For the wing and its attachment to the hull or main float --
(a) The aerodynamic wing lift is assumed to be zero; and
(b) A downward inertia load, corresponding to a load factor computed from the following formula, must be applied:
![[formula]](/data_img/FARS/23.531_1.gif)
Where --
n=inertia load factor;
CTO=empirical seaplane operations factor equal to 0.004;
VS1=seaplane stalling speed (knots) at the design takeoff weight with the flaps extended in the appropriate takeoff position;
β=angle of dead rise at the main step (degrees); and
W=design water takeoff weight in pounds.
[Doc. No. 26269, 58 FR 42161, Aug. 6, 1993]
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