Originally Posted by
Aihkio
Yes, wing lift distribution affects the max bending moment but it does not affect the loads transfered to the fuselage. The total lift is not affected by the distribution. What might cause a slight difference is the larger displacements caused by larger moment but as a guess that is not the first concern.
I afraid it does affect the loads into the fuselage.
you are right in that the "Shear Loads" must be the same, as the weight inboard of the wing-root is the same, so the wings have to lift the same weight, however the bending moment going into the fuselage is increase, because the lift is further outboard. So the combination of loads going into the fuselage changes. These forks look like they "Predominantly" take vertical load, but the load transfer in this part of an aircraft is extremely complex and different loads combine in different ways, all depending on the various component stiffness.
Maximum loads and fatigue loads will have changed by a different factor or %, this looks like fatigue and I'd expect the fatigue loads to increase by a higher % that the static cases when putting a large winglet on the end of the tip