Airbus Operations Gmbh

Nebojsa Sakota

Philip Henry Garland

Norman Wijker

An aircraft is disclosed including a fuel tank for storing liquid hydrogen, an aircraft power plant and/or an aircraft refuelling port, and a hydrogen fuel line extending from a first end to a second end, the first end at the fuel tank and the second end at one of the aircraft power plant and the aircraft refuelling port. The hydrogen fuel line is rigidly continuous and substantially unconstrained along an axial direction of the hydrogen fuel line between the first end and the second end. The first and/or second end is moveable in the axial direction of the hydrogen fuel line.

Aircraft

An aircraft assembly is disclosed including an aircraft panel, a channel attached to the aircraft panel, a fuel line for carrying cryogenic fuel, the fuel line disposed in the channel, and a sealed containment space around the fuel line for containing cryogenic fuel leaked from the fuel line, the containment space defined between the channel, the fuel pipe, and the aircraft panel.

Aircraft assembly

A landing gear is disclosed having a main strut connected at one end to an aircraft via a main joint is disclosed. The landing gear further includes an inboard sidestay assembly connected to the main strut. The inboard sidestay assembly includes a forward stay connected at one end to the aircraft, a rear stay connected at one end to the fuselage, and a shear web extending between the forward stay and the rear stay and configured to resist movement of the forward stay relative to the rear stay. The landing gear is arranged such that when the landing gear is extended substantially all the landing gear loads are transferred from the landing gear to the aircraft via one or more of the main joint, the forward stay and the rear stay.

Landing gear

The invention provides a deployment mechanismfor deploying an auxiliary wing surface devicefrom an aircraft wing body, the deployment mechanism providing a first connector portionfor connecting the deployment mechanism to the aircraft wing body, a second connector portionfor connecting the deployment mechanism to the auxiliary wing surface device, and a telescopic rodlinking the first and second connector portions, the telescopic rod comprising an inner rodextendable from inside of an outer rodto increase the length of the telescopic rod, such that the distance between the first and second connector portions can be increased. The invention also provides an aircraft wing, an aircraft and a method of operating an aircraft.

Deployment mechanism

A method of removing a component from an aircraft includes attaching a device comprising a guide member to the aircraft; attaching the component (such as an actuator) to the guide member; detaching the component from the rest of the aircraft; and moving the guide member so that the component follows a predefined path of removal of the component. A device for use in such a method is also described.

Removal of components from aircraft

A device for facilitating the removal of a component from an aircraft includes a mounting member, a guide member and a handle. The mounting member provides an attachment portion for attaching the device to the aircraft. The guide member includes a support portion for receipt of the component to be removed and is pivotally mounted to the mounting member so that, when the component is being supported by the support portion in use, the support portion moves pivotally away from the aircraft along a predefined path. The handle is operatively associated with the guide member for assisting in the pivotal movement of the guide member.

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Bristol, United Kingdom

Nebojsa Sakota