MIL-PRF-46187A
conformance inspection shall be repeated on additional sample units (all tests
and examinations, or the test which the original sample failed, at the option of
the procuring activity). Conformance inspections shall be reinstituted, however,
final acceptance and shipment shall be withheld until the conformance inspection
has shown that the corrective action was successful. In the event of failure
after reinspection, information concerning the failure shall be furnished to the
cognizant inspection activity and the procuring activity.
4.3
Sampling for inspection.
Sampling for inspection shall be performed in
accordance with the provisions set forth in ASTM D1898 or as otherwise specified.
4.4 Test methods.
Testing of resins, fibers, prepregs and composite laminates
for compliance with
the requirements of this specification shall be performed in
accordance with the
applicable test methods described in this specification to
the maximum extent
practicable, or as otherwise specified by the procuring
activity.
4.5
Identification marking.
Verify the presence of the required markings.
5.
PACKAGING
5.1 Packaging. For acquisition purposes, the packaging requirements shall be as
specified in the contract or order (see 6.2). When actual packaging of materiel
is to be performed by DoD personnel, these personnel need to contact the
responsible packaging activity to ascertain requisite packaging requirements.
Packaging requirements are maintained by the Inventory Control Point's packaging
activity within the Military Department or Defense Agency, or within the Military
Department's System Command.
Packaging data retrieval is available from the
managing Military Department's or Defense Agency's automated packaging files, CD-
ROM products, or by contacting the responsible packaging activity.
6.
NOTES
(This section contains information of a general or explanatory nature that may be
helpful, but is not mandatory.)
6.1 Intended use. The composite material specified herein is military unique
because it is the only proven material used in aging aircraft replacement parts.
This composite has been increasingly accepted as an engineering material for the
design and fabrication of aerospace structural components, particularly
aeropropulsion structural components. Material procured in accordance with this
specification is intended for use in airframe, aerospace, and similarly related
primary or secondary load-bearing structures where high stiffness and strength-
to-weight ratios are required. Historically PMR-15 resin has been employed but
comparable resin systems may be utilized. Polyimide (PMR-15) composite material
has been extensively characterized in the NASA Composites for Advanced Space
Transportation Systems (CASTS) Program, and is used in aircraft engine hardware
such as cowls, nozzle flaps, and ducts.
6.1.1
Design allowables.
A design allowables test program was conducted on
graphite/polyimide composites by NASA (NASA CR-165840) to establish material
performance over a 116°K (-250°F) to 589°K (600°F) temperature range. Effects of
aging, thermal cycling and moisture were also evaluated. Tension, compression
and in-plane shear properties were determined for uniaxial, pseudoisotropic and
± 45 degree laminates. Test results show sufficient strength and stiffness to
substantiate graphite/polyimide composites as an acceptable structural material
for high temperature structural applications.
5
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