MIL-DTL-22263C
3.7.4 Fuel resistance. The coupling assembly shall not leak (sufficient to form a drop)
nor show evidence of damage when subjected to high temperature fuel aging at 200 °F, low
temperature fuel aging at -65 °F and air dry out at 200 °F when tested as specified in 4.7.4.
3.7.5 Salt fog. The coupling assembly shall pass the salt fog test specified in 4.7.5
without any evidence of excessive corrosion, peeling, blistering of the finish or exposure of base
metal. Threads and connecting surfaces and sealing surfaces shall be free of corrosion.
3.7.6 Repeated assembly. There shall be no evidence of deformation, damage or
degradation in the connection of the coupling halves after 25 repeated assembly and disassembly
test specified in 4.7.6 follow by the proof pressure test without leakage.
3.7.7 Flexure. The coupling assembly, when tested as specified in 4.7.7 with a 3 degree
tubing misalignment and flexure at ±0.5 degree for 28,800 cycles followed by the proof pressure
test shall show no evidence of leakage, rupture, permanent set, permanent deformation or
damage (see figure 4).
3.7.8 Vibration. The coupling assembly shall show no evidence of malfunction or
structural failure and shall pass the proof pressure test after exposure to vibration levels as
specified in MIL-STD-810 (see table VII) and tested as specified in 4.7.8.
3.7.9 Surge pressure. The coupling assembly shall withstand 50,000 pressure surge
cycles without evidence of malfunction or leakage when tested at room temperature specified in
4.7.9.
3.7.10 Burst pressure. The coupling assembly shall be designed to meet the burst
pressure requirements at room temperature and extreme temperatures and shall pass the
requirements when tested as specified in 4.7.10.
3.8 Maintainability. The coupling assembly when installed in aircraft shall not require
periodic maintenance. The seals installed in the coupling shall be easily replaceable without
damage to other parts and shall be able to be removed with a minimum of disturbance or
displacement of the installed coupling and tubing. The coupling system maintainability
requirements shall be integrated with the overall aircraft system maintainability programs and
shall comply with the requirements of MIL-HDBK-470.
3.9 Reliability. The coupling assembly shall be designed to withstand the strains,
vibrations, and temperature environment incident to aircraft installation and services usage. The
reliability of the coupling assembly shall be an integral part of reliability requirements of the
total aircraft systems.
3.10 Interchangeability. All parts having the same manufacturer's part number
shall be directly and completely interchangeable with each other with respect to installation
and performance.
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