As the rotor RPM will be maintained by the governor, the total rotor thrust will stay the same. However, transiently while the aircraft is yawing to the right, the advancing blade will experience a slight increase in lift (rotational speed plus speed of rotation of the fuselage) and the retreating blade a slight decrease. This would cause the disc to flap back a little more than in the steady state which would cause a slight (but, I suspect, very slight) pitch up. Vaguely similar to the spot turn situation where a spot turn to the right causes a slight climb and to the left a descent (all valid of course only for proper helicopters where the rotor rotates clockwise!).