What was found
LOWER RIGHT WING ACCESS PANEL, ORIGINAL P/N LB57650007-1 REV- HAS A NACA AIR SCOOP AIR DUCT THAT CONNECTS TO FUEL SYSTEM VENT SYSTEM. THIS PANEL RECEIVED A MINOR ALTERATION , BY INSTALLING THE BENDIX KING KLR-10 AOA SYSTEM HEATED PITOT TUBE ASSY P/N 89000008-544001 TO THE NACA ACCESS PANEL. DURING THE CURRENT ANNUAL INSPECTION VISUAL INSPECTION, IT WAS NOTED THE PAINT ON THE PANEL WAS CRACKED AND THE UNDERLYING PANEL, WHICH IS MADE OF E-GLASS WAS INDICATING HEAT DAMAGE. THE ACCESS PANEL WAS REMOVED WITHOUT DISTURBING THE AOA HEATED PITOT PROBE CURRENT SETTING. THE PANEL THE SURFACE UNDER THE AOA HEATED PROBE AND MOUNTED DOUBLER PLATE INDICATED HEAT DAMAGE DIRECTLY UNDER THE DOUBLER PLATE. THE PAINT ON THE OUTSIDE SURFACE OF THE ACCESS PANEL HAS BLISTERED PAINT FROM THE HEAT TRANSFER OF THE AOA HEATED PITOT PROBE. AFTER REVIEWING THE BENDIX / KING KLR 10 INSTALLATION MANUAL, SECTIONS 2 & 3 INSTALLATION, PARAGRAPHS 2.4 & 3.1 FOR PROBE MOUNTING PLATE DOES NOT SPECIFY ANY RESTRICTIONS OF MOUNTING THE HEATED AOA PROBE ON COMPOSITE TYPE PANELS OR COMPOSITE STRUTURE. THIS DAMAGED CAUSED BY EXCESSIVE PROBE HEAT IS IN THE SAME PANEL AS THE FUEL VENT AIR SCOOP. ADDITIONALLY, THIS AIRCRAFT HAS AN OPERATIONAL TKS ICE PROTECTION SYSTEM THAT WEEPS TKS FLUID OUT THE LEADING EDGE PANELS TO PREVENT ICE BUILD UP. TKS FLUID LIQUID & VAPOR IS HIGHLY FLAMMABLE, WHICH IS A POTENTIAL HAZARD IF THIS TKS FLUID CONTACTS AN OPERATIONAL HEATED AOA PROBE. ADDITIONAL INSTALLATION INSTRUCTIONS ARE REFERED TO USE AC43-13-1B CHAPTER 4, AC43.13-2B, CHAPTER 1 & CHAPTER 3 FOR GUIDANCE. NO RESTRICTIONS FOR INSTALLATIONS ON COMPOSITE AIRCRAFT NOTED.