Matt, mine's on the front of the firewall and I haven't had any problems due
to the location in 13+ years.

Having learned that a high percentage of experimental "incidents" were fuel
system related, I took a good look at quite a number of installations on
certificated aircraft when I got ready to install mine. Most, if not all, of
the ones I looked at had the boost pump on the engine side of the firewall.
Several had the pump boxed in in a cooling shroud with air piped in from the
rear baffling. Some merely had a cooling air hose directed at the pump and
many had nothing at all. The decision the designers made on various
airplanes on which way to go likely was based on the specific installation -
(but that may be giving them too much credit - can't say).

In any case, I decided to go with the cooling hose (approx. 3/4 inch dia.)
without a cooling shroud and, with quite a few hours flying in a high
temperature environment (California and Nevada high desert), there were no
noticeable problems.

The only caveat I can think of is the fact that my engine is a Lyc 0-235 and
may produce less waste heat in the area between the baffle and the firewall
than your 360. Of course, with the pump and gascolator located quite low on
the firewall, the temperature rise there is probably minimal compared to the
top of the firewall.

Cheers,

Dan Schaefer