Abstract: A fuel circuit of an aircraft engine including a fuel tank; an engine fuel system including a low-pressure pump and a high-pressure pump, and a fuel recirculating pipeline connected to the engine fuel system; and a fuel recirculating valve arranged so as to switch between an open position and a closed position according to the pressure differential of the low-pressure pump, the valve being able to obstruct the fuel recirculating pipeline in the closed position, and to bring the fuel recirculating pipeline into communication with the fuel tank in the open position.

Abstract: A method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit including a fuel tank, an engine fuel system connected to the fuel tank capable of delivering a flow of fuel to the engine depending on a speed of the engine, a fuel return pipe connected between the engine fuel system and the fuel tank, a fuel return valve arranged to switch between an open and closed position, the valve being capable of blocking the fuel return pipe in the closed position, and of bringing the fuel return pipe into communication with the fuel tank in the open position, the method including measuring a pressure of the flow of fuel from the fuel tank, and if the measured pressure is lower than a predefined threshold, measuring the engine speed.

Abstract: A method detects a failure in a fuel return valve of an aircraft engine fuel circuit. A fuel system is connected to a fuel tank of the circuit and includes a high-pressure pump delivering a flow rate to an actuating cylinder, a cutoff valve capable of feeding the actuating cylinder disposed in a feed pipe of the engine; a fuel return pipe; a fuel return valve arranged to switch between an open position and a closed position. The method includes starting the engine at an engine speed; increasing the engine speed until a flow rate reaches a predefined value sufficient for opening the cutoff valve; measuring the position of the actuating cylinder and an engine speed corresponding to the opening of said cutoff valve.

Abstract: A method detects a failure in a fuel return valve of an aircraft engine fuel circuit. A fuel system is connected to a fuel tank of the circuit and includes a high-pressure pump delivering a flow rate to an actuating cylinder, a cutoff valve capable of feeding the actuating cylinder disposed in a feed pipe of the engine; a fuel return pipe; a fuel return valve arranged to switch between an open position and a closed position. The method includes starting the engine at an engine speed; increasing the engine speed until a flow rate reaches a predefined value sufficient for opening the cutoff valve; measuring the position of the actuating cylinder and an engine speed corresponding to the opening of said cutoff valve.

Abstract: A method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit including a fuel tank, an engine fuel system connected to the fuel tank capable of delivering a flow of fuel to the engine depending on a speed of the engine, a fuel return pipe connected between the engine fuel system and the fuel tank, a fuel return valve arranged to switch between an open and closed position, the valve being capable of blocking the fuel return pipe in the closed position, and of bringing the fuel return pipe into communication with the fuel tank in the open position, the method including measuring a pressure of the flow of fuel from the fuel tank, and if the measured pressure is lower than a predefined threshold, measuring the engine speed.

Abstract: The invention relates to a method for testing equipment with variable geometries of an aircraft engine, especially turbomachine. In a first phase, a computer tests the chain of controls of the fuel dosage function. In a second phase, said computer tests the jacks of the chains of controls of equipment with variable geometries by keeping the aircraft shut-off valve open during rod extensions of jacks and by controlling the injection shut-off valve to expel fuel into the injection chamber during their rod retractions.

Abstract: A fuel circuit of an aircraft engine including a fuel tank; an engine fuel system including a low-pressure pump and a high-pressure pump, and a fuel recirculating pipeline connected to the engine fuel system; and a fuel recirculating valve arranged so as to switch between an open position and a closed position according to the pressure differential of the low-pressure pump, the valve being able to obstruct the fuel recirculating pipeline in the closed position, and to bring the fuel recirculating pipeline into communication with the fuel tank in the open position.

Abstract: The invention relates to a method for testing equipment with variable geometries of an aircraft engine, especially turbomachine. In a first phase, a computer tests the chain of controls of the fuel dosage function. In a second phase, said computer tests the jacks of the chains of controls of equipment with variable geometries by keeping the aircraft shut-off valve open during rod extensions of jacks and by controlling the injection shut-off valve to expel fuel into the injection chamber during their rod retractions.

Abstract: The aircraft refuelling equipment (20) of an aircraft comprises a pipework (22) in which a fuel supply line (13) is connected to a plurality of tank supply lines, fuel tanks connected to tank supply lines of the pipework, first valves (24, 25,26) allowing each fuel tank to be disconnected from the fuel supply line, and at least one captor (30) that provides a signal indicative of a pressure or a flow rate. For each of said first valves, a first valve flow parameter can be estimated, using said captor. The equipment further comprises:—at least one actuator associated with each of said first valves, the actuator allowing adjustment of the opening of the associated first valve; and an electronic control unit (ECU) connected to the respective actuator-first valve assemblies and adapted to regulate an opening of the first ECU valves, using respective first valve flow parameter data.

Abstract: The aircraft refuelling equipment (20) of an aircraft comprises a pipework (22) in which a fuel supply line (13) is connected to a plurality of tank supply lines, fuel tanks connected to tank supply lines of the pipework, first valves (24, 25,26) allowing each fuel tank to be disconnected from the fuel supply line, and at least one captor (30) that provides a signal indicative of a pressure or a flow rate. For each of said first valves, a first valve flow parameter can be estimated, using said captor. The equipment further comprises:—at least one actuator associated with each of said first valves, the actuator allowing adjustment of the opening of the associated first valve; and an electronic control unit (ECU) connected to the respective actuator-first valve assemblies and adapted to regulate an opening of the first ECU valves, using respective first valve flow parameter data.