Fatigue Substantiation Procedures for General Aviation Aircraft Structures 710404

Fatigue substantiation of wing structure on small airplanes is now required by the Federal Aviation Regulations for civil type certification of new designs. Methods for substantiation of this structure under the “safe-life” concept, including suggested loading spectra and procedures for strength determination are outlined. The background leading to these methods and a basis for establishing scatter factors are presented. Procedures for substantiation under the “fail-safe” concept are also given.


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