Airbus Operations Gmbh

Phillip Teague

Arnaud Didey

Fraser Wilson

Stephen P Briancourt

Martin Geoffrey Warren

A drive system for an aircraft landing gear is described. The drive system includes a drive pinion, a drive shaft arranged to rotate the drive pinion about a drive axis, and a casing which rotatably supports the drive shaft. The drive pinion is rotatably supported on the casing by a self-aligning bearing. The drive pinion is coupled to the drive shaft by a flexible coupling adapted to transfer torque between the drive pinion and the drive shaft and to permit tilting of the drive pinion relative to the drive axis.

Drive system for aircraft landing gear

A fastener assembly for attaching a component or bracket to the inner surface of the skin of an aircraft wing is disclosed. The fastener assembly comprises a bolt having a shaft and a bolt retaining member that threadingly cooperates with the shaft to retain the bolt in a position in which it extends through a hole in the skin. The fastener also includes a component or bracket retaining member that also threadingly cooperates with a portion of the shaft protruding through said bolt retaining member to attach a component or bracket to said inner surface.

Fastener assembly

A system for detecting misalignment of an aero surface relative to other aero surfaces during simultaneous deployment of the aero surfaces is disclosed. A generator configured to shine a laser through aligned apertures in a series of aero surfaces towards a reflector during deployment of the aero surfaces, a receptor to detect reflection of the laser from the reflector back through the apertures to the generator and, a controller operable to terminate further deployment of the aero surfaces in the event that no reflection is detected by the receptor, or if an actual time taken for the reflected beam of light to be detected by the receptor differs from a predetermined time.

System for detecting misalignment of an aero surface

An electrical connector for providing electrical communication between a fixed structure of an aircraft and a movable component mechanically connected to the fixed structure, wherein the electrical connector is arranged to be mechanically connected to the fixed structure at a first end of the connector and is arranged to be mechanically connected to the movable component at a second end of the connector, the electrical connector comprising a first telescopic element, at least a portion of which is electrically conductive and which is arranged to provide a first current path between the fixed structure and the movable component.

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Bristol, United Kingdom

Phillip Teague