Search Results

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

Heat Application for Thermosetting Resin Curing

2011-11-16

HISTORICAL

ARP5144

This SAE Aerospace Recommended Practice (ARP) describes standard methods of heat application to cure thermosetting resins for commercial aircraft composite repairs. 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.

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

Core Restoration of Thermosetting Composite Components

1998-12-01

HISTORICAL

ARP4991

This SAE Aerospace Recommended Practice (ARP) describes standard methods for restoring damaged core on commercial aircraft sandwich structures. It currently applies to wet lay up repairs only. 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.

Standard

Core Restoration of Thermosetting Composite Components

2014-02-03

CURRENT

ARP4991A

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.

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

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

Composite and Bonded Structure Technician/Specialist Training Document

2017-06-05

HISTORICAL

AIR4938B

This is a general curriculum that has been developed to identify the minimum knowledge and skill requirements of a composite and/or metal bond repair technician/specialist. This revision changes the document from an all-inclusive curriculum into a modular set of curricula. 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. These minimums may be exceeded and may include an increase in the total number of training hours and/or increases in the teaching levels. Each curriculum is a subpart of this document. Part 1 is the General Composite Structure Bonded Repair curriculum, independent of the application. Part 2 is the Commercial Aircraft Composite Structure Bonded Repair curriculum.

Standard

Composite and Bonded Structure Inspector: Training Document

2016-10-13

HISTORICAL

AIR5279

This document provides recommendations concerning the minimum knowledge and skill guidelines for a composite and metal bond repair inspector. Teaching levels have been assigned to this curriculum to define the knowledge, skills and abilities needed to inspect repairs. Minimum hours of instruction have been provided to ensure adequate lecture and laboratory coverage of all subject matter. These minimums may be exceeded, and may include an increase in the total number of training hours and/or increases in the teaching levels.

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 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

Carbon Fiber Fabric and Epoxy Resin Wet Lay-Up Repair Material Part 1 - General Requirements

2006-01-26

HISTORICAL

AMS2980/1A

AMS 2980/1 gives information about the technical requirements and qualification procedure for carbon fiber fabric and epoxy resin systems used for wet lay-up repair of carbon fiber reinforced epoxy structures.

Standard

Carbon Fiber Fabric and Epoxy Resin Wet Lay-Up Repair Material Part 1 - General Requirements

2021-09-23

CURRENT

AMS2980/1B

AMS2980/1 gives information about the technical requirements and qualification procedure for carbon fiber fabric and epoxy resin systems used for wet lay-up repair of carbon fiber reinforced epoxy structures.

Standard

Carbon Fiber Fabric and Epoxy Resin Wet Lay-Up Repair Material Part 0 - Introduction

2021-09-23

CURRENT

AMS2980B

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.

Standard

Carbon Fiber Fabric and Epoxy Resin Wet Lay-Up Repair Material Part 0 - Introduction

2006-01-26

HISTORICAL

AMS2980A

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.

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, 125 °C (250 °F) Vacuum Curing Part 0 - Introduction

1999-12-01

HISTORICAL

AMS3970

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.