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|  MIL-H-8891A
Other publications - The following documents form a part
2.2
of this specification to the extent specified herein. Unless otherwise in-
dicated, the issue in effect on date of invitation for bids or request for
proposal shall apply.
Society of Automotive Engineers, Inc., Aerospace Recommended Practices
Nomenclature, Aircraft Hydraulic and Pneumatic Systems
ARP 243
ARP 584
Coiled Tubing
*
Recommended Practice for the Design of Tubing Installa-
ARP 994
tion for Aerospace Fluid Power System
Graphic Symbols for Aircraft Hydraulic and Pneumatic
AS 1290
Systems
*
AIR 1362
Physical Properties of Hydraulic Fluids
(Application for copies should be addressed to the Society of Automotive
*
Engineers, Inc., 400 Commonwealth Drive, Warrendale, Pa. 15096.)
National Aerospace Standards Association, Inc., Standard
Cleanliness Requirements of Parts used in Hydraulic
NAS 1638
Systems
(Application for copies should be addressed to the National Aerospace
Standards Association, Inc., 1321 Fourteenth St., N.W., Washington D.C.
20005. )
DESIGN REQUIREMENTS
3.
Configuration requirements - The hydraulic system and
3.1
*
components thereof shall be designed to operate satisfactorily under all
.
conditions that the vehicle may encounter within the structural limitations
,
of the vehicle, including forces or conditions caused by accelerations de-
celeration, zero gravity (g)~ negative g, or any flight altitudes obtainable
with the vehicle, structural deflection, vibration, or other environmental
conditions. (For Navy use only, see Navy Department publications SD-24,
Volumes I and II.) The hydraulic system(s) shall be configured such that
any two fluid system failures due to combat or other damage which cause loss
of fluid or pressure will not result in complete loss of flight control. For
fixed-wing aircraft, the surviving system(s) shall provide sufficient control
to meet the level 3 flying qualities of MIL-F-8785 for conventional takeoff
and landing and MIL-F-83300 for vertical takeoff and landing. For rotary-
wing aircraft, the surviving system(s) shall provide sufficient control for
return to the intended landing area (including shipboard areas).
Subsystem isolation - Two or more
subsystems pressurized
3.1.1
by a common pressure source, one of which is essential
to flight operation and
the other not essentials shall be so isolated that the
system essential to
flight operation will not be affected by any damage to
the nonessential system.
4
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