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AMS CACRC Commercial Aircraft Composite Repair Committee Management and Organizations Aerodynamics Manufacturing processes

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Standard

Vacuum Bagging of Thermosetting Composite and Metalbond Repairs
2023-08-14
CURRENT
ARP5143A
This Aerospace Recommended Practice (ARP) describes methods of vacuum bagging, a process used to apply pressure in adhesive bonding and heat curing of thermosetting composite materials and metalbond for commercial aircraft parts. If this document is used for the vacuum bagging of other than thermosetting composite materials and metalbond, 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).
Standard

Unidirectional Carbon Fiber Tape Epoxy Repair Prepreg, Vacuum Curing Part 4 - Purchasing Specification for Film Adhesive
2021-02-22
CURRENT
AMS6885/4
This Purchasing Specification, AMS6885/4, 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 repair system defined in AMS6885 and AMS6885/1. This specification also defines the procedure and requirements for storage life extension of materials purchased against this specification. It is only applicable for materials qualified against AMS6885 (refer to PRI-QPL-AMS6885), and shall be carried out within the responsibility of the purchaser and under control of its Quality organisation.
Standard

Unidirectional Carbon Fiber Tape Epoxy Repair Prepreg, Vacuum Curing Part 3 - Purchasing Specification for Unidirectional Carbon Fiber Tape Epoxy Repair Prepreg
2021-02-22
CURRENT
AMS6885/3
This Purchasing Specification, AMS6885/3, specifies the batch release and delivery requirements for unidirectional carbon fiber tape epoxy prepreg used for repair. This specification is applicable only when the unidirectional carbon fiber tape epoxy prepreg is used as part of the repair system defined in AMS6885 and AMS6885/1. This specification also defines the procedure and requirements for storage life extension of materials purchased against this specification. It is only applicable for materials qualified against AMS6885 (refer to PRI-QPL-AMS6885) and shall be carried out within the responsibility of the purchaser and under control of its Quality organisation.
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

Repair Tooling
2011-11-16
CURRENT
AIR5431
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

Maintenance Life Cycle Cost Model
2016-10-13
CURRENT
AIR5416
This document describes a life cycle cost model for commercial aircraft composite structure. The term life cycle cost used herein, refers to the airline costs for maintenance, spares support, fuel, repair material and labor associated with composites after introduction into service and throughout its useful life. This document contains the equations that can be programmed into software which is used to estimate the total cost of ownership aircraft, including structure. Modification costs and operating costs are estimated over a specified life (any period up to 30 years). Modification costs include spares holding, training, support equipment, and other system related costs. Annual operating costs include: Schedule interruption, fuel, spares, insurance, and maintenance. Maintenance costs are separated by scheduled maintenance or unscheduled damage, or can by grouped into the typical organizations of line, shop, and hangar maintenance.
Standard

Machining of Composite Materials, Components and Structures
2015-04-15
CURRENT
AIR5367
This SAE Aerospace Information Report (AIR) provides information related to machining of composite materials, components and structures. This document is intended to supplement the machining processes and guidelines provided in OEM repair manuals and structural repair manuals. It is not intended to supersede the approved data provided in OEM repair documents.
Standard

Impregnation of Dry Fabric and Ply Lay-Up
2023-08-14
CURRENT
ARP5319
This SAE Aerospace Recommended Practice (ARP) describes and gives general guidelines on use and applicability of standard methods for impregnating dry fabric and lay-up of the impregnated plies. The methods of impregnating dry fabric and ply lay-up described in this document have specific application and are not interchangeable. The methods should only be used when specified in an approved repair procedure or with the agreement of the Original Equipment Manufacturer (OEM) or regulatory authority.
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.
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