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Standard

Automated Manufacture of Continuous Multi-Ply Carbon Fiber/Epoxy Resin Impregnated Broadgoods

2022-06-05

CURRENT

ARP1674A

This document describes a manufacturing method for processing unidirectional carbon fiber/epoxy resin impregnated sheet and tape into multi-ply broadgoods and tape produced on an automated cross-plying machine. Broadgoods or tape of two or more ply configurations may be processed, where ply orientations of 0°, 45°, 90°, and 135° (as examples) may be automatically layed in a programmed sequence. In all configurations, the 0° ply direction is parallel to the length of the broadgoods roll or sheet, or tape.

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

ADHESIVE, EPOXY PASTE, FOR STRUCTURAL WELDBOND For 80°C (180°F) Service

1995-10-01

HISTORICAL

AMS3708

This specification covers a one-part modified epoxy adhesive in the form of paste.

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

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

Quality Inspection Procedure, Composites Tracer Fluoroscopy and Radiography

2022-06-05

CURRENT

ARP1611A

This document describes an inspection procedure for detecting, by use of a radiographic opaque tracer and fluoroscopy or radiography methods, flaws which have been produced as the result of cutting, machining, or drilling operations in composite or laminate structures.

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 for Structural Adhesive Bonding Titanium Alloy Parts

2022-06-07

CURRENT

ARP1843A

This recommended practice establishes the procedures and requirements for cleaning titanium alloy parts prior to adhesive bonding operations.