N818AN

Part: RIB — CRACKED (RT WING) · airframe 38,121 hrs · 37,915 cycles

DURING MAINTENANCE TWO CRACKS WERE DISCOVERED ON THE RIGHT HAND CLOSEOUT RIB AT RWS 106.79 (P/N: 5122115-56). THESE CRACKS ORIGINATE FROM TWO SEPARATE HOLES COMMON TO THE FORWARD ROW OF FASTENERS ATTACHING THE AFT MAIN LANDING GEAR TRUNNION SUPPORT PLATE. THE FIRST CRACK ORIGINATES FROM THE 4TH FASTENER UP FROM THE BOTTOM OF THIS FORWARD ROW, AND EXTENDS FORWARD APPROXIMATELY 1.308 INCHES. THE SECOND ORIGINATED FROM THE 6TH HOLE UP FROM THE BOTTOM ALSO EXTENDING FORWARD APPROXIMATELY 1.840 INCHES. THESE CRACKS ARE CONSISTENT WITH OTHERS FOUND ON THIS RIB USING A DETAILED VISUAL INSPECTION. THIS RIB WILL BE REPLACED USING NEW PARTS.

Part: BEAM — DAMAGED (ZONE 400) · airframe 37,568 hrs · 37,168 cycles

DURING MAINTENANCE, WORKING FASTENERS WERE IDENTIFIED ON THE RH OUTBOARD BEAM'S, AFT ENGINE MOUNT'S FORWARD MOUNTING BLOCK. THIS BLOCK P/N 5654130-202 WAS INSTALLED AS PART OF THE SK414-19B SERVICE KIT AND IS LOCATED ON THE OUTBOARD FACE OF THE BEAM. UPON REMOVAL OF THE BLOCK IT WAS DISCOVERED THAT THE MOUNTING HOLES FOR THIS BLOCK COMMON TO THE ENGINE BEAM HAD POOR EDGE DISTANCE TO THEIR SURROUNDING FASTENERS. THIS EDGE DISTANCE IS NOT VISIBLE WITH THE –202 BLOCK INSTALLED. FOR THIS REASON THE RH OB ENGINE BEAM ASSEMBLY P/N 5654109 WILL BE REPLACED USING NEW PARTS.

Part: ACTUATOR — EXCESS PLAY (ELEVATOR TAB) · airframe 37,173 hrs

PILOT REPORTED ELEVATOR FLUTTER FROM RIGHT SIDE, SUSPECT TRIM TAB. MAINTENANCE INSPECTED AND FOUND THE ELEVATOR TRIM ACTUATOR WITH PLAY. THE ACTUATOR WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: ATTACH FITTING — CORRODED (ZONE 500) · airframe 37,079 hrs · 363,323 cycles

WHILE PERFORMING SPECIAL INSPECTION 402-22 PER INSPECTION PROGRAM MANUAL, AND MAINTENANCE MANUAL 5-20-01, CORROSION WAS VISUALLY IDENTIFIED ON THE LEFT WING'S, FORWARD SPAR'S, LOWER, AFT, WING FITTING. THIS CORROSION IS ON THE LOWER HORIZONTAL FLANGE OF THE FITTING MEASURING APPROXIMATELY 3 INCHES LONG, AND .250 INCHES WIDE, WITH A MAX DEPTH OF .022 INCHES DEEP. THIS FITTING WILL BE REMOVED AND REPLACED USING NEW PARTS.

Part: BEAM — CRACKED (RT NACELLE) · airframe 37,057 hrs · 36,285 cycles

DURING MAINTENANCE TWO CRACKS WERE DISCOVERED ON THE INBOARD FACE OF THE RIGHT HAND INBOARD ENGINE BEAM IN THE AREA OF THE VERTICAL ATTACH CHANNELS FOR THE CROSSOVER BEAM. THESE CRACKS WERE DISCOVERED AFTER CHANGING THE CROSSOVER BEAM VERTICAL ATTACH BRACKET P/N: 5654107-15 AND THE ASSOCIATED 5654107-10 UPRIGHT, THEREFORE NOT VISIBLE UNTIL THE BRACKET WAS REMOVED. THE FORWARD MOST CRACK MEASURES APPROXIMATELY 1.531 INCHES, THE SECOND CRACK DIRECTLY AFT OF THAT MEASURES APPROXIMATELY .648 INCHES. THIS BEAM WILL BE REPLACED USING NEW PARTS.

