A method and apparatus for servicing a shock absorber (102) on a landing gear assembly (108; 110) of an aircraft (101) in a weight-on-wheels state is described. The shock absorber comprises at least one chamber (111) containing both hydraulic fluid (135) and a gas (121) in fluid communication with each other. Gas is exhausted from the chamber into a tank. Dissolved gas is degassed from the hydraulic fluid. The apparatus (250) comprises a source (gas cylinders 251; nitrogen delivery system 203) of gas and a source (201) of hydraulic fluid. The amount of hydraulic fluid in the chamber is corrected, preferably such that the chamber is then filled with a known amount of degassed hydraulic fluid. A single pre-set mass of gas may be created in the tank and then injected into the chamber by the gas delivery system (203). The process may be at least semi-automatically performed, for example under the control of a control unit (205). By delivering a pre-set mass of gas into the chamber, there is no need to rely on a measure of gas pressure or H-dimension (h) when servicing the shock absorber (102), and more accurate servicing of a shock absorber may thus be provided.
LANDING GEAR SHOCK ABSORBER SERVICING
FAHRWERKSTOSSDÄMPFERWARTUNG
MAINTENANCE D'AMORTISSEUR DE CHOCS DE TRAIN D'ATTERRISSAGE
2021-04-21
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / 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 / F16F SPRINGS , Federn / G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen |