Rolling g limits are actaully more to do with a phenominum known as 'yaw divergence'. A rapidly rolling aircraft, if pitched slightly will develope two c of gs, one at each end of the fuselage. The resultant moment's of inertia have an effect on the longitudianal axis and the airaraft will pitch further causing loss of control.
Many early jet fighters were lost to this before it was understood. IIRC, the Hawk has a rolling limit of one and a half turns because of yaw divergence.