(b)
For multiengine rotorcraft,informationidentifyingeach operating conditionin which thefuel systemindependenceprescribedinSec.29.953is necessaryfor safety must be furnished, together with instructions for placing the fuel system in a con.gura-tion used to show compliance with that section.

(c)
For helicopters for which a VNE (power-o.) is established under Sec. 29.1505(c), information must be furnished to explain the VNE (power-o.)and the procedures for reducing airspeed to not more than the VNE (power-o.)following failure of all engines.

(d)
Foreach rotorcraft showing compliancewithSec.29.1353(c)(6)(ii) or(c)(6)(iii),the operating procedures for disconnecting the battery from its charging source must be furnished.

(e)
If the unusable fuel supply in any tank exceeds 5 percent of the tank capacity, or 1 gallon, whichever is greater, information must be furnished which indicates that when the fuel quantity indicator reads ”zero” in level .ight, any fuel remaining in the fuel tank cannot be used safely in .ight.

(f)
Information on the totalquantity of usablefuelfor eachfuel tank mustbe furnished.

(g)
[For Category B rotorcraft, the airspeeds and corresponding rotor speeds for mi-nimum rate of descent and best glide angle as prescribed in Sec. 29.71 must be provided.]

Amdt. 29-24, E.. 12/6/84
FAR 29.1587 : Performance information.
Flight manual performance information which exceeds any operating limitation may be shownonly tothe extent necessaryforpresentationclarity ortodeterminethe e.ects of approved optional equipment or procedures. When data beyond operating limits are shown, the limits must be clearly indicated. The following must be provided :
(a) Category A. For each category A rotorcraft, the Rotorcraft Flight Manual must contain a summary of the performance data, including data necessary for the ap-plication of any operating rule of this chapter, together with descriptions of the conditions, such as airspeeds, under which this data was determined, and must contain–
(1)
The indicated airspeeds corresponding with those determined for takeo., and the procedures to be followed if the critical engine fails during takeo.;

(2)
The airspeed calibrations;

(3)
The techniques, associated airspeeds, and rates of descent for autorotative landings;

(4)
The rejected takeo. distance determined under Sec. 29.62 and the takeo. dis-tancedetermined underSec.29.61[];

(5)
Thelanding datadetermined underSec.29.81 or[Sec.29.85;]

(6)
The steady gradient of climb for each weight, altitude, and temperature for which takeo. data are to be scheduled, along the takeo. path determined in the .ightconditionsrequiredinSec.29.67(a)(1) and(a)(2) :

(i)
Inthe .ight conditionsrequiredinSec.29.67(a)(1)betweentheend of the takeo. distance and the point at which the rotorcraft is 200 feet above the takeo. surface(or200feet above thelowestpoint of the takeo.pro.le for elevatedheliports);

(ii)
In the .ight conditions required in Sec. 29.67(a)(2) between the points at whichthe rotorcraftis200 and1000feet abovethetakeo. surface(or 200 and1000feet abovethelowestpoint of thetakeo.pro.lefor elevate heliports); and

(7)
Out-of-ground e.ect hover performance determined under Sec. 29.49 and the maximum safewinddemonstrated underthe ambientconditionsfordatapre-sented.

(b) Category B. For each category B rotorcraft, the Rotorcraft Flight Manual must contain–
(1)
The takeo. distance and the climbout speed together with the pertinent in-formation de.ning the .ight path with respect to autorotative landing if an engine fails, including the calculated e.ects of altitude and temperature;

(2)
The steadyrates of climb andhovering ceiling, together with the corresponding airspeeds and other pertinent information, including the calculated e.ects of altitude and temperature;
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(109)