An aircraft fuel storage structure cover 10 has an inlet port 30a and outlet port 30b. The inlet is configured to interface with, and receive fuel from, aircraft refuelling apparatus (fig.1,90), and is connected to the outlet providing fuel into a fuel tank 110 when the cover is over an access port or manhole 5; the manhole allowing a human operator to access tank interior when the cover is removed. Preferably, a variable volume reinforced flurosilicone bladder (fig.5b,120) is coupled to the cover and inserted in a collapsed state through the manhole, the tank being a first wing fuel tank occupying a first rib bay, adjacent a second wing tank (fig.7,114), in a second rib bay, in which the bladder is housed when the cover is on the manhole. A pipe (fig.7,165) may connect the outlet to the bladder for refuelling. The cover may have two panels which attach together clamping a surface 115 of the fuel storage structure; the inlet and outlet may be located on the first panel 11, the outlet revived in an opening 40 in the second panel 12. The inlet and outlet can drain fluid to outside the fuel storage structure.


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    Titel :

    Aircraft access cover


    Beteiligte:
    HENRY EDWARDS (Autor:in)

    Erscheinungsdatum :

    27.11.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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