violate the Federal Aviation Act of l958, as amended: (1) Any person who violates any provision of Title III, V, VI, or XII of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than the amount specified in the Act for each violation in accordance with section 901 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1471, <E T="03">et seq.</E>). (2) Any person who violates section 404(d) of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than the amount specified in the Act for each violation in accordance with section 404(d) or section 901 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1374, 1471, <E T="03">et seq.</E>). (3) Any person who operates aircraft for the carriage of persons or property for compensation or hire (other than an airman serving in the capacity of an airman) is subject to a civil penalty of not more than $10,000 for each violation of Title III, VI, or XII of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, occurring after December 30, 1987, in accordance with section 901 of the Federal Aviation Act of l958, as amended (49 U.S.C. 1471 <E T="03">et seq.</E>). (b) The authority of the Administrator, under section 901 of the Federal Aviation Act of 1958, as amended, to propose a civil penalty for a violation of that Act, or a rule, regulation, or order issued thereunder, and the ability to refer cases to the United States Attorney General, or the delegate of the Attorney General, for prosecution of civil penalty actions proposed by the Administrator, involving an amount in controversy in excess of $50,000, an <E T="03">in rem</E> action, seizure of aircraft subject to lien, or suit for injunctive relief, or for collection of an assessed civil penalty, is delegated to the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, the Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel. (c) The Administrator may compromise any civil penalty, proposed in accordance with section 901 of the Federal Aviation Act of 1958, as amended, involving an amount in controversy in excess of $50,000, an <E T="03">in rem</E> action, seizure of aircraft subject to lien, or suit for injunctive relief, prior to referral of the civil penalty action to the United <PRTPAGE P="36"/>States Attorney General, or the delegate of the Attorney General, for prosecution. (1) The Administrator, through the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, the Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel sends a civil penalty letter to the person charged with a violation of the Federal Aviation Act of 1958, as amended, or a rule, regulation, or order issued thereunder. The civil penalty letter contains a statement of the charges, the applicable law, rule, regulation, or order, the amount of civil penalty that the Administrator will accept in full settlement of the action or an offer to compromise the civil penalty. (2) Not later than 30 days after receipt of the civil penalty letter, the person charged with a violation may present any material or information in answer to the charges to the agency attorney, either orally or in writing, that may explain, mitigate, or deny the violation or that may show extenuating circumstances. The Administrator will consider any material or information submitted in accordance with this paragraph to determine whether the person is subject to a civil penalty or to determine the amount for which the Administrator will compromise the action. (3) If the person charged with the violation offers to compromise for a specific amount, that person shall send a certified check or money order for that amount, payable to the Federal Aviation Administration, to the agency attorney. The Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, the Regional Counsel, the Aeronautical Center Counsel, or the Technical Center Counsel may accept the certified check or money order or may refuse and return the certified check or money order. (4) If the offer to compromise is accepted by the Administrator, the agency attorney will send a letter to the person charged with the violation stating that the certified check or money order is accepted in full settlement of the civil penalty action. (5) If the parties cannot agree to compromise the civil penalty action or the offer to compromise is rejected and the certified check or money order submitted in compromise is returned, the Administrator may refer the civil penalty action to the United States Attorney General, or the delegate of the Attorney General, to begin proceedings in a United States District Court, pursuant to the authority in section 903 of the Federal Aviation Act, as amended (49 U.S.C. 1473), to prosecute and collect the civil penalty. <CITA>[Amdt. 13-18, 53 FR 34653, Sept. 7, 1988, as amended by Amdt. 13-20, 55 FR 15128, Apr. 20, 1990; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.16</SECTNO> <SUBJECT>Civil penalties: Federal Aviation Act of 1958, involving an amount in controversy not exceeding $50,000; Hazardous Materials Transportation Act.</SUBJECT> (a) <E T="03">General.</E> The following penalties apply to persons who violate the Federal Aviation Act of 1958, as amended, and the Hazardous Materials Transportation Act: (1) Any person who violates any provision of title III, V, VI, or XII of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than the amount specified in the Act for each violation in accordance with section 901 of the Federal Aviation Act, of 1958, as amended (49 U.S.C. 1471, <E T="03">et seq</E>.). (2) Any person who violates section 404(d) of the Federal Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than the amount specified in the Act for each violation in accordance with section 404(d) or section 901 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1374, 1471, <E T="03">et seq</E>.). (3) Any person who operates aircraft for the carriage of persons or property for compensation or hire (other than an airman serving in the capacity of an airman) is subject to a civil penalty of not more than $10,000 for each violation of title III, VI, or XII of the Federal <PRTPAGE P="37"/>Aviation Act of 1958, as amended, or any rule, regulation, or order issued thereunder, occurring after December 30, 1987, in accordance with section 901 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1471, <E T="03">et seq</E>.). (4) Any person who knowingly commits an act in violation of the Hazardous Materials Transportation Act, or any rule, regulation, or order issued thereunder, is subject to a civil penalty of not more than $10,000 for each violation in accordance with section 901 of the Federal Aviation Act of 1958, as amended, and section 110 of the Hazardous Materials Transportation Act (49 U.S.C. 1471 and 1809, <E T="03">et seq</E>.). An order assessing civil penalty for a violation under the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder, will be issued only after consideration of— (i) The nature and circumstances of the violation; (ii) The extent and gravity of the violation; (iii) The person's degree of culpability; (iv) The person's history of prior violations; (v) The person's ability to pay the civil penalty; (vi) The effect on the person's ability to continue in business; and (vii) Such other matters as justice may require. (b) <E T="03">Order assessing civil penalty</E>. An order assessing civil penalty may be issued for a violation described in paragraph (a) of this section, or as otherwise provided by statute, after notice and opportunity for a hearing. A person charged with a violation may be subject to an order assessing civil penalty in the following circumstances: (1) An order assessing civil penalty may be issued if a person charged with a violation submits or agrees to submit a civil penalty for a violation. (2) An order assessing civil penalty may be issued if a person charged with a violation does not request a hearing under paragraph (e)(2)(ii) of this section within 15 days after receipt of a final notice of proposed civil penalty. (3) Unless an appeal is filed with the FAA decisionmaker in a timely manner, an initial decision or order of an administrative law judge shall be considered an order assessing civil penalty if an administrative law judge finds that an alleged violation occurred and determines that a civil penalty, in an amount found appropriate by the administrative law judge, is warranted. (4) Unless a petition for review is filed with a U.S. Court of Appeals in a timely manner, a final decision and order of the Administrator shall be considered an order assessing civil penalty if the FAA decisionmaker finds that an alleged violation occurred and a civil penalty is warranted. (c) <E T="03">Delegation of authority</E>. The authority of the Administrator, under section 901 and section 905 of the Federal Aviation Act of 1958, as amended, and section 110 of the Hazardous Materials Transportation Act, to initiate and assess civil penalties for a violation of those Acts, or a rule, regulation, or order issued thereunder, is delegated to the Deputy Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel. The authority of the Administrator to refer cases to the Attorney General of the United States, or the delegate of the Attorney General, for the collection of civil penalties, is delegated to the Chief Counsel, the Deputy Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, the Aeronautical Center Counsel, and the Technical Center Counsel. (d) <E T="03">Notice of proposed civil penalty</E>. A civil penalty action is initiated by sending a notice of proposed civil penalty to the person charged with a violation of the Federal Aviation Act of 1958, as amended, the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder. A notice of proposed civil penalty will be sent to the individual charged with a violation or to the president of the corporation or company charged with a violation. In response to a notice of proposed civil penalty, a corporation or <PRTPAGE P="38"/>company may designate in writing another person to receive documents in that civil penalty action. The notice of proposed civil penalty contains a statement of the charges and the amount of the proposed civil penalty. Not later than 30 days after receipt of the notice of proposed civil penalty, the person charged with a violation shall— (1) Submit the amount of the proposed civil penalty or an agreed-upon amount, in which case either an order assessing civil penalty or compromise order shall be issued in that amount; (2) Submit to the agency attorney one of the following: (i) Written information, including documents and witness statements, demonstrating that a violation of the regulations did not occur or that a penalty or the amount of the penalty is not warranted by the circumstances. (ii) A written request to reduce the proposed civil penalty, the amount of reduction, and the reasons and any documents supporting a reduction of the proposed civil penalty, including records indicating a financial inability to pay or records showing that payment of the proposed civil penalty would prevent the person from continuing in business. (iii) A written request for an informal conference to discuss the matter with the agency attorney and to submit relevant information or documents; or (3) Request a hearing in which case a complaint shall be filed with the hearing docket clerk. (e) <E T="03">Final notice of proposed civil penalty</E>. A final notice of proposed civil penalty may be issued after participation in informal procedures provided in paragraph (d)(2) of this section or failure to respond in a time1y manner to a notice of proposed civil penalty. A final notice of proposed civil penalty will be sent to the individual charged with a violation, to the president of the corporation or company charged with a violation, or a person previously designated in writing by the individual, corporation, or company to receive documents in that civil penalty action. If not previously done in response to a notice of proposed civil penalty, a corporation or company may designate in writing another person to receive documents in that civil penalty action. The final notice of proposed civil penalty contains a statement of the charges and the amount of the proposed civil penalty and, as a result of information submitted to the agency attorney during informal procedures, may modify an allegation or a proposed civil penalty contained in a notice of proposed civil penalty. (1) A final notice of proposed civil penalty may be issued— (i) If the person charged with a violation fails to respond to the notice of proposed civil penalty within 30 days after receipt of that notice; or (ii) If the parties participated in any informal procedures under paragraph (d)(2) of this section and the parties have not agreed to compromise the action or the agency attorney has not agreed to withdraw the notice of proposed civil penalty. (2) Not later than 15 days after receipt of the final notice of proposed civil penalty, the person charged with a violation shall do one of the following— (i) Submit the amount of the proposed civil penalty or an agreed-upon amount, in which case either an order assessing civil penalty or a compromise order shall be issued in that amount; or (ii) Request a hearing in which case a complaint shall be filed with the hearing docket clerk. (f) <E T="03">Request for a hearing.</E> Any person charged with a violation may request a hearing, pursuant to paragraph (d)(3) or paragraph (e)(2)(ii) of this section, to be conducted in accordance with the procedures in subpart G of this part. A person requesting a hearing shall file a written request for a hearing with the hearing docket clerk (Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591, Attention: Hearing Docket Clerk) and shall mail a copy of the request to the agency attorney. The request for a hearing may be in the form of a letter but must be dated and signed by the person requesting a hearing. The request for a hearing may be typewritten or may be legibly handwritten. (g) <E T="03">Hearing.</E> If the person charged with a violation requests a hearing <PRTPAGE P="39"/>pursuant to paragraph (d)(3) or paragraph (e)(2)(ii) of this section, the original complaint shall be filed with the hearing docket clerk and a copy shall be sent to the person requesting the hearing. The procedural rules in subpart G of this part apply to the hearing and any appeal. At the close of the hearing, the administrative law judge shall issue, either orally on the record or in writing, an initial decision, including the reasons for the decision, that contains findings or conclusions on the allegations contained, and the civil penalty sought, in the complaint. (h) <E T="03">Appeal.</E> Either party may appeal the administrative law judge's initial decision to the FAA decisionmaker pursuant to the procedures in subpart G of this part. If a party files a notice of appeal pursuant to § 13.233 of subpart G, the effectiveness of the initial decision is stayed until a final decision and order of the Administrator have been entered on the record. The FAA decisionmaker shall review the record and issue a final decision and order of the Administrator that affirm, modify, or reverse the initial decision. The FAA decisionmaker may assess a civil penalty but shall not assess a civil penalty in an amount greater than that sought in the complaint. (i) <E T="03">Payment.</E> A person shall pay a civil penalty by sending a certified check or money order, payable to the Federal Aviation Administration, to the agency attorney. (j) <E T="03">Collection of civil penalties.</E> If a person does not pay a civil penalty imposed by an order assessing civil penalty or a compromise order within 60 days after service of the order, the Administrator may refer the order to the United States Attorney General, or the delegate of the Attorney General, to begin proceedings to collect the civil penalty. The action shall be brought in a United States District Court, pursuant to the authority in section 903 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1473), or section 110 of the Hazardous Materials Transportation Act (49 U.S.C. 1809). (k) <E T="03">Exhaustion of administrative remedies.</E> A party may only petition for review of a final decision and order of the Administrator to the courts of appeals of the United States or the United States Court of Appeals for the District of Columbia pursuant to section 1006 of the Federal Aviation Act of 1958, as amended. Neither an initial decision or order issued by an administrative law judge, that has not been appealed to the FAA decisionmaker, nor an order compromising a civil penalty action constitutes a final order of the Administrator for the purposes of judicial appellate review under section 1006 of the Federal Aviation Act of 1958, as amended. (l) <E T="03">Compromise.</E> The FAA may compromise any civil penalty action initiated in accordance with section 901 and section 905 of the Federal Aviation Act of 1958, as amended, involving an amount in controversy not exceeding $50,000, or any civil penalty action initiated in accordance with section 901 of the Federal Aviation Act of 1958, as amended, and section 110 of the Hazardous Materials Transportation Act, at any time before referring the action to the United States Attorney for collection. (1) An agency attorney may compromise any civil penalty action where a person charged with a violation agrees to pay a civil penalty and the FAA agrees to make no finding of violation. Pursuant to such agreement, a compromise order shall be issued, stating: (i) The person agrees to pay a civil penalty. (ii) The FAA makes no finding of a violation. (iii) The compromise order shall not be used as evidence of a prior violation in any subsequent civil penalty proceeding or certificate action proceeding. (2) An agency attorney may compromise the amount of any civil penalty proposed in a notice, assessed in an order, or imposed in a compromise order. <CITA>[Amdt. 13-21, 55 FR 27574, July 3, 1990; 55 FR 29293, July 18, 1990; 55 FR 31027, July 30, 1990; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.17</SECTNO> <SUBJECT>Seizure of aircraft.</SUBJECT> (a) Under section 903 of the Federal Aviation Act of 1958 (49 U.S.C. 1473), a <PRTPAGE P="40"/>State or Federal law enforcement officer, or a Federal Aviation Administration safety inspector, authorized in an order of seizure issued by the Regional Administrator of the region, or by the Chief Counsel, may summarily seize an aircraft that is involved in a violation for which a civil penalty may be imposed on its owner or operator. (b) Each person seizing an aircraft under this section shall place it in the nearest available and adequate public storage facility in the judicial district in which it was seized. (c) The Regional Administrator or Chief Counsel, without delay, sends a written notice and a copy of this section, to the registered owner of the seized aircraft, and to each other persons shown by FAA records to have an interest in it, stating the— (1) Time, date, and place of seizure; (2) Name and address of the custodian of the aircraft; (3) Reasons for the seizure, including the violations believed, or judicially determined, to have been committed; and (4) Amount that may be tendered as— (i) A compromise of a civil penalty for the alleged violation; or (ii) Payment for a civil penalty imposed by a Federal court for a proven violation. (d) The Chief Counsel, or the Regional Counsel or Assistant Chief Counsel for the region or area in which an aircraft is seized under this section, immediately sends a report to the United States District Attorney for the judicial district in which it was seized, requesting the District Attorney to institute proceedings to enforce a lien against the aircraft. (e) The Regional Administrator or Chief Counsel directs the release of a seized aircraft whenever— (1) The alleged violator pays a civil penalty or an amount agreed upon in compromise, and the costs of seizing, storing, and maintaining the aircraft; (2) The aircraft is seized under an order of a Federal Court in proceedings in rem to enforce a lien against the aircraft, or the United States District Attorney for the judicial district concerned notifies the FAA that the District Attorney refuses to institute those proceedings; or (3) A bond in the amount and with the sureties prescribed by the Chief Counsel, the Regional Counsel, or the Assistant Chief Counsel is deposited, conditioned on payment of the penalty, or the compromise amount, and the costs of seizing, storing, and maintaining the aircraft. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.19</SECTNO> <SUBJECT>Certificate action.</SUBJECT> (a) Under section 609 of the Federal Aviation Act of 1958 (49 U.S.C. 1429), the Administrator may reinspect any civil aircraft, aircraft engine, propeller, appliance, air navigation facility, or air agency, and may re-examine any civil airman. Under section 501(e) of the FA Act, any Certificate of Aircraft Registration may be suspended or revoked by the Administrator for any cause that renders the aircraft ineligible for registration. (b) If, as a result of such a reinspection re-examination, or other investigation made by the Administrator under section 609 of the FA Act, the Administrator determines that the public interest and safety in air commerce requires it, the Administrator may issue an order amending, suspending, or revoking, all or part of any type certificate, production certificate, airworthiness certificate, airman certificate, air carrier operating certificate, air navigation facility certificate, or air agency certificate. This authority may be exercised for remedial purposes in cases involving the Hazardous Materials Transportation Act (49 U.S.C. 1801 et seq.) or regulations issued under that Act. This authority is also exercised by the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, and the Aeronautical Center Counsel. If the Administrator finds that any aircraft registered under Part 47 of this chapter is ineligible for registration or if the <PRTPAGE P="41"/>holder of a Certificate of Aircraft Registration has refused or failed to submit AC Form 8050-73, as required by § 47.51 of this chapter, the Administrator issues an order suspending or revoking that certificate. This authority as to aircraft found ineligible for registration is also exercised by each Regional Counsel, the Aeronautical Center Counsel, and the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office. (c) Before issuing an order under paragraph (b) of this section, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, or the Aeronautical Center Counsel advises the certificate holder of the charges or other reasons upon which the Administrator bases the proposed action and, except in an emergency, allows the holder to answer any charges and to be heard as to why the certificate should not be amended, suspended, or revoked. The holder may, by checking the appropriate box on the form that is sent to the holder with the notice of proposed certificate action, elect to— (1) Admit the charges and surrender his or her certificate; (2) Answer the charges in writing; (3) Request that an order be issued in accordance with the notice of proposed certificate action so that the certificate holder may appeal to the National Transportation Safety Board, if the charges concerning a matter under Title VI of the FA Act; (4) Request an opportunity to be heard in an informal conference with the FAA counsel; or (5) Request a hearing in accordance with Subpart D of this part if the charges concern a matter under Title V of the FA Act. <FP>Except as provided in § 13.35(b), unless the certificate holder returns the form and, where required, an answer or motion, with a postmark of not later than 15 days after the date of receipt of the notice, the order of the Administrator is issued as proposed. If the certificate holder has requested an informal conference with the FAA counsel and the charges concern a matter under Title V of the FA Act, the holder may after that conference also request a formal hearing in writing with a postmark of not later than 10 days after the close of the conference. After considering any information submitted by the certificate holder, the Chief Counsel, the Assistant Chief Counsel for Regulations and Enforcement, the Regional Counsel concerned, or the Aeronautical Center Counsel (as to matters under Title V of the FA Act) issues the order of the Administrator, except that if the holder has made a valid request for a formal hearing on a matter under Title V of the FA Act initially or after an informal conference, Subpart D of this part governs further proceedings.</FP> (d) Any person whose certificate is affected by an order issued under this section may appeal to the National Transportation Safety Board. If the certificate holder files an appeal with the Board, the Administrator's order is stayed unless the Administrator advises the Board that an emergency exists and safety in air commerce requires that the order become effective immediately. If the Board is so advised, the order remains effective and the Board shall finally dispose of the appeal within 60 days after the date of the advice. This paragraph does not apply to any person whose Certificate of Aircraft Registration is affected by an order issued under this section. <CITA>[Doc. No. 13-14, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-15, 45 FR 20773, Mar. 31, 1980; Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.20</SECTNO> <SUBJECT>Orders of compliance, cease and desist orders, orders of denial, and other orders.</SUBJECT> (a) This section applies to orders of compliance, cease and desist orders, orders of denial, and other orders issued by the Administrator to carry out the provisions of the Federal Aviation Act of 1958, as amended, the Hazardous Materials Transportation Act, the Airport and Airway Development Act of 1970, and the Airport and Airway Improvement Act of 1982, or the Airport and Airway Improvement Act of 1982 as amended by the Airport and Airway Safety and Capacity Expansion Act of 1987. This section does not apply to orders issued pursuant to section 602 or <PRTPAGE P="42"/>section 609 of the Federal Aviation Act of 1958, as amended. (b) Unless the Administrator determines that an emergency exists and safety in air commerce requires the immediate issuance of an order under this section, the person subject to the order shall be provided with notice prior to issuance. (c) Within 30 days after service of the notice, the person subject to the order may reply in writing or request a hearing in accordance with Subpart D of this part. (d) If a reply is filed, as to any charges not dismissed or not subject to a consent order, the person subject to the order may, within 10 days after receipt of notice that the remaining charges are not dismissed, request a hearing in accordance with Subpart D of this part. (e) Failure to request a hearing within the period provided in paragraphs (c) or (d) of this section— (1) Constitutes a waiver of the right to appeal and the right to a hearing, and (2) Authorizes the official who issued the notice to find the facts to be as alleged in the notice, or as modified as the official may determine necessary based on any written response, and to issue an appropriate order, without further notice or proceedings. (f) If a hearing is requested in accordance with paragraph (c) or (d) of this section, the procedure of Subpart D of this part applies. At the close of the hearing, the Hearing Officer, on the record or subsequently in writing, shall set forth findings and conclusions and the reasons therefor, and either— (1) Dismiss the notice; or (2) Issue an order. (g) Any party to the hearing may appeal from the order of the Hearing Officer by filing a notice of appeal with the Administrator within 20 days after the date of issuance of the order. (h) If a notice of appeal is not filed from the order issued by a Hearing Officer, such order is the final agency order. (i) Any person filing an appeal authorized by paragraph (g) of this section shall file an appeal brief with the Administrator within 40 days after the date of issuance of the order, and serve a copy on the other party. A reply brief must be filed within 20 days after service of the appeal brief and a copy served on the appellant. (j) On appeal the Administrator reviews the available record of the proceeding, and issues an order dismissing, reversing, modifying or affirming the order. The Administrator's order includes the reasons for the Administrator's action. (k) For good cause shown, requests for extensions of time to file any document under this section may be granted by— (1) The official who issued the order, if the request is filed prior to the designation of a Hearing Officer; or (2) The Hearing Officer, if the request is filed prior to the filing of a notice of appeal; or (3) The Administrator, if the request is filed after the filing of a notice of appeal. (l) Except in the case of an appeal from the decision of a Hearing Officer, the authority of the Administrator under this section is also exercised by the Chief Counsel, Deputy Chief Counsel, each Assistant Chief Counsel, each Regional Counsel, and the Aeronautical Center Counsel (as to matters under Title V of the Federal Aviation Act of 1958). (m) Filing and service of documents under this section shall be accomplished in accordance with § 13.43; and the periods of time specified in this section shall be computed in accordance with § 13.44. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-17, 53 FR 33783, Aug. 31, 1988; Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46865, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.21</SECTNO> <SUBJECT>Military personnel.</SUBJECT> If a report made under this part indicates that, while performing official duties, a member of the Armed Forces, or a civilian employee of the Department of Defense who is subject to the Uniform Code of Military Justice (10 U.S.C. Ch. 47), has violated the Federal Aviation Act of 1958, or a regulation or order issued under it, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East <PRTPAGE P="43"/>Area Office, each Regional Counsel, and the Aeronautical Center Counsel send a copy of the report to the appropriate military authority for such disciplinary action as that authority considers appropriate and a report to the Administrator thereon. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.23</SECTNO> <SUBJECT>Criminal penalties.</SUBJECT> (a) Sections 902 and 1203 of the Federal Aviation Act of 1958 (49 U.S.C. 1472 and 1523), provide criminal penalties for any person who knowingly and willfully violates specified provisions of that Act, or any regulation or order issued under those provisions. Section 110(b) of the Hazardous Materials Transportation Act (49 U.S.C. 1809(b)) provides for a criminal penalty of a fine of not more than $25,000, imprisonment for not more than five years, or both, for any person who willfully violates a provision of that Act or a regulation or order issued under it. (b) If an inspector or other employee of the FAA becomes aware of a possible violation of any criminal provision of the Federal Aviation Act of 1958 (except a violation of section 902 (i) through (m) which is reported directly to the Federal Bureau of Investigation), or of the Hazardous Materials Transportation Act, relating to the transportation or shipment by air of hazardous materials, he or she shall report it to the Office of the Chief Counsel or the Regional Counsel or Assistant Chief Counsel for the region or area concerned. If appropriate, that office refers the report to the Department of Justice for criminal prosecution of the offender. If such an inspector or other employee becomes aware of a possible violation of a Federal statute that is within the investigatory jurisdiction of another Federal agency, he or she shall immediately report it to that agency according to standard FAA practices. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.25</SECTNO> <SUBJECT>Injunctions.</SUBJECT> (a) Whenever it is determined that a person has engaged, or is about to engage, in any act or practice constituting a violation of the Federal Aviation Act of 1958, or any regulation or order issued under it for which the FAA exercises enforcement responsibility, or, with respect to the transportation or shipment by air of any hazardous materials, in any act or practice constituting a violation of the Hazardous Materials Transportation Act, or any regulation or order issued under it for which the FAA exercises enforcement responsibility, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, and the Aeronautical Center Counsel may request the United States Attorney General, or the delegate of the Attorney General, to bring an action in the appropriate United States District Court for such relief as is necessary or appropriate, including mandatory or prohibitive injunctive relief, interim equitable relief, and punitive damages, as provided by section 1007 of the Federal Aviation Act of 1958 (49 U.S.C. 1487) and section 111(a) of the Hazardous Materials Transportation Act (49 U.S.C. 1810). (b) Whenever it is determined that there is substantial likelihood that death, serious illness, or severe personal injury, will result from the transportation by air of a particular hazardous material before an order of compliance proceeding, or other administrative hearing or formal proceeding to abate the risk of the harm can be completed, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, and the Aeronautical Center Counsel may bring, or request the United States Attorney General to bring, an action in the appropriate United States District Court for an order suspending or restricting the transportation by air of the hazardous material or for such other order as is necessary to eliminate or ameliorate the imminent hazard, as provided by <PRTPAGE P="44"/>section 111(b) of the Hazardous Materials Transportation Act (49 U.S.C. 1810). <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.27</SECTNO> <SUBJECT>Final order of Hearing Officer in certificate of aircraft registration proceedings.</SUBJECT> (a) If, in proceedings under section 501(b) of the Federal Aviation Act of 1958 (49 USC 1401), the Hearing Officer determines that the holder of the Certificate of Aircraft Registration has refused or failed to submit AC Form 8050-73, as required by § 47.51 of this chapter, or that the aircraft is ineligible for a Certificate of Aircraft Registration, the Hearing Officer shall suspend or revoke the respondent's certificate, as proposed in the notice of proposed certificate action. (b) If the final order of the Hearing Officer makes a decision on the merits, it shall contain a statement of the findings and conclusions of law on all material issues of fact and law. If the Hearing Officer finds that the allegations of the notice have been proven, but that no sanction is required, the Hearing Officer shall make appropriate findings and issue an order terminating the notice. If the Hearing Officer finds that the allegations of the notice have not been proven, the Hearing Officer shall issue an order dismissing the notice. If the Hearing Officer finds it to be equitable and in the public interest, the Hearing Officer shall issue an order terminating the proceeding upon payment by the respondent of a civil penalty in an amount agreed upon by the parties. (c) If the order is issued in writing, it shall be served upon the parties. <CITA>[Doc. No. 13-14, 44 FR 63723, Nov. 5, 1979; as amended by Amdt. 13-15, 45 FR 20773, Mar. 31, 1980]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.29</SECTNO> <SUBJECT>Civil penalties: Streamlined enforcement procedures for certain security violations.</SUBJECT> This section may be used, at the agency's discretion, in enforcement actions involving individuals presenting dangerous or deadly weapons for screening at airports or in checked baggage where the amount of the proposed civil penalty is less than $5,000. In these cases, sections 13.16(a), 13.16(c), and 13.16 (f) through (l) of this chapter are used, as well as paragraphs (a) through (d) of this section: (a) <E T="03">Delegation of authority.</E> The authority of the Administrator, under 49 U.S.C. 46301, to initiate the assessment of civil penalties for a violation of 49 U.S.C. Subtitle VII, or a rule, regulation, or order issued thereunder, is delegated to the regional Civil Aviation Security Division Manager and the regional Civil Aviation Security Deputy Division Manager for the purpose of issuing notices of violation in cases involving violations of 49 U.S.C. Subtitle VII and the FAA's regulations by individuals presenting dangerous or deadly weapons for screening at airport checkpoints or in checked baggage. This authority may not be delegated below the level of the regional Civil Aviation Security Deputy Division Manager. (b) <E T="03">Notice of violation.</E> A civil penalty action is initiated by sending a notice of violation to the person charged with the violation. The notice of violation contains a statement of the charges and the amount of the proposed civil penalty. Not later than 30 days after receipt of the notice of violation, the person charged with a violation shall: (1) Submit the amount of the proposed civil penalty or an agreed-upon amount, in which case either an order assessing a civil penalty or a compromise order shall be issued in that amount; or (2) Submit to the agency attorney identified in the material accompanying the notice any of the following: (i) Written information, including documents and witness statements, demonstrating that a violation of the regulations did not occur or that a penalty or the penalty amount is not warranted by the circumstances; or (ii) A written request to reduce the proposed civil penalty, the amount of reduction, and the reasons and any documents supporting a reduction of the proposed civil penalty, including records indicating a financial inability to pay or records showing that payment of the proposed civil penalty would prevent the person from continuing in business; or<PRTPAGE P="45"/> (iii) A written request for an informal conference to discuss the matter with an agency attorney and submit relevant information or documents; or (3) Request a hearing in which case a complaint shall be filed with the hearing docket clerk. (c) <E T="03">Final notice of violation and civil penalty assessment order.</E> A final notice of violation and civil penalty assessment order (“final notice and order”) may be issued after participation in any informal proceedings as provided in paragraph (b)(2) of this section, or after failure of the respondent to respond in a timely manner to a notice of violation. A final notice and order will be sent to the individual charged with a violation. The final notice and order will contain a statement of the charges and the amount of the proposed civil penalty and, as a result of information submitted to the agency attorney during any informal procedures, may reflect a modified allegation or proposed civil penalty. A final notice and order may be issued— (1) If the person charged with a violation fails to respond to the notice of violation within 30 days after receipt of that notice; or (2) If the parties participated in any informal procedures under paragraph (b)(2) of this section and the parties have not agreed to compromise the action or the agency attorney has not agreed to withdraw the notice of violation. (d) <E T="03">Order assessing civil penalty.</E> An order assessing civil penalty may be issued after notice and opportunity for a hearing. A person charged with a violation may be subject to an order assessing civil penalty in the following circumstances: (1) An order assessing civil penalty may be issued if a person charged with a violation submits, or agrees to submit, the amount of civil penalty proposed in the notice of violation. (2) An order assessing civil penalty may be issued if a person charged with a violation submits, or agrees to submit, an agreed-upon amount of civil penalty that is not reflected in either the notice of violation or the final notice and order. (3) The final notice and order becomes (and contains a statement so indicating) an order assessing a civil penalty when the person charged with a violation submits the amount of the proposed civil penalty that is reflected in the final notice and order. (4) The final notice and order becomes (and contains a statement so indicating) an order assessing a civil penalty 16 days after receipt of the final notice and order, <E T="03">unless</E> not later than 15 days after receipt of the final notice and order, the person charged with a violation does one of the following— (i) Submits an agreed-upon amount of civil penalty that is not reflected in the final notice and order, in which case an order assessing civil penalty or a compromise order shall be issued in that amount; or (ii) Requests a hearing in which case a complaint shall be filed with the hearing docket clerk. (5) Unless an appeal is filed with the FAA decisionmaker in a timely manner, an initial decision or order of an administrative law judge shall be considered an order assessing civil penalty if an administrative law judge finds that an alleged violation occurred and determines that a civil penalty, in an amount found to be appropriate by the administrative law judge, is warranted. (6) Unless a petition for review is filed with a U.S. Court of Appeals in a timely manner, a final decision and order of the Administrator shall be considered an order assessing civil penalty if the FAA decisionmaker finds that an alleged violation occurred and a civil penalty is warranted. <CITA>[Doc. No. 27873, 61 FR 44155, Aug. 28, 1996]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Rules of Practice for FAA Hearings</HD> <SECTION> <SECTNO>§ 13.31</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart applies to proceedings in which a hearing has been requested in accordance with §§ 13.19(c)(5), 13.20(c), 13.20(d), 13.75(a)(2), 13.75(b), or 13.81(e). <CITA>[Amdt. 13-18, 53 FR 34655, Sept. 7, 1988]</CITA> </SECTION> <SECTION> <PRTPAGE P="46"/> <SECTNO>§ 13.33</SECTNO> <SUBJECT>Appearances.</SUBJECT> Any party to a proceeding under this subpart may appear and be heard in person or by attorney. </SECTION> <SECTION> <SECTNO>§ 13.35</SECTNO> <SUBJECT>Request for hearing.</SUBJECT> (a) A request for hearing must be made in writing to the Hearing Docket, Room 924A, Federal Aviation Administration, 800 Independence Avenue, S.W., Washington, D.C. 20591. It must describe briefly the action proposed by the FAA, and must contain a statement that a hearing is requested. A copy of the request for hearing and a copy of the answer required by paragraph (b) of this section must be served on the official who issued the notice of proposed action. (b) An answer to the notice of proposed action must be filed with the request for hearing. All allegations in the notice not specifically denied in the answer are deemed admitted. (c) Within 15 days after service of the copy of the request for hearing, the official who issued the notice of proposed action forwards a copy of that notice, which serves as the complaint, to the Hearing Docket. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.37</SECTNO> <SUBJECT>Hearing Officer's powers.</SUBJECT> Any Hearing Officer may— (a) Give notice concerning, and hold, prehearing conferences and hearings; (b) Administrator oaths and affirmations; (c) Examine witnesses; (d) Adopt procedures for the submission of evidence in written form; (e) Issue subpoenas and take depositions or cause them to be taken; (f) Rule on offers of proof; (g) Receive evidence; (h) Regulate the course of the hearing; (i) Hold conferences, before and during the hearing, to settle and simplify issues by consent of the parties; (j) Dispose of procedural requests and similar matters; and (k) Issue decisions, make findings of fact, make assessments, and issue orders, as appropriate. </SECTION> <SECTION> <SECTNO>§ 13.39</SECTNO> <SUBJECT>Disqualification of Hearing Officer.</SUBJECT> If disqualified for any reason, the Hearing Officer shall withdraw from the case. </SECTION> <SECTION> <SECTNO>§ 13.41</SECTNO> <RESERVED>[Reserved]</RESERVED> </SECTION> <SECTION> <SECTNO>§ 13.43</SECTNO> <SUBJECT>Service and filing of pleadings, motions, and documents.</SUBJECT> (a) Copies of all pleadings, motions, and documents filed with the Hearing Docket must be served upon all parties to the proceedings by the person filing them. (b) Service may be made by personal delivery or by mail. (c) A certificate of service shall accompany all documents when they are tendered for filing and shall consist of a certificate of personal delivery or a certificate of mailing, executed by the person making the personal delivery or mailing the document. (d) Whenever proof of service by mail is made, the date of mailing or the date as shown on the postmark shall be the date of service, and where personal service is made, the date of personal delivery shall be the date of service. (e) The date of filing is the date the document is actually received. </SECTION> <SECTION> <SECTNO>§ 13.44</SECTNO> <SUBJECT>Computation of time and extension of time.</SUBJECT> (a) In computing any period of time prescribed or allowed by this subpart, the date of the act, event, default, notice or order after which the designated period of time begins to run is not to be included in the computation. The last day of the period so computed is to be included unless it is a Saturday, Sunday, or legal holiday for the FAA, in which event the period runs until the end of the next day which is neither a Saturday, Sunday nor a legal holiday. (b) Upon written request filed with the Hearing Docket and served upon all parties, and for good cause shown, a Hearing Officer may grant an extension of time to file any documents specified in this subpart. </SECTION> <SECTION> <SECTNO>§ 13.45</SECTNO> <SUBJECT>Amendment of notice and answer.</SUBJECT> At any time more than 10 days before the date of hearing, any party may <PRTPAGE P="47"/>amend his or her notice, answer, or other pleading, by filing the amendment with the Hearing Officer and serving a copy of it on each other party. After that time, amendments may be allowed only in the discretion of the Hearing Officer. If an amendment to an initial pleading has been allowed, the Hearing Officer shall allow the other parties a reasonable opportunity to answer. </SECTION> <SECTION> <SECTNO>§ 13.47</SECTNO> <SUBJECT>Withdrawal of notice or request for hearing.</SUBJECT> At any time before the hearing, the FAA counsel may withdraw the notice of proposed action, and the party requesting the hearing may withdraw the request for hearing. </SECTION> <SECTION> <SECTNO>§ 13.49</SECTNO> <SUBJECT>Motions.</SUBJECT> (a) <E T="03">Motion to dismiss for insufficiency.</E> A respondent who requests a formal hearing may, in place of an answer, file a motion to dismiss for failure of the allegations in the notice of proposed action to state a violation of the FA Act or of this chapter or to show lack of qualification of the respondent. If the Hearing Officer denies the motion, the respondent shall file an answer within 10 days. (b) [Reserved] (c) <E T="03">Motion for more definite statement.</E> The certificate holder may, in place of an answer, file a motion that the allegations in the notice be made more definite and certain. If the Hearing Officer grants the motion, the FAA counsel shall comply within 10 days after the date it is granted. If the Hearing Officer denies the motion the certificate holder shall file an answer within 10 days after the date it is denied. (d) <E T="03">Motion for judgment on the pleadings.</E> After the pleadings are closed, either party may move for a judgment on the pleadings. (e) <E T="03">Motion to strike.</E> Upon motion of either party, the Hearing Officer may order stricken, from any pleadings, any insufficient allegation or defense, or any immaterial, impertinent, or scandalous matter. (f) <E T="03">Motion for production of documents.</E> Upon motion of any party showing good cause, the Hearing Officer may, in the manner provided by Rule 34, Federal Rules of Civil Procedure, order any party to produce any designated document, paper, book, account, letter, photograph, object, or other tangible thing, that is not privileged, that constitutes or contains evidence relevant to the subject matter of the hearings, and that is in the party's possession, custody, or control. (g) <E T="03">Consolidation of motions.</E> A party who makes a motion under this section shall join with it all other motions that are then available to the party. Any objection that is not so raised is considered to be waived. (h) <E T="03">Answers to motions.</E> Any party may file an answer to any motion under this section within 5 days after service of the motion. </SECTION> <SECTION> <SECTNO>§ 13.51</SECTNO> <SUBJECT>Intervention.</SUBJECT> Any person may move for leave to intervene in a proceeding and may become a party thereto, if the Hearing Officer, after the case is sent to the Hearing Officer for hearing, finds that the person may be bound by the order to be issued in the proceedings or has a property or financial interest that may not be adequately represented by existing parties, and that the intervention will not unduly broaden the issues or delay the proceedings. Except for good cause shown, a motion for leave to intervene may not be considered if it is filed less than 10 days before the hearing. </SECTION> <SECTION> <SECTNO>§ 13.53</SECTNO> <SUBJECT>Depositions.</SUBJECT> After the respondent has filed a request for hearing and an answer, either party may take testimony by deposition in accordance with section 1004 of the Federal Aviation Act of 1958 (49 U.S.C. 1484) or Rule 26, Federal Rules of Civil Procedure. </SECTION> <SECTION> <SECTNO>§ 13.55</SECTNO> <SUBJECT>Notice of hearing.</SUBJECT> The Hearing Officer shall set a reasonable date, time, and place for the hearing, and shall give the parties adequate notice thereof and of the nature of the hearing. Due regard shall be given to the convenience of the parties with respect to the place of the hearing. </SECTION> <SECTION> <SECTNO>§ 13.57</SECTNO> <SUBJECT>Subpoenas and witness fees.</SUBJECT> (a) The Hearing Officer to whom a case is assigned may, upon application <PRTPAGE P="48"/>by any party to the proceeding, issue subpoenas requiring the attendance of witnesses or the production of documentary or tangible evidence at a hearing or for the purpose of taking depositions. However, the application for producing evidence must show its general relevance and reasonable scope. This paragraph does not apply to the attendance of FAA employees or to the production of documentary evidence in the custody of such an employee at a hearing. (b) A person who applies for the production of a document in the custody of an FAA employee must follow the procedure in § 13.49(f). A person who applies for the attendance of an FAA employee must send the application, in writing, to the Hearing Officer setting forth the need for that employee's attendance. (c) A witness in a proceeding under this subpart is entitled to the same fees and mileage as is paid to a witness in a court of the United States under comparable circumstances. The party at whose instance the witness is subpoenaed or appears shall pay the witness fees. (d) Notwithstanding the provisions of paragraph (c) of this section, the FAA pays the witness fees and mileage if the Hearing Officer who issued the subpoena determines, on the basis of a written request and good cause shown, that— (1) The presence of the witness will materially advance the proceeding; and (2) The party at whose instance the witness is subpoenaed would suffer a serious hardship if required to pay the witness fees and mileage. </SECTION> <SECTION> <SECTNO>§ 13.59</SECTNO> <SUBJECT>Evidence.</SUBJECT> (a) Each party to a hearing may present the party's case or defense by oral or documentary evidence, submit evidence in rebuttal, and conduct such cross-examination as may be needed for a full disclosure of the facts. (b) Except with respect to affirmative defenses and orders of denial, the burden of proof is upon the FAA counsel. (c) The Hearing Officer may order information contained in any report or document filed or in any testimony given pursuant to this subpart withheld from public disclosure when, in the judgment of the Hearing Officer, disclosure would adversely affect the interests of any person and is not required in the public interest or is not otherwise required by statute to be made available to the public. Any person may make written objection to the public disclosure of such information, stating the ground for such objection. </SECTION> <SECTION> <SECTNO>§ 13.61</SECTNO> <SUBJECT>Argument and submittals.</SUBJECT> The Hearing Officer shall give the parties adequate opportunity to present arguments in support of motions, objections, and the final order. The Hearing Officer may determine whether arguments are to be oral or written. At the end of the hearing the Hearing Officer may, in the discretion of the Hearing Officer, allow each party to submit written proposed findings and conclusions and supporting reasons for them. </SECTION> <SECTION> <SECTNO>§ 13.63</SECTNO> <SUBJECT>Record.</SUBJECT> The testimony and exhibits presented at a hearing, together with all papers, requests, and rulings filed in the proceedings are the exclusive basis for the issuance of an order. Either party may obtain a transcript from the official reporter upon payment of the fees fixed therefor. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Orders of Compliance Under the Hazardous Materials Transportation Act</HD> <SECTION> <SECTNO>§ 13.71</SECTNO> <SUBJECT>Applicability.</SUBJECT> Whenever the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, or a Regional Counsel has reason to believe that a person is engaging in the transportation or shipment by air of hazardous materials in violation of the Hazardous Materials Transportation Act, or any regulation or order issued under it for which the FAA exercises enforcement responsibility, and the circumstances do not require the issuance of an order of immediate compliance, he may conduct proceedings pursuant to section 109 of that Act (49 U.S.C. 1808) to determine the nature and extent of the violation, and may <PRTPAGE P="49"/>thereafter issue an order directing compliance. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.73</SECTNO> <SUBJECT>Notice of proposed order of compliance.</SUBJECT> A compliance order proceeding commences when the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, or a Regional Counsel sends the alleged violator a notice of proposed order of compliance advising the alleged violator of the charges and setting forth the remedial action sought in the form of a proposed order of compliance. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.75</SECTNO> <SUBJECT>Reply or request for hearing.</SUBJECT> (a) Within 30 days after service upon the alleged violator of a notice of proposed order of compliance, the alleged violator may— (1) File a reply in writing with the official who issued the notice; or (2) Request a hearing in accordance with Subpart D of this part. (b) If a reply is filed, as to any charges not dismissed or not subject to a consent order of compliance, the alleged violator may, within 10 days after receipt of notice that the remaining charges are not dismissed, request a hearing in accordance with Subpart D of this part. (c) Failure of the alleged violator to file a reply or request a hearing within the period provided in paragraph (a) or (b) of this section— (1) Constitutes a waiver of the right to a hearing and the right to an appeal, and (2) Authorizes the official who issued the notice to find the facts to be as alleged in the notice and to issue an appropriate order directing compliance, without further notice or proceedings. </SECTION> <SECTION> <SECTNO>§ 13.77</SECTNO> <SUBJECT>Consent order of compliance.</SUBJECT> (a) At any time before the issuance of an order of compliance, the official who issued the notice and the alleged violator may agree to dispose of the case by the issuance of a consent order of compliance by the official. (b) A proposal for a consent order submitted to the official who issued the notice under this section must include— (1) A proposed order of compliance; (2) An admission of all jurisdictional facts; (3) An express waiver of right to further procedural steps and of all rights to judicial review; (4) An incorporation by reference of the notice and an acknowledgement that the notice may be used to construe the terms of the order of compliance; and (5) If the issuance of a consent order has been agreed upon after the filing of a request for hearing in accordance with Subpart D of this part, the proposal for a consent order shall include a request to be filed with the Hearing Officer withdrawing the request for a hearing and requesting that the case be dismissed. </SECTION> <SECTION> <SECTNO>§ 13.79</SECTNO> <SUBJECT>Hearing.</SUBJECT> If an alleged violator requests a hearing in accordance with § 13.75, the procedure of Subpart D of this part applies. At the close of the hearing, the Hearing Officer, on the record or subsequently in writing, sets forth the Hearing Officer's findings and conclusion and the reasons therefor, and either— (a) Dismisses the notice of proposed order of compliance; or (b) Issues an order of compliance. </SECTION> <SECTION> <SECTNO>§ 13.81</SECTNO> <SUBJECT>Order of immediate compliance.</SUBJECT> (a) Notwithstanding §§ 13.73 through 13.79, the Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, or a Regional Counsel may issue an order of immediate compliance, which is effective upon issuance, if the person who issues the order finds that— (1) There is strong probability that a violation is occurring or is about to occur; (2) The violation poses a substantial risk to health or to safety of life or property; and<PRTPAGE P="50"/> (3) The public interest requires the avoidance or amelioration of that risk through immediate compliance and waiver of the procedures afforded under §§ 13.73 through 13.79. (b) An order of immediate compliance is served promptly upon the person against whom the order is issued by telephone or telegram, and a written statement of the relevant facts and the legal basis for the order, including the findings required by paragraph (a) of this section, is served promptly by personal service or by mail. (c) The official who issued the order of immediate compliance may rescind or suspend the order if it appears that the criteria set forth in paragraph (a) of this section are no longer satisfied, and, when appropriate, may issue a notice of proposed order of compliance under § 13.73 in lieu thereof. (d) If at any time in the course of a proceeding commenced in accordance with § 13.73 the criteria set forth in paragraph (a) of this section are satisfied, the official who issued the notice may issue an order of immediate compliance, even if the period for filing a reply or requesting a hearing specified in § 13.75 has not expired. (e) Within three days after receipt of service of an order of immediate compliance, the alleged violator may request a hearing in accordance with Subpart D of this part and the procedure in that subpart will apply except that— (1) The case will be heard within fifteen days after the date of the order of immediate compliance unless the alleged violator requests a later date; (2) The order will serve as the complaint; and (3) The Hearing Officer shall issue his decision and order dismissing, reversing, modifying, or affirming the order of immediate compliance on the record at the close of the hearing. (f) The filing of a request for hearing in accordance with paragraph (e) of this section does not stay the effectiveness of an order of immediate compliance. (g) At any time after an order of immediate compliance has become effective, the official who issued the order may request the United States Attorney General, or the delegate of the Attorney General, to bring an action for appropriate relief in accordance with § 13.25. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 13-19, 54 FR 39290, Sept. 25, 1989; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.83</SECTNO> <SUBJECT>Appeal.</SUBJECT> (a) Any party to the hearing may appeal from the order of the Hearing Officer by filing a notice of appeal with the Administrator within 20 days after the date of issuance of the order. (b) Any person against whom an order of immediate compliance has been issued in accordance with § 13.81 or the official who issued the order of immediate compliance may appeal from the order of the Hearing Officer by filing a notice of appeal with the Administrator within three days after the date of issuance of the order by the Hearing Officer. (c) Unless the Administrator expressly so provides, the filing of a notice of appeal does not stay the effectiveness of an order of immediate compliance. (d) If a notice of appeal is not filed from the order of compliance issued by a Hearing Officer, such order is the final agency order of compliance. (e) Any person filing an appeal authorized by paragraph (a) of this section shall file an appeal brief with the Administrator within 40 days after the date of the issuance of the order, and serve a copy on the other party. Any reply brief must be filed within 20 days after service of the appeal brief. A copy of the reply brief must be served on the appellant. (f) Any person filing an appeal authorized by paragraph (b) of this section shall file an appeal brief with the Administrator with the notice of appeal and serve a copy on the other party. Any reply brief must be filed within 3 days after receipt of the appeal brief. A copy of the reply brief must be served on the appellant. (g) On appeal the Administrator reviews the available record of the proceeding, and issues an order dismissing, reversing, modifying or affirming the <PRTPAGE P="51"/>order of compliance or the order of immediate compliance. The Administrator's order includes the reasons for the action. (h) In cases involving an order of immediate compliance, the Administrator's order on appeal is issued within ten days after the filing of the notice of appeal. </SECTION> <SECTION> <SECTNO>§ 13.85</SECTNO> <SUBJECT>Filing, service and computation of time.</SUBJECT> Filing and service of documents under this subpart shall be accomplished in accordance with § 13.43 except service of orders of immediate compliance under § 13.81(b); and the periods of time specified in this subpart shall be computed in accordance with § 13.44. </SECTION> <SECTION> <SECTNO>§ 13.87</SECTNO> <SUBJECT>Extension of time.</SUBJECT> (a) The official who issued the notice of proposed order of compliance, for good cause shown, may grant an extension of time to file any document specified in this subpart, except documents to be filed with the Administrator. (b) Extensions of time to file documents with the Administrator may be granted by the Administrator upon written request, served upon all parties, and for good cause shown. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Formal Fact-Finding Investigation Under an Order of Investigation</HD> <SECTION> <SECTNO>§ 13.101</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart applies to fact-finding investigations in which an order of investigation has been issued under § 13.3(c) or § 13.5(i) of this part. (b) This subpart does not limit the authority of duly designated persons to issue subpoenas, administer oaths, examine witnesses and receive evidence in any informal investigation as provided for in sections 313 and 1004(a) of the Federal Aviation Act (49 U.S.C. 1354 and 1484(a)) and section 109(a) of the Hazardous Materials Transportation Act (49 U.S.C. 1808(a)). </SECTION> <SECTION> <SECTNO>§ 13.103</SECTNO> <SUBJECT>Order of investigation.</SUBJECT> The order of investigation— (a) Defines the scope of the investigation by describing the information sought in terms of its subject matter or its relevancy to specified FAA functions; (b) Sets forth the form of the investigation which may be either by individual deposition or investigative proceeding or both; and (c) Names the official who is authorized to conduct the investigation and serve as the Presiding Officer. </SECTION> <SECTION> <SECTNO>§ 13.105</SECTNO> <SUBJECT>Notification.</SUBJECT> Any person under investigation and any person required to testify and produce documentary or physical evidence during the investigation will be advised of the purpose of the investigation, and of the place where the investigative proceeding or deposition will be convened. This may be accomplished by a notice of investigation or by a subpoena. A copy of the order of investigation may be sent to such persons, when appropriate. </SECTION> <SECTION> <SECTNO>§ 13.107</SECTNO> <SUBJECT>Designation of additional parties.</SUBJECT> (a) The Presiding Officer may designate additional persons as parties to the investigation, if in the discretion of the Presiding Officer, it will aid in the conduct of the investigation. (b) The Presiding Officer may designate any person as a party to the investigation if that person— (1) Petitions the Presiding Officer to participate as a party; and (2) Is so situated that the disposition of the investigation may as a practical matter impair the ability to protect that person's interest unless allowed to participate as a party, and (3) Is not adequately represented by existing parties. </SECTION> <SECTION> <SECTNO>§ 13.109</SECTNO> <SUBJECT>Convening the investigation.</SUBJECT> The investigation shall be conducted at such place or places designated by the Presiding Officer, and as convenient to the parties involved as expeditious and efficient handling of the investigation permits. </SECTION> <SECTION> <SECTNO>§ 13.111</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> (a) Upon motion of the Presiding Officer, or upon the request of a party to the investigation, the Presiding Officer may issue a subpoena directing any person to appear at a designated time <PRTPAGE P="52"/>and place to testify or to produce documentary or physical evidence relating to any matter under investigation. (b) Subpoenas shall be served by personal service, or upon an agent designated in writing for the purpose, or by registered or certified mail addressed to such person or agent. Whenever service is made by registered or certified mail, the date of mailing shall be considered as the time when service is made. (c) Subpoenas shall extend in jurisdiction throughout the United States or any territory or possession thereof. </SECTION> <SECTION> <SECTNO>§ 13.113</SECTNO> <SUBJECT>Noncompliance with the investigative process.</SUBJECT> If any person fails to comply with the provisions of this subpart or with any subpoena or order issued by the Presiding Officer or the designee of the Presiding Officer, judicial enforcement may be initiated against that person under applicable statutes. </SECTION> <SECTION> <SECTNO>§ 13.115</SECTNO> <SUBJECT>Public proceedings.</SUBJECT> (a) All investigative proceedings and depositions shall be public unless the Presiding Officer determines that the public interest requires otherwise. (b) The Presiding Officer may order information contained in any report or document filed or in any testimony given pursuant to this subpart withheld from public disclosure when, in the judgment of the Presiding Officer, disclosure would adversely affect the interests of any person and is not required in the public interest or is not otherwise required by statute to be made available to the public. Any person may make written objection to the public disclosure of such information, stating the grounds for such objection. </SECTION> <SECTION> <SECTNO>§ 13.117</SECTNO> <SUBJECT>Conduct of investigative proceeding or deposition.</SUBJECT> (a) The Presiding Officer or the designee of the Presiding Officer may question witnesses. (b) Any witness may be accompanied by counsel. (c) Any party may be accompanied by counsel and either the party or counsel may— (1) Question witnesses, provided the questions are relevant and material to the matters under investigation and would not unduly impede the progress of the investigation; and (2) Make objections on the record and argue the basis for such objections. (d) Copies of all notices or written communications sent to a party or witness shall upon request be sent to that person's attorney of record. </SECTION> <SECTION> <SECTNO>§ 13.119</SECTNO> <SUBJECT>Rights of persons against self-incrimination.</SUBJECT> (a) Whenever a person refuses, on the basis of a privilege against self-incrimination, to testify or provide other information during the course of any investigation conducted under this subpart, the Presiding Officer may, with the approval of the Attorney General of the United States, issue an order requiring the person to give testimony or provide other information. However, no testimony or other information so compelled (or any information directly or indirectly derived from such testimony or other information) may be used against the person in any criminal case, except in a prosecution for perjury, giving a false statement, or otherwise failing to comply with the order. (b) The Presiding Officer may issue an order under this section if— (1) The testimony or other information from the witness may be necessary to the public interest; and (2) The witness has refused or is likely to refuse to testify or provide other information on the basis of a privilege against self-incrimination. (c) Immunity provided by this section will not become effective until the person has refused to testify or provide other information on the basis of a privilege against self-incrimination, and an order under this section has been issued. An order, however, may be issued prospectively to become effective in the event of a claim of the privilege. </SECTION> <SECTION> <SECTNO>§ 13.121</SECTNO> <SUBJECT>Witness fees.</SUBJECT> All witnesses appearing shall be compensated at the same rate as a witness appearing before a United States District Court. </SECTION> <SECTION> <PRTPAGE P="53"/> <SECTNO>§ 13.123</SECTNO> <SUBJECT>Submission by party to the investigation.</SUBJECT> (a) During an investigation conducted under this subpart, a party may submit to the Presiding Officer— (1) A list of witnesses to be called, specifying the subject matter of the expected testimony of each witness, and (2) A list of exhibits to be considered for inclusion in the record. (b) If the Presiding Officer determines that the testimony of a witness or the receipt of an exhibit in accordance with paragraph (a) of this section will be relevant, competent and material to the investigation, the Presiding Officer may subpoena the witness or use the exhibit during the investigation. </SECTION> <SECTION> <SECTNO>§ 13.125</SECTNO> <SUBJECT>Depositions.</SUBJECT> Depositions for investigative purposes may be taken at the discretion of the Presiding Officer with reasonable notice to the party under investigation. Such depositions shall be taken before the Presiding Officer or other person authorized to administer oaths and designated by the Presiding Officer. The testimony shall be reduced to writing by the person taking the deposition, or under the direction of that person, and where possible shall then be subscribed by the deponent. Any person may be compelled to appear and testify and to produce physical and documentary evidence. </SECTION> <SECTION> <SECTNO>§ 13.127</SECTNO> <SUBJECT>Reports, decisions and orders.</SUBJECT> The Presiding Officer shall issue a written report based on the record developed during the formal investigation, including a summary of principal conclusions. A summary of principal conclusions shall be prepared by the official who issued the order of investigation in every case which results in no action, or no action as to a particular party to the investigation. All such reports shall be furnished to the parties to the investigation and filed in the public docket. Insertion of the report in the Public Docket shall constitute “entering of record” and publication as prescribed by section 313(b) of the Federal Aviation Act. </SECTION> <SECTION> <SECTNO>§ 13.129</SECTNO> <SUBJECT>Post-investigation action.</SUBJECT> A decision on whether to initiate subsequent action shall be made on the basis of the record developed during the formal investigation and any other information in the possession of the Administrator. </SECTION> <SECTION> <SECTNO>§ 13.131</SECTNO> <SUBJECT>Other procedures.</SUBJECT> Any question concerning the scope or conduct of a formal investigation not covered in this subpart may be ruled on by the Presiding Officer on motion of the Presiding Officer, or on the motion of a party or a person testifying or producing evidence. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Rules of Practice in FAA Civil Penalty Actions</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 13-21, 55 FR 27575, July 3, 1990, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 13.201</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart applies to the following actions: (1) A civil penalty action in which a complaint has been issued for an amount not exceeding $50,000 for a violation arising under the Federal Aviation Act of 1958, as amended (49 U.S.C. 1301, <E T="03">et seq</E>.), or a rule, regulation, or order issued thereunder. (2) A civil penalty action in which a complaint has been issued for a violation arising under the Federal Aviation Act of 1958, as amended (49 U.S.C. 1471, <E T="03">et seq</E>.) and the Hazardous Materials Transportation Act (49 U.S.C. 1801 <E T="03">et seq</E>.), or a rule, regulation, or order issued thereunder. (b) This subpart applies only to proceedings initiated after September 7, 1988. All other cases, hearings, or other proceedings pending or in progress before September 7, 1988, are not affected by the rules in this subpart. (c) Notwithstanding the provisions of paragraph (a) of this section, the United States district courts shall have exclusive jurisdiction of any civil penalty action initiated by the Administrator: (1) Which involves an amount in controversy in excess of $50,000; (2) Which is an <E T="03">in rem</E> action or in which an <E T="03">in rem</E> action based on the same violation has been brought;<PRTPAGE P="54"/> (3) Regarding which an aircraft subject to lien has been seized by the United States; and (4) In which a suit for injunctive relief based on the violation giving rise to the civil penalty has also been brought. </SECTION> <SECTION> <SECTNO>§ 13.202</SECTNO> <SUBJECT>Definitions.</SUBJECT> <E T="03">Administrative law judge</E> means an administrative law judge appointed pursuant to the provisions of 5 U.S.C. 3105. <E T="03">Agency attorney</E> means the Deputy Chief Counsel, the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, the Aeronautical Center Counsel, or the Technical Center Counsel, or an attorney on the staff of the Assistant Chief Counsel, Enforcement, the Assistant Chief Counsel, Regulations, the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office, each Regional Counsel, the Aeronautical Center Counsel, or the Technical Center Counsel who prosecutes a civil penalty action. An agency attorney shall not include: (1) The Chief Counsel, the Assistant Chief Counsel for Litigation, or the Special Counsel and Director of Civil Penalty Adjudications; or (2) Any attorney on the staff of either the Assistant Chief Counsel for Litigation or the Special Counsel and Director of Civil Penalty Adjudications who advises the FAA decisionmaker regarding an initial decision or any appeal to the FAA decisionmaker; or (3) Any attorney who is supervised in a civil penalty action by a person who provides such advice to the FAA decisionmaker in that action or a factually-related action. <E T="03">Attorney</E> means a person licensed by a state, the District of Columbia, or a territory of the United States to practice law or appear before the courts of that state or territory. <E T="03">Complaint</E> means a document issued by an agency attorney alleging a violation of the Federal Aviation Act of 1958, as amended, or a rule, regulation, or order issued thereunder, or the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder that has been filed with the hearing docket after a hearing has been requested pursuant to § 13.16(d)(3) or § 13.16(e)(2)(ii) of this part. <E T="03">FAA decisionmaker</E> means the Administrator of the Federal Aviation Administration, acting in the capacity of the decisionmaker on appeal, or any person to whom the Administrator has delegated the Administrator's decisionmaking authority in a civil penalty action. As used in this subpart, the FAA decisionmaker is the official authorized to issue a final decision and order of the Administrator in a civil penalty action. <E T="03">Mail</E> includes U.S. certified mail, U.S. registered mail, or use of an overnight express courier service. <E T="03">Order assessing civil penalty</E> means a document that contains a finding of violation of the Federal Aviation Act of 1958, as amended, or a rule, regulation, or order issued thereunder, or the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder and may direct payment of a civil penalty. Unless an appeal is filed with the FAA decisionmaker in a timely manner, an initial decision or order of an administrative law judge shall be considered an order assessing civil penalty if an administrative law judge finds that an alleged violation occurred and determines that a civil penalty, in an amount found appropriate by the administrative law judge, is warranted. Unless a petition for review is filed with a U.S. Court of Appeals in a timely manner, a final decision and order of the Administrator shall be considered an order assessing civil penalty if the FAA decisionmaker finds that an alleged violation occurred and a civil penalty is warranted. <E T="03">Party</E> means the respondent or the Federal Aviation Administration (FAA). <E T="03">Personal delivery</E> includes hand-delivery or use of a contract or express messenger service. “Personal delivery” does not include the use of Government interoffice mail service. <E T="03">Pleading</E> means a complaint, an answer, and any amendment of these documents permitted under this subpart. <E T="03">Properly addressed</E> means a document that shows an address contained in agency records, a residential, business, or other address submitted by a person <PRTPAGE P="55"/>on any document provided under this subpart, or any other address shown by other reasonable and available means. <E T="03">Respondent</E> means a person, corporation, or company named in a complaint. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990, as amended by Amdt. 13-24, 58 FR 50241, Sept. 24, 1993; Amdt. 13-29, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.203</SECTNO> <SUBJECT>Separation of functions.</SUBJECT> (a) Civil penalty proceedings, including hearings, shall be prosecuted by an agency attorney. (b) An agency employee engaged in the performance of investigative or prosecutorial functions in a civil penalty action shall not, in that case or a factually-related case, participate or give advice in a decision by the administrative law judge or by the FAA decisionmaker on appeal, except as counsel or a witness in the public proceedings. (c) The Chief Counsel, the Assistant Chief Counsel for Litigation, the Special Counsel and Director of Civil Penalty Adjudications, or an attorney on the staff of either the Assistant Chief Counsel for Litigation or the Special Counsel and Director of Civil Penalty Adjudications, will advise the FAA decisionmaker regarding an initial decision or any appeal of a civil penalty action to the FAA decisionmaker. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990, as amended by Amdt. 13-24, 58 FR 50241, Sept. 24, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.204</SECTNO> <SUBJECT>Appearances and rights of parties.</SUBJECT> (a) Any party may appear and be heard in person. (b) Any party may be accompanied, represented, or advised by an attorney or representative designated by the party and may be examined by that attorney or representative in any proceeding governed by this subpart. An attorney or representative who represents a party may file a notice of appearance in the action, in the manner provided in § 13.210 of this subpart, and shall serve a copy of the notice of appearance on each party, in the manner provided in § 13.211 of this subpart, before participating in any proceeding governed by this subpart. The attorney or representative shall include the name, address, and telephone number of the attorney or representative in the notice of appearance. (c) Any person may request a copy of a document upon payment of reasonable costs. A person may keep an original document, data, or evidence, with the consent of the administrative law judge, by substituting a legible copy of the document for the record. </SECTION> <SECTION> <SECTNO>§ 13.205</SECTNO> <SUBJECT>Administrative law judges.</SUBJECT> (a) <E T="03">Powers of an administrative law judge.</E> In accordance with the rules of this subpart, an administrative law judge may: (1) Give notice of, and hold, prehearing conferences and hearings; (2) Administer oaths and affirmations; (3) Issue subpoenas authorized by law and issue notices of deposition requested by the parties; (4) Rule on offers of proof; (5) Receive relevant and material evidence; (6) Regulate the course of the hearing in accordance with the rules of this subpart; (7) Hold conferences to settle or to simplify the issues by consent of the parties; (8) Dispose of procedural motions and requests; and (9) Make findings of fact and conclusions of law, and issue an initial decision. (b) <E T="03">Limitations on the power of the administrative law judge.</E> The administrative law judge shall not issue an order of contempt, award costs to any party, or impose any sanction not specified in this subpart. If the administrative law judge imposes any sanction not specified in this subpart, a party may file an interlocutory appeal of right with the FAA decisionmaker pursuant to § 13.219(c)(4) of this subpart. This section does not preclude an administrative law judge from issuing an order that bars a person from a specific proceeding based on a finding of obstreperous or disruptive behavior in that specific proceeding. (c) <E T="03">Disqualification.</E> The administrative law judge may disqualify himself or herself at any time. A party may file a motion, pursuant to § 13.218(f)(6), requesting that an administrative law <PRTPAGE P="56"/>judge be disqualified from the proceedings. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990; 55 FR 29293, July 18, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.206</SECTNO> <SUBJECT>Intervention.</SUBJECT> (a) A person may submit a motion for leave to intervene as a party in a civil penalty action. Except for good cause shown, a motion for leave to intervene shall be submitted not later than 10 days before the hearing. (b) If the administrative law judge finds that intervention will not unduly broaden the issues or delay the proceedings, the administrative law judge may grant a motion for leave to intervene if the person will be bound by any order or decision entered in the action or the person has a property, financial, or other legitimate interest that may not be addressed adequately by the parties. The administrative law judge may determine the extent to which an intervenor may participate in the proceedings. </SECTION> <SECTION> <SECTNO>§ 13.207</SECTNO> <SUBJECT>Certification of documents.</SUBJECT> (a) <E T="03">Signature required.</E> The attorney of record, the party, or the party's representative shall sign each document tendered for filing with the hearing docket clerk, the administrative law judge, the FAA decisionmaker on appeal, or served on each party. (b) <E T="03">Effect of signing a document.</E> By signing a document, the attorney of record, the party, or the party's representative certifies that the attorney, the party, or the party's representative has read the document and, based on reasonable inquiry and to the best of that person's knowledge, information, and belief, the document is— (1) Consistent with these rules; (2) Warranted by existing law or that a good faith argument exists for extension, modification, or reversal of existing law; and (3) Not unreasonable or unduly burdensome or expensive, not made to harass any person, not made to cause unnecessary delay, not made to cause needless increase in the cost of the proceedings, or for any other improper purpose. (c) <E T="03">Sanctions</E>. If the attorney of record, the party, or the party's representative signs a document in violation of this section, the administrative law judge or the FAA decisionmaker shall: (1) Strike the pleading signed in violation of this section; (2) Strike the request for discovery or the discovery response signed in violation of this section and preclude further discovery by the party; (3) Deny the motion or request signed in violation of this section; (4) Exclude the document signed in violation of this section from the record; (5) Dismiss the interlocutory appeal and preclude further appeal on that issue by the party who filed the appeal until an initial decision has been entered on the record; or (6) Dismiss the appeal of the administrative law judge's initial decision to the FAA decisionmaker. </SECTION> <SECTION> <SECTNO>§ 13.208</SECTNO> <SUBJECT>Complaint.</SUBJECT> (a) <E T="03">Filing</E>. The agency attorney shall file the original and one copy of the complaint with the hearing docket clerk, or may file a written motion pursuant to § l3.218(f)(2)(i) of this subpart instead of filing a complaint, not later than 20 days after receipt by the agency attorney of a request for hearing. The agency attorney should suggest a location for the hearing when filing the complaint. (b) <E T="03">Service</E>. An agency attorney shall personally deliver or mail a copy of the complaint on the respondent, the president of the corporation or company named as a respondent, or a person designated by the respondent to accept service of documents in the civil penalty action. (c) <E T="03">Contents</E>. A complaint shall set forth the facts alleged, any regulation allegedly violated by the respondent, and the proposed civil penalty in sufficient detail to provide notice of any factual or legal allegation and proposed civil penalty. (d) <E T="03">Motion to dismiss allegations or complaint.</E> Instead of filing an answer to the complaint, a respondent may move to dismiss the complaint, or that part of the complaint, alleging a violation that occurred on or after August 2, 1990, and more than 2 years before an <PRTPAGE P="57"/>agency attorney issued a notice of proposed civil penalty to the respondent. (1) An administrative law judge may not grant the motion and dismiss the complaint or part of the complaint if the administrative law judge finds that the agency has shown good cause for any delay in issuing the notice of proposed civil penalty. (2) If the agency fails to show good cause for any delay, an administrative law judge may dismiss the complaint, or that part of the complaint, alleging a violation that occurred more than 2 years before an agency attorney issued the notice of proposed civil penalty to the respondent. (3) A party may appeal the administrative law judge's ruling on the motion to dismiss the complaint or any part of the complaint in accordance with § 13.219(b) of this subpart. <CITA>[Admt. 13-21, 55 FR 27575, July 3, 1990, as amended by Admt. 13-22, 55 FR 31176, Aug. 1, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.209</SECTNO> <SUBJECT>Answer.</SUBJECT> (a) <E T="03">Writing required</E>. A respondent shall file a written answer to the complaint, or may file a written motion pursuant to § 13.208(d) or § 13.218(f)(1-4) of this subpart instead of filing an answer, not later than 30 days after service of the complaint. The answer may be in the form of a letter but must be dated and signed by the person responding to the complaint. An answer may be typewritten or may be legibly handwritten. (b) <E T="03">Filing and address</E>. A person filing an answer shall personally deliver or mail the original and one copy of the answer for filing with the hearing docket clerk, not later than 30 days after service of the complaint, to the Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591, Attention: Hearing Docket Clerk. The person filing an answer should suggest a location for the hearing when filing the answer. (c) <E T="03">Service</E>. A person filing an answer shall serve a copy of the answer on the agency attorney who filed the complaint. (d) <E T="03">Contents</E>. An answer shall specifically state any affirmative defense that the respondent intends to assert at the hearing. A person filing an answer may include a brief statement of any relief requested in the answer. (e) <E T="03">Specific denial of allegations required</E>. A person filing an answer shall admit, deny, or state that the person is without sufficient knowledge or information to admit or deny, each numbered paragraph of the complaint. Any statement or allegation contained in the complaint that is not specifically denied in the answer may be deemed an admission of the truth of that allegation. A general denial of the complaint is deemed a failure to file an answer. (f) <E T="03">Failure to file answer</E>. A person's failure to file an answer without good cause shall be deemed an admission of the truth of each allegation contained in the complaint. </SECTION> <SECTION> <SECTNO>§ 13.210</SECTNO> <SUBJECT>Filing of documents.</SUBJECT> (a) <E T="03">Address and method of filing</E>. A person tendering a document for filing shall personally deliver or mail the signed original and one copy of each document to the Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591, Attention: Hearing Docket Clerk. A person shall serve a copy of each document on each party in accordance with § 13.211 of this subpart. (b) <E T="03">Date of filing.</E> A document shall be considered to be filed on the date of personal delivery; or if mailed, the mailing date shown on the certificate of service, the date shown on the postmark if there is no certificate of service, or other mailing date shown by other evidence if there is no certificate of service or postmark. (c) <E T="03">Form.