Abstract: An aircraft wing assembly with a fixed wing and a wing tip device are disclosed. The wing tip device is moveable between a flight configuration and a ground configuration. In the ground configuration the span of the aircraft wing assembly is reduced. The fixed wing includes a fixed wing lug and the wing tip device comprises a wing tip lug. A locking pin is provided. In the flight configuration the fixed wing lug and wing tip device lug are aligned such that the locking pin may be inserted through the fixed wing lug and wing tip device lug into a locking position to lock the wing tip device in the flight configuration. The locking pin is hollow and includes a heating element.

Abstract: A wing hinge assembly is disclosed a wing tip fitting pivotally mounted to a fixed wing fitting. The wing tip fitting is rotatable about a hinge axis (H) with respect to the fixed wing fitting. One of the wing tip fittings and the fixed wing fitting defines a locking channel. The other of the wing tip fitting and the fixed wing fitting includes a locking member which defines a locking member axis. The wing hinge assembly is configurable to a locked configuration in which the locking member is received in the locking channel by moving the locking member in a direction perpendicular to the locking member axis.

Abstract: A latch mechanism for locking an aircraft folding wing is disclosed including at least one lug having an aperture and a latch pin moveable within the aperture between a latched configuration in which the latch pin is received in the aperture, and an unlatched configuration in which the latch pin is withdrawn from the aperture. At least part of one of the pin and the aperture has a hydrophobic coating. A hydrophobic coating may be applied to all apertures in the mechanism and/or to the latch pin. The provision of a hydrophobic coating helps to prevent the formation of moisture and hence ice on the latch pin and/or in the aperture, which ice can inhibit the pin from moving along the aperture into and out of its latching position.

Abstract: An aircraft wing assembly (31) is disclosed. The aircraft wing assembly (31) comprises a wing tip device (11) rotatable about a hinge axis (H) between a flight configuration and a ground configuration and a wing tip device actuation system (20) comprising a bell crank (21) and a linear actuator (23). The bell crank (21) is rotatably mounted to the aircraft wing assembly (31) and is rotatable about a bell crank axis (C) which is offset from the hinge axis (H). The linear actuator (23) is operable to rotate the bell crank (21) about the bell crank axis (C) to thereby move the wing tip device (11) about the hinge axis (H), between the flight configuration and the ground configuration.

Abstract: A compliant mount for an aircraft, for attaching equipment (such as a latching unit, for example) to a structural member of the aircraft, the compliant mount comprising: a mounting member for attachment to the structural member of the aircraft; a receptacle for supporting the equipment, the receptacle being coupled to the mounting member along a longitudinal axis; and one or more spring elements arranged to resiliently bias the receptacle into alignment with the longitudinal axis and to allow angular movement of the receptacle away from the longitudinal axis. Also provided is an aircraft equipment assembly comprising such a compliant mount, and aircraft equipment supported by the receptacle, and an aircraft having one or more such equipment assemblies. The aircraft may be a folding wingtip aircraft and the equipment assembly may be part of a folding wingtip actuation mechanism.

Abstract: An aircraft wing tip that is movable by an actuator between a flight configuration, and a ground configuration which has a shorter wingspan for use in ground-based operations. Lugs that connect to arms of the actuator are integrally formed as part of the primary structure of either the fixed wing or outboard wing section, such as a folding tip section.

Abstract: An aircraft including an aircraft wing wherein the aircraft wing includes a fixed wing, a wing tip device at an end of the fixed wing, and a wing tip device actuator configured to move the wing tip device between a flight configuration and a ground configuration. The wing tip device actuator includes a shaft which is rotatable about a shaft axis to selectively displace respective first and second elbows of the wing tip device actuator towards or away from the shaft. The first elbow is connected to the wing tip device and the second elbow is connected to the fixed wing such that movement of the respective elbows away from the shaft causes the wing tip device to move away from the flight configuration and such that movement of the respective elbows towards the shaft causes the wing tip device to move towards the flight configuration.

Abstract: A bush is provided including a sleeve for receiving a pin; a shoulder extending from the sleeve, the shoulder for delimiting insertion of the sleeve into an aperture; and a sensor mount for mounting a sensor such that the sensor may detect the presence of a pin within the sleeve. Installing such a bush within an aperture of a component may negate the requirement for lugs and/or brackets on the component. This may enable reduction of the weight, size and/or complexity of the component.

Abstract: A latch for locking an aircraft folding wing is disclosed having a lug including an aperture, and a latch pin moveable within the aperture. The latch further includes a seal configured to inhibit fluid transfer between the aperture and the latch pin as the latch pin moves within the aperture.

