The flight control indicator may include a set of information sources, a computation unit connected to said set of information sources, and a head-up display device. The computation unit determines, on the basis of information emanating from the set of information sources, at least one maximum total slope of the aircraft. The maximum total slope corresponds to the maximum thrust and is obtained on the basis of the measurement of the current performance of the aircraft, extrapolated to the condition of maximum slope and in anticipation of an engine fault. The head-up display device presents, on a display screen, at least one indicator which indicates the maximum total slope and which is presented superimposed on the environment existing in front of the aircraft.