</E> Each document shall be typewritten or legibly handwritten. (d) <E T="03">Contents.</E> Unless otherwise specified in this subpart, each document must contain a short, plain statement of the facts on which the person's case rests and a brief statement of the action requested in the document. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990; 55 FR 29293, July 18, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.211</SECTNO> <SUBJECT>Service of documents.</SUBJECT> (a) <E T="03">General.</E> A person shall serve a copy of any document filed with the Hearing Docket on each party at the <PRTPAGE P="58"/>time of filing. Service on a party's attorney of record or a party's designated representative may be considered adequate service on the party. (b) <E T="03">Type of service.</E> A person may serve documents by personal delivery or by mail. (c) <E T="03">Certificate of service.</E> A person may attach a certificate of service to a document tendered for filing with the hearing docket clerk. A certificate of service shall consist of a statement, dated and signed by the person filing the document, that the document was personally delivered or mailed to each party on a specific date. (d) <E T="03">Date of service.</E> The date of service shall be the date of personal delivery; or if mailed, the mailing date shown on the certificate of service, the date shown on the postmark if there is no certificate of service, or other mailing date shown by other evidence if there is no certificate of service or postmark. (e) <E T="03">Additional time after service by mail.</E> Whenever a party has a right or a duty to act or to make any response within a prescribed period after service by mail, or on a date certain after service by mail, 5 days shall be added to the prescribed period. (f) <E T="03">Service by the administrative law judge.</E> The administrative law judge shall serve a copy of each document including, but not limited to, notices of prehearing conferences and hearings, rulings on motions, decisions, and orders, upon each party to the proceedings by personal delivery or by mail. (g) <E T="03">Valid service.</E> A document that was properly addressed, was sent in accordance with this subpart, and that was returned, that was not claimed, or that was refused, is deemed to have been served in accordance with this subpart. The service shall be considered valid as of the date and the time that the document was deposited with a contract or express messenger, the document was mailed, or personal delivery of the document was refused. (h) <E T="03">Presumption of service.</E> There shall be a presumption of service where a party or a person, who customarily receives mail, or receives it in the ordinary course of business, at either the person's residence or the person's principal place of business, acknowledges receipt of the document. </SECTION> <SECTION> <SECTNO>§ 13.212</SECTNO> <SUBJECT>Computation of time.</SUBJECT> (a) This section applies to any period of time prescribed or allowed by this subpart, by notice or order of the administrative law judge, or by any applicable statute. (b) The date of an act, event, or default, after which a designated time period begins to run, is not included in a computation of time under this subpart. (c) The last day of a time period is included in a computation of time unless it is a Saturday, Sunday, or a legal holiday. If the last day of the time period is a Saturday, Sunday, or legal holiday, the time period runs until the end of the next day that is not a Saturday, Sunday, or legal holiday. </SECTION> <SECTION> <SECTNO>§ 13.213</SECTNO> <SUBJECT>Extension of time.</SUBJECT> (a) <E T="03">Oral requests.</E> The parties may agree to extend for a reasonable period the time for filing a document under this subpart. If the parties agree, the administrative law judge shall grant one extension of time to each party. The party seeking the extension of time shall submit a draft order to the administrative law judge to be signed by the administrative law judge and filed with the hearing docket clerk. The administrative law judge may grant additional oral requests for an extension of time where the parties agree to the extension. (b) <E T="03">Written motion.</E> A party shall file a written motion for an extension of time with the administrative law judge not later than 7 days before the document is due unless good cause for the late filing is shown. A party filing a written motion for an extension of time shall serve a copy of the motion on each party. The administrative law judge may grant the extension of time if good cause for the extension is shown. (c) <E T="03">Failure to rule.</E> If the administrative law judge fails to rule on a written motion for an extension of time by the date the document was due, the motion for an extension of time is deemed granted for no more than 20 days after the original date the document was to be filed. </SECTION> <SECTION> <PRTPAGE P="59"/> <SECTNO>§ 13.214</SECTNO> <SUBJECT>Amendment of pleadings.</SUBJECT> (a) <E T="03">Filing and service.</E> A party shall file the amendment with the administrative law judge and shall serve a copy of the amendment on all parties to the proceeding. (b) <E T="03">Time.</E> A party shall file an amendment to a complaint or an answer within the following: (1) Not later than 15 days before the scheduled date of a hearing, a party may amend a complaint or an answer without the consent of the administrative law judge. (2) Less than 15 days before the scheduled date of a hearing, the administrative law judge may allow amendment of a complaint or an answer only for good cause shown in a motion to amend. (c) <E T="03">Responses.</E> The administrative law judge shall allow a reasonable time, but not more than 20 days from the date of filing, for other parties to respond if an amendment to a complaint, answer, or other pleading has been filed with the administrative law judge. </SECTION> <SECTION> <SECTNO>§ 13.215</SECTNO> <SUBJECT>Withdrawal of complaint or request for hearing.</SUBJECT> At any time before or during a hearing, an agency attorney may withdraw a complaint or a party may withdraw a request for a hearing without the consent of the administrative law judge. If an agency attorney withdraws the complaint or a party withdraws the request for a hearing and the answer, the administrative law judge shall dismiss the proceedings under this subpart with prejudice. </SECTION> <SECTION> <SECTNO>§ 13.216</SECTNO> <SUBJECT>Waivers.</SUBJECT> Waivers of any rights provided by statute or regulation shall be in writing or by stipulation made at a hearing and entered into the record. The parties shall set forth the precise terms of the waiver and any conditions. </SECTION> <SECTION> <SECTNO>§ 13.217</SECTNO> <SUBJECT>Joint procedural or discovery schedule.</SUBJECT> (a) <E T="03">General.</E> The parties may agree to submit a schedule for filing all prehearing motions, a schedule for conducting discovery in the proceedings, or a schedule that will govern all prehearing motions and discovery in the proceedings. (b) <E T="03">Form and content of schedule.</E> If the parties agree to a joint procedural or discovery schedule, one of the parties shall file the joint schedule with the administrative law judge, setting forth the dates to which the parties have agreed, and shall serve a copy of the joint schedule on each party. (1) The joint schedule may include, but need not be limited to, requests for discovery, any objections to discovery requests, responses to discovery requests to which there are no objections, submission of prehearing motions, responses to prehearing motions, exchange of exhibits to be introduced at the hearing, and a list of witnesses that may be called at the hearing. (2) Each party shall sign the original joint schedule to be filed with the administrative law judge. (c) <E T="03">Time.</E> The parties may agree to submit all prehearing motions and responses and may agree to close discovery in the proceedings under the joint schedule within a reasonable time before the date of the hearing, but not later than 15 days before the hearing. (d) <E T="03">Order establishing joint schedule.</E> The administrative law judge shall approve the joint schedule filed by the parties. One party shall submit a draft order establishing a joint schedule to the administrative law judge to be signed by the administrative law judge and filed with the hearing docket clerk. (e) <E T="03">Disputes.</E> The administrative law judge shall resolve disputes regarding discovery or disputes regarding compliance with the joint schedule as soon as possible so that the parties may continue to comply with the joint schedule. (f) <E T="03">Sanctions for failure to comply with joint schedule.</E> If a party fails to comply with the administrative law judge's order establishing a joint schedule, the administrative law judge may direct that party to comply with a motion to discovery request or, limited to the extent of the party's failure to comply with a motion or discovery request, the administrative law judge may: (1) Strike that portion of a party's pleadings; (2) Preclude prehearing or discovery motions by that party;<PRTPAGE P="60"/> (3) Preclude admission of that portion of a party's evidence at the hearing, or (4) Preclude that portion of the testimony of that party's witnesses at the hearing. </SECTION> <SECTION> <SECTNO>§ 13.218</SECTNO> <SUBJECT>Motions.</SUBJECT> (a) <E T="03">General.</E> A party applying for an order or ruling not specifically provided in this subpart shall do so by motion. A party shall comply with the requirements of this section when filing a motion with the administrative law judge. A party shall serve a copy of each motion on each party. (b) <E T="03">Form and contents.</E> A party shall state the relief sought by the motion and the particular grounds supporting that relief. If a party has evidence in support of a motion, the party shall attach any supporting evidence, including affidavits, to the motion. (c) <E T="03">Filing of motions.</E> A motion made prior to the hearing must be in writing. Unless otherwise agreed by the parties or for good cause shown, a party shall file any prehearing motion, and shall serve a copy on each party, not later than 30 days before the hearing. Motions introduced during a hearing may be made orally on the record unless the administrative law judge directs otherwise. (d) <E T="03">Answers to motions.</E> Any party may file an answer, with affidavits or other evidence in support of the answer, not later than 10 days after service of a written motion on that party. When a motion is made during a hearing, the answer may be made at the hearing on the record, orally or in writing, within a reasonable time determined by the administrative law judge. (e) <E T="03">Rulings on motions.</E> The administrative law judge shall rule on all motions as follows: (1) <E T="03">Discovery motions.</E> The administrative law judge shall resolve all pending discovery motions not later than 10 days before the hearing. (2) <E T="03">Prehearing motions.</E> The administrative law judge shall resolve all pending prehearing motions not later than 7 days before the hearing. If the administrative law judge issues a ruling or order orally, the administrative law judge shall serve a written copy of the ruling or order, within 3 days, on each party. In all other cases, the administrative law judge shall issue rulings and orders in writing and shall serve a copy of the ruling or order on each party. (3) <E T="03">Motions made during the hearing.</E> The administrative law judge may issue rulings and orders on motions made during the hearing orally. Oral rulings or orders on motions must be made on the record. (f) <E T="03">Specific motions.</E> A party may file the following motions with the administrative law judge: (1) <E T="03">Motion to dismiss for insufficiency.</E> A respondent may file a motion to dismiss the complaint for insufficiency instead of filing an answer. If the administrative law judge denies the motion to dismiss the complaint for insufficiency, the respondent shall file an answer not later than 10 days after service of the administrative law judge's denial of the motion. A motion to dismiss the complaint for insufficiency must show that the complaint fails to state a violation of the Federal Aviation Act of 1958, as amended, or a rule, regulation, or order issued thereunder, or a violation of the Hazardous Materials Transportation Act, or a rule, regulation, or order issued thereunder. (2) <E T="03">Motion to dismiss.</E> A party may file a motion to dismiss, specifying the grounds for dismissal. If an administrative law judge grants a motion to dismiss in part, a party may appeal the administrative law judge's ruling on the motion to dismiss under § 13.219(b) of this subpart. (i) <E T="03">Motion to dismiss a request for a hearing.</E> An agency attorney may file a motion to dismiss a request for a hearing instead of filing a complaint. If the motion to dismiss is not granted, the agency attorney shall file the complaint and shall serve a copy of the complaint on each party not later than 10 days after service of the administrative law judge's ruling or order on the motion to dismiss. If the motion to dismiss is granted and the proceedings are terminated without a hearing, the respondent may file an appeal pursuant to § 13.233 of this subpart. If required by the decision on appeal, the agency attorney shall file a complaint and shall serve a copy of the complaint on each <PRTPAGE P="61"/>party not later than 10 days after service of the decision on appeal. (ii) <E T="03">Motion to dismiss a complaint.</E> A respondent may file a motion to dismiss a complaint instead of filing an answer. If the motion to dismiss is not granted, the respondent shall file an answer and shall serve a copy of the answer on each party not later than 10 days after service of the administrative law judge's ruling or order on the motion to dismiss. If the motion to dismiss is granted and the proceedings are terminated without a hearing, the agency attorney may file an appeal pursuant to § 13.233 of this subpart. If required by the decision on appeal, the respondent shall file an answer and shall serve a copy of the answer on each party not later than 10 days after service of the decision on appeal. (3) <E T="03">Motion for more definite statement.</E> A party may file a motion for more definite statement of any pleading which requires a response under this subpart. A party shall set forth, in detail, the indefinite or uncertain allegations contained in a complaint or response to any pleading and shall submit the details that the party believes would make the allegation or response definite and certain. (i) <E T="03">Complaint.</E> A respondent may file a motion requesting a more definite statement of the allegations contained in the complaint instead of filing an answer. If the administrative law judge grants the motion, the agency attorney shall supply a more definite statement not later than 15 days after service of the ruling granting the motion. If the agency attorney fails to supply a more definite statement, the administrative law judge shall strike the allegations in the complaint to which the motion is directed. If the administrative law judge denies the motion, the respondent shall file an answer and shall serve a copy of the answer on each party not later than 10 days after service of the order of denial. (ii) <E T="03">Answer.</E> An agency attorney may file a motion requesting a more definite statement if an answer fails to respond clearly to the allegations in the complaint. If the administrative law judge grants the motion, the respondent shall supply a more definite statement not later than 15 days after service of the ruling on the motion. If the respondent fails to supply a more definite statement, the administrative law judge shall strike those statements in the answer to which the motion is directed. The respondent's failure to supply a more definite statement may be deemed an admission of unanswered allegations in the complaint. (4) <E T="03">Motion to strike.</E> Any party may make a motion to strike any insufficient allegation or defense, or any redundant, immaterial, or irrelevant matter in a pleading. A party shall file a motion to strike with the administrative law judge and shall serve a copy on each party before a response is required under this subpart or, if a response is not required, not later than 10 days after service of the pleading. (5) <E T="03">Motion for decision.</E> A party may make a motion for decision, regarding all or any part of the proceedings, at any time before the administrative law judge has issued an initial decision in the proceedings. The administrative law judge shall grant a party's motion for decision if the pleadings, depositions, answers to interrogatories, admissions, matters that the administrative law judge has officially noticed, or evidence introduced during the hearing show that there is no genuine issue of material fact and that the party making the motion is entitled to a decision as a matter of law. The party making the motion for decision has the burden of showing that there is no genuine issue of material fact disputed by the parties. (6) <E T="03">Motion for disqualification.</E> A party may file a motion for disqualification with the administrative law judge and shall serve a copy on each party. A party may file the motion at any time after the administrative law judge has been assigned to the proceedings but shall make the motion before the administrative law judge files an initial decision in the proceedings. (i) <E T="03">Motion and supporting affidavit.</E> A party shall state the grounds for disqualification, including, but not limited to, personal bias, pecuniary interest, or other factors showing disqualification, in the motion for disqualification. A party shall submit an affidavit with the motion for disqualification that sets forth, in detail, the matters <PRTPAGE P="62"/>alleged to constitute grounds for disqualification. (ii) <E T="03">Answer.</E> A party shall respond to the motion for disqualification not later than 5 days after service of the motion for disqualification. (iii) <E T="03">Decision on motion for disqualification.</E> The administrative law judge shall render a decision on the motion for disqualification not later than 15 days after the motion has been filed. If the administrative law judge finds that the motion for disqualification and supporting affidavit show a basis for disqualification, the administrative law judge shall withdraw from the proceedings immediately. If the administrative law judge finds that disqualification is not warranted, the administrative law judge shall deny the motion and state the grounds for the denial on the record. If the administrative law judge fails to rule on a party's motion for disqualification within 15 days after the motion has been filed, the motion is deemed granted. (iv) <E T="03">Appeal.</E> A party may appeal the administrative law judge's denial of the motion for disqualification in accordance with § 13.219(b) of this subpart. </SECTION> <SECTION> <SECTNO>§ 13.219</SECTNO> <SUBJECT>Interlocutory appeals.</SUBJECT> (a) <E T="03">General.</E> Unless otherwise provided in this subpart, a party may not appeal a ruling or decision of the administrative law judge to the FAA decisionmaker until the initial decision has been entered on the record. A decision or order of the FAA decisionmaker on the interlocutory appeal does not constitute a final order of the Administrator for the purposes of judicial appellate review under section 1006 of the Federal Aviation Act of 1958, as amended. (b) <E T="03">Interlocutory appeal for cause.</E> If a party files a written request for an interlocutory appeal for cause with the administrative law judge, or orally requests an interlocutory appeal for cause, the proceedings are stayed until the administrative law judge issues a decision on the request. If the administrative law judge grants the request, the proceedings are stayed until the FAA decisionmaker issues a decision on the interlocutory appeal. The administrative law judge shall grant an interlocutory appeal for cause if a party shows that delay of the appeal would be detrimental to the public interest or would result in undue prejudice to any party. (c) <E T="03">Interlocutory appeals of right.</E> If a party notifies the administrative law judge of an interlocutory appeal of right, the proceedings are stayed until the FAA decisionmaker issues a decision on the interlocutory appeal. A party may file an interlocutory appeal with the FAA decisionmaker, without the consent of the administrative law judge, before an initial decision has been entered in the case of: (1) A ruling or order by the administrative law judge barring a person from the proceedings. (2) Failure of the administrative law judge to dismiss the proceedings in accordance with § 13.215 of this subpart. (3) A ruling or order by the administrative law judge in violation of § 13.205(b) of this subpart. (d) <E T="03">Procedure.</E> A party shall file a notice of interlocutory appeal, with supporting documents, with the FAA decisionmaker and the hearing docket clerk, and shall serve a copy of the notice and supporting documents on each party and the administrative law judge, not later than 10 days after the administrative law judge's decision forming the basis of an interlocutory appeal of right or not later than 10 days after the administrative law judge's decision granting an interlocutory appeal for cause, whichever is appropriate. A party shall file a reply brief, if any, with the FAA decisionmaker and serve a copy of the reply brief on each party, not later than 10 days after service of the appeal brief. The FAA decisionmaker shall render a decision on the interlocutory appeal, on the record and as a part of the decision in the proceedings, within a reasonable time after receipt of the interlocutory appeal. (e) The FAA decisionmaker may reject frivolous, repetitive, or dilatory appeals, and may issue an order precluding one or more parties from making further interlocutory appeals in a proceeding in which there have been <PRTPAGE P="63"/>frivolous, repetitive, or dilatory interlocutory appeals. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990, as amended by Amdt. 13-23, 55 FR 45983, Oct. 31, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.220</SECTNO> <SUBJECT>Discovery.</SUBJECT> (a) <E T="03">Initiation of discovery.</E> Any party may initiate discovery described in this section, without the consent or approval of the administrative law judge, at any time after a complaint has been filed in the proceedings. (b) <E T="03">Methods of discovery.</E> The following methods of discovery are permitted under this section: depositions on oral examination or written questions of any person; written interrogatories directed to a party; requests for production of documents or tangible items to any person; and requests for admission by a party. A party is not required to file written interrogatories and responses, requests for production of documents or tangible items and responses, and requests for admission and response with the administrative law judge or the hearing docket clerk. In the event of a discovery dispute, a party shall attach a copy of these documents in support of a motion made under this section. (c) <E T="03">Service on the agency.</E> A party shall serve each discovery request directed to the agency or any agency employee on the agency attorney of record. (d) <E T="03">Time for response to discovery requests.</E> Unless otherwise directed by this subpart or agreed by the parties, a party shall respond to a request for discovery, including filing objections to a request for discovery, not later than 30 days of service of the request. (e) <E T="03">Scope of discovery.</E> Subject to the limits on discovery set forth in paragraph (f) of this section, a party may discover any matter that is not privileged and that is relevant to the subject matter of the proceeding. A party may discover information that relates to the claim or defense of any party including the existence, description, nature, custody, condition, and location of any document or other tangible item and the identity and location of any person having knowledge of discoverable matter. A party may discover facts known, or opinions held, by an expert who any other party expects to call to testify at the hearing. A party has no ground to object to a discovery request on the basis that the information sought would not be admissible at the hearing if the information sought during discovery is reasonably calculated to lead to the discovery of admissible evidence. (f) <E T="03">Limiting discovery.</E> The administrative law judge shall limit the frequency and extent of discovery permitted by this section if a party shows that— (1) The information requested is cumulative or repetitious; (2) The information requested can be obtained from another less burdensome and more convenient source; (3) The party requesting the information has had ample opportunity to obtain the information through other discovery methods permitted under this section; or (4) The method or scope of discovery requested by the party is unduly burdensome or expensive. (g) <E T="03">Confidential orders.</E> A party or person who has received a discovery request for information that is related to a trade secret, confidential or sensitive material, competitive or commercial information, proprietary data, or information on research and development, may file a motion for a confidential order with the administrative law judge and shall serve a copy of the motion for a confidential order on each party. (1) The party or person making the motion must show that the confidential order is necessary to protect the information from disclosure to the public. (2) If the administrative law judge determines that the requested material is not necessary to decide the case, the administrative law judge shall preclude any inquiry into the matter by any party. (3) If the administrative law judge determines that the requested material may be disclosed during discovery, the administrative law judge may order that the material may be discovered and disclosed under limited conditions or may be used only under certain terms and conditions. (4) If the administrative law judge determines that the requested material is <PRTPAGE P="64"/>necessary to decide the case and that a confidential order is warranted, the administrative law judge shall provide: (i) An opportunity for review of the document by the parties off the record; (ii) Procedures for excluding the information from the record; and (iii) Order that the parties shall not disclose the information in any manner and the parties shall not use the information in any other proceeding. (h) <E T="03">Protective orders.</E> A party or a person who has received a request for discovery may file a motion for protective order with the administrative law judge and shall serve a copy of the motion for protective order on each party. The party or person making the motion must show that the protective order is necessary to protect the party or the person from annoyance, embarrassment, oppression, or undue burden or expense. As part of the protective order, the administrative law judge may: (1) Deny the discovery request; (2) Order that discovery be conducted only on specified terms and conditions, including a designation of the time or place for discovery or a determination of the method of discovery; or (3) Limit the scope of discovery or preclude any inquiry into certain matters during discovery. (i) <E T="03">Duty to supplement or amend responses.</E> A party who has responded to a discovery request has a duty to supplement or amend the response, as soon as the information is known, as follows: (1) A party shall supplement or amend any response to a question requesting the identity and location of any person having knowledge of discoverable matters. (2) A party shall supplement or amend any response to a question requesting the identity of each person who will be called to testify at the hearing as an expert witness and the subject matter and substance of that witness’ testimony. (3) A party shall supplement or amend any response that was incorrect when made or any response that was correct when made but is no longer correct, accurate, or complete. (j) <E T="03">Depositions.</E> The following rules apply to depositions taken pursuant to this section: (1) <E T="03">Form.</E> A deposition shall be taken on the record and reduced to writing. The person being deposed shall sign the deposition unless the parties agree to waive the requirement of a signature. (2) <E T="03">Administration of oaths.</E> Within the United States, or a territory or possession subject to the jurisdiction of the United States, a party shall take a deposition before a person authorized to administer oaths by the laws of the United States or authorized by the law of the place where the examination is held. In foreign countries, a party shall take a deposition in any manner allowed by the Federal Rules of Civil Procedure. (3) <E T="03">Notice of deposition.</E> A party shall serve a notice of deposition, stating the time and place of the deposition and the name and address of each person to be examined, on the person to be deposed, on the administrative law judge, on the hearing docket clerk, and on each party not later than 7 days before the deposition. A party may serve a notice of deposition less than 7 days before the deposition only with consent of the administrative law judge. If a subpoena <E T="03">duces tecum</E> is to be served on the person to be examined, the party shall attach a copy of the subpoena <E T="03">duces tecum</E> that describes the materials to be produced at the deposition to the notice of deposition. (4) <E T="03">Use of depositions.</E> A party may use any part or all of a deposition at a hearing authorized under this subpart only upon a showing of good cause. The deposition may be used against any party who was present or represented at the deposition or who had reasonable notice of the deposition. (k) <E T="03">Interrogatories.</E> A party, the party's attorney, or the party's representative may sign the party's responses to interrogatories. A party shall answer each interrogatory separately and completely in writing.If a party objects to an interrogatory, the party shall state the objection and the reasons for the objection. An opposing party may use any part or all of a party's responses to interrogatories at a hearing authorized under this subpart to the extent that the response is relevant, material, and not repetitious. (1) A party shall not serve more than 30 interrogatories to each other party. <PRTPAGE P="65"/>Each subpart of an interrogatory shall be counted as a separate interrogatory. (2) A party shall file a motion for leave to serve additional interrogatories on a party with the administrative law judge before serving additional interrogatories on a party. The administrative law judge shall grant the motion only if the party shows good cause for the party's failure to inquire about the information previously and that the information cannot reasonably be obtained using less burdensome discovery methods or be obtained from other sources. (l) <E T="03">Requests for admission.</E> A party may serve a written request for admission of the truth of any matter within the scope of discovery under this section or the authenticity of any document described in the request. A party shall set forth each request for admission separately. A party shall serve copies of documents referenced in the request for admission unless the documents have been provided or are reasonably available for inspection and copying. (1) <E T="03">Time</E>. A party's failure to respond to a request for admission, in writing and signed by the attorney or the party, not later than 30 days after service of the request, is deemed an admission of the truth of the statement or statements contained in the request for admission. The administrative law judge may determine that a failure to respond to a request for admission is not deemed an admission of the truth if a party shows that the failure was due to circumstances beyond the control of the party or the party's attorney. (2) <E T="03">Response.</E> A party may object to a request for admission and shall state the reasons for objection. A party may specifically deny the truth of the matter or describe the reasons why the party is unable to truthfully deny or admit the matter. If a party is unable to deny or admit the truth of the matter, the party shall show that the party has made reasonable inquiry into the matter or that the information known to, or readily obtainable by, the party is insufficient to enable the party to admit or deny the matter. A party may admit or deny any part of the request for admission. If the administrative law judge determines that a response does not comply with the requirements of this rule or that the response is insufficient, the matter is deemed admitted. (3) <E T="03">Effect of admission.</E> Any matter admitted or deemed admitted under this section is conclusively established for the purpose of the hearing and appeal. (m) <E T="03">Motion to compel discovery</E>. A party may make a motion to compel discovery if a person refuses to answer a question during a deposition, a party fails or refuses to answer an interrogatory, if a person gives an evasive or incomplete answer during a deposition or when responding to an interrogatory, or a party fails or refuses to produce documents or tangible items. During a deposition, the proponent of a question may complete the deposition or may adjourn the examination before making a motion to compel if a person refuses to answer. (n) <E T="03">Failure to comply with a discovery order or order to compel.</E> If a party fails to comply with a discovery order or an order to compel, the administrative law judge, limited to the extent of the party's failure to comply with the discovery order or motion to compel, may: (1) Strike that portion of a party's pleadings; (2) Preclude prehearing or discovery motions by that party; (3) Preclude admission of that portion of a party's evidence at the hearing; or (4) Preclude that portion of the testimony of that party's witnesses at the hearing. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990, as amended by Amdt. 13-23, 55 FR 45983, Oct. 31, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.221</SECTNO> <SUBJECT>Notice of hearing.</SUBJECT> (a) <E T="03">Notice.</E> The administrative law judge shall give each party at least 60 days notice of the date, time, and location of the hearing. (b) <E T="03">Date, time, and location of the hearing.</E> The administrative law judge to whom the proceedings have been assigned shall set a reasonable date, time, and location for the hearing. The administrative law judge shall consider the need for discovery and any joint <PRTPAGE P="66"/>procedural or discovery schedule submitted by the parties when determining the hearing date. The administrative law judge shall give due regard to the convenience of the parties, the location where the majority of the witnesses reside or work, and whether the location is served by a scheduled air carrier. (c) <E T="03">Earlier hearing.</E> With the consent of the administrative law judge, the parties may agree to hold the hearing on an earlier date than the date specified in the notice of hearing. </SECTION> <SECTION> <SECTNO>§ 13.222</SECTNO> <SUBJECT>Evidence.</SUBJECT> (a) <E T="03">General.</E> A party is entitled to present the party's case or defense by oral, documentary, or demonstrative evidence, to submit rebuttal evidence, and to conduct any cross-examination that may be required for a full and true disclosure of the facts. (b) <E T="03">Admissibility.</E> A party may introduce any oral, documentary, or demonstrative evidence in support of the party's case or defense. The administrative law judge shall admit any oral, documentary, or demonstrative evidence introduced by a party but shall exclude irrelevant, immaterial, or unduly repetitious evidence. (c) <E T="03">Hearsay evidence.</E> Hearsay evidence is admissible in proceedings governed by this subpart. The fact that evidence submitted by a party is hearsay goes only to the weight of the evidence and does not affect its admissibility. </SECTION> <SECTION> <SECTNO>§ 13.223</SECTNO> <SUBJECT>Standard of proof.</SUBJECT> The administrative law judge shall issue an initial decision or shall rule in a party's favor only if the decision or ruling is supported by, and in accordance with, the reliable, probative, and substantial evidence contained in the record. In order to prevail, the party with the burden of proof shall prove the party's case or defense by a preponderance of reliable, probative, and substantial evidence. </SECTION> <SECTION> <SECTNO>§ 13.224</SECTNO> <SUBJECT>Burden of proof.</SUBJECT> (a) Except in the case of an affirmative defense, the burden of proof is on the agency. (b) Except as otherwise provided by statute or rule, the proponent of a motion, request, or order has the burden of proof. (c) A party who has asserted an affirmative defense has the burden of proving the affirmative defense. </SECTION> <SECTION> <SECTNO>§ 13.225</SECTNO> <SUBJECT>Offer of proof.</SUBJECT> A party whose evidence has been excluded by a ruling of the administrative law judge may offer the evidence for the record on appeal. </SECTION> <SECTION> <SECTNO>§ 13.226</SECTNO> <SUBJECT>Public disclosure of evidence.</SUBJECT> (a) The administrative law judge may order that any information contained in the record be withheld from public disclosure. Any person may object to disclosure of information in the record by filing a written motion to withhold specific information with the administrative law judge and serving a copy of the motion on each party. The party shall state the specific grounds for nondisclosure in the motion. (b) The administrative law judge shall grant the motion to withhold information in the record if, based on the motion and any response to the motion, the administrative law judge determines that disclosure would be detrimental to aviation safety, disclosure would not be in the public interest, or that the information is not otherwise required to be made available to the public. </SECTION> <SECTION> <SECTNO>§ 13.227</SECTNO> <SUBJECT>Expert or opinion witnesses.</SUBJECT> An employee of the agency may not be called as an expert or opinion witness, for any party other than the FAA, in any proceeding governed by this subpart. An employee of a respondent may not be called by an agency attorney as an expert or opinion witness for the FAA in any proceeding governed by this subpart to which the respondent is a party. </SECTION> <SECTION> <SECTNO>§ 13.228</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> (a) <E T="03">Request for subpoena.</E> A party may obtain a subpoena to compel the attendance of a witness at a deposition or hearing or to require the production of documents or tangible items from the hearing docket clerk. The hearing docket clerk shall deliver the subpoena, signed by the hearing docket clerk or an administrative law judge but otherwise in blank, to the party. <PRTPAGE P="67"/>The party shall complete the subpoena, stating the title of the action and the date and time for the witness’ attendance or production of documents or items. The party who obtained the subpoena shall serve the subpoena on the witness. (b) <E T="03">Motion to quash or modify the subpoena.</E> A party, or any person upon whom a subpoena has been served, may file a motion to quash or modify the subpoena with the administrative law judge at or before the time specified in the subpoena for compliance. The applicant shall describe, in detail, the basis for the application to quash or modify the supoena including, but not limited to, a statement that the testimony, document, or tangible evidence is not relevant to the proceeding, that the subpoena is not reasonably tailored to the scope of the proceeding, or that the subpoena is unreasonable and oppressive. A motion to quash or modify the subpoena will stay the effect of the subpoena pending a decision by the administrative law judge on the motion. (c) <E T="03">Enforcement of subpoena.</E> Upon a showing that a person has failed or refused to comply with a subpoena, a party may apply to the local Federal district court to seek judicial enforcement of the subpoena in accordance with section 1004 of the Federal Aviation Act of 1958, as amended. </SECTION> <SECTION> <SECTNO>§ 13.229</SECTNO> <SUBJECT>Witness fees.</SUBJECT> (a) <E T="03">General.</E> Unless otherwise authorized by the administrative law judge, the party who applies for a subpoena to compel the attendance of a witness at a deposition or hearing, or the party at whose request a witness appears at a deposition or hearing, shall pay the witness fees described in this section. (b) <E T="03">Amount.</E> Except for an employee of the agency who appears at the direction of the agency, a witness who appears at a deposition or hearing is entitled to the same fees and mileage expenses as are paid to a witness in a court of the United States in comparable circumstances. </SECTION> <SECTION> <SECTNO>§ 13.230</SECTNO> <SUBJECT>Record.</SUBJECT> (a) <E T="03">Exclusive record.</E> The transcript of all testimony in the hearing, all exhibits received into evidence, and all motions, applications, requests, and rulings shall constitute the exclusive record for decision of the proceedings and the basis for the issuance of any orders in the proceeding. Any proceedings regarding the disqualification of an administrative law judge shall be included in the record. (b) <E T="03">Examination and copying of record.</E> Any person may examine the record at the Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591. Any person may have a copy of the record after payment of reasonable costs to copy the record. </SECTION> <SECTION> <SECTNO>§ 13.231</SECTNO> <SUBJECT>Argument before the administrative law judge.</SUBJECT> (a) <E T="03">Arguments during the hearing.</E> During the hearing, the administrative law judge shall give the parties a reasonable opportunity to present arguments on the record supporting or opposing motions, objections, and rulings if the parties request an opportunity for argument. The administrative law judge may request written arguments during the hearing if the administrative law judge finds that submission of written arguments would be reasonable. (b) <E T="03">Final oral argument.</E> At the conclusion of the hearing and before the administrative law judge issues an initial decision in the proceedings, the parties are entitled to submit oral proposed findings of fact and conclusions of law, exceptions to rulings of the administrative law judge, and supporting arguments for the findings, conclusions, or exceptions. At the conclusion of the hearing, a party may waive final oral argument. (c) <E T="03">Posthearing briefs.</E> The administrative law judge may request written posthearing briefs before the administrative law judge issues an initial decision in the proceedings if the administrative law judge finds that submission of written arguments would be reasonable. If a party files a written posthearing brief, the party shall include proposed findings of fact and conclusions of law, exceptions to rulings of the administrative law judge, and supporting arguments for the findings, conclusions, or exceptions. The administrative law judge shall give the parties a reasonable opportunity, not more than 30 days after receipt of the <PRTPAGE P="68"/>transcript, to prepare and submit the briefs. </SECTION> <SECTION> <SECTNO>§ 13.232</SECTNO> <SUBJECT>Initial decision.</SUBJECT> (a) <E T="03">Contents.</E> The administrative law judge shall issue an initial decision at the conclusion of the hearing. In each oral or written decision, the administrative law judge shall include findings of fact and conclusions of law, and the grounds supporting those findings and conclusions, upon all material issues of fact, the credibility of witnesses, the applicable law, any exercise of the administrative law judge's discretion, the amount of any civil penalty found appropriate by the administrative law judge, and a discussion of the basis for any order issued in the proceedings. The administrative law judge is not required to provide a written explanation for rulings on objections, procedural motions, and other matters not directly relevant to the substance of the initial decision. If the administrative law judge refers to any previous unreported or unpublished initial decision, the administrative law judge shall make copies of that initial decision available to all parties and the FAA decisionmaker. (b) <E T="03">Oral decision.</E> Except as provided in paragraph (c) of this section, at the conclusion of the hearing, the administrative law judge shall issue the initial decision and order orally on the record. (c) <E T="03">Written decision.</E> The administrative law judge may issue a written initial decision not later than 30 days after the conclusion of the hearing or submission of the last posthearing brief if the administrative law judge finds that issuing a written initial decision is reasonable. The administrative law judge shall serve a copy of any written initial decision on each party. (d) <E T="03">Order assessing civil penalty.</E> Unless appealed pursuant to § 13.233 of this subpart, the initial decision issued by the administrative law judge shall be considered an order assessing civil penalty if the administrative law judge finds that an alleged violation occurred and determines that a civil penalty, in an amount found appropriate by the administrative law judge, is warranted. </SECTION> <SECTION> <SECTNO>§ 13.233</SECTNO> <SUBJECT>Appeal from initial decision.</SUBJECT> (a) <E T="03">Notice of appeal.</E> A party may appeal the initial decision, and any decision not previously appealed pursuant to § 13.219, by filing a notice of appeal with the FAA decisionmaker. A party shall file the notice of appeal with the Federal Aviation Administration, 800 Independence Avenue, SW., Room 924A, Washington, DC 20591, Attention: Appellate Docket Clerk. A party shall file the notice of appeal not later than 10 days after entry of the oral initial decision on the record or service of the written initial decision on the parties and shall serve a copy of the notice of appeal on each party. (b) <E T="03">Issues on appeal.</E> A party may appeal only the following issues: (1) Whether each filing of fact is supported by a preponderance of reliable, probative, and substantial evidence; (2) Whether each conclusion of law is made in accordance with applicable law, precedent, and public policy; and (3) Whether the administrative law judge committed any prejudicial errors during the hearing that support the appeal. (c) <E T="03">Perfecting an appeal.</E> Unless otherwise agreed by the parties, a party shall perfect an appeal, not later than 50 days after entry of the oral initial decision on the record or service of the written initial decision on the party, by filing an appeal brief with the FAA decisionmaker. (1) <E T="03">Extension of time by agreement of the parties.</E> The parties may agree to extend the time for perfecting the appeal with the consent of the FAA decisionmaker. If the FAA decisionmaker grants an extension of time to perfect the appeal, the appellate docket clerk shall serve a letter confirming the extension of time on each party. (2) <E T="03">Written motion for extension.</E> If the parties do not agree to an extension of time for perfecting an appeal, a party desiring an extension of time may file a written motion for an extension with the FAA decisionmaker and shall serve a copy of the motion on each party. The FAA decisionmaker may grant an extension if good cause for the extension is shown in the motion.<PRTPAGE P="69"/> (d) <E T="03">Appeal briefs.</E> A party shall file the appeal brief with the FAA decisionmaker and shall serve a copy of the appeal brief on each party. (1) A party shall set forth, in detail, the party's specific objections to the initial decision or rulings in the appeal brief. A party also shall set forth, in detail, the basis for the appeal, the reasons supporting the appeal, and the relief requested in the appeal. If the party relies on evidence contained in the record for the appeal, the party shall specifically refer to the pertinent evidence contained in the transcript in the appeal brief. (2) The FAA decisionmaker may dismiss an appeal, on the FAA decisionmaker's own initiative or upon motion of any other party, where a party has filed a notice of appeal but fails to perfect the appeal by timely filing an appeal brief with the FAA decisionmaker. (e) <E T="03">Reply brief.</E> Unless otherwise agreed by the parties, any party may file a reply brief with the FAA decisionmaker not later than 35 days after the appeal brief has been served on that party. The party filing the reply brief shall serve a copy of the reply brief on each party. If the party relies on evidence contained in the record for the reply, the party shall specifically refer to the pertinent evidence contained in the transcript in the reply brief. (1) <E T="03">Extension of time by agreement of the parties.</E> The parties may agree to extend the time for filing a reply brief with the consent of the FAA decisionmaker. If the FAA decisionmaker grants an extension of time to file the reply brief, the appellate docket clerk shall serve a letter confirming the extension of time on each party. (2) <E T="03">Written motion for extension.</E> If the parties do not agree to an extension of time for filing a reply brief, a party desiring an extension of time may file a written motion for an extension with the FAA decisionmaker and shall serve a copy of the motion on each party. The FAA decisionmaker may grant an extension if good cause for the extension is shown in the motion. (f) <E T="03">Other briefs.</E> The FAA decisionmaker may allow any person to submit an <E T="03">amicus curiae</E> brief in an appeal of an initial decision. A party may not file more than one appeal brief or reply brief. A party may petition the FAA decisionmaker, in writing, for leave to file an additional brief and shall serve a copy of the petition on each party. The party may not file the additional brief with the petition. The FAA decisionmaker may grant leave to file an additional brief if the party demonstrates good cause for allowing additional argument on the appeal. The FAA decisionmaker will allow a reasonable time for the party to file the additional brief. (g) <E T="03">Number of copies.</E> A party shall file the original appeal brief or the original reply brief, and two copies of the brief, with the FAA decisionmaker. (h) <E T="03">Oral argument.</E> The FAA decisionmaker has sole discretion to permit oral argument on the appeal. On the FAA decisionmaker's own initiative or upon written motion by any party, the FAA decisionmaker may find that oral argument will contribute substantially to the development of the issues on appeal and may grant the parties an opportunity for oral argument. (i) <E T="03">Waiver of objections on appeal.</E> If a party fails to object to any alleged error regarding the proceedings in an appeal or a reply brief, the party waives any objection to the alleged error. The FAA decisionmaker is not required to consider any objection in an appeal brief or any argument in the reply brief if a party's objection is based on evidence contained on the record and the party does not specifically refer to the pertinent evidence from the record in the brief. (j) <E T="03">FAA decisionmaker's decision on appeal.</E> The FAA decisionmaker will review the briefs on appeal and the oral argument, if any, to determine if the administrative law judge committed prejudicial error in the proceedings or that the initial decision should be affirmed, modified, or reversed. The FAA decisionmaker may affirm, modify, or reverse the initial decision, make any necessary findings, or may remand the case for any proceedings that the FAA decisionmaker determines may be necessary. (1) The FAA decisionmaker may raise any issue, on the FAA decisionmaker's own initiative, that is required for proper disposition of the proceedings. <PRTPAGE P="70"/>The FAA decisionmaker will give the parties a reasonable opportunity to submit arguments on the new issues before making a decision on appeal. If an issue raised by the FAA decisionmaker requires the consideration of additional testimony or evidence, the FAA decisionmaker will remand the case to the administrative law judge for further proceedings and an initial decision related to that issue. If an issue raised by the FAA decisionmaker is solely an issue of law or the issue was addressed at the hearing but was not raised by a party in the briefs on appeal, a remand of the case to the administrative law judge for further proceedings is not required but may be provided in the discretion of the FAA decisionmaker. (2) The FAA decisionmaker will issue the final decision and order of the Administrator on appeal in writing and will serve a copy of the decision and order on each party. Unless a petition for review is filed pursuant to § 13.235, a final decision and order of the Administrator shall be considered an order assessing civil penalty if the FAA decisionmaker finds that an alleged violation occurred and a civil penalty is warranted. (3) A final decision and order of the Administrator after appeal is precedent in any other civil penalty action. Any issue, finding or conclusion, order, ruling, or initial decision of an administrative law judge that has not been appealed to the FAA decisionmaker is not precedent in any other civil penalty action. </SECTION> <SECTION> <SECTNO>§ 13.234</SECTNO> <SUBJECT>Petition to reconsider or modify a final decision and order of the FAA decisionmaker on appeal.</SUBJECT> (a) <E T="03">General.</E> Any party may petition the FAA decisionmaker to reconsider or modify a final decision and order issued by the FAA decisionmaker on appeal from an initial decision. A party shall file a petition to reconsider or modify with the FAA decisionmaker not later than 30 days after service of the FAA decisionmaker's final decision and order on appeal and shall serve a copy of the petition on each party. The FAA decisionmaker will not reconsider or modify an initial decision and order issued by an administrative law judge that has not been appealed by any party to the FAA decisionmaker. (b) <E T="03">Form and number of copies.</E> A party shall file a petition to reconsider or modify, in writing, with the FAA decisionmaker. The party shall file the original petition with the FAA decisionmaker and shall serve a copy of the petition on each party. (c) <E T="03">Contents.</E> A party shall state briefly and specifically the alleged errors in the final decision and order on appeal, the relief sought by the party, and the grounds that support, the petition to reconsider or modify. (1) If the petition is based, in whole or in part, on allegations regarding the consequences of the FAA decisionmaker's decision, the party shall describe these allegations and shall describe, and support, the basis for the allegations. (2) If the petition is based, in whole or in part, on new material not previously raised in the proceedings, the party shall set forth the new material and include affidavits of prospective witnesses and authenticated documents that would be introduced in support of the new material. The party shall explain, in detail, why the new material was not discovered through due diligence prior to the hearing. (d) <E T="03">Repetitious and frivolous petitions.</E> The FAA decisionmaker will not consider repetitious or frivolous petitions. The FAA decisionmaker may summarily dismiss repetitious or frivolous petitions to reconsider or modify. (e) <E T="03">Reply petitions.</E> Any other party may reply to a petition to reconsider or modify, not later than 10 days after service of the petition on that party, by filing a reply with the FAA decisionmaker. A party shall serve a copy of the reply on each party. (f) <E T="03">Effect of filing petition.</E> Unless otherwise ordered by the FAA decisionmaker, filing of a petition pursuant to this section will not stay or delay the effective date of the FAA decisionmaker's final decision and order on appeal and shall not toll the time allowed for judicial review. (g) <E T="03">FAA decisionmaker's decision on petition.</E> The FAA decisionmaker has sole discretion to grant or deny a petition to reconsider or modify. The FAA decisionmaker will grant or deny a petition <PRTPAGE P="71"/>to reconsider or modify within a reasonable time after receipt of the petition or receipt of the reply petition, if any. The FAA decisionmaker may affirm, modify, or reverse the final decision and order on appeal, or may remand the case for any proceedings that the FAA decisionmaker determines may be necessary. <CITA>[Amdt. 13-21, 55 FR 27575, July 3, 1990; 55 FR 29293, July 18, 1990; Amdt. 13-23, 55 FR 45983, Oct. 31, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 13.235</SECTNO> <SUBJECT>Judicial review of a final decision and order.</SUBJECT> A person may seek judicial review of a final decision and order of the Administrator as provided in section 1006 of the Federal Aviation Act of 1958, as amended. A party seeking judicial review of a final decision and order shall file a petition for review not later than 60 days after the final decision and order has been served on the party. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Civil Monetary Penalty Inflation Adjustment</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 28762, 61 FR 67445, Dec. 20, 1996, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 13.301</SECTNO> <SUBJECT>Scope and purpose.</SUBJECT> (a) This subpart provides a mechanism for the regular adjustment for inflation of civil monetary penalties in conformity with the Federal Civil Penalties Inflation Adjustment Act of 1990, 28 U.S.C. 2461 (note), as amended by the Debt Collection Improvement Act of 1996, Public Law 104-134, April 26, 1996, in order to maintain the deterrent effect of civil monetary penalties and to promote compliance with the law. This subpart also sets out the current adjusted maximum civil monetary penalties or range of minimum and maximum civil monetary penalties for each statutory civil penalty subject to the FAA's jurisdiction. (b) Each adjustment to the maximum civil monetary penalty or the range of minimum and maximum civil monetary penalties, as applicable, made in accordance with this subpart applies prospectively from the date it becomes effective to actions initiated under this part, notwithstanding references to a specific maximum civil monetary penalty or range of minimum and maximum civil monetary penalties contained elsewhere in this part. </SECTION> <SECTION> <SECTNO>§ 13.303</SECTNO> <SUBJECT>Definitions.</SUBJECT> (a) <E T="03">Civil Monetary Penalty</E> means any penalty, fine, or other sanction that: (1) Is for a specific monetary amount as provided by Federal law or has a maximum amount provided by Federal law; (2) Is assessed or enforced by the FAA pursuant to Federal law; and (3) Is assessed or enforced pursuant to an administrative proceeding or a civil action in the Federal courts. (b) <E T="03">Consumer Price Index</E> means the Consumer Price Index for all urban consumers published by the Department of Labor. </SECTION> <SECTION> <SECTNO>§ 13.305</SECTNO> <SUBJECT>Cost of living adjustments of civil monetary penalties.</SUBJECT> (a) Except for the limitation to the initial adjustment to statutory maximum civil monetary penalties or range of minimum and maximum civil monetary penalties set forth in paragraph (c) of this section, the inflation adjustment under this subpart is determined by increasing the maximum civil monetary penalty or range of minimum and maximum civil monetary penalty for each civil monetary penalty by the cost-of-living adjustment. Any increase determined under paragraph (a) of this section is rounded to the nearest: (1) Multiple of $10 in the case of penalties less than or equal to $100; (2) Multiple of $100 in the case of penalties greater than $100 but less than or equal to $1,000; (3) Multiple of $1,000 in the case of penalties greater than $1,000 but less than or equal to $10,000; (4) Multiple of $5,000 in the case of penalties greater than $10,000 but less than or equal to $100,000; (5) Multiple of $10,000 in the case of penalties greater than $100,000 but less than or equal to $200,000; and (6) Multiple of $25,000 in the case of penalties greater than $200,000. (b) For purposes of paragraph (a) of this section, the term “cost-of-living adjustment” means the percentage (if any) for each civil monetary penalty by which the Consumer Price Index for the month of June of the calendar year <PRTPAGE P="72"/>preceding the adjustment exceeds the Consumer Price Index for the month of June of the calendar year in which the amount of such civil monetary penalty was last set or adjusted pursuant to law. (c) Limitation on initial adjustment. The initial adjustment of maximum civil penalty or range of minimum and maximum civil monetary penalties made pursuant to this subpart does not exceed 10 percent of the statutory maximum civil penalty before an adjustment under this subpart is made. This limitation applies only to the initial adjustment, effective on January 21, 1997. (d) <E T="03">Inflation adjustment.</E> Minimum and maximum civil monetary penalties within the jurisdiction of the FAA are adjusted for inflation as follows: <GPOTABLE CDEF="s50,r75,xls40,xls40,r50,r50" COLS="6" OPTS="L2,i1"> <TTITLE> <E T="04">Minimum and Maximum Civil Penalties—Adjusted for Inflation, Effective January 21, 1997</E> </TTITLE> <BOXHD> <CHED H="1">United States Code<LI>citation</LI> </CHED> <CHED H="1">Civil monetary penalty<LI>description</LI> </CHED> <CHED H="1">Minimum penalty amount as of<LI>10/23/96</LI> </CHED> <CHED H="1">New adjusted minimum penalty amount</CHED> <CHED H="1">Maximum penalty amount as of 10/26/96</CHED> <CHED H="1">New adjusted maximum penalty amount</CHED> </BOXHD> <ROW> <ENT I="01">49 U.S.C. 5123(a) (changed 1990) </ENT> <ENT>Violations of hazardous materials transportation law or regulations </ENT> <ENT>$250 per violation per day </ENT> <ENT>$250 per violation per day </ENT> <ENT>$25,000 per violation per day </ENT> <ENT>$27,500 per violation per day.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46301(a)(1) (1958) </ENT> <ENT>Violations of FAA statute or regulations by a person </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$1,000 per violation per day or per flight </ENT> <ENT>$1,100 per violation per day or per flight.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46301(a)(2) (changed 1987) </ENT> <ENT>Violations of FAA statute or regulations by a person operating an aircraft for the transportation of passengers or property for compensation </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation per day or per flight </ENT> <ENT>$11,000 per violation per day or per flight.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46301(a)(3)(A) (1974) </ENT> <ENT>Violations of FAA statute or regulations involving the transportation of hazardous materials by air </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation per day or per flight </ENT> <ENT>$11,000 per violation per day or per flight.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 463(a)(3)(B) (1988) </ENT> <ENT>Violations of FAA statute or regulations involving the registration or recordation under chapter 441 of aircraft not used to provide air transportation </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation per day or per flight </ENT> <ENT>$11,000 per violation per day or per flight.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46301(b) (1987) </ENT> <ENT>Tampering with a smoke alarm device </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$2,000 per violation </ENT> <ENT>$2,200 per violation.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46302 (1984) </ENT> <ENT>Knowingly providing false information about alleged violations involving the special aircraft jurisdiction of the United States </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation </ENT> <ENT>$11,000 per violation.</ENT> </ROW> <ROW> <ENT I="01">49 U.S.C. 46303 (1984) </ENT> <ENT>Carrying a concealed deadly or dangerous weapon </ENT> <ENT>N/A </ENT> <ENT>N/A </ENT> <ENT>$10,000 per violation </ENT> <ENT>$11,000 per violation.</ENT> </ROW> </GPOTABLE> <CITA TYPE="W">[61 FR 67445, Dec. 20, 1996, as amended by Amdt. 13-28, 62 FR 4134, Jan. 29, 1997]</CITA> </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 14</EAR> <HD SOURCE="HED">PART 14—RULES IMPLEMENTING THE EQUAL ACCESS TO JUSTICE ACT OF 1980</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—General Provisions</HD> <SECHD>Sec.</SECHD> <SECTNO>14.01</SECTNO> <SUBJECT>Purpose of these rules.</SUBJECT> <SECTNO>14.02</SECTNO> <SUBJECT>Proceedings covered.</SUBJECT> <SECTNO>14.03</SECTNO> <SUBJECT>Eligibility of applicants.</SUBJECT> <SECTNO>14.04</SECTNO> <SUBJECT>Standards for awards.</SUBJECT> <SECTNO>14.05</SECTNO> <SUBJECT>Allowance fees and expenses.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Information Required From Applicants</HD> <SECTNO>14.10</SECTNO> <SUBJECT>Contents of application.</SUBJECT> <SECTNO>14.11</SECTNO> <SUBJECT>Net worth exhibit.</SUBJECT> <SECTNO>14.12</SECTNO> <SUBJECT>Documentation of fees and expenses.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Procedures for Considering Applications</HD> <SECTNO>14.20</SECTNO> <SUBJECT>When an application may be filed.</SUBJECT> <SECTNO>14.21</SECTNO> <SUBJECT>Filing and service of documents.</SUBJECT> <SECTNO>14.22</SECTNO> <SUBJECT>Answer to application.</SUBJECT> <SECTNO>14.23</SECTNO> <SUBJECT>Reply.</SUBJECT> <SECTNO>14.24</SECTNO> <SUBJECT>Comments by other parties.</SUBJECT> <SECTNO>14.25</SECTNO> <SUBJECT>Settlement.<PRTPAGE P="73"/> </SUBJECT> <SECTNO>14.26</SECTNO> <SUBJECT>Further proceedings.</SUBJECT> <SECTNO>14.27</SECTNO> <SUBJECT>Decision.</SUBJECT> <SECTNO>14.28</SECTNO> <SUBJECT>Review by FAA Decisionmaker.</SUBJECT> <SECTNO>14.29</SECTNO> <SUBJECT>Judicial review.</SUBJECT> <SECTNO>14.30</SECTNO> <SUBJECT>Payment of award.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 5 U.S.C. 504; 49 U.S.C. 106(g), 40113, 46104. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> 54 FR 46199, Nov. 1, 1989, unless otherwise noted. </SOURCE> <SUBPART> <HD SOURCE="HED">Subpart A—General Provisions</HD> <SECTION> <SECTNO>§ 14.01</SECTNO> <SUBJECT>Purpose of these rules.</SUBJECT> The Equal Access to Justice Act, 5 U.S.C. 504 (the Act), provides for the award of attorney fees and other expenses to eligible individuals and entities who are parties to certain administrative proceedings (adversary adjudications) before the Federal Aviation Administration (FAA). An eligible party may receive an award when it prevails over the FAA, unless the agency's position in the proceeding was substantially justified or special circumstances make an award unjust. The rules in this part describe the parties eligible for awards and the proceedings that are covered. They also explain how to apply for awards, and the procedures and standards that the FAA Decisionmaker will use to make them. As used hereinafter, the term “agency” applies to the FAA. </SECTION> <SECTION> <SECTNO>§ 14.02</SECTNO> <SUBJECT>Proceedings covered.</SUBJECT> (a) The Act applies to certain adversary adjudications conducted by the FAA. These are adjudications under 5 U.S.C. 554 in which the position of the FAA is represented by an attorney or other representative who enters an appearance and participates in the proceeding. This subpart applies to proceedings under 49 U.S.C. App. 1475 and 49 U.S.C. App. 1471(a). (b) If a proceeding includes both matters covered by the Act and matters specifically excluded from coverage, any award made will include only fees and expenses related to covered issues. (c) Fees and other expenses may not be awarded to a party for any portion of the adversary adjudication in which such party has unreasonably protracted the proceedings. </SECTION> <SECTION> <SECTNO>§ 14.03</SECTNO> <SUBJECT>Eligibility of applicants.</SUBJECT> (a) To be eligible for an award of attorney fees and other expenses under the Act, the applicant must be a party to the adversary adjudication for which it seeks an award. The term “party” is defined in 5 U.S.C. 551(3). The applicant must show that it meets all conditions or eligibility set out in this subpart and in subpart B of this part. (b) The types of eligible applicants are as follows: (1) An individual with a net worth of not more than $2 million at the time the adversary adjudication was initiated; (2) The sole owner of an unincorporated business who has a net worth of not more than $7 million, including both personal and business interests, and not more than 500 employees at the time the adversary adjudication was initiated; (3) A charitable or other tax-exempt organization described in section 501(c)(3) of the Internal Revenue Code (26 U.S.C. 501(c)(3)) with not more than 500 employees at the time the adversary adjudication was initiated; and (4) A cooperative association as defined in section 15(a) of the Agricultural Marketing Act (12 U.S.C. 1141j(a)) with not more than 500 employees at the time the adversary adjudication was initiated; and (5) Any other partnership, corporation, association, or public or private organization with a net worth of not more than $7 million and not more than 500 employees at the time the adversary adjudication was initiated. (c) For the purpose of eligibility, the net worth and number of employees of an applicant shall be determined as of the date the proceeding was initiated. (d) An applicant who owns an unincorporated business will be considered an “individual” rather than a “sole owner of an unincorporated business” if the issues on which the applicant prevails are related primarily to personal interests rather than to business interest. (e) The employees of an applicant include all persons who regularly perform services for remuneration for the applicant, under the applicant's direction and control. Part-time employees <PRTPAGE P="74"/>shall be included on a proportional basis. (f) The net worth and number of employees of the applicant and all of its affiliates shall be aggregated to determine eligibility. Any individual, corporation, or other entity that directly or indirectly controls or owns a majority of the voting shares or other interest of the applicant, or any corporation or other entity of which the applicant directly or indirectly owns or controls a majority of the voting shares or other interest, will be considered an affiliate for purposes of this part, unless the administrative law judge determines that such treatment would be unjust and contrary to the purposes of the Act in light of the actual relationship between the affiliated entities. In addition, the administrative law judge may determine that financial relationships of the applicant, other than those described in this paragraph, constitute special circumstances that would make an award unjust. (g) An applicant that participates in a proceeding primarily on behalf of one or more other persons or entities that would be ineligible if not itself eligible for an award. </SECTION> <SECTION> <SECTNO>§ 14.04</SECTNO> <SUBJECT>Standards for awards.</SUBJECT> (a) A prevailing applicant may receive an award for attorney fees and other expenses incurred in connection with a proceeding, or in a significant and discrete substantive portion of the proceeding, unless the position of the agency over which the applicant has prevailed was substantially justified. Whether or not the position of the FAA was substantially justified shall be determined on the basis of the record (including the record with respect to the action or failure to act by the agency upon which the civil action is based) which was made in the civil action for which fees and other expenses are sought. The burden of proof that an award should not be made to an eligible prevailing applicant is on the agency counsel, who may avoid an award by showing that the agency's position was reasonable in law and fact. (b) An award will be reduced or denied if the applicant has unduly or unreasonably protracted the proceeding or if special circumstances make the award sought unjust. </SECTION> <SECTION> <SECTNO>§ 14.05</SECTNO> <SUBJECT>Allowance fees and expenses.</SUBJECT> (a) Awards will be based on rates customarily charged by persons engaged in the business of acting as attorneys, agents, and expert witnesses, even if the services were made available without charge or at a reduced rate to the applicant. (b) No award for the fee of an attorney or agent under these rules may exceed $75 per hour. No award to compensate an expert witness may exceed the highest rate at which the agency pays expert witnesses. However, an award may also include the reasonable expenses of the attorney, agent, or witness as a separate item, if the attorney, agent, or witness ordinarily charges clients separately for such expenses. (c) In determining the reasonableness of the fee sought for an attorney, agent, or expert witness, the administrative law judge shall consider the following: (1) If the attorney, agent, or witness is in private practice, his or her customary fee for similar services, or if an employee of the applicant, the fully allocated cost of the services; (2) The prevailing rate for similar services in the community in which the attorney, agent, or witness ordinarily performs services; (3) The time actually spent in the representation of the applicant; (4) The time reasonably spent in light of the difficulty or complexity of the issues in the proceeding; and (5) Such other factors as may bear on the value of the services provided. (d) The reasonable cost of any study, analysis, engineering report, test, project, or similar matter prepared on behalf of a party may be awarded, to the extent that the charge for the service does not exceed the prevailing rate for similar services, and the study or other matter was necessary for preparation of the applicant's case. (e) Fees may be awarded only for work performed after the issuance of a complaint. <CITA>[Amdt. 13-18, 53 FR 34655, Sept. 7, 1988, as amended by Amdt. 14-1, 55 FR 15131, Apr. 20, 1990]</CITA> </SECTION> </SUBPART> <SUBPART> <PRTPAGE P="75"/> <HD SOURCE="HED">Subpart B—Information Required From Applicants</HD> <SECTION> <SECTNO>§ 14.10</SECTNO> <SUBJECT>Contents of application.</SUBJECT> (a) An application for an award of fees and expenses under the Act shall identify the applicant and the proceeding for which an award is sought. The application shall show that the applicant has prevailed and identify the position of the agency in the proceeding that the applicant alleges was not substantially justified. Unless the applicant is an individual, the application shall also state the number of employees of the applicant and describe briefly the type and purpose of its organization or business. (b) The application shall also include a statement that the applicant's net worth does not exceed $2 million (if an individual) or $7 million (for all other applicants, including their affiliates) at the time the adversary adjudication was initiated. However, an applicant may omit this statement if: (1) It attaches a copy of a ruling by the Internal Revenue Service that it qualifies as an organization described in section 501(c)(3) of the Internal Revenue Code (26 U.S.C. 501(c)(3)), or in the case of a tax-exempt organization not required to obtain a ruling from the Internal Revenue Service on its exempt status, a statement that describes the basis for the applicant's belief that it qualifies under such section; or (2) It states that it is a cooperative association as defined in section 15(a) of the Agricultural Marketing Act (12 U.S.C. 1141j(a)). (c) The application shall state the amount of fees and expenses for which an award is sought. (d) The application may also include any other matters that the applicant wishes this agency to consider in determining whether and in what amount an award should be made. (e) The application shall be signed by the applicant or an authorized officer or attorney for the applicant. It shall also contain or be accompanied by a written verification under oath or under penalty of perjury that the information provided in the application is true and correct. (f) If the applicant is a partnership, corporation, association, organization, or sole owner of an unincorporated business, the application shall state that the applicant did not have more than 500 employees at the time the adversary adjudication was initiated, giving the number of its employees and describing briefly the type and purpose of its organization or business. </SECTION> <SECTION> <SECTNO>§ 14.11</SECTNO> <SUBJECT>Net worth exhibit.</SUBJECT> (a) Each applicant except a qualified tax-exempt organization or cooperative association must provide with its application a detailed exhibit showing the net worth of the applicant and any affiliates when the proceeding was initiated. If any individual, corporation, or other entity directly or indirectly controls or owns a majority of the voting shares or other interest of the applicant, or if the applicant directly or indirectly owns or controls a majority of the voting shares or other interest of any corporation or other entity, the exhibit must include a showing of the net worth of all such affiliates or of the applicant including the affiliates. The exhibit may be in any form convenient to the applicant that provides full disclosure of the applicant's and its affiliates’ assets and liabilities and is sufficient to determine whether the applicant qualifies under the standards in this part. The administrative law judge may require an applicant to file additional information to determine the eligibility for an award. (b) The net worth exhibit shall describe any transfers of assets from, or obligations incurred by, the applicant or any affiliate, occurring in the one-year period prior to the date on which the proceeding was initiated, that reduced the net worth of the applicant and its affiliates below the applicable net worth ceiling. If there were no such transactions, the applicant shall so state. (c) Ordinarily, the net worth exhibit will be included in the public record of the proceeding. However, an applicant that objects to public disclosure of information in any portion of the exhibit and believes there are legal grounds for withholding it from disclosure may submit that portion of the exhibit directly to the administrative law judge <PRTPAGE P="76"/>in a sealed envelope labeled “Confidential Financial Information,” accompanied by a motion to withhold the information from public disclosure. The motion shall describe the information sought to be withheld and explain, in detail, why it falls within one or more of the specific exemptions from mandatory disclosure under the Freedom of Information Act, 5 U.S.C. 552(b)(1)-(9), why public disclosure of the information would adversely affect the applicant, and why disclosure is not required in the public interest. The material in question shall be served on counsel representing the agency against which the applicant seeks an award, but need not be served on any other party to the proceeding. If the administrative law judge finds that the information should not be withheld from disclosure, it shall be placed in the public record of the proceeding. Otherwise, any request to inspect or copy the exhibit shall be disposed of in accordance with the FAA's established procedures under the Freedom of Information Act as implemented by 49 CFR part 7, appendix C of the FAA's rules. </SECTION> <SECTION> <SECTNO>§ 14.12</SECTNO> <SUBJECT>Documentation of fees and expenses.</SUBJECT> The application shall be accompanied by full documentation of the fees and expenses, including the cost of any study, analysis, engineering report, test, project or similar matter, for which an award is sought. A separate itemized statement shall be submitted for each professional firm or individual whose services are covered by the application, showing the hours spent in connection with the proceedings by each individual, a description of the specific services performed, the rate at which each fee has been computed, any expenses for which reimbursement is sought, the total amount claimed, and the total amount paid or payable by the applicant or by any other person or entity for the services provided. The administrative law judge may require the applicant to provide vouchers, receipts, or other substantiation for any expenses claimed. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Procedures for Considering Applications</HD> <SECTION> <SECTNO>§ 14.20</SECTNO> <SUBJECT>When an application may be filed.</SUBJECT> (a) An application may be filed whenever the applicant has prevailed in the proceeding, but in no case later than 30 days after the FAA Decisionmaker's final disposition of the proceeding. (b) If review or reconsideration is sought or taken of a decision to which an applicant believes it has prevailed, proceedings for the award of fees shall be stayed pending final disposition of the underlying controversy. (c) For purposes of this rule, final disposition means the later of: (1) The date on which an unappealed initial decision becomes administratively final; (2) Issuance of an order disposing of any petitions for reconsideration of the FAA Decisionmaker's Final order in the proceeding; (3) If no petition for reconsideration is filed, the last date on which such a petition could have been filed; or (4) Issuance of a final order or any other final resolution of a proceeding, such as a settlement or voluntary dismissal, which is not subject to a petition for reconsideration. </SECTION> <SECTION> <SECTNO>§ 14.21</SECTNO> <SUBJECT>Filing and service of documents.</SUBJECT> Any application for an award or other pleading or document related to an application shall be filed and served on all parties to the proceeding in the same manner as other pleadings in the proceeding, except as provided in § 14.11(b) for confidential financial information. </SECTION> <SECTION> <SECTNO>§ 14.22</SECTNO> <SUBJECT>Answer to application.</SUBJECT> (a) Within 30 days after service of an application, counsel representing the agency against which an award is sought may file an answer to the application. Unless agency counsel requests an extension of time for filing or files a statement of intent to negotiate under paragraph (b) of the section, failure to file an answer within the 30-day period may be treated as a consent to the award requested.<PRTPAGE P="77"/> (b) If agency counsel and the applicant believe that the issues in the fee application can be settled, they may jointly file a statement of their intent to negotiate a settlement. The filing of this statement shall extend the time for filing an answer for an additional 30 days, and further extensions may be granted by the administrative law judge upon request by agency counsel and the applicant. (c) The answer shall explain in detail any objections to the award requested and identify the facts relied on in support of agency counsel's position. If the answer is based on any alleged facts not already in the record of the proceeding, agency counsel shall include with the answer either supporting affidavits or a request for further proceedings under § 14.26. </SECTION> <SECTION> <SECTNO>§ 14.23</SECTNO> <SUBJECT>Reply.</SUBJECT> Within 15 days after service of an answer, the applicant may file a reply. If the reply is based on any alleged facts not already in the record of the proceeding, the applicant shall include with the reply either supporting affidavits or a request for further proceedings under § 14.26. </SECTION> <SECTION> <SECTNO>§ 14.24</SECTNO> <SUBJECT>Comments by other parties.</SUBJECT> Any party to a proceeding other than the applicant and agency counsel may file comments on an application within 30 days after it is served or on an answer within 15 days after it is served. A commenting party may not participate further in proceedings on the application unless the administrative law judge determines that the public interest requires such participation in order to permit full exploration of matters raised in the comments. </SECTION> <SECTION> <SECTNO>§ 14.25</SECTNO> <SUBJECT>Settlement.</SUBJECT> The applicant and agency counsel may agree on a proposed settlement of the award before final action on the application, either in connection with a settlement of the underlying proceeding, or after the underlying proceeding has been concluded. If a prevailing party and agency counsel agree on a proposed settlement of an award before an application has been filed, the application shall be filed with the proposed settlement. </SECTION> <SECTION> <SECTNO>§ 14.26</SECTNO> <SUBJECT>Further proceedings.</SUBJECT> (a) Ordinarily the determination of an award will be made on the basis of the written record; however, on request of either the applicant or agency counsel, or on his or her own initiative, the administrative law judge assigned to the matter may order further proceedings, such as an informal conference, oral argument, additional written submissions, or an evidentiary hearing. Such further proceedings shall be held only when necessary for full and fair resolution of the issues arising from the application and shall be conducted as promptly as possible. (b) A request that the administrative law judge order further proceedings under this section shall specifically identify the information sought or the disputed issues and shall explain why the additional proceedings are necessary to resolve the issues. </SECTION> <SECTION> <SECTNO>§ 14.27</SECTNO> <SUBJECT>Decision.</SUBJECT> The administrative law judge shall issue an initial decision on the application within 60 days after completion of proceedings on the application. The decision shall include written findings and conclusions on the applicant's eligibility and status as a prevailing party and an explanation of the reasons for any difference between the amount requested and the amount awarded. The decision shall also include, if at issue, findings on whether the agency's position was substantially justified, whether the applicant unduly protracted the proceedings, or whether special circumstances make an award unjust. </SECTION> <SECTION> <SECTNO>§ 14.28</SECTNO> <SUBJECT>Review by FAA Decisionmaker.</SUBJECT> Either the applicant or the FAA counsel may seek review of the initial decision on the fee application in accordance with subpart G of part 13 of the Federal Aviation Regulations, specifically 14 CFR 13.233. Additionally, the FAA Decisionmaker may decide to review the decision on its own initiative. If neither the applicant nor the agency counsel seeks review within 30 days after the decision is issued, it shall become final. Whether to review a decision is a matter within the discretion of the FAA Decisionmaker. If review is taken, the FAA Decisionmaker <PRTPAGE P="78"/>will issue a final decision on the application or remand the application to the administrative law judge who issued the initial fee award determination for further proceedings. </SECTION> <SECTION> <SECTNO>§ 14.29</SECTNO> <SUBJECT>Judicial review.</SUBJECT> If an applicant is dissatisfied with the determination of fees and other expenses made under this subsection, pursuant 5 U.S.C. 504(c)(2), that applicant may, within thirty (30) days after the determination is made, appeal the determination to the court of the United States having jurisdiction to review the merits of the underlying decision of the FAA adversary adjudication. The court's determination on any appeal heard under this paragraph shall be based solely on the factual record made before the FAA. The court may modify the determination of fees and other expenses only if the court finds that the failure to make an award of fees and other expenses, or the calculation of the amount of the award, was unsupported by substantial evidence. </SECTION> <SECTION> <SECTNO>§ 14.30</SECTNO> <SUBJECT>Payment of award.</SUBJECT> An applicant seeking payment of an award shall submit to the disbursing official of the FAA a copy of the FAA Decisionmaker's final decision granting the award, accompanied by a statement that the applicant will not seek review of the decision in the United States courts. Applications for award grants in cases involving the FAA shall be sent to: The Office of Accounting and Audit, AAA-1, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591. The agency will pay the amount awarded to the applicant within 60 days, unless judicial review of the award or of the underlying decision of the adversary adjudication has been sought by the applicant or any other party to the proceeding. </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 15</EAR> <HD SOURCE="HED">PART 15—ADMINISTRATIVE CLAIMS UNDER FEDERAL TORT CLAIMS ACT</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—General Procedures</HD> <SECHD>Sec.</SECHD> <SECTNO>15.1</SECTNO> <SUBJECT>Scope of regulations.</SUBJECT> <SECTNO>15.3</SECTNO> <SUBJECT>Administrative claim, when presented; appropriate office.</SUBJECT> <SECTNO>15.5</SECTNO> <SUBJECT>Administrative claim, who may file.</SUBJECT> <SECTNO>15.7</SECTNO> <SUBJECT>Administrative claims; evidence and information to be submitted.</SUBJECT> <SECTNO>15.9</SECTNO> <SUBJECT>Investigation and examination.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Indemnification Under Section 1118 of the Federal Aviation Act of 1958</HD> <SECTNO>15.101</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>15.103</SECTNO> <SUBJECT>Exclusions.</SUBJECT> <SECTNO>15.105</SECTNO> <SUBJECT>Filing of requests for indemnification.</SUBJECT> <SECTNO>15.107</SECTNO> <SUBJECT>Notification requirements.</SUBJECT> <SECTNO>15.109</SECTNO> <SUBJECT>Settlements.