Abstract: Systems and methods for determining a throttle position of an aircraft are described herein. A first throttle position is obtained from a first sensor, a second throttle position is obtained from a second sensor, and a third throttle position is obtained from a third sensor. The first, second, and third sensors are separately coupled to a throttle of the aircraft for obtaining independent throttle position measurements therefrom. A difference between the first throttle position and the second throttle position is determined. A mismatch is detected when the difference between the first throttle position and the second throttle position exceeds a threshold. A valid one of the first throttle position and the second throttle position is selected based on the third throttle position, in response to detecting the mismatch. A signal indicative of the throttle position is outputted based on the valid one of the first throttle position and the second throttle position.

Abstract: There is described a shaft shear event detection method. The method comprises storing in memory a shaft oscillation signature determined as a function of known characteristics of the shaft and associated with a shaft shear event; monitoring a rotational speed of the shaft; detecting from the rotational speed an oscillation wave superimposed on the rotational speed by detecting a first period below a lower threshold and a second period above an upper threshold, and detecting a rate of occurrence of the first period and the second period, the oscillation wave having a wave modulation frequency corresponding to the rate of occurrence and a wave modulation amplitude; comparing the oscillation signature to the oscillation wave; and detecting the shaft shear event when the oscillation wave corresponds to the oscillation signature.

Abstract: Herein provided are methods and systems for detecting an abnormal engine start of a gas turbine engine. An inter-turbine temperature of the engine is measured during engine start. The inter-turbine temperature is compared to an inter-turbine temperature threshold which depends on at least one additional parameter. An abnormal engine start is detected when the inter-turbine temperature exceeds the threshold. The at least one additional parameter may comprise engine rotational speed. The at least one additional parameter may comprise time.

Abstract: Systems and methods for determining a throttle position of an aircraft are described herein. A first throttle position is obtained from a first sensor, a second throttle position is obtained from a second sensor, and a third throttle position is obtained from a third sensor. The first, second, and third sensors are separately coupled to a throttle of the aircraft for obtaining independent throttle position measurements therefrom. A difference between the first throttle position and the second throttle position is determined. A mismatch is detected when the difference between the first throttle position and the second throttle position exceeds a threshold. A valid one of the first throttle position and the second throttle position is selected based on the third throttle position, in response to detecting the mismatch. A signal indicative of the throttle position is outputted based on the valid one of the first throttle position and the second throttle position.

Abstract: Systems and methods for controlling thrust of an engine for an aircraft are described herein. A position of a thrust lever for controlling the engine is obtained from one or more sensors. Air data is obtained from one or more air data inputs. An air temperature data input is detected as compromised from the air data. In response to detecting the air temperature data input is compromised, a target engine rotational speed is determined based on the position of the thrust lever and at least one of altitude data and Mach number data from the air data. A rotational speed of the engine is adjusted to the target engine rotational speed to control thrust of the engine.

Abstract: Methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft are described. The method comprises detecting an abnormal engine response as a function of a fuel flow error, the fuel flow error indicative of a presence of excess thrust; in response to detecting the fuel flow error, detecting a UHT event based on the excess thrust and as a function of a threshold; and accommodating the UHT event when the UHT event is detected.

Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, detecting a fuel flow error when an actual fuel flow minus a commanded fuel flow exceeds a first threshold, the fuel flow error indicative of a presence of excess thrust, detecting a UHT event based on excess thrust and as a function of a second threshold, upon detection of the fuel flow error, and accommodating the UHT event.

Abstract: Herein provided are methods and systems for monitoring vibration in an engine. A vibration signal from at least one sensor coupled to the engine and a speed signal representative of an operating speed of the engine are received at a computing device. A target frequency of the engine is determined, at the computing device, based on the speed signal. A center frequency of a filtering system is altered, via the computing device, so that a pass-band of the filtering system contains the target frequency. The vibration signal is filtered with the filtering system to obtain a filtered vibration signal. A vibration amplitude for the engine is determined, at the computing device, based on the filtered vibration signal.

