of the controls about any one axis
Change that to read something like -
.. one full input of any single control in isolation followed by relaxation of the input ...
and the intent is OK.
This covers
(a) the (usual) case where pitching is limiting and structural limit load (maximum load without something bending to the point of stretching or breaking). In this situation, accelerated stall occurs at the limit load factor.
(b) the case where pitching is not the limiting case. For instance, as I recall, the HS125 Va was rudder input limiting. Stretching the memory I vaguely recall that the problem was a yaw divergence instability.
(c) .. and don't play an organ tune on the pedals ...
extremely rapid control input may do the same
Probably not for most aircraft but certainly a potential pitching problem in aircraft with very high pitch rate capability where a vortex can be established on top of the wing with a significant overshoot of the normal stall angle.