Federal Aviation Administration, DOT

Pt. 60, App. C

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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 Section0.5 pound (0.22 daN) in 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. 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. Motion System Tests:
(a) The minimum excursions, accelerations, and velocities for pitch, roll, and yaw
must be measurable about a single, common
reference point and must be achieved by
driving one degree of freedom at a time.
(b) The minimum excursions, accelerations, and velocities for heave, sway, and
surge may be measured about different, identifiable reference points and must be
achieved by driving one degree of freedom at
a time.
j. Tests of handling qualities must include
validation of augmentation devices. FFSs 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.
k. Some tests will not be required for helicopters using helicopter hardware in the
simulator flight deck (e.g.,  - helicopter modular controller - ). These exceptions are noted
in Table C2A 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.
l. 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 - , as defined in Appendix F
of this part, may not be appropriate for the
simulation of light-class helicopters.
END QPS REQUIREMENTS
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BEGIN INFORMATION
m. 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.
n. 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

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