What was found
CRACK ON INSIDE ANGLE AT STOP FITTING 2, THE PAN AT STOP 14 CRACKED. REPAIRED IAW SRM 52-05 FIG. 51.
As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
CRACK ON INSIDE ANGLE AT STOP FITTING 2, THE PAN AT STOP 14 CRACKED. REPAIRED IAW SRM 52-05 FIG. 51.