An actuator failure or disconnection detection device (20) for an aircraft leading edge slat (6) comprises a base (22) and a biasing assembly (24) mounted to the base (22) and movable relative thereto. The base (22) and biasing assembly (24) are removably mountable between a fixed structure (202) in the aircraft wing and the slat (6) at an actuator location. The device (20) further comprises an indicator (132) for indicating the amount of movement of the biasing assembly (24) in a direction towards the base (22) when the slat (6) is retracted towards the wing leading edge (4). The indicator (122) may be a collar (132) slidably mounted on the device (20).


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    Title :

    WING SLAT ACTUATOR DISCONNECTION DETECTION


    Additional title:

    DETECTION DE DESACCOUPLEMENT D'ACTIONNEUR DE BEC DE BORD D'ATTAQUE


    Contributors:

    Publication date :

    2018-06-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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