248
14 CFR Ch. I (1–1–14 Edition)
§ 23.737
where—
KE=Kinetic energy per wheel (ft.-lb.);
W=Design landing weight (lb.);
V=Airplane speed in knots. V must be not
less than V
S
√
, the poweroff stalling speed
of the airplane at sea level, at the design
landing weight, and in the landing con-
figuration; and
N=Number of main wheels with brakes.
(b) Brakes must be able to prevent
the wheels from rolling on a paved run-
way with takeoff power on the critical
engine, but need not prevent movement
of the airplane with wheels locked.
(c) During the landing distance deter-
mination required by § 23.75, the pres-
sure on the wheel braking system must
not exceed the pressure specified by the
brake manufacturer.
(d) If antiskid devices are installed,
the devices and associated systems
must be designed so that no single
probable malfunction or failure will re-
sult in a hazardous loss of braking abil-
ity or directional control of the air-
plane.
(e) For airplanes required to meet
§ 23.55, the rejected takeoff brake ki-
netic energy capacity rating of each
main wheel brake assembly may not be
less than the kinetic energy absorption
requirements determined under either
of the following methods—
(1) The brake kinetic energy absorp-
tion requirements must be based on a
conservative rational analysis of the
sequence of events expected during a
rejected takeoff at the design takeoff
weight.
(2) Instead of a rational analysis, the
kinetic energy absorption require-
ments for each main wheel brake as-
sembly may be derived from the fol-
lowing formula—
KE = 0.0443 WV
2
/N where;
KE = Kinetic energy per wheel (ft.-
lbs.);
W = Design takeoff weight (lbs.);
V = Ground speed, in knots, associated
with the maximum value of V
1
se-
lected in accordance with
§ 23.51(c)(1);
N = Number of main wheels with
brakes.
[Amdt. 23–7, 34 FR 13092, Aug. 13, 1969, as
amended by Amdt. 23–24, 44 FR 68742, Nov. 29,
1979; Amdt. 23–42, 56 FR 354, Jan. 3, 1991;
Amdt. 23–49, 61 FR 5166, Feb. 9, 1996; Amdt.
23–62, 76 FR 75757, Dec. 2, 2011]
§ 23.737
Skis.
The maximum limit load rating for
each ski must equal or exceed the max-
imum limit load determined under the
applicable ground load requirements of
this part.
[Doc. No. 26269, 58 FR 42165, Aug. 6, 1993]
§ 23.745
Nose/tail wheel steering.
(a) If nose/tail wheel steering is in-
stalled, it must be demonstrated that
its use does not require exceptional
pilot skill during takeoff and landing,
in crosswinds, or in the event of an en-
gine failure; or its use must be limited
to low speed maneuvering.
(b) Movement of the pilot’s steering
control must not interfere with the re-
traction or extension of the landing
gear.
[Doc. No. 27806, 61 FR 5166, Feb. 9, 1996]
F
LOATS AND
H
ULLS
§ 23.751
Main float buoyancy.
(a) Each main float must have—
(1) A buoyancy of 80 percent in excess
of the buoyancy required by that float
to support its portion of the maximum
weight of the seaplane or amphibian in
fresh water; and
(2) Enough watertight compartments
to provide reasonable assurance that
the seaplane or amphibian will stay
afloat without capsizing if any two
compartments of any main float are
flooded.
(b) Each main float must contain at
least four watertight compartments
approximately equal in volume.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–45, 58 FR 42165, Aug. 6,
1993]
§ 23.753
Main float design.
Each seaplane main float must meet
the requirements of § 23.521.
[Doc. No. 26269, 58 FR 42165, Aug. 6, 1993]
§ 23.755
Hulls.
(a) The hull of a hull seaplane or am-
phibian of 1,500 pounds or more max-
imum weight must have watertight
compartments designed and arranged
so that the hull auxiliary floats, and
tires (if used), will keep the airplane
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