NoD beat me to it.....
An aircraft can spin (auto rotate) quite happily with both wings stalled. In fact, this is usually the case.
Also, whilst the recovery procedure is VERY type specific, the order of actions just given doesn't sit easy with me.
The whole point of easing the control column forward is to recover from the stall. Unless you have to for POH reasons, you do not want to be auto-rotating whilst stuffing the nose down.
Saying
stick forward until rotation stops
suggests that you think this is what causes the rotation to stop. It is the opposite rudder which achieves this.
A more sensible recovery sequence for a genreic type would have you easing the control column forward AFTER the autorotation has stopped. Otherwise you run the risk of tightening the spin.
EK