MIL-H-18325B(Aer)
Standard Parts - Army-Navy standard parts and the applicable numbers thereof shall
3.3.2
be used when available. When AN parts are not available, the specification to be used for
procurement of parts shall be in accordance with the policy outlined in ANA Bulletin No.143.
Threads - Machine- screw threads shall conform to Specification MIL-S-7742. Pips
3.3.3
threads shall conform to Specification MIL-P-7105.
Finish
3.4
3.4.1 Anodized Parts - Aluminum alloy parts shall be anodized in accordance with the
requirements of Specification MIL-A-8625(ASG).
3.4.2 Surface Treatment - Corrosion resisting a11Oy and best resisting alloy parts shall
receive surface treatment in accordance with Specifications MIL-S-5002. All other steel parts
and those copper and nickel alloy parts in contact with aluminum or plated steel parts shall
be cadmium plated in accordance with Specifcation QQ-P-461 or zinc plated in accordance
with Specification QQ-Z-325.
3.4.3 Printed Surfaces - Exposed corrosion and heat resisting steel parts need not be
painted. All other exposed metal surfaces shall be coated with one coat of zinc chromate
primer, Specification MIL-P-8585 finished with one coat of ML-E-5557 enamel.
3.5 Heating - Aircraft heating systems shall be capable of maintaining a temperature of +60°F
in occupied spaces, during flight in atmospheric conditions where the outside air temperature is
-650F or above. At lower outside air temperatures, the heating system shall be capable of
maintaining a temperature rise of 125°F above outside air temperature. At outside air
tempumtures above -55°F the heating and ventilating system shall automatically regulate the air
temperature to 70°F plus or minus 5°F in occupied spaces.
Temperature Variation - In each space to be heated the temperature between any two points
3.5.1
shall not vary more than 10°F.
3.5.2 Insulation - Attention shall be given to the use of thermal insulation in conjunction
with heating equipment in order to prevent excessive heat loss from compartments, and to reduce
the weight of equipment necessary to provide heat for the aircraft. Thermal insulation shall
conform with the requirements of Specification MIL-I-7171(ASG).
Ground Operations - In multi-engine seaplanes, airships and amphibious airplanes the heating
3.5.3
system shall be designed to operate While the aircraft is on the ground or on water where the
engines are not operating.
3.6 Fuel Vapors and Flammable Gases - Concentration of fuel vapors and other flammable gases
in any part of the airplane shall not exceed the following percentages of the lower explosive
limit of the mixture, except that there shall be no conflict with the requirements of Specifica-
tion MIL-G-38591(Aer) for gases contaminated with carbon monoxide
% LEL (Av.)
Location
Any compartment occupied by personnel (Extended
2-1/2
periods)
Any compartment intended for occupancy for periods
up to five minutes in duration
7-1/2
Any part of the airplane
20
Adequate ventilation shall be provided under all possible flight conditions to
3.7 Cooling -
prevent a rise in temperature exceeding 100F above ambient temperature within occupied compartments.
3.7.1 Ground Cooling - When required by the airplane detail specification, a ground cooling
inlet(s) in accordance with Military Standard qP Standard MS16052(Aer) shall be installed on the airplane
fuselage. The inlet(s) shall be located for easy accessibility to ground personnel. Any door
or cover required for the inlet shall automatically close and lock after removal of the ground
cooling air hose coupling, Military standard MS-16051(Aer). On aircraft designed for carrier
deck operation, the cooling air inlet shall be located as near as possible to the lower surface
center line of the fuselage to permit external cooling at either a port or starboard ship's
Catapult station.
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