Abstract: A slat support assembly is disclosed. It comprises a slat support arm having a toothed rack (10), the slat support arm being movable to deploy a slat attached to one end of said slat support arm from a leading edge of an aircraft wing and, a pinion (11) having teeth that cooperate with the rack so that the slat moves in response to actuation of a rotary actuator coupled to the pinion. The cooperating teeth (13,14) are helical in shape.

Abstract: There is provided an aerofoil comprising an inboard section, a tip section moveable between a flying configuration and a parked configuration, a hinge shaft mounted at a compound angle in the inboard section, a fixed gear mounted concentrically on the hinge shaft and a drive gear coupled to the tip section and configured to mesh with the fixed gear, wherein a rotation of the drive gear against the fixed gear causes the tip section to rotate about the hinge shaft between the flying configuration and the parked configuration.

Abstract: A bearing assembly for mounting a pair of spaced parallel actuators (3) between a wing and a control surface of an aircraft so that the actuators control deployment of said control surface from the wing in tandem is disclosed. The bearing assembly comprises a fixed member (18) for attachment to the aircraft and a movable member (8) attachable to the actuators. The fixed and movable members are coupled via a part-spherical bearing (14) and are configured such that the part-spherical bearing is located in the space between the actuators (3).

Abstract: A device for locating a first aerospace component relative to a second aerospace component, comprising a bladder with a flexible membrane which defines a fluid receiving space such that, when a hardenable hydraulic fluid is injected into the bladder, said membrane is urged to deform into abutment with said first and second aerospace components to locate said components relative to each other when the hydraulic fluid hardens.

Abstract: A structural assembly for an aircraft comprising a cover with outer and inner faces, an inner support element and urging means on the inner support element, wherein opposing edges of the cover are fixedly mounted relative to the inner support element, and the urging means acts on the inner face of the cover to urge the cover to distend outwardly and locate in a predetermined position. Another aspect of the invention relates to a method of forming a structural assembly for an aircraft comprising an cover with outer and inner faces, an inner support element and urging means on the inner support element, the method comprising the steps of fixedly mounting opposing edges of the cover relative to the inner support element and operating the urging means to act on the inner face of the cover so that the cover is urged to distend outwardly into a predetermined position.

Abstract: An apparatus for fixedly locating a first aerospace component relative to a second aerospace component comprising a housing mountable on a first component with a cylinder formed in said housing, and a piston slidably received in said cylinder, wherein a first end of the piston is extendible from the housing such that, when a hardenable hydraulic fluid is injected into the cylinder to act on a second end of said piston, said first end of the piston is urged to slide away from the housing and into abutment with a second component to locate said second component, and said second component is fixedly located in a desired position relative to said first component when the hydraulic fluid hardens.

Abstract: A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path.

Abstract: A slat support assembly is disclosed. It comprises a slat support arm (3) having a plurality of bearing surfaces (28a, 28b, 29a, 29b) extending along its length, the slat (2) support arm being movable to deploy a slat attached to one end (4) of said slat support arm from a leading edge of an aircraft wing (1), and a plurality of bearings (27a, 27b, 31a, 31b) mountable within the wing, each bearing being in rolling contact with an associated bearing surface to support the slat support arm and guide it during deployment and retraction of the slat. At least some of the bearing surfaces and associated bearings are configured so that each bearing counteracts load applied to the slat support arm in more than one direction.

Abstract: A seal (500) comprises a seal body (502) having a mounting portion (504), a first leg (506) and a second leg (508), a first stiffening member (514) and a second stiffening member (516) separated by an arcuate shear seal portion (529) in which the motions of the first leg (506) and second leg (508) are relatively constrained by the second stiffening member (516).

Abstract: A hinge sealing element to substantially prevent airflow between an edge of a moveable aero surface structure and an edge of a fixed skin of an aircraft wing in the vicinity of the ribs to which the moveable aero surface structure is pivotally mounted is disclosed. The hinge sealing element comprising a deformable elongate, resiliently flexible strip having an upper face to contact a trailing edge of a fixed skin and one end attachable to a moveable aero surface structure such that said strip extends from an upper surface of said moveable aero surface structure beyond its leading edge and into a space between the edge of the fixed skin and the rib of the aircraft wing to a second, free end. The strip is configured such that it deforms during pivotal movement of the moveable aero surface structure to maintain contact between the upper face of the flexible element and the trailing edge of the fixed skin.