A lighter airplane can develop a high load factor more easily than a heavier, if otherwise similar, one can. They usually share the same "n" figures in order to achieve certification (+3.8 g's/-1.52 g's).

Load factor (n)= Lift / weight; but Lift= q*CL*A; so if CL and A are held the same for two similar airplanes, then only q can be changed. Q is dynamic pressure or speed of the air. So, to get the same ratio of lift to weight in a lighter airplane, you need to go slower. A or alpha would be the same for a given wing design or even different loadings, and is independent of speed, because by the definition of Va, the wing must be at its stalling angle of attack at Va.

Not sure if I am answering the right question or not...