Federal Aviation Administration, DOT § 23.203

least plus and minus 15 percent is sud- roll or yaw by the normal use of con- denly released, the response of the air- trols. plane must not exhibit any dangerous (f) Compliance with the requirements characteristics nor be excessive in rela- of this section must be shown under tion to the magnitude of the control the following conditions: force released. Any long-period oscilla- (1) Wing flaps: Retracted, fully ex- tion of flight path, phugoid oscillation, tended, and each intermediate normal that results must not be so unstable as operating position, as appropriate for to increase the pilot’s workload or oth- the phase of flight. erwise endanger the airplane. (2) : Retracted and ex- tended as appropriate for the altitude. [Amdt. 23–21, 43 FR 2318, Jan. 16, 1978, as (3) Cowl flaps: Appropriate to configu- amended by Amdt. 23–45, 58 FR 42158, Aug. 6, 1993; Amdt. 23–62, 76 FR 75755, Dec. 2, 2011] ration. (4) Spoilers/speedbrakes: Retracted and STALLS extended unless they have no measureable effect at low speeds. § 23.201 Wings level . (5) Power: (a) It must be possible to produce and (i) Power/Thrust off; and to correct roll by unreversed use of the (ii) For reciprocating engine powered rolling control and to produce and to airplanes: 75 percent of maximum con- correct yaw by unreversed use of the tinuous power. However, if the power- directional control, up to the time the to-weight ratio at 75 percent of max- airplane stalls. imum continuous power results in (b) The wings level stall characteris- nose-high attitudes exceeding 30 de- tics must be demonstrated in flight as grees, the test may be carried out with follows. Starting from a speed at least the power required for level flight in 10 knots above the stall speed, the ele- the landing configuration at maximum vator control must be pulled back so landing weight and a speed of 1.4 VSO, that the rate of speed reduction will except that the power may not be less not exceed one knot per second until a than 50 percent of maximum contin- stall is produced, as shown by either: uous power; or (1) An uncontrollable downward (iii) For turbine engine powered air- pitching motion of the airplane; planes: The maximum engine thrust, (2) A downward pitching motion of except that it need not exceed the the airplane that results from the acti- thrust necessary to maintain level vation of a stall avoidance device (for flight at 1.5 VS1 (where VS1 corresponds example, stick pusher); or to the stalling speed with flaps in the (3) The control reaching the stop. approach position, the landing gear re- (c) Normal use of control for tracted, and maximum landing weight). recovery is allowed after the downward (6) Trim: At 1.5 VS1 or the minimum pitching motion of paragraphs (b)(1) or trim speed, whichever is higher. (b)(2) of this section has unmistakably (7) Propeller: Full increase r.p.m. posi- been produced, or after the control has tion for the power off condition. been held against the stop for not less [Doc. No. 27807, 61 FR 5191, Feb. 9, 1996, as than the longer of two seconds or the amended by Amdt. 23–62, 76 FR 75755, Dec. 2, time employed in the minimum steady 2011] slight speed determination of § 23.49. (d) During the entry into and the re- § 23.203 Turning flight and accelerated covery from the maneuver, it must be turning stalls. possible to prevent more than 15 de- Turning flight and accelerated turn- grees of roll or yaw by the normal use ing stalls must be demonstrated in of controls except as provided for in tests as follows: paragraph (e) of this section. (a) Establish and maintain a coordi- (e) For airplanes approved with a nated turn in a 30 degree bank. Reduce maximum operating altitude at or speed by steadily and progressively above 25,000 feet during the entry into tightening the turn with the elevator and the recovery from stalls performed until the airplane is stalled, as defined at or above 25,000 feet, it must be pos- in § 23.201(b). The rate of speed reduc- sible to prevent more than 25 degrees of tion must be constant, and—

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