Abstract: A dust retainer for a brake system comprising a retainer receptacle mounted integrally to one or more components of the brake assembly, wherein the retainer receptacle comprises a drum have first and second open ends, one open end being secured to a component of the brake system and the other open end being closed by a dust retainer cap, the drum defining a space within which a brake disk of the brake system is located, in use, wherein removal of the dust retainer cap allows the brake disk to be removed from the open end of the retainer drum, and a removable drawer integrated in the drum. A fastening means to removably secure brake components to each other is also disclosed.

Abstract: A torque limiter device includes an input shaft having a first contact surface and an output shaft having a second contact surface. The input and output shafts are operable in an engaged position and a disengaged position A biasing mechanism provides a bias force that mechanically biases the input and output shafts in one of the positions and sets a threshold torque. An electromagnet is arranged to selectively provide an electromagnetic force that opposes the bias force when an activation current is supplied. A controller determines a difference in rotations of the shafts and selectively supply the activation current to the electromagnet so as to disengage the input and output shafts when the rotation difference exceeds a threshold. Each of the contact surfaces comprises one or more grooves, wherein at least one rotatable member is disposed in at least one of said grooves.

Abstract: An apparatus for monitoring the pressurisation of a control valve for a hydraulic actuator and a control valve. The apparatus including a spool movable along an axis (X), wherein the spool is configured to control the flow of hydraulic fluid through the control valve based on its position along the axis (X), and wherein in an unpressurised state of the control valve the spool occupies a first axial position, and in a pressurised state of the control valve the spool occupies a second, different axial position. The apparatus also including a position sensor configured to monitor the position of the spool within the control valve and detect whether the spool occupies the first axial position or the second axial position, wherein the first axial position and the second axial position correspond to neutral positions of the spool.

Abstract: A multi-layer braided article and a method of making the multi-layer braided article. The multi-layer braided article includes a braid extending along a first axis, wherein the braid is folded over itself to form a first layer and a second layer; and a wrapper laid over the first layer of the braid and extending circumferentially around the first axis, wherein the wrapper defines an edge of the first layer about which the braid is folded. The multi-layer braided article may form part of a blade for an aircraft. A sleeve may be provided around a conical portion of the article to connect the article to something else, such as a propeller hub, where the multi-layer braided article is formed as part of a blade. The sleeve may provide a primary or secondary load path.

Abstract: An asynchronous first device in communication with an asynchronous second device. The time for the first device to complete a processing cycle is a first device major frame and the first device major frame comprises a first device dedicated processing time slot at the end of the first device major frame. The first device is configured to send a rescheduling signal to the second device when it has completed a first device major frame. The first device is configured, during every first device dedicated processing slot, to: monitor for a rescheduling signal sent from the second device to the first device; and if a rescheduling signal from the second device is received: reschedule the current first device major frame to a rescheduled first device major frame; wherein the end of the rescheduled first device major frame coincides with the time the rescheduling signal from the second device was received.

Abstract: A thrust bearing includes cylindrical rollers arranged circumferentially in a bearing race with their rotational axes pointing radially to the central axis of the thrust bearing and each having a contact surface extending around and lengthwise of the cylindrical roller. The rollers includes at least pairs of radially adjacent first rollers with a radially inner first roller of each pair arranged with its rotational axis in alignment with the rotational axis of a radially outer first roller of the pair. The rollers also includes second rollers with at least one such second roller being arranged between adjacent pairs of first rollers in the circumferential direction, the at least one second roller being offset in the radial direction relative to the radially outer first rollers between which it is circumferentially arranged.

Abstract: An actuator assembly may comprise a screw shaft having a shaft axis; a drive arrangement pivotally supported about the screw shaft axis for driving the screw shaft, e.g., about the shaft axis or along the shaft axis, and a rod mounted to the drive arrangement at a location off the shaft axis for providing a primary function of reacting torque about the shaft axis on the drive arrangement. The rod may comprise a rod axis and provide a load path along the rod axis for reacting torque. The rod may also comprise a device for which provides a secondary function for the actuator assembly based on the load experienced along the load path provided by the rod.

Abstract: An aircraft inceptor system includes an inceptor member arranged to be operated by a user to cause a corresponding movement of a moveable aircraft surface. The system also includes means for detecting the operation of the inceptor member by the user and for providing a movement signal, associated with the detected operation, to a flight control computer, the flight control computer providing a control signal to an actuator to move the aircraft surface according to the movement signal. The means for detecting the operation of the inceptor member by the user comprises a force sensor configured to sense the force applied by the user to the inceptor member, the movement signal being derived based on the sensed force.

