A throttle control lever (2) suitable for controlling the magnitude and direction of thrust of one or more aircraft engines is described. The throttle control lever (2) comprises a frame (4), a trigger mechanism (6), a connection element (8), a cam engagement mechanism (10), a biasing means (12), a cam (14), and a grip (52) suitable for gripping by a user when the throttle control lever (2) is in use, The cam (14) comprises a slot (16) having first and second slot portions (18, 20) and a stop portion (22). The stop portion (22) extends between and connects the first and second slot portions (18, 20). The cam engagement mechanism (10) comprises a cam lever (34) and a slot engagement element (36), the cam lever (34) is pivotally attached to the frame (4) via a cam lever pivot (38), and the slot engagement element (36) is attached to the cam lever (34). The trigger mechanism (6) comprises a trigger lever (46) and a trigger (48), the trigger lever (46) is pivotally attached to the frame (4) via a trigger pivot (50). The trigger (48) extends through the grip (52). The connection element (8) is attached to the trigger lever (46) and the cam lever (34). The biasing means (12) biases the cam lever (34) to rotate in a first direction around the cam lever pivot (38).


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    Title :

    THROTTLE CONTROL LEVERS


    Additional title:

    DROSSELKLAPPENSTEUERHEBEL
    LEVIERS DE COMMANDE DE PAPILLON


    Contributors:

    Publication date :

    2023-11-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G05G CONTROL DEVICES OR SYSTEMS INSOFAR AS CHARACTERISED BY MECHANICAL FEATURES ONLY , Steuer- oder Regelvorrichtungen oder Steuer- oder Regelsysteme gekennzeichnet ausschließlich durch mechanische Einzelheiten



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