N402BF
Registered owner: SNELL MARION LEA, TX (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
Maintenance disclosures
LT MAIN LANDING COLLAPSED ON LANDING. IT APPEARS THAT BELLCRANK ASSEMBLY, PN 50410015 FAILED DURING EXTENSION CYCLE. (K)
WHILE ON FINAL APPROACH, THE PILOT REPORTED A LOSS OF MANIFOLD PRESSURE WITH THE RIGHT ENGINE. IT WAS FOUND THAT THERE WAS A HOLE APPROX 1.5 X 3.0 INCHES IN THE RIGHT ENGINE EXHAUST, MOST SPECIFICALLY FOCUSED AROUND THE NR 3 CYLINDER EXHAUST PIPE. THE EXHAUST STACK ASSEMBLY WAS REPLACED.
ASG/LIT - WHILE EN ROUTE AND ON APPROACH AT ABOUT 500 AGL, PILOT EXPERIENCED A FLAP SYSTEM FAILURE UPON DEPLOYMENT OF THE FLAPS, ONLY THE LT SIDE CAME DOWN. THIS CAUSED THE AIRPLANE TO ROLL VIOLENTLY. THE FLAPS WERE RETRACTED, CONTROL OF THE AIRCRAFT WAS REGAINED, AND LANDING WAS MADE WITHOUT EVENT. DETERMINED THE UPPER FLAP EXTEND CABLE ON THE RT SIDE HAD BROKEN APPROX 6 INCHES OUTBOARD OF THE ACTUATOR CHAIN ATTACH POINT. NO PREV EVIDENCEOF CHAFING. FLAP CABLE INSPECTED 132 HRS PRIOR AS A 200-HR INSP, NO EVIDENCE OF CHAFING, CABLE TENSION GOOD. POSSIBLE CAUSE UNKNOWN. (X)
DURING THE COURSE OF A 100-HOUR INSPECTION, THE MECHANIC NOTICED THE LEFT ENGINE, NR 1 CYLINDER, MOST FORWARD UPPER STUD HAD BROKEN OFF FLUSH WITH THE CYLINDER BASE/SKIRT. THE CYLINDER WAS REMOVED AND THE CASE WAS INSPECTED FOR CRACKS AND ANY SIGNS OF CHAFING. NONE WAS FOUND. IT IS SUSPECTED THAT TIME IN SERVICE IS THE MAIN CAUSE FOR BREAKAGE OF THE STUD. NO WAY TO DETERMINE THE TOTAL TIME OF THIS STUD OR THE CRANKCASE DUE TO THE REMOVAL OF THE DATA PLATE DURING THE OVERHAUL/CRANKCASE RECERTIFICATION PROCESS.
DURING 50-HOUR INSPECTION, MECH TURNED PROP AND NOTICED A 'HISSING' SOUND EMITTING FROM NR 4 CYLINDER ON LT ENGINE. UPON CLOSER INSP, THE HISS WAS DETERMINED TO BE COMING FROM THE CHT PROBE HOLE. SLIGHT SIGNS OF SOOT IN AREA. CYLINDER CHECKED WITH DIFFERENTIAL PRESS GAUGE, FOUND 30/80 HEAVY LEAKAGE THROUGH THE CHT PROBE HOLE. SUSPECT CAUSE: AFTER CYL REMOVED, APPLIED AIR PRESS TO OUTSIDE OF PROBE HOLE, DETERMINED PROBE HOLE BOTTOM LOCATED WHERE CYL HEAD ATTACHES TO BARREL, AND EITHER THE PROBE HOLE DRILLED TOO DEEP OR INSIDE OF HEAD GIVEN TOO MUCH CLEARANCE PRIOR TO ASSY.
