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.
Fatigue Substantiation Procedures for General Aviation Aircraft Structures
Sae Technical Papers
National Business Aircraft Meeting and Engineering Display ; 1971
1971-02-01
Aufsatz (Konferenz)
Englisch
FAR 23 Fatigue Substantiation Procedures: GAMA Committee Report
SAE Technical Papers | 1971
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