But isn't that just wings
Actually the wing should see more load cycles than the pressure hull, which basically sees one per flight cycle.
The fuselage is generally more critical on metallic designs because of the potentially instable crack growth (aka the balloon pop). We find more fatigue cracks in other areas of the aircraft, the big difference is that we have some time to find them, as they grow slowly and controlled.
One detail I sometimes think about, is the fact that in metal aircraft design standard fasteners are never the fatigue critical components. Cracks start in the structural parts, typically at fastener holes. If the structural parts become fatigue resistant, are we going to experience fatigue to bolts and rivets some day?