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Viewing 1 to 15 of 15
2015-03-06
WIP Standard
AMS6891
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250°F for primary or secondary aircraft structures.
2014-08-26
WIP Standard
P1713AI/1
Detail specification for T700S-12K-50C/#2511 Plain Weave Fabric
2014-03-20
WIP Standard
P1713AJ
To define the requirements for temperature (plus pressure and vacuum) measurement, control and calibration for composite processing equipment such as autoclaves, ovens and presses (perhaps) based on AMS2750E.
2013-11-27
WIP Standard
P1713AI
This specification establishes the requirements for a #2511 epoxy resin preimpregnated T700SC-12K-50C Carbon Fiber Plain Weave Fabric product. The prepreg has a nominal fiber weight of 190 g/m2 (without sizing), and nominal resin content of 42% by weight.
2013-09-18
WIP Standard
P1713AF
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the basic spec and it will have three slash/detail specs.
2013-09-18
WIP Standard
P1713AE
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the first slash/detail spec.
2013-09-18
WIP Standard
P1713AH
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the third detail spec.
2013-09-18
WIP Standard
P1713AG
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the second detail spec.
2012-03-01
WIP Standard
P1712AG
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated glass fiber 8-hanress satin weave fabric product. The prepreg is a plain weave fabric with 3K tows, a nominal fiber areal weight of 193 gsm, and nominal resin content of 42%.
2012-02-22
WIP Standard
P1712AE
The specification established the procures and requirements for fabrication and acceptance of monolithic composites laminates and non-metallic honeycomb core sandwich composite assemblies using fiber reinforced toughened epoxy resin intended for cure with atmospheric (vacuum) pressure only
2012-02-21
WIP Standard
P1712AB
This specification establishes the requirements for fiberglass fiber fabric impregnated with a modified B-staged toughened epoxy resin intended for cure using atmospheric (vacuum) pressure only.
2012-02-21
WIP Standard
P1712AC
This specification establishes the requirements for unidirectional I intermediate modulus carbon fiber impregnated with a modified B-staged toughened epoxy resin intended for cure using atmospheric (vacuum ) pressure only
2012-02-21
WIP Standard
P1712AD
This specification establishes the requirements for woven continuous high strength modulus carbon fiber fabric impregnated with a modified B-staged toughened epoxy resin intended for cure using atmospheric (vacuum) pressure only
2012-02-21
WIP Standard
P1712AF
This specification establishes the requirements for a woven continuous quartz fiber fabric impregnated with a modified B-staged toughened epoxy resin intended for cure using atmospheric (vacuum) pressure only.
2012-01-20
WIP Standard
P1712AA
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated glass fiber 8-hanress satin fabric product. The prepreg is a plain weave fabric with 3K tows, a nominal fiber areal weight of 193 gsm, and nominal resin content of 42%.
Viewing 1 to 15 of 15

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