N3292M
Registered owner: HYANNIS AIR SERVICE INC, MA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| HYANNIS AIR SERVICE INC. (HYIA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING MAINTENANCE AN AREA OF CORROSION WAS VISUALLY IDENTIFIED ON THE RH AFT LOWER OUTBOARD SPAR CAP, OEM P/N: 5122041-24. THIS CORROSION IS LOCATED ON THE FORWARD FACE OF THE VERTICAL LEG AT APPROXIMATE RWS 229.71. THIS CORROSION MEASURES APPROXIMATELY .020 AT ITS DEEPEST WHICH IS EXCESS OF ALLOWABLE LIMITS FOR REMOVAL PER CESSNA MEB 95-11R1 SECTION 3. THIS CAP WILL BE REMOVED AND REPLACED USING FACTORY NEW PARTS.
PILOT REPORTED A NOXIOUS SMELL DURING FLIGHT, AND NOTED THE HEATER DID NOT FEEL LIKE IT WAS PERFORMING. MAINTENANCE INSPECTED AND FOUND THE HEATER IGNITION UNIT TO BE BURNT OUT. REPLACED THE UNIT WITH NO FURTHER DEFECTS NOTED.
WHILE PERFORMING SPECIAL INSPECTION 402-22 IAW INSPECTION PROGRAM MANUAL, AND MM 5-20-01, CORROSION WAS VISUALLY IDENTIFIED ON THE LEFT WING'S, FORWARD SPAR'S, UPPER, AFT, WING FITTING (P/N 082255-45). THIS CORROSION IS ON THE UPPER HORIZONTAL FLANGE OF THE FITTING MEASURING APPROXIMATELY 1.360 INCHES LONG, AND .540 INCHES WIDE, WITH A MAX DEPTH OF .061 INCHES DEEP. THE FITTING WAS REMOVED AND REPLACED USING NEW PARTS.
PILOT REPORTED SMOKE IN COCKPIT AND THE AUTOPILOT SYSTEM CIRCUIT BREAKER POPPED. MX PERFORMED INITIAL INSPECTION AND FOUND THE AUTOPILOT INTERFACE CONNECTOR DAMAGED. THE SYSTEM WAS PLACED ON MEL, FURTHER DETAILS WILL BE PROVIDED IF ADDITIONAL FAILED PARTS ARE IDENTIFIED AS TROUBLESHOOTING AND FINAL REPAIR ARE ACCOMPLISHED.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
PILOT REPORTED ACFT ROLLS TO THE RT WHEN FLAPS ARE 15 DEGREES EXTENDED. INSPECTED & FOUND AN ASYMMETRICAL CONDITION WITH FLAPS. RIGGED FLAPS IAW MM CHAPTER 27.
DURING SCHEDULED INSPECTION THE LT NACELLE CROSSOVER BEAM ASSEMBLY WAS FOUND TO BE CRACKED AT OTBD LOWER U CHANNEL. REMOVAL OF CROSSOVER BEAM ASSEMBLY, DETAILED VISUAL INSPECTION OF SURROUNDING STRUCTURE FOR ADDITIONAL DEFECTS & INSTALLATION OF NEW BEAM ASSEMBLY. A SUPPLEMENT ILLUSTRATING DAMAGED AREA WILL BE SUBMITTED.
PILOT REPORTED FUEL ODOR IN CABIN. INSPECTED BOTH WINGS, FUEL TANKS, STRAINERS, FUEL LINES, NOSE COMPARTMENT & FUSELAGE. NO DEFECTS FOUND.
HEAVY FUEL SMELL IN CABIN. INSPECTED THE CABIN, BOTH WINGS & NOSE BAGGAGE COMPARTMENT FOR ANY EVIDENCE OF FUEL LEAK. NO DEFECTS NOTED.
DURING A REGULARLY SCHEDULED MX EVENT, DAMAGE WAS DISCOVERED ON THE REAR SPAR WEBS IN BOTH FORWARD AND AFT POSITIONS. DAMAGE WAS MAPPED AND SENT. REPAIRS WERE CARRIED OUT IAW REPAIR PLANS SUPPLIED AND SUBSTANTIATED.
AT SCHEDULED INSPECTION, NLG DRAG BRACE, 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 BEYOND LIMIT ALLOWABLE OF MEB91-11R1. THIS UNIT HAS BEEN SCRAPPED & A REPLACEMENT DRAG BRACE HAS BEEN INSTALLED IN ACFT.
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.
AIRCRAFT OVERNIGHTED IN TEMPS WELL BELOW ZERO, WITHOUT PROPER PREHEAT. AFTER TAKEOFF, BREATHER SYSTEM BLOCKED UP FROM FREEZING MOISTURE. AT APPROXIMATELY 1000 AGL, THE LEFT ENGINE OIL PRESSURE BEGAN TO RISE ABOVE THE GREEN ARC. AS CREW BEGAN TO SHUT DOWN ENGINE, THE OIL ACCESS PANEL OPENED, RESULTING IN SOME OIL LOSS AND A MISSING DIPSTICK. ENGINE SHUT DOWN NORMAL, RETURN UNEVENTFUL. MAINTENANCE CLEANED AIR/OIL SEPARATOR, AND ASSOCIATED LINES OF MOISTURE. SERVICED OIL, INSTALLED NEW OIL DIPSTICK, GROUND RUN OK, RELEASED FOR SERVICE.
RIGHT ENGINE'S INBOARD ENGINE BEAM IS CRACKED AT THE AFT UPPER WEB 0NE HALF OF AN INCH. REMOVAL AND REPLACEMENT OF THE ENGINE BEAM.
WEAR FROM BLENDING DUE TO SOFTER MATERIAL USED IN NEW STYLE CABLE.
DURING INSPECTION, FOUND RT NOSE STEERING CABLE BLENDED AND FRAYED AT PULLEY. NEW MFG CABLES (STANLESS STEEL) LAST ONLY FRACTION OF TIME AS OLD STYLE CABLES. HAS BECOME MUCH MORE COMMON OCCURRANCE. (K)
DURING PHASE INSPECTION, DIQSCOVERED L.E. LEFT MAGNETO HAD OIL INTERNALLY. DISSAMBLED MAGNETO IAW OM. FOUND OIL SLINGER WAS NOT INSTALLED.