This invention relates generally to aircraft fuel tank structures, and more particularly to a secondary enclosure for an aircraft fuel tank configured to seal the tank against fuel vapor leakage into occupied aircraft compartments. In the observance of appropriate safety precautions and design criteria for aircraft fuel tanks, fuel carried within an occupied compartment of the aircraft must be enclosed in two separate (inner and outer) fuel vapor-tight containers, and the space between the two containers must be continuously drained and ventilated during flight. Certain high wing aircraft, such as the C17A, may have the center wing section within the fuselage configured to include an auxiliary fuel tank. In such instances, special safety precautions are taken in the structure of the aircraft to ensure that the center wing tank is designed to protect the aircraft occupants and cargo from contact with liquid fuel or fuel vapors. In this type of aircraft, it is desirable to enclose the entire wing box structure containing the center wing tank with a secondary enclosure separate from the tank structure itself.


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    Titel :

    Removable Secondary Aircraft Fuel Enclosure


    Beteiligte:
    D. L. Gibler (Autor:in)

    Erscheinungsdatum :

    1982


    Format / Umfang :

    17 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Removable Secondary Aircraft Fuel Enclosure

    D. L. Gibler / D. J. O'Connell | NTIS | 1982


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