# Can spar stresses be calculated using zero (wing) fuel?

For a homebuilt prototype aircraft meant for the primary or Canadian JAR-VLA category, is it OK to assume that spar stresses (other than landing loads) can be calculated using zero-wing-fuel numbers? Or perhaps the landing loads usually negate that zero-fuel stress relief?

So, when specifying plus and minus stresses, both the wing and its fuel content can be discounted except for full-fuel aileron loads?