A device to engage with a steering mechanism of a nose landing gear of an aircraft to limit steering rotation of the nose landing gear. The device includes a first chock sized to fit within a first space formed in the nose landing gear at a first cylinder of a steering mechanism, and a second chock sized to fit within a second space formed in the nose landing gear at a second cylinder. The first chock is configured to engage with the first cylinder and to compress to prevent retraction of the first cylinder beyond a first predetermined length. The second chock is configured to engage with the second cylinder and to compress to prevent retraction of the second cylinder beyond a second predetermined length.


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    Title :

    Chock for Steering Mechanism of an Aircraft Nose Landing Gear


    Contributors:

    Publication date :

    2024-11-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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