Carbon Fiber and Fiberglass Epoxy Prepreg Products with 350°F Cure for Aerospace Applications

Scope:

The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250°F for primary or secondary aircraft structures.

Rationale:

Widely distributed and available industry material specifications are required for procurement of composite materials whose allowables data is published in CMH-17.

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