§29.351 Yawing conditions

(a) Each rotorcraft must be designed for the loads resulting from the m anoeuvres specified in sub-paragraphs (b) and (c) , with: (1) Unbal anced aerodynamic moments about t he cent re of gravi ty whi ch the aircraft reacts to in a rational or conservative m anner considering the principal masses furnishing the reacting inertia forces; and (2) Maximum main rotor speed. (b) To produce t he l oad required in sub-paragraph (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 t he m aximum defl ection limited by the control stops or by the maximum pilot force specified in CS 29.397(a); (2) Attain a resu lting sid eslip an gle or 90°, whichever is less; and (3) Return th e d irectional control suddenly to neutral. (c) To produce t he l oad required in sub-paragraph (a) , in unaccelerated flight with zero yaw, at forward speeds from 0.6 V NE up to VNE or VH, whichever is less: (1) Displace the cockpit directional control suddenl y t o t he maximum deflection limited by t he cont rol st ops or by the maximum pilot force specified in CS 29.397(a); (2) Attain a resu lting sid eslip an gle or 15°, wh ichever is less, at the lesser speed of VNE or VH; (3) Vary t he si deslip angl es of sub-paragraphs (b)(2) and (c)(2) directly with speed; and (4) Return th e d irectional control suddenly to neutral.