Abstract: A method is provided for operating an aircraft system. During this operating method, a plurality of drive units are provided that include a thermal engine drive unit and an electric machine drive unit. A mechanical load is powered using a first of the drive units. The first of the drive units includes a first rotating structure. A parameter of the first rotating structure is monitored. A failure of the first of the drive units is detected based on the monitored parameter. A switch is made from the first of the drive units to a second of the drive units to power the mechanical load where the failure of the first of the drive units is detected.

Abstract: An erroneous turboprop blade angle accommodation system includes a sensor configured to output a beta signal in response to adjusting a rotational pitch of a rotatable propeller blade, and a controller in signal communication with the sensor to receive the beta signal. The controller is configured to determine a beta angle of the rotatable propeller blade based on the beta signal and to control the rotational pitch based on an activated beta control logic. The controller is further configured to detect a beta error of the beta angle and to deactivate the beta control logic in response to detecting the beta error.

Abstract: Methods and systems for mitigating corrosion and/or erosion in an aircraft engine are provided. A method includes receiving usage data characterizing a medium accumulated inside the aircraft engine. Using a trained model, the usage data is related to an assigned aircraft engine condition from a plurality of aircraft engine conditions. The trained model is trained using machine learning and historical data relating characteristics of the medium to the plurality of aircraft engine conditions. When the assigned aircraft engine condition is indicative of a corrosion risk for the aircraft engine, a corrosion-mitigating action is initiated for the aircraft engine. When the assigned aircraft engine condition is indicative of an erosion risk for the aircraft engine, an erosion-mitigating action is initiated for the aircraft engine.

Abstract: A system and method for controlling an aircraft engine is provided. The method includes a) producing first sensor data using a first sensor sensing a first parameter during operation of the aircraft engine on a flight mission; b) producing other sensor data using a plurality of second sensors sensing a plurality of other parameters, during operation of the aircraft engine; c) providing the first and other sensor data to a control unit during operation of the aircraft engine; d) storing the first and other sensor data during operation of the aircraft engine; e) using an artificial intelligence (AI) model that is trained using the stored first and other sensor data produced during operation of the aircraft engine, to produce one or more derived first parameter values; and f) selectively providing the one or more derived first parameter values to the control unit for use in controlling the aircraft engine.

Abstract: Methods and systems for mitigating corrosion and/or erosion in an aircraft engine are provided. A method includes receiving usage data characterizing a medium accumulated inside the aircraft engine. Using a trained model, the usage data is related to an assigned aircraft engine condition from a plurality of aircraft engine conditions. The trained model is trained using machine learning and historical data relating characteristics of the medium to the plurality of aircraft engine conditions. When the assigned aircraft engine condition is indicative of a corrosion risk for the aircraft engine, a corrosion-mitigating action is initiated for the aircraft engine. When the assigned aircraft engine condition is indicative of an erosion risk for the aircraft engine, an erosion-mitigating action is initiated for the aircraft engine.

Abstract: An erroneous turboprop blade angle accommodation system includes a sensor configured to output a beta signal in response to adjusting a rotational pitch of a rotatable propeller blade, and a controller in signal communication with the sensor to receive the beta signal. The controller is configured to determine a beta angle of the rotatable propeller blade based on the beta signal and to control the rotational pitch based on an activated beta control logic. The controller is further configured to detect a beta error of the beta angle and to deactivate the beta control logic in response to detecting the beta error.

Abstract: A method for monitoring a bleed valve of an aircraft engine includes obtaining operational data of the aircraft engine, the operational data indicative of operational performance of the aircraft engine. The method further includes utilizing one or more neural networks to determine a health status of a bleed valve of the aircraft engine based on the operational data, the bleed valve configured to bleed air from a compressor section of the aircraft engine, wherein the one or more neural networks have been trained with root cause data relating to a plurality of potential failure modes of the bleed valve.

Abstract: A method for monitoring a bleed valve of an aircraft engine includes obtaining operational data of the aircraft engine, the operational data indicative of operational performance of the aircraft engine. The method further includes utilizing one or more neural networks to determine a health status of a bleed valve of the aircraft engine based on the operational data, the bleed valve configured to bleed air from a compressor section of the aircraft engine, wherein the one or more neural networks have been trained with root cause data relating to a plurality of potential failure modes of the bleed valve.

Abstract: An assembly for recording rotor blade replacement data for a bladed rotor includes an imaging device and a processing system. The imaging device is configured to capture image data for the bladed rotor including a plurality of rotor blades. The processing system is configured to identify each of the plurality of rotor blades installed on the bladed rotor in pre-repair image data of the captured image data and store a pre-repair position of each of the identified plurality of rotor blades installed on the bladed rotor in the pre-repair image data, identify each of the plurality of rotor blades installed on the bladed rotor in post-repair image data and store a post-repair position of each of the identified plurality of rotor blades installed on the bladed rotor in the post-repair image data, and identify at least one replaced rotor blade installed on the bladed rotor in the post-repair image data using the pre-repair image data and the post-repair image data.

