(b) The wings level stall characteristics must be demonstrated in flight as follows. Starting from a speed at least 10 knots above the stall speed, the elevator control must be pulled back so that the rate of speed reduction will not exceed one knot per second until a stall is produced, as shown by either:
(1) An uncontrollable downward pitching motion of the airplane;
(2) A downward pitching motion of the airplane that results from the activation of a stall avoidance device (for example, stick pusher); or
(3) The control reaching the stop.
(c) Normal use of elevator control for recovery is allowed after the downward pitching motion of paragraphs (b)(1) or (b)(2) of this section has unmistakably been produced, or after the control has been held against the stop for not less than the longer of two seconds or the time employed in the minimum steady slight speed determination of §23.49.
(d) During the entry into and the recovery from the maneuver, it must be possible to prevent more than 15 degrees of roll or yaw by the normal use of controls.
(e) Compliance with the requirements of this section must be shown under the following conditions:
(1) Wing flaps. Retracted, fully extended, and each intermediate normal operating position.
(2) Landing gear. Retracted and extended.
(3) Cowl flaps. Appropriate to configuration.
(i) Power off; and
(ii) 75 percent of maximum continuous power. However, if the power-to-weight ratio at 75 percent of maximum continuous power result in extreme nose-up attitudes, the test may be carried out with the power required for level flight in the landing configuration at maximum landing weight and a speed of 1.4 VSO, except that the power may not be less than 50 percent of maximum continuous power.
(5) Trim. The airplane trimmed at a speed as near 1.5 VS1as practicable.
(6) Propeller. Full increase r.p.m. position for the power off condition.
[Doc. No. 27807, 61 FR 5191, Feb. 9, 1996]