Abstract: A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative ( d ? ? N ? ? 2 ? ? i d ? t ) ” , and automatically stopping the engine when the current derivative ( d ? ? N ? ? 2 ? ? i d ? t ) changes sign.

Abstract: A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative ( d ? ? N ? ? 2 ? ? i d ? t ) ” , and automatically stopping the engine when the current derivative ( d ? ? N ? ? 2 ? ? i d ? t ) changes sign.

Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

Abstract: An assisted piloting method for an aircraft having at least two engines (2, 3) includes monitoring a set of parameters (Ng, T4, Tq) of the engines. A first limit indicator (10) displays information relating to a value of a limiting parameter of the engines. The limiting parameter is the parameter (Ng, T4, Tq) of the engines that is the closest to its limit. An assisted piloting mode is activated during which each parameter (Ng, T4, Tq) is maintained below a predetermined threshold whenever the first limit indicator is not in a position to display the information.

Abstract: The present invention relates to a method and to an instrument for determining the limiting margin of a surveillance parameter of a turboshaft engine. During a preliminary stage, a secondary processor means (11) determines a preliminary comfort margin. Thereafter, during a main stage, it estimates a useful comfort margin from the preliminary comfort margin, and then an apparent difference between the current value and the limit value of the surveillance parameter, and finally the limiting margin by subtracting the useful comfort margin from the apparent difference.

Abstract: An assisted piloting method for an aircraft having at least two engines (2, 3) for use in the event of a first limit indicator (10) breakdown down, a plurality of monitoring parameters (Ng, T4, Tq) of the engines (2, 3) of said aircraft being monitored, said first limit indicator (10) displaying information relating to a value of a limiting parameter of said engines (2, 3), the limiting parameter being that one of the monitoring parameter (Ng, T4, Tq) of the engines that is the closest to its limits. Under such circumstances, an assisted piloting mode is activated during which each monitoring parameter (Ng, T4, Tq) is maintained below a predetermined threshold whenever said first limit indicator (10) is not in a position to display said information.

Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.

Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.

Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.

Abstract: The present invention relates to a method and to an instrument for determining the limiting margin of a surveillance parameter of a turboshaft engine. During a preliminary stage, a secondary processor means (11) determines a preliminary comfort margin. Thereafter, during a main stage, it estimates a useful comfort margin from the preliminary comfort margin, and then an apparent difference between the current value and the limit value of the surveillance parameter, and finally the limiting margin by subtracting the useful comfort margin from the apparent difference.

Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.