CS 25.203 Stall characteristics

• ED Decision 2003/2/RM found in: CS-25 Amdt 27 - Large Aeroplanes (Jan 2023)

CS 25.203 Stall characteristics ED Decision 2003/2/RM (See [AMC 25.203](#_DxCrossRefBm1709820871).) (a) It must be possible to produce and to correct roll and yaw by unreversed use of aileron and rudder controls, up to the time the aeroplane is stalled. No abnormal nose-up pitching may occur. The longitudinal control force must be positive up to and throughout the stall. In addition, it must be possible to promptly prevent stalling and to recover from a stall by normal use of the controls. (b) For level wing stalls, the roll occurring between the stall and the completion of the recovery may not exceed approximately 20°. (c) For turning flight stalls, the action of the aeroplane after the stall may not be so violent or extreme as to make it difficult, with normal piloting skill, to effect a prompt recovery and to regain control of the aeroplane. The maximum bank angle that occurs during the recovery may not exceed – (1) Approximately 60° in the original direction of the turn, or 30°in the opposite direction, for deceleration rates up to 0.5 m/s2 (1 knot per second); and (2) Approximately 90° in the original direction of the turn, or 60°in the opposite direction, for deceleration rates in excess of 0.5 m/s2 (1 knot per second).