SAE AMS3970/6 PDF
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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
Description
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.
History
| AMS3970/6 | 2016-12-05 | Latest | Reaffirmed |
| ISSUING COMMITTEE | AMS CACRC Commercial Aircraft Composite Repair Committee |
|---|---|
| DATE | 2016-12-05 |
| DOI | |
| ISCURRENT | Current |
| PAGE | 24 |
| PUBLISHER | SAE International |
| REVISED | REAFFIRMED |
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