ED Decision 2003/15/RM
(a) Each rotorcaft must be designed for the loads resulting from the manoeuvres specified in sub-paragraphs (b) and (c) with:
(1) Unbalanced aerodynamic moments about the centre of gravity which the aircraft reacts to in a rational or conservative manner considering the principal masses furnishing the reacting inertia forces; and
(2) Maximum main rotor speed.
(b) To produce the load required in subparagraph (a), in unaccelerated flight with zero yaw, at forward speeds from zero up to 0.6 VNE:
(1) Displace the cockpit directional control suddenly to the maximum deflection limited by the control stops or by the maximum pilot force specified in CS 27.397(a);
(2) Attain a resulting sideslip angle or 90°, whichever is less; and
(3) Return the directional control suddenly to neutral.
(c) To produce the load required in sub-paragraph (a), in unaccelerated flight with zero yaw, at forward speeds from 0.6 VNE up to VNE or VH, whichever is less:
(1) Displace the cockpit directional control suddenly to the maximum deflection limited by the control stops or by the maximum pilot force specified in CS 27.397(a);
(2) Attain a resulting sideslip angle or 15°, whichever is less, at the lesser speed of VNE or VH;
(3) Vary the sideslip angles of subparagraphs (b)(2) and (c)(2) directly with speed; and
(4) Return the directional control suddenly to neutral.
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