Abstract: A turbo engine includes a system for changing a pitch of blades of a propeller, the system including an annular fluid cylinder with a linear drive and a link mechanism linking the cylinder to the blades of the propeller to change an orientation of the propeller. The annular cylinder of the system can be rigidly mounted on a fixed housing supporting the propeller and internal to the propeller, unlike the blades mounted in an external rotating hub of the propeller, and the link mechanism includes a displacement transfer bearing fixed, on one side, to the mobile part of the cylinder and cooperating, on the other side, with a mechanism linking to the blades of the rotating hub of the propeller.

Abstract: A propeller assembly having a hub having at least one receiver opening, a receiver located within the receiver opening and having a first collar defining a blade opening, a blade having a second collar and a protrusion with the second collar abutting the first collar and the protrusion received within the blade opening, and a first retainer, and a second retainer.

Abstract: A system for detecting the location of arc faults in an aircraft electrical wiring arrangement is provided. The system comprises a controller, operable to generate a test signal and a directional coupler for coupling the test signal into electrical wiring and for coupling reflected test signals from the electrical wiring to the controller. The electrical wiring comprises one or more wire under test and the controller is further operable to detect test signals reflected from arc faults in the wire under test and to analyze reflected test signals in order to determine one or more arc fault position therefrom. The wire under test may be live and testing can be performed without the need to use invasive in-line components.

Abstract: A passive leakage management circuit for a switch leakage current includes a switch being operable in a first operating mode, wherein the switch output supplies an output current having a first predetermined voltage. In a second operating mode, the switch output supplies a leakage current having a second voltage, a first current path, and a leakage current path.

Abstract: The present embodiments relate to providing electrical connectivity to electric-powered components mounted in parallel on a wiring board. An electrical apparatus is provided in which electricity is conducted from an electrically conductive member onto first and second electrically conductive pathways, of a wiring board through the use of first and second resiliently-deformable electrically conductive connectors. First and second electric-powered components are mounted to the respective first and second electrically conductive pathways. The first and second resiliently-deformable electrically conductive connectors are compressed between the electrically conductive member and the wiring board such that the first connector provides an electrical connection between the conductive member and the first electrically conductive pathway, and the second connector provides an electrical connection between the conductive member and the second electrically conductive pathway.

Abstract: A method of diagnosing a speed brake fault, where the method includes receiving a position signal from the at least one position sensor, determining a variation in the position signal relative to a reference position and diagnosing a fault in the speed brake system based on the variation.

Abstract: A method of diagnosing a bleed air system fault, where the method includes receiving a sensor signal from the at least one of the bleed air system sensor to define a sensor output, comparing the sensor output to a reference value, and diagnosing a fault in the bleed air system based on the comparison.

Abstract: One aspect of the present invention provides a propeller for an aircraft. The propeller comprises a propeller hub, a spinner for streamlining the propeller and a plurality of composite propeller blades mounted to the propeller hub. The propeller blades are arranged to rotate together in the same rotational direction in at least two parallel planes substantially perpendicular to an axis of rotation of the propeller. The propeller has a reduced sized spinner with an improved aerodynamic profile that can be better matched to an engine nacelle and also has reduced drag.

Abstract: Methods of predicting a speed brake fault in an aircraft having a speed brake system including multiple control surfaces, a handle for setting the position of the multiple control surfaces, and at least one control surface position sensor, the methods include receiving a position signal from the at least one position sensor, determining a variation in the position signal and predicting a fault in the speed brake system.

Abstract: A method of predicting an auxiliary power unit fault in an aircraft having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, including receiving a sensor signal from at least one of the multiple sensors to define a sensor output, comparing the sensor output to a reference value and predicting a fault in the auxiliary power unit based on the comparison.

Abstract: A method of testing a voltage protection device in a circuit is provided. The circuit comprises a source and load and a detector is provided in parallel with the protection device. The method comprises opening a switching device provided in the circuit. The method further comprises detecting a property of a voltage spike caused by the rate of change of current in the circuit inductance produced by the opening of the switching device to determine the condition of the protection device.

Abstract: A pitch control mechanism for an open rotor gas turbine engine is provided, the engine having a first rotor assembly and a second rotor assembly, with a plurality of airfoil blades circumferentially mounted on each rotor assembly, and arranged in contra-rotational relationship to each other. The pitch control mechanism includes an actuator assembly configured to be secured to a non-rotating frame of the engine, the actuator assembly having a first actuator and a second actuator, with the actuator assembly being rotationally isolatable from and couplable to the first and second rotor assemblies such that, in use, an actuation signal from the first or second actuator induces a corresponding desired change in pitch of the airfoil blades of the respective first or second rotor assembly independently of the pitch of the airfoil blades of the second or first rotor assembly.

Abstract: The present invention relates to built-in testing of detectors for the detection of electrical arc faults or transients, where the detector is integrated into or electrically coupled to an electrical power supply system.

Abstract: A system for automatically analysing aircraft systems data is described. The system comprises a data acquisition module operable to acquire aircraft systems data, a data archiving module operable to store aircraft systems data and a data analysis module operable to analyse the aircraft systems data to identify non-predetermined troubleshooting procedures for fault rectification. Automated identification of improved maintenance techniques can thus be provided, with the added benefit that maintenance manuals and procedures may thereby be automatically adapted over time. A related method is also described.

Abstract: A method of monitoring hydraulic fluid levels in an aircraft includes identifying segments of operation where the aircraft meets a predetermined stability criteria, receiving output from the fluid sensor, calculating hydraulic fluid levels within the at least one hydraulic storage tank, determining a hydraulic fluid value indicative of the amount of hydraulic fluid in the aircraft based on at least the calculated hydraulic fluid level, and providing an indication of the hydraulic fluid value.

Abstract: A method of diagnosing a trailing edge flap fault in an aircraft having a trailing edge flap system including multiple trailing edge flaps, a flap handle for setting the position of the trailing edge flaps, and a flap position sensor, the method includes receiving a position signal, determining a variation in the position signal relative to a reference position, diagnosing a fault, and providing an indication of the diagnosed fault.

Abstract: A cable for transmitting a transmissible element, such as power or data, from a source to a device, the cable includes at least a first plug configured to mate with at least one of the source and the device, and an audio player for playing back audio recording.

Abstract: A method for allocation of network resources in an operations network for a selected environment includes, among other things, a plurality of applications communicating over a network having a bandwidth capacity and a plurality of modes including at least a first mode and a second mode.

Abstract: The present invention relates generally to power switches for aircraft. According to a first aspect, the present invention provides an integrated solid state power switch for fault protection in an aircraft power distribution system. The integrated solid state power switch is formed of semiconductor material that provides a field effect transistor (FET) channel that is operable during normal device operation to provide an operating current flow path and a bipolar transistor channel that is operable during device overload conditions to provide an overload current flow path. A method for manufacturing such an integrated solid state power switch is also described. Various embodiments of the invention provide automatic overload current protection for aircraft systems without the need to use bulky switches or heavy cooling equipment.

Abstract: A power distribution system which may be provided in an aircraft for example is described, the power distribution system comprising: a power distribution bus and a plurality of localized voltage converters each supplied by the power distribution bus. By providing a plurality of localized voltage converters, the power distribution system may use fewer, or just a single power distribution bus at a particular voltage and convert to the desired voltage at or near to each of a plurality of pieces of electrical equipment being supplied.