[Title 14 CFR ]
[Code of Federal Regulations (annual edition) - January 1, 2009 Edition]
[From the U.S. Government Printing Office]
[[Page i]]
14
Parts 60 to 109
Revised as of January 1, 2009
Aeronautics and Space
________________________
Containing a codification of documents of general
applicability and future effect
As of January 1, 2009
With Ancillaries
Published by:
Office of the Federal Register
National Archives and Records
Administration
A Special Edition of the Federal Register
[[Page ii]]
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[[Page iii]]
As of Jan. 1, 2009
Title 14, Parts 60 to 139
Revised as of Jan. 1, 2008
Is Replaced by
Title 14, Parts 60 to 109
[[Page v]]
Table of Contents
Page
Explanation................................................. vii
Title 14:
Chapter I--Federal Aviation Administration,
Department of Transportation (Continued) 3
Finding Aids:
Table of CFR Titles and Chapters........................ 939
Alphabetical List of Agencies Appearing in the CFR...... 959
List of CFR Sections Affected........................... 969
[[Page vi]]
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Cite this Code: CFR
To cite the regulations in
this volume use title,
part and section number.
Thus, 14 CFR 60.1 refers
to title 14, part 60,
section 1.
----------------------------
[[Page vii]]
EXPLANATION
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[[Page viii]]
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[[Page ix]]
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Office of the Federal Register.
January 1, 2009.
[[Page xi]]
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,
60-109, 110-199, 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 and chapter VI--Office of Management and
Budget. The contents of these volumes represent all current regulations
codified under this title of the CFR as of January 1, 2009.
For this volume, Bonnie Fritts was Chief Editor. The Code of Federal
Regulations publication program is under the direction of Michael L.
White, assisted by Ann Worley.
[[Page 1]]
TITLE 14--AERONAUTICS AND SPACE
(This book contains parts 60 to 109)
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Part
chapter i--Federal Aviation Administration, Department of
Transportation (Continued)................................ 60
[[Page 3]]
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
(CONTINUED)
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SUBCHAPTER D--AIRMEN
Part Page
60 Flight simulation training device initial
and continuing qualification and use.... 5
61 Certification: Pilots, flight instructors,
and ground instructors.................. 406
63 Certification: Flight crewmembers other than
pilots.................................. 521
65 Certification: Airmen other than flight
crewmembers............................. 539
67 Medical standards and certification......... 563
SUBCHAPTER E--AIRSPACE
71 Designation of class A, B, C, D, and E
airspace areas; air traffic service
routes; and reporting points............ 577
73 Special use airspace........................ 580
75 [Reserved]
77 Objects affecting navigable airspace........ 582
SUBCHAPTER F--AIR TRAFFIC AND GENERAL OPERATING RULES
91 General operating and flight rules.......... 596
93 Special air traffic rules................... 855
95 IFR altitudes............................... 907
97 Standard instrument procedures.............. 915
99 Security control of air traffic............. 917
101 Moored balloons, kites, unmanned rockets and
unmanned free balloons.................. 921
103 Ultralight vehicles......................... 927
105 Parachute Operations........................ 930
106-109 [Reserved]
[[Page 5]]
SUBCHAPTER D_AIRMEN
PART 60_FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION
AND USE--Table of Contents
Sec.
60.1 Applicability.
60.2 Applicability of sponsor rules to persons who are not sponsors and
who are engaged in certain unauthorized activities.
60.3 Definitions.
60.4 Qualification Performance Standards.
60.5 Quality management system.
60.7 Sponsor qualification requirements.
60.9 Additional responsibilities of the sponsor.
60.11 FSTD use.
60.13 FSTD objective data requirements.
60.14 Special equipment and personnel requirements for qualification of
the FSTD.
60.15 Initial qualification requirements.
60.16 Additional qualifications for a currently qualified FSTD.
60.17 Previously qualified FSTDs.
60.19 Inspection, continuing qualification evaluation, and maintenance
requirements.
60.20 Logging FSTD discrepancies.
60.21 Interim qualification of FSTDs for new aircraft types or models.
60.23 Modifications to FSTDs.
60.25 Operation with missing, malfunctioning, or inoperative components.
60.27 Automatic loss of qualification and procedures for restoration of
qualification.
60.29 Other losses of qualification and procedures for restoration of
qualification.
60.31 Recordkeeping and reporting.
60.33 Applications, logbooks, reports, and records: Fraud,
falsification, or incorrect statements.
60.35 Specific full flight simulator compliance requirements.
60.37 FSTD qualification on the basis of a Bilateral Aviation Safety
Agreement (BASA).
Appendix A to Part 60--Qualification Performance Standards for Airplane
Full Flight Simulators
Appendix B to Part 60--Qualification Performance Standards for Airplane
Flight Training Devices
Appendix C to Part 60--Qualification Performance Standards for
Helicopter Full Flight Simulators
Appendix D to Part 60--Qualification Performance Standards for
Helicopter Flight Training Devices
Appendix E to Part 60--Qualification Performance Standards for Quality
Management Systems for Flight Simulation Training Devices
Appendix F to Part 60--Definitions and Abbreviations for Flight
Simulation Training Devices
Authority: 49 U.S.C. 106(g), 40113, and 44701.
Source: Doc. No. FAA-2002-12461, 71 FR 63426, Oct. 30, 2006, unless
otherwise noted.
Sec. 60.1 Applicability.
(a) This part prescribes the rules governing the initial and
continuing qualification and use of all aircraft flight simulation
training devices (FSTD) used for meeting training, evaluation, or flight
experience requirements of this chapter for flight crewmember
certification or qualification.
(b) The rules of this part apply to each person using or applying to
use an FSTD to meet any requirement of this chapter.
(c) The requirements of Sec. 60.33 regarding falsification of
applications, records, or reports also apply to each person who uses an
FSTD for training, evaluation, or obtaining flight experience required
for flight crewmember certification or qualification under this chapter.
Sec. 60.2 Applicability of sponsor rules to persons who are not sponsors and
who are engaged in certain unauthorized activities.
(a) The rules of this part that are directed to a sponsor of an FSTD
also apply to any person who uses or causes the use of an FSTD when--
(1) That person knows that the FSTD does not have an FAA-approved
sponsor; and
(2) The use of the FSTD by that person is nonetheless claimed for
purposes of meeting any requirement of this chapter or that person knows
or should have known that the person's acts or omissions would cause
another person to mistakenly credit use of the FSTD for purposes of
meeting any requirement of this chapter.
(b) A situation in which paragraph (a) of this section would not
apply to a
[[Page 6]]
person would be when each of the following conditions are met:
(1) The person sold or leased the FSTD and merely represented to the
purchaser or lessee that the FSTD is in a condition in which it should
be able to obtain FAA approval and qualification under this part;
(2) The person does not falsely claim to be the FAA-approved sponsor
for the FSTD;
(3) The person does not falsely make representations that someone
else is the FAA-approved sponsor of the FSTD at a time when that other
person is not the FAA-approved sponsor of the FSTD; and
(4) The person's acts or omissions do not cause another person to
detrimentally rely on such acts or omissions for the mistaken conclusion
that the FSTD is FAA-approved and qualified under this part at the time
the FSTD is sold or leased.
Sec. 60.3 Definitions.
In addition to the definitions in part 1 of this chapter, other
terms and definitions applicable to this part are found in appendix F of
this part.
Sec. 60.4 Qualification Performance Standards.
The Qualification Performance Standards (QPS) are published in
appendices to this part as follows:
(a) Appendix A contains the QPS for Airplane Flight Simulators.
(b) Appendix B contains the QPS for Airplane Flight Training
Devices.
(c) Appendix C contains the QPS for Helicopter Flight Simulators.
(d) Appendix D contains the QPS for Helicopter Flight Training
Devices.
(e) Appendix E contains the QPS for Quality Management Systems for
FSTDs.
(f) Appendix F contains the QPS for Definitions and Abbreviations
for FSTDs.
Sec. 60.5 Quality management system.
(a) After October 30, 2009, no sponsor may use or allow the use of
or offer the use of an FSTD for flight crewmember training or evaluation
or for obtaining flight experience to meet any requirement of this
chapter unless the sponsor has established and follows a quality
management system (QMS), currently approved by the National Simulator
Program Manager (NSPM), for the continuing surveillance and analysis of
the sponsor's performance and effectiveness in providing a satisfactory
FSTD for use on a regular basis as described in QPS appendix E of this
part.
(b) The QMS program must provide a process for identifying
deficiencies in the program and for documenting how the program will be
changed to address these deficiencies.
(c) Whenever the NSPM finds that the QMS program does not adequately
address the procedures necessary to meet the requirements of this part,
the sponsor must, after notification by the NSPM, change the program so
the procedures meet the requirements of this part. Each such change must
be approved by the NSPM prior to implementation.
(d) Within 30 days after the sponsor receives a notice described in
paragraph (c) of this section, the sponsor may file a petition with the
Director of Flight Standards Service (the Director) for reconsideration
of the NSPM finding. The sponsor must address its petition to the
Director, Flight Standards Service, AFS-1, Federal Aviation
Administration, 800 Independence Ave., SW., Washington, DC 20591. The
filing of such a petition to reconsider stays the notice pending a
decision by the Director. However, if the Director finds that there is a
situation that requires immediate action in the interest of safety in
air commerce, he may, upon a statement of the reasons, require a change
effective without stay.
[Doc. No. FAA-2002-12461, 71 FR 63426, Oct. 30, 2006; Amdt. 60-2, 72 FR
59599, Oct. 22, 2007]
Sec. 60.7 Sponsor qualification requirements.
(a) A person is eligible to apply to be a sponsor of an FSTD if the
following conditions are met:
(1) The person holds, or is an applicant for, a certificate under
part 119, 141, or 142 of this chapter; or holds, or is an applicant for,
an approved flight engineer course in accordance with part 63 of this
chapter.
(2) The FSTD will be used, or will be offered for use, in the
sponsor's FAA-approved flight training program for
[[Page 7]]
the aircraft being simulated as evidenced in a request for evaluation
submitted to the NSPM.
(b) A person is a sponsor if the following conditions are met:
(1) The person is a certificate holder under part 119, 141, or 142
of this chapter or has an approved flight engineer course in accordance
with part 63 of this chapter.
(2) The person has--
(i) Operations specifications authorizing the use of the specific
aircraft or set of aircraft and has an FAA-approved training program
under which at least one FSTD, simulating the aircraft or set of
aircraft and for which the person is the sponsor, is used by the sponsor
as described in paragraphs (b)(5) or (b)(6) of this section; or
(ii) Training specifications or an FAA-approved course of training
under which at least one FSTD, simulating that aircraft or set of
aircraft and for which the person is the sponsor, is used by the sponsor
as described in paragraphs (b)(5) or (b)(6) of this section.
(3) The person has a quality management system currently approved by
the NSPM in accordance with Sec. 60.5.
(4) The NSPM has accepted the person as the sponsor of the FSTD and
that acceptance has not been withdrawn by the FAA.
(5) At least one FSTD (as referenced in paragraph (b)(2)(i) or
(b)(2)(ii) of this section) that is initially qualified on or after
October 30, 2007, is used within the sponsor's FAA-approved flight
training program for the aircraft or set of aircraft at least once
within the 12-month period following the initial/upgrade evaluation, and
at least once within each subsequent 12-month period thereafter.
(6) At least one FSTD (as referenced in paragraph (b)(2)(i) or
(b)(2)(ii) of this section) that was qualified before October 30, 2007,
is used within the sponsor's FAA-approved flight training program for
the aircraft or set of aircraft at least once within the 12-month period
following the first continuing qualification evaluation conducted by the
NSPM after October 30, 2007 and at least once within each subsequent 12-
month period thereafter.
(c) If the use requirements of paragraphs (b)(2) and either (b)(5)
or (b)(6) of this section are not met, the person will forfeit the right
to sponsor that FSTD and that person will not be eligible to apply to
sponsor that FSTD for at least 12 calendar months following the
expiration of the qualification status.
(d) In addition to the FSTD described in paragraph (b) of this
section, an FSTD sponsor may sponsor any number of other FSTDs
regardless of specific aircraft or set of aircraft provided either--
(1) During the preceding 12-month period, all of the other FSTDs are
used within the sponsor's or another certificate holder's FAA-approved
flight training program for the aircraft or set of aircraft simulated;
or
(2) The sponsor obtains a written statement at least annually from a
qualified pilot who has flown the aircraft or set of aircraft (as
appropriate) during the preceding 12-month period stating that the
subject FSTD's performance and handling qualities, within the normal
operating envelope, represent the aircraft or set of aircraft described
in the FAA Type Certificate and the type data sheet, if appropriate. The
sponsor must retain the two most current written statements for review
by the NSPM.
[Doc. No. FAA-2002-12461, 71 FR 63426, Oct. 30, 2006; Amdt. 60-2, 72 FR
59599, Oct. 22, 2007]
Sec. 60.9 Additional responsibilities of the sponsor.
(a) The sponsor must allow the NSPM upon request to inspect the FSTD
as soon as practicable. This inspection may include all records and
documents relating to the FSTD, to determine its compliance with this
part.
(b) The sponsor must do the following for each FSTD:
(1) Establish a mechanism to receive written comments regarding the
FSTD and its operation in accordance with the QPS appendix E of this
part.
(2) Post in or adjacent to the FSTD the Statement of Qualification
issued by the NSPM. An electronic copy of the Statement of Qualification
that may be accessed by an appropriate terminal or display in or
adjacent to the FSTD is satisfactory.
[[Page 8]]
(c) Each sponsor of an FSTD must identify to the NSPM by name, one
individual to be the management representative (MR).
(1) One person may serve as an MR for more than one FSTD, but one
FSTD must not have more than one person serving in this capacity.
(2) Each MR must be an employee of the sponsor with the
responsibility and authority to--
(i) Monitor the on-going qualification of assigned FSTDs to ensure
that all matters regarding FSTD qualification are being carried out as
provided for in this part;
(ii) Ensure that the QMS is properly established, implemented, and
maintained by overseeing the structure (and modifying where necessary)
of the QMS policies, practices, and procedures; and
(iii) Regularly brief sponsor's management on the status of the on-
going FSTD qualification program and the effectiveness and efficiency of
the QMS.
(3) The MR serves as the primary contact point for all matters
between the sponsor and the NSPM regarding the qualification of that
FSTD as provided for in this part.
(4) The MR may delegate the duties described in paragraph (c)(2) and
(c)(3) of this section to an individual at each of the sponsor's
locations.
Sec. 60.11 FSTD use.
No person may use or allow the use of or offer the use of an FSTD
for flight crewmember training or evaluation or for obtaining flight
experience to meet any of the requirements under this chapter unless, in
accordance with the QPS for the specific device, the FSTD meets all of
the following:
(a) Has a single sponsor who is qualified under Sec. 60.7. The
sponsor may arrange with another person for services of document
preparation and presentation, as well as FSTD inspection, maintenance,
repair, and servicing; however, the sponsor remains responsible for
ensuring that these functions are conducted in a manner and with a
result of continually meeting the requirements of this part.
(b) Is qualified as described in the Statement of Qualification.
(c) Remains qualified, through satisfactory inspection, continuing
qualification evaluations, appropriate maintenance, and use requirements
in accordance with this part and the applicable QPS.
(d) Functions during day-to-day training, evaluation, or flight
experience activities with the software and hardware that was evaluated
as satisfactory by the NSPM and, if modified, modified only in
accordance with the provisions of this part. However, this section does
not apply to routine software or hardware changes that do not fall under
the requirements of Sec. 60.23.
(e) Is operated in accordance with the provisions and limitations of
Sec. 60.25.
Sec. 60.13 FSTD objective data requirements.
(a) Except as provided in paragraph (b) and (c) of this section, for
the purposes of validating FSTD performance and handling qualities
during evaluation for qualification, the data made available to the NSPM
(the validation data package) must include the aircraft manufacturer's
flight test data and all relevant data developed after the type
certificate was issued (e.g., data developed in response to an
airworthiness directive) if such data results from a change in
performance, handling qualities, functions, or other characteristics of
the aircraft that must be considered for flight crewmember training,
evaluation, or for meeting experience requirements of this chapter.
(b) The validation data package may contain flight test data from a
source in addition to or independent of the aircraft manufacturer's data
in support of an FSTD qualification, but only if this data is gathered
and developed by that source in accordance with flight test methods,
including a flight test plan, as described in the applicable QPS.
(c) The validation data package may also contain predicted data,
engineering simulation data, data from pilot owner or pilot operating
manuals, or data from public domain sources, provided this data is
acceptable to the NSPM. If found acceptable the data may then be used in
particular applications for FSTD qualification.
[[Page 9]]
(d) Data or other material or elements must be submitted in a form
and manner acceptable to the NSPM.
(e) The NSPM may require additional objective data, which may
include flight testing if necessary, if the validation data package does
not support FSTD qualification requirements as described in this part
and the applicable QPS appendix.
(f) When an FSTD sponsor learns, or is advised by an aircraft
manufacturer or other data provider, that an addition to, an amendment
to, or a revision of data that may relate to FSTD performance or
handling characteristics is available, the sponsor must notify the NSPM
as described in the applicable QPS.
Sec. 60.14 Special equipment and personnel requirements for qualification of
the FSTD.
When notified by the NSPM, the sponsor must make available all
special equipment and qualified personnel needed to accomplish or assist
in the accomplishment of tests during initial qualification, continuing
qualification, or special evaluations.
Sec. 60.15 Initial qualification requirements.
(a) For each FSTD, the sponsor must submit a request to the NSPM to
evaluate the FSTD for initial qualification at a specific level and
simultaneously request the Training Program Approval Authority (TPAA)
forward a concurring letter to the NSPM. The request must be submitted
in the form and manner described in the applicable QPS.
(b) The management representative described in Sec. 60.9(c) must
sign a statement (electronic signature is acceptable for electronic
transmissions) after confirming the following:
(1) The performance and handling qualities of the FSTD represent
those of the aircraft or set of aircraft within the normal operating
envelope. This determination must be made by a pilot(s) meeting the
requirements of paragraph (d) of this section after having flown all of
the Operations Tasks listed in the applicable QPS appendix relevant to
the qualification level of the FSTD. Exceptions, if any, must be noted.
The name of the person(s) making this determination must be available to
the NSPM upon request.
(2) The FSTD systems and sub-systems (including the simulated
aircraft systems) functionally represent those in the aircraft or set of
aircraft. This determination must be made by the pilot(s) described in
paragraph (b)(1) of this section, or by a person(s) trained on simulator
systems/sub-systems and trained on the operation of the simulated
aircraft systems, after having exercised the operation of the FSTD and
the pertinent functions available through the Instructor Operating
Station(s). Exceptions, if any, must be noted. The name of the person(s)
making this determination must be available to the NSPM upon request.
