585
Federal Aviation Administration, DOT
§ 29.173
(2) Critical center of gravity;
(3) Critical rotor r.p.m.; and
(4) Power off (except for helicopters
demonstrating compliance with para-
graph (f) of this section) and power on.
(c) Wind velocities from zero to at
least 17 knots, from all azimuths, 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 cross-
wind 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 takeoff
and landing altitude capability of the
rotorcraft.
(d) Wind velocities from zero to at
least 17 knots, from all azimuths, must
be established in which the rotorcraft
can be operated without loss of control
out-of-ground effect, with—
(1) Weight selected by the applicant;
(2) Critical center of gravity;
(3) Rotor r.p.m. selected by the appli-
cant; and
(4) Altitude, from standard sea level
conditions to the maximum takeoff
and landing altitude capability of the
rotorcraft.
(e) The rotorcraft, after (1) failure of
one engine, in the case of multiengine
rotorcraft that meet Transport Cat-
egory A engine isolation requirements,
or (2) complete power failure in the
case of other rotorcraft, must be con-
trollable over the range of speeds and
altitudes for which certification is re-
quested 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 sec-
ond, or normal pilot reaction time
(whichever is greater); and
(ii) For any other condition, normal
pilot reaction time.
(f) For helicopters for which a V
NE
(power-off) is established under
§ 29.1505(c), compliance must be dem-
onstrated with the following require-
ments with critical weight, critical
center of gravity, and critical rotor
r.p.m.:
(1) The helicopter must be safely
slowed to V
NE
(power-off), without ex-
ceptional pilot skill after the last oper-
ating engine is made inoperative at
power-on V
NE
.
(2) At a speed of 1.1 V
NE
(power-off),
the margin of cyclic control must
allow satisfactory roll and pitch con-
trol with power off.
(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral 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; Amdt.
29–51, 73 FR 11001, Feb. 29, 2008]
§ 29.151
Flight controls.
(a) Longitudinal, lateral, directional,
and collective 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, 49 FR 44436, Nov. 6, 1984]
§ 29.161
Trim control.
The trim control—
(a) Must trim any steady longitu-
dinal, lateral, and collective control
forces to zero in level flight at any ap-
propriate speed; and
(b) May not introduce any undesir-
able discontinuities in control force
gradients.
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–24, 49 FR 44436, Nov. 6,
1984]
§ 29.171
Stability: general.
The rotorcraft must be able to be
flown, without undue pilot fatigue or
strain, in any normal maneuver for a
period of time as long as that expected
in normal operation. At least three
landings and takeoffs must be made
during this demonstration.
§ 29.173
Static longitudinal stability.
(a) The longitudinal control must be
designed so that a rearward movement
of the control is necessary to obtain an
airspeed less than the trim speed, and a
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