Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

Abstract: A method of driving a rotorcraft rotor (1, 2) at variable controlled speeds. Starting from a required speed (Nr), a setpoint for total power (Pt) is calculated while taking account of an anticipated power (Pf) to be delivered by the power plant (3) for driving the main rotor (1) at the required speed (Nr), and while taking account of a power surplus (S) relating to progressive power needs to be delivered from a current power (Pc) for driving the main rotor (1) at a current speed (V) of rotation to an anticipated power (Pf) for driving the main rotor (1) at the required speed (Nr). By way of example, account may be taken at least of the acceleration or conversely of the deceleration of the main rotor (1) between the current speed (V) and the required speed (Nr), or indeed account may be taken of the flight circumstance of the rotorcraft 30 determining the calculated required speed (Nr).

Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch maneuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

Abstract: A method of driving a rotorcraft rotor (1, 2) at variable controlled speeds. Starting from a required speed (Nr), a setpoint for total power (Pt) is calculated while taking account of an anticipated power (Pf) to be delivered by the power plant (3) for driving the main rotor (1) at the required speed (Nr), and while taking account of a power surplus (S) relating to progressive power needs to be delivered from a current power (Pc) for driving the main rotor (1) at a current speed (V) of rotation to an anticipated power (Pf) for driving the main rotor (1) at the required speed (Nr). By way of example, account may be taken at least of the acceleration or conversely of the deceleration of the main rotor (1) between the current speed (V) and the required speed (Nr), or indeed account may be taken of the flight circumstance of the rotorcraft 30 determining the calculated required speed (Nr).

Abstract: A control method for controlling an overspeed safety system (5) of an aircraft (1) having at least a first engine (10) and a second engine (20), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold.

Abstract: A method of driving a rotorcraft rotor (1, 2) at variable controlled speeds. Starting from a required speed (Nr), a setpoint for total power (Pt) is calculated while taking account of an anticipated power (Pf) to be delivered by the power plant (3) for driving the main rotor (1) at the required speed (Nr), and while taking account of a power surplus (S) relating to progressive power needs to be delivered from a current power (Pc) for driving the main rotor (1) at a current speed (V) of rotation to an anticipated power (Pf) for driving the main rotor (1) at the required speed (Nr). By way of example, account may be taken at least of the acceleration or conversely of the deceleration of the main rotor (1) between the current speed (V) and the required speed (Nr), or indeed account may be taken of the flight circumstance of the rotorcraft determining the calculated required speed (Nr).

Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

Abstract: A method of driving a rotorcraft rotor (1, 2) at variable controlled speeds. Starting from a required speed (Nr), a setpoint for total power (Pt) is calculated while taking account of an anticipated power (Pf) to be delivered by the power plant (3) for driving the main rotor (1) at the required speed (Nr), and while taking account of a power surplus (S) relating to progressive power needs to be delivered from a current power (Pc) for driving the main rotor (1) at a current speed (V) of rotation to an anticipated power (Pf) for driving the main rotor (1) at the required speed (Nr). By way of example, account may be taken at least of the acceleration or conversely of the deceleration of the main rotor (1) between the current speed (V) and the required speed (Nr), or indeed account may be taken of the flight circumstance of the rotorcraft determining the calculated required speed (Nr).

Abstract: A method of monitoring at least one limited-lifetime part. During an identification step (STP1), storage means (40) store a list including a reference for each limited-lifetime part of an engine (3). During an information-search step (STP2), the storage means (40) communicate with a centralized data system (DB) in order to store for each identified part the corresponding maintenance data. During a monitoring step (STP3), the wear of the engine is monitored by using the information stored in the storage means (40).

Abstract: A control method for controlling an overspeed safety system (5) of an aircraft (1) having at least a first engine (10) and a second engine (20), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold.