Abstract: A wing assembly for an aircraft comprising a spar, a wing cover and a rib; wherein the spar has a web portion and a flange portion joined by a radius corner; wherein a gap is formed at an interface between the spar, the wing cover and the rib; wherein the assembly further comprises a seal member which substantially covers the gap, and sealant provided between the seal member and the rib and/or the wing cover and/or the spar so as to seal the gap. Also a method for sealing a gap in an aircraft wing assembly.

Abstract: A sensor device for a fuel system, the sensor device comprising sensing means configured to sense a property of fuel within the fuel system, and transmitting means configured to wirelessly transmit a signal representative of the sensed fuel property to a remote receiver. Also a sensor device comprising a photo-diode which is operable to function as an antenna or part of an antenna for the device. Also a method for communicating with a plurality of sensor devices.

Abstract: An integral composite wing spar (12) and composite stiffener (32) formed by simultaneous curing of the matrix components in a specialised tool. A method of manufacture and tool is also provided.

Abstract: The invention provides a filter for a pipe, the filter comprising an attachment portion for attaching to the pipe, and a filter surface for presentation to and filtering of an oncoming flow of the pipe, wherein the filter surface has at least one pointed apex for protruding into the oncoming flow. The invention also provides a pipe for transporting an oncoming flow, wherein the pipe is provided with a filter surface across the cross-sectional area of the pipe and wherein the filter surface has at least one pointed apex protruding along the longitudinal axis of the pipe. The invention also provides an aircraft with such a filter or pipe and a method of filtering an oncoming flow of a pipe.

Abstract: The invention provides a test apparatus for providing axial stresses in a structure, comprising a first set of formations for abutting a first surface of the structure at a first plurality of locations, a second set of formations for abutting a second surface of the structure at a second plurality of locations, and a force actuator, and wherein each set of formations comprises at least three formations and wherein at least two formations in each set of formations are aligned with a notional alignment line along the structure and at least one formation in each set of formations is out of alignment along the structure with said notional alignment line, such that when the force actuator applies a force, loads are applied at different locations, causing the structure to bend biaxially and thereby providing biaxial stresses in the structure.

Abstract: A clamp block assembly for securing hydraulic pipes, the clamp block assembly comprising one or more unitary clamp blocks of deformable material each having a through hole for receiving a respective pipe, and a clamp adapted to apply a predetermined load around the clamp block(s).

Abstract: A composite structure comprising: a first stack comprising a plurality of plies of composite material and at least one ply of self-healing material, the ply of self-healing material comprising a plurality of containers each containing a curable healing liquid; and a second stack comprising a plurality of plies of composite material, the stacks being joined together at a bond line. By placing a ply of self-healing material in one of the stacks (preferably relatively close to the bond line) the ply of self-healing material can resist the propagation of cracks between the first stack and the second stack. Preferably the global strength of the first stack is greater than the global strength of the second stack.

Abstract: An electrical cable raceway for an aircraft, the electrical cable raceway being formed at least in part from a ceramic material.

Abstract: A battery case for a power tool, comprising a body defining a cavity configured to receive a battery, a body surface of the battery case being formed to have a curved outward profile.

Abstract: An aircraft noise-reduction apparatus comprise a flow-facing element (1) and a flow control device (2) positioned downstream of the flow-facing element (1). The flow control device (2) is arranged, in use, to reduce noise induced by unsteady flow downstream of the flow-facing element (1).

Abstract: A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face and a recess defined there within, a display screen assembly in the recess in the fin body, the display screen assembly comprising a translucent face, substantially flush with and forming at least part of the inboard face or the outboard face of the fin body, and a display screen arranged in the recess such that images displayed on the display screen are visible through the translucent face.

Abstract: A cable protector for connection to an aircraft electrical cable raceway, comprising a flexible conductive body defining a conduit through which an electrical cable can pass and an electrically conductive connection arrangement configured to enable connection of the body of the protector to a raceway in an electrically conductive manner.

Abstract: A device and method for securing a plurality of electrical conductors in a bundle. The device (10) comprises first and second portions (12a, 12b) connected so as to be moveable between a closed configuration in which the first and second portions define at least one enclosed space which extends through the device and an open configuration in which a conductor may be moved laterally into the at least one space from the periphery of the device. The device further includes a plurality of recesses (20) for receiving conductors disposed around its peripheral edge.

Abstract: A calibration block and method for sensitivity calibration. The calibration block has a curved calibration surface having a central axis and a surface for coupling to a transducer element of an angular scanning phased array ultrasonic testing scanner. The block is configured such that the surface positions the transducer such that its scanning axis is coaxial with the central axis of the curved calibration surface.

Abstract: A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of projections extending from a bond surface of the first component, each projection having a base, a tapered tip and a tapered overhang beneath the tip, wherein the overhang has an undercut surface which is inclined and faces towards the local bond surface; bringing the components together so as to embed the projections in the second component; and hardening the second component after the array of projections has been embedded into it. Also, a joint so formed.

Abstract: A tool for manipulating a transducer assembly. The tool had a shaft to space the transducer assembly from a handle end. The tool rotatably mounts the transducer assembly so that the transducer assembly can transmissively coupled to and follow an arcuate scanning path. The tool includes a guide member for following an edge of a component to be tested.

Abstract: The present application relates to a shaft locking device. The device has an locking element configured to be mounted on a shaft in a first position so that the locking element indicates the angular position of the shaft. The locking element is also configured to be mounted on a shaft in a second position so that the locking element is locatable against a stop to prevent rotation of the shaft. The present application also relates to a device for determining the angular position of a shaft, a valve assembly and an actuating unit for a valve.

Abstract: An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted upon a slat deployment mechanism for moving the slat between a retracted position and an extended position with respect to the fixed leading edge, the fixed leading edge having an aperture to accommodate the slat deployment mechanism, and a closing plate mounted off the slat deployment mechanism for closing a gap between a lower trailing edge of the slat and a lower edge of the aperture when the slat is retracted. The closing plate can include a first portion and a second portion, and a hinge connecting the first and the second portions. The closing plate can include a plurality of integrally formed spacer elements for positioning the closing plate with respect to the slat deployment mechanism. Also, a method of removing an access panel in an aircraft wing assembly.

Abstract: An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted for movement between a retracted position and an extended position with respect to the fixed leading edge, and a translating cable device for electrically connecting the slat to the wing and having a strut coupled at one end to the slat, the fixed leading edge having an aperture to accommodate the strut, and a seal assembly for sealing between the strut and the aperture.

Abstract: A plastic hand-held measuring device, can measure the depth of a hole or bore or the length of a fixing, having particular application with composite aircraft components. A hook or tang, at the end of an elongate portion, can engage with the far end of the bore allowing the depth ascertained from a first measurement scale. A first formation can engage with a fixing, allowing measurement of the length of the fixing from a second measurement scale. A plastic slide can abut against a portion of the component to be measured and indicate the distance on the measurement scale that corresponds to the length of the dimension being measured. The slide may be arranged to engage with successive indexed formations along the length of the device, so that it is inclined to remain in a position corresponding to an indexed formation.