Abstract: Systems and methods for controlling thrust of an engine for an aircraft are described herein. A position of a thrust lever for controlling the engine is obtained from one or more sensors. Air data is obtained from one or more air data inputs. An air temperature data input is detected as compromised from the air data. In response to detecting the air temperature data input is compromised, a target engine rotational speed is determined based on the position of the thrust lever and at least one of altitude data and Mach number data from the air data. A rotational speed of the engine is adjusted to the target engine rotational speed to control thrust of the engine.

Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, comparing an engine fan speed to a reference target and detecting a first condition when a first threshold is exceeded, comparing a rate of change of a high pressure rotor speed to a reference deceleration schedule and detecting a second condition when a second threshold is exceeded, detecting a UHT event based on excess thrust when the first condition and the second condition are detected, and accommodating the UHT event.

Abstract: There is described a shaft shear event detection method. The method comprises storing in memory a shaft oscillation signature determined as a function of known characteristics of the shaft and associated with a shaft shear event; monitoring a rotational speed of the shaft; detecting from the rotational speed an oscillation wave superimposed on the rotational speed by detecting a first period below a lower threshold and a second period above an upper threshold, and detecting a rate of occurrence of the first period and the second period, the oscillation wave having a wave modulation frequency corresponding to the rate of occurrence and a wave modulation amplitude; comparing the oscillation signature to the oscillation wave; and detecting the shaft shear event when the oscillation wave corresponds to the oscillation signature.

Abstract: There is described a shaft shear event detection method. The method comprises storing in memory a shaft oscillation signature determined as a function of known characteristics of the shaft and associated with a shaft shear event; monitoring a rotational speed of the shaft; detecting from the rotational speed an oscillation wave superimposed on the rotational speed, the oscillation wave having a wave modulation frequency and a wave modulation amplitude; comparing the oscillation signature to the oscillation wave; and detecting the shaft shear event when the oscillation wave corresponds to the oscillation signature.

Abstract: Herein provided are methods and systems for detecting an abnormal engine start of a gas turbine engine. An inter-turbine temperature of the engine is measured during engine start. The inter-turbine temperature is compared to an inter-turbine temperature threshold which depends on at least one additional parameter. An abnormal engine start is detected when the inter-turbine temperature exceeds the threshold. The at least one additional parameter may comprise engine rotational speed. The at least one additional parameter may comprise time.

Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, comparing an engine fan speed to a reference target and detecting a first condition when a first threshold is exceeded, comparing a rate of change of a high pressure rotor speed to a reference deceleration schedule and detecting a second condition when a second threshold is exceeded, detecting a UHT event based on excess thrust when the first condition and the second condition are detected, and accommodating the UHT event.

Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, detecting a fuel flow error when an actual fuel flow minus a commanded fuel flow exceeds a first threshold, the fuel flow error indicative of a presence of excess thrust, detecting a UHT event based on excess thrust and as a function of a second threshold, upon detection of the fuel flow error, and accommodating the UHT event.

Abstract: There is described a shaft shear event detection method. The method comprises storing in memory a shaft oscillation signature determined as a function of known characteristics of the shaft and associated with a shaft shear event; monitoring a rotational speed of the shaft; detecting from the rotational speed an oscillation wave superimposed on the rotational speed, the oscillation wave having a wave modulation frequency and a wave modulation amplitude; comparing the oscillation signature to the oscillation wave; and detecting the shaft shear event when the oscillation wave corresponds to the oscillation signature.

Abstract: This application reveals a gate latch assembly in which a pivoting bolt permits substantial misalignment occur between the bolt and latch members and yet permit successful latching of the assembly.

Abstract: This application reveals a gate latch assembly in which a pivoting bolt permits substantial misalignment to occur between the bolt and latch members and yet permit successful latching of the assembly.