Interesting answers !
Point is, in conventionally-configured aircraft (like -51 platform) the “horizontal stabilizer” (to give its correct name ) “flies down” ! That is it applies force in 180’ opposition to the aerodynamic forces from the main plain, (i.e. wing) ! Suddenly remove this force and the aircraft “pitches over “ i.e. noses “down” from the pilot’s viewpoint.
IOW, some conclusions/suppositions I’ve read, here and elswhere, claiming the “tail failure caused the pitch up” are, IMO, pretty much false to known fact. Loss of the trim tab might - indeed probably - increased stick pitch forces but not - IMNSHO - to the point of causing a LOC. (I know I’d configure the aircraft W/B and consummable loads consumption CG changes to create/maintain a neutral or aft limit CG in order to minimize “trim drag”.)
Want a real world description of what a “tail loss stall” is ? Read Bob Cardenas’ description of his first stall in the first Northrup flying wing ! It had no tail ! >PS
The wings (obviously) provide lift at approx. the aircraft's center of gravity. The horizonal stabilizer does just that -- stabilizes the aircraft's pitch. The elevators provide the up or down movement to the tailplane to cause the nose (and angle of attack) to go up or down, according to the pilot's wishes. i.e., the pilot pulls back the stick, the elevators move up, pushing the tail down which rotates the nose up. (pitch rotates about the center of gravity)