Pulled out the trusty straight edges & cam degree wheel using my typical "less than really accurate measuring methods" ...

Assumptions:
. SIG frequently designs their kits (source is SIG mfg rep) with the stab at 0 degrees incidence.
. I'm calling the line extending from the bottom of the stab forward to the firewall, parallel to and flush with the bottom of the stab the "datum line".

Measurements:
. The firewall is installed at 90 degrees to the datum line.
. The motor mount (mounted at 90 degrees) is angled 3 degrees down from the datum line (with washers installed). I'm assuming that this is 3 degrees of down thrust.
. The chord of the wing (center of the wing's trailing edge to center of its leading edge) is about 1/2 degree below the datum line.

In flight I'm assuming that the forces on the wing's center-line will dominate when trying to fly straight-n-level. With the stab's center-line angled above the wing's center-line the stab and elevator (when extended in the same plane as the stab) will generate an upward force behind the center of lift of the wing forcing the nose down. As a result up elevator needs to be applied to push the stab back down.

If this is scenario is correct what are my alternatives?
. adjust the elevator to be in line with the wing center line. This would requiring "breaking" the entire tail assembly apart and reconstructing / recovering.
. adjust the wing to be in line with the elevator (datum line). This would require moving the dowel hole thru the fuse down dropping the rear of the wing a bit to bring it parallel to the datum line.
. add more down thrust to the engine. The affect of this modification would seem to be dependent on throttle position.

What 'cha think?

Update: just checked the planes from a new SSE kit off the shelf: the wing center line & the stab / elevator should both be at 0 degrees. Guess that that means dropping the trailing edge of the wing a bit ...