Patent ID: 7175134
Filing Date: 2007-02-13
Classification: B64C

Abstract:
1. A hydraulic system for steering a landing gear wheel of an aircraft and having a supply line carrying pressurized fluid from a source and a return line that conveys fluid to a reservoir, the hydraulic system comprising: a hydraulic motor operatively connected to turn the landing gear wheel and having first and second ports; a flow control valve arrangement having a first state in which fluid from the supply line is conveyed to the first port, a second state in which fluid from the supply line is conveyed to the second port, and a third state where the supply line is disconnected from the first port and the second port; and a damper having a bore with a piston slidably received therein thereby defining a first chamber and a second chamber in the bore on opposite sides of the piston, the second chamber is coupled to the second port, the damper including a first orifice coupling the first chamber to the first port, wherein the piston moves within the bore uninfluenced by any fastening external to the bore.