The computation of launch time for P12 rely obviously on CSM orbit characteristics and CSM position on this orbit. The liftoff and ascent belong already to the main target as that time of the mission: to realize an optimum rendezvous (fuel usage) with the CSM.
As you probably remarked, the liftoff of the ascent stage will always occur when the CSM pass over the landing site. This is probably because it is the optimal position for an efficient rendezvous.
Now, the challenge is to obtain that the numerous orbits the CSM do until it reach this precise launch position respect the historical timings too. This is not obvious at all, because Orbiter do not simulate all the true characteristics of Moon orbits. It will also become more and more difficult to achieve this goal with all successive missions, because the time passed on the surface will increase more and more and you have therefore more and more CSM orbits until that time.
Therefore, you will have to cheat more or less, with Orbit characteristics (first eliptical orbit after LOI #1, and the most important, the more or less circular orbit, after LOI #2) in order the CSM to remain as close as possible on historical timings.
In fact, this timing problem begin even before that. It begin with the TLI and TLCC (flight correction) characteristics, in order to obtain a LOI #1 burn, right on historical time, to start with. This is now perfectly possible to do, thanks to the incredible precision of the flight instrument "LunarTransfertMFD".
I hope this help.
ACS