</SUBJECT> <SECTNO>15.111</SECTNO> <SUBJECT>Conduct of litigation.</SUBJECT> <SECTNO>15.113</SECTNO> <SUBJECT>Indemnification agreements.</SUBJECT> <SECTNO>15.115</SECTNO> <SUBJECT>Payment.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 5 U.S.C. 301; 28 U.S.C. 2672, 2675; 49 U.S.C. 106(g), 40113, 44721. </AUTH> <SUBPART> <HD SOURCE="HED">Subpart A—General Procedures</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 25264, 52 FR 18171, May 13, 1987, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 15.1</SECTNO> <SUBJECT>Scope of regulations.</SUBJECT> (a) These regulations apply to claims asserted under the Federal Tort Claims Act, as amended, for money damages against the United States for injury to, or loss of property, or for personal injury or death, caused by the negligent or wrongful act or omission of an employee of the FAA acting within the scope of office or employment. The regulations in this part supplement the Attorney General's regulations in 28 CFR Part 14, as amended. The regulations in 28 CFR Part 14, as amended, and the regulations in this part apply to consideration by the FAA of administrative claims under the Federal Tort Claims Act. </SECTION> <SECTION> <SECTNO>§ 15.3</SECTNO> <SUBJECT>Administrative claim, when presented; appropriate office.</SUBJECT> (a) A claim is deemed to have been presented when the FAA receives, at a place designated in paragraph (b) of this section, an executed Standard Form 95 or other written notification of an incident, accompanied by a claim for money damages in a sum certain for injury to, or loss of, property or for personal injury or death, alleged to have occurred by reason of the incident. A claim which should have been presented to the FAA but which was mistakenly filed with another Federal <PRTPAGE P="79"/>agency, is deemed presented to the FAA on the date the claim is received by the FAA at a place designated in paragraph (b) of this section. A claim addressed to, or filed with, the FAA by mistake will be transferred to the appropriate Federal agency, if that agency can be determined, or returned to the claimant. (b) Claims shall be delivered or mailed to the Assistant Chief Counsel, Litigation Division, AGC-400, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591, or alternatively, may be mailed or delivered to the Regional Counsel in any of the FAA Regional Offices or the Assistant Chief Counsel, Europe, Africa, and Middle East Area Office. (d) A claim presented in accordance with this section may be amended by the claimant at any time prior to final FAA action or prior to the exercise of the claimant's option, under 28 U.S.C. 2675(a), to deem the agency's failure to make a final disposition of his or her claim within 6 months after it was filed as a final denial. Each amendment to a claim shall be submitted in writing and signed by the claimant or the claimant's duly authorized agent or legal representative. Upon the timely filing of an amendment to a pending claim, the FAA has 6 months thereafter in which to make a final disposition of the claim as amended, and the claimant's option under 28 U.S.C. 2675(a) does not accrue until 6 months after the filing of the amendment. <CITA>[Doc. No. 18884, 44 FR 63723, Nov. 5, 1979, as amended by Amdt. 15-1, 54 FR 39290, Sept. 25, 1989; Amdt. 15-4, 62 FR 46866, Sept. 4, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 15.5</SECTNO> <SUBJECT>Administrative claim, who may file.</SUBJECT> (a) A claim for injury to, or loss of, property may be presented by the owner of the property interest which is the subject of the claim or by the owner's duly authorized agent or legal representative. (b) A claim for personal injury may be presented by the injured person or that person's duly authorized agent or legal representative. (c) A claim based on death may be presented by the executor or administrator of the decedent's estate or by any other person legally entitled to assert such a claim under applicable State law. (d) A claim for loss wholly compensated by an insurer with the rights of a subrogee may be presented by the insurer. A claim for loss partially compensated by an insurer with the rights of a subrogee may be presented by the insurer or the insured individually, as their respective interest appear, or jointly. Whenever an insurer presents a claim asserting the rights of a subrogee, it shall present with its claim appropriate evidence that it has the rights of a subrogee. (e) A claim presented by an agent or legal representative shall be presented in the name of the claimant, be signed by the agent or legal representative, show the title or legal capacity of the person signing, and be accompanied by evidence of authority to present a claim on behalf of the claimant as agent, executor, administrator, parent, guardian, or other representative. </SECTION> <SECTION> <SECTNO>§ 15.7</SECTNO> <SUBJECT>Administrative claims; evidence and information to be submitted.</SUBJECT> (a) <E T="03">Death.</E> In support of a claim based on death, the claimant may be required to submit the following evidence or information: (1) An authenticated death certificate or other competent evidence showing cause of death, date of death, and age of the decedent. (2) The decedent's employment or occupation at time of death, including monthly or yearly salary or earnings (if any), and the duration of last employment or occupation. (3) Full names, addresses, birth dates, kinship, and marital status of the decedent's survivors, including identification of those survivors who were dependent for support upon the decedent at the time of death. (4) Degree of support afforded by the decedent to each survivor dependent upon decedent for support at the time of death. (5) Decedent's general, physical, and mental conditions before death. (6) Itemized bills for medical and burial expenses incurred by reason of the incident causing death or itemized receipts of payment for such expenses.<PRTPAGE P="80"/> (7) If damages for pain and suffering prior to death are claimed, a physician's detailed statement specifying the injuries suffered, duration of pain and suffering, any drugs administered for pain, and the decedent's physical condition in the interval between injury and death. (8) Any other evidence or information which may have a bearing on either the responsibility of the United States for the death or the amount of damages claimed. (b) <E T="03">Personal injury.</E> In support of a claim for personal injury, including pain and suffering, the claimant may be required to submit the following evidence or information: (1) A written report by the attending physician or dentist setting forth the nature and extent of the injuries, nature and extent of treatment, any degree of temporary or permanent disability, the prognosis, period of hospitalization, and any diminished earning capacity. (2) In addition to the report required by paragraph (b)(1) of this section, the claimant may be required to submit to a physical or mental examination by a physician employed by the FAA or another Federal agency. A copy of the report of the examining physician is made available to the claimant upon the claimant's written request if the claimant has, upon request, furnished the report required by paragraph (b)(1), and has made or agrees to make available to the FAA any other physician's reports previously or thereafter made on the physical or mental condition which is the subject matter of the claim. (3) Itemized bills for medical, dental, and hospital expenses incurred or itemized receipts of payment for such expenses. (4) If the prognosis reveals the necessity for future treatment, a statement of expected expenses for such treatment. (5) If a claim is made for loss of time from employment, a written statement from the claimant's employer showing actual time lost from employment, whether the claimant is a full or part-time employee, and wages or salary actually lost. (6) If a claim is made for loss of income and the claimant is self-employed, documentary evidence showing the amount of earnings actually lost. (7) Any other evidence or information which may have a bearing on the responsibility of the United States for the personal injury or the damages claimed. (c) <E T="03">Property damage.</E> In support of a claim for injury to or loss of property, real or personal, the claimant may be required to submit the following evidence or information: (1) Proof of ownership of the property interest which is the subject of the claim. (2) A detailed statement of the amount claimed with respect to each item of property. (3) An itemized receipt of payment for necessary repairs or itemized written estimates of the cost of such repairs. (4) A statement listing date of purchase, purchase price, and salvage value, where repair is not economical. (5) Any other evidence or information which may have a bearing on either the responsibility of the United States for the injury to or loss of property or the damages claimed. </SECTION> <SECTION> <SECTNO>§ 15.9</SECTNO> <SUBJECT>Investigation and examination.</SUBJECT> The FAA may investigate a claim or conduct a physical examination of a claimant. The FAA may request any other Federal agency to investigate a claim or conduct a physical examination of a claimant and provide a report of the investigation or examination to the FAA. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Indemnification Under Section 1118 of the Federal Aviation Act of 1958</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 15-2, 55 FR 18710, May 3, 1990, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 15.101</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the indemnification of a publisher of aeronautical charts or maps under section 1118 of the Federal Aviation Act of 1958, as amended, when the publisher incurs liability as a result of publishing—<PRTPAGE P="81"/> (a) A chart or map accurately depicting a defective or deficient flight procedure or airway that was promulgated by the FAA; or (b) Aeronautical data that— (1) Is visually displayed in the cockpit of an aircraft; and (2) When visually displayed, accurately depicts a defective or deficient flight procedure or airway promulgated by the FAA. </SECTION> <SECTION> <SECTNO>§ 15.103</SECTNO> <SUBJECT>Exclusions.</SUBJECT> A publisher that requests indemnification under this part will not be indemnified if— (a) The complaint filed against the publisher, or demand for payment against the publisher, first occurred before December 19, 1985; (b) The publisher does not negotiate a good faith settlement; (c) The publisher does not conduct a good faith defense; (d) The defective or deficient flight procedure or airway— (1) Was not promulgated by the FAA; (2) Was not accurately depicted on the publisher's chart or map; (3) Was not accurately displayed on a visual display in the cockpit, or (4) Was obviously defective or deficient; (e) The publisher does not give notice as required by § 15.107 of this part and that failure is prejudicial to the Government; or (f) The publisher does not appeal a lower court's decision pursuant to a request by the Administrator under § 15.111(d)(2) of this part. </SECTION> <SECTION> <SECTNO>§ 15.105</SECTNO> <SUBJECT>Filing of requests for indemnification.</SUBJECT> A request for indemnification under this part— (a) May be filed by— (1) A publisher described in § 15.101 of this part; or (2) The publisher's duly authorized agent or legal representative; (b) Shall be filed with the Chief Counsel, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; and (c) Shall state the basis for the publisher's assertion that indemnification under this part is required. </SECTION> <SECTION> <SECTNO>§ 15.107</SECTNO> <SUBJECT>Notification requirements.</SUBJECT> A request for indemnification will not be considered by the FAA unless the following conditions are met: (a) The publisher must notify the Chief Counsel of the FAA, within the time limits prescribed in paragraph (b) or (c) of this section, of the publisher's first receipt of a demand for payment, or service of a complaint in any proceeding, federal or state, in which it appears that indemnification under this part may be required. (b) For each complaint filed, or demand for payment made, on or after December 19, 1985, and before June 4, 1990, the notice required by paragraph (a) of this section must be received by the FAA on or before July 2, 1990. (c) For each complaint filed, or demand for payment made, on or after June 4, 1990, the notice required by paragraph (a) of this section must be received by the FAA within 60 days after the day the publisher first receives the demand for payment or service of the complaint. (d) Within 5 days after the day a judgment is rendered against the publisher in any proceeding, or within 30 days of the denial of an appeal, whichever is later, the publisher must notify the FAA Chief Counsel that— (1) There is an adverse judgment against the publisher; and (2) The publisher has a claim for indemnification against the FAA arising out of that judgment. </SECTION> <SECTION> <SECTNO>§ 15.109</SECTNO> <SUBJECT>Settlements.</SUBJECT> (a) A publisher may not settle a claim with another party, for which the publisher has sought, or intends to seek, indemnification under this part, unless— (1) The publisher submits a copy of the proposed settlement, and a statement justifying the settlement, to the Chief Counsel of the FAA; and (2) The Administrator and where necessary, the appropriate official of the Department of Justice, approves the proposed settlement. (3) The publisher submits a signed release that clearly releases the United States from any further liability to the publisher and the claimant.<PRTPAGE P="82"/> (b) If the Administrator does not approve the proposed settlement, the Administrator will— (1) So notify the publisher by registered mail within 60 days of receipt of the proposed settlement; and (2) Explain why the request for indemnification was not approved. (c) If the Administrator approves the proposed settlement, the Administrator will so notify the publisher by registered mail within 60 days after the FAA's receipt of the proposed settlement. (d) If the Administrator does not have sufficient information to approve or disapprove the proposed settlement, the Administrator will request, within 60 days after receipt of the proposed settlement, the additional information needed to make a determination. </SECTION> <SECTION> <SECTNO>§ 15.111</SECTNO> <SUBJECT>Conduct of litigation.</SUBJECT> (a) If a lawsuit is filed against the publisher and the publisher has sought, or intends to seek, indemnification under this part, the publisher shall— (1) Give notice as required by § 15.107 of this part; (2) If requested by the United States— (i) Implead the United States as a third-party defendant in the action; and (ii) Arrange for the removal of the action to Federal Court; (3) Promptly provide any additional information requested by the United States; and (4) Cooperate with the United States in the defense of the lawsuit. (b) If the lawsuit filed against the publisher results in a proposed settlement, the publisher shall submit that proposed settlement to the FAA for approval in accordance with § 15.109 of this part. (c) If the lawsuit filed against the publisher results in a judgment against the publisher and the publisher has sought, or intends to seek, indemnification under this part as a result of the adverse judgment, the publisher shall— (1) Give notice to the FAA as required by § 15.107(d) of this part; (2) Submit a copy of the trial court's decision to the FAA Chief Counsel not more than 5 business days after the adverse judgment is rendered; and (3) If an appeal is taken from the adverse judgment, submit a copy of the appellate decision to the FAA Chief Counsel not more than 30 days after that decision is rendered. (d) Within 60 days after receipt of the trial court's decision, the Administrator by registered mail will— (1) Notify the publisher that indemnification is required under this part; (2) Request that the publisher appeal the trial court's adverse decision; or (3) Notify the publisher that it is not entitled to indemnification under this part and briefly state the basis for the denial. </SECTION> <SECTION> <SECTNO>§ 15.113</SECTNO> <SUBJECT>Indemnification agreements.</SUBJECT> (a) Upon a finding of the Administrator that indemnification is required under this part, and after obtaining the concurrence of the United States Department of Justice, the FAA will promptly enter into an indemnification agreement providing for the payment of the costs specified in paragraph (c) of this section. (b) The indemnification agreement will be signed by the Chief Counsel and the publisher. (c) The FAA will indemnify the publisher for— (1) Compensatory damages awarded by the court against the publisher; (2) Reasonable costs and fees, including reasonable attorney fees at a rate not to exceed that permitted under the Equal Access to Justice Act (5 U.S.C. 504), and any postjudgment interest, if the publisher conducts a good faith defense, or pursues a good faith appeal, at the request, or with the concurrence, of the FAA. (d) Except as otherwise provided in this section, the FAA will not indemnify the publisher for— (1) Punitive or exemplary damages; (2) Civil or criminal fines or any other litigation sanctions; (3) Postjudgment interest; (4) Costs; (5) Attorney fees; or (6) Other incidental expenses. (e) The indemnification agreement must provide that the Government will be subrogated to all claims or rights of the publisher, including third-party <PRTPAGE P="83"/>claims, cross-claims, and counterclaims. </SECTION> <SECTION> <SECTNO>§ 15.115</SECTNO> <SUBJECT>Payment.</SUBJECT> After execution of the indemnification agreement, the FAA will submit the agreement to the United States Department of Justice and request payment, in accordance with the agreement, from the Judgment Fund. </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 16</EAR> <HD SOURCE="HED">PART 16—RULES OF PRACTICE FOR FEDERALLY-ASSISTED AIRPORT ENFORCEMENT PROCEEDINGS</HD> <CONTENTS> <SUBPART> <HD SOURCE="HED">Subpart A—General Provisions</HD> <SECHD>Sec.</SECHD> <SECTNO>16.1</SECTNO> <SUBJECT>Applicability and description of part.</SUBJECT> <SECTNO>16.3</SECTNO> <SUBJECT>Definitions.</SUBJECT> <SECTNO>16.5</SECTNO> <SUBJECT>Separation of functions.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—General Rules Applicable to Complaints, Proceedings Initiated by the FAA, and Appeals</HD> <SECTNO>16.11</SECTNO> <SUBJECT>Expedition and other modification of process.</SUBJECT> <SECTNO>16.13</SECTNO> <SUBJECT>Filing of documents.</SUBJECT> <SECTNO>16.15</SECTNO> <SUBJECT>Service of documents on the parties and the agency.</SUBJECT> <SECTNO>16.17</SECTNO> <SUBJECT>Computation of time.</SUBJECT> <SECTNO>16.19</SECTNO> <SUBJECT>Motions.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Special Rules Applicable to Complaints</HD> <SECTNO>16.21</SECTNO> <SUBJECT>Pre-complaint resolution.</SUBJECT> <SECTNO>16.23</SECTNO> <SUBJECT>Complaints, answers, replies, rebuttals, and other documents.</SUBJECT> <SECTNO>16.25</SECTNO> <SUBJECT>Dismissals.</SUBJECT> <SECTNO>16.27</SECTNO> <SUBJECT>Incomplete complaints.</SUBJECT> <SECTNO>16.29</SECTNO> <SUBJECT>Investigations.</SUBJECT> <SECTNO>16.31</SECTNO> <SUBJECT>Director's determinations after investigations.</SUBJECT> <SECTNO>16.33</SECTNO> <SUBJECT>Final decisions without hearing.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Special Rules Applicable to Proceedings Initiated by the FAA</HD> <SECTNO>16.101</SECTNO> <SUBJECT>Basis for the initiation of agency action.</SUBJECT> <SECTNO>16.103</SECTNO> <SUBJECT>Notice of investigation.</SUBJECT> <SECTNO>16.105</SECTNO> <SUBJECT>Failure to resolve informally.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Proposed Orders of Compliance</HD> <SECTNO>16.109</SECTNO> <SUBJECT>Orders terminating eligibility for grants, cease and desist orders, and other compliance orders.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Hearings</HD> <SECTNO>16.201</SECTNO> <SUBJECT>Notice and order of hearing.</SUBJECT> <SECTNO>16.202</SECTNO> <SUBJECT>Powers of a hearing officer.</SUBJECT> <SECTNO>16.203</SECTNO> <SUBJECT>Appearances, parties, and rights of parties.</SUBJECT> <SECTNO>16.207</SECTNO> <SUBJECT>Intervention and other participation.</SUBJECT> <SECTNO>16.209</SECTNO> <SUBJECT>Extension of time.</SUBJECT> <SECTNO>16.211</SECTNO> <SUBJECT>Prehearing conference.</SUBJECT> <SECTNO>16.213</SECTNO> <SUBJECT>Discovery.</SUBJECT> <SECTNO>16.215</SECTNO> <SUBJECT>Depositions.</SUBJECT> <SECTNO>16.217</SECTNO> <SUBJECT>Witnesses.</SUBJECT> <SECTNO>16.219</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> <SECTNO>16.221</SECTNO> <SUBJECT>Witness fees.</SUBJECT> <SECTNO>16.223</SECTNO> <SUBJECT>Evidence.</SUBJECT> <SECTNO>16.225</SECTNO> <SUBJECT>Public disclosure of evidence.</SUBJECT> <SECTNO>16.227</SECTNO> <SUBJECT>Standard of proof.</SUBJECT> <SECTNO>16.229</SECTNO> <SUBJECT>Burden of proof.</SUBJECT> <SECTNO>16.231</SECTNO> <SUBJECT>Offer of proof.</SUBJECT> <SECTNO>16.233</SECTNO> <SUBJECT>Record.</SUBJECT> <SECTNO>16.235</SECTNO> <SUBJECT>Argument before the hearing officer.</SUBJECT> <SECTNO>16.237</SECTNO> <SUBJECT>Waiver of procedures.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Initial Decisions, Orders and Appeals</HD> <SECTNO>16.241</SECTNO> <SUBJECT>Initial decisions, orders, and appeals.</SUBJECT> <SECTNO>16.243</SECTNO> <SUBJECT>Consent orders.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Judicial Review</HD> <SECTNO>16.247</SECTNO> <SUBJECT>Judicial review of a final decision and order.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart I—Ex Parte Communications</HD> <SECTNO>16.301</SECTNO> <SUBJECT>Definitions.</SUBJECT> <SECTNO>16.303</SECTNO> <SUBJECT>Prohibited ex parte communications.</SUBJECT> <SECTNO>16.305</SECTNO> <SUBJECT>Procedures for handling ex parte communications.</SUBJECT> <SECTNO>16.307</SECTNO> <SUBJECT>Requirement to show cause and imposition of sanction.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 49 U.S.C. 106(g), 322, 1110, 1111, 1115, 1116, 1718 (a) and (b), 1719, 1723, 1726, 1727, 40103(e), 40113, 40116, 44502(b), 46101, 46104, 46110, 47104, 47106(e), 47107, 47108, 47111(d), 47122, 47123-47125, 47151-47153, 48103. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 27783, 61 FR 54004, October 16, 1996, unless otherwise noted. </SOURCE> <SUBPART> <HD SOURCE="HED">Subpart A—General Provisions</HD> <SECTION> <SECTNO>§ 16.1</SECTNO> <SUBJECT>Applicability and description of part.</SUBJECT> (a) <E T="03">General.</E> The provisions of this part govern all proceedings involving Federally-assisted airports, except for disputes between U.S. and foreign air carriers and airport proprietors concerning the reasonableness of airport fees covered by 14 CFR part 302, whether the proceedings are instituted by order of the FAA or by filing with the FAA a complaint, under the following authorities: (1) 49 U.S.C. 40103(e), prohibiting the grant of exclusive rights for the use of <PRTPAGE P="84"/>any landing area or air navigation facility on which Federal funds have been expended (formerly section 308 of the Federal Aviation Act of 1958, as amended). (2) Requirements of the Anti-Head Tax Act, 49 U.S.C. 40116. (3) The assurances contained in grant-in-aid agreements issued under the Federal Airport Act of 1946, 49 U.S.C. 1101 <E T="03">et seq</E> (repealed 1970). (4) The assurances contained in grant-in-aid agreements issued under the Airport and Airway Development Act of 1970, as amended, 49 U.S.C. 1701 <E T="03">et seq.</E> (5) The assurances contained in grant-in-aid agreements issued under the Airport and Airway Improvement Act of 1982 (AAIA), as amended, 49 U.S.C. 47101 <E T="03">et seq.,</E> specifically section 511(a), 49 U.S.C. 47107(a) and (b). (6) Section 505(d) of the Airport and Airway Improvement Act of 1982, as amended, 49 U.S.C. 47113. (7) Obligations contained in property deeds for property transferred pursuant to section 16 of the Federal Airport Act (49 U.S.C. 1115), section 23 of the Airport and Airway Development Act (49 U.S.C. 1723), or section 516 of the Airport and Airway Improvement Act (49 U.S.C. 47125). (8) Obligations contained in property deeds for property transferred under the Surplus Property Act (49 U.S.C. 47151-47153). (b) <E T="03">Other agencies.</E> Where a grant assurance concerns a statute, executive order, regulation, or other authority that provides an administrative process for the investigation or adjudication of complaints by a Federal agency other than the FAA, persons shall use the administrative process established by those authorities. Where a grant assurance concerns a statute, executive order, regulation, or other authority that enables a Federal agency other than the FAA to investigate, adjudicate, and enforce compliance under those authorities on its own initiative, the FAA may defer to that Federal agency. (c) <E T="03">Other enforcement.</E> If a complaint or action initiated by the FAA involves a violation of the 49 U.S.C. subtitle VII or FAA regulations, except as specified in paragraphs (a)(1) and (a)(2) of this section, the FAA may take investigative and enforcement action under 14 CFR part 13, “Investigative and Enforcement Procedures.” (d) <E T="03">Effective date.</E> This part applies to a complaint filed with the FAA and to an investigation initiated by the FAA on or after December 16, 1996. </SECTION> <SECTION> <SECTNO>§ 16.3</SECTNO> <SUBJECT>Definitions.</SUBJECT> Terms defined in the Acts are used as so defined. As used in this part: <E T="03">Act</E> means a statute listed in § 16.1 and any regulation, agreement, or document of conveyance issued or made under that statute. <E T="03">Agency attorney</E> means the Deputy Chief Counsel; the Assistant Chief Counsel and attorneys in the Airports/Environmental Law Division of the Office of the Chief Counsel; the Assistant Chief Counsel and attorneys in an FAA region or center who represent the FAA during the investigation of a complaint or at a hearing on a complaint, and who prosecute on behalf of the FAA, as appropriate. An agency attorney shall not include the Chief Counsel; the Assistant Chief Counsel for Litigation, or any attorney on the staff of the Assistant Chief Counsel for Litigation, who advises the Associate Administrator regarding an initial decision of the hearing officer or any appeal to the Associate Administrator or who is supervised in that action by a person who provides such advice in an action covered by this part. <E T="03">Agency employee</E> means any employee of the U.S. Department of Transportation. <E T="03">Associate Administrator</E> means the Associate Administrator for Airports or a designee. <E T="03">Complainant</E> means the person submitting a complaint. <E T="03">Complaint</E> means a written document meeting the requirements of this part filed with the FAA by a person directly and substantially affected by anything allegedly done or omitted to be done by any person in contravention of any provision of any Act, as defined in this section, as to matters within the jurisdiction of the Administrator. <E T="03">Director</E> means the Director of the Office of Airport Safety and Standards.<PRTPAGE P="85"/> <E T="03">Director's determination</E> means the initial determination made by the Director following an investigation, which is a non-final agency decision. <E T="03">File</E> means to submit written documents to the FAA for inclusion in the Part 16 Airport Proceedings Docket or to a hearing officer. <E T="03">Final decision and order</E> means a final agency decision that disposes of a complaint or determines a respondent's compliance with any Act, as defined in this section, and directs appropriate action. <E T="03">Hearing officer</E> means an attorney designated by the FAA in a hearing order to serve as a hearing officer in a hearing under this part. The following are not designated as hearing officers: the Chief Counsel and Deputy Chief Counsel; the Assistant Chief Counsel and attorneys in the FAA region or center in which the noncompliance has allegedly occurred or is occurring; the Assistant Chief Counsel and attorneys in the Airports and Environmental Law Division of the FAA Office of the Chief Counsel; and the Assistant Chief Counsel and attorneys in the Litigation Division of the FAA Office of Chief Counsel. <E T="03">Initial decision</E> means a decision made by the hearing officer in a hearing under subpart F of this part. <E T="03">Mail</E> means U.S. first class mail; U.S. certified mail; and U.S. express mail. <E T="03">Noncompliance</E> means anything done or omitted to be done by any person in contravention of any provision of any Act, as defined in this section, as to matters within the jurisdiction of the Administrator. <E T="03">Party</E> means the complainant(s) and the respondent(s) named in the complaint and, after an initial determination providing an opportunity for hearing is issued under § 16.31 and subpart E of this part, the agency. <E T="03">Person</E> in addition to its meaning under 49 U.S.C. 40102(a)(33), includes a public agency as defined in 49 U.S.C. 47102(a)(15). <E T="03">Personal delivery</E> means hand delivery or overnight express delivery service. <E T="03">Respondent</E> means any person named in a complaint as a person responsible for noncompliance. <E T="03">Sponsor</E> means: (1) Any public agency which, either individually or jointly with one or more other public agencies, has received Federal financial assistance for airport development or planning under the Federal Airport Act, Airport and Airway Development Act or Airport and Airway Improvement Act; (2) Any private owner of a public-use airport that has received financial assistance from the FAA for such airport; and (3) Any person to whom the Federal Government has conveyed property for airport purposes under section 13(g) of the Surplus Property Act of 1944, as amended. </SECTION> <SECTION> <SECTNO>§ 16.5</SECTNO> <SUBJECT>Separation of functions.</SUBJECT> (a) Proceedings under this part, including hearings under subpart F of this part, will be prosecuted by an agency attorney. (b) After issuance of an initial determination in which the FAA provides the opportunity for a hearing, an agency employee engaged in the performance of investigative or prosecutorial functions in a proceeding under this part will not, in that case or a factually related case, participate or give advice in an initial decision by the hearing officer, or a final decision by the Associate Administrator or designee on written appeal, and will not, except as counsel or as witness in the public proceedings, engage in any substantive communication regarding that case or a related case with the hearing officer, the Associate Administrator on written appeal, or agency employees advising those officials in that capacity. (c) The Chief Counsel, the Assistant Chief Counsel for Litigation, or an attorney on the staff of the Assistant Chief Counsel for Litigation advises the Associate Administrator regarding an initial decision, an appeal, or a final decision regarding any case brought under this part. </SECTION> </SUBPART> <SUBPART> <PRTPAGE P="86"/> <HD SOURCE="HED">Subpart B—General Rules Applicable to Complaints, Proceedings Initiated by the FAA, and Appeals</HD> <SECTION> <SECTNO>§ 16.11</SECTNO> <SUBJECT>Expedition and other modification of process.</SUBJECT> (a) Under the authority of 49 U.S.C. 40113 and 47121, the Director may conduct investigations, issue orders, and take such other actions as are necessary to fulfill the purposes of this part, including the extension of any time period prescribed where necessary or appropriate for a fair and complete hearing of matters before the agency. (b) Notwithstanding any other provision of this part, upon finding that circumstances require expedited handling of a particular case or controversy, the Director may issue an order directing any of the following prior to the issuance of the Director's determination: (1) Shortening the time period for any action under this part consistent with due process; (2) If other adequate opportunity to respond to pleadings is available, eliminating the reply, rebuttal, or other actions prescribed by this part; (3) Designating alternative methods of service; or (4) Directing such other measures as may be required. </SECTION> <SECTION> <SECTNO>§ 16.13</SECTNO> <SUBJECT>Filing of documents.</SUBJECT> Except as otherwise provided in this part, documents shall be filed with the FAA during a proceeding under this part as follows: (a) <E T="03">Filing address.</E> Documents to be filed with the FAA shall be filed with the Office of the Chief Counsel, Attention: FAA Part 16 Airport Proceedings Docket, AGC-610, Federal Aviation Administration, 800 Independence Ave., SW., Washington, DC, 20591. Documents to be filed with a hearing officer shall be filed at the address stated in the hearing order. (b) <E T="03">Date and method of filing.</E> Filing of any document shall be by personal delivery or mail as defined in this part, or by facsimile (when confirmed by filing on the same date by one of the foregoing methods). Unless the date is shown to be inaccurate, documents to be filed with the FAA shall be deemed to be filed on the date of personal delivery, on the mailing date shown on the certificate of service, on the date shown on the postmark if there is no certificate of service, on the send date shown on the facsimile (provided filing has been confirmed through one of the foregoing methods), or on the mailing date shown by other evidence if there is no certificate of service and no postmark. (c) <E T="03">Number of copies.</E> Unless otherwise specified, an executed original and three copies of each document shall be filed with the FAA Part 16 Airport Proceedings Docket. Copies need not be signed, but the name of the person signing the original shall be shown. If a hearing order has been issued in the case, one of the three copies shall be filed with the hearing officer. If filing by facsimile, the facsimile copy does not constitute one of the copies required under this section. (d) <E T="03">Form.</E> Documents filed with the FAA shall be typewritten or legibly printed. In the case of docketed proceedings, the document shall include the docket number of the proceeding on the front page. (e) <E T="03">Signing of documents and other papers.</E> The original of every document filed shall be signed by the person filing it or the person's duly authorized representative. The signature shall serve as a certification that the signer has read the document and, based on reasonable inquiry and to the best of the signer's knowledge, information, and belief, the document is— (1) Consistent with this part; (2) Warranted by existing law or that a good faith argument exists for extension, modification, or reversal of existing law; and (3) Not interposed for any improper purpose, such as to harass or to cause unnecessary delay or needless increase in the cost of the administrative process. (f) <E T="03">Designation of person to receive service.</E> The initial document filed by any person shall state on the first page the name, post office address, telephone number, and facsimile number, if any, of the person(s) to be served with documents in the proceeding. If any of these items change during the proceeding, the person shall promptly file notice of <PRTPAGE P="87"/>the change with the FAA Part 16 Airport Proceedings Docket and the hearing officer and shall serve the notice on all parties. (g) <E T="03">Docket numbers.</E> Each submission identified as a complaint under this part by the submitting person will be assigned a docket number. </SECTION> <SECTION> <SECTNO>§ 16.15</SECTNO> <SUBJECT>Service of documents on the parties and the agency.</SUBJECT> Except as otherwise provided in this part, documents shall be served as follows: (a) <E T="03">Who must be served.</E> Copies of all documents filed with the FAA Part 16 Airport Proceedings Docket shall be served by the persons filing them on all parties to the proceeding. A certificate of service shall accompany all documents when they are tendered for filing and shall certify concurrent service on the FAA and all parties. Certificates of service shall be in substantially the following form: <EXTRACT> I hereby certify that I have this day served the foregoing [name of document] on the following persons at the following addresses and facsimile numbers (if also served by facsimile) by [specify method of service]: <FP>[list persons, addresses, facsimile numbers]</FP> Dated this <E T="72">___</E> day of <E T="72">___</E>, 19<E T="72">__</E>. <FP>[signature], for [party]</FP> </EXTRACT> (b) <E T="03">Method of service.</E> Except as otherwise agreed by the parties and the hearing officer, the method of service is the same as set forth in § 16.13(b) for filing documents. (c) <E T="03">Where service shall be made.</E> Service shall be made to the persons identified in accordance with § 16.13(f). If no such person has been designated, service shall be made on the party. (d) <E T="03">Presumption of service.</E> There shall be a presumption of lawful service— (1) When acknowledgment of receipt is by a person who customarily or in the ordinary course of business receives mail at the address of the party or of the person designated under § 16.13(f); or (2) When a properly addressed envelope, sent to the most current address submitted under § 16.13(f), has been returned as undeliverable, unclaimed, or refused. (e) <E T="03">Date of service.</E> The date of service shall be determined in the same manner as the filing date under § 16.13(b). </SECTION> <SECTION> <SECTNO>§ 16.17</SECTNO> <SUBJECT>Computation of time.</SUBJECT> This section applies to any period of time prescribed or allowed by this part, by notice or order of the hearing officer, or by an applicable statute. (a) The date of an act, event, or default, after which a designated time period begins to run, is not included in a computation of time under this part. (b) The last day of a time period is included in a computation of time unless it is a Saturday, Sunday, or legal holiday for the FAA, in which case, the time period runs until the end of the next day that is not a Saturday, Sunday, or legal holiday. (c) Whenever a party has the right or is required to do some act within a prescribed period after service of a document upon the party, and the document is served on the party by mail, 3 days shall be added to the prescribed period. </SECTION> <SECTION> <SECTNO>§ 16.19</SECTNO> <SUBJECT>Motions.</SUBJECT> (a) <E T="03">General.</E> An application for an order or ruling not otherwise specifically provided for in this part shall be by motion. Unless otherwise ordered by the agency, the filing of a motion will not stay the date that any action is permitted or required by this part. (b) <E T="03">Form and contents.</E> Unless made during a hearing, motions shall be made in writing, shall state with particularity the relief sought and the grounds for the relief sought, and shall be accompanied by affidavits or other evidence relied upon. Motions introduced during hearings may be made orally on the record, unless the hearing officer directs otherwise. (c) <E T="03">Answers to motions.</E> Except as otherwise provided in this part, or except when a motion is made during a hearing, any party may file an answer in support of or in opposition to a motion, accompanied by affidavits or other evidence relied upon, provided that the answer to the motion is filed within 10 days after the motion has been served upon the person answering, or any other period set by the hearing officer. Where a motion is made during a hearing, the answer and the ruling thereon may be made at the hearing, or orally or in writing within the time set by the hearing officer. </SECTION> </SUBPART> <SUBPART> <PRTPAGE P="88"/> <HD SOURCE="HED">Subpart C—Special Rules Applicable to Complaints</HD> <SECTION> <SECTNO>§ 16.21</SECTNO> <SUBJECT>Pre-complaint resolution.</SUBJECT> (a) Prior to filing a complaint under this part, a person directly and substantially affected by the alleged noncompliance shall initiate and engage in good faith efforts to resolve the disputed matter informally with those individuals or entities believed responsible for the noncompliance. These efforts at informal resolution may include, without limitation, at the parties’ expense, mediation, arbitration, or the use of a dispute resolution board, or other form of third party assistance. The FAA Airports District Office, FAA Airports Field Office, or FAA Regional Airports Division responsible for administrating financial assistance to the respondent airport proprietor, will be available upon request to assist the parties with informal resolution. (b) A complaint under this part will not be considered unless the person or authorized representative filing the complaint certifies that substantial and reasonable good faith efforts to resolve the disputed matter informally prior to filing the complaint have been made and that there appears no reasonable prospect for timely resolution of the dispute. This certification shall include a brief description of the party's efforts to obtain informal resolution but shall not include information on monetary or other settlement offers made but not agreed upon in writing by all parties. </SECTION> <SECTION> <SECTNO>§ 16.23</SECTNO> <SUBJECT>Complaints, answers, replies, rebuttals, and other documents.</SUBJECT> (a) A person directly and substantially affected by any alleged noncompliance may file a complaint with the Administrator. A person doing business with an airport and paying fees or rentals to the airport shall be considered directly and substantially affected by alleged revenue diversion as defined in 49 U.S.C. 47107(b). (b) Complaints filed under this part shall— (1) State the name and address of each person who is the subject of the complaint and, with respect to each person, the specific provisions of each Act that the complainant believes were violated; (2) Be served, in accordance with § 16.15, along with all documents then available in the exercise of reasonable diligence, offered in support of the complaint, upon all persons named in the complaint as persons responsible for the alleged action(s) or omission(s) upon which the complaint is based; (3) Provide a concise but complete statement of the facts relied upon to substantiate each allegation; and (4) Describe how the complainant was directly and substantially affected by the things done or omitted to be done by the respondents. (c) Unless the complaint is dismissed pursuant to § 16.25 or § 16.27, the FAA notifies the complainant and respondents in writing within 20 days after the date the FAA receives the complaint that the complaint has been docketed and that respondents are required to file an answer within 20 days of the date of service of the notification. (d) The respondent shall file an answer within 20 days of the date of service of the FAA notification. (e) The complainant may file a reply within 10 days of the date of service of the answer. (f) The respondent may file a rebuttal within 10 days of the date of service of the complainant's reply. (g) The answer, reply, and rebuttal shall, like the complaint, be accompanied by supporting documentation upon which the parties rely. (h) The answer shall deny or admit the allegations made in the complaint or state that the person filing the document is without sufficient knowledge or information to admit or deny an allegation, and shall assert any affirmative defense. (i) The answer, reply, and rebuttal shall each contain a concise but complete statement of the facts relied upon to substantiate the answers, admissions, denials, or averments made. (j) The respondent's answer may include a motion to dismiss the complaint, or any portion thereof, with a supporting memorandum of points and authorities. If a motion to dismiss is filed, the complainant may respond as part of its reply notwithstanding the <PRTPAGE P="89"/>10-day time limit for answers to motions in § 16.19(c). </SECTION> <SECTION> <SECTNO>§ 16.25</SECTNO> <SUBJECT>Dismissals.</SUBJECT> Within 20 days after the receipt of the complaint, the Director will dismiss a complaint, or any claim made in a complaint, with prejudice if: (a) It appears on its face to be outside the jurisdiction of the Administrator under the Acts listed in § 16.1; (b) On its face it does not state a claim that warrants an investigation or further action by the FAA; or (c) The complainant lacks standing to file a complaint under §§ 16.3 and 16.23. The Director's dismissal will include the reasons for the dismissal. </SECTION> <SECTION> <SECTNO>§ 16.27</SECTNO> <SUBJECT>Incomplete complaints.</SUBJECT> If a complaint is not dismissed pursuant to § 16.25 of this part, but is deficient as to one or more of the requirements set forth in § 16.21 or § 16.23(b), the Director will dismiss the complaint within 20 days after receiving it. Dismissal will be without prejudice to the refiling of the complaint after amendment to correct the deficiency. The Director's dismissal will include the reasons for the dismissal. </SECTION> <SECTION> <SECTNO>§ 16.29</SECTNO> <SUBJECT>Investigations.</SUBJECT> (a) If, based on the pleadings, there appears to be a reasonable basis for further investigation, the FAA investigates the subject matter of the complaint. (b) The investigation may include one or more of the following, at the sole discretion of the FAA: (1) A review of the written submissions or pleadings of the parties, as supplemented by any informal investigation the FAA considers necessary and by additional information furnished by the parties at FAA request. In rendering its initial determination, the FAA may rely entirely on the complaint and the responsive pleadings provided under this subpart. Each party shall file documents that it considers sufficient to present all relevant facts and argument necessary for the FAA to determine whether the sponsor is in compliance. (2) Obtaining additional oral and documentary evidence by use of the agency's authority to compel production of such evidence under section 313 Aviation Act, 49 U.S.C. 40113 and 46104, and section 519 of the Airport and Airway Improvement Act, 49 U.S.C. 47122. The Administrator's statutory authority to issue compulsory process has been delegated to the Chief Counsel, the Deputy Chief Counsel, the Assistant Chief Counsel for Airports and Environmental Law, and each Assistant Chief Counsel for a region or center. (3) Conducting or requiring that a sponsor conduct an audit of airport financial records and transactions as provided in 49 U.S.C. 47107 and 47121. </SECTION> <SECTION> <SECTNO>§ 16.31</SECTNO> <SUBJECT>Director's determinations after investigations.</SUBJECT> (a) After consideration of the pleadings and other information obtained by the FAA after investigation, the Director will render an initial determination and provide it to each party by certified mail within 120 days of the date the last pleading specified in § 16.23 was due. (b) The Director's determination will set forth a concise explanation of the factual and legal basis for the Director's determination on each claim made by the complainant. (c) A party adversely affected by the Director's determination may appeal the initial determination to the Associate Administrator as provided in § 16.33. (d) If the Director's determination finds the respondent in noncompliance and proposes the issuance of a compliance order, the initial determination will include notice of opportunity for a hearing under subpart F of this part, if such an opportunity is provided by the FAA. The respondent may elect or waive a hearing as provided in subpart E of this part. </SECTION> <SECTION> <SECTNO>§ 16.33</SECTNO> <SUBJECT>Final decisions without hearing.</SUBJECT> (a) The Associate Administrator will issue a final decision on appeal from the Director's determination, without a hearing, where— (1) The complaint is dismissed after investigation; (2) A hearing is not required by statute and is not otherwise made available by the FAA; or<PRTPAGE P="90"/> (3) The FAA provides opportunity for a hearing to the respondent and the respondent waives the opportunity for a hearing as provided in subpart E of this part. (b) In the cases described in paragraph (a) of this section, a party adversely affected by the Director's determination may file an appeal with the Associate Administrator within 30 days after the date of service of the initial determination. (c) A reply to an appeal may be filed with the Associate Administrator within 20 days after the date of service of the appeal. (d) The Associate Administrator will issue a final decision and order within 60 days after the due date of the reply. (e) If no appeal is filed within the time period specified in paragraph (b) of this section, the Director's determination becomes the final decision and order of the FAA without further action. A Director's determination that becomes final because there is no administrative appeal is not judicially reviewable. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Special Rules Applicable to Proceedings Initiated by the FAA</HD> <SECTION> <SECTNO>§ 16.101</SECTNO> <SUBJECT>Basis for the initiation of agency action.</SUBJECT> The FAA may initiate its own investigation of any matter within the applicability of this part without having received a complaint. The investigation may include, without limitation, any of the actions described in § 16.29(b). </SECTION> <SECTION> <SECTNO>§ 16.103</SECTNO> <SUBJECT>Notice of investigation.</SUBJECT> Following the initiation of an investigation under § 16.101, the FAA sends a notice to the person(s) subject to investigation. The notice will set forth the areas of the agency's concern and the reasons therefor; request a response to the notice within 30 days of the date of service; and inform the respondent that the FAA will, in its discretion, invite good faith efforts to resolve the matter. </SECTION> <SECTION> <SECTNO>§ 16.105</SECTNO> <SUBJECT>Failure to resolve informally.</SUBJECT> If the matters addressed in the FAA notices are not resolved informally, the FAA may issue a Director's determination under § 16.31. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Proposed Orders of Compliance</HD> <SECTION> <SECTNO>§ 16.109</SECTNO> <SUBJECT>Orders terminating eligibility for grants, cease and desist orders, and other compliance orders.</SUBJECT> This section applies to initial determinations issued under § 16.31 that provide the opportunity for a hearing. (a) The agency will provide the opportunity for a hearing if, in the Director's determination, the agency proposes to issue an order terminating eligibility for grants pursuant to 49 U.S.C. 47106(e) and 47111(d), an order suspending the payment of grant funds, an order withholding approval of any new application to impose a passenger facility charge pursuant to section 112 of the Federal Aviation Administration Act of 1994, 49 U.S.C. 47111(e), a cease and desist order, an order directing the refund of fees unlawfully collected, or any other compliance order issued by the Administrator to carry out the provisions of the Acts, and required to be issued after notice and opportunity for a hearing. In cases in which a hearing is not required by statute, the FAA may provide opportunity for a hearing at its discretion. (b) In a case in which the agency provides the opportunity for a hearing, the Director's determination issued under § 16.31 will include a statement of the availability of a hearing under subpart F of this part. (c) Within 20 days after service of a Director's determination under § 16.31 and paragraph (b) of this section, a person subject to the proposed compliance order may— (1) Request a hearing under subpart F of this part; (2) Waive hearing and appeal the Director's determination in writing to the Associate Administrator, as provided in § 16.33; (3) File, jointly with a complainant, a motion to withdraw the complaint and to dismiss the proposed compliance action; or (4) Submit, jointly with the agency attorney, a proposed consent order under § 16.243(e).<PRTPAGE P="91"/> (d) If the respondent fails to request a hearing or to file an appeal in writing within the time periods provided in paragraph (c) of this section, the Director's determination becomes final. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Hearings</HD> <SECTION> <SECTNO>§ 16.201</SECTNO> <SUBJECT>Notice and order of hearing.</SUBJECT> (a) If a respondent is provided the opportunity for hearing in an initial determination and does not waive hearing, the Deputy Chief Counsel within 10 days after the respondent elects a hearing will issue and serve on the respondent and complainant a hearing order. The hearing order will set forth: (1) The allegations in the complaint, or notice of investigation, and the chronology and results of the investigation preliminary to the hearing; (2) The relevant statutory, judicial, regulatory, and other authorities; (3) The issues to be decided; (4) Such rules of procedure as may be necessary to supplement the provisions of this part; (5) The name and address of the person designated as hearing officer, and the assignment of authority to the hearing officer to conduct the hearing in accordance with the procedures set forth in this part; and (6) The date by which the hearing officer is directed to issue an initial decision. (b) Where there are no genuine issues of material fact requiring oral examination of witnesses, the hearing order may contain a direction to the hearing officer to conduct a hearing by submission of briefs and oral argument without the presentation of testimony or other evidence. </SECTION> <SECTION> <SECTNO>§ 16.202</SECTNO> <SUBJECT>Powers of a hearing officer.</SUBJECT> In accordance with the rules of this subpart, a hearing officer may: (a) Give notice of, and hold, prehearing conferences and hearings; (b) Administer oaths and affirmations; (c) Issue subpoenas authorized by law and issue notices of deposition requested by the parties; (d) Limit the frequency and extent of discovery; (e) Rule on offers of proof; (f) Receive relevant and material evidence; (g) Regulate the course of the hearing in accordance with the rules of this part to avoid unnecessary and duplicative proceedings in the interest of prompt and fair resolution of the matters at issue; (h) Hold conferences to settle or to simplify the issues by consent of the parties; (i) Dispose of procedural motions and requests; (j) Examine witnesses; and (k) Make findings of fact and conclusions of law, and issue an initial decision. </SECTION> <SECTION> <SECTNO>§ 16.203</SECTNO> <SUBJECT>Appearances, parties, and rights of parties.</SUBJECT> (a) <E T="03">Appearances.</E> Any party may appear and be heard in person. (1) Any party may be accompanied, represented, or advised by an attorney licensed by a State, the District of Columbia, or a territory of the United States to practice law or appear before the courts of that State or territory, or by another duly authorized representative. (2) An attorney, or other duly authorized representative, who represents a party shall file a notice of appearance in accordance with § 16.13. (b) <E T="03">Parties and agency participation.</E> (1) The parties to the hearing are the respondent (s) named in the hearing order, the complainant(s), and the agency. (2) Unless otherwise specified in the hearing order, the agency attorney will serve as prosecutor for the agency from the date of issuance of the Director's determination providing an opportunity for hearing. </SECTION> <SECTION> <SECTNO>§ 16.207</SECTNO> <SUBJECT>Intervention and other participation.</SUBJECT> (a) A person may submit a motion for leave to intervene as a party. Except for good cause shown, a motion for leave to intervene shall be submitted not later than 10 days after the notice of hearing and hearing order. (b) If the hearing officer finds that intervention will not unduly broaden the issues or delay the proceedings and, if the person has a property or financial interest that may not be addressed <PRTPAGE P="92"/>adequately by the parties, the hearing officer may grant a motion for leave to intervene. The hearing officer may determine the extent to which an intervenor may participate in the proceedings. (c) Other persons may petition the hearing officer for leave to participate in the hearing. Participation is limited to the filing of post-hearing briefs and reply to the hearing officer and the Associate Administrator. Such briefs shall be filed and served on all parties in the same manner as the parties’ post hearing briefs are filed. (d) Participation under this section is at the discretion of the FAA, and no decision permitting participation shall be deemed to constitute an expression by the FAA that the participant has such a substantial interest in the proceeding as would entitle it to judicial review of such decision. </SECTION> <SECTION> <SECTNO>§ 16.209</SECTNO> <SUBJECT>Extension of time.</SUBJECT> (a) <E T="03">Extension by oral agreement.</E> The parties may agree to extend for a reasonable period of time for filing a document under this part. If the parties agree, the hearing officer shall grant one extension of time to each party. The party seeking the extension of time shall submit a draft order to the hearing officer to be signed by the hearing officer and filed with the hearing docket. The hearing officer may grant additional oral requests for an extension of time where the parties agree to the extension. (b) <E T="03">Extension by motion.</E> A party shall file a written motion for an extension of time with the hearing officer not later than 7 days before the document is due unless good cause for the late filing is shown. A party filing a written motion for an extension of time shall serve a copy of the motion on each party. (c) <E T="03">Failure to rule.</E> If the hearing officer fails to rule on a written motion for an extension of time by the date the document was due, the motion for an extension of time is deemed denied. (d) <E T="03">Effect on time limits.</E> In a hearing required by section 519(b) of the Airport and Airways Improvement Act, as amended in 1987, 49 U.S.C. 47106(e) and 47111(d), the due date for the hearing officer's initial decision and for the final agency decision are extended by the length of the extension granted by the hearing officer only if the hearing officer grants an extension of time as a result of an agreement by the parties as specified in paragraph (a) of this section or, if the hearing officer grants an extension of time as a result of the sponsor's failure to adhere to the hearing schedule. In any other hearing, an extension of time granted by the hearing officer for any reason extends the due date for the hearing officer's initial decision and for the final agency decision by the length of time of the hearing officer's decision. </SECTION> <SECTION> <SECTNO>§ 16.211</SECTNO> <SUBJECT>Prehearing conference.</SUBJECT> (a) <E T="03">Prehearing conference notice.</E> The hearing officer schedules a prehearing conference and serves a prehearing conference notice on the parties promptly after being designated as a hearing officer. (1) The prehearing conference notice specifies the date, time, place, and manner (in person or by telephone) of the prehearing conference. (2) The prehearing conference notice may direct the parties to exchange proposed witness lists, requests for evidence and the production of documents in the possession of another party, responses to interrogatories, admissions, proposed procedural schedules, and proposed stipulations before the date of the prehearing conference. (b) <E T="03">The prehearing conference.</E> The prehearing conference is conducted by telephone or in person, at the hearing officer's discretion. The prehearing conference addresses matters raised in the prehearing conference notice and such other matters as the hearing officer determines will assist in a prompt, full and fair hearing of the issues. (c) <E T="03">Prehearing conference report.</E> At the close of the prehearing conference, the hearing officer rules on any requests for evidence and the production of documents in the possession of other parties, responses to interrogatories, and admissions; on any requests for depositions; on any proposed stipulations; and on any pending applications for subpoenas as permitted by § 16.219. In addition, the hearing officer establishes the schedule, which shall provide for the issuance of an initial decision <PRTPAGE P="93"/>not later than 110 days after issuance of the Director's determination order unless otherwise provided in the hearing order. </SECTION> <SECTION> <SECTNO>§ 16.213</SECTNO> <SUBJECT>Discovery.</SUBJECT> (a) Discovery is limited to requests for admissions, requests for production of documents, interrogatories, and depositions as authorized by § 16.215. (b) The hearing officer shall limit the frequency and extent of discovery permitted by this section if a party shows that— (1) The information requested is cumulative or repetitious; (2) The information requested may be obtained from another less burdensome and more convenient source; (3) The party requesting the information has had ample opportunity to obtain the information through other discovery methods permitted under this section; or (4) The method or scope of discovery requested by the party is unduly burdensome or expensive. </SECTION> <SECTION> <SECTNO>§ 16.215</SECTNO> <SUBJECT>Depositions.</SUBJECT> (a) <E T="03">General.</E> For good cause shown, the hearing officer may order that the testimony of a witness may be taken by deposition and that the witness produce documentary evidence in connection with such testimony. Generally, an order to take the deposition of a witness is entered only if: (1) The person whose deposition is to be taken would be unavailable at the hearing; (2) The deposition is deemed necessary to perpetuate the testimony of the witness; or (3) The taking of the deposition is necessary to prevent undue and excessive expense to a party and will not result in undue burden to other parties or in undue delay. (b) <E T="03">Application for deposition</E>. Any party desiring to take the deposition of a witness shall make application therefor to the hearing officer in writing, with a copy of the application served on each party. The application shall include: (1) The name and residence of the witness; (2) The time and place for the taking of the proposed deposition; (3) The reasons why such deposition should be taken; and (4) A general description of the matters concerning which the witness will be asked to testify. (c) <E T="03">Order authorizing deposition</E>. If good cause is shown, the hearing officer, in his or her discretion, issues an order authorizing the deposition and specifying the name of the witness to be deposed, the location and time of the deposition and the general scope and subject matter of the testimony to be taken. (d) <E T="03">Procedures for deposition.</E> (1) Witnesses whose testimony is taken by deposition shall be sworn or shall affirm before any questions are put to them. Each question propounded shall be recorded and the answers of the witness transcribed verbatim. (2) Objections to questions or evidence shall be recorded in the transcript of the deposition. The interposing of an objection shall not relieve the witness of the obligation to answer questions, except where the answer would violate a privilege. (3) The written transcript shall be subscribed by the witness, unless the parties by stipulation waive the signing, or the witness is ill, cannot be found, or refuses to sign. The reporter shall note the reason for failure to sign. </SECTION> <SECTION> <SECTNO>§ 16.217</SECTNO> <SUBJECT>Witnesses.</SUBJECT> (a) Each party may designate as a witness any person who is able and willing to give testimony that is relevant and material to the issues in the hearing case, subject to the limitation set forth in paragraph (b) of this section. (b) The hearing officer may exclude testimony of witnesses that would be irrelevant, immaterial, or unduly repetitious. (c) Any witness may be accompanied by counsel. Counsel representing a nonparty witness has no right to examine the witness or otherwise participate in the development of testimony. </SECTION> <SECTION> <SECTNO>§ 16.219</SECTNO> <SUBJECT>Subpoenas.</SUBJECT> (a) <E T="03">Request for subpoena</E>. A party may apply to the hearing officer, within the time specified for such applications in the prehearing conference report, for a <PRTPAGE P="94"/>subpoena to compel testimony at a hearing or to require the production of documents only from the following persons: (1) Another party; (2) An officer, employee, or agent of another party; (3) Any other person named in the complaint as participating in or benefiting from the actions of the respondent alleged to have violated any Act; (4) An officer, employee, or agent of any other person named in the complaint as participating in or benefiting from the actions of the respondent alleged to have violated any Act. (b) <E T="03">Issuance and service of subpoena.</E> (1) The hearing officer issues the subpoena if the hearing officer determines that the evidence to be obtained by the subpoena is relevant and material to the resolution of the issues in the case. (2) Subpoenas shall be served by personal service, or upon an agent designated in writing for the purpose, or by certified mail, return receipt addressed to such person or agent. Whenever service is made by registered or certified mail, the date of mailing shall be considered as the time when service is made. (3) A subpoena issued under this part is effective throughout the United States or any territory or possession thereof. (c) <E T="03">Motions to quash or modify subpoena.</E> (1) A party or any person upon whom a subpoena has been served may file a motion to quash or modify the subpoena with the hearing officer at or before the time specified in the subpoena for the filing of such motions. The applicant shall describe in detail the basis for the application to quash or modify the subpoena including, but not limited to, a statement that the testimony, document, or tangible evidence is not relevant to the proceeding, that the subpoena is not reasonably tailored to the scope of the proceeding, or that the subpoena is unreasonable and oppressive. (2) A motion to quash or modify the subpoena stays the effect of the subpoena pending a decision by the hearing officer on the motion. </SECTION> <SECTION> <SECTNO>§ 16.221</SECTNO> <SUBJECT>Witness fees.</SUBJECT> (a) The party on whose behalf a witness appears is responsible for paying any witness fees and mileage expenses. (b) Except for employees of the United States summoned to testify as to matters related to their public employment, witnesses summoned by subpoena shall be paid the same fees and mileage expenses as are paid to a witness in a court of the United States in comparable circumstances. </SECTION> <SECTION> <SECTNO>§ 16.223</SECTNO> <SUBJECT>Evidence.</SUBJECT> (a) <E T="03">General.</E> A party may submit direct and rebuttal evidence in accordance with this section. (b) <E T="03">Requirement for written testimony and evidence.</E> Except in the case of evidence obtained by subpoena, or in the case of a special ruling by the hearing officer to admit oral testimony, a party's direct and rebuttal evidence shall be submitted in written form in advance of the oral hearing pursuant to the schedule established in the hearing officer's prehearing conference report. Written direct and rebuttal fact testimony shall be certified by the witness as true and correct. Subject to the same exception (for evidence obtained by subpoena or subject to a special ruling by the hearing officer), oral examination of a party's own witness is limited to certification of the accuracy of written evidence, including correction and updating, if necessary, and reexamination following cross-examination by other parties. (c) <E T="03">Subpoenaed testimony.</E> Testimony of witnesses appearing under subpoena may be obtained orally. (d) <E T="03">Cross-examination.</E> A party may conduct cross-examination that may be required for disclosure of the facts, subject to control by the hearing officer for fairness, expedition and exclusion of extraneous matters. (e) <E T="03">Hearsay evidence.</E> Hearsay evidence is admissible in proceedings governed by this part. The fact that evidence is hearsay goes to the weight of evidence and does not affect its admissibility. (f) <E T="03">Admission of evidence.</E> The hearing officer admits evidence introduced by a <PRTPAGE P="95"/>party in support of its case in accordance with this section, but may exclude irrelevant, immaterial, or unduly repetitious evidence. (g) <E T="03">Expert or opinion witnesses.</E> An employee of the FAA or DOT may not be called as an expert or opinion witness for any party other than the agency except as provided in Department of Transportation regulations at 49 CFR part 9. </SECTION> <SECTION> <SECTNO>§ 16.225</SECTNO> <SUBJECT>Public disclosure of evidence.</SUBJECT> (a) Except as provided in this section, the hearing shall be open to the public. (b) The hearing officer may order that any information contained in the record be withheld from public disclosure. Any person may object to disclosure of information in the record by filing a written motion to withhold specific information with the hearing officer. The person shall state specific grounds for nondisclosure in the motion. (c) The hearing officer shall grant the motion to withhold information from public disclosure if the hearing officer determines that disclosure would be in violation of the Privacy Act, would reveal trade secrets or privileged or confidential commercial or financial information, or is otherwise prohibited by law. </SECTION> <SECTION> <SECTNO>§ 16.227</SECTNO> <SUBJECT>Standard of proof.</SUBJECT> The hearing officer shall issue an initial decision or shall rule in a party's favor only if the decision or ruling is supported by, and in accordance with, reliable, probative, and substantial evidence contained in the record and is in accordance with law. </SECTION> <SECTION> <SECTNO>§ 16.229</SECTNO> <SUBJECT>Burden of proof.</SUBJECT> (a) The burden of proof of noncompliance with an Act or any regulation, order, agreement or document of conveyance issued under the authority of an Act is on the agency. (b) Except as otherwise provided by statute or rule, the proponent of a motion, request, or order has the burden of proof. (c) A party who has asserted an affirmative defense has the burden of proving the affirmative defense. </SECTION> <SECTION> <SECTNO>§ 16.231</SECTNO> <SUBJECT>Offer of proof.</SUBJECT> A party whose evidence has been excluded by a ruling of the hearing officer may offer the evidence on the record when filing an appeal. </SECTION> <SECTION> <SECTNO>§ 16.233</SECTNO> <SUBJECT>Record.</SUBJECT> (a) <E T="03">Exclusive record</E>. The transcript of all testimony in the hearing, all exhibits received into evidence, all motions, applications requests and rulings, and all documents included in the hearing record shall constitute the exclusive record for decision in the proceedings and the basis for the issuance of any orders. (b) <E T="03">Examination and copy of record</E>. Any interested person may examine the record at the Part 16 Airport Proceedings Docket, AGC-600, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591. Any person may have a copy of the record after payment of reasonable costs for search and reproduction of the record. </SECTION> <SECTION> <SECTNO>§ 16.235</SECTNO> <SUBJECT>Argument before the hearing officer.</SUBJECT> (a) <E T="03">Argument during the hearing</E>. During the hearing, the hearing officer shall give the parties reasonable opportunity to present oral argument on the record supporting or opposing motions, objections, and rulings if the parties request an opportunity for argument. The hearing officer may direct written argument during the hearing if the hearing officer finds that submission of written arguments would not delay the hearing. (b) <E T="03">Posthearing briefs.</E> The hearing officer may request or permit the parties to submit posthearing briefs. The hearing officer may provide for the filing of simultaneous reply briefs as well, if such filing will not unduly delay the issuance of the hearing officer's initial decision. Posthearing briefs shall include proposed findings of fact and conclusions of law; exceptions to rulings of the hearing officer; references to the record in support of the findings of fact; and supporting arguments for the proposed findings, proposed conclusions, and exceptions. </SECTION> <SECTION> <PRTPAGE P="96"/> <SECTNO>§ 16.237</SECTNO> <SUBJECT>Waiver of procedures.</SUBJECT> (a) The hearing officer shall waive such procedural steps as all parties to the hearing agree to waive before issuance of an initial decision. (b) Consent to a waiver of any procedural step bars the raising of this issue on appeal. (c) The parties may not by consent waive the obligation of the hearing officer to enter an initial decision on the record. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Initial Decisions, Orders and Appeals</HD> <SECTION> <SECTNO>§ 16.241</SECTNO> <SUBJECT>Initial decisions, order, and appeals.</SUBJECT> (a) The hearing officer shall issue an initial decision based on the record developed during the proceeding and shall send the initial decision to the parties not later than 110 days after the Director's determination unless otherwise provided in the hearing order. (b) Each party adversely affected by the hearing officer's initial decision may file an appeal with the Associate Administrator within 15 days of the date the initial decision is issued. Each party may file a reply to an appeal within 10 days after it is served on the party. Filing and service of appeals and replies shall be by personal delivery. (c) If an appeal is filed, the Associate Administrator reviews the entire record and issues a final agency decision and order within 30 days of the due date of the reply. If no appeal is filed, the Associate Administrator may take review of the case on his or her own motion. If the Associate Administrator finds that the respondent is not in compliance with any Act or any regulation, agreement, or document of conveyance issued or made under such Act, the final agency order includes a statement of corrective action, if appropriate, and identifies sanctions for continued noncompliance. (d) If no appeal is filed, and the Associate Administrator does not take review of the initial decision on the Associate Administrator's own motion, the initial decision shall take effect as the final agency decision and order on the sixteenth day after the actual date the initial decision is issued. (e) The failure to file an appeal is deemed a waiver of any rights to seek judicial review of an initial decision that becomes a final agency decision by operation of paragraph (d) of this section. (f) If the Associate Administrator takes review on the Associate Administrator's own motion, the Associate Administrator issues a notice of review by the sixteenth day after the actual date the initial decision is issued. (1) The notice sets forth the specific findings of fact and conclusions of law in the initial decision that are subject to review by the Associate Administrator. (2) Parties may file one brief on review to the Associate Administrator or rely on their posthearing briefs to the hearing officer. Briefs on review shall be filed not later than 10 days after service of the notice of review. Filing and service of briefs on review shall be by personal delivery. (3) The Associate Administrator issues a final agency decision and order within 30 days of the due date of the briefs on review. If the Associate Administrator finds that the respondent is not in compliance with any Act or any regulation, agreement or document of conveyance issued under such Act, the final agency order includes a statement of corrective action, if appropriate, and identifies sanctions for continued noncompliance. </SECTION> <SECTION> <SECTNO>§ 16.243</SECTNO> <SUBJECT>Consent orders.</SUBJECT> (a) The agency attorney and the respondents may agree at any time before the issuance of a final decision and order to dispose of the case by issuance of a consent order. Good faith efforts to resolve a complaint through issuance of a consent order may continue throughout the administrative process. Except as provided in § 16.209, such efforts may not serve as the basis for extensions of the times set forth in this part. (b) A proposal for a consent order, specified in paragraph (a) of this section, shall include: (1) A proposed consent order; (2) An admission of all jurisdictional facts;<PRTPAGE P="97"/> (3) An express waiver of the right to further procedural steps and of all rights of judicial review; and (4) The hearing order, if issued, and an acknowledgment that the hearing order may be used to construe the terms of the consent order. (c) If the issuance of a consent order has been agreed upon by all parties to the hearing, the proposed consent order shall be filed with the hearing officer, along with a draft order adopting the consent decree and dismissing the case, for the hearing officer's adoption. (d) The deadline for the hearing officer's initial decision and the final agency decision is extended by the amount of days elapsed between the filing of the proposed consent order with the hearing officer and the issuance of the hearing officer's order continuing the hearing. (e) If the agency attorney and sponsor agree to dispose of a case by issuance of a consent order before the FAA issues a hearing order, the proposal for a consent order is submitted jointly to the official authorized to issue a hearing order, together with a request to adopt the consent order and dismiss the case. The official authorized to issue the hearing order issues the consent order as an order of the FAA and terminates the proceeding. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Judicial Review</HD> <SECTION> <SECTNO>§ 16.247</SECTNO> <SUBJECT>Judicial review of a final decision and order.</SUBJECT> (a) A person may seek judicial review, in a United States Court of Appeals, of a final decision and order of the Associate Administrator as provided in 49 U.S.C. 46110 or section 519(b)(4) of the Airport and Airway Improvement Act of 1982, as amended, (AAIA), 49 U.S.C. 47106(d) and 47111(d). A party seeking judicial review of a final decision and order shall file a petition for review with the Court not later than 60 days after a final decision and order under the AAIA has been served on the party or within 60 days after the entry of an order under 49 U.S.C. 40101 <E T="03">et seq.</E> (b) The following do not constitute final decisions and orders subject to judicial review: (1) An FAA decision to dismiss a complaint without prejudice, as set forth in § 16.27; (2) A Director's determination; (3) An initial decision issued by a hearing officer at the conclusion of a hearing; (4) A Director's determination or an initial decision of a hearing officer that becomes the final decision of the Associate Administrator because it was not appealed within the applicable time periods provided under §§ 16.33(b) and 16.241(b). </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart I—Ex Parte Communications</HD> <SECTION> <SECTNO>§ 16.301</SECTNO> <SUBJECT>Definitions.</SUBJECT> As used in this subpart: <E T="03">Decisional employee</E> means the Administrator, Deputy Administrator, Associate Administrator, Director, hearing officer, or other FAA employee who is or who may reasonably be expected to be involved in the decisional process of the proceeding. <E T="03">Ex parte communication</E> means an oral or written communication not on the public record with respect to which reasonable prior notice to all parties is not given, but it shall not include requests for status reports on any matter or proceeding covered by this part, or communications between FAA employees who participate as parties to a hearing pursuant to 16.203(b) of this part and other parties to a hearing. </SECTION> <SECTION> <SECTNO>§ 16.303</SECTNO> <SUBJECT>Prohibited ex parte communications.</SUBJECT> (a) The prohibitions of this section shall apply from the time a proceeding is noticed for hearing unless the person responsible for the communication has knowledge that it will be noticed, in which case the prohibitions shall apply at the time of the acquisition of such knowledge. (b) Except to the extent required for the disposition of ex parte matters as authorized by law: (1) No interested person outside the FAA and no FAA employee participating as a party shall make or knowingly cause to be made to any decisional employee an ex parte communication relevant to the merits of the proceeding;<PRTPAGE P="98"/> (2) No FAA employee shall make or knowingly cause to be made to any interested person outside the FAA an ex parte communication relevant to the merits of the proceeding; or (3) Ex parte communications regarding solely matters of agency procedure or practice are not prohibited by this section. </SECTION> <SECTION> <SECTNO>§ 16.305</SECTNO> <SUBJECT>Procedures for handling ex parte communications.</SUBJECT> A decisional employee who receives or who makes or knowingly causes to be made a communication prohibited by § 16.303 shall place in the public record of the proceeding: (a) All such written communications; (b) Memoranda stating the substance of all such oral communications; and (c) All written responses, and memoranda stating the substance of all oral responses, to the materials described in paragraphs (a) and (b) of this section. </SECTION> <SECTION> <SECTNO>§ 16.307</SECTNO> <SUBJECT>Requirement to show cause and imposition of sanction.</SUBJECT> (a) Upon receipt of a communication knowingly made or knowingly caused to be made by a party in violation of § 16.303, the Associate Administrator or his designee or the hearing officer may, to the extent consistent with the interests of justice and the policy of the underlying statutes, require the party to show cause why his or her claim or interest in the proceeding should not be dismissed, denied, disregarded, or otherwise adversely affected on account of such violation. (b) The Associate Administrator may, to the extent consistent with the interests of justice and the policy of the underlying statutes administered by the FAA, consider a violation of this subpart sufficient grounds for a decision adverse to a party who has knowingly committed such violation or knowingly caused such violation to occur. </SECTION> </SUBPART> </PART> </SUBCHAP> <SUBCHAP TYPE="P"> <PRTPAGE P="99"/> <HD SOURCE="HED">SUBCHAPTER C—AIRCRAFT</HD> <PART> <EAR>Pt. 21</EAR> <HD SOURCE="HED">PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS</HD> <CONTENTS> <SUBJGRP> <HD SOURCE="HED">Special Federal Aviation Regulations</HD> </SUBJGRP> <FP SOURCE="FP-2"> <E T="04">SFAR No.</E> 26</FP> <FP SOURCE="FP-2"> <E T="04">SFAR No.</E> 29-4</FP> <FP SOURCE="FP-2"> <E T="04">SFAR No.</E> 41</FP> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECHD>Sec.</SECHD> <SECTNO>21.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.2</SECTNO> <SUBJECT>Falsification of applications, reports, or records.</SUBJECT> <SECTNO>21.3</SECTNO> <SUBJECT>Reporting of failures, malfunctions, and defects.</SUBJECT> <SECTNO>21.5</SECTNO> <SUBJECT>Airplane or Rotorcraft Flight Manual.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Type Certificates</HD> <SECTNO>21.11</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.13</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.15</SECTNO> <SUBJECT>Application for type certificate.</SUBJECT> <SECTNO>21.16</SECTNO> <SUBJECT>Special conditions.</SUBJECT> <SECTNO>21.17</SECTNO> <SUBJECT>Designation of applicable regulations.</SUBJECT> <SECTNO>21.19</SECTNO> <SUBJECT>Changes requiring a new type certificate.</SUBJECT> <SECTNO>21.21</SECTNO> <SUBJECT>Issue of type certificate: normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; special classes of aircraft; aircraft engines; propellers.</SUBJECT> <SECTNO>21.23</SECTNO> <SUBJECT>[Reserved]</SUBJECT> <SECTNO>21.24</SECTNO> <SUBJECT>Issuance of type certificate: primary category aircraft.</SUBJECT> <SECTNO>21.25</SECTNO> <SUBJECT>Issue of type certificate: Restricted category aircraft.</SUBJECT> <SECTNO>21.27</SECTNO> <SUBJECT>Issue of type certificate: surplus aircraft of the Armed Forces.</SUBJECT> <SECTNO>21.29</SECTNO> <SUBJECT>Issue of type certificate: import products.</SUBJECT> <SECTNO>21.31</SECTNO> <SUBJECT>Type design.</SUBJECT> <SECTNO>21.33</SECTNO> <SUBJECT>Inspection and tests.</SUBJECT> <SECTNO>21.35</SECTNO> <SUBJECT>Flight tests.</SUBJECT> <SECTNO>21.37</SECTNO> <SUBJECT>Flight test pilot.</SUBJECT> <SECTNO>21.39</SECTNO> <SUBJECT>Flight test instrument calibration and correction report.</SUBJECT> <SECTNO>21.41</SECTNO> <SUBJECT>Type certificate.</SUBJECT> <SECTNO>21.43</SECTNO> <SUBJECT>Location of manufacturing facilities.</SUBJECT> <SECTNO>21.45</SECTNO> <SUBJECT>Privileges.</SUBJECT> <SECTNO>21.47</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.49</SECTNO> <SUBJECT>Availability.</SUBJECT> <SECTNO>21.50</SECTNO> <SUBJECT>Instructions for continued airworthiness and manufacturer's maintenance manuals having airworthiness limitations sections.</SUBJECT> <SECTNO>21.51</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.53</SECTNO> <SUBJECT>Statement of conformity.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Provisional Type Certificates</HD> <SECTNO>21.71</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.73</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.75</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.77</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.79</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.81</SECTNO> <SUBJECT>Requirements for issue and amendment of Class I provisional type certificates.</SUBJECT> <SECTNO>21.83</SECTNO> <SUBJECT>Requirements for issue and amendment of Class II provisional type certificates.</SUBJECT> <SECTNO>21.85</SECTNO> <SUBJECT>Provisional amendments to type certificates.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Changes to Type Certificates</HD> <SECTNO>21.91</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.93</SECTNO> <SUBJECT>Classification of changes in type design.</SUBJECT> <SECTNO>21.95</SECTNO> <SUBJECT>Approval of minor changes in type design.</SUBJECT> <SECTNO>21.97</SECTNO> <SUBJECT>Approval of major changes in type design.</SUBJECT> <SECTNO>21.99</SECTNO> <SUBJECT>Required design changes.</SUBJECT> <SECTNO>21.101</SECTNO> <SUBJECT>Designation of applicable regulations.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Supplemental Type Certificates</HD> <SECTNO>21.111</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.113</SECTNO> <SUBJECT>Requirement of supplemental type certificate.</SUBJECT> <SECTNO>21.115</SECTNO> <SUBJECT>Applicable requirements.</SUBJECT> <SECTNO>21.117</SECTNO> <SUBJECT>Issue of supplemental type certificates.</SUBJECT> <SECTNO>21.119</SECTNO> <SUBJECT>Privileges.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Production Under Type Certificate Only</HD> <SECTNO>21.121</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.123</SECTNO> <SUBJECT>Production under type certificate.</SUBJECT> <SECTNO>21.125</SECTNO> <SUBJECT>Production inspection system: Materials Review Board.</SUBJECT> <SECTNO>21.127</SECTNO> <SUBJECT>Tests: aircraft.</SUBJECT> <SECTNO>21.128</SECTNO> <SUBJECT>Tests: aircraft engines.</SUBJECT> <SECTNO>21.129</SECTNO> <SUBJECT>Tests: propellers.</SUBJECT> <SECTNO>21.130</SECTNO> <SUBJECT>Statement of conformity.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Production Certificates</HD> <SECTNO>21.131</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.133</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.135</SECTNO> <SUBJECT>Requirements for issuance.</SUBJECT> <SECTNO>21.137</SECTNO> <SUBJECT>Location of manufacturing facilities.</SUBJECT> <SECTNO>21.139</SECTNO> <SUBJECT>Quality control.</SUBJECT> <SECTNO>21.143</SECTNO> <SUBJECT>Quality control data requirements; prime manufacturer.</SUBJECT> <SECTNO>21.147</SECTNO> <SUBJECT>Changes in quality control system.</SUBJECT> <SECTNO>21.149</SECTNO> <SUBJECT>Multiple products.</SUBJECT> <SECTNO>21.151</SECTNO> <SUBJECT>Production limitation record.</SUBJECT> <SECTNO>21.153</SECTNO> <SUBJECT>Amendment of the production certificates.<PRTPAGE P="100"/> </SUBJECT> <SECTNO>21.155</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.157</SECTNO> <SUBJECT>Inspections and tests.</SUBJECT> <SECTNO>21.159</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.161</SECTNO> <SUBJECT>Display.</SUBJECT> <SECTNO>21.163</SECTNO> <SUBJECT>Privileges.</SUBJECT> <SECTNO>21.165</SECTNO> <SUBJECT>Responsibility of holder.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Airworthiness Certificates</HD> <SECTNO>21.171</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.173</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.175</SECTNO> <SUBJECT>Airworthiness certificates: classification.</SUBJECT> <SECTNO>21.177</SECTNO> <SUBJECT>Amendment or modification.</SUBJECT> <SECTNO>21.179</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.181</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.182</SECTNO> <SUBJECT>Aircraft identification.</SUBJECT> <SECTNO>21.183</SECTNO> <SUBJECT>Issue of standard airworthiness certificates for normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; and special classes of aircraft.</SUBJECT> <SECTNO>21.184</SECTNO> <SUBJECT>Issue of special airworthiness certificates for primary category aircraft.</SUBJECT> <SECTNO>21.185</SECTNO> <SUBJECT>Issue of airworthiness certificates for restricted category aircraft.</SUBJECT> <SECTNO>21.187</SECTNO> <SUBJECT>Issue of multiple airworthiness certification.</SUBJECT> <SECTNO>21.189</SECTNO> <SUBJECT>Issue of airworthiness certificate for limited category aircraft.</SUBJECT> <SECTNO>21.191</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> <SECTNO>21.193</SECTNO> <SUBJECT>Experimental certificates: general.</SUBJECT> <SECTNO>21.195</SECTNO> <SUBJECT>Experimental certificates: Aircraft to be used for market surveys, sales demonstrations, and customer crew training.