TRANS-EXEC AIR SERVICE INC

DURING A 5000 LANDING GEAR INSPECTION, CORROSION WAS NOTED IN THE LEFT AND RIGHT MAIN LANDING GEAR TRUNNION BORES. REPAIRED IAW CS27764.

COMBINED HYDRAULIC SYSTEM FLUID LOSS DUE TO FITTING BECOMING LOOSE AT FLIGHT POWER SHUTOFF VALVE. SECURED FITTING, SERVICED AND TESTED SYSTEM, SUBSEQUENT OPERATION NORMAL.

CORROSION AT LT AND RT MLG TRUNNION RIB FITTING ATTACH LUGS, FORWARD AND AFT LOCATIONS, DISCOVERED DURING 5000 LANDING INSPECTION. REPAIR ACCOMPLISHED IAW WO CS451500 AND REPAIR DWGS SE45732903 AND SE05732105.

DURING APPROACH WHEN THROTTLES WERE RETARDED THE RIGHT ENGINE FLAMED OUT, ENGINE WAS SECURED AND UNEVENTFUL LANDING ACCOMPLISHED. UPON INVESTIGATION FOUND THE RIGHT ENGINE LOW PRESSURE COMPRESSOR/LOW PRESSURE TURBINE SECTION WOULD NOT ROTATE. HIGH PRESSURE COMPRESSOR/TURBINE SECTION WAS ABLE TO BE ROTATED. ACCOMPLISHED BORESCOPE INSPECTION, NO APPARENT INGESTION OR FAILURE IN COMPRESSOR SECTIONS WAS EVIDENT, NOR WERE THERE ANY ABNORMALITIES NOTED IN THE HP TURBINE SECTION. DEBRIS WAS NOTED IN THE TAILPIPE, APPEARED TO BE PIECES OF THE LP TURBINE SECTION, ALSO NOTED THE LP2 TURBINE HAD BLADES DAMAGED AND DISLODGED. CONDITION APPEARS TO BE CAUSED BY A FAILURE IN ONE OF THE LP TURBINES. FURTHER INFORMATION WILL NOT BE AVAILABLE UNTIL ENGINE IS DISASSEMBLED.

BAGGAGE DOOR FRAME LOWER CORNERS, FORE AND AFT, HAD OUTER SKIN PEELING BACK AND CRACKING FROM NORMAL WEAR. THIS AREA IS A SKIN BUILDUP AND IS SUSCEPTIBLE TO THE OUTER SKIN BEING SEPARATED AND/OR CRACKED FROM IN SERVICE LOADING AND UNLOADING. STRUCTURAL DER DESIGNED REPAIR TO CUT SECTION OUT OF OUTER SKIN AT FORE AND AFT CORNERS, INSERT STAINLESS STEEL DOUBLER BETWEEN SKINS, AND FINISH WITH FLUSH PATCH OF CUTOUT AREAS.

DURING SCHEDULED ACCOMPLISHMENT OF CMP CODES 573013 (LT AND RT WINGLET ATTACH HARDWARE- INSP) CORROSION WAS NOTED IN SEVERAL OF THE HOLE BORES IN THE CENTER OF THE HOLES WHERE THE BUSHINGS DO NOT CONTACT EACH OTHER. MFG IS AWARE OF THIS CONDITION AND THE HOLES WILL BE REWORKED IAW AN EXISTING PROCEDURE. THIS INSP HAS A 12 YEAR INTERVAL AND IT IS CRITICAL THAT THE ENDS OF THE HOLE BORES ARE SEALED CORRECTLY TO AVOID ANY MOISTURE INTRUSION.

SURFACE COATING BUBBLING AND SEPARATING FROM EXTERIOR SURFACE OF DIPLEXER COMPONENT OF AVIONICS ANTENNA PLATFORM. ANTENNA PLATFORM IS A PART OF THE STACOM SYSTEM. SYSTEM DESCRIBED IS BEING REPLACED. (K)

WHILE EN ROUTE FROM KVNY TO KTEB, EXPERIENCED A CRACK IN THE NR 2 WINDSHIELD, 30 MINUTES INTO FLIGHT. THE PILOT IN COMMAND RETURNED THE AIRCRAFT TO THE MAINTENANCE FACILITY IN KVNY. AFTER RETURNING, THE WINDOW WAS ASSESSED BY TRANS-EXEC AIR SERVICE, INC MX DEPT. THE AIRCRAFT NR 2 WINDSHIELD WAS REPLACED WITH A NEW UNIT, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)

FOLLOW-UP OF SDR RELATING TO PRESSURIZATION PROBLEM, DIFFICULTY TRACED TO TEMP CONTROL BOX LOCATED IN AFT EQUIPMENT AREA. CONTROLLER REPLACED. OPERATIONAL CHECKS GOOD, AIRCRAFT RETURNED TO SERVICE.