Airframe manufacturers seem to have a much better understanding of avoiding fatigue cracks in wing structures now.
I remember the Trident wing crack problems in 1977
https://www.flightglobal.com/FlightP...20-%202406.PDF
Extra metal straps fitted under the wing and wing lift redistribution with less lift outboard (ailerons rigged upwards) and more lift inboard (flaps rigged slightly extended) in an attempt to extend the fatigue life.
Weight not carried in the wings will result in extra wing flexing / bending / stressing somewhere.