</SUBJECT> <SECTNO>21.197</SECTNO> <SUBJECT>Special flight permits.</SUBJECT> <SECTNO>21.199</SECTNO> <SUBJECT>Issue of special flight permits.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart I—Provisional Airworthiness Certificates</HD> <SECTNO>21.211</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.213</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.215</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.217</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.219</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.221</SECTNO> <SUBJECT>Class I provisional airworthiness certificates.</SUBJECT> <SECTNO>21.223</SECTNO> <SUBJECT>Class II provisional airworthiness certificates.</SUBJECT> <SECTNO>21.225</SECTNO> <SUBJECT>Provisional airworthiness certificates corresponding with provisional amendments to type certificates.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart J—Delegation Option Authorization Procedures</HD> <SECTNO>21.231</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.235</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.239</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.243</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.245</SECTNO> <SUBJECT>Maintenance of eligibility.</SUBJECT> <SECTNO>21.247</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.249</SECTNO> <SUBJECT>Inspections.</SUBJECT> <SECTNO>21.251</SECTNO> <SUBJECT>Limits of applicability.</SUBJECT> <SECTNO>21.253</SECTNO> <SUBJECT>Type certificates: application.</SUBJECT> <SECTNO>21.257</SECTNO> <SUBJECT>Type certificates: issue.</SUBJECT> <SECTNO>21.261</SECTNO> <SUBJECT>Equivalent safety provisions.</SUBJECT> <SECTNO>21.267</SECTNO> <SUBJECT>Production certificates.</SUBJECT> <SECTNO>21.269</SECTNO> <SUBJECT>Export airworthiness approvals.</SUBJECT> <SECTNO>21.271</SECTNO> <SUBJECT>Airworthiness approval tags.</SUBJECT> <SECTNO>21.273</SECTNO> <SUBJECT>Airworthiness certificates other than experimental.</SUBJECT> <SECTNO>21.275</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> <SECTNO>21.277</SECTNO> <SUBJECT>Data review and service experience.</SUBJECT> <SECTNO>21.289</SECTNO> <SUBJECT>Major repairs, rebuilding and alteration.</SUBJECT> <SECTNO>21.293</SECTNO> <SUBJECT>Current records.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart K—Approval of Materials, Parts, Processes, and Appliances</HD> <SECTNO>21.301</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.303</SECTNO> <SUBJECT>Replacement and modification parts.</SUBJECT> <SECTNO>21.305</SECTNO> <SUBJECT>Approval of materials, parts, processes, and appliances.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart L—Export Airworthiness Approvals</HD> <SECTNO>21.321</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.323</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.325</SECTNO> <SUBJECT>Export airworthiness approvals.</SUBJECT> <SECTNO>21.327</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.329</SECTNO> <SUBJECT>Issue of export certificates of airworthiness for Class I products.</SUBJECT> <SECTNO>21.331</SECTNO> <SUBJECT>Issue of airworthiness approval tags for Class II products.</SUBJECT> <SECTNO>21.333</SECTNO> <SUBJECT>Issue of export airworthiness approval tags for Class III products.</SUBJECT> <SECTNO>21.335</SECTNO> <SUBJECT>Responsibilities of exporters.</SUBJECT> <SECTNO>21.337</SECTNO> <SUBJECT>Performance of inspections and overhauls.</SUBJECT> <SECTNO>21.339</SECTNO> <SUBJECT>Special export airworthiness approval for aircraft.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart M—Designated Alteration Station Authorization Procedures</HD> <SECTNO>21.431</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.435</SECTNO> <SUBJECT>Application.</SUBJECT> <SECTNO>21.439</SECTNO> <SUBJECT>Eligibility.</SUBJECT> <SECTNO>21.441</SECTNO> <SUBJECT>Procedure manual.</SUBJECT> <SECTNO>21.443</SECTNO> <SUBJECT>Duration.</SUBJECT> <SECTNO>21.445</SECTNO> <SUBJECT>Maintenance of eligibility.</SUBJECT> <SECTNO>21.447</SECTNO> <SUBJECT>Transferability.</SUBJECT> <SECTNO>21.449</SECTNO> <SUBJECT>Inspections.</SUBJECT> <SECTNO>21.451</SECTNO> <SUBJECT>Limits of applicability.</SUBJECT> <SECTNO>21.461</SECTNO> <SUBJECT>Equivalent safety provisions.</SUBJECT> <SECTNO>21.463</SECTNO> <SUBJECT>Supplemental type certificates.</SUBJECT> <SECTNO>21.473</SECTNO> <SUBJECT>Airworthiness certificates other than experimental.</SUBJECT> <SECTNO>21.475</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> <SECTNO>21.477</SECTNO> <SUBJECT>Data review and service experience.</SUBJECT> <SECTNO>21.493</SECTNO> <SUBJECT>Current records.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart N—Approval of Engines, Propellers, Materials, Parts, and Appliances: Import</HD> <SECTNO>21.500</SECTNO> <SUBJECT>Approval of engines and propellers.</SUBJECT> <SECTNO>21.502</SECTNO> <SUBJECT>Approval of materials, parts, and appliances.</SUBJECT> </SUBPART> <SUBPART> <PRTPAGE P="101"/> <HD SOURCE="HED">Subpart O—Technical Standard Order Authorizations</HD> <SECTNO>21.601</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>21.603</SECTNO> <SUBJECT>TSO marking and privileges.</SUBJECT> <SECTNO>21.605</SECTNO> <SUBJECT>Application and issue.</SUBJECT> <SECTNO>21.607</SECTNO> <SUBJECT>General rules governing holders of TSO authorizations.</SUBJECT> <SECTNO>21.609</SECTNO> <SUBJECT>Approval for deviation.</SUBJECT> <SECTNO>21.611</SECTNO> <SUBJECT>Design changes.</SUBJECT> <SECTNO>21.613</SECTNO> <SUBJECT>Recordkeeping requirements.</SUBJECT> <SECTNO>21.615</SECTNO> <SUBJECT>FAA inspection.</SUBJECT> <SECTNO>21.617</SECTNO> <SUBJECT>Issue of letters of TSO design approval: import appliances.</SUBJECT> <SECTNO>21.619</SECTNO> <SUBJECT>Noncompliance.</SUBJECT> <SECTNO>21.621</SECTNO> <SUBJECT>Transferability and duration.</SUBJECT> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 42 U.S.C. 7572; 49 U.S.C. 106(g), 40105, 40113, 44701-44702, 44707, 44709, 44711, 44713, 44715, 45303. </AUTH> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For miscellaneous amendments to cross references in this Part 21 see Amdt. 21-10, 31 FR 9211, July 6, 1966. </EDNOTE> <SUBJGRP> <HD SOURCE="HED">Special Federal Aviation Regulations</HD> </SUBJGRP> <EAR>Pt. 21, SFAR No. 26</EAR> <SUBJGRP> <HD SOURCE="HED">SFAR No. <E T="01">26</E> </HD> </SUBJGRP> <EXTRACT> Contrary provisions of §§ 21.29, 21.500, and 21.502 of the Federal Aviation Regulations notwithstanding— 1. A type certificate may be issued under § 21.29 for an aircraft engine or propeller manufactured in a foreign country with which the United States has a currently effective bilateral agreement for the acceptance of powered aircraft for export and import and that is to be imported into the United States if (i) a type certificate has previously been issued by the Administrator for a product manufactured in that country which is of the same kind as the product for which a type certificate is requested; and (ii) the Administrator determines that the design standards and practices, the quality control standards, and the certification procedures utilized by such country for the particular product being imported are the equivalent of those required in the United States. 2. Aircraft engines, propellers, materials, parts (including subassemblies), or appliances (hereinafter referred to as aircraft components), manufactured in a foreign country with which the United States has a currently effective bilateral agreement for the acceptance of powered aircraft may be approved under § 21.500 or § 21.502, as applicable, if (i) an approval has previously been issued by the Administrator for an aircraft component manufactured in that country which is of the same kind as the aircraft component for which approval is requested; and (ii) the Administrator determines that the quality control standards and the certification and approval procedures utilized by such country for the particular aircraft component being imported are the equivalent of those required in the United States. 3. Aircraft subassemblies not covered under paragraph 2 that are to be incorporated on aircraft designed and manufactured in the United States, and that are manufactured in a foreign country with which the United States has a currently effective bilateral agreement for the acceptance of powered aircraft may be approved if (i) an approval has previously been issued by the Administrator for any other subassembly manufactured in that country; (ii) the Administrator determines that the quality control standards and the certification and approval procedures utilized by that country for the particular subassembly being imported are equivalent to those required in the United States; and (iii) the competent aeronautical authorities of the country certify that the subassembly meets the applicable design requirements. 4. Appropriate procedures for the execution of the provisions contained in paragraphs 1, 2, and 3 of the regulation may be embodied in agreements between the Administrator and the competent aeronautical authorities of the country of manufacture of the aircraft component. 5. In the event that the Administrator determines that the quality control standards and certification and approval procedures being utilized in the foreign countries to which this regulation is applicable no longer meet the quality control and certification and approval requirements equivalent to those required in the United States, the approval given under this regulation for the import into the United States of those aeronautical products covered by the regulation will be terminated. 6. After October 1, 1977, this special regulation applies only to aircraft components and subassemblies produced in Japan pursuant to contracts between Japanese manufacturers and United States product manufacturers entered into prior to October 1, 1977. This special regulation shall terminate December 1, 1977, unless sooner rescinded or superseded. </EXTRACT> <CITA>[35 FR 12749, Aug. 12, 1970, as amended at 40 FR 28604, July 8, 1975; 41 FR 27954, July 8, 1976; Doc. No. 10492, 42 FR 35634, July 11, 1977; Amdt. 26-11, 42 FR 54408, Oct. 6, 1977]</CITA> <EAR>Pt. 21, SFAR No. 29-4</EAR> <SUBJGRP> <HD SOURCE="HED">SFAR No. <E T="01">29-4</E> </HD> </SUBJGRP> <EXTRACT> <HD SOURCE="HD1">Limited IFR Operations of Rotorcraft</HD> 1. Contrary provisions of Parts 21, 27, and 29 of the Federal Aviation Regulations notwithstanding, an operator of a rotorcraft that is not otherwise certificated for IFR operations may conduct an approved limited IFR operation in the rotorcraft when— (a) FAA approval for the operation has been issued under paragraph 2 of this SFAR;<PRTPAGE P="102"/> (b) The operator complies with all conditions and limitations established by this SFAR and the approval; and (c) A copy of the approval and this SFAR are set forth as a supplement to the Rotorcraft Flight Manual. 2. FAA approval for the operation of a rotorcraft in limited IFR operations may be issued when the following conditions are met: (a) The operation is approved as part of the FAA study of limited rotorcraft IFR operations. (b) Specific FAA approval has been obtained for the following: (i) The rotorcraft (make, model, and serial number). (ii) The flightcrew. (iii) The procedures to be followed in the operation of the rotorcraft under IFR and the equipment that must be operable during such operations. (c) The conditions and limitations necessary for the safe operation of the rotorcraft in limited IFR operations have been established, approved, and incorporated into the operating limitations section of the Rotorcraft Flight Manual. 3. An approval issued under paragraph 2 of this Special Federal Aviation Regulation and the change to the Rotorcraft Flight Manual specified in paragraph 2(c) of this Special Federal Aviation Regulation constitute a supplemental type certificate for each rotorcraft approved under paragraph 2 of this SFAR. The supplemental type certificate will remain in effect until the approval to operate issued under the Special Federal Aviation Regulation is surrendered, revoked, or otherwise terminated. 4. Notwithstanding § 91.167(a)(3) of the Federal Aviation Regulations, a person may operate a rotorcraft in a limited IFR operation approved under paragraph 2(a) of the Special Federal Aviation Regulation with enough fuel to fly, after reaching the alternate airport, for not less than 30 minutes, when that period of time has been approved. 5. Expiration. (a) New applications for limited IFR rotorcraft operations under SFAR No. 29 may be submitted for approval until, but not including, the effective date of Amendment No. 1 of the Rotorcraft Regulatory Review Program. On and after the effective date of Amendment No. 1 of the Rotorcraft Regulatory Review Program, all applicants for certification of IFR rotorcraft operations must comply with the applicable provisions of the Federal Aviation Regulations. (b) This Special Federal Aviation Regulation will terminate when all approvals issued under Special Federal Aviation Regulation No. 29 are surrendered, revoked, or otherwise terminated. </EXTRACT> <CITA>[Doc. No. 14237, 48 FR 632, Jan. 6, 1983, as amended at 54 FR 34329, Aug. 18, 1989]</CITA> <EAR>Pt. 21, SFAR No. 41</EAR> <SUBJGRP> <HD SOURCE="HED">SFAR No. <E T="01">41</E> </HD> </SUBJGRP> <EXTRACT> 1. <E T="03">Applicability.</E> (a) Contrary provisions of Parts 21 and 23 of the Federal Aviation Regulations notwithstanding, an applicant is entitled to an amended or supplemental type certificate in the normal category for a reciprocating or turbopropeller-powered multiengine small airplane originally type certificated prior to October 17, 1979 in accordance with Part 23 of the Federal Aviation Regulations in effect on March 13, 1971, or later, that is to be certificated with a passenger seating configuration, excluding pilot seats, of 10 seats or more (but not more than 19 seats) at a maximum certificated takeoff weight of 12,500 pounds or less, if the applicant complies with— (1) The regulations incorporated in the type certificate; and (2) The requirements of appendix A of Part 135 of the Federal Aviation Regulations in effect on September 26, 1978, except that the landing distance must be determined for standard atmosphere at each weight, altitude, and wind within the operating limits established by the applicant in accordance with § 23.75(a) of this chapter in effect on September 26, 1978. Instead of a gliding approach specified in § 23.75(a), the landing may be preceded by a steady approach down to the 50-foot height at a gradient of descent not greater than 5.2 percent (3°) at a calibrated airspeed not less than 1.3V<E T="22">s1</E>. (b) Contrary provisions of Parts 1, 21, 23, 91, 121, and 135 of the Federal Aviation Regulations notwithstanding, an applicant is entitled to an amended or supplemental type certificate in the normal category for a reciprocating or turbopropeller powered multiengine airplane originally type certified prior to October 17, 1979 that is to be certificated with a maximum takeoff weight in excess of 12,500 pounds, a specified maximum zero fuel weight to be established by the applicant, and, where requested by the applicant, an increase in passenger seating configuration, (but not more than 19 passenger seats), if the applicant complies with— (1) The regulations incorporated in the type certificate; (2) The requirements of appendix A of Part 135 of the Federal Aviation Regulations in effect on September 26, 1978 with the exceptions specified in section 5 of this Special Federal Aviation Regulation; and (3) The additional requirements specified in sections 7 through 14 of this Special Federal Aviation Regulation applicable to -takeoff weights in excess of 12,500 pounds.<PRTPAGE P="103"/> (c) Contrary provisions of Part 1 of the Federal Aviation Regulations notwithstanding, an airplane certificated under paragraph (b) of this section is considered to be a small airplane for purposes of Parts 21, 23, 36, 121, 135, and 139 of the Federal Aviation Regulations, and a large airplane for purposes of Parts 61 and 91. Compliance with the small airplane provisions of Part 36 of the Federal Aviation Regulations must be shown at the maximum certificated takeoff weight approved under this Special Federal Aviation Regulation. 2. <E T="03">Eligibility.</E> Any person may apply for a supplemental type certificate (or an amended type certificate in the case of a type certificate holder) under this Special Federal Aviation Regulation. 3. <E T="03">Production limitation.</E> An amended or supplemental type certificate issued pursuant to section 1.(b) of this Special Federal Aviation Regulation is effective for the purpose of obtaining an original or an amended airworthiness certificate, until October 17, 1991 unless the type certificate is sooner surrendered, suspended, revoked, or terminated. 4. <E T="03">Restrictions.</E> For airplanes certificated under section 1.(b) of this Special Federal Aviation Regulation— (a) The maximum zero fuel weight of the airplane must be established as an operating limitation; and (b) Except as provided in paragraph (c) of this section the airworthiness certificate shall be endorsed “This airplane at weights in excess of 5,700 kg does not meet the airworthiness requirements of ICAO, as prescribed by Annex 8 of the Convention on International Civil Aviation.” (c) An applicant is entitled to type certificate amendment or a supplemental type certificate that shows compliance with ICAO Annex 8 if the airplane meets SFAR 41 and the following requirements prescribed by the Administrator in effect on October 17, 1979: (1) At each weight, altitude, and temperature within the operational limits selected by the applicant— (i) For approach climb performance, comply with §§ 25.121(d) and 25.1533(a)(2). (ii) For takeoff performance, comply with §§ 25.105(d), 25.111, 25.113(a), and 25.115. (2) For gust loads design at rough air gust speed V<E T="22">B</E>, comply with §§ 25.335(d), 25.341(a)(1), and 25.351(b). (3) For smoke evacuation design, comply with § 25.831(d). (4) For engine rotation and restarting design, comply with § 25.903 (c) and (e). (5) For engine cooling design, comply with § 25.1521(e). 5. <E T="03">Exceptions.</E> For purposes of obtaining an amended or supplemental type certificate under section 1.(b) of this Special Federal Aviation Regulation, the following exceptions apply. All references in this section to specific sections of Parts 23 and 25 of this chapter are to those in effect on September 26, 1978 if no other date is given: (a) Compliance with section 1 of appendix A of Part 135 of the Federal Aviation Regulations is not required. (b) Compliance may be shown with the applicable regulations incorporated in the type certificate in lieu of the requirements of appendix A of Part 135 of the Federal Aviation Regulations for takeoff weights of 12,500 pounds or less, if the airplane was type certificated— (1) Under FAR Part 23 in effect prior to Amendment 23-10 and the airplane is to be used only in FAR Part 91 operations; (2) Before July 19, 1970, in the normal category with a passenger seating configuration, excluding any pilot seat, of 10 seats or more, (but not to exceed 19 passenger seats), and meets special conditions issued by the Administrator for airplanes intended for use in operations under FAR Part 135; or (3) Before July 19, 1970, in the normal category with a passenger seating configuration, excluding any pilot seat, of 10 seats or more, (but not to exceed 19 passenger seats), and meets the additional airworthiness standards in Special Federal Aviation Regulation No. 23. (c) In lieu of compliance with sections 7., and 19.(c) of appendix A of Part 135 of the Federal Aviation Regulations, comply with the following at takeoff weights in excess of 12,500 pounds: <HD SOURCE="HD1"> <E T="03">Landing</E> </HD> (<E T="03">a</E>) The landing distance must be determined for standard atmosphere at each weight, altitude, and wind within the operational limits established by the applicant in accordance with § 23.75(a) of this chapter. Instead of a gliding approach specified in § 23.75(a), the landing may be preceded by a steady approach down to the 50-foot height at a gradient of descent not greater than 5.2 percent (3°) at a calibrated airspeed not less than 1.3 V<E T="22">S1</E>. (<E T="03">b</E>) The landing distance data must include correction factors for not more than 50 percent of the nominal wind components along the landing path opposite to the direction of landing, and not less than 150 percent of the nominal wind components along the landing path in the direction of landing. (d) In lieu of compliance with section 28 of appendix A of Part 135 of the Federal Aviation Regulations, comply with the following: <E T="03">Fatigue evaluation of flight structure.</E> Unless it is shown that the structure, operating stress levels, materials, and expected use are comparable from a fatigue standpoint to a similar design which has had substantial satifactory service experience, the strength, detail design, and the fabrication of those parts of the wing, wing carrythrough, vertical fin, horizortal stabilizer, and attaching <PRTPAGE P="104"/>structure whose failure would be catastrophic must be evaluted under either— (<E T="03">a</E>) A fatigue strength investigation in which the structure is shown by analysis, tests, or both, to be able to withstand the repeated loads of variable magnitude expected in service. Analysis alone is acceptable only when it is conservative and applied to simple structures; or (<E T="03">b</E>) A fail-safe strength investigation in which it is shown by analysis, tests, or both, that catastrophic failure of the structure is not probable after fatigue, or obvious partial failure, of a principal structural element, and that the remaining structure is able to withstand a static ultimate load factor of 75 percent of the critical limit load factor at V<E T="22">C</E>. These loads must be multiplied by a factor of 1.15 unless the dynamic effects of failure under static load are otherwise considered. (e) In lieu of compliance with section 32 of appendix A of Part 135 of the Federal Aviation Regulations, comply with the following: <E T="03">Doors and exits.</E> The airplane must meet the requirements of §§23.783 and 23.807 (a)(3), (b), and (c) of this chapter, and in addition the following requirements: (<E T="03">a</E>) Each cabin must have at least one easily accessible external door. (<E T="03">b</E>) There must be a means to lock and safeguard each external door against opening in flight (either inadvertently by persons or as a result of mechanical failure or failure of a single structural element). Each external door must be operable from both the inside and the outside, even though persons may be crowded against the door on the inside of the airplane. Inward opening doors may be used if there are means to prevent occupants from crowding against the door to an extent that would interfere with the opening of the door. The means of opening must be simple and obvious and must be arranged and marked so that it can be readily located and operated, even in darkness. Auxiliary locking devices may be used. (<E T="03">c</E>) Each external door must be reasonably free from jamming as a result of fuselage deformation in a minor crash. (<E T="03">d</E>) Each external door must be located where persons using it will not be endangered by the propellers when appropriate operating procedures are used. (<E T="03">e</E>) There must be a provision for direct visual inspection of the locking mechanism by crewmembers to determine whether external doors, for which the initial opening movement is outward (including passenger, crew, service, and cargo doors), are fully locked. In addition, there must be a visual means to signal to appropriate crewmembers when normally used external doors are closed and fully locked. (<E T="03">f</E>) Cargo and service doors not suitable for use as exits in an emergency need only meet paragraph (<E T="03">e</E>) of section 5(<E T="03">e</E>) of this regulation and be safeguarded against opening in flight as a result of mechanical failure or failure of a single structural element. (<E T="03">g</E>) The passenger entrance door must qualify as a floor level emergency exit. If an integral stair is installed at such a passenger entry door, the stair must be designed so that when subjected to the inertia forces specified in § 23.561 of this chapter, and following the collapse of one or more legs of the landing gear, it will not interfere to an extent that will reduce the effectiveness of emergency egress through the passenger entry door. Each additional required emergency exit except floor level exits must be located over the wing or must be provided with acceptable means to assist the occupants in descending to the ground. In addition to the passenger entrance door— (1) For a total passenger seating capacity of 15 or less, an emergency exit, as defined in § 23.807(b) of this chapter, is required on each side of the cabin; and (2) For a total passenger seating capacity of 16 through 19, three emergency exits, as defined in § 23.807(b) of this chapter, are required with one on the same side as the door and two on the side opposite the door. (<E T="03">h</E>) An evacuation demonstration must be conducted utilizing the maximum number of occupants for which certification is desired. It must be conducted under simulated night conditions utilizing only the emergency exits on the most critical side of the aircraft. The participants must be representative of average airline passengers with no prior practice or rehearsal for the demonstration. Evacuation must be completed within 90 seconds. (<E T="03">i</E>) Each emergency exit must be marked with the word “Exit” by a sign which has white letters 1 inch high on a red background 2 inches high, be self-illuminated or independently internally electrically illuminated, and have a minimum luminescence (brightness) of at least 160 microlamberts. The colors may be reversed if the passenger compartment illumination is essentially the same. (<E T="03">j</E>) Access to window type emergency exits may not be obstructed by seats or seat backs. (<E T="03">k</E>) The width of the main passenger aisle at any point between seats must equal or exceed the values in the following table: <GPOTABLE CDEF="s50,r36,r36" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Number of passenger seats</CHED> <CHED H="1">Minimum main passenger aisle width</CHED> <CHED H="2">Less than 25 inches from floor</CHED> <CHED H="2">25 inches and more from floor</CHED> </BOXHD> <ROW> <ENT I="01">10 through 19</ENT> <ENT>9 inches</ENT> <ENT>15 inches.</ENT> </ROW> </GPOTABLE> (f) In lieu of compliance with Section 45 of appendix A of Part 135 of the Federal Aviation Regulations, comply with § 23.954 of this chapter.<PRTPAGE P="105"/> (g) In lieu of compliance with Section 56 of appendix A of Part 135 of the Federal Aviation Regulations, comply with the following: <E T="03">Cowlings.</E> The airplane must be designed and constructed so that no fire originating in any engine compartment can enter, either through openings or by burn through, any other region where it would create additional hazards. (h) In lieu of complaince with Section 57 of appendix A of Part 135 of the Federal Aviation Regulations, comply with § 25.863 of this chapter. 6. <E T="03">Additional requirements—general.</E> The additional requirements specified in sections 7 through 14 apply to the certification of airplanes pursuant to section 1.(b) of this Special Federal Aviation Regulation. 7. <E T="03">Compartment interiors.</E> (a) If smoking is to be prohibited, there must be a placard so stating, and if smoking is to be allowed— (1) There must be an adequate number of self-contained removable ashtrays; and (2) Where the crew compartment is separated from the passenger compartment, there must be at least one sign (using either letters or symbols) notifying all passengers when smoking is prohibited. Signs which notify when smoking is prohibited must— (i) Be legible to each passenger seated in the passenger cabin under all probable lighting conditions; and (ii) When illuminated, be so constructed that the crew can turn them on and off. (b) Each disposal receptacle for towels, paper, or waste must be fully enclosed and constructed of at least fire resistant materials, and must contain fires likely to occur in it under normal use. The ability of the disposal receptacle to contain those fires under all probable conditions of wear, misalignment, and ventilation expected in service must be demonstrated by test. A placard containing the legible words “No Cigarette Disposal” must be located on or near each disposal receptacle door. (c) Lavatories must have “No Smoking” or “No Smoking in Lavatory” placards located conspicuously on each side of the entry door, and self-contained removable ashtrays located conspicuously on or near the entry side of each lavatory door, except that one ashtray may serve more than one lavatory door if it can be seen from the cabin side of each lavatory door served. The placards must have red letters at least one-half inch high on a white background at least one inch high. (A “No smoking” symbol may be included on the placard). (d) There must be at least one hand fire extinguisher conventiently located in the pilot compartment. (e) There must be at least one hand fire extinguisher conventiently located in the passenger compartment. 8. <E T="03">Landing gear.</E> Comply with § 25.721(a)(2), (b), and (c) of this chapter in effect on September 26, 1978. 9. <E T="03">Fuel system components crashworthiness.</E> Comply with §§ 25.963(d) and 25.994 of this chapter in effect on September 26, 1978. 10. <E T="03">Shutoff means.</E> Comply with § 23.1189 of this chapter in effect on September 26, 1978. 11. <E T="03">Fire detector and extinguishing systems—</E>(a) <E T="03">Fire detector systems.</E> (1) There must be a means which ensures the prompt detection of a fire in an engine compartment. (2) Each fire detector must be constructed and installed to withstand the vibration, inertia, and other loads to which it may be subjected in operation. (3) No fire detector may be affected by any oil, water, other fluids, or fumes that might be present. (4) There must be means to allow the crew to check, in flight, the function of each fire detector electric circuit. (5) Wiring and other components of each fire detector system in an engine compartment must be at least fire resistant. (b) <E T="03">Fire extinguishing systems.</E> (1) Except for combustor, turbine, and tail pipe sections of turbine engine installations that contain lines or components carrying flammable fluids or gases for which it is shown that a fire originating in these sections can be controlled, there must be a fire extinguisher system serving each engine compartment. (2) The fire extinguishing system, the quantity of the extinguishing agent, the rate of discharge, and the discharge distribution must be adequate to extinguish fires. An individual “one shot” system may be used. (3) The fire-extinguishing system for a nacelle must be able to simultaneously protect each compartment of the nacelle for which protection is provided. 12. <E T="03">Fire extinguishing agents.</E> Comply with § 25.1197 of this chapter in effect on September 26, 1978. 13. <E T="03">Extinguishing agent containers.</E> Comply with § 25.1199 of this chapter in effect on September 26, 1978. 14. <E T="03">Fire extinguishing system materials.</E> Comply with § 25.1201 of this chapter in effect on September 26, 1978. 15. <E T="03">Expiration.</E> This Special Federal Aviation Regulation terminates on September 13, 1983, unless sooner rescinded or superseded. </EXTRACT> <CITA>[Doc. No. 18315, 44 FR 53729, Sept. 17, 1979; 45 FR 25047, Apr. 14, 1980; 45 FR 80973, Dec. 8, 1980, as amended by Doc. No. 21716, 47 FR 35153, Aug. 12, 1982]</CITA> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECTION> <SECTNO>§ 21.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This part prescribes— (1) Procedural requirements for the issue of type certificates and changes <PRTPAGE P="106"/>to those certificates; the issue of production certificates; the issue of airworthiness certificates; and the issue of export airworthiness approvals. (2) Rules governing the holders of any certificate specified in paragraph (a)(1) of this section; and (3) Procedural requirements for the approval of certain materials, parts, processes, and appliances. (b) For the purposes of this part, the word “product” means an aircraft, aircraft engine, or propeller. In addition, for the purposes of Subpart L only, it includes components and parts of aircraft, of aircraft engines, and of propellers; also parts, materials, and appliances, approved under the Technical Standard Order system. <CITA>[Doc. No. 5085, 29 FR 14563, Oct. 24, 1964, as amended by Amdt. 21-2, 30 FR 8465, July 2, 1965; Amdt. 21-6, 30 FR 11379, Sept. 8, 1965]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.2</SECTNO> <SUBJECT>Falsification of applications, reports, or records.</SUBJECT> (a) No person shall make or cause to be made— (1) Any fraudulent or intentionally false statement on any application for a certificate or approval under this part; (2) Any fraudulent or intentionally false entry in any record or report that is required to be kept, made, or used to show compliance with any requirement for the issuance or the exercise of the privileges of any certificate or approval issued under this part; (3) Any reproduction for a fraudulent purpose of any certificate or approval issued under this part. (4) Any alteration of any certificate or approval issued under this part. (b) The commission by any person of an act prohibited under paragraph (a) of this section is a basis for suspending or revoking any certificate or approval issued under this part and held by that person. <CITA>[Doc. No. 23345, 57 FR 41367, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.3</SECTNO> <SUBJECT>Reporting of failures, malfunctions, and defects.</SUBJECT> (a) Except as provided in paragraph (d) of this section, the holder of a Type Certificate (including a Supplemental Type Certificate), a Parts Manufacturer Approval (PMA), or a TSO authorization, or the licensee of a Type Certificate shall report any failure, malfunction, or defect in any product, part, process, or article manufactured by it that it determines has resulted in any of the occurrences listed in paragraph (c) of this section. (b) The holder of a Type Certificate (including a Supplemental Type Certificate), a Parts Manufacturer Approval (PMA), or a TSO authorization, or the licensee of a Type of Certificate shall report any defect in any product, part, or article manufactured by it that has left its quality control system and that it determines could result in any of the occurrences listed in paragraph (c) of this section. (c) The following occurrences must be reported as provided in paragraphs (a) and (b) of this section: (1) Fires caused by a system or equipment failure, malfunction, or defect. (2) An engine exhaust system failure, malfunction, or defect which causes damage to the engine, adjacent aircraft structure, equipment, or components. (3) The accumulation or circulation of toxic or noxious gases in the crew compartment or passenger cabin. (4) A malfunction, failure, or defect of a propeller control system. (5) A propeller or rotorcraft hub or blade structural failure. (6) Flammable fluid leakage in areas where an ignition source normally exists. (7) A brake system failure caused by structural or material failure during operation. (8) A significant aircraft primary structural defect or failure caused by any autogenous condition (fatigue, understrength, corrosion, etc.). (9) Any abnormal vibration or buffeting caused by a structural or system malfunction, defect, or failure. (10) An engine failure. (11) Any structural or flight control system malfunction, defect, or failure which causes an interference with normal control of the aircraft for which derogates the flying qualities. (12) A complete loss of more than one electrical power generating system or hydraulic power system during a given operation of the aircraft. (13) A failure or malfunction of more than one attitude, airspeed, or altitude <PRTPAGE P="107"/>instrument during a given operation of the aircraft. (d) The requirements of paragraph (a) of this section do not apply to— (1) Failures, malfunctions, or defects that the holder of a Type Certificate (including a Supplemental Type Certificate), Parts Manufacturer Approval (PMA), or TSO authorization, or the licensee of a Type Certificate— (i) Determines were caused by improper maintenance, or improper usage; (ii) Knows were reported to the FAA by another person under the Federal Aviation Regulations; or (iii) Has already reported under the accident reporting provisions of Part 430 of the regulations of the National Transportation Safety Board. (2) Failures, malfunctions, or defects in products, parts, or articles manufactured by a foreign manufacturer under a U.S. Type Certificate issued under § 21.29 or § 21.617, or exported to the United States under § 21.502. (e) Each report required by this section— (1) Shall be made to the Aircraft Certification Office in the region in which the person required to make the report is located within 24 hours after it has determined that the failure, malfunction, or defect required to be reported has occurred. However, a report that is due on a Saturday or a Sunday may be delivered on the following Monday and one that is due on a holiday may be delivered on the next workday; (2) Shall be transmitted in a manner and form acceptable to the Administrator and by the most expeditious method available; and (3) Shall include as much of the following information as is available and applicable: (i) Aircraft serial number. (ii) When the failure, malfunction, or defect is associated with an article approved under a TSO authorization, the article serial number and model designation, as appropriate. (iii) When the failure, malfunction, or defect is associated with an engine or propeller, the engine or propeller serial number, as appropriate. (iv) Product model. (v) Identification of the part, component, or system involved. The identification must include the part number. (vi) Nature of the failure, malfunction, or defect. (f) Whenever the investigation of an accident or service difficulty report shows that an article manufactured under a TSO authorization is unsafe because of a manufacturing or design defect, the manufacturer shall, upon request of the Administrator, report to the Administrator the results of its investigation and any action taken or proposed by the manufacturer to correct that defect. If action is required to correct the defect in existing articles, the manufacturer shall submit the data necessary for the issuance of an appropriate airworthiness directive to the Manager of the Aircraft Certification Office for the geographic area of the FAA regional office in the region in which it is located. <CITA>[Amdt. 21-36, 35 FR 18187, Nov. 28, 1970, as amended by Amdt. 21-37, 35 FR 18450, Dec. 4, 1970; Amdt. 21-50, 45 FR 38346, June 9, 1980; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.5</SECTNO> <SUBJECT>Airplane or Rotorcraft Flight Manual.</SUBJECT> (a) With each airplane or rotorcraft that was not type certificated with an Airplane or Rotorcraft Flight Manual and that has had no flight time prior to March 1, 1979, the holder of a Type Certificate (including a Supplemental Type Certificate) or the licensee of a Type Certificate shall make available to the owner at the time of delivery of the aircraft a current approved Airplane or Rotorcraft Flight Manual. (b) The Airplane or Rotorcraft Flight Manual required by paragraph (a) of this section must contain the following information: (1) The operating limitations and information required to be furnished in an Airplane or Rotorcraft Flight Manual or in manual material, markings, and placards, by the applicable regulations under which the airplane or rotorcraft was type certificated. (2) The maximum ambient atmospheric temperature for which engine cooling was demonstrated must be stated in the performance information section of the Flight Manual, if the applicable regulations under which the <PRTPAGE P="108"/>aircraft was type certificated do not require ambient temperature on engine cooling operating limitations in the Flight Manual. <CITA>[Amdt. 21-46, 43 FR 2316, Jan. 16, 1978]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Type Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14564, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.11</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes— (a) Procedural requirements for the issue of type certificates for aircraft, aircraft engines, and propellers; and (b) Rules governing the holders of those certificates. </SECTION> <SECTION> <SECTNO>§ 21.13</SECTNO> <SUBJECT>Eligibility.</SUBJECT> Any interested person may apply for a type certificate. <CITA>[Amdt. 21-25, 34 FR 14068, Sept. 5, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.15</SECTNO> <SUBJECT>Application for type certificate.</SUBJECT> (a) An application for a type certificate is made on a form and in a manner prescribed by the Administrator and is submitted to the appropriate Aircraft Certification Office. (b) An application for an aircraft type certificate must be accompanied by a three-view drawing of that aircraft and available preliminary basic data. (c) An application for an aircraft engine type certificate must be accompanied by a description of the engine design features, the engine operating characteristics, and the proposed engine operating limitations. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-40, 39 FR 35459, Oct. 1, 1974; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.16</SECTNO> <SUBJECT>Special conditions.</SUBJECT> If the Administrator finds that the airworthiness regulations of this subchapter do not contain adequate or appropriate safety standards for an aircraft, aircraft engine, or propeller because of a novel or unusual design feature of the aircraft, aircraft engine or propeller, he prescribes special conditions and amendments thereto for the product. The special conditions are issued in accordance with Part 11 of this chapter and contain such safety standards for the aircraft, aircraft engine or propeller as the Administrator finds necessary to establish a level of safety equivalent to that established in the regulations. <CITA>[Amdt. 21-19, 32 FR 17851, Dec. 13, 1967; as amended by Amdt. 21-51, 45 FR 60170, Sept. 11, 1980]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.17</SECTNO> <SUBJECT>Designation of applicable regulations.</SUBJECT> (a) Except as provided in § 23.2, § 25.2, § 27.2, § 29.2 and in parts 34 and 36 of this chapter, an applicant for a type certificate must show that the aircraft, aircraft engine, or propeller concerned meets— (1) The applicable requirements of this subchapter that are effective on the date of application for that certificate unless— (i) Otherwise specified by the Administrator; or (ii) Compliance with later effective amendments is elected or required under this section; and (2) Any special conditions prescribed by the Administrator. (b) For special classes of aircraft, including the engines and propellers installed thereon (e.g., gliders, airships, and other nonconventional aircraft), for which airworthiness standards have not been issued under this subchapter, the applicable requirements will be the portions of those other airworthiness requirements contained in Parts 23, 25, 27, 29, 31, 33, and 35 found by the Administrator to be appropriate for the aircraft and applicable to a specific type design, or such airworthiness criteria as the Administrator may find provide an equivalent level of safety to those parts. (c) An application for type certification of a transport category aircraft is effective for 5 years and an application for any other type certificate is effective for 3 years, unless an applicant shows at the time of application that his product requires a longer period of time for design, development, and testing, and the Administrator approves a longer period. (d) In a case where a type certificate has not been issued, or it is clear that a type certificate will not be issued, within the time limit established under <PRTPAGE P="109"/>paragraph (c) of this section, the applicant may— (1) File a new application for a type certificate and comply with all the provisions of paragraph (a) of this section applicable to an original application; or (2) File for an extension of the original application and comply with the applicable airworthiness requirements of this subchapter that were effective on a date, to be selected by the applicant, not earlier than the date which precedes the date of issue of the type certificate by the time limit established under paragraph (c) of this section for the original application. (e) If an applicant elects to comply with an amendment to this subchapter that is effective after the filing of the application for a type certificate, he must also comply with any other amendment that the Administrator finds is directly related. (f) For primary category aircraft, the requirements are: (1) The applicable airworthiness requirements contained in parts 23, 27, 31, 33, and 35 of this subchapter, or such other airworthiness criteria as the Administrator may find appropriate and applicable to the specific design and intended use and provide a level of safety acceptable to the Administrator. (2) The noise standards of part 36 applicable to primary category aircraft. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-19, 32 FR 17851, Dec. 13, 1967; Amdt. 21-24, 34 FR 364, Jan. 10, 1969; Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-58, 50 FR 46877, Nov. 13, 1985; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-69, 56 FR 41051, Aug. 16, 1991; Amdt. 21-70, 57 FR 41367, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.19</SECTNO> <SUBJECT>Changes requiring a new type certificate.</SUBJECT> Any person who proposes to change a product must make a new application for a type certificate if— (a) The Administrator finds that the proposed change in design, configuration, power, power limitations (engines), speed limitations (engines), or weight is so extensive that a substantially complete investigation of compliance with the applicable regulations is required; (b) In the case of a normal, utility, acrobatic, commuter or transport category aircraft, the proposed change is— (1) In the number of engines or rotors; or (2) To engines or rotors using different principles of propulsion or to rotors using different principles of operation; (c) In the case of an aircraft engine, the proposed change is in the principle of operation; or (d) In the case of propellers, the proposed change is in the number of blades or principle of pitch change operation. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.21</SECTNO> <SUBJECT>Issue of type certificate: normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; special classes of aircraft; aircraft engines; propellers.</SUBJECT> An applicant is entitled to a type certificate for an aircraft in the normal, utility, acrobatic, commuter, or transport category, or for a manned free balloon, special class of aircraft, or an aircraft engine or propeller, if— (a) The product qualifies under § 21.27; or (b) The applicant submits the type design, test reports, and computations necessary to show that the product to be certificated meets the applicable airworthiness, aircraft noise, fuel venting, and exhaust emission requirements of the Federal Aviation Regulations and any special conditions prescribed by the Administrator, and the Administrator finds— (1) Upon examination of the type design, and after completing all tests and inspections, that the type design and the product meet the applicable noise, fuel venting, and emissions requirements of the Federal Aviation Regulations, and further finds that they meet the applicable airworthiness requirements of the Federal Aviation Regulations or that any airworthiness provisions not complied with are compensated for by factors that provide an equivalent level of safety; and (2) For an aircraft, that no feature or characteristic makes it unsafe for the <PRTPAGE P="110"/>category in which certification is requested. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-15, 32 FR 3735, Mar. 4, 1967; Amdt. 21-27, 34 FR 18368, Nov. 18, 1969; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.23</SECTNO> <RESERVED>[Reserved]</RESERVED> </SECTION> <SECTION> <SECTNO>§ 21.24</SECTNO> <SUBJECT>Issuance of type certificate: primary category aircraft.</SUBJECT> (a) The applicant is entitled to a type certificate for an aircraft in the primary category if— (1) The aircraft— (i) Is unpowered; is an airplane powered by a single, naturally aspirated engine with a 61-knot or less V<E T="52">so</E> stall speed as defined in § 23.49; or is a rotorcraft with a 6-pound per square foot main rotor disc loading limitation, under sea level standard day conditions; (ii) Weighs not more than 2,700 pounds; or, for seaplanes, not more than 3,375 pounds; (iii) Has a maximum seating capacity of not more than four persons, including the pilot; and (iv) Has an unpressurized cabin. (2) The applicant has submitted— (i) Except as provided by paragraph (c) of this section, a statement, in a form and manner acceptable to the Administrator, certifying that: the applicant has completed the engineering analysis necessary to demonstrate compliance with the applicable airworthiness requirements; the applicant has conducted appropriate flight, structural, propulsion, and systems tests necessary to show that the aircraft, its components, and its equipment are reliable and function properly; the type design complies with the airworthiness standards and noise requirements established for the aircraft under § 21.17(f); and no feature or characteristic makes it unsafe for its intended use; (ii) The flight manual required by § 21.5(b), including any information required to be furnished by the applicable airworthiness standards; (iii) Instructions for continued airworthiness in accordance with § 21.50(b); and (iv) A report that: summarizes how compliance with each provision of the type certification basis was determined; lists the specific documents in which the type certification data information is provided; lists all necessary drawings and documents used to define the type design; and lists all the engineering reports on tests and computations that the applicant must retain and make available under § 21.49 to substantiate compliance with the applicable airworthiness standards. (3) The Administrator finds that— (i) The aircraft complies with those applicable airworthiness requirements approved under § 21.17(f) of this part; and (ii) The aircraft has no feature or characteristic that makes it unsafe for its intended use. (b) An applicant may include a special inspection and preventive maintenance program as part of the aircraft's type design or supplemental type design. (c) For aircraft manufactured outside of the United States in a country with which the United States has a bilateral airworthiness agreement for the acceptance of these aircraft, and from which the aircraft is to be imported into the United States— (1) The statement required by paragraph (a)(2)(i) of this section must be made by the civil airworthiness authority of the exporting country; and (2) The required manuals, placards, listings, instrument markings, and documents required by paragraphs (a) and (b) of this section must be submitted in English. <CITA>[Doc. No. 23345, 57 FR 41367, Sept. 9, 1992; as amended by Amdt. 21-75, 62 FR 62808, Nov. 25, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.25</SECTNO> <SUBJECT>Issue of type certificate: Restricted category aircraft.</SUBJECT> (a) An applicant is entitled to a type certificate for an aircraft in the restricted category for special purpose operations if he shows compliance with the applicable noise requirements of Part 36 of this chapter, and if he shows that no feature or characteristic of the aircraft makes it unsafe when it is operated under the limitations prescribed for its intended use, and that the aircraft— (1) Meets the airworthiness requirements of an aircraft category except <PRTPAGE P="111"/>those requirements that the Administrator finds inappropriate for the special purpose for which the aircraft is to be used; or (2) Is of a type that has been manufactured in accordance with the requirements of and accepted for use by, an Armed Force of the United States and has been later modified for a special purpose. (b) For the purposes of this section, “special purpose operations” includes— (1) Agricultural (spraying, dusting, and seeding, and livestock and predatory animal control); (2) Forest and wildlife conservation; (3) Aerial surveying (photography, mapping, and oil and mineral exploration); (4) Patrolling (pipelines, power lines, and canals); (5) Weather control (cloud seeding); (6) Aerial advertising (skywriting, banner towing, airborne signs and public address systems); and (7) Any other operation specified by the Administrator. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-42, 40 FR 1033, Jan. 6, 1975]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.27</SECTNO> <SUBJECT>Issue of type certificate: surplus aircraft of the Armed Forces.</SUBJECT> (a) Except as provided in paragraph (b) of this section an applicant is entitled to a type certificate for an aircraft in the normal, utility, acrobatic, commuter, or transport category that was designed and constructed in the United States, accepted for operational use, and declared surplus by, an Armed Force of the United States, and that is shown to comply with the applicable certification requirements in paragraph (f) of this section. (b) An applicant is entitled to a type certificate for a surplus aircraft of the Armed Forces of the United States that is a counterpart of a previously type certificated civil aircraft, if he shows compliance with the regulations governing the original civil aircraft type certificate. (c) Aircraft engines, propellers, and their related accessories installed in surplus Armed Forces aircraft, for which a type certificate is sought under this section, will be approved for use on those aircraft if the applicant shows that on the basis of the previous military qualifications, acceptance, and service record, the product provides substantially the same level of airworthiness as would be provided if the engines or propellers were type certificated under Part 33 or 35 of the Federal Aviation Regulations. (d) The Administrator may relieve an applicant from strict compliance with a specific provision of the applicable requirements in paragraph (f) of this section, if the Administrator finds that the method of compliance proposed by the applicant provides substantially the same level of airworthiness and that strict compliance with those regulations would impose a severe burden on the applicant. The Administrator may use experience that was satisfactory to an Armed Force of the United States in making such a determination. (e) The Administrator may require an applicant to comply with special conditions and later requirements than those in paragraphs (c) and (f) of this section, if the Administrator finds that compliance with the listed regulations would not ensure an adequate level of airworthiness for the aircraft. (f) Except as provided in paragraphs (b) through (e) of this section, an applicant for a type certificate under this section must comply with the appropriate regulations listed in the following table: <GPOTABLE CDEF="s120,r65,r95" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Type of aircraft</CHED> <CHED H="1">Date accepted for operational use by the Armed Forces of the United States</CHED> <CHED H="1">Regulations that apply <SU>1</SU> </CHED> </BOXHD> <ROW> <ENT I="01">Small reciprocating-engine powered airplanes</ENT> <ENT>Before May 16, 1956<LI>After May 15, 1956</LI> </ENT> <ENT>CAR Part 3, as effective May 15, 1956.<LI>CAR Part 3, or FAR Part 23.</LI> </ENT> </ROW> <ROW> <ENT I="01">Small turbine engine-powered airplanes</ENT> <ENT>Before Oct. 2, 1959<LI>After Oct. 1, 1959</LI> </ENT> <ENT>CAR Part 3, as effective Oct. 1, 1959. <LI>CAR Part 3 or FAR Part 23.</LI> </ENT> </ROW> <ROW> <ENT I="01">Commuter category airplanes</ENT> <ENT>After (Feb. 17, 1987) <LI>FAR Part 23 as of (Feb. 17, 1987).</LI> </ENT> </ROW> <ROW> <ENT I="01">Large reciprocating-engine powered airplanes</ENT> <ENT>Before Aug. 26, 1955<LI>After Aug. 25, 1959</LI> </ENT> <ENT>CAR Part 4b, as effective Aug. 25, 1955. <LI>CAR Part 4b or FAR Part 25.</LI> </ENT> </ROW> <ROW> <PRTPAGE P="112"/> <ENT I="01">Large turbine engine-powered airplanes</ENT> <ENT>Before Oct. 2, 1959<LI>After Oct. 1, 1959</LI> </ENT> <ENT>CAR Part 4b, as effective Oct. 1, 1959. <LI>CAR Part 4b or FAR Part 25.</LI> </ENT> </ROW> <ROW> <ENT I="11">Rotorcraft with maximum certificated takeoff weight of:</ENT> </ROW> <ROW> <ENT I="02">6,000 pounds or less</ENT> <ENT>Before Oct. 2, 1959<LI>After Oct. 1, 1959</LI> </ENT> <ENT>CAR Part 6, as effective Oct. 1, 1959. <LI>CAR Part 6, or FAR Part 27.</LI> </ENT> </ROW> <ROW> <ENT I="02">Over 6,000 pounds</ENT> <ENT>Before Oct. 2, 1959<LI>After Oct. 1, 1959</LI> </ENT> <ENT>CAR Part 7, as effective Oct. 1, 1959. <LI>CAR Part 7, or FAR Part 29.</LI> </ENT> </ROW> <TNOTE> <SU>1</SU> Where no specific date is listed, the applicable regulations are those in effect on the date that the first aircraft of the particular model was accepted for operational use by the Armed Forces.</TNOTE> </GPOTABLE> <CITA TYPE="W">[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987; 52 FR 7262, Mar. 9, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.29</SECTNO> <SUBJECT>Issue of type certificate: import products.</SUBJECT> (a) A type certificate may be issued for a product that is manufactured in a foreign country with which the United States has an agreement for the acceptance of these products for export and import and that is to be imported into the United States if— (1) The country in which the product was manufactured certifies that the product has been examined, tested, and found to meet— (i) The applicable aircraft noise, fuel venting and exhaust emissions requirements of this subchapter as designated in § 21.17, or the applicable aircraft noise, fuel venting and exhaust emissions requirements of the country in which the product was manufactured, and any other requirements the Administrator may prescribe to provide noise, fuel venting and exhaust emission levels no greater than those provided by the applicable aircraft noise, fuel venting, and exhaust emission requirements of this subchapter as designated in § 21.17; and (ii) The applicable airworthiness requirements of this subchapter as designated in § 21.17, or the applicable airworthiness requirements of the country in which the product was manufactured and any other requirements the Administrator may prescribe to provide a level of safety equivalent to that provided by the applicable airworthiness requirements of this subchapter as designated in § 21.17; (2) The applicant has submitted the technical data, concerning aircraft noise and airworthiness, respecting the product required by the Administrator; and (3) The manuals, placards, listings, and instrument markings required by the applicable airworthiness (and noise, where applicable) requirements are presented in the English language. (b) A product type certificated under this section is considered to be type certificated under the noise standards of part 36, and the fuel venting and exhaust emission standards of part 34, of the Federal Aviation Regulations where compliance therewith is certified under paragraph (a)(1)(i) of this section, and under the airworthiness standards of that part of the Federal Aviation Regulations with which compliance is certified under paragraph (a)(1)(ii) of this section or to which an equivalent level of safety is certified under paragraph (a)(1)(ii) of this section. <CITA>[Amdt. 21-27, 34 FR 18363, Nov. 18, 1969, as amended by Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; 55 FR 37287, Sept. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.31</SECTNO> <SUBJECT>Type design.</SUBJECT> The type design consists of— (a) The drawings and specifications, and a listing of those drawings and specifications, necessary to define the configuration and the design features of the product shown to comply with the requirements of that part of this subchapter applicable to the product; (b) Information on dimensions, materials, and processes necessary to define the structural strength of the product; (c) The Airworthiness Limitations section of the Instructions for Continued Airworthiness as required by Parts <PRTPAGE P="113"/>23, 25, 27, 29, 31, 33, and 35 of this chapter or as otherwise required by the Administrator; and as specified in the applicable airworthiness criteria for special classes of aircraft defined in § 21.17(b); and (d) For primary category aircraft, if desired, a special inspection and preventive maintenance program designed to be accomplished by an appropriately rated and trained pilot-owner. (e) Any other data necessary to allow, by comparison, the determination of the airworthiness, noise characteristics, fuel venting, and exhaust emissions (where applicable) of later products of the same type. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-27, 34 FR 18363, Nov. 18, 1969; Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.33</SECTNO> <SUBJECT>Inspection and tests.</SUBJECT> (a) Each applicant must allow the Administrator to make any inspection and any flight and ground test necessary to determine compliance with the applicable requirements of the Federal Aviation Regulations. However, unless otherwise authorized by the Administrator— (1) No aircraft, aircraft engine, propeller, or part thereof may be presented to the Administrator for test unless compliance with paragraphs (b)(2) through (b)(4) of this section has been shown for that aircraft, aircraft engine, propeller, or part thereof; and (2) No change may be made to an aircraft, aircraft engine, propeller, or part thereof between the time that compliance with paragraphs (b)(2) through (b)(4) of this section is shown for that aircraft, aircraft engine, propeller, or part thereof and the time that it is presented to the Administrator for test. (b) Each applicant must make all inspections and tests necessary to determine— (1) Compliance with the applicable airworthiness, aircraft noise, fuel venting, and exhaust emission requirements; (2) That materials and products conform to the specifications in the type design; (3) That parts of the products conform to the drawings in the type design; and (4) That the manufacturing processes, construction and assembly conform to those specified in the type design. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-17, 32 FR 14926, Oct. 28, 1967; Amdt. 21-27, 34 FR 18363, Nov. 18, 1969; Amdt. 21-44, 41 FR 55463, Dec. 20, 1976; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.35</SECTNO> <SUBJECT>Flight tests.</SUBJECT> (a) Each applicant for an aircraft type certificate (other than under §§ 21.24 through 21.29) must make the tests listed in paragraph (b) of this section. Before making the tests the applicant must show— (1) Compliance with the applicable structural requirements of this subchapter; (2) Completion of necessary ground inspections and tests; (3) That the aircraft conforms with the type design; and (4) That the Administrator received a flight test report from the applicant (signed, in the case of aircraft to be certificated under Part 25 [New] of this chapter, by the applicant's test pilot) containing the results of his tests. (b) Upon showing compliance with paragraph (a) of this section, the applicant must make all flight tests that the Administrator finds necessary— (1) To determine compliance with the applicable requirements of this subchapter; and (2) For aircraft to be certificated under this subchapter, except gliders and except airplanes of 6,000 lbs. or less maximum certificated weight that are to be certificated under Part 23 of this chapter, to determine whether there is reasonable assurance that the aircraft, its components, and its equipment are reliable and function properly. (c) Each applicant must, if practicable, make the tests prescribed in paragraph (b)(2) of this section upon the aircraft that was used to show compliance with— (1) Paragraph (b)(1) of this section; and<PRTPAGE P="114"/> (2) For rotorcraft, the rotor drive endurance tests prescribed in § 27.923 or § 29.923 of this chapter, as applicable. (d) Each applicant must show for each flight test (except in a glider or a manned free balloon) that adequate provision is made for the flight test crew for emergency egress and the use of parachutes. (e) Except in gliders and manned free balloons, an applicant must discontinue flight tests under this section until he shows that corrective action has been taken, whenever— (1) The applicant's test pilot is unable or unwilling to make any of the required flight tests; or (2) Items of noncompliance with requirements are found that may make additional test data meaningless or that would make further testing unduly hazardous. (f) The flight tests prescribed in paragraph (b)(2) of this section must include— (1) For aircraft incorporating turbine engines of a type not previously used in a type certificated aircraft, at least 300 hours of operation with a full complement of engines that conform to a type certificate; and (2) For all other aircraft, at least 150 hours of operation. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-40, 39 FR 35459, Oct. 1, 1974; Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.37</SECTNO> <SUBJECT>Flight test pilot.</SUBJECT> Each applicant for a normal, utility, acrobatic, commuter, or transport category aircraft type certificate must provide a person holding an appropriate pilot certificate to make the flight tests required by this part. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.39</SECTNO> <SUBJECT>Flight test instrument calibration and correction report.</SUBJECT> (a) Each applicant for a normal, utility, acrobatic, commuter, or transport category aircraft type certificate must submit a report to the Administrator showing the computations and tests required in connection with the calibration of instruments used for test purposes and in the correction of test results to standard atmospheric conditions. (b) Each applicant must allow the Administrator to conduct any flight tests that he finds necessary to check the accuracy of the report submitted under paragraph (a) of this section. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.41</SECTNO> <SUBJECT>Type certificate.</SUBJECT> Each type certificate is considered to include the type design, the operating limitations, the certificate data sheet, the applicable regulations of this subchapter with which the Administrator records compliance, and any other conditions or limitations prescribed for the product in this subchapter. </SECTION> <SECTION> <SECTNO>§ 21.43</SECTNO> <SUBJECT>Location of manufacturing facilities.</SUBJECT> Except as provided in § 21.29, the Administrator does not issue a type certificate if the manufacturing facilities for the product are located outside of the United States, unless the Administrator finds that the location of the manufacturer's facilities places no undue burden on the FAA in administering applicable airworthiness requirements. </SECTION> <SECTION> <SECTNO>§ 21.45</SECTNO> <SUBJECT>Privileges.</SUBJECT> The holder or licensee of a type certificate for a product may— (a) In the case of aircraft, upon compliance with §§ 21.173 through 21.189, obtain airworthiness certificates; (b) In the case of aircraft engines or propellers, obtain approval for installation or certified aircraft; (c) In the case of any product, upon compliance with §§ 21.133 through 21.163, obtain a production certificate for the type certificated product; (d) Obtain approval of replacement parts for that product. </SECTION> <SECTION> <SECTNO>§ 21.47</SECTNO> <SUBJECT>Transferability.</SUBJECT> A type certificate may be transferred to or made available to third persons by licensing agreements. Each grantor shall, within 30 days after the transfer of a certificate or execution or termination of a licensing agreement, notify in writing the appropriate Aircraft Certification Office. The notification must <PRTPAGE P="115"/>state the name and address of the transferee or licensee, date of the transaction, and in the case of a licensing agreement, the extent of authority granted the licensee. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.49</SECTNO> <SUBJECT>Availability.</SUBJECT> The holder of a type certificate shall make the certificate available for examination upon the request of the Administrator or the National Transportation Safety Board. <CITA>[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.50</SECTNO> <SUBJECT>Instructions for continued airworthiness and manufacturer's maintenance manuals having airworthiness limitations sections.</SUBJECT> (a) The holder of a type certificate for a rotorcraft for which a Rotorcraft Maintenance Manual containing an “Airworthiness Limitations” section has been issued under § 27.1529 (a)(2) or § 29.1529 (a)(2) of this chapter, and who obtains approval of changes to any replacement time, inspection interval, or related procedure in that section of the manual, shall make those changes available upon request to any operator of the same type of rotorcraft. (b) The holder of a design approval, including either the type certificate or supplemental type certificate for an aircraft, aircraft engine, or propeller for which application was made after January 28, 1981, shall furnish at least one set of complete Instructions for Continued Airworthiness, prepared in accordance with §§ 23.1529, 25.1529, 27.1529, 29.1529, 31.82, 33.4, or 35.4 of this chapter, or as specified in the applicable airworthiness criteria for special classes of aircraft defined in § 21.17(b), as applicable, to the owner of each type of aircraft, aircraft engine, or propeller upon its delivery, or upon issuance of the first standard airworthiness certificate for the affected aircraft, whichever occurs later, and thereafter make those instructions available to any other person required by this chapter to comply with any of the terms of these instructions. In addition, changes to the Instructions for Continued Airworthiness shall be made available to any person required by this chapter to comply with any of those instructions. <CITA>[Amdt. No. 21-23, 33 FR 14105, Sept. 18, 1968, as amended by Amdt. No 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.51</SECTNO> <SUBJECT>Duration.</SUBJECT> A type certificate is effective until surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.53</SECTNO> <SUBJECT>Statement of conformity.</SUBJECT> (a) Each applicant must submit a statement of conformity (FAA Form 317) to the Administrator for each aircraft engine and propeller presented to the Administrator for type certification. This statement of conformity must include a statement that the aircraft engine or propeller conforms to the type design therefor. (b) Each applicant must submit a statement of conformity to the Administrator for each aircraft or part thereof presented to the Administrator for tests. This statement of conformity must include a statement that the applicant has complied with § 21.33(a) (unless otherwise authorized under that paragraph). <CITA>[Amdt. 21-17, 32 FR 14926, Oct. 28, 1967]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Provisional Type Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14566, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.71</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes— (a) Procedural requirements for the issue of provisional type certificates, amendments to provisional type certificates, and provisional amendments to type certificates; and (b) Rules governing the holders of those certificates. </SECTION> <SECTION> <SECTNO>§ 21.73</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) Any manufacturer of aircraft manufactured within the United States who is a United States citizen may apply for Class I or Class II provisional type certificates, for amendments to provisional type certificates held by <PRTPAGE P="116"/>him, and for provisional amendments to type certificates held by him. (b) Any manufacturer of aircraft manufactured in a foreign country with which the United States has an agreement for the acceptance of those aircraft for export and import may apply for a Class II provisional type certificate, for amendments to provisional type certificates held by him, and for provisional amendments to type certificates held by him. (c) An aircraft engine manufacturer who is a United States citizen and who has altered a type certificated aircraft by installing different type certificated aircraft engines manufactured by him within the United States may apply for a Class I provisional type certificate for the aircraft, and for amendments to Class I provisional type certificates held by him, if the basic aircraft, before alteration, was type certificated in the normal, utility, acrobatic, commuter, or transport category. <CITA>[Doc. No. 5085, 29 FR 14566, Oct. 24, 1964, as amended by Amdt. 21-12, 31 FR 13380, Oct. 15, 1966; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.75</SECTNO> <SUBJECT>Application.</SUBJECT> Applications for provisional type certificates, for amendments thereto, and for provisional amendments to type certificates must be submitted to the Manager of the Aircraft Certification Office for the geographic area in which the applicant is located (or in the case of European, African, Middle East Region, the Manager, Aircraft Engineering Division), and must be accompanied by the pertinent information specified in this subpart. <CITA>[Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.77</SECTNO> <SUBJECT>Duration.</SUBJECT> (a) Unless sooner surrendered, superseded, revoked, or otherwise terminated, provisional type certificates and amendments thereto are effective for the periods specified in this section. (b) A Class I provisional type certificate is effective for 24 months after the date of issue. (c) A Class II provisional type certificate is effective for twelve months after the date of issue. (d) An amendment to a Class I or Class II provisional type certificate is effective for the duration of the amended certificate. (e) A provisional amendment to a type certificate is effective for six months after its approval or until the amendment of the type certificate is approved, whichever is first. <CITA>[Doc. No. 5085, 29 FR 14566, Oct. 24, 1964 as amended by Amdt. 21-7, 30 FR 14311, Nov. 16, 1965]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.79</SECTNO> <SUBJECT>Transferability.</SUBJECT> Provisional type certificates are not transferable. </SECTION> <SECTION> <SECTNO>§ 21.81</SECTNO> <SUBJECT>Requirements for issue and amendment of Class I provisional type certificates.</SUBJECT> (a) An applicant is entitled to the issue or amendment of a Class I provisional type certificate if he shows compliance with this section and the Administrator finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations established in paragraph (e) of this section and in § 91.317 of this chapter. (b) The applicant must apply for the issue of a type or supplemental type certificate for the aircraft. (c) The applicant must certify that— (1) The aircraft has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type or supplemental type certificate applied for; (2) The aircraft substantially meets the applicable flight characteristic requirements for the type or supplemental type certificate applied for; and (3) The aircraft can be operated safely under the appropriate operating limitations specified in paragraph (a) of this section. (d) The applicant must submit a report showing that the aircraft had been flown in all maneuvers necessary to show compliance with the flight requirements for the issue of the type or supplemental type certificate applied for, and to establish that the aircraft can be operated safely in accordance with the limitations contained in this subchapter. (e) The applicant must establish all limitations required for the issue of the type or supplemental type certificate <PRTPAGE P="117"/>applied for, including limitations on weights, speeds, flight maneuvers, loading, and operation of controls and equipment unless, for each limitation not so established, appropriate operating restrictions are established for the aircraft. (f) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (g) The applicant must show that a prototype aircraft has been flown for at least 50 hours under an experimental certificate issued under §§ 21.191 through 21.195, or under the auspices of an Armed Force of the United States. However, in the case of an amendment to a provisional type certificate, the Administrator may reduce the number of required flight hours. <CITA>[Doc. No. 5085, 29 FR 14566, Oct. 24, 1964, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.83</SECTNO> <SUBJECT>Requirements for issue and amendment of Class II provisional type certificates.</SUBJECT> (a) An applicant who manufactures aircraft within the United States is entitled to the issue or amendment of a Class II provisional type certificate if he shows compliance with this section and the Administrator finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations in paragraph (h) of this section, and §§ 91.317 and 121.207 of this chapter. (b) An applicant who manufactures aircraft in a country with which the United States has an agreement for the acceptance of those aircraft for export and import is entitled to the issue or amendment of a Class II provisional type certificate if the country in which the aircraft was manufactured certifies that the applicant has shown compliance with this section, that the aircraft meets the requirements of paragraph (f) of this section and that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations in paragraph (h) of this section and §§ 91.317 and 121.207 of this chapter. (c) The applicant must apply for a type certificate, in the transport category, for the aircraft. (d) The applicant must hold a U.S. type certificate for at least one other aircraft in the same transport category as the subject aircraft. (e) The FAA's official flight test program or the flight test program conducted by the authorities of the country in which the aircraft was manufactured, with respect to the issue of a type certificate for that aircraft, must be in progress. (f) The applicant or, in the case of a foreign manufactured aircraft, the country in which the aircraft was manufactured, must certify that— (1) The aircraft has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type certificate applied for; (2) The aircraft substantially complies with the applicable flight characteristic requirements for the type certificate applied for; and (3) The aircraft can be operated safely under the appropriate operating limitations in this subchapter. (g) The applicant must submit a report showing that the aircraft has been flown in all maneuvers necessary to show compliance with the flight requirements for the issue of the type certificate and to establish that the aircraft can be operated safely in accordance with the limitations in this subchapter. (h) The applicant must prepare a provisional aircraft flight manual containing all limitations required for the issue of the type certificate applied for, including limitations on weights, speeds, flight maneuvers, loading, and operation of controls and equipment unless, for each limitation not so established, appropriate operating restrictions are established for the aircraft. (i) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (j) The applicant must show that a prototype aircraft has been flown for at least 100 hours. In the case of an <PRTPAGE P="118"/>amendment to a provisional type certificate, the Administrator may reduce the number of required flight hours. <CITA>[Amdt. 21-12, 31 FR 13386, Oct. 15, 1966, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.85</SECTNO> <SUBJECT>Provisional amendments to type certificates.</SUBJECT> (a) An applicant who manufactures aircraft within the United States is entitled to a provisional amendment to a type certificate if he shows compliance with this section and the Administrator finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated under the appropriate limitations contained in this subchapter. (b) An applicant who manufactures aircraft in a foreign country with which the United States has an agreement for the acceptance of those aircraft for export and import is entitled to a provisional amendment to a type certificate if the country in which the aircraft was manufactured certifies that the applicant has shown compliance with this section, that the aircraft meets the requirements of paragraph (e) of this section and that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated under the appropriate limitations contained in this subchapter. (c) The applicant must apply for an amendment to the type certificate. (d) The FAA's official flight test program or the flight test program conducted by the authorities of the country in which the aircraft was manufactured, with respect to the amendment of the type certificate, must be in progress. (e) The applicant or, in the case of foreign manufactured aircraft, the country in which the aircraft was manufactured, must certify that— (1) The modification involved in the amendment to the type certificate has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type certificate for the aircraft; (2) The aircraft substantially complies with the applicable flight characteristic requirements for the type certificate; and (3) The aircraft can be operated safely under the appropriate operating limitations in this subchapter. (f) The applicant must submit a report showing that the aircraft incorporating the modifications involved has been flown in all maneuvers necessary to show compliance with the flight requirements applicable to those modifications and to establish that the aircraft can be operated safely in accordance with the limitations specified in §§ 91.317 and 121.207 of this chapter. (g) The applicant must establish and publish, in a provisional aircraft flight manual or other document and on appropriate placards, all limitations required for the issue of the type certificate applied for, including weight, speed, flight maneuvers, loading, and operation of controls and equipment, unless, for each limitation not so established, appropriate operating restrictions are established for the aircraft. (h) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (i) The applicant must operate a prototype aircraft modified in accordance with the corresponding amendment to the type certificate for the number of hours found necessary by the Administrator. <CITA>[Amdt. 21-12, 31 FR 13388, Oct. 15, 1966, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Changes to Type Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14567, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.91</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the approval of changes to type certificates. </SECTION> <SECTION> <SECTNO>§ 21.93</SECTNO> <SUBJECT>Classification of changes in type design.</SUBJECT> (a) In addition to changes in type design specified in paragraph (b) of this section, changes in type design are classified as minor and major. A “minor change” is one that has no appreciable effect on the weight, balance, <PRTPAGE P="119"/>structural strength, reliability, operational characteristics, or other characteristics affecting the airworthiness of the product. All other changes are “major changes” (except as provided in paragraph (b) of this section). (b) For the purpose of complying with Part 36 of this chapter, and except as provided in paragraphs (b)(2), (b)(3), and (b)(4) of this section, any voluntary change in the type design of an aircraft that may increase the noise levels of that aircraft is an “acoustical change” (in addition to being a minor or major change as classified in paragraph (a) of this section) for the following aircraft: (1) Transport category large airplanes. (2) Turbojet powered airplanes (regardless of category). For airplanes to which this paragraph applies, “acoustical changes” do not include changes in type design that are limited to one of the following— (i) Gear down flight with one or more retractable landing gear down during the entire flight, or (ii) Spare engine and nacelle carriage external to the skin of the airplane (and return of the pylon or other external mount), or (iii) Time-limited engine and/or nacelle changes, where the change in type design specifies that the airplane may not be operated for a period of more than 90 days unless compliance with the applicable acoustical change provisions of Part 36 of this chapter is shown for that change in type design. (3) Propeller driven commuter category and small airplanes in the primary, normal, utility, acrobatic, transport, and restricted categories, except for airplanes that are: (i) Designated for “agricultural aircraft operations” (as defined in § 137.3 of this chapter, effective January 1, 1966) to which § 36.1583 of this chapter does not apply, or (ii) Designated for dispensing fire fighting materials to which § 36.1583 of this chapter does not apply, or (iii) U.S. registered, and that had flight time prior to January 1, 1955 or (iv) Land configured aircraft reconfigured with floats or skis. This reconfiguration does not permit further exception from the requirements of this section upon any acoustical change not enumerated in § 21.93(b). (4) Helicopters except: (i) Those helicopters that are designated exclusively: (A) For “agricultural aircraft operations”, as defined in § 137.3 of this chapter, as effective on January 1, 1966; (B) For dispensing fire fighting materials; or (C) For carrying external loads, as defined in § 133.1(b) of this chapter, as effective on December 20, 1976. (ii) Those helicopters modified by installation or removal of external equipment. For purposes of this paragraph, “external equipment” means any instrument, mechanism, part, apparatus, appurtenance, or accessory that is attached to, or extends from, the helicopter exterior but is not used nor is intended to be used in operating or controlling a helicopter in flight and is not part of an airframe or engine. An “acoustical change” does not include: (A) Addition or removal of external equipment; (B) Changes in the airframe made to accommodate the addition or removal of external equipment, to provide for an external load attaching means, to facilitate the use of external equipment or external loads, or to facilitate the safe operation of the helicopter with external equipment mounted to, or external loads carried by, the helicopter; (C) Reconfiguration of the helicopter by the addition or removal of floats and skis; (D) Flight with one or more doors and/or windows removed or in an open position; or (E) Any changes in the operational limitations placed on the helicopter as a consequence of the addition or removal of external equipment, floats, and skis, or flight operations with doors and/or windows removed or in an open position. (c) For purposes of complying with part 34 of this chapter, any voluntary change in the type design of the airplane or engine which may increase <PRTPAGE P="120"/>fuel venting or exhaust emissions is an “emissions change.” <CITA>[Amdt. 21-27, 34 FR 18363, Nov. 18, 1969, as amended by Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-47, 43 FR 28419, June 29, 1978; Amdt. 21-56, 47 FR 758, Jan. 7, 1982; Amdt. 21-61, 53 FR 3539, Feb. 5, 1988; Amdt. 21-62, 53 FR 16365, May 6, 1988; Amdt. 21-63, 53 FR 47399, Nov. 22, 1988; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992; Amdt. 21-73, 61 FR 20699, May 7, 1996; 61 FR 57002, Nov. 5, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.95</SECTNO> <SUBJECT>Approval of minor changes in type design.</SUBJECT> Minor changes in a type design may be approved under a method acceptable to the Administrator before submitting to the Administrator any substantiating or descriptive data. </SECTION> <SECTION> <SECTNO>§ 21.97</SECTNO> <SUBJECT>Approval of major changes in type design.</SUBJECT> (a) In the case of a major change in type design, the applicant must submit substantiating data and necessary descriptive data for inclusion in the type design. (b) Approval of a major change in the type design of an aircraft engine is limited to the specific engine configuration upon which the change is made unless the applicant identifies in the necessary descriptive data for inclusion in the type design the other configurations of the same engine type for which approval is requested and shows that the change is compatible with the other configurations. <CITA>[Amdt. 21-40, 39 FR 35459, Oct. 1, 1974]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.99</SECTNO> <SUBJECT>Required design changes.</SUBJECT> (a) When an Airworthiness Directive is issued under Part 39 the holder of the type certificate for the product concerned must— (1) If the Administrator finds that design changes are necessary to correct the unsafe condition of the product, and upon his request, submit appropriate design changes for approval; and (2) Upon approval of the design changes, make available the descriptive data covering the changes to all operators of products previously certif-icated under the type certificate. (b) In a case where there are no current unsafe conditions, but the Administrator or the holder of the type certificate finds through service experience that changes in type design will contribute to the safety of the product, the holder of the type certificate may submit appropriate design changes for approval. Upon approval of the changes, the manufacturer shall make information on the design changes available to all operators of the same type of product. <CITA>[Doc. No. 5085, 29 FR 14567, Oct. 24, 1964, as amended by Amdt. 21-3, 30 FR 8826, July 24, 1965]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.101</SECTNO> <SUBJECT>Designation of applicable regulations.