Airbus Operations Gmbh

Antony Charles Peacock

Paul James Edwards

Ross Salisbury

Timothy J Sanderson

Phillip Scott

Christopher Payne

Geoffrey Richard Williams

Raymond Bullock

Peter Griggs

Glenn Watson

Jonathan Paisley

Timothy Sanderson

Paul Edwards

An aircraft engine nacelle for coupling to a wing of an aircraft is disclosed having a fore end, and an aft end that is immoveable relative to the fore end. The aft end includes a major axis Mj and a minor axis Mi, and the nacelle is configured such the minor axis Mi is closer to vertical V than the major axis Mj when the nacelle is coupled to the wing and the aircraft is stationary on the ground. An aircraft system and an aircraft are disclosed each including the aircraft engine nacelle.

Aircraft engine nacelle with an aft end major axis substantially parallel to the leading edge of a wing

An aircraft wing box is disclosed having a first cover, a second cover, a partition extending between the first and second cover and configured to provide a fuel tight boundary between the first and second covers, a first joint coupling the partition to the first cover, and a second joint coupling the partition to the second cover. The first joint is a slip joint configured to inhibit fuel leakage across the slip joint whilst permitting relative movement between the partition and the first cover.

Aircraft wing box

An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.

A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.

Aircraft fuel tank aperture sealing

Seal plates are typically mounted over stringer-receiving openings in aircraft ribs. A sealing tool for sealing a stringer-receiving opening in an aircraft rib is disclosed. The sealing tool includes a seal member arranged to seal a gap formed by the opening between the stringer and the rib. An intermediate member is configured to be adjustably mounted on the rib. The adjustable member receives and aligns the seal member over the gap.

Sealing tool for sealing an opening in an aircraft rib

An assembly apparatus for forming an interfay joint during manufacture of an aircraft (). The assembly apparatus includes an assembly jig () to hold a first joint component (), and an applicator () configured to apply an uncured layer of shim to the first joint component. The assembly jig locates, subsequent to the uncured layer of shim being applied, a second joint component () in an assembled joint position spaced from the first joint component. As such the uncured layer of shim is compressed between the first and second joint components. A method of forming an interfay joint during manufacture of an aircraft, an interfay joint for an aircraft, an aircraft aerodynamic surface, an aircraft, and a shim layer applicator.

Assembly apparatus for forming an interfay joint during manufacture of an aircraft

An aircraft wing cover () comprising an integrally stiffened sandwich panel including first and second skins () sandwiching a core layer (), wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness () accommodated by corresponding regions () of decreased thickness in the core. Also, a method of fabricating an aircraft wing cover, and a method of designing an aircraft wing.

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Bristol, United Kingdom

Antony Charles Peacock