Search Results

Standard

COMPOSITES AND METAL BONDING GLOSSARY

1997-03-01

HISTORICAL

AIR4844A

The following terminology has been generated by the ATA/IATA/SAE Commercial Aircraft Composite Repair Committee (CACRC) and provides terminology for design, fabrication, and repair of composite and bonded metal structures.

Standard

COMPOSITES AND METAL BONDING GLOSSARY

1994-12-01

HISTORICAL

AIR4844

The following terminology has been generated by the ATA/IATA/SAE Commercial Aircraft Composite Repair Committee (CACRC) and provides terminology for design, fabrication, and repair of composite and bonded metal structures.

Standard

Composites and Metal Bonding Glossary

1999-09-01

HISTORICAL

AIR4844B

The following terminology has been generated by the ATA/IATA/SAE Commercial Aircraft Composite Repair Committee (CACRC) and provides terminology for design, fabrication, and repair of composite and bonded metal structures.

Standard

Composites and Metal Bonding Glossary

2017-06-20

CURRENT

AIR4844C

The following terminology has been generated by the ATA/IATA/SAE Commercial Aircraft Composite Repair Committee (CACRC) and provides terminology for design, fabrication, and repair of composite and bonded metal structures.

Standard

Carbon Fiber Fabric Repair Prepreg, 125 °C (250 °F) Vacuum Curing Part 1 - General Requirements

1999-12-01

HISTORICAL

AMS3970/1

AMS 3970/1 gives information about the technical requirements and qualification procedure for carbon fiber fabric epoxy prepreg used for repair of carbon fiber reinforced epoxy structures. The prepreg system may include a film adhesive to be applied in a co-curing process with the prepreg for joint and sandwich bonding. The need for a film adhesive shall be established during screening tests.

Standard

Carbon Fiber Fabric Repair Prepreg, 120 °C (250 °F) Vacuum Curing Part 1 - General Requirements

2016-12-06

CURRENT

AMS3970/1A

AMS3970/1 gives information about the technical requirements and qualification procedure for carbon fiber fabric epoxy prepreg and a companion non-structural glass prepreg used for repair of carbon fiber reinforced epoxy structures. The prepreg system may include a film adhesive to be applied in a co-curing process with the prepreg for joint and sandwich bonding. The need for a film adhesive shall be established during screening tests.

Standard

Composite Honeycomb NDI Reference Standards

2001-09-01

HISTORICAL

ARP5606

This recommended practice establishes generic reference standards that will accommodate nondestructive inspections (NDI) on a broad range of non-metallic composite honeycomb structures found on aircraft.

Standard

Composite Honeycomb NDI Reference Standards

2011-12-20

CURRENT

ARP5606A

This recommended practice establishes generic reference standards that will accommodate nondestructive inspections (NDI) on a broad range of non-metallic composite honeycomb structures found on aircraft.

Standard

Repair Tooling

2011-11-16

CURRENT

AIR5431

This SAE Aerospace Information Report (AIR) offers information about the use of support tooling for composite repair processes, as well as descriptions of some of the different tooling materials used and their applications. If the repair document requires the use of tooling, refer to this AIR for additional information.

Standard

Carbon Fiber Fabric Repair Prepreg, 120 °C (250 °F) Vacuum Curing Part 6 - Material Specification: Carbon Fiber Fabric Reinforced Epoxy Prepreg for Repair, Plain Weave Fabric, 193 g/m2, Adhesive Film for Repair and Non-Structural Glass Fiber Fabric Reinforced Epoxy Prepreg, 105 g/m2

2016-12-05

CURRENT

AMS3970/6

This Material Specification defines the requirements of carbon fiber reinforced epoxy prepreg for repair, 120 °C (250 °F) Vacuum curing, Plain Weave Fabric, 193 g/m2 and a companion non-structural glass fiber fabric reinforced epoxy prepreg, 105 g/m2, qualified according to AMS3970/1 and AMS3970/2 for aerospace application. The prepreg system may include an epoxy film adhesive to be applied in a co-curing process with the prepreg for joint and sandwich bonding. The need for a film adhesive shall be established during screening tests. If included, the requirements to be met by the adhesive are also defined in this document.

Standard

Unidirectional Carbon Fiber Tape Epoxy Repair Prepreg, Vacuum Curing Part 2 - Qualification Program for Fiber, Carbon Fiber Tape Prepreg, and Film Adhesive

2021-02-23

CURRENT

AMS6885/2

AMS6885/2 gives specific information about the qualification program for unidirectional carbon fiber tape epoxy repair prepreg capable of curing under vacuum for repair of carbon fiber reinforced epoxy structures. The prepreg system shall include an epoxy film adhesive to be applied in a co-bonding process with the prepreg for solid laminate and sandwich bonding.

