Delamination is like a piece of plywood that evntually buckles and sags.
Cracks through a solid beam spontaneously snap and the beam collapses.
What level of load, across a supporting structure, is carried (basic everyday stress) plays a part. Only the designer knows what level of basic stress is present. Thus I don't sense a conclusion between a fuselage and wing part without knowing this stress (its not just a load issue)