Patent application number | Description | Published |
20130045075 | FITTING, CRANE HOOK, AND CRANE HOOK ASSEMBLY - 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. | 02-21-2013 |
20130076767 | INSTALLATION OPTIMISATION - A computer-implemented method for determining a configuration of a plurality of components in a systems installation which satisfies one or more constraints. | 03-28-2013 |
20130080137 | CONVERSION METHOD AND SYSTEM - 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. | 03-28-2013 |
20130087662 | FLAP SUPPORT - 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. | 04-11-2013 |
20130091955 | METHOD AND APPARATUS FOR MEASURING RESIDUAL STRESSES IN A COMPONENT - A process for measuring the through stress distribution ( | 04-18-2013 |
20130092267 | FUEL TANK INSTALLATION - 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. | 04-18-2013 |
20130118612 | CLACK VALVE ASSEMBLY - 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. | 05-16-2013 |
20130124107 | FUEL TANK CONTAMINANT PREDICTION - 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. | 05-16-2013 |
20130125374 | FASTENER JOINT WITH SEALING GASKET - 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. | 05-23-2013 |
20130125375 | FASTENER JOINT WITH SEALING GASKET - 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. | 05-23-2013 |
20130126670 | DEPLOYMENT SYSTEM - 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. | 05-23-2013 |
20130127152 | AIRCRAFT TOOL - 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. | 05-23-2013 |
20130128914 | THERMAL TEST APPARATUS AND METHOD - 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. | 05-23-2013 |
20130129526 | WRINKLE CONTROL METHOD AND TOOL THEREFOR - 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. | 05-23-2013 |
20130139421 | WINGTIP FIN OF AN AIRCRAFT - 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. | 06-06-2013 |
20130146707 | METHOD AND APPARATUS FOR PROVIDING POWER IN AN AIRCRAFT TO ONE OR MORE AIRCRAFT SYSTEMS - 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. | 06-13-2013 |
20130146711 | AIRCRAFT RIB ASSEMBLY - A spoiler rib assembly ( | 06-13-2013 |
20130146712 | APPARATUS FOR ATTACHMENT OF WING PANELS - A shroud panel ( | 06-13-2013 |
20130152398 | HOLE DEPTH MEASUREMENT DEVICE - 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. | 06-20-2013 |
20130153712 | AIRCRAFT WING ASSEMBLY - 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. | 06-20-2013 |
20130153713 | TRANSLATING CABLE DEVICE SEALING - 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. | 06-20-2013 |
20130153802 | SHAFT LOCKING DEVICE - 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. | 06-20-2013 |
20130174663 | TOOL AND METHOD FOR MANIPULATING A TRANSDUCER ASSEMBLY - 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. | 07-11-2013 |
20130180312 | CALIBRATION BLOCK AND METHOD - 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. | 07-18-2013 |
20130183082 | PROFILE OF INTERFACING PROJECTIONS - 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. | 07-18-2013 |
20130187012 | CABLE RETAINER - A device and method for securing a plurality of electrical conductors in a bundle. The device ( | 07-25-2013 |
20130192892 | ELECTRICAL CABLE PROTECTOR - 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. | 08-01-2013 |
20130193268 | BLUFF BODY NOISE CONTROL - An aircraft noise-reduction apparatus comprise a flow-facing element ( | 08-01-2013 |
20130193273 | WINGTIP FIN OF AN AIRCRAFT - 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. | 08-01-2013 |