Description is given of derivation of test loads and design of loading systems for fullscale fatigue test on CF-100 military aircraft; test procedure and events leading up to catastrophic failure of wing transport joint are also described; results show that dangerous cracks in wing transport joint may occur at lives in excess of 4000 service hr, and that catastrophic failure may occur at upwards of 4800 service hr; cracks that developed in vertical fin are not likely to occur prior to wing failure, but appropriate inspection techniques are available.


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    Title :

    Fatigue life of CF-100 aircraft


    Additional title:

    Canada. Nat Research Council -- Aeronautical Report


    Contributors:


    Publication date :

    1965


    Size :

    136 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English




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