ED Decision 2003/18/RM
(a) At speeds up to VA, the vertical tail surfaces must be designed to withstand the following conditions. In computing the tail loads, the yawing velocity may be assumed to be zero -
(1) With the aeroplane in unaccelerated flight at zero yaw, it is assumed that the rudder control is suddenly displaced to the maximum deflection, as limited by the control stops or by limit pilot forces.
(2) With the rudder deflected as specified in sub-paragraph (a)(1) of this paragraph, it is assumed that the aeroplane yaws to the resulting sideslip angle. In lieu of a rational analysis, an overswing angle equal to 1.3 times the static sideslip angle of sub-paragraph (a)(3) of this paragraph may be assumed.
(3) A yaw angle of 15 degrees with the rudder control maintained in the neutral position (except as limited by pilot strength).
(b) The average loading of Appendix B, B11 and figure B1 of Appendix B and the distribution in figures B6, B7 and B8 of Appendix B may be used instead of requirements of subparagraphs (a)(2), (a)(1) and (a)(3) of this paragraph, respectively.
(c) The yaw angles specified in sub-paragraph (a)(3) of this paragraph may be reduced if the yaw angle chosen for a particular speed cannot be exceeded in -
(1) Steady slip conditions;
(2) Uncoordinated rolls from steep banks.
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