(e)
For helicopters for which a VNE (power-o.) is established under Sec. 29.1505(c), compliance must be demonstrated with the following requirements with critical weight, critical center of gravity, and critical rotor r.p.m. :

(1)
The helicopter must be safely slowed to VNE (power-o.), without exceptional pilotskill after thelast operating engineis madeinoperative atpower-on VNE.

(2)
At a speed of 1.1 VNE (power-o.), the margin of cyclic control must allow satisfactory roll and pitch control with power o..

Amdt. 29-24, E.. 12/6/84
FAR 29.151 : Flight controls.
(a)
[Longitudinal, lateral, directional, andcollective controls may not exhibit excessive breakout force, friction, or preload.

(b)
Control system forces and free play may not inhibit a smooth, direct rotorcraft response to control system input.]

Amdt. 29-24, E.. 12/6/84
FAR 29.161 : Trim control.
The trim control–
(a)
[Must trim anysteady longitudinal, lateral, and collective control forces to zero in level .ight at any appropriate speed; and]

(b)
May notintroduce any undesirablediscontinuitiesin controlforcegradients. Amdt. 29-24, E.. 12/6/84

FAR 29.171 : Stability : general.
Therotorcraft mustbeabletobe .own,withoutunduepilotfatigueorstrain,inany normal maneuver for a period of time as long as that expected in normal operation. At least three landings and takeo.s must be made during this demonstration.
FAR 29.173 : Static longitudinal stability.
(a) [The longitudinal control must be designed so that a rearward movement of the control is necessary to obtain a speed less than the trim speed, and a forward movement of the control is necessary to obtain a speed more than the trim speed.
′
Elodie Roux. Septembre 2003
Subpart B : Flight
(b)
With thethrottle and collectivepitchheld constantduring the maneuvers speci.ed inSec.29.175(a) through(c), the slope ofthe controlposition versus speed curve must be positive throughout the full range of altitude for which certi.cation is requested.

(c)
During the maneuver speci.ed in Sec. 29.175(d), the longitudinal control position versus speed curve may have a negative slope within the speci.ed speed range if the negative motion is not greater than 10 percent of total control travel.

Amdt. 29-24, E.. 12/6/84
FAR 29.175 : Demonstration of static longitudinal stability.
(a)
[Climb. Static longitudinal stability must be shown in the climb condition at speeds from 0.85 VY or 15 knots below VY , whichever is less, to 1.2 VY or 15 knots above VY , whichever is greater, with-]

(1)
Critical weight;

(2)
Critical center of gravity;

(3)
Maximum continuouspower;

(4)
The landing gear retracted; and

(5)
The rotorcraft trimmed at VY .

(b)
Cruise.Staticlongitudinal stability mustbe showninthe cruiseconditionatspeeds from 0.7 VH or 0.7 VNE, whichever is less to 1.1 VH or 1.1 VNE, whichever is less, with–

(1)
Critical weight;

(2)
Critical center of gravity;

(3)
Power for level .ight at 0.9 VH or 0.9 VNE, whichever is less;

(4)
The landing gear retracted; and

(5)
The rotorcraft trimmed at 0.9 VH or 0.9 VNE, whichever is less.

(c)
[Autorotation. Static longitudinal stability must be shown in autorotation at airs-peeds from0.5times the speed for minimum rate of descent, or0.5 times the maxi-mum rangeglide speedforCategoryA rotorcraft, to VNE or to1.1 VNE (power-o.) if VNE (power-o.)is established under Sec. 29.1505(c), and with–]

(1)
Critical weight;

(2)
Critical center of gravity;

(3)
Power o.;

(4)
The landing gear–
　
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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(18)