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 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 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 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: 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.

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 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 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: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

Abstract: An aircraft wing having a main wing and a trailing edge flight control surface movable between a retracted position, a first extended position in which the control surface is positioned rearwardly in the chord wise direction relative to its retracted position, and a second extended position in which the control surface is rotated relative to its retracted position. A closure panel, mounted to the main wing, extends from the main wing to the control surface, to provide an air flow surface between the main wing and control surface, both when the control surface is in its retracted position and its first extended position. The closure panel is movable, relative to the control surface, to an open configuration in which it opens an airflow passage provided between the control surface and an opposed surface of the aircraft wing when the control surface is in its second extended position.

Abstract: An aircraft brake control system for controlling anti-skid braking of at least first and second wheels in a wheel set of an aircraft is disclosed. The system includes a control assembly having wheel speed inputs including an input of an indication of the wheel speed of the first wheel, and an input of an indication of the wheel speed of the second wheel, a wheel speed comparator for determining which of the wheel speeds indicated is a lowest wheel speed, and an output for indicating a wheel speed other than the lowest wheel speed. An aircraft landing gear, an aircraft, and methods of braking an aircraft are also disclosed.

Abstract: A computer-implemented method of obtaining an excursion report for an aircraft is disclosed. The aircraft includes one or more sensors and a vision system, and the method includes obtaining sensor data from the one or more sensors; storing and time-stamping the sensor data; operating the vision system to detect the aircraft leaving a runway or taxiway; recording a start time of an excursion period based on a time of detection of the aircraft leaving the runway or taxiway; operating the vision system to detect the aircraft returning to the runway or taxiway; recording an end time of the excursion period based on a time of detection of the aircraft returning to the runway or taxiway; and compiling an excursion report, the excursion report comprising: the start time of the excursion period, the end time of the excursion period and a subset of the sensor data which was time-stamped during the excursion period.

Abstract: A cover panel for an aircraft including: a first region, a second region for forming an overlap with a second panel, and a ramp, wherein at least a portion of the ramp is between the first and second regions, wherein the ramp includes a tapered region such that a width of the ramp tapers towards a free-edge of the first region, and wherein the free-edge is configured to form a butt-joint with the second panel.

Abstract: A wing tip device for a fixed wing aircraft is disclosed having an alular-like projection, a first leading edge region having a first sweep angle, a second leading edge region outboard of the first leading edge region in a spanwise direction and having a second sweep angle greater than the first sweep angle, a third leading edge region outboard of the second leading edge region in the spanwise direction and adjacent a tip end of the wing tip device and having a third sweep angle greater than the first sweep angle. The second leading edge region is adapted to generate a first vortex, and the third leading edge region is adapted to generate a second vortex which builds towards the tip end of the wing tip device.