(b)
The net takeo. .ight path data must be determined so that they represent the actual takeo. .ight paths, as determined in accordance with Sec. 23.57 and with paragraph(a) of this section, reduced at eachpointby agradient of climb equal to–

(1)
0.8 percent for two-engine airplanes;

(2)
0.9 percent for three-engine airplanes; and

(3)
1.0 percent for four-engine airplanes.

(c)
Theprescribedreductionin climbgradient maybe applied as an equivalent reduction in acceleration along that part of the takeo. .ight path at which the airplane is accelerated in level .ight.]

Amdt. 23-34, E.. 02/17/87
′
Elodie Roux. Septembre 2003
Subpart B : Flight
FAR 23.63 : Climb : general.
(a)
[Compliance with the requirements of Secs. 23.65, 23.66, 23.67, 23.69, and 23.77 must be shown–

(1)
Out ofground e.ect; and

(2)
Atspeeds that are notless than those at which compliance with thepowerplant cooling requirements ofSecs.23.1041 to23.1047hasbeendemonstrated; and

(3)
Unless otherwise speci.ed, with one engine inoperative, at a bank angle not exceeding 5 degrees.

(b)
For normal, utility, and acrobatic category reciprocating engine-powered airplanes of 6,000 pounds or less maximum weight, compliance must be shown with Sec. 23.65(a), Sec. 23.67(a), where appropriate, and Sec. 23.77(a) at maximum takeo. or landing weight, as appropriate, in a standard atmosphere.

(c)
For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than6,000pounds maximum weight, and turbine engine-powered airplanesin the normal, utility, and acrobatic category, compliance must be shown at weights as a function of airport altitude and ambient temperature, within the operational limits established for takeo. and landing, respectively, with–

(1)
Sections23.65(b) and23.67(b)(1) and(2), where appropriate,fortakeo., and

(2)
Section 23.67(b)(2), where appropriate, and Sec. 23.77(b), for landing.

(d)
For commuter categoryairplanes, compliance mustbe shown at weights as afunction of airport altitude and ambient temperature within the operational limits establi-shed for takeo. and landing, respectively, with–

(1) Sections 23.67(c)(1), 23.67(c)(2), and 23.67(c)(3) for takeo.; and

(2)
Sections 23.67(c)(3), 23.67(c)(4), and 23.77(c) for landing.] Amdt. 23-50, E.. 03/11/96

FAR 23.65 : Climb : all engines operating.

(a)
[Eachnormal, utility, and acrobatic category reciprocating engine-powered airplane of 6,000 pounds or less maximum weight must have a steady climb gradient at sea level of at least 8.3 percent for landplanes or 6.7 percent for seaplanes and amphibians with–

(1)
Not morethan maximum continuouspower on each engine;

(2)
The landing gear retracted;

(3)
Thewing .apsinthetakeo.position(s); and

(4)
A climb speed notless than thegreater of1.1 VMC and1.2 VS1 for multiengine airplanes and not less than 1.2 VS1 for single-engine airplanes.

(b)
Each normal, utility, and acrobatic category reciprocating engine-powered airplane of morethan6,000poundsmaximum weightand turbine engine-powered airplanes inthe normal, utility, and acrobaticcategory musthavea steadygradient of climb after takeo. of at least 4 percent with

(1)
Takeo.power on each engine;

(2)
The landing gear extended, except that if the landing gear can be retracted in not more than seven seconds, the test may be conducted with the gear retracted;

(3) Thewing .apsinthetakeo.position(s); and
(4) A climb speed as speci.ed in Sec. 23.65(a)(4).] Amdt. 23-50, E.. 03/11/96
FAR23.66:[Takeo.climb: oneengineinoperative.]
[For normal, utility, and acrobatic category reciprocating engine-powered airplanes of more than 6,000 pounds maximum weight, and turbine engine-powered airplanes in the normal, utility, and acrobatic category,the steadygradient of climb ordescent must be determined at each weight, altitude, and ambient temperature within the operational limits established by the applicant with–
　
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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(126)