Abstract: A method and device for aiding the monitoring of a turbine engine of an aircraft, which displays on one and the same indicator of a of a display indication elements illustrating as a percentage the engine start progression or the current sub-idle state of the turbine engine, a margin to a limit temperature of the turbine engine, a margin to a maximum temperature of the turbine engine and a margin to a possible failure of the start that is generated by a too low speed increase of the turbine engine.

Abstract: A method and device aids in monitoring at least one turbine engine in an aircraft. The method includes determining a value illustrating a thermomechanical state of the turbine engine, and comparing the determined value with at least one threshold. The method also includes displaying in the cockpit of the aircraft, at least one indication related to the operation of the turbine engine, according to this comparison. As a result, conditions that could result in mechanical degradation or failure of the turbine engine are identified for a crew of the aircraft.

Abstract: The device displays on one and the same indicator (11) of display means (7) indication elements (14, 16, 17, 33) illustrating as a percentage the engine start progression or the current sub-idle state of the turbine engine, a margin to a possible exceeding of a limit temperature of the turbine engine, a margin to a possible exceeding of a maximum temperature of the turbine engine and a margin to a possible failure of the start that is generated by a too low speed increase of the turbine engine.

Abstract: The device includes means for determining a value illustrating a thermomechanical state (ET) of the turbine engine, means for comparing this value with at least one threshold (S1, S2) and means for displaying in the cockpit of the aircraft, at least one indication (I1 to I3) related to the operation of the turbine engine, according to this comparison.