As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
DURING ROUTINE INSP THE FITTING WAS FOUND CRACKED FROM AN OB ATTACHMENT SCREW BORE TO THE FLANGE EDGE. A NEW FITTING WAS INSTALLED. THIS IS A COMMON FAILURE FOR THIS PART. PART MAY HAVE BEEN SHIMMED INCORRECTLY OR BORE HOLE NOT ALIGNED PERFECTLY. SUGGEST A MORE DURABLE MATERIAL BE USED IN THIS PARTS MFG SUCH AS TITANIUM OR SS AS ALUMINUM ALLOY FAILS ROUTINELY UNDER THE NORMAL STRESS APPLIED TO THIS PART. (K)