What was found
CRACKING DAMAGE WAS DISCOVERED ON THE TAIL CONE UPPER FRAME 7 IN THE RADIUS ADJACENT TO THE SKIN FLANGE ON THE R/H SIDE. THE APPROXIMATE LENGTH OF THE CRACK WAS MEASURED AT 0.20”. THE CRACK WAS STOP DRILLED AND AN L-SHAPED REPAIR DOUBLER OF 0.050” ALUMINUM WAS FABRICATED AND INSTALLED, AND THE SPACE BETWEEN DOUBLER FLANGE AND UPPER FRAME 7 FLANGES WERE SHIMMED USING 2024-T3 TO ACCOMMODATE FOR THE EXISTING JOGGLE. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDURES IS PROVIDED IN AIR METHODS ENGINEERING AUTHORIZATION 23-5300-EA-5580 REV. – DATED 25 MAR 2026 AND IS SUBSTANTIATED BY FAA FORM 8110-3