(2)
Takeo., landing gear retracted. The steady gradient of climb at an altitude of 400 feet above the takeo. surface must not be less than 2.0 percent for two-engine airplanes, 2.3 percent for three-engine airplanes, and 2.6 percent for four-engine airplanes with–

(i)
The critical engine inoperative and its propeller in the position it rapidly and automatically assumes;

(ii)
The remaining engine(s) attakeo.power;

(iii) The landing gear retracted;
(iv)
Thewing .apsinthetakeo.position(s);

(v)
A climb speed equal to V2.

(3)
Enroute. The steady gradient of climb at an altitude of 1,500 feet above the takeo. orlanding surface, as appropriate, mustbe notless than1.2percentfor two-engine airplanes, 1.5 percent for three-engine airplanes, and 1.7 percent for four-engine airplanes with–

(i)
The critical engine inoperative and its propeller in the minimum drag position;

(ii)
The remaining engine(s) at not more than maximum continuous power;

(iii) The landing gear retracted;
(iv)
The wing .aps retracted; and

(v)
A climb speed not less than 1.2 VS1.

(4) Discontinued approach. The steady gradient of climb at an altitude of 400 feet above the landing surface must be not less than 2.1 percent for two-engine airplanes, 2.4 percent for three-engine airplanes, and 2.7 percent for four-engine airplanes, with–
(i)
The critical engine inoperative and its propeller in the minimum drag position;

(ii)
The remaining engine(s) attakeo.power;

(iii) Landing gear retracted;
(iv)
Wing .apsintheapproachposition(s)inwhich VS1 for theseposition(s) does notexceed110percent ofthe VS1 forthe relatedall-engines-operating landing position(s); and

(v)
A climb speed established in connection with normal landing procedures

but not exceeding 1.5 VS1.] Amdt. 23-50, E.. 03/11/96
FAR23.69 :[Enroute climb/descent.]
(a)
[All engines operating. The steady gradient and rate of climb must be determined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with–

(1)
Not more than maximum continuous power on each engine;

(2)
The landing gear retracted;

(3)
The wing .aps retracted; and

(4)
A climb speed not less than 1.3 VS1 .

(b)
One engine inoperative.The steadygradient and rate of climb/descent mustbede-termined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with–

(1)
The criticalengineinoperative anditspropellerin the minimumdragposition;

(2)
The remaining engine(s) at not more than maximum continuous power;

(3)
The landing gear retracted;

(4)
The wing .aps retracted; and

(5)
A climb speed not less than 1.2 VS1 .] Amdt. 23-50, E.. 03/11/96

FAR23.71:[Glide: single-engineairplanes.]
[The maximum horizontal distance traveled in still air, in nautical miles, per 1,000 feet of altitudelostin aglide, and the speed necessaryto achieve this mustbedetermined with the engineinoperative,itspropellerin the minimumdragposition, andlandinggear and wing .apsinthemostfavorableavailableposition.] Amdt. 23-50, E.. 03/11/96
′
Elodie Roux. Septembre 2003
Subpart B : Flight
FAR23.73:[Referencelanding approach speed.]
(a)
[For normal, utility, andacrobatic category reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, the reference landing approach speed, VREF, must notbeless than thegreater of VMC, determinedinSec.23.149(b) with the wing .aps in the most extended takeo. position, and 1.3 VS0.

(b)
For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than6,000pounds maximum weight, and turbine engine-powered airplanes in the normal, utility, andacrobatic category, the referencelanding approach speed, VREF, must not be less than thegreater of VMC, determined in Sec. 23.149(c), and
　
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本文鏈接地址：FAA規(guī)章 美國聯邦航空規(guī)章 Federal Aviation Regulations 1(128)