Bend alot
This does not seem correct. The change in pitch moment is regardless of the length of the aft fuselage. The shorter the aft fuselage the greater the required force to offset the pitch moment change, so the greater the stabilizer movement to generate that force. Consider if the tail was at the rear of the wing but had to compensate for the same pitch moment. The loads would be far higher and require far more deflection to attain.
I don't foresee a large difference in pitch moment vs AoA for the nacelles based on aft-fuselage length so just going with the shortest aft fuselage should represent the worst case for that parameter.