Airbus Operations Gmbh

Bae Systems, Inc.

Trevor Anthony Brighton

Matthew Gadd

Robert Ian Thompson

Martin Rowlands

Maxwell William Jones

Graham King

Martin Griffith Rowlands

Martin John Elms

Oliver McCambridge

Oliver Mccambridge

Maxwell Jones

An uplock for use with an aircraft landing gear is disclosed having a hook configured to engage a capture pin mounted on the landing gear. The hook is mounted for movement between a closed and locked position and an open and unlocked position. A proximity detector directly detects whether the pin is 'up'. An uplock hook sensor detects when the hook is in the closed and locked position. The outputs of the proximity detector and the uplock hook sensor may be used to indicate the 'up and locked' condition, i.e., landing gear up, and/or to indicate a fault. Such outputs may be provided by an associated device of an avionics system.

Aircraft landing gear uplock system

An uplock is disclosed including a hook configured to engage a capture pin mounted on an aircraft component. The hook is mounted for movement between a closed position and an open position. The uplock further includes an indicator system configured to detect whether a pin is engaged with the hook when the hook is in the closed position.

Aircraft uplock

A control system has first and second processing modules for controlling retraction and extension of an aircraft landing gear assembly. The processing modules operate independently providing redundancy. Each processing module is configured to perform a first sequence of steps for retracting the landing gear assembly and a second sequence of steps for extending the landing gear assembly. A step of switching control from one processing module to the other (e.g. an avionics side changeover step) is performed (a) as part of the first sequence of steps, but only after the landing gear assembly has been retracted, or (b) as part of the second sequence of steps. By ensuring that the step of switching control is performed at such times, and not for example between initiation of the first sequence of steps and the retraction of the landing gear assembly, the landing gear assembly may be retracted sooner after such initiation.

Control system and method for landing gear extension/retraction

In the retracted position, aircraft landing gear of an aircraft is supported by an uplock hook. The deployment of the aircraft landing gear includes the steps of supporting at least part of the weight of the landing gear by a releasable catch in the form of an uplock hook, applying a lifting force to the landing gear to remove at least part of the load sustained by the releasable catch, releasing the catch and effecting the downward movement of the landing gear to the deployed position.

Landing gear

An aircraft undercarriage mechanism,comprising a first lock member,mounted on the undercarriage,, the first lock member being engageable with a second lock member,mounted on a wing,of the aircraft. The first lock member,comprises a pivotable arm,which carries a roller,. The roller,is rotatable and slidable on the arm,and is engageable with a catch,on the second lock member,. The provision of the pivotable arm,and slidable roller,permits relative movement between the lock members,when the undercarriage,is retracted with the lock members interengaged to minimise transmission of forces created by wing deflection from one lock member to the other.

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Bristol, United Kingdom

Trevor Anthony Brighton