Aircraft engine control during icing of temperature probe

A device useful in controlling an aircraft turbine engine, the device comprising:

• at least one digital processor configured to receive a first signal representative of a total temperature of inlet air using a heated temperature probe and use the first signal as a control parameter to generate a second signal useful in controlling the engine;
• memory containing machine-readable instructions for execution by the at least one processor, the machine-readable instructions causing the at least one processor to:
• detect, based on the first signal, an icing condition of the probe;
• use a substitute signal representing a substitute temperature as the control parameter instead of the first signal for producing the second signal useful in controlling the engine;
• cause deactivation of a heating element associated with the probe following the detection of the icing condition;
• and
• cause the at least one digital processor to resume the use of the first signal as the control parameter for producing the second signal useful in controlling the engine after the deactivation of the heating element.