441 

Federal Aviation Administration, DOT 

Pt. 60, App. D 

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 helicopter weight and CG envelope. 
(2) The operational envelope. 
(3) Varying atmospheric ambient and envi-

ronmental conditions—including the ex-
tremes authorized for the respective heli-
copter or set of helicopters. 

f. When comparing the parameters listed to 

those of the helicopter, sufficient data must 
also be provided to verify the correct flight 
condition and helicopter 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, helicopter 
configuration, altitude, and other appro-
priate datum identification parameters must 
also be given. If comparing short period dy-
namics, normal acceleration may be used to 
establish a match to the helicopter, but air-
speed, altitude, control input, helicopter 
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 helicopter, 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 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. Tests of handling qualities must include 

validation of augmentation devices. FTDs 

for highly augmented helicopters will be 
validated both in the unaugmented configu-
ration (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. For those per-
formance and static handling qualities tests 
where the primary concern is control posi-
tion in the unaugmented configuration, un-
augmented data are not required if the de-
sign of the system precludes any affect on 
control position. In those instances where 
the unaugmented helicopter response is di-
vergent and non-repeatable, it may not be 
feasible to meet the specified tolerances. Al-
ternative requirements for testing will be 
mutually agreed upon by the sponsor and the 
NSPM on a case-by-case basis. 

j. Some tests will not be required for heli-

copters using helicopter hardware in the 
FTD flight deck (e.g., ‘‘helicopter modular 
controller’’). These exceptions are noted in 
Section 2 ‘‘Handling Qualities’’ in Table D2A 
of this attachment. However, in these cases, 
the sponsor must provide a statement that 
the helicopter hardware meets the appro-
priate manufacturer’s specifications and the 
sponsor must have supporting information to 
that fact available for NSPM review. 

k. In cases where light-class helicopters 

are being simulated, prior coordination with 
the NSPM on acceptable weight ranges is re-
quired. The terms ‘‘light,’’ ‘‘medium,’’ and 
‘‘near maximum,’’ may not be appropriate 
for the simulation of light-class helicopters. 

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l. In those cases where the objective test 

results authorize a ‘‘snapshot test’’ or a ‘‘se-
ries of snapshot test’’ 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 in-
stant of time captured by the snap shot. 

m. Refer to AC 120–27, Aircraft Weight and 

Balance; and FAA–H–8083–1, Aircraft Weight 
and Balance Handbook, for more informa-
tion. 

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