MIL-DTL-27536C
3.4
Design. The coupling shall be designed to conform to the various
sizes, types, temperatures, and loads in accordance with MIL-DTL-27576/1, MIL-
DTL-27576/2, and MIL-DTL-27576/3. The coupling sizes shall be in accordance
with MS24563, Figure 2A Flanges.
The coupling shall consist of the following components:
a.
Latching member or members.
b.
Retaining member or members.
The latch of the quick-release type (Type R) shall be positive locking but
easily released when the nut is backed off. All component parts of the quick-
release couplings shall remain as an assembly during installation or removal.
The basic T-bolt latches (Type B) may require removal of latch components such
as the nut. Type L latches shall provide a secondary safety latch to preclude
complete separation of the mated flanges in the event of failure of the
primary T-bolt.
3.4 .1 Welding. Resistance or fusion welding of elements carrying hoop
tension load shall be in accordance with MIL-W-6858 or MIL-STD-2219. Spot
welding shall be in accordance with MIL-W-6858. Welding which is not critical
to the structural integrity of the coupling, such as positioning spotwelds,
need not conform to this requirement.
3.4 .2 Assembly. The coupling design shall be such as to allow ease of
assembly and disassembly on tubing or flange ends in close and confined spaces
such as are normally encountered in aircraft installations.
3.5 Performance.
The coupling shall satisfy the following performance
requirements.
3.5.1 Position. The connector assembly shall operate satisfactorily in
any position attitude in the aircraft system. The coupling shall function
satisfactorily with fluid flow in either direction.
3.5.2 Temperature. The coupling shall be capable of operation through the
temperature range specified on the applicable MS standard with load ratings
adjusted in accordance with table I.
3.5.3 Rated load. The coupling shall be capable of carrying total applied
operating loads in accordance with the axial load rating of the applicable MS
standard and the temperature load factor specified in table I.
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