Abstract: A hybrid-electric powerplant (HEP) of an aircraft comprises a thermal engine providing a first torque input to the HEP and an electric motor providing a second torque input to the HEP. A power management system connected to one or both of the thermal engine and the electric motor comprises an engine control unit (ECU) connected to the thermal engine. The ECU controls fuel supplied to the thermal engine. An electric propulsion control (EPC) is connected to the electric motor and controls power supplied to the electric motor. The EPC includes an EPC protection module in communication with a power source for the electric motor. The EPC protection module disables power supplied to the electric motor upon receipt of a signal indicative of one or more of an over-speed condition and an over-torque condition detected in the HEP.

Abstract: The method can include, while the airplane is on the ground: entering a disking mode including positioning the blades at a disking pitch including rotating each blade around the length, the disking pitch oriented parallel to the plane of rotation; maintaining the blades at the disking pitch; and exiting the disking mode when a disking mode exit condition is met, including rotating each blade around the length, away from the disking pitch.

Abstract: A method of deactivating a liquid distribution system of a gas turbine engine in the event of a fire condition includes introducing a quantity of air into the liquid distribution system at a location upstream of a liquid pump of the liquid distribution system. The quantity of air is greater than a liquid discharge capacity of the liquid pump, thereby starving the liquid pump.

Abstract: There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.

Abstract: A method of deactivating a liquid distribution system of a gas turbine engine in the event of a fire condition includes introducing a quantity of air into the liquid distribution system at a location upstream of a liquid pump of the liquid distribution system. The quantity of air is greater than a liquid discharge capacity of the liquid pump, thereby starving the liquid pump.

Abstract: The described gas turbine engine includes a fire mitigation system in fluid system thereof, and includes an air-introduction component located in a fluid conveying conduit upstream of a liquid pump of the fluid system. The air-introduction component has a sacrificial element which remains in place during normal operation of the gas turbine engine but has a heat-induced failure point lower than that of a remainder of the fluid conveying conduit such that it fails when exposed to a threshold temperature greater than the heat-induced failure point. Failure of the sacrificial element allows air introduction into the fluid conveying conduit upstream of the liquid pump, thereby starving the liquid pump in the event of a fire condition generating the threshold temperature.

Abstract: There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.

Abstract: There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.

Abstract: The described gas turbine engine includes a fire mitigation system in fluid system thereof, and includes an air-introduction component located in a fluid conveying conduit upstream of a liquid pump of the fluid system. The air-introduction component has a sacrificial element which remains in place during normal operation of the gas turbine engine but has a heat-induced failure point lower than tat of a remainder of the fluid conveying conduit such that it fails when exposed to a threshold temperature greater than the heat-induced failure point. Failure of the sacrificial element allows air introduction into the fluid conveying conduit upstream of the liquid pump, thereby starving the liquid pump in the event of a fire condition generating the threshold temperature.

Abstract: There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. The method comprises measuring a resistance value across a magnetic chip detector mounted to a fluid system of the aircraft engine and transmitting the resistance value to an engine computer of the aircraft engine. The method further comprises, in the engine computer, comparing the resistance value to a first threshold and issuing a first warning indicative of a chip in the fluid when the resistance value exceeds the first threshold.

Abstract: The present disclosure describes methods and systems for automatically detecting and calculating an offset of an engine-based pressure measurement transducer after engine shutdown, and applying a correction factor to subsequent pressure measurements of the transducer once the engine is in operation.