Abstract: An aircraft wing has a fixed wing portion and a trailing edge flap movable with respect to the fixed wing portion to define a gap between the fixed wing and the flap. A seal assembly has a first rigid seal member fixed to the fixed wing portion and a second resilient seal member fixed to an upper surface leading edge portion of the flap. The trailing edge flap is deployable between a first flap position in which the trailing edge flap conforms to a profile of the fixed wing portion, a second flap position in which the trailing edge flap is deflected upwardly from the first flap position, and a third flap position in which the trailing edge flap is deflected downwardly from the first flap position. In the first flap position the first seal member contacts the second seal member to at least partially seal the gap, and in the second flap position the first seal member presses against the second seal member and deflects the second seal member to at least partially seal the gap.

Abstract: An aircraft wing has a fixed wing portion and a trailing edge flap movable with respect to the fixed wing portion to define a gap between the fixed wing and the flap. A seal assembly has a first rigid seal member fixed to the fixed wing portion and a second resilient seal member fixed to an upper surface leading edge portion of the flap. The trailing edge flap is deployable between a first flap position in which the trailing edge flap conforms to a profile of the fixed wing portion, a second flap position in which the trailing edge flap is deflected upwardly from the first flap position, and a third flap position in which the trailing edge flap is deflected downwardly from the first flap position. In the first flap position the first seal member contacts the second seal member to at least partially seal the gap, and in the second flap position the first seal member presses against the second seal member and deflects the second seal member to at least partially seal the gap.

Abstract: An aircraft structure, for example a wing, includes a section of skin, for example a lower wing panel, the panel defining an external (lower) surface that in use is on the exterior of the aircraft and an internal (upper) surface opposite the external surface, and a duct comprising a section of duct for transporting cooling fluid, for example air, between the internal and external surfaces of the panel from a first location in the panel to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the panel. The cooling air cools an electronic hydrostatic actuator (EHA 4b) in the wing 2.

Abstract: An aircraft structure comprising; a rear spar, an upper cover which is attached to the rear spar and overhangs to its rear; a lower cover which is attached to the rear spar and overhangs to its rear, a hinge rib assembly comprising: a first hinge rib arm attached to a first one of the covers; and a second hinge rib arm connected to the first hinge rib arm and attached to a second one of the covers; and an aerodynamic control element pivotally mounted to the hinge rib assembly. The first and second hinge rib arms are separate parts. This provides the ability to disassemble the hinge rib in-situ for repair or maintenance purposes; the ability to install or remove the hinge rib without having to move it inboard along the structure; reduced material wastage during manufacture; and the ability to install one or more elongate lines which extend in a span-wise direction along the aircraft structure.

Abstract: A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge.

Abstract: A hinge rib for pivotally connecting an aerodynamic control element such as a spoiler or aileron to an aircraft structure. The hinge rib includes a first hinge rib arm having a grain oriented in a first direction and a second hinge rib arm having a grain oriented in a second direction which is not parallel with the first grain direction. The arms may be formed together from a single piece of material, or more typically they are formed separately before being attached together such that the grain of the first arm is not parallel with the grain of the second arm.

Abstract: An aircraft structure comprising: a rear spar; and a composite cover attached to the rear spar and having an overhanging portion extending to its rear. The overhanging portion of the cover comprises one or more ramps along which the thickness of the cover reduces. A second cover is attached to the rear spar and overhangs to its rear. A hinge rib is attached to one or both of the covers, and an aerodynamic control element such as an aileron, rudder or elevator is pivotally mounted to the hinge rib.

Abstract: An aircraft structure comprising: a rear spar; and a composite cover attached to the rear spar and having an overhanging portion extending to its rear. The overhanging portion of the cover comprises one or more ramps along which the thickness of the cover reduces. A second cover is attached to the rear spar and overhangs to its rear. A hinge rib is attached to one or both of the covers, and an aerodynamic control element such as an aileron, rudder or elevator is pivotally mounted to the hinge rib.

Abstract: A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge.

Abstract: A hinge rib for pivotally connecting an aerodynamic control element such as a spoiler or aileron to an aircraft structure. The hinge rib comprises: a first hinge rib arm having a grain oriented in a first direction; and a second hinge rib arm having a grain oriented in a second direction which is not parallel with the first grain direction. The arms may be formed together from a single piece of material, or more typically they are formed separately before being attached together such that the grain of the first arm is not parallel with the grain of the second arm.

Abstract: An aircraft structure comprising; a rear spar, an upper cover which is attached to the rear spar and overhangs to its rear; a lower cover which is attached to the rear spar and overhangs to its rear, a hinge rib assembly comprising: a first hinge rib arm attached to a first one of the covers; and a second hinge rib arm connected to the first hinge rib arm and attached to a second one of the covers; and an aerodynamic control element pivotally mounted to the hinge rib assembly. The first and second hinge rib arms are separate parts. This provides the ability to disassemble the hinge rib in-situ for repair or maintenance purposes; the ability to install or remove the hinge rib without having to move it inboard along the structure; reduced material wastage during manufacture; and the ability to install one or more elongate lines which extend in a span-wise direction along the aircraft structure.

Abstract: An aircraft structure, for example a wing, includes a section of skin, for example a lower wing panel, the panel defining an external (lower) surface that in use is on the exterior of the aircraft and an internal (upper) surface opposite the external surface, and a duct comprising a section of duct for transporting cooling fluid, for example air, between the internal and external surfaces of the panel from a first location in the panel to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the panel. The cooling air cools an electronic hydrostatic actuator (EHA 4b) in the wing 2.

Abstract: The fairing arrangement 28 comprises a first fairing portion 32 on a wing 10 and a second fairing portion 34 on an aileron 12 which is mounted on and angularly displaceable with respect to the wing. The fairing arrangement protrudes 28 outwardly of the aerodynamic profile S of the wing to cover part of an actuating device for the aileron. Parts of the first and second fairing portions 32, 34 are arranged to overlap each other to form a seal 45, one of said overlap parts defines an oblique sealing surface 44 which lies substantially in the direction of the path of movement of the aileron 12 over the normal operational range of movement of the aileron. The overlap parts 32, 34 of the first and second fairing portions overlap each other over a normal operational range of the aileron 12 to form the seal 45 but do not overlap to form a seal over the remainder of the range in one of the directions of movement of the control surface.