A method for repairing a damaged aircraft fuselage outer skin part, the damaged skin part comprising a static pressure port around which is arranged a stopper fastened to a structure of the fuselage at which a pipe of the static pressure port opens, the method including removing the stopper from the static port, fitting a patch including an opening for housing the stopper, and re-fitting the stopper on an adjustable-thickness spacer. A repair assembly configured to apply the repair method is also provided. Advantageously, it is thus possible to recreate an aerodynamic profile in accordance with the requirements for taking static pressure of the aircraft, with a reduced down-time of the aircraft.


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    Titel :

    REPAIR ASSEMBLY FOR AIRCRAFT STATIC PRESSURE PORT


    Beteiligte:
    CHAUVEAU BRUNO (Autor:in) / COLLIN OLIVIER (Autor:in) / CHAUVET OLIVIER (Autor:in)

    Erscheinungsdatum :

    01.06.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B64C AEROPLANES , Flugzeuge / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen




    Measurement of static pressure on aircraft

    Gracey, William | NTRS | 1958


    Measurement of static pressure on aircraft

    Gracey, William | TIBKAT | 1957


    Measurement of static pressure on aircraft

    Gracey, William | SLUB | 1959


    Measurement of Static Pressure on Aircraft

    Gracey, William | NTRS | 1957