Abstract: The invention relates to a method (E) for detecting the ignition of a turbine engine combustion chamber, the method (E) comprising the steps of: receiving (E11) a first measurement of the exhaust gas temperature downstream from the combustion chamber, before an attempt to ignite said combustion chamber; receiving (E12) a temperature threshold; receiving (E13) a secondary detection criterion; updating (E14) the received temperature threshold as a function of the secondary detection criterion received; receiving (E15) a second measurement of the exhaust gas temperature, after the attempt to ignite the combustion chamber; comparing (E16) the updated temperature threshold with the difference between the first and second exhaust gas temperature measurements; and determining (E17) the state of ignition of the combustion chamber.

Abstract: The invention relates to a method (E) for detecting the ignition of a turbine engine combustion chamber, the method (E) comprising the steps of: receiving (E11) a first measurement of the exhaust gas temperature downstream from the combustion chamber, before an attempt to ignite said combustion chamber; receiving (E12) a temperature threshold; receiving (E13) a secondary detection criterion; updating (E14) the received temperature threshold as a function of the secondary detection criterion received; receiving (E15) a second measurement of the exhaust gas temperature, after the attempt to ignite the combustion chamber; comparing (E16) the updated temperature threshold with the difference between the first and second exhaust gas temperature measurements; and determining (E17) the state of ignition of the combustion chamber.

Abstract: The present invention concerns a method (200) for managing a breakdown of a starter valve of a starting circuit of an aircraft turbine engine, comprising the following steps: —starting (203) the turbine engine, a state-change command being sent to the starter valve in order for it to open; —increasing (204) the engine speed of the turbine engine to a predefined first threshold, —during said increase (204) in engine speed, —if a difference in position has been detected (201) between the position sensors before the step of starting the turbine engine or if a difference in position is detected (205) between said position sensors, determining (207) the position sensor that has switched between the closed position and the open position, the other position sensor having remained in the open or closed position; —when the first threshold is reached, storing (209) the position sensor that has switched between the closed position and the open position as healthy and the position sensor that has remained in the open or

Abstract: The present invention concerns a method (200) for managing a breakdown of a starter valve of a starting circuit of an aircraft turbine engine, comprising the following steps: —starting (203) the turbine engine, a state-change command being sent to the starter valve in order for it to open;—increasing (204) the engine speed of the turbine engine to a predefined first threshold,—during said increase (204) in engine speed,—if a difference in position has been detected (201) between the position sensors before the step of starting the turbine engine or if a difference in position is detected (205) between said position sensors, determining (207) the position sensor that has switched between the closed position and the open position, the other position sensor having remained in the open or closed position;—when the first threshold is reached, storing (209) the position sensor that has switched between the closed position and the open position as healthy and the position sensor that has remained in the open or clos