Part: CONNECTING ROD — BENT (NR 5 CYLINDER) · airframe 35,047 hrs · 33,511 cycles

PILOT REPORTED LEFT ENGINE RAN ROUGH DURING CLIMB AND THEN LATER ON GROUND AT IDLE. UPON INSPECTION, THE CONNECTING ROD ON THE NR 5 CYLINDER WAS FOUND TO BE BENT. THE ENGINE WAS REPLACED.

Part: FITTING — CRACKED (RT NACELLE) · airframe 34,590 hrs · 32,922 cycles

DURING A ROUTINE INSPECTION, THREE CRACKS WERE FOUND IN THE RT OUTBOARD NACELLE FITTING. TWO CRACKS WERE FOUND ON THE INBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. THEY MEASURED .161 AND .088 IN LENGTH. THE THIRD CRACK WAS FOUND ON THE OUTBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. IT MEASURED .093 IN LENGTH.

Part: EXHAUST VALVE — DAMAGED (NR 2 CYLINDER) · airframe 34,394 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 6 CYLINDER) · airframe 34,339 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 34,176 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 3 CYLIDER) · airframe 34,176 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 1 CYLINDER) · airframe 34,176 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 2 CYLIDER) · airframe 34,176 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: DOOR — OPEN (CABIN) · airframe 32,736 hrs · 29,875 cycles

PILOT REPORTED, DOOR WARN, ILLUMINATED 8 MILES FROM DESTINATION. UPPER CABIN DOOR OPENED 4 MILES FROM DESTINATION DURING DESCENT. INSPECTED THE CABIN DOOR WITH NO DAMAGE OR DISCREPANCIES NOTED.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 32,407 hrs · 29,277 cycles

PILOT REPORTED BURNING SMELL FROM HEATER IN FLIGHT. INSPECTED THE HEATER IAW MM 21, RAN ENG & HEATER, ALL OPERATIONS CHECKED GOOD. NO SMELL NOTED.

Part: CONNECTING ROD — SEPARATED (ENGINE) · airframe 32,097 hrs · 28,788 cycles

LEFT ENG FAILED AFTER TAKEOFF. UPON INSPECTION, IT WAS NOTED THE NR 5 CYLINDER CONNECTING ROD SEPARATED FROM THE CRANKSHAFT, CAUSING PENETRATION THROUGH THE CASE, EJECTING BOTH MAGNETOS FROM THEIR MOUNTS & CAUSING EXTENSIVE DAMAGE TO THE CYLINDER, CASE & ENG COWLING. THE MAGNETOS REMAINED TETHERED TO THE ENG BY THE LEAD HARNESSES & DEBRIS WAS CONTAINED WITHIN THE ENG COWLING. WE DO NOT BELIEVE ANY COMPONENTS OR MATERIAL SEPARATED FROM THE ACFT. R & R ENG & COWLING. ENG HAS BEEN SENT OUT FOR TEAR DOWN ANALYSIS. FURTHER DETERMINATION TO BE REACHED UPON TEAR DOWN ANALYSIS.

