What is the relationship between the UH60 Blackhawk stabilator function lateral sideslip and pitch coupling? I'm having a hard time understanding the correlation between the wind gusts (where are they coming from, what are they affecting) and why, in a nose left situation,  the stabilator is driven down. 

I keep thinking it would make sense for it to go up (e.g. left pedal, more tail rotor torque, tail up, nose down. 


  sideslip to pitch coupling to reduce susceptibility to gusts.    When the helicopter is out of trim in a slip or skid, pitch excursions > are also induced as a result of the canted tail rotor and downwash on the stabilator.
  
  Lateral accelerometers sense this out of trim condition and signal the stabilator amplifiers to compensate for the pitch attitude change (called lateral to sideslip to pitch coupling). 
  
  Nose left (right slip) results in the trailing edge programming down. 
  Nose right produces the opposite stabilator reaction.  


If the stabilator drives down, this will make the nose go down further.

I know I'm missing something big here but can't put it together.
The sideslip to pitch coupling is a result of the canted tail rotor and the asymmetry of the main rotor downwash. The tail rotor thrust pushes the tail to the right and upward (pitch down). The main rotor downwash across the tail boom also generates a pitch up motion.  The 'static' position of the stabilator is set (stab range is 10 deg up to 45 deg down based on airspeed) to counter this pitch tendency.  

A right sideslip condition will result in a reduction of tail rotor vertical thrust resulting in a pitch up motion. The stabilator is programmed downward to counter the pitch up. Conversely a left sideslip will result in increased tail rotor vertical thrust and a pitch down motion.  In this case the stabilator will be programmed up to counter the downward pitch.