Abstract: A lubrication system comprises a lubricant reservoir, a lubricant supply passage fluidly connecting the lubricant reservoir and a space requiring lubrication, and a lubricant supply pump. The supply pump includes a piston having a first piston head slidably received in a chamber in fluid communication with the lubricant reservoir and a second piston head slidably received in a pumping chamber. The pumping chamber is divided into a first and second cavities by the second piston head. The first cavity is between the first piston head and second piston head. The first and second cavities are placeable in fluid communication with pressure sources externally of the pumping chamber to provide a pressure differential between the first cavity and the second cavity, whereby the piston may move as a result of the pressure differential to cause the first piston head to dispense lubricant from the lubricant reservoir to the space.

Abstract: A multiplexer switching device is described herein comprising a first data network comprising a plurality of NO contacts; and a second data network comprising a plurality of NC contacts; wherein said a first data network is connected to said second data network via a common DC voltage link.

Abstract: A thrust control assembly includes a balk application arrangement which provides, in response to a received balk command to prohibit command of thrust in a balk direction, a balk force on a rotatable thrust lever acting to oppose an attempt by the pilot to move the lever in a direction so as to command or increase thrust in the balk direction. The balk application arrangement controls an auto-throttle actuator to provide the balk force on the thrust lever.

Abstract: A method of monitoring the health of an aircraft propeller whilst the propeller is in operation, the propeller having a plurality of blades extending radially outwardly from hub arms of a propeller hub, which in turn extend radially outwardly from a central axis extending through the propeller and a propeller drive shaft, is provided. The method comprises obtaining measurements representative of the strain in each of at least some of the hub arms using strain sensors, each of the strain sensors being provided on a respective hub arm. A corresponding propeller health monitoring system, an aircraft propeller comprising the system and an aircraft comprising the propeller are also provided.

Abstract: A propeller health monitoring system for an aircraft includes an aircraft having one or more propellers that includes light in or on them. The system includes one or more receptors mounted to a fuselage or a nacelle of the aircraft, each receptor having a sensor surface which is able to detect a position for each light beam crossing over the sensor surface as the propeller rotates, such that the receptor generates a signal that is indicative of the position as a measure of blade tip trajectory for each passing propeller blade The system also includes a processing unit which analyses the signals from the receptor to determine health of the propeller blades of the one or more propellers based on where the beams of light from the propeller blades have crossed over the sensor surface.

Abstract: A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yam extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.

Abstract: A system for monitoring propeller health includes a processing unit having a processor which is programmed to apply a plurality of algorithms to inputted aircraft parameter data. The system also includes a plurality of data inputs for inputting aircraft parameter data into the algorithms, wherein the processor is configured to apply the physics based algorithms to the aircraft parameter data to determine at least the fatigue life consumption of one or more critical components of a propeller. In addition, the system includes an output device which is able to output an indication of the determined fatigue life consumption to an observer.

Abstract: A blade pitch actuation mechanism comprising a rotating race member in which is formed a race configured to receive a trunnion pin attached to a blade, whereby the race defines a cam profile such that rotation of the race member causes the trunnion pin received in the race to rotate as it slides over the cam profile.

Abstract: A method and system for simulating pilot controls in a cockpit simulator by controlling one or more arms on which is/are mounted a control grip, pedal or the like, to locate the grip at different positions and allow movement of the grip in a plurality of movement directions and trajectories while allowing varying force feedback.

Abstract: A torque limiter device includes an input shaft having a first contact surface and an output shaft having a second contact surface. The input and output shafts are operable in an engaged position wherein the contact surfaces are brought into mechanical engagement, and a disengaged position wherein the contact surfaces are separated. A biasing mechanism provides a bias force that mechanically biases the input and output shafts in one of the positions and sets a threshold torque. An electromagnet is arranged to selectively provide an electromagnetic force that opposes the bias force when an activation current is supplied. A rotation sensor arrangement measures a respective rotation of the input shaft and of the output shaft. A controller determines a difference in rotations of the shafts and selectively supply the activation current to the electromagnet so as to disengage the input and output shafts when the rotation difference exceeds a threshold.

Abstract: A serial communications bus system comprising a plurality of end users arranged to transmit data on a common data bus, each end user provided with a bus arbiter, physically separate from the respective end user, configured to define, for that end user, a cycle of transmission enable intervals whereby the end user may transmit data on the data bus and transmission disable intervals whereby the end user may not transmit data on the data bus.

Abstract: A propeller blade arrangement comprising a propeller blade attached to and rotatable with a hub, via a retention bearing, the blade being rotatable about a center line of the blade, the retention bearing configured to tilt the blade such that its center line is tilted with respect to the hub.