I believe the current plan is to retain MCP, only reducing to 70% TQ if a crack is detected. EC are adamant that the cracking is not caused by MCP torque, merely that once cracked, reducing the torque slows the propagation rate. However the story does seem to change quite often!
So why does this exist?
“
MAXIMUM CONTINUOUS TORQUE LIMITED TO 70% DURING LEVEL FLIGHTS AT IAS≥ 60 KTS ”
As for the view from TM that EC think corrosion is the issue. From G-REDW bulletin:-
The MGB was fitted to G-REDW on 18 March 2012, following overhaul at the helicopter manufacturer’s facility, where a new bevel gear vertical shaft (serial number M385) was fitted. This shaft failed in flight after approximately 167 flying hours.
Edited to add :- shows the mark of TM that in the spirt of open debate he has deleted all of his posts. No doubt makes the PR easier if the grunts are left in the dark?