Aircraft Report for n818an



Registration History for n818an









N-Number Make Model Serial Location Description Time
N818AN CESSNA 402C 402C0501 SALT LAKE CITY, UT Aircraft registered to BANK OF UTAH TRUSTEE, airworthiness date 1981-06-25, expiration date 2024-08-31, serial number 402C0501. 2022-07-20
N818AN CESSNA 402C 402C0501 SALT LAKE CITY, UT Aircraft registered to BANK OF UTAH TRUSTEE, airworthiness date 1981-06-25, expiration date 2024-08-31, serial number 402C0501. 2021-08-25
N818AN CESSNA 402C 402C0501 HYANNIS, MA Aircraft registered to HYANNIS AIR SERVICE INC, airworthiness date 1981-06-25, expiration date 2022-10-31, serial number 402C0501. 2019-07-29
N818AN CESSNA 402C 402C0501 HYANNIS, MA Aircraft registered to HYANNIS AIR SERVICE INC, airworthiness date 1981-06-25, expiration date 2019-10-31, serial number 402C0501. 2016-05-14
N818AN CESSNA 402C 402C0501 HYANNIS, MA Aircraft registered to HYANNIS AIR SERVICE INC, airworthiness date 1981-06-25, expiration date 2019-10-31, serial number 402C0501. 2016-05-14
N818AN CESSNA 402C 402C0501 HYANNIS, MA Aircraft registered to HYANNIS AIR SERVICE INC, airworthiness date 1981-06-25, expiration date 2016-10-31, serial number 402C0501. 2013-09-09
N818AN CESSNA 402C 402C0501 HYANNIS, MA Aircraft registered to HYANNIS AIR SERVICE INC, airworthiness date 1981-06-25, expiration date 2013-10-31, serial number 402C0501. 2010-11-19
N818AN CESSNA 402C 402C0324 LAS VEGAS, NV Aircraft registered to ABBEYMERE INC, serial number 402C0324. 1993-04-12

Accident History for n818an





N-Number Make Model Location Description Time
N818AN CESSNA 402C NANTUCKET, MA AFTER A NORMAL TAKE OFF RUNWAY 15 AT ACK CLIMBING THROUGH 600 FEET THE PILOT HEARD A SLIGHT POP POP SOUND. THE PILO 2014-09-24
N818AN CESSNA 402C NANTUCKET, MA (-23) ON 2/12/2009 THE NEW ENGLAND REGIONAL COMMUNICATIONS CENTER ADVISED AT APPROXIMATELY 1334 HYIA - CAPE AIR FLIGHT 58, N818AN, LANDED GEAR UP IN NANTUCKET, MA (ACK). THERE WAS 1 PILOT AND 5 PASSENGERS ONBOARD AND THERE WERE NO INJURIES REPORTED. THE PILOT CONTACTED THE ACK TOWER TO ADVISE OF A GEAR EMERGENCY. THE PILOT REPORTED AN UNSAFE NOSE GEAR LIGHT. THE PILOT FOLLOWED THE EMERGENCY CHECKLIST, BLEW THE GEAR DOWN BUT STILL HAD AN UNSAFE NOSE GEAR INDICATION. THE PILOT FLEW BY THE TOWER FOR CONFIRMATION OF THE NOSE GEAR POSITION BUT WAS ADVISED BY THE TOWER THAT THE GEAR WAS NOT DOWN AND WAS STILL RETRACTED. THE AIRCRAFT LANDED ON RUNWAY 24 WITH THE NOSE GEAR RETRACTED. THE AIRPORT SUPERVISOR ^PRIVACY DATA OMITTED^ ADVISED ME THAT ONCE THE PILOT WAS OVER THE RUNWAY HE SHUT BOTH ENGINES DOWN JUST PRIOR TO TOUCHDOWN TO MINIMIZE DAMAGE. DAMAGE WAS LIMITED TO BOTH PROPELLERS, GEAR DOOR AND NOSE FUSELAGE SKIN DAMAGE. THE DAMAGE WAS MINOR IN NATURE AND OCCURRED AS A RESULT OF THE RIGHT GEAR DOOR BRACKET EARS BREAKING OFF AT THE ACTUATOR ROD END. THE RIGHT GEAR DOOR CLOSED ON AIRCRAFT ROTATION. AS THE GEAR WAS RETRACTED IT CAUSED THE GEAR TO BE PINNED IN THE WHEEL WELL. 2009-02-12
N818AN CESSNA 402C NANTUCKET, MA (-23) ACCORDING TO THE PILOT'S STATEMENT, THE AIRCRAFT WAS MAKING A VISUAL APPROACH TO RNWY 24 AT NANTUCKET AIRPORT (ACK). AT 50 FT AGL, THE PILOT HEARD A LOUD BANG AND THE AIRCRAFT ROLLED TO THE RIGHT. THE PILOT PERFORMED A GO-AROUND BY ADDING POWER AND RETRACTING THE FLAPS. THE PILOT CLIMBED TO 1500 FT AGL AND MADE A NO FLAP APPROACH TO RNWY 24. UPON LANDING THE PILOT SAID HE FOUND THE RIGHT FLAP ASSEMBLY BROKEN AND WAS MOVEABLE BY HAND. 2007-02-04
N818AN CESSNA 402CESSNA LAS VEGAS, NV CARGO DOOR OPEN ON CLIMBOUT. BEGAN NOSE HIGH RIGHT TURN TO RETURN. LOST RIGHT ENGINE. BELOW VMC. ROLLED. DIVED IN. 1993-07-12

