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:[GRAPHIC] [TIFF OMITTED] TC28SE91.038 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;[beta]=angle of dead rise at the main step (degrees); andW=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]