(3) The cockpit represents the configuration of the specific type;
or aircraft make, model, and series aircraft being simulated, as
appropriate. This determination must be made by the pilot(s) described
in paragraph (b)(1) of this section, or by a person(s) trained on the
configuration and operation of the aircraft simulated. Exceptions, if
any, must be noted. The name of the person(s) making this determination
must be available to the NSPM upon request.
(c) Except for those FSTDs previously qualified and described in
Sec. 60.17, each FSTD evaluated for initial qualification must meet the
standard that is in effect at the time of the evaluation. However--
(1) If the FAA publishes a change to the existing standard or
publishes a new standard for the evaluation for initial qualification, a
sponsor may request that the NSPM apply the standard that was in effect
when an FSTD was ordered for delivery if the sponsor--
(i) Within 30 days of the publication of the change to the existing
standard or publication of the new standard, notifies the NSPM that an
FSTD has been ordered;
(ii) Within 90 days of the NSPM notification described in paragraph
(c)(1)(i) of this section, requests that the standard in effect at the
time the order was placed be used for the evaluation for initial
qualification; and
[[Page 10]]
(iii) The evaluation is conducted within 24 months following the
publication of the change to the existing standard or publication of the
new standard.
(2) This notification must include a description of the FSTD; the
anticipated qualification level of the FSTD; the make, model, and series
of aircraft simulated; and any other pertinent information.
(3) Any tests, tolerances, or other requirements that are current at
the time of the evaluation may be used during the initial evaluation, at
the request of the sponsor, if the sponsor provides acceptable updates
to the required qualification test guide.
(4) The standards used for the evaluation for initial qualification
will be used for all subsequent evaluations of the FSTD.
(d) The pilot(s) who contributes to the confirmation statement
required by paragraph (b) of this section must--
(1) Be designated by the sponsor; and
(2) Be qualified in--
(i) The aircraft or set of aircraft being simulated; or
(ii) For aircraft not yet issued a type certificate, or aircraft not
previously operated by the sponsor or not having previous FAA-approved
training programs conducted by the sponsor, an aircraft similar in size
and configuration.
(e) The subjective tests that form the basis for the statements
described in paragraph (b) of this section and the objective tests
referenced in paragraph (f) of this section must be accomplished at the
sponsor's training facility, except as provided for in the applicable
QPS.
(f) The person seeking to qualify the FSTD must provide the NSPM
access to the FSTD for the length of time necessary for the NSPM to
complete the required evaluation of the FSTD for initial qualification,
which includes the conduct and evaluation of objective and subjective
tests, including general FSTD requirements, as described in the
applicable QPS, to determine that the FSTD meets the standards in that
QPS.
(g) When the FSTD passes an evaluation for initial qualification,
the NSPM issues a Statement of Qualification that includes all of the
following:
(1) Identification of the sponsor.
(2) Identification of the make, model, and series of the aircraft or
set of aircraft being simulated.
(3) Identification of the configuration of the aircraft or set of
aircraft being simulated (e.g., engine model or models, flight
instruments, or navigation or other systems).
(4) A statement that the FSTD is qualified as either a full flight
simulator or a flight training device.
(5) Identification of the qualification level of the FSTD.
(6) A statement that (with the exception of the noted exclusions for
which the FSTD has not been subjectively tested by the sponsor or the
NSPM and for which qualification is not sought) the qualification of the
FSTD includes the tasks set out in the applicable QPS appendix relevant
to the qualification level of the FSTD.
(h) After the NSPM completes the evaluation for initial
qualification, the sponsor must update the Qualification Test Guide
(QTG), with the results of the FAA-witnessed tests together with the
results of all the objective tests described in the applicable QPS.
(i) Upon issuance of the Statement of Qualification the updated QTG
becomes the Master Qualification Test Guide (MQTG). The MQTG must be
made available to the NSPM upon request.
Sec. 60.16 Additional qualifications for a currently qualified FSTD.
(a) A currently qualified FSTD is required to undergo an additional
qualification process if a user intends to use the FSTD for meeting
training, evaluation, or flight experience requirements of this chapter
beyond the qualification issued for that FSTD. This process consists of
the following:
(1) The sponsor:
(i) Must submit to the NSPM all modifications to the MQTG that are
required to support the additional qualification.
(ii) Must describe to the NSPM all modifications to the FSTD that
are required to support the additional qualification.
[[Page 11]]
(iii) Must submit to the NSPM a confirmation statement as described
in Sec. 60.15(c) that a pilot, designated by the sponsor in accordance
with Sec. 60.15(d), has subjectively evaluated the FSTD in those areas
not previously evaluated.
(2) The FSTD must successfully pass an evaluation--
(i) Consisting of all the elements of an initial evaluation for
qualification in those circumstances where the NSPM has determined that
all the elements of an initial evaluation for qualification is
necessary; or
(ii) Consisting of those elements of an initial evaluation for
qualification designated as necessary by the NSPM.
(b) In making the determinations described in paragraph (a)(2) of
this section, the NSPM considers factors including the existing
qualification of the FSTD, any modifications to the FSTD hardware or
software that are involved, and any additions or modifications to the
MQTG.
(c) The FSTD is qualified for the additional uses when the NSPM
issues an amended Statement of Qualification in accordance with Sec.
60.15(h).
(d) The sponsor may not modify the FSTD except as described in Sec.
60.23.
Sec. 60.17 Previously qualified FSTDs.
(a) Unless otherwise specified by an FSTD Directive, further
referenced in the applicable QPS, or as specified in paragraph (e) of
this section, an FSTD qualified before October 30, 2007 will retain its
qualification basis as long as it continues to meet the standards,
including the objective test results recorded in the MQTG and subjective
tests, under which it was originally evaluated, regardless of sponsor.
The sponsor of such an FSTD must comply with the other applicable
provisions of this part.
(b) For each FSTD qualified before October 30, 2007, no sponsor may
use or allow the use of or offer the use of such an FSTD after October
30, 2013 for flight crewmember training, evaluation or flight experience
to meet any of the requirements of this chapter, unless that FSTD has
been issued a Statement of Qualification, including the Configuration
List and the List of Qualified Tasks in accordance with the procedures
set out in the applicable QPS.
(c) If the FSTD qualification is lost under Sec. 60.27 and--
(i) Restored under Sec. 60.27 in less than (2) years, then the
qualification basis (in terms of objective tests and subjective tests)
for the re-qualification will be those against which the FSTD was
originally evaluated and qualified.
(ii) Not restored under Sec. 60.27 for two (2) years or more, then
the qualification basis (in terms of objective tests and subjective
tests) for the re-qualification will be those standards in effect and
current at the time of re-qualification application.
(d) Except as provided in paragraph (e) of this section, any change
in FSTD qualification level initiated on or after October 30, 2007
requires an evaluation for initial qualification in accordance with this
part.
(e) A sponsor may request that an FSTD be permanently downgraded. In
such a case, the NSPM may downgrade a qualified FSTD without requiring
and without conducting an initial evaluation for the new qualification
level. Subsequent continuing qualification evaluations will use the
existing MQTG, modified as necessary to reflect the new qualification
level.
(f) When the sponsor has appropriate validation data available and
receives approval from the NSPM, the sponsor may adopt tests and
associated tolerances described in the current qualification standards
as the tests and tolerances applicable for the continuing qualification
of a previously qualified FSTD. The updated test(s) and tolerance(s)
must be made a permanent part of the MQTG.
[Doc. No. FAA-2002-12461, 71 FR 63426, Oct. 30, 2006; Amdt. 60-2, 72 FR
59599, Oct. 22, 2007]
Sec. 60.19 Inspection, continuing qualification evaluation, and maintenance
requirements.
(a) Inspection. No sponsor may use or allow the use of or offer the
use of an FSTD for flight crewmember training, evaluation, or flight
experience to meet any of the requirements of this chapter unless the
sponsor does the following:
[[Page 12]]
(1) Accomplishes all appropriate objective tests each year as
specified in the applicable QPS.
(2) Completes a functional preflight check within the preceding 24
hours.
(b) Continuing qualification evaluation.
(1) This evaluation consists of objective tests, and subjective
tests, including general FSTD requirements, as described in the
applicable QPS or as may be amended by an FSTD Directive.
(2) The sponsor must contact the NSPM to schedule the FSTD for
continuing qualification evaluations not later than 60 days before the
evaluation is due.
(3) The sponsor must provide the NSPM access to the objective test
results in the MQTG and access to the FSTD for the length of time
necessary for the NSPM to complete the required continuing qualification
evaluations.
(4) The frequency of NSPM-conducted continuing qualification
evaluations for each FSTD will be established by the NSPM and specified
in the MQTG.
(5) Continuing qualification evaluations conducted in the calendar
month before or after the calendar month in which these continuing
qualification evaluations are required will be considered to have been
conducted in the calendar month in which they were required.
(6) No sponsor may use or allow the use of or offer the use of an
FSTD for flight crewmember training or evaluation or for obtaining
flight experience for the flight crewmember to meet any requirement of
this chapter unless the FSTD has passed an NSPM-conducted continuing
qualification evaluation within the time frame specified in the MQTG or
within the grace period as described in paragraph (b)(5) of this
section.
(c) Maintenance. The sponsor is responsible for continuing
corrective and preventive maintenance on the FSTD to ensure that it
continues to meet the requirements of this part and the applicable QPS
appendix. No sponsor may use or allow the use of or offer the use of an
FSTD for flight crewmember training, evaluation, or flight experience to
meet any of the requirements of this chapter unless the sponsor does the
following:
(1) Maintains a discrepancy log.
(2) Ensures that, when a discrepancy is discovered, the following
requirements are met:
(i) A description of each discrepancy is entered in the log and
remains in the log until the discrepancy is corrected as specified in
Sec. 60.25(b).
(ii) A description of the corrective action taken for each
discrepancy, the identity of the individual taking the action, and the
date that action is taken is entered in the log.
(iii) The discrepancy log is kept in a form and manner acceptable to
the Administrator and is kept in or adjacent to the FSTD. An electronic
log that may be accessed by an appropriate terminal or display in or
adjacent to the FSTD is satisfactory.
Sec. 60.20 Logging FSTD discrepancies.
Each instructor, check airman, or representative of the
Administrator conducting training, evaluation, or flight experience, and
each person conducting the preflight inspection who discovers a
discrepancy, including any missing, malfunctioning, or inoperative
components in the FSTD, must write or cause to be written a description
of that discrepancy into the discrepancy log at the end of the FSTD
preflight or FSTD use session.
Sec. 60.21 Interim qualification of FSTDs for new aircraft types or models.
(a) A sponsor may apply for and the NSPM may issue an interim
qualification level for an FSTD for a new type or model of aircraft,
even though the aircraft manufacturer's aircraft data package is
preliminary, if the sponsor provides the following to the satisfaction
of the NSPM--
(1) The aircraft manufacturer's data, which consists of at least
predicted data, validated by a limited set of flight test data;
(2) The aircraft manufacturer's description of the prediction
methodology used to develop the predicted data; and
(3) The QTG test results.
(b) An FSTD that has been issued interim qualification is deemed to
have been issued initial qualification unless the NSPM rescinds the
qualification. Interim qualification terminates two
[[Page 13]]
years after its issuance, unless the NSPM determines that specific
conditions warrant otherwise.
(c) Within twelve months of the release of the final aircraft data
package by the aircraft manufacturer, but no later than two years after
the issuance of the interim qualification status, the sponsor must apply
for initial qualification in accordance with Sec. 60.15 based on the
final aircraft data package approved by the aircraft manufacturer,
unless the NSPM determines that specific conditions warrant otherwise.
(d) An FSTD with interim qualification may be modified only in
accordance with Sec. 60.23.
Sec. 60.23 Modifications to FSTDs.
(a) Description of a modification. For the purposes of this part, an
FSTD is said to have been modified when:
(1) Equipment or devices intended to simulate aircraft appliances
are added to or removed from FSTD, which change the Statement of
Qualification or the MQTG; or
(2) Changes are made to either software or hardware that are
intended to impact flight or ground dynamics; changes are made that
impact performance or handling characteristics of the FSTD (including
motion, visual, control loading, or sound systems for those FSTD levels
requiring sound tests and measurements); or changes are made to the
MQTG.
(b) FSTD Directive. When the FAA determines that FSTD modification
is necessary for safety of flight reasons, the sponsor of each affected
FSTD must ensure that the FSTD is modified according to the FSTD
Directive regardless of the original qualification standards applicable
to any specific FSTD.
(c) Using the modified FSTD. The sponsor may not use, or allow the
use of, or offer the use of, the FSTD with the proposed modification for
flight crewmember training or evaluation or for obtaining flight
experience for the flight crewmember to meet any requirement of this
chapter unless:
(1) The sponsor has notified the NSPM and the TPAA of their intent
to incorporate the proposed modification, and one of the following has
occurred;
(i) Twenty-one days have passed since the sponsor notified the NSPM
and the TPAA of the proposed modification and the sponsor has not
received any response from either the NSPM or the TPAA;
(ii) Twenty-one days have passed since the sponsor notified the NSPM
and the TPAA of the proposed modification and one has approved the
proposed modification and the other has not responded;
(iii) Fewer than twenty-one days have passed since the sponsor
notified the NSPM and the TPAA of the proposed modification and the NSPM
and TPAA both approve the proposed modification;
(iv) The sponsor has successfully completed any evaluation the NSPM
may require in accordance with the standards for an evaluation for
initial qualification or any part thereof before the modified FSTD is
placed in service.
(2) The notification is submitted with the content as, and in a form
and manner as, specified in the applicable QPS.
(d) User notification. When a modification is made to an FSTD that
affects the Statement of Qualification, the sponsor must post an
addendum to the Statement of Qualification until such time as a
permanent, updated statement is posted.
(e) MQTG update. The MQTG must be updated with current objective
test results in accordance with Sec. 60.15(h) and (i) and appropriate
objective data in accordance with Sec. 60.13, each time an FSTD is
modified and an objective test or other MQTG section is affected by the
modification. If an FSTD Directive is the cause of this update, the
direction to make the modification and the record of the modification
completion must be filed in the MQTG.
Sec. 60.25 Operation with missing, malfunctioning, or inoperative components.
(a) No person may knowingly use or allow the use of or misrepresent
the capability of an FSTD for any maneuver, procedure, or task that is
to be accomplished to meet training, evaluation, or flight experience
requirements of this chapter for flight crewmember certification or
qualification when there is a
[[Page 14]]
missing, malfunctioning, or inoperative (MMI) component that is required
to be present and correctly operate for the satisfactory completion of
that maneuver, procedure, or task.
(b) Each MMI component as described in paragraph (a) of this
section, or any MMI component installed and required to operate
correctly to meet the current Statement of Qualification, must be
repaired or replaced within 30 calendar days, unless otherwise required
or authorized by the NSPM.
(c) A list of the current MMI components must be readily available
in or adjacent to the FSTD for review by users of the device. Electronic
access to this list via an appropriate terminal or display in or
adjacent to the FSTD is satisfactory. The discrepancy log may be used to
satisfy this requirement provided each currently MMI component is listed
in the discrepancy log.
Sec. 60.27 Automatic loss of qualification and procedures for restoration of
qualification.
(a) An FSTD qualification is automatically lost when any of the
following occurs:
(1) The FSTD is not used in the sponsor's FAA-approved flight
training program in accordance with Sec. 60.7(b)(5) or (b)(6) and the
sponsor does not obtain and maintain the written statement as described
in Sec. 60.7(d)(2).
(2) The FSTD is not inspected in accordance with Sec. 60.19.
(3) The FSTD is physically moved from one location and installed in
a different location, regardless of distance.
(4) The MQTG is missing or otherwise not available and a replacement
is not made within 30 days.
(b) If FSTD qualification is lost under paragraph (a) of this
section, qualification is restored when either of the following
provisions is met:
(1) The FSTD successfully passes an evaluation:
(i) For initial qualification, in accordance with Sec. Sec. 60.15
and 60.17(c) in those circumstances where the NSPM has determined that a
full evaluation for initial qualification is necessary; or
(ii) For those elements of an evaluation for initial qualification,
in accordance with Sec. Sec. 60.15 and 60.17(c), as determined to be
necessary by the NSPM.
(2) The NSPM advises the sponsor that an evaluation is not
necessary.
(c) In making the determinations described in paragraph (b) of this
section, the NSPM considers factors including the number of continuing
qualification evaluations missed, the number of sponsor-conducted
quarterly inspections missed, and the care that had been taken of the
device since the last evaluation.
Sec. 60.29 Other losses of qualification and procedures for restoration of
qualification.
(a) Except as provided in paragraph (c) of this section, when the
NSPM determines that the FSTD no longer meets qualification standards,
the following procedure applies:
(1) The NSPM notifies the sponsor in writing that the FSTD no longer
meets some or all of its qualification standards.
(2) The NSPM sets a reasonable period (but not less than 7 days)
within which the sponsor may submit written information, views, and
arguments on the FSTD qualification.
(3) After considering all material presented, the NSPM notifies the
sponsor about the determination with regard to the qualification of the
FSTD.
(4) When the NSPM notifies the sponsor that some or all of the FSTD
is no longer qualified, the action described in the notification becomes
effective not less than 30 days after the sponsor receives that notice
unless--
(i) The NSPM finds under paragraph (c) of this section that there is
an emergency requiring immediate action with respect to safety in air
commerce; or
(ii) The sponsor petitions the Director of Flight Standards Service
for reconsideration of the NSPM finding under paragraph (b) of this
section.
(b) When a sponsor seeks reconsideration of a decision from the NSPM
concerning the FSTD qualification, the following procedure applies:
(1) The sponsor must petition for reconsideration of that decision
within 30 days of the date that the sponsor receives a notice that some
or all of the FSTD is no longer qualified.
[[Page 15]]
(2) The sponsor must address its petition to the Director, Flight
Standards Service, AFS-1, Federal Aviation Administration, 800
Independence Ave., SW., Washington, DC 20591.
(3) A petition for reconsideration, if filed within the 30-day
period, suspends the effectiveness of the determination by the NSPM that
the FSTD is no longer qualified unless the NSPM has found, under
paragraph (c) of this section, that an emergency exists requiring
immediate action with respect to safety in air commerce.
(c) If the NSPM find that an emergency exists requiring immediate
action with respect to safety in air commerce that makes the procedures
set out in this section impracticable or contrary to the public
interest:
(1) The NSPM withdraws qualification of some or all of the FSTD and
makes the withdrawal of qualification effective on the day the sponsor
receives notice of it.
(2) In the notice to the sponsor, the NSPM articulates the reasons
for its finding that an emergency exists requiring immediate action with
respect to safety in air transportation or air commerce or that makes it
impracticable or contrary to the public interest to stay the
effectiveness of the finding.