</SUBJECT> (a) Except as provided in §§ 23.2, § 25.2, 27.2 and 29.2 and parts 34 and 36 of this chapter, an applicant for a change to a type certificate must comply with either— (1) The regulations incorporated by reference in the type certificate; or (2) The applicable regulations in effect on the date of the application, plus any other amendments the Administrator finds to be directly related. (b) If the Administrator finds that a proposed change consists of a new design or a substantially complete redesign of a component, equipment installation, or system installation, and that the regulations incorporated by reference in the type certificate for the product do not provide adequate standards with respect to the proposed change, the applicant must comply with— (1) The applicable provisions of this subchapter, in effect on the date of the application for the change, that the Administrator finds necessary to provide a level of safety equal to that established by the regulations incorporated by reference in the type certificate for the product; and (2) Any special conditions, and amendments to those special conditions, prescribed by the Administrator to provide a level of safety equal to that established by the regulations incorporated by reference in the type certificate for the product. (c) Unless otherwise required by § 21.19(a), an applicant for a change to a type certificate for a transport category airplane involving the replacement of reciprocating engines with the <PRTPAGE P="121"/>same number of turbopropeller powerplants must comply with the requirements of Part 25 of this chapter applicable to the airplane as type certificated with reciprocating engines, and with the following: (1) The certification performance requirements prescribed in §§ 25.101 through 25.125 and 25.149, 25.1533, 25.1583, and 25.1587. (2) The powerplant requirements of Part 25 of this chapter applicable to turbopropeller engine-powered airplanes. (3) The requirements of Part 25 of this chapter for the standardization of cockpit controls and instruments, unless the Administrator finds that compliance with a particular detailed requirement would be impractical and would not contribute materially to standardization. (4) Any other requirement of Part 25 of this chapter applicable to turbopropeller engine-powered airplanes that the Administrator finds to be related to the changes in engines and that are necessary to ensure a level of safety equal to that of the airplane certificated with reciprocating engines. <FP>For each new limitation established with respect to weight, speed, or altitude that is significantly altered from those approved for the airplane with reciprocating engines, the applicant must show compliance with the requirements of Part 25 of this chapter applicable to the limitations being changed.</FP> <CITA>[Doc. No. 5085, 29 FR 14567, Oct. 24, 1964, as amended by Amdt. 21-16, 32 FR 13262, Sept. 20, 1967; Amdt. 21-19, 32 FR 17851, Dec. 13, 1967; Amdt. 21-27, 34 FR 18363, Nov. 18, 1969; Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-58, 50 FR 46877, Nov. 13, 1985; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-69, 56 FR 41051, Aug. 16, 1991]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Supplemental Type Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14568, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.111</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the issue of supplemental type certificates. </SECTION> <SECTION> <SECTNO>§ 21.113</SECTNO> <SUBJECT>Requirement of supplemental type certificate.</SUBJECT> Any person who alters a product by introducing a major change in type design, not great enough to require a new application for a type certificate under § 21.19, shall apply to the Administrator for a supplemental type certificate, except that the holder of a type certificate for the product may apply for amendment of the original type certificate. The application must be made in a form and manner prescribed by the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.115</SECTNO> <SUBJECT>Applicable requirements.</SUBJECT> (a) Each applicant for a supplemental type certificate must show that the altered product meets applicable airworthiness requirements as specified in paragraphs (a) and (b) of § 21.101 and, in the case of an acoustical change described in § 21.93(b), show compliance with the applicable noise requirements of part 36 of this chapter and, in the case of an emissions change described in § 21.93(c), show compliance with the applicable fuel venting and exhaust emissions requirements of part 34 of this chapter. (b) Each applicant for a supplemental type certificate must meet §§ 21.33 and 21.53 with respect to each change in the type design. <CITA>[Amdt. 21-17, 32 FR 14927, Oct. 28, 1967, as amended by Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-52A, 45 FR 79009, Nov. 28, 1980; Amdt. 21-61, 53 FR 3540, Feb. 5, 1988; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-71, 57 FR 42854, Sept. 16, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.117</SECTNO> <SUBJECT>Issue of supplemental type certificates.</SUBJECT> (a) An applicant is entitled to a supplemental type certificate if he meets the requirements of §§ 21.113 and 21.115. (b) A supplemental type certificate consists of— (1) The approval by the Administrator of a change in the type design of the product; and (2) The type certificate previously issued for the product. </SECTION> <SECTION> <SECTNO>§ 21.119</SECTNO> <SUBJECT>Privileges.</SUBJECT> The holder of a supplemental type certificate may— (a) In the case of aircraft, obtain airworthiness certificates;<PRTPAGE P="122"/> (b) In the case of other products, obtain approval for installation on certificated aircraft; and (c) Obtain a production certificate for the change in the type design that was approved by that supplemental type certificate. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart F—Production Under Type Certificate Only</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14568, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.121</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes rules for production under a type certificate only. </SECTION> <SECTION> <SECTNO>§ 21.123</SECTNO> <SUBJECT>Production under type certificate.</SUBJECT> Each manufacturer of a product being manufactured under a type certificate only shall— (a) Make each product available for inspection by the Administrator; (b) Maintain at the place of manufacture the technical data and drawings necessary for the Administrator to determine whether the product and its parts conform to the type design; (c) Except as otherwise authorized by the Aircraft Certification Directorate Manager for the geographic area which the manufacturer is located, for products manufactured more than 6 months after the date of issue of the type certificate, establish and maintain an approved production inspection system that insures that each product conforms to the type design and is in condition for safe operation; and (d) Upon the establishment of the approved production inspection system (as required by paragraph (c) of this section) submit to the Administrator a manual that describes that system and the means for making the determinations required by § 21.125(b). <CITA>[Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21-34, 35 FR 13008, Aug. 15, 1970; Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.125</SECTNO> <SUBJECT>Production inspection system: Materials Review Board.</SUBJECT> (a) Each manufacturer required to establish a production inspection system by § 21.123(c) shall— (1) Establish a Materials Review Board (to include representatives from the inspection and engineering departments) and materials review procedures; and (2) Maintain complete records of Materials Review Board action for at least two years. (b) The production inspection system required in § 21.123(c) must provide a means for determining at least the following: (1) Incoming materials, and bought or subcontracted parts, used in the finished product must be as specified in the type design data, or must be suitable equivalents. (2) Incoming materials, and bought or subcontracted parts, must be properly identified if their physical or chemical properties cannot be readily and accurately determined. (3) Materials subject to damage and deterioration must be suitably stored and adequately protected. (4) Processes affecting the quality and safety of the finished product must be accomplished in accordance with acceptable industry or United States specifications. (5) Parts and components in process must be inspected for conformity with the type design data at points in production where accurate determinations can be made. (6) Current design drawings must be readily available to manufacturing and inspection personnel, and used when necessary. (7) Design changes, including material substitutions, must be controlled and approved before being incorporated in the finished product. (8) Rejected materials and parts must be segregated and identified in a manner that precludes installation in the finished product. (9) Materials and parts that are withheld because of departures from design data or specifications, and that are to be considered for installation in the finished product, must be processed through the Materials Review Board. Those materials and parts determined by the Board to be serviceable must be properly identified and reinspected if rework or repair is necessary. Materials and parts rejected by the Board <PRTPAGE P="123"/>must be marked and disposed of to ensure that they are not incorporated in the final product. (10) Inspection records must be maintained, identified with the completed product where practicable, and retained by the manufacturer for at least two years. </SECTION> <SECTION> <SECTNO>§ 21.127</SECTNO> <SUBJECT>Tests: aircraft.</SUBJECT> (a) Each person manufacturing aircraft under a type certificate only shall establish an approved production flight test procedure and flight check-off form, and in accordance with that form, flight test each aircraft produced. (b) Each production flight test procedure must include the following: (1) An operational check of the trim, controllability, or other flight characteristics to establish that the production aircraft has the same range and degree of control as the prototype aircraft. (2) An operational check of each part or system operated by the crew while in flight to establish that, during flight, instrument readings are within normal range. (3) A determination that all instruments are properly marked, and that all placards and required flight manuals are installed after flight test. (4) A check of the operational characteristics of the aircraft on the ground. (5) A check on any other items peculiar to the aircraft being tested that can best be done during the ground or flight operation of the aircraft. </SECTION> <SECTION> <SECTNO>§ 21.128</SECTNO> <SUBJECT>Tests: aircraft engines.</SUBJECT> (a) Each person manufacturing aircraft engines under a type certificate only shall subject each engine (except rocket engines for which the manufacturer must establish a sampling technique) to an acceptable test run that includes the following: (1) Break-in runs that include a determination of fuel and oil consumption and a determination of power characteristics at rated maximum continuous power or thrust and, if applicable, at rated takeoff power or thrust. (2) At least five hours of operation at rated maximum continuous power or thrust. For engines having a rated takeoff power or thrust higher than rated maximum continuous power or thrust, the five-hour run must include 30 minutes at rated takeoff power or thrust. (b) The test runs required by paragraph (a) of this section may be made with the engine appropriately mounted and using current types of power and thrust measuring equipment. <CITA>[Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21-5, 32 FR 3735, Mar. 4, 1967]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.129</SECTNO> <SUBJECT>Tests: propellers.</SUBJECT> Each person manufacturing propellers under a type certificate only shall give each variable pitch propeller an acceptable functional test to determine if it operates properly throughout the normal range of operation. </SECTION> <SECTION> <SECTNO>§ 21.130</SECTNO> <SUBJECT>Statement of conformity.</SUBJECT> Each holder or licensee of a type certificate only, for a product manufactured in the United States, shall, upon the initial transfer by him of the ownership of such product manufactured under that type certificate, or upon application for the original issue of an aircraft airworthiness certificate or an aircraft engine or propeller airworthiness approval tag (FAA Form 8130-3), give the Administrator a statement of conformity (FAA Form 317). This statement must be signed by an authorized person who holds a responsible position in the manufacturing organization, and must include— (a) For each product, a statement that the product conforms to its type certificate and is in condition for safe operation; (b) For each aircraft, a statement that the aircraft has been flight checked; and (c) For each aircraft engine or variable pitch propeller, a statement that the engine or propeller has been subjected by the manufacturer to a final operational check. <FP>However, in the case of a product manufactured for an Armed Force of the United States, a statement of conformity is not required if the product has been accepted by that Armed Force.</FP> <CITA>[Amdt. 21-25, 34 FR 14068, Sept. 5, 1969]</CITA> </SECTION> </SUBPART> <SUBPART> <PRTPAGE P="124"/> <HD SOURCE="HED">Subpart G—Production Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14569, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.131</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the issue of production certificates and rules governing the holders of those certificates. </SECTION> <SECTION> <SECTNO>§ 21.133</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) Any person may apply for a production certificate if he holds, for the product concerned, a— (1) Current type certificate; (2) Right to the benefits of that type certificate under a licensing agreement; or (3) Supplemental type certificate. (b) Each application for a production certificate must be made in a form and manner prescribed by the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.135</SECTNO> <SUBJECT>Requirements for issuance.</SUBJECT> An applicant is entitled to a production certificate if the Administrator finds, after examination of the supporting data and after inspection of the organization and production facilities, that the applicant has complied with §§ 21.139 and 21.143. </SECTION> <SECTION> <SECTNO>§ 21.137</SECTNO> <SUBJECT>Location of manufacturing facilities.</SUBJECT> The Administrator does not issue a production certificate if the manufacturing facilities concerned are located outside the United States, unless the Administrator finds no undue burden on the United States in administering the applicable requirements of the Federal Aviation Act of 1958 or of the Federal Aviation Regulations. </SECTION> <SECTION> <SECTNO>§ 21.139</SECTNO> <SUBJECT>Quality control.</SUBJECT> The applicant must show that he has established and can maintain a quality control system for any product, for which he requests a production certificate, so that each article will meet the design provisions of the pertinent type certificate. </SECTION> <SECTION> <SECTNO>§ 21.143</SECTNO> <SUBJECT>Quality control data requirements; prime manufacturer.</SUBJECT> (a) Each applicant must submit, for approval, data describing the inspection and test procedures necessary to ensure that each article produced conforms to the type design and is in a condition for safe operation, including as applicable— (1) A statement describing assigned responsibilities and delegated authority of the quality control organization, together with a chart indicating the functional relationship of the quality control organization to management and to other organizational components, and indicating the chain of authority and responsibility within the quality control organization; (2) A description of inspection procedures for raw materials, purchased items, and parts and assemblies produced by manufacturers’ suppliers including methods used to ensure acceptable quality of parts and assemblies that cannot be completely inspected for conformity and quality when delivered to the prime manufacturer's plant; (3) A description of the methods used for production inspection of individual parts and complete assemblies, including the identification of any special manufacturing processes involved, the means used to control the processes, the final test procedure for the complete product, and, in the case of aircraft, a copy of the manufacturer's production flight test procedures and checkoff list; (4) An outline of the materials review system, including the procedure for recording review board decisions and disposing of rejected parts; (5) An outline of a system for informing company inspectors of current changes in engineering drawings, specifications, and quality control procedures; and (6) A list or chart showing the location and type of inspection stations. (b) Each prime manufacturer shall make available to the Administrator information regarding all delegation of authority to suppliers to make major inspections of parts or assemblies for <PRTPAGE P="125"/>which the prime manufacturer is responsible. <CITA>[Doc. No. 5085, 29 FR 14569, Oct. 24, 1964, as amended by Amdt. 21-51, 45 FR 60170, Sept. 11, 1980]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.147</SECTNO> <SUBJECT>Changes in quality control system.</SUBJECT> After the issue of a production certificate, each change to the quality control system is subject to review by the Administrator. The holder of a production certificate shall immediately notify the Administrator, in writing of any change that may affect the inspection, conformity, or airworthiness of the product. </SECTION> <SECTION> <SECTNO>§ 21.149</SECTNO> <SUBJECT>Multiple products.</SUBJECT> The Administrator may authorize more than one type certificated product to be manufactured under the terms of one production certificate, if the products have similar production characteristics. </SECTION> <SECTION> <SECTNO>§ 21.151</SECTNO> <SUBJECT>Production limitation record.</SUBJECT> A production limitation record is issued as part of a production certificate. The record lists the type certificate of every product that the applicant is authorized to manufacture under the terms of the production certificate. </SECTION> <SECTION> <SECTNO>§ 21.153</SECTNO> <SUBJECT>Amendment of the production certificates.</SUBJECT> The holder of a production certificate desiring to amend it to add a type certificate or model, or both, must apply therefor in a form and manner prescribed by the Administrator. The applicant must comply with the applicable requirements of §§ 21.139, 21.143, and 21.147. </SECTION> <SECTION> <SECTNO>§ 21.155</SECTNO> <SUBJECT>Transferability.</SUBJECT> A production certificate is not transferable. </SECTION> <SECTION> <SECTNO>§ 21.157</SECTNO> <SUBJECT>Inspections and tests.</SUBJECT> Each holder of a production certificate shall allow the Administrator to make any inspections and tests necessary to determine compliance with the applicable regulations in this subchapter. </SECTION> <SECTION> <SECTNO>§ 21.159</SECTNO> <SUBJECT>Duration.</SUBJECT> A production certificate is effective until surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, or the location of the manufacturing facility is changed. </SECTION> <SECTION> <SECTNO>§ 21.161</SECTNO> <SUBJECT>Display.</SUBJECT> The holder of a production certificate shall display it prominently in the main office of the factory in which the product concerned is manufactured. </SECTION> <SECTION> <SECTNO>§ 21.163</SECTNO> <SUBJECT>Privileges.</SUBJECT> (a) The holder of a production certificate may— (1) Obtain an aircraft airworthiness certificate without further showing, except that the Administrator may inspect the aircraft for conformity with the type design; or (2) In the case of other products, obtain approval for installation on type certificated aircraft. (b) Notwithstanding the provisions of § 147.3 of this chapter, the holder of a production certificate for a primary category aircraft, or for a normal, utility, or acrobatic category aircraft of a type design that is eligible for a special airworthiness certificate in the primary category under § 21.184(c), may— (1) Conduct training for persons in the performance of a special inspection and preventive maintenance program approved as a part of the aircraft's type design under § 21.24(b), provided the training is given by a person holding a mechanic certificate with appropriate airframe and powerplant ratings issued under part 65 of this chapter; and (2) Issue a certificate of competency to persons successfully completing the approved training program, provided the certificate specifies the aircraft make and model to which the certificate applies. <CITA>[Doc. No. 23345, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.165</SECTNO> <SUBJECT>Responsibility of holder.</SUBJECT> The holder of a production certificate shall— (a) Maintain the quality control system in conformity with the data and procedures approved for the production certificate; and<PRTPAGE P="126"/> (b) Determine that each part and each completed product, including primary category aircraft assembled under a production certificate by another person from a kit provided by the holder of the production certificate, submitted for airworthiness certification or approval conforms to the approved design and is in a condition for safe operation. <CITA>[Doc. No. 5085, 29 FR 14569, Oct. 24, 1964, as amended by Amdt. 21-64, 53 FR 48521, Dec. 1, 1988; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart H—Airworthiness Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14569, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.171</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the issue of airworthiness certificates. </SECTION> <SECTION> <SECTNO>§ 21.173</SECTNO> <SUBJECT>Eligibility.</SUBJECT> Any registered owner of a U.S.-registered aircraft (or the agent of the owner) may apply for an airworthiness certificate for that aircraft. An application for an airworthiness certificate must be made in a form and manner acceptable to the Administrator, and may be submitted to any FAA office. <CITA>[Amdt. 21-26, 34 FR 15244, Sept. 30, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.175</SECTNO> <SUBJECT>Airworthiness certificates: classification.</SUBJECT> (a) Standard airworthiness certificates are airworthiness certificates issued for aircraft type certificated in the normal, utility, acrobatic, commuter, or transport category, and for manned free balloons, and for aircraft designated by the Administrator as special classes of aircraft. (b) Special airworthiness certificates are primary, restricted, limited, and provisional airworthiness certificates, special flight permits, and experimental certificates. <CITA>[Amdt. 21-21, 33 FR 6858, May 7, 1968, as amended by Amdt. 21-60, 52 FR 8043, Mar. 13, 1987; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.177</SECTNO> <SUBJECT>Amendment or modification.</SUBJECT> An airworthiness certificate may be amended or modified only upon application to the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.179</SECTNO> <SUBJECT>Transferability.</SUBJECT> An airworthiness certificate is transferred with the aircraft. </SECTION> <SECTION> <SECTNO>§ 21.181</SECTNO> <SUBJECT>Duration.</SUBJECT> (a) Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, airworthiness certificates are effective as follows: (1) Standard airworthiness certificates, special airworthiness certificates—primary category, and airworthiness certificates issued for restricted or limited category aircraft are effective as long as the maintenance, preventive maintenance, and alterations are performed in accordance with Parts 43 and 91 of this chapter and the aircraft are registered in the United States. (2) A special flight permit is effective for the period of time specified in the permit. (3) An experimental certificate for research and development, showing compliance with regulations, crew training, or market surveys is effective for one year after the date of issue or renewal unless a shorter period is prescribed by the Administrator. The duration of amateur-built, exhibition, and air-racing experimental certificates will be unlimited unless the Administrator finds for good cause that a specific period should be established. (b) The owner, operator, or bailee of the aircraft shall, upon request, make it available for inspection by the Administrator. (c) Upon suspension, revocation, or termination by order of the Administrator of an airworthiness certificate, the owner, operator, or bailee of an aircraft shall, upon request, surrender the certificate to the Administrator. <CITA>[Amdt. 21-21, 33 FR 6858, May 7, 1968, as amended by Amdt. 21-49, 44 FR 46781, Aug. 9, 1979; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.182</SECTNO> <SUBJECT>Aircraft identification.</SUBJECT> (a) Except as provided in paragraph (b) of this section, each applicant for <PRTPAGE P="127"/>an airworthiness certificate under this subpart must show that his aircraft is identified as prescribed in § 45.11. (b) Paragraph (a) of this section does not apply to applicants for the following: (1) A special flight permit. (2) An experimental certificate for an aircraft that is not amateur-built or kit-built. (3) A change from one airworthiness classification to another, for an aircraft already identified as prescribed in § 45.11. <CITA>[Amdt. 21-13, 32 FR 188, Jan. 10, 1967, as amended by Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-70, 57 FR 41368, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.183</SECTNO> <SUBJECT>Issue of standard airworthiness certificates for normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; and special classes of aircraft.</SUBJECT> (a) <E T="03">New aircraft manufactured under a production certificate.</E> An applicant for a standard airworthiness certificate for a new aircraft manufactured under a production certificate is entitled to a standard airworthiness certificate without further showing, except that the Administrator may inspect the aircraft to determine conformity to the type design and condition for safe operation. (b) <E T="03">New aircraft manufactured under type certificate only.</E> An applicant for a standard airworthiness certificate for a new aircraft manufactured under a type certificate only is entitled to a standard airworthiness certificate upon presentation, by the holder or licensee of the type certificate, of the statement of conformity prescribed in § 21.130 if the Administrator finds after inspection that the aircraft conforms to the type design and is in condition for safe operation. (c) <E T="03">Import aircraft.</E> An applicant for a standard airworthiness certificate for an import aircraft type certificated in accordance with § 21.29 is entitled to an airworthiness certificate if the country in which the aircraft was manufactured certifies, and the Administrator finds, that the aircraft conforms to the type design and is in condition for safe operation. (d) <E T="03">Other aircraft.</E> An applicant for a standard airworthiness certificate for aircraft not covered by paragraphs (a) through (c) of this section is entitled to a standard airworthiness certificate if— (1) He presents evidence to the Administrator that the aircraft conforms to a type design approved under a type certificate or a supplemental type certificate and to applicable Airworthiness Directives; (2) The aircraft (except an experimentally certificated aircraft that previously had been issued a different airworthiness certificate under this section) has been inspected in accordance with the performance rules for 100-hour inspections set forth in § 43.15 of this chapter and found airworthy by— (i) The manufacturer; (ii) The holder of a repair station certificate as provided in Part 145 of this chapter; (iii) The holder of a mechanic certificate as authorized in Part 65 of this chapter; or (iv) The holder of a certificate issued under Part 121 or 127 of this chapter, and having a maintenance and inspection organization appropriate to the aircraft type; and (3) The Administrator finds after inspection, that the aircraft conforms to the type design, and is in condition for safe operation. (e) <E T="03">Noise requirements.</E> Notwithstanding all other provisions of this section, the following must be complied with for the original issuance of a standard airworthiness certificate: (1) For transport category large airplanes and turbojet powered airplanes that have not had any flight time before the dates specified in § 36.1(d), no standard airworthiness certificate is originally issued under this section unless the Administrator finds that the type design complies with the noise requirements in § 36.1(d) in addition to the applicable airworthiness requirements in this section. For import airplanes, compliance with this paragraph is shown if the country in which the airplane was manufactured certifies, and the Administrator finds, that § 36.1(d) (or the applicable airplane noise requirements of the country in which the airplane was manufactured <PRTPAGE P="128"/>and any other requirements the Administrator may prescribe to provide noise levels no greater than those provided by compliance with § 36.1(d)) and paragraph (c) of this section are complied with. (2) For normal, utility, acrobatic, commuter, or transport category propeller driven small airplanes (except for those airplanes that are designed for “agricultural aircraft operations” (as defined in § 137.3 of this chapter, as effective on January 1, 1966) or for dispensing fire fighting materials to which § 36.1583 of this chapter does not apply) that have not had any flight time before the applicable date specified in Part 36 of this chapter, no standard airworthiness certificate is originally issued under this section unless the applicant shows that the type design complies with the applicable noise requirements of Part 36 of this chapter in addition to the applicable airworthiness requirements in this section. For import airplanes, compliance with this paragraph is shown if the country in which the airplane was manufactured certifies, and the Administrator finds, that the applicable requirements of Part 36 of this chapter (or the applicable airplane noise requirements of the country in which the airplane was manufactured and any other requirements the Administrator may prescribe to provide noise levels no greater than those provided by compliance with the applicable requirements of Part 36 of this chapter) and paragraph (c) of this section are complied with. (f) <E T="03">Passenger emergency exit requirements.</E> Notwithstanding all other provisions of this section, each applicant for issuance of a standard airworthiness certificate for a transport category airplane manufactured after October 16, 1987, must show that the airplane meets the requirements of § 25.807(c)(7) in effect on July 24, 1989. For the purposes of this paragraph, the date of manufacture of an airplane is the date the inspection acceptance records reflect that the airplane is complete and meets the FAA-approved type design data. (g) <E T="03">Fuel venting and exhaust emission requirements.</E> Notwithstanding all other provisions of this section, and irrespective of the date of application, no airworthiness certificate is issued, on and after the dates specified in part 34 for the airplanes specified therein, unless the airplane complies with the applicable requirements of that part. <CITA>[Amdt. 21-17, 32 FR 14927, Oct. 28, 1967, as amended by Amdt. 21-20, 33 FR 3055, Feb. 16, 1968; Amdt. 21-25, 34 FR 14068, Sept. 5, 1969; Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-47, 43 FR 28419, June 29, 1978; Amdt. 21-52, 45 FR 67066, Oct. 9, 1980; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987; Amdt. 21-60, 52 FR 8043, Mar. 13, 1987; Amdt. 21-65, 54 FR 26695, June 23, 1989; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.184</SECTNO> <SUBJECT>Issue of special airworthiness certificates for primary category aircraft.</SUBJECT> (a) <E T="03">New primary category aircraft manufactured under a production certificate.</E> An applicant for an original, special airworthiness certificate-primary category for a new aircraft that meets the criteria of § 21.24(a)(1), manufactured under a production certificate, including aircraft assembled by another person from a kit provided by the holder of the production certificate and under the supervision and quality control of that holder, is entitled to a special airworthiness certificate without further showing, except that the Administrator may inspect the aircraft to determine conformity to the type design and condition for safe operation. (b) <E T="03">Imported aircraft.</E> An applicant for a special airworthiness certificate-primary category for an imported aircraft type certificated under § 21.29 is entitled to a special airworthiness certificate if the civil airworthiness authority of the country in which the aircraft was manufactured certifies, and the Administrator finds after inspection, that the aircraft conforms to an approved type design that meets the criteria of § 21.24(a)(1) and is in a condition for safe operation. (c) <E T="03">Aircraft having a current standard airworthiness certificate.</E> An applicant for a special airworthiness certificate-primary category, for an aircraft having a current standard airworthiness certificate that meets the criteria of § 21.24(a)(1), may obtain the primary category certificate in exchange for its standard airworthiness certificate <PRTPAGE P="129"/>through the supplemental type certification process. For the purposes of this paragraph, a current standard airworthiness certificate means that the aircraft conforms to its approved normal, utility, or acrobatic type design, complies with all applicable airworthiness directives, has been inspected and found airworthy within the last 12 calendar months in accordance with § 91.409(a)(1) of this chapter, and is found to be in a condition for safe operation by the Administrator. (d) <E T="03">Other aircraft.</E> An applicant for a special airworthiness certificate-primary category for an aircraft that meets the criteria of § 21.24(a)(1), and is not covered by paragraph (a), (b), or (c) of this section, is entitled to a special airworthiness certificate if— (1) The applicant presents evidence to the Administrator that the aircraft conforms to an approved primary, normal, utility, or acrobatic type design, including compliance with all applicable airworthiness directives; (2) The aircraft has been inspected and found airworthy within the past 12 calendar months in accordance with § 91.409(a)(1) of this chapter and; (3) The aircraft is found by the Administrator to conform to an approved type design and to be in a condition for safe operation. (e) <E T="03">Multiple-category airworthiness certificates</E> in the primary category and any other category will not be issued; a primary category aircraft may hold only one airworthiness certificate. <CITA>[Doc. No. 23345, 57 FR 41368, Sept. 9, 1992, as amended by Amdt. 21-70, 57 FR 43776, Sept. 22, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.185</SECTNO> <SUBJECT>Issue of airworthiness certificates for restricted category aircraft.</SUBJECT> (a) <E T="03">Aircraft manufactured under a production certificate or type certificate only.</E> An applicant for the original issue of a restricted category airworthiness certificate for an aircraft type certificated in the restricted category, that was not previously type certificated in any other category, must comply with the appropriate provisions of § 21.183. (b) <E T="03">Other aircraft.</E> An applicant for a restricted category airworthiness certificate for an aircraft type certificated in the restricted category, that was either a surplus aircraft of the Armed Forces or previously type certificated in another category, is entitled to an airworthiness certificate if the aircraft has been inspected by the Administrator and found by him to be in a good state of preservation and repair and in a condition for safe operation. (c) <E T="03">Import aircraft.</E> An applicant for the original issue of a restricted category airworthiness certificate for an import aircraft type certificated in the restricted category only in accordance with § 21.29 is entitled to an airworthiness certificate if the country in which the aircraft was manufactured certifies, and the Administrator finds, that the aircraft conforms to the type design and is in a condition for safe operation. (d) <E T="03">Noise requirements.</E> For propeller-driven small airplanes (except airplanes designed for “agricultural aircraft operations,” as defined in § 137.3 of this chapter, as effective on January 1, 1966, or for dispensing fire fighting materials) that have not had any flight time before the applicable date specified in Part 36 of this chapter, and notwithstanding the other provisions of this section, no original restricted category airworthiness certificate is issued under this section unless the Administrator finds that the type design complies with the applicable noise requirements of Part 36 of this chapter in addition to the applicable airworthiness requirements of this section. For import airplanes, compliance with this paragraph is shown if the country in which the airplane was manufactured certifies, and the Administrator finds, that the applicable requirements of Part 36 of this chapter (or the applicable airplane noise requirements of the country in which the airplane was manufactured and any other requirements the Administrator may prescribe to provide noise levels no greater than those provided by compliance with the applicable requirements of Part 36 of this chapter) and paragraph (c) of this section are complied with. <CITA>[Amdt. 21-10, 31 FR 9211, July 6, 1966; as amended by Amdt. 21-32, 35 FR 10202, June 23, 1970; Amdt. 21-42, 40 FR 1034, Jan. 6, 1975]</CITA> </SECTION> <SECTION> <PRTPAGE P="130"/> <SECTNO>§ 21.187</SECTNO> <SUBJECT>Issue of multiple airworthiness certification.</SUBJECT> (a) An applicant for an airworthiness certificate in the restricted category, and in one or more other categories except primary category, is entitled to the certificate, if— (1) He shows compliance with the requirements for each category, when the aircraft is in the configuration for that category; and (2) He shows that the aircraft can be converted from one category to another by removing or adding equipment by simple mechanical means. (b) The operator of an aircraft certif-icated under this section shall have the aircraft inspected by the Administrator, or by a certificated mechanic with an appropriate airframe rating, to determine airworthiness each time the aircraft is converted from the restricted category to another category for the carriage of passengers for compensation or hire, unless the Administrator finds this unnecessary for safety in a particular case. (c) The aircraft complies with the applicable requirements of part 34. <CITA>[Doc. No. 5085, 29 FR 14569, Oct. 24, 1964, as amended by Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-70, 57 FR 41369, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.189</SECTNO> <SUBJECT>Issue of airworthiness certificate for limited category aircraft.</SUBJECT> (a) An applicant for an airworthiness certificate for an aircraft in the limited category is entitled to the certificate when— (1) He shows that the aircraft has been previously issued a limited category type certificate and that the aircraft conforms to that type certificate; and (2) The Administrator finds, after inspection (including a flight check by the applicant), that the aircraft is in a good state of preservation and repair and is in a condition for safe operation. (b) The Administrator prescribes limitations and conditions necessary for safe operation. <CITA>[Doc. No. 5085, 29 FR 14570, Oct. 24, 1964, as amended by Amdt. 21-4, 30 FR 9437, July 29, 1965]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.191</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> Experimental certificates are issued for the following purposes: (a) <E T="03">Research and development.</E> Testing new aircraft design concepts, new aircraft equipment, new aircraft installations, new aircraft operating techniques, or new uses for aircraft. (b) <E T="03">Showing compliance with regulations.</E> Conducting flight tests and other operations to show compliance with the airworthiness regulations including flights to show compliance for issuance of type and supplemental type certificates, flights to substantiate major design changes, and flights to show compliance with the function and reliability requirements of the regulations. (c) <E T="03">Crew training.</E> Training of the applicant's flight crews. (d) <E T="03">Exhibition.</E> Exhibiting the aircraft's flight capabilities, performance, or unusual characteristics at air shows, motion picture, television, and similar productions, and the maintenance of exhibition flight proficiency, including (for persons exhibiting aircraft) flying to and from such air shows and productions. (e) <E T="03">Air racing.</E> Participating in air races, including (for such participants) practicing for such air races and flying to and from racing events. (f) <E T="03">Market surveys.</E> Use of aircraft for purposes of conducting market surveys, sales demonstrations, and customer crew training only as provided in § 21.195. (g) <E T="03">Operating amateur-built aircraft.</E> Operating an aircraft the major portion of which has been fabricated and assembled by persons who undertook the construction project solely for their own education or recreation. (h) <E T="03">Operating kit-built aircraft.</E> Operating a primary category aircraft that meets the criteria of § 21.24(a)(1) that was assembled by a person from a kit manufactured by the holder of a production certificate for that kit, without the supervision and quality control of the production certificate holder under § 21.184(a). <CITA>[Amdt. 21-21, 38 FR 6858, May 7, 1968, as amended by Amdt. 21-57, 49 FR 39651, Oct. 9, 1984; Amdt. 21-70, 57 FR 41369, Sept. 9, 1992]</CITA> </SECTION> <SECTION> <PRTPAGE P="131"/> <SECTNO>§ 21.193</SECTNO> <SUBJECT>Experimental certificates: general.</SUBJECT> An applicant for an experimental certificate must submit the following information: (a) A statement, in a form and manner prescribed by the Administrator setting forth the purpose for which the aircraft is to be used. (b) Enough data (such as photographs) to identify the aircraft. (c) Upon inspection of the aircraft, any pertinent information found necessary by the Administrator to safeguard the general public. (d) In the case of an aircraft to be used for experimental purposes— (1) The purpose of the experiment; (2) The estimated time or number of flights required for the experiment; (3) The areas over which the experiment will be conducted; and (4) Except for aircraft converted from a previously certificated type without appreciable change in the external configuration, three-view drawings or three-view dimensioned photographs of the aircraft. </SECTION> <SECTION> <SECTNO>§ 21.195</SECTNO> <SUBJECT>Experimental certificates: Aircraft to be used for market surveys, sales demonstrations, and customer crew training.</SUBJECT> (a) A manufacturer of aircraft manufactured within the United States may apply for an experimental certificate for an aircraft that is to be used for market surveys, sales demonstrations, or customer crew training. (b) A manufacturer of aircraft engines who has altered a type certificated aircraft by installing different engines, manufactured by him within the United States, may apply for an experimental certificate for that aircraft to be used for market surveys, sales demonstrations, or customer crew training, if the basic aircraft, before alteration, was type certificated in the normal, acrobatic, commuter, or transport category. (c) A person who has altered the design of a type certificated aircraft may apply for an experimental certificate for the altered aircraft to be used for market surveys, sales demonstrations, or customer crew training if the basic aircraft, before alteration, was type certificated in the normal, utility, acrobatic, or transport category. (d) An applicant for an experimental certificate under this section is entitled to that certificate if, in addition to meeting the requirements of § 21.193— (1) He has established an inspection and maintenance program for the continued airworthiness of the aircraft; and (2) He shows that the aircraft has been flown for at least 50 hours, or for at least 5 hours if it is a type certificated aircraft which has been modified. <CITA>[Amdt. 21-21, 33 FR 6858, May 7, 1968, as amended by Amdt. 21-28, 35 FR 2818, Feb. 11, 1970; Amdt. 21-57, 49 FR 39651, Oct. 9, 1984; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.197</SECTNO> <SUBJECT>Special flight permits.</SUBJECT> (a) A special flight permit may be issued for an aircraft that may not currently meet applicable airworthiness requirements but is capable of safe flight, for the following purposes: (1) Flying the aircraft to a base where repairs, alterations, or maintenance are to be performed, or to a point of storage. (2) Delivering or exporting the aircraft. (3) Production flight testing new production aircraft. (4) Evacuating aircraft from areas of impending danger. (5) Conducting customer demonstration flights in new production aircraft that have satisfactorily completed production flight tests. (b) A special flight permit may also be issued to authorize the operation of an aircraft at a weight in excess of its maximum certificated takeoff weight for flight beyond the normal range over water, or over land areas where adequate landing facilities or appropriate fuel is not available. The excess weight that may be authorized under this paragraph is limited to the additional fuel, fuel-carrying facilities, and navigation equipment necessary for the flight. (c) Upon application, as prescribed in §§ 121.79, 127.27, and 135.17 of this chapter, a special flight permit with a continuing authorization may be issued for aircraft that may not meet applicable airworthiness requirements but are <PRTPAGE P="132"/>capable of safe flight for the purpose of flying aircraft to a base where maintenance or alterations are to be performed. The permit issued under this paragraph is an authorization, including conditions and limitations for flight, which is set forth in the certificate holder's operations specifications. The permit issued under this paragraph may be issued to— (1) Certificate holders authorized to conduct operations under Part 121 or Part 127 of this chapter; or (2) Certificate holders authorized to conduct operations under Part 135 for those aircraft they operate and maintain under a continuous airworthiness maintenance program prescribed by § 135.411 (a)(2) or (b) of that part. <FP>The permit issued under this paragraph is an authorization, including any conditions and limitations for flight, which is set forth in the certificate holder's operations specifications.</FP> <CITA>[Doc. No. 5085, 29 FR 14570, Oct. 24, 1964, as amended by Amdt. 21-21, 33 FR 6859, May 7, 1968; Amdt. 21—51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-54, 46 FR 37878, July 23, 1981]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.199</SECTNO> <SUBJECT>Issue of special flight permits.</SUBJECT> (a) Except as provided in § 21.197(c), an applicant for a special flight permit must submit a statement in a form and manner prescribed by the Administrator, indicating— (1) The purpose of the flight. (2) The proposed itinerary. (3) The crew required to operate the aircraft and its equipment, e.g., pilot, co-pilot, navigator, etc. (4) The ways, if any, in which the aircraft does not comply with the applicable airworthiness requirements. (5) Any restriction the applicant considers necessary for safe operation of the aircraft. (6) Any other information considered necessary by the Administrator for the purpose of prescribing operating limitations. (b) The Administrator may make, or require the applicant to make appropriate inspections or tests necessary for safety. <CITA>[Doc. No. 5085, 29 FR 14570, Oct. 24, 1964, as amended by Amdt. 21-21, 33 FR 6859, May 7, 1968; Amdt. 21-22, 33 FR 11901, Aug. 22, 1968]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart I—Provisional Airworthiness Certificates</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14571, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.211</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the issue of provisional airworthiness certificates. </SECTION> <SECTION> <SECTNO>§ 21.213</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) A manufacturer who is a United States citizen may apply for a Class I or Class II provisional airworthiness certificate for aircraft manufactured by him within the U.S. (b) Any holder of an air carrier operating certificate under Part 121 or Part 127 of this chapter who is a United States citizen may apply for a Class II provisional airworthiness certificate for transport category aircraft that meet either of the following: (1) The aircraft has a current Class II provisional type certificate or an amendment thereto. (2) The aircraft has a current provisional amendment to a type certificate that was preceded by a corresponding Class II provisional type certificate. (c) An aircraft engine manufacturer who is a United States citizen and who has altered a type certificated aircraft by installing different type certificated engines, manufactured by him within the United States, may apply for a Class I provisional airworthiness certificate for that aircraft, if the basic aircraft, before alteration, was type certificated in the normal, utility, acrobatic, commuter, or transport category. <CITA>[Doc. No. 5085, 29 FR 14571, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.215</SECTNO> <SUBJECT>Application.</SUBJECT> Applications for provisional airworthiness certificates must be submitted to the Manufacturing Inspection District Office in the geographic area in which the manufacturer or air carrier is located. The application must be accompanied by the pertinent information specified in this subpart. <CITA>[Amdt. 21-67, 54 FR 39291, Sept. 25, 1989; 54 FR 52872, Dec. 22, 1989]</CITA> </SECTION> <SECTION> <PRTPAGE P="133"/> <SECTNO>§ 21.217</SECTNO> <SUBJECT>Duration.</SUBJECT> Unless sooner surrendered, superseded, revoked, or otherwise terminated, provisional airworthiness certificates are effective for the duration of the corresponding provisional type certificate, amendment to a provisional type certificate, or provisional amendment to the type certificate. </SECTION> <SECTION> <SECTNO>§ 21.219</SECTNO> <SUBJECT>Transferability.</SUBJECT> Class I provisional airworthiness certificates are not transferable. Class II provisional airworthiness certificates may be transferred to an air carrier eligible to apply for a certificate under § 21.213(b). </SECTION> <SECTION> <SECTNO>§ 21.221</SECTNO> <SUBJECT>Class I provisional airworthiness certificates.</SUBJECT> (a) Except as provided in § 21.225, an applicant is entitled to a Class I provisional airworthiness certificate for an aircraft for which a Class I provisional type certificate has been issued if— (1) He meets the eligibility requirements of § 21.213 and he complies with this section; and (2) The Administrator finds that there is no feature, characteristic or condition of the aircraft that would make the aircraft unsafe when operated in accordance with the limitations established in §§ 21.81(e) and 91.317 of this subchapter. (b) The manufacturer must hold a provisional type certificate for the aircraft. (c) The manufacturer must submit a statement that the aircraft conforms to the type design corresponding to the provisional type certificate and has been found by him to be in safe operating condition under all applicable limitations. (d) The aircraft must be flown at least five hours by the manufacturer. (e) The aircraft must be supplied with a provisional aircraft flight manual or other document and appropriate placards containing the limitations established by §§ 21.81(e) and 91.317. <CITA>[Doc. No. 5085, 29 FR 14571, Oct. 24, 1964, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]s</CITA> </SECTION> <SECTION> <SECTNO>§ 21.223</SECTNO> <SUBJECT>Class II provisional airworthiness certificates.</SUBJECT> (a) Except as provided in § 21.225, an applicant is entitled to a Class II provisional airworthiness certificate for an aircraft for which a Class II provisional type certificate has been issued if— (1) He meets the eligibility requirements of § 21.213 and he complies with this section; and (2) The Administrator finds that there is no feature, characteristic, or condition of the aircraft that would make the aircraft unsafe when operated in accordance with the limitations established in §§ 21.83(h), 91.317, and 121.207 of this chapter. (b) The applicant must show that a Class II provisional type certificate for the aircraft has been issued to the manufacturer. (c) The applicant must submit a statement by the manufacturer that the aircraft has been manufactured under a quality control system adequate to ensure that the aircraft conforms to the type design corresponding with the provisional type certificate. (d) The applicant must submit a statement that the aircraft has been found by him to be in a safe operating condition under the applicable limitations. (e) The aircraft must be flown at least five hours by the manufacturer. (f) The aircraft must be supplied with a provisional aircraft flight manual containing the limitations established by §§ 21.83(h), 91.317, and 121.207 of this chapter. <CITA>[Doc. No. 5085, 29 FR 14571, Oct. 24, 1964, as amended by Amdt. 21-12, 31 FR 13389, Oct. 15, 1966; Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.225</SECTNO> <SUBJECT>Provisional airworthiness certificates corresponding with provisional amendments to type certificates.</SUBJECT> (a) An applicant is entitled to a Class I or a Class II provisional airworthiness certificate, for an aircraft, for which a provisional amendment to the type certificate has been issued, if— (1) He meets the eligibility requirements of § 21.213 and he complies with this section; and (2) The Administrator finds that there is no feature, characteristic, or condition of the aircraft, as modified in <PRTPAGE P="134"/>accordance with the provisionally amended type certificate, that would make the aircraft unsafe when operated in accordance with the applicable limitations established in §§ 21.85(g), 91.317, and 121.207 of this chapter. (b) The applicant must show that the modification was made under a quality control system adequate to ensure that the modification conforms to the provisionally amended type certificate. (c) The applicant must submit a statement that the aircraft has been found by him to be in a safe operating condition under the applicable limitations. (d) The aircraft must be flown at least five hours by the manufacturer. (e) The aircraft must be supplied with a provisional aircraft flight manual or other document and appropriate placards containing the limitations required by §§ 21.85(g), 91.317, and 121.207 of this chapter. <CITA>[Doc. No. 5085, 29 FR 14571, Oct. 24, 1964, as amended by Amdt. 21-12, 31 FR 13389, Oct. 15, 1966; Amdt. 21-66, 54 FR 34329, Aug. 18, 1989]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart J—Delegation Option Authorization Procedures</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.231</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedures for— (a) Obtaining and using a delegation option authorization for type, production, and airworthiness certification (as applicable) of— (1) Small airplanes and small gliders; (2) Commuter category airplanes; (3) Normal category rotorcraft; (4) Turbojet engines of not more than 1,000 pounds thrust; (5) Turbopropeller and reciprocating engines of not more than 500 brake horsepower; and (6) Propellers manufactured for use on engines covered by paragraph (a)(4) of this section; and (b) Issuing airworthiness approval tags for engines, propellers, and parts of products covered by paragraph (a) of this section. <CITA>[Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, as amended by Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.235</SECTNO> <SUBJECT>Application.</SUBJECT> (a) An application for a delegation option authorization must be submitted, in a form and manner prescribed by the Administrator, to the Aircraft Certification Office for the area in which the manufacturer is located. (b) The application must include the names, signatures, and titles of the persons for whom authorization to sign airworthiness certificates, repair and alteration forms, and inspection forms is requested. <CITA>[Doc. No. 5085, 29 FR 14574, Oct. 24, 1964, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.239</SECTNO> <SUBJECT>Eligibility.</SUBJECT> To be eligible for a delegation option authorization, the applicant must— (a) Hold a current type certificate, issued to him under the standard procedures, for a product type certificated under the same part as the products for which the delegation option authorization is sought; (b) Hold a current production certificate issued under the standard procedures; (c) Employ a staff of engineering, flight test, production and inspection personnel who can determine compliance with the applicable airworthiness requirements of this chapter; and (d) Meet the requirements of this subpart. </SECTION> <SECTION> <SECTNO>§ 21.243</SECTNO> <SUBJECT>Duration.</SUBJECT> A delegation option authorization is effective until it is surrendered or the Administrator suspends, revokes, or otherwise terminates it. </SECTION> <SECTION> <SECTNO>§ 21.245</SECTNO> <SUBJECT>Maintenance of eligibility.</SUBJECT> The holder of a delegation option authorization shall continue to meet the requirements for issue of the authorization or shall notify the Administrator within 48 hours of any change (including a change of personnel) that <PRTPAGE P="135"/>could affect the ability of the holder to meet those requirements. </SECTION> <SECTION> <SECTNO>§ 21.247</SECTNO> <SUBJECT>Transferability.</SUBJECT> A delegation option authorization is not transferable. </SECTION> <SECTION> <SECTNO>§ 21.249</SECTNO> <SUBJECT>Inspections.</SUBJECT> Upon request, each holder of a delegation option authorization and each applicant shall let the Administrator inspect his organization, facilities, product, and records. </SECTION> <SECTION> <SECTNO>§ 21.251</SECTNO> <SUBJECT>Limits of applicability.</SUBJECT> (a) Delegation option authorizations apply only to products that are manufactured by the holder of the authorization. (b) Delegation option authorizations may be used for— (1) Type certification; (2) Changes in the type design of products for which the manufacturer holds, or obtains, a type certificate; (3) The amendment of a production certificate held by the manufacturer to include additional models or additional types for which he holds or obtains a type certificate; and (4) The issue of— (i) Experimental certificates for aircraft for which the manufacturer has applied for a type certificate or amended type certificate under § 21.253, to permit the operation of those aircraft for the purpose of research and development, crew training, market surveys, or the showing of compliance with the applicable airworthiness requirements; (ii) Airworthiness certificates (other than experimental certificates) for aircraft for which the manufacturer holds a type certificate and holds or is in the process of obtaining a production certificate; (iii) Airworthiness approval tags (FAA Form 8130-3) for engines and propellers for which the manufacturer holds a type certificate and holds or is in the process of obtaining a production certificate; and (iv) Airworthiness approval tags (FAA Form 8130-3) for parts of products covered by this section. (c) Delegation option procedures may be applied to one or more types selected by the manufacturer, who must notify the FAA of each model, and of the first serial number of each model manufactured by him under the delegation option procedures. Other types or models may remain under the standard procedures. (d) Delegation option authorizations are subject to any additional limitations prescribed by the Administrator after inspection of the applicant's facilities or review of the staff qualifications. <CITA>[Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, as amended by Amdt. 21-31, 35 FR 7292, May 9, 1970; Amdt. 21-43, 40 FR 2576, Jan. 14, 1975]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.253</SECTNO> <SUBJECT>Type certificates: application.</SUBJECT> (a) To obtain, under the delegation option authorization, a type certificate for a new product or an amended type certificate, the manufacturer must submit to the Administrator— (1) An application for a type certificate (FAA Form 312); (2) A statement listing the airworthiness requirements of this chapter (by part number and effective date) that the manufacturer considers applicable; (3) After determining that the type design meets the applicable requirements, a statement certifying that this determination has been made; (4) After placing the required technical data and type inspection report in the technical data file required by § 21.293(a)(1)(i), a statement certifying that this has been done; (5) A proposed type certificate data sheet; and (6) An Aircraft Flight Manual (if required) or a summary of required operating limitations and other information necessary for safe operation of the product. </SECTION> <SECTION> <SECTNO>§ 21.257</SECTNO> <SUBJECT>Type certificates: issue.</SUBJECT> An applicant is entitled to a type certificate for a product manufactured under a delegation option authorization if the Administrator finds that the product meets the applicable airworthiness, noise, fuel venting, and exhaust emission requirements (including applicable acoustical change or emissions change requirements in the case of changes in type design). <CITA>[Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <PRTPAGE P="136"/> <SECTNO>§ 21.261</SECTNO> <SUBJECT>Equivalent safety provisions.</SUBJECT> The manufacturer shall obtain the Administrator's concurrence on the application of all equivalent safety provisions applied under § 21.21. </SECTION> <SECTION> <SECTNO>§ 21.267</SECTNO> <SUBJECT>Production certificates.</SUBJECT> To have a new model or new type certificate listed on his production certificate (issued under Subpart G of this part), the manufacturer must submit to the Administrator— (a) An application for an amendment to the production certificate; (b) After determining that the production certification requirements of Subpart G, with respect to the new model or type, are met, a statement certifying that this determination has been made; (c) A statement identifying the type certificate number under which the product is being manufactured; and (d) After placing the manufacturing and quality control data required by § 21.143 with the data required by § 21.293(a)(1)(ii), a statement certifying that this has been done. </SECTION> <SECTION> <SECTNO>§ 21.269</SECTNO> <SUBJECT>Export airworthiness approvals.</SUBJECT> The manufacturer may issue export airworthiness approvals. </SECTION> <SECTION> <SECTNO>§ 21.271</SECTNO> <SUBJECT>Airworthiness approval tags.</SUBJECT> (a) A manufacturer may issue an airworthiness approval tag (FAA Form 8130-3) for each engine and propeller covered by § 21.251(b)(4), and may issue an airworthiness approval tag for parts of each product covered by that section, if he finds, on the basis of inspection and operation tests, that those products conform to a type design for which he holds a type certificate and are in condition for safe operation. (b) When a new model has been included on the Production Limitation Record, the production certification number shall be stamped on the engine or propeller identification data place instead of issuing an airworthiness approval tag. <CITA>[Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, as amended by Amdt. 21-43, 40 FR 2577, Jan. 14, 1975]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.273</SECTNO> <SUBJECT>Airworthiness certificates other than experimental.</SUBJECT> (a) The manufacturer may issue an airworthiness certificate for aircraft manufactured under a delegation option authorization if he finds, on the basis of the inspection and production flight check, that each aircraft conforms to a type design for which he holds a type certificate and is in a condition for safe operation. (b) The manufacturer may authorize any employee to sign airworthiness certificates if that employee— (1) Performs, or is in direct charge of, the inspection specified in paragraph (a) of this section; and (2) Is listed on the manufacturer's application for the delegation option authorization, or on amendments thereof. <CITA>[Amdt. 21-5, 30 FR 11375, Sept. 8, 1965, as amended by Amdt. 21-18, 32 FR 15472, Nov. 7, 1967]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.275</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> (a) The manufacturer shall, before issuing an experimental certificate, obtain from the Administration any limitations and conditions that the Administrator considers necessary for safety. (b) For experimental certificates issued by the manufacturer, under this subpart, for aircraft for which the manufacturer holds the type certificate and which have undergone changes to the type design requiring flight test, the manufacturer may prescribe any operating limitations that he considers necessary. </SECTION> <SECTION> <SECTNO>§ 21.277</SECTNO> <SUBJECT>Data review and service experience.</SUBJECT> (a) If the Administrator finds that a product for which a type certificate was issued under this subpart does not meet the applicable airworthiness requirements, or that an unsafe feature or characteristic caused by a defect in design or manufacture exists, the manufacturer, upon notification by the Administrator, shall investigate the matter and report to the Administrator the results of the investigation and the action, if any, taken or proposed. (b) If corrective action by the user of the product is necessary for safety because of any noncompliance or defect specified in paragraph (a) of this section, the manufacturer shall submit <PRTPAGE P="137"/>the information necessary for the issue of an Airworthiness Directive under Part 39. </SECTION> <SECTION> <SECTNO>§ 21.289</SECTNO> <SUBJECT>Major repairs, rebuilding and alteration.</SUBJECT> For types covered by a delegation option authorization, a manufacturer may— (a) After finding that a major repair or major alteration meets the applicable airworthiness requirements of this chapter, approve that repair or alteration; and (b) Authorize any employee to execute and sign FAA Form 337 and make required log book entries if that employee— (1) Inspects, or is in direct charge of inspecting, the repair, rebuilding, or alteration; and (2) Is listed on the application for the delegation option authorization, or on amendments thereof. </SECTION> <SECTION> <SECTNO>§ 21.293</SECTNO> <SUBJECT>Current records.</SUBJECT> (a) The manufacturer shall maintain at his factory, for each product type certificated under a delegation option authorization, current records containing the following: (1) For the duration of the manufacturing operating under the delegation option authorization— (i) A technical data file that includes the type design drawings, specifications, reports on tests prescribed by this part, and the original type inspection report and amendments to that report; (ii) The data (including amendments) required to be submitted with the original application for each production certificate; and (iii) A record of any rebuilding and alteration performed by the manufacturer on products manufactured under the delegation option authorization. (2) For 2 years— (i) A complete inspection record for each product manufactured, by serial number, and data covering the processes and tests to which materials and parts are subjected; and (ii) A record of reported service difficulties. (b) The records and data specified in paragraph (a) of this section shall be— (1) Made available, upon the Administrator's request, for examination by the Administrator at any time; and (2) Identified and sent to the Administrator as soon as the manufacturer no longer operates under the delegation option procedures. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart K—Approval of Materials, Parts, Processes, and Appliances</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 5085, 29 FR 14574, Oct. 24, 1964, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.301</SECTNO> <SUBJECT>Applicability.</SUBJECT> This subpart prescribes procedural requirements for the approval of certain materials, parts, processes, and appliances. </SECTION> <SECTION> <SECTNO>§ 21.303</SECTNO> <SUBJECT>Replacement and modification parts.</SUBJECT> (a) Except as provided in paragraph (b) of this section, no person may produce a modification or replacement part for sale for installation on a type certificated product unless it is produced pursuant to a Parts Manufacturer Approval issued under this subpart. (b) This section does not apply to the following: (1) Parts produced under a type or production certificate. (2) Parts produced by an owner or operator for maintaining or altering his own product. (3) Parts produced under an FAA Technical Standard Order. (4) Standard parts (such as bolts and nuts) conforming to established industry or U.S. specifications. (c) An application for a Parts Manufacturer Approval is made to the Manager of the Aircraft Certification Office for the geographic area in which the manufacturing facility is located and must include the following: (1) The identity of the product on which the part is to be installed. (2) The name and address of the manufacturing facilities at which these parts are to be manufactured. (3) The design of the part, which consists of— (i) Drawings and specifications necessary to show the configuration of the part; and<PRTPAGE P="138"/> (ii) Information on dimensions, materials, and processes necessary to define the structural strength of the part. (4) Test reports and computations necessary to show that the design of the part meets the airworthiness requirements of the Federal Aviation Regulations applicable to the product on which the part is to be installed, unless the applicant shows that the design of the part is identical to the design of a part that is covered under a type certificate. If the design of the part was obtained by a licensing agreement, evidence of that agreement must be furnished. (d) An applicant is entitled to a Parts Manufacturer Approval for a replacement or modification part if— (1) The Administrator finds, upon examination of the design and after completing all tests and inspections, that the design meets the airworthiness requirements of the Federal Aviation Regulations applicable to the product on which the part is to be installed; and (2) He submits a statement certifying that he has established the fabrication inspection system required by paragraph (h) of this section. (e) Each applicant for a Parts Manufacturer Approval must allow the Administrator to make any inspection or test necessary to determine compliance with the applicable Federal Aviation Regulations. However, unless otherwise authorized by the Administrator— (1) No part may be presented to the Administrator for an inspection or test unless compliance with paragraphs (f)(2) through (4) of this section has been shown for that part; and (2) No change may be made to a part between the time that compliance with paragraphs (f)(2) through (4) of this section is shown for that part and the time that the part is presented to the Administrator for the inspection or test. (f) Each applicant for a Parts Manufacturer Approval must make all inspections and tests necessary to determine— (1) Compliance with the applicable airworthiness requirements; (2) That materials conform to the specifications in the design; (3) That the part conforms to the drawings in the design; and (4) That the fabrication processes, construction, and assembly conform to those specified in the design. (g) The Administrator does not issue a Parts Manufacturer Approval if the manufacturing facilities for the part are located outside of the United States, unless the Administrator finds that the location of the manufacturing facilities places no burden on the FAA in administering applicable airworthiness requirements. (h) Each holder of a Parts Manufacturer Approval shall establish and maintain a fabrication inspection system that ensures that each completed part conforms to its design data and is safe for installation on applicable type certificated products. The system shall include the following: (1) Incoming materials used in the finished part must be as specified in the design data. (2) Incoming materials must be properly identified if their physical and chemical properties cannot otherwise be readily and accurately determined. (3) Materials subject to damage and deterioration must be suitably stored and adequately protected. (4) Processes affecting the quality and safety of the finished product must be accomplished in accordance with acceptable specifications. (5) Parts in process must be inspected for conformity with the design data at points in production where accurate determination can be made. Statistical quality control procedures may be employed where it is shown that a satisfactory level of quality will be maintained for the particular part involved. (6) Current design drawings must be readily available to manufacturing and inspection personnel, and used when necessary. (7) Major changes to the basic design must be adequately controlled and approved before being incorporated in the finished part. (8) Rejected materials and components must be segregated and identified in such a manner as to preclude their use in the finished part. (9) Inspection records must be maintained, identified with the completed part, where practicable, and retained in <PRTPAGE P="139"/>the manufacturer's file for a period of at least 2 years after the part has been completed. (i) A Parts Manufacturer Approval issued under this section is not transferable and is effective until surrendered or withdrawn or otherwise terminated by the Administrator. (j) The holder of a Parts Manufacturer Approval shall notify the FAA in writing within 10 days from the date the manufacturing facility at which the parts are manufactured is relocated or expanded to include additional facilities at other locations. (k) Each holder of a Parts Manufacturer Approval shall determine that each completed part conforms to the design data and is safe for installation on type certificated products. <CITA>[Amdt. 21-38, 37 FR 10659, May 26, 1972, as amended by Amdt. 21-41, 39 FR 41965, Dec. 4, 1974; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.305</SECTNO> <SUBJECT>Approval of materials, parts, processes, and appliances.</SUBJECT> Whenever a material, part, process, or appliance is required to be approved under this chapter, it may be approved— (a) Under a Parts Manufacturer Approval issued under § 21.303; (b) Under a Technical Standard Order issued by the Administrator. Advisory Circular 20-110 contains a list of Technical Standard Orders that may be used to obtain approval. Copies of the Advisory Circular may be obtained from the U.S. Department of Transportation, Publication Section (M-443.1), Washington, D.C. 20590; (c) In conjunction with type certification procedures for a product; or (d) In any other manner approved by the Administrator. <CITA>[Amdt. 21-38, 37 FR 10659, May 26, 1972, as amended by Amdt. 21-50, 45 FR 38346, June 9, 1980]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart L—Export Airworthiness Approvals</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 21-2, 30 FR 8465, July 2, 1965, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.321</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart prescribes— (1) Procedural requirements for the issue of export airworthiness approv-als; and (2) Rules governing the holders of those approvals. (b) For the purposes of this subpart— (1) A Class I product is a complete aircraft, aircraft engine, or propeller, which— (i) Has been type certificated in accordance with the applicable Federal Aviation Regulations and for which Federal Aviation Specifications or type certificate data sheets have been issued; or (ii) Is identical to a type certificated product specified in paragraph (b)(1)(i) of this section in all respects except as is otherwise acceptable to the civil aviation authority of the importing state. (2) A Class II product is a major component of a Class I product (e.g., wings, fuselages, empennage assemblies, landing gears, power transmissions, control surfaces, etc), the failure of which would jeopardize the safety of a Class I product; or any part, material, or appliance, approved and manufactured under the Technical Standard Order (TSO) system in the “C” series. (3) A Class III product is any part or component which is not a Class I or Class II product and includes standard parts, i.e., those designated as AN, NAS, SAE, etc. (4) The words “newly overhauled” when used to describe a product means that the product has not been operated or placed in service, except for functional testing, since having been overhauled, inspected and approved for return to service in accordance with the applicable Federal Aviation Regulations. <CITA>[Amdt. 21-2, 30 FR 11375, July 2, 1965, as amended by Amdt. 21-48, 44 FR 15649, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.323</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) Any exporter or his authorized representative may obtain an export airworthiness approval for a Class I or Class II product. (b) Any manufacturer may obtain an export airworthiness approval for a Class III product if the manufacturer— (1) Has in his employ a designated representative of the Administrator <PRTPAGE P="140"/>who has been authorized to issue that approval; and (2) Holds for that product— (i) A production certificate; (ii) An approved production inspection system; (iii) An FAA Parts Manufacturer Approval (PMA); or (iv) A Technical Standard Order authorization. </SECTION> <SECTION> <SECTNO>§ 21.325</SECTNO> <SUBJECT>Export airworthiness approvals.</SUBJECT> (a) <E T="03">Kinds of approvals.</E> (1) Export airworthiness approval of Class I products is issued in the form of Export Certificates of Airworthiness, FAA Form 8130-4. Such a certificate does not authorize the operation of aircraft. (2) Export airworthiness approval of Class II and III products is issued in the form of Airworthiness Approval Tags, FAA Form 8130-3. (b) <E T="03">Products which may be approved.</E> Export airworthiness approvals are issued for— (1) New aircraft that are assembled and that have been flight-tested, and other Class I products located in the United States, except that export airworthiness approval may be issued for any of the following without assembly or flight-test: (i) A small airplane type certificated under Part 3 or 4a of the Civil Air Regulations, or Part 23 of the Federal Aviation Regulations, and manufactured under a production certificate; (ii) A glider type certificated under § 21.23 of this part and manufactured under a production certificate; or (iii) A normal category rotorcraft type certificated under Part 6 of the Civil Air Regulations or Part 27 of the Federal Aviation Regulations and manufactured under a production certificate. (2) Used aircraft possessing a valid U.S. airworthiness certificate, or other used Class I products that have been maintained in accordance with the applicable CAR's or FAR's and are located in a foreign country, if the Administrator finds that the location places no undue burden upon the FAA in administering the provisions of this regulation. (3) Class II and III products that are manufactured and located in the United States. (c) <E T="03">Export airworthiness approval exceptions.</E> If the export airworthiness approval is issued on the basis of a written statement by the importing state as provided for in § 21.327(e)(4), the requirements that are not met and the differences in configuration, if any, between the product to be exported and the related type certificated product, are listed on the export airworthiness approval as exceptions. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Amdt. 21-14, 32 FR 2999, Feb. 17, 1967; Amdt. 21-43, 40 FR 2577, Jan. 14, 1975; Amdt. 21-48, 44 FR 15649, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.327</SECTNO> <SUBJECT>Application.</SUBJECT> (a) Except as provided in paragraph (b) of this section, an application for export airworthiness approval for a Class I or Class II product is made on a form and in a manner prescribed by the Administrator and is submitted to the appropriate Flight Standards District Office or to the nearest international field office. (b) A manufacturer holding a production certificate may apply orally to the appropriate Flight Standards District Office or the nearest international field office for export airworthiness approval of a Class II product approved under his production certificate. (c) Application for export airworthiness approval of Class III products is made to the designated representative of the Administrator authorized to issue those approvals. (d) A separate application must be made for— (1) Each aircraft; (2) Each engine and propeller, except that one application may be made for more than one engine or propeller, if all are of the same type and model and are exported to the same purchaser and country; and (3) Each type of Class II product, except that one application may be used for more than one type of Class II product when— (i) They are separated and identified in the application as to the type and model of the related Class I product; and<PRTPAGE P="141"/> (ii) They are to be exported to the same purchaser and country. (e) Each application must be accompanied by a written statement from the importing country that will validate the export airworthiness approval if the product being exported is— (1) An aircraft manufactured outside the United States and being exported to a country with which the United States has a reciprocal agreement concerning the validation of export certificates; (2) An unassembled aircraft which has not been flight-tested; (3) A product that does not meet the special requirement of the importing country; or (4) A product that does not meet a requirement specified in §§ 21.329, 21.331, or 21.333, as applicable, for the issuance of an export airworthiness approval. The written statement must list the requirements not met. (f) Each application for export airworthiness approval of a Class I product must include, as applicable: (1) A Statement of Conformity, FAA Form 8130-9, for each new product that has not been manufactured under a production certificate. (2) A weight and balance report, with a loading schedule when applicable, for each aircraft in accordance with Part 43 of this chapter. For transport aircraft and commuter category airplanes this report must be based on an actual weighing of the aircraft within the preceding twelve months, but after any major repairs or alterations to the aircraft. Changes in equipment not classed as major changes that are made after the actual weighing may be accounted for on a “computed” basis and the report revised accordingly. Manufacturers of new nontransport category air-planes, normal category rotorcraft, and gliders may submit reports having computed weight and balance data, in place of an actual weighing of the aircraft, if fleet weight control procedures approved by the FAA have been established for such aircraft. In such a case, the following statement must be entered in each report: “The weight and balance data shown in this report are computed on the basis of Federal Aviation Administration approved procedures for establishing fleet weight averages.” The weight and balance report must include an equipment list showing weights and moment arms of all required and optional items of equipment that are included in the certificated empty weight. (3) A maintenance manual for each new product when such a manual is required by the applicable airworthiness rules. (4) Evidence of compliance with the applicable airworthiness directives. A suitable notation must be made when such directives are not complied with. (5) When temporary installations are incorporated in an aircraft for the purpose of export delivery, the application form must include a general description of the installations together with a statement that the installation will be removed and the aircraft restored to the approved configuration upon completion of the delivery flight. (6) Historical records such as aircraft and engine log books, repair and alteration forms, etc., for used aircraft and newly overhauled products. (7) For products intended for overseas shipment, the application form must describe the methods used, if any, for the preservation and packaging of such products to protect them against corrosion and damage while in transit or storage. The description must also indicate the duration of the effectiveness of such methods. (8) The Airplane or Rotorcraft Flight Manual when such material is required by the applicable airworthiness regulations for the particular aircraft. (9) A statement as to the date when title passed or is expected to pass to a foreign purchaser. (10) The data required by the special requirements of the importing country. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967; Amdt. 21-48, 44 FR 15650, Mar. 15, 1979; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.329</SECTNO> <SUBJECT>Issue of export certificates of airworthiness for Class I products.</SUBJECT> An applicant is entitled to an export certificate of airworthiness for a Class I product if that applicant shows at the time the product is submitted to the Administrator for export airworthiness approval that it meets the requirements of paragraphs (a) through (f) of <PRTPAGE P="142"/>this section, as applicable, except as provided in paragraph (g) of this section: (a) New or used aircraft manufactured in the United States must meet the airworthiness requirement for a standard U.S. airworthiness certificate under § 21.183, or meet the airworthiness certification requirements for a “restricted” airworthiness certificate under § 21.185. (b) New or used aircraft manufactured outside the United States must have a valid U.S. standard airworthiness certificate. (c) Used aircraft must have undergone an annual type inspection and be approved for return to service in accordance with Part 43 of this chapter. The inspection must have been performed and properly documented within 30 days before the date the application is made for an export certificate of airworthiness. In complying with this paragraph, consideration may be given to the inspections performed on an aircraft maintained in accordance with a continuous airworthiness maintenance program under Part 121 or 127 of this chapter or a progressive inspection program under Part 91 of this chapter, within the 30 days prior to the date the application is made for an export certificate of airworthiness. (d) New engines and propellers must conform to the type design and must be in a condition for safe operation. (e) Used engines and propellers which are not being exported as part of a certificated aircraft must have been newly overhauled. (f) The special requirements of the importing country must have been met. (g) A product need not meet a requirement specified in paragraphs (a) through (f) of this section, as applicable, if acceptable to the importing country and the importing country indicates that acceptability in accordance with § 21.327(e)(4) of this part. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Amdt. 21-8, 31 FR 2421, Feb. 5, 1966; Amdt. 21-9, 31 FR 3336, Mar. 3, 1966; Amdt. 21-48, 44 FR 15650, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.331</SECTNO> <SUBJECT>Issue of airworthiness approval tags for Class II products.</SUBJECT> (a) An applicant is entitled to an export airworthiness approval tag for Class II products if that applicant shows, except as provided in paragraph (b) of this section, that-- (1) The products are new or have been newly overhauled and conform to the approved design data; (2) The products are in a condition for safe operation; (3) The products are identified with at least the manufacturer's name, part number, model designation (when applicable), and serial number or equivalent; and (4) The products meet the special requirements of the importing country. (b) A product need not meet a requirement specified in paragraph (a) of this section if acceptable to the importing country and the importing country indicates that acceptability in accordance with § 21.327(e)(4) of this part. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, l965, as amended by Amdt. 21-48, 44 FR 15650, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.333</SECTNO> <SUBJECT>Issue of export airworthiness approval tags for Class III products.</SUBJECT> (a) An applicant is entitled to an export airworthiness approval tag for Class III products if that applicant shows, except as provided in paragraph (b) of this section, that— (1) The products conform to the approved design data applicable to the Class I or Class II product of which they are a part; (2) The products are in a condition for safe operation; and (3) The products comply with the special requirements of the importing country. (b) A product need not meet a requirement specified in paragraph (a) of this section if acceptable to the importing country and the importing country indicates that acceptability in accordance with § 21.327(e)(4) of this part. