An electric control system (1) comprises a control unit (4) which
comprises a member (5) able to be actuated by a pilot and a means of load-wise
protection (7), and which delivers a first deflection order representative
of the action exerted by the pilot on the member (5), and of the contribution
made by the means of load-wise protection (7), an actuator (11) which
moves said control surface (2) about an axis (Z-Z), as a function of a deflection
order, and a correction device (12) which comprises a means (13)
for determining a second deflection order making it possible to limit the load,
to which a stabilizer element of the aircraft is subjected, to a maximum load,
and a means (14) for choosing one of the first and second deflection orders,
which is transmitted to said actuator (11) so as to move said control surface (2).