(d) FSTD qualification lost under paragraph (a) or (c) of this
section may be restored when either of the following provisions are met:
(1) The FSTD successfully passes an evaluation for initial
qualification, in accordance with Sec. Sec. 60.15 and 60.17(c) in those
circumstances where the NSPM has determined that a full evaluation for
initial qualification is necessary; or
(2) The FSTD successfully passes an evaluation for those elements of
an initial qualification evaluation, in accordance with Sec. Sec. 60.15
and 60.17(c), as determined to be necessary by the NSPM.
(e) In making the determinations described in paragraph (d) of this
section, the NSPM considers factors including the reason for the loss of
qualification, any repairs or replacements that may have to have been
completed, the number of continuing qualification evaluations missed,
the number of sponsor-conducted quarterly inspections missed, and the
care that had been taken of the device since the loss of qualification.
Sec. 60.31 Recordkeeping and reporting.
(a) The FSTD sponsor must maintain the following records for each
FSTD it sponsors:
(1) The MQTG and each amendment thereto.
(2) A record of all FSTD modifications affected under Sec. 60.23
since the issuance of the original Statement of Qualification.
(3) A copy of all of the following:
(i) Results of the qualification evaluations (initial and each
upgrade) since the issuance of the original Statement of Qualification.
(ii) Results of the objective tests conducted in accordance with
Sec. 60.19(a) for a period of 2 years.
(iii) Results of the previous three continuing qualification
evaluations, or the continuing qualification evaluations from the
previous 2 years, whichever covers a longer period.
(iv) Comments obtained in accordance with Sec. 60.9(b) for a period
of at least 90 days.
(4) A record of all discrepancies entered in the discrepancy log
over the previous 2 years, including the following:
(i) A list of the components or equipment that were or are missing,
malfunctioning, or inoperative.
(ii) The action taken to correct the discrepancy.
(iii) The date the corrective action was taken.
(iv) The identity of the person determining that the discrepancy has
been corrected.
(b) The records specified in this section must be maintained in
plain language form or in coded form if the coded form provides for the
preservation and retrieval of information in a manner acceptable to the
NSPM.
Sec. 60.33 Applications, logbooks, reports, and records: Fraud,
falsification, or incorrect statements.
(a) No person may make, or cause to be made, any of the following:
(1) A fraudulent or intentionally false statement in any application
or any
[[Page 16]]
amendment thereto, or any other report or test result required by this
part.
(2) A fraudulent or intentionally false statement in or a known
omission from any record or report that is kept, made, or used to show
compliance with this part, or to exercise any privileges under this
chapter.
(3) Any reproduction or alteration, for fraudulent purpose, of any
report, record, or test result required under this part.
(b) The commission by any person of any act prohibited under
paragraph (a) of this section is a basis for any one or any combination
of the following:
(1) A civil penalty.
(2) Suspension or revocation of any certificate held by that person
that was issued under this chapter.
(3) The removal of FSTD qualification and approval for use in a
training program.
(c) The following may serve as a basis for removal of qualification
of an FSTD including the withdrawal of approval for use of an FSTD; or
denying an application for a qualification:
(1) An incorrect statement, upon which the FAA relied or could have
relied, made in support of an application for a qualification or a
request for approval for use.
(2) An incorrect entry, upon which the FAA relied or could have
relied, made in any logbook, record, or report that is kept, made, or
used to show compliance with any requirement for an FSTD qualification
or an approval for use.
Sec. 60.35 Specific full flight simulator compliance requirements.
(a) No device will be eligible for initial or upgrade qualification
to a FFS at Level C or Level D under this part unless it includes the
equipment and appliances installed and operating to the extent necessary
for the issuance of an airman certificate or rating.
(b) No device will be eligible for initial or upgrade qualification
to a FFS at Level A or Level B under this part unless it includes the
equipment and appliances installed and operating to the extent necessary
for the training, testing, and/or checking that comprise the simulation
portion of the requirements for issuance of an airman certificate or
rating.
Sec. 60.37 FSTD qualification on the basis of a Bilateral Aviation Safety
Agreement (BASA).
(a) The evaluation and qualification of an FSTD by a contracting
State to the Convention on International Civil Aviation for the sponsor
of an FSTD located in that contracting State may be used as the basis
for issuing a U.S. statement of qualification (see applicable QPS,
attachment 4, figure 4) by the NSPM to the sponsor of that FSTD in
accordance with--
(1) A BASA between the United States and the Contracting State that
issued the original qualification; and
(2) A Simulator Implementation Procedure (SIP) established under the
BASA.
(b) The SIP must contain any conditions and limitations on
validation and issuance of such qualification by the U.S.
Sec. Appendix A to Part 60--Qualification Performance Standards for
Airplane Full Flight Simulators
________________________________________________________________________
Begin Information
This appendix establishes the standards for Airplane FFS evaluation
and qualification. The NSPM is responsible for the development,
application, and implementation of the standards contained within this
appendix. The procedures and criteria specified in this appendix will be
used by the NSPM, or a person assigned by the NSPM, when conducting
airplane FFS evaluations.
Table of Contents
1. Introduction.
2. Applicability (Sec. Sec. 60.1 and 60.2).
3. Definitions (Sec. 60.3).
4. Qualification Performance Standards (Sec. 60.4).
5. Quality Management System (Sec. 60.5).
6. Sponsor Qualification Requirements (Sec. 60.7).
7. Additional Responsibilities of the Sponsor (Sec. 60.9).
8. FFS Use (Sec. 60.11).
9. FFS Objective Data Requirements (Sec. 60.13).
10. Special Equipment and Personnel Requirements for Qualification of
the FFS (Sec. 60.14).
11. Initial (and Upgrade) Qualification Requirements (Sec. 60.15).
[[Page 17]]
12. Additional Qualifications for a Currently Qualified FFS (Sec.
60.16).
13. Previously Qualified FFSs (Sec. 60.17).
14. Inspection, Continuing Qualification Evaluation, and Maintenance
Requirements (Sec. 60.19).
15. Logging FFS Discrepancies (Sec. 60.20).
16. Interim Qualification of FFSs for New Airplane Types or Models
(Sec. 60.21).
17. Modifications to FFSs (Sec. 60.23).
18. Operations With Missing, Malfunctioning, or Inoperative Components
(Sec. 60.25).
19. Automatic Loss of Qualification and Procedures for Restoration of
Qualification (Sec. 60.27).
20. Other Losses of Qualification and Procedures for Restoration of
Qualification (Sec. 60.29).
21. Record Keeping and Reporting (Sec. 60.31).
22. Applications, Logbooks, Reports, and Records: Fraud, Falsification,
or Incorrect Statements (Sec. 60.33).
23. Specific FFS Compliance Requirements (Sec. 60.35).
24. [Reserved]
25. FFS Qualification on the Basis of a Bilateral Aviation Safety
Agreement (BASA) (Sec. 60.37).
Attachment 1 to Appendix A to Part 60--General Simulator Requirements.
Attachment 2 to Appendix A to Part 60--FFS Objective Tests.
Attachment 3 to Appendix A to Part 60--Simulator Subjective Evaluation.
Attachment 4 to Appendix A to Part 60--Sample Documents.
Attachment 5 to Appendix A to Part 60--Simulator Qualification
Requirements for Windshear Training Program Use.
Attachment 6 to Appendix A to Part 60--FSTD Directives Applicable to
Airplane Flight Simulators.
End Information
________________________________________________________________________
1. Introduction
________________________________________________________________________
Begin Information
a. This appendix contains background information as well as
regulatory and informative material as described later in this section.
To assist the reader in determining what areas are required and what
areas are permissive, the text in this appendix is divided into two
sections: ``QPS Requirements'' and ``Information.'' The QPS Requirements
sections contain details regarding compliance with the part 60 rule
language. These details are regulatory, but are found only in this
appendix. The Information sections contain material that is advisory in
nature, and designed to give the user general information about the
regulation.
b. Questions regarding the contents of this publication should be
sent to the U.S. Department of Transportation, Federal Aviation
Administration, Flight Standards Service, National Simulator Program
Staff, AFS-205, 100 Hartsfield Centre Parkway, Suite 400, Atlanta,
Georgia 30354. Telephone contact numbers for the NSP are: Phone, 404-
832-4700; fax, 404-761-8906. The general e-mail address for the NSP
office is: [email protected]. The NSP Internet Web site address
is: http://www.faa.gov/safety/programs--initiatives/aircraft--aviation/
nsp/. On this Web site you will find an NSP personnel list with
telephone and e-mail contact information for each NSP staff member, a
list of qualified flight simulation devices, advisory circulars (ACs), a
description of the qualification process, NSP policy, and an NSP ``In-
Works'' section. Also linked from this site are additional information
sources, handbook bulletins, frequently asked questions, a listing and
text of the Federal Aviation Regulations, Flight Standards Inspector's
handbooks, and other FAA links.
c. The NSPM encourages the use of electronic media for all
communication, including any record, report, request, test, or statement
required by this appendix. The electronic media used must have adequate
security provisions and be acceptable to the NSPM. The NSPM recommends
inquiries on system compatibility, and minimum system requirements are
also included on the NSP Web site.
d. Related Reading References.
(1) 14 CFR part 60.
(2) 14 CFR part 61.
(3) 14 CFR part 63.
(4) 14 CFR part 119.
(5) 14 CFR part 121.
(6) 14 CFR part 125.
(7) 14 CFR part 135.
(8) 14 CFR part 141.
(9) 14 CFR part 142.
(10) AC 120-28, as amended, Criteria for Approval of Category III
Landing Weather Minima.
(11) AC 120-29, as amended, Criteria for Approving Category I and
Category II Landing Minima for part 121 operators.
(12) AC 120-35, as amended, Line Operational Simulations: Line-
Oriented Flight Training, Special Purpose Operational Training, Line
Operational Evaluation.
(13) AC 120-40, as amended, Airplane Simulator Qualification.
(14) AC 120-41, as amended, Criteria for Operational Approval of
Airborne Wind Shear Alerting and Flight Guidance Systems.
(15) AC 120-57, as amended, Surface Movement Guidance and Control
System (SMGCS).
(16) AC 150/5300-13, as amended, Airport Design.
[[Page 18]]
(17) AC 150/5340-1, as amended, Standards for Airport Markings.
(18) AC 150/5340-4, as amended, Installation Details for Runway
Centerline Touchdown Zone Lighting Systems.
(19) AC 150/5340-19, as amended, Taxiway Centerline Lighting System.
(20) AC 150/5340-24, as amended, Runway and Taxiway Edge Lighting
System.
(21) AC 150/5345-28, as amended, Precision Approach Path Indicator
(PAPI) Systems.
(22) International Air Transport Association document, ``Flight
Simulator Design and Performance Data Requirements,'' as amended.
(23) AC 25-7, as amended, Flight Test Guide for Certification of
Transport Category Airplanes.
(24) AC 23-8, as amended, Flight Test Guide for Certification of
Part 23 Airplanes.
(25) International Civil Aviation Organization (ICAO) Manual of
Criteria for the Qualification of Flight Simulators, as amended.
(26) Airplane Flight Simulator Evaluation Handbook, Volume I, as
amended and Volume II, as amended, The Royal Aeronautical Society,
London, UK.
(27) FAA Publication FAA-S-8081 series (Practical Test Standards for
Airline Transport Pilot Certificate, Type Ratings, Commercial Pilot, and
Instrument Ratings).
(28) The FAA Aeronautical Information Manual (AIM). An electronic
version of the AIM is on the Internet at http://www.faa.gov/atpubs.
(29) Aeronautical Radio, Inc. (ARINC) document number 436, titled
Guidelines For Electronic Qualification Test Guide (as amended).
(30) Aeronautical Radio, Inc. (ARINC) document 610, Guidance for
Design and Integration of Aircraft Avionics Equipment in Simulators (as
amended).
End Information
________________________________________________________________________
2. Applicability (Sec. Sec. 60.1 and 60.2)
________________________________________________________________________
Begin Information
No additional regulatory or informational material applies to Sec.
60.1, Applicability, or to Sec. 60.2, Applicability of sponsor rules to
persons who are not sponsors and who are engaged in certain unauthorized
activities.
End Information
________________________________________________________________________
3. Definitions (Sec. 60.3)
________________________________________________________________________
Begin Information
See Appendix F of this part for a list of definitions and
abbreviations from part 1 and part 60, including the appropriate
appendices of part 60.
End Information
________________________________________________________________________
4. Qualification Performance Standards (Sec. 60.4)
________________________________________________________________________
Begin Information
No additional regulatory or informational material applies to Sec.
60.4, Qualification Performance Standards.
End Information
________________________________________________________________________
5. Quality Management System (Sec. 60.5)
________________________________________________________________________
Begin Information
See Appendix E of this part for additional regulatory and
informational material regarding Quality Management Systems.
End Information
________________________________________________________________________
6. Sponsor Qualification Requirements (Sec. 60.7)
________________________________________________________________________
Begin Information
a. The intent of the language in Sec. 60.7(b) is to have a specific
FFS, identified by the sponsor, used at least once in an FAA-approved
flight training program for the airplane simulated during the 12-month
period described. The identification of the specific FFS may change from
one 12-month period to the next 12-month period as long as the sponsor
sponsors and uses at least one FFS at least once during the prescribed
period. No minimum number of hours or minimum FFS periods are required.
b. The following examples describe acceptable operational practices:
(1) Example One.
(a) A sponsor is sponsoring a single, specific FFS for its own use,
in its own facility or elsewhere--this single FFS forms the basis for
the sponsorship. The sponsor uses that FFS at least once in each 12-
month period in the sponsor's FAA-approved flight training program for
the airplane simulated. This 12-month period is established according to
the following schedule:
(i) If the FFS was qualified prior to May 30, 2008, the 12-month
period begins on the date of the first continuing qualification
evaluation conducted in accordance with Sec. 60.19 after May 30, 2008,
and continues for each subsequent 12-month period;
[[Page 19]]
(ii) A device qualified on or after May 30, 2008, will be required
to undergo an initial or upgrade evaluation in accordance with Sec.
60.15. Once the initial or upgrade evaluation is complete, the first
continuing qualification evaluation will be conducted within 6 months.
The 12-month continuing qualification evaluation cycle begins on that
date and continues for each subsequent 12-month period.
(b) There is no minimum number of hours of FFS use required.
(c) The identification of the specific FFS may change from one 12-
month period to the next 12-month period as long as the sponsor sponsors
and uses at least one FFS at least once during the prescribed period.
(2) Example Two.
(a) A sponsor sponsors an additional number of FFSs, in its facility
or elsewhere. Each additionally sponsored FFS must be--
(i) Used by the sponsor in the sponsor's FAA-approved flight
training program for the airplane simulated (as described in Sec.
60.7(d)(1));
OR
(ii) Used by another FAA certificate holder in that other
certificate holder's FAA-approved flight training program for the
airplane simulated (as described in Sec. 60.7(d)(1)). This 12-month
period is established in the same manner as in example one;
OR
(iii) Provided a statement each year from a qualified pilot (after
having flown the airplane, not the subject FFS or another FFS, during
the preceding 12-month period), stating that the subject FFS's
performance and handling qualities represent the airplane (as described
in Sec. 60.7(d)(2)). This statement is provided at least once in each
12-month period established in the same manner as in example one.
(b) No minimum number of hours of FFS use is required.
(3) Example Three.
(a) A sponsor in New York (in this example, a Part 142 certificate
holder) establishes ``satellite'' training centers in Chicago and
Moscow.
(b) The satellite function means that the Chicago and Moscow centers
must operate under the New York center's certificate (in accordance with
all of the New York center's practices, procedures, and policies; e.g.,
instructor and/or technician training/checking requirements, record
keeping, QMS program).
(c) All of the FFSs in the Chicago and Moscow centers could be dry-
leased (i.e., the certificate holder does not have and use FAA-approved
flight training programs for the FFSs in the Chicago and Moscow centers)
because--
(i) Each FFS in the Chicago center and each FFS in the Moscow center
is used at least once each 12-month period by another FAA certificate
holder in that other certificate holder's FAA-approved flight training
program for the airplane (as described in Sec. 60.7(d)(1));
OR
(ii) A statement is obtained from a qualified pilot (having flown
the airplane, not the subject FFS or another FFS, during the preceding
12-month period) stating that the performance and handling qualities of
each FFS in the Chicago and Moscow centers represents the airplane (as
described in Sec. 60.7(d)(2)).
End Information
________________________________________________________________________
7. Additional Responsibilities of the Sponsor (Sec. 60.9)
________________________________________________________________________
Begin Information
The phrase ``as soon as practicable'' in Sec. 60.9(a) means without
unnecessarily disrupting or delaying beyond a reasonable time the
training, evaluation, or experience being conducted in the FFS.
End Information
________________________________________________________________________
8. FFS Use (Sec. 60.11)
________________________________________________________________________
Begin Information
No additional regulatory or informational material applies to Sec.
60.11, Simulator Use.
End Information
________________________________________________________________________
9. FFS Objective Data Requirements (Sec. 60.13)
________________________________________________________________________
Begin QPS Requirements
a. Flight test data used to validate FFS performance and handling
qualities must have been gathered in accordance with a flight test
program containing the following:
(1) A flight test plan consisting of:
(a) The maneuvers and procedures required for aircraft certification
and simulation programming and validation.
(b) For each maneuver or procedure--
(i) The procedures and control input the flight test pilot and/or
engineer used.
(ii) The atmospheric and environmental conditions.
(iii) The initial flight conditions.
(iv) The airplane configuration, including weight and center of
gravity.
(v) The data to be gathered.
[[Page 20]]
(vi) All other information necessary to recreate the flight test
conditions in the FFS.
(2) Appropriately qualified flight test personnel.
(3) An understanding of the accuracy of the data to be gathered
using appropriate alternative data sources, procedures, and
instrumentation that is traceable to a recognized standard as described
in Attachment 2, Table A2E of this appendix.
(4) Appropriate and sufficient data acquisition equipment or
system(s), including appropriate data reduction and analysis methods and
techniques, as would be acceptable to the FAA's Aircraft Certification
Service.
b. The data, regardless of source, must be presented as follows:
(1) In a format that supports the FFS validation process.
(2) In a manner that is clearly readable and annotated correctly and
completely.
(3) With resolution sufficient to determine compliance with the
tolerances set forth in Attachment 2, Table A2A of this appendix.
(4) With any necessary instructions or other details provided, such
as yaw damper or throttle position.
(5) Without alteration, adjustments, or bias. Data may be corrected
to address known data calibration errors provided that an explanation of
the methods used to correct the errors appears in the QTG. The corrected
data may be re-scaled, digitized, or otherwise manipulated to fit the
desired presentation.
c. After completion of any additional flight test, a flight test
report must be submitted in support of the validation data. The report
must contain sufficient data and rationale to support qualification of
the FFS at the level requested.
d. As required by Sec. 60.13(f), the sponsor must notify the NSPM
when it becomes aware that an addition to, an amendment to, or a
revision of data that may relate to FFS performance or handling
characteristics is available. The data referred to in this paragraph is
data used to validate the performance, handling qualities, or other
characteristics of the aircraft, including data related to any relevant
changes occurring after the type certificate was issued. The sponsor
must--
(1) Within 10 calendar days, notify the NSPM of the existence of
this data; and
(2) Within 45 calendar days, notify the NSPM of--
(a) The schedule to incorporate this data into the FFS; or
(b) The reason for not incorporating this data into the FFS.
e. In those cases where the objective test results authorize a
``snapshot test'' or a ``series of snapshot tests'' results in lieu of a
time-history result, the sponsor or other data provider must ensure that
a steady state condition exists at the instant of time captured by the
``snapshot.'' The steady state condition must exist from 4 seconds prior
to, through 1 second following, the instant of time captured by the
snapshot.
