Disclosed is a sub-system (200) for an aircraft hydraulic system (20). The sub-system (200) comprises a first inlet (202) for receiving fluid from a supply (22) of hydraulic fluid, a system valve (210) for controlling fluid flow from the sub-system (200) to a hydraulically-operable system (24) of the aircraft hydraulic system (20), a check valve (220) for permitting fluid flow from the sub-system (200) and preventing or hindering fluid flow into the sub-system (200), a second inlet (240) for receiving fluid from a second supply (28) of hydraulic fluid, and a selector (230). The selector (230) configured to place the system valve (210) in fluid communication with the first inlet (202) when the selector (230) is in a first state, and to place the system valve (210) in fluid communication with the check valve (220) and the second inlet (240) when the selector (230) is in a second state different from the first state. Also disclosed is an aircraft hydraulic system (20), a method (300) to help maintain fluid pressure in a sub-system of an aircraft hydraulic system, and an aircraft (400).


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    Title :

    AIRCRAFT HYDRAULIC SYSTEM


    Additional title:

    FLUGZEUGHYDRAULIKSYSTEM
    SYSTÈME HYDRAULIQUE D'AÉRONEF


    Contributors:

    Publication date :

    2022-08-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein



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