Standard

Unidirectional Carbon Fiber Tape Epoxy Repair Prepreg, Vacuum Curing Part 0 - Introduction

2021-02-23

CURRENT

AMS6885

This document (Technical Specification) gives information about qualification rules and the relation between the different specification parts involved, such as the Technical Specification (TS), the Material Specification (MS), and the Purchasing Specifications (PS).

Standard

Unidirectional Carbon Fiber Tape Epoxy Repair Prepreg, Vacuum Curing Part 1 - General Requirements

2021-02-23

CURRENT

AMS6885/1

AMS6885/1 gives information about the technical requirements and qualification procedure for unidirectional carbon fiber tape epoxy repair prepreg capable of curing under vacuum for repair of carbon fiber reinforced epoxy structures. The repair system includes an epoxy film adhesive to be applied in a co-bonding process with the prepreg for solid laminate and sandwich bonding.

Standard

Unidirectional Carbon Fiber Tape Epoxy Repair Prepreg, Vacuum Curing Part 4 - Purchasing Specification for Film Adhesive

2021-02-22

CURRENT

AMS6885/4

This Purchasing Specification, AMS6885/4, specifies the batch release and delivery requirements for film adhesive used for repair. This specification is applicable only when the film adhesive is used as part of the repair system defined in AMS6885 and AMS6885/1. This specification also defines the procedure and requirements for storage life extension of materials purchased against this specification. It is only applicable for materials qualified against AMS6885 (refer to PRI-QPL-AMS6885), and shall be carried out within the responsibility of the purchaser and under control of its Quality organisation.

Standard

Unidirectional Carbon Fiber Tape Epoxy Repair Prepreg, Vacuum Curing Part 5 - Material Specification for Unidirectional Carbon Fiber Tape Epoxy Prepreg for Repair and Film Adhesive for Repair, 120 to 145 °C (250 to 290 °F) Curing

2021-02-22

CURRENT

AMS6885/5

AMS6885/5 is the Material Specification (MS) which defines the requirements of a unidirectional carbon fiber tape epoxy repair prepreg capable of curing under vacuum for repair of carbon fiber reinforced epoxy structures. It also defines the requirements of an epoxy film adhesive to be applied in a co-bonding process with the prepreg for solid laminate and sandwich bonding.

Standard

Teaching Points for an Awareness Class on "Critical Issues in Composite Maintenance and Repair"

2009-10-02

HISTORICAL

AIR5719

This document is to be used as a checklist by curriculum developers to create awareness training for critical composite repair and maintenance issues. This document will not take place of training requirements for specific job roles of a composite repair technician or engineer.

Standard

Carbon Fiber Fabric and Epoxy Resin Wet Lay-up Repair Material Part 2 - Qualification Program

2021-09-24

CURRENT

AMS2980/2B

AMS2980/2 gives specific information about the qualification program for carbon fiber fabric, epoxy systems and the material combination used for wet lay-up repair of carbon fiber reinforced epoxy structures.

Standard

Composites and Metal Bonding Glossary

2019-04-24

WIP

AIR4844D

The following terminology has been generated by the ATA/IATA/SAE Commercial Aircraft Composite Repair Committee (CACRC) and provides terminology for design, fabrication, and repair of composite and bonded metal structures. The purpose of this AIR is to provide terminology that should be used when developing CACRC repair documents or repair documents produced by airlines or airframe and engine manufacturers. It is intended to develop this AIR into an AS.

Standard

Composite and Bonded Structure Technician/Specialist Training Document

2018-09-19

CURRENT

AIR4938C

This document establishes the minimum curriculum requirements for training, practical assessments, and certifying composite structure repair personnel and metalbond repair personnel. It establishes criteria for the certification of personnel requiring appropriate knowledge of the technical principles underlying the composite structural repairs and/or metalbond they perform. Persons certified under this document may be eligible for licensing/certification/qualification by an appropriate authority, in addition to this industry accepted technician certification. Teaching levels have been assigned to the curriculum to define the knowledge, skills, and abilities graduates will need to make repairs to composite or metalbond structure. Minimum hours of instruction have been provided to ensure adequate coverage of all subject matter including lecture and laboratory.

Standard

Solid Composite Laminate NDI Reference Standards

2011-12-20

CURRENT

ARP5605A

This recommended practice establishes a generic composite reference standard that will accommodate nondestructive inspections (NDI) on the full array of glass fiber and carbon fiber laminates found on aircraft.