A mounting arrangement for attaching a gas turbine engine (10 see fig 1) to an aircraft is provided that has a mounting bracket 110 having fixing holes. The fixing holes are arranged in two sets either side of the centreline AA of the bracket 110. Each set of fixing holes has two outer fixing holes 112 and an intermediate fixing hole 114. The intermediate fixing hole 114 is further from the bracket centreline AA than the outer fixing holes 112 and is typically larger. Further intermediate holes and a complementary mounting block (140 see fig 5) may also be provided. The invention is at least aimed at providing for failsafe, reliable and weight minimised mounting of a gas turbine engine.


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    Titel :

    Gas Turbine Engine Mounting Arrangement


    Beteiligte:

    Erscheinungsdatum :

    06.04.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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