Abstract: Methods and systems for mitigating corrosion and/or erosion in an aircraft engine are provided. A method includes receiving usage data characterizing a medium accumulated inside the aircraft engine. Using a trained model, the usage data is related to an assigned aircraft engine condition from a plurality of aircraft engine conditions. The trained model is trained using machine learning and historical data relating characteristics of the medium to the plurality of aircraft engine conditions. When the assigned aircraft engine condition is indicative of a corrosion risk for the aircraft engine, a corrosion-mitigating action is initiated for the aircraft engine. When the assigned aircraft engine condition is indicative of an erosion risk for the aircraft engine, an erosion-mitigating action is initiated for the aircraft engine.

Abstract: A method of mitigating corrosion and erosion in an aircraft engine, includes: receiving a concentration of contaminants contained within a sample of an environmental medium ingested by the aircraft engine; determining a frequency of corrosion and erosion mitigation actions based on the concentration of the contaminants; and instructing a performance of the corrosion and erosion mitigation actions at the frequency.

Abstract: A system and method for controlling an aircraft engine is provided. The method includes a) producing first sensor data using a first sensor sensing a first parameter during operation of the aircraft engine on a flight mission; b) producing other sensor data using a plurality of second sensors sensing a plurality of other parameters, during operation of the aircraft engine; c) providing the first and other sensor data to a control unit during operation of the aircraft engine; d) storing the first and other sensor data during operation of the aircraft engine; e) using an artificial intelligence (AI) model that is trained using the stored first and other sensor data produced during operation of the aircraft engine, to produce one or more derived first parameter values; and f) selectively providing the one or more derived first parameter values to the control unit for use in controlling the aircraft engine.

Abstract: A method and system for processing parameter values from a redundant sensor configured to sense a parameter used in the control of an aircraft engine is provided. The method includes: a) receiving a plurality of parameter values from a redundant sensor by sensing the same parameter at the same time; b) identifying mismatched parameter values; c) producing a predicted parameter value using an artificial intelligence (AI) model having a database of parameter values representative of the sensed parameter; d) providing the predicted parameter value to a control unit; and e) operating the control unit to select a first parameter value or a second parameter value using the predicted parameter for use in the control of the aircraft engine.

Abstract: A method is provided for operating an aircraft system. During this operating method, a plurality of drive units are provided that include a thermal engine drive unit and an electric machine drive unit. A mechanical load is powered using a first of the drive units. The first of the drive units includes a first rotating structure. A parameter of the first rotating structure is monitored. A failure of the first of the drive units is detected based on the monitored parameter. A switch is made from the first of the drive units to a second of the drive units to power the mechanical load where the failure of the first of the drive units is detected.

Abstract: A method is provided involving a turbine engine. During this method, data is received indicative of twist of a shaft of the turbine engine. The data is monitored over time to identity one or more reversal events while the turbine engine is operating, where each of the reversal events corresponds to a reversal in a value sign of the data. Shaft shear is identified in the shaft based on occurrence of N number of the reversal events.

Abstract: A method is provided involving a turbine engine. During this method, data is received indicative of twist of a shaft of the turbine engine. The data is monitored over time to identity one or more reversal events while the turbine engine is operating, where each of the reversal events corresponds to a reversal in a value sign of the data. Shaft shear is identified in the shaft based on occurrence of N number of the reversal events.

Abstract: Herein provided are systems and methods for synchrophasing multi-engine aircraft. A phonic wheel is coupled to a first propeller of a first engine of the aircraft. A sensor is disposed and configured for producing a signal in response to passage of first and second position markers on the phonic wheel. A control system is communicatively coupled to the sensor for obtaining the signal, and configured for: determining an expected delay between two subsequent signal pulses of the signal; identifying from within the plurality of signal pulses a particular pulse associated with the second position marker; determining, based on a particular time at which the particular pulse associated with the second position marker was produced, that a rotational position of the first propeller corresponds to a reference position at the particular time; and performing at least one synchrophasing operation for the aircraft based on the rotational position of the first propeller.

Abstract: Herein provided are systems and methods for synchrophasing multi-engine aircraft. A phonic wheel is coupled to a first propeller of a first engine of the aircraft. A sensor is disposed and configured for producing a signal in response to passage of first and second position markers on the phonic wheel. A control system is communicatively coupled to the sensor for obtaining the signal, and configured for: determining an expected delay between two subsequent signal pulses of the signal; identifying from within the plurality of signal pulses a particular pulse associated with the second position marker; determining, based on a particular time at which the particular pulse associated with the second position marker was produced, that a rotational position of the first propeller corresponds to a reference position at the particular time; and performing at least one synchrophasing operation for the aircraft based on the rotational position of the first propeller.