A mounting arrangement for mounting an aircraft gas turbine engine to an aircraft includes an engine nacelle with a distal assembly including a part annular engine cowl, a gas turbine engine core housing surrounded by the cowl and a distal bifurcation extending between the engine core housing and engine cowl in a first direction to define a first axis. The mounting arrangement includes a proximal assembly having a mount configured to mount the proximal assembly to the engine core housing. The proximal assembly includes a pylon configured to mount the proximal assembly to mounting location such as a wing of the aircraft at an engine mounting location. The pylon extends in a line between the wing and the engine core housing to define a second axis which is normal to a distal surface of the wing at the engine mounting location and is non-parallel to the vertical axis.


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    Title :

    GAS TURBINE ENGINE MOUNT ARRANGEMENT


    Contributors:

    Publication date :

    2020-01-23


    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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