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|  MIL-D-19326H
3.7.1 Leakage. The oxygen system, when tested as specified in 4.5.2, shall not
show any evidence of system leaks.
3.7.2 Pressure decay. The oxygen system, when tested as specified in 4.5.3,
shall not exhibit a pressure decay greater than that specified in Table IX.
3.7.3 Functional tests.
3.7.3.1 Panel mounted regulator.
3.7.3.1.1 Flow indicator. The oxygen system, when tested as specified in
4.5.4.1.1, shall permit a free flow of oxygen and the flow indicator of the panel
mounted regulator shall function freely with each breath.
3.7.3.1.2 Emergency switch. The oxygen system, when tested as specified in
4.5.4.1.2, shall permit a free continuous flow of oxygen through the mask.
3.7.3.2 Non-panel mounted regulator. The oxygen system, when tested as
specified in 4.5.4.2, shall permit a flow of oxygen through the mask without any
appreciable resistance to breathing.
3.7.4 Evaporation loss. The oxygen system, when tested as specified in 4.5.5,
shall not have liquid oxygen loss greater than that specified in Table X.
3.7.5 Electrical continuity. The liquid oxygen quantity indicator, when tested
as specified in 4.5.6, shall have capacitance inputs within the limits specified in
Table XI.
3.7.5.1 Low-level warning. The press-to-test button, when tested aS specified
in 4.5.6.1, shall actuate the low-level light when the indicator is within the
lowest 10 percent of the indicator scale and shall remain actuated until the
indicator exceeds 10 percent of full scale indication. When the indicator is
moving upscale, the low-level light may remain actuated past 10 percent but not to
exceed 20 percent of full scale indication.
3.7.6 Flight test. When specified, flight tests on the oxygen systems shall
be conducted to determine the proper functioning of all the oxygen equipment in
the aircraft by actual crew use and functional measurements. In addition, a
determination may be made of the suitability of the arrangement of the items from
the standpoint of accessibility and convenience to all crewmembers during their
flight duties.
3.8 Antiseize tape. Antiseize tape shall be used on all male pipe thread
fittings. Antiseize tape shall conform to and shall be avoided as specified in
MIL-T-27730. Antiseize tape shall not be used on flare tube fitting<, straight
threads, coupling sleeves, or on the outer side of tube flares None of the tape
shall be allowed to enter the inside of a fitting.
* 3.9 System cleanliness. The completed installation shall be cleaned to a
specified level by the removal of contaminants such as oil, grease, fuel, water,
dust, dirt, objectionable odors, or any other foreign matters, both internally and
externally, prior to introducing oxygen in the system. The internal surface of
the system shall not exceed a maximum of non-volatile residue of 3.0 milligrams
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