Advanced Composites Prepreg – Nominal 250 °F Cure – Glass Fiber and Epoxy Resin, 7781 Weave Fabric
- Aerospace Material Specification
- AMS3915A
- Revised
Scope
Rationale
Recommended Content
| Aerospace Material Specification | Advanced Composites Prepreg - Nominal 250 °F Cure - Carbon Fiber and Epoxy Resin, Unidirectional Tape |
| Aerospace Material Specification | Advanced Composites Prepreg – Nominal 250 °F Cure – 12K Tow Carbon Fiber and Epoxy Resin, Plain Weave Fabric |
| Aerospace Material Specification | Carbon Fiber Fabric Repair Prepreg, 120 °C (250 °F) Vacuum Curing Part 0 - Introduction |
Topic
Data Sets - Support Documents
| Title | Description | Download |
|---|---|---|
| Unnamed Dataset 1 | ||
| Unnamed Dataset 2 | ||
| Unnamed Dataset 3 | ||
| Unnamed Dataset 4 | ||
| Table 1 | Uncured prepreg physical and chemical properties | |
| Table 2 | Cured lamina physical properties | |
| Table 3 | Cured lamina mechanical properties | |
| Unnamed Dataset 8 | ||
| Unnamed Dataset 9 | ||
| Table 4 | Test panel requirements |
Issuing Committee
AMS P17 Polymer Matrix Composites Committee
AMS P-17, Polymer Matrix Composites, is a technical committee in SAE’s Aerospace Materials Systems Group with the responsibility to develop and maintain material specifications and other SAE technical reports for composite materials, including prepregs, reinforcing fibers and fabrics, matrix resins, adhesives, and core materials. The committee works in conjunction with related bodies such as the Composite Materials Handbook -17 (CMH-17), ASTM Committee D30 on Composite Materials, the National Center for Advanced Materials Performance (NCAMP), the Performance Review Institute (PRI), and regulatory authorities such as FAA and EASA.