227
Federal Aviation Administration, DOT
§ 23.525
Tow point
Position
Load
Magnitude No.
Direction
Swiveled 45
°
from forward ..............
0.15W
9
10
Forward, in plane of wheel.
Aft, in plane of wheel.
Swiveled 45
°
from aft ......................
0.15W
11
12
Forward, in plane of wheel.
Aft, in plane of wheel.
[Amdt. 23–14, 38 FR 31821, Nov. 19, 1973]
§ 23.511
Ground load; unsymmetrical
loads on multiple-wheel units.
(a)
Pivoting loads. The airplane is as-
sumed to pivot about on side of the
main gear with—
(1) The brakes on the pivoting unit
locked; and
(2) Loads corresponding to a limit
vertical load factor of 1, and coefficient
of friction of 0.8 applied to the main
gear and its supporting structure.
(b)
Unequal tire loads. The loads es-
tablished under §§ 23.471 through 23.483
must be applied in turn, in a 60/40 per-
cent distribution, to the dual wheels
and tires in each dual wheel landing
gear unit.
(c)
Deflated tire loads. For the deflated
tire condition—
(1) 60 percent of the loads established
under §§ 23.471 through 23.483 must be
applied in turn to each wheel in a land-
ing gear unit; and
(2) 60 percent of the limit drag and
side loads, and 100 percent of the limit
vertical load established under §§ 23.485
and 23.493 or lesser vertical load ob-
tained under paragraph (c)(1) of this
section, must be applied in turn to
each wheel in the dual wheel landing
gear unit.
[Amdt. 23–7, 34 FR 13090, Aug. 13, 1969]
W
ATER
L
OADS
§ 23.521
Water load conditions.
(a) The structure of seaplanes and
amphibians must be designed for water
loads developed during takeoff and
landing with the seaplane in any atti-
tude likely to occur in normal oper-
ation at appropriate forward and sink-
ing velocities under the most severe
sea conditions likely to be encoun-
tered.
(b) Unless the applicant makes a ra-
tional analysis of the water loads,
§§ 23.523 through 23.537 apply.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–45, 58 FR 42160, Aug. 6,
1993; Amdt. 23–48, 61 FR 5147, Feb. 9, 1996]
§ 23.523
Design weights and center of
gravity positions.
(a)
Design weights. The water load re-
quirements must be met at each oper-
ating weight up to the design landing
weight except that, for the takeoff con-
dition prescribed in § 23.531, the design
water takeoff weight (the maximum
weight for water taxi and takeoff run)
must be used.
(b)
Center of gravity positions. The
critical centers of gravity within the
limits for which certification is re-
quested must be considered to reach
maximum design loads for each part of
the seaplane structure.
[Doc. No. 26269, 58 FR 42160, Aug. 6, 1993]
§ 23.525
Application of loads.
(a) Unless otherwise prescribed, the
seaplane as a whole is assumed to be
subjected to the loads corresponding to
the load factors specified in § 23.527.
(b) In applying the loads resulting
from the load factors prescribed in
§ 23.527, the loads may be distributed
over the hull or main float bottom (in
order to avoid excessive local shear
loads and bending moments at the lo-
cation of water load application) using
pressures not less than those pre-
scribed in § 23.533(c).
(c) For twin float seaplanes, each
float must be treated as an equivalent
hull on a fictitious seaplane with a
weight equal to one-half the weight of
the twin float seaplane.
(d) Except in the takeoff condition of
§ 23.531, the aerodynamic lift on the
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