Part: SPAR — DAMAGED · airframe 29,965 hrs

DURING A ROUTINE MX INSPECTION DAMAGE WAS NOTED AT THE RT LOWER STUB WING IN THE AREA OF THE RT JACK POINT. INITIAL DAMAGE WAS IDENTIFIED AS A WRINKLING OF THE SKIN. SKIN WAS DERIVETED TO INSPECT UNDERLYING STRUCTURE (AFT CARRY THROUGH SPAR ASSY 5211173-2 AT FS 186.15). ADDITIONAL DAMAGE WAS NOTED AT AFT CARRY THROUGH SPAR ASSY RT OTBD LOWER WEB FLANGES. THE EXTENT OF DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIED AND SUBSTANTIATED. REPORT NR AND ISSUE DATE PENDING.

Part: WIRE — SMOKE (FAN SWITCH) · airframe 29,924 hrs

PILOT REPORTED THAT DURING CRUISE FLIGHT, SMOKE WAS SEEN COMING FROM BELOW THE YOKE. ON LANDING, MX INSPECTED THE ACFT AND REPLACED RING TERMINALS, WIRING, AND HARDWARE AT CABIN FAN SWITCH.

Part: ATTACH FITTING — CORRODED (ZONE 100) · airframe 29,615 hrs

DURING A SCHEDULED MX, CORROSION WAS NOTED ON THE LT LOWER FORWARD FUSELAGE FITTING. R & R FITTING WITH NEW PART.

Part: SPAR — DAMAGED (CENTER SECTION) · airframe 29,615 hrs

DURING A REGULARLY SCHEDULED MX INSPECTION, AFT CARRY THROUGH SPAR (CENTER SECTION) UPPER CAP AND CORRESPONDING WEB FLANGES WERE FOUND TO HAVE MISDRILLED DAMAGE FROM PREVIOUS REPAIR ATTEMPTS. UPON ACFT ARRIVAL IN FACILITY, A REPAIR WAS DEVELOPED IAW REPAIR DEFINITION REPORT NUMBER AAS-SSR-2012-017.

Part: SPAR CAP — DAMAGED (FUSELAGE) · airframe 29,612 hrs

DURING A SCHEDULED MX EVENT, DAMAGE WAS FOUND ON THE AFT CARRY THRU SPAR ASSY. DAMAGE INCLUDES UPPER SPAR WEB FLANGE CRACKS AND MISSING MATERIAL, CRACK STOP DRILL DAMAGE TO UPPER SPAR CAP, AND IMPROPERLY DRILLED HOLES THAT PENETRATE THE SPAR CAP VERTICAL FLANGES AND BULK UPPER SECTION OF UPPER SPAR CAP. UPON FINDING DAMAGE, A WO WAS OPENED WITH MRO WHO IN TERM SUBMITTED AN ENGINEERING REQUEST. ENGINEERING HAS BEEN RECEIVED AND REPAIRS ARE IN PROCESS.

Part: DRAG BRACE — CRACKED (NLG) · airframe 28,506 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: CONTROLLER — FAILED (WINDSHIELD HEAT) · airframe 28,406 hrs

CREW REPORTED, IN CRUISE, IMC CONDITIONS, LIGHT TO MODERATE RIME ICE WITH OAT OF -8 DEGREES CELCIUS, WINDSHIELD HEAT FAILED. EMERGENCY DECLARED AND REQUESTED 2000 FT FROM ATC, CONTINUED DESCENT TO KBOS,ICE STARTED TO SHED FROM WINDSHIELD, LANDING WAS UNEVENTFUL. MAINTENANCE INSPECTED AIRCRAFT, FOUND HEATED WINDSHIELD STATIC INVERTER INOPERATIVE. REMOVED AND REPLACED INVERTER. AIRCRAFT RELEASED BACK TO SERVICE.

Part: DRAG BRACE — CRACKED (NLG) · airframe 28,273 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 — BROKEN (LT ENGINE) · airframe 28,078 hrs

CREW REPORTED, AFTER LEVELING AT 4000 FT, IN CRUISE CONFIGURATION, POWER WAS REDUCED TO 26" OF MANIFOLD PRESSURE. LT ENGINE WENT TO TO 26" OF MANIFOLD PRESSURE, BUT RT ENGINE REMAINED AT 29". CREW ELECTED TO DIVERT, WHERE AN EMERGENCY WAS DECLARED. LANDING WAS UNEVENTFUL. MX R & R BROKEN MANIFOLD PRESSURE INDICATOR LINE. ACFT RETURNED TO SERVICE.

