Section 29.45

14 CFR Ch. I (1-1-19 Edition)

when the speed of a main rotor approaches a value that can jeopardize
safe flight.
(2) The warning may be furnished either through the inherent aerodynamic
qualities of the helicopter or by a device.
(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 device must automatically deactivate
and reset when the low-speed condition
is corrected. If the device has an audible warning, it must also be equipped
with a means for the pilot to manually
silence the audible warning before the
low-speed condition is corrected.
(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. 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]

spaschal on DSK3GDR082PROD with CFR

PERFORMANCE
Section 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 atmospheric variables.
(c) The available power must correspond to engine power, not exceeding
the approved power, less - 
(1) Installation losses; and
(2) The power absorbed by the accessories and services at the values for
which certification is requested and approved.
(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 rotorcraft, the performance, as affected by
engine power, must be based on a relative humidity of - 
(1) 80 percent, at and below standard
temperature; and
(2) 34 percent, at and above standard
temperature plus 50 SectionF.
Between these two temperatures, the
relative humidity must vary linearly.
(f) For turbine-engine-power rotorcraft, a means must be provided to permit the pilot to detemine prior to takeoff that each engine is capable of developing the power necessary to achieve
the applicable rotorcraft performance
prescribed in this subpart.
(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), 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]

Section 29.49 Performance at minimum operating speed.
(a) For each Category A helicopter,
the hovering performance must be determined over the ranges of weight, altitude, 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 determined over the ranges of weight, altitude, and temperature for which certification is requested, with - 
(1) Takeoff power;
(2) The landing gear extended; and
(3) The helicopter in ground effect at
a height consistent with normal takeoff procedures.
(c) For each helicopter, the out-ofground 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 helicopters, the steady rate of climb at the

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