Normal tendency of helicopter with counter clockwise rotating main rotors (top view) with force trim off and leaving controls?
With a American made helicopter equipped with a CCW rotating rotor, the helicopter will, as it accelerates past 10-15 KIAS, begin to pitch nose up as well as roll to the right.  This is a direct result of Effective Translational Lift (ETL) as well as Transverse Flow Effect.  Airflow through the main rotor disk past these speeds begins to take a more horizontal flow through the rotor disk, increasing lift on the advancing side of the rotor disk resulting in this.  European made helicopters with a CW turning main rotor will have a tendency to still pitch up as ETL becomes effective but will roll left due to gyroscopic precession from a greater lift imbalance on the front of the rotor disk being applied to the right side of the disk.