As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
UPON COMPLIANCE OF 2C INSPECTION TASK 5320-141/142-01I, THE FUSELAGE SKIN SUPPORT AT FRAME 21, BETWEEN STRINGERS 21L AND 21R, WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.