End QPS Requirements
________________________________________________________________________
Begin Information
f. The FFS sponsor is encouraged to maintain a liaison with the
manufacturer of the aircraft being simulated (or with the holder of the
aircraft type certificate for the aircraft being simulated if the
manufacturer is no longer in business), and, if appropriate, with the
person having supplied the aircraft data package for the FFS in order to
facilitate the notification required by Sec. 60.13(f).
g. It is the intent of the NSPM that for new aircraft entering
service, at a point well in advance of preparation of the Qualification
Test Guide (QTG), the sponsor should submit to the NSPM for approval, a
descriptive document (see Table A2C, Sample Validation Data Roadmap for
Airplanes) containing the plan for acquiring the validation data,
including data sources. This document should clearly identify sources of
data for all required tests, a description of the validity of these data
for a specific engine type and thrust rating configuration, and the
revision levels of all avionics affecting the performance or flying
qualities of the aircraft. Additionally, this document should provide
other information, such as the rationale or explanation for cases where
data or data parameters are missing, instances where engineering
simulation data are used or where flight test methods require further
explanations. It should also provide a brief narrative describing the
cause and effect of any deviation from data requirements. The aircraft
manufacturer may provide this document.
h. There is no requirement for any flight test data supplier to
submit a flight test plan or program prior to gathering flight test
data. However, the NSPM notes that inexperienced data gatherers often
provide data that is irrelevant, improperly marked, or lacking adequate
justification for selection. Other problems include inadequate
information regarding initial conditions or test maneuvers. The NSPM has
been forced to refuse these data submissions as validation data for an
FFS evaluation. It is for this reason that the NSPM recommends that any
data supplier not previously experienced in this area review the data
necessary for programming and for validating the performance of the FFS,
and discuss the flight test plan anticipated for acquiring such data
with the NSPM well in advance of commencing the flight tests.
i. The NSPM will consider, on a case-by-case basis, whether to
approve supplemental
[[Page 21]]
validation data derived from flight data recording systems, such as a
Quick Access Recorder or Flight Data Recorder.
End Information
________________________________________________________________________
10. Special Equipment and Personnel Requirements for Qualification of
the FFSs (Sec. 60.14)
________________________________________________________________________
Begin Information
a. In the event that the NSPM determines that special equipment or
specifically qualified persons will be required to conduct an
evaluation, the NSPM will make every attempt to notify the sponsor at
least one (1) week, but in no case less than 72 hours, in advance of the
evaluation. Examples of special equipment include spot photometers,
flight control measurement devices, and sound analyzers. Examples of
specially qualified personnel include individuals specifically qualified
to install or use any special equipment when its use is required.
b. Examples of a special evaluation include an evaluation conducted
after an FFS is moved, at the request of the TPAA, or as a result of
comments received from users of the FFS that raise questions about the
continued qualification or use of the FFS.
End Information
________________________________________________________________________
11. Initial (and Upgrade) Qualification Requirements (Sec. 60.15)
________________________________________________________________________
Begin QPS Requirements
a. In order to be qualified at a particular qualification level, the
FFS must:
(1) Meet the general requirements listed in Attachment 1 of this
appendix;
(2) Meet the objective testing requirements listed in Attachment 2
of this appendix; and
(3) Satisfactorily accomplish the subjective tests listed in
Attachment 3 of this appendix.
b. The request described in Sec. 60.15(a) must include all of the
following:
(1) A statement that the FFS meets all of the applicable provisions
of this part and all applicable provisions of the QPS.
(2) A confirmation that the sponsor will forward to the NSPM the
statement described in Sec. 60.15(b) in such time as to be received no
later than 5 business days prior to the scheduled evaluation and may be
forwarded to the NSPM via traditional or electronic means.
(3) A QTG, acceptable to the NSPM, that includes all of the
following:
(a) Objective data obtained from traditional aircraft testing or
another approved source.
(b) Correlating objective test results obtained from the performance
of the FFS as prescribed in the appropriate QPS.
(c) The result of FFS subjective tests prescribed in the appropriate
QPS.
(d) A description of the equipment necessary to perform the
evaluation for initial qualification and the continuing qualification
evaluations.
c. The QTG described in paragraph (a)(3) of this section, must
provide the documented proof of compliance with the simulator objective
tests in Attachment 2, Table A2A of this appendix.
d. The QTG is prepared and submitted by the sponsor, or the
sponsor's agent on behalf of the sponsor, to the NSPM for review and
approval, and must include, for each objective test:
(1) Parameters, tolerances, and flight conditions;
(2) Pertinent and complete instructions for the conduct of automatic
and manual tests;
(3) A means of comparing the FFS test results to the objective data;
(4) Any other information as necessary, to assist in the evaluation
of the test results;
(5) Other information appropriate to the qualification level of the
FFS.
e. The QTG described in paragraphs (a)(3) and (b) of this section,
must include the following:
(1) A QTG cover page with sponsor and FAA approval signature blocks
(see Attachment 4, Figure A4C, of this appendix for a sample QTG cover
page).
(2) A continuing qualification evaluation requirements page. This
page will be used by the NSPM to establish and record the frequency with
which continuing qualification evaluations must be conducted and any
subsequent changes that may be determined by the NSPM in accordance with
Sec. 60.19. See Attachment 4, Figure A4G, of this appendix for a sample
Continuing Qualification Evaluation Requirements page.
(3) An FFS information page that provides the information listed in
this paragraph (see Attachment 4, Figure A4B, of this appendix for a
sample FFS information page). For convertible FFSs, the sponsor must
submit a separate page for each configuration of the FFS.
(a) The sponsor's FFS identification number or code.
(b) The airplane model and series being simulated.
(c) The aerodynamic data revision number or reference.
(d) The source of the basic aerodynamic model and the aerodynamic
coefficient data used to modify the basic model.
(e) The engine model(s) and its data revision number or reference.
[[Page 22]]
(f) The flight control data revision number or reference.
(g) The flight management system identification and revision level.
(h) The FFS model and manufacturer.
(i) The date of FFS manufacture.
(j) The FFS computer identification.
(k) The visual system model and manufacturer, including display
type.
(l) The motion system type and manufacturer, including degrees of
freedom.
(4) A Table of Contents.
(5) A log of revisions and a list of effective pages.
(6) A list of all relevant data references.
(7) A glossary of terms and symbols used (including sign conventions
and units).
(8) Statements of Compliance and Capability (SOCs) with certain
requirements.
(9) Recording procedures or equipment required to accomplish the
objective tests.
(10) The following information for each objective test designated in
Attachment 2, Table A2A, of this appendix as applicable to the
qualification level sought:
(a) Name of the test.
(b) Objective of the test.
(c) Initial conditions.
(d) Manual test procedures.
(e) Automatic test procedures (if applicable).
(f) Method for evaluating FFS objective test results.
(g) List of all relevant parameters driven or constrained during the
automatically conducted test(s).
(h) List of all relevant parameters driven or constrained during the
manually conducted test(s).
(i) Tolerances for relevant parameters.
(j) Source of Validation Data (document and page number).
(k) Copy of the Validation Data (if located in a separate binder, a
cross reference for the identification and page number for pertinent
data location must be provided).
(l) Simulator Objective Test Results as obtained by the sponsor.
Each test result must reflect the date completed and must be clearly
labeled as a product of the device being tested.
f. A convertible FFS is addressed as a separate FFS for each model
and series airplane to which it will be converted and for the FAA
qualification level sought. If a sponsor seeks qualification for two or
more models of an airplane type using a convertible FFS, the sponsor
must submit a QTG for each airplane model, or a QTG for the first
airplane model and a supplement to that QTG for each additional airplane
model. The NSPM will conduct evaluations for each airplane model.
g. Form and manner of presentation of objective test results in the
QTG:
(1) The sponsor's FFS test results must be recorded in a manner
acceptable to the NSPM, that allows easy comparison of the FFS test
results to the validation data (e.g., use of a multi-channel recorder,
line printer, cross plotting, overlays, transparencies).
(2) FFS results must be labeled using terminology common to airplane
parameters as opposed to computer software identifications.
(3) Validation data documents included in a QTG may be
photographically reduced only if such reduction will not alter the
graphic scaling or cause difficulties in scale interpretation or
resolution.
(4) Scaling on graphical presentations must provide the resolution
necessary to evaluate the parameters shown in Attachment 2, Table A2A of
this appendix.
(5) Tests involving time histories, data sheets (or transparencies
thereof) and FFS test results must be clearly marked with appropriate
reference points to ensure an accurate comparison between the FFS and
the airplane with respect to time. Time histories recorded via a line
printer are to be clearly identified for cross plotting on the airplane
data. Over-plots must not obscure the reference data.
h. The sponsor may elect to complete the QTG objective and
subjective tests at the manufacturer's facility or at the sponsor's
training facility. If the tests are conducted at the manufacturer's
facility, the sponsor must repeat at least one-third of the tests at the
sponsor's training facility in order to substantiate FFS performance.
The QTG must be clearly annotated to indicate when and where each test
was accomplished. Tests conducted at the manufacturer's facility and at
the sponsor's training facility must be conducted after the FFS is
assembled with systems and sub-systems functional and operating in an
interactive manner. The test results must be submitted to the NSPM.
i. The sponsor must maintain a copy of the MQTG at the FFS location.
j. All FFSs for which the initial qualification is conducted after
May 30, 2014, must have an electronic MQTG (eMQTG) including all
objective data obtained from airplane testing, or another approved
source (reformatted or digitized), together with correlating objective
test results obtained from the performance of the FFS (reformatted or
digitized) as prescribed in this appendix. The eMQTG must also contain
the general FFS performance or demonstration results (reformatted or
digitized) prescribed in this appendix, and a description of the
equipment necessary to perform the initial qualification evaluation and
the continuing qualification evaluations. The eMQTG must include the
original validation data used to validate FFS performance and handling
qualities in either the original digitized format from the data supplier
or an electronic scan of the
[[Page 23]]
original time-history plots that were provided by the data supplier. A
copy of the eMQTG must be provided to the NSPM.
k. All other FFSs not covered in subparagraph ``j'' must have an
electronic copy of the MQTG by May 30, 2014. An electronic copy of the
MQTG must be provided to the NSPM. This may be provided by an electronic
scan presented in a Portable Document File (PDF), or similar format
acceptable to the NSPM.
l. During the initial (or upgrade) qualification evaluation
conducted by the NSPM, the sponsor must also provide a person who is a
user of the device (e.g., a qualified pilot or instructor pilot with
flight time experience in that aircraft) and knowledgeable about the
operation of the aircraft and the operation of the FFS.
End QPS Requirements
________________________________________________________________________
Begin Information
m. Only those FFSs that are sponsored by a certificate holder as
defined in Appendix F of this part will be evaluated by the NSPM.
However, other FFS evaluations may be conducted on a case-by-case basis
as the Administrator deems appropriate, but only in accordance with
applicable agreements.
n. The NSPM will conduct an evaluation for each configuration, and
each FFS must be evaluated as completely as possible. To ensure a
thorough and uniform evaluation, each FFS is subjected to the general
simulator requirements in Attachment 1 of this appendix, the objective
tests listed in Attachment 2 of this appendix, and the subjective tests
listed in Attachment 3 of this appendix. The evaluations described
herein will include, but not necessarily be limited to the following:
(1) Airplane responses, including longitudinal and lateral-
directional control responses (see Attachment 2 of this appendix);
(2) Performance in authorized portions of the simulated airplane's
operating envelope, to include tasks evaluated by the NSPM in the areas
of surface operations, takeoff, climb, cruise, descent, approach, and
landing as well as abnormal and emergency operations (see Attachment 2
of this appendix);
(3) Control checks (see Attachment 1 and Attachment 2 of this
appendix);
(4) Flight deck configuration (see Attachment 1 of this appendix);
(5) Pilot, flight engineer, and instructor station functions checks
(see Attachment 1 and Attachment 3 of this appendix);
(6) Airplane systems and sub-systems (as appropriate) as compared to
the airplane simulated (see Attachment 1 and Attachment 3 of this
appendix);
(7) FFS systems and sub-systems, including force cueing (motion),
visual, and aural (sound) systems, as appropriate (see Attachment 1 and
Attachment 2 of this appendix); and
(8) Certain additional requirements, depending upon the
qualification level sought, including equipment or circumstances that
may become hazardous to the occupants. The sponsor may be subject to
Occupational Safety and Health Administration requirements.
o. The NSPM administers the objective and subjective tests, which
includes an examination of functions. The tests include a qualitative
assessment of the FFS by an NSP pilot. The NSP evaluation team leader
may assign other qualified personnel to assist in accomplishing the
functions examination and/or the objective and subjective tests
performed during an evaluation when required.
(1) Objective tests provide a basis for measuring and evaluating FFS
performance and determining compliance with the requirements of this
part.
(2) Subjective tests provide a basis for:
(a) Evaluating the capability of the FFS to perform over a typical
utilization period;
(b) Determining that the FFS satisfactorily simulates each required
task;
(c) Verifying correct operation of the FFS controls, instruments,
and systems; and
(d) Demonstrating compliance with the requirements of this part.
p. The tolerances for the test parameters listed in Attachment 2 of
this appendix reflect the range of tolerances acceptable to the NSPM for
FFS validation and are not to be confused with design tolerances
specified for FFS manufacture. In making decisions regarding tests and
test results, the NSPM relies on the use of operational and engineering
judgment in the application of data (including consideration of the way
in which the flight test was flown and the way the data was gathered and
applied), data presentations, and the applicable tolerances for each
test.
q. In addition to the scheduled continuing qualification evaluation,
each FFS is subject to evaluations conducted by the NSPM at any time
without prior notification to the sponsor. Such evaluations would be
accomplished in a normal manner (i.e., requiring exclusive use of the
FFS for the conduct of objective and subjective tests and an examination
of functions) if the FFS is not being used for flight crewmember
training, testing, or checking. However, if the FFS were being used, the
evaluation would be conducted in a non-exclusive manner. This non-
exclusive evaluation will be conducted by the FFS evaluator accompanying
the check airman, instructor, Aircrew Program Designee (APD), or FAA
inspector aboard the FFS along with the student(s) and observing the
operation of the FFS during the training, testing, or checking
activities.
[[Page 24]]
r. Problems with objective test results are handled as follows:
(1) If a problem with an objective test result is detected by the
NSP evaluation team during an evaluation, the test may be repeated or
the QTG may be amended.
(2) If it is determined that the results of an objective test do not
support the level requested but do support a lower level, the NSPM may
qualify the FFS at that lower level. For example, if a Level D
evaluation is requested and the FFS fails to meet sound test tolerances,
it could be qualified at Level C.
s. After an FFS is successfully evaluated, the NSPM issues a
Statement of Qualification (SOQ) to the sponsor. The NSPM recommends the
FFS to the TPAA, who will approve the FFS for use in a flight training
program. The SOQ will be issued at the satisfactory conclusion of the
initial or continuing qualification evaluation and will list the tasks
for which the FFS is qualified, referencing the tasks described in Table
A1B in Attachment 1 of this appendix. However, it is the sponsor's
responsibility to obtain TPAA approval prior to using the FFS in an FAA-
approved flight training program.
t. Under normal circumstances, the NSPM establishes a date for the
initial or upgrade evaluation within ten (10) working days after
determining that a complete QTG is acceptable. Unusual circumstances may
warrant establishing an evaluation date before this determination is
made. A sponsor may schedule an evaluation date as early as 6 months in
advance. However, there may be a delay of 45 days or more in
rescheduling and completing the evaluation if the sponsor is unable to
meet the scheduled date. See Attachment 4 of this appendix, Figure A4A,
Sample Request for Initial, Upgrade, or Reinstatement Evaluation.
u. The numbering system used for objective test results in the QTG
should closely follow the numbering system set out in Attachment 2 of
this appendix, FFS Objective Tests, Table A2A.
v. Contact the NSPM or visit the NSPM Web site for additional
information regarding the preferred qualifications of pilots used to
meet the requirements of Sec. 60.15(d).
w. Examples of the exclusions for which the FFS might not have been
subjectively tested by the sponsor or the NSPM and for which
qualification might not be sought or granted, as described in Sec.
60.15(g)(6), include windshear training and circling approaches.
End Information
________________________________________________________________________
12. Additional Qualifications for a Currently Qualified FFS (Sec.
60.16)
________________________________________________________________________
Begin Information
No additional regulatory or informational material applies to Sec.
60.16, Additional Qualifications for a Currently Qualified FFS.
End Information
________________________________________________________________________
13. Previously Qualified FFSs (Sec. 60.17)
________________________________________________________________________
Begin QPS Requirements
a. In instances where a sponsor plans to remove an FFS from active
status for a period of less than two years, the following procedures
apply:
(1) The NSPM must be notified in writing and the notification must
include an estimate of the period that the FFS will be inactive;
(2) Continuing Qualification evaluations will not be scheduled
during the inactive period;
(3) The NSPM will remove the FFS from the list of qualified FSTDs on
a mutually established date not later than the date on which the first
missed continuing qualification evaluation would have been scheduled;
(4) Before the FFS is restored to qualified status, it must be
evaluated by the NSPM. The evaluation content and the time required to
accomplish the evaluation is based on the number of continuing
qualification evaluations and sponsor-conducted quarterly inspections
missed during the period of inactivity.
(5) The sponsor must notify the NSPM of any changes to the original
scheduled time out of service;
b. Simulators qualified prior to May 30, 2008, are not required to
meet the general simulation requirements, the objective test
requirements or the subjective test requirements of attachments 1, 2,
and 3 of this appendix as long as the simulator continues to meet the
test requirements contained in the MQTG developed under the original
qualification basis.
c. After May 30, 2009, each visual scene or airport model beyond the
minimum required for the FFS qualification level that is installed in
and available for use in a qualified FFS must meet the requirements
described in attachment 3 of this appendix.
d. Simulators qualified prior to May 30, 2008, may be updated. If an
evaluation is deemed appropriate or necessary by the NSPM after such an
update, the evaluation will not require an evaluation to standards
beyond those against which the simulator was originally qualified.
