Federal Aviation Administration, DOT

Pt. 60, App. D

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supported by aircraft data at one extreme
weight or CG, another test supported by aircraft 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 indicative of the device-s performance and handling qualities throughout all of the following:
(1) The helicopter weight and CG envelope.
(2) The operational envelope.
(3) Varying atmospheric ambient and environmental conditions - including the extremes authorized for the respective helicopter 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 airspeed, power, thrust or torque, helicopter
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 helicopter, but airspeed, 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 subsystem 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 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. For those performance and static handling qualities tests
where the primary concern is control position in the unaugmented configuration, unaugmented data are not required if the design of the system precludes any affect on
control position. In those instances where
the unaugmented helicopter response is divergent and non-repeatable, it may not be
feasible to meet the specified tolerances. Alternative 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 helicopters 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 appropriate 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 required. The terms  - light, -   - medium, -  and
 - near maximum, -  may not be appropriate
for the simulation of light-class helicopters.
END QPS REQUIREMENTS
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BEGIN INFORMATION
l. In those cases where the objective test
results authorize a  - snapshot test -  or a  - series 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 instant 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 information.
END INFORMATION

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