Text in force at CS29-12: from CS29-0, effective 14 Nov 2003.
(a) A rotor is an assem bly of rotating components, which includes the rotor hub, blades, blade dampers, the pitch control m echanisms, and all other parts that rotate with the assembly.
(b) Each rotor assem bly m ust be desi gned as prescribed i n t his paragraph and must function safely fo r th e critical flig ht lo ad an d operating conditions. A desi gn assessm ent m ust be performed, including a d etailed failu re an alysis to identify all failu res th at will prevent continued safe flight or safe l anding, and m ust i dentify t he means to m inimise t he l ikelihood of t heir occurrence.
(c) The rot or st ructure m ust be designed to withstand th e fo llowing lo ads p rescribed in CS 29.337 to 29.341, and CS 29.351:
(1) Critical flight loads.
(2) Limit loads occurri ng under norm al conditions of autorotation.
(d) The rot or st ructure m ust be designed to withstand loads simulating:
(1) For t he rot or bl ades, hubs and flapping hinges, the impact force of each blade against its stop during ground operation; and
(2) Any ot her cri tical condi tion expected in normal operation.
(e) The rot or st ructure m ust be designed to withstand th e limit to rque at any rotational speed, including zero. In addition:
(1) The limit torque need not be great er than the torque defi ned by a t orque l imiting device (where provi ded), and m ay not be l ess than the greater of:
(i) The maximum torque likely to be tran smitted to th e rotor structure, in either direction, by t he rot or dri ve or by sudden application of the rotor brake; and
(ii) For th e m ain ro tor, th e lim it engine torque specified in CS 29.361.
(2) The limit torque m ust b e eq ually and rationally distributed to the rotor blades.
ED Decision 2003/016/RM · Source