Abstract: A shroud panel (60) is attached to a wing skin overhang (28) by a series of pivoting butt straps (86) to permit relative strains to occur.

Abstract: A spoiler rib assembly (110) comprises a rib (144) which is attached to a spar (112) on one side and a stiffener (160) on a second side which abuts the upper and lower flanges of the spar in order to react the loads. The invention is applicable to the mounting of any movable control surface.

Abstract: A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear.

Abstract: A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face, a sign assembly in the fin body, the assembly comprising a translucent, graphic bearing face, substantially flush with and forming at least part of the inboard face or the outboard face of the fin body, a recess in the fin body behind the graphic-bearing face, and a light source arranged in the recess to illuminate the graphic-bearing face from inside the fin body.

Abstract: A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall. The gasket comprises a ring of sealing material surrounding a hole for receiving a fastener, the sealing material comprising an at least partially cured polysulphide sealant. The gasket has a region of increased thickness positioned towards the inner periphery of the ring which flows to form the collar.

Abstract: Thermal test apparatus comprising a specimen supported by a fixture, a thermal shroud comprising a flexible insulating fabric forming an enclosure around at least a portion of the specimen, and a temperature controlled air supply connected to an opening formed in the enclosure for delivering a supply of temperature controlled air into the enclosure. Also, a method of conducting a thermal test.

Abstract: A method for forming a laminate component, the method comprising the steps of: a) providing a tool having a moulding surface; b) arranging a stack of ply layers on the moulding surface of the tool; and c) moulding the stack of ply layers over the moulding surface in a moulding process, wherein the tool has a wrinkle control feature in its moulding surface for managing the development of wrinkle in the ply layers during the moulding process, and wherein the wrinkle control feature cooperates with the stack of ply layers during the moulding process to produce a local surface undulation in a nominal surface of the laminate component nearest the tool to either prevent wrinkling in the ply layers or initiate wrinkling in one or more of the ply layers at a predetermined location. Also, a tool having a wrinkle control feature, and a laminate component so formed.

Abstract: A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall. The gasket comprises a ring of sealing material surrounding a hole for receiving a fastener, the sealing material comprising an at least partially cured polysulphide sealant. The gasket has a region of increased thickness positioned towards the inner periphery of the ring which flows to form the collar.

Abstract: The invention relates to the installation of pipes, for example aircraft fuel pipes and fuel systems, in an aircraft. The invention further relates to guidance tool for restricting the potential angular misalignment between the axial centrelines of a pipe end and corresponding socket arrangement during a pipe installation process. The guidance tool may comprise a sleeve and a clamp. The clamp may be configured to removably engage the sleeve with an external surface of a pipe end, such that at least part of the sleeve and pipe end may be inserted into a corresponding socket arrangement.

Abstract: A deployment mechanism is disclosed for deploying a deployable member supported on tracks relative to a base member and comprising a brake system operable in response to relative skewing of the tracks.

Abstract: A method for predicting a quantity of a contaminant in a fuel tank at the end of a time period, the method comprising the steps of: determining a quantity of the contaminant in the fuel tank at the start of the time period; determining at least one operating condition of the fuel tank during the time period; using information relating to the at least one operating condition of the fuel tank to generate a predicted quantity of the contaminant accumulated in the fuel tank during the time period; and calculating, based upon the quantity of the contaminant at the start of the time period and the predicted quantity of the contaminant accumulated during the time period, a predicted quantity of the contaminant at the end of a time period.

Abstract: A clack valve assembly comprising: a valve seat comprising an opening; a bearing comprising a recess with a base, a mouth, and a pair of side walls between the base and the mouth; a lid comprising a lid plate and a shaft, the shaft being received in the recess of the bearing; and a shaft retaining member which closes the mouth of the recess in the bearing, thus retaining the shaft within the recess. The shaft and the lid plate are integrally formed elements of a single part. The shaft can rotate within the recess to enable the lid to rotate from a closed position in which the lid engages the valve seat and covers the opening, to an open position in which the lid lifts away from the valve seat enabling fluid to flow through the opening in the valve seat.

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: The invention relates to an aircraft protection device for protecting potentially exposed aircraft structures from direct impacts and a method of protecting an exposed edge of an aircraft component. The method includes the steps of winding filament around a foam core to create an impact protection device. A portion of the filament winding and foam core is removed from the impact protection device to create a receiving section whereby the receiving section is configured to correspond to and receive the exposed edge of the aircraft component. The impact protection device is secured to the exposed edge of the aircraft component such that the exposed edge is received in the receiving portion of the impact protection device.

Abstract: A fuel tank installation comprising: a fuel tank for holding fuel, the fuel tank comprising a fuel tank wall formed with a hole; a fuel pump assembly fitted into the hole in the fuel tank wall with an inner part of the fuel pump assembly protruding from an inner side of the hole and an outer part of the fuel pump assembly protruding from an outer side of the hole; a cage surrounding the outer part of the fuel pump assembly; and a mounting piece which attaches both the cage and the fuel pump assembly to the fuel tank wall.

Abstract: A process for measuring the through stress distribution (12) in a workpiece (10) by taking progressive cuts (14, 16) and measuring the deflection of the workpiece at the cut point.

Abstract: A flap support structure for an aircraft wing having a trailing edge flap, the flap support structure comprising: a flap support beam including an aerodynamic fairing; and a drive unit including a universal support structure which rotatably receives a drive shaft connected to a drive arm for moving the trailing edge flap, wherein the universal support structure also forms part of the flap support beam and supports the aerodynamic fairing.

Abstract: A computer-implemented method for converting a representation of a system into a behaviour model of the system is provided. The method can be used to convert a schematic diagram into a behavioural model.

Abstract: A computer-implemented method for determining a configuration of a plurality of components in a systems installation which satisfies one or more constraints.

Abstract: A method of lifting an aircraft at a lifting location, the method comprising: securing a fitting to the aircraft when the aircraft is at the lifting location; engaging the fitting with a crane hook; transmitting lifting load from the crane hook to the aircraft via the fitting; and removing the fitting from the aircraft. A fitting for transmitting lifting loads from a crane hook to an item, the fitting comprising: an attachment member configured to be secured to the item; and a lifting member which is pivotally coupled to the attachment member and configured to be engaged by the crane hook so as to transmit lifting loads from the crane hook to the item. A crane hook with a ball-and-socket connection is provided.