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, l965, as amended by Amdt. 21-48, 44 FR 15650, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <PRTPAGE P="143"/> <SECTNO>§ 21.335</SECTNO> <SUBJECT>Responsibilities of exporters.</SUBJECT> Each exporter receiving an export airworthiness approval for a product shall— (a) Forward to the air authority of the importing country all documents and information necessary for the proper operation of the products being exported, e.g., Flight Manuals, Maintenance Manuals, Service Bulletins, and assembly instructions, and such other material as is stipulated in the special requirements of the importing country. The documents, information, and material may be forwarded by any means consistent with the special requirements of the importing country; (b) Forward the manufacturer's assembly instructions and an FAA-approved flight test checkoff form to the air authority of the importing country when unassembled aircraft are being exported. These instructions must be in sufficient detail to permit whatever rigging, alignment, and ground testing is necessary to ensure that the aircraft will conform to the approved configuration when assembled; (c) Remove or cause to be removed any temporary installation incorporated on an aircraft for the purpose of export delivery and restore the aircraft to the approved configuration upon completion of the delivery flight; (d) Secure all proper foreign entry clearances from all the countries involved when conducting sales demonstrations or delivery flights; and (e) When title to an aircraft passes or has passed to a foreign purchaser— (1) Request cancellation of the U.S. registration and airworthiness certificates, giving the date of transfer of title, and the name and address of the foreign owner; (2) Return the Registration and Airworthiness Certificates, AC Form 8050.3 and FAA Form 8100-2, to the FAA; and (3) Submit a statement certifying that the United States’ identification and registration numbers have been removed from the aircraft in compliance with § 45.33. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Amdt. 21-48, 44 FR 15650, Mar. 15, 1979]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.337</SECTNO> <SUBJECT>Performance of inspections and overhauls.</SUBJECT> Unless otherwise provided for in this subpart, each inspection and overhaul required for export airworthiness approval of Class I and Class II products must be performed and approved by one of the following: (a) The manufacturer of the product. (b) An appropriately certificated domestic repair station. (c) An appropriately certificated foreign repair station having adequate overhaul facilities, and maintenance organization appropriate to the product involved, when the product is a Class I product located in a foreign country and an international office of Flight Standards Service has approved the use of such foreign repair station. (d) The holder of an inspection authorization as provided in Part 65 of this chapter. (e) An air carrier, when the product is one that the carrier has maintained under its own or another air carrier's continuous airworthiness maintenance program and maintenance manuals as provided in Part 121 or 127 of this chapter. (f) A commercial operator, when the product is one that the operator has maintained under its continuous airworthiness maintenance program and maintenance manual as provided in Part 121 of this chapter. <CITA>[Amdt. 21-2, 30 FR 8465, July 2, 1965, as amended by Amdt. 21-8, 31 FR 2421, Feb. 5, 1966]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.339</SECTNO> <SUBJECT>Special export airworthiness approval for aircraft.</SUBJECT> A special export certificate of airworthiness may be issued for an aircraft located in the United States that is to be flown to several foreign countries for the purpose of sale, without returning the aircraft to the United States for the certificate if— (a) The aircraft possesses either— (1) A standard U.S. certificate of airworthiness; or (2) A special U.S. certificate of airworthiness in the restricted category issued under § 21.185; (b) The owner files an application as required by § 21.327 except that items 3 and 4 of the application (FAA Form 8130-1) need not be completed;<PRTPAGE P="144"/> (c) The aircraft is inspected by the Administrator before leaving the United States and is found to comply with all the applicable requirements; (d) A list of foreign countries in which it is intended to conduct sales demonstrations, together with the expected dates and duration of such demonstration, is included in the application; (e) For each prospective importing country, the applicant shows that— (1) He has met that country's special requirements, other than those requiring that documents, information, and materials be furnished; and (2) He has the documents, information, and materials necessary to meet the special requirements of that country; and (f) All other requirements for the issuance of a Class I export certificate of airworthiness are met. <CITA>[Amdt. 21-12, 31 FR 12565, Sept. 23, 1966, as amended by Amdt. 21-43, 40 FR 2577, Jan. 14, 1975; Amdt. 21-55, 46 FR 44737, Sept. 8, 1981]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart M—Designated Alteration Station Authorization Procedures</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Amdt. 21-6, 30 FR 11379, Sept. 8, 1965; 30 FR 11849, Sept. 16, 1965, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.431</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart prescribes Designated Alteration Station (DAS) authorization procedures for— (1) Issuing supplemental type certificates; (2) Issuing experimental certificates; and (3) Amending standard airworthiness certificates. (b) This subpart applies to domestic repair stations, air carriers, commercial operators of large aircraft, and manufacturers of products. <CITA>[Amdt. 21-6, 30 FR 11379, Sept. 8, 1965; 30 FR 11849, Sept. 16, 1965, as amended by Amdt. 21-74, 62 FR 13253, Mar. 19, 1997]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.435</SECTNO> <SUBJECT>Application.</SUBJECT> The applicant for a DAS authorization must submit an application, in writing and signed by an official of the applicant, to the Aircraft Certification Office responsible for the geographic area in which the applicant is located. The application must contain— (a) The repair station certificate number held by the repair station applicant, and the current ratings covered by the certificate; (b) The air carrier or commercial operator operating certificate number held by the air carrier or commercial operator applicant, and the products that it may operate and maintain under the certificate; (c) A statement by the manufacturer applicant of the products for which he holds the type certificate; (d) The names, signatures, and titles of the persons for whom authorization to issue supplemental type certificates or experimental certificates, or amend airworthiness certificates, is requested; and (e) A description of the applicant's facilities, and of the staff with which compliance with § 21.439(a)(4) is to be shown. <CITA>[Amdt. 21-6, 30 FR 11379, Sept. 8, 1965; 30 FR 11849, Sept. 16, 1965, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.439</SECTNO> <SUBJECT>Eligibility.</SUBJECT> (a) To be eligible for a DAS authorization, the applicant must— (1) Hold a current domestic repair station certificate under Part 145, or air carrier or commercial operator operating certificate under Part 121; (2) Be a manufacturer of a product for which it has alteration authority under § 43.3(i) of this subchapter; (3) Have adequate maintenance facilities and personnel, in the United States, appropriate to the products that it may operate and maintain under its certificate; and (4) Employ, or have available, a staff of engineering, flight test, and inspection personnel who can determine compliance with the applicable airworthiness requirements of this chapter. (b) At least one member of the staff required by paragraph (a)(4) of this section must have all of the following qualifications: (1) A thorough working knowledge of the applicable requirements of this chapter.<PRTPAGE P="145"/> (2) A position, on the applicant's staff, with authority to establish alteration programs that ensure that altered products meet the applicable requirements of this chapter. (3) At least one year of satisfactory experience in direct contact with the FAA (or its predecessor agency (CAA)) while processing engineering work for type certification or alteration projects. (4) At least eight years of aeronautical engineering experience (which may include the one year required by paragraph (b)(3) of this section). (5) The general technical knowledge and experience necessary to determine that altered products, of the types for which a DAS authorization is requested, are in condition for safe operation. </SECTION> <SECTION> <SECTNO>§ 21.441</SECTNO> <SUBJECT>Procedure manual.</SUBJECT> (a) No DAS may exercise any authority under this subpart unless it submits, and obtains approval of, a procedure manual containing— (1) The procedures for issuing STCs; and (2) The names, signatures, and responsibilities of officials and of each staff member required by § 21.439(a)(4), identifying those persons who— (i) Have authority to make changes in procedures that require a revision to the procedure manual; and (ii) Are to conduct inspections (including conformity and compliance inspections) or approve inspection reports, prepare or approve data, plan or conduct tests, approve the results of tests, amend airworthiness certificates, issue experimental certificates, approve changes to operating limitations or Aircraft Flight Manuals, and sign supplemental type certificates. (b) No DAS may continue to perform any DAS function affected by any change in facilities or staff necessary to continue to meet the requirements of § 21.439, or affected by any change in procedures from those approved under paragraph (a) of this section, unless that change is approved and entered in the manual. For this purpose, the manual shall contain a log-of-revisions page with space for the identification of each revised item, page, or date, and the signature of the person approving the change for the Administrator. </SECTION> <SECTION> <SECTNO>§ 21.443</SECTNO> <SUBJECT>Duration.</SUBJECT> (a) A DAS authorization is effective until it is surrendered or the Administrator suspends, revokes, or otherwise terminates it. (b) The DAS shall return the authorization certificate to the Administrator when it is no longer effective. </SECTION> <SECTION> <SECTNO>§ 21.445</SECTNO> <SUBJECT>Maintenance of eligibility.</SUBJECT> The DAS shall continue to meet the requirements for issue of the authorization or shall notify the Administrator within 48 hours of any change (including a change of personnel) that could affect the ability of the DAS to meet those requirements. </SECTION> <SECTION> <SECTNO>§ 21.447</SECTNO> <SUBJECT>Transferability.</SUBJECT> A DAS authorization is not transferable. </SECTION> <SECTION> <SECTNO>§ 21.449</SECTNO> <SUBJECT>Inspections.</SUBJECT> Upon request, each DAS and each applicant shall let the Administrator inspect his facilities, products, and rec-ords. </SECTION> <SECTION> <SECTNO>§ 21.451</SECTNO> <SUBJECT>Limits of applicability.</SUBJECT> (a) DAS authorizations apply only to products— (1) Covered by the ratings of the repair station applicant; (2) Covered by the operating certificate and maintenance manual of the air carrier or commercial operator applicant; and (3) For which the manufacturer applicant has alteration authority under § 43.3(i) of this subchapter. (b) DAS authorizations may be used for— (1) The issue of supplemental type certificates; (2) The issue of experimental certificates for aircraft that— (i) Are altered by the DAS under a supplemental type certificate issued by the DAS; and (ii) Require flight tests in order to show compliance with the applicable airworthiness requirements of this chapter; and (3) The amendment of standard airworthiness certificates for aircraft altered under this subpart.<PRTPAGE P="146"/> (c) DAS authorizations are subject to any additional limitations prescribed by the Administrator after inspection of the applicant's facilities or review of the staff qualifications. (d) Notwithstanding any other provision of this subpart, a DAS may not issue a supplemental type certificate involving the exhaust emissions change requirements of part 34 or the acoustical change requirements of part 36 of this chapter until the Administrator finds that those requirements are met. <CITA>[Amdt. 21-6, 30 FR 11379, Sept. 8, 1965; 30 FR 11849, Sept. 16, 1965, as amended by Amdt. 21-42, 40 FR 1034, Jan. 6, 1975; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.461</SECTNO> <SUBJECT>Equivalent safety provisions.</SUBJECT> The DAS shall obtain the Administrator's concurrence on the application of all equivalent safety provisions applied under § 21.21. </SECTION> <SECTION> <SECTNO>§ 21.463</SECTNO> <SUBJECT>Supplemental type certificates.</SUBJECT> (a) For each supplemental type certificate issued under this subpart, the DAS shall follow the procedure manual prescribed in § 21.441 and shall, before issuing the certificate— (1) Submit to the Administrator a statement describing— (i) The type design change; (ii) The airworthiness requirements of this chapter (by part and effective date) that the DAS considers applicable; and (iii) The proposed program for meeting the applicable airworthiness requirements; (2) Find that each applicable airworthiness requirement is met; and (3) Find that the type of product for which the STC is to be issued, as modified by the supplemental type design data upon which the STC is based, is of proper design for safe operation. (b) Within 30 days after the date of issue of the STC, the DAS shall submit to the Administrator— (1) Two copies of the STC; (2) One copy of the design data approved by the DAS and referred to in the STC; (3) One copy of each inspection and test report; and (4) Two copies of each revision to the Aircraft Flight Manual or to the operating limitations, and any other information necessary for safe operation of the product. </SECTION> <SECTION> <SECTNO>§ 21.473</SECTNO> <SUBJECT>Airworthiness certificates other than experimental.</SUBJECT> For each amendment made to a standard airworthiness certificate under this subpart, the DAS shall follow the procedure manual prescribed in § 21.441 and shall, before making that amendment— (a) Complete each flight test necessary to meet the applicable airworthiness requirements of this chapter; (b) Find that each applicable airworthiness requirement of this chapter is met; and (c) Find that the aircraft is in condition for safe operation. </SECTION> <SECTION> <SECTNO>§ 21.475</SECTNO> <SUBJECT>Experimental certificates.</SUBJECT> The DAS shall, before issuing an experimental certificate, obtain from the Administrator any limitations and conditions that the Administrator considers necessary for safety. </SECTION> <SECTION> <SECTNO>§ 21.477</SECTNO> <SUBJECT>Data review and service experience.</SUBJECT> (a) If the Administrator finds that a product for which an STC was issued under this subpart does not meet the applicable airworthiness requirements, or that an unsafe feature or characteristic caused by a defect in design or manufacture exists, the DAS, upon notification by the Administrator, shall investigate the matter and report to the Administrator the results of the investigation and the action, if any, taken or proposed. (b) If corrective action by the user of the product is necessary for safety because of any noncompliance or defect specified in paragraph (a) of this section, the DAS shall submit the information necessary for the issue of an Airworthiness Directive under Part 39. </SECTION> <SECTION> <SECTNO>§ 21.493</SECTNO> <SUBJECT>Current records.</SUBJECT> (a) The DAS shall maintain, at its facility, current records containing— (1) For each product for which it has issued an STC under this subpart, a technical data file that includes any <PRTPAGE P="147"/>data and amendments thereto (including drawings, photographs, specifications, instructions, and reports) necessary for the STC; (2) A list of products by make, model, manufacturer's serial number and, if applicable, any FAA identification, that have been altered under the DAS authorization; and (3) A file of information from all available sources on alteration difficulties of products altered under the DAS authorization. (b) The records prescribed in paragraph (a) of this section shall be— (1) Made available by the DAS, upon the Administrator's request, for examination by the Administrator at any time; and (2) In the case of the data file prescribed in paragraph (a)(1) of this section, identified by the DAS and sent to the Administrator as soon as the DAS no longer operates under this subpart. </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart N—Approval of Engines, Propellers, Materials, Parts, and Appliances: Import</HD> <SECTION> <SECTNO>§ 21.500</SECTNO> <SUBJECT>Approval of engines and propellers.</SUBJECT> Each holder or licensee of a U.S. type certificate for an aircraft engine or propeller manufactured in a foreign country with which the United States has an agreement for the acceptance of those products for export and import, shall furnish with each such aircraft engine or propeller imported into this country, a certificate of airworthiness for export issued by the country of manufacture certifying that the individual aircraft engine or propeller— (a) Conforms to its U.S. type certificate and is in condition for safe operation; and (b) Has been subjected by the manufacturer to a final operational check. <CITA>[Amdt. 21-25, 34 FR 14068, Sept. 5, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.502</SECTNO> <SUBJECT>Approval of materials, parts, and appliances.</SUBJECT> (a) A material, part, or appliance, manufactured in a foreign country with which the United States has an agreement for the acceptance of those materials, parts, or appliances for export and import, is considered to meet the requirements for approval in the Federal Aviation Regulations when the country of manufacture issues a certificate of airworthiness for export certifying that the individual material, part, or appliance meets those requirements, unless the Administrator finds, based on the technical data submitted under paragraph (b) of this section, that the material, part, or appliance is otherwise not consistent with the intent of the Federal Aviation Regulations. (b) An applicant for approval of a material, part, or appliance must, upon request, submit to the Administrator any technical data respecting that material, part, or appliance. <CITA>[Amdt. 21-25, 34 FR 14068, Sept. 5, 1969]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart O—Technical Standard Order Authorizations</HD> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 19589, 45 FR 38346, June 9, 1980, unless otherwise noted. </SOURCE> <SECTION> <SECTNO>§ 21.601</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This subpart prescribes— (1) Procedural requirements for the issue of Technical Standard Order authorizations; (2) Rules governing the holders of Technical Standard Order authorizations; and (3) Procedural requirements for the issuance of a letter of Technical Standard Order design approval. (b) For the purpose of this subpart— (1) A Technical Standard Order (referred to in this subpart as “TSO”) is issued by the Administrator and is a minimum performance standard for specified articles (for the purpose of this subpart, articles means materials, parts, processes, or appliances) used on civil aircraft. (2) A TSO authorization is an FAA design and production approval issued to the manufacturer of an article which has been found to meet a specific TSO. (3) A letter of TSO design approval is an FAA design approval for a foreign-manufactured article which has been found to meet a specific TSO in accordance with the procedures of § 21.617. (4) An article manufactured under a TSO authorization, an FAA letter of <PRTPAGE P="148"/>acceptance as described in § 21.603(b), or an appliance manufactured under a letter of TSO design approval described in § 21.617 is an approved article or appliance for the purpose of meeting the regulations of this chapter that require the article to be approved. (5) An article manufacturer is the person who controls the design and quality of the article produced (or to be produced, in the case of an application), including the parts of them and any processes or services related to them that are procured from an outside source. (c) The Administrator does not issue a TSO authorization if the manufacturing facilities for the product are located outside of the United States, unless the Administrator finds that the location of the manufacturer's facilities places no undue burden on the FAA in administering applicable airworthiness requirements. </SECTION> <SECTION> <SECTNO>§ 21.603</SECTNO> <SUBJECT>TSO marking and privileges.</SUBJECT> (a) Except as provided in paragraph (b) of this section and § 21.617(c), no person may identify an article with a TSO marking unless that person holds a TSO authorization and the article meets applicable TSO performance standards. (b) The holder of an FAA letter of acceptance of a statement of conformance issued for an article before July 1, 1962, or any TSO authorization issued after July 1, 1962, may continue to manufacture that article without obtaining a new TSO authorization but shall comply with the requirements of §§ 21.3, 21.607 through 21.615, 21.619, and 21.621. (c) Notwithstanding paragraphs (a) and (b) of this section, after August 6, 1976, no person may identify or mark an article with any of the following TSO numbers: (1) TSO-C18, -C18a, -C18b, -C18c. (2) TSO-C24. (3) TSO-C33. (4) TSO-C61 or C61a. </SECTION> <SECTION> <SECTNO>§ 21.605</SECTNO> <SUBJECT>Application and issue.</SUBJECT> (a) The manufacturer (or an authorized agent) shall submit an application for a TSO authorization, together with the following documents, to the Manager of the Aircraft Certification Office for the geographic area in which the applicant is located: (1) A statement of conformance certifying that the applicant has met the requirements of this subpart and that the article concerned meets the applicable TSO that is effective on the date of application for that article. (2) One copy of the technical data required in the applicable TSO. (3) A description of its quality control system in the detail specified in § 21.143. In complying with this section, the applicant may refer to current quality control data filed with the FAA as part of a previous TSO authorization application. (b) When a series of minor changes in accordance with § 21.611 is anticipated, the applicant may set forth in its application the basic model number of the article and the part number of the components with open brackets after it to denote that suffix change letters or numbers (or combinations of them) will be added from time to time. (c) After receiving the application and other documents required by paragraph (a) of this section to substantiate compliance with this part, and after a determination has been made of its ability to produce duplicate articles under this part, the Administrator issues a TSO authorization (including all TSO deviations granted to the applicant) to the applicant to identify the article with the applicable TSO marking. (d) If the application is deficient, the applicant must, when requested by the Administrator, submit any additional information necessary to show compliance with this part. If the applicant fails to submit the additional information within 30 days after the Administrator's request, the application is denied and the applicant is so notified. (e) The Administrator issues or denies the application within 30 days after its receipt or, if additional information has been requested, within 30 days after receiving that information. <CITA>[Doc. No. 19589, 45 FR 38346, June 9, 1980, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <PRTPAGE P="149"/> <SECTNO>§ 21.607</SECTNO> <SUBJECT>General rules governing holders of TSO authorizations.</SUBJECT> Each manufacturer of an article for which a TSO authorization has been issued under this part shall— (a) Manufacture the article in accordance with this part and the applicable TSO; (b) Conduct all required tests and inspections and establish and maintain a quality control system adequate to ensure that the article meets the requirements of paragraph (a) of this section and is in condition for safe operation; (c) Prepare and maintain, for each model of each article for which a TSO authorization has been issued, a current file of complete technical data and records in accordance with § 21.613; and (d) Permanently and legibly mark each article to which this section applies with the following information: (1) The name and address of the manufacturer. (2) The name, type, part number, or model designation of the article. (3) The serial number or the date of manufacture of the article or both. (4) The applicable TSO number. </SECTION> <SECTION> <SECTNO>§ 21.609</SECTNO> <SUBJECT>Approval for deviation.</SUBJECT> (a) Each manufacturer who requests approval to deviate from any performance standard of a TSO shall show that the standards from which a deviation is requested are compensated for by factors or design features providing an equivalent level of safety. (b) The request for approval to deviate, together with all pertinent data, must be submitted to the Manager of the Aircraft Certification Office for the geographic area in which the manufacturer is located. If the article is manufactured in another country, the request for approval to deviate, together with all pertinent data, must be submitted through the civil aviation authority in that country to the FAA. <CITA>[Doc. No. 19589, 45 FR 38346, June 9, 1980, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.611</SECTNO> <SUBJECT>Design changes.</SUBJECT> (a) <E T="03">Minor changes by the manufacturer holding a TSO authorization.</E> The manufacturer of an article under an authorization issued under this part may make minor design changes (any change other than a major change) without further approval by the Administrator. In this case, the changed article keeps the original model number (part numbers may be used to identify minor changes) and the manufacturer shall forward to the appropriate Aircraft Certification Office for the geographic area, any revised data that are necessary for compliance with § 21.605(b). (b) <E T="03">Major changes by manufacturer holding a TSO authorization.</E> Any design change by the manufacturer that is extensive enough to require a substantially complete investigation to determine compliance with a TSO is a major change. Before making such a change, the manufacturer shall assign a new type or model designation to the article and apply for an authorization under § 21.605. (c) <E T="03">Changes by person other than manufacturer.</E> No design change by any person (other than the manufacturer who submitted the statement of conformance for the article) is eligible for approval under this part unless the person seeking the approval is a manufacturer and applies under § 21.605(a) for a separate TSO authorization. Persons other than a manufacturer may obtain approval for design changes under Part 43 or under the applicable airworthiness regulations. <CITA>[Doc. No. 19589, 45 FR 38346, June 9, 1980, as amended by Amdt. 21-67, 54 FR 39291, Sept. 25, 1989]</CITA> </SECTION> <SECTION> <SECTNO>§ 21.613</SECTNO> <SUBJECT>Recordkeeping requirements.</SUBJECT> (a) <E T="03">Keeping the records.</E> Each manufacturer holding a TSO authorization under this part shall, for each article manufactured under that authorization, keep the following records at its factory: (1) A complete and current technical data file for each type or model article, including design drawings and specifications. (2) Complete and current inspection records showing that all inspections and tests required to ensure compliance with this part have been properly completed and documented. (b) <E T="03">Retention of records.</E> The manufacturer shall retain the records described in paragraph (a)(1) of this section until it no longer manufactures the article. <PRTPAGE P="150"/>At that time, copies of these records shall be sent to the Administrator. The manufacturer shall retain the records described in paragraph (a)(2) of this section for a period of at least 2 years. </SECTION> <SECTION> <SECTNO>§ 21.615</SECTNO> <SUBJECT>FAA inspection.</SUBJECT> Upon the request of the Administrator, each manufacturer of an article under a TSO authorization shall allow the Administrator to— (a) Inspect any article manufactured under that authorization; (b) Inspect the manufacturer's quality control system; (c) Witness any tests; (d) Inspect the manufacturing facilities; and (e) Inspect the technical data files on that article. </SECTION> <SECTION> <SECTNO>§ 21.617</SECTNO> <SUBJECT>Issue of letters of TSO design approval: import appliances.</SUBJECT> (a) A letter of TSO design approval may be issued for an appliance that is manufactured in a foreign country with which the United States has an agreement for the acceptance of these appliances for export and import and that is to be imported into the United States if— (1) The country in which the appliance was manufactured certifies that the appliance has been examined, tested, and found to meet the applicable TSO designated in § 21.305(b) or the applicable performance standards of the country in which the appliance was manufactured and any other performance standards the Administrator may prescribe to provide a level of safety equivalent to that provided by the TSO designated in § 21.305(b); and (2) The manufacturer has submitted one copy of the technical data required in the applicable performance standard through its civil aviation authority. (b) The letter of TSO design approval will be issued by the Administrator and must list any deviation granted to the manufacturer under § 21.609. (c) After the Administrator has issued a letter of TSO design approval and the country of manufacture issues a Certificate of Airworthiness for Export as specified in § 21.502(a), the manufacturer shall be authorized to identify the appliance with the TSO marking requirements described in § 21.607(d) and in the applicable TSO. Each appliance must be accompanied by a Certificate of Airworthiness for Export as specified in § 21.502(a) issued by the country of manufacture. </SECTION> <SECTION> <SECTNO>§ 21.619</SECTNO> <SUBJECT>Noncompliance.</SUBJECT> The Administrator may, upon notice, withdraw the TSO authorization or letter of TSO design approval of any manufacturer who identifies with a TSO marking an article not meeting the performance standards of the applicable TSO. </SECTION> <SECTION> <SECTNO>§ 21.621</SECTNO> <SUBJECT>Transferability and duration.</SUBJECT> A TSO authorization or letter of TSO design approval issued under this part is not transferable and is effective until surrendered, withdrawn, or otherwise terminated by the Administrator. </SECTION> </SUBPART> </PART> <PART> <EAR>Pt. 23</EAR> <HD SOURCE="HED">PART 23—AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES</HD> <CONTENTS> <SUBJGRP> <HD SOURCE="HED">Special Federal Aviation Regulations</HD> </SUBJGRP> <FP SOURCE="FP-2"> <E T="04">SFAR</E> No. 23</FP> <FP SOURCE="FP-2"> <E T="04">SFAR</E> No. 41 [Note]</FP> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECHD>Sec.</SECHD> <SECTNO>23.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> <SECTNO>23.2</SECTNO> <SUBJECT>Special retroactive requirements.</SUBJECT> <SECTNO>23.3</SECTNO> <SUBJECT>Airplane categories.</SUBJECT> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Flight</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTNO>23.21</SECTNO> <SUBJECT>Proof of compliance.</SUBJECT> <SECTNO>23.23</SECTNO> <SUBJECT>Load distribution limits.</SUBJECT> <SECTNO>23.25</SECTNO> <SUBJECT>Weight limits.</SUBJECT> <SECTNO>23.29</SECTNO> <SUBJECT>Empty weight and corresponding center of gravity.</SUBJECT> <SECTNO>23.31</SECTNO> <SUBJECT>Removable ballast.</SUBJECT> <SECTNO>23.33</SECTNO> <SUBJECT>Propeller speed and pitch limits.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Performance</HD> <SECTNO>23.45</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.49</SECTNO> <SUBJECT>Stalling period.</SUBJECT> <SECTNO>23.51</SECTNO> <SUBJECT>Takeoff speeds.</SUBJECT> <SECTNO>23.53</SECTNO> <SUBJECT>Takeoff performance.</SUBJECT> <SECTNO>23.55</SECTNO> <SUBJECT>Accelerate-stop distance.</SUBJECT> <SECTNO>23.57</SECTNO> <SUBJECT>Takeoff path.</SUBJECT> <SECTNO>23.59</SECTNO> <SUBJECT>Takeoff distance and takeoff run.</SUBJECT> <SECTNO>23.61</SECTNO> <SUBJECT>Takeoff flight path.</SUBJECT> <SECTNO>23.63</SECTNO> <SUBJECT>Climb: general.</SUBJECT> <SECTNO>23.65</SECTNO> <SUBJECT>Climb: All engines operating.</SUBJECT> <SECTNO>23.66</SECTNO> <SUBJECT>Takeoff climb: One-engine inoperative.</SUBJECT> <SECTNO>23.67</SECTNO> <SUBJECT>Climb: one engine inoperative.<PRTPAGE P="151"/> </SUBJECT> <SECTNO>23.69</SECTNO> <SUBJECT>Enroute climb/descent.</SUBJECT> <SECTNO>23.71</SECTNO> <SUBJECT>Glide: Single-engine airplanes.</SUBJECT> <SECTNO>23.73</SECTNO> <SUBJECT>Reference landing approach speed.</SUBJECT> <SECTNO>23.75</SECTNO> <SUBJECT>Landing distance.</SUBJECT> <SECTNO>23.77</SECTNO> <SUBJECT>Balked landing.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Flight Characteristics</HD> <SECTNO>23.141</SECTNO> <SUBJECT>General.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Controllability and Maneuverability</HD> <SECTNO>23.143</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.145</SECTNO> <SUBJECT>Longitudinal control.</SUBJECT> <SECTNO>23.147</SECTNO> <SUBJECT>Directional and lateral control.</SUBJECT> <SECTNO>23.149</SECTNO> <SUBJECT>Minimum control speed.</SUBJECT> <SECTNO>23.151</SECTNO> <SUBJECT>Acrobatic maneuvers.</SUBJECT> <SECTNO>23.153</SECTNO> <SUBJECT>Control during landings.</SUBJECT> <SECTNO>23.155</SECTNO> <SUBJECT>Elevator control force in maneuvers.</SUBJECT> <SECTNO>23.157</SECTNO> <SUBJECT>Rate of roll.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Trim</HD> <SECTNO>23.161</SECTNO> <SUBJECT>Trim.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Stability</HD> <SECTNO>23.171</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.173</SECTNO> <SUBJECT>Static longitudinal stability.</SUBJECT> <SECTNO>23.175</SECTNO> <SUBJECT>Demonstration of static longitudinal stability.</SUBJECT> <SECTNO>23.177</SECTNO> <SUBJECT>Static directional and lateral stability.</SUBJECT> <SECTNO>23.181</SECTNO> <SUBJECT>Dynamic stability.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Stalls</HD> <SECTNO>23.201</SECTNO> <SUBJECT>Wings level stall.</SUBJECT> <SECTNO>23.203</SECTNO> <SUBJECT>Turning flight and accelerated turning stalls.</SUBJECT> <SECTNO>23.207</SECTNO> <SUBJECT>Stall warning.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Spinning</HD> <SECTNO>23.221</SECTNO> <SUBJECT>Spinning.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ground and Water Handling Characteristics</HD> <SECTNO>23.231</SECTNO> <SUBJECT>Longitudinal stability and control.</SUBJECT> <SECTNO>23.233</SECTNO> <SUBJECT>Directional stability and control.</SUBJECT> <SECTNO>23.235</SECTNO> <SUBJECT>Operation on unpaved surfaces.</SUBJECT> <SECTNO>23.237</SECTNO> <SUBJECT>Operation on water.</SUBJECT> <SECTNO>23.239</SECTNO> <SUBJECT>Spray characteristics.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Miscellaneous Flight Requirements</HD> <SECTNO>23.251</SECTNO> <SUBJECT>Vibration and buffeting.</SUBJECT> <SECTNO>23.253</SECTNO> <SUBJECT>High speed characteristics.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Structure</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTNO>23.301</SECTNO> <SUBJECT>Loads.</SUBJECT> <SECTNO>23.302</SECTNO> <SUBJECT>Canard or tandem wing configurations.</SUBJECT> <SECTNO>23.303</SECTNO> <SUBJECT>Factor of safety.</SUBJECT> <SECTNO>23.305</SECTNO> <SUBJECT>Strength and deformation.</SUBJECT> <SECTNO>23.307</SECTNO> <SUBJECT>Proof of structure.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Flight Loads</HD> <SECTNO>23.321</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.331</SECTNO> <SUBJECT>Symmetrical flight conditions.</SUBJECT> <SECTNO>23.333</SECTNO> <SUBJECT>Flight envelope.</SUBJECT> <SECTNO>23.335</SECTNO> <SUBJECT>Design airspeeds.</SUBJECT> <SECTNO>23.337</SECTNO> <SUBJECT>Limit maneuvering load factors.</SUBJECT> <SECTNO>23.341</SECTNO> <SUBJECT>Gust loads factors.</SUBJECT> <SECTNO>23.343</SECTNO> <SUBJECT>Design fuel loads.</SUBJECT> <SECTNO>23.345</SECTNO> <SUBJECT>High lift devices.</SUBJECT> <SECTNO>23.347</SECTNO> <SUBJECT>Unsymmetrical flight conditions.</SUBJECT> <SECTNO>23.349</SECTNO> <SUBJECT>Rolling conditions.</SUBJECT> <SECTNO>23.351</SECTNO> <SUBJECT>Yawing conditions.</SUBJECT> <SECTNO>23.361</SECTNO> <SUBJECT>Engine torque.</SUBJECT> <SECTNO>23.363</SECTNO> <SUBJECT>Side load on engine mount.</SUBJECT> <SECTNO>23.365</SECTNO> <SUBJECT>Pressurized cabin loads.</SUBJECT> <SECTNO>23.367</SECTNO> <SUBJECT>Unsymmetrical loads due to engine failure.</SUBJECT> <SECTNO>23.369</SECTNO> <SUBJECT>Rear lift truss.</SUBJECT> <SECTNO>23.371</SECTNO> <SUBJECT>Gyroscopic and aerodynamic loads.</SUBJECT> <SECTNO>23.373</SECTNO> <SUBJECT>Speed control devices.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Control Surface and System Loads</HD> <SECTNO>23.391</SECTNO> <SUBJECT>Control surface loads.</SUBJECT> <SECTNO>23.393</SECTNO> <SUBJECT>Loads parallel to hinge line.</SUBJECT> <SECTNO>23.395</SECTNO> <SUBJECT>Control system loads.</SUBJECT> <SECTNO>23.397</SECTNO> <SUBJECT>Limit control forces and torques.</SUBJECT> <SECTNO>23.399</SECTNO> <SUBJECT>Dual control system.</SUBJECT> <SECTNO>23.405</SECTNO> <SUBJECT>Secondary control system.</SUBJECT> <SECTNO>23.407</SECTNO> <SUBJECT>Trim tab effects.</SUBJECT> <SECTNO>23.409</SECTNO> <SUBJECT>Tabs.</SUBJECT> <SECTNO>23.415</SECTNO> <SUBJECT>Ground gust conditions.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Horizontal Stabilizing and Balancing Surfaces</HD> <SECTNO>23.421</SECTNO> <SUBJECT>Balancing loads.</SUBJECT> <SECTNO>23.423</SECTNO> <SUBJECT>Maneuvering loads.</SUBJECT> <SECTNO>23.425</SECTNO> <SUBJECT>Gust loads.</SUBJECT> <SECTNO>23.427</SECTNO> <SUBJECT>Unsymmetrical loads.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Vertical Surfaces</HD> <SECTNO>23.441</SECTNO> <SUBJECT>Maneuvering loads.</SUBJECT> <SECTNO>23.443</SECTNO> <SUBJECT>Gust loads.</SUBJECT> <SECTNO>23.445</SECTNO> <SUBJECT>Outboard fins or winglets.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ailerons and Special Devices</HD> <SECTNO>23.455</SECTNO> <SUBJECT>Ailerons.</SUBJECT> <SECTNO>23.459</SECTNO> <SUBJECT>Special devices.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ground Loads</HD> <SECTNO>23.471</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.473</SECTNO> <SUBJECT>Ground load conditions and assumptions.</SUBJECT> <SECTNO>23.477</SECTNO> <SUBJECT>Landing gear arrangement.</SUBJECT> <SECTNO>23.479</SECTNO> <SUBJECT>Level landing conditions.</SUBJECT> <SECTNO>23.481</SECTNO> <SUBJECT>Tail down landing conditions.</SUBJECT> <SECTNO>23.483</SECTNO> <SUBJECT>One-wheel landing conditions.</SUBJECT> <SECTNO>23.485</SECTNO> <SUBJECT>Side load conditions.</SUBJECT> <SECTNO>23.493</SECTNO> <SUBJECT>Braked roll conditions.</SUBJECT> <SECTNO>23.497</SECTNO> <SUBJECT>Supplementary conditions for tail wheels.</SUBJECT> <SECTNO>23.499</SECTNO> <SUBJECT>Supplementary conditions for nose wheels.</SUBJECT> <SECTNO>23.505</SECTNO> <SUBJECT>Supplementary conditions for ski-planes.</SUBJECT> <SECTNO>23.507</SECTNO> <SUBJECT>Jacking loads.</SUBJECT> <SECTNO>23.509</SECTNO> <SUBJECT>Towing loads.</SUBJECT> <SECTNO>23.511</SECTNO> <SUBJECT>Ground load; unsymmetrical loads on multiple-wheel units.</SUBJECT> </SUBJGRP> <SUBJGRP> <PRTPAGE P="152"/> <HD SOURCE="HED">Water Loads</HD> <SECTNO>23.521</SECTNO> <SUBJECT>Water load conditions.</SUBJECT> <SECTNO>23.523</SECTNO> <SUBJECT>Design weights and center of gravity positions.</SUBJECT> <SECTNO>23.525</SECTNO> <SUBJECT>Application of loads.</SUBJECT> <SECTNO>23.527</SECTNO> <SUBJECT>Hull and main float load factors.</SUBJECT> <SECTNO>23.529</SECTNO> <SUBJECT>Hull and main float landing conditions.</SUBJECT> <SECTNO>23.531</SECTNO> <SUBJECT>Hull and main float takeoff condition.</SUBJECT> <SECTNO>23.533</SECTNO> <SUBJECT>Hull and main float bottom pressures.</SUBJECT> <SECTNO>23.535</SECTNO> <SUBJECT>Auxiliary float loads.</SUBJECT> <SECTNO>23.537</SECTNO> <SUBJECT>Seawing loads.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Emergency Landing Conditions</HD> <SECTNO>23.561</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.562</SECTNO> <SUBJECT>Emergency landing dynamic conditions.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Fatigue Evaluation</HD> <SECTNO>23.571</SECTNO> <SUBJECT>Metallic pressurized cabin structures.</SUBJECT> <SECTNO>23.572</SECTNO> <SUBJECT>Metallic wing, empennage, and associated structures.</SUBJECT> <SECTNO>23.573</SECTNO> <SUBJECT>Damage tolerance and fatigue evaluation of structure.</SUBJECT> <SECTNO>23.574</SECTNO> <SUBJECT>Metallic damage tolerance and fatigue evaluation of commuter category airplanes.</SUBJECT> <SECTNO>23.575</SECTNO> <SUBJECT>Inspections and other procedures.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart D—Design and Construction</HD> <SECTNO>23.601</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.603</SECTNO> <SUBJECT>Materials and workmanship.</SUBJECT> <SECTNO>23.605</SECTNO> <SUBJECT>Fabrication methods.</SUBJECT> <SECTNO>23.607</SECTNO> <SUBJECT>Fasteners.</SUBJECT> <SECTNO>23.609</SECTNO> <SUBJECT>Protection of structure.</SUBJECT> <SECTNO>23.611</SECTNO> <SUBJECT>Accessibility provisions.</SUBJECT> <SECTNO>23.613</SECTNO> <SUBJECT>Material strength properties and design values.</SUBJECT> <SECTNO>23.619</SECTNO> <SUBJECT>Special factors.</SUBJECT> <SECTNO>23.621</SECTNO> <SUBJECT>Casting factors.</SUBJECT> <SECTNO>23.623</SECTNO> <SUBJECT>Bearing factors.</SUBJECT> <SECTNO>23.625</SECTNO> <SUBJECT>Fitting factors.</SUBJECT> <SECTNO>23.627</SECTNO> <SUBJECT>Fatigue strength.</SUBJECT> <SECTNO>23.629</SECTNO> <SUBJECT>Flutter.</SUBJECT> <SUBJGRP> <HD SOURCE="HED">Wings</HD> <SECTNO>23.641</SECTNO> <SUBJECT>Proof of strength.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Control Surfaces</HD> <SECTNO>23.651</SECTNO> <SUBJECT>Proof of strength.</SUBJECT> <SECTNO>23.655</SECTNO> <SUBJECT>Installation.</SUBJECT> <SECTNO>23.657</SECTNO> <SUBJECT>Hinges.</SUBJECT> <SECTNO>23.659</SECTNO> <SUBJECT>Mass balance.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Control Systems</HD> <SECTNO>23.671</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.672</SECTNO> <SUBJECT>Stability augmentation and automatic and power-operated systems.</SUBJECT> <SECTNO>23.673</SECTNO> <SUBJECT>Primary flight controls.</SUBJECT> <SECTNO>23.675</SECTNO> <SUBJECT>Stops.</SUBJECT> <SECTNO>23.677</SECTNO> <SUBJECT>Trim systems.</SUBJECT> <SECTNO>23.679</SECTNO> <SUBJECT>Control system locks.</SUBJECT> <SECTNO>23.681</SECTNO> <SUBJECT>Limit load static tests.</SUBJECT> <SECTNO>23.683</SECTNO> <SUBJECT>Operation tests.</SUBJECT> <SECTNO>23.685</SECTNO> <SUBJECT>Control system details.</SUBJECT> <SECTNO>23.687</SECTNO> <SUBJECT>Spring devices.</SUBJECT> <SECTNO>23.689</SECTNO> <SUBJECT>Cable systems.</SUBJECT> <SECTNO>23.691</SECTNO> <SUBJECT>Artificial stall barrier system.</SUBJECT> <SECTNO>23.693</SECTNO> <SUBJECT>Joints.</SUBJECT> <SECTNO>23.697</SECTNO> <SUBJECT>Wing flap controls.</SUBJECT> <SECTNO>23.699</SECTNO> <SUBJECT>Wing flap position indicator.</SUBJECT> <SECTNO>23.701</SECTNO> <SUBJECT>Flap interconnection.</SUBJECT> <SECTNO>23.703</SECTNO> <SUBJECT>Takeoff warning system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Landing Gear</HD> <SECTNO>23.721</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.723</SECTNO> <SUBJECT>Shock absorption tests.</SUBJECT> <SECTNO>23.725</SECTNO> <SUBJECT>Limit drop tests.</SUBJECT> <SECTNO>23.726</SECTNO> <SUBJECT>Ground load dynamic tests.</SUBJECT> <SECTNO>23.727</SECTNO> <SUBJECT>Reserve energy absorption drop test.</SUBJECT> <SECTNO>23.729</SECTNO> <SUBJECT>Landing gear extension and retraction system.</SUBJECT> <SECTNO>23.731</SECTNO> <SUBJECT>Wheels.</SUBJECT> <SECTNO>23.733</SECTNO> <SUBJECT>Tires.</SUBJECT> <SECTNO>23.735</SECTNO> <SUBJECT>Brakes.</SUBJECT> <SECTNO>23.737</SECTNO> <SUBJECT>Skis.</SUBJECT> <SECTNO>23.745</SECTNO> <SUBJECT>Nose/tail wheel steering.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Floats and Hulls</HD> <SECTNO>23.751</SECTNO> <SUBJECT>Main float buoyancy.</SUBJECT> <SECTNO>23.753</SECTNO> <SUBJECT>Main float design.</SUBJECT> <SECTNO>23.755</SECTNO> <SUBJECT>Hulls.</SUBJECT> <SECTNO>23.757</SECTNO> <SUBJECT>Auxiliary floats.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Personnel and Cargo Accommodations</HD> <SECTNO>23.771</SECTNO> <SUBJECT>Pilot compartment.</SUBJECT> <SECTNO>23.773</SECTNO> <SUBJECT>Pilot compartment view.</SUBJECT> <SECTNO>23.775</SECTNO> <SUBJECT>Windshields and windows.</SUBJECT> <SECTNO>23.777</SECTNO> <SUBJECT>Cockpit controls.</SUBJECT> <SECTNO>23.779</SECTNO> <SUBJECT>Motion and effect of cockpit controls.</SUBJECT> <SECTNO>23.781</SECTNO> <SUBJECT>Cockpit control knob shape.</SUBJECT> <SECTNO>23.783</SECTNO> <SUBJECT>Doors.</SUBJECT> <SECTNO>23.785</SECTNO> <SUBJECT>Seats, berths, litters, safety belts, and shoulder harnesses.</SUBJECT> <SECTNO>23.787</SECTNO> <SUBJECT>Baggage and cargo compartments.</SUBJECT> <SECTNO>23.791</SECTNO> <SUBJECT>Passenger information signs.</SUBJECT> <SECTNO>23.803</SECTNO> <SUBJECT>Emergency evacuation.</SUBJECT> <SECTNO>23.805</SECTNO> <SUBJECT>Flightcrew emergency exits.</SUBJECT> <SECTNO>23.807</SECTNO> <SUBJECT>Emergency exits.</SUBJECT> <SECTNO>23.811</SECTNO> <SUBJECT>Emergency exit marking.</SUBJECT> <SECTNO>23.812</SECTNO> <SUBJECT>Emergency lighting.</SUBJECT> <SECTNO>23.813</SECTNO> <SUBJECT>Emergency exit access.</SUBJECT> <SECTNO>23.815</SECTNO> <SUBJECT>Width of aisle.</SUBJECT> <SECTNO>23.831</SECTNO> <SUBJECT>Ventilation.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Pressurization</HD> <SECTNO>23.841</SECTNO> <SUBJECT>Pressurized cabins.</SUBJECT> <SECTNO>23.843</SECTNO> <SUBJECT>Pressurization tests.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Fire Protection</HD> <SECTNO>23.851</SECTNO> <SUBJECT>Fire extinguishers.</SUBJECT> <SECTNO>23.853</SECTNO> <SUBJECT>Passenger and crew compartment interiors.</SUBJECT> <SECTNO>23.855</SECTNO> <SUBJECT>Cargo and baggage compartment fire protection.</SUBJECT> <SECTNO>23.859</SECTNO> <SUBJECT>Combustion heater fire protection.</SUBJECT> <SECTNO>23.863</SECTNO> <SUBJECT>Flammable fluid fire protection.</SUBJECT> <SECTNO>23.865</SECTNO> <SUBJECT>Fire protection of flight controls, engine mounts, and other flight structure.</SUBJECT> </SUBJGRP> <SUBJGRP> <PRTPAGE P="153"/> <HD SOURCE="HED">Electrical Bonding and Lightning Protection</HD> <SECTNO>23.867</SECTNO> <SUBJECT>Electrical bonding and protection against lightning and static electricity.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Miscellaneous</HD> <SECTNO>23.871</SECTNO> <SUBJECT>Leveling means.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart E—Powerplant</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTNO>23.901</SECTNO> <SUBJECT>Installation.</SUBJECT> <SECTNO>23.903</SECTNO> <SUBJECT>Engines.</SUBJECT> <SECTNO>23.904</SECTNO> <SUBJECT>Automatic power reserve system.</SUBJECT> <SECTNO>23.905</SECTNO> <SUBJECT>Propellers.</SUBJECT> <SECTNO>23.907</SECTNO> <SUBJECT>Propeller vibration.</SUBJECT> <SECTNO>23.909</SECTNO> <SUBJECT>Turbocharger systems.</SUBJECT> <SECTNO>23.925</SECTNO> <SUBJECT>Propeller clearance.</SUBJECT> <SECTNO>23.929</SECTNO> <SUBJECT>Engine installation ice protection.</SUBJECT> <SECTNO>23.933</SECTNO> <SUBJECT>Reversing systems.</SUBJECT> <SECTNO>23.934</SECTNO> <SUBJECT>Turbojet and turbofan engine thrust reverser systems tests.</SUBJECT> <SECTNO>23.937</SECTNO> <SUBJECT>Turbopropeller-drag limiting systems.</SUBJECT> <SECTNO>23.939</SECTNO> <SUBJECT>Powerplant operating characteristics.</SUBJECT> <SECTNO>23.943</SECTNO> <SUBJECT>Negative acceleration.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Fuel System</HD> <SECTNO>23.951</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.953</SECTNO> <SUBJECT>Fuel system independence.</SUBJECT> <SECTNO>23.954</SECTNO> <SUBJECT>Fuel system lightning protection.</SUBJECT> <SECTNO>23.955</SECTNO> <SUBJECT>Fuel flow.</SUBJECT> <SECTNO>23.957</SECTNO> <SUBJECT>Flow between interconnected tanks.</SUBJECT> <SECTNO>23.959</SECTNO> <SUBJECT>Unusable fuel supply.</SUBJECT> <SECTNO>23.961</SECTNO> <SUBJECT>Fuel system hot weather operation.</SUBJECT> <SECTNO>23.963</SECTNO> <SUBJECT>Fuel tanks: General.</SUBJECT> <SECTNO>23.965</SECTNO> <SUBJECT>Fuel tank tests.</SUBJECT> <SECTNO>23.967</SECTNO> <SUBJECT>Fuel tank installation.</SUBJECT> <SECTNO>23.969</SECTNO> <SUBJECT>Fuel tank expansion space.</SUBJECT> <SECTNO>23.971</SECTNO> <SUBJECT>Fuel tank sump.</SUBJECT> <SECTNO>23.973</SECTNO> <SUBJECT>Fuel tank filler connection.</SUBJECT> <SECTNO>23.975</SECTNO> <SUBJECT>Fuel tank vents and carburetor vapor vents.</SUBJECT> <SECTNO>23.977</SECTNO> <SUBJECT>Fuel tank outlet.</SUBJECT> <SECTNO>23.979</SECTNO> <SUBJECT>Pressure fueling systems.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Fuel System Components</HD> <SECTNO>23.991</SECTNO> <SUBJECT>Fuel pumps.</SUBJECT> <SECTNO>23.993</SECTNO> <SUBJECT>Fuel system lines and fittings.</SUBJECT> <SECTNO>23.994</SECTNO> <SUBJECT>Fuel system components.</SUBJECT> <SECTNO>23.995</SECTNO> <SUBJECT>Fuel valves and controls.</SUBJECT> <SECTNO>23.997</SECTNO> <SUBJECT>Fuel strainer or filter.</SUBJECT> <SECTNO>23.999</SECTNO> <SUBJECT>Fuel system drains.</SUBJECT> <SECTNO>23.1001</SECTNO> <SUBJECT>Fuel jettisoning system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Oil System</HD> <SECTNO>23.1011</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1013</SECTNO> <SUBJECT>Oil tanks.</SUBJECT> <SECTNO>23.1015</SECTNO> <SUBJECT>Oil tank tests.</SUBJECT> <SECTNO>23.1017</SECTNO> <SUBJECT>Oil lines and fittings.</SUBJECT> <SECTNO>23.1019</SECTNO> <SUBJECT>Oil strainer or filter.</SUBJECT> <SECTNO>23.1021</SECTNO> <SUBJECT>Oil system drains.</SUBJECT> <SECTNO>23.1023</SECTNO> <SUBJECT>Oil radiators.</SUBJECT> <SECTNO>23.1027</SECTNO> <SUBJECT>Propeller feathering system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Cooling</HD> <SECTNO>23.1041</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1043</SECTNO> <SUBJECT>Cooling tests.</SUBJECT> <SECTNO>23.1045</SECTNO> <SUBJECT>Cooling test procedures for turbine engine powered airplanes.</SUBJECT> <SECTNO>23.1047</SECTNO> <SUBJECT>Cooling test procedures for reciprocating engine powered airplanes.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Liquid Cooling</HD> <SECTNO>23.1061</SECTNO> <SUBJECT>Installation.</SUBJECT> <SECTNO>23.1063</SECTNO> <SUBJECT>Coolant tank tests.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Induction System</HD> <SECTNO>23.1091</SECTNO> <SUBJECT>Air induction system.</SUBJECT> <SECTNO>23.1093</SECTNO> <SUBJECT>Induction system icing protection.</SUBJECT> <SECTNO>23.1095</SECTNO> <SUBJECT>Carburetor deicing fluid flow rate.</SUBJECT> <SECTNO>23.1097</SECTNO> <SUBJECT>Carburetor deicing fluid system capacity.</SUBJECT> <SECTNO>23.1099</SECTNO> <SUBJECT>Carburetor deicing fluid system detail design.</SUBJECT> <SECTNO>23.1101</SECTNO> <SUBJECT>Induction air preheater design.</SUBJECT> <SECTNO>23.1103</SECTNO> <SUBJECT>Induction system ducts.</SUBJECT> <SECTNO>23.1105</SECTNO> <SUBJECT>Induction system screens.</SUBJECT> <SECTNO>23.1107</SECTNO> <SUBJECT>Induction system filters.</SUBJECT> <SECTNO>23.1109</SECTNO> <SUBJECT>Turbocharger bleed air system.</SUBJECT> <SECTNO>23.1111</SECTNO> <SUBJECT>Turbine engine bleed air system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Exhaust System</HD> <SECTNO>23.1121</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1123</SECTNO> <SUBJECT>Exhaust system.</SUBJECT> <SECTNO>23.1125</SECTNO> <SUBJECT>Exhaust heat exchangers.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Powerplant Controls and Accessories</HD> <SECTNO>23.1141</SECTNO> <SUBJECT>Powerplant controls: General.</SUBJECT> <SECTNO>23.1142</SECTNO> <SUBJECT>Auxiliary power unit controls.</SUBJECT> <SECTNO>23.1143</SECTNO> <SUBJECT>Engine controls.</SUBJECT> <SECTNO>23.1145</SECTNO> <SUBJECT>Ignition switches.</SUBJECT> <SECTNO>23.1147</SECTNO> <SUBJECT>Mixture controls.</SUBJECT> <SECTNO>23.1149</SECTNO> <SUBJECT>Propeller speed and pitch controls.</SUBJECT> <SECTNO>23.1153</SECTNO> <SUBJECT>Propeller feathering controls.</SUBJECT> <SECTNO>23.1155</SECTNO> <SUBJECT>Turbine engine reverse thrust and propeller pitch settings below the flight regime.</SUBJECT> <SECTNO>23.1157</SECTNO> <SUBJECT>Carburetor air temperature controls.</SUBJECT> <SECTNO>23.1163</SECTNO> <SUBJECT>Powerplant accessories.</SUBJECT> <SECTNO>23.1165</SECTNO> <SUBJECT>Engine ignition systems.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Powerplant Fire Protection</HD> <SECTNO>23.1181</SECTNO> <SUBJECT>Designated fire zones; regions included.</SUBJECT> <SECTNO>23.1182</SECTNO> <SUBJECT>Nacelle areas behind firewalls.</SUBJECT> <SECTNO>23.1183</SECTNO> <SUBJECT>Lines, fittings, and components.</SUBJECT> <SECTNO>23.1189</SECTNO> <SUBJECT>Shutoff means.</SUBJECT> <SECTNO>23.1191</SECTNO> <SUBJECT>Firewalls.</SUBJECT> <SECTNO>23.1192</SECTNO> <SUBJECT>Engine accessory compartment diaphragm.</SUBJECT> <SECTNO>23.1193</SECTNO> <SUBJECT>Cowling and nacelle.</SUBJECT> <SECTNO>23.1195</SECTNO> <SUBJECT>Fire extinguishing systems.</SUBJECT> <SECTNO>23.1197</SECTNO> <SUBJECT>Fire extinguishing agents.</SUBJECT> <SECTNO>23.1199</SECTNO> <SUBJECT>Extinguishing agent containers.</SUBJECT> <SECTNO>23.1201</SECTNO> <SUBJECT>Fire extinguishing systems materials.</SUBJECT> <SECTNO>23.1203</SECTNO> <SUBJECT>Fire detector system.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <PRTPAGE P="154"/> <HD SOURCE="HED">Subpart F—Equipment</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTNO>23.1301</SECTNO> <SUBJECT>Function and installation.</SUBJECT> <SECTNO>23.1303</SECTNO> <SUBJECT>Flight and navigation instruments.</SUBJECT> <SECTNO>23.1305</SECTNO> <SUBJECT>Powerplant instruments.</SUBJECT> <SECTNO>23.1307</SECTNO> <SUBJECT>Miscellaneous equipment.</SUBJECT> <SECTNO>23.1309</SECTNO> <SUBJECT>Equipment, systems, and installations.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Instruments: Installation</HD> <SECTNO>23.1311</SECTNO> <SUBJECT>Electronic display instrument systems.</SUBJECT> <SECTNO>23.1321</SECTNO> <SUBJECT>Arrangement and visibility.</SUBJECT> <SECTNO>23.1322</SECTNO> <SUBJECT>Warning, caution, and advisory lights.</SUBJECT> <SECTNO>23.1323</SECTNO> <SUBJECT>Airspeed indicating system.</SUBJECT> <SECTNO>23.1325</SECTNO> <SUBJECT>Static pressure system.</SUBJECT> <SECTNO>23.1326</SECTNO> <SUBJECT>Pitot heat indication systems.</SUBJECT> <SECTNO>23.1327</SECTNO> <SUBJECT>Magnetic direction indicator.</SUBJECT> <SECTNO>23.1329</SECTNO> <SUBJECT>Automatic pilot system.</SUBJECT> <SECTNO>23.1331</SECTNO> <SUBJECT>Instruments using a power source.</SUBJECT> <SECTNO>23.1335</SECTNO> <SUBJECT>Flight director systems.</SUBJECT> <SECTNO>23.1337</SECTNO> <SUBJECT>Powerplant instruments installation.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Electrical Systems and Equipment</HD> <SECTNO>23.1351</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1353</SECTNO> <SUBJECT>Storage battery design and installation.</SUBJECT> <SECTNO>23.1357</SECTNO> <SUBJECT>Circuit protective devices.</SUBJECT> <SECTNO>23.1359</SECTNO> <SUBJECT>Electrical system fire protection.</SUBJECT> <SECTNO>23.1361</SECTNO> <SUBJECT>Master switch arrangement.</SUBJECT> <SECTNO>23.1365</SECTNO> <SUBJECT>Electric cables and equipment.</SUBJECT> <SECTNO>23.1367</SECTNO> <SUBJECT>Switches.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Lights</HD> <SECTNO>23.1381</SECTNO> <SUBJECT>Instrument lights.</SUBJECT> <SECTNO>23.1383</SECTNO> <SUBJECT>Taxi and landing lights.</SUBJECT> <SECTNO>23.1385</SECTNO> <SUBJECT>Position light system installation.</SUBJECT> <SECTNO>23.1387</SECTNO> <SUBJECT>Position light system dihedral angles.</SUBJECT> <SECTNO>23.1389</SECTNO> <SUBJECT>Position light distribution and intensities.</SUBJECT> <SECTNO>23.1391</SECTNO> <SUBJECT>Minimum intensities in the horizontal plane of position lights.</SUBJECT> <SECTNO>23.1393</SECTNO> <SUBJECT>Minimum intensities in any vertical plane of position lights.</SUBJECT> <SECTNO>23.1395</SECTNO> <SUBJECT>Maximum intensities in overlapping beams of position lights.</SUBJECT> <SECTNO>23.1397</SECTNO> <SUBJECT>Color specifications.</SUBJECT> <SECTNO>23.1399</SECTNO> <SUBJECT>Riding light.</SUBJECT> <SECTNO>23.1401</SECTNO> <SUBJECT>Anticollision light system.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Safety Equipment</HD> <SECTNO>23.1411</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1415</SECTNO> <SUBJECT>Ditching equipment.</SUBJECT> <SECTNO>23.1416</SECTNO> <SUBJECT>Pneumatic de-icer boot system.</SUBJECT> <SECTNO>23.1419</SECTNO> <SUBJECT>Ice protection.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Miscellaneous Equipment</HD> <SECTNO>23.1431</SECTNO> <SUBJECT>Electronic equipment.</SUBJECT> <SECTNO>23.1435</SECTNO> <SUBJECT>Hydraulic systems.</SUBJECT> <SECTNO>23.1437</SECTNO> <SUBJECT>Accessories for multiengine airplanes.</SUBJECT> <SECTNO>23.1438</SECTNO> <SUBJECT>Pressurization and pneumatic systems.</SUBJECT> <SECTNO>23.1441</SECTNO> <SUBJECT>Oxygen equipment and supply.</SUBJECT> <SECTNO>23.1443</SECTNO> <SUBJECT>Minimum mass flow of supplemental oxygen.</SUBJECT> <SECTNO>23.1445</SECTNO> <SUBJECT>Oxygen distribution system.</SUBJECT> <SECTNO>23.1447</SECTNO> <SUBJECT>Equipment standards for oxygen dispensing units.</SUBJECT> <SECTNO>23.1449</SECTNO> <SUBJECT>Means for determining use of oxygen.</SUBJECT> <SECTNO>23.1450</SECTNO> <SUBJECT>Chemical oxygen generators.</SUBJECT> <SECTNO>23.1451</SECTNO> <SUBJECT>Fire protection for oxygen equipment.</SUBJECT> <SECTNO>23.1453</SECTNO> <SUBJECT>Protection of oxygen equipment from rupture.</SUBJECT> <SECTNO>23.1457</SECTNO> <SUBJECT>Cockpit voice recorders.</SUBJECT> <SECTNO>23.1459</SECTNO> <SUBJECT>Flight recorders.</SUBJECT> <SECTNO>23.1461</SECTNO> <SUBJECT>Equipment containing high energy rotors.</SUBJECT> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart G—Operating Limitations and Information</HD> <SECTNO>23.1501</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1505</SECTNO> <SUBJECT>Airspeed limitations.</SUBJECT> <SECTNO>23.1507</SECTNO> <SUBJECT>Operating maneuvering speed.</SUBJECT> <SECTNO>23.1511</SECTNO> <SUBJECT>Flap extended speed.</SUBJECT> <SECTNO>23.1513</SECTNO> <SUBJECT>Minimum control speed.</SUBJECT> <SECTNO>23.1519</SECTNO> <SUBJECT>Weight and center of gravity.</SUBJECT> <SECTNO>23.1521</SECTNO> <SUBJECT>Powerplant limitations.</SUBJECT> <SECTNO>23.1522</SECTNO> <SUBJECT>Auxiliary power unit limitations.</SUBJECT> <SECTNO>23.1523</SECTNO> <SUBJECT>Minimum flight crew.</SUBJECT> <SECTNO>23.1524</SECTNO> <SUBJECT>Maximum passenger seating configuration.</SUBJECT> <SECTNO>23.1525</SECTNO> <SUBJECT>Kinds of operation.</SUBJECT> <SECTNO>23.1527</SECTNO> <SUBJECT>Maximum operating altitude.</SUBJECT> <SECTNO>23.1529</SECTNO> <SUBJECT>Instructions for Continued Airworthiness.</SUBJECT> <SUBJGRP> <HD SOURCE="HED">Markings and Placards</HD> <SECTNO>23.1541</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1543</SECTNO> <SUBJECT>Instrument markings: General.</SUBJECT> <SECTNO>23.1545</SECTNO> <SUBJECT>Airspeed indicator.</SUBJECT> <SECTNO>23.1547</SECTNO> <SUBJECT>Magnetic direction indicator.</SUBJECT> <SECTNO>23.1549</SECTNO> <SUBJECT>Powerplant and auxiliary power unit instruments.</SUBJECT> <SECTNO>23.1551</SECTNO> <SUBJECT>Oil quantity indicator.</SUBJECT> <SECTNO>23.1553</SECTNO> <SUBJECT>Fuel quantity indicator.</SUBJECT> <SECTNO>23.1555</SECTNO> <SUBJECT>Control markings.</SUBJECT> <SECTNO>23.1557</SECTNO> <SUBJECT>Miscellaneous markings and placards.</SUBJECT> <SECTNO>23.1559</SECTNO> <SUBJECT>Operating limitations placard.</SUBJECT> <SECTNO>23.1561</SECTNO> <SUBJECT>Safety equipment.</SUBJECT> <SECTNO>23.1563</SECTNO> <SUBJECT>Airspeed placards.</SUBJECT> <SECTNO>23.1567</SECTNO> <SUBJECT>Flight maneuver placard.</SUBJECT> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Airplane Flight Manual and Approved Manual Material</HD> <SECTNO>23.1581</SECTNO> <SUBJECT>General.</SUBJECT> <SECTNO>23.1583</SECTNO> <SUBJECT>Operating limitations.</SUBJECT> <SECTNO>23.1585</SECTNO> <SUBJECT>Operating procedures.</SUBJECT> <SECTNO>23.1587</SECTNO> <SUBJECT>Performance information.</SUBJECT> <SECTNO>23.1589</SECTNO> <SUBJECT>Loading information.</SUBJECT> <APP> <E T="04">Appendix A to Part</E> 23<E T="04">—Simplified Design Load Criteria</E> </APP> <APP> <E T="04">Appendix B to Part</E> 23<E T="04"> [Reserved]</E> <PRTPAGE P="155"/> </APP> <APP> <E T="04">Appendix C to Part</E> 23<E T="04">—Basic Landing Conditions</E> </APP> <APP> <E T="04">Appendix D to Part</E> 23<E T="04">—Wheel Spin-Up and Spring-Back Loads</E> </APP> <APP> <E T="04">Appendix E to Part</E> 23<E T="04"> [Reserved]</E> </APP> <APP> <E T="04">Appendix F to Part</E> 23<E T="04">—Test Procedure</E> </APP> <APP> <E T="04">Appendix G to Part</E> 23<E T="04">—Instructions for Continued Airworthiness</E> </APP> <APP> <E T="04">Appendix H to Part</E> 23<E T="04">—Installation of An Automatic Power Reserve (APR) System</E> </APP> <APP> <E T="04">Appendix I to Part</E> 23<E T="04">—Seaplane Loads</E> </APP> </SUBJGRP> </SUBPART> </CONTENTS> <AUTH> <HD SOURCE="HED">Authority: </HD> 49 U.S.C. 106(g), 40113, 44701-44702, 44704. </AUTH> <SOURCE> <HD SOURCE="HED">Source: </HD> Docket No. 4080, 29 FR 17955, Dec. 18. 1964; 30 FR 258, Jan. 9, 1965, unless otherwise noted. </SOURCE> <EAR>Pt. 23, SFAR No. 23</EAR> <SUBJGRP> <HD SOURCE="HED">Special Federal Aviation Regulations SFAR No. <E T="01">23</E> </HD> </SUBJGRP> <EXTRACT> 1. <E T="03">Applicability.</E> An applicant is entitled to a type certificate in the normal category for a reciprocating or turbopropeller multiengine powered small airplane that is to be certificated to carry more than 10 occupants and that is intended for use in operations under Part 135 of the Federal Aviation Regulations if he shows compliance with the applicable requirements of Part 23 of the Federal Aviation Regulations, as supplemented or modified by the additional airworthiness requirements of this regulation. 2. <E T="03">References.</E> Unless otherwise provided, all references in this regulation to specific sections of Part 23 of the Federal Aviation Regulations are those sections of Part 23 in effect on March 30, 1967. <HD SOURCE="HD1">Flight Requirements</HD> 3. <E T="03">General.</E> Compliance must be shown with the applicable requirements of Subpart B of Part 23 of the Federal Aviation Regulations in effect on March 30, 1967, as supplemented or modified in sections 4 through 10 of this regulation. <HD SOURCE="HD1">Performance</HD> 4. <E T="03">General.</E> (a) Unless otherwise prescribed in this regulation, compliance with each applicable performance requirement in sections 4 through 7 of this regulation must be shown for ambient atmospheric conditions and still air. (b) The performance must correspond to the propulsive thrust available under the particular ambient atmospheric conditions and the particular flight condition. The available propulsive thrust must correspond to engine power or thrust, not exceeding the approved power or thrust less— (1) Installation losses; and (2) The power or equivalent thrust absorbed by the accessories and services appropriate to the particular ambient atmospheric conditions and the particular flight condition. (c) Unless otherwise prescribed in this regulation, the applicant must select the take-off, en route, and landing configurations for the airplane. (d) The airplane configuration may vary with weight, altitude, and temperature, to the extent they are compatible with the operating procedures required by paragraph (e) of this section. (e) Unless otherwise prescribed in this regulation, in determining the critical engine inoperative takeoff performance, the accelerate-stop distance, takeoff distance, changes in the airplane's configuration, speed, power, and thrust, must be made in accordance with procedures established by the applicant for operation in service. (f) Procedures for the execution of balked landings must be established by the applicant and included in the Airplane Flight Manual. (g) The procedures established under paragraphs (e) and (f) of this section must— (1) Be able to be consistently executed in service by a crew of average skill; (2) Use methods or devices that are safe and reliable; and (3) Include allowance for any time delays, in the execution of the procedures, that may reasonably be expected in service. 5. <E T="03">Takeoff</E>—(a) <E T="03">General.</E> The takeoff speeds described in paragraph (b), the accelerate-stop distance described in paragraph (c), and the takeoff distance described in paragraph (d), must be determined for— (1) Each weight, altitude, and ambient temperature within the operational limits selected by the applicant; (2) The selected configuration for takeoff; (3) The center of gravity in the most unfavorable position; (4) The operating engine within approved operating limitation; and (5) Takeoff data based on smooth, dry, hard-surface runway. (b) <E T="03">Takeoff speeds.</E> (1) The decision speed <E T="03">V</E> <E T="22">1</E> is the calibrated airspeed on the ground at which, as a result of engine failure or other reasons, the pilot is assumed to have made a decision to continue or discontinue the takeoff. The speed <E T="03">V</E> <E T="22">1</E> must be selected by the applicant but may not be less than— (i) 1.10 <E T="03">V</E> <E T="24">s1</E>; (ii) 1.10 <E T="03">V</E> <E T="24">MC</E>; (iii) A speed that permits acceleration to <E T="03">V</E> <E T="22">1</E> and stop in accordance with paragraph (c) allowing credit for an overrun distance equal to that required to stop the airplane from a ground speed of 35 knots utilizing maximum braking; or (iv) A speed at which the airplane can be rotated for takeoff and shown to be adequate to safely continue the takeoff, using normal piloting skill, when the critical engine is suddenly made inoperative.<PRTPAGE P="156"/> (2) Other essential takeoff speeds necessary for safe operation of the airplane must be determined and shown in the Airplane Flight Manual. (c) <E T="03">Accelerate-stop distance.</E> (1) The accelerate-stop distance is the sum of the distances necessary to— (i) Accelerate the airplane from a standing start to <E T="03">V</E> <E T="22">1</E>; and (ii) Decelerate the airplane from <E T="03">V</E> <E T="22">1</E> to a speed not greater than 35 knots, assuming that in the case of engine failure, failure of the critical engine is recognized by the pilot at the speed <E T="03">V</E> <E T="22">1</E>. The landing gear must remain in the extended position and maximum braking may be utilized during deceleration. (2) Means other than wheel brakes may be used to determine the accelerate-stop distance if that means is available with the critical engine inoperative and— (i) Is safe and reliable; (ii) Is used so that consistent results can be expected under normal operating conditions; and (iii) Is such that exceptional skill is not required to control the airplane. (d) <E T="03">All engines operating takeoff distance.</E> The all engine operating takeoff distance is the horizontal distance required to takeoff and climb to a height of 50 feet above the takeoff surface according to procedures in FAR 23.51(a). (e) <E T="03">One-engine-inoperative takeoff.</E> The maximum weight must be determined for each altitude and temperature within the operational limits established for the airplane, at which the airplane has takeoff capability after failure of the critical engine at or above <E T="03">V</E> <E T="22">1</E> determined in accordance with paragraph (b) of this section. This capability may be established— (1) By demonstrating a measurably positive rate of climb with the airplane in the takeoff configuration, landing gear extended; or (2) By demonstrating the capability of maintaining flight after engine failure utilizing procedures prescribed by the applicant. 6. <E T="03">Climb</E>—(a) <E T="03">Landing climb: All-engines-operating.</E> The maximum weight must be determined with the airplane in the landing configuration, for each altitude, and ambient temperature within the operational limits established for the airplane and with the most unfavorable center of gravity and out-of-ground effect in free air, at which the steady gradient of climb will not be less than 3.3 percent, with: (1) The engines at the power that is available 8 seconds after initiation of movement of the power or thrust controls from the mimimum flight idle to the takeoff position. (2) A climb speed not greater than the approach speed established under section 7 of this regulation and not less than the greater of 1.05<E T="24">MC</E> or 1.10V<E T="24">S</E> <E T="22">1</E>. (b) <E T="03">En route climb, one-engine-inoperative.</E> (1) the maximum weight must be determined with the airplane in the en route configuration, the critical engine inoperative, the remaining engine at not more than maximum continuous power or thrust, and the most unfavorable center of gravity, at which the gradient at climb will be not less than— (i) 1.2 percent (or a gradient equivalent to 0.20 <E T="03">V</E> <E T="24">so</E> 2<E T="11">, if greater) at 5,000 feet and an ambient temperature of 41° F. or</E> (ii) 0.6 percent (or a gradient equivalent to 0.01 <E T="03">V</E> <E T="24">so</E> 2<E T="11">, if greater) at 5,000 feet and ambient temperature of 81° F.</E> (2) The minimum climb gradient specified in subdivisions (i) and (ii) of subparagraph (1) of this paragraph must vary linearly between 41° F. and 81° F. and must change at the same rate up to the maximum operational temperature approved for the airplane. 7. <E T="03">Landing.</E> The landing distance must be determined for standard atmosphere at each weight and altitude in accordance with FAR 23.75(a), except that instead of the gliding approach specified in FAR 23.75(a)(1), the landing may be preceded by a steady approach down to the 50-foot height at a gradient of descent not greater than 5.2 percent (3°) at a calibrated airspeed not less than 1.3<E T="24">s</E> <E T="22">1</E>. <HD SOURCE="HD1">Trim</HD> 8. <E T="03">Trim</E>—(a) <E T="03">Lateral and directional trim.</E> The airplane must maintain lateral and directional trim in level flight at a speed of <E T="03">V</E> <E T="24">h</E> or <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO,</E> whichever is lower, with landing gear and wing flaps retracted. (b) <E T="03">Longitudinal trim.</E> The airplane must maintain longitudinal trim during the following conditions, except that it need not maintain trim at a speed greater than <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO:</E> (1) In the approach conditions specified in FAR 23.161(c)(3) through (5), except that instead of the speeds specified therein, trim must be maintained with a stick force of not more than 10 pounds down to a speed used in showing compliance with section 7 of this regulation or 1.4 <E T="03">V</E> <E T="23">s</E> <E T="22">1</E> whichever is lower. (2) In level flight at any speed from <E T="03">V</E> <E T="24">H</E> or <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E>, whichever is lower, to either <E T="03">Vx</E> or 1.4 <E T="03">V</E> <E T="24">s</E> <E T="22">1</E>, with the landing gear and wing flaps retracted. <HD SOURCE="HD1">Stability</HD> 9. <E T="03">Static longitudinal stability.</E> (a) In showing compliance with the provisions of FAR 23.175(b) and with paragraph (b) of this section, the airspeed must return to within <E T="21">±</E>7<FR>1/2</FR> percent of the trim speed. (b) <E T="03">Cruise stability.</E> The stick force curve must have a stable slope for a speed range of <E T="21">±</E>50 knots from the trim speed except that the speeds need not exceed <E T="03">V</E> <E T="24">FC</E>/<E T="03">M</E> <E T="24">FC</E> or be less than 1.4 <E T="03">V</E> <E T="24">s</E> <E T="22">1</E>. This speed range will be considered to begin at the outer extremes of the <PRTPAGE P="157"/>friction band and the stick force may not exceed 50 pounds with— (i) Landing gear retracted; (ii) Wing flaps retracted; (iii) The maximum cruising power as selected by the applicant as an operating limitation for turbine engines or 75 percent of maximum continuous power for reciprocating engines except that the power need not exceed that required at <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO:</E> (iv) Maximum takeoff weight; and (v) The airplane trimmed for level flight with the power specified in subparagraph (iii) of this paragraph. <E T="03">V</E> <E T="24">FC</E>/<E T="03">M</E> <E T="24">FC</E> may not be less than a speed midway between <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> and <E T="03">V</E> <E T="24">DF</E>/<E T="03">M</E> <E T="24">DF</E>, except that, for altitudes where Mach number is the limiting factor, <E T="03">M</E> <E T="24">FC</E> need not exceed the Mach number at which effective speed warning occurs. (c) <E T="03">Climb stability. For turbopropeller powered airplanes only.</E> In showing compliance with FAR 23.175(a), an applicant must in lieu of the power specified in FAR 23.175(a)(4), use the maximum power or thrust selected by the applicant as an operating limitation for use during climb at the best rate of climb speed except that the speed need not be less than 1.4 <E T="03">V</E> <E T="24">s</E> <E T="22">1</E>. <HD SOURCE="HD1">Stalls</HD> 10. <E T="03">Stall warning.</E> If artificial stall warning is required to comply with the requirements of FAR 23.207, the warning device must give clearly distinguishable indications under expected conditions of flight. The use of a visual warning device that requires the attention of the crew within the cockpit is not acceptable by itself. <HD SOURCE="HD1">Control Systems</HD> 11. <E T="03">Electric trim tabs.</E> The airplane must meet the requirements of FAR 23.677 and in addition it must be shown that the airplane is safely controllable and that a pilot can perform all the maneuvers and operations necessary to effect a safe landing following any probable electric trim tab runaway which might be reasonably expected in service allowing for appropriate time delay after pilot recognition of the runaway. This demonstration must be conducted at the critical airplane weights and center of gravity positions. <HD SOURCE="HD1">Instruments: Installation</HD> 12. <E T="03">Arrangement and visibility.</E> Each instrument must meet the requirements of FAR 23.1321 and in addition— (a) Each flight, navigation, and powerplant instrument for use by any pilot must be plainly visible to him from his station with the minimum practicable deviation from his normal position and line of vision when he is looking forward along the flight path. (b) The flight instruments required by FAR 23.1303 and by the applicable operating rules must be grouped on the instrument panel and centered as nearly as practicable about the vertical plane of each pilot's forward vision. In addition— (1) The instrument that most effectively indicates the attitude must be on the panel in the top center position; (2) The instrument that most effectively indicates airspeed must be adjacent to and directly to the left of the instrument in the top center position; (3) The instrument that most effectively indicates altitude must be adjacent to and directly to the right of the instrument in the top center position; and (4) The instrument that most effectively indicates direction of flight must be adjacent to and directly below the instrument in the top center position. 13. <E T="03">Airspeed indicating system.</E> Each airspeed indicating system must meet the requirements of FAR 23.1323 and in addition— (a) Airspeed indicating instruments must be of an approved type and must be calibrated to indicate true airspeed at sea level in the standard atmosphere with a mimimum practicable instrument calibration error when the corresponding pilot and static pressures are supplied to the instruments. (b) The airspeed indicating system must be calibrated to determine the system error, i.e., the relation between IAS and CAS, in flight and during the accelerate takeoff ground run. The ground run calibration must be obtained between 0.8 of the mimimum value of <E T="03">V</E> <E T="22">1</E> and 1.2 times the maximum value of <E T="03">V</E> <E T="22">1</E>, considering the approved ranges of altitude and weight. The ground run calibration will be determined assuming an engine failure at the mimimum value of <E T="03">V</E> <E T="22">1</E>. (c) The airspeed error of the installation excluding the instrument calibration error, must not exceed 3 percent or 5 knots whichever is greater, throughout the speed range from <E T="03">V</E> <E T="24">MO</E> to 1.3<E T="03">S</E> <E T="22">1</E> with flaps retracted and from 1.3 <E T="03">VS</E> <E T="24">O</E> to <E T="03">V</E> <E T="24">FE</E> with flaps in the landing position. (d) Information showing the relationship between IAS and CAS must be shown in the Airplane Flight Manual. 14. <E T="03">Static air vent system.</E> The static air vent system must meet the requirements of FAR 23.1325. The altimeter system calibration must be determined and shown in the Airplane Flight Manual. <HD SOURCE="HD1">Operating Limitations and Information</HD> 15. <E T="03">Maximum operating limit speed V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO.</E> Instead of establishing operating limitations based on <E T="03">V</E> <E T="24">ME</E> and <E T="03">V</E> <E T="24">NO</E>, the applicant must establish a maximum operating limit speed <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> in accordance with the following: (a) The maximum operating limit speed must not exceed the design cruising speed <E T="03">Vc</E> <PRTPAGE P="158"/>and must be sufficiently below <E T="03">V</E> <E T="24">D</E>/<E T="03">M</E> <E T="24">D</E> or <E T="03">V</E> <E T="24">DF</E>/<E T="03">M</E> <E T="24">DF</E> to make it highly improbable that the latter speeds will be inadvertently exceeded in flight. (b) The speed <E T="03">Vmo</E> must not exceed 0.8 <E T="03">V</E> <E T="24">D</E>/<E T="03">M</E> <E T="24">D</E> or 0.8 <E T="03">V</E> <E T="24">DF</E>/<E T="03">M</E> <E T="24">DF</E> unless flight demonstrations involving upsets as specified by the Administrator indicates a lower speed margin will not result in speeds exceeding <E T="03">V</E> <E T="24">D</E>/<E T="03">M</E> <E T="24">D</E> or <E T="03">V</E> <E T="24">DF</E>. Atmospheric variations, horizontal gusts, and equipment errors, and airframe production variations will be taken into account. 16. <E T="03">Minimum flight crew.</E> In addition to meeting the requirements of FAR 23.1523, the applicant must establish the minimum number and type of qualified flight crew personnel sufficient for safe operation of the airplane considering— (a) Each kind of operation for which the applicant desires approval; (b) The workload on each crewmember considering the following: (1) Flight path control. (2) Collision avoidance. (3) Navigation. (4) Communications. (5) Operation and monitoring of all essential aircraft systems. (6) Command decisions; and (c) The accessibility and ease of operation of necessary controls by the appropriate crewmember during all normal and emergency operations when at his flight station. 17. <E T="03">Airspeed indicator.</E> The airspeed indicator must meet the requirements of FAR 23.1545 except that, the airspeed notations and markings in terms of <E T="03">V</E> <E T="24">NO</E> and <E T="03">V</E> <E T="24">NE</E> must be replaced by the <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> notations. The airspeed indicator markings must be easily read and understood by the pilot. A placard adjacent to the airspeed indicator is an acceptable means of showing compliance with the requirements of FAR 23.1545(c). <HD SOURCE="HD1">Airplane Flight Manual</HD> 18. <E T="03">General.</E> The Airplane Flight Manual must be prepared in accordance with the requirements of FARs 23.1583 and 23.1587, and in addition the operating limitations and performance information set forth in sections 19 and 20 must be included. 19. <E T="03">Operating limitations.</E> The Airplane Flight Manual must include the following limitations— (a) <E T="03">Airspeed limitations.</E> (1) The maximum operating limit speed <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> and a statement that this speed limit may not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training; (2) If an airspeed limitation is based upon compressibility effects, a statement to this effect and information as to any symptoms, the probable behavior of the airplane, and the recommended recovery procedures; and (3) The airspeed limits, shown in terms of <E T="03">V</E> <E T="24">MO</E>/<E T="03">M</E> <E T="24">MO</E> instead of <E T="03">V</E> <E T="24">NO</E> and <E T="03">V</E> <E T="24">NE</E>. (b) <E T="03">Takeoff weight limitations.</E> The maximum takeoff weight for each airport elevation, ambient temperature, and available takeoff runway length within the range selected by the applicant. This weight may not exceed the weight at which: (1) The all-engine operating takeoff distance determined in accordance with section 5(d) or the accelerate-stop distance determined in accordance with section 5(c), which ever is greater, is equal to the available runway length; (2) The airplane complies with the one-engine-inoperative takeoff requirements specified in section 5(e); and (3) The airplane complies with the one-engine-inoperative en route climb requirements specified in section 6(b), assuming that a standard temperature lapse rate exists from the airport elevation to the altitude of 5,000 feet, except that the weight may not exceed that corresponding to a temperature of 41° F at 5,000 feet. 20. <E T="03">Performance information.</E> The Airplane Flight Manual must contain the performance information determined in accordance with the provisions of the performance requirements of this regulation. The information must include the following: (a) Sufficient information so that the take-off weight limits specified in section 19(b) can be determined for all temperatures and altitudes within the operation limitations selected by the applicant. (b) The conditions under which the performance information was obtained, including the airspeed at the 50-foot height used to determine landing distances. (c) The performance information (determined by extrapolation and computed for the range of weights between the maximum landing and takeoff weights) for— (1) Climb in the landing configuration; and (2) Landing distance. (d) Procedure established under section 4 of this regulation related to the limitations and information required by this section in the form of guidance material including any relevant limitations or information. (e) An explanation of significant or unusual flight or ground handling characteristics of the airplane. (f) Airspeeds, as indicated airspeeds, corresponding to those determined for takeoff in accordance with section 5(b). 21. <E T="03">Maximum operating altitudes.</E> The maximum operating altitude to which operation is permitted, as limited by flight, structural, powerplant, functional, or equipment characteristics, must be specified in the Airplane Flight Manual. 22. <E T="03">Stowage provision for Airplane Flight Manual.</E> Provision must be made for stowing the Airplane Flight Manual in a suitable <PRTPAGE P="159"/>fixed container which is readily accessible to the pilot. 23. <E T="03">Operating procedures.</E> Procedures for restarting turbine engines in flight (including the effects of altitude) must be set forth in the Airplane Flight Manual. <HD SOURCE="HD1">Airframe Requirements</HD> <HD SOURCE="HD1">flight loads</HD> 24. <E T="03">Engine torque.</E> (a) Each turbopropeller engine mount and its supporting structure must be designed for the torque effects of— (1) The conditions set forth in FAR 23.361(a). (2) The limit engine torque corresponding to takeoff power and propeller speed, multiplied by a factor accounting for propeller control system malfunction, including quick feathering action, simultaneously with 1 <E T="03">g</E> level flight loads. In the absence of a rational analysis, a factor of 1.6 must be used. (b) The limit torque is obtained by multiplying the mean torque by a factor of 1.25. 25. <E T="03">Turbine engine gyroscopic loads.</E> Each turbopropeller engine mount and its supporting structure must be designed for the gyroscopic loads that result, with the engines at maximum continuous r.p.m., under either— (a) The conditions prescribed in FARs 23.351 and 23.423; or (b) All possible combinations of the following: (1) A yaw velocity of 2.5 radius per second. (2) A pitch velocity of 1.0 radians per second. (3) A normal load factor of 2.5. (4) Maximum continuous thrust. 26. <E T="03">Unsymmetrical loads due to engine failure.</E> (a) Turbopropeller powered airplanes must be designed for the unsymmetrical loads resulting from the failure of the critical engine including the following conditions in combination with a single malfunction of the propeller drag limiting system, considering the probable pilot corrective action on the flight controls. (1) At speeds between <E T="03">V</E> <E T="24">MC</E> and V<E T="24">D</E>, the loads resulting from power failure because of fuel flow interruption are considered to be limit loads. (2) At speeds between <E T="03">V</E> <E T="24">MC</E> and <E T="03">V</E> <E T="24">C</E>, the loads resulting from the disconnection of the engine compressor from the turbine or from loss of the turbine blades are considered to be ultimate loads. (3) The time history of the thrust decay and drag buildup occurring as a result of the prescribed engine failures must be substantiated by test or other data applicable to the particular engine-propeller combination. (4) The timing and magnitude of the probable pilot corrective action must be conservatively estimated, considering the characteristics of the particular engine-propeller-airplane combination. (b) Pilot corrective action may be assumed to be initiated at the time maximum yawing velocity is reached, but not earlier than two seconds after the engine failure. The magnitude of the corrective action may be based on the control forces specified in FAR 23.397 except that lower forces may be assumed where it is shown by analysis or test that these forces can control the yaw and roll resulting from the prescribed engine failure conditions. <HD SOURCE="HD1">Ground Loads</HD> 27. <E T="03">Dual wheel landing gear units.</E> Each dual wheel landing gear unit and its supporting structure must be shown to comply with the following: (a) <E T="03">Pivoting.</E> The airplane must be assumed to pivot about one side of the main gear with the brakes on that side locked. The limit vertical load factor must be 1.0 and the coefficient of friction 0.8. This condition need apply only to the main gear and its supporting structure. (b) <E T="03">Unequal tire inflation.</E> A 60-40 percent distribution of the loads established in accordance with FAR 23.471 through FAR 23.483 must be applied to the dual wheels. (c) <E T="03">Flat tire.</E> (1) Sixty percent of the loads specified in FAR 23.471 through FAR 23.483 must be applied to either wheel in a unit. (2) Sixty percent of the limit drag and side loads and 100 percent of the limit vertical load established in accordance with FARs 23.493 and 23.485 must be applied to either wheel in a unit except that the vertical load need not exceed the maximum vertical load in paragraph (c)(1) of this section. <HD SOURCE="HD1">Fatigue Evaluation</HD> 28. <E T="03">Fatigue evaluation of wing and associated structure.</E> Unless it is shown that the structure, operating stress levels, materials, and expected use are comparable from a fatigue standpoint to a similar design which has had substantial satisfactory service experience, the strength, detail design, and the fabrication of those parts of the wing, wing carrythrough, and attaching structure whose failure would be catastrophic must be evaluated under either— (a) A fatigue strength investigation in which the structure is shown by analysis, tests, or both to be able to withstand the repeated loads of variable magnitude expected in service; or (b) A fail-safe strength investigation in which it is shown by analysis, tests, or both that catastrophic failure of the structure is not probable after fatigue, or obvious partial failure, of a principal structural element, and that the remaining structure is able to withstand a static ultimate load factor of 75 percent of the critical limit load factor at <PRTPAGE P="160"/> <E T="03">V</E> <E T="24">c</E>. These loads must be multiplied by a factor of 1.15 unless the dynamic effects of failure under static load are otherwise considered. <HD SOURCE="HD1">Design and Construction</HD> 29. <E T="03">Flutter.</E> For Multiengine turbopropeller powered airplanes, a dynamic evaluation must be made and must include— (a) The significant elastic, inertia, and aerodynamic forces associated with the rotations and displacements of the plane of the propeller; and (b) Engine-propeller-nacelle stiffness and damping variations appropriate to the particular configuration. <HD SOURCE="HD1">Landing Gear</HD> 30. <E T="03">Flap operated landing gear warning device.</E> Airplanes having retractable landing gear and wing flaps must be equipped with a warning device that functions continuously when the wing flaps are extended to a flap position that activates the warning device to give adequate warning before landing, using normal landing procedures, if the landing gear is not fully extended and locked. There may not be a manual shut off for this warning device. The flap position sensing unit may be installed at any suitable location. The system for this device may use any part of the system (including the aural warning device) provided for other landing gear warning devices. <HD SOURCE="HD1">Personnel and Cargo Accommodations</HD> 31. <E T="03">Cargo and baggage compartments.