A method of removing hydraulic fluid from an aircraft hydraulic system is disclosed including a hydraulically actuated mechanism that is actuated by an electrohydraulic servo valve, a hydraulic fluid port through which hydraulic fluid can escape, and a hydraulic fuse with a closed state and an open state between the electrohydraulic servo valve and the hydraulic fluid port. The hydraulic fluid port is opened, and then the activation of the electrohydraulic servo valve is controlled to force hydraulic fluid to escape from the hydraulic system via the hydraulic fluid port, the control being so that the hydraulic fuse does not enter and remain in the closed state.
A METHOD OF REMOVING HYDRAULIC FLUID FROM AN AIRCRAFT HYDRAULIC SYSTEM, AN AIRCRAFT HYDRAULIC SYSTEM, AND AN AIRCRAFT
VERFAHREN ZUR ENTFERNUNG EINER HYDRAULIKFLÜSSIGKEIT AUS EINEM FLUGZEUGHYDRAULIKSYSTEM, FLUGZEUGHYDRAULIKSYSTEM UND FLUGZEUG
PROCÉDÉ D'ÉLIMINATION DE FLUIDE HYDRAULIQUE D'UN SYSTÈME HYDRAULIQUE D'AÉRONEF, SYSTÈME HYDRAULIQUE D'AÉRONEF ET AÉRONEF
2024-04-17
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 |
European Patent Office | 2024
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