(b)
For single-engine or multiengine rotorcraft that do not meet the Category A engine isolation requirements,theheight-velocityenvelopefor completepowerfailure must be established.]

Amdt. 29-39, E.. 6/10/96
72.3 Flight Characteristics
FAR 29.141 : General.
The rotorcraft must–
(a) [Except as speci.callyrequired in the applicable section, meet the .ight characteris-tics requirements of this subpart–
(1)
At the approved operating altitudes and temperatures;]

(2)
Under any critical loading condition within the range of weights and centers ofgravity for which certi.cationis requested; and

′
Elodie Roux. Septembre 2003
Subpart B : Flight
(3)
Forpower-on operations, under anycondition of speed,power, and rotor r.p.m. for which certi.cation is requested; and

(4)
For power-o. operations, under any condition of speed and rotor r.p.m. for which certi.cation is requested that is attainable with the controls rigged in accordance with the approved rigging instructions and tolerances;

(b)
Beabletomaintainanyrequired.ight conditionand makeasmooth transitionfrom any .ightconditiontoany other .ightconditionwithoutexceptionalpiloting skill, alertness, or strength, and without danger of exceeding the limit load factor under any operating condition probable for the type, including–

(1)
Sudden failure of one engine, for multiengine rotorcraft meeting transport ca-tegory A engine isolation requirements;

(2)
Sudden, complete power failure, for other rotorcraft; and

(3)
Sudden, complete control system failures speci.ed in Sec. 29.695 of this Part; and

(c)
Have any additional characteristics required for night or instrument operation, if certi.cation for those kinds of operation is requested. Requirements for helicopter instrument .ight are contained in Appendix B of this Part.

Amdt. 29-24, E.. 12/6/84
FAR 29.143 : Controllability and maneuverability.
(a)
The rotorcraft must be safely controllable and maneuverable–

(1)
During steady .ight; and

(2)
During any maneuver appropriate to the type, including–

(i)
Takeo.;

(ii)
Climb;

(iii) Level .ight;
(iv)
Turning .ight;

(v)
Glide; and

(vi)
Landing(power on andpower o.).

(b)
The margin of cyclic control must allow satisfactory roll and pitch control at VNE with–

(1)
Critical weight;

(2)
Critical center of gravity;

(3)
Critical rotor r.p.m.; and

(4)
Power o.(exceptforhelicoptersdemonstratingcompliance withparagraph(e) of this section) and power on.

(c)
A wind velocity of notless than 17knots must be establishedin which the rotorcraft can be operated without loss of control on or near the ground in any manner appropriatetothetype(such ascrosswindtakeo.s,sideward .ight,and rearward .ight), with–

(1)
[Criticalweight;

(2)
Critical center of gravity; and

(3)
Critical motor r.p.m.]

(d)
The rotorcraft, after(1) failure of one engine,inthe case of multiengine rotorcraft that meettransport category A engineisolation requirements, or(2) completepo-wer failure in the case of other rotorcraft, must be controllable over the range of speeds and altitudes for which certi.cation is requested when such power failures occurs with maximum continuous power and critical weight. No corrective action timedelay for any conditionfollowingpowerfailure may belessthan–

(i)
Forthe cruise condition, one second, or normalpilot reactiontime(whichever is greater); and

(ii)
For any other condition, normalpilot reactiontime.
　
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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(17)