(a)
(1) The location of the aircraft and the place where the demonstrations are to be conducted; and
(2) The date the demonstrations are to commence (at least 10 days after filing the application).
(b)
(1) The registration number, make, and model of the aircraft to which it applies;
(2) A maintenance program as specified in section 4 of this appendix; and
(3) The procedures and instructions related to recognition of decision height, use of runway visual range information, approach monitoring, the decision region (the region between the middle marker and the decision height), the maximum permissible deviations of the basic ILS indicator within the decision region, a missed approach, use of airborne low approach equipment, minimum altitude for the use of the autopilot, instrument and equipment failure warning systems, instrument failure, and other procedures, instructions, and limitations that may be found necessary by the Administrator.
The instruments and equipment listed in this section must be installed in each aircraft operated in a Category II operation. This section does not require duplication of instruments and equipment required by § 91.205 or any other provisions of this chapter.
(a)
(2) A communications system that does not affect the operation of at least one of the ILS systems.
(3) A marker beacon receiver that provides distinctive aural and visual indications of the outer and the middle markers.
(4) Two gyroscopic pitch and bank indicating systems.
(5) Two gyroscopic direction indicating systems.
(6) Two airspeed indicators.
(7) Two sensitive altimeters adjustable for barometric pressure, each having a placarded correction for altimeter scale error and for the wheel height of the aircraft. After June 26, 1979, two sensitive altimeters adjustable for barometric pressure, having markings at 20-foot intervals and each having a placarded correction for altimeter scale error and for the wheel height of the aircraft.
(8) Two vertical speed indicators.
(9) A flight control guidance system that consists of either an automatic approach coupler or a flight director system. A flight director system must display computed information as steering command in relation to an ILS localizer and, on the same instrument, either computed information as pitch command in relation to an ILS glide slope or basic ILS glide slope information. An automatic approach coupler must provide at least automatic steering in relation to an ILS localizer. The flight control guidance system may be operated from one of the receiving systems required by subparagraph (1) of this paragraph.
(10) For Category II operations with decision heights below 150 feet either a marker beacon receiver providing aural and visual indications of the inner marker or a radio altimeter.
(b)
(2) Dual controls.
(3) An externally vented static pressure system with an alternate static pressure source.
(4) A windshield wiper or equivalent means of providing adequate cockpit visibility for a safe visual transition by either pilot to touchdown and rollout.
(5) A heat source for each airspeed system pitot tube installed or an equivalent means of preventing malfunctioning due to icing of the pitot system.
(a)
(1) The ILS localizer and glide slope equipment were bench checked according to the manufacturer's instructions and found to meet those standards specified in RTCA Paper 23-63/DO-117 dated March 14, 1963, “Standard Adjustment Criteria for Airborne Localizer and Glide Slope Receivers,” which may be obtained from the RTCA Secretariat, 1425 K St., NW., Washington, DC 20005.
(2) The altimeters and the static pressure systems were tested and inspected in accordance with appendix E to part 43 of this chapter; and
(3) All other instruments and items of equipment specified in section 2(a) of this appendix that are listed in the proposed maintenance program were bench checked and found to meet the manufacturer's specifications.
(b)
(c)
(1) It must display to the flight crew clearly and positively the wheel height of the main landing gear above the terrain.
(2) It must display wheel height above the terrain to an accuracy of plus or minus 5 feet or 5 percent, whichever is greater, under the following conditions:
(i) Pitch angles of zero to plus or minus 5 degrees about the mean approach attitude.
(ii) Roll angles of zero to 20 degrees in either direction.
(iii) Forward velocities from minimum approach speed up to 200 knots.
(iv) Sink rates from zero to 15 feet per second at altitudes from 100 to 200 feet.
(3) Over level ground, it must track the actual altitude of the aircraft without significant lag or oscillation.
(4) With the aircraft at an altitude of 200 feet or less, any abrupt change in terrain representing no more than 10 percent of the aircraft's altitude must not cause the altimeter to unlock, and indicator response to such changes must not exceed 0.1 seconds and, in addition, if the system unlocks for greater changes, it must reacquire the signal in less than 1 second.
