If you read what Inbalance says carefully, he is absolutely correct. If we ignore compressibility effects, in pitch you trim an aircraft in straight and level flight to an AoA (not an altitude or IAS). Therefore, if you trim straight and level, roll into a turn and RELEASE THE CONTROLS, the AoA will be the trim value so long as there is no significant pitch rate.
A lot of the discussion above is dependent on perspective (chicken and egg syndrome). In a stabilised manoeuvre there will be a given elevator angle which is directly a function of AoA and pitch rate. However, this elevator angle will, for a given AoA and pitch rate, be a function of mainly EAS, c.g. position and Mach number. Pitch rate is a function of TAS, normal acceleration and attitude. It is then a juggling act of these parameters from your required perspective. The above list may not be totally complete, and I will edit this post after a bit of thought if I come up with any more.