The invention relates to a locking mechanism for a cargo door in a fuselage cell of an aircraft. The cargo door is attached by a hinge in the area of a recess to open outwards. The locking mechanism comprises inter alia a number of fuselage cell fitments which are disposed in the area of a loading edge of the cargo door, and a corresponding number of cargo door fitments which are fixed in the area of a lower edge of the cargo door. In accordance with the invention the cargo door fitments can be brought into positive locking engagement in at least some areas with the fuselage cell fitments and the peripheral loads arising inside the fuselage cell which cause the main stress on the locking mechanism and which consequently form the basis for the dimensions are transferred substantially by a preferably flat load transfer surface, whilst the generally smaller radial loads are taken up substantially only by the sliding element. The locking of the cargo door is carried out by a movable sliding element which can be secured against accidental displacement by means of an optional security bar. Even in the event of the sliding element breaking, the cargo door remains fully secured against uncontrolled opening.


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    Titel :

    LOCKING MECHANISM FOR A CARGO DOOR IN AN AIRCRAFT


    Weitere Titelangaben:

    MECANISME DE VERROUILLAGE POUR UNE PORTE DE SOUTE D'UN AERONEF


    Beteiligte:
    RISCH RONALD (Autor:in)

    Erscheinungsdatum :

    01.12.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    E05C Riegel oder Feststellvorrichtungen für Flügel, insbesondere für Türen oder Fenster , BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS / B64C AEROPLANES , Flugzeuge



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