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This document provides general guidelines for showing compliance to the applicable certification requirements associated with the modification or alteration to type design of composite aircraft structure or installation of composite parts on metallic or composite airframes, of all aircraft product types. The types of modifications or alterations that this document is meant to address are: • Modification or alteration of metal or composite baseline structure, necessary to install a cargo or mission equipment pod, antenna, winglets, etc. • Installation of composite parts onto metallic or composite baseline structure, such as the pods, antennas, performance enhancing aerodynamic fairings, radomes, cowlings, interior components, etc.

It is recognized that the structural integrity of repaired composite structures depends upon the capabilities of the individuals who are responsible for performing the repairs. This document is intended to address repairs of composite structure regardless of the type of structure such as marine, wind turbine, automotive, aircraft, or other applications. This certification standard establishes the minimum requirements for training, examining, and certifying composite structure repair personnel. It establishes criteria for the certification of personnel requiring appropriate knowledge of the technical principles underlying the composite structural repairs they perform. Persons certified under this document may be eligible for licensing or certification/ qualification by an appropriate authority, in addition to this industry accepted basic composite repair technician certification.

It is recognized that the structural integrity of repaired composite structures depends upon the capabilities of the individuals who are responsible for performing the repairs. This document is intended to address repairs of composite structure regardless of the type of structure such as marine, wind turbine, automotive, aircraft, or other applications. This certification standard establishes the minimum requirements for training, examining, and certifying composite structure repair personnel. It establishes criteria for the certification of personnel requiring appropriate knowledge of the technical principles underlying the composite structural repairs they perform. Persons certified under this document may be eligible for licensing or certification/ qualification by an appropriate authority, in addition to this industry accepted basic composite repair technician certification.

This SAE Aerospace Information Report (AIR) gives guidelines for the design of local “controlled contamination area” (CCA) which can provide a particle-free zone in a hangar or field environment. These guidelines may be used when performing bonded repairs specified in an approved repair procedure or with the agreement of the Original Equipment Manufacturer (OEM) or regulatory authority.

Increased use of advanced composite structural materials on aircraft has resulted in the need to address the more demanding quality and non-destructive testing procedures. Accordingly, increased utilization of solid laminate composites is driving changes to airline NDT training requirements and greater emphasis on the application of accurate NDT methods. Modules, including an introduction to composite materials, composite NDI theory and practice, special cases and lessons learned, have been produced in addition to various hands-on NDT exercises. A set of proficiency specimens containing realistic composite structures and representative damage has been designed in order to reinforce teaching points of the course and “test” inspector’s proficiency. Extensive details of the course modules, hand-on exercises and the proficiency specimens are all presented in this report.

This document provides background information on the design, application, repair and inspection of composite structures, including metal bonding, used on civil transport aircraft. The objective of this document is to assist inspectors to know where to expect composite and metal bonded parts on the aircraft, to understand the capabilities of current NDT methods and to aid interpretation of inspection results. This document does not contain inspection procedures. It is intended to be informative and should not be used singularly, that is, it does not override any instructions that may be issued within a manufacturer's or operator's published documentation.

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 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 PS, AMS3970/3, specifies the batch release and delivery requirements for carbon fiber fabric epoxy prepreg used for repair.

This document (Technical Specification) gives information about qualification rules and the relation between the different specification parts involved, such as the Technical Specification (TS), Material Specification (MS), and Purchasing Specification (PS). The link to the material qualification and qualified products is presented.

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.

AMS3970/2 gives specific information about the qualification program for carbon fiber reinforced epoxy structural repair prepreg systems, applicable for 120 °C (250 °F) vacuum curing. 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.

The PS, AMS3970/3, specifies the batch release and delivery requirements for carbon fiber fabric epoxy prepreg used for repair.

AMS3970/4 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 prepreg system as defined in AMS3970 and AMS3970/1.

The PS, AMS3970/5, specifies the batch release and delivery requirements for the companion non-structural glass fiber fabric prepreg.

The PS, AMS3970/5, specifies the batch release and delivery requirements for the companion non-structural glass fiber fabric prepreg.

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.

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.

This document (Technical Specification) gives information about qualification rules and the relation between the different specification parts involved, such as the Technical Specification (TS), Material Specification (MS), and Purchasing Specification (PS). The link to the material qualification and qualified products is presented.

AMS 3970 gives information about qualification rules and the relation between the different specification parts involved, such as the Technical Specification (TS), Material Specification (MS), and Purchasing Specification (PS). The link to the material qualification and qualified products is presented.