The tail boom is stressed to take a lot more load than could be applied to a tail rotor at idle and below. There is absolutely no chance of doing damage to the bolts or any other structure.
There may be other reasons for not wanting to use tail rotor pitch to slow the rotors, but none would be caused by loads on the tail boom attachment bolts.
It's also impossible to get into dynamic rollover with the rotor blades unpowered and decelerating from idle RPM - you can't generate enough rolling moment or thrust to tilt the helicopter over.
You might have a problem with blade flapping, but not with dynamic rollover.
Same thing with ground resonance - first of all, you can't get ground resonance in a two bladed rotor (if that's what you're flying). And in any other multi-bladed head, with no power going to the rotor blades the rotor blades will find their own place in lead-lag. If one lead-lag damper was going bad, it would have gone bad when there was a large difference in drag between advancing and retreating side wouldn't it?
Raising the collective would increase the drag on all the blades at the same time, and if you were going to get ground resonance, the collective position wouldn't make any difference.
Where do these last two old wives tales come from???