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| MIL-D-23222A(AS)
ANTI-ICING. - Demonstrate that the engine-airframe
3.10.7.5
combination operates satisfactorily through all
altitudes and Mach number ranges within the design envelope of the
helicopter, without adverse effect from ice-ingestion. Demonstrate
that the anti-icing system will anti-ice to the design parameters.
AIR STARTS. - Three satisfactory air starts on
3.10.8
one engine shall be demonstrated at the maximum
altitude as set forth in the engine model specification. If starts
cannot be made at this altitude the maximum altitude at which
satisfactory air starts can be made shall be determined. Air starts
shall also be demonstrated with manual (emergency) controls, if
provided.
FUEL DUMPING. - Operation in flight of fuel
3.10.9
dumping arrangements shall be demonstrated in
accordance with MIL-F-17874. Fluids other than fuel may be used.
FUEL VENTING. - The fuel vent system and impinge-
3.10.10
ment tests shall be demonstrated in accordance
with Spec MIL-F-17874 for compliance with the design requirements
of the detail specification. Fuel Tank Venting shall also be demon-
strated for adequacy in accordance with Spec MIL-F-17874. Fluids
other than fuel may be used. Tests shall be demonstrated under the
following conditions:
(1) sideward flight, left and right
(2) Climb
(3) Hover
(4) Rearward flight
(5) Automation
(6) Level flight at V maximum
(7) Ground taxi
FLAME DAMPING. - Satisfactory flare damping shall
3.10.11
be demonstrated in accordance with the procedure
outlined in Spec MIL-D-6728. All phases of flame damping effective-
ness shall be reported with particular emphasis on hazards of night
landing approach and takeoffs both for land and for aircraft carriers.
ROTOR BRAKES. - Rotor brakes shall be demonstra-
3.10.12
ted to show compliance with contract requirements.
FUELING AND DEFUELING. - Fueling and defueling
3.10.13
tests shall be conducted to determine compliance
with the design requirements of the Detail Specification and of Spec
MIL-F-17874.
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