May someone please suggest EHA design procedures for AFS?
This 1986 USAF experiment might help.


  The purpose of this test was to demonstrate in flight for the first time the
  feasibility of powering a primary flight control surface with an
  electromechanical actuator (EMA) in place of the standard hydromechanical
  actuation system. An advanced development model model EMA drove the left aileron
  on a specially modified C-141A aircraft and was to duplicate the functions of the
  standard hydromechanical unit. Lockheed-Georgia Co. (GeLac) was the prime
  contractor with Sundstrand Corp. as the subcontractor.
  
  [...]
  
  The C-141 aileron is statically and dynamically stable with
  the critical flutter parameters being tip weight and actuator stiffness. If
  either parameter were not present, the damping would still be sufficient within
  the aircraft normal operating envelope. Laboratory studies had shown that the
  stiffness or spring rate of the EMA was identical to the hydraulic unit. All
  else remaining unchanged, the structural damping of the modified aircraft was
  expected to be the same as that of the baseline aircraft. The baseline aircraft
  has a flutter margin more than 20% above the normal operating limitations of the
  C-141A, and well above the military specification (MILSPEC) requirements.