PILOT SUPPORT SYSTEM OF AN AIRCRAFT DURING STALL

The method involves determining a pitch angle limiting value representative of a maximum admissible angle of incidence, depends on a set of flight parameters and aircraft configurations. A maximum angle of incidence pointer (33) indicating pitch angle limiting value is displayed on pitch scale (23) of the display screen. The maximum angle of incidence pointer and trajectory pointer (27) is provided to form upper and lower limits of dynamic safety envelope (37) representative of normal flight of the aircraft respectively. An independent claim is included for a system to assist piloting of aircraft.