Search Results

Standard

Cloth, Type “E” Glass “B” Stage Polyester Resin Impregnated 1581 and 7781 Type Fabric

2016-11-10

CURRENT

AMS3826C

This specification covers two styles of glass cloth impregnated with a polyester resin system, the resin being processed to a “B” stage condition. Either style of glass may be used.

Standard

CLOTH, TYPE “E” GLASS “B” Stage Polyester Resin Impregnated 1581 and 7781 Type Fabric

1995-07-01

HISTORICAL

AMS3826B

This specification covers two styles of glass cloth impregnated with a polyester resin system, the resin being processed to a “B” stage condition. Either style of glass may be used.

Standard

Resin, Polyimide, Laminating High Temperature Resistant, 315 °C (599 °F)

1998-09-01

HISTORICAL

AMS3619C

This specification covers a single-component, heat-reactive, thermosetting aromatic system which thermally cures to form a polyimide polymer structure.

Standard

Syntactic Foam Tiles

2016-11-10

CURRENT

AMS3709D

This specification covers dielectrically-loaded syntactic foam tiles having a polyimide resin matrix.

Standard

Structural Weldbonding of Aluminum Structures

2014-08-14

CURRENT

ARP1675

This SAE Aerospace Recommended Practice describes the aluminum weldbonding process for fabrication of secondary aircraft structural assemblies possessing excellent strength, fatigue life, and environmental durability.

Standard

Application of Direct Pressure to Resin in Curing of Epoxy and Addition Type Polyimides

2022-06-07

CURRENT

ARP1927

This recommended practice describes the materials, related equipment, and particular processing techniques utilized in process science curing of composite hardware where pressure is imparted specifically to the resin of curing composites. Included as Appendix "A" to this ARP is a discussion of the particular techniques developed for a processing science philosophy which has consistently produced void and porosity-free, large area, thick composite structures.

Standard

Advanced Composites Prepreg - Nominal 250 °F Cure - Carbon Fiber and Epoxy Resin, Unidirectional Tape

2021-03-25

WIP

AMS3960B

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

Advanced Composites Prepreg - Nominal 250 °F Cure - Carbon Fiber and Epoxy Resin, Unidirectional Tape

2011-09-01

HISTORICAL

AMS3960

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.

Standard

Advanced Composites Prepreg - Nominal 250 °F Cure - Carbon Fiber and Epoxy Resin, Unidirectional Tape

2015-08-11

CURRENT

AMS3960A

The purpose of this specification is to allow procurement of a defined material corresponding to the statistically derived material properties published in CMH-17 Volume II.

Standard

Organic Fiber (Para-Aramid), Yarn and Roving, High Modulus

1998-09-01

CURRENT

AMS3901C

This specification and its supplementary detail specifications covers organic fibers in the form of continuous, multifilament yarn and roving.

Standard

Physical-Chemical Characterization Techniques, Epoxy Adhesive and Prepreg Resin Systems

2022-06-05

CURRENT

ARP1610A

This recommended practice describes the physical and chemical characterization techniques for identification of epoxy adhesive and prepreg resin systems in order to verify the chemical formulation, resin B-staging (See 8.1), cure reaction rates, adhesive moisture content, and resin component mix ratios, as necessary to achieve manufacturing and quality producibility and engineering performance.

Standard

350 °F Autoclave Cure, Low Flow Toughened Epoxy Prepregs

2015-12-02

CURRENT

AMS3961

The intent of this specification is for the procurement of the material listed on the QPL and, therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program shall refer to the Quality Assurance section of this base specification, AMS3961. All material qualification and equivalency data has been archived and is available for review upon request. Contact the CMH-17 Secretariat (www.cmh17.org) for additional information.

Standard

350 °F Autoclave Cure, Low Flow Toughened Epoxy Prepregs

2019-03-12

WIP

AMS3961A

The intent of this specification is for the procurement of the material listed on the QPL and, therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program shall refer to the Quality Assurance section of this base specification, AMS3961. All material qualification and equivalency data has been archived and is available for review upon request. Contact the CMH-17 Secretariat (www.cmh17.org) for additional information.

Standard

Advanced Composites Prepreg – Nominal 250 °F Cure –Glass Fiber and Epoxy Resin, 7781 Weave Fabric

2021-03-25

WIP

AMS3915B

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

Advanced Composites Prepreg - Nominal 250 °F Cure – 12K Tow Carbon Fiber and Epoxy Resin, Plain Weave Fabric

2021-03-25

WIP

AMS3914B

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%.

Standard

Advanced Composites Prepreg – Nominal 250 °F Cure –Glass Fiber and Epoxy Resin, 7781 Weave Fabric

2013-02-08

HISTORICAL

AMS3915

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

Advanced Composites Prepreg – Nominal 250 °F Cure – 12K Tow Carbon Fiber and Epoxy Resin, Plain Weave Fabric

2015-09-03

CURRENT

AMS3914A

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%.

Standard

Advanced Composites Prepreg – Nominal 250 °F Cure – Glass Fiber and Epoxy Resin, 7781 Weave Fabric

2015-08-10

CURRENT

AMS3915A

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

Advanced Composites Prepreg – Nominal 250 °F Cure – 12K Tow Carbon Fiber and Epoxy Resin, Plain Weave Fabric

2012-09-14

HISTORICAL

AMS3914

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%.

Standard

Surface Preparation and Priming of Aluminum Alloy Parts for High Durability Structural Adhesive Bonding

2018-11-15

WIP

ARP1524B

This Aerospace Recommended Practice (ARP) describes the processing system and techniques for the surface preparation and priming of aluminum alloy parts for structural adhesive bonding to achieve optimum bondline durability, corrosion resistance, and manufacturing producibility. While this surface preparation has been developed and validated for two high strength aluminum alloys, 2024 and 7075, in the hardened condition it is expected to be applicable to other alloys and tempers. This surface preparation system has been validated for use with 180 degrees F (82 degrees C) and with 250 degrees F (121 degrees C) curing elastomer-modified epoxy adhesive and corrosion-inhibiting primer. The processes described herein are the result of laboratory evaluation of structural and durability performance.