As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
FOUND ONE INCH LONG CRACK IN AFT UPPER FUSELAGE SKIN AT BASE OF VERTICAL FIN. CRACK STARTS AT LEFT FORWARD STABILIZER SPAR EXTENSION CUTOUT AND EXTENDS UPWARD. SUSPECT LACK OF PROPER RADIUS IN CORNER OF CUTOUT CREATED A STRESS RISER WHICH CAUSED THE SKIN TO CRACK DURING NORMAL FLEXING OF AFT FUSELAGE.