Just thinking out loud here. I have no hands on experience with CFRP construction or structural repair.
CFRP consist of two key components, the carbon fiber and the epoxy matrix that ties it together. The carbon fiber seems unlikely to have been significantly damaged by the level of apparent heat that was developed in this fire. Primarily, it is the epoxy matrix that has been degraded by thermal effects.
Although epoxies are essentially insoluble, it might be possible to remove thermally degraded matrix without significantly disturbing the carbon fibers.
A laser method of CFRP surface preparation is discussed
here.
There may be variations of the water jet technique that will work assuming the proper working fluid.
If the end points of the carbon fibers are still anchored by adjacent structure that has not been thermally degraded, then vacuum assisted resin transfer could then be used to restore the damaged area to nearly new condition. Additional Carbon fiber cloth could be overlaid as needed to restore full strength.
I suspect the professionals in the subject repair will say, 'Why go to all that bother when a stepped ply repair will more easily and reliably restore the same strength.' In any case, although the structural repair may be a bit tedious, it seems to be eminently practicable.
The driver as to whether the aircraft is written off will be the cost to return the interior of the aircraft to serviceability, not the difficulty of structural repair.
Has anyone here actually seen the condition of the interior?