End QPS Requirements
________________________________________________________________________
[[Page 25]]
Begin Information
e. Other certificate holders or persons desiring to use an FFS may
contract with FFS sponsors to use FFSs previously qualified at a
particular level for an airplane type and approved for use within an
FAA-approved flight training program. Such FFSs are not required to
undergo an additional qualification process, except as described in
Sec. 60.16.
f. Each FFS user must obtain approval from the appropriate TPAA to
use any FFS in an FAA-approved flight training program.
g. The intent of the requirement listed in Sec. 60.17(b), for each
FFS to have a SOQ within 6 years, is to have the availability of that
statement (including the configuration list and the limitations to
authorizations) to provide a complete picture of the FFS inventory
regulated by the FAA. The issuance of the statement will not require any
additional evaluation or require any adjustment to the evaluation basis
for the FFS.
h. Downgrading of an FFS is a permanent change in qualification
level and will necessitate the issuance of a revised SOQ to reflect the
revised qualification level, as appropriate. If a temporary restriction
is placed on an FFS because of a missing, malfunctioning, or inoperative
component or on-going repairs, the restriction is not a permanent change
in qualification level. Instead, the restriction is temporary and is
removed when the reason for the restriction has been resolved.
i. The NSPM will determine the evaluation criteria for an FFS that
has been removed from active status. The criteria will be based on the
number of continuing qualification evaluations and quarterly inspections
missed during the period of inactivity. For example, if the FFS were out
of service for a 1 year period, it would be necessary to complete the
entire QTG, since all of the quarterly evaluations would have been
missed. The NSPM will also consider how the FFS was stored, whether
parts were removed from the FFS and whether the FFS was disassembled.
j. The FFS will normally be requalified using the FAA-approved MQTG
and the criteria that was in effect prior to its removal from
qualification. However, inactive periods of 2 years or more will require
requalification under the standards in effect and current at the time of
requalification.
End Information
________________________________________________________________________
14. Inspection, Continuing Qualification Evaluation, and Maintenance
Requirements (Sec. 60.19)
________________________________________________________________________
Begin QPS Requirements
a. The sponsor must conduct a minimum of four evenly spaced
inspections throughout the year. The objective test sequence and content
of each inspection must be developed by the sponsor and must be
acceptable to the NSPM.
b. The description of the functional preflight check must be
contained in the sponsor's QMS.
c. Record ``functional preflight'' in the FFS discrepancy log book
or other acceptable location, including any item found to be missing,
malfunctioning, or inoperative.
d. During the continuing qualification evaluation conducted by the
NSPM, the sponsor must also provide a person knowledgeable about the
operation of the aircraft and the operation of the FFS.
e. The NSPM will conduct continuing qualification evaluations every
12 months unless:
(1) The NSPM becomes aware of discrepancies or performance problems
with the device that warrants more frequent evaluations; or
(2) The sponsor implements a QMS that justifies less frequent
evaluations. However, in no case shall the frequency of a continuing
qualification evaluation exceed 36 months.
End QPS Requirements
________________________________________________________________________
Begin Information
f. The sponsor's test sequence and the content of each quarterly
inspection required in Sec. 60.19(a)(1) should include a balance and a
mix from the objective test requirement areas listed as follows:
(1) Performance.
(2) Handling qualities.
(3) Motion system (where appropriate).
(4) Visual system (where appropriate).
(5) Sound system (where appropriate).
(6) Other FFS systems.
g. If the NSP evaluator plans to accomplish specific tests during a
normal continuing qualification evaluation that requires the use of
special equipment or technicians, the sponsor will be notified as far in
advance of the evaluation as practical; but not less than 72 hours.
Examples of such tests include latencies, control dynamics, sounds and
vibrations, motion, and/or some visual system tests.
h. The continuing qualification evaluations, described in Sec.
60.19(b), will normally require 4 hours of FFS time. However,
flexibility is necessary to address abnormal situations or situations
involving aircraft with additional levels of complexity (e.g., computer
controlled aircraft). The sponsor should anticipate that some tests may
require additional time. The continuing qualification evaluations will
consist of the following:
(1) Review of the results of the quarterly inspections conducted by
the sponsor since
[[Page 26]]
the last scheduled continuing qualification evaluation.
(2) A selection of approximately 8 to 15 objective tests from the
MQTG that provide an adequate opportunity to evaluate the performance of
the FFS. The tests chosen will be performed either automatically or
manually and should be able to be conducted within approximately one-
third (\1/3\) of the allotted FFS time.
(3) A subjective evaluation of the FFS to perform a representative
sampling of the tasks set out in attachment 3 of this appendix. This
portion of the evaluation should take approximately two-thirds (\2/3\)
of the allotted FFS time.
(4) An examination of the functions of the FFS may include the
motion system, visual system, sound system, instructor operating
station, and the normal functions and simulated malfunctions of the
airplane systems. This examination is normally accomplished
simultaneously with the subjective evaluation requirements.
End Information
________________________________________________________________________
15. Logging FFS Discrepancies (Sec. 60.20)
Begin Information
No additional regulatory or informational material applies to Sec.
60.20. Logging FFS Discrepancies.
End Information
________________________________________________________________________
16. Interim Qualification of FFSs for New Airplane Types or Models
(Sec. 60.21)
________________________________________________________________________
Begin Information
No additional regulatory or informational material applies to Sec.
60.21, Interim Qualification of FFSs for New Airplane Types or Models.
End Information
________________________________________________________________________
17. Modifications to FFSs (Sec. 60.23)
Begin QPS Requirements
a. The notification described in Sec. 60.23(c)(2) must include a
complete description of the planned modification, with a description of
the operational and engineering effect the proposed modification will
have on the operation of the FFS and the results that are expected with
the modification incorporated.
b. Prior to using the modified FFS:
(1) All the applicable objective tests completed with the
modification incorporated, including any necessary updates to the MQTG
(e.g., accomplishment of FSTD Directives) must be acceptable to the
NSPM; and
(2) The sponsor must provide the NSPM with a statement signed by the
MR that the factors listed in Sec. 60.15(b) are addressed by the
appropriate personnel as described in that section.
End QPS Requirements
________________________________________________________________________
Begin Information
FSTD Directives are considered modifications of an FFS. See
Attachment 4 of this appendix for a sample index of effective FSTD
Directives. See Attachment 6 of this appendix for a list of all
effective FSTD Directives applicable to Airplane FFSs.
End Information
________________________________________________________________________
18. Operation with Missing, Malfunctioning, or Inoperative Components
(Sec. 60.25)
Begin Information
a. The sponsor's responsibility with respect to Sec. 60.25(a) is
satisfied when the sponsor fairly and accurately advises the user of the
current status of an FFS, including any missing, malfunctioning, or
inoperative (MMI) component(s).
b. It is the responsibility of the instructor, check airman, or
representative of the administrator conducting training, testing, or
checking to exercise reasonable and prudent judgment to determine if any
MMI component is necessary for the satisfactory completion of a specific
maneuver, procedure, or task.
c. If the 29th or 30th day of the 30-day period described in Sec.
60.25(b) is on a Saturday, a Sunday, or a holiday, the FAA will extend
the deadline until the next business day.
d. In accordance with the authorization described in Sec. 60.25(b),
the sponsor may develop a discrepancy prioritizing system to accomplish
repairs based on the level of impact on the capability of the FFS.
Repairs having a larger impact on FFS capability to provide the required
training, evaluation, or flight experience will have a higher priority
for repair or replacement.
End Information
________________________________________________________________________
19. Automatic Loss of Qualification and Procedures for Restoration of
Qualification (Sec. 60.27)
________________________________________________________________________
[[Page 27]]
Begin Information
If the sponsor provides a plan for how the FFS will be maintained
during its out-of-service period (e.g., periodic exercise of mechanical,
hydraulic, and electrical systems; routine replacement of hydraulic
fluid; control of the environmental factors in which the FFS is to be
maintained) there is a greater likelihood that the NSPM will be able to
determine the amount of testing required for requalification.
End Information
________________________________________________________________________
20. Other Losses of Qualification and Procedures for Restoration of
Qualification (Sec. 60.29)
________________________________________________________________________
Begin Information
If the sponsor provides a plan for how the FFS will be maintained
during its out-of-service period (e.g., periodic exercise of mechanical,
hydraulic, and electrical systems; routine replacement of hydraulic
fluid; control of the environmental factors in which the FFS is to be
maintained) there is a greater likelihood that the NSPM will be able to
determine the amount of testing required for requalification.
End Information
________________________________________________________________________
21. Recordkeeping and Reporting (Sec. 60.31)
________________________________________________________________________
Begin QPS Requirements
a. FFS modifications can include hardware or software changes. For
FFS modifications involving software programming changes, the record
required by Sec. 60.31(a)(2) must consist of the name of the aircraft
system software, aerodynamic model, or engine model change, the date of
the change, a summary of the change, and the reason for the change.
b. If a coded form for record keeping is used, it must provide for
the preservation and retrieval of information with appropriate security
or controls to prevent the inappropriate alteration of such records
after the fact.
End QPS Requirements
________________________________________________________________________
22. Applications, Logbooks, Reports, and Records: Fraud, Falsification,
or Incorrect Statements (Sec. 60.33)
________________________________________________________________________
Begin Information
No additional regulatory or informational material applies to Sec.
60.33, Applications, Logbooks, Reports, and Records: Fraud,
Falsification, or Incorrect Statements.
23. Specific FFS Compliance Requirements (Sec. 60.35)
No additional regulatory or informational material applies to Sec.
60.35, Specific FFS Compliance Requirements.
24. [Reserved]
25. FFS Qualification on the Basis of a Bilateral Aviation Safety
Agreement (BASA) (Sec. 60.37)
No additional regulatory or informational material applies to Sec.
60.37, FFS Qualification on the Basis of a Bilateral Aviation Safety
Agreement (BASA).
End Information
________________________________________________________________________
Attachment 1 to Appendix A to Part 60--General Simulator Requirements
Begin QPS Requirements
1. Requirements
a. Certain requirements included in this appendix must be supported
with an SOC as defined in Appendix F, which may include objective and
subjective tests. The requirements for SOCs are indicated in the
``General Simulator Requirements'' column in Table A1A of this appendix.
b. Table A1A describes the requirements for the indicated level of
FFS. Many devices include operational systems or functions that exceed
the requirements outlined in this section. However, all systems will be
tested and evaluated in accordance with this appendix to ensure proper
operation.
End QPS Requirements
________________________________________________________________________
Begin Information
2. Discussion
a. This attachment describes the general simulator requirements for
qualifying an airplane FFS. The sponsor should also consult the
objective tests in Attachment 2 of this appendix and the examination of
functions and subjective tests listed in Attachment 3 of this appendix
to determine the complete requirements for a specific level simulator.
b. The material contained in this attachment is divided into the
following categories:
(1) General flight deck configuration.
(2) Simulator programming.
[[Page 28]]
(3) Equipment operation.
(4) Equipment and facilities for instructor/evaluator functions.
(5) Motion system.
(6) Visual system.
(7) Sound system.
c. Table A1A provides the standards for the General Simulator
Requirements.
d. Table A1B provides the tasks that the sponsor will examine to
determine whether the FFS satisfactorily meets the requirements for
flight crew training, testing, and experience, and provides the tasks
for which the simulator may be qualified.
e. Table A1C provides the functions that an instructor/check airman
must be able to control in the simulator.
f. It is not required that all of the tasks that appear on the List
of Qualified Tasks (part of the SOQ) be accomplished during the initial
or continuing qualification evaluation.
End Information
________________________________________________________________________
Table A1A--Minimum Simulator Requirements
------------------------------------------------------------------------
QPS requirements Simulator levels Information
------------------------------------------------------------------------
General
Entry No. simulator A B C D Notes
requirements
------------------------------------------------------------------------
1. General Flight deck Configuration.
------------------------------------------------------------------------
1.a........ The simulator X X X X For simulator
must have a purposes, the flight
flight deck deck consists of all
that is a that space forward
replica of the of a cross section
airplane of the flight deck
simulated with at the most extreme
controls, aft setting of the
equipment, pilots' seats,
observable including additional
flight deck required crewmember
indicators, duty stations and
circuit those required
breakers, and bulkheads aft of the
bulkheads pilot seats. For
properly clarification,
located, bulkheads containing
functionally only items such as
accurate and landing gear pin
replicating the storage
airplane. The compartments, fire
direction of axes and
movement of extinguishers, spare
controls and light bulbs, and
switches must aircraft document
be identical to pouches are not
the airplane. considered essential
Pilot seats and may be omitted.
must allow the
occupant to
achieve the
design ``eye
position''
established for
the airplane
being
simulated.
Equipment for
the operation
of the flight
deck windows
must be
included, but
the actual
windows need
not be
operable.
Additional
equipment such
as fire axes,
extinguishers,
and spare light
bulbs must be
available in
the FFS but may
be relocated to
a suitable
location as
near as
practical to
the original
position. Fire
axes, landing
gear pins, and
any similar
purpose
instruments
need only be
represented in
silhouette.
------------------------------------------------------------------------
1.b........ Those circuit X X X X
breakers that
affect
procedures or
result in
observable
flight deck
indications
must be
properly
located and
functionally
accurate.
------------------------------------------------------------------------
2. Programming.
------------------------------------------------------------------------
2.a........ A flight X X X X
dynamics model
that accounts
for various
combinations of
drag and thrust
normally
encountered in
flight must
correspond to
actual flight
conditions,
including the
effect of
change in
airplane
attitude,
thrust, drag,
altitude,
temperature,
gross weight,
moments of
inertia, center
of gravity
location, and
configuration.
An SOC is
required.
------------------------------------------------------------------------
2.b........ The simulator X X X X
must have the
computer
capacity,
accuracy,
resolution, and
dynamic
response needed
to meet the
qualification
level sought.
An SOC is
required..
------------------------------------------------------------------------
[[Page 29]]
2.c........ Surface X
operations must
be represented
to the extent
that allows
turns within
the confines of
the runway and
adequate
controls on the
landing and
roll-out from a
crosswind
approach to a
landing.
------------------------------------------------------------------------
2.d........ Ground handling
and aerodynamic
programming
must include
the following:
------------------------------------------------------------------------
2.d.1...... Ground effect... X X X Ground effect
includes modeling
that accounts for
roundout, flare,
touchdown, lift,
drag, pitching
moment, trim, and
power while in
ground effect.
------------------------------------------------------------------------
2.d.2...... Ground reaction. X X X Ground reaction
includes modeling
that accounts for
strut deflections,
tire friction, and
side forces. This is
the reaction of the
airplane upon
contact with the
runway during
landing, and may
differ with changes
in factors such as
gross weight,
airspeed, or rate of
descent on
touchdown.
------------------------------------------------------------------------
2.d.3...... Ground handling X X X
characteristics
, including
aerodynamic and
ground reaction
modeling
including
steering
inputs,
operations with
crosswind,
braking, thrust
reversing,
deceleration,
and turning
radius.
------------------------------------------------------------------------
2.e........ If the aircraft X X If desired, Level A
being simulated and B simulators may
is one of the qualify for
aircraft listed windshear training
in Sec. by meeting these
121.358, Low- standards; see
altitude Attachment 5 of this
windshear appendix. Windshear
system models may consist
equipment of independent
requirements, variable winds in
the simulator multiple
must employ simultaneous
windshear components. The FAA
models that Windshear Training
provide Aid presents one
training for acceptable means of
recognition of compliance with
windshear simulator wind model
phenomena and requirements.
the execution
of recovery
procedures.
Models must be
available to
the instructor/
evaluator for
the following
critical phases
of flight:
(1) Prior to
takeoff
rotation..
(2) At liftoff..
(3) During
initial climb..
(4) On final
approach, below
500 ft AGL..
The QTG must
reference the
FAA Windshear
Training Aid or
present
alternate
airplane
related data,
including the
implementation
method(s) used.
If the
alternate
method is
selected, wind
models from the
Royal Aerospace
Establishment
(RAE), the
Joint Airport
Weather Studies
(JAWS) Project
and other
recognized
sources may be
implemented,
but must be
supported and
properly
referenced in
the QTG. Only
those
simulators
meeting these
requirements
may be used to
satisfy the
training
requirements of
part 121
pertaining to a
certificate
holder's
approved low-
altitude
windshear
flight training
program as
described in
Sec. 121.409.
------------------------------------------------------------------------
[[Page 30]]
2.f........ The simulator X X Automatic
must provide ``flagging'' of out-
for manual and of-tolerance
automatic situations is
testing of encouraged.
simulator
hardware and
software
programming to
determine
compliance with
simulator
objective tests
as prescribed
in Attachment 2
of this
appendix.
An SOC is
required..
------------------------------------------------------------------------
2.g........ Relative The intent is to
responses of verify that the
the motion simulator provides
system, visual instrument, motion,
system, and and visual cues that
flight deck are, within the
instruments, stated time delays,
measured by like the airplane
latency tests responses. For
or transport airplane response,
delay tests. acceleration in the
Motion onset appropriate,
should occur corresponding
before the rotational axis is
start of the preferred.
visual scene
change (the
start of the
scan of the
first video
field
containing
different
information)
but must occur
before the end
of the scan of
that video
field.
Instrument
response may
not occur prior
to motion
onset. Test
results must be
within the
following
limits:
------------------------------------------------------------------------
2.g.1...... 300 milliseconds X X
of the airplane
response.
------------------------------------------------------------------------
2.g.2...... 150 milliseconds X X
of the airplane
response.
------------------------------------------------------------------------
2.h........ The simulator X X
must accurately
reproduce the
following
runway
conditions:
(1) Dry.........
(2) Wet.........
(3) Icy.........
(4) Patchy Wet..
(5) Patchy Icy..
(6) Wet on
Rubber Residue
in Touchdown
Zone.
An SOC is
required.
------------------------------------------------------------------------
2.i........ The simulator X X Simulator pitch, side
must simulate: loading, and
(1) brake and directional control
tire failure characteristics
dynamics, should be
including representative of
antiskid the airplane.
failure.
(2) decreased
brake
efficiency due
to high brake
temperatures,
if applicable.
An SOC is
required..
------------------------------------------------------------------------
2.j........ The simulator X X
must replicate
the effects of
airframe and
engine icing.
------------------------------------------------------------------------
2.k........ The aerodynamic X See Attachment 2 of
modeling in the this appendix,
simulator must paragraph 5, for
include: further information
(1) Low-altitude on ground effect.
level-flight
ground effect;.
(2) Mach effect
at high
altitude;.
(3) Normal and
reverse dynamic
thrust effect
on control
surfaces;.
(4) Aeroelastic
representations
; and
(5)
Nonlinearities
due to
sideslip.
An SOC is
required and
must include
references to
computations of
aeroelastic
representations
and of
nonlinearities
due to
sideslip.
------------------------------------------------------------------------
2.l........ The simulator X X X
must have
aerodynamic and
ground reaction
modeling for
the effects of
reverse thrust
on directional
control, if
applicable.
An SOC is
required..
