delta3 and Lu,
That is a nice study of what happens, the reason why the control sneaks all the way to the stops is that the rotor control power is nil at zero g, since the thrust is zero. If you try that with an articulated or "rigid" system the control will be retained. It has nothing to do with any missing rigging angles.
Teetering rotors have zero cyclic control at zero g. Thus any unbalancing force will upset thye aircraft.