syseng68k,
Because this is a rate of change limit, it means that increasing oscillatory demand input above the slew rate capability will result in ever decreasing amplitude at the control surface.
I believe this is a non-starter unless you posit the pilot was trying to get a little more speed by really flapping the control surfaces far harder than they are designed to take. There's a fairly simple reason for this beyond the fact that the design engineers were very probably quite competent with servo design. Think about the hydraulic loads during landing and take off when the landing gear and flaps are being extended and retracted. Can anything in flight even in a storm equal that load on the hydraulic pumps?
Unless my impression that the landing gear and flaps are hydraulic motors is wrong the entire issue is not worth commenting upon it's so far fetched. Even if the motors are electric for these two functions the design for the servo system would account for worst case operations as you noted.
{^_^}