One solution cooked up early on was to have the aircraft automatically boot in opposite rudder, but it worked too good!
The aircraft had no "engine failure" recognition system as such. The yaw SAS system comprised three yaw rate gyros, three lateral accelerometers, three computers and two servo channels (A & B hydraulic systems). The lateral accelerometers provided long term damping and provided corrective inputs to minimise sideslip. SAS authority was limited to approx 8° left and right. Rudder travel is 20° left and right when below Mach 0.5, and limited (by manual handle selection) to 10° L/R when above Mach 0.5.