192
14 CFR Ch. I (1–1–14 Edition)
§ 23.59
(3) The takeoff flight path must be
based on the airplane’s performance
without utilizing ground effect.
[Amdt. 23–34, 52 FR 1827, Jan. 15, 1987, as
amended by Amdt. 23–50, 61 FR 5185, Feb. 9,
1996, as amended by Amdt. 23–62, 76 FR 75753,
Dec. 2, 2011]
§ 23.59
Takeoff distance and takeoff
run.
For normal, utility, and acrobatic
category multiengine jets of more than
6,000 pounds maximum weight and
commuter category airplanes, the
takeoff distance and, at the option of
the applicant, the takeoff run, must be
determined.
(a) Takeoff distance is the greater
of—
(1) The horizontal distance along the
takeoff path from the start of the take-
off to the point at which the airplane is
35 feet above the takeoff surface as de-
termined under § 23.57; or
(2) With all engines operating, 115
percent of the horizontal distance from
the start of the takeoff to the point at
which the airplane is 35 feet above the
takeoff surface, determined by a proce-
dure consistent with § 23.57.
(b) If the takeoff distance includes a
clearway, the takeoff run is the greater
of—
(1) The horizontal distance along the
takeoff path from the start of the take-
off to a point equidistant between the
liftoff point and the point at which the
airplane is 35 feet above the takeoff
surface as determined under § 23.57; or
(2) With all engines operating, 115
percent of the horizontal distance from
the start of the takeoff to a point equi-
distant between the liftoff point and
the point at which the airplane is 35
feet above the takeoff surface, deter-
mined by a procedure consistent with
§ 23.57.
[Amdt. 23–34, 52 FR 1827, Jan. 15, 1987, as
amended by Amdt. 23–50, 61 FR 5185, Feb. 9,
1996, as amended by Amdt. 23–62, 76 FR 75753,
Dec. 2, 2011]
§ 23.61
Takeoff flight path.
For normal, utility, and acrobatic
category multiengine jets of more than
6,000 pounds maximum weight and
commuter category airplanes, the
takeoff flight path must be determined
as follows:
(a) The takeoff flight path begins 35
feet above the takeoff surface at the
end of the takeoff distance determined
in accordance with § 23.59.
(b) The net takeoff flight path data
must be determined so that they rep-
resent the actual takeoff flight paths,
as determined in accordance with
§ 23.57 and with paragraph (a) of this
section, reduced at each point by a gra-
dient of climb equal to—
(1) 0.8 percent for two-engine air-
planes;
(2) 0.9 percent for three-engine air-
planes; and
(3) 1.0 percent for four-engine air-
planes.
(c) The prescribed reduction in climb
gradient may be applied as an equiva-
lent reduction in acceleration along
that part of the takeoff flight path at
which the airplane is accelerated in
level flight.
[Amdt. 23–34, 52 FR 1827, Jan. 15, 1987, as
amended by Amdt. 23–62, 76 FR 75753, Dec. 2,
2011]
§ 23.63
Climb: General.
(a) Compliance with the require-
ments of §§ 23.65, 23.66, 23.67, 23.69, and
23.77 must be shown—
(1) Out of ground effect; and
(2) At speeds that are not less than
those at which compliance with the
powerplant cooling requirements of
§§ 23.1041 to 23.1047 has been dem-
onstrated; and
(3) Unless otherwise specified, with
one engine inoperative, at a bank angle
not exceeding 5 degrees.
(b) For normal, utility, and acrobatic
category reciprocating engine-powered
airplanes of 6,000 pounds or less max-
imum weight, compliance must be
shown with § 23.65(a), § 23.67(a), where
appropriate, and § 23.77(a) at maximum
takeoff or landing weight, as appro-
priate, in a standard atmosphere.
(c) For reciprocating engine-powered
airplanes of more than 6,000 pounds
maximum weight, single-engine tur-
bines, and multiengine turbine air-
planes of 6,000 pounds or less maximum
weight in the normal, utility, and acro-
batic category, compliance must be
shown at weights as a function of air-
port altitude and ambient temperature,
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