An aircraft landing gear shock absorber assembly (200) comprising: an outer casing (204) having a bore (203) which extends through the outer casing, the bore having a first opening (203a) and a second opening (203b); a rod (202) slidably coupled within the bore such that a first end (202a) of the rod projects out of the first opening of the bore, the first end of the rod being arranged to be attached to a wheel assembly; a closure (220) for the second opening of the bore; wherein the bore comprises a reduced width portion (210) relative to the second opening of the bore; and the rod includes a radially enlarged portion (212) that is wider than the reduced width portion of the bore;


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    Titel :

    AIRCRAFT LANDING GEAR SHOCK ABSORBER ASSEMBLY


    Weitere Titelangaben:

    FLUGZEUGFAHRWERKSTOSSDÄMPFERANORDNUNG
    ENSEMBLE AMORTISSEUR DE CHOCS DE TRAIN D'ATTERRISSAGE D'AVION


    Beteiligte:

    Erscheinungsdatum :

    04.10.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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