(ii)
Reducethe airplane speed usingpitch control at a rate of approximately 1knotper second untilthepitch control reachesthe stop;then, with thepitch controlpulledback andheld againstthe stop,apply full rudder control in a manner to promote spin entry for a period of 7 seconds or through a 360 degree heading change, whichever occurs .rst. If the 360 degree heading change is reached .rst, it must have taken no fewer than 4 seconds. This maneuver must be performed .rst with the ailerons in the neutral position, and then with the ailerons de.ected opposite the direction of turn in the most adverse manner. Power and airplane con.-guration must be set in accordance with Sec. 23.201(e) without change during the maneuver. At the end of 7 seconds or a 360 degree heading change,the airplane must respondimmediately and normally toprimary

.ight controls applied to regain coordinated, unstalled .ight without re-versal of control e.ect and without exceedingthe temporary controlforces speci.ed by Sec. 23.143(c); and
(iii) Compliance withSecs.23.201and23.203 mustbedemonstrated with the airplane in uncoordinated .ight, corresponding to one ball width displa-cement on a slip-skidindicator, unless oneball widthdisplacement cannot be obtained with full rudder, in which case the demonstration must be with full rudder applied.
(b)
Utility category airplanes. A utility category airplane must meet the requirements of paragraph(a) of this section. In addition, the requirements ofparagraph(c) of this section and Sec. 23.807(b)(7) must be met if approval for spinning is requested.

(c)
Acrobatic category airplanes. An acrobatic category airplane must meet the spin requirements ofparagraph(a) ofthis section andSec. 23.807(b)(6).In addition, the following requirements must be met in each con.guration for which approval for spinning is requested :

(1)
The airplane must recover from any point in a spin up to and including six turns, or anygreater number ofturnsfor which certi.cationis requested,in not morethanoneand one-half additional turnsafterinitiationof the .rst control actionfor recovery.However,beyond3 turns,the spin may bediscontinuedif spiral characteristics appear.

(2)
Theapplicableairspeedlimitsandlimit maneuveringloadfactorsmustnotbe exceeded. For .aps-extended con.gurations for which approval is requested, the .aps must not be retracted during the recovery.

(3)
It must be impossible to obtain unrecoverable spins with any use of the .ight or engine power controls either at the entry into or during the spin.

(4)
There must be no characteristicsduring the spin(such as excessive rates of ro-tation or extreme oscillatory motion) that mightprevent a successful recovery due to disorientation or incapacitation of the pilot.]

Amdt. 23-50, E.. 03/11/96
29.9 Ground and Water Handling Characteristics
FAR 23.231 : Longitudinal stability and control.
(a)
A landplane may have no uncontrollable tendency to nose over in any reasonably expected operating condition, including rebound during landing or takeo.. Wheel brakes must operate smoothly and may not induce any undue tendency to nose over.

(b)
A seaplaneoramphibian may nothavedangerousoruncontrollableporpoising cha-racteristics at any normal operating speed on the water.

FAR 23.233 : Directional stability and control.

(a)
[A 90 degree cross-component ofwind velocity, demonstrated to be safe for taxiing, takeo., and landing must be established and must be not less than 0.2 VS0.]

(b)
The airplane must be satisfactorily controllable in power-o. landings at normal landing speed, without using brakes or engine power to maintain a straight path until the speed has decreased to at least 50 percent of the speed at touchdown.

′
Elodie Roux. Septembre 2003
Subpart B : Flight
(c)
The airplane must have adequate directional control during taxiing.
　
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 1(139)