Abstract: A joint assembly for joining a first aircraft structural component to a second aircraft structural component. The joint assembly has a double eccentric bush for mounting to one of the first and second aircraft structural components, and a spigot mounted on the double eccentric bush. Rotating elements of the double eccentric bush enable adjustment of the spigot relative to the respective aircraft structural component in two orthogonal directions normal to a longitudinal axis of the spigot prior to joining the first aircraft structural component to the second aircraft structural component. A spigot receptacle is provided for mounting to, or is integrally formed with, the other of the first and second aircraft structural components. The spigot receptacle is arranged to receive the spigot. At least one fastener joins the first and second aircraft structural components together when the spigot is received in the spigot receptacle.

Abstract: A wing structure is disclosed having a first span portion including a depth that reduces in a spanwise outward direction, and a second span portion outboard of the first span portion and having a substantially uniform spanwise depth D3. The second span portion may be non-tapered, and may include parallel fore and aft spar portions. In some embodiments the non-tapered portion supports a movable wing tip device. A wing assembly and an aircraft are also disclosed.

Abstract: A wing assembly for an aircraft has a wing, a moveable wing tip device and an actuation assembly to move the wing tip device. The actuation assembly is disposed externally of the wing assembly. In a further aspect, the actuation assembly has a first connector member connected externally of the wing assembly at the actuator and pivotably connected at a lower portion of the wing or wing tip. This can facilitate the provision of effective internal supporting structure for transferring flight loads across the interface of the wing and wing tip device, especially in wing assemblies having a high aspect ratio. In a still further aspect, the wing assembly has a seal extending chordwise within the wing assembly, for resisting passage of air through an interface region between the wing and the wing tip device.

Abstract: A wing assembly for an aircraft is disclosed having an actuation assembly configured to move a wing tip device between a flight configuration and a ground configuration. The actuation assembly includes at least two linear actuation devices mounted within the wing assembly. A wing and a wing tip device for the wing assembly, and an aircraft comprising the wing assembly, wing or wing tip, are also disclosed.

Abstract: Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.

Abstract: Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.

Abstract: Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.

Abstract: A wing structure is disclosed having a first span portion including a depth that reduces in a spanwise outward direction, and a second span portion outboard of the first span portion and having a substantially uniform spanwise depth D3. The second span portion may be non-tapered, and may include parallel fore and aft spar portions. In some embodiments the non-tapered portion supports a movable wing tip device. A wing assembly and an aircraft are also disclosed.

Abstract: A wing assembly for an aircraft is disclosed having an actuation assembly configured to move a wing tip device between a flight configuration and a ground configuration. The actuation assembly includes at least two linear actuation devices mounted within the wing assembly. A wing and a wing tip device for the wing assembly, and an aircraft comprising the wing assembly, wing or wing tip, are also disclosed.

Abstract: A wing assembly for an aircraft has a wing, a moveable wing tip device and an actuation assembly to move the wing tip device. The actuation assembly is disposed externally of the wing assembly. In a further aspect, the actuation assembly has a first connector member connected externally of the wing assembly at the actuator and pivotably connected at a lower portion of the wing or wing tip. This can facilitate the provision of effective internal supporting structure for transferring flight loads across the interface of the wing and wing tip device, especially in wing assemblies having a high aspect ratio. In a still further aspect, the wing assembly has a seal extending chordwise within the wing assembly, for resisting passage of air through an interface region between the wing and the wing tip device.

Abstract: Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.