(ii)
[0.9times the maximum speed shown under Secs. 29.251 and 29.629; or

(iii) 0.9timesthe maximum speedsubstantiatedfor advancingbladetip mach number e.ects under critical altitude conditions.]

(b)
VNE may vary with altitude, r.p.m., temperature, and weight, if–

(1)
No more than two of these variables(or no more than twoinstrumentsinte-grating morethan one of these variables) are used at onetime; and

(2)
The rangesof these variables(or of theindications oninstrumentsintegrating more than one of these variables) are large enough to allow an operationally practical and safe variation of VNE.

(c)
For helicopters, a stabilized power-o. VNE denoted as VNE power-o.) may be es-tablished at a speed less than VNE establishedpursuant toparagraph(a) of this section, if the following conditions are met :

(1)
VNE (power-o.)is not less than a speed midway between the power-on VNE and the speed used in meeting the requirements of–

(i)
Sec. 29.67(a)(3) for Category A helicopters;

(ii)
Sec. 29.65(a) for Category B helicopters, except multi-engine helicopters meeting the requirements of Sec. 29.67(b); and

(iii) Sec.29.67(b)formulti-engineCategoryBhelicoptersmeeting the requi-rements of Sec. 29.67(b).

(2)
VNE (power-o.)is–

(i)
A constant airspeed;

(ii)
A constant amount less than power-on VNE ; or

′
Elodie Roux. Septembre 2003
Subpart G : Operating Limitations and Information
(iii) A constant airspeed for a portion of the altitude range for which certi-.cation is requested, and a constant amount less than power-on VNE for the remainder of the altitude range.
Amdt. 29-24, E.. 12/6/84
FAR 29.1509 : Rotor speed.
(a)
Maximum power-o. (autorotation). The maximum power-o. rotor speed must be established so that it does not exceed 95 percent of the lesser of–

(1)
The maximum design r.p.m. determined under Sec. 29.309(b); and

(2)
The maximum r.p.m. shown during the type tests.

(b)
Minimum power-o.. The minimum power-o. rotor speed must be established so that it is not less than 105 percent of the greater of–

(1)
The minimum shownduring thetypetests; and

(2)
The minimum determined by design substantiation.

(c)
Minimumpower-on.The minimumpower-on rotor speed mustbe established so that it is–

(1)
Not less than the greater of–

(i)
The minimum shownduring thetypetests; and

(ii)
The minimum determined by design substantiation; and

(2)
Not morethan a valuedetermined underSec.29.33(a)(1) and(c)(1).

FAR 29.1517 : Limiting height-speed envelope.
[For CategoryA rotorcraft, if a range of heights exists at any speed, including zero, within which it is not possible to make a safe landing following power failure, the range of heights and its variation with forward speed must be established, together with any other pertinent information, such as the kind of landing surface.] Amdt. 29-24, E.. 12/6/84
FAR 29.1519 : Weight and center of gravity.
The weight and center ofgravity limitationsdetermined underSecs.29.25 and29.27 respectively, must be established as operating limitations.
FAR 29.1521 : Powerplant limitations.
(a)
General. The powerplant limitations prescribed in this section must be established so that they do not exceed the corresponding limits for which the engines are type certi.cated.

(b)
Takeo. operation. The powerplant takeo. operation must be limited by–

(1)
The maximum rotational speed which may not be greater than–
　
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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(103)