(b)
In applying the loads resulting from the load factors prescribed in Sec. 23.527, the loads may be distributed over the hull or main .oat bottom (in order to avoid excessive local shear loads and bending moments at the location of water load application) using pressures not less than those prescribed in Sec. 23.533(c).
(c)
Fortwin .oatseaplanes, each.oat mustbetreated asanequivalenthull ona .ctitious seaplane with a weight equal to one-half the weight of the twin .oat seaplane.
(d)
Except in the takeo. condition of Sec. 23.531, the aerodynamic lift on the seaplane during the impact is assumed to be 2 of the weight of the seaplane.]
3
Amdt. 23-45, E.. 09/07/93
′
Elodie Roux. Septembre 2003
Subpart C : Structure
FAR23.527:[Hull andmain .oatloadfactors.]
(a) [Water reaction load factorsnw must be computed in the following manner :
(1) For the step landing case
2
C1 VS0
nw =
2313
(tanβ)
W
(2) For the bow and stern landing cases
2
C1 VS0 K1
nw =
2323
13
(1+
r2
x
(tanβ)
W
)
(b)
The following values are used :
(1)
nw = water reactionloadfactor(thatis, the water reactiondividedby seaplane weight).
(2)
C1 = empirical seaplane operations factor equal to 0.012 (except that this factor may not be less than that necessary to obtain the minimum value of step load factor of 2.33).
(3)
VS0 = seaplane stalling speed in knots with .aps extended in the appropriate landing position and with no slipstream e.ect.
(4)
β = angle of dead rise at the longitudinal station at which the load factor is being determined in accordance with .gure 1 of appendix I of this part.
(5)
W = seaplane design landing weight in pounds.
(6)
K1 = empirical hull station weighing factor, in accordance with .gure 2 of appendix I of this part.
(7)
rx = ratio of distance, measuredparallel to hull reference axis,from the center of gravity of the seaplane to the hull longitudinal station at which the load factorisbeing computed to the radius ofgyrationinpitch of the seaplane, the hull reference axis being a straight line, in the plane of symmetry, tangential to the keel at the main step.
(c)
For a twin .oat seaplane, because of the e.ect of .exibility of the attachment of the .oats to the seaplane, the factor K1 may be reduced at the bow and stern to 0.8 of the value shown in .gure 2 of appendix I of this part. This reduction applies only to the design of the carrythrough and seaplane structure.]
Amdt. 23-45, E.. 09/07/93
FAR23.529:[Hull andmain .oatlanding conditions.]
(a) [Symmetrical step, bow, and stern landing. For symmetrical step, bow, and stern landings,thelimitwater reactionloadfactors arethose computed underSec.23.527. In addition–
(1)
For symmetrical steplandings, the resultant waterload mustbe applied at the keel, through the center of gravity, and must be directed perpendicularly to the keel line;
(2)
For symmetricalbowlandings, the resultant waterload mustbe applied at the keel, one-.fth of the longitudinal distance from the bow to the step, and must bedirectedperpendicularly tothekeelline; and
(3) For symmetrical stern landings, the resultant water load must be applied at the keel, at a point 85 percent of the longitudinal distance from the step to the stern post, and must be directed perpendicularly to the keel line.
(b)
Unsymmetrical landing for hull and single .oat seaplanes.Unsymmetrical step,bow, and stern landing conditions must be investigated. In addition–
(1)
The loading for each condition consists of an upward component and a side component equal, respectively, to 0.75 and 0.25 tan times the resultant load in the corresponding symmetrical landing condition; and
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 2(13)
