Without any atmosphere (and no Time Square lights..) the moon's night is COMPLETELY BLACK.

Also the first and last days of the moon day are unusable because the shadows are too large.

The number of usable moon days is around 10-12 max and in these days the LSAM must land, remain a week for the exploration and come back to lunar orbit.

Then, to arrive on the moon in the "right days", the CEV/LSAM must leave the earth orbit exactly 3-4 days before the better moon days.

This is the first (unquestionable!) ARGUMENT that reduces the 95 days of max orbital loither time to less than 30 (really usable) days.

But not all the hours of these days can be used for the launch of the CEV because, while the LSAM/EDS rotates with its orbital inclination, also the earth rotate by itself.

Then, inside these 30 days, will be a number of "launch windows" that must be used to launch the CEV in the right orbit, with the right inclination to rendez-vous the LSAM/EDS (not before nor after!).

If the delays will happen in these critical hours the mission will fails.

But... how many delays will happen with the second launches?

I don't know and no one can know to-day the real figures.

We must wait the 2018-2020 to know them.

I only make a simple statement (that, I think, is another unquestionable ARGUMENT): "with the "one-and-half" launch architecture, a (possible) "sum of delays" will be equal to a MISSION FAILS, while, with a single launch architecture, also DOZENS of delays (for weeks, months or years!) will NEVER mean a FAILS (with a GIANT loss of hardware and money!) but ONLY a simple "delay of the mission"!" (and this is clearly an ARGUMENT)