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μ=
ΩR where–
The airspeed along .ight path (ft/s)
α The angle between the projection, in the plane of symmetry, of the axis (rad)
of no feathering and a line perpendicular to the .ight path (positive
when axis is pointing aft)
Ω The angular velocity of rotor (rad/s)
R The rotor radius (ft)
Amdt. 27-11, E.. 2/1/77
FAR 27.341 : Gust loads
The rotorcraft must be designed to withstand, at each critical airspeed including hovering,theloads resulting from a verticalgust of30feetper second.
FAR 27.351 : Yawing conditions
(a)
Eachrotorcraft mustbedesignedfortheloads resultingfrom the maneuvers speci.ed inparagraphs(b) and(c) of this section with–

(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 directional control suddenly to the maximum de.ection limitedby the control stops orby the[maximumpilotforce speci.edinSec. 27.397(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 this section,inunaccelerated .ight with zeroyaw, atforward speedsfrom0.6 VNE up to VNE or VH, whicheverisless–

(1) Displace the cockpit directional control suddenly to the maximum de.ection limitedby the control stops orby the[maximumpilotforce speci.edinSec. 27.397(a);]
′
Elodie Roux. Septembre 2003
Subpart C : Strength Requirements
(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. 27-34, E.. 11/28/97

FAR 27.361 : Engine torque

(a)
[For turbine engines, the limit torque maynot be less than the highest of–

(1)
The meantorquefor maximum continuouspower multipliedby 1.25;

(2)
The torque required by Sec. 27.923;

(3)
The torque required by Sec. 27.927; or

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

 

(b)
For reciprocating engines, the limit torque may not be less than the mean torque for 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. 27-23, E.. 10/3/88
63.3 Control Surface and System Loads
FAR 27.391 : General
Each auxiliary rotor, each .xed or movable stabilizing or control surface, and each systemoperating any .ightcontrol mustmeettherequirementsof[Secs.27.395,27.397, 27.399, 27.411, and 27.427.] Amdt. 27-34, E.. 11/28/97
FAR 27.395 : Control system
(a)
The part of each control system from the pilot’s controls to the control stops must be designed to withstand pilot forces of not less than–

(1)
The forces speci.ed in Sec. 27.397; or

(2)
If the system prevents the pilot from applying the limit pilot forces to the system, the maximum forces that the system allows the pilot to apply, but not less than 0.60 times the forces speci.ed in Sec. 27.397.

 

(b)
[Eachprimarycontrol system,including its supporting structure, mustbedesigned as follows :
　
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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(75)