Abstract: A method for limiting torque on a rotorcraft. The rotorcraft comprises an installation having a rotor, the installation including at least three motors driving a power transmission gearbox, the MGB including a rotor mast for moving the rotor. The method comprises a step of determining a engine torque limit for each of at least the three motors, each engine torque limit being established by a control computer of the aircraft by taking into consideration the distribution among the at least three motors of the total power (Ptot) delivered by the at least three motors for enabling the rotorcraft to operate.

Abstract: A method for limiting torque on a rotorcraft. The rotorcraft comprises an installation having a rotor, the installation including at least three motors driving a power transmission gearbox, the MGB including a rotor mast for moving the rotor. The method comprises a step of determining a engine torque limit for each of at least the three motors, each engine torque limit being established by a control computer of the aircraft by taking into consideration the distribution among the at least three motors of the total power (Ptot) delivered by the at least three motors for enabling the rotorcraft to operate.

Abstract: A method of managing a loss of power from a power plant having three engines. During a monitoring step, each engine is monitored in order to detect whether the engine is suffering a loss of power. During a verification step, it is determined whether the power plant is overpowered. During a signalling step, a first alert is generated when an engine has lost power but the power plant is in fact overpowered, and a second alert different from the first alert is generated when an engine has lost power and the power plant is not overpowered.

Abstract: A method of starting a turboshaft engine (5) of an aircraft (1), said aircraft (1) being provided with a rotary wing, said aircraft (1) having a freewheel (15) interposed in a drive train (10) between said engine (5) and a rotor (2) of said rotary wing (1), said engine (5) comprising a gas generator (6) and a free turbine (9), the drive train (10) including an upstream portion (11) connecting said free turbine (9) to said freewheel (15), the method comprising the following steps: measuring the torque (Tq) exerted on said upstream portion (11), and measuring a speed of rotation (Ng) of said gas generator (6); comparing said torque (Tq) with a torque threshold (Stq) and comparing said speed of rotation (Ng) with a gas generator speed threshold (Sng); and stopping said engine (5) when said torque (Tq) is less than the torque threshold (Stq) and when said speed of rotation (Ng) is greater than the gas generator speed threshold (Sng).

Abstract: A method of managing a loss of power from a power plant having three engines. During a monitoring step, each engine is monitored in order to detect whether the engine is suffering a loss of power. During a verification step, it is determined whether the power plant is overpowered. During a signalling step, a first alert is generated when an engine has lost power but the power plant is in fact overpowered, and a second alert different from the first alert is generated when an engine has lost power and the power plant is not overpowered.

Abstract: A method of starting a turboshaft engine (5) of an aircraft (1), said aircraft (1) being provided with a rotary wing, said aircraft (1) having a freewheel (15) interposed in a drive train (10) between said engine (5) and a rotor (2) of said rotary wing (1), said engine (5) comprising a gas generator (6) and a free turbine (9), the drive train (10) including an upstream portion (11) connecting said free turbine (9) to said freewheel (15), the method comprising the following steps: measuring the torque (Tq) exerted on said upstream portion (11), and measuring a speed of rotation (Ng) of said gas generator (6); comparing said torque (Tq) with a torque threshold (Stq) and comparing said speed of rotation (Ng) with a gas generator speed threshold (Sng); and stopping said engine (5) when said torque (Tq) is less than the torque threshold (Stq) and when said speed of rotation (Ng) is greater than the gas generator speed threshold (Sng).

Abstract: A method of starting a turboshaft engine (5) of an aircraft (1), said aircraft (1) being provided with a rotary wing, said aircraft (1) having a freewheel (15) interposed in a drive train (10) between said engine (5) and a rotor (2) of said rotary wing (1), said engine (5) comprising a gas generator (6) and a free turbine (9), the drive train (10) including an upstream portion (11) connecting said free turbine (9) to said freewheel (15), the method comprising the following steps: measuring the torque (Tq) exerted on said upstream portion (11), and measuring a speed of rotation (Ng) of said gas generator (6); comparing said torque (Tq) with a torque threshold (Stq) and comparing said speed of rotation (Ng) with a speed threshold (Sng); and stopping said engine (5) when said torque (Tq) is less than the torque threshold (Stq) and when said speed of rotation (Ng) is greater than the speed threshold (Sng).