[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2004]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR29.143]

[Page 649]
 
                     TITLE 14--AERONAUTICS AND SPACE
 
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
 
PART 29--AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY ROTORCRAFT--Table of Contents
 
                            Subpart B--Flight
 
Sec. 29.143  Controllability and maneuverability.

    (a) The rotorcraft must be safely controllable and maneuverable--
    (1) During steady flight; and
    (2) During any maneuver appropriate to the type, including--
    (i) Takeoff;
    (ii) Climb;
    (iii) Level flight;
    (iv) Turning flight;
    (v) Glide; and
    (vi) Landing (power on and power off).
    (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 off (except for helicopters demonstrating compliance with 
paragraph (e) of this section) and power on.
    (c) A wind velocity of not less than 17 knots must be established in 
which the rotorcraft can be operated without loss of control on or near 
the ground in any maneuver appropriate to the type (such as crosswind 
takeoffs, sideward flight, and rearward flight), with--
    (1) Critical weight;
    (2) Critical center of gravity; and
    (3) Critical rotor r.p.m.
    (d) The rotorcraft, after (1) failure of one engine, in the case of 
multiengine rotorcraft that meet Transport Category A engine isolation 
requirements, or (2) complete power failure in the case of other 
rotorcraft, must be controllable over the range of speeds and altitudes 
for which certification is requested when such power failure occurs with 
maximum continuous power and critical weight. No corrective action time 
delay for any condition following power failure may be less than--
    (i) For the cruise condition, one second, or normal pilot reaction 
time (whichever is greater); and
    (ii) For any other condition, normal pilot reaction time.
    (e) For helicopters for which a VNE (power-off) 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-
off), without exceptional pilot skill after the last operating engine is 
made inoperative at power-on VNE.
    (2) At a speed of 1.1 VNE (power-off), the margin of 
cyclic control must allow satisfactory roll and pitch control with power 
off.

(Secs. 313(a), 601, 603, 604, and 605 of the Federal Aviation Act of 
1958 (49 U.S.C. 1354(a), 1421, 1423, 1424, and 1425); and sec. 6(c) of 
the Dept. of Transportation Act (49 U.S.C. 1655(c)))

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as amended by Amdt. 29-3, 33 
FR 965, Jan. 26, 1968; Amdt. 29-15, 43 FR 2326, Jan. 16, 1978; Amdt. 29-
24, 49 FR 44436, Nov. 6, 1984]