------------------------------------------------------------------------
[[Page 31]]
3. Equipment Operation.
------------------------------------------------------------------------
3.a........ All relevant X X X X
instrument
indications
involved in the
simulation of
the airplane
must
automatically
respond to
control
movement or
external
disturbances to
the simulated
airplane; e.g.,
turbulence or
windshear.
Numerical
values must be
presented in
the appropriate
units.
------------------------------------------------------------------------
3.b........ Communications, X X X X See Attachment 3 of
navigation, this appendix for
caution, and further information
warning regarding long-range
equipment must navigation
be installed equipment.
and operate
within the
tolerances
applicable for
the airplane.
------------------------------------------------------------------------
3.c........ Simulated X X X X
airplane
systems must
operate as the
airplane
systems operate
under normal,
abnormal, and
emergency
operating
conditions on
the ground and
in flight.
------------------------------------------------------------------------
3.d........ The simulator X X X X
must provide
pilot controls
with control
forces and
control travel
that correspond
to the
simulated
airplane. The
simulator must
also react in
the same manner
as in the
airplane under
the same flight
conditions.
------------------------------------------------------------------------
3.e........ Simulator X X
control feel
dynamics must
replicate the
airplane. This
must be
determined by
comparing a
recording of
the control
feel dynamics
of the
simulator to
airplane
measurements.
For initial and
upgrade
qualification
evaluations,
the control
dynamic
characteristics
must be
measured and
recorded
directly from
the flight deck
controls, and
must be
accomplished in
takeoff,
cruise, and
landing flight
conditions and
configurations.
------------------------------------------------------------------------
4. Instructor or Evaluator Facilities.
------------------------------------------------------------------------
4.a........ In addition to X X X X The NSPM will
the flight consider
crewmember alternatives to this
stations, the standard for
simulator must additional seats
have at least based on unique
two suitable flight deck
seats for the configurations.
instructor/
check airman
and FAA
inspector.
These seats
must provide
adequate vision
to the pilot's
panel and
forward
windows. All
seats other
than flight
crew seats need
not represent
those found in
the airplane,
but must be
adequately
secured to the
floor and
equipped with
similar
positive
restraint
devices.
4.b........ The simulator X X X X
must have
controls that
enable the
instructor/
evaluator to
control all
required system
variables and
insert all
abnormal or
emergency
conditions into
the simulated
airplane
systems as
described in
the sponsor's
FAA-approved
training
program; or as
described in
the relevant
operating
manual as
appropriate.
------------------------------------------------------------------------
[[Page 32]]
4.c........ The simulator X X X X
must have
instructor
controls for
all
environmental
effects
expected to be
available at
the IOS; e.g.,
clouds,
visibility,
icing,
precipitation,
temperature,
storm cells,
and wind speed
and direction.
------------------------------------------------------------------------
4.d........ The simulator X X For example, another
must provide airplane crossing
the instructor the active runway or
or evaluator converging airborne
the ability to traffic.
present ground
and air hazards.
------------------------------------------------------------------------
5. Motion System.
------------------------------------------------------------------------
5.a........ The simulator X X X X For example,
must have touchdown cues
motion (force) should be a function
cues of the rate of
perceptible to descent (RoD) of the
the pilot that simulated airplane.
are
representative
of the motion
in an airplane.
------------------------------------------------------------------------
5.b........ The simulator X X
must have a
motion (force
cueing) system
with a minimum
of three
degrees of
freedom (at
least pitch,
roll, and
heave).
An SOC is
required..
------------------------------------------------------------------------
5.c........ The simulator X X
must have a
motion (force
cueing) system
that produces
cues at least
equivalent to
those of a six-
degrees-of-
freedom,
synergistic
platform motion
system (i.e.,
pitch, roll,
yaw, heave,
sway, and
surge).
An SOC is
required..
------------------------------------------------------------------------
5.d........ The simulator X X X X
must provide
for the
recording of
the motion
system response
time.
An SOC is
required..
------------------------------------------------------------------------
5.e........ The simulator X X X
must provide
motion effects
programming to
include:
------------------------------------------------------------------------
(1) Thrust
effect with
brakes set.
(2) Runway
rumble, oleo
deflections,
effects of
ground speed,
uneven runway,
centerline
lights, and
taxiway
characteristics
.
(3) Buffets on
the ground due
to spoiler/
speedbrake
extension and
thrust
reversal.
(4) Bumps
associated with
the landing
gear.
(5 O='xl')
Buffet during
extension and
retraction of
landing gear..
(6) Buffet in
the air due to
flap and
spoiler/
speedbrake
extension.
(7) Approach-to-
Stall buffet.
(8)
Representative
touchdown cues
for main and
nose gear.
(9) Nosewheel
scuffing, if
applicable.
(10) Mach and
maneuver
buffet.
------------------------------------------------------------------------
5.f........ The simulator X The simulator should
must provide be programmed and
characteristic instrumented in such
motion a manner that the
vibrations that characteristic
result from buffet modes can be
operation of measured and
the airplane if compared to airplane
the vibration data.
marks an event
or airplane
state that can
be sensed in
the flight deck.
------------------------------------------------------------------------
6. Visual System.
------------------------------------------------------------------------
[[Page 33]]
6.a........ The simulator X X X X
must have a
visual system
providing an
out-of-the-
flight deck
view.
------------------------------------------------------------------------
6.b........ The simulator X X Additional field-of-
must provide a view capability may
continuous be added at the
collimated sponsor's discretion
field-of-view provided the minimum
of at least fields of view are
45[deg] retained.
horizontally
and 30[deg]
vertically per
pilot seat or
the number of
degrees
necessary to
meet the visual
ground segment
requirement,
whichever is
greater. Both
pilot seat
visual systems
must be
operable
simultaneously.
The minimum
horizontal
field-of-view
coverage must
be plus and
minus one-half
(\1/2\) of the
minimum
continuous
field-of-view
requirement,
centered on the
zero degree
azimuth line
relative to the
aircraft
fuselage.
An SOC is
required and
must explain
the system
geometry
measurements
including
system
linearity and
field-of-view..
------------------------------------------------------------------------
6.c........ (Reserved)......
------------------------------------------------------------------------
6.d........ The simulator X X The horizontal field-
must provide a of-view is
continuous traditionally
collimated described as a
visual field-of- 180[deg] field-of-
view of at view. However, the
least 176[deg] field-of-view is
horizontally technically no less
and 36[deg] than 176[deg].
vertically or Additional field-of-
the number of view capability may
degrees be added at the
necessary to sponsor's discretion
meet the visual provided the minimum
ground segment fields-of-view are
requirement, retained.
whichever is
greater. The
minimum
horizontal
field-of-view
coverage must
be plus and
minus one-half
(\1/2\) of the
minimum
continuous
field-of-view
requirement,
centered on the
zero degree
azimuth line
relative to the
aircraft
fuselage.
An SOC is
required and
must explain
the system
geometry
measurements
including
system
linearity and
field-of-view..
------------------------------------------------------------------------
6.e........ The visual X X X X Non-realistic cues
system must be might include image
free from ``swimming'' and
optical image ``roll-off,''
discontinuities that may lead a
and artifacts pilot to make
that create non- incorrect
realistic cues. assessments of
speed, acceleration,
or situational
awareness.
------------------------------------------------------------------------
6.f........ The simulator X X X X
must have
operational
landing lights
for night
scenes. Where
used, dusk (or
twilight)
scenes require
operational
landing lights.
------------------------------------------------------------------------
6.g........ The simulator X X X X
must have
instructor
controls for
the following:
(1) Visibility
in statute
miles (km) and
runway visual
range (RVR) in
ft. (m)..
(2) Airport
selection..
(3) Airport
lighting..
------------------------------------------------------------------------
6.h........ The simulator X X X X
must provide
visual system
compatibility
with dynamic
response
programming.
------------------------------------------------------------------------
[[Page 34]]
6.i........ The simulator X X X X This will show the
must show that modeling accuracy of
the segment of RVR, glideslope, and
the ground localizer for a
visible from given weight,
the simulator configuration, and
flight deck is speed within the
the same as airplane's
from the operational envelope
airplane flight for a normal
deck (within approach and
established landing.
tolerances)
when at the
correct
airspeed, in
the landing
configuration,
at the
appropriate
height above
the touchdown
zone, and with
appropriate
visibility.
------------------------------------------------------------------------
6.j........ The simulator X X X
must provide
visual cues
necessary to
assess sink
rates (provide
depth
perception)
during takeoffs
and landings,
to include:
(1) Surface on
runways,
taxiways, and
ramps..
(2) Terrain
features..
------------------------------------------------------------------------
6.k........ The simulator X X X X Visual attitude vs.
must provide simulator attitude
for accurate is a comparison of
portrayal of pitch and roll of
the visual the horizon as
environment displayed in the
relating to the visual scene
simulator compared to the
attitude. display on the
attitude indicator.
------------------------------------------------------------------------
6.l........ The simulator X X
must provide
for quick
confirmation of
visual system
color, RVR,
focus, and
intensity.
An SOC is
required..
------------------------------------------------------------------------
6.m........ The simulator X X
must be capable
of producing at
least 10 levels
of occulting.
------------------------------------------------------------------------
6.n........ Night Visual X X X X
Scenes. When
used in
training,
testing, or
checking
activities, the
simulator must
provide night
visual scenes
with sufficient
scene content
to recognize
the airport,
the terrain,
and major
landmarks
around the
airport. The
scene content
must allow a
pilot to
successfully
accomplish a
visual landing.
Scenes must
include a
definable
horizon and
typical terrain
characteristics
such as fields,
roads and
bodies of water
and surfaces
illuminated by
airplane
landing lights.
------------------------------------------------------------------------
[[Page 35]]
6.o........ Dusk (or X X
Twilight)
Visual Scenes.
When used in
training,
testing, or
checking
activities, the
simulator must
provide dusk
(or twilight)
visual scenes
with sufficient
scene content
to recognize
the airport,
the terrain,
and major
landmarks
around the
airport. The
scene content
must allow a
pilot to
successfully
accomplish a
visual landing.
Dusk (or
twilight)
scenes, as a
minimum, must
provide full
color
presentations
of reduced
ambient
intensity,
sufficient
surfaces with
appropriate
textural cues
that include
self-
illuminated
objects such as
road networks,
ramp lighting
and airport
signage, to
conduct a
visual
approach,
landing and
airport
movement
(taxi). Scenes
must include a
definable
horizon and
typical terrain
characteristics
such as fields,
roads and
bodies of water
and surfaces
illuminated by
airplane
landing lights.
If provided,
directional
horizon
lighting must
have correct
orientation and
be consistent
with surface
shading
effects. Total
night or dusk
(twilight)
scene content
must be
comparable in
detail to that
produced by
10,000 visible
textured
surfaces and
15,000 visible
lights with
sufficient
system capacity
to display 16
simultaneously
moving objects.
An SOC is
required..
------------------------------------------------------------------------
6.p........ Daylight Visual X X
Scenes. The
simulator must
provide
daylight visual
scenes with
sufficient
scene content
to recognize
the airport,
the terrain,
and major
landmarks
around the
airport. The
scene content
must allow a
pilot to
successfully
accomplish a
visual landing.
Any ambient
lighting must
not ``washout''
the displayed
visual scene.
Total daylight
scene content
must be
comparable in
detail to that
produced by
10,000 visible
textured
surfaces and
6,000 visible
lights with
sufficient
system capacity
to display 16
simultaneously
moving objects.
The visual
display must be
free of
apparent and
distracting
quantization
and other
distracting
visual effects
while the
simulator is in
motion.
An SOC is
required..
------------------------------------------------------------------------
6.q........ The simulator X X For example: short
must provide runways, landing
operational approaches over
visual scenes water, uphill or
that portray downhill runways,
physical rising terrain on
relationships the approach path,
known to cause unique topographic
landing features.
illusions to
pilots.
------------------------------------------------------------------------
[[Page 36]]
6.r........ The simulator X X
must provide
special weather
representations
of light,
medium, and
heavy
precipitation
near a
thunderstorm on
takeoff and
during approach
and landing.
Representations
need only be
presented at
and below an
altitude of
2,000 ft. (610
m) above the
airport surface
and within 10
miles (16 km)
of the airport.
------------------------------------------------------------------------
6.s........ The simulator X X
must present
visual scenes
of wet and snow-
covered
runways,
including
runway lighting
reflections for
wet conditions,
partially
obscured lights
for snow
conditions, or
suitable
alternative
effects.
------------------------------------------------------------------------
6.t........ The simulator X X
must present
realistic color
and
directionality
of all airport
lighting.
------------------------------------------------------------------------
7. Sound System.
------------------------------------------------------------------------
7.a........ The simulator X X X X
must provide
flight deck
sounds that
result from
pilot actions
that correspond
to those that
occur in the
airplane.
------------------------------------------------------------------------
7.b........ The volume X X X X
control must
have an
indication of
sound level
setting which
meets all
qualification
requirements..
------------------------------------------------------------------------
7.c........ The simulator X X
must accurately
simulate the
sound of
precipitation,
windshield
wipers, and
other
significant
airplane noises
perceptible to
the pilot
during normal
and abnormal
operations, and
include the
sound of a
crash (when the
simulator is
landed in an
unusual
attitude or in
excess of the
structural gear
limitations);
normal engine
and thrust
reversal
sounds; and the
sounds of flap,
gear, and
spoiler
extension and
retraction.
An SOC is
required..
------------------------------------------------------------------------
7.d........ The simulator X
must provide
realistic
amplitude and
frequency of
flight deck
noises and
sounds.
Simulator
performance
must be
recorded,
compared to
amplitude and
frequency of
the same sounds
recorded in the
airplane, and
be made a part
of the QTG.
------------------------------------------------------------------------
Table A1B--Table of Tasks vs. Simulator Level
------------------------------------------------------------------------
QPS requirements Information
------------------------------------------------------------------------
Subjective Simulator levels
requirements In --------------------
order to be qualified
at the simulator
qualification level
indicated, the
Entry No. simulator must be Notes
able to perform at A B C D
least the tasks
associated with that
level of
qualification.
------------------------------------------------------------------------
1. Preflight Procedures
------------------------------------------------------------------------
1.a........ Preflight Inspection X X X X
(flight deck only).
------------------------------------------------------------------------
1.b........ Engine Start......... X X X X
------------------------------------------------------------------------
[[Page 37]]
1.c........ Taxiing.............. R X X
------------------------------------------------------------------------
1.d........ Pre-takeoff Checks... X X X X
------------------------------------------------------------------------
2. Takeoff and Departure Phase
------------------------------------------------------------------------
2.a........ Normal and Crosswind R X X
Takeoff
------------------------------------------------------------------------
2.b........ Instrument Takeoff... X X X X
------------------------------------------------------------------------
2.c........ Engine Failure During A X X X
Takeoff.
------------------------------------------------------------------------
2.d........ Rejected Takeoff..... X X X X
------------------------------------------------------------------------
2.e........ Departure Procedure.. X X X X
------------------------------------------------------------------------
3. Inflight Maneuvers
------------------------------------------------------------------------
3.a........ Steep Turns.......... X X X X
------------------------------------------------------------------------
3.b........ Approaches to Stalls. X X X X
------------------------------------------------------------------------
3.c........ Engine Failure-- X X X X
Multiengine Airplane.
------------------------------------------------------------------------
3.d........ Engine Failure-- X X X X
Single-Engine
Airplane.
------------------------------------------------------------------------
3.e........ Specific Flight A A A A
Characteristics
incorporated into
the user's FAA
approved flight
training program.
------------------------------------------------------------------------
3.f........ Recovery From Unusual X X X X Within the
Attitudes. normal flight
envelope
supported by
applicable
simulation
validation
data.
------------------------------------------------------------------------
4. Instrument Procedures
------------------------------------------------------------------------
4.a........ Standard Terminal X X X X
Arrival/Flight
Management System
Arrivals Procedures.
------------------------------------------------------------------------
4.b........ Holding.............. X X X X
------------------------------------------------------------------------
4.c........ Precision Instrument.
------------------------------------------------------------------------
4.c.1...... All Engines Operating X X X X e.g., Autopilot,
Manual (Flt.
Dir. Assisted),
Manual (Raw
Data).
------------------------------------------------------------------------
4.c.2...... One Engine X X X X e.g., Manual
Inoperative. (Flt. Dir.
Assisted),
Manual (Raw
Data).
------------------------------------------------------------------------
4.d........ Non-Precision X X X X e.g., NDB, VOR,
Instrument Approach. VOR/DME, VOR/
TAC, RNAV, LOC,
LOC/BC, ADF,
and SDF.
------------------------------------------------------------------------
4.e........ Circling Approach.... X X X X Specific
authorization
required.
------------------------------------------------------------------------
4.f........ Missed Approach......
------------------------------------------------------------------------
4.f.1...... Normal............... X X X X
------------------------------------------------------------------------
4.f.2...... One Engine X X X X
Inoperative.
------------------------------------------------------------------------
5. Landings and Approaches to Landings
------------------------------------------------------------------------
5.a........ Normal and Crosswind R X X
Approaches and
Landings.
------------------------------------------------------------------------
5.b........ Landing From a R X X
Precision/Non-
Precision Approach.
------------------------------------------------------------------------
[[Page 38]]
5.c........ Approach and Landing ... R X X
with (Simulated)
Engine Failure--
Multiengine Airplane.
------------------------------------------------------------------------
5.d........ Landing From Circling R X X
Approach.
------------------------------------------------------------------------
5.e........ Rejected Landing..... X X X X
------------------------------------------------------------------------
5.f........ Landing From a No R X X
Flap or a
Nonstandard Flap
Configuration
Approach.
------------------------------------------------------------------------
6. Normal and Abnormal Procedures
------------------------------------------------------------------------
6.a........ Engine (including X X X X
shutdown and
restart).
------------------------------------------------------------------------
6.b........ Fuel System.......... X X X X
------------------------------------------------------------------------
6.c........ Electrical System.... X X X X
------------------------------------------------------------------------
6.d........ Hydraulic System..... X X X X
------------------------------------------------------------------------
6.e........ Environmental and X X X X
Pressurization
Systems.
------------------------------------------------------------------------
6.f........ Fire Detection and X X X X
Extinguisher Systems.
------------------------------------------------------------------------
6.g........ Navigation and X X X X
Avionics Systems.
------------------------------------------------------------------------
6.h........ Automatic Flight X X X X
Control System,
Electronic Flight
Instrument System,
and Related
Subsystems.
------------------------------------------------------------------------
6.i........ Flight Control X X X X
Systems.
------------------------------------------------------------------------
6.j........ Anti-ice and Deice X X X X
Systems.
------------------------------------------------------------------------
6.k........ Aircraft and Personal X X X X
Emergency Equipment.
------------------------------------------------------------------------
7. Emergency Procedures
------------------------------------------------------------------------
7.a........ Emergency Descent X X X X
(Max. Rate).
------------------------------------------------------------------------
7.b........ Inflight Fire and X X X X
Smoke Removal.
