The invention discloses an operating control system for an aircraft engine. The operating control system comprises an electromagnetic flight idle lock controlled by a wheel load switch of an aircraft landing gear, wherein the electromagnetic flight idle lock is also in electric signal connection with a wheel speed controlling box; the wheel speed controlling box extracts wheel speed signals of the aircraft landing gear; when any of the wheel speed signals reaches a set value, the wheel speed controlling box outputs a signal, and the signal controls the switching on of the power supply circuit of the electromagnetic flight idle lock.


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    Title :

    Operating control system for aircraft engine


    Contributors:
    YAN DONG (author) / YAN JUN (author) / TIAN SHIXIONG (author)

    Publication date :

    2015-09-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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