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AMS CACRC Commercial Aircraft Composite Repair Committee Test procedures Heat resistant materials

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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

Identification and Assessment of Damage to Composite Aircraft Structures Training Document
2020-08-03
CURRENT
AIR6825
Individuals who complete the applicable modules aligned with this training document will be able to define the type of damage, define the extent of damage, determine if further inspection is required, evaluate the damage against published allowable damage limits, and provide accurate documentation of the damage. The intended outcome of the training is increased safety such that no aircraft is released with unknown damage and that the aircraft meets continued airworthiness requirements. The goal is to change the culture from damage discovery to damage reporting while also reducing or eliminating flight delays due to incorrect or insufficient information. Teaching levels have been assigned to the curriculum to define the knowledge, skills, and abilities graduates will need. Minimum hours of instruction have been provided to ensure adequate coverage of all subject matter including lecture and practical exercise.
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

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 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 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.
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