Federal Aviation Administration, DOT

Section 29.71

within the operational limits established for the rotorcraft and with the
most unfavorable center of gravity for
each configuration. Cowl flaps, or other
means of controlling the engine-cooling air supply, will be in the position
that provides adequate cooling at the
temperatures and altitudes for which
certification is requested.
[Doc. No. 24802, 61 FR 21900, May 10, 1996]

Section 29.65

Climb: All engines operating.

(a) The steady rate of climb must be
determined - 
(1) With maximum continuous power;
(2) With the landing gear retracted;
and
(3) At Vy for standard sea level conditions and at speeds selected by the applicant for other conditions.
(b) For each Category B rotorcraft
except helicopters, the rate of climb
determined under paragraph (a) of this
section must provide a steady climb
gradient of at least 1:6 under standard
sea level conditions.
(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. 29-39, 61 FR 21900, May 10, 1996; 61
FR 33963, July 1, 1996]

spaschal on DSK3GDR082PROD with CFR

Section 29.67 Climb: One engine inoperative
(OEI).
(a) For Category A rotorcraft, in the
critical takeoff configuration existing
along the takeoff path, the following
apply:
(1) The steady rate of climb without
ground effect, 200 feet above the takeoff surface, must be at least 100 feet per
minute for each weight, altitude, and
temperature for which takeoff data are
to be scheduled with - 
(i) The critical engine inoperative
and the remaining engines within approved operating limitations, except
that for rotorcraft for which the use of
30-second/2-minute OEI power is requested, only the 2-minute OEI power
may be used in showing compliance
with this paragraph;
(ii) The landing gear extended; and
(iii) The takeoff safety speed selected
by the applicant.

(2) The steady rate of climb without
ground effect, 1000 feet above the takeoff surface, must be at least 150 feet per
minute, for each weight, altitude, and
temperature for which takeoff data are
to be scheduled with - 
(i) The critical engine inoperative
and the remaining engines at maximum continuous power including continuous OEI power, if approved, or at
30-minute OEI power for rotorcraft for
which certification for use of 30-minute
OEI power is requested;
(ii) The landing gear retracted; and
(iii) The speed selected by the applicant.
(3) The steady rate of climb (or descent) in feet per minute, at each altitude and temperature at which the
rotorcraft is expected to operate and at
any weight within the range of weights
for which certification is requested,
must be determined with - 
(i) The critical engine inoperative
and the remaining engines at maximum continuous power including continuous OEI power, if approved, and at
30-minute OEI power for rotorcraft for
which certification for the use of 30minute OEI power is requested;
(ii) The landing gear retracted; and
(iii) The speed selected by the applicant.
(b) For multiengine Category B
rotorcraft meeting the Category A engine isolation requirements, the steady
rate of climb (or descent) must be determined at the speed for best rate of
climb (or minimum rate of descent) at
each altitude, temperature, and weight
at which the rotorcraft is expected to
operate, with the critical engine inoperative and the remaining engines at
maximum continuous power including
continuous OEI power, if approved, and
at 30-minute OEI power for rotorcraft
for which certification for the use of 30minute OEI power is requested.
[Doc. No. 24802, 61 FR 21900, May 10, 1996; 61
FR 33963, July 1, 1996, as amended by Amdt.
29-44, 64 FR 45337, Aug. 19, 1999; 64 FR 47563,
Aug. 31, 1999]

Section 29.71 Helicopter angle of glide: Category B.
For each category B helicopter, except multiengine helicopters meeting
the requirements of Section 29.67(b) and the
powerplant installation requirements

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