Abstract: A method and apparatus of displaying data in an aircraft, the method including receiving data, from at least one sensor operably coupled to the aircraft, averaging, by a control module, at least two data points of the received data to define a delta and averaged data, comparing, by the control module, the delta to a reference threshold value, and providing an indication, on a display of the aircraft, of the averaged data based on the comparing.

Abstract: The method of reducing error in rotor speed measurement includes synchronously measuring a rotor having a target including at least one geometric imperfection. Time intervals for the passing of each tooth of a rotor are stored in a circular buffer memory array. Speed is always determined by extracting the time for a complete revolution, so that geometric imperfections and asymmetry of the rotating target do not influence the speed determination, which is always representing the average speed over the latest complete revolution.

Abstract: A method and apparatus of displaying data in an aircraft, the method including receiving data, from at least one sensor operably coupled to the aircraft, averaging, by a control module, at least two data points of the received data to define a delta and averaged data, comparing, by the control module, the delta to a reference threshold value, and providing an indication, on a display of the aircraft, of the averaged data based on the comparing.

Abstract: The method of reducing error in rotor speed measurement includes synchronously measuring a rotor having a target including at least one geometric imperfection. Time intervals for the passing of each tooth of a rotor are stored in a circular buffer memory array. Speed is always determined by extracting the time for a complete revolution, so that geometric imperfections and asymmetry of the rotating target do not influence the speed determination, which is always representing the average speed over the latest complete revolution.

Abstract: A method for operating a gas turbine engine includes coupling at least one sensor within the gas turbine engine to transmit a signal indicative of a vibration level of a rotor assembly within the gas turbine engine, detecting the vibration level of the rotor assembly based on the signal transmitted from the at least one sensor, comparing the detected vibration level to a predetermined vibration threshold, and generating an output if the detected vibration amplitude exceeds the threshold amplitude for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

Abstract: A method of verifying the operation of an accelerometer is provided. The method includes channeling a high frequency signal through a positive lead of the accelerometer, and detecting a signal at a negative lead of the accelerometer. If the detected signal is substantially similar to the high frequency signal channeled through the positive lead, the integrity of the accelerometer is verified.

Abstract: A method of verifying the operation of an accelerometer is provided. The method includes channeling a high frequency signal through a positive lead of the accelerometer, and detecting a signal at a negative lead of the accelerometer. If the detected signal is substantially similar to the high frequency signal channeled through the positive lead, the integrity of the accelerometer is verified.