Originally Posted by
Aihkio
When the wing has the max +g load the fuselage has a high bending load tension at the top. A heavy landing might cause slightly higher bending moment but the sense is the same. I have never calculated the shear but I expect a heavy landing would be the worst case.
Freight doors being at the lower half of the hull would require some strange shape changes to pop off as it would be under longitudinal compression.
Isn’t that only true in flight? During a static test of the wings there will be no bending of the fuselage as the centre section is pinned down to oppose the wing-bending force. Circumferential distortion, maybe...