Abstract: A humidity control system and method for controlling the humidity of ambient air is disclosed. The system includes a humidification and dehumidification systems to increase and/or decrease the humidity level of an indoor space and a sensor to sense ambient conditions of the space. The system further includes a controller that receives a humidity setpoint for the indoor space, determines the humidity level associated with the indoor space, compares the determined humidity level to the humidity setpoint, and causes activation of one of a humidification system or a dehumidification system. In response to causing the activation of one of the humidification or dehumidification system, the controller initiates a lockout condition during which the other of the one of the humidification or dehumidification system is prevented from activation. The controller also monitors for an override condition and enables activation of the other of the humidification system or the dehumidification system accordingly.

Abstract: A method for calibrating a position sensor of a variable vane assembly for a gas turbine engine includes positioning an actuator member in at least one predetermined position, determining a first measured position of the actuator member in the at least one predetermined position with a first channel of a position sensor, determining a second measured position of the actuator member in the at least one predetermined position with a second channel of a position sensor, determining a measured position difference between the first measured position and the second measured position, and calibrating the second channel of the position sensor by adjusting the second measured position by the measured position difference to determine a second calibrated position.

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: 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: The present disclosure provides methods and systems for fault detection for a speed sensing system of a multi-engine rotorcraft. A shaft speed for a first engine and a rotor speed for at least one rotor of the multi-engine rotorcraft are obtained. The shaft speed is compared to the rotor speed. When the shaft speed is greater than the rotor speed, a first fault in the speed sensing system is detected and a first speed sensing system fault signal is issued. When the shaft speed is less than the rotor speed, a determination is made regarding whether the first engine is coupled the at least one rotor based on a fuel flow to the first engine. A second fault in the speed sensing system is detected and a second speed sensing system fault signal is issued responsive to determining that the first engine is coupled to the at least one rotor.

Abstract: There is provided a monitoring method and system for an aircraft engine. At an engine controller, a current value of an ageing parameter of at least one component of the aircraft engine is obtained, the at least one component having a life limit associated therewith. Based on the current value of the ageing parameter, it is determined, at the engine controller, whether the life limit of the at least one component has been reached. A start of the aircraft engine is inhibited, at the engine controller, when the life limit of the at least one component has been reached.

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: Methods and systems for operating an aircraft powerplant comprising an engine coupled to a variable-pitch propeller capable of generating forward and reverse thrust are described herein. A request to enable a mode for automated reverse thrust is received. Reverse thrust conditions are determined to have been met when the aircraft is on-ground, a blade angle of the propeller is below a blade angle threshold and a position of a power lever is at a selected idle region of the power lever. Reverse thrust of the propeller is triggered when the mode for automated reverse thrust is enabled and the reverse thrust conditions have been met.

Abstract: A system and a method for fault detection for a liquid level sensing device are provided. The liquid level sensing device comprising a plurality of switches arranged to measure variance in a liquid level. A sensing signal comprising a plurality of measurements indicative of the liquid level is received from the liquid level sensing device. Each measurement is obtained in response to one or more of the plurality of switches being in a given position at a given liquid level. It is determined, based on the sensing signal, whether the liquid level changed according to one or more expected change patterns. A fault signal is output in response to determining that the liquid level changed according to an abnormal change pattern.

Abstract: The present disclosure provides methods and systems for fault detection for a speed sensing system of a multi-engine rotorcraft. A shaft speed for a first engine and a rotor speed for at least one rotor of the multi-engine rotorcraft are obtained. The shaft speed is compared to the rotor speed. When the shaft speed is greater than the rotor speed, a first fault in the speed sensing system is detected and a first speed sensing system fault signal is issued. When the shaft speed is less than the rotor speed, a determination is made regarding whether the first engine is coupled the at least one rotor based on a fuel flow to the first engine. A second fault in the speed sensing system is detected and a second speed sensing system fault signal is issued responsive to determining that the first engine is coupled to the at least one rotor.

