Abstract: An aircraft wing assembly including a wing having a main body 5 and a movable portion 6, so that the wing may be folded when taxiing. A lighting system is provided with a light source 9; a light emitter 11 arranged on one of the main body and the movable portion, and a light guide 10 arranged to transmit light from the light source along a path between the main body and the movable portion to the light emitter. The provision of a light guide between the light source and the emitter allows for light to be transmitted to the emitter across the joint 8 between the wing main body and the movable portion. Thus, lighting on the wing may be provided without the need to provide electrical wiring across the joint. A single light source 9 may be employed to illuminate multiple light emitters 11, 13 on the wing.

Abstract: An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). An external strut (9) extends between the wing (1) and the wing tip device (3), the strut (9) being joined to the wing (1) at a second connection (13). The second connection (13) is inboard of the first connection, such that loadings on the wing tip device (3) generated during use, are transferred, via the strut (9), to a location on the wing (1) that is inboard of where the root (7) of the wing tip device (3) is joined to the tip of the wing.

Abstract: An aircraft wing assembly including a wing having a main body 5 and a movable portion 6, so that the wing may be folded when taxiing. A lighting system is provided with a light source 9; a light emitter 11 arranged on one of the main body and the movable portion, and a light guide 10 arranged to transmit light from the light source along a path between the main body and the movable portion to the light emitter. The provision of a light guide between the light source and the emitter allows for light to be transmitted to the emitter across the joint 8 between the wing main body and the movable portion. Thus, lighting on the wing may be provided without the need to provide electrical wiring across the joint. A single light source 9 may be employed to illuminate multiple light emitters 11, 13 on the wing.

Abstract: Sustained ground contact of an aircraft is determined by detecting a change in a mechanical vibration characteristic of a part of the aircraft. Apparatus for determining sustained ground contact of an aircraft includes an analyser [300] for analysing aircraft vibration signals and a trigger [310] for triggering occurrence of sustained ground contact to an aircraft control system [315] when the analyser [300] detects sustained ground contact.

Abstract: An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). An external strut (9) extends between the wing (1) and the wing tip device (3), the strut (9) being joined to the wing (1) at a second connection (13). The second connection (13) is inboard of the first connection, such that loadings on the wing tip device (3) generated during use, are transferred, via the strut (9), to a location on the wing (1) that is inboard of where the root (7) of the wing tip device (3) is joined to the tip of the wing.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flamer barrier means, when refueling.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with a compact vent pipe comprising one or more built-in flame barrier elements providing high liquid fuel outflow rate.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT).

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear.

Abstract: A vent pipe is disclosed for use in the vent tank of an aircraft fuel system. The vent pipe is arranged with guide vanes or corner cascades for assisting the flow of fluid around the corners.

Abstract: A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT).

Abstract: An aircraft insulation apparatus is disclosed having a variable thermal insulating member adjacent the inner fuselage wall and adjacent an aircraft heat source. The variable thermal insulating member is operable to provide variable thermal insulation between the heat source and the exterior of the inner fuselage wall by being changeable between a first state and a second state, the first state providing a first level of thermal insulation and the second state providing a second level of thermal insulation.

Abstract: A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT).

Abstract: An aircraft fuselage interior comprises a side wall that extends in a direction along the length of the fuselage and includes an upper section that slopes inwardly. In one embodiment, the side wall comprises a multiplicity of visible elongate features, such as sloping lines, arranged along the length of the side wall. Each elongate feature extends from a lower portion to an upper portion and slopes relative to a notional line defined by the intersection of the interior surface of the side wall and a plane whose normal axis is parallel to the length of the fuselage. When viewed by a seated passenger, the sloping elongate features may cause the side wall to appear to have a degree of inward sloping less than the actual degree of inward sloping. The fuselage interior may therefore appear larger than it is.

Abstract: The invention relates to an aircraft toilet facility, particularly an aircraft toilet facility on a single passenger-deck aircraft. The invention provides a first toilet unit situated at least partially in the space below the floor of a passenger deck of the aircraft, and a second toilet unit situated at least partially in the space above the ceiling of the passenger deck. The first toilet unit is proximate the second toilet unit, and both the first toilet unit and second toilet unit are accessible from the passenger deck.