</E> Cargo and baggage compartments must be designed to meet the requirements of FAR 23.787 (a) and (b), and in addition means must be provided to protect passengers from injury by the contents of any cargo or baggage compartment when the ultimate forward inertia force is 9<E T="03">g.</E> 32. <E T="03">Doors and exits.</E> The airplane must meet the requirements of FAR 23.783 and FAR 23.807 (a)(3), (b), and (c), and in addition: (a) There must be a means to lock and safeguard each external door and exit against opening in flight either inadvertently by persons, or as a result of mechanical failure. Each external door must be operable from both the inside and the outside. (b) There must be means for direct visual inspection of the locking mechanism by crewmembers to determine whether external doors and exits, for which the initial opening movement is outward, are fully locked. In addition, there must be a visual means to signal to crewmembers when normally used external doors are closed and fully locked. (c) The passenger entrance door must qualify as a floor level emergency exit. Each additional required emergency exit except floor level exits must be located over the wing or must be provided with acceptable means to assist the occupants in descending to the ground. In addition to the passenger entrance door: (1) For a total seating capacity of 15 or less, an emergency exit as defined in FAR 23.807(b) is required on each side of the cabin. (2) For a total seating capacity of 16 through 23, three emergency exits as defined in 23.807(b) are required with one on the same side as the door and two on the side opposite the door. (d) An evacuation demonstration must be conducted utilizing the maximum number of occupants for which certification is desired. It must be conducted under simulated night conditions utilizing only the emergency exits on the most critical side of the aircraft. The participants must be representative of average airline passengers with no prior practice or rehearsal for the demonstration. Evacuation must be completed within 90 seconds. (e) Each emergency exit must be marked with the word “Exit” by a sign which has white letters 1 inch high on a red background 2 inches high, be self-illuminated or independently internally electrically illuminated, and have a minimum luminescence (brightness) of at least 160 microlamberts. The colors may be reversed if the passenger compartment illumination is essentially the same. (f) Access to window type emergency exits must not be obstructed by seats or seat backs. (g) The width of the main passenger aisle at any point between seats must equal or exceed the values in the following table. <GPOTABLE CDEF="s50,r40,r40" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Total seating capacity</CHED> <CHED H="1">Minimum main passenger aisle width</CHED> <CHED H="2">Less than 25 inches from floor</CHED> <CHED H="2">25 inches and more from floor</CHED> </BOXHD> <ROW> <ENT I="01">10 through 23</ENT> <ENT>9 inches</ENT> <ENT>15 inches.</ENT> </ROW> </GPOTABLE> <HD SOURCE="HD1">Miscellaneous</HD> 33. <E T="03">Lightning strike protection.</E> Parts that are electrically insulated from the basic airframe must be connected to it through lightning arrestors unless a lightning strike on the insulated part— (a) Is improbable because of shielding by other parts; or (b) Is not hazardous. 34. <E T="03">Ice protection.</E> If certification with ice protection provisions is desired, compliance with the following requirements must be shown: (a) The recommended procedures for the use of the ice protection equipment must be set forth in the Airplane Flight Manual. (b) An analysis must be performed to establish, on the basis of the airplane's operational needs, the adequacy of the ice protection system for the various components of <PRTPAGE P="161"/>the airplane. In addition, tests of the ice protection system must be conducted to demonstrate that the airplane is capable of operating safely in continuous maximum and intermittent maximum icing conditions as described in FAR 25, appendix C. (c) Compliance with all or portions of this section may be accomplished by reference, where applicable because of similarity of the designs, to analysis and tests performed by the applicant for a type certificated model. 35. <E T="03">Maintenance information.</E> The applicant must make available to the owner at the time of delivery of the airplane the information he considers essential for the proper maintenance of the airplane. That information must include the following: (a) Description of systems, including electrical, hydraulic, and fuel controls. (b) Lubrication instructions setting forth the frequency and the lubricants and fluids which are to be used in the various systems. (c) Pressures and electrical loads applicable to the various systems. (d) Tolerances and adjustments necessary for proper functioning. (e) Methods of leveling, raising, and towing. (f) Methods of balancing control surfaces. (g) Identification of primary and secondary structures. (h) Frequency and extent of inspections necessary to the proper operation of the airplane. (i) Special repair methods applicable to the airplane. (j) Special inspection techniques, including those that require X-ray, ultrasonic, and magnetic particle inspection. (k) List of special tools. <HD SOURCE="HD1">Propulsion</HD> <HD SOURCE="HD1">general</HD> 36. <E T="03">Vibration characteristics.</E> For turbopropeller powered airplanes, the engine installation must not result in vibration characteristics of the engine exceeding those established during the type certification of the engine. 37. <E T="03">In-flight restarting of engine.</E> If the engine on turbopropeller powered airplanes cannot be restarted at the maximum cruise altitude, a determination must be made of the altitude below which restarts can be consistently accomplished. Restart information must be provided in the Airplane Flight Manual. 38. <E T="03">Engines</E>—(a) <E T="03">For turbopropeller powered airplanes.</E> The engine installation must comply with the following requirements: (1) <E T="03">Engine isolation.</E> The powerplants must be arranged and isolated from each other to allow operation, in at least one configuration, so that the failure or malfunction of any engine, or of any system that can affect the engine, will not— (i) Prevent the continued safe operation of the remaining engines; or (ii) Require immediate action by any crewmember for continued safe operation. (2) <E T="03">Control of engine rotation.</E> There must be a means to individually stop and restart the rotation of any engine in flight except that engine rotation need not be stopped if continued rotation could not jeopardize the safety of the airplane. Each component of the stopping and restarting system on the engine side of the firewall, and that might be exposed to fire, must be at least fire resistant. If hydraulic propeller feathering systems are used for this purpose, the feathering lines must be at least fire resistant under the operating conditions that may be expected to exist during feathering. (3) <E T="03">Engine speed and gas temperature control devices.</E> The powerplant systems associated with engine control devices, systems, and instrumentation must provide reasonable assurance that those engine operating limitations that adversely affect turbine rotor structural integrity will not be exceeded in service. (b) <E T="03">For reciprocating-engine powered airplanes.</E> To provide engine isolation, the powerplants must be arranged and isolated from each other to allow operation, in at least one configuration, so that the failure or malfunction of any engine, or of any system that can affect that engine, will not— (1) Prevent the continued safe operation of the remaining engines; or (2) Require immediate action by any crewmember for continued safe operation. 39. <E T="03">Turbopropeller reversing systems.</E> (a) Turbopropeller reversing systems intended for ground operation must be designed so that no single failure or malfunction of the system will result in unwanted reverse thrust under any expected operating condition. Failure of structural elements need not be considered if the probability of this kind of failure is extremely remote. (b) Turbopropeller reversing systems intended for in-flight use must be designed so that no unsafe condition will result during normal operation of the system, or from any failure (or reasonably likely combination of failures) of the reversing system, under any anticipated condition of operation of the airplane. Failure of structural elements need not be considered if the probability of this kind of failure is extremely remote. (c) Compliance with this section may be shown by failure analysis, testing, or both for propeller systems that allow propeller blades to move from the flight low-pitch position to a position that is substantially less than that at the normal flight low-pitch stop position. The analysis may include or be supported by the analysis made to show compliance with the type certification of the propeller and associated installation components. Credit will be given for pertinent <PRTPAGE P="162"/>analysis and testing completed by the engine and propeller manufacturers. 40. <E T="03">Turbopropeller drag-limiting systems.</E> Turbopropeller drag-limiting systems must be designed so that no single failure or malfunction of any of the systems during normal or emergency operation results in propeller drag in excess of that for which the airplane was designed. Failure of structural elements of the drag-limiting systems need not be considered if the probability of this kind of failure is extremely remote. 41. <E T="03">Turbine engine powerplant operating characteristics.</E> For turbopropeller powered airplanes, the turbine engine powerplant operating characteristics must be investigated in flight to determine that no adverse characteristics (such as stall, surge, or flameout) are present to a hazardous degree, during normal and emergency operation within the range of operating limitations of the airplane and of the engine. 42. <E T="03">Fuel flow.</E> (a) For turbopropeller powered airplanes— (1) The fuel system must provide for continuous supply of fuel to the engines for normal operation without interruption due to depletion of fuel in any tank other than the main tank; and (2) The fuel flow rate for turbopropeller engine fuel pump systems must not be less than 125 percent of the fuel flow required to develop the standard sea level atmospheric conditions takeoff power selected and included as an operating limitation in the Airplane Flight Manual. (b) For reciprocating engine powered airplanes, it is acceptable for the fuel flow rate for each pump system (main and reserve supply) to be 125 percent of the takeoff fuel consumption of the engine. <HD SOURCE="HD1">Fuel System Components</HD> 43. <E T="03">Fuel pumps.</E> For turbopropeller powered airplanes, a reliable and independent power source must be provided for each pump used with turbine engines which do not have provisions for mechanically driving the main pumps. It must be demonstrated that the pump installations provide a reliability and durability equivalent to that provided by FAR 23.991(a). 44. <E T="03">Fuel strainer or filter.</E> For turbopropeller powered airplanes, the following apply: (a) There must be a fuel strainer or filter between the tank outlet and the fuel metering device of the engine. In addition, the fuel strainer or filter must be— (1) Between the tank outlet and the engine-driven positive displacement pump inlet, if there is an engine-driven positive displacement pump; (2) Accessible for drainage and cleaning and, for the strainer screen, easily removable; and (3) Mounted so that its weight is not supported by the connecting lines or by the inlet or outlet connections of the strainer or filter itself. (b) Unless there are means in the fuel system to prevent the accumulation of ice on the filter, there must be means to automatically maintain the fuel flow if ice-clogging of the filter occurs; and (c) The fuel strainer or filter must be of adequate capacity (with respect to operating limitations established to insure proper service) and of appropriate mesh to insure proper engine operation, with the fuel contaminated to a degree (with respect to particle size and density) that can be reasonably expected in service. The degree of fuel filtering may not be less than that established for the engine type certification. 45. <E T="03">Lightning strike protection.</E> Protection must be provided against the ignition of flammable vapors in the fuel vent system due to lightning strikes. <HD SOURCE="HD1">Cooling</HD> 46. <E T="03">Cooling test procedures for turbopropeller powered airplanes.</E> (a) Turbopropeller powered airplanes must be shown to comply with the requirements of FAR 23.1041 during takeoff, climb en route, and landing stages of flight that correspond to the applicable performance requirements. The cooling test must be conducted with the airplane in the configuration and operating under the conditions that are critical relative to cooling during each stage of flight. For the cooling tests a temperature is “stabilized” when its rate of change is less than 2° F. per minute. (b) Temperatures must be stabilized under the conditions from which entry is made into each stage of flight being investigated unless the entry condition is not one during which component and engine fluid temperatures would stabilize, in which case, operation through the full entry condition must be conducted before entry into the stage of flight being investigated in order to allow temperatures to reach their natural levels at the time of entry. The takeoff cooling test must be preceded by a period during which the powerplant component and engine fluid temperatures are stabilized with the engines at ground idle. (c) Cooling tests for each stage of flight must be continued until— (1) The component and engine fluid temperatures stabilize; (2) The stage of flight is completed; or (3) An operating limitation is reached. <HD SOURCE="HD1">Induction System</HD> 47. <E T="03">Air induction.</E> For turbopropeller powered airplanes— (a) There must be means to prevent hazardous quantities of fuel leakage or overflow from drains, vents, or other components of flammable fluid systems from entering the engine intake system; and<PRTPAGE P="163"/> (b) The air inlet ducts must be located or protected so as to minimize the ingestion of foreign matter during takeoff, landing, and taxiing. 48. <E T="03">Induction system icing protection.</E> For turbopropeller powered airplanes, each turbine engine must be able to operate throughout its flight power range without adverse effect on engine operation or serious loss of power or thrust, under the icing conditions specified in appendix C of FAR 25. In addition, there must be means to indicate to appropriate flight crewmembers the functioning of the powerplant ice protection system. 49. <E T="03">Turbine engine bleed air systems.</E> Turbine engine bleed air systems of turbopropeller powered airplanes must be investigated to determine— (a) That no hazard to the airplane will result if a duct rupture occurs. This condition must consider that a failure of the duct can occur anywhere between the engine port and the airplane bleed service; and (b) That if the bleed air system is used for direct cabin pressurization, it is not possible for hazardous contamination of the cabin air system to occur in event of lubrication system failure. <HD SOURCE="HD1">Exhaust System</HD> 50. <E T="03">Exhaust system drains.</E> Turbopropeller engine exhaust systems having low spots or pockets must incorporate drains at such locations. These drains must discharge clear of the airplane in normal and ground attitudes to prevent the accumulation of fuel after the failure of an attempted engine start. <HD SOURCE="HD1">Powerplant Controls and Accessories</HD> 51. <E T="03">Engine controls.</E> If throttles or power levers for turbopropeller powered airplanes are such that any position of these controls will reduce the fuel flow to the engine(s) below that necessary for satisfactory and safe idle operation of the engine while the airplane is in flight, a means must be provided to prevent inadvertent movement of the control into this position. The means provided must incorporate a positive lock or stop at this idle position and must require a separate and distinct operation by the crew to displace the control from the normal engine operating range. 52. <E T="03">Reverse thrust controls.</E> For turbopropeller powered airplanes, the propeller reverse thrust controls must have a means to prevent their inadvertent operation. The means must have a positive lock or stop at the idle position and must require a separate and distinct operation by the crew to displace the control from the flight regime. 53. <E T="03">Engine ignition systems.</E> Each turbopropeller airplane ignition system must be considered an essential electrical load. 54. <E T="03">Powerplant accessories.</E> The powerplant accessories must meet the requirements of FAR 23.1163, and if the continued rotation of any accessory remotely driven by the engine is hazardous when malfunctioning occurs, there must be means to prevent rotation without interfering with the continued operation of the engine. <HD SOURCE="HD1">Powerplant Fire Protection</HD> 55. <E T="03">Fire detector system.</E> For turbopropeller powered airplanes, the following apply: (a) There must be a means that ensures prompt detection of fire in the engine compartment. An overtemperature switch in each engine cooling air exit is an acceptable method of meeting this requirement. (b) Each fire detector must be constructed and installed to withstand the vibration, inertia, and other loads to which it may be subjected in operation. (c) No fire detector may be affected by any oil, water, other fluids, or fumes that might be present. (d) There must be means to allow the flight crew to check, in flight, the functioning of each fire detector electric circuit. (e) Wiring and other components of each fire detector system in a fire zone must be at least fire resistant. 56. <E T="03">Fire protection, cowling and nacelle skin.</E> For reciprocating engine powered airplanes, the engine cowling must be designed and constructed so that no fire originating in the engine compartment can enter, either through openings or by burn through, any other region where it would create additional hazards. 57. <E T="03">Flammable fluid fire protection.</E> If flammable fluids or vapors might be liberated by the leakage of fluid systems in areas other than engine compartments, there must be means to— (a) Prevent the ignition of those fluids or vapors by any other equipment; or (b) Control any fire resulting from that ignition. <HD SOURCE="HD1">Equipment</HD> 58. <E T="03">Powerplant instruments.</E> (a) The following are required for turbopropeller airplanes: (1) The instruments required by FAR 23.1305 (a)(1) through (4), (b)(2) and (4). (2) A gas temperature indicator for each engine. (3) Free air temperature indicator. (4) A fuel flowmeter indicator for each engine. (5) Oil pressure warning means for each engine. (6) A torque indicator or adequate means for indicating power output for each engine. (7) Fire warning indicator for each engine. (8) A means to indicate when the propeller blade angle is below the low-pitch position corresponding to idle operation in flight. (9) A means to indicate the functioning of the ice protection system for each engine.<PRTPAGE P="164"/> (b) For turbopropeller powered airplanes, the turbopropeller blade position indicator must begin indicating when the blade has moved below the flight low-pitch position. (c) The following instruments are required for reciprocating-engine powered airplanes: (1) The instruments required by FAR 23.1305. (2) A cylinder head temperature indicator for each engine. (3) A manifold pressure indicator for each engine. <HD SOURCE="HD1">Systems and Equipments</HD> <HD SOURCE="HD1">general</HD> 59. <E T="03">Function and installation.</E> The systems and equipment of the airplane must meet the requirements of FAR 23.1301, and the following: (a) Each item of additional installed equipment must— (1) Be of a kind and design appropriate to its intended function; (2) Be labeled as to its identification, function, or operating limitations, or any applicable combination of these factors, unless misuse or inadvertent actuation cannot create a hazard; (3) Be installed according to limitations specified for that equipment; and (4) Function properly when installed. (b) Systems and installations must be designed to safeguard against hazards to the aircraft in the event of their malfunction or failure. (c) Where an installation, the functioning of which is necessary in showing compliance with the applicable requirements, requires a power supply, such installation must be considered an essential load on the power supply, and the power sources and the distribution system must be capable of supplying the following power loads in probable operation combinations and for probable durations: (1) All essential loads after failure of any prime mover, power converter, or energy storage device. (2) All essential loads after failure of any one engine on two-engine airplanes. (3) In determining the probable operating combinations and durations of essential loads for the power failure conditions described in subparagraphs (1) and (2) of this paragraph, it is permissible to assume that the power loads are reduced in accordance with a monitoring procedure which is consistent with safety in the types of operations authorized. 60. <E T="03">Ventilation.</E> The ventilation system of the airplane must meet the requirements of FAR 23.831, and in addition, for pressurized aircraft the ventilating air in flight crew and passenger compartments must be free of harmful or hazardous concentrations of gases and vapors in normal operation and in the event of reasonably probable failures or malfunctioning of the ventilating, heating, pressurization, or other systems, and equipment. If accumulation of hazardous quantities of smoke in the cockpit area is reasonably probable, smoke evacuation must be readily accomplished. <HD SOURCE="HD1">Electrical Systems and Equipment</HD> 61. <E T="03">General.</E> The electrical systems and equipment of the airplane must meet the requirements of FAR 23.1351, and the following: (a) <E T="03">Electrical system capacity.</E> The required generating capacity, and number and kinds of power sources must— (1) Be determined by an electrical load analysis, and (2) Meet the requirements of FAR 23.1301. (b) <E T="03">Generating system.</E> The generating system includes electrical power sources, main power busses, transmission cables, and associated control, regulation, and protective devices. It must be designed so that— (1) The system voltage and frequency (as applicable) at the terminals of all essential load equipment can be maintained within the limits for which the equipment is designed, during any probable operating conditions; (2) System transients due to switching, fault clearing, or other causes do not make essential loads inoperative, and do not cause a smoke or fire hazard; (3) There are means, accessible in flight to appropriate crewmembers, for the individual and collective disconnection of the electrical power sources from the system; and (4) There are means to indicate to appropriate crewmembers the generating system quantities essential for the safe operation of the system, including the voltage and current supplied by each generator. 62. <E T="03">Electrical equipment and installation.</E> Electrical equipment controls, and wiring must be installed so that operation of any one unit or system of units will not adversely affect the simultaneous operation of to the safe operation. 63. <E T="03">Distribution system.</E> (a) For the purpose of complying with this section, the distribution system includes the distribution busses, their associated feeders and each control and protective device. (b) Each system must be designed so that essential load circuits can be supplied in the event of reasonably probable faults or open circuits, including faults in heavy current carrying cables. (c) If two independent sources of electrical power for particular equipment or systems are required by this regulation, their electrical energy supply must be insured by means such as duplicate electrical equipment, throwover switching, or multichannel or loop circuits separately routed. 64. <E T="03">Circuit protective devices.</E> The circuit protective devices for the electrical circuits of the airplane must meet the requirements <PRTPAGE P="165"/>of FAR 23.1357, and in addition circuits for loads which are essential to safe operation must have individual and exclusive circuit protection. </EXTRACT> <CITA>[Doc. No. 8070, 34 FR 189, Jan. 7, 1969, as amended by SFAR 23-1, 34 FR 20176, Dec. 24, 1969; 35 FR 1102, Jan. 28, 1970]</CITA> <EAR>Pt. 23, SFAR No. 41</EAR> <SUBJGRP> <HD SOURCE="HED">SFAR No. <E T="01">41</E> </HD> <EDNOTE> <HD SOURCE="HED">Editorial Note:</HD> For the text of SFAR No. 41, see part 21 of this chapter. </EDNOTE> </SUBJGRP> <SUBPART> <HD SOURCE="HED">Subpart A—General</HD> <SECTION> <SECTNO>§ 23.1</SECTNO> <SUBJECT>Applicability.</SUBJECT> (a) This part prescribes airworthiness standards for the issue of type certificates, and changes to those certificates, for airplanes in the normal, utility, acrobatic, and commuter categories. (b) Each person who applies under Part 21 for such a certificate or change must show compliance with the applicable requirements of this part. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-34, 52 FR 1825, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.2</SECTNO> <SUBJECT>Special retroactive requirements.</SUBJECT> (a) Notwithstanding §§ 21.17 and 21.101 of this chapter and irrespective of the type certification basis, each normal, utility, and acrobatic category airplane having a passenger seating configuration, excluding pilot seats, of nine or less, manufactured after December 12, 1986, or any such foreign airplane for entry into the United States must provide a safety belt and shoulder harness for each forward- or aft-facing seat which will protect the occupant from serious head injury when subjected to the inertia loads resulting from the ultimate static load factors prescribed in § 23.561(b)(2) of this part, or which will provide the occupant protection specified in § 23.562 of this part when that section is applicable to the airplane. For other seat orientations, the seat/restraint system must be designed to provide a level of occupant protection equivalent to that provided for forward- or aft-facing seats with a safety belt and shoulder harness installed. (b) Each shoulder harness installed at a flight crewmember station, as required by this section, must allow the crewmember, when seated with the safety belt and shoulder harness fastened, to perform all functions necessary for flight operations. (c) For the purpose of this section, the date of manufacture is: (1) The date the inspection acceptance records, or equivalent, reflect that the airplane is complete and meets the FAA approved type design data; or (2) In the case of a foreign manufactured airplane, the date the foreign civil airworthiness authority certifies the airplane is complete and issues an original standard airworthiness certificate, or the equivalent in that country. <CITA>[Amdt. 23-36, 53 FR 30812, Aug. 15, 1988]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.3</SECTNO> <SUBJECT>Airplane categories.</SUBJECT> (a) The normal category is limited to airplanes that have a seating configuration, excluding pilot seats, of nine or less, a maximum certificated takeoff weight of 12,500 pounds or less, and intended for nonacrobatic operation. Nonacrobatic operation includes: (1) Any maneuver incident to normal flying; (2) Stalls (except whip stalls); and (3) Lazy eights, chandelles, and steep turns, in which the angle of bank is not more than 60 degrees. (b) The utility category is limited to airplanes that have a seating configuration, excluding pilot seats, of nine or less, a maximum certificated takeoff weight of 12,500 pounds or less, and intended for limited acrobatic operation. Airplanes certificated in the utility category may be used in any of the operations covered under paragraph (a) of this section and in limited acrobatic operations. Limited acrobatic operation includes: (1) Spins (if approved for the particular type of airplane); and (2) Lazy eights, chandelles, and steep turns, or similar maneuvers, in which the angle of bank is more than 60 degrees but not more than 90 degrees. (c) The acrobatic category is limited to airplanes that have a seating configuration, excluding pilot seats, of nine or less, a maximum certificated takeoff weight of 12,500 pounds or less, <PRTPAGE P="166"/>and intended for use without restrictions, other than those shown to be necessary as a result of required flight tests. (d) The commuter category is limited to propeller-driven, multiengine airplanes that have a seating configuration, excluding pilot seats, of 19 or less, and a maximum certificated takeoff weight of 19,000 pounds or less. The commuter category operation is limited to any maneuver incident to normal flying, stalls (except whip stalls), and steep turns, in which the angle of bank is not more than 60 degrees. (e) Except for commuter category, airplanes may be type certificated in more than one category if the requirements of each requested category are met. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-4, 32 FR 5934, Apr. 14, 1967; Amdt. 23-34, 52 FR 1825, Jan. 15, 1987; 52 FR 34745, Sept. 14, 1987; Amdt. 23-50, 61 FR 5183, Feb. 9, 1996]</CITA> </SECTION> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart B—Flight</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTION> <SECTNO>§ 23.21</SECTNO> <SUBJECT>Proof of compliance.</SUBJECT> (a) Each requirement of this subpart must be met at each appropriate combination of weight and center of gravity within the range of loading conditions for which certification is requested. This must be shown— (1) By tests upon an airplane of the type for which certification is requested, or by calculations based on, and equal in accuracy to, the results of testing; and (2) By systematic investigation of each probable combination of weight and center of gravity, if compliance cannot be reasonably inferred from combinations investigated. (b) The following general tolerances are allowed during flight testing. However, greater tolerances may be allowed in particular tests: <GPOTABLE CDEF="s80,r50" COLS="2" OPTS="L2"> <BOXHD> <CHED H="1">Item</CHED> <CHED H="1">Tolerance</CHED> </BOXHD> <ROW> <ENT I="01">Weight</ENT> <ENT>+5%, -10%.</ENT> </ROW> <ROW> <ENT I="01">Critical items affected by weight</ENT> <ENT>+5%, -1%.</ENT> </ROW> <ROW> <ENT I="01">C.G</ENT> <ENT> <E T="21">±</E>7% total travel.</ENT> </ROW> </GPOTABLE> </SECTION> <SECTION> <SECTNO>§ 23.23</SECTNO> <SUBJECT>Load distribution limits.</SUBJECT> (a) Ranges of weights and centers of gravity within which the airplane may be safely operated must be established. If a weight and center of gravity combination is allowable only within certain lateral load distribution limits that could be inadvertently exceeded, these limits must be established for the corresponding weight and center of gravity combinations. (b) The load distribution limits may not exceed any of the following: (1) The selected limits; (2) The limits at which the structure is proven; or (3) The limits at which compliance with each applicable flight requirement of this subpart is shown. <CITA>[Doc. No. 26269, 58 FR 42156, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.25</SECTNO> <SUBJECT>Weight limits.</SUBJECT> (a) <E T="03">Maximum weight.</E> The maximum weight is the highest weight at which compliance with each applicable requirement of this part (other than those complied with at the design landing weight) is shown. The maximum weight must be established so that it is— (1) Not more than the least of— (i) The highest weight selected by the applicant; or (ii) The design maximum weight, which is the highest weight at which compliance with each applicable structural loading condition of this part (other than those complied with at the design landing weight) is shown; or (iii) The highest weight at which compliance with each applicable flight requirement is shown, and (2) Not less than the weight with— (i) Each seat occupied, assuming a weight of 170 pounds for each occupant for normal and commuter category airplanes, and 190 pounds for utility and acrobatic category airplanes, except that seats other than pilot seats may be placarded for a lesser weight; and (A) Oil at full capacity, and (B) At least enough fuel for maximum continuous power operation of at least 30 minutes for day-VFR approved airplanes and at least 45 minutes for night-VFR and IFR approved airplanes; or<PRTPAGE P="167"/> (ii) The required minimum crew, and fuel and oil to full tank capacity. (b) <E T="03">Minimum weight.</E> The minimum weight (the lowest weight at which compliance with each applicable requirement of this part is shown) must be established so that it is not more than the sum of— (1) The empty weight determined under § 23.29; (2) The weight of the required minimum crew (assuming a weight of 170 pounds for each crewmember); and (3) The weight of— (i) For turbojet powered airplanes, 5 percent of the total fuel capacity of that particular fuel tank arrangement under investigation, and (ii) For other airplanes, the fuel necessary for one-half hour of operation at maximum continuous power. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13086, Aug. 13, 1969; Amdt. 23-21, 43 FR 2317, Jan. 16, 1978; Amdt. 23-34, 52 FR 1825, Jan. 15, 1987; Amdt. 23-45, 58 FR 42156, Aug. 6, 1993; Amdt. 23-50, 61 FR 5183, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.29</SECTNO> <SUBJECT>Empty weight and corresponding center of gravity.</SUBJECT> (a) The empty weight and corresponding center of gravity must be determined by weighing the airplane with— (1) Fixed ballast; (2) Unusable fuel determined under § 23.959; and (3) Full operating fluids, including— (i) Oil; (ii) Hydraulic fluid; and (iii) Other fluids required for normal operation of airplane systems, except potable water, lavatory precharge water, and water intended for injection in the engines. (b) The condition of the airplane at the time of determining empty weight must be one that is well defined and can be easily repeated. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-21, 43 FR 2317, Jan. 16, 1978]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.31</SECTNO> <SUBJECT>Removable ballast.</SUBJECT> Removable ballast may be used in showing compliance with the flight requirements of this subpart, if— (a) The place for carrying ballast is properly designed and installed, and is marked under § 23.1557; and (b) Instructions are included in the airplane flight manual, approved manual material, or markings and placards, for the proper placement of the removable ballast under each loading condition for which removable ballast is necessary. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-13, 37 FR 20023, Sept. 23, 1972]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.33</SECTNO> <SUBJECT>Propeller speed and pitch limits.</SUBJECT> (a) <E T="03">General.</E> The propeller speed and pitch must be limited to values that will assure safe operation under normal operating conditions. (b) <E T="03">Propellers not controllable in flight.</E> For each propeller whose pitch cannot be controlled in flight— (1) During takeoff and initial climb at the all engine(s) operating climb speed specified in § 23.65, the propeller must limit the engine r.p.m., at full throttle or at maximum allowable takeoff manifold pressure, to a speed not greater than the maximum allowable takeoff r.p.m.; and (2) During a closed throttle glide, at V<E T="52">NE</E>, the propeller may not cause an engine speed above 110 percent of maximum continuous speed. (c) <E T="03">Controllable pitch propellers without constant speed controls.</E> Each propeller that can be controlled in flight, but that does not have constant speed controls, must have a means to limit the pitch range so that— (1) The lowest possible pitch allows compliance with paragraph (b)(1) of this section; and (2) The highest possible pitch allows compliance with paragraph (b)(2) of this section. (d) <E T="03">Controllable pitch propellers with constant speed controls.</E> Each controllable pitch propeller with constant speed controls must have— (1) With the governor in operation, a means at the governor to limit the maximum engine speed to the maximum allowable takeoff r.p.m.; and (2) With the governor inoperative, the propeller blades at the lowest possible pitch, with takeoff power, the airplane stationary, and no wind, either—<PRTPAGE P="168"/> (i) A means to limit the maximum engine speed to 103 percent of the maximum allowable takeoff r.p.m., or (ii) For an engine with an approved overspeed, a means to limit the maximum engine and propeller speed to not more than the maximum approved overspeed. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42156, Aug. 6, 1993; Amdt. 23-50, 61 FR 5183, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Performance</HD> <SECTION> <SECTNO>§ 23.45</SECTNO> <SUBJECT>General.</SUBJECT> (a) Unless otherwise prescribed, the performance requirements of this part must be met for— (1) Still air and standard atmosphere; and (2) Ambient atmospheric conditions, for commuter category airplanes, for reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and for turbine engine-powered airplanes. (b) Performance data must be determined over not less than the following ranges of conditions— (1) Airport altitudes from sea level to 10,000 feet; and (2) For reciprocating engine-powered airplanes of 6,000 pounds, or less, maximum weight, temperature from standard to 30 °C above standard; or (3) For reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight and turbine engine-powered airplanes, temperature from standard to 30 °C above standard, or the maximum ambient atmospheric temperature at which compliance with the cooling provisions of § 23.1041 to § 23.1047 is shown, if lower. (c) Performance data must be determined with the cowl flaps or other means for controlling the engine cooling air supply in the position used in the cooling tests required by § 23.1041 to § 23.1047. (d) The available propulsive thrust must correspond to engine power, not exceeding the approved power, less— (1) Installation losses; and (2) The power absorbed by the accessories and services appropriate to the particular ambient atmospheric conditions and the particular flight condition. (e) The performance, as affected by engine power or thrust, must be based on a relative humidity: (1) Of 80 percent at and below standard temperature; and (2) From 80 percent, at the standard temperature, varying linearly down to 34 percent at the standard temperature plus 50 °F. (f) Unless otherwise prescribed, in determining the takeoff and landing distances, changes in the airplane's configuration, speed, and power must be made in accordance with procedures established by the applicant for operation in service. These procedures must be able to be executed consistently by pilots of average skill in atmospheric conditions reasonably expected to be encountered in service. (g) The following, as applicable, must be determined on a smooth, dry, hard-surfaced runway— (1) Takeoff distance of § 23.53(b); (2) Accelerate-stop distance of § 23.55; (3) Takeoff distance and takeoff run of § 23.59; and (4) Landing distance of § 23.75. <NOTE> <HD SOURCE="HED">Note:</HD> The effect on these distances of operation on other types of surfaces (for example, grass, gravel) when dry, may be determined or derived and these surfaces listed in the Airplane Flight Manual in accordance with § 23.1583(p). </NOTE> (h) For commuter category airplanes, the following also apply: (1) Unless otherwise prescribed, the applicant must select the takeoff, enroute, approach, and landing configurations for the airplane. (2) The airplane configuration may vary with weight, altitude, and temperature, to the extent that they are compatible with the operating procedures required by paragraph (h)(3) of this section. (3) Unless otherwise prescribed, in determining the critical-engine-inoperative takeoff performance, takeoff flight path, and accelerate-stop distance, changes in the airplane's configuration, speed, and power must be made in accordance with procedures established by the applicant for operation in service. (4) Procedures for the execution of discontinued approaches and balked landings associated with the conditions prescribed in § 23.67(c)(4) and § 23.77(c) must be established.<PRTPAGE P="169"/> (5) The procedures established under paragraphs (h)(3) and (h)(4) of this section must— (i) Be able to be consistently executed by a crew of average skill in atmospheric conditions reasonably expected to be encountered in service; (ii) Use methods or devices that are safe and reliable; and (iii) Include allowance for any reasonably expected time delays in the execution of the procedures. <CITA>[Doc. No. 27807, 61 FR 5184, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.49</SECTNO> <SUBJECT>Stalling period.</SUBJECT> (a) V<E T="52">SO</E> and V<E T="52">S1</E> are the stalling speeds or the minimum steady flight speeds, in knots (CAS), at which the airplane is controllable with— (1) For reciprocating engine-powered airplanes, the engine(s) idling, the throttle(s) closed or at not more than the power necessary for zero thrust at a speed not more than 110 percent of the stalling speed; (2) For turbine engine-powered airplanes, the propulsive thrust not greater than zero at the stalling speed, or, if the resultant thrust has no appreciable effect on the stalling speed, with engine(s) idling and throttle(s) closed; (3) The propeller(s) in the takeoff position; (4) The airplane in the condition existing in the test, in which V<E T="52">SO</E> and V<E T="52">S1</E> are being used; (5) The center of gravity in the position that results in the highest value of V<E T="52">SO</E> and V<E T="52">S1</E>; and (6) The weight used when V<E T="52">SO</E> and V<E T="52">S1</E> are being used as a factor to determine compliance with a required performance standard. (b) V<E T="52">SO</E> and V<E T="52">S1</E> must be determined by flight tests, using the procedure and meeting the flight characteristics specified in § 23.201. (c) Except as provided in paragraph (d) of this section, V<E T="52">SO</E> and V<E T="52">S1</E> at maximum weight must not exceed 61 knots for— (1) Single-engine airplanes; and (2) Multiengine airplanes of 6,000 pounds or less maximum weight that cannot meet the minimum rate of climb specified in § 23.67(a) (1) with the critical engine inoperative. (d) All single-engine airplanes, and those multiengine airplanes of 6,000 pounds or less maximum weight with a V<E T="52">SO</E> of more than 61 knots that do not meet the requirements of § 23.67(a)(1), must comply with § 23.562(d). <CITA>[Doc. No. 27807, 61 FR 5184, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.51</SECTNO> <SUBJECT>Takeoff speeds.</SUBJECT> (a) For normal, utility, and acrobatic category airplanes, rotation speed, V<E T="52">R</E>, is the speed at which the pilot makes a control input, with the intention of lifting the airplane out of contact with the runway or water surface. (1) For multiengine landplanes, V<E T="52">R</E>, must not be less than the greater of 1.05 V<E T="52">MC</E>; or 1.10 V<E T="52">S1</E>; (2) For single-engine landplanes, V<E T="52">R</E>, must not be less than V<E T="52">S1</E>; and (3) For seaplanes and amphibians taking off from water, V<E T="52">R</E>, may be any speed that is shown to be safe under all reasonably expected conditions, including turbulence and complete failure of the critical engine. (b) For normal, utility, and acrobatic category airplanes, the speed at 50 feet above the takeoff surface level must not be less than: (1) or multiengine airplanes, the highest of— (i) A speed that is shown to be safe for continued flight (or emergency landing, if applicable) under all reasonably expected conditions, including turbulence and complete failure of the critical engine; (ii) 1.10 V<E T="52">MC</E>; or (iii) 1.20 V<E T="52">S1</E>. (2) For single-engine airplanes, the higher of— (i) A speed that is shown to be safe under all reasonably expected conditions, including turbulence and complete engine failure; or (ii) 1.20 V<E T="52">S1</E>. (c) For commuter category airplanes, the following apply: (l) V<E T="52">1</E> must be established in relation to V<E T="52">EF</E> as follows: (i) V<E T="52">EF</E> is the calibrated airspeed at which the critical engine is assumed to fail. V<E T="52">EF</E> must be selected by the applicant but must not be less than 1.05 V<E T="52">MC</E> determined under § 23.149(b) or, at the option of the applicant, not less than V<E T="52">MCG</E> determined under § 23.149(f). (ii) The takeoff decision speed, V<E T="52">1</E>, is the calibrated airspeed on the ground at which, as a result of engine failure <PRTPAGE P="170"/>or other reasons, the pilot is assumed to have made a decision to continue or discontinue the takeoff. The takeoff decision speed, V<E T="52">1</E>, must be selected by the applicant but must not be less than V<E T="52">EF</E> plus the speed gained with the critical engine inoperative during the time interval between the instant at which the critical engine is failed and the instant at which the pilot recognizes and reacts to the engine failure, as indicated by the pilot's application of the first retarding means during the accelerate-stop determination of § 23.55. (2) The rotation speed, V<E T="52">R</E>, in terms of calibrated airspeed, must be selected by the applicant and must not be less than the greatest of the following: (i) V<E T="52">1</E>; (ii) 1.05 V<E T="52">MC</E> determined under § 23.149(b); (iii) 1.10 V<E T="52">S1</E>; or (iv) The speed that allows attaining the initial climb-out speed, V<E T="52">2</E>, before reaching a height of 35 feet above the takeoff surface in accordance with § 23.57(c)(2). (3) For any given set of conditions, such as weight, altitude, temperature, and configuration, a single value of V<E T="52">R</E> must be used to show compliance with both the one-engine-inoperative takeoff and all-engines-operating takeoff requirements. (4) The takeoff safety speed, V<E T="52">2</E>, in terms of calibrated airspeed, must be selected by the applicant so as to allow the gradient of climb required in § 23.67 (c)(1) and (c)(2) but mut not be less than 1.10 V<E T="52">MC</E> or less than 1.20 V<E T="52">S1</E>. (5) The one-engine-inoperative takeoff distance, using a normal rotation rate at a speed 5 knots less than V<E T="52">R</E>, established in accordance with paragraph (c)(2) of this section, must be shown not to exceed the corresponding one-engine-inoperative takeoff distance, determined in accordance with § 23.57 and § 23.59(a)(1), using the established V<E T="52">R</E>. The takeoff, otherwise performed in accordance with § 23.57, must be continued safely from the point at which the airplane is 35 feet above the takeoff surface and at a speed not less than the established V<E T="52">2</E> minus 5 knots. (6) The applicant must show, with all engines operating, that marked increases in the scheduled takeoff distances, determined in accordance with § 23.59(a)(2), do not result from over-rotation of the airplane or out-of-trim conditions. <CITA>[Doc. No. 27807, 61 FR 5184, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.53</SECTNO> <SUBJECT>Takeoff performance.</SUBJECT> (a) For normal, utility, and acrobatic category airplanes, the takeoff distance must be determined in accordance with paragraph (b) of this section, using speeds determined in accordance with § 23.51 (a) and (b). (b) For normal, utility, and acrobatic category airplanes, the distance required to takeoff and climb to a height of 50 feet above the takeoff surface must be determined for each weight, altitude, and temperature within the operational limits established for takeoff with— (1) Takeoff power on each engine; (2) Wing flaps in the takeoff position(s); and (3) Landing gear extended. (c) For commuter category airplanes, takeoff performance, as required by §§ 23.55 through 23.59, must be determined with the operating engine(s) within approved operating limitations. <CITA>[Doc. No. 27807, 61 FR 5185, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.55</SECTNO> <SUBJECT>Accelerate-stop distance.</SUBJECT> For each commuter category airplane, the accelerate-stop distance must be determined as follows: (a) The accelerate-stop distance is the sum of the distances necessary to— (1) Accelerate the airplane from a standing start to V<E T="52">EF</E> with all engines operating; (2) Accelerate the airplane from V<E T="52">EF</E> to V<E T="52">1</E>, assuming the critical engine fails at V<E T="52">EF</E>; and (3) Come to a full stop from the point at which V<E T="52">1</E> is reached. (b) Means other than wheel brakes may be used to determine the accelerate-stop distances if that means— (1) Is safe and reliable; (2) Is used so that consistent results can be expected under normal operating conditions; and (3) Is such that exceptional skill is not required to control the airplane. <CITA>[Amdt. 23-34, 52 FR 1826, Jan. 15, 1987, as amended by Amdt. 23-50, 61 FR 5185, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <PRTPAGE P="171"/> <SECTNO>§ 23.57</SECTNO> <SUBJECT>Takeoff path.</SUBJECT> For each commuter category airplane, the takeoff path is as follows: (a) The takeoff path extends from a standing start to a point in the takeoff at which the airplane is 1500 feet above the takeoff surface at or below which height the transition from the takeoff to the enroute configuration must be completed; and (1) The takeoff path must be based on the procedures prescribed in § 23.45; (2) The airplane must be accelerated on the ground to V<E T="54">EF</E> at which point the critical engine must be made inoperative and remain inoperative for the rest of the takeoff; and (3) After reaching V<E T="54">EF</E>, the airplane must be accelerated to V<E T="54">2</E>. (b) During the acceleration to speed V<E T="52">2</E>, the nose gear may be raised off the ground at a speed not less than V<E T="52">R</E>. However, landing gear retraction must not be initiated until the airplane is airborne. (c) During the takeoff path determination, in accordance with paragraphs (a) and (b) of this section— (1) The slope of the airborne part of the takeoff path must not be negative at any point; (2) The airplane must reach V<E T="54">2</E> before it is 35 feet above the takeoff surface, and must continue at a speed as close as practical to, but not less than V<E T="54">2</E>, until it is 400 feet above the takeoff surface; (3) At each point along the takeoff path, starting at the point at which the airplane reaches 400 feet above the takeoff surface, the available gradient of climb must not be less than— (i) 1.2 percent for two-engine airplanes; (ii) 1.5 percent for three-engine airplanes; (iii) 1.7 percent for four-engine airplanes; and (4) Except for gear retraction and automatic propeller feathering, the airplane configuration must not be changed, and no change in power that requires action by the pilot may be made, until the airplane is 400 feet above the takeoff surface. (d) The takeoff path to 35 feet above the takeoff surface must be determined by a continuous demonstrated takeoff. (e) The takeoff path to 35 feet above the takeoff surface must be determined by synthesis from segments; and (1) The segments must be clearly defined and must be related to distinct changes in configuration, power, and speed; (2) The weight of the airplane, the configuration, and the power must be assumed constant throughout each segment and must correspond to the most critical condition prevailing in the segment; and (3) The takeoff flight path must be based on the airplane's performance without utilizing ground effect. <CITA>[Amdt. 23-34, 52 FR 1827, Jan. 15, 1987, as amended by Amdt. 23-50, 61 FR 5185, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.59</SECTNO> <SUBJECT>Takeoff distance and takeoff run.</SUBJECT> For each commuter category airplane, the takeoff distance and, at the option of the applicant, the takeoff run, must be determined. (a) Takeoff distance is the greater of— (1) The horizontal distance along the takeoff path from the start of the takeoff to the point at which the airplane is 35 feet above the takeoff surface as determined under § 23.57; or (2) With all engines operating, 115 percent of the horizontal distance from the start of the takeoff to the point at which the airplane is 35 feet above the takeoff surface, determined by a procedure consistent with § 23.57. (b) If the takeoff distance includes a clearway, the takeoff run is the greater of— (1) The horizontal distance along the takeoff path from the start of the takeoff to a point equidistant between the liftoff point and the point at which the airplane is 35 feet above the takeoff surface as determined under § 23.57; or (2) With all engines operating, 115 percent of the horizontal distance from the start of the takeoff to a point equidistant between the liftoff point and the point at which the airplane is 35 feet above the takeoff surface, determined by a procedure consistent with § 23.57. <CITA>[Amdt. 23-34, 52 FR 1827, Jan. 15, 1987, as amended by Amdt. 23-50, 61 FR 5185, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <PRTPAGE P="172"/> <SECTNO>§ 23.61</SECTNO> <SUBJECT>Takeoff flight path.</SUBJECT> For each commuter category airplane, the takeoff flight path must be determined as follows: (a) The takeoff flight path begins 35 feet above the takeoff surface at the end of the takeoff distance determined in accordance with § 23.59. (b) The net takeoff flight path data must be determined so that they represent the actual takeoff flight paths, as determined in accordance with § 23.57 and with paragraph (a) of this section, reduced at each point by a gradient of climb equal to— (1) 0.8 percent for two-engine airplanes; (2) 0.9 percent for three-engine airplanes; and (3) 1.0 percent for four-engine airplanes. (c) The prescribed reduction in climb gradient may be applied as an equivalent reduction in acceleration along that part of the takeoff flight path at which the airplane is accelerated in level flight. <CITA>[Amdt. 23-34, 52 FR 1827, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.63</SECTNO> <SUBJECT>Climb: general.</SUBJECT> (a) Compliance with the requirements of §§ 23.65, 23.66, 23.67, 23.69, and 23.77 must be shown— (1) Out of ground effect; and (2) At speeds that are not less than those at which compliance with the powerplant cooling requirements of §§ 23.1041 to 23.1047 has been demonstrated; and (3) Unless otherwise specified, with one engine inoperative, at a bank angle not exceeding 5 degrees. (b) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, compliance must be shown with § 23.65(a), § 23.67(a), where appropriate, and § 23.77(a) at maximum takeoff or landing weight, as appropriate, in a standard atmosphere. (c) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-powered airplanes in the normal, utility, and acrobatic category, compliance must be shown at weights as a function of airport altitude and ambient temperature, within the operational limits established for takeoff and landing, respectively, with— (1) Sections 23.65(b) and 23.67(b) (1) and (2), where appropriate, for takeoff, and (2) Section 23.67(b)(2), where appropriate, and § 23.77(b), for landing. (d) For commuter category airplanes, compliance must be shown at weights as a function of airport altitude and ambient temperature within the operational limits established for takeoff and landing, respectively, with— (1) Sections 23.67(c)(1), 23.67(c)(2), and 23.67(c)(3) for takeoff; and (2) Sections 23.67(c)(3), 23.67(c)(4), and 23.77(c) for landing. <CITA>[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.65</SECTNO> <SUBJECT>Climb: all engines operating.</SUBJECT> (a) Each normal, utility, and acrobatic category reciprocating engine-powered airplane of 6,000 pounds or less maximum weight must have a steady climb gradient at sea level of at least 8.3 percent for landplanes or 6.7 percet for seaplanes and amphibians with— (1) Not more than maximum continuous power on each engine; (2) The landing gear retracted; (3) The wing flaps in the takeoff position(s); and (4) A climb speed not less than the greater of 1.1 V<E T="52">MC</E> and 1.2 V<E T="52">S1</E> for multiengine airplanes and not less than 1.2 V<E T="52">S1</E> for single—engine airplanes. (b) Each normal, utility, and acrobatic category reciprocating engine-powered airplane of more than 6,000 pounds maximum weight and turbine engine-powered airplanes in the normal, utility, and acrobatic category must have a steady gradient of climb after takeoff of at least 4 percent with (1) Take off power on each engine; (2) The landing gear extended, except that if the landing gear can be retracted in not more than sven seconds, the test may be conducted with the gear retracted; (3) The wing flaps in the takeoff position(s); and (4) A climb speed as specified in § 23.65(a)(4). <CITA>[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <PRTPAGE P="173"/> <SECTNO>§ 23.66</SECTNO> <SUBJECT>Takeoff climb: One-engine inoperative.</SUBJECT> For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-powered airplanes in the normal, utility, and acrobatic category, the steady gradient of climb or descent must be determined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with— (a) The critical engine inoperative and its propeller in the position it rapidly and automatically assumes; (b) The remaining engine(s) at takeoff power; (c) The landing gear extended, except that if the landing gear can be retracted in not more than seven seconds, the test may be conducted with the gear retracted; (d) The wing flaps in the takeoff position(s): (e) The wings level; and (f) A climb speed equal to that achieved at 50 feet in the demonstration of § 23.53. <CITA>[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.67</SECTNO> <SUBJECT>Climb: One engine inoperative.</SUBJECT> (a) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, the following apply: (1) Except for those airplanes that meet the requirements prescribed in § 23.562(d), each airplane with a V<E T="52">SO</E> of more than 61 knots must be able to maintain a steady climb gradient of at least 1.5 percent at a pressure altitude of 5,000 feet with the— (i) Critical engine inoperative and its propeller in the minimum drag position; (ii) Remaining engine(s) at not more than maximum continuous power; (iii) Landing gear retracted; (iv) Wing flaps retracted; and (v) Climb speed not less than 1.2 V<E T="52">S1</E>. (2) For each airplane that meets the requirements prescribed in § 23.562(d), or that has a V<E T="52">SO</E> of 61 knots or less, the steady gradient of climb or descent at a pressure altitude of 5,000 feet must be determined with the— (i) Critical engine inoperative and its propeller in the minimum drag position; (ii) Remaining engine(s) at not more than maximum continuous power; (iii) Landing gear retracted; (iv) Wing flaps retracted; and (v) Climb speed not less than 1.2V<E T="52">S1</E>. (b) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-powered airplanes in the normal, utility, and acrobatic category— (1) The steady gradient of climb at an altitude of 400 feet above the takeoff must be measurably positive with the— (i) Critical engine inoperative and its propeller in the minimum drag position; (ii) Remaining engine(s) at takeoff power; (iii) Landing gear retracted; (iv) Wing flaps in the takeoff position(s); and (v) Climb speed equal to that achieved at 50 feet in the demonstration of § 23.53. (2) The steady gradient of climb must not be less than 0.75 percent at an altitude of 1,500 feet above the takeoff surface, or landing surface, as appropriate, with the— (i) Critical engine inoperative and its propeller in the minimum drag position; (ii) Remaining engine(s) at not more than maximum continuous power; (iii) Landing gear retracted; (iv) Wing flaps retracted; and (v) Climb speed not less than 1.2 V<E T="52">S1</E>. (c) For commuter category airplanes, the following apply: (1) <E T="03">Takeoff; landing gear extended.</E> The steady gradient of climb at the altitude of the takeoff surface must be measurably positive for two-engine airplanes, not less than 0.3 percent for three-engine airplanes, or 0.5 percent for four-engine airplanes with— (i) The critical engine inoperative and its propeller in the position it rapidly and automatically assumes; (ii) The remaining engine(s) at takeoff power; (iii) The landing gear extended, and all landing gear doors open; (iv) The wing flaps in the takeoff position(s);<PRTPAGE P="174"/> (v) The wings level; and (vi) A climb speed equal to V<E T="52">2</E>. (2) <E T="03">Takeoff; landing gear retracted.</E> The steady gradient of climb at an altitude of 400 feet above the takeoff surface must be not less than 2.0 percent of two-engine airplanes, 2.3 percent for three-engine airplanes, and 2.6 percent for four-engine airplanes with— (i) The critical engine inoperative and its propeller in the position it rapidly and automatically assumes; (ii) The remaining engine(s) at takeoff power; (iii) The landing gear retracted; (iv) The wing flaps in the takeoff position(s); (v) A climb speed equal to V<E T="52">2</E>. (3) <E T="03">Enroute.</E> The steady gradient of climb at an altitude of 1,500 feet above the takeoff or landing surface, as appropriate, must be not less than 1.2 percent for two-engine airplanes, 1.5 percent for three-engine airplanes, and 1.7 percent for four-engine airplanes with— (i) The critical engine inoperative and its propeller in the minimum drag position; (ii) The remaining engine(s) at not more than maximum continuous power; (iii) The landing gear retracted; (iv) The wing flaps retracted; and (v) A climb speed not less than 1.2 V<E T="52">S1</E>. (4) <E T="03">Discontinued approach.</E> The steady gradient of climb at an altitude of 400 feet above the landing surface must be not less than 2.1 percent for two-engine airplanes, 2.4 percent for three-engine airplanes, and 2.7 percent for four-engine airplanes, with— (i) The critical engine inoperative and its propeller in the minimum drag position; (ii) The remaining engine(s) at takeoff power; (iii) Landing gear retracted; (iv) Wing flaps in the approach position(s) in which V<E T="52">S1</E> for these position(s) does not exceed 110 percent of the V<E T="52">S1</E> for the related all-engines-operated landing position(s); and (v) A climb speed established in connection with normal landing procedures but not exceeding 1.5 V<E T="52">S1</E>. <CITA>[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.69</SECTNO> <SUBJECT>Enroute climb/descent.</SUBJECT> (a) <E T="03">All engines operating.</E> The steady gradient and rate of climb must be determined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with— (1) Not more than maximum continuous power on each engine; (2) The landing gear retracted; (3) The wing flaps retracted; and (4) A climb speed not less than 1.3 V<E T="52">S1</E>. (b) <E T="03">One engine inoperative.</E> The steady gradient and rate of climb/descent must be determined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with— (1) The critical engine inoperative and its propeller in the minimum drag position; (2) The remaining engine(s) at not more than maximum continuous power; (3) The landing gear retracted; (4) The wing flaps retracted; and (5) A climb speed not less than 1.2 V<E T="52">S1</E>. <CITA>[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.71</SECTNO> <SUBJECT>Glide: Single-engine airplanes.</SUBJECT> The maximum horizontal distance traveled in still air, in nautical miles, per 1,000 feet of altitude lost in a glide, and the speed necessary to achieve this must be determined with the engine inoperative, its propeller in the minimum drag position, and landing gear and wing flaps in the most favorable available position. <CITA>[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.73</SECTNO> <SUBJECT>Reference landing approach speed.</SUBJECT> (a) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, the reference landing approach speed, V<E T="52">REF</E>, must not be less than the greater of V<E T="52">MC</E>, determined in § 23.149(b) with the wing flaps in the most extended takeoff position, and 1.3 V<E T="52">SO</E>. (b) For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-<PRTPAGE P="175"/>powered airplanes in the normal, utility, and acrobatic category, the reference landing approach speed, V<E T="52">REF</E>, must not be less than the greater of V<E T="52">MC</E>, determined in § 23.149(c), and 1.3 V<E T="52">SO</E>. (c) For commuter category airplanes, the reference landing approach speed, V<E T="52">REF</E>, must not be less than the greater of 1.05 V<E T="52">MC</E>, determined in § 23.149(c), and 1.3 V<E T="52">SO</E>. <CITA>[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.75</SECTNO> <SUBJECT>Landing distance.</SUBJECT> The horizontal distance necessary to land and come to a complete stop from a point 50 feet above the landing surface must be determined, for standard temperatures at each weight and altitude within the operational limits established for landing, as follows: (a) A steady approach at not less than V<E T="52">REF</E>, determined in accordance with § 23.73 (a), (b), or (c), as appropriate, must be maintained down to the 50 foot height and— (1) The steady approach must be at a gradient of descent not greater than 5.2 percent (3 degrees) down to the 50-foot height. (2) In addition, an applicant may demonstrate by tests that a maximum steady approach gradient steeper than 5.2 percent, down to the 50-foot height, is safe. The gradient must be established as an operating limitation and the information necessary to display the gradient must be available to the pilot by an appropriate instrument. (b) A constant configuration must be maintained throughout the maneuver. (c) The landing must be made without excessive vertical acceleration or tendency to bounce, nose over, ground loop, porpoise, or water loop. (d) It must be shown that a safe transition to the balked landing conditions of § 23.77 can be made from the conditions that exist at the 50 foot height, at maximum landing weight, or at the maximum landing weight for altitude and temperature of § 23.63 (c)(2) or (d)(2), as appropriate. (e) The brakes must be used so as to not cause excessive wear of brakes or tires. (f) Retardation means other than wheel brakes may be used if that means— (1) Is safe and reliable; and (2) Is used so that consistent results can be expected in service. (g) If any device is used that depends on the operation of any engine, and the landing distance would be increased when a landing is made with that engine inoperative, the landing distance must be determined with that engine inoperative unless the use of other compensating means will result in a landing distance not more than that with each engine operating. <CITA>[Amdt. 23-21, 43 FR 2318, Jan. 16, 1978, as amended by Amdt. 23-34, 52 FR 1828, Jan. 15, 1987; Amdt. 23-42, 56 FR 351, Jan. 3, 1991; Amdt. 23-50, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.77</SECTNO> <SUBJECT>Balked landing.</SUBJECT> (a) Each normal, utility, and acrobatic category reciprocating engine-powered airplane at 6,000 pounds or less maximum weight must be able to maintain a steady gradient of climb at sea level of at least 3.3 percent with— (1) Takeoff power on each engine; (2) The landing gear extended; (3) The wing flaps in the landing position, except that if the flaps may safely be retracted in two seconds or less without loss of altitude and without sudden changes of angle of attack, they may be retracted; and (4) A climb speed equal to V<E T="52">REF</E>, as defined in § 23.73(a). (b) Each normal, utility, and acrobatic category reciprocating engine-powered airplane of more than 6,000 pounds maximum weight and each normal, utility, and acrobatic category turbine engine-powered airplane must be able to maintain a steady gradient of climb of at least 2.5 percent with— (1) Not more than the power that is available on each engine eight seconds after initiation of movement of the power controls from minimum flight-idle position; (2) The landing gear extended; (3) The wing flaps in the landing position; and (4) A climb speed equal to V<E T="52">REF</E>, as defined in § 23.73(b). (c) Each commuter category airplane must be able to maintain a steady gradient of climb of at least 3.2 percent with— (1) Not more than the power that is available on each engine eight seconds <PRTPAGE P="176"/>after initiation of movement of the power controls from the minimum flight idle position; (2) Landing gear extended; (3) Wing flaps in the landing position; and (4) A climb speed equal to V<E T="52">REF</E>, as defined in § 23.73(c). <CITA>[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Flight Characteristics</HD> <SECTION> <SECTNO>§ 23.141</SECTNO> <SUBJECT>General.</SUBJECT> The airplane must meet the requirements of §§ 23.143 through 23.253 at all practical loading conditions and operating altitudes for which certification has been requested, not exceeding the maximum operating altitude established under § 23.1527, and without requiring exceptional piloting skill, alertness, or strength. <CITA>[Doc. No. 26269, 58 FR 42156, Aug. 6, 1993]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Controllability and Maneuverability</HD> <SECTION> <SECTNO>§ 23.143</SECTNO> <SUBJECT>General.</SUBJECT> (a) The airplane must be safely controllable and maneuverable during all flight phases including— (1) Takeoff; (2) Climb; (3) Level flight; (4) Descent; (5) Go-around; and (6) Landing (power on and power off) with the wing flaps extended and retracted. (b) It must be possible to make a smooth transition from one flight condition to another (including turns and slips) without danger of exceeding the limit load factor, under any probable operating condition (including, for multiengine airplanes, those conditions normally encountered in the sudden failure of any engine). (c) If marginal conditions exist with regard to required pilot strength, the control forces necessary must be determined by quantitative tests. In no case may the control forces under the conditions specified in paragraphs (a) and (b) of this section exceed those prescribed in the following table: <GPOTABLE CDEF="s25,6,6,6" COLS="4" OPTS="L2,i1"> <BOXHD> <CHED H="1">Values in pounds force applied to the relevant control</CHED> <CHED H="1">Pitch</CHED> <CHED H="1">Roll</CHED> <CHED H="1">Yaw</CHED> </BOXHD> <ROW> <ENT I="22">(a) For temporary application:</ENT> </ROW> <ROW> <ENT I="02">Stick</ENT> <ENT>60</ENT> <ENT>30</ENT> <ENT/> </ROW> <ROW> <ENT I="02">Wheel (Two hands on rim)</ENT> <ENT>75</ENT> <ENT>50</ENT> <ENT/> </ROW> <ROW> <ENT I="02">Wheel (One hand on rim)</ENT> <ENT>50</ENT> <ENT>25</ENT> <ENT/> </ROW> <ROW> <ENT I="02">Rudder Pedal</ENT> <ENT/> <ENT/> <ENT>150</ENT> </ROW> <ROW> <ENT I="01">(b) For prolonged application</ENT> <ENT>10</ENT> <ENT>5</ENT> <ENT>20</ENT> </ROW> </GPOTABLE> <CITA>[Doc. No, 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-14, 38 FR 31819, Nov. 19, 1973; Amdt. 23-17, 41 FR 55464, Dec. 20, 1976; Amdt. 23-45, 58 FR 42156, Aug. 6, 1993; Amdt. 23-50, 61 FR 5188, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.145</SECTNO> <SUBJECT>Longitudinal control.</SUBJECT> (a) With the airplane as nearly as possible in trim at 1.3 V<E T="52">S1</E>, it must be possible, at speeds below the trim speed, to pitch the nose downward so that the rate of increase in airspeed allows prompt acceleration to the trim speed with— (1) Maximum continuous power on each engine; (2) Power off; and (3) Wing flap and landing gear— (i) retracted, and (ii) extended. (b) Unless otherwise required, it must be possible to carry out the following maneuvers without requiring the application of single-handed control forces exceeding those specified in § 23.143(c). The trimming controls must not be adjusted during the maneuvers: (1) With the landing gear extended, the flaps retracted, and the airplanes as nearly as possible in trim at 1.4 V<E T="52">S1</E>, extend the flaps as rapidly as possible and allow the airspeed to transition from 1.4V<E T="52">S1</E> to 1.4 V<E T="52">SO:</E> (i) With power off; and (ii) With the power necessary to maintain level flight in the initial condition. (2) With landing gear and flaps extended, power off, and the airplane as nearly as possible in trim at 1.3 V<E T="52">SO</E>, quickly apply takeoff power and retract the flaps as rapidly as possible to the recommended go around setting and allow the airspeed to transition from 1.3 V<E T="52">SO</E> to 1.3 V<E T="52">S1</E>. Retract the gear when a positive rate of climb is established. (3) With landing gear and flaps extended, in level flight, power necessary to attain level flight at 1.1 V<E T="52">SO</E>, and the airplane as nearly as possible in trim, <PRTPAGE P="177"/>it must be possible to maintain approximately level flight while retracting the flaps as rapidly as possible with simultaneous application of not more than maximum continuous power. If gated flat positions are provided, the flap retraction may be demonstrated in stages with power and trim reset for level flight at 1.1 V<E T="52">S1</E>, in the initial configuration for each stage— (i) From the fully extended position to the most extended gated position; (ii) Between intermediate gated positions, if applicable; and (iii) From the least extended gated position to the fully retracted position. (4) With power off, flaps and landing gear retracted and the airplane as nearly as possible in trim at 1.4 V<E T="52">S1</E>, apply takeoff power rapidly while maintaining the same airspeed. (5) With power off, landing gear and flaps extended, and the airplane as nearly as possible in trim at V<E T="52">REF</E>, obtain and maintain airspeeds between 1.1 V<E T="52">SO</E>, and either 1.7 V<E T="52">SO</E> or V<E T="52">FE</E>, whichever is lower without requiring the application of two-handed control forces exceeding those specified in § 23.143(c). (6) With maximum takeoff power, landing gear retracted, flaps in the takeoff position, and the airplane as nearly as possible in trim at V<E T="52">FE</E> appropriate to the takeoff flap position, retract the flaps as rapidly as possible while maintaining constant speed. (c) At speeds above V<E T="52">MO</E>/M<E T="52">MO</E>, and up to the maximum speed shown under § 23.251, a maneuvering capability of 1.5 g must be demonstrated to provide a margin to recover from upset or inadvertent speed increase. (d) It must be possible, with a pilot control force of not more than 10 pounds, to maintain a speed of not more than V<E T="52">REF</E> during a power-off glide with landing gear and wing flaps extended, for any weight of the airplane, up to and including the maximum weight. (e) By using normal flight and power controls, except as otherwise noted in paragraphs (e)(1) and (e)(2) of this section, it must be possible to establish a zero rate of descent at an attitude suitable for a controlled landing without exceeding the operational and structural limitations of the airplane, as follows: (1) For single-engine and multiengine airplanes, without the use of the primary longitudinal control system. (2) For multiengine airplanes— (i) Without the use of the primary directional control; and (ii) If a single failure of any one connecting or transmitting link would affect both the longitudinal and directional primary control system, without the primary longitudinal and directional control system. <CITA>[Doc. No. 26269, 58 FR 42157, Aug. 6, 1993; Amdt. 23-45, 58 FR 51970, Oct. 5, 1993, as amended by Amdt. 23-50, 61 FR 5188, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.147</SECTNO> <SUBJECT>Directional and lateral control.</SUBJECT> (a) For each multiengine airplane, it must be possible, while holding the wings level within five degrees, to make sudden changes in heading safely in both directions. This ability must be shown at 1.4 V<E T="52">S1</E> with heading changes up to 15 degrees, except that the heading change at which the rudder force corresponds to the limits specified in § 23.143 need not be exceeded, with the— (1) Critical engine inoperative and its propeller in the minimum drag position; (2) Remaining engines at maximum continuous power; (3) Landing gear— (i) Retracted; and (ii) Extended; and (4) Flaps retracted. (b) For each multiengine airplane, it must be possible to regain full control of the airplane without exceeding a bank angle of 45 degrees, reaching a dangerous attitude or encountering dangerous characteristics, in the event of a sudden and complete failure of the critical engine, making allowance for a delay of two seconds in the initiation of recovery action appropriate to the situation, with the airplane initially in trim, in the following condition: (1) Maximum continuous power on each engine; (2) The wing flaps retracted; (3) The landing gear retracted; (4) A speed equal to that at which compliance with § 23.69(a) has been shown; and<PRTPAGE P="178"/> (5) All propeller controls in the position at which compliance with § 23.69(a) has been shown. (c) For all airplanes, it must be shown that the airplane is safely controllable without the use of the primary lateral control system in any all-engine configuration(s) and at any speed or altitude within the approved operating envelope. It must also be shown that the airplane's flight characteristics are not impaired below a level needed to permit continued safe flight and the ability to maintain attitudes suitable for a controlled landing without exceeding the operational and structural limitations of the airplane. If a single failure of any one connecting or transmitting link in the lateral control system would also cause the loss of additional control system(s), compliance with the above requirement must be shown with those additional systems also assumed to be inoperative. <CITA>[Doc. No. 27807, 61 FR 5188, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.149</SECTNO> <SUBJECT>Minimum control speed.</SUBJECT> (a) V<E T="52">MC</E> is the calibrated airspeed at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the airplane with that engine still inoperative, and thereafter maintain straight flight at the same speed with an angle of bank of not more than 5 degrees. The method used to simulate critical engine failure must represent the most critical mode of powerplant failure expected in service with respect to controllability. (b) V<E T="52">MC</E> for takeoff must not exceed 1.2 V<E T="52">S1</E>, where V<E T="52">S1</E> is determined at the maximum takeoff weight. V<E T="52">MC</E> must be determined with the most unfavorable weight and center of gravity position and with the airplane airborne and the ground effect negligible, for the takeoff configuration(s) with— (1) Maximum available takeoff power initially on each engine; (2) The airplane trimmed for takeoff; (3) Flaps in the takeoff position(s); (4) Landing gear retracted; and (5) All propeller controls in the recommended takeoff position throughout. (c) For all airplanes except reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, the conditions of paragraph (a) of this section must also be met for the landing configuration with— (1) Maximum available takeoff power initially on each engine; (2) The airplane trimmed for an approach, with all engines operating, at V<E T="52">REF</E>, at an approach gradient equal to the steepest used in the landing distance demonstration of § 23.75; (3) Flaps in the landing position; (4) Landing gear extended; and (5) All propeller controls in the position recommended for approach with all engines operating. (d) A minimum speed to intentionally render the critical engine inoperative must be established and designated as the safe, intentional, one-engine-inoperative speed, V<E T="52">SSE</E>. (e) At V<E T="52">MC</E>, the rudder pedal force required to maintain control must not exceed 150 pounds and it must not be necessary to reduce power of the operative engine(s). During the maneuver, the airplane must not assume any dangerous attitude and it must be possible to prevent a heading change of more than 20 degrees. (f) At the option of the applicant, to comply with the requirements of § 23.51(c)(1), V<E T="52">MCG</E> may be determined. V<E T="52">MCG</E> is the minimum control speed on the ground, and is the calibrated airspeed during the takeoff run at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the airplane using the rudder control alone (without the use of nosewheel steering), as limited by 150 pounds of force, and using the lateral control to the extent of keeping the wings level to enable the takeoff to be safely continued. In the determination of V<E T="52">MCG</E>, assuming that the path of the airplane accelerating with all engines operating is along the centerline of the runway, its path from the point at which the critical engine is made inoperative to the point at which recovery to a direction parallel to the centerline is completed may not deviate more than 30 feet laterally from the centerline at any point. V<E T="52">MCG</E> must be established with— (1) The airplane in each takeoff configuration or, at the option of the applicant, in the most critical takeoff configuration;<PRTPAGE P="179"/> (2) Maximum available takeoff power on the operating engines; (3) The most unfavorable center of gravity; (4) The airplane trimmed for takeoff; and (5) The most unfavorable weight in the range of takeoff weights. <CITA>[Doc. No. 27807, 61 FR 5189, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.151</SECTNO> <SUBJECT>Acrobatic maneuvers.</SUBJECT> Each acrobatic and utility category airplane must be able to perform safely the acrobatic maneuvers for which certification is requested. Safe entry speeds for these maneuvers must be determined. </SECTION> <SECTION> <SECTNO>§ 23.153</SECTNO> <SUBJECT>Control during landings.</SUBJECT> It must be possible, while in the landing configuration, to safely complete a landing without exceeding the one-hand control force limits specified in § 23.143(c) following an approach to land— (a) At a speed of V<E T="52">REF</E> minus 5 knots; (b) With the airplane in trim, or as nearly as possible in trim and without the trimming control being moved throughout the maneuver; (c) At an approach gradient equal to the steepest used in the landing distance demonstration of § 23.75; and (d) With only those power changes, if any, that would be made when landing normally from an approach at V<E T="52">REF</E>. <CITA>[Doc. No. 27807, 61 FR 5189, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.155</SECTNO> <SUBJECT>Elevator control force in maneuvers.</SUBJECT> (a) The elevator control force needed to achieve the positive limit maneuvering load factor may not be less than: (1) For wheel controls, W/100 (where W is the maximum weight) or 20 pounds, whichever is greater, except that it need not be greater than 50 pounds; or (2) For stick controls, W/140 (where W is the maximum weight) or 15 pounds, whichever is greater, except that it need not be greater than 35 pounds. (b) The requirement of paragraph (a) of this section must be met at 75 percent of maximum continuous power for reciprocating engines, or the maximum continuous power for turbine engines, and with the wing flaps and landing gear retracted— (1) In a turn, with the trim setting used for wings level flight at V<E T="52">O</E>; and (2) In a turn with the trim setting used for the maximum wings level flight speed, except that the speed may not exceed V<E T="52">NE</E> or V<E T="52">MO</E>/M<E T="52">MO</E>, whichever is appropriate. (c) There must be no excessive decrease in the gradient of the curve of stick force versus maneuvering load factor with increasing load factor. <CITA>[Amdt. 23-14, 38 FR 31819, Nov. 19, 1973; 38 FR 32784, Nov. 28, 1973, as amended by Amdt. 23-45, 58 FR 42158, Aug. 6, 1993; Amdt. 23-50, 61 FR 5189 Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.157</SECTNO> <SUBJECT>Rate of roll.</SUBJECT> (a) <E T="03">Takeoff.</E> It must be possible, using a favorable combination of controls, to roll the airplane from a steady 30-degree banked turn through an angle of 60 degrees, so as to reverse the direction of the turn within: (1) For an airplane of 6,000 pounds or less maximum weight, 5 seconds from initiation of roll; and (2) For an airplane of over 6,000 pounds maximum weight, <EXTRACT> <HD SOURCE="HD3">(W+500)/1,300</HD> </EXTRACT> <FP>seconds, but not more than 10 seconds, where W is the weight in pounds.</FP> (b) The requirement of paragraph (a) of this section must be met when rolling the airplane in each direction with— (1) Flaps in the takeoff position; (2) Landing gear retracted; (3) For a single-engine airplane, at maximum takeoff power; and for a multiengine airplane with the critical engine inoperative and the propeller in the minimum drag position, and the other engines at maximum takeoff power; and (4) The airplane trimmed at a speed equal to the greater of 1.2 V<E T="52">S1</E> or 1.1 V<E T="52">MC</E>, or as nearly as possible in trim for straight flight. (c) <E T="03">Approach.</E> It must be possible, using a favorable combination of controls, to roll the airplane from a steady 30-degree banked turn through an angle of 60 degrees, so as to reverse the direction of the turn within:<PRTPAGE P="180"/> (1) For an airplane of 6,000 pounds or less maximum weight, 4 seconds from initiation of roll; and (2) For an airplane of over 6,000 pounds maximum weight, <CTRHD>(W+2,800)/2,200<FP>seconds, but not more than 7 seconds, where W is the weight in pounds.</FP> </CTRHD> (d) The requirement of paragraph (c) of this section must be met when rolling the airplane in each direction in the following conditions— (1) Flaps in the landing position(s); (2) Landing gear extended; (3) All engines operating at the power for a 3 degree approach; and (4) The airplane trimmed at V<E T="52">REF</E>. <CITA>[Amdt. 23-14, 38 FR 31819, Nov. 19, 1973, as amended by Amdt. 23-45, 58 FR 42158, Aug. 6, 1993; Amdt. 23-50, 61 FR 5189, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Trim</HD> <SECTION> <SECTNO>§ 23.161</SECTNO> <SUBJECT>Trim.</SUBJECT> (a) <E T="03">General</E>. Each airplane must meet the trim requirements of this section after being trimmed and without further pressure upon, or movement of, the primary controls or their corresponding trim controls by the pilot or the automatic pilot. In addition, it must be possible, in other conditions of loading, configuration, speed and power to ensure that the pilot will not be unduly fatigued or distracted by the need to apply residual control forces exceeding those for prolonged application of § 23.143(c). This applies in normal operation of the airplane and, if applicable, to those conditions associated with the failure of one engine for which performance characteristics are established. (b) <E T="03">Lateral and directional trim.</E> The airplane must maintain lateral and directional trim in level flight with the landing gear and wing flaps retracted as follows: (1) For normal, utility, and acrobatic category airplanes, at a speed of 0.9 V<E T="52">H</E>, V<E T="52">C</E>, or V<E T="52">MO</E>/M<E T="52">O</E>, whichever is lowest; and (2) For commuter category airplanes, at all speeds from 1.4 V<E T="52">S1</E> to the lesser of V<E T="52">H</E> or V<E T="52">MO</E>/M<E T="52">MO</E>. (c) <E T="03">Longitudinal trim.</E> The airplane must maintain longitudinal trim under each of the following conditions: (1) A climb with— (i) Takeoff power, landing gear retracted, wing flaps in the takeoff position(s), at the speeds used in determining the climb performance required by § 23.65; and (ii) Maximum continuous power at the speeds and in the configuration used in determining the climb performance required by § 23.69(a). (2) Level flight at all speeds from the lesser of V<E T="52">H</E> and either V<E T="52">NO</E> or V<E T="52">MO</E>/M<E T="52">MO</E> (as appropriate), to 1.4 V<E T="52">S1</E>, with the landing gear and flaps retracted. (3) A descent at V<E T="52">NO</E> or V<E T="52">MO</E>/M<E T="52">MO</E>, whichever is applicable, with power off and with the landing gear and flaps retracted. (4) Approach with landing gear extended and with— (i) A 3 degree angle of descent, with flaps retracted and at a speed of 1.4 V<E T="52">S1</E>; (ii) A 3 degree angle of descent, flaps in the landing position(s) at V<E T="52">REF</E>; and (iii) An approach gradient equal to the steepest used in the landing distance demonstrations of § 23.75, flaps in the landing position(s) at V<E T="52">REF</E>. (d) In addition, each multiple airplane must maintain longitudinal and directional trim, and the lateral control force must not exceed 5 pounds at the speed used in complying with § 23.67(a), (b)(2), or (c)(3), as appropriate, with— (1) The critical engine inoperative, and if applicable, its propeller in the minimum drag position; (2) The remaining engines at maximum continuous power; (3) The landing gear retracted; (4) Wing flaps retracted; and (5) An angle of bank of not more than five degrees. (e) In addition, each commuter category airplane for which, in the determination of the takeoff path in accordance with § 23.57, the climb in the takeoff configuration at V<E T="52">2</E> extends beyond 400 feet above the takeoff surface, it must be possible to reduce the longitudinal and lateral control forces to 10 pounds and 5 pounds, respectively, and the directional control force must not exceed 50 pounds at V<E T="52">2</E> with— (1) The critical engine inoperative and its propeller in the minimum drag position; (2) The remaining engine(s) at takeoff power;<PRTPAGE P="181"/> (3) Landing gear retracted; (4) Wing flaps in the takeoff position(s); and (5) An angle of bank not exceeding 5 degrees. