In order to reduce the size of the attachment means between a aircraft engine (10) and its attachment device, the invention provides an engine assembly (5) for which the primary structure (8) of the attachment device includes a central box (8a) and two movable structural cowls (8b). Further the means for attaching the engine on the structure (8) comprise a group of main ties laid out in a main transverse plane (P1) for absorbing forces crossing a front end of the movable structural cowls (8b), this group consisting of three main shearing pins (50', 50") radially oriented and distributed around a longitudinal axis (6) of the engine, each pin crossing a first shearing orifice (54) provided on a fitting (56) secured to the hub (16) of the intermediate case on the one hand, and a second shearing orifice (58) provided on one of the movable cowls (8b) or on its connecting structure to the central box on the other hand.


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    Titel :

    AIRCRAFT ENGINE ASSEMBLY, COMPRISING AN ENGINE ATTACHMENT DEVICE EQUIPPED WITH STRUCTURAL MOVABLE COWLS CONNECTED TO THE CENTRAL BOX


    Weitere Titelangaben:

    ASSEMBLAGE DE MOTEUR D'AERONEF COMPRENANT UN DISPOSITIF DE FIXATION DE MOTEUR EQUIPE DE COLS AMOVIBLES STRUCTURELS CONNECTES A LA BOITE CENTRALE


    Beteiligte:
    PAUTIS OLIVIER (Autor:in) / LAFONT LAURENT (Autor:in) / GOUGEON PASCAL (Autor:in)

    Erscheinungsdatum :

    23.08.2017


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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