Sec. 25.207 - Stall warning.
(a) Stall warning with sufficient margin to prevent inadvertent stalling with the flaps and landing gear in any normal position must be clear and distinctive to the pilot in straight and turning flight.
(b) The warning must be furnished either through the inherent aerodynamic qualities of the airplane or by a device that will give clearly distinguishable indications under expected conditions of flight. However, a visual stall warning device that requires the attention of the crew within the cockpit is not acceptable by itself. If a warning device is used, it must provide a warning in each of the airplane configurations prescribed in paragraph (a) of this section at the speed prescribed in paragraphs (c) and (d) of this section.
(c) When the speed is reduced at rates
not exceeding one knot per second, stall warning must begin, in each
normal configuration, at a speed, V
(d) In addition to the requirement of
paragraph (c) of this section, when the speed is reduced at rates not
exceeding one knot per second, in straight flight with engines idling and
at the center-of-gravity position specified in §25.103(b)(5), V
(e) The stall warning margin must be
sufficient to allow the pilot to prevent stalling (as defined in
§25.201(d)) when recovery is initiated not less than one second after the
onset of stall warning in slow-down turns with at least 1.5g load factor
normal to the flight path and airspeed deceleration rates of at least 2
knots per second, with the flaps and landing gear in any normal position,
with the airplane trimmed for straight flight at a speed of 1.3 V
(f) Stall warning must also be provided in each abnormal configuration of the high lift devices that is likely to be used in flight following system failures (including all configurations covered by Airplane Flight Manual procedures).
[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25-7, 30 FR 13118, Oct. 15, 1965; Amdt. 25-42, 43 FR
2322, Jan. 16, 1978; Amdt. 1-49, 67 FR 70827, Nov. 26, 2002]