Abstract: A pitch limit symbol is generated at an aircraft attitude indicator which provides a pilot with display of a stall warning angle of attack margin which is referenced to an airplane symbol on the primary attitude indicator. The position of the pitch limit symbol relative to the aircraft symbol is a function of the difference in angle of attack between the current angle of attack at the aircraft, and a predetermined angle of attack at which the onset of stall warning occurs. Additional information is provided on the attitude indicator by a flight path angle symbol. The pitch limit symbol together with the flight path angle symbol provides the pilot with information to achieve a positive rate of climb during a pitch up maneuver while adjusting the pitch attitude of the aircraft to avoid a stall situation. The position of the pitch limit symbol may be compensated by various means to decrease the distance between the aircraft symbol and the pitch limit symbol.This is a continuation of application Ser. No.