A fault can be detected in an uplock 101 for an aircraft component, such as landing gear or a wingtip device, using an uplock with a hook 102, moving between open and closed positions, engaging a pin 126; an indicator system detects whether the pin is held within the closed hook, and alerts a possible fault if the pin is not present. The indicator system may have a biased lever 130 which is moved when the capture pin contacts it, with a proximity sensor detecting a sensor target 136 position. The indicator system may measure the resistance of a sensor wire (fig.14,1090) extending across the hook, the wire having two conductors (fig.14,1092a,1092b) insulated from each other; failure of the hook causes deformation of the wire, causing the two conductors to contact, altering the resistance. A biasing mechanism with two springs may be provided. One spring urges the hook to close, with a lock 108 to hold it closed; when the lock is disengaged the force of the pin moves the hook to open; beyond a predetermined point the second spring urges hook to open. A friction generator may be provided for resisting opening of the hook.


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    Titel :

    Aircraft uplock


    Beteiligte:
    TREVOR BRIGHTON (Autor:in) / MATTHEW GADD (Autor:in)

    Erscheinungsdatum :

    17.10.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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