[Code of Federal Regulations]

[Title 14, Volume 1]

[Revised as of January 1, 2006]

From the U.S. Government Printing Office via GPO Access

[CITE: 14CFR27.143]



[Page 574-575]

 

                     TITLE 14--AERONAUTICS AND SPACE

 

CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION

 

PART 27_AIRWORTHINESS STANDARDS: NORMAL CATEGORY ROTORCRAFT--Table 

of Contents

 

                            Subpart B_Flight

 

Sec. 27.143  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;

    (vi) Landing (power on and power off); and

    (vii) Recovery to power-on flight from a balked autorotative 

approach.

    (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;

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

    (4) Altitude, from standard sea level conditions to the maximum 

altitude capability of the rotorcraft or 7,000 feet, whichever is less.



[[Page 575]]



    (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 engine 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. 27.1505(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. 5074, 29 FR 15695, Nov. 24, 1964, as amended by Amdt. 27-2, 33 

FR 963, Jan. 26, 1968; Amdt. 27-14, 43 FR 2325, Jan. 16, 1978; Amdt. 27-

21, 49 FR 44433, Nov. 6, 1984]