Chop jock. WEIGHT is a function of the earths gravity acting on mass. So if you increase the MASS of your helicopter the earth will pull harder. The components of the helicopter are certified SAFE provided the helicopter is operated within the limitations in the flight manual. MAXIMUM TAKE-OFF MASS is always a limiting factor to prevent the earths gravity pulling so had things might break.
ROC ect is just performance. Some days the performance may be insufficient to even take-off at the maximum mass. Some days there may be enough performance to take off way over the maximum mass.
TQ and TOT provide no indication of the helicopters mass. These parameters are solely a result of LIFT or ROTOR THRUST to be more precise as DRAG increases proportional to LIFT and Tq must be increased to prevent the Nr decaying. TOT, N1, N2 increases as the engine responds to the TQ demand.
Finally, MAXIMUM take-off mass is affected by G forces. In fixed wing G force limits are sometimes specified. In Helicopters AOB IAS limits can suffice.
Needless to say, MTOM limitations should be considered abosolute. You statements on this thread are stone cold heracy to professional pilots and the venerable generation of SAS, Crab etc. In short, you understanding of basic physics and flight dynamics are seriously flawed.