Abstract: Methods and systems for operating an aircraft engine. A health parameter for the engine received from a first instrument is monitored by a health evaluation device communicatively coupled to a communication link between an engine controller and a second instrument which generates an operation parameter signal indicative of an engine operating condition. The health parameter is compared, by the health evaluation device, to a predetermined threshold. When the health parameter is below the threshold, the health evaluation device causes the operation parameter signal to be transmitted from the second instrument to the controller. When the health parameter reaches the threshold, the health evaluation device prevents the operation parameter signal from being transmitted from the second instrument to the controller, and transmits to the controller a fault signal to elicit a health response therefrom, the fault signal containing at least two mutually-exclusive fault codes associated with the operating condition.

Abstract: A chip detection system for an engine fluid system includes an emitter located in a first position proximate to a fluid passage of the engine fluid system, the emitter including a radioactive source that generates ionizing radiation particles and transmits the ionizing radiation particles through a liquid within the fluid passage. A detector includes a detecting element located in a second position relative to the fluid passage with the liquid disposed between the emitter and the detector. The detecting element generates an electric current in response to the ionizing radiation particles contacting the detector. A controller is in communication with the detector to receive the electric current generated by the detecting element. The controller is operable to detect chips in the liquid when the electric current generated by the detecting element is greater than a threshold value of the electric current.

Abstract: A chip detection system for an engine fluid system includes an emitter located in a first position proximate to a fluid passage of the engine fluid system, the emitter including a radioactive source that generates ionizing radiation particles and transmits the ionizing radiation particles through a liquid within the fluid passage. A detector includes a detecting element located in a second position relative to the fluid passage with the liquid disposed between the emitter and the detector. The detecting element generates an electric current in response to the ionizing radiation particles contacting the detector. A controller is in communication with the detector to receive the electric current generated by the detecting element. The controller is operable to detect chips in the liquid when the electric current generated by the detecting element is greater than a threshold value of the electric current.

Abstract: There is described a multi-channel, multi-range transducer for measuring a parameter, the transducer comprising N channels and M sensing elements, the M sensing elements centered on distinct calibration points of distinct measuring ranges, the M sensing elements distributed across the N channels of the transducer, wherein sensing elements having adjacent measuring ranges are provided in different ones of the N channels.

Abstract: Electromagnetic chip detectors and associated methods of detecting a metallic chip in engine fluid of an engine are provided. The method comprises supplying an electric current to a circuit extending between a first node and a second node to magnetize both a first electrically conductive terminal and a second electrically conductive terminal spaced apart from each other to define a chip-receiving gap therebetween, and detecting a change in resistance across the first node and the second node. The change in resistance is indicative of a capture of the chip by the electromagnetic chip detector. The chip electrically connects the first electrically conductive terminal to the second electrically conductive terminal. The first electrically conductive terminal is electrically connected to the first node. The second electrically conductive terminal is electrically connected to the second node.

Abstract: Electromagnetic chip detectors and associated methods of detecting a metallic chip in engine fluid of an engine are provided. The method comprises supplying an electric current to a circuit extending between a first node and a second node to magnetize both a first electrically conductive terminal and a second electrically conductive terminal spaced apart from each other to define a chip-receiving gap therebetween, and detecting a change in resistance across the first node and the second node. The change in resistance is indicative of a capture of the chip by the electromagnetic chip detector. The chip electrically connects the first electrically conductive terminal to the second electrically conductive terminal. The first electrically conductive terminal is electrically connected to the first node. The second electrically conductive terminal is electrically connected to the second node.

Abstract: Methods and systems for operating an aircraft engine. A health parameter for the engine received from a first instrument is monitored by a health evaluation device communicatively coupled to a communication link between an engine controller and a second instrument which generates an operation parameter signal indicative of an engine operating condition. The health parameter is compared, by the health evaluation device, to a predetermined threshold. When the health parameter is below the threshold, the health evaluation device causes the operation parameter signal to be transmitted from the second instrument to the controller. When the health parameter reaches the threshold, the health evaluation device prevents the operation parameter signal from being transmitted from the second instrument to the controller, and transmits to the controller a fault signal to elicit a health response therefrom, the fault signal containing at least two mutually-exclusive fault codes associated with the operating condition.

Abstract: A method of operating a gas turbine engine having a bleed air system with a switching valve, operable to switch between multiple air sources depending on an operating mode of the gas turbine engine (e.g. a motive powered mode or a standby mode), is described. The method includes operating the switching valve to provide pressurized air from a selected one or more of the multiple air sources to a cavity of the gas turbine engine having seals, and testing the switching valve to determine if the switching valve is functioning normally or abnormally. The switching valve is functioning normally when operable to switch between the multiple air sources and is functioning abnormally when switching between the multiple air sources is not possible. If the switching valve is determined to be functioning abnormally, the gas turbine engine is controlled to prevent a change of the operating mode.

Abstract: There is described a multi-channel, multi-range transducer for measuring a parameter, the transducer comprising N channels and M sensing elements, the M sensing elements centered on distinct calibration points of distinct measuring ranges, the M sensing elements distributed across the N channels of the transducer, wherein sensing elements having adjacent measuring ranges are provided in different ones of the N channels.

Abstract: A method of operating a gas turbine engine having a bleed air system with a switching valve, operable to switch between multiple air sources depending on an operating mode of the gas turbine engine (e.g. a motive powered mode or a standby mode), is described. The method includes operating the switching valve to provide pressurized air from a selected one or more of the multiple air sources to a cavity of the gas turbine engine having seals, and testing the switching valve to determine if the switching valve is functioning normally or abnormally. The switching valve is functioning normally when operable to switch between the multiple air sources and is functioning abnormally when switching between the multiple air sources is not possible. If the switching valve is determined to be functioning abnormally, the gas turbine engine is controlled to prevent a change of the operating mode.

Abstract: A bus seat for use in a bus comprises a base having a generally rectangular shape when viewed from a bottom. The bus seat further comprises a cushioning material arranged over a top and front portion of the base. The bus seat further comprises a cover material having a fastener with a first end and a second end attached thereto. The first end of the fastener is attached to the cover material while the second end of the fastener is connected to a predetermined portion of the base on a bottom surface thereof.

Abstract: A bus seat for use in a bus comprises a base having a generally rectangular shape when viewed from a bottom. The bus seat further comprises a cushioning material arranged over a top and front portion of the base. The bus seat further comprises a cover material having a fastener with a first end and a second end attached thereto. The first end of the fastener is attached to the cover material while the second end of the fastener is connected to a predetermined portion of the base on a bottom surface thereof.