Service Difficulty Reports for n818an
































N-Number Make Model Serial Description Time
N818AN CESSNA 402C During INSP/MAINT - 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. 2020-11-03
N818AN CESSNA 402C During INSP/MAINT - 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 FACEOF 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. 2020-06-18
N818AN CESSNA 402C During CRUISE - 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. 2020-01-10
N818AN CESSNA 402C During INSP/MAINT - WHILE PERFORMING SPECIAL INSPECTION 402-22 PER INSPECTION PROGRAM MANUAL, AND MAINTENANCE MANUAL 5-20-01, CORROSION WASVISUALLY 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 INCHESDEEP. THIS FITTING WILL BE REMOVED AND REPLACED USING NEW PARTS. 2019-11-21
N818AN CESSNA 402C During INSP/MAINT - 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. 2019-10-24
N818AN CESSNA 402C During INSP/MAINT - 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 WASFOUND ON THE OUTBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. IT MEASURED .093 IN LENGTH. 2017-11-30
N818AN CESSNA 402C During CRUISE - PILOT REPORTED LEFT ENGINE RAN ROUGH DURING CLIMB AND THEN LATER ON GROUND AT IDLE. UPON INSPECTION, THE CONNECTING RODON THE NR 5 CYLINDER WAS FOUND TO BE BENT. THE ENGINE WAS REPLACED. 2017-09-15
N818AN CESSNA 402C During INSP/MAINT - CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE. 2016-10-25
N818AN CESSNA 402C During INSP/MAINT - CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE. 2016-09-15
N818AN CESSNA 402C During INSP/MAINT - CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE. 2016-08-04
N818AN CESSNA 402C During INSP/MAINT - CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE. 2016-08-04
N818AN CESSNA 402C During INSP/MAINT - CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE. 2016-08-04
N818AN CESSNA 402C During INSP/MAINT - CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE. 2016-08-04
N818AN CESSNA 402C During DESCENT - 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. 2015-05-06
N818AN CESSNA 402C During CRUISE - PILOT REPORTED BURNING SMELL FROM HEATER IN FLIGHT. INSPECTED THE HEATER IAW MM 21, RAN ENG & HEATER, ALL OPERATIONS CHECKED GOOD. NO SMELL NOTED. 2015-02-12
N818AN CESSNA 402C During CLIMB - 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. 2014-11-12
N818AN CESSNA 402C During INSP/MAINT - 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. 2014-06-18
N818AN CESSNA 402C During INSP/MAINT - 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. 2014-06-17
N818AN CESSNA 402C During INSP/MAINT - 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. 2012-12-27
N818AN CESSNA 402C During CRUISE - PILOT REPORTED THAT DURING CRUISE FLIGHT, SMOKE WAS SEEN COMING FROM BELOW THE YOKE. ON LANDING, MX INSPECTED THE ACFTAND REPLACED RING TERMINALS, WIRING, AND HARDWARE AT CABIN FAN SWITCH. 2012-12-14
N818AN CESSNA 402C During INSP/MAINT - 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. 2012-09-19
N818AN CESSNA 402C During INSP/MAINT - DURING A SCHEDULED MX, CORROSION WAS NOTED ON THE LT LOWER FORWARD FUSELAGE FITTING. R & R FITTING WITH NEW PART. 2012-09-19
N818AN CESSNA 402C During INSP/MAINT - 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. 2012-06-01
N818AN CESSNA 402C During CRUISE - 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 ANDREPLACED INVERTER. AIRCRAFT RELEASED BACK TO SERVICE. 2011-04-15
N818AN CESSNA 402C During CRUISE - 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. 2010-11-29
N818AN CESSNA 402C During INSP/MAINT - 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. 2009-11-16
N818AN CESSNA 402C During CLIMB - 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 PERFORMEDFULL POWER RUN UP. OPS AND LEAK CHECK GOOD AFTER RUN UP AIRCRAFT RETURNED TO SERVICE. 2008-12-05
N818AN CESSNA 402C During APPROACH - 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 THEAPPROPRIATE 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. THESFP WAS PERFORMED IN VFR CONDITIONS USING HAND HELD COMM RADIOS. MAINTENANCE CURRENTLY STILL TROUBLESHOOTING THE DISCRE 2008-03-07
N818AN CESSNA 402C During UNKNOWN - CREW REPORTED AVIONICS MASTER SWITCH INOP. MX CHANGED CIRCUIT BREAKER SWITCH. 2006-08-01
N818AN CESSNA 402C During NOT REPORTED - 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. 2003-09-19
N818AN CESSNA 402C During CRUISE - 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. 1999-07-09

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