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| MIL-D-23222A(AS)
3.10.1
(Cont)
but rather, that the data should be obtained during those demonstra-
tions, if at all possible. Any tests or demonstrations completed
and properly witnessed by a test authority (3.1.2) in accordance
with, but prior to the scheduled demonstration, shall be included in
reports submitted in compliance with 3.19.
3.10.1.1
DEFINITION OF POWER. - The term "power" as
USEd
in this section shall be interpreted as the
paremeter on which engine performance is based as follows:
Power Parameter
Engine
Reciprocating
Brake horsepower
Turbo-Shaft
shaft horsepower plus
thrust or equivalent
shaft horsepower
combination of
Use parameters of each
power plants
applicable engine in-
volved
3.10.1.2
FLIGHT RESTRICTIONS. -
NOne of the following tests
shall be construed to require operation of the
helicopter under structural condition exceeding the structural demon-
St-ration requirements as listed in 3.7.
3.1O.2
Engine POWER (Output TESTS. - These tests are
conduted to determine any power discrepancies and
to provide accurate information on power output for a more accurate
preliminary evaluation of the helicopter.
3.10.2.1
Reciprocating Engines. - The level flight critical
altitude(s) for intermediate power and normal-rated
power (normal only if no intermediate rating assigned) shall be determined.
The altitudes for full throttle, minimum couplinjg slip or closed waste
gate position, as applicable to the particular engine in question,
shall be determined. In the event that the measured performance does
not meet specified values, complete data shall be forwarded to NAVAIR
for Comments. Altitude values shall be based on standard pressure
altitude as defined in NASA Technical Report Number 1235.
3.10.2.2
TURBO-SHAFT. - The equivalent shaft horsepower
developed by the engine in level flight at an
altitude of approximately 5,000 feet shall be determined. This shall
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