Code of Federal Regulations - Title 14

Federal Aviation Administration, DOT

Pt. 60, App. A

changes. For example, to show that control
force is within the parameters for a static
stability test, data to show the correct air-
speed, power, thrust or torque, airplane con-
figuration, altitude, and other appropriate
datum identification parameters must also
be given. If comparing short period dynam-
ics, normal acceleration may be used to es-
tablish a match to the airplane, but airspeed,
altitude, control input, airplane configura-
tion, 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 pro-
vided. 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 simu-
lator subsystem may be tested independ-
ently, but overall integrated testing of the
simulator must be accomplished to assure
that the total simulator system meets the
prescribed standards. A manual test proce-
dure 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 qualifica-
tion evaluations for any given test if the
sponsor has submitted a proposed MQTG re-
vision to the NSPM and has received NSPM
approval.

i. Simulators are evaluated and qualified

with an engine model simulating the air-
plane 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 Air-

craft (CCA) simulators, or other highly aug-
mented 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 inde-
pendent of control state, Normal or Non-nor-
mal control data may be used. All tests in
Table A2A require test results in the Normal
control state unless specifically noted other-
wise in the Test Details section following the
CCA designation. The NSPM will determine
what tests are appropriate for airplane sim-
ulation data. When making this determina-
tion, the NSPM may require other levels of
control state degradation for specific air-
plane tests. Where Non-normal control

states are required, test data must be pro-
vided for one or more Non-normal control
states, and must include the least aug-
mented state. Where applicable, flight test
data must record Normal and Non-normal
states for:

(1) Pilot controller deflections or electroni-

cally generated inputs, including location of
input; and

(2) Flight control surface positions unless

test results are not affected by, or are inde-
pendent 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 lev-
els 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 air-

planes using airplane hardware in the simu-
lator flight deck (e.g., ‘‘side stick con-
troller’’). These exceptions are noted in Sec-
tion 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 spon-
sor must have supporting information to
that fact available for NSPM review.

m. For objective test purposes, see Appen-

dix F of this part for the definitions of ‘‘Near
maximum,’’ ‘‘Light,’’ and ‘‘Medium’’ gross
weight.

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n. In those cases where the objective test

results authorize a ‘‘snapshot test’’ or a ‘‘se-
ries 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 in-
stant 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.’’

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