Abstract: An aircraft engine diagnostic system includes at least one sensor and a diagnostic controller. The at least one sensor measures a parameter of a gas turbine engine. The diagnostic controller is in signal communication with the at least one sensor. The diagnostic controller determines an actual thrust output of the gas turbine engine and an execution of at least one control system limiter configured to limit control of the gas turbine engine based on the measured parameter. The diagnostic controller further determines an existence of an engine fault based on the actual thrust output of the gas turbine engine and an execution of the at least one control system limiter.

Abstract: An aircraft engine diagnostic system includes at least one sensor and a diagnostic controller. The at least one sensor measures a parameter of a gas turbine engine. The diagnostic controller is in signal communication with the at least one sensor. The diagnostic controller determines an actual thrust output of the gas turbine engine and an execution of at least one control system limiter configured to limit control of the gas turbine engine based on the measured parameter. The diagnostic controller further determines an existence of an engine fault based on the actual thrust output of the gas turbine engine and an execution of the at least one control system limiter.

Abstract: A shaft event is detected, such as a shaft shear, a shaft decoupling, and/or a shaft failure in a gas turbine engine comprising a first spool and a second spool different from the first spool. First and second parameters indicative of the power of the first spool and a load transfer through a shaft of the second spool are obtained. A detection threshold is determined as a function of the first parameter. The second parameter is compared to the detection threshold. The shaft event is detected when the second parameter is beyond the detection threshold and then a signal indicative of the shaft event is transmitted.

Abstract: There is described herein methods and systems for detecting a shaft event, such as a shaft shear, a shaft decoupling, and/or a shaft failure in a gas turbine engine comprising a first spool and a second spool different from the first spool. A first parameter indicative of one of power of the first spool and a load transfer through a shaft of the second spool is obtained and a second parameter indicative of the other one of power of the first spool and the load transfer through the shaft of the second spool is obtained. A detection threshold is determined as a function of the first parameter. The second parameter is compared to the detection threshold. The shaft event is detected when the second parameter is beyond the detection threshold and then a signal indicative of the shaft event is transmitted.

Abstract: A system and method for controlling a variable inlet geometry mechanism of an aircraft engine. At least one first input signal indicative of at least one operating parameter of an aircraft engine is received. At least one second input signal indicative of a level of crosswind experienced by the aircraft and of an airspeed of the aircraft being below a predetermined threshold is received. A schedule is determined for positioning a the variable inlet geometry mechanism based on the at least one first input signal and of the at least one second input signal. The variable inlet geometry mechanism is then positioned in accordance with the schedule.

Abstract: A system and method for controlling a variable inlet geometry mechanism of an aircraft engine. At least one first input signal indicative of at least one operating parameter of an aircraft engine is received. At least one second input signal indicative of a level of crosswind experienced by the aircraft and of an airspeed of the aircraft being below a predetermined threshold is received. A schedule is determined for positioning a the variable inlet geometry mechanism based on the at least one first input signal and of the at least one second input signal. The variable inlet geometry mechanism is then positioned in accordance with the schedule.