193
Federal Aviation Administration, DOT
§ 23.67
within the operational limits estab-
lished for takeoff and landing, respec-
tively, with—
(1) Sections 23.65(b) and 23.67(b) (1)
and (2), where appropriate, for takeoff,
and
(2) Section 23.67(b)(2), where appro-
priate, and § 23.77(b), for landing.
(d) For multiengine turbine airplanes
over 6,000 pounds maximum weight in
the normal, utility, and acrobatic cat-
egory and commuter category air-
planes, compliance must be shown at
weights as a function of airport alti-
tude and ambient temperature within
the operational limits established for
takeoff and landing, respectively,
with—
(1) Sections 23.67(c)(1), 23.67(c)(2), and
23.67(c)(3) for takeoff; and
(2) Sections 23.67(c)(3), 23.67(c)(4), and
23.77(c) for landing.
[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996, as
amended by Amdt. 23–62, 76 FR 75753, Dec. 2,
2011]
§ 23.65
Climb: All engines operating.
(a) Each normal, utility, and acro-
batic category reciprocating engine-
powered airplane of 6,000 pounds or less
maximum weight must have a steady
climb gradient at sea level of at least
8.3 percent for landplanes or 6.7 percet
for seaplanes and amphibians with—
(1) Not more than maximum contin-
uous power on each engine;
(2) The landing gear retracted;
(3) The wing flaps in the takeoff posi-
tion(s); and
(4) A climb speed not less than the
greater of 1.1 V
MC
and 1.2 V
S1
for multi-
engine airplanes and not less than 1.2
V
S1
for single—engine airplanes.
(b) Each normal, utility, and acro-
batic category reciprocating engine-
powered airplane of more than 6,000
pounds maximum weight, single-engine
turbine, and multiengine turbine air-
planes of 6,000 pounds or less maximum
weight in the normal, utility, and acro-
batic category must have a steady gra-
dient of climb after takeoff of at least
4 percent with
(1) Take off power on each engine;
(2) The landing gear extended, except
that if the landing gear can be re-
tracted in not more than seven sec-
onds, the test may be conducted with
the gear retracted;
(3) The wing flaps in the takeoff posi-
tion(s); and
(4) A climb speed as specified in
§ 23.65(a)(4).
[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996, as
amended by Amdt. 23–62, 76 FR 75753, Dec. 2,
2011]
§ 23.66
Takeoff climb: One-engine inop-
erative.
For normal, utility, and acrobatic
category reciprocating engine-powered
airplanes of more than 6,000 pounds
maximum weight, and turbine engine-
powered airplanes in the normal, util-
ity, and acrobatic category, the steady
gradient of climb or descent must be
determined at each weight, altitude,
and ambient temperature within the
operational limits established by the
applicant with—
(a) The critical engine inoperative
and its propeller in the position it rap-
idly and automatically assumes;
(b) The remaining engine(s) at take-
off power;
(c) The landing gear extended, except
that if the landing gear can be re-
tracted in not more than seven sec-
onds, the test may be conducted with
the gear retracted;
(d) The wing flaps in the takeoff posi-
tion(s):
(e) The wings level; and
(f) A climb speed equal to that
achieved at 50 feet in the demonstra-
tion of § 23.53.
[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]
§ 23.67
Climb: One engine inoperative.
(a) For normal, utility, and acrobatic
category reciprocating engine-powered
airplanes of 6,000 pounds or less max-
imum weight, the following apply:
(1) Except for those airplanes that
meet the requirements prescribed in
§ 23.562(d), each airplane with a V
SO
of
more than 61 knots must be able to
maintain a steady climb gradient of at
least 1.5 percent at a pressure altitude
of 5,000 feet with the—
(i) Critical engine inoperative and its
propeller in the minimum drag posi-
tion;
(ii) Remaining engine(s) at not more
than maximum continuous power;
(iii) Landing gear retracted;
(iv) Wing flaps retracted; and
(v) Climb speed not less than 1.2 V
S1
.
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