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This guidebook will assist in the design and integration of composite commercial aircraft structures that exhibit improved durability, maintainability and repairability. For international use by composite aircraft component designers, this book identifies problems that have occurred with various composite components and provides potential problem-solving recommendations. Written primarily for composite design engineers, Design of Durable, Repairable, and Maintainable Aircraft Composites should also prove valuable to those in structural engineering, materials and processing, product support, advanced product development, systems engineering, technical services, and maintenance operations.

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 Recommended Practice (ARP) describes standard methods for restoring damaged core on commercial aircraft sandwich structures. The methods shall only be used when specified in an approved repair procedure or with the agreement of the Original Equipment Manufacturer (OEM) or regulatory authority. The repair materials shall be defined in the approved repairs referencing these methods.

The SAE Aerospace Information Report (AIR) is intended to be used as a process verification guide for evaluating implementation of key factors in bonded repair of fiber reinforced composite structure in a repair shop environment. The guide will be used in conjunction with a regulatory approved and substantiated repair, and is intended to promote consistency and reliability.

This Aerospace Recommended Practice (ARP) describes methods of vacuum bagging, a process used to apply pressure in adhesive bonding and heat curing of thermosetting epoxy and polyester matrix fabrications for commercial aircraft composite parts. If this document is used for the vacuum bagging of other than thermosetting epoxy and polyester materials, the fitness for this purpose must be determined by the user. The methods shall only be used when specified in an approved repair document or with the agreement of the Original Equipment Manufacturer (OEM) or regulatory authority.

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.

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.

This PS specifies the batch release and delivery requirements for epoxy resin systems (base resin and curing agent) used for wet lay-up repair purposes.

AMS 2980/2 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.

This PS specifies the batch release and delivery requirements for carbon fiber and carbon fabric used for wet lay-up repair purposes.

This Material Specification defines the requirements of carbon fiber fabric and epoxy resin systems used for wet lay-up repair of carbon fiber reinforced epoxy structures, qualified according to AMS 2980/1 and 2980/2. Unless otherwise specified by the drawing, the order or the inspection schedule, the present specification shall be used in conjunction with the referenced documents.

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

AMS 3970/4 specifies the batch release and delivery requirements for film adhesive used for repair. This specification is applicable when the film adhesive is part of the prepreg system as defined in AMS 3970 and AMS 3970/1.

AMS 3970/3 specifies the batch release and delivery requirements for carbon fiber fabric epoxy prepreg used for repair.

This PS specifies the batch release and delivery requirements for epoxy resin systems (base resin and curing agent) used for wet lay-up repair purposes.

This PS specifies the batch release and delivery requirements for carbon fiber and carbon fabric used for wet lay-up repair purposes.