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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

Maintenance Life Cycle Cost Model

2010-03-22
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

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

2006-01-26
HISTORICAL
AMS2980/5
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.
Standard

Composite and Bonded Structure Inspector: Training Document

1999-03-01
CURRENT
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 and Bonded Structure Engineers: Training Document

1999-03-01
CURRENT
AIR5278
This document provides recommendations concerning the minimum knowledge and analytical skill guidelines for a composite and metal bond repair design engineer. Teaching levels have been assigned to this curriculum to define the knowledge, skills and abilities needed to design appropriate 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

MASKING AND CLEANING OF EPOXY AND POLYESTER MATRIX THERMOSETTING COMPOSITE MATERIALS

1997-03-01
CURRENT
ARP4916
This SAE Aerospace Recommended Practice (ARP) describes methods of masking and cleaning commercial aircraft, epoxy and polyester matrix, composite parts prior to their entry into the composites shop, masking and cleaning of on-wing repair areas in preparation for carrying out repairs and wipe cleaning during repair and prior to bonding. If this document is used for the masking or cleaning of materials other than epoxy and polyester matrix thermosetting composite materials, the fitness for this purpose must be determined by the user. The methods of masking and cleaning described in this document have specific limited application and are not interchangeable. 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.
Standard

COMPOSITE REPAIR NDT/NDI HANDBOOK

1996-11-01
CURRENT
ARP5089
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.
Standard

DRYING OF THERMOSETTING COMPOSITE MATERIALS

1996-08-01
CURRENT
ARP4977
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.
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