Abstract: A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.

Abstract: A seal plate (201) for maintaining a continuous aerodynamic surface between a fixed part (302) of an aerostructure such as an aerofoil (103) and a movable surface such as a spoiler (304) is provided. The seal plate (201) includes a resilient material such as fiberglass and has an aerodynamic surface (203). It is configured to be mounted to the fixed part (302) of the aerofoil along one edge (205) and to slidably seal with the control surface (304) at a second edge (207). The seal plate (201) is stepped and has a rigid lever (217) to engage behind the control surface (304) to bend the seal plate precisely according to movement of the control surface (304) and maintain the continuous aerodynamic surface.

Abstract: A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.

Abstract: A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.

Abstract: A method and system for actuating an aircraft component is disclosed including an actuating material in which an actual deformation change undergone by the actuating material in response to an activation input signal is determined by analysis of an output signal generated by the actuating material in response to the actual deformation. At least a portion of the aircraft component includes an actuating material which undergoes deformation in response to the application of an electrical signal thereto, and which generates an electrical signal in response to a deformation of the actuating material.

Abstract: A seal plate (201) for maintaining a continuous aerodynamic surface between a fixed part (302) of an aerostructure such as an aerofoil (103) and a movable surface such as a spoiler (304) is provided. The seal plate (201) includes a resilient material such as fiberglass and has an aerodynamic surface (203). It is configured to be mounted to the fixed part (302) of the aerofoil along one edge (205) and to slidably seal with the control surface (304) at a second edge (207). The seal plate (201) is stepped and has a rigid lever (217) to engage behind the control surface (304) to bend the seal plate precisely according to movement of the control surface (304) and maintain the continuous aerodynamic surface.

Abstract: A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.

Abstract: A plain journal bearing couples first and second components. A pin passes through the components. A clamping bush surrounds the pin. A clamping member is mounted on the pin and provides a clamping force to urge the clamping bush into clamping engagement with the first component. During normal operation, when the components rotate relative to each other, the second component and the clamping bush rotate relative to each other about a primary slip path, and the clamping bush remains in clamping engagement with the first component. During degraded operation, when the components rotate relative to each other and the coefficient of friction of the primary slip path has increased to overcome the clamping force, the pin and the clamping bush or the pin and the first component rotate relative to each other about a subsidiary slip path.

Abstract: An assembly comprising first and second structural components and a packer disposed between the first and second components, wherein the first component and the packer have mating part-spherical surfaces, and the first and second components are fixed relative to one another. Also, a method of aligning first and second structural components relative to one another to form an assembly, the method comprising bringing together first and second structural components with a packer disposed between the components, wherein the first component and the packer have mating part-spherical surfaces, sliding adjustment of the first component relative to the packer until the first and second components are aligned in a desired relationship, and then fixing the first and second components relative to one another.

Abstract: A panel assembly for an aircraft comprises a panel rotatably connected to a support structure and moveable between a first position and a second position. The panel has an aerodynamic surface with a slot at one edge thereof which receives a portion of the support structure when the panel is in the first position. The assembly further comprises a resilient seal member which occupies the slot when the panel is in the second position. The panel may be an aircraft flight control surface, or an aircraft landing gear bay door.

Abstract: An aircraft control surface failsafe hinge configuration is disclosed. The arrangement comprises a drop link configuration which is adapted to attach a control surface to an aircraft structure where the drop link additionally incorporates a failsafe hinge means which provides a backup hinge connection between the control surface and the aircraft structure to which it is attached. The improved failsafe hinge construction may be applied to any aircraft control surface such as an aileron, elevator, vertical tail plane and the like.

Abstract: A bearing failure indication arrangement which has a bearing with an inner and outer races, a first part arranged to be attached in fixed relation to either the bearing inner race or bearing outer race, a failure indicator arranged in fixed relation to both the first part and either the bearing inner race or the bearing outer race, the failure indicator constructed so that if relative movement occurs between the first part and the bearing race to which it is attached, the failure indicator responds to the relative movement thereby indicating failure of the bearing.

Abstract: An assembly comprising first and second structural components and a packer disposed between the first and second components, wherein the first component and the packer have mating part-spherical surfaces, and the first and second components are fixed relative to one another. Also, a method of aligning first and second structural components relative to one another to form an assembly, the method comprising bringing together first and second structural components with a packer disposed between the components, wherein the first component and the packer have mating part-spherical surfaces, sliding adjustment of the first component relative to the packer until the first and second components are aligned in a desired relationship, and then fixing the first and second components relative to one another.

Abstract: A panel assembly for an aircraft comprises a panel rotatably connected to a support structure and moveable between a first position and a second position. The panel has an aerodynamic surface with a slot at one edge thereof which receives a portion of the support structure when the panel is in the first position. The assembly further comprises a resilient seal member which occupies the slot when the panel is in the second position. The panel may be an aircraft flight control surface, or an aircraft landing gear bay door.

Abstract: An aircraft control surface failsafe hinge configuration is disclosed. The arrangement comprises a drop link configuration which is adapted to attach a control surface to an aircraft structure where the drop link additionally incorporates a failsafe hinge means which provides a backup hinge connection between the control surface and the aircraft structure to which it is attached. The improved failsafe hinge construction may be applied to any aircraft control surface such as an aileron, elevator, vertical tail plane and the like.

Abstract: The invention provides a bearing failure indication arrangement comprising a bearing having an inner and outer race, a first part arranged to be attached in fixed relation to either the bearing inner race or bearing outer race, a failure indicator arranged in fixed relation to both the first part and either the bearing inner race or the bearing outer race, the failure indicator constructed so that if relative movement occurs between the first part and the bearing race to which it is attached, the failure indicator responds to the relative movement thereby indicating failure of the bearing. The failure indicator is particularly adapted for use in aircraft structures and indicates full of partial bearing failure by means of movement and/or deformation of the indicator.