(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. 29-15, E.. 3/1/78
FAR 29.31 : Removable ballast.
Removable ballast may be used in showing compliance with the .ight requirements of this subpart.
FAR 29.33 : 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 rotorhighpitchlimits(power-on). For rotorcraft, except helicopters requiredtohave a main rotorlow speed warning underparagraph(e) ofthis section, it must be shown withpower 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 rotorhighpitch 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 rotor low pitch limit (power o.). It must be shown, with power 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 cannotbeexceededinadvertently,additional pitch may be made available for emergency use.

(e)
[Main rotor low speed warning for helicopters. For each single engine helicopter, and each multiengine helicopter that does not have an approved device that automa-tically increasespower onthe operating engines when one enginefails,there must be a main rotor low speed warning which meets the following requirements :

(1)
The warning must be furnished to the pilot in all .ight conditions, including power-on and power-o. .ight, when the speed of a main rotor approaches a valuethatcanjeopardizesafe .ight.

(2)
The warning may be furnished either through the inherent aerodynamic qua-lities of the helicopter or by a device.

(3)
The warning must be clear and distinct under all conditions, and must be clearly distinguishable from all other warnings. A visual device that requires the attention of the crew within the cockpit is not acceptable by itself.

(4)
If a warning device is used, the device must automatically deactivate and reset when the low-speed condition is corrected. If the device has an audible warning, it must also be equipped with a means for the pilot to manually silence the audible warning before the low-speed condition is corrected.]

Amdt. 29-15, E.. 3/1/78
72.2 Performance
FAR 29.45 : General.
(a) The performance prescribed in this subpart must be determined–
(1)
With normalpiloting skill; and

(2)
Without exceptionally favorable conditions.

′
Elodie Roux. Septembre 2003
Subpart B : Flight
(b)
　
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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(11)