FCeng84. With the above in mind; my supposition for comment;- perhaps a scenario of 1.1Vs stick-shake (trim point 1.3/1.4Vs), has insufficient stability margin to manage a ‘powering out - approach to stall recovery’, such that the pitching moment from thrust is greater than that could be negated by acceleration. i.e. the aircraft pitches faster than it accelerates such that it reaches stall AoA during recovery (~ even more forward stick during a go around.).
Bergerie. Further supposition following the above; a nudger would apply a nose down force - relating to stick force / speed stability, which in the 737 appears to addressed by STS.
Whereas in the MAX, the problem might be the rate of pitch up relating to thrust and AoA, which feature as inputs to the trim computation.
“… electric trim is just blipped…”.
Or worse still if the pilot holds the finger on the electric trim ???