To: NickLappos
Yes Lu, you were wrong when you wrote : "CFR-14-27.351 requires full deflection of the tail rotor pedals while airborne from 0 to 0.6 VNE " That was WRONG Lu.
CFR-14-351 paragraph (2b) states: To produce the load required in paragraph (a) of this section, in unaccelerated flight with zero yaw, at forward speeds from zero up to 0.6 VNE followed by paragraph (1) Displace the cockpit directional control suddenly to the maximum deflection limited by the control stops or, by pilot force specified in 27-395 (Note: the R-22 control system is very simple and offers no resistance to pilot input other than that generated by the tail rotor and therefore CFR-14-395 does not apply.
This is followed by paragraph (2) which states, Attain a resulting sideslip angle of 90-degrees, whichever is less. The controls are suddenly returned to neutral and the test is repeated in the opposite direction.
