Clarification
OK guys, I confused the canopy repairs with structural disbonds originally discussed on this thread. Sorry about that.
I also need to state that my experience (and hence my comments) relate to generic repair of structures, not to any specific aircraft type. I am not implying any ongoing problems with any aircraft type.
What I am saying is that any adhesive bonded structure which relies on peel plies (no, not the canopy) and uses removal of the peel ply as the only surface preparation is highly susceptible to disbonding.
I am also saying that any attempt to repair anything by resin injection is futile.
Scomp, these reinforcements, are they in a plane parallel to the canopy? In other words is there any of the glass applied that bridges the open end of the crack? Perhaps you could send me a PM with a photo.