Abstract: A sealant smoothing tool for smoothing sealant in a gap between two aircraft parts is disclosed including a main body having a base surface for abutting sliding along a top surface of the aircraft parts, a spatula holder for holding a spatula, the spatula holder being configured to movably mount the spatula relative to the main body, and a resilient biasing member, configured to provide a biasing against the spatula or the spatula holder, such that the spatula supplies a biasing force to the sealant. An aircraft having two parts sealed by the sealant smoothing tool, a kit of parts including a sealant smoothing tool and one or more spatulas, and a method of smoothing sealant to seal a gap between two aircraft parts are also disclosed.

Abstract: Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.

Abstract: An aircraft wing section assembly is disclosed having a structural spine, a movement mechanism including a support rod 1 extending through the structural spine, a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the support rod, a second similar lever for connection to and for moving a second moveable control surface, and a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever causes pivotal movement of the second lever, and an actuation mechanism for actuating pivotal movement of the first lever, such that, in use, when the actuation mechanism actuates pivotal movement of the first lever, the second lever also pivotally moves, thus causing movement of both the first and second moveable control surfaces. Also disclosed is an aircraft wing assembly, an aircraft and a method of operating an aircraft.

Abstract: A cradle for supporting an aircraft landing gear assembly is disclosed including a chassis for transporting the cradle and an arm movable between a stowed position and an elevated position with respect to the chassis. The arm has a set of clamps for securing the landing gear assembly to the cradle. In this way the landing gear assembly is held securely in the stowed position for storage and transport, and held securely in the elevated position for installation to an aircraft, such that damage to the landing gear assembly during transportation and installation is minimised.

Abstract: A lightning strike protection layer for an aircraft is disclosed having a first portion and a second portion, the first portion includes a first fibre reinforced polymer composite layer and a first electrically conductive metal layer and the second portion includes a second fibre reinforced polymer composite layer and a second electrically conductive metal layer, and the first and second portions are joined at a butt joint, with the first and second fibre reinforced polymer composite layers abutting and the first and second electrically conductive metal layers abutting; and a butt-strap extending across the butt joint, the butt-strap comprising a third electrically conductive metal layer electrically connected to the first and second electrically conductive metal layers.

Abstract: A rib mounting assembly for an aircraft is disclosed including a rib post and a seal member. The rib post has a rib post foot to mount with a longitudinal spar and a rib post web upstanding from the rib post foot. The seal member has a seal body and a mounting flange. The mounting flange is mounted with the rib post foot and the seal body extends from an end of the rib post.

Abstract: A computer-implemented method of predicting tire pressure of a tire of an aircraft, the method including obtaining first data indicative of an inflation pressure of the tire, obtaining second data indicative of a brake temperature of a brake associated with an aircraft wheel to which the tire is mounted, obtaining third data indicative of a gas temperature of the tire, and obtaining fourth data indicative of one or more predicted operational conditions of the aircraft during a future time period. The method includes determining, based at least in part on the first, second, third and fourth data, predicted tire pressure characteristics of the tire during the future time period.

Abstract: A spark containment cap for enclosing an end of a fastener protruding from a structure, the enclosed body having a base and a cover portion, the cover portion extending from the base, the base providing an adhering surface for adhering the spark containment cap to a structure, and the base and the cover portion together forming a cavity within the enclosed body inside which the end of a fastener can be enclosed.

Abstract: A stiffener is disclosed including a core and a shell which surrounds the core. The shell is formed from a fibre material, and the core includes first and second battens arranged side by side, and a foam spacer between the battens. The stiffener extends in a lengthwise direction, and the battens and the foam spacer have respective lengths which extend in the lengthwise direction of the stiffener. The core is assembled with the spacer between the battens, then surrounded with the shell. The stiffener may be a stringer for an aircraft wing.

Abstract: A method of landing an aircraft in which the aircraft receives information from a second aircraft via a direct aircraft-to-aircraft communication from the second aircraft to the aircraft; determines a landing plan of the aircraft based on the information; and lands the aircraft based on the landing plan. The use of a direct aircraft-to-aircraft communication (i.e. a communication from the second aircraft to the first aircraft which does not travel via an intermediary such as a land station, air traffic controller or satellite) makes the method reliable because such a communication is inherently secure and difficult to hack.

