Abstract: Systems and methods for diagnosing an engine or an aircraft are described herein. Flight data of at least one of the engine and the aircraft is obtained. A graph-based representation modeling a mathematical relationship between parameters of at least one of the engine and the aircraft is obtained. The graph-based representation has a plurality of permutations. Output data for the plurality of permutations is generated based on the flight data. The output data for the plurality of permutations is compared and a fault is detected based on a discrepancy in the output data. A signal indicative of the fault is outputted in response to detecting the fault.

Abstract: Methods and systems for setting a target power of an aircraft engine are described herein. A power lever position is obtained. At least one flight condition indicative of a phase of flight of the aircraft is obtained. A maximum rated power of the engine is determined for one or more engine rating based on the phase of flight. The target power of the engine is set based on the power lever position and the maximum rated power of the one or more engine ratings.

Abstract: Systems and methods for diagnosing an engine or an aircraft are described herein. Flight data of at least one of the engine and the aircraft is obtained. A graph-based representation modeling a mathematical relationship between parameters of at least one of the engine and the aircraft is obtained. The graph-based representation has a plurality of permutations. Output data for the plurality of permutations is generated based on the flight data. The output data for the plurality of permutations is compared and a fault is detected based on a discrepancy in the output data. A signal indicative of the fault is outputted in response to detecting the fault.

Abstract: Methods and systems for setting a target power of an aircraft engine are described herein. A power lever position is obtained. At least one flight condition indicative of a phase of flight of the aircraft is obtained. A maximum rated power of the engine is determined for one or more engine rating based on the phase of flight. The target power of the engine is set based on the power lever position and the maximum rated power of the one or more engine ratings.

Abstract: The disclosure teaches an improvement in a free turbine type engine which comprises a power limit unit. The unit includes a first sensor for measuring pressure at the turbine inlet, and a second sensor for measuring temperature at the turbine inlet. A third means provides a measurement indicative of turbine exhaust pressure and may be a sensor located in the exhaust duct which is downstream of the turbine or may comprise means for providing outside ambient pressure readily available from existing aircraft instrumentation, e.g., altimeter. A processor means calculates shaft horse power (SHP) from the above measurements. Other means are provided for generating a reference signal, and the reference signal is compared with SHP. When SHP is greater than the reference signal, then fuel to the engine is controlled to reduce engine power. The unit can also be adapted for calculating torque, and for reducing the torque when the torque is greater than the reference level.