Servo-control reversibility and G limits
Found the following in the EC-120B RFM:
Maximum load factor is determined by the servo-control reversibility limit. This phenomenon is smooth and presents no danger. Maximum load factor is a combination of TAS / Hσ / Weight. This servocontrol reversibility limit may be reached in a turn or in a pull-up or when maneuvering near VNE. In this case reduce collective pitch and airspeed.
Anyone care to explain this phenomenon? Also, I haven't found any reference to G limits in any other RFM... Is it that helicopters are "unbreakable" by abrupt control inputs?