As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
(CAN) WING SPAR CENTRE SECTION LOWER FORWARD CAP ANGLE VERTICAL FLANGE LEG WHERE RIVETED TO SPAR WEB HAS 25 PERCENT LOSS OF THICKNESS IN SEVERAL AREAS PROBABLY DUE TO INTERGRANULAR STRESS CORROSION. NO STRUCTURES REPAIR MANUAL EXISTS FOR THICKNESS LIMITS. ANOTHER WING WAS CHECKED AND IT HAS MORE SEVERE CORROSION THICKNESS LOSS. CONSIDER THIS A SAFETY CONCERN ON THIS AGING AIRCRAFT.