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WIP Standard
2014-03-20
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.
WIP Standard
2013-12-11
This standard covers the general requirements and methods for testing sandwich core materials and for testing sandwich construction of the types used primarily in aircraft structures. This standard does not include test methods applicable only to a specific product; such test methods are included in the detailed specifications for the product.
WIP Standard
2013-11-27
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.
WIP Standard
2013-09-18
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.
WIP Standard
2013-09-18
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.
WIP Standard
2013-09-18
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.
WIP Standard
2013-09-18
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.
WIP Standard
2013-04-15
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated carbon fiber plain weave fabric product. The prepreg is a plain weave fabric with 12K tows, a nominal fiber areal weight of 193 gsm, and nominal resin content of 42%. The purpose of this specification is to allow procurement of the material corresponding to the statistically derived material properties published in MIL-HDBK-17.
WIP Standard
2013-04-15
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated 7781 glass fabric. The prepreg has a nominal fiber areal weight of 294 gsm, and nominal resin content of 38%.
WIP Standard
2013-04-15
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated carbon fiber unidirectional tape product. This material is intended for use in laminate applications with a service temperature of -65 to 180 °F. The composite may be used for the manufacture of primary and secondary aircraft structure.
WIP Standard
2013-04-02
Convert NCAMP NMS 128 Base Specification to AMS Format.
Standard
2013-02-08
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated 7781 glass fabric. The prepreg has a nominal fiber areal weight of 294 gsm, and nominal resin content of 38%.
Standard
2012-09-14
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated carbon fiber plain weave fabric product. The prepreg is a plain weave fabric with 12K tows, a nominal fiber areal weight of 193 gsm, and nominal resin content of 42%. The purpose of this specification is to allow procurement of a defined material corresponding to the statistically derived material properties published in MIL-HDBK-17. This material is intended for use in laminate applications with a service temperature of -65 to 180 °F. The composite may be used for the manufacture of primary and secondary aircraft structure.
WIP Standard
2012-09-05
This specification covers treated aluminum core material for structural sandwich construction.
WIP Standard
2012-03-01
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%.
WIP Standard
2012-02-22
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
WIP Standard
2012-02-21
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.
WIP Standard
2012-02-21
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
WIP Standard
2012-02-21
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
WIP Standard
2012-02-21
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.
WIP Standard
2012-01-20
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%.
WIP Standard
2011-11-03
This specification establishes the requirements for FiberCote E 765 epoxy prepregs for airframe components under 14 CFR 23 requirements.
Standard
2011-09-01
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated carbon fiber unidirectional tape product. This material is intended for use in laminate applications with a service temperature of -65 to 180 °F. The composite may be used for the manufacture of primary and secondary aircraft structure.
Standard
2009-07-20
This specification covers a two-component compound, an epoxy resin base and a hardener, in the form of a paste. This adhesive compound has been used typically for nonstructural bonding of metallic alloys and thermosetting plastics to themselves and to each other; it is intended primarily as an adhesive for electrical components operating at not higher than 185 °F (85 °C), but usage is not limited to such applications.
Standard
2008-12-29
This specification covers one type of organic fiber in the form of roving. The product shall be formed as five ends of 1420 denier (1580 d tex) yarn (AMS3901/4) collected into an approximately parallel arrangement without twist. Organic 7100 denier (7900 d tex) roving with 450 ksi (3103 MPa) or 21.0 g/d minimum tensile strength and 17.5 Msi (121 GPa) or 900 g/d minimum tensile modulus for use in filament winding requiring high tensile strength and high modulus of elasticity in tension.
Standard
2008-12-29
This specification covers one type of organic fiber in the form of roving. The product shall be formed as four ends of 1140 denier (1270 d tex) yarn (AMS3901/3) collected into an approximately parallel arrangement without twist. Organic 4560 denier (5070 d tex) roving with 500 ksi (3447 MPa) or 21.0 g/d minimum tensile strength and 17.5 Msi (121 GPa) or 815 g/d minimum tensile modulus for use in filament winding requiring high tensile strength and high modulus of elasticity in tension.
Standard
2008-12-29
This specification covers one type of organic fiber in the form of yarn. The product shall be formed as a multiplicity of filaments drawn together and gathered into an approximately parallel arrangement. Organic 2160 denier (2400 d tex) yarn with 390 ksi (2689 MPa) or 19.0 g/d minimum tensile strength and 16.5 Msi (114 GPa) or 750 g/d minimum tensile modulus for use in filament winding requiring high tensile strength and high modulus of elasticity in tension.
Viewing 1 to 30 of 255