------------------------------------------------------------------------
7.c........ Rapid Decompression.. X X X X
------------------------------------------------------------------------
7.d........ Emergency Evacuation. X X X X
------------------------------------------------------------------------
8. Postflight Procedures
------------------------------------------------------------------------
8.a........ After-Landing X X X X
Procedures.
------------------------------------------------------------------------
8.b........ Parking and Securing. X X X X
------------------------------------------------------------------------
``A''--indicates that the system, task, or procedure may be examined if
the appropriate aircraft system or control is simulated in the FSTD
and is working properly.
``R''--indicates that the simulator may be qualified for this task for
continuing qualification training.
``X''--indicates that the simulator must be able to perform this task
for this level of qualification.
Table A1C--Table of Simulator System Tasks
------------------------------------------------------------------------
QPS requirements Information
------------------------------------------------------------------------
Subjective Simulator levels
requirements In --------------------
order to be qualified
at the simulator
qualification level
indicated, the
Entry No. simulator must be Notes
able to perform at A B C D
least the tasks
associated with that
level of
qualification.
------------------------------------------------------------------------
1. Instructor Operating Station (IOS), as appropriate
------------------------------------------------------------------------
1.a........ Power switch(es)..... X X X X
------------------------------------------------------------------------
[[Page 39]]
1.b........ Airplane conditions.. X X X X e.g., GW, CG,
Fuel loading
and Systems.
------------------------------------------------------------------------
1.c........ Airports/Runways..... X X X X e.g., Selection,
Surface,
Presets,
Lighting
controls.
------------------------------------------------------------------------
1.d........ Environmental X X X X e.g., Clouds,
controls. Visibility,
RVR, Temp,
Wind, Ice,
Snow, Rain, and
Windshear.
------------------------------------------------------------------------
1.e........ Airplane system X X X X
malfunctions
(Insertion/deletion).
------------------------------------------------------------------------
1.f........ Locks, Freezes, and X X X X
Repositioning.
------------------------------------------------------------------------
2. Sound Controls
------------------------------------------------------------------------
2.a........ On/off/adjustment.... X X X X
------------------------------------------------------------------------
3. Motion/Control Loading System
------------------------------------------------------------------------
3.a........ On/off/emergency stop X X X X
------------------------------------------------------------------------
4. Observer Seats/Stations
------------------------------------------------------------------------
4.a........ Position/Adjustment/ X X X X
Positive restraint
system.
------------------------------------------------------------------------
Attachment 2 to Appendix A to Part 60--FFS Objective Tests
Table of Contents
------------------------------------------------------------------------
Paragraph No. Title
------------------------------------------------------------------------
1................................. Introduction.
------------------------------------------------------------------------
2................................. Test Requirements.
------------------------------------------------------------------------
Table A2A, Objective Tests.
------------------------------------------------------------------------
3................................. General.
------------------------------------------------------------------------
4................................. Control Dynamics.
------------------------------------------------------------------------
5................................. Ground Effect.
------------------------------------------------------------------------
6................................. Motion System.
------------------------------------------------------------------------
7................................. Sound System.
------------------------------------------------------------------------
8................................. Additional Information About Flight
Simulator Qualification for New or
Derivative Airplanes.
------------------------------------------------------------------------
9................................. Engineering Simulator--Validation
Data.
------------------------------------------------------------------------
10................................ [Reserved]
------------------------------------------------------------------------
11................................ Validation Test Tolerances.
------------------------------------------------------------------------
12................................ Validation Data Roadmap.
------------------------------------------------------------------------
13................................ Acceptance Guidelines for
Alternative Engines Data.
------------------------------------------------------------------------
14................................ Acceptance Guidelines for
Alternative Avionics (Flight-
Related Computers and Controllers).
------------------------------------------------------------------------
15................................ Transport Delay Testing.
------------------------------------------------------------------------
16................................ Continuing Qualification
Evaluations--Validation Test Data
Presentation.
------------------------------------------------------------------------
17................................ Alternative Data Sources,
Procedures, and Instrumentation:
Level A and Level B Simulators
Only.
------------------------------------------------------------------------
________________________________________________________________________
Begin Information
1. Introduction
a. For the purposes of this attachment, the flight conditions
specified in the Flight Conditions Column of Table A2A of this appendix,
are defined as follows:
(1) Ground--on ground, independent of airplane configuration;
(2) Take-off--gear down with flaps/slats in any certified takeoff
position;
(3) First segment climb--gear down with flaps/slats in any certified
takeoff position (normally not above 50 ft AGL);
(4) Second segment climb--gear up with flaps/slats in any certified
takeoff position (normally between 50 ft and 400 ft AGL);
(5) Clean--flaps/slats retracted and gear up;
[[Page 40]]
(6) Cruise--clean configuration at cruise altitude and airspeed;
(7) Approach--gear up or down with flaps/slats at any normal
approach position as recommended by the airplane manufacturer; and
(8) Landing--gear down with flaps/slats in any certified landing
position.
b. The format for numbering the objective tests in Appendix A,
Attachment 2, Table A2A, and the objective tests in Appendix B,
Attachment 2, Table B2A, is identical. However, each test required for
FFSs is not necessarily required for FTDs. Also, each test required for
FTDs is not necessarily required for FFSs. Therefore, when a test number
(or series of numbers) is not required, the term ``Reserved'' is used in
the table at that location. Following this numbering format provides a
degree of commonality between the two tables and substantially reduces
the potential for confusion when referring to objective test numbers for
either FFSs or FTDs.
c. The reader is encouraged to review the Airplane Flight Simulator
Evaluation Handbook, Volumes I and II, published by the Royal
Aeronautical Society, London, UK, and AC 25-7, as amended, Flight Test
Guide for Certification of Transport Category Airplanes, and AC 23-8, as
amended, Flight Test Guide for Certification of Part 23 Airplanes, for
references and examples regarding flight testing requirements and
techniques.
d. If relevant winds are present in the objective data, the wind
vector should be clearly noted as part of the data presentation,
expressed in conventional terminology, and related to the runway being
used for the test.
End Information
________________________________________________________________________
Begin QPS Requirements
2. Test Requirements
a. The ground and flight tests required for qualification are listed
in Table A2A, FFS Objective Tests. Computer generated simulator test
results must be provided for each test except where an alternative test
is specifically authorized by the NSPM. If a flight condition or
operating condition is required for the test but does not apply to the
airplane being simulated or to the qualification level sought, it may be
disregarded (e.g., an engine out missed approach for a single-engine
airplane or a maneuver using reverse thrust for an airplane without
reverse thrust capability). Each test result is compared against the
validation data described in Sec. 60.13 and in this appendix. Although
use of a driver program designed to automatically accomplish the tests
is encouraged for all simulators and required for Level C and Level D
simulators, it must be possible to conduct each test manually while
recording all appropriate parameters. The results must be produced on an
appropriate recording device acceptable to the NSPM and must include
simulator number, date, time, conditions, tolerances, and appropriate
dependent variables portrayed in comparison to the validation data. Time
histories are required unless otherwise indicated in Table A2A. All
results must be labeled using the tolerances and units given.
b. Table A2A in this attachment sets out the test results required,
including the parameters, tolerances, and flight conditions for
simulator validation. Tolerances are provided for the listed tests
because mathematical modeling and acquisition and development of
reference data are often inexact. All tolerances listed in the following
tables are applied to simulator performance. When two tolerance values
are given for a parameter, the less restrictive may be used unless
otherwise indicated. In those cases where a tolerance is expressed only
as a percentage, the tolerance percentage applies to the maximum value
of that parameter within its normal operating range as measured from the
neutral or zero position unless otherwise indicated.
c. Certain tests included in this attachment must be supported with
an SOC. In Table A2A, requirements for SOCs are indicated in the ``Test
Details'' column.
d. When operational or engineering judgment is used in making
assessments for flight test data applications for simulator validity,
such judgment must not be limited to a single parameter. For example,
data that exhibit rapid variations of the measured parameters may
require interpolations or a ``best fit'' data selection. All relevant
parameters related to a given maneuver or flight condition must be
provided to allow overall interpretation. When it is difficult or
impossible to match simulator to airplane data throughout a time
history, differences must be justified by providing a comparison of
other related variables for the condition being assessed.
e. It is not acceptable to program the FFS so that the mathematical
modeling is correct only at the validation test points. Unless otherwise
noted, simulator tests must represent airplane performance and handling
qualities at operating weights and centers of gravity (CG) typical of
normal operation. If a test is supported by airplane data at one extreme
weight or CG, another test supported by airplane data at mid-conditions
or as close as possible to the other extreme must be included. Certain
tests that are relevant only at one extreme CG or weight condition need
not be repeated at the other extreme. Tests of handling qualities must
include validation of augmentation devices.
f. When comparing the parameters listed to those of the airplane,
sufficient data must also be provided to verify the correct flight
condition and airplane configuration
[[Page 41]]
changes. For example, to show that control force is within the
parameters for a static stability test, data to show the correct
airspeed, power, thrust or torque, airplane configuration, altitude, and
other appropriate datum identification parameters must also be given. If
comparing short period dynamics, normal acceleration may be used to
establish a match to the airplane, but airspeed, altitude, control
input, airplane configuration, and other appropriate data must also be
given. If comparing landing gear change dynamics, pitch, airspeed, and
altitude may be used to establish a match to the airplane, but landing
gear position must also be provided. All airspeed values must be
properly annotated (e.g., indicated versus calibrated). In addition, the
same variables must be used for comparison (e.g., compare inches to
inches rather than inches to centimeters).
g. The QTG provided by the sponsor must clearly describe how the
simulator will be set up and operated for each test. Each simulator
subsystem may be tested independently, but overall integrated testing of
the simulator must be accomplished to assure that the total simulator
system meets the prescribed standards. A manual test procedure with
explicit and detailed steps for completing each test must also be
provided.
h. For previously qualified simulators, the tests and tolerances of
this attachment may be used in subsequent continuing qualification
evaluations for any given test if the sponsor has submitted a proposed
MQTG revision to the NSPM and has received NSPM approval.
i. Simulators are evaluated and qualified with an engine model
simulating the airplane data supplier's flight test engine. For
qualification of alternative engine models (either variations of the
flight test engines or other manufacturer's engines) additional tests
with the alternative engine models may be required. This attachment
contains guidelines for alternative engines.
j. For testing Computer Controlled Aircraft (CCA) simulators, or
other highly augmented airplane simulators, flight test data is required
for the Normal (N) and/or Non-normal (NN) control states, as indicated
in this attachment. Where test results are independent of control state,
Normal or Non-normal control data may be used. All tests in Table A2A
require test results in the Normal control state unless specifically
noted otherwise in the Test Details section following the CCA
designation. The NSPM will determine what tests are appropriate for
airplane simulation data. When making this determination, the NSPM may
require other levels of control state degradation for specific airplane
tests. Where Non-normal control states are required, test data must be
provided for one or more Non-normal control states, and must include the
least augmented state. Where applicable, flight test data must record
Normal and Non-normal states for:
(1) Pilot controller deflections or electronically generated inputs,
including location of input; and
(2) Flight control surface positions unless test results are not
affected by, or are independent of, surface positions.
k. Tests of handling qualities must include validation of
augmentation devices. FFSs for highly augmented airplanes will be
validated both in the unaugmented configuration (or failure state with
the maximum permitted degradation in handling qualities) and the
augmented configuration. Where various levels of handling qualities
result from failure states, validation of the effect of the failure is
necessary. Requirements for testing will be mutually agreed to between
the sponsor and the NSPM on a case-by-case basis.
l. Some tests will not be required for airplanes using airplane
hardware in the simulator flight deck (e.g., ``side stick controller'').
These exceptions are noted in Section 2 ``Handling Qualities'' in Table
A2A of this attachment. However, in these cases, the sponsor must
provide a statement that the airplane hardware meets the appropriate
manufacturer's specifications and the sponsor must have supporting
information to that fact available for NSPM review.
m. For objective test purposes, see Appendix F of this part for the
definitions of ``Near maximum,'' ``Light,'' and ``Medium'' gross weight.
End QPS Requirements
________________________________________________________________________
Begin Information
n. In those cases where the objective test results authorize a
``snapshot test'' or a ``series of snapshot tests'' results in lieu of a
time-history result, the sponsor or other data provider must ensure that
a steady state condition exists at the instant of time captured by the
``snapshot.'' The steady state condition should exist from 4 seconds
prior to, through 1 second following, the instant of time captured by
the snap shot.
o. For references on basic operating weight, see AC 120-27,
``Aircraft Weight and Balance;'' and FAA-H-8083-1, ``Aircraft Weight and
Balance Handbook.''
End Information
[[Page 42]]
________________________________________________________________________
Table A2A--Full Flight Simulator (FFS) Objective Tests
--------------------------------------------------------------------------------------------------------------------------------------------------------
QPS Requirements Information
--------------------------------------------------------------------------------------------------------------------------------------------------------
Test Simulator level
----------------------------------------- Tolerance Flight conditions Test details -------------------- Notes
Entry No. Title A B C D
--------------------------------------------------------------------------------------------------------------------------------------------------------
1. Performance.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.............. Taxi.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.1............ Minimum Radius Turn.. 3 ft (0.9m) or Nose gear turning
20% of airplane turn radius. This test is
radius. to be accomplished
without the use of
brakes and only
minimum thrust,
except for airplanes
requiring asymmetric
thrust or braking to
turn.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.a.2............ Rate of Turn vs. 10% or 2[de than minimum turning
g]/sec. turn rate. radius speed, with a
spread of at least 5
knots groundspeed, in
normal taxi speed
conditions.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.............. Takeoff. All commonly used
takeoff flap settings
are to be
demonstrated at least
once in the tests for
minimum unstick
(1.b.3.), normal
takeoff (1.b.4.),
critical engine
failure on takeoff
(1.b.5.), or
crosswind takeoff
(1.b.6.).
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 43]]
1.b.1............ Ground Acceleration 5% time and time and distance for normal takeoff
distance or 5% the time from brake rejected takeoff
time and 200 Preliminary aircraft data should be
ft (61 m) of certification data shown using
distance. may be used.. appropriate scales
for each portion of
the maneuver.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.2............ Minimum Control Speed- 25% of maximum must be within 1 acceptable
only (per applicable deviation or 5 ft engine failure speed. flight test snap
standard) or (1.5 m). Engine thrust decay engine deceleration
alternative low Additionally, for must be that to idle at a speed
speed engine those simulators of resulting from the between V1 and V1 -
inoperative test to airplanes with mathematical model 10 knots, followed
demonstrate ground reversible flight for the engine by control of
control control systems: variant applicable to heading using
characteristics. Rudder pedal force; the FFS under test. aerodynamic control
10% or 5 lb the airplane with the main gear
(2.2 daN). manufacturer's flight on the ground. To
test engine, a ensure only
further test may be aerodynamic control
run with the same is used, nosewheel
initial conditions steering should be
using the thrust from disabled (i.e.,
the flight test data castored) or the
as the driving nosewheel held
parameter. slightly off the
ground.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 44]]
1.b.3............ Minimum Unstick Speed 3 kts airspeed gear strut the minimum speed
test to demonstrate 1.5[deg] pitch equivalent air/ground main landing gear
takeoff angle. signal. Record from leaves the ground.
characteristics. 10 kt before start of Main landing gear
rotation until at strut compression
least 5 seconds after or equivalent air/
the occurrence of ground signal
main gear lift-off. should be recorded.
If a Vmu test is
not available,
alternative
acceptable flight
tests are a
constant high-
attitude take-off
run through main
gear lift-off or an
early rotation take-
off.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 45]]
1.b.4............ Normal Takeoff....... 3 kts airspeed from brake release to used for ground
1.5[deg] pitch m) above ground level and distance
angle 1.5[deg] airplane has more data should be
angle of attack than one certificated shown using
20 ft (6 m) configurations, a for each portion of
height. different the maneuver.
Additionally, for configuration must be
those simulators of used for each weight.
airplanes with Data are required for
reversible flight a takeoff weight at
control systems: near maximum takeoff
Stick/Column Force; weight with a mid-
10% or 5 lb weight with an aft
(2.2 daN). center of gravity, as
defined in Appendix F
of this part.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.5............ Critical Engine 3 kts airspeed at near maximum
1.5[deg] pitch prior to engine
angle, 1.5[ 200 ft (61 m) AGL.
deg] angle of Engine failure speed
attack, 20 minus3 kts
ft (6 m) height, of airplane data.
3[deg] heading
angle, 2[de
g] bank angle, 2[de
g] sideslip angle.
Additionally, for
those simulators of
airplanes with
reversible flight
control systems:
Stick/Column Force;
10% or 5 lb
(2.2 daN)); Wheel
Force; 10%
or 3 lb (1.3
daN); and Rudder
Pedal Force; 10%
or 5 lb (2.2
daN).
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 46]]
1.b.6............ Crosswind Takeoff.... 3 kts airspeed, from brake release to where a maximum
1.5[deg] pitch m) AGL. Requires test maximum
angle, 1.5[ information on wind crosswind is not
deg] angle of profile for a known, contact the
attack, 20 as direct head-wind
ft (6 m) height, and direct cross-wind
2[deg] bank least 60% of the
angle, 2[de at 33 ft (10 m) above
g] sideslip angle; the runway.
3[deg] heading
angle. Correct trend
at groundspeeds
below 40 kts. for
rudder/pedal and
heading.
Additionally, for
those simulators of
airplanes with
reversible flight
control systems:
10% or 5 lb
(2.2 daN) stick/
column force, 10%
or 3 lb (1.3
daN) wheel force,
10% or 5 lb
(2.2 daN) rudder
pedal force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.b.7............ Rejected Takeoff..... 5% time or 1.5 release to full stop. applicable.
sec 7.5% distance of the reject must be
or 250 ft (76 must be at or near
m). the maximum takeoff
gross weight. Use
maximum braking
effort, auto or
manual.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 47]]
1.b.8............ Dynamic Engine 20% or 2[de minus3 Kts airplane flight
g]/sec body angular of airplane data. test may be
rates. Record Hands Off from performed out of
5 secs. before to at ground effect at a
least 5 secs. after safe altitude, but
engine failure or with correct
30[deg] Bank, airplane
whichever occurs configuration and
first. Engine failure airspeed.
may be a snap
deceleration to idle.
CCA: Test in Normal
and Non-normal
control state.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.............. Climb.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.1............ Normal Climb, all 3 kts airspeed, preferred, however,
5% or 100 acceptable
FPM (0.5 m/Sec.) alternative. Record
climb rate. at nominal climb
speed and mid-initial
climb altitude.
Flight simulator
performance must be
recorded over an
interval of at least
1,000 ft. (300 m).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.2............ One engine 3 kts airspeed, airplanes, in preferred, however,
5% or 100 airplanes, Second acceptable
FPM (0.5 m/Sec.) Segment Climb. alternative. Test at
climb rate, but not weight, altitude, or
less than the climb temperature limiting
gradient conditions. Record at
requirements of 14 nominal climb speed.
