N2714M
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
Maintenance disclosures
DURING APPROACH, THE CAPTAINS OVERHEAD LIGHT SWITCH WAS ACTUATED AND THE LIGHT DID NOT ILLUMINATED. THE CREW SUBSEQUENTLY ACTUATED THE COPILOT'S OVERHEAD LIGHT SWITCH WHICH ILLUMINATED AND WAS ACCOMPANIED BY AN ODOR OF SMOKE. THE CAPTAIN SHUTDOWN ALL ELECTRICAL SYSTEMS AND WAS ABLE TO SEE A SMALL FLAME IN THE OVERHEAD CONSOLE. AN EMERGENCY WAS DECLARED AND THE FLIGHT DIVERTED. THE FLAME SELF EXTINGUISHED PRIOR TO ARRIVAL. SUBSEQUENT INSPECTION REVEALED A RESISTOR WITHIN THE OVERHEAD DIMMER ASSEMBLY HAD FAILED AND CAUSED THE FLAME.
DURING A ROUTINE INSPECTION, TWO CRACKS WERE FOUND IN THE RT OUTBOARD NACELLE FITTING. THERE WAS ONE CRACK IN THE INBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. THE CRACK WAS .108 IN LENGTH. THE OTHER CRACK WAS DISCOVERED ON THE OUTBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. THE CRACK WAS .060 IN LENGTH.
DURING A ROUTINE INSPECTION, A CRACK WAS FOUND ON THE LT OUTBOARD NACELLE FITTING. THE CRACK WAS FOUND ON THE INBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. THE CRACK WAS MEASURED AT .191 IN LENGTH.
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.
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.
UPON DISASSEMBLY OF RT NACELLE LOWER FAIRING FOR INSPECTION OF RT WING SPAR STRAP IAW SID 57-10-16, UNINTENTIONAL DRILL DAMAGE AT WING SPAR STRAP WAS FOUND BY VISUAL INSPECTION. THE DAMAGE EXISTS JUST OTBD OF THE INBD NACELLE FITTING WITH FWD FACE OF RT WING SPAR STRAP 5292029-2. THE LOWER FWD WING SPAR CAP STRAP 5292029-2 WAS ORIGINALLY INSTALLED ON 04/08/2004 & HAS BEEN IN SERVICE FOR A TOTAL OF 12498.0 HOURS. THE DRILL DAMAGE LOCATED AT THIS DATE APPEARS TO HAVE BEEN INDUCED AT A PREVIOUS REPAIR OF NACELLE FIREWALL. THIS AREA OF WING SPAR STRAP IS NOT ACCESSIBLE FOR VISUAL INSPECTION WITHOUT DISASSEMBLY OF LOWER NACELLE FAIRING WHICH IS INSTALLED WITH MS RIVETS. DAMAGE MAPPING & REPORT REQUIRED BY MANUFACTURER HAS BEEN SUBMITTED. THIS DISCREPANCY WILL BE REPLACEMENT OF SPAR STRAP ASSEMBLY IAW CURRENT REVISION OF MANUFACTURERâS INSTRUCTIONS SK402-47B. A SUPPLEMENTAL FILE WILL BE SUBMITTED ALONG WITH THIS SDR ILLUSTRATING DAMAGE.
ON INITIAL CLIMB, THE PILOT REPORTED FUEL FLOW OF 160PPH. AFTER REACHING CