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.
REPAIR ASSEMBLY FOR AIRCRAFT STATIC PRESSURE PORT
01.06.2023
Patent
Elektronische Ressource
Englisch
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 |
Static pressure port errors in hyprsonic turbulent flow
AIAA | 1971
|Measurement of static pressure on aircraft
NTRS | 1958
|Measurement of static pressure on aircraft
TIBKAT | 1957
|Measurement of static pressure on aircraft
SLUB | 1959
|Measurement of Static Pressure on Aircraft
NTRS | 1957
|