title-14-part-29-sec29-33

578

14 CFR Ch. I (1–1–24 Edition)

§ 29.31

(i) Oil;
(ii) Hydraulic fluid; and
(iii) Other fluids required for normal

operation of rotorcraft systems, except
water intended for injection in the en-
gines.

(b) The condition of the rotorcraft at

the time of determining empty weight
must be one that is well defined and
can be easily repeated, particularly
with respect to the weights of fuel, oil,
coolant, and installed equipment.

(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. 29–15, 43 FR 2326, Jan. 16,
1978]

§ 29.31

Removable ballast.

Removable ballast may be used in

showing compliance with the flight re-
quirements of this subpart.

§ 29.33

Main rotor speed and pitch lim-

its.

(a)

Main rotor speed limits. A range of

main rotor speeds must be established
that—

(1) With power on, provides adequate

margin to accommodate the variations
in rotor speed occurring in any appro-
priate maneuver, and is consistent
with the kind of governor or synchro-
nizer used; and

(2) With power off, allows each appro-

priate autorotative maneuver to be
performed throughout the ranges of
airspeed and weight for which certifi-
cation is requested.

(b)

Normal main rotor high pitch limit

(power on). For rotorcraft, except heli-
copters required to have a main rotor
low speed warning under paragraph (e)
of this section, it must be shown, with
power on and without exceeding ap-
proved engine maximum limitations,
that main rotor speeds substantially
less than the minimum approved main
rotor speed will not occur under any
sustained flight condition. This must
be met by—

(1) Appropriate setting of the main

rotor high pitch stop;

(2) Inherent rotorcraft characteris-

tics that make unsafe low main rotor
speeds unlikely; or

(3) Adequate means to warn the pilot

of unsafe main rotor speeds.

(c)

Normal main rotor low pitch limit

(power off). It must be shown, with
power off, that—

(1) The normal main rotor low pitch

limit provides sufficient rotor speed, in
any autorotative condition, under the
most critical combinations of weight
and airspeed; and

(2) It is possible to prevent over-

speeding of the rotor without excep-
tional piloting skill.

(d)

Emergency high pitch. If the main

rotor high pitch stop is set to meet
paragraph (b)(1) of this section, and if
that stop cannot be exceeded inadvert-
ently, additional pitch may be made
available for emergency use.

(e)

Main rotor low speed warning for

helicopters. For each single engine heli-
copter, and each multiengine heli-
copter that does not have an approved
device that automatically increases
power on the operating engines when
one engine fails, there must be a main
rotor low speed warning which meets
the following requirements:

(1) The warning must be furnished to

the pilot in all flight conditions, in-
cluding power-on and power-off flight,
when the speed of a main rotor ap-
proaches a value that can jeopardize
safe flight.

(2) The warning may be furnished ei-

ther through the inherent aerodynamic
qualities of the helicopter or by a de-
vice.

(3) The warning must be clear and

distinct under all conditions, and must
be clearly distinguishable from all
other warnings. A visual device that
requires the attention of the crew
within the cockpit is not acceptable by
itself.

(4) If a warning device is used, the de-

vice must automatically deactivate
and reset when the low-speed condition
is corrected. If the device has an audi-
ble warning, it must also be equipped
with a means for the pilot to manually

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§ 29.51

silence the audible warning before the
low-speed condition is corrected.

(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]

ERFORMANCE

§ 29.45

General.

(a) The performance prescribed in

this subpart must be determined—

(1) With normal piloting skill and;
(2) Without exceptionally favorable

conditions.

(b) Compliance with the performance

requirements of this subpart must be
shown—

(1) For still air at sea level with a

standard atmosphere and;

(2) For the approved range of atmos-

pheric variables.

respond to engine power, not exceeding
the approved power, less—

(1) Installation losses; and
(2) The power absorbed by the acces-

sories and services at the values for
which certification is requested and ap-
proved.

(d) For reciprocating engine-powered

rotorcraft, the performance, as affected
by engine power, must be based on a
relative humidity of 80 percent in a
standard atmosphere.

(e) For turbine engine-powered rotor-

craft, the performance, as affected by
engine power, must be based on a rel-
ative humidity of—

(1) 80 percent, at and below standard

temperature; and

(2) 34 percent, at and above standard

temperature plus 50

Between these two temperatures, the
relative humidity must vary linearly.

(f) For turbine-engine-power rotor-

craft, a means must be provided to per-
mit the pilot to determine prior to
takeoff that each engine is capable of
developing the power necessary to

achieve the applicable rotorcraft per-
formance prescribed in this subpart.

(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)))

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

§ 29.49

Performance at minimum oper-

ating speed.

(a) For each Category A helicopter,

the hovering performance must be de-
termined over the ranges of weight, al-
titude, and temperature for which
takeoff data are scheduled—

(1) With not more than takeoff

power;

(2) With the landing gear extended;

and

(3) At a height consistent with the

procedure used in establishing the
takeoff, climbout, and rejected takeoff
paths.

(b) For each Category B helicopter,

the hovering performance must be de-
termined over the ranges of weight, al-
titude, and temperature for which cer-
tification is requested, with—

(1) Takeoff power;
(2) The landing gear extended; and
(3) The helicopter in ground effect at

a height consistent with normal take-
off procedures.

ground effect hovering performance
must be determined over the ranges of
weight, altitude, and temperature for
which certification is requested with
takeoff power.

(d) For rotorcraft other than heli-

copters, the steady rate of climb at the
minimum operating speed must be de-
termined over the ranges of weight, al-
titude, and temperature for which cer-
tification is requested with—

(1) Takeoff power; and
(2) The landing gear extended.

[Doc. No. 24802, 61 FR 21898, May 10, 1996; 61
FR 33963, July 1, 1996]

§ 29.51

Takeoff data: general.

(a) The takeoff data required by

§§ 29.53, 29.55, 29.59, 29.60, 29.61, 29.62,
29.63, and 29.67 must be determined—

(1) At each weight, altitude, and tem-

perature selected by the applicant; and