N3249M
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 A CRACK WAS VISUALLY IDENTIFIED ON THE RIGHT HAND CROSSOVER BEAM. THIS CRACK IS LOCATED ON THE AFT FACE OF THE BEAM, COMMON TO THE TOP OUTBOARD BOLT HOLE FOR THE TURBOCHARGER SUPPORT BRACKET. THIS CRACK MEASURES APPROXIMATELY .875 INCHES LONG TRAVELING LONGITUDINALLY ACROSS THE FASTENER LOCATION. IT IS CONSISTENT WITH OTHER CRACKS VISUALLY IDENTIFIED IN THIS AREA. THIS BEAM WILL BE REMOVED AND REPLACED.
DURING SCHEDULED MAINTENANCE A SMALL AREA OF SURFACE CORROSION WAS VISUALLY IDENTIFIED ON THE RIGHT WING UPPER AFT WING FITTING. (OEM PN: 0822550-46). THIS CORROSION MEASURES APPROX. 1.25" LONG WITH A MAX DEPTH OF APPROX. .009" AND IS CONSISTENT WITH OTHER CORROSION FOUND ON THESE FITTINGS IN THE PAST. THIS FITTING WILL BE CHANGED USING NEW PARTS.
WHILE PERFORMING THE LIGHTED BORESCOPE PROCEDURE AS OUTLINED IN TEXTRON MEL-54-02 R2 TO SATISFY AD2017-10-19, A CRACK WAS IDENTIFIED ON THE OUTBOARD SIDE OF THE LEFT-HAND OUTBOARD FITTING. THIS CRACK MEASURES .130 AND IS CONSISTENT WITH OTHER FOUND USING THIS SAME METHOD. THIS FITTING WILL BE REPLACED WITH A FACTORY NEW PART.
PILOT REPORTED RIGHT ALTERNATOR INOPERATIVE. MAINTENANCE INSPECTED AND FOUND THE ALTERNATOR HUB NUT MISSING, FLY WHEEL BOLTS MISSING AND DAMAGE TO THE FLY WHEEL. THE ENGINE IS BEING REPLACED DUE TO METAL CONTAMINATION.
DURING MAINTENANCE A CRACK WAS DISCOVERED ON THE LEFT HAND CLOSEOUT RIB (P/N: 5122115-55) AT L.W.S. 106.79. THIS CRACK ORIGINATES FROM A HOLE IN THE FORWARD ROW OF FASTENERS COMMON TO THE AFT MAIN LANDING GEAR TRUNNION SUPPORT PLATE AND TRAVELS FORWARD AN APPROXIMATE LENGTH OF .992 INCHES. THE CRACK IS CONSISTENT WITH OTHERS VISUALLY IDENTIFIED IN THIS SAME AREA. THIS RIB WILL BE REPLACED.
DURING MAINTENANCE AREAS OF CORROSION WERE IDENTIFIED ON THE LEFT HAND LOWER AFT SPAR CAP (P/N: 5122041-23) BETWEEN L.W.S. 216.71 AND 229.71. THE DEEPEST AREA OF CORROSION IS AT L.W.S. 218.71 ON THE LOWER HORIZONTAL LEG AND MEASURES APPROXIMATELY .028 INCHES DEEP. 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.
PILOT REPORTED AFTER 45 MINUTES OF FLIGHT THE HEATER BEGAN PRODUCING A STRONG EXHAUST SMELL. MAINTENANCE INSPECTED AND FOUND THE HEATER IGNITION UNIT BURNT. THE IGNITION UNIT WAS REPLACED WITH NO FURTHER DEFECTS NOTED.
PILOT REPORTED RIGHT ENGINE RUNNING ROUGH IN FLIGHT WITH ONE INCH MAP FLUCTUATION INTERMITTENT. MAINTENANCE INSPECTED AND FOUND THE EXHAUST VALVE DISCOLORED AND BROKEN. THE CYLINDER WAS REPLACED WITH NO FURTHER DEFECTS NOTED.
