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Carbon Fiber Fabric Repair Prepreg, 120 °C (250 °F) Vacuum Curing Part 1 - General Requirements
- Aerospace Material Specification
- AMS3970/1A
- Reaffirmed
Downloadable datasets available
Annotation ability available
Sector:
Issuing Committee:
Language:
English
Scope
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.
Rationale
AMS3970/1A has been reaffirmed to comply with the SAE five-year review policy.
Topic
Data Sets - Support Documents
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TABLE 1 | SIDE QUALIFICATION PROGRAM | |
TABLE 2 | FLUID TYPES FOR IMMERSION TESTING | |
TABLE 3 | STORAGE CONDITIONS AND TIMES FOR LAMINATE PANELS AND LAMINATE SPECIMENS | |
TABLE 4 | STORAGE CONDITIONS AND TIMES FOR SANDWICH PANELS AND SANDWICH SPECIMENS | |
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Issuing Committee
AMS CACRC Commercial Aircraft Composite Repair Committee
Scope: The charter of the ATA/IATA/SAE Commercial Aircraft Composite Repair Committee (CACRC) is to develop and improve maintenance, inspection and repair of commercial aircraft composite structure and components. The seven CACRC task groups are: Repair Materials, Repair Techniques, Analytical Repair Techniques, Design, Inspection, Training and Airline Inspection & Repair Conditions.
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