An actuator failure or disconnection detection device for an aircraft leading edge slat comprises a base and a biasing assembly mounted to the base and movable relative thereto. The base and biasing assembly are removably mountable between a fixed structure in the aircraft wing and the slat at an actuator location. The device further comprises an indicator for indicating the amount of movement of the biasing assembly in a direction towards the base when the slat is retracted towards the wing leading edge. The indicator may be a collar slidably mounted on the device.


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    Titel :

    WING SLAT ACTUATOR DISCONNECTION DETECTION


    Beteiligte:
    HUBBERSTEY MARK (Autor:in) / TIMMS MARK (Autor:in)

    Erscheinungsdatum :

    28.06.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / G07C TIME OR ATTENDANCE REGISTERS , Zeit- oder Anwesenheitskontrollgeräte



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