155 

Federal Aviation Administration, DOT 

Pt. 60, App. B 

B

EGIN

QPS R

EQUIREMENTS

 

2. T

EST

R

EQUIREMENTS

 

a. The ground and flight tests required for 

qualification are listed in Table B2A Objec-
tive Tests. Computer generated FTD test re-
sults must be provided for each test except 
where an alternate test is specifically au-
thorized 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 air-
plane; a maneuver using reverse thrust for 
an airplane without reverse thrust capa-
bility). Each test result is compared against 
the validation data described in § 60.13, and 
in Appendix B. The results must be produced 
on an appropriate recording device accept-
able to the NSPM and must include FTD 
number, date, time, conditions, tolerances, 
and appropriate dependent variables por-
trayed in comparison to the validation data. 
Time histories are required unless otherwise 
indicated in Table B2A. All results must be 
labeled using the tolerances and units given. 

b. Table B2A in this attachment sets out 

the test results required, including the pa-
rameters, tolerances, and flight conditions 
for FTD validation. Tolerances are provided 
for the listed tests because mathematical 
modeling and acquisition and development of 
reference data are often inexact. All toler-
ances listed in the following tables are ap-
plied to FTD performance. When two toler-
ance 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 attach-

ment must be supported with a SOC. In 
Table B2A, requirements for SOCs are indi-
cated in the ‘‘Test Details’’ column. 

d. When operational or engineering judg-

ment is used in making assessments for 
flight test data applications for FTD valid-
ity, such judgment may not be limited to a 
single parameter. For example, data that ex-
hibit rapid variations of the measured pa-
rameters may require interpolations or a 
‘‘best fit’’ data section. All relevant param-
eters related to a given maneuver or flight 
condition must be provided to allow overall 
interpretation. When it is difficult or impos-
sible to match FTD 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 FTD 

so that the mathematical modeling is cor-
rect only at the validation test points. Un-

less noted otherwise, 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 aircraft data at one extreme 
weight or CG, another test supported by air-
craft data at mid-conditions or as close as 
possible to the other extreme is necessary. 
Certain tests that are relevant only at one 
extreme CG or weight condition need not be 
repeated at the other extreme. The results of 
the tests for Level 6 are expected to be indic-
ative of the device’s performance and han-
dling qualities throughout all of the fol-
lowing: 

(1) The airplane weight and CG envelope; 
(2) The operational envelope; and 
(3) Varying atmospheric ambient and envi-

ronmental conditions—including the ex-
tremes authorized for the respective airplane 
or set of airplanes. 

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 
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 FTD will be set up 
and operated for each test. Each FTD sub-
system may be tested independently, but 
overall integrated testing of the FTD must 
be accomplished to assure that the total 
FTD 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 FTDs, 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. FTDs are evaluated and qualified with an 

engine model simulating the airplane data 
supplier’s flight test engine. For qualifica-
tion of alternative engine models (either 
variations of the flight test engines or other 
manufacturer’s engines) additional tests 

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