(1)
Unbalanced aerodynamic moments about the center of gravity which the air-craft reacts to in a rational or conservative manner considering the principal masses furnishing the reacting inertia forces; and

(2)  
Maximum main rotor speed.

(b)
Toproducetheload requiredinparagraph(a) of this section,inunaccelerated .ight with zeroyaw, atforward speedsfrom zero up to0.6 VNE –

(1)
[Displace the cockpit directionalcontrol suddenly to the maximum de.ection limited by the control stops or by the maximum pilot force speci.ed in Sec. 29.397(a)];

(2)  
Attain a resulting sideslip angle or 90', whichever is less; and

(3)  
Return the directional control suddenly to neutral.

(c)
Toproducetheload requiredinparagraph(a) of thesection,inunaccelerated .ight with zeroyaw, atforward speedsfrom0.6 VNE up to VNE or VH, whicheverisless–

(1)
[Displace the cockpit directionalcontrol suddenly to the maximum de.ection limited by the control stops or by the maximum pilot force speci.ed in Sec. 29.397(a)];

(2)
Attain a resulting sideslip angle or 15', whichever is less, at the lesser speed of VNE or VH ;

(3)
Vary thesideslip anglesofparagraphs(b)(2) and(c)(2) of this sectiondirectly with speed; and

(4)
Return the directional control suddenly to neutral. Amdt. 29-41, E.. 11/28/97

′
Elodie Roux. Septembre 2003
Subpart C : Strength Requirements
FAR 29.361 : Engine torque.
[The limit engine torque maynot be less than the following :
(a)
For turbine engines, the highest of–

(1)
The meantorquefor maximum continuouspower multipliedby 1.25;

(2)
The torque required by Sec. 29.923;

(3)
The torque required by Sec. 29.927; or

(4)
The torque imposed by sudden engine stoppage due to malfunction or struc-turalfailure(such as compressorjamming).

(b)
For reciprocating engines, the mean torque maximum continuous power multiplied by–

(1)
1.33,forengineswith .veormorecylinders; and

(2)
Two, three, and four, for engines with four, three, and two cylinders, respecti-vely.]

Amdt. 29-26, E.. 10/3/88
73.3 Control Surface and System Loads
FAR 29.391 : General.
[Eachauxiliary rotor, each .xed or movable stabilizing or control surface, and each system operating any .ight control must meet the requirements of Secs. 29.395 through 29.399, 29.411, and 29.427.] Amdt. 29-41, E.. 11/28/97
FAR 29.395 : Control system.
(a)
The reaction to the loads prescribed in Sec. 29.397 must be provided by–

(1)
The control stops only;

(2)
The control locks only;

(3)
The irreversible mechanism only (with the mechanism locked and with the control surface in the critical positions for the e.ective parts of the system withinitslimit of motion);

(4)
The attachment of the control system to the rotor blade pitch control horn only (with the control in the critical positions for the a.ected parts of the system withinthelimits ofits motion); and

(5)
The attachment ofthe control systemtothe control surfacehorn(withthe controlinthe criticalpositionsforthe a.ectedparts of the system withinthe limits of its motion).

(b)
[Eachprimarycontrol system,including its supporting structure, mustbedesigned as follows :

(1) The system must withstandloads resulting fromthelimitpilotforcesprescri-bed in Sec. 29.397;
(2)
Notwithstandingparagraph(b)(3) of this section, whenpower-operated actua-tor controlsorpowerboost controlsareused,the system must also withstand the loads resulting from the limit pilot forces prescribed in Sec. 29.397 in conjunction with the forces output of each normally energized power device, including any singlepowerboost or actuator systemfailure;
　
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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(22)