N763EA

Part: FITTING — CRACKED (LT NACELLE) · airframe 36,721 hrs · 41,970 cycles

DURING NDT INSPECTION AS NOTED IN SID 57-10-16, A CRACK WAS DISCOVERED ON THE LEFT HAND INBOARD NACELLE FITTING. (P/N: 5292029-21) THIS CRACK MEASURES APPROXIMATELY .145 INCHES LONG ON THE INBOARD LOWER LEG OF THE FITTING, AND IS CONSISTENT WITH OTHER CRACKS FOUND USING THE LIGHTED BORESCOPE INSPECTION TECHNIQUE (TEXTRON MEL54-02R2) TO SATISFY REQUIREMENT OF AD2017-10-09. THIS FITTING WILL BE REPLACED USING NEW PARTS.

Part: FITTING — CORRODED (LT WING) · airframe 36,721 hrs · 41,970 cycles

DURING MAINTENANCE AN AREA OF CORROSION WAS VISUALLY IDENTIFIED ON THE LEFT HAND LOWER FUSELAGE ATTACH FITTING (P/N: 0811350-10) ON N763EA. THIS CORROSION MEASURES APPROXIMATELY .390 INCHES TALL, .429 WIDE, AND HAS A MAXIMUM DEPTH OF .056. IT IS LOCATED ON THE AFT FACE OF THE FITTING. THIS FITTING HAS BEEN REMOVED AND WILL BE REPLACED USING NEW PARTS.

Part: ATTACH FITTING — CRACKED (RT NACELLE) · airframe 36,611 hrs · 41,795 cycles

WHILE PERFORMING THE LIGHTED BOROSCOPE INSPECTION PROCEDURE AS OUTLINED IN TEXTRON MEL-54-02R2 TO SATISFY AD2017-10-19, A CRACK WAS IDENTIFIED ON THE OUTBOARD RADIUS OF THE RIGHT HAND INBOARD NACELLE ATTACH FITTING (P/N: 5292029-22). THIS CRACK MEASURES APPROXIMATELY 1.760 INCHES LONG AND ITS LOCATION IS CONSISTENT WITH OTHERS FOUND USING THIS SAME METHOD. THIS FITTING HAS BEEN REMOVED AND REPLACED USING NEW SUPERSEDED P/N:5292029-30.

Part: SPAR CAP — CORRODED (LT WING) · airframe 35,603 hrs · 40,231 cycles

DURING MAINTENANCE CORROSION WAS DISCOVERED ON THE OUTBOARD LEFT LOWER SPAR CAP (P/N: 5122041-23) THIS CORROSION IS LOCATED ON THE BOTTOM OF THE HORIZONTAL LEG BETWEEN LWS 119.29 AND 106.79. THE DEEPEST MEASUREMENT MEASURES APPROXIMATELY .050 INCHES DEEP AT APPROXIMATE LWS 113.04. THIS IS IN EXCESS OF THE MAXIMUM REMOVABLE LIMITS ALLOWED UNDER MEB95-11R1 SECTION 3. THIS CAP WILL BE REMOVED AND REPLACED USING NEW PARTS.

Part: INTAKE VALVE — DAMAGED (RT ENGINE) · airframe 35,413 hrs

PILOT REPORTED RIGHT ENGINE SHUDDERED, THEN STARTED RUNNING ROUGH IN FLIGHT. PRELIMINARY INSPECTION FOUND DAMAGE TO THE NR 1 INTAKE VALVE, DAMAGE TO THE NR 1 AND NR 5 PISTON HEADS AND THE NR 5 CYLINDER INTAKE LIFTER SLEEVE EXTRUDING FROM LIFTER TUBE IN CRANK CASE, CONTACTING THE CAM SHAFT. THE ENGINE IS BEING REMOVED FOR FURTHER INVESTIGATION.

Part: CYLINDER — DAMAGED (NR 6) · airframe 34,117 hrs · 38,189 cycles

AT CRUISE POWER SETTING, CREW REPORTED A ROUGH RUNNING RT ENGINE ALONG WITH A CONTINUOUS MODERATE VIBRATION THROUGHOUT RANGE OF POWER SETTINGS. THE FLIGHT DIVERTED AND LANDED SAFELY. INSPECTION REVEALED THE NR 6 CYLINDER AND PISTON ASSEMBLY WERE SEVERELY DAMAGED. THE INTAKE AND EXHAUST VALVES DID NOT EXHIBIT SIGNS OF DAMAGE. THE DAMAGE APPEARS TO HAVE BEEN CAUSED BY A PREIGNITION EVENT IN THE NR 6 CYLINDER. THIS ENGINE HAS BEEN REMOVED FROM SERVICE DUE TO METAL CONTAMINATION CAUSED BY THIS EVENT.

Part: SPAR — DAMAGED (FUSELAGE) · airframe 27,989 hrs

DURING A MX EVENT, DAMAGE WAS DISCOVERED ON THE AFT CARRY THROUGH SPAR STRUCTURE. DAMAGE INCLUDES FWD UPPER SPAR WEB FLANGE CRACKS AND MISSING MATERIAL AT SAME LOCATION. PREVIOUS EFFORTS IN REPAIRING THIS AREA HAVE RESULTED IN ADDITIONAL FASTENER LOCATIONS PENETRATING THE UPPER FLANGE. UPON DISCOVERY, ACFT WAS SUBMITTED TO MRO. MRO REQUESTED AND RECEIVED ENGINEERING PLANS. REPAIRS ARE IN PROCESS.

Part: DRAG BRACE — CRACKED (NLG) · airframe 26,618 hrs

AT SCHEDULED INSPECTION, NLG DRAG BRACE, OEM PN 5142002-5, WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE WITHIN ALLOWABLE LIMIT. THIS UNIT HAS BEEN REPAIRED IAW PROCEDURE OUTLINED IN MEB941-11R1 & RETURNED TO SERVICE.

Part: LINE — RUPTURED (HYDRAULIC SYS) · airframe 24,266 hrs

DURING INITIAL CLIMB OUT, HYD FLOW LIGHTS ILLUMINATED. LANDING GEAR CYCLED WITH NO EFFECT. EMERGENCY DECLARED, GEAR EXTENDED BY USE OF EMERGENCY EXTENSION SYS. MX REMOVED AND REPLACED HYD LINE IN RT STUB WING AREA. OPS CHECK AND LEAK CHECK PERFORMED. ACFT RELEASED BACK TO SERVICE.

Part: HYDRAULIC LINE — RUPTURED (ZONE 600) · airframe 24,266 hrs

DURING INITIAL CLIMB OUT, HYDRAULIC FLOW LIGHTS ILLUMINATED. LANDING GEAR CYCLED WITH NO EFFECT. EMERGENCY DECLARED GEAR EXTENDED BY USE OF EMERGENCY EXTENSION SYSTEM MAINTENANCE REMOVED AND REPLACED HYDRAULIC LINE IN RIGHT STUB WING AREA. OPERATIONAL CHECK AND LEAK CHECK PERFORMED. AIRCRAFT RELEASED BACK TO SERVICE.

Part: BOLT — UNSERVICEABLE (RT ENGINE) · airframe 23,986 hrs

CREW REPORTED RIGHT ALTERNATOR INOPERATIVE. MAINTENANCE REMOVED ALTERNATOR AND FOUND ALTERNATOR DRIVE GEAR ATTACH BOLTS SHEARED. MAINTENANCE REMOVED AND REPLACED RIGHT ENGINE.

Part: TURBOCHARGER — FAILED (ENGINE) · airframe 22,574 hrs

THE MANIFOLD PRESSURE DROPPED TO AMBIENT AND OIL PRESSURE DECREASED SHORTLY THERE AFTER. PILOT PERFORMED PRECAUTIONARY ENGINE SHUT DOWN. MAINTENANCE INSPECTED ENGINE AND FOUND BAD TURBOCHARGER AND REPLACED. MAINTENANCE PERFORMED PRECAUTIONARY OIL FILTER, AND PROPELLER GOVERNOR SCREEN INSPECTION, AND INSTALLED MEB-009 FOR POSSIBLE ICE BUILD UP IN OIL SCAVENGE LINES.

Part: MASTER SWITCH — INOPERATIVE (COCKPIT)

CREW REPORTED AVIONICS MASTER SWITCH INOP. MX CHANGED CIRCUIT BREAKER SWITCH.

Part: TORQUE TUBE — FAILED (RUDDER PEDAL)

ON TAKE OFF ROLL, RIGHT RUDDER PEDAL FAILED. MECHANIC FOUND RUDDER PEDAL TORQUE TUBE FAILED AT POST WELD. REMOVED AND REPLACED TORQUE TUBE AND RETURNED AIRCRAFT TO SERVICE.

Part: DRAG BRACE — CRACKED (NLG)

REGULAR SCHEDULED INSPECTION, FOUND NOSE GEAR DRAG BRACE CRACKED AT ACTUATOR ATTACH LUG. MECHANIC REMOVED AND REPLACED NOSE GEAR DRAG BRACE.(K)

Part: HOOK — FAILED (LT MLG UPLOCK)

UPLOCK HOOK FAILED. UNABLE TO DETERMINE THE OLD PART NUMBER IN CESSNA PARTS BOOK. INSTALLED NEW STEEL HOOK, P/N 5141312-2. SUBMITTER STATED THIS HOOK (STEEL) IS THE WAY TO GO. THE STOCK PART DELIVERED (THIN ALUMINUM) AND THE ONE SUPPLIED BY SERVICE KITS (THICK ALUMINUM), FAIL ALOT.