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2. Condition "G" need not be investigated when the supplementary condition pecified in § 23.369 is investigated.

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AVERAGE SURFACE LOADING POUNDS/SQ.FT.

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(2) HORIZONTAL TAIL (UP & DOWN LOADS)

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DESIGN MANEUVERING WING LOADING POUNDS/SQ. FT.

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(a) If allowed by the specific requirements in this part, the values of control surface loading in this appendix may be used to determine the detailed rational requirements of §§ 23.397 through 23.459 unless the Administrator finds that these values result in unrealistic loads.

(b) For a seaplane version of a landplane, the landplane wing loadings may be used to determine the limit maneuvering control surface loadings (in accordance with B23.11 and figure 1 of Appendix B) if—

(1) The power of the seaplane engines does not exceed the power of the landplane engines;

(2) The placard maneuver speed of the seaplane does not exceed the placard maneuver speed of the landplane;

(8) The maximum weight of the seaplane does not exceed the maximum weight of the landplane by more than 10 percent;

(4) The landplane service experience does not show any serious control-surface load problem; and

(5) The landplane service experience is of sufficient scope to ascertain with reasonable accuracy that no serious control-surface load problem will develop on the seaplane.

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obtained from figure 1 of this Appendix accordance with the following:

(a) For horizontal tall surfaces

(1) With the conditions in 23.423 (8) obtain w as a function of W/S and surfac deflection, using

(1) Curve C of figure 1 for a deflection 10° or less;

(11) Curve B of figure 1 for a deflectio of 20°;

(iii) Curve A for a deflection of 30° more;

(iv) Interpolation for all other deflection and

(v) The distribution of figure 7; and (2) With the conditions in § 23.423 (b obtain w from Curve B of figure 1 using th distribution of figure 7.

(b) For vertical tail surfaces

(1) With the conditions in § 23.441(a) (1 obtain w as a function of W/S and surfa deflection using the same requirements used in subdivisions (a) (1) (1) throug (a) (1) (v);

(2) With the conditions in § 23.441(a) (2 obtain w from Curve C, using the distrib tion of figure 6; and

obtain w from Curve A, using the dist (3) With the conditions in § 23.441(a) (3 bution of figure 8.

(c) For ailerons, obtain w from Curve acting in both the up and down direction using the distribution of figure 9.

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FIGURE 2-MANEUVERING TAIL LOAD INCREMENT (UP OR DOWN)

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OVERALL LENGTH OF AIRPLANE (FT)

DESIGN SPEED (MPH)

FIGURE 8-DOWN GUST LOADING ON HORIZONTAL TAIL SURFACE

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