title-14-part-29-sec29-143

584

14 CFR Ch. I (1–1–24 Edition)

§ 29.87

(b) From the LDP on the approach

path selected by the applicant, a safe
climbout can be made at speeds allow-
ing compliance with the climb require-
ments of § 29.67(a)(1) and (2); and

below 15 feet above the landing surface.
For elevated heliport operations, de-
scent may be below the level of the
landing surface provided the deck edge
clearance of § 29.60 is maintained and
the descent (loss of height) below the
landing surface is determined.

[Doc. No. 24802, 64 FR 45338, Aug. 19, 1999]

§ 29.87

Height-velocity envelope.

(a) If there is any combination of

height and forward velocity (including
hover) under which a safe landing can-
not be made after failure of the critical
engine and with the remaining engines
(where applicable) operating within ap-
proved limits, a height-velocity enve-
lope must be established for—

(1) All combinations of pressure alti-

tude and ambient temperature for
which takeoff and landing are ap-
proved; and

(2) Weight from the maximum weight

(at sea level) to the highest weight ap-
proved for takeoff and landing at each
altitude. For helicopters, this weight
need not exceed the highest weight al-
lowing hovering out-of-ground effect at
each altitude.

(b) For single-engine or multiengine

rotorcraft that do not meet the Cat-
egory A engine isolation requirements,
the height-velocity envelope for com-
plete power failure must be estab-
lished.

[Doc. No. 24802, 61 FR 21901, May 10, 1996; 61
FR 33963, July 1, 1996]

LIGHT

HARACTERISTICS

§ 29.141

General.

The rotorcraft must—
(a) Except as specifically required in

the applicable section, meet the flight
characteristics requirements of this
subpart—

(1) At the approved operating alti-

tudes and temperatures;

(2) Under any critical loading condi-

tion within the range of weights and
centers of gravity for which certifi-
cation is requested; and

(3) For power-on operations, under

any condition of speed, power, and
rotor r.p.m. for which certification is
requested; and

(4) For power-off operations, under

any condition of speed, and rotor r.p.m.
for which certification is requested
that is attainable with the controls
rigged in accordance with the approved
rigging instructions and tolerances;

(b) Be able to maintain any required

flight condition and make a smooth
transition from any flight condition to
any other flight condition without ex-
ceptional piloting skill, alertness, or
strength, and without danger of ex-
ceeding the limit load factor under any
operating condition probable for the
type, including—

(1) Sudden failure of one engine, for

multiengine rotorcraft meeting Trans-
port Category A engine isolation re-
quirements;

(2) Sudden, complete power failure,

for other rotorcraft; and

(3) Sudden, complete control system

failures specified in § 29.695 of this part;
and

tics required for night or instrument
operation, if certification for those
kinds of operation is requested. Re-
quirements for helicopter instrument
flight are contained in appendix B of
this part.

[Doc. No. 5084, 29 FR 16150, Dec. 8, 1964, as
amended by Amdt. 29–3, 33 FR 905, Jan. 26,
1968; Amdt. 29–12, 41 FR 55471, Dec. 20, 1976;
Amdt. 29–21, 48 FR 4391, Jan. 31, 1983; Amdt.
29–24, 49 FR 44436, Nov. 6, 1984]

§ 29.143

Controllability and maneuver-

ability.

(a) The rotorcraft must be safely con-

trollable 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) Autorotation; and
(vi) Landing (power on and power

off).

(b) The margin of cyclic control must

allow satisfactory roll and pitch con-
trol at V

with—

(1) Critical weight;

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§ 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.

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

(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

(power-off), without ex-

ceptional pilot skill after the last oper-
ating engine is made inoperative at
power-on V

(2) At a speed of 1.1 V

(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.