FIELD: aviation.
SUBSTANCE: invention relates to aircraft gas turbine engine starting circuit start-up valve malfunction monitoring method (200), including the following stages: gas turbine engine (100) starting (203), wherein a start command is sent to the start-up valve to open it; increasing (204) mode of gas turbine engine to the first predetermined threshold; during said increase (204) of gas turbine engine (100) mode: if detected (201) deviation between position sensors before gas turbine engine start-up phase or if deviation (205) is detected between position sensors, determination (207) of position sensor, switched between closed position and open position, wherein other position sensor remained in open or closed position; when first threshold is reached, memorizing (209) position sensor, switched between closed position and open position, as serviceable, and position sensor, left in open or closed position, as faulty, in order to measure the state of the start-up valve only based on the position of a good position sensor. Also disclosed are an aircraft gas turbine engine and a starting circuit.
EFFECT: invention makes it possible to ensure safety of flights without spending additional means and without complicating operation of the aircraft.
10 cl, 7 dwg
