Forces that wing attach fittings must transfer to fuselage?
For your first question, it depends on the way they are attached, as is often the case in structures. I haven't seen this model up close to know their fitting type, but:


If they are fixed by a joint that allows them to rotate (the easiest and cheapest solution) then they can only carry one kind of load, that being tensile (or compressive) stresses. this would mean they can only transmit force along their own axis.
If they are rigidly jointed (cannot rotate at the joint) then they also carry some torque, although how much is a matter for the structural engineers. My guess is not much as the attachment points already offer a large moment arm.


For your second question, I believe you mean to ask for what part of the overall lift are the lift struts responsible for. That I cannot readily answer without some calculations I don't have time for right now, but it is not as straightforward as you imply. The Wing-Fuselage-Strut structure is hyperstatic (statically indeterminate or over-constrained) so it is a bit too long to napkin-math.