581 

Federal Aviation Administration, DOT 

§ 29.71 

within the operational limits estab-
lished for the rotorcraft and with the 
most unfavorable center of gravity for 
each configuration. Cowl flaps, or other 
means of controlling the engine-cool-
ing 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] 

§ 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 V

y

for standard sea level condi-

tions and at speeds selected by the ap-
plicant 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 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. 29–39, 61 FR 21900, May 10, 1996; 61 
FR 33963, July 1, 1996] 

§ 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 take-
off 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 ap-
proved operating limitations, except 
that for rotorcraft for which the use of 
30-second/2-minute OEI power is re-
quested, 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 take-
off 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 max-
imum continuous power including con-
tinuous 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 appli-

cant. 

(3) The steady rate of climb (or de-

scent) in feet per minute, at each alti-
tude 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 max-
imum continuous power including con-
tinuous OEI power, if approved, and at 
30-minute OEI power for rotorcraft for 
which certification for the use of 30- 
minute OEI power is requested; 

(ii) The landing gear retracted; and 
(iii) The speed selected by the appli-

cant. 

(b) For multiengine Category B 

rotorcraft meeting the Category A en-
gine isolation requirements, the steady 
rate of climb (or descent) must be de-
termined 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 inop-
erative 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 30- 
minute 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] 

§ 29.71

Helicopter angle of glide: Cat-

egory B. 

For each category B helicopter, ex-

cept multiengine helicopters meeting 
the requirements of § 29.67(b) and the 
powerplant installation requirements 

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