A piloting assistance method for an aircraft, for assisting the aircraft crew in recovering the aircraft from a stall condition, said method comprising at least the following steps: - an angle of attack reduction step (E1), implemented by a first angle of attack reduction unit at a predetermined time after a stall warning has been transmitted in the event of a lack of response from the crew, the angle of attack reduction step (E1) comprising a computation sub-step involving generating a first nose down target angle of attack and converting this first target angle of attack into a first pitch command, and a display sub-step involving displaying, on at least one vertical display system of the aircraft (AC), at least one first indicator representing said first pitch command; - a stabilization step (E3), implemented by a stabilization unit after the angle of attack reduction step (E1), said stabilization step (E3) comprising a computation sub-step involving generating a second nose up target angle of attack and converting this second target angle of attack into a second pitch command, and a second display sub-step involving displaying, on the vertical display system of the aircraft (AC), at least one second indicator representing said second pitch command; - a roll control step (E2), implemented by a roll control unit , comprising a computation sub-step involving converting a target roll angle into a roll command and a display sub-step involving displaying, on at least one lateral display system of the aircraft (AC), at least one indicator representing said roll command, the roll control step (E2) being implemented from the moment when the lateral bank angle of the aircraft (AC) is greater than a predetermined value and the pitch angle of the aircraft (AC) is negative, until the end of the stabilization step (E3), the method being characterized in that if, when the stabilization step (E3) is implemented, the current angle of attack of the aircraft (AC) approaches a predetermined additional margin of a stall warning angle of attack, the angle of attack reduction step (E1) is implemented again instead of said stabilization step (E3). - an angle of attack reduction step (E1), implemented by a first angle of attack reduction unit at a predetermined time after a stall warning has been transmitted in the event of a lack of response from the crew, the angle of attack reduction step (E1) comprising a computation sub-step involving generating a first nose down target angle of attack and converting this first target angle of attack into a first pitch command, and a display sub-step involving displaying, on at least one vertical display system of the aircraft (AC), at least one first indicator representing said first pitch command; - a stabilization step (E3), implemented by a stabilization unit after the angle of attack reduction step (E1), said stabilization step (E3) comprising a computation sub-step involving generating a second nose up target angle of attack and converting this second target angle of attack into a second pitch command, and a second display sub-step involving displaying, on the vertical display system of the aircraft (AC), at least one second indicator representing said second pitch command; - a roll control step (E2), implemented by a roll control unit , comprising a computation sub-step involving converting a target roll angle into a roll command and a display sub-step involving displaying, on at least one lateral display system of the aircraft (AC), at least one indicator representing said roll command, the roll control step (E2) being implemented from the moment when the lateral bank angle of the aircraft (AC) is greater than a predetermined value and the pitch angle of the aircraft (AC) is negative, until the end of the stabilization step (E3), <EOS>