Text in force at CS29-12: from CS29-1, effective 30 Nov 2007.
(a) The directional controls m ust operat e i n such a m anner t hat t he sense and di rection of motion of the rotorcraft following control displacement are in the direction of the pedal motion with th rottle an d co llective co ntrols h eld constant at th e trim co nditions sp ecified in CS 29.175 (a), (b), (c) and (d). Si deslip angl es m ust increase with steadily increasing di rectional control deflection for si deslip angl es up t o t he lesser of:
(1) ±25 degrees from trim at a speed of 28 km/h (15 knot s) l ess t han t he speed for minimum rate o f d escent v arying lin early to ±10 degrees from trim at VNE;
(2) The steady-state sideslip angles established by CS 29.351;
(3) A sideslip angle selected by the applicant which corresponds to a sideforce of at least 0.1g; or
(4) The sid eslip an gle attain ed by maximum directional control input.
(b) Sufficient cues must accom pany the sideslip to alert th e p ilot wh en approaching sideslip limits.
(c) During t he m anoeuvre speci fied in sub-paragraph (a) of t his paragraph, the sideslip angle versus directional control position curve may have a negative slope within a sm all range of angl es around trim, provided t he desi red headi ng can be maintained without excep tional piloting skill or alertness.
ED Decision 2007/014/R · Source