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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    Title :

    Fatigue Substantiation Procedures for General Aviation Aircraft Structures


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    National Business Aircraft Meeting and Engineering Display ; 1971



    Publication date :

    1971-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English