(5)
Operation of the rotorcraft at a total weight greater than the maximum cer-ti.cated weight established underparagraph(a) of this sectionislimitedby appropriate operating limitations underSec.27.865(a) and(d) of thispart.]

Amdt. 27-36, E.. 10/5/99
FAR 27.27 : Center of gravity limits
[The extremeforwardand aft centers ofgravity and, where critical,the extremelateral centersofgravity mustbe establishedfor each weight established underSec.27.25.Such an extreme may not lie beyond–
(a)
The extremes selected by the applicant;

(b)
The extremes within which the structure is proven, or

(c)
The extremes within which compliance with the applicable .ight requirements is

shown.] Amdt. 27-2, E.. 2/25/68
FAR 27.29 : Empty weight and corresponding center of gravity
(a)
The empty weight and corresponding center of gravity must be determined by wei-ghing the rotorcraft without the crew and payload, but with–

(1)
Fixed ballast;

(2)
Unusable fuel;[and

(3)
Full operating .uids, including–

(i)
Oil;

(ii)
Hydraulic .uid; and

(iii) Other .uids required for normal operation of rotorcraft systems, except water intended for injection in the engines.]

(b)
The condition of the rotorcraft at the time of determining empty weight must be onethatiswellde.ned and canbe easily repeated,particularly with respecttothe weights of fuel, oil, coolant, and installed equipment.

Amdt. 27-14, E.. 3/1/78
′
Elodie Roux. Septembre 2003
Subpart B : Flight
FAR 27.31 : Removable ballast
Removable ballast may be used in showing compliance with the .ight requirements of this subpart.
FAR 27.33 : Main rotor speed and pitch limits
(a) Main rotor speed limits. A range of main rotor speeds must be established that–
(1)
With power on, provides adequate margin to accommodate the variations in rotor speed occurringin any appropriate maneuver, andis consistent with the kind ofgovernoror synchronizer used; and

(2)
With power o., allows each appropriate autorotative maneuver to be perfor-med throughout the ranges of airspeed and weight for which certi.cation is requested.

[(b) Normal main rotorpitch limits(power-on).For rotorcraft, excepthelicopters requi-red tohave a main rotorlow speed warning underparagraph(e) of this section,it must be shown with power on and without exceeding approved engine maximum limitations, that main rotor speeds substantially less than the minimum approved main rotor speed will not occur under any sustained .ight condition. This must be met by–]
(1)
Appropriate setting of the main rotor high pitch stop;

(2)
Inherent rotorcraft characteristics that make unsafe low main rotor speeds unlikely; or

(3)
Adequate means to warn the pilot of unsafe main rotor speeds.

(c)
Normal main rotorlowpitchlimits(power o.).It mustbe shown, withpower o., that–

(1)
The normal main rotor low pitch limit provides su.cient rotor speed, in any autorotative condition, under the most critical combinations of weight and airspeed; and

(2)
Itispossibletopreventoverspeeding of the rotorwithout exceptionalpiloting skill.

(d)
Emergency high pitch. If the main rotor high pitch stop is set to meet paragraph (b)(1)of this section,andif thatstop cannotbe exceededinadvertently,additional pitch may be made available for emergency use.

[(e) Main rotorlow speed warningforhelicopters.For each single engine helicopter, and each multiengine helicopter that does not have an approved device that automa-tically increases power on the operating engines when one engine fails, there must be a main rotor low speed warning which meets the following requirements :
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(67)