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Federal Aviation Administration, DOT

§ 29.1517

the crewmembers as prescribed in
§§ 29.1541 through 29.1589.

(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), Dept.
of Transportation Act (49 U.S.C. 1655(c)))

[Amdt. 29–15, 43 FR 2327, Jan. 16, 1978]

PERATING

IMITATIONS

§ 29.1503

Airspeed limitations: general.

(a) An operating speed range must be

established.

(b) When airspeed limitations are a

function of weight, weight distribution,
altitude, rotor speed, power, or other
factors, airspeed limitations cor-
responding with the critical combina-
tions of these factors must be estab-
lished.

§ 29.1505

Never-exceed speed.

(a) The never-exceed speed, V

NE,

must

be established so that it is—

(1) Not less than 40 knots (CAS); and
(2) Not more than the lesser of—
(i) 0.9 times the maximum forward

speeds established under § 29.309;

(ii) 0.9 times the maximum speed

shown under §§ 29.251 and 29.629; or

(iii) 0.9 times the maximum speed

substantiated for advancing blade tip
mach number effects under critical al-
titude conditions.

(b) V

may vary with altitude,

r.p.m., temperature, and weight, if—

(1) No more than two of these vari-

ables (or no more than two instru-
ments integrating more than one of
these variables) are used at one time;
and

(2) The ranges of these variables (or

of the indications on instruments inte-
grating more than one of these vari-
ables) are large enough to allow an
operationally practical and safe vari-
ation of V

power-off V

denoted as V

(power-

off) may be established at a speed less
than V

established pursuant to para-

graph (a) of this section, if the fol-
lowing conditions are met:

(1) V

(power-off) is not less than a

speed midway between the power-on
V

and the speed used in meeting the

requirements of—

(i) § 29.67(a)(3) for Category A heli-

copters;

(ii) § 29.65(a) for Category B heli-

copters, except multi-engine heli-
copters meeting the requirements of
§ 29.67(b); and

(iii) § 29.67(b) for multi-engine Cat-

egory B helicopters meeting the re-
quirements of § 29.67(b).

(2) V

(power-off) is—

(i) A constant airspeed;
(ii) A constant amount less than

power-on V

(iii) A constant airspeed for a portion

of the altitude range for which certifi-
cation is requested, and a constant
amount less than power-on V

for the

remainder of the altitude range.

(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), Dept.
of Transportation Act (49 U.S.C. 1655(c)))

[Amdt. 29–3, 33 FR 971, Jan. 26, 1968, as
amended by Amdt. 29–15, 43 FR 2327, Jan. 16,
1978; Amdt. 29–24, 49 FR 44440, Nov. 6, 1984]

§ 29.1509

Rotor speed.

(a)

Maximum power-off (autorotation).

The maximum power-off rotor speed
must be established so that it does not
exceed 95 percent of the lesser of—

(1) The maximum design r.p.m. deter-

mined under § 29.309(b); and

(2) The maximum r.p.m. shown dur-

ing the type tests.

(b)

Minimum power-off.

The minimum

power-off rotor speed must be estab-
lished so that it is not less than 105
percent of the greater of—

(1) The minimum shown during the

type tests; and

(2) The minimum determined by de-

sign substantiation.

(c)

Minimum power-on.

The minimum

power-on rotor speed must be estab-
lished so that it is—

(1) Not less than the greater of—
(i) The minimum shown during the

type tests; and

(ii) The minimum determined by de-

sign substantiation; and

(2) Not more than a value determined

under § 29.33 (a)(1) and (c)(1).

§ 29.1517

Limiting height-speed enve-

lope.

For Category A rotorcraft, if a range

of heights exists at any speed, includ-
ing zero, within which it is not possible
to make a safe landing following power
failure, the range of heights and its

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