Patent ID: 8800277
Filing Date: 2014-08-12
Classification: F15B

Abstract:
1. An aircraft hydraulic system comprising: two independent hydraulic circuits, with each of said circuits being supplied by at least two pumps respectively, wherein each of said pumps associated with a same one of said circuits is driven by a different propulsion engine, and further wherein one of said two independent hydraulic circuits supplies hydraulic power to a set of consuming units, and the other of said two independent hydraulic circuit supplies hydraulic power to the same set of consuming units; wherein for each of said independent circuits: and further wherein the at least one suction line and the at least one HP discharge line each comprise at least one pressure sensor respectively, able to deliver a signal characteristic of a hydraulic fluid pressure value in the line under consideration between the pump and the cut-out valve, respectively between the pump and the check valve, and wherein the hydraulic circuit comprises a control system for the cut-out valve that: