This is a question, not an assertion; Believing that the trim tab failure caused a very unusual and uncontrollable pitch change, would it be possible for the aircraft to sustain a very brief pitch up to record the stated 21G? Could it occur, but not for long enough for the aircraft to actually stall at that G load and relieve itself? Like gust loading, could an event like this occur, cause various loads and effects to the aircraft, but not be sustained long enough for the aircraft to actually stall?