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|  MIL-D-19326H
3.6.7 Disconnects. The disconnect for the removable converters shall be in
accordance with MS22068-7 and MS22068-8. Where the supply line is required to be
uncoupled for maintenance purposes, the quick disconnect shall be in accordance
with MS22068-1 or MS22068-2.
3.6.8 Hoses. Flexible hoses shall be used for the aircraft system connections
to removable converters and to shock mounted converters where movement relative to
the aircraft will occur. The flow capacity of the hoses used in lieu of aluminum
tubing shall be essentially equivalent to the aluminum tubing size specified for
that connection. The bend radii imposed on the hoses during remove and replace
actions shall be greater than the minimum established by that hose specification.
Hose layouts shall avoid the imposition of torsional forces when being connected
to the converter and also avoid the necessity for a particular rotational
orientation when the flare nut is torqued. Hoses shall be of sufficient length to
provide unstressed connections and be protected against chaffing on surfaces or
objects which may damage the wire covering.
3.6.8.1 Metal hose. This wire braid covered hose shall be in accordance with
MIL-H-22343 and the applicable part number of MS90457. This hose is flexible at
temperatures down to -297F (-183 C) but since it contains a metal bellows, it is
somewhat vulnerable to fatigue failure if subjected to repeated severe flexing.
3.6.8.2 Tetrafluoroethylene hose. This wire braid covered hose shall be in
accordance with MIL-H-266 26 and the applicable part number of MS24548. This hose
is flexible at temperatures down to -65F (-54C); therefore, disconnecting and
manipulating the hose should be delayed until a few minutes after the flow of LOX
has ceased.
3.6.9 Tubing. The tubing shall be of aluminum alloy conforming to AMS 4071,
or corrosion resistant annealed steel (304), conforming to MIL-T-8506. The
minimum outside diameter of tubing used for oxygen supply lines shall be 5/16 inch
(7.94 mm). Tubing for "FILL" and "VENT" lines shall have minimum outside diameter
of 3/8 and 1/2 inch (9.53 and 12.7 mm), respectively. All aluminum tubing shall
have a wall thickness of 0.035 inch (0.889 mm), while corrosion resistant steel
tubing shall conform to AND101O4 and have a wall thickness of 0.020, 0.028 or
0.035 inch (0.508, 0.711 or 0.889 mm) as necessary in the application. All tubing
shall be electrically bonded in accordance with MIL-B-5087.
3.6.9.1 Evaporation and warming tubing. Where the converter does not include
warming coils or a heat exchanger, the aircraft shall include a heat exchanger or
a minimum length of tubing, indicated in Table VI, between converter and first
crew station for the indicated flow rate. Table VII indicates the approximate
length of supply tubing along which frost and condensation can be expected for the
indicated flow rate. Where other equipment might be affected by condensation, the
supply tubing shall be provided with drip shields or other suitable means of
protection. For flows greater than 100 litres per minute (1,666.6 cu.cm/s),
pressure losses in 5/16 inch (7.94 mm) tubing may be excessive and necessitate the
provision of more than one supply tube or a tube of larger size. The design flow
quantity shall be supplied to the oxygen dispensing regulators at a temperature
within +10, -20 F (+5.5, -11 C) of the cabin ambient temperature and at a pressure
not less than 55 psig (379.2 kPa).
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