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 validating a fluid level sensor having a floating element are provided. First readings are acquired from the fluid level sensor indicative of fluid levels sensed via the floating element during a first period of operation of the fluid level sensor. A validated range of fluid levels for the fluid level sensor is determined based on the first readings. At least one second reading is acquired from the fluid level sensor during a second period of operation, subsequent to the first period of operation. A starting position of the floating element for the second period of operation is determined based on the at least one second reading. When the starting position of the floating element is within the validated range, validating the at least one second reading.

Abstract: Systems and methods for operating an engine in a multi-engine rotorcraft are described herein. A first parameter indicative of torque of a first engine is obtained. A decrease of the first parameter is detected. In response to detecting the decrease of the first parameter, an autorotation of the rotorcraft is accommodated, A second parameter indicative of torque of a second engine of the rotorcraft is assessed while accommodating the autorotation. If the second parameter has not decreased, a shaft shear of the first engine is identified and accommodating of the autorotation is ended. If the second parameter has decreased, the accommodating is maintained.

Abstract: A method and system are described for detecting a fault of a fluid level sensing device associated with an aircraft engine, the fluid level sensing device arranged to measure a variance in a fluid level. The method comprises triggering a timer, while the timer is running, receiving a measurement indicative of the fluid level from the fluid level sensing device, resetting the timer when at least one timer-reset condition has been met, and outputting a fault signal when the timer reaches a timer threshold.

Abstract: Methods and systems for validating a fluid level sensor having a floating element are provided. First readings are acquired from the fluid level sensor indicative of fluid levels sensed via the floating element during a first period of operation of the fluid level sensor. A validated range of fluid levels for the fluid level sensor is determined based on the first readings. At least one second reading is acquired from the fluid level sensor during a second period of operation, subsequent to the first period of operation. A starting position of the floating element for the second period of operation is determined based on the at least one second reading. When the starting position of the floating element is within the validated range, validating the at least one second reading.

Abstract: Methods and systems for operating an aircraft powerplant are described herein. One or more powerplant or aircraft parameters indicative of one or more conditions at landing or during an approach to landing are obtained. A reverse thrust rating is determined based on the one or more powerplant or aircraft parameters. Reverse thrust of the powerplant is controlled based on the reverse thrust rating when reverse thrust is requested.

Abstract: A method and system are described for detecting a fault of a fluid level sensing device associated with an aircraft engine, the fluid level sensing device arranged to measure a variance in a fluid level. The method comprises triggering a timer, while the timer is running, receiving a measurement indicative of the fluid level from the fluid level sensing device, resetting the timer when at least one timer-reset condition has been met, and outputting a fault signal when the timer reaches a timer threshold.

Abstract: Methods and systems for operating an aircraft powerplant comprising an engine coupled to a variable-pitch propeller capable of generating forward and reverse thrust are described herein. A request to enable a mode for automated reverse thrust is received. Reverse thrust conditions are determined to have been met when the aircraft is on-ground, a blade angle of the propeller is below a blade angle threshold and a position of a power lever is at a selected idle region of the power lever. Reverse thrust of the propeller is triggered when the mode for automated reverse thrust is enabled and the reverse thrust conditions have been met.

Abstract: Systems and methods for operating an engine in a multi-engine rotorcraft are described herein. A first parameter indicative of torque of a first engine is obtained. A decrease of the first parameter is detected. In response to detecting the decrease of the first parameter, an autorotation of the rotorcraft is accommodated, A second parameter indicative of torque of a second engine of the rotorcraft is assessed while accommodating the autorotation. If the second parameter has not decreased, a shaft shear of the first engine is identified and accommodating of the autorotation is ended. If the second parameter has decreased, the accommodating is maintained.

Abstract: A method and system for managing power to an engine controller operatively coupled to an engine of an aircraft are described. The method comprises powering the engine controller from an aircraft battery, starting a timer in response to a predetermined trigger to maintain the engine controller powered by the aircraft battery for a predetermined time, and removing power from the aircraft battery to the engine controller when the timer expires.