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:
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. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-23, 35 FR 5673, Apr. 8, 1970]
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