Abstract: A propulsion system for an aircraft comprises a closed cooling circuit which has at least one main segment and at least two secondary segments, in which a heat-transfer fluid circulates. Each secondary segment has: a leak detection device, a shut-off valve, and a non-return valve. The cooling circuit also has electronic circuitry configured to close the shut-off valve of a secondary segment when a leak is detected by the leak detection device of said secondary segment.

Abstract: The present invention refers to a method for controlling an aircraft propeller system during thrust reversal, wherein it is checked whether each power plant is ready for the transition to negative pitch, and where the propellers transition to negative pitch is controlled from a flight control system, such as only when both power plants are ready for the transition to negative pitch, the flight control system instructs the aircraft propeller system to reverse thrust. If a power plant failure is detected before a reversal order is received, then the flight control system is informed of that failure condition, and then the flight control system will disable the thrust reversal operation as long as the failure condition remains. The method of the invention improves the aircraft controllability during landing operations, reduces pilot workload, and improves passenger comfort during landing and taxing.

Abstract: The present invention refers to a method for controlling an aircraft propeller system during thrust reversal, wherein it is checked whether each power plant is ready for the transition to negative pitch, and where the propellers transition to negative pitch is controlled from a flight control system, such as only when both power plants are ready for the transition to negative pitch, the flight control system instructs the aircraft propeller system to reverse thrust. If a power plant failure is detected before a reversal order is received, then the flight control system is informed of that failure condition, and then the flight control system will disable the thrust reversal operation as long as the failure condition remains. The method of the invention improves the aircraft controllability during landing operations, reduces pilot workload, and improves passenger comfort during landing and taxing.

Abstract: A system for controlling at least one aircraft engine and an aircraft comprising such a control system are disclosed. The system (4) comprises a control lever (5), the intermediary range of automatic regulation thereof of the engine speed comprises a single marked position (II) with which there are associated a climbing speed and an automatic regulation speed. Such a lever is able to occupy another take-off and go-around marked position, with which there are associated a take-off speed and a go-around speed.

Abstract: A system for controlling at least one aircraft engine and an aircraft comprising such a control system. The system (4) comprises a control lever (5) of the engine, the intermediary range of automatic regulation thereof of the engine speed of which comprises a single marked position (II) with which there is associated a plurality of speeds, corresponding to each one of the flight phases of the aircraft (AC) such as take-off and climbing phases.

Abstract: A system for controlling at least one aircraft engine and an aircraft comprising such a control system are disclosed. The system (4) comprises a control lever (5), the intermediary range of automatic regulation thereof of the engine speed comprises a single marked position (II) with which there are associated a climbing speed and an automatic regulation speed. Such a lever is able to occupy another take-off and go-around marked position, with which there are associated a take-off speed and a go-around speed.