DURING A 100 HOUR INSPECTION, MECHANIC NOTICED CRACK IN THE WING SKIN IN MOST AFT OTBD SECTION OF LT WING. MECHANIC ALSO OBSERVED 2 RIVETS SHEARED THAT ATTACH THE OTBD AILERON HINGE BRACKET ASSY (CESSNA P/N 5021002-12) WHICH ARE SAME RIVETS THAT ATTACH THE TIP TANK SUPPORT BRACKETS (CESSNA P/N'S 0822600-29 AND -30 TO THE WING. THE MOST OTBD WING RIB WAS ALSO CRACKED IN THE MOST AFT LOWER SECTION (CESSNA P/N 0822040-17). TIP TANK STINGER (MOST AFT POINT) HAS SOME SLIGHT DAMAGE AS THOUGH IT STRUCK A SOLID OBJECT. AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUTING FACTOR.
DURING A 100 HOUR INSPECTION, MECHANIC NOTICED CRACK IN THE WING SKIN IN MOST AFT OTBD SECTION OF LT WING. MECHANIC ALSO OBSERVED 2 RIVETS SHEARED THAT ATTACH THE OTBD AILERON HINGE BRACKET ASSY (CESSNA P/N 5021002-12) WHICH ARE SAME RIVETS THAT ATTACH THE TIP TANK SUPPORT BRACKETS (CESSNA P/N'S 0822600-29 AND -30 TO THE WING. THE MOST OTBD WING RIB WAS ALSO CRACKED IN THE MOST AFT LOWER SECTION (CESSNA P/N 0822040-17). TIP TANK STINGER (MOST AFT POINT) HAS SOME SLIGHT DAMAGE AS THOUGH IT STRUCK A SOLID OBJECT. AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUTING FACTOR.
DURING A 100 HOUR INSPECTION, MECHANIC NOTICED CRACK IN THE WING SKIN IN MOST AFT OTBD SECTION OF LT WING. MECHANIC ALSO OBSERVED 2 RIVETS SHEARED THAT ATTACH THE OTBD AILERON HINGE BRACKET ASSY (CESSNA P/N 5021002-12) WHICH ARE SAME RIVETS THAT ATTACH THE TIP TANK SUPPORT BRACKETS (CESSNA P/N'S 0822600-29 AND -30 TO THE WING. THE MOST OTBD WING RIB WAS ALSO CRACKED IN THE MOST AFT LOWER SECTION (CESSNA P/N 0822040-17). TIP TANK STINGER (MOST AFT POINT) HAS SOME SLIGHT DAMAGE AS THOUGH IT STRUCK A SOLID OBJECT. AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUTING FACTOR.
DURING A 100 HOUR INSPECTION, MECHANIC NOTICED CRACK IN THE WING SKIN IN MOST AFT OTBD SECTION OF LT WING. MECHANIC ALSO OBSERVED 2 RIVETS SHEARED THAT ATTACH THE OTBD AILERON HINGE BRACKET ASSY (CESSNA P/N 5021002-12) WHICH ARE SAME RIVETS THAT ATTACH THE TIP TANK SUPPORT BRACKETS (CESSNA P/N'S 0822600-29 AND -30 TO THE WING. THE MOST OTBD WING RIB WAS ALSO CRACKED IN THE MOST AFT LOWER SECTION (CESSNA P/N 0822040-17). TIP TANK STINGER (MOST AFT POINT) HAS SOME SLIGHT DAMAGE AS THOUGH IT STRUCK A SOLID OBJECT. AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUTING FACTOR.
DURING A 100 HOUR INSPECTION, MECHANIC NOTICED CRACK IN THE WING SKIN IN MOST AFT OTBD SECTION OF LT WING. MECHANIC ALSO OBSERVED 2 RIVETS SHEARED THAT ATTACH THE OTBD AILERON HINGE BRACKET ASSY (CESSNA P/N 5021002-12) WHICH ARE SAME RIVETS THAT ATTACH THE TIP TANK SUPPORT BRACKETS (CESSNA P/N'S 0822600-29 AND -30 TO THE WING. THE MOST OTBD WING RIB WAS ALSO CRACKED IN THE MOST AFT LOWER SECTION (CESSNA P/N 0822040-17). TIP TANK STINGER (MOST AFT POINT) HAS SOME SLIGHT DAMAGE AS THOUGH IT STRUCK A SOLID OBJECT. AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUTING FACTOR.