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 FUEL SMELL IN CABIN WITH HEATER RUNNING. INSPECTED & FOUND HEATER FUEL SCREEN BOWL IN RT WING HOSE & LEAKING. RE-TIGHTENED SCREEN BOWL IAW MM CH 21-40-00. OPERATIONS & LEAK CHECKED GOOD AT THIS TIME.
WHEN EXTENDING FLAPS 15 DEGREES, ACFT ROLLS RT UNCOMMANDED. REST OF FLAP DEPLOYMENT AFTER TRIM INITIATED FEELS NORMAL. INSPECTED & FOUND THE RT INBD & OTBD FLAP RODS BENT. R & R RIT INBD & OTBD FLAP PUSH & PULL RODS & RE-RIGGED FLAP CABLES.
DURING REPLACEMENT OF THE NR 2 CYLINDER, THE CONNECTING ROD BUSHING, PN 530658, HAD MOVED FROM THE CONNECTING ROD BORE IN A REARWARD DIRECTION & EXHIBITED MISSING MATERIAL FROM CONTACT WITH THE PISTON PIN BORE BOSS. THE ENG WAS COMPLETELY DISASSEMBLED FOR FURTHER EXAMINATION. INSPECTION REVEALED THAT NR 1, 2, 3 & 4 CONNECTING ROD BUSHINGS WERE DISPLACED FROM THEIR NORMAL POSITION. THE BUSHINGS WERE REMOVED FROM EACH OF THE SIX CONNECTING RODS. THE CONNECTING ROD, PN 655911, BUSHING BORES WERE MEASURED & NR 1, 2, 3 & 4 CONNECTING ROD BUSHING BORES MEASURED OVERSIZE BEYOND PUBLISHED LIMITATIONS. THESE CONNECTING RODS HAD BEEN OVERHAULED BY AN OUTSIDE REPAIR STATION IN DECEMBER 2013 WHEN THE ENG LAST OVERHAULED. THE NR 5 & 6 CONNECTING ROD BUSHING BORES MEASURED WITHIN PRESCRIBED LIMITATIONS.
WHILE TAXIING, THE PILOT ATTEMPTED TO EXECUTE A RT TURN. THE RT BRAKE PEDAL WENT SOFT & THE ACFT STOPPED TURNING & TAXIED STRAIGHT FWD. THE PILOT CLOSED THE THROTTLE & STOPPED, BUT THE ACFTS NOSE & LT TIRE WENT INTO THE GRASS. THE ACFT COULD NOT BE MOVED WITH DIFFERENTIAL POWER SO THE PASSENGERS WERE OFF LOADED & TRANSPORTED BACK TO THE TERMINAL. MX INSPECTED ALL COMPONENTS & FOUND THE RT CYLINDER FLUID LEVEL LOW. THE RT CYLINDER WAS SERVICED IAW MM CHAPTER 12-10-05. THE ACFT WAS FUNCTIONALLY TESTED & NO DEFECTS WERE NOTED.
AUTOPILOT COMPUTER CIRCUIT BREAKER TRIPPED WITH A HOT ELECTRICAL ODOR IN CABIN. INSPECTED & FOUND ODOR FROM ALTITUDE SENSOR. DISCONNECTED AUTOPILOT SYS.
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.
DURING SCHEDULED MX, DAMAGE WAS DISCOVERED ON THE AFT CARRY THROUGH SPAR STRUCTURE. DAMAGE INCLUDES FORWARD UPPER SPAR WEB FLANGE CRACKS EXTENDING FROM FASTENER LOCATIONS TO EDGE OF WEB FLANGE AND ALSO IN THE FLANGE RADIUS. UPON DISCOVERY OF DAMAGE, ACFT WAS SUBMITTED TO MRO FOR REPAIRS. MRO SUBMITTED AND RECEIVED EO. REPAIRS ARE IN PROCESS.
