A blade-fold bushing system includes a splined bushing comprising a first plurality of teeth, a castellated bushing comprising a second plurality of teeth and a shaft portion configured to coaxially fit within the splined bushing, and a lock bushing coaxially aligned with the castellated bushing. A support tool for use with a blade-fold bushing system includes an outer head comprising a third plurality of teeth configured to mesh with the first plurality of teeth of the splined bushing, and an inner head comprising a fourth plurality of teeth configured to mesh with the second plurality of teeth of the castellated bushing.


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    Titel :

    SEMI-AUTOMATIC ROTOR BLADE FOLD MECHANISM


    Beteiligte:
    SHUNDO KEN (Autor:in) / SHIMEK GLENN ALAN (Autor:in)

    Erscheinungsdatum :

    2019-12-19


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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