Landing gear systems and methods of testing
AssigneeAirbus Operations GmbH
InventorSean Kerr
Life of this patent
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Abstract
A method of extending a landing gear of an aircraft is disclosed. The aircraft includes an uplock arranged to retain the landing gear in a retracted position, a primary landing gear system configured to retract and extend the landing gear, and an alternate landing gear system, independent from the primary landing gear system. The method includes the primary landing gear system holding the landing gear in place while the uplock is moved from a first configuration to a second configuration by the alternate landing gear system.
Claims15
A method of extending a landing gear of an aircraft, the aircraft comprising:
- an uplock arranged to retain the landing gear in a retracted position,
- a primary landing gear system having a main actuator configured to retract and extend the landing gear, and
- an alternate landing gear system, independent from the primary landing gear system,
- wherein the alternate landing gear system comprises an actuator arranged to move the uplock between a first configuration and a second configuration,
- wherein the method comprises the main actuator of the primary landing gear system holding the landing gear in place while the uplock is moved from the first configuration to the second configuration by the actuator of the alternate landing gear system.
A method of testing a landing gear system in an aircraft, the aircraft comprising:
- an uplock arranged to retain the landing gear in a retracted position;
- a primary landing gear system having a main actuator configured to extend and retract the landing gear;
- and
- an alternate landing gear system, independent of the primary landing gear system,
- wherein the alternate landing gear system comprises an actuator arranged to move the uplock between a first configuration and a second configuration,
- wherein the method comprises the alternate landing gear system moving the uplock from the first configuration to the second configuration while the landing gear is extended and the aircraft is on the ground.
Dependencies are inferred from the claim text.