Abstract: A method of determining a status of a tyre monitoring device that includes a power supply. The method includes determining a value indicative of consumption of the power supply, determining a status of the tyre monitoring device based on the value indicative of consumption of the power supply, and providing an indication based on the determined status.

Abstract: A computer-implemented method of tire maintenance including: receiving data of a plurality of tire gas pressure measurements each measurement having an associated time; analyzing the received data to determine maintenance information, wherein the maintenance information comprises at least one of: an inflation event, a maximum pressure, a minimum pressure and a tire replacement event; and providing an indication based the determined maintenance information.

Abstract: An aircraft engine incudes: a catalyst, e.g. platinum, applied to turbine blades (580c, 590c) and/or to a catalytic grid downstream of the engine's combustion chamber. An exhaust fluid additive injection system is incorporated upstream of the catalyst via a line 560, in a stator blade within the engine. The catalyst is used to reduce NOx emissions from the engine by a Selective Catalytic Reduction reaction.

Abstract: A method of monitoring friction associated with a plurality of aircraft wheels of an aircraft, the method including, for each of the plurality of aircraft wheels, obtaining wheel speed data associated with the aircraft wheel. The method includes determining, based at least in part on the wheel speed data, deceleration of the aircraft wheel during a time interval, and determining, based at least in part on the determined deceleration, a value indicative of friction associated with the aircraft wheel. The method includes providing, based at least in part on the determined value, a signal indicative of a level of friction associated with the aircraft wheel.

Abstract: A method and apparatus for cutting a Non-Crimp Fabric for improving edge stability and reducing stitch retraction is disclosed. The part of the NCF to be cut is treated with a binder and heated to activate the binder and therefore bind the tows and stitches together. By treating only the cutting path the drapability of the wider fabric is maintained. This may be achieved by heating only the part of the NCF to be cut, or applying binder to only the part of the NCF to be cut. The NCF may be compressed and cooled before cutting to improve binding action. A ply cutter may be adapted to carry out the invention by including a heat source and optionally a binder dispenser, compressor and cooler.

Abstract: A blind fastener is disclosed having a head, a shaft with a tail, a tail of the blind fastener including the tail of the shaft and a sleeve surrounding the tail of the shaft, and a barrier secured to the tail of the blind fastener. The sleeve is configured to expand away from the tail of the shaft to form an expanded sleeve which is forced against a face of a workpiece to clamp the workpiece between the head and the expanded sleeve. The barrier is configured to be forced against the face of the workpiece to form a sealed cover around the tail of the blind fastener.

Abstract: A fluid pipe connection is disclosed having an inner pipe assembly including a first inner pipe section and a second inner pipe section, and an inner joint between the first inner pipe section and second inner pipe section; an outer pipe assembly having a first outer pipe section, a second outer pipe section, a shroud covering the inner joint and mechanically connecting the first outer pipe section to the second outer pipe section via a mechanical connection, and a hatch fastened to the shroud by one or more fasteners and covering a hole in the shroud, wherein the hatch is moveable between a closed position and an open position to provide access to the inner joint through the hole.

Abstract: An actuator is disclosed including an actuator body mounted for movement over a range of motion, the range of motion including a first part and a second part, the first part being the range of motion extending between an end position and the second part. The actuator includes a motor coupled to the actuator body to move the actuator body in the first direction and a controller configured to control the supply of current to drive the motor. The mechanical resistance to movement of the actuator body in the first direction is higher in the first part of the range of motion than in the second part of the range of motion. The controller is configured such that any additional current supplied to the motor when the actuator body is in the first part of the range of motion is limited thereby causing the speed of the actuator body to reduce as the actuator body approaches the end position.

Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

Abstract: An aircraft assembly is disclosed including an aircraft panel, a channel attached to the aircraft panel, a fuel line for carrying cryogenic fuel, the fuel line disposed in the channel, and a sealed containment space around the fuel line for containing cryogenic fuel leaked from the fuel line, the containment space defined between the channel, the fuel pipe, and the aircraft panel.