This report presents a detailed description of the flightworthy graphite fiber reinforced composite aircraft primary structural assemblies program. The following tasks were completed: Component selection and preliminary design; materials development; test and quality control procedures development; design allowables and criteria; design allowables testing; and analysis procedure assessment and definition. Demonstration items selected were the F-5A supersonic fighter main landing gear strut door, speed brake, wing leading edge flap, wing trailing edge flap, horizontal stabilizer, and vertical stabilizer main spar. (P.S.-PL)


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