(1)
For reciprocatingengine-powered airplanes,the engine(s)idling, the throttle(s) closed or at not more than the power necessary for zero thrust at a speed not morethan110percent of the stalling speed;

(2)
For turbine engine-powered airplanes, the propulsive thrust not greater than zero at the stalling speed, or, if the resultant thrust has no appreciable e.ect on the stalling speed, with engine(s) idling and throttle(s) closed;

(3)
The propeller(s) in the takeo. position;

(4)
The airplane in the condition existing in the test, in which VS0 and VS1 are being used;

(5)
The center of gravity in the position that results in the highest value of VS0 and VS1 ; and

(6)
The weight used when VS0 or VS1 are being used as a factor to determine compliance with a requiredperformance standard.

(b)
VS0 and VS1 must be determined by .ight tests, using the procedure and meeting the .ight characteristics speci.ed in Sec. 23.201.

(c)
Except asprovidedinparagraph(d) ofthis section, VS0 at maximum weight must not exceed 61 knots for–

(1)
Single-engine airplanes; and

(2)
Multiengine airplanes of 6,000 pounds or less maximum weight that cannot meet the minimum rate of climb speci.ed in Sec. 23.67(a)(1) with the critical engine inoperative.

(d)
All single-engine airplanes, and those multi-engine airplanes of6,000pounds orless maximum weight with a VS0 of more than 61 knots that do not meet the require-ments of Sec. 23.67(a)(1), must comply with Sec. 23.562(d).]

Amdt. 23-50, E.. 03/11/96
′
Elodie Roux. Septembre 2003
Subpart B : Flight
FAR23.51 :Takeo.[speeds.]
(a)
[For normal, utility, andacrobatic category airplanes, rotation speed, VR,isthe speed at which the pilot makes a control input, with the intention of lifting the airplane out of contact with the runway or water surface.

(1)
For multienginelandplanes,VR, must notbeless than thegreater of1.05 VMC ; or 1.10 VS1 ;

(2)
For single-engine landplanes, VR, must not be less than VS1 ; and

(3)
For seaplanes and amphibians taking o. from water, VR, may be any speed that is shown to be safe under all reasonably expected conditions, including turbulence and complete failure of the critical engine.

(b)
For normal, utility, and acrobatic category airplanes, the speed at 50 feet above the takeo. surface level must not be less than :

(1)
For multiengine airplanes, the highest of–

(i)
Aspeedthatisshowntobesafeforcontinued .ight(oremergencylan-ding, if applicable) under all reasonable expected conditions, including turbulence and complete failure of the critical engine;

(ii)
1.10 VMC ; or

(iii) 1.20 VS1.

(2)
For single-engine airplanes, the higher of–

(i)
A speed thatis shown tobe safe under all reasonably expected conditions, including turbulence and complete enginefailure; or

(ii)
1.20 VS1.

(c)
For commuter category airplanes, the following apply :

(1)
V1 must be established in relation to VEF as follows :

(i)
VEF is the calibrated airspeed at which the critical engine is assumed to fail. VEF mustbe selectedby the applicantbut must notbeless than1.05 VMC determined under Sec. 23.149(b) or, at the option of the applicant, not less than VMCG determined under Sec. 23.149(f)

(ii)
The takeo.decision speed, V1,is the calibrated airspeed on theground at which, as a result of enginefailure or other reasons, thepilotis assumedto have made a decision to continue or discontinue the takeo.. The takeo. decision speed, V1, must be selected by the applicant but must not be less than VEF plus the speed gained with the critical engine inoperative during the time interval between the instant at which the critical engine is failed and the instant at which the pilot recognizes and reacts to the enginefailure,asindicatedby thepilot’sapplicationof the .rstretarding means during the accelerate-stop determination of Sec. 23.55.
　
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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(123)