Abstract: A slat support and deployment apparatus comprising a master slat support and deployment assembly and a slave slat support and deployment assembly is disclosed. The master and the slave slat support and deployment assembly each include an arm having a free end attachable to the same slat at spaced locations along its length for deployment and retraction of said slat in a direction generally parallel to a wing in response to simultaneous movement of said arms. The master and the slave slat support assemblies each include a coupling for attaching said free end of each arm to a slat and the coupling that couples the free end of the arm of each slat support and deployment assembly to a slat is configured to allow movement of that slat relative to said free end of said arm of each slat support and deployment assembly during deployment and retraction of said slat.

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 slat support assembly is disclosed. It comprises a slat support arm which is movable to deploy a slat from a leading edge of an aircraft wing about an axis of rotation of the arm and a slat mount on a slat which is coupled to one end of said slat support arm by a joint. The joint is configured to allow the slat mount to slide in a direction of the axis of rotation of the arm.

Abstract: A hinge assembly for rotatably mounting a control surface on an aircraft comprising an actuating shaft, a support element configured to mount the actuating shaft to a first component of an aircraft and a hinge element configured to mount the actuating shaft to a second component of an aircraft, wherein the actuating shaft is slidably mounted to the support element and configured to slide along its longitudinal axis relative to the support element, and the hinge element engages with the actuating shaft so that the actuating shaft and the hinge element are urged to rotate relative to each other about the longitudinal axis of the actuating shaft when the actuating shaft is urged to slide along its longitudinal axis, such that one of said first and second components is urged to rotate relative to the other said component about the longitudinal axis.

Abstract: A method of attaching first and second aerofoil sections to each other is disclosed. The method comprises the steps of: positioning one aerofoil section in an initial assembly orientation with respect to the other aerofoil section so that hinge elements on each aerofoil section are in alignment with each other, inserting a hinge shaft through said aligned hinge elements to initially couple the aerofoil sections together whilst the aerofoil sections are in their initial assembly orientation; and rotating one aerofoil section relative to the other aerofoil section about a compound angle defined by the hinge shaft into a second orientation in which the aerofoil sections are in their final, assembled orientation relative to each other. An aerofoil assembly is also disclosed.

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 system and method for determining whether the relative rate of deployment of all the slats extending from a leading edge of an aircraft wing is the same as a predetermined relative rate of deployment. Each slat includes at least one slat deployment mechanism that includes a drive pinion drivingly coupled to each slat and a rotary actuator having an output shaft driven by a common input drive shaft. The system of the invention comprises a sensor associated with each rotary actuator to generate a signal indicative of the rate of rotation of the corresponding output shaft and to supply that signal to a controller. The controller is configured to analyze the signals supplied by the sensors and to generate an alarm signal if a relative rate of rotation of any of the output shafts differs from a predetermined relative rate of rotation.

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: 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.

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

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: An aircraft wing assembly, comprising: a fixed wing portion; a first and second flight control surfaces; a first and second actuators operatively coupled to the first and second flight control surfaces for moving respective first and second flight control surfaces with respect to the fixed wing portion; a control system operatively coupled to the first and second actuators for controlling movement of the first and second flight control surfaces; and a third actuator selectively engaged with the second flight control surface for engaging and moving the second flight control surface out of a path of movement of the first flight control surface only in the event of a failure in the second actuator or its control, so as to avoid direct contact between the first and second flight control surfaces.

Abstract: A slat support and deployment apparatus comprising a master slat support and deployment assembly and a slave slat support and deployment assembly is disclosed. The master and the slave slat support and deployment assembly each include an arm having a free end attachable to the same slat at spaced locations along its length for deployment and retraction of said slat in a direction generally parallel to a wing in response to simultaneous movement of said arms. The master and the slave slat support assemblies each include a coupling for attaching said free end of each arm to a slat and the coupling that couples the free end of the arm of each slat support and deployment assembly to a slat is configured to allow movement of that slat relative to said free end of said arm of each slat support and deployment assembly during deployment and retraction of said slat.

Abstract: A method of attaching first and second aerofoil sections to each other is disclosed. The method comprises the steps of: positioning one aerofoil section in an initial assembly orientation with respect to the other aerofoil section so that hinge elements on each aerofoil section are in alignment with each other, inserting a hinge shaft through said aligned hinge elements to initially couple the aerofoil sections together whilst the aerofoil sections are in their initial assembly orientation; and rotating one aerofoil section relative to the other aerofoil section about a compound angle defined by the hinge shaft into a second orientation in which the aerofoil sections are in their final, assembled orientation relative to each other. An aerofoil assembly is also disclosed.

Abstract: A slat support assembly is disclosed. It comprises a slat support arm which is movable to deploy a slat from a leading edge of an aircraft wing about an axis of rotation of the arm and a slat mount on a slat which is coupled to one end of said slat support arm by a joint. The joint is configured to allow the slat mount to slide in a direction of the axis of rotation of the arm.

Abstract: A hinge assembly for rotatably mounting a control surface on an aircraft comprising an actuating shaft, a support element configured to mount the actuating shaft to a first component of an aircraft and a hinge element configured to mount the actuating shaft to a second component of an aircraft, wherein the actuating shaft is slidably mounted to the support element and configured to slide along its longitudinal axis relative to the support element, and the hinge element engages with the actuating shaft so that the actuating shaft and the hinge element are urged to rotate relative to each other about the longitudinal axis of the actuating shaft when the actuating shaft is urged to slide along its longitudinal axis, such that one of said first and second components is urged to rotate relative to the other said component about the longitudinal axis.

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 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 system for determining whether the relative rate of deployment of all the slats (11) extending from a leading edge (12) of an aircraft wing (10) is the same as a predetermined relative rate of deployment is disclosed. Each slat includes at least one slat deployment mechanism that includes a drive pinion (8) drivingly coupled to each slat and a rotary actuator (14) having an output shaft (20), the output shaft being driven by a common input drive shaft (13) via the rotary actuator and being coupled to said drive pinion. The system of the invention comprises a sensor (21) associated with each rotary actuator to generate a signal indicative of the rate of rotation of its corresponding output shaft and to supply that signal to a controller (23). The controller is configured to analyse the signals supplied by the sensors and to generate an alarm signal if a relative rate of rotation of all the output shafts differs from a predetermined relative rate of rotation. A method is also disclosed.

Abstract: An aircraft wing assembly, comprising: a fixed wing portion; a first and second flight control surfaces; a first and second actuators operatively coupled to the first and second flight control surfaces for moving respective first and second flight control surfaces with respect to the fixed wing portion; a control system operatively coupled to the first and second actuators for controlling movement of the first and second flight control surfaces; and a third actuator selectively engaged with the second flight control surface for engaging and moving the second flight control surface out of a path of movement of the first flight control surface only in the event of a failure in the second actuator or its control, so as to avoid direct contact between the first and second flight control surfaces.