196
14 CFR Ch. I (1–1–14 Edition)
§ 23.77
a point 50 feet above the landing sur-
face must be determined, for standard
temperatures at each weight and alti-
tude within the operational limits es-
tablished for landing, as follows:
(a) A steady approach at not less
than V
REF
, determined in accordance
with § 23.73 (a), (b), or (c), as appro-
priate, must be maintained down to the
50 foot height and—
(1) The steady approach must be at a
gradient of descent not greater than 5.2
percent (3 degrees) down to the 50-foot
height.
(2) In addition, an applicant may
demonstrate by tests that a maximum
steady approach gradient steeper than
5.2 percent, down to the 50-foot height,
is safe. The gradient must be estab-
lished as an operating limitation and
the information necessary to display
the gradient must be available to the
pilot by an appropriate instrument.
(b) A constant configuration must be
maintained throughout the maneuver.
(c) The landing must be made with-
out excessive vertical acceleration or
tendency to bounce, nose over, ground
loop, porpoise, or water loop.
(d) It must be shown that a safe tran-
sition to the balked landing conditions
of § 23.77 can be made from the condi-
tions that exist at the 50 foot height, at
maximum landing weight, or at the
maximum landing weight for altitude
and temperature of § 23.63 (c)(2) or
(d)(2), as appropriate.
(e) The brakes must be used so as to
not cause excessive wear of brakes or
tires.
(f) Retardation means other than
wheel brakes may be used if that
means—
(1) Is safe and reliable; and
(2) Is used so that consistent results
can be expected in service.
(g) If any device is used that depends
on the operation of any engine, and the
landing distance would be increased
when a landing is made with that en-
gine inoperative, the landing distance
must be determined with that engine
inoperative unless the use of other
compensating means will result in a
landing distance not more than that
with each engine operating.
[Amdt. 23–21, 43 FR 2318, Jan. 16, 1978, as
amended by Amdt. 23–34, 52 FR 1828, Jan. 15,
1987; Amdt. 23–42, 56 FR 351, Jan. 3, 1991;
Amdt. 23–50, 61 FR 5187, Feb. 9, 1996]
§ 23.77
Balked landing.
(a) Each normal, utility, and acro-
batic category reciprocating engine-
powered airplane at 6,000 pounds or less
maximum weight must be able to
maintain a steady gradient of climb at
sea level of at least 3.3 percent with—
(1) Takeoff power on each engine;
(2) The landing gear extended;
(3) The wing flaps in the landing posi-
tion, except that if the flaps may safely
be retracted in two seconds or less
without loss of altitude and without
sudden changes of angle of attack, they
may be retracted; and
(4) A climb speed equal to V
REF
, as de-
fined in § 23.73(a).
(b) Each normal, utility, and acro-
batic category reciprocating engine-
powered and single engine turbine pow-
ered airplane of more than 6,000 pounds
maximum weight, and multiengine tur-
bine engine-powered airplane of 6,000
pounds or less maximum weight in the
normal, utility, and acrobatic category
must be able to maintain a steady gra-
dient of climb of at least 2.5 percent
with—
(1) Not more than the power that is
available on each engine eight seconds
after initiation of movement of the
power controls from minimum flight-
idle position;
(2) The landing gear extended;
(3) The wing flaps in the landing posi-
tion; and
(4) A climb speed equal to V
REF
, as de-
fined in § 23.73(b).
(c) Each normal, utility, and acro-
batic multiengine turbine powered air-
plane over 6,000 pounds maximum
weight and each commuter category
airplane must be able to maintain a
steady gradient of climb of at least 3.2
percent with—
(1) Not more than the power that is
available on each engine eight seconds
after initiation of movement of the
power controls from the minimum
flight idle position;
(2) Landing gear extended;
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