Abstract: A multi-engine aircraft that includes two or more powerplants, each including an electric motor, and an electric power system controlling electrical distribution and operatively connected to the electric motors. The electric power system includes primary battery packs operatively connected to the electric motor of a respective one of the two or more powerplants, a reserve battery pack, and a switch interconnecting the reserve battery pack and the electric motors. The reserve battery pack is shared by the electric motors by the switch and configured such that the reserve battery pack provides electric power to a selected one of the electric motors.

Abstract: A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the ECU being configured to determine whether the electric motor system and/or the heat engine system are in a normal mode such that the electric motor system and/or the heat engine can provide a predetermined amount of torque (e.g., full power). The ECU can be configured to receive a total torque setting and split output power between the electric motor system and the heat engine system in accordance with the normal mode as a function of the total torque setting. The ECU can be configured to detect and command recharging or regenerating of the battery system in some flight conditions.

Abstract: Methods and systems for validating component integrity in an engine are described. First usage data associated with a period of operation of the engine is obtained at an engine controller. An indication of the first usage data is transmitted from the engine controller to a first presentation device. Second usage data associated with the period of operation of the engine is received at the engine controller from an input device. The first usage data is compared to the second usage data at the engine controller. Based on the comparing, an alert is issued to a second presentation device independent from the first presentation device.

Abstract: There is described a method for and system for starting at least one engine from a twin engine installation.

Abstract: Methods and Systems for monitoring an engine fluid level in a fluid recipient are described. In one example, the method comprises, during a fluid replenishing procedure, detecting when the fluid level reaches a level associated with the recipient being full; in response to the detecting, triggering a timer corresponding to a predetermined number of operating hours of the engine based on a fluid volume capacity of the fluid recipient; when the timer expires, verifying the fluid level; and issuing a first alert signal when the fluid level is at the level associated with the recipient being full and the timer has expired.

Abstract: Methods and systems for monitoring component integrity during operation of an engine are provided. Usage data associated with a period of operation of the engine is obtained at an engine controller. The engine controller has assigned thereto a first trust level. A first indication of the usage data is transmitted from the engine controller to a first presentation device forming part of a first communication path, which has assigned thereto a second trust level lower than the first trust level. A second indication of the usage data is transmitted from the engine controller to a second presentation device forming part of a second communication path, which is independent from the first communication path and has assigned thereto the second trust level. The trust level of the first and second communication paths is elevated by having the usage data transmitted through the first and second independent communication paths.

Abstract: Methods and Systems for monitoring an engine fluid level in a fluid recipient are described. In one example, the method comprises, during a fluid replenishing procedure, detecting when the fluid level reaches a level associated with the recipient being full; in response to the detecting, triggering a timer corresponding to a predetermined number of operating hours of the engine based on a fluid volume capacity of the fluid recipient; when the timer expires, verifying the fluid level; and issuing a first alert signal when the fluid level is at the level associated with the recipient being full and the timer has expired.

Abstract: A multi-engine aircraft that includes two or more powerplants, each including an electric motor, and an electric power system controlling electrical distribution and operatively connected to the electric motors. The electric power system includes primary battery packs operatively connected to the electric motor of a respective one of the two or more powerplants, a reserve battery pack, and a switch interconnecting the reserve battery pack and the electric motors. The reserve battery pack is shared by the electric motors by the switch and configured such that the reserve battery pack provides electric power to a selected one of the electric motors.

Abstract: A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the ECU being configured to determine whether the electric motor system and/or the heat engine system are in a normal mode such that the electric motor system and/or the heat engine can provide a predetermined amount of torque (e.g., full power). The ECU can be configured to receive a total torque setting and split output power between the electric motor system and the heat engine system in accordance with the normal mode as a function of the total torque setting. The ECU can be configured to detect and command recharging or regenerating of the battery system in some flight conditions.

Abstract: A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to receive a torque command and split output power between the electric motor system and the heat engine system. Additionally and/or alternatively, the ECU can be configured to balance a total torque against a second total torque of a second aircraft powerplant.

Abstract: A hybrid electric engine control module (ECU) can be configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to determine whether at least one of the electric motor system or the heat engine system are in a normal mode such that one of the electric motor system and/or the heat engine can provide a predetermined amount of torque. The ECU can be configured to switch to a degraded mode if either of the electric motor system or the heat engine system cannot provide the predetermined amount of torque. In the degraded mode the ECU can be configured to control the electric motor system and the heat engine system differently than in the normal mode or to not control one or both of the electric motor system or the heat engine system.

Abstract: Methods and systems for validating component integrity in an engine are described. First usage data associated with a period of operation of the engine is obtained at an engine controller. An indication of the first usage data is transmitted from the engine controller to a first presentation device. Second usage data associated with the period of operation of the engine is received at the engine controller from an input device. The first usage data is compared to the second usage data at the engine controller. Based on the comparing, an alert is issued to a second presentation device independent from the first presentation device.

Abstract: Methods and systems for monitoring component integrity during operation of an engine are provided. Usage data associated with a period of operation of the engine is obtained at an engine controller. The engine controller has assigned thereto a first trust level. A first indication of the usage data is transmitted from the engine controller to a first presentation device forming part of a first communication path, which has assigned thereto a second trust level lower than the first trust level. A second indication of the usage data is transmitted from the engine controller to a second presentation device forming part of a second communication path, which is independent from the first communication path and has assigned thereto the second trust level. The trust level of the first and second communication paths is elevated by having the usage data transmitted through the first and second independent communication paths.

Abstract: There is described a method for and system for starting at least one engine from a twin engine installation.

Abstract: There is described a method for and system for starting at least one engine from a twin engine installation.

Abstract: An overthrust protection system for an aircraft engine. The system comprises an engine overspeed protection unit comprising overspeed logic and an overspeed solenoid valve controlled by the overspeed logic, the overspeed logic configured to energize the overspeed solenoid valve for removing fuel flow to the engine upon detection of an overspeed condition of the aircraft engine; and an overthrust controller coupled to the overspeed protection unit and configured to measure engine thrust and to detect an overthrust condition when an engine thrust threshold has been exceeded, and configured to trigger energizing of the overspeed solenoid valve upon detection of the overthrust condition and an aircraft-on-ground condition.

Abstract: There is described a method for and system for starting at least one engine from a twin engine installation.

Abstract: There is described a method and system for starting at least one engine from a twin engine installation having a first engine arrangement and a second engine arrangement. The method comprises receiving a first voltage level from a power source and increasing the first voltage level to a second voltage level; charging an energy storage unit having at least a first super-capacitor and a second super-capacitor to the second voltage level; selectively connecting one of the first super-capacitor and the second super-capacitor to a first power control unit in the first engine arrangement; controlling a discharge current to a first electric machine in the first engine arrangement via the first power control unit; and rotating a rotor of the first electric machine to an above engine idle speed to start a first engine of the twin engine installation.

Abstract: An overthrust protection system for an aircraft engine. The system comprises an engine overspeed protection unit comprising overspeed logic and an overspeed solenoid valve controlled by the overspeed logic, the overspeed logic configured to energize the overspeed solenoid valve for removing fuel flow to the engine upon detection of an overspeed condition of the aircraft engine; and an overthrust controller coupled to the overspeed protection unit and configured to measure engine thrust and to detect an overthrust condition when an engine thrust threshold has been exceeded, and configured to trigger energizing of the overspeed solenoid valve upon detection of the overthrust condition and an aircraft-on-ground condition.

Abstract: There is described a method for and system for starting at least one engine from a twin engine installation.