MIL-DTL-87255A(USAF)
3.2.2.1 Dissimilar metals.
Unless protected against electrolytic corrosion, dissimilar metals as defined in MIL-STD-889
shall not be used in intimate contact with each other.
3.2.3
Nonmetallic materials.
Any nonmetallic material that is adversely affected by continued use with air shall not be used.
3.2.3.1 Elastomer components.
Elastomer components, except silicone, shall be not more than 12 months old from the date of
manufacture to the date of delivery to any government service or to any airframe or accessory
manufacturer.
3.2.4
Protective treatment.
Materials shall be protected from deterioration in a manner that shall in no way prevent
compliance with the performance requirements of this specification. The valve shall resist
corrosion and deterioration due to fuels, salt fog, microorganisms, moisture, hydraulic fluid,
lubricating oils, grease, ozone, or atmospheric conditions likely to be encountered in storage or
normal service. Protective coatings which might crack, chip, or scale during normal service or
storage life or under extremes of environmental conditions shall not be used.
3.3
Standard parts.
Military standard parts shall be used when they suit the purpose. Use of non-standard parts
requires contracting officer approval prior to use.
3.4
Design and construction.
The valve shall be designed to pass air at a regulated pressure to the aircrew member's anti-G
suit and to the sense line of the regulator (if applicable) and shall contain provisions for suit
exhaust. The valve shall include provision for inlet and outlet fittings that incorporate swivel
features. The fittings shall have a diameter and finish compatible with the aircraft inlet hose,
anti-g suit delivery hose, and the outlet pressure sense line (if applicable). The outlet fitting
shall be in accordance with figures 1, 2 or 3, as required. The outlet pressure shall be a
design shall enable manual operation (press-to-test) of the valve and shall provide means to
specified in 3.5. Moisture in the air source to the valve shall not adversely affect operation of
the valve.
3.4.1 Installation.
The valve shall be designed such that it can be properly installed in the applicable aircraft. This
includes proper alignment with the mounting brackets and connections with the inlet and outlet
hoses. The existing control panels shall also be accommodated. There shall be no interference
with aircraft structure. Minimum requirements for installation are given on figures 1, 2, and 3.
Proper installation shall be demonstrated as specified in 4.5.1.1.1. Should there be a conflict
between the installation demonstration specified in this document and figures 1, 2, and 3, the
installation demonstration shall take precedence.
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