A system for mounting a gas turbine engine (10) to a pylon (50) on a wing of an aircraft. At least one temporary forward link (68), being length-adjustable, and at least one temporary rearward link (100, 101), being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine (10) to the pylon (50). The temporary forward link (68) and the temporary rearward link(s) (100, 101) each comprise a respective winch (73, 106) operable to adjust pay out of a respective tension member (72, 110) thereby to provide length adjustment. The temporary forward link (68) and the temporary rearward link(s) (100, 101) maintain a positional relationship between the gas turbine engine (10) and the pylon (50) in the absence of adjustment of the lengths of the temporary forward link (68) and the temporary rearward link(s) (100, 101). Adjustment of the length of the temporary links brings engine mounts (64, 66) into alignment with pylon mounts (60, 62) for service attachment of the gas turbine engine (10) to the pylon (50).


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    Titel :

    Mounting System and Mounting Method for Gas Turbine Aero Engine


    Erscheinungsdatum :

    11.07.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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