CFR part 23 or part Flight simulator
25, as appropriate. performance must be
recorded over an
interval of at least
1,000 ft. (300 m).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.c.3............ One Engine 10% time, 10% m) climb segment.
distance, 10% airplane performance
fuel used. manual data may be
used.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 48]]
1.c.4............ One Engine 3 kts airspeed, maximum gross landing be configured with
Climb (if operations 5% or 100 part. Flight test operating normally,
FPM (0.5 m/Sec.) data or airplane with the gear up
climb rate, but not performance manual and go-around flaps
less than the climb data may be used. set. All icing
gradient Flight simulator accountability
requirements of 14 performance must be considerations
CFR parts 23 or 25 recorded over an should be applied
climb gradient, as interval of at least in accordance with
appropriate. 1,000 ft. (300 m). the aircraft
certification or
authorization for
an approach in
icing conditions.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.............. Cruise/Descent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.1............ Level flight 5% Time. minimum of 50 kts
speed increase using
maximum continuous
thrust rating or
equivalent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.2............ Level flight 5% Time. minimum of 50 kts.
speed decrease using
idle power.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 49]]
1.d.3............ Cruise performance... 0.05 EPR or 5% instantaneous fuel
of N1, or 5% of Torque, 2 consecutive
5% of snapshots with a
fuel flow. spread of at least 3
minutes in steady
flight.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.4............ Idle descent......... 3 kt airspeed, idle power descent at
5% or 200 Flight simulator
ft/min (1.0m/sec) performance must be
descent rate. recorded over an
interval of at least
1,000 ft. (300 m).
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.d.5............ Emergency descent.... 5 kt airspeed, recorded over an descent should be
5% or 300 extended, if
ft/min (1.5m/s) applicable, at mid-
descent rate. altitude and near
Vmo speed or in
accordance with
emergency descent
procedures.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.............. Stopping.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.1............ Stopping time and 5% of time. For distance for at least
manual application distance up to 4000 80% of the total time
of wheel brakes and ft (1220 m): 200 full stop. Data is
a dry runway. ft (61 m) or 10%, at medium and near
whichever is maximum landing
smaller. For weights. Data for
distance greater brake system pressure
than 4000 ft (1220 and position of
m): 5% of (including method of
distance. deployment, if used)
must be provided.
Engineering data may
be used for the
medium gross weight
condition.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 50]]
1.e.2............ Stopping time and 5% time and the distance for at least
reverse thrust and smaller of 10% from initiation of
dry runway. or 200 ft (61 m) minimum operating
of distance. speed with full
reverse thrust. Data
is required for
medium and near
maximum landing gross
weights. Data on the
position of ground
spoilers, (including
method of deployment,
if used) must be
provided. Engineering
data may be used for
the medium gross
weight condition.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.3............ Stopping distance, 10% of distance data or
and no reverse or 200 ft (61 m). performance manual
runway. data must be used
where available.
Engineering data
based on dry runway
flight test stopping
distance modified by
the effects of
contaminated runway
braking coefficients
are an acceptable
alternative.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.e.4............ Stopping distance, 10% of distance manufacturer's
and no reverse or 200 ft (61 m). data must be used,
runway. where available.
Engineering data
based on dry runway
flight test stopping
distance modified by
the effects of
contaminated runway
braking coefficients
are an acceptable
alternative.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.f.............. Engines.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 51]]
1.f.1............ Acceleration......... (10% Tt) and (N1, N2, EPR, Torque) this part for
(10% Ti, from flight idle to definitions of Ti
or 0.25 go-around power for a and Tt.
sec.). rapid (slam) throttle
movement.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1.f.2............ Deceleration......... (10% Tt) and (N1, N2, EPR, Torque) this part for
(10% Ti, from Max T/O power to definitions of Ti
or 0.25 90% decay of Max T/O and Tt.
sec.). power for a rapid
(slam) throttle
movement.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2. Handling Qualities.
--------------------------------------------------------------------------------------------------------------------------------------------------------
For simulators requiring Static or Dynamic tests at the controls (i.e., column, wheel, Contact the NSPM for
rudder pedal), special test fixtures will not be required during initial or upgrade clarification of
evaluations if the sponsor's QTG/MQTG shows both test fixture results and the results of any issue regarding
an alternative approach, such as computer plots produced concurrently, that provide airplanes with
satisfactory agreement. Repeat of the alternative method during the initial or upgrade reversible
evaluation satisfies this test requirement. For initial and upgrade evaluations, the controls.
control dynamic characteristics must be measured at and recorded directly from the flight
deck controls, and must be accomplished in takeoff, cruise, and landing flight conditions
and configurations. Testing of position versus force is not applicable if forces are
generated solely by use of airplane hardware in the FFS.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.............. Static Control Tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.1.a.......... Pitch Controller 2 lb (0.9 daN) uninterrupted control be validated (where
and Surface Position breakout, 10% flight data from
or 5 lb (2.2 longitudinal static
daN) force, 2[de stalls. Static and
g] elevator. dynamic flight
control tests
should be
accomplished at the
same feel or impact
pressures.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.1.b.......... (Reserved)
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 52]]
2.a.2.a.......... Roll Controller 2 lb (0.9 daN) uninterrupted control be validated with
and Surface Position breakout, 10% tests such as
or 3 lb (1.3 or steady state
daN) force, 2[de and dynamic flight
g] aileron, 3[de should be
g] spoiler angle. accomplished at the
same feel or impact
pressures.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.2.b.......... (Reserved)
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.3.a.......... Rudder Pedal Position 5 lb (2.2 daN) uninterrupted control be validated with
Surface Position breakout, 10% tests such as
or 5 lb (2.2 or steady state
daN) force, 2[de and dynamic flight
g] rudder angle. control tests
should be
accomplished at the
same feel or impact
pressures.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.3.b.......... (Reserved)
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 53]]
2.a.4............ Nosewheel Steering 2 lb (0.9 daN) uninterrupted control
Position Calibration. breakout, 10%
or 3 lb (1.3
daN) force, 2[de
g] nosewheel angle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.5............ Rudder Pedal Steering 2[deg] nosewheel uninterrupted control
angle. sweep to the stops.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.6............ Pitch Trim Indicator 0.5[deg] of test is to compare
Calibration. computed trim FFS against design
surface angle. data or equivalent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.7............ Pitch Trim Rate...... 10% trim rate checked using the
([deg]/sec). pilot primary trim
(ground) and using
the autopilot or
pilot primary trim in
flight at go-around
flight conditions.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.8............ Alignment of Flight 5[deg] of recording for all
vs. Selected Engine throttle lever engines. The
Parameter. angle, or 3% against airplane data
N1, or .03 In the case of
EPR, or 3% airplanes, if a
maximum rated propeller lever is
manifold pressure, present, it must also
or 3% torque. airplanes with
For propeller-driven throttle ``detents,''
airplanes where the all detents must be
propeller control presented. May be a
levers do not have series of snapshot
angular travel, a test results.
tolerance of 0.8
inch (2 cm.)
applies.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.a.9............ Brake Pedal Position 5 lb (2.2 daN) or pressure must be results may be used
System Pressure 10% force, 150 position through a
psi (1.0 MPa) or ground static test.
10% brake system
pressure.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.............. Dynamic Control Tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 54]]
Tests 2.b.1., 2.b.2., and 2.b.3. are not applicable if dynamic response is generated solely ... ... ... ...
by use of airplane hardware in the FFS. Power setting is that required for level flight
unless otherwise specified.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 55]]
2.b.1............ Pitch Control........ For underdamped Takeoff, Cruise, and Data must show normal X X ``n'' is the
systems: 10% in both directions. of a full cycle of
of time from 90% of Tolerances apply oscillation. Refer
initial displacement against the absolute to paragraph 4 of
(0.9 Ad) to first values of each period this attachment for
zero crossing and (considered more information.
10 independently). Static and dynamic
(n+1)% of period Normal control flight control
thereafter. 10% amplitude test is 25% to 50% of accomplished at the
of first overshoot full throw or 25% to same feel or impact
applied to all 50% of the maximum pressures.
overshoots greater allowable pitch
than 5% of initial controller deflection
displacement (.05 for flight conditions
Ad). 1 limited by the
overshoot (first maneuvering load
significant envelope.
overshoot must be
matched). For
overdamped systems:
10% of
time from 90% of
initial displacement
(0.9 Ad) to 10% of
initial displacement
(0.1 Ad). For the
alternate method see
paragraph 4 of this
attachment. The slow
sweep is the
equivalent to the
static test 2.a.1.
For the moderate and
rapid sweeps: 2 lb (0.9 daN)
or 10%
dynamic increment
above the static
force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 56]]
2.b.2............ Roll Control......... For underdamped Takeoff, Cruise, and Data must show normal X X ``n'' is the
systems: 10% in both directions. of a full cycle of
of time from 90% of Tolerance applies oscillation. Refer
initial displacement against the absolute to paragraph 4 of
(0.9 Ad) to first values of each period this attachment for
zero crossing, and (considered more information.
10 independently). Static and dynamic
(n+1)% of period Normal control flight control
thereafter. 10% amplitude test is 25% to 50% of accomplished at the
of first overshoot, the maximum allowable same feel or impact
applied to all roll controller pressures.
overshoots greater deflection for flight
than 5% of initial conditions limited by
displacement (.05 the maneuvering load
Ad), 1 envelope.
overshoot (first
significant
overshoot must be
matched). For
overdamped systems:
10% of
time from 90% of
initial displacement
(0.9 Ad) to 10% of
initial displacement
(0.1Ad). For the
alternate method see
paragraph 4 of this
attachment. The slow
sweep is the
equivalent to the
static test 2.a.2.
For the moderate and
rapid sweeps: 2 lb (0.9 daN)
or 10%
dynamic increment
above the static
force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 57]]
2.b.3............ Yaw Control.......... For underdamped Takeoff, Cruise, and Data must show normal X X ``n'' is the
systems: 10% in both directions. of a full cycle of
of time from 90% of Tolerance applies oscillation. Refer
initial displacement against the absolute to paragraph 4 of
(0.9 Ad) to first values of each period this attachment for
zero crossing, and (considered more information.
10 independently). Static and dynamic
(n+1)% of period Normal control flight control
thereafter. 10% amplitude test is 25% to 50% of accomplished at the
of first overshoot the maximum allowable same feel or impact
applied to all yaw controller pressures.
overshoots greater deflection for flight
than 5% of initial conditions limited by
displacement (.05 the maneuvering load
Ad). 1 envelope.
overshoot (first
significant
overshoot must be
matched). For
overdamped systems:
10% of
time from 90% of
initial displacement
(0.9 Ad) to 10% of
initial displacement
(0.1 Ad). For the
alternate method
(see paragraph 4 of
this attachment).
The slow sweep is
the equivalent to
the static test
2.a.3. For the
moderate and rapid
sweeps: 2 lb (0.9 daN)
or 10%
dynamic increment
above the static
force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 58]]
2.b.4............ Small Control Inputs-- 0.15[deg]/sec typical of minor
body pitch rate or corrections made
20% of peak body an ILS approach
pitch rate applied course, using from
throughout the time 0.5[deg]/sec to
history. 2[deg]/sec pitch
rate. The test must
be in both
directions, showing
time history data
from 5 seconds before
until at least 5
seconds after
initiation of control
input.
CCA: Test in normal
and non-normal
control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.b.5............ Small Control Inputs-- 0.15[deg]/sec typical of minor
body roll rate or corrections made
20% of peak body an ILS approach
roll rate applied course, using from
throughout the time 0.5[deg]/sec to
history. 2[deg]/sec roll rate.
The test may be run
in only one
direction; however,
for airplanes that
exhibit non-
symmetrical behavior,
the test must include
both directions. Time
history data must be
recorded from 5
seconds before until
at least 5 seconds
after initiation of
control input.
CCA: Test in normal
and non-normal
control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 59]]
2.b.6............ Small Control Inputs-- 0.15[deg]/sec typical of minor
body yaw rate or corrections made
20% of peak body an ILS approach
yaw rate applied course, using from
throughout the time 0.5[deg]/sec to
history. 2[deg]/sec yaw rate.
The test may be run
in only one
direction; however,
for airplanes that
exhibit non-
symmetrical behavior,
the test must include
both directions. Time
history data must be
recorded from 5
seconds before until
at least 5 seconds
after initiation of
control input.
CCA: Test in normal
and non-normal
control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.............. Longitudinal Control Tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Power setting is that required for level flight unless otherwise specified.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.1............ Power Change Dynamics 3 kt airspeed, the thrust setting
100 ft (30 m) or level flight to
altitude, 20% thrust or go-around
or 1.5[deg] the uncontrolled free
pitch angle. response from at
least 5 seconds
before the power
change is initiated
to 15 seconds after
the power change is
completed.
CCA: Test in normal
and non-normal
control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.2............ Flap/Slat Change 3 kt airspeed, initial flap uncontrolled free
100 ft (30 m) approach to landing. least 5 seconds
altitude, 20% configuration change
or 1.5[deg] seconds after the
pitch angle. configuration change
is completed.
CCA: Test in normal
and non-normal
control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 60]]
2.c.3............ Spoiler/Speedbrake 3 kt airspeed, uncontrolled free
100 ft (30 m) least 5 seconds
altitude, 20% configuration change
or 1.5[deg] seconds after the
pitch angle. configuration change
is completed. Record
results for both
extension and
retraction.
CCA: Test in normal
and non-normal
control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.4............ Gear Change Dynamics. 3 kt airspeed, and Approach history of
100 ft (30 m) response for a time
altitude, 20% least 5 seconds
or 1.5[deg] configuration change
pitch angle. is initiated to 15
seconds after the
configuration change
is completed.
CCA: Test in normal
and non-normal
control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.5............ Longitudinal Trim.... 0.5[deg] trim Landing. condition with wings
surface angle, 1[de for level flight. May
g] elevator, 1[de snapshot tests.
g] pitch angle, CCA: Test in normal or
5% net thrust or states..
equivalent.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 61]]
2.c.6............ Longitudinal 5 lb (2.2 series of snapshot
Force/g). daN) or 10% Record results up to
pitch controller 30[deg] of bank for
force. Alternative approach and landing
method: 1[de Record results for up
g] or 10% change of for the cruise
elevator. configuration. The
force tolerance is
not applicable if
forces are generated
solely by the use of
airplane hardware in
the FFS. The
alternative method
applies to airplanes
that do not exhibit
``stick-force-per-g''
characteristics.
CCA: Test in normal
and non-normal
control states.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.7............ Longitudinal Static 5 lb (2.2 and 2 speeds below
daN) or 10% series of snapshot
pitch controller test results. The
force. Alternative force tolerance is
method: 1[de forces are generated
g] or 10% change of airplane hardware in
elevator. the FFS. The
alternative method
applies to airplanes
that do not exhibit
speed stability
characteristics.
CCA: Test in normal or
non-normal control
states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 62]]
2.c.8............ Stall Characteristics 3 kt airspeed for and Approach or must be entered with
initial buffet, Landing. thrust at or near
stall warning, and idle power and wings
stall speeds. 2[de the stall warning
g] bank for speeds signal and initial
greater than stick buffet, if
shaker or initial applicable. Time
buffet. history data must be
Additionally, for recorded for full
those simulators stall and initiation
with reversible of recovery. The
flight control stall warning signal
systems: 10% proper relation to
or 5 lb (2.2 airplanes exhibiting
daN) Stick/Column a sudden pitch
force (prior to ``g attitude change or
break'' only). ``g break'' must
demonstrate this
characteristic.
CCA: Test in normal
and non-normal
control states..
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.9............ Phugoid Dynamics..... 10% period, 10% the following: Three
of time to \1/2\ or full cycles (six
double amplitude or overshoots after the
.02 of damping or the number of
ratio. cycles sufficient to
determine time to \1/
2\ or double
amplitude.
CCA: Test in Non-
normal control states.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.10........... Short Period 1.5[deg] pitch and Non-normal
angle or 2[de
g]/sec pitch rate,
0.10g
acceleration.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.c.11........... (Reserved)
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.............. Lateral Directional Tests.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 63]]
Power setting is that required for level flight unless otherwise specified.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.1............ Minimum Control 3 kt airspeed. (whichever is most used on the operating Inoperative
Vmcl), per critical in the engine(s). A time Handling may be
Applicable airplane). history or a series governed by a
Airworthiness of snapshot tests may performance or
Standard or Low be used. control limit that
Speed Engine CCA: Test in Normal or prevents
Inoperative Handling Non-normal control demonstration of
Characteristics in state.. Vmca or Vmcl in the
the Air. conventional
manner.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.2............ Roll Response (Rate). 10% or 2[de controller deflection
g]/sec roll rate. (about one-third of
Additionally, for maximum roll
those simulators of controller travel).
airplanes with May be combined with
reversible flight step input of flight
control systems: deck roll controller
10% or 3 lb
(1.3 daN) wheel
force.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.3............ Roll Response to 10% or 2[de seconds after control control input using
Input. g] bank angle. is returned to approximately one-
neutral and released. third of the roll
May be combined with controller travel.
roll response (rate) When reaching
test (2.d.2). approximately
CCA: Test in Normal 20[deg] to 30[deg]
and Non-normal of bank, abruptly
control states. return the roll
controller to
neutral and allow
approximately 10
seconds of airplane
free response.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 64]]
2.d.4............ Spiral Stability..... Correct trend and Cruise, and Approach Record results for X X X X
2[deg] or 10% averaged from
bank angle in 20 multiple tests may be
seconds. Alternate used. As an alternate
test requires test, demonstrate the
correct trend and lateral control
2[deg] aileron. a steady turn with a
bank angle of 28[deg]
to 32[deg].
CCA: Test in Non-
normal control state.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.5............ Engine Inoperative 1[deg] rudder and Approach or snapshot tests. performed in a
angle or 1[de that for which a
g] tab angle or pilot is trained to
equivalent pedal, trim an engine
2[deg] sideslip Second segment
angle. climb test should
be at takeoff
thrust. Approach or
landing test should
be at thrust for
level flight.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.6............ Rudder Response...... 2[deg]/sec or stability
10% yaw rate. ON and OFF. A rudder
step input of 20%-30%
rudder pedal throw is
used.
CCA: Test in Normal
and Non-normal
control states.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 65]]
2.d.7............ Dutch Roll, (Yaw 0.5 sec or 10% cycles with stability
of period, 10% CCA: Test in Non-
of time to \1/2\ or normal control state..
double amplitude or
.02 of damping
ratio. 20%
or 1 sec of time
difference between
peaks of bank and
sideslip.
--------------------------------------------------------------------------------------------------------------------------------------------------------
2.d.8............ Steady State Sideslip For given rudder Approach or Landing.. Use at least two X X X X
position 2[de of which must be near
g] bank angle,