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Basic Composite Repair Technician Certification Standard

2019-09-10
CURRENT
ARP6262A
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.
Standard

Identification and Assessment for Damage to Composite Aircraft Structures Training Document

2018-10-23
WIP
AIR6825
Individuals who complete this course will be able to define the type of damage, define the extent of damage, determine if further inspection is required, 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.
Standard

COMPOSITE INSPECTOR TRAINING COURSE TO ENHANCE PROFICIENCY AND IMPROVE RELIABILITY

2018-07-24
WIP
AIR7491
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.
Standard

Repair Tooling

2017-10-30
WIP
AIR5431A
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

Drying of Thermosetting Composite Materials

2017-05-26
WIP
ARP4977A
This SAE Aerospace Recommended Practice (ARP) describes standard methods for drying commercial aircraft composite structures prior to repair and gives general guidelines on use and applicability. It addresses the removal of liquids that have collected inside the structures through open damage, microcracks, or porosity and the removal of absorbed moisture from the composite material. The methods described in this document shall only be used when specified in an approved repair document or with the agreement of the original equipment manufacturer (OEM) or regulatory authority. If this document is used for the drying of materials other than thermosetting composite materials, the fitness for this purpose must be determined by the user. The purpose of this document is to provide a set of standard drying methods that may be referenced in repair documents produced by airlines or airframe and engine manufacturers.
Standard

Design of Durable, Repairable, and Maintainable Aircraft Composite Structures

2016-02-25
WIP
AIR6902
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.
Standard

Carbon Fiber Fabric and Epoxy Resin Wet Lay-Up Repair Material Part 5 - Carbon Fiber Fabrics, Plain Weave, 193 g/m2, and Epoxy Resin

2014-04-11
CURRENT
AMS2980/5A
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 AMS2980/1 and AMS2980/2. Unless otherwise specified by the drawing, the order or the inspection schedule, the present specification shall be used in conjunction with the referenced documents.
Standard

Basic Composite Repair Technician Certification Standard

2014-02-13
HISTORICAL
ARP6262
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.
Standard

Guidelines for Repair Process Evaluation of Fiber Reinforced Composite Bonded Structure

2014-01-29
WIP
AIR6292
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.
Standard

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

2011-04-06
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

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

2011-04-01
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

Carbon Fiber Fabric Repair Prepreg, 120 °C (250 °F) Vacuum Curing Part 2 - Qualification Program for Fiber, Fabric, Carbon Prepreg, Film Adhesive and Non-Structural Glass Prepreg

2011-04-01
CURRENT
AMS3970/2A
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.
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