Abstract: A seal between two aircraft surfaces which are able to move relative to each other. A wing tip device moves between a flight configuration and a ground configuration, in which ground configuration the wing tip device is moved away from the fixed wing such that the span of the aircraft wing is reduced. The fixed wing and wing tip device each comprise an outer surface, and a male seal and female seal are arranged such that when the wing tip device is in the flight configuration the female seal receives the male seal, and the female seal and male seal cooperate to provide a smooth transition from the fixed wing outer surface to the wing tip device outer surface.

Abstract: A seal between two aircraft surfaces which are able to move relative to each other. A wing tip device moves between a flight configuration and a ground configuration, in which ground configuration the wing tip device is moved away from the fixed wing such that the span of the aircraft wing is reduced. The fixed wing and wing tip device each comprise an outer surface, and a male seal and female seal are arranged such that when the wing tip device is in the flight configuration the female seal receives the male seal, and the female seal and male seal cooperate to provide a smooth transition from the fixed wing outer surface to the wing tip device outer surface.

Abstract: A pin joint assembly is disclosed having a first lug and a second lug, a pin extending through the first and second lugs, a U-shaped bushing between the first lug and the pin, wherein the U-shaped bushing includes a first end flange and a second end flange that extend radially outwards and retain the U-shaped bushing to the first lug, and wherein the U-shaped bushing includes a bearing surface between the first and second end flanges on which the first lug is slidable.

Abstract: A pin joint assembly including: a first end lug and a second end lug; a pin hole extending through the first and second end lugs; a first retaining feature and a second retaining feature arrangeable at opposing ends of the pin hole; a headless pin including a pin body for inserting through the pin hole to rotatably couple the first and second end lugs, such that the pin body is retained between the first and second retaining features; a first bushing for positioning between the headless pin and the first end lug, and a second bushing for positioning between the headless pin and the second end lug; wherein the headless pin is isolated from the first and second retaining features.

Abstract: A hinge assembly 8a for an aircraft component comprises first and second hinge plates 9, 10, each hinge plate including a plurality of fingers 13 to 17. The fingers of the first and second hinge plates are interleaved. A seal assembly 28 to 32 is provided between at least some of the fingers. The provision of a hinge including interposed fingers allows for a hinge assembly having a complex aerodynamic profile to be made, while the sealing function is performed by the seals filling the gaps between the fingers.

Abstract: An aircraft wing having a fixed wing and a wing tip device rotatable about a hinge at the tip of the fixed wing is disclosed. The wing further includes an actuation assembly for rotating the wing tip device about the hinge. The upper cover of the wing tip device includes an offset region extending inboard of the hinge axis, such that when the wing tip device is rotated to the ground configuration, the offset region extends into a space previously-occupied by the actuation assembly, but is outside the space occupied by the actuation assembly in the ground configuration.

Abstract: An aircraft wing including a fixed wing and a wing tip device rotatable about a hinge at the tip of the fixed wing is disclosed. The wing further includes a hinged panel at the boundary between the wing tip device and the fixed wing. In the flight configuration the panel is closed such that the panel is substantially flush with the upper surface of the wing, and the hinged panel is located in the path of a moveable element (for example part of an actuation mechanism, such as a curved rack). In the ground configuration the panel is hinged open to a position outside the path of the moveable element such that clashing of the moveable element with the stationary structure at the tip of the fixed wing is avoided.

Abstract: A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.

Abstract: An aircraft wing having a fixed wing and a wing tip device at the tip of the fixed wing is disclosed. The wing tip device being movable relative to the fixed wing between flight and ground configurations, the aircraft wing having a locking mechanism including a locking bore and a locking pin, the locking mechanism being configurable between a locked configuration, in which the locking pin is received in the locking bore, to lock the wing tip device in one of the flight or ground configurations, and an unlocked configuration in which the locking pin is withdrawn from the locking bore such that the wing tip device is moveable relative to the fixed wing, and wherein the locking pin is configured such that it has a replaceable tip.

Abstract: A pin joint assembly is disclosed having a first lug and a second lug, a pin extending through the first and second lugs, a U-shaped bushing between the first lug and the pin, wherein the U-shaped bushing includes a first end flange and a second end flange that extend radially outwards and retain the U-shaped bushing to the first lug, and wherein the U-shaped bushing includes a bearing surface between the first and second end flanges on which the first lug is slidable.

Abstract: A pin joint assembly including: a first end lug and a second end lug; a pin hole extending through the first and second end lugs; a first retaining feature and a second retaining feature arrangeable at opposing ends of the pin hole; a headless pin including a pin body for inserting through the pin hole to rotatably couple the first and second end lugs, such that the pin body is retained between the first and second retaining features; a first bushing for positioning between the headless pin and the first end lug, and a second bushing for positioning between the headless pin and the second end lug; wherein the headless pin is isolated from the first and second retaining features.