PILOT REPORTED THAT DURING NIGHT TRAINING FLIGHT, THE ODOR OF SMOKE WAS NOTED IN THE CABIN. NOTED SMOKE COMING FROM OVERHEAD LIGHTS. PILOT PERFORMED "CABIN ELECTRICAL FIRE OR SMOKE" MEMORY ITEMS, CONTACTED ATC, AND LANDED WITHOUT INCIDENT. UPON INSPECTION, THE OVERHEAD LIGHT DIMMER ASSEMBLY WAS R & R IAW MM.
CREW WAS ATTEPMTING TO VERIFY FUCNTIONALITY OF WEATHER RADAR. WHEN ADJUSTING TILT AND GAIN, SMOKE IMMEDIATELY BEGAN POURING INTO THE COCKPIT FROM BENEATH THE WEATHER RADAR INDICATOR. AN EMERGENCY WAS DECLARED, AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED RADAR INDICATOR AND FOUND THAT IT SMELLED BURNT.
ON APPROACH, GEAR SELECTED DOWN, NO LT MAIN DOWN LOCK INDICATION. LAMP TESTED OK, PROCEDED WITH EMERGENGY EXTENSION CHECK LIST, STILL NO INDICATION. DECLARED EMERGENCY, LANDED WITHOUT INCIDENT. MX REPAIR LT MAIN DOWN LOCK INDICATOR GROUND WIRE. GEAR SWING CHECKS GOOD, RELEASED ACFT BACK TO SERVICE.
FLIGHT CREW NOTICED HYD LEAKAGE INBD WING. INSPECTION NOTED PIN HOLE IN LINE AT HYD FLOW SWITCH AREA. REPLACED LINE AND SERVICED SYSTEM. DETERIORATION OF LINE WAS CAUSE FOR LEAKAGE. SUBMITTER RECOMMENDS PRESSURE TESTS CONTINUE, BUT PREVENTIVE MAINT SHOULD BE CONSIDERED (16 YEAR OLD PART.)
AFTER COMPLETION OF FLIGHT AT THE GATE, FLIGHT CREW NOTICED LT MAIN TIRE FLAT. UPON TEAR-DOWN INSPECTION, NOTED WIRE FROM SIDE WALL DAMAGED THE TUBE. TOTAL TIME ON TIRE, 196 HOURS. MCCRARY 6.50X10, 8-PLY RECAP.
ENGINE ROUGNESS NOTED. INSPECTION REVEALED RIGHT MAGNETO DISTRIBUTOR GEAR MISSING SOME OF ITS TEETH (NOTED 259.6 HRS SINCE ITS LAST INSPECTION). CAUSE UNKNOWN.
BAGGAGE DOOR WAS OPERATED AND FLIGHT CREW NOTICED BROKEN HINGE. HINGE IS WHITE METAL AND SUSPECTED TO BE OLD STYLE SLIDE LOCKS THAT CAUSED FRACTURE. CURRENTLY, S.K. KIT OF HYD ACTUATOR INSTALLED. SUBMITTER SUGGESTS WHEN LOADING, MAKE SURE BAGGAGE DOES NOT STRESS DOOR.
FLIGHT CREW NOTICED ROUGHNESS IN LEFT ENGINE. INSPECTED MAGS, COMPRESSION TESTED CYLINDERS, CHECKED SPARK PLUGS. ENGINE WAS GROUND RUN. FLIGHT OK'D. NOTED NO PROBLEMS. RETURNED TO SERVICE. NOTED: MINUS 21 DEGREES FAHRENHEIT TEMPERATURE.
ENGINE HAD SLIGHT ROUGHNESS AND TIMING JUMP TO THE TIME OF FAILURE. FOUND DISTRIBUTOR GEAR TEETH MISSING. RECOMMEND SHIMS BE CHECKED FOR GEAR FREEDOM AND UNIT BE REPLACED AT ONE-HALF OF SPECIFIC T.B.O. OF MAGNETO.