MIL-PRF-83867D (USAF)
3.6 Construction.
The connector shall be constructed so that no parts will become loose in service. It shall be
built to withstand the strains, jars, vibrations, and any other conditions incident to shipment,
storage, installation, and service.
3.6.1 Screw assemblies.
Assembly screws and bolts shall be tight. Tight shall be defined to mean that the screw or bolt
cannot be appreciably tightened further without damage to the screw, bolt, or screw threads.
3.6.2 Installation of threaded parts.
All threaded parts shall be positively installed by self-locking nuts, or any other approved
methods so that the threaded parts will not work loose in service.
3.6.3 Lubrication.
Lubrication used in any component of the connector that may be exposed to oxygen shall be
approved by the procuring activity (see 6.5).
3.6.4 Cleanliness.
The connectors shall be free of oil, grease, debris, and any other contaminant that creates a
hazard in an oxygen environment.
3.7
Performance.
3.7.1 Disconnection force.
The aircraft supply port of the connector shall disconnect from a jig conforming to MS22058
when a load of 12 to 20 pounds is applied along the longitudinal axis of the aircraft supply port.
3.7.2 Disconnection force reliability.
The disconnection force shall remain in the range specified in 3.7.1 for a minimum of 500
connection-disconnection cycles.
3.7.3 Leakage.
When subjected to an internal pressure of 1 psi, leakage of the connector shall not exceed 0.01
liter per minute (LPM) between -65 and 160 °F.
3.7.4 Pressure drop through connector.
With the valve closed and pressure or suction applied to obtain a flow of 15 LPM from the
regulator to the mask end, the pressure drop through the connector shall be within 4 to 6 inches
of water.
3.7.5 Pressure drop through connector with jig.
With the connector mated to a jig that has internal dimensions of the connector specified in
MS22058, the pressure drop through the assembly shall not exceed the values shown in table I.
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