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-21, 43 FR 2318, Jan. 16, 1978; Amdt. 23-34, 52 FR 1828, Jan. 15, 1987; Amdt. 23-42, 56 FR 351, Jan. 3, 1991; 56 FR 5455, Feb. 11, 1991; Amdt. 23-50, 61 FR 5189, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Stability</HD> <SECTION> <SECTNO>§ 23.171</SECTNO> <SUBJECT>General.</SUBJECT> The airplane must be longitudinally, directionally, and laterally stable under §§ 23.173 through 23.181. In addition, the airplane must show suitable stability and control “feel” (static stability) in any condition normally encountered in service, if flight tests show it is necessary for safe operation. </SECTION> <SECTION> <SECTNO>§ 23.173</SECTNO> <SUBJECT>Static longitudinal stability.</SUBJECT> Under the conditions specified in § 23.175 and with the airplane trimmed as indicated, the characteristics of the elevator control forces and the friction within the control system must be as follows: (a) A pull must be required to obtain and maintain speeds below the specified trim speed and a push required to obtain and maintain speeds above the specified trim speed. This must be shown at any speed that can be obtained, except that speeds requiring a control force in excess of 40 pounds or speeds above the maximum allowable speed or below the minimum speed for steady unstalled flight, need not be considered. (b) The airspeed must return to within the tolerances specified for applicable categories of airplanes when the control force is slowly released at any speed within the speed range specified in paragraph (a) of this section. The applicable tolerances are— (1) The airspeed must return to within plus or minus 10 percent of the original trim airspeed; and (2) For commuter category airplanes, the airspeed must return to within plus or minus 7.5 percent of the original trim airspeed for the cruising condition specified in § 23.175(b). (c) The stick force must vary with speed so that any substantial speed change results in a stick force clearly perceptible to the pilot. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-14, 38 FR 31820 Nov. 19, 1973; Amdt. 23-34, 52 FR 1828, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.175</SECTNO> <SUBJECT>Demonstration of static longitudinal stability.</SUBJECT> Static longitudinal stability must be shown as follows: (a) <E T="03">Climb.</E> The stick force curve must have a stable slope at speeds between 85 and 115 percent of the trim speed, with— (1) Flaps retracted; (2) Landing gear retracted; (3) Maximum continuous power; and (4) The airplane trimmed at the speed used in determining the climb performance required by § 23.69(a). (b) <E T="03">Cruise.</E> With flaps and landing gear retracted and the airplane in trim with power for level flight at representative cruising speeds at high and low altitudes, including speeds up to V<E T="52">NO</E> or V<E T="52">MO</E>/M<E T="52">MO</E>, as appropriate, except that the speed need not exceed V<E T="52">H</E>— (1) For normal, utility, and acrobatic category airplanes, the stick force curve must have a stable slope at all speeds within a range that is the greater of 15 percent of the trim speed plus the resulting free return speed range, or 40 knots plus the resulting free return speed range, above and below the trim speed, except that the slope need not be stable— (i) At speeds less than 1.3 V<E T="52">S1</E>; or (ii) For airplanes with V<E T="52">NE</E> established under § 23.1505(a), at speeds greater than V<E T="52">NE</E>; or (iii) For airplanes with V<E T="52">MO</E>/M<E T="52">MO</E> established under § 23.1505(c), at speeds greater than V<E T="52">FC</E>/M<E T="52">FC</E>. (2) For commuter category airplanes, the stick force curve must have a stable slope at all speeds within a range of 50 knots plus the resulting free return speed range, above and below the trim speed, except that the slope need not be stable— (i) At speeds less than 1.4 V<E T="52">S1</E>; or (ii) At speeds greater than V<E T="52">FC</E>/M<E T="52">FC</E>; or (iii) At speeds that require a stick force greater than 50 pounds.<PRTPAGE P="182"/> (c) <E T="03">Landing.</E> The stick force curve must have a stable slope at speeds between 1.1 V<E T="52">S1</E> and 1.8 V<E T="52">S1</E> with— (1) Flaps in the landing position; (2) Landing gear extended; and (3) The airplane trimmed at— (i) V<E T="52">REF</E>, or the minimum trim speed if higher, with power off; and (ii) V<E T="52">REF</E> with enough power to maintain a 3 degree angle of descent. <CITA>[Doc. No. 27807, 61 FR 5190, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.177</SECTNO> <SUBJECT>Static directional and lateral stability.</SUBJECT> (a) The static directional stability, as shown by the tendency to recover from a wings level sideslip with the rudder free, must be positive for any landing gear and flap position appropriate to the takeoff, climb, cruise, approach, and landing configurations. This must be shown with symmetrical power up to maximum continuous power, and at speeds from 1.2 V<E T="52">S1</E> up to the maximum allowable speed for the condition being investigated. The angel of sideslip for these tests must be appropriate to the type of airplane. At larger angles of sideslip, up to that at which full rudder is used or a control force limit in § 23.143 is reached, whichever occurs first, and at speeds from 1.2 V<E T="52">S1</E> to V<E T="52">O</E>, the rudder pedal force must not reverse. (b) The static lateral stability, as shown by the tendency to raise the low wing in a sideslip, must be positive for all landing gear and flap positions. This must be shown with symmetrical power up to 75 percent of maximum continuous power at speeds above 1.2 V<E T="52">S1</E> in the take off configuration(s) and at speeds above 1.3 V<E T="52">S1</E> in other configurations, up to the maximum allowable speed for the configuration being investigated, in the takeoff, climb, cruise, and approach configurations. For the landing configuration, the power must be that necessary to maintain a 3 degree angle of descent in coordinated flight. The static lateral stability must not be negative at 1.2 V<E T="52">S1</E> in the takeoff configuration, or at 1.3 V<E T="52">S1</E> in other configurations. The angle of sideslip for these tests must be appropriate to the type of airplane, but in no case may the constant heading sideslip angle be less than that obtainable with a 10 degree bank, or if less, the maximum bank angle obtainable with full rudder deflection or 150 pound rudder force. (c) Paragraph (b) of this section does not apply to acrobatic category airplanes certificated for inverted flight. (d) In straight, steady slips at 1.2 V<E T="52">S1</E> for any landing gear and flap positions, and for any symmetrical power conditions up to 50 percent of maximum continuous power, the aileron and rudder control movements and forces must increase steadily, but not necessarily in constant proportion, as the angle of sideslip is increased up to the maximum appropriate to the type of airplane. At larger slip angles, up to the angle at which full rudder or aileron control is used or a control force limit contained in § 23.143 is reached, the aileron and rudder control movements and forces must not reverse as the angle of sideslip is increased. Rapid entry into, and recovery from, a maximum sideslip considered appropriate for the airplane must not result in uncontrollable flight characteristics. <CITA>[Doc. No. 27807, 61 FR 5190, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.181</SECTNO> <SUBJECT>Dynamic stability.</SUBJECT> (a) Any short period oscillation not including combined lateral-directional oscillations occurring between the stalling speed and the maximum allowable speed appropriate to the configuration of the airplane must be heavily damped with the primary controls— (1) Free; and (2) In a fixed position. (b) Any combined lateral-directional oscillations (“Dutch roll”) occurring between the stalling speed and the maximum allowable speed appropriate to the configuration of the airplane must be damped to 1/10 amplitude in 7 cycles with the primary controls— (1) Free; and (2) In a fixed position. (c) If it is determined that the function of a stability augmentation system, reference § 23.672, is needed to meet the flight characteristic requirements of this part, the primary control requirements of paragraphs (a)(2) and (b)(2) of this section are not applicable to the tests needed to verify the acceptability of that system.<PRTPAGE P="183"/> (d) During the conditions as specified in § 23.175, when the longitudinal control force required to maintain speeds differing from the trim speed by at least plus and minus 15 percent is suddenly released, the response of the airplane must not exhibit any dangerous characteristics nor be excessive in relation to the magnitude of the control force released. Any long-period oscillation of flight path, phugoid oscillation, that results must not be so unstable as to increase the pilot's workload or otherwise endanger the airplane. <CITA>[Amdt. 23-21, 43 FR 2318, Jan. 16, 1978, as amended by Amdt. 23-45, 58 FR 42158, Aug. 6, 1993]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Stalls</HD> <SECTION> <SECTNO>§ 23.201</SECTNO> <SUBJECT>Wings level stall.</SUBJECT> (a) It must be possible to produce and to correct roll by unreversed use of the rolling control and to produce and to correct yaw by unreversed use of the directional control, up to the time the airplane stalls. (b) The wings level stall characteristics must be demonstrated in flight as follows. Starting from a speed at least 10 knots above the stall speed, the elevator control must be pulled back so that the rate of speed reduction will not exceed one knot per second until a stall is produced, as shown by either: (1) An uncontrollable downward pitching motion of the airplane; (2) A downward pitching motion of the airplane that results from the activation of a stall avoidance device (for example, stick pusher); or (3) The control reaching the stop. (c) Normal use of elevator control for recovery is allowed after the downward pitching motion of paragraphs (b)(1) or (b)(2) of this section has unmistakably been produced, or after the control has been held against the stop for not less than the longer of two seconds or the time employed in the minimum steady slight speed determination of § 23.49. (d) During the entry into and the recovery from the maneuver, it must be possible to prevent more than 15 degrees of roll or yaw by the normal use of controls. (e) Compliance with the requirements of this section must be shown under the following conditions: (1) <E T="03">Wing flaps.</E> Retracted, fully extended, and each intermediate normal operating position. (2) <E T="03">Landing gear.</E> Retracted and extended. (3) <E T="03">Cowl flaps.</E> Appropriate to configuration. (4) <E T="03">Power:</E> (i) Power off; and (ii) 75 percent of maximum continuous power. However, if the power-to-weight ratio at 75 percent of maximum continuous power result in extreme nose-up attitudes, the test may be carried out with the power required for level flight in the landing configuration at maximum landing weight and a speed of 1.4 V<E T="52">SO</E>, except that the power may not be less than 50 percent of maximum continuous power. (5) <E T="03">Trim.</E> The airplane trimmed at a speed as near 1.5 V<E T="52">S1</E> as practicable. (6) <E T="03">Propeller.</E> Full increase r.p.m. position for the power off condition. <CITA>[Doc. No. 27807, 61 FR 5191, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.203</SECTNO> <SUBJECT>Turning flight and accelerated turning stalls.</SUBJECT> Turning flight and accelerated turning stalls must be demonstrated in tests as follows: (a) Establish and maintain a coordinated turn in a 30 degree bank. Reduce speed by steadily and progressively tightening the turn with the elevator until the airplane is stalled, as defined in § 23.201(b). The rate of speed reduction must be constant, and— (1) For a turning flight stall, may not exceed one knot per second; and (2) For an accelerated turning stall, be 3 to 5 knots per second with steadily increasing normal acceleration. (b) After the airplane has stalled, as defined in § 23.201(b), it must be possible to regain wings level flight by normal use of the flight controls, but without increasing power and without— (1) Excessive loss of altitude; (2) Undue pitchup; (3) Uncontrollable tendency to spin; (4) Exceeding a bank angle of 60 degrees in the original direction of the turn or 30 degrees in the opposite direction in the case of turning flight stalls; (5) Exceeding a bank angle of 90 degrees in the original direction of the <PRTPAGE P="184"/>turn or 60 degrees in the opposite direction in the case of accelerated turning stalls; and (6) Exceeding the maximum permissible speed or allowable limit load factor. (c) Compliance with the requirements of this section must be shown under the following conditions: (1) <E T="03">Wing flaps:</E> Retracted, fully extended, and each intermediate normal operating position; (2) <E T="03">Landing gear:</E> Retracted and extended; (3) <E T="03">Cowl flaps:</E> Appropriate to configuration; (4) <E T="03">Power:</E> (i) Power off; and (ii) 75 percent of maximum continuous power. However, if the power-to-weight ratio at 75 percent of maximum continuous power results in extreme nose-up attitudes, the test may be carried out with the power required for level flight in the landing configuration at maximum landing weight and a speed of 1.4 V<E T="52">SO</E>, except that the power may not be less than 50 percent of maximum continuous power. (5) <E T="03">Trim:</E> The airplane trimmed at a speed as near 1.5 V<E T="52">S1</E> as practicable. (6) <E T="03">Propeller.</E> Full increase rpm position for the power off condition. <CITA>[Amdt. 23-14, 38 FR 31820, Nov. 19, 1973, as amended by Amdt. 23-45, 58 FR 42159, Aug. 6, 1993; Amdt. 23-50, 61 FR 5191, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.207</SECTNO> <SUBJECT>Stall warning.</SUBJECT> (a) There must be a clear and distinctive stall warning, with the flaps and landing gear in any normal position, in straight and turning flight. (b) The stall warning may be furnished either through the inherent aerodynamic qualities of the airplane or by a device that will give clearly distinguishable indications under expected conditions of flight. However, a visual stall warning device that requires the attention of the crew within the cockpit is not acceptable by itself. (c) During the stall tests required by § 23.201(b) and § 23.203(a)(1), the stall warning must begin at a speed exceeding the stalling speed by a margin of not less than 5 knots and must continue until the stall occurs. (d) When following procedures furnished in accordance with § 23.1585, the stall warning must not occur during a takeoff with all engines operating, a takeoff continued with one engine inoperative, or during an approach to landing. (e) During the stall tests required by § 23.203(a)(2), the stall warning must begin sufficiently in advance of the stall for the stall to be averted by pilot action taken after the stall warning first occurs. (f) For acrobatic category airplanes, an artificial stall warning may be mutable, provided that it is armed automatically during takeoff and rearmed automatically in the approach configuration. <CITA>[Amdt. 23-7, 34 FR 13087, Aug. 13, 1969, as amended by Amdt. 23-45, 58 FR 42159, Aug. 6, 1993; Amdt. 23-50, 61 FR 5191, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Spinning</HD> <SECTION> <SECTNO>§ 23.221</SECTNO> <SUBJECT>Spinning.</SUBJECT> (a) <E T="03">Normal category airplanes.</E> A single-engine, normal category airplane must be able to recover from a one-turn spin or a three-second spin, whichever takes longer, in not more than one additional turn after initiation of the first control action for recovery, or demonstrate compliance with the optional spin resistant requirements of this section. (1) The following apply to one turn or three second spins: (i) For both the flaps-retracted and flaps-extended conditions, the applicable airspeed limit and positive limit maneuvering load factor must not be exceeded; (ii) No control forces or characteristic encountered during the spin or recovery may adversely affect prompt recovery; (iii) It must be impossible to obtain unrecoverable spins with any use of the flight or engine power controls either at the entry into or during the spin; and (iv) For the flaps-extended condition, the flaps may be retracted during the recovery but not before rotation has ceased. (2) At the applicant's option, the airplane may be demonstrated to be spin resistant by the following: (i) During the stall maneuver contained in § 23.201, the pitch control <PRTPAGE P="185"/>must be pulled back and held against the stop. Then, using ailerons and rudders in the proper direction, it must be possible to maintain wings-level flight within 15 degrees of bank and to roll the airplane from a 30 degree bank in one direction to a 30 degree bank in the other direction; (ii) Reduce the airplane speed using pitch control at a rate of approximately one knot per second until the pitch control reaches the stop; then, with the pitch control pulled back and held against the stop, apply full rudder control in a manner to promote spin entry for a period of seven seconds or through a 360 degree heading change, whichever occurs first. If the 360 degree heading change is reached first, it must have taken no fewer than four seconds. This maneuver must be performed first with the ailerons in the neutral position, and then with the ailerons deflected opposite the direction of turn in the most adverse manner. Power and airplane configuration must be set in accordance with § 23.201(e) without change during the maneuver. At the end of seven seconds or a 360 degree heading change, the airplane must respond immediately and normally to primary flight controls applied to regain coordinated, unstalled flight without reversal of control effect and without exceeding the temporary control forces specified by § 23.143(c); and (iii) Compliance with §§ 23.201 and 23.203 must be demonstrated with the airplane in uncoordinated flight, corresponding to one ball width displacement on a slip-skid indicator, unless one ball width displacement cannot be obtained with full rudder, in which case the demonstration must be with full rudder applied. (b) <E T="03">Utility category airplanes.</E> A utility category airplane must meet the requirements of paragraph (a) of this section. In addition, the requirements of paragraph (c) of this section and § 23.807(b)(7) must be met if approval for spinning is requested. (c) <E T="03">Acrobatic category airplanes.</E> An acrobatic category airplane must meet the spin requirements of paragraph (a) of this section and § 23.807(b)(6). In addition, the following requirements must be met in each configuration for which approval for spinning is requested: (1) The airplane must recover from any point in a spin up to and including six turns, or any greater number of turns for which certification is requested, in not more than one and one-half additional turns after initiation of the first control action for recovery. However, beyond three turns, the spin may be discontinued if spiral characteristics appear. (2) The applicable airspeed limits and limit maneuvering load factors must not be exceeded. For flaps-extended configurations for which approval is requested, the flaps must not be retracted during the recovery. (3) It must be impossible to obtain unrecoverable spins with any use of the flight or engine power controls either at the entry into or during the spin. (4) There must be no characteristics during the spin (such as excessive rates of rotation or extreme oscillatory motion) that might prevent a successful recovery due to disorientation or incapacitation of the pilot. <CITA>[Doc. No. 27807, 61 FR 5191, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ground and Water Handling Characteristics</HD> <SECTION> <SECTNO>§ 23.231</SECTNO> <SUBJECT>Longitudinal stability and control.</SUBJECT> (a) A landplane may have no uncontrollable tendency to nose over in any reasonably expected operating condition, including rebound during landing or takeoff. Wheel brakes must operate smoothly and may not induce any undue tendency to nose over. (b) A seaplane or amphibian may not have dangerous or uncontrollable porpoising characteristics at any normal operating speed on the water. </SECTION> <SECTION> <SECTNO>§ 23.233</SECTNO> <SUBJECT>Directional stability and control.</SUBJECT> (a) A 90 degree cross-component of wind velocity, demonstrated to be safe for taxiing, takeoff, and landing must be established and must be not less than 0.2 V<E T="52">SO</E>. (b) The airplane must be satisfactorily controllable in power-off landings at normal landing speed, without using brakes or engine power to maintain a straight path until the speed has decreased to at least 50 percent of the speed at touchdown.<PRTPAGE P="186"/> (c) The airplane must have adequate directional control during taxiing. (d) Seaplanes must demonstrate satisfactory directional stability and control for water operations up to the maximum wind velocity specified in paragraph (a) of this section. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42159, Aug. 6, 1993; Amdt. 23-50, 61 FR 5192, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.235</SECTNO> <SUBJECT>Operation on unpaved surfaces.</SUBJECT> The airplane must be demonstrated to have satisfactory characteristics and the shock-absorbing mechanism must not damage the structure of the airplane when the airplane is taxied on the roughest ground that may reasonably be expected in normal operation and when takeoffs and landings are performed on unpaved runways having the roughest surface that may reasonably be expected in normal operation. <CITA>[Doc. No. 27807, 61 FR 5192, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.237</SECTNO> <SUBJECT>Operation on water.</SUBJECT> A wave height, demonstrated to be safe for operation, and any necessary water handling procedures for seaplanes and amphibians must be established. <CITA>[Doc. No. 27807, 61 FR 5192, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.239</SECTNO> <SUBJECT>Spray characteristics.</SUBJECT> Spray may not dangerously obscure the vision of the pilots or damage the propellers or other parts of a seaplane or amphibian at any time during taxiing, takeoff, and landing. </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Miscellaneous Flight Requirements</HD> <SECTION> <SECTNO>§ 23.251</SECTNO> <SUBJECT>Vibration and buffeting.</SUBJECT> There must be no vibration or buffeting severe enough to result in structural damage, and each part of the airplane must be free from excessive vibration, under any appropriate speed and power conditions up to V<E T="52">D</E>/M<E T="52">D</E>. In addition, there must be no buffeting in any normal flight condition severe enough to interfere with the satisfactory control of the airplane or cause excessive fatigue to the flight crew. Stall warning buffeting within these limits is allowable. <CITA>[Doc. No. 26269, 58 FR 42159, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.253</SECTNO> <SUBJECT>High speed characteristics.</SUBJECT> If a maximum operating speed <E T="03">V</E> <E T="24">MO</E> <E T="03">/M</E> <E T="24">MO</E> is established under § 23.1505(c), the following speed increase and recovery characteristics must be met: (a) Operating conditions and characteristics likely to cause inadvertent speed increases (including upsets in pitch and roll) must be simulated with the airplane trimmed at any likely speed up to V<E T="52">MO</E>/M<E T="52">MO</E>. These conditions and characteristics include gust upsets, inadvertent control movements, low stick force gradients in relation to control friction, passenger movement, leveling off from climb, and descent from Mach to airspeed limit altitude. (b) Allowing for pilot reaction time after occurrence of the effective inherent or artificial speed warning specified in § 23.1303, it must be shown that the airplane can be recovered to a normal attitude and its speed reduced to V<E T="52">MO</E>/M<E T="52">MO</E>, without— (1) Exceeding <E T="03">V</E> <E T="24">D</E> <E T="03">/M</E> <E T="24">D</E>, the maximum speed shown under § 23.251, or the structural limitations; or (2) Buffeting that would impair the pilot's ability to read the instruments or to control the airplane for recovery. (c) There may be no control reversal about any axis at any speed up to the maximum speed shown under § 23.251. Any reversal of elevator control force or tendency of the airplane to pitch, roll, or yaw must be mild and readily controllable, using normal piloting techniques. <CITA>[Amdt. 23-7, 34 FR 13087, Aug. 13, 1969; as amended by Amdt. 23-26, 45 FR 60170, Sept. 11, 1980; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993; Amdt. 23-50, 61 FR 5192, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> </SUBPART> <SUBPART> <HD SOURCE="HED">Subpart C—Structure</HD> <SUBJGRP> <HD SOURCE="HED">General</HD> <SECTION> <SECTNO>§ 23.301</SECTNO> <SUBJECT>Loads.</SUBJECT> (a) Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety). Unless otherwise provided, prescribed loads are limit loads. (b) Unless otherwise provided, the air, ground, and water loads must be placed in equilibrium with inertia forces, considering each item of mass <PRTPAGE P="187"/>in the airplane. These loads must be distributed to conservatively approximate or closely represent actual conditions. Methods used to determine load intensities and distribution on canard and tandem wing configurations must be validated by flight test measurement unless the methods used for determining those loading conditions are shown to be reliable or conservative on the configuration under consideration. (c) If deflections under load would significantly change the distribution of external or internal loads, this redistribution must be taken into account. (d) Simplified structural design criteria may be used if they result in design loads not less than those prescribed in §§ 23.331 through 23.521. For airplane configurations described in appendix A, § 23.1, the design criteria of appendix A of this part are an approved equivalent of §§ 23.321 through 23.459. If appendix A of this part is used, the entire appendix must be substituted for the corresponding sections of this part. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-28, 47 FR 13315, Mar. 29, 1982; Amdt. 23-42, 56 FR 352, Jan. 3, 1991; Amdt. 23-48, 61 FR 5143, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.302</SECTNO> <SUBJECT>Canard or tandem wing configurations.</SUBJECT> The forward structure of a canard or tandem wing configuration must: (a) Meet all requirements of subpart C and subpart D of this part applicable to a wing; and (b) Meet all requirements applicable to the function performed by these surfaces. <CITA>[Amdt. 23-42, 56 FR 352, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.303</SECTNO> <SUBJECT>Factor of safety.</SUBJECT> Unless otherwise provided, a factor of safety of 1.5 must be used. </SECTION> <SECTION> <SECTNO>§ 23.305</SECTNO> <SUBJECT>Strength and deformation.</SUBJECT> (a) The structure must be able to support limit loads without detrimental, permanent deformation. At any load up to limit loads, the deformation may not interfere with safe operation. (b) The structure must be able to support ultimate loads without failure for at least three seconds, except local failures or structural instabilities between limit and ultimate load are acceptable only if the structure can sustain the required ultimate load for at least three seconds. However when proof of strength is shown by dynamic tests simulating actual load conditions, the three second limit does not apply. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.307</SECTNO> <SUBJECT>Proof of structure.</SUBJECT> (a) Compliance with the strength and deformation requirements of § 23.305 must be shown for each critical load condition. Structural analysis may be used only if the structure conforms to those for which experience has shown this method to be reliable. In other cases, substantiating load tests must be made. Dynamic tests, including structural flight tests, are acceptable if the design load conditions have been simulated. (b) Certain parts of the structure must be tested as specified in Subpart D of this part. </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Flight Loads</HD> <SECTION> <SECTNO>§ 23.321</SECTNO> <SUBJECT>General.</SUBJECT> (a) Flight load factors represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of the airplane) to the weight of the airplane. A positive flight load factor is one in which the aerodynamic force acts upward, with respect to the airplane. (b) Compliance with the flight load requirements of this subpart must be shown— (1) At each critical altitude within the range in which the airplane may be expected to operate; (2) At each weight from the design minimum weight to the design maximum weight; and (3) For each required altitude and weight, for any practicable distribution of disposable load within the operating limitations specified in §§ 23.1583 through 23.1589. (c) When significant, the effects of compressibility must be taken into account. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <PRTPAGE P="188"/> <SECTNO>§ 23.331</SECTNO> <SUBJECT>Symmetrical flight conditions.</SUBJECT> (a) The appropriate balancing horizontal tail load must be accounted for in a rational or conservative manner when determining the wing loads and linear inertia loads corresponding to any of the symmetrical flight conditions specified in §§ 23.333 through 23.341. (b) The incremental horizontal tail loads due to maneuvering and gusts must be reacted by the angular inertia of the airplane in a rational or conservative manner. (c) Mutual influence of the aerodynamic surfaces must be taken into account when determining flight loads. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-42, 56 FR 352, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.333</SECTNO> <SUBJECT>Flight envelope.</SUBJECT> (a) <E T="03">General.</E> Compliance with the strength requirements of this subpart must be shown at any combination of airspeed and load factor on and within the boundaries of a flight envelope (similar to the one in paragraph (d) of this section) that represents the envelope of the flight loading conditions specified by the maneuvering and gust criteria of paragraphs (b) and (c) of this section respectively. (b) <E T="03">Maneuvering envelope.</E> Except where limited by maximum (static) lift coefficients, the airplane is assumed to be subjected to symmetrical maneuvers resulting in the following limit load factors: (1) The positive maneuvering load factor specified in § 23.337 at speeds up to <E T="03">V</E> <E T="24">D</E>; (2) The negative maneuvering load factor specified in § 23.337 at <E T="03">V</E> <E T="24">C</E>; and (3) Factors varying linearly with speed from the specified value at <E T="03">V</E> <E T="24">C</E> to 0.0 at <E T="03">V</E> <E T="24">D</E> for the normal and commuter category, and —1.0 at <E T="03">V</E> <E T="24">D</E> for the acrobatic and utility categories. (c) <E T="03">Gust envelope.</E> (1) The airplane is assumed to be subjected to symmetrical vertical gusts in level flight. The resulting limit load factors must correspond to the conditions determined as follows: (i) Positive (up) and negative (down) gusts of 50 f.p.s. at <E T="03">V</E> <E T="24">C</E> must be considered at altitudes between sea level and 20,000 feet. The gust velocity may be reduced linearly from 50 f.p.s. at 20,000 feet to 25 f.p.s. at 50,000 feet. (ii) Positive and negative gusts of 25 f.p.s. at <E T="03">V</E> <E T="24">D</E> must be considered at altitudes between sea level and 20,000 feet. The gust velocity may be reduced linearly from 25 f.p.s. at 20,000 feet to 12.5 f.p.s. at 50,000 feet. (iii) In addition, for commuter category airplanes, positive (up) and negative (down) rough air gusts of 66 f.p.s. at V<E T="64">Β</E> must be considered at altitudes between sea level and 20,000 feet. The gust velocity may be reduced linearly from 66 f.p.s. at 20,000 feet to 38 f.p.s. at 50,000 feet. (2) The following assumptions must be made: (i) The shape of the gust is— <MATH DEEP="30" SPAN="1"> <MID>EC28SE91.000</MID> </MATH> <EXTRACT> <FP>Where—</FP> </EXTRACT> <FP SOURCE="FP-2"> <E T="03">s</E> =Distance penetrated into gust (ft.);</FP> <FP SOURCE="FP-2"> <E T="03">C</E> =Mean geometric chord of wing (ft.); and</FP> <FP SOURCE="FP-2"> <E T="03">Ude</E> =Derived gust velocity referred to in subparagraph (1) of this section.</FP> (ii) Gust load factors vary linearly with speed between <E T="03">V</E> <E T="24">C</E> and <E T="03">V</E> <E T="24">D</E> . (d) <E T="03">Flight envelope.</E> <GPH DEEP="196" SPAN="2"> <PRTPAGE P="189"/> <GID>EC28SE91.001</GID> </GPH> <CITA TYPE="W">[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13087, Aug. 13, 1969; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.335</SECTNO> <SUBJECT>Design airspeeds.</SUBJECT> Except as provided in paragraph (a)(4) of this section, the selected design airspeeds are equivalent airspeeds (EAS). (a) <E T="03">Design cruising speed, V</E> <E T="24">C</E> <E T="11">.</E> For <E T="03">V</E> <E T="24">C</E> the following apply: (1) Where W/S′=wing loading at the design maximum takeoff weight, V<E T="52">c</E> (in knots) may not be less than— (i) 33 |(W/S) (for normal, utility, and commuter category airplanes); (ii) 36 |(W/S) (for acrobatic category airplanes). (2) For values of <E T="03">W/S</E> more than 20, the multiplying factors may be decreased linearly with <E T="03">W/S</E> to a value of 28.6 where <E T="03">W/S</E> =100. (3) <E T="03">V</E> <E T="24">C</E> need not be more than 0.9 <E T="03">V</E> <E T="24">H</E> at sea level. (4) At altitudes where an <E T="03">M</E> <E T="24">D</E> is established, a cruising speed <E T="03">M</E> <E T="24">C</E> limited by compressibility may be selected. (b) <E T="03">Design dive speed V</E> <E T="24">D</E>. For <E T="03">V</E> <E T="24">D</E>, the following apply: (1) <E T="03">V</E> <E T="24">D</E>/M<E T="24">D</E> may not be less than 1.25 <E T="03">V</E> <E T="24">C</E>/M<E T="24">C</E>; and (2) With <E T="03">V</E> <E T="24">C min,</E> the required minimum design cruising speed, <E T="03">V</E> <E T="24">D</E> (in knots) may not be less than— (i) 1.40 V<E T="52">c</E> <E T="03">min</E> (for normal and commuter category airplanes); (ii) 1.50 <E T="03">V</E> <E T="24">C min</E> (for utility category airplanes); and (iii) 1.55 <E T="03">V</E> <E T="24">C min</E> (for acrobatic category airplanes). (3) For values of <E T="03">W/S</E> more than 20, the multiplying factors in paragraph (b)(2) of this section may be decreased linearly with <E T="03">W/S</E> to a value of 1.35 where <E T="03">W/S=100.</E> (4) Compliance with paragraphs (b)(1) and (2) of this section need not be shown if <E T="03">V</E> <E T="24">D</E> <E T="03">/M</E> <E T="24">D</E> is selected so that the minimum speed margin between <E T="03">V</E> <E T="24">C</E> <E T="03">/M</E> <E T="24">C</E> and <E T="03">V</E> <E T="24">D</E> <E T="03">/M</E> <E T="24">D</E> is the greater of the following: (i) The speed increase resulting when, from the initial condition of stabilized flight at <E T="03">V</E> <E T="24">C</E> <E T="03">/M</E> <E T="24">C</E>, the airplane is assumed to be upset, flown for 20 seconds along a flight path 7.5° below the initial path, and then pulled up with a load factor of 1.5 (0.5 <E T="03">g.</E> acceleration increment). At least 75 percent maximum continuous power for reciprocating engines, and maximum cruising power for turbines, or, if less, the power required for <E T="03">V</E> <E T="24">C</E>/<E T="03">M</E> <E T="24">C</E> for both kinds of engines, must be assumed until the pullup is initiated, at which point power reduction and pilot-controlled drag devices may be used; and either—<PRTPAGE P="190"/> (ii) Mach 0.05 for normal, utility, and acrobatic category airplanes (at altitudes where M<E T="52">D</E> is established); or (iii) Mach 0.07 for commuter category airplanes (at altitudes where M<E T="52">D</E> is established) unless a rational analysis, including the effects of automatic systems, is used to determine a lower margin. If a rational analysis is used, the minimum speed margin must be enough to provide for atmospheric variations (such as horizontal gusts), and the penetration of jet streams or cold fronts), instrument errors, airframe production variations, and must not be less than Mach 0.05. (c) <E T="03">Design maneuvering speed V</E> <E T="24">A.</E> For <E T="03">V</E> <E T="24">A</E>, the following applies: (1) <E T="03">V</E> <E T="24">A</E> may not be less than <E T="03">V</E> <E T="24">S</E>|<E T="13">n</E> <E T="01">where—</E> (i) <E T="03">V</E> <E T="24">S</E> is a computed stalling speed with flaps retracted at the design weight, normally based on the maximum airplane normal force coefficients, <E T="03">C</E> <E T="24">NA</E> <E T="03">;</E> and (ii) <E T="03">n</E> is the limit maneuvering load factor used in design (2) The value of <E T="03">V</E> <E T="24">A</E> need not exceed the value of <E T="03">V</E> <E T="24">C</E> used in design. (d) <E T="03">Design speed for maximum gust intensity, V</E> <E T="54">B</E>. For V<E T="54">B</E>, the following apply: (1) V<E T="52">B</E> may not be less than the speed determined by the intersection of the line representing the maximum positive lift, C<E T="52">NMAX</E>, and the line representing the rough air gust velocity on the gust V-n diagram, or V<E T="52">S1</E>|n<E T="52">g,</E> whichever is less, where: (i) n<E T="54">g</E> the positive airplane gust load factor due to gust, at speed V<E T="54">C</E> (in accordance with § 23.341), and at the particular weight under consideration; and (ii) V<E T="54">S1</E> is the stalling speed with the flaps retracted at the particular weight under consideration. (2) V<E T="54">B</E> need not be greater than V<E T="54">C</E>. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13088, Aug. 13, 1969; Amdt. 23-16, 40 FR 2577, Jan. 14, 1975; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987; Amdt. 23-24, 52 FR 34745, Sept. 14, 1987; Amdt. 23-48, 61 FR 5143, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.337</SECTNO> <SUBJECT>Limit maneuvering load factors.</SUBJECT> (a) The positive limit maneuvering load factor <E T="03">n</E> may not be less than— (1) 2.1+(24,000÷(W+10,000)) for normal and commuter category airplanes, where W=design maximum takeoff weight, except that n need not be more than 3.8; (2) 4.4 for utility category airplanes; or (3) 6.0 for acrobatic category airplanes. (b) The negative limit maneuvering load factor may not be less than— (1) 0.4 times the positive load factor for the normal utility and commuter categories; or (2) 0.5 times the positive load factor for the acrobatic category. (c) Maneuvering load factors lower than those specified in this section may be used if the airplane has design features that make it impossible to exceed these values in flight. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13088, Aug. 13, 1969; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987; Amdt. 23-48, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.341</SECTNO> <SUBJECT>Gust loads factors.</SUBJECT> (a) Each airplane must be designed to withstand loads on each lifting surface resulting from gusts specified in § 23.333(c). (b) The gust load for a canard or tandem wing configuration must be computed using a rational analysis, or may be computed in accordance with paragraph (c) of this section, provided that the resulting net loads are shown to be conservative with respect to the gust criteria of § 23.333(c). (c) In the absence of a more rational analysis, the gust load factors must be computed as follows— <MATH DEEP="30" SPAN="1"> <MID>ER09FE96.010</MID> </MATH> <EXTRACT> <FP>Where—</FP> <FP SOURCE="FP-2"> <E T="03">K</E> <E T="22">g</E> <E T="03">=0.88</E> <E T="21">μ</E> <E T="22">g</E>/5.3+<E T="21">μ</E> <E T="22">g</E>=gust alleviation factor;</FP> <FP SOURCE="FP-2"> <E T="21">μ</E> <E T="22">g</E>=2(W/S)/<E T="22">ρ</E> Cag=<E T="01">airplane mass ratio;</E> </FP> <FP SOURCE="FP-2"> <E T="03">U</E> <E T="24">de</E>=<E T="01">Derived gust velocities referred to in § 23.333(c) (f.p.s.);</E> </FP> <FP SOURCE="FP-2"> <E T="22">ρ</E>=Density of air (slugs/cu.ft.);</FP> <FP SOURCE="FP-2"> <E T="03">W/S</E> =Wing loading (p.s.f.) due to the applicable weight of the airplane in the particular load case.</FP> <FP SOURCE="FP-2"> <E T="03">W/S</E> =Wing loading (p.s.f.);</FP> <FP SOURCE="FP-2"> <E T="03">C</E> =Mean geometric chord (ft.);</FP> <FP SOURCE="FP-2"> <E T="03">g</E> =Acceleration due to gravity (ft./sec.<E T="21"> 2</E>)</FP> <FP SOURCE="FP-2"> <E T="03">V</E> =Airplane equivalent speed (knots); and</FP> <FP SOURCE="FP-2"> <E T="03">a</E> =Slope of the airplane normal force coefficient curve <E T="03">C</E> <E T="24">NA</E> per radian if the gust <PRTPAGE P="191"/>loads are applied to the wings and horizontal tail surfaces simultaneously by a rational method. The wing lift curve slope <E T="03">C</E> <E T="24">L</E> per radian may be used when the gust load is applied to the wings only and the horizontal tail gust loads are treated as a separate condition. </FP> </EXTRACT> <CITA>[Amdt. 23-7, 34 FR 13088, Aug. 13, 1969, as amended by Amdt. 23-42, 56 FR 352, Jan. 3, 1991; Amdt. 23-48, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.343</SECTNO> <SUBJECT>Design fuel loads.</SUBJECT> (a) The disposable load combinations must include each fuel load in the range from zero fuel to the selected maximum fuel load. (b) If fuel is carried in the wings, the maximum allowable weight of the airplane without any fuel in the wing tank(s) must be established as “maximum zero wing fuel weight,” if it is less than the maximum weight. (c) For commuter category airplanes, a structural reserve fuel condition, not exceeding fuel necessary for 45 minutes of operation at maximum continuous power, may be selected. If a structural reserve fuel condition is selected, it must be used as the minimum fuel weight condition for showing compliance with the flight load requirements prescribed in this part and— (1) The structure must be designed to withstand a condition of zero fuel in the wing at limit loads corresponding to: (i) Ninety percent of the maneuvering load factors defined in § 23.337, and (ii) Gust velocities equal to 85 percent of the values prescribed in § 23.333(c). (2) The fatigue evaluation of the structure must account for any increase in operating stresses resulting from the design condition of paragraph (c)(1) of this section. (3) The flutter, deformation, and vibration requirements must also be met with zero fuel in the wings. <CITA>[Doc. No. 27805, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.345</SECTNO> <SUBJECT>High lift devices.</SUBJECT> (a) If flaps or similar high lift devices are to be used for takeoff, approach or landing, the airplane, with the flaps fully extended at V<E T="52">F</E>, is assumed to be subjected to symmetrical maneuvers and gusts within the range determined by— (1) Maneuvering, to a positive limit load factor of 2.0; and (2) Positive and negative gust of 25 feet per second acting normal to the flight path in level flight. (b) V<E T="52">F</E> must be assumed to be not less than 1.4 V<E T="52">S</E> or 1.8 V<E T="52">SF</E>, whichever is greater, where— (1) V<E T="52">S</E> is the computed stalling speed with flaps retracted at the design weight; and (2) V<E T="52">SF</E> is the computed stalling speed with flaps fully extended at the design weight. (3) If an automatic flap load limiting device is used, the airplane may be designed for the critical combinations of airspeed and flap position allowed by that device. (c) In determining external loads on the airplane as a whole, thrust, slipstream, and pitching acceleration may be assumed to be zero. (d) The flaps, their operating mechanism, and their supporting structures, must be designed to withstand the conditions prescribed in paragraph (a) of this section. In addition, with the flaps fully extended at V<E T="52">F</E>, the following conditions, taken separately, must be accounted for: (1) A head-on gust having a velocity of 25 feet per second (EAS), combined with propeller slipstream corresponding to 75 percent of maximum continuous power; and (2) The effects of propeller slipstream corresponding to maximum takeoff power. <CITA>[Doc. No. 27805, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.347</SECTNO> <SUBJECT>Unsymmetrical flight conditions.</SUBJECT> (a) The airplane is assumed to be subjected to the unsymmetrical flight conditions of §§ 23.349 and 23.351. Unbalanced aerodynamic moments about the center of gravity must be reacted in a rational or conservative manner, considering the principal masses furnishing the reacting inertia forces. (b) Acrobatic category airplanes certified for flick maneuvers (snap roll) must be designed for additional asymmetric loads acting on the wing and the horizontal tail. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-48, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <PRTPAGE P="192"/> <SECTNO>§ 23.349</SECTNO> <SUBJECT>Rolling conditions.</SUBJECT> The wing and wing bracing must be designed for the following loading conditions: (a) Unsymmetrical wing loads appropriate to the category. Unless the following values result in unrealistic loads, the rolling accelerations may be obtained by modifying the symmetrical flight conditions in § 23.333(d) as follows: (1) For the acrobatic category, in conditions A and F, assume that 100 percent of the semispan wing airload acts on one side of the plane of symmetry and 60 percent of this load acts on the other side. (2) For normal, utility, and commuter categories, in Condition A, assume that 100 percent of the semispan wing airload acts on one side of the airplane and 75 percent of this load acts on the other side. (b) The loads resulting from the aileron deflections and speeds specified in § 23.455, in combination with an airplane load factor of at least two thirds of the positive maneuvering load factor used for design. Unless the following values result in unrealistic loads, the effect of aileron displacement on wing torsion may be accounted for by adding the following increment to the basic airfoil moment coefficient over the aileron portion of the span in the critical condition determined in § 23.333(d): <EXTRACT> <E T="21">Δ</E> <E T="03">c</E> <E T="24">m</E>=—0.01<E T="21">δ</E> <FP>where— </FP> </EXTRACT> <EXTRACT> <FP SOURCE="FP-1"> <E T="21">Δ</E> <E T="03">c</E> <E T="24">m</E> is the moment coefficient increment; and</FP> <FP SOURCE="FP-1"> <E T="21">δ</E> is the down aileron deflection in degrees in the critical condition.</FP> </EXTRACT> <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13088, Aug. 13, 1969; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987; Amdt. 23-48, 61 FR 5144, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.351</SECTNO> <SUBJECT>Yawing conditions.</SUBJECT> The airplane must be designed for yawing loads on the vertical surfaces resulting from the loads specified in §§ 23.441 through 23.445. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 FR 258, Jan. 9, 1965, as amended by Amdt. 23-42, 56 FR 352, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.361</SECTNO> <SUBJECT>Engine torque.</SUBJECT> (a) Each engine mount and its supporting structure must be designed for the effects of— (1) A limit engine torque corresponding to takeoff power and propeller speed acting simultaneously with 75 percent of the limit loads from flight condition A of § 23.333(d); (2) A limit engine torque corresponding to maximum continuous power and propeller speed acting simultaneously with the limit loads from flight condition A of § 23.333(d); and (3) For turbopropeller installations, in addition to the conditions specified in paragraphs (a)(1) and (a)(2) of this section, a limit engine torque corresponding to takeoff power and propeller speed, multiplied by a factor accounting for propeller control system malfunction, including quick feathering, acting simultaneously with lg level flight loads. In the absence of a rational analysis, a factor of 1.6 must be used. (b) For turbine engine installations, the engine mounts and supporting structure must be designed to withstand each of the following: (1) A limit engine torque load imposed by sudden engine stoppage due to malfunction or structural failure (such as compressor jamming). (2) A limit engine torque load imposed by the maximum acceleration of the engine. (c) The limit engine torque to be considered under paragraph (a) of this section must be obtained by multiplying the mean torque by a factor of— (1) 1.25 for turbopropeller installations; (2) 1.33 for engines with five or more cylinders; and (3) Two, three, or four, for engines with four, three, or two cylinders, respectively. <CITA>[Amdt. 23-26, 45 FR 60171, Sept. 11, 1980, as amended by Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.363</SECTNO> <SUBJECT>Side load on engine mount.</SUBJECT> (a) Each engine mount and its supporting structure must be designed for a limit load factor in a lateral direction, for the side load on the engine mount, of not less than— (1) 1.33, or<PRTPAGE P="193"/> (2) One-third of the limit load factor for flight condition A. (b) The side load prescribed in paragraph (a) of this section may be assumed to be independent of other flight conditions. </SECTION> <SECTION> <SECTNO>§ 23.365</SECTNO> <SUBJECT>Pressurized cabin loads.</SUBJECT> For each pressurized compartment, the following apply: (a) The airplane structure must be strong enough to withstand the flight loads combined with pressure differential loads from zero up to the maximum relief valve setting. (b) The external pressure distribution in flight, and any stress concentrations, must be accounted for. (c) If landings may be made with the cabin pressurized, landing loads must be combined with pressure differential loads from zero up to the maximum allowed during landing. (d) The airplane structure must be strong enough to withstand the pressure differential loads corresponding to the maximum relief valve setting multiplied by a factor of 1.33, omitting other loads. (e) If a pressurized cabin has two or more compartments separated by bulkheads or a floor, the primary structure must be designed for the effects of sudden release of pressure in any compartment with external doors or windows. This condition must be investigated for the effects of failure of the largest opening in the compartment. The effects of intercompartmental venting may be considered. </SECTION> <SECTION> <SECTNO>§ 23.367</SECTNO> <SUBJECT>Unsymmetrical loads due to engine failure.</SUBJECT> (a) Turbopropeller airplanes must be designed for the unsymmetrical loads resulting from the failure of the critical engine including the following conditions in combination with a single malfunction of the propeller drag limiting system, considering the probable pilot corrective action on the flight controls: (1) At speeds between <E T="03">V</E> <E T="24">MC</E> and <E T="03">V</E> <E T="24">D,</E> the loads resulting from power failure because of fuel flow interruption are considered to be limit loads. (2) At speeds between <E T="03">V</E> <E T="24">MC</E> and <E T="03">V</E> <E T="24">C</E>, the loads resulting from the disconnection of the engine compressor from the turbine or from loss of the turbine blades are considered to be ultimate loads. (3) The time history of the thrust decay and drag buildup occurring as a result of the prescribed engine failures must be substantiated by test or other data applicable to the particular engine-propeller combination. (4) The timing and magnitude of the probable pilot corrective action must be conservatively estimated, considering the characteristics of the particular engine-propeller-airplane combination. (b) Pilot corrective action may be assumed to be initiated at the time maximum yawing velocity is reached, but not earlier than 2 seconds after the engine failure. The magnitude of the corrective action may be based on the limit pilot forces specified in § 23.397 except that lower forces may be assumed where it is shown by analysis or test that these forces can control the yaw and roll resulting from the prescribed engine failure conditions. <CITA>[Amdt. 23-7, 34 FR 13089, Aug. 13, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.369</SECTNO> <SUBJECT>Rear lift truss.</SUBJECT> (a) If a rear lift truss is used, it must be designed to withstand conditions of reversed airflow at a design speed of— V = 8.7 |(W/S) + 8.7 (knots), where W/S = wing loading at design maximum takeoff weight. (b) Either aerodynamic data for the particular wing section used, or a value of <E T="03">C</E> <E T="24">L</E> equalling −0.8 with a chordwise distribution that is triangular between a peak at the trailing edge and zero at the leading edge, must be used. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969; 34 FR 17509, Oct. 30, 1969; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993; Amdt. 23-48, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.371</SECTNO> <SUBJECT>Gyroscopic and aerodynamic loads.</SUBJECT> (a) Each engine mount and its supporting structure must be designed for the gyroscopic, inertial, and aerodynamic loads that result, with the engine(s) and propeller(s), if applicable, at maximum continuous r.p.m., under either: (1) The conditions prescribed in § 23.351 and § 23.423; or<PRTPAGE P="194"/> (2) All possible combinations of the following— (i) A yaw velocity of 2.5 radians per second; (ii) A pitch velocity of 1.0 radian per second; (iii) A normal load factor of 2.5; and (iv) Maximum continuous thrust. (b) For airplanes approved for aerobatic maneuvers, each engine mount and its supporting structure must meet the requirements of paragraph (a) of this section and be designed to withstand the load factors expected during combined maximum yaw and pitch velocities. (c) For airplanes certificated in the commuter category, each engine mount and its supporting structure must meet the requirements of paragraph (a) of this section and the gust conditions specified in § 23.341 of this part. <CITA>[Doc. No. 27805, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.373</SECTNO> <SUBJECT>Speed control devices.</SUBJECT> If speed control devices (such as spoilers and drag flaps) are incorporated for use in enroute conditions— (a) The airplane must be designed for the symmetrical maneuvers and gusts prescribed in §§ 23.333, 23.337, and 23.341, and the yawing maneuvers and lateral gusts in §§ 23.441 and 23.443, with the device extended at speeds up to the placard device extended speed; and (b) If the device has automatic operating or load limiting features, the airplane must be designed for the maneuver and gust conditions prescribed in paragraph (a) of this section at the speeds and corresponding device positions that the mechanism allows. <CITA>[Amdt. 23-7, 34 FR 13089, Aug. 13, 1969]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Control Surface and System Loads</HD> <SECTION> <SECTNO>§ 23.391</SECTNO> <SUBJECT>Control surface loads.</SUBJECT> The control surface loads specified in §§ 23.397 through 23.459 are assumed to occur in the conditions described in §§ 23.331 through 23.351. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-48, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.393</SECTNO> <SUBJECT>Loads parallel to hinge line.</SUBJECT> (a) Control surfaces and supporting hinge brackets must be designed to withstand inertial loads acting parallel to the hinge line. (b) In the absence of more rational data, the inertial loads may be assumed to be equal to KW, where— (1) K = 24 for vertical surfaces; (2) K = 12 for horizontal surfaces; and (3) W = weight of the movable surfaces. <CITA>[Doc. No. 27805, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.395</SECTNO> <SUBJECT>Control system loads.</SUBJECT> (a) Each flight control system and its supporting structure must be designed for loads corresponding to at least 125 percent of the computed hinge moments of the movable control surface in the conditions prescribed in §§ 23.391 through 23.459. In addition, the following apply: (1) The system limit loads need not exceed the higher of the loads that can be produced by the pilot and automatic devices operating the controls. However, autopilot forces need not be added to pilot forces. The system must be designed for the maximum effort of the pilot or autopilot, whichever is higher. In addition, if the pilot and the autopilot act in opposition, the part of the system between them may be designed for the maximum effort of the one that imposes the lesser load. Pilot forces used for design need not exceed the maximum forces prescribed in § 23.397(b). (2) The design must, in any case, provide a rugged system for service use, considering jamming, ground gusts, taxiing downwind, control inertia, and friction. Compliance with this subparagraph may be shown by designing for loads resulting from application of the minimum forces prescribed in § 23.397(b). (b) A 125 percent factor on computed hinge moments must be used to design elevator, aileron, and rudder systems. However, a factor as low as 1.0 may be used if hinge moments are based on accurate flight test data, the exact reduction depending upon the accuracy and reliability of the data. (c) Pilot forces used for design are assumed to act at the appropriate control <PRTPAGE P="195"/>grips or pads as they would in flight, and to react at the attachments of the control system to the control surface horns. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.397</SECTNO> <SUBJECT>Limit control forces and -torques.</SUBJECT> (a) In the control surface flight loading condition, the airloads on movable surfaces and the corresponding deflections need not exceed those that would result in flight from the application of any pilot force within the ranges specified in paragraph (b) of this section. In applying this criterion, the effects of control system boost and servo-mechanisms, and the effects of tabs must be considered. The automatic pilot effort must be used for design if it alone can produce higher control surface loads than the human pilot. (b) The limit pilot forces and -torques are as follows: <GPOTABLE CDEF="s65,r40,r30" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Control</CHED> <CHED H="1">Maximum forces or torques for design weight, weight equal to or less than 5,000 pounds <SU>1</SU> </CHED> <CHED H="1">Minimum forces or torques <SU>2</SU> </CHED> </BOXHD> <ROW> <ENT I="11">Aileron:</ENT> </ROW> <ROW> <ENT I="02">Stick</ENT> <ENT>67 lbs</ENT> <ENT>40 lbs.</ENT> </ROW> <ROW> <ENT I="02">Wheel <SU>3</SU> </ENT> <ENT>50 D in.-lbs <SU>4</SU> </ENT> <ENT>40 D in.-lbs.<SU>4</SU> </ENT> </ROW> <ROW> <ENT I="11">Elevator:</ENT> </ROW> <ROW> <ENT I="02">Stick</ENT> <ENT>167 lbs</ENT> <ENT>100 lbs.</ENT> </ROW> <ROW> <ENT I="02">Wheel (symmetrical)</ENT> <ENT>200 lbs </ENT> <ENT>100 lbs.</ENT> </ROW> <ROW> <ENT I="02">Wheel (unsymmetrical) <SU>5</SU> </ENT> <ENT/> <ENT>100 lbs.</ENT> </ROW> <ROW> <ENT I="01">Rudder</ENT> <ENT>200 lbs</ENT> <ENT>150 lbs.</ENT> </ROW> <TNOTE> <SU>1</SU> For design weight <E T="03">(W)</E> more than 5,000 pounds, the specified maximum values must be increased linearly with weight to 1.18 times the specified values at a design weight of 12,500 pounds and for commuter category airplanes, the specified values must be increased linearly with weight to 1.35 times the specified values at a design weight of 19,000 pounds.</TNOTE> <TNOTE> <SU>2</SU> If the design of any individual set of control systems or surfaces makes these specified minimum forces or torques inapplicable, values corresponding to the present hinge moments obtained under § 23.415, but not less than 0.6 of the specified minimum forces or torques, may be used.</TNOTE> <TNOTE> <SU>3</SU> The critical parts of the aileron control system must also be designed for a single tangential force with a limit value of 1.25 times the couple force determined from the above criteria.</TNOTE> <TNOTE> <SU>4</SU> D=wheel diameter (inches).</TNOTE> <TNOTE> <SU>5</SU> The unsymmetrical force must be applied at one of the normal handgrip points on the control wheel.</TNOTE> </GPOTABLE> <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969; Amdt. 23-17, 41 FR 55464, Dec. 20, 1976; Amdt. 23-34, 52 FR 1829, Jan. 15, 1987; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.399</SECTNO> <SUBJECT>Dual control system.</SUBJECT> (a) Each dual control system must be designed to withstand the force of the pilots operating in opposition, using individual pilot forces not less than the greater of— (1) 0.75 times those obtained under § 23.395; or (2) The minimum forces specified in § 23.397(b). (b) Each dual control system must be designed to withstand the force of the pilots applied together, in the same direction, using individual pilot forces not less than 0.75 times those obtained under § 23.395. <CITA>[Doc. No. 27805, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.405</SECTNO> <SUBJECT>Secondary control system.</SUBJECT> Secondary controls, such as wheel brakes, spoilers, and tab controls, must be designed for the maximum forces that a pilot is likely to apply to those controls. </SECTION> <SECTION> <SECTNO>§ 23.407</SECTNO> <SUBJECT>Trim tab effects.</SUBJECT> The effects of trim tabs on the control surface design conditions must be accounted for only where the surface loads are limited by maximum pilot effort. In these cases, the tabs are considered to be deflected in the direction that would assist the pilot. These deflections must correspond to the maximum degree of “out of trim” expected at the speed for the condition under consideration. </SECTION> <SECTION> <SECTNO>§ 23.409</SECTNO> <SUBJECT>Tabs.</SUBJECT> Control surface tabs must be designed for the most severe combination of airspeed and tab deflection likely to be obtained within the flight envelope for any usable loading condition. </SECTION> <SECTION> <SECTNO>§ 23.415</SECTNO> <SUBJECT>Ground gust conditions.</SUBJECT> (a) The control system must be investigated as follows for control surface loads due to ground gusts and taxiing downwind: (1) If an investigation of the control system for ground gust loads is not required by paragraph (a)(2) of this section, but the applicant elects to design a part of the control system of these loads, these loads need only be carried from control surface horns through the <PRTPAGE P="196"/>nearest stops or gust locks and their supporting structures. (2) If pilot forces less than the minimums specified in § 23.397(b) are used for design, the effects of surface loads due to ground gusts and taxiing downwind must be investigated for the entire control system according to the formula: <FP SOURCE="FP-2">H = K c S q</FP> <FP SOURCE="FP-2">where—</FP> <FP SOURCE="FP-2">H = limit hinge moment (ft.-lbs.);</FP> <FP SOURCE="FP-2">c = mean chord of the control surface aft of the hinge line (ft.);</FP> <FP SOURCE="FP-2">S = area of control surface aft of the hinge line (sq. ft.);</FP> <FP SOURCE="FP-2">q = dynamic pressure (p.s.f.) based on a design speed not less than 14.6 |(W/S) + 14.6 (f.p.s.) where W/S = wing loading at design maximum weight, except that the design speed need not exceed 88 (f.p.s.);</FP> <FP SOURCE="FP-2">K = limit hinge moment factor for ground gusts derived in paragraph (b) of this section. (For ailerons and elevators, a positive value of K indicates a moment tending to depress the surface and a negative value of K indicates a moment tending to raise the surface).</FP> (b) The limit hinge moment factor <E T="03">K</E> for ground gusts must be derived as follows: <GPOTABLE CDEF="xs45,6,r50" COLS="3" OPTS="L2"> <BOXHD> <CHED H="1">Surface</CHED> <CHED H="1"> <E T="03">K</E> </CHED> <CHED H="1">Position of controls</CHED> </BOXHD> <ROW> <ENT I="01">(a) Aileron</ENT> <ENT>0.75 </ENT> <ENT>Control column locked lashed in mid-position.</ENT> </ROW> <ROW> <ENT I="01">(b) Aileron</ENT> <ENT> <E T="21">±</E>0.50</ENT> <ENT>Ailerons at full throw; + moment on one aileron, − moment on the other.</ENT> </ROW> <ROW> <ENT I="01">(c) Elevator</ENT> <ENT> <E T="21">±</E>0.75</ENT> <ENT>(c) Elevator full up (−).</ENT> </ROW> <ROW> <ENT I="01">(d) Elevator</ENT> <ENT/> <ENT>(d) Elevator full down (+).</ENT> </ROW> <ROW> <ENT I="01">(e) Rudder</ENT> <ENT> <E T="21">±</E>0.75</ENT> <ENT>(e) Rudder in neutral.</ENT> </ROW> <ROW> <ENT I="01">(f) Rudder</ENT> <ENT/> <ENT>(f) Rudder at full throw.</ENT> </ROW> </GPOTABLE> (c) At all weights between the empty weight and the maximum weight declared for tie-down stated in the appropriate manual, any declared tie-down points and surrounding structure, control system, surfaces and associated gust locks, must be designed to withstand the limit load conditions that exist when the airplane is tied down and that result from wind speeds of up to 65 knots horizontally from any direction. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993; Amdt. 23-48, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Horizontal Stabilizing and Balancing Surfaces</HD> <SECTION> <SECTNO>§ 23.421</SECTNO> <SUBJECT>Balancing loads.</SUBJECT> (a) A horizontal surface balancing load is a load necessary to maintain equilibrium in any specified flight condition with no pitching acceleration. (b) Horizontal balancing surfaces must be designed for the balancing loads occurring at any point on the limit maneuvering envelope and in the flap conditions specified in § 23.345. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089, Aug. 13, 1969; Amdt. 23-42, 56 FR 352, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.423</SECTNO> <SUBJECT>Maneuvering loads.</SUBJECT> Each horizontal surface and its supporting structure, and the main wing of a canard or tandem wing configuration, if that surface has pitch control, must be designed for the maneuvering loads imposed by the following conditions: (a) A sudden movement of the pitching control, at the speed V<E T="52">A</E>, to the maximum aft movement, and the maximum forward movement, as limited by the control stops, or pilot effort, whichever is critical. (b) A sudden aft movement of the pitching control at speeds above V<E T="52">A</E>, followed by a forward movement of the pitching control resulting in the following combinations of normal and angular acceleration: <GPOTABLE CDEF="s50,xls28,xls64" COLS="3" OPTS="L2,i1"> <BOXHD> <CHED H="1">Condition</CHED> <CHED H="1">Normal acceleration (n)</CHED> <CHED H="1">Angular acceleration (radian/sec<E T="52">2</E>)</CHED> </BOXHD> <ROW> <ENT I="01">Nose-up pitching</ENT> <ENT>1.0</ENT> <ENT>+39n<E T="52">m</E>÷V×(n<E T="52">m</E>−1.5)</ENT> </ROW> <ROW> <ENT I="01">Nose-down ptiching</ENT> <ENT>n<E T="52">m</E> </ENT> <ENT>−39n<E T="52">m</E>÷V×(n<E T="52">m</E>−1.5)</ENT> </ROW> </GPOTABLE> <FP>where—</FP> (1) n<E T="52">m</E>=positive limit maneuvering load factor used in the design of the airplane; and (2) V=initial speed in knots. The conditions in this paragraph involve loads corresponding to the loads that may occur in a “checked maneuver” (a maneuver in which the pitching control is suddenly displaced in one direction and then suddenly moved in the opposite direction). The deflections and timing of the “checked maneuver” must avoid exceeding the limit maneuvering load factor. The total horizontal <PRTPAGE P="197"/>surface load for both nose-up and nose-down pitching conditions is the sum of the balancing loads at <E T="03">V</E> and the specified value of the normal load factor <E T="03">n</E>, plus the maneuvering load increment due to the specified value of the angular acceleration. <CITA>[Amdt. 23-42, 56 FR 353, Jan. 3, 1991; 56 FR 5455, Feb. 11, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.425</SECTNO> <SUBJECT>Gust loads.</SUBJECT> (a) Each horizontal surface, other than a main wing, must be designed for loads resulting from— (1) Gust velocities specified in § 23.333(c) with flaps retracted; and (2) Positive and negative gusts of 25 f.p.s. nominal intensity at <E T="03">V</E> <E T="24">F</E> corresponding to the flight conditions specified in § 23.345(a)(2). (b) [Reserved] (c) When determining the total load on the horizontal surfaces for the conditions specified in paragraph (a) of this section, the initial balancing loads for steady unaccelerated flight at the pertinent design speeds V<E T="52">F,</E> V<E T="52">C</E>, and V<E T="52">D</E> must first be determined. The incremental load resulting from the gusts must be added to the initial balancing load to obtain the total load. (d) In the absence of a more rational analysis, the incremental load due to the gust must be computed as follows only on airplane configurations with aft-mounted, horizontal surfaces, unless its use elsewhere is shown to be conservative: <MATH DEEP="30" SPAN="1"> <MID>EC28SE91.002</MID> </MATH> <EXTRACT> <FP>where—</FP> <FP SOURCE="FP-2">ΔL<E T="22">ht</E>=Incremental horizontal tailload (lbs.);</FP> <FP SOURCE="FP-2">K<E T="22">g</E>=Gust alleviation factor defined in § 23.341;</FP> <FP SOURCE="FP-2">U<E T="22">de</E>=Derived gust velocity (f.p.s.);</FP> <FP SOURCE="FP-2">V=Airplane equivalent speed (knots);</FP> <FP SOURCE="FP-2">a<E T="22">ht</E>=Slope of aft horizontal lift curve (per radian)</FP> <FP SOURCE="FP-2">S<E T="52">ht</E>=Area of aft horizontal lift surface (ft<E T="51">2</E>); and</FP> </EXTRACT> <MATH DEEP="30" SPAN="1"> <MID>EC28SE91.003</MID> </MATH> <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13089 Aug. 13, 1969; Amdt. 23-42, 56 FR 353, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.427</SECTNO> <SUBJECT>Unsymmetrical loads.</SUBJECT> (a) Horizontal surfaces other than main wing and their supporting structure must be designed for unsymmetrical loads arising from yawing and slipstream effects, in combination with the loads prescribed for the flight conditions set forth in §§ 23.421 through 23.425. (b) In the absence of more rational data for airplanes that are conventional in regard to location of engines, wings, horizontal surfaces other than main wing, and fuselage shape: (1) 100 percent of the maximum loading from the symmetrical flight conditions may be assumed on the surface on one side of the plane of symmetry; and (2) The following percentage of that loading must be applied to the opposite side: <EXTRACT> Percent=100−10 (n−1), where n is the specified positive maneuvering load factor, but this value may not be more than 80 percent. </EXTRACT> (c) For airplanes that are not conventional (such as airplanes with horizontal surfaces other than main wing having appreciable dihedral or supported by the vertical tail surfaces) the surfaces and supporting structures must be designed for combined vertical and horizontal surface loads resulting from each prescribed flight condition taken separately. <CITA>[Amdt. 23-14, 38 FR 31820, Nov. 19, 1973, as amended by Amdt. 23-42, 56 FR 353, Jan. 3, 1991]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Vertical Surfaces</HD> <SECTION> <SECTNO>§ 23.441</SECTNO> <SUBJECT>Maneuvering loads.</SUBJECT> (a) At speeds up to <E T="03">V</E> <E T="24">A</E>, the vertical surfaces must be designed to withstand the following conditions. In computing the loads, the yawing velocity may be assumed to be zero: (1) With the airplane in unaccelerated flight at zero yaw, it is assumed that the rudder control is suddenly displaced to the maximum deflection, as limited by the control stops or by limit pilot forces. (2) With the rudder deflected as specified in paragraph (a)(1) of this section, it is assumed that the airplane yaws to the overswing sideslip angle. In lieu of a rational analysis, an overswing angle <PRTPAGE P="198"/>equal to 1.5 times the static sideslip angle of paragraph (a)(3) of this section may be assumed. (3) A yaw angle of 15 degrees with the rudder control maintained in the neutral position (except as limited by pilot strength). (b) For commuter category airplanes, the loads imposed by the following additional maneuver must be substantiated at speeds from V<E T="52">A</E> to V<E T="52">D</E>/M<E T="52">D</E>. When computing the tail loads— (1) The airplane must be yawed to the largest attainable steady state sideslip angle, with the rudder at maximum deflection caused by any one of the following: (i) Control surface stops; (ii) Maximum available booster effort; (iii) Maximum pilot rudder force as shown below: <GPH DEEP="470" SPAN="2"> <PRTPAGE P="199"/> <GID>ER09FE96.006</GID> </GPH> (2) The rudder must be suddenly displaced from the maximum deflection to the neutral position. (c) The yaw angles specified in paragraph (a)(3) of this section may be reduced if the yaw angle chosen for a particular speed cannot be exceeded in—<PRTPAGE P="200"/> (1) Steady slip conditions; (2) Uncoordinated rolls from steep banks; or (3) Sudden failure of the critical engine with delayed corrective action. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13090, Aug. 13, 1969; Amdt. 23-14, 38 FR 31821, Nov. 19, 1973; Amdt. 23-28, 47 FR 13315, Mar. 29, 1982; Amdt. 23-42, 56 FR 353, Jan. 3, 1991; Amdt. 23-48, 61 FR 5145, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.443</SECTNO> <SUBJECT>Gust loads.</SUBJECT> (a) Vertical surfaces must be designed to withstand, in unaccelerated flight at speed <E T="03">V</E> <E T="22">C</E>, lateral gusts of the values prescribed for <E T="03">V</E> <E T="22">C</E> in § 23.333(c). (b) In addition, for commuter category airplanes, the airplane is assumed to encounter derived gusts normal to the plane of symmetry while in unaccelerated flight at V<E T="54">B</E>, V<E T="54">C</E>, V<E T="54">D</E>, and V<E T="54">F</E>. The derived gusts and airplane speeds corresponding to these conditions, as determined by §§ 23.341 and 23.345, must be investigated. The shape of the gust must be as specified in § 23.333(c)(2)(i). (c) In the absence of a more rational analysis, the gust load must be computed as follows: <MATH DEEP="28" SPAN="1"> <MID>ER09FE96.000</MID> </MATH> <FP SOURCE="FP-2">Where—</FP> <FP SOURCE="FP-2">L<E T="52">vt</E>=Vertical surface loads (lbs.);</FP> <MATH DEEP="29" SPAN="1"> <MID>ER09FE96.001</MID> </MATH> <MATH DEEP="31" SPAN="1"> <MID>ER09FE96.002</MID> </MATH> <FP SOURCE="FP-2">U<E T="52">de</E>=Derived gust velocity (f.p.s.);</FP> <FP SOURCE="FP-2"> <E T="61">ρ</E>=Air density (slugs/cu.ft.);</FP> <FP SOURCE="FP-2">W=the applicable weight of the airplane in the particular load case (lbs.);</FP> <FP SOURCE="FP-2">S<E T="52">vt</E>=Area of vertical surface (ft.<E T="51">2</E>);</FP> <FP SOURCE="FP-2">c<AC T="08"/> <E T="52">t</E>=Mean geometric chord of vertical surface (ft.);</FP> <FP SOURCE="FP-2">a<E T="52">vt</E>=Lift curve slope of vertical surface (per radian);</FP> <FP SOURCE="FP-2">K=Radius of gyration in yaw (ft.);</FP> <FP SOURCE="FP-2">l<E T="52">vt</E>=Distance from airplane c.g. to lift center of vertical surface (ft.);</FP> <FP SOURCE="FP-2">g=Acceleration due to gravity (ft./sec.<E T="51">2</E>); and</FP> <FP SOURCE="FP-2">V=Equivalent airspeed (knots).</FP> <CITA>[Amdt. 23-7, 34 FR 13090, Aug. 13, 1969, as amended by Amdt. 23-34, 52 FR 1830, Jan. 15, 1987; 52 FR 7262, Mar. 9, 1987; Amdt. 23-24, 52 FR 34745, Sept. 14, 1987; Amdt. 23-42, 56 FR 353, Jan. 3, 1991; Amdt. 23-48, 61 FR 5147, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.445</SECTNO> <SUBJECT>Outboard fins or winglets.</SUBJECT> (a) If outboard fins or winglets are included on the horizontal surfaces or wings, the horizontal surfaces or wings must be designed for their maximum load in combination with loads induced by the fins or winglets and moments or forces exerted on the horizontal surfaces or wings by the fins or winglets. (b) If outboard fins or winglets extend above and below the horizontal surface, the critical vertical surface loading (the load per unit area as determined under §§ 23.441 and 23.443) must be applied to— (1) The part of the vertical surfaces above the horizontal surface with 80 percent of that loading applied to the part below the horizontal surface; and (2) The part of the vertical surfaces below the horizontal surface with 80 percent of that loading applied to the part above the horizontal surface. (c) The end plate effects of outboard fins or winglets must be taken into account in applying the yawing conditions of §§ 23.441 and 23.443 to the vertical surfaces in paragraph (b) of this section. (d) When rational methods are used for computing loads, the maneuvering loads of § 23.441 on the vertical surfaces and the one-g horizontal surface load, including induced loads on the horizontal surface and moments or forces exerted on the horizontal surfaces by the vertical surfaces, must be applied simultaneously for the structural loading condition. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-14, 38 FR 31821, Nov. 19, 1973; Amdt. 23-42, 56 FR 353, Jan. 3, 1991]</CITA> </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ailerons and Special Devices</HD> <SECTION> <SECTNO>§ 23.455</SECTNO> <SUBJECT>Ailerons.</SUBJECT> (a) The ailerons must be designed for the loads to which they are subjected—<PRTPAGE P="201"/> (1) In the neutral position during symmetrical flight conditions; and (2) By the following deflections (except as limited by pilot effort), during unsymmetrical flight conditions: (i) Sudden maximum displacement of the aileron control at <E T="03">V</E> <E T="24">A</E>. Suitable allowance may be made for control system deflections. (ii) Sufficient deflection at <E T="03">V</E> <E T="24">C</E>, where <E T="03">V</E> <E T="24">C</E> is more than <E T="03">V</E> <E T="24">A</E>, to produce a rate of roll not less than obtained in paragraph (a)(2)(i) of this section. (iii) Sufficient deflection at <E T="03">V</E> <E T="24">D</E> to produce a rate of roll not less than one-third of that obtained in paragraph (a)(2)(i) of this section. (b) [Reserved] <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13090, Aug. 13, 1969; Amdt. 23-42, 56 FR 353, Jan. 3, 1991]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.459</SECTNO> <SUBJECT>Special devices.</SUBJECT> The loading for special devices using aerodynamic surfaces (such as slots and spoilers) must be determined from test data. </SECTION> </SUBJGRP> <SUBJGRP> <HD SOURCE="HED">Ground Loads</HD> <SECTION> <SECTNO>§ 23.471</SECTNO> <SUBJECT>General.</SUBJECT> The limit ground loads specified in this subpart are considered to be external loads and inertia forces that act upon an airplane structure. In each specified ground load condition, the external reactions must be placed in equilibrium with the linear and angular inertia forces in a rational or conservative manner. </SECTION> <SECTION> <SECTNO>§ 23.473</SECTNO> <SUBJECT>Ground load conditions and assumptions.</SUBJECT> (a) The ground load requirements of this subpart must be complied with at the design maximum weight except that §§ 23.479, 23.481, and 23.483 may be complied with at a design landing weight (the highest weight for landing conditions at the maximum descent velocity) allowed under paragraphs (b) and (c) of this section. (b) The design landing weight may be as low as— (1) 95 percent of the maximum weight if the minimum fuel capacity is enough for at least one-half hour of operation at maximum continuous power plus a capacity equal to a fuel weight which is the difference between the design maximum weight and the design landing weight; or (2) The design maximum weight less the weight of 25 percent of the total fuel capacity. (c) The design landing weight of a multiengine airplane may be less than that allowed under paragraph (b) of this section if— (1) The airplane meets the one-engine-inoperative climb requirements of § 23.67(b)(1) or (c); and (2) Compliance is shown with the fuel jettisoning system requirements of § 23.1001. (d) The selected limit vertical inertia load factor at the center of gravity of the airplane for the ground load conditions prescribed in this subpart may not be less than that which would be obtained when landing with a descent velocity (<E T="03">V</E>), in feet per second, equal to 4.4 (W/S)<FR>1/4</FR>, except that this velocity need not be more than 10 feet per second and may not be less than seven feet per second. (e) Wing lift not exceeding two-thirds of the weight of the airplane may be assumed to exist throughout the landing impact and to act through the center of gravity. The ground reaction load factor may be equal to the inertia load factor minus the ratio of the above assumed wing lift to the airplane weight. (f) If energy absorption tests are made to determine the limit load factor corresponding to the required limit descent velocities, these tests must be made under § 23.723(a). (g) No inertia load factor used for design purposes may be less than 2.67, nor may the limit ground reaction load factor be less than 2.0 at design maximum weight, unless these lower values will not be exceeded in taxiing at speeds up to takeoff speed over terrain as rough as that expected in service. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13090, Aug. 13, 1969; Amdt. 23-28, 47 FR 13315, Mar. 29, 1982; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993; Amdt. 23-48, 61 FR 5147, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.477</SECTNO> <SUBJECT>Landing gear arrangement.</SUBJECT> Sections 23.479 through 23.483, or the conditions in appendix C, apply to airplanes with conventional arrangements <PRTPAGE P="202"/>of main and nose gear, or main and tail gear. </SECTION> <SECTION> <SECTNO>§ 23.479</SECTNO> <SUBJECT>Level landing conditions.</SUBJECT> (a) For a level landing, the airplane is assumed to be in the following attitudes: (1) For airplanes with tail wheels, a normal level flight attitude. (2) For airplanes with nose wheels, attitudes in which— (i) The nose and main wheels contact the ground simultaneously; and (ii) The main wheels contact the ground and the nose wheel is just clear of the ground. <FP>The attitude used in paragraph (a)(2)(i) of this section may be used in the analysis required under paragraph (a)(2)(ii) of this section.</FP> (b) When investigating landing conditions, the drag components simulating the forces required to accelerate the tires and wheels up to the landing speed (spin-up) must be properly combined with the corresponding instantaneous vertical ground reactions, and the forward-acting horizontal loads resulting from rapid reduction of the spin-up drag loads (spring-back) must be combined with vertical ground reactions at the instant of the peak forward load, assuming wing lift and a tire-sliding coefficient of friction of 0.8. However, the drag loads may not be less than 25 percent of the maximum vertical ground reactions (neglecting wing lift). (c) In the absence of specific tests or a more rational analysis for determining the wheel spin-up and spring-back loads for landing conditions, the method set forth in appendix D of this part must be used. If appendix D of this part is used, the drag components used for design must not be less than those given by appendix C of this part. (d) For airplanes with tip tanks or large overhung masses (such as turbo-propeller or jet engines) supported by the wing, the tip tanks and the structure supporting the tanks or overhung masses must be designed for the effects of dynamic responses under the level landing conditions of either paragraph (a)(1) or (a)(2)(ii) of this section. In evaluating the effects of dynamic response, an airplane lift equal to the weight of the airplane may be assumed. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-17, 41 FR 55464, Dec. 20, 1976; Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.481</SECTNO> <SUBJECT>Tail down landing conditions.</SUBJECT> (a) For a tail down landing, the airplane is assumed to be in the following attitudes: (1) For airplanes with tail wheels, an attitude in which the main and tail wheels contact the ground simultaneously. (2) For airplanes with nose wheels, a stalling attitude, or the maximum angle allowing ground clearance by each part of the airplane, whichever is less. (b) For airplanes with either tail or nose wheels, ground reactions are assumed to be vertical, with the wheels up to speed before the maximum vertical load is attained. </SECTION> <SECTION> <SECTNO>§ 23.483</SECTNO> <SUBJECT>One-wheel landing conditions.</SUBJECT> For the one-wheel landing condition, the airplane is assumed to be in the level attitude and to contact the ground on one side of the main landing gear. In this attitude, the ground reactions must be the same as those obtained on that side under § 23.479. </SECTION> <SECTION> <SECTNO>§ 23.485</SECTNO> <SUBJECT>Side load conditions.</SUBJECT> (a) For the side load condition, the airplane is assumed to be in a level attitude with only the main wheels contacting the ground and with the shock absorbers and tires in their static positions. (b) The limit vertical load factor must be 1.33, with the vertical ground reaction divided equally between the main wheels. (c) The limit side inertia factor must be 0.83, with the side ground reaction divided between the main wheels so that— (1) 0.5 (<E T="03">W</E>) is acting inboard on one side; and (2) 0.33 (<E T="03">W</E>) is acting outboard on the other side. (d) The side loads prescribed in paragraph (c) of this section are assumed to be applied at the ground contact point <PRTPAGE P="203"/>and the drag loads may be assumed to be zero. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-45, 58 FR 42160, Aug. 6, 1993]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.493</SECTNO> <SUBJECT>Braked roll conditions.</SUBJECT> Under braked roll conditions, with the shock absorbers and tires in their static positions, the following apply: (a) The limit vertical load factor must be 1.33. (b) The attitudes and ground contacts must be those described in § 23.479 for level landings. (c) A drag reaction equal to the vertical reaction at the wheel multiplied by a coefficient of friction of 0.8 must be applied at the ground contact point of each wheel with brakes, except that the drag reaction need not exceed the maximum value based on limiting brake torque. </SECTION> <SECTION> <SECTNO>§ 23.497</SECTNO> <SUBJECT>Supplementary conditions for tail wheels.</SUBJECT> In determining the ground loads on the tail wheel and affected supporting structures, the following apply: (a) For the obstruction load, the limit ground reaction obtained in the tail down landing condition is assumed to act up and aft through the axle at 45 degrees. The shock absorber and tire may be assumed to be in their static positions. (b) For the side load, a limit vertical ground reaction equal to the static load on the tail wheel, in combination with a side component of equal magnitude, is assumed. In addition— (1) If a swivel is used, the tail wheel is assumed to be swiveled 90 degrees to the airplane longitudinal axis with the resultant ground load passing through the axle; (2) If a lock, steering device, or shimmy damper is used, the tail wheel is also assumed to be in the trailing position with the side load acting at the ground contact point; and (3) The shock absorber and tire are assumed to be in their static positions. (c) If a tail wheel, bumper, or an energy absorption device is provided to show compliance with § 23.925(b), the following apply: (1) Suitable design loads must be established for the tail wheel, bumper, or energy absorption device; and (2) The supporting structure of the tail wheel, bumper, or energy absorption device must be designed to withstand the loads established in paragraph (c)(1) of this section. <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-48, 61 FR 5147, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.499</SECTNO> <SUBJECT>Supplementary conditions for nose wheels.</SUBJECT> In determining the ground loads on nose wheels and affected supporting structures, and assuming that the shock absorbers and tires are in their static positions, the following conditions must be met: (a) For aft loads, the limit force components at the axle must be— (1) A vertical component of 2.25 times the static load on the wheel; and (2) A drag component of 0.8 times the vertical load. (b) For forward loads, the limit force components at the axle must be— (1) A vertical component of 2.25 times the static load on the wheel; and (2) A forward component of 0.4 times the vertical load. (c) For side loads, the limit force components at ground contact must be— (1) A vertical component of 2.25 times the static load on the wheel; and (2) A side component of 0.7 times the vertical load. (d) For airplanes with a steerable nose wheel that is controlled by hydraulic or other power, at design takeoff weight with the nose wheel in any steerable position, the application of 1.33 times the full steering torque combined with a vertical reaction equal to 1.33 times the maximum static reaction on the nose gear must be assumed. However, if a torque limiting device is installed, the steering torque can be reduced to the maximum value allowed by that device. (e) For airplanes with a steerable nose wheel that has a direct mechanical connection to the rudder pedals, the mechanism must be designed to withstand the steering torque for the <PRTPAGE P="204"/>maximum pilot forces specified in § 23.397(b). <CITA>[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-48, 61 FR 5147, Feb. 9, 1996]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.505</SECTNO> <SUBJECT>Supplementary conditions for skiplanes.</SUBJECT> In determining ground loads for skiplanes, and assuming that the airplane is resting on the ground with one main ski frozen at rest and the other skis free to slide, a limit side force equal to 0.036 times the design maximum weight must be applied near the tail assembly, with a factor of safety of 1. <CITA>[Amdt. 23-7, 34 FR 13090, Aug. 13, 1969]</CITA> </SECTION> <SECTION> <SECTNO>§ 23.507</SECTNO> <SUBJECT>Jacking loads.</SUBJECT> (a) The airplane must be designed for the loads developed when the aircraft is supported on jacks at the design maximum weight assuming the following load factors for landing gear jacking points at a three-point attitude and for primary flight structure jacking points in the level attitude: (1) Vertical-load factor of 1.35 times the static reactions. (2) Fore, aft, and lateral load factors of 0.4 ti