da Rock

The real problem isn't at the very center of the wing, but everywhere along the wing that resists the wing from naturally dealing with the forces from root to tip.

Using the 208 lbs for a start, where the unmovable cradle stops a couple of inches out from the center of the wing there is going to be pretty close to 208 lbs of force trying to snap that wing off right there where the most vicious stress riser will be. There will also be some mean stress risers out on the dihedral joint outboard on the wing.

Everywhere we reinforce the hell out of things, those things experience hell when the entire system is stressed. The hell will be focused where the flexing is stopped.

BTW, the saddle will of course be strong enough to shift a lot of stress elsewhere. (the stress isn't absorbed by absolutely rigid structures) So where could the stress go? How about where the pylon enters the fuselage? and there is no steel to completely pass the stress to somewhere else.