Abstract: A device for controlling a propeller, having variable-pitch blades, of a turboprop engine, has a first hydromechanical device for controlling the pitch of the blades of the propeller and a second hydromechanical device for controlling the speed of rotation of the propeller. The device includes a single electromechanical actuator with a movable actuator member mechanically connected both to the first hydromechanical device for controlling the pitch, in order to manage the pitch setpoint, and to the second hydromechanical device for controlling the speed, in order to manage the speed setpoint.

Abstract: A device for controlling a propeller, having variable-pitch blades, of a turboprop engine, has a first hydromechanical device for controlling the pitch of the blades of the propeller and a second hydromechanical device for controlling the speed of rotation of the propeller. The device includes a single electromechanical actuator with a movable actuator member mechanically connected both to the first hydromechanical device for controlling the pitch, in order to manage the pitch setpoint, and to the second hydromechanical device for controlling the speed, in order to manage the speed setpoint.

Abstract: A method to optimize resources needed to continue flight if at least one main engine is lost, by relieving a propulsion system that has remained operative of all or some of non-propulsive energy demands, by additional generation of non-propulsive power, operating continuously. The method uses a GPP unit that operates constantly in flight while taking up some of nominal total non-propulsive power of the aircraft, to supply increased non-propulsive power almost instantaneously, based on at least three respective emergency regimes at a time of engine failure. A control and monitoring function of the GPP calculates elapsed time for each emergency regime, and informs a data processing unit thereof, while emitting an alarm if operating periods allocated to each emergency regime are exceeded, and the emergency function adjusts non-propulsive power demands made by the aircraft between main engines and the unit GPP either automatically or on orders of a pilot.

Abstract: A method to optimize resources needed to continue flight if at least one main engine is lost, by relieving a propulsion system that has remained operative of all or some of non-propulsive energy demands, by additional generation of non-propulsive power, operating continuously. The method uses a GPP unit that operates constantly in flight while taking up some of nominal total non-propulsive power of the aircraft, to supply increased non-propulsive power almost instantaneously, based on at least three respective emergency regimes at a time of engine failure. A control and monitoring function of the GPP calculates elapsed time for each emergency regime, and informs a data processing unit thereof, while emitting an alarm if operating periods allocated to each emergency regime are exceeded, and the emergency function adjusts non-propulsive power demands made by the aircraft between main engines and the unit GPP either automatically or on orders of a pilot.