(2)
The speeds VMC, VO, VLE, and VLO, if established, and their signi.cance.

(3)
[In addition, for turbine poweredcommuter category airplanes–

′
Elodie Roux. Septembre 2003
Subpart G : Operating Limitations and Information
(i)
The maximum operating limit speed, VMO/MMO and a statement that thisspeed must notbedeliberately exceededinany regimeof.ight(climb, cruise, ordescent) unlessahigherspeedisauthorizedfor .ighttest orpilot training;]

(ii)
Ifan airspeedlimitationisbased upon compressibility e.ects, a statement tothis e.ect andinformation asto any symptoms,theprobablebehavior of the airplane, and the recommended recoveryprocedures; and

(iii) The airspeed limits must be shown in terms of VMO/MMO instead of VNO and VNE.
(b)
Powerplant limitations. The following information must be furnished :

(1)
Limitations required by Sec. 23.1521.

(2)
Explanation of the limitations, when appropriate.

(3)
Information necessary for marking the instruments required by Secs. 23.1549 through Sec. 23.1553.

(c)
Weight. The airplane .ight manual must include–

(1)
The maximum weight; and

(2)
The maximum landing weight, if the design landing weight selected by the applicant is less than the maximum weight.

(3)
[For normal, utility, andacrobatic category reciprocating engine-powered air-planes of more than 6,000 pounds maximum weight and for turbine engine-powered airplanesinthe normal, utility, and acrobatic category,performance operating limitations as follows–

(i)
The maximum takeo. weight for each airport altitude and ambient tem-perature within the range selected by the applicant at which the airplane complies with the climb requirements of Sec. 23.63(c)(1).

(ii)
The maximum landing weight for each airport altitude and ambient tem-perature within the range selected by the applicant at which the airplane complies with the climb requirements of Sec. 23.63(c)(2).

(4)
For commuter categoryairplanes, the maximum takeo. weightfor each airport altitude and ambient temperature within the range selected by the applicant at which–

(i)
The airplane complies with the climb requirements of Sec. 23.63(d)(1); and

(ii)
The accelerate-stop distance determined under Sec. 23.55 is equal to the availablerunwaylengthplusthelength ofany stopway,if utilized; and either :

(iii) The takeo.distancedetermined under Sec. 23.59(a)is equal to the avai-lable runway length; or
(iv) At the option of the applicant, the takeo. distance determined under Sec. 23.59(a) is equal to the available runway length plus the length of any clearway and the takeo. run determined under Sec. 23.59(b)is equal to the available runway length.

(5)
For commuter categoryairplanes,the maximumlanding weightfor each airport altitude within the range selected by the applicant at which–

(i)
The airplane complies with the climb requirements of Sec. 23.63(d)(2) for ambient temperatures within the range selected by the applicant; and

(ii)
The landing distance determined under Sec. 23.75 for standard tempera-tures is equal to the available runway length.

(6) The maximum zero wing fuel weight, where relevant, as established in accor-dance with Sec. 23.343.
(d)
Center of gravity. The established center of gravity limits.

(e)
Maneuvers. The following authorized maneuvers, appropriate airspeed limitations, and unauthorized maneuvers, as prescribed in this section.

(1)
Normal category airplanes. No acrobatic maneuvers, including spins, are au-thorized.

(2)
Utility category airplanes. A list of authorized maneuvers demonstrated in the type .ight tests, together with recommended entry speeds and any other associated limitations. No other maneuver is authorized.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 3(3)