Abstract: A method for protecting, on spin-up, an aircraft engine including a power supply source, an engine with a rotor and associated with a starter system to, when supplied with power, produce a mechanical force to spin the rotor. The method includes an acquisition step performed continuously, wherein the engine control avionics acquire rotational speed of the rotor, a comparison step wherein the engine control avionics continuously compare acquired rotational speed against a predetermined rotational speed, and a checking step wherein the engine control avionics check that rotation of the rotor corresponds to deliberate pilot action, and if so, the engine control avionics authorize supply of power to the starter system, and, if not, in a deactivation step, the engine control avionics disconnect the engine starter system from its power supply source in order to stop the rotation of the rotor.

Abstract: The invention relates to a control method of a measurement supplied by a first turbomachine sensor (20), by means of a first channel (3), and by a second turbomachine sensor (22), by means of a second communication channel (4), and also comprising the steps of: acquisition of a first signal from the first communication channel (3), and of a second signal from the second communication channel (4), determination of a validity status of each of the acquired signals, and transmission of a signal to be processed.