(5) Systems that contain a push-to-test feature must test the entire system (with or without an antenna) at a simulated altitude of less than 500 feet.
(6) The system must provide to the flight crew a positive failure warning display any time there is a loss of power or an absence of ground return signals within the designed range of operating altitudes.
(d)
(e)
(2)
(i) At the 100-foot decision height, the indicated airspeed and heading are satisfactory for a normal flare and landing (speed must be plus or minus 5 knots of programmed airspeed, but may not be less than computed threshold speed if autothrottles are used);
(ii) The aircraft at the 100-foot decision height, is positioned so that the cockpit is within, and tracking so as to remain within, the lateral confines of the runway extended;
(iii) Deviation from glide slope after leaving the outer marker does not exceed 50 percent of full-scale deflection as displayed on the ILS indicator;
(iv) No unusual roughness or excessive attitude changes occur after leaving the middle marker; and
(v) In the case of an aircraft equipped with an approach coupler, the aircraft is sufficiently in trim when the approach coupler is disconnected at the decision height to allow for the continuation of a normal approach and landing.
(3)
(i) Each deficiency in airborne instruments and equipment that prevented the initiation of an approach.
(ii) The reasons for discontinuing an approach, including the altitude above the runway at which it was discontinued.
(iii) Speed control at the 100-foot decision height if auto throttles are used.
(iv) Trim condition of the aircraft upon disconnecting the auto coupler with respect to continuation to flare and landing.
(v) Position of the aircraft at the middle marker and at the decision height indicated both on a diagram of the basic ILS display and a diagram of the runway extended to the middle marker. Estimated touchdown point must be indicated on the runway diagram.
(vi) Compatibility of flight director with the auto coupler, if applicable.
(vii) Quality of overall system performance.
(4)
(a) Each maintenance program must contain the following:
(1) A list of each instrument and item of equipment specified in § 2 of this appendix that is installed in the aircraft and approved for Category II operations, including the make and model of those specified in § 2(a).
(2) A schedule that provides for the performance of inspections under subparagraph (5) of this paragraph within 3 calendar months after the date of the previous inspection. The inspection must be performed by a person authorized by part 43 of this chapter, except that each alternate inspection may be replaced by a functional flight check. This functional flight check must be performed by a pilot holding a Category II pilot authorization for the type aircraft checked.
(3) A schedule that provides for the performance of bench checks for each listed instrument and item of equipment that is specified in section 2(a) within 12 calendar months after the date of the previous bench check.
(4) A schedule that provides for the performance of a test and inspection of each static pressure system in accordance with appendix E to part 43 of this chapter within 12 calendar months after the date of the previous test and inspection.
(5) The procedures for the performance of the periodic inspections and functional flight checks to determine the ability of each listed instrument and item of equipment specified in section 2(a) of this appendix to perform as approved for Category II operations including a procedure for recording functional flight checks.
(6) A procedure for assuring that the pilot is informed of all defects in listed instruments and items of equipment.
(7) A procedure for assuring that the condition of each listed instrument and item of equipment upon which maintenance is performed is at least equal to its Category II approval condition before it is returned to service for Category II operations.
(8) A procedure for an entry in the maintenance records required by § 43.9 of this chapter that shows the date, airport, and reasons for each discontinued Category II operation because of a malfunction of a listed instrument or item of equipment.
(b)
(1) It must be performed by a certificated repair station holding one of the following ratings as appropriate to the equipment checked:
(i) An instrument rating.
(ii) A radio rating.
(2) It must consist of removal of an instrument or item of equipment and performance of the following:
(i) A visual inspection for cleanliness, impending failure, and the need for lubrication, repair, or replacement of parts;
(ii) Correction of items found by that visual inspection; and
(iii) Calibration to at least the manufacturer's specifications unless otherwise specified in the approved Category II manual for the aircraft in which the instrument or item of equipment is installed.
(c)