Part: SPAR CAP — CRACKED (RT WING) · airframe 26,941 hrs

DURING SCHEDULED MX VISIT, MX FOUND POSSIBLE CRACK ON RT WING FWD SPAR, UPPER CAP. CRACK CONFIRMED BY EDDY CURRENT INSP. SPAR CAP REPLACEMENT IN PROGRESS.

Part: GARLOCK SEAL — LEAKING (ZONE 500) · airframe 25,981 hrs · 17,507 cycles

LEFT ENGINE LEAKING OIL IN FLIGHT CREW SHUT DOWN ENGINE. MAINTENANCE INSPECTED FOUND VACUUM PUMP'S GARLOC SEAL WAS LEAKING. MX REMOVED AND REPLACED GARLOC SEAL AND VACUUM PUMP ASSY. MX CLEAN OIL SEPARATOR FILTER AND LINES. MX PERFORMED FULL POWER RUN UP. OPS AND LEAK CHECK GOOD AFTER RUN UP AIRCRAFT RETURNED TO SERVICE.

Part: RADIO — MALFUNCTIONED · airframe 24,980 hrs

THIS IS A PRELIMINARY REPORT WITH A FINAL REPORT TO FOLLOW. ON APPROACH TO MVY, AIRCRAFT WAS UNABLE TO TRANSMIT ON EITHER COMM 1 OR COMM 2 RADIO WITH PILOTS PTT OR MICROPHONE, ACCOMPANIED BY A SMALL WISP OF SMOKE. THE PILOT PERFORMED THE APPROPRIATE BOX MEMORY ITEMS AND NO MORE SMOKE WAS SEEN. THE PILOT THEN RESTORED POWER FOR GEAR AND FLAPS WITH NO ADDITIONAL SMOKE DETECTED. PILOT CONTACTED TOWER USING CELL PHONE AND WAS ABLE TO LAND WITHOUT INCIDENT. MAINTENANCE WAS DISPATCHED TO MVY AND INSPECTED AIRCRAFT. AIRCRAFT WAS FLOWN ON A SPECIAL FLIGHT PERMIT TO MAINTENANCE BASE AT HYA. THE SFP WAS PERFORMED IN VFR CONDITIONS USING HAND HELD COMM RADIOS. MAINTENANCE CURRENTLY STILL TROUBLESHOOTING THE DISCREPANCY.

Part: CIRCUIT BREAKER — DEFECTIVE (COCKPIT)

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

Part: BOLT — MISSING (ELEV TRIM TAB)

SHORTLY AFTER ROTATION AND GEAR SELECT UP (APPROX 200MSL) CREW REPORTED SEVERE ELEVATOR VIBARATION. EMERGENCY WAS DECLARED, LANDING W/O FURTHER PROBLEMS. MECHANIC INSPECTED ENTIRE ELEVATOR TRIM CONTROL SYSTEMS AND HORIZONTAL STABILIZER. MECHANIC FOUND ELEVATOR TRIM TAB ACTUATOR PUSH PULL ROD TO TAB HORN BOLT MISSING. CREW CONFIRMED HARDWARE WAS PRESENT ON ALL CONTROL TABS DURING PREFLIGHT. MECHANIC REPLACED MISSING BOLT AND RETURNED AIRCRAFT TO SERVICE.

Part: ENGINE — FAILED (RIGHT)

IN CRUISE FLIGHT, RIGHT ENGINE HAD A CATASTROPHIC FAILURE. FOR UKNOWN REASONS, CONNECTING RODS, NR 1, NR 2, NR 4, FAILED. TCM HAS BEEN NOTIFIED AND WILL INSPECT ASAP. AN UNEVENTFUL LANDING WAS MADE.