This latest discussion supports my theory of the stab actuator jackscrew fuselage attach bolt falling out. As the bolt worked its way out to the point where only the threads were engaged with the jackscrew, there would be enough slack to allow an aerodynamically preloaded stab to move slightly stab nose down resulting in a slight pitch up. The PF would instinctively push forward on the column aerodynamically unloading the stab rotational force and allow the bolt to fall out and the stab to rotate stab nose up past its design limit. When the stab moved pat the design limits, contact with the stab structure and the elevator control cables would have compromised the control cable integrity rendering the elevator controls useless. Due to the sudden unexpected negative Gs, the PF would instinctively think they were in a wind shear stall ant push forward on the column and throttles. The other pilot would respond to the precipitous nose down attitude by pulling aft on the column. Being in a sudden loss of control situation, and both pilots equally convinced that their recovery attempt was correct would result in a column disconnect with no resulting elevator movement as the control cable integrity was compromised. When the sudden and severe pitch down occurred, the pitch momentum would allow the stab to stall out. As the pitch down momentum continued, the greater flat square area of the stab forward of the hinge point would push the stab to a stab nose down causing the final pitch up. Look at the picture of the jackscrew and notice no blot or compromise of the attachment lug.