Patent ID: 9266606
Filing Date: 2016-02-23
CPC Classification: B64C

Claim Text:
1. An aircraft landing gear including: a main strut having an upper portion arranged to be coupled to an underside of an aircraft and a lower portion telescopically mounted with respect to the upper portion; a bogie including a bogie beam pivotally coupled to the lower portion of the main strut, the bogie beam having a plurality of axles mounted on it, each axle carrying one or more wheel assemblies; an actuator arranged such that a change in its effective length causes a change in the angular position of the bogie relative to the main strut, and a control port arranged to be coupled to a control fluid supply system, wherein the aircraft landing gear includes or is in combination with a control valve having a first configuration in which it permits control fluid to be supplied to the control port of the actuator at a first pressure and a second configuration in which the control valve permits the supply of control fluid to the control port at a second pressure less than the first pressure, the actuator being arranged such that its operating pressure is reduced when the control valve is in the second configuration so as to reduce loads experienced by components of the actuator during taxiing.