Can't direct you to a publication, but the key issues are as follows:
1. The hinge line should be ahead of the centre of pressure CP otherwise the whole surface will want to flip 180. Having said that, with irreversible power actuated controls, the hinge line could be behind the CP for low speed flight, given that the CP moves aft as the critical Mach No increases. This photo of a Tornado is interesting in that respect:
http://www.aerophot.co.uk/images/VAL...20GR4%2008.jpg
2. The length of the moment arm between the CP and hinge line depends on what characteristics the designer wants in terms of b1/b2 ratio, which essentially sets how "heavy" the controls feel (if they are reversible, e.g. PA28, Robin DR400, etc). For aircraft with irreversible, power actuated controls (e.g. F4, Hawk, etc), the moment arm is fairly small to minimise the loads on the actuator. Next time you have a chance to look at an aircraft with an all-moving horizontal tailplane you will see the hinge line is normally some way back from the leading edge.
3. Not sure about CG position, but would suggest that most of the mass of the control surface would be near the hinge line.
Hope this helps!