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. The composite may be used for the manufacture of primary and secondary aircraft structure.
This is the basic spec and it will have three slash/detail specs.
Rationale: Widely distributed and available industry material specifications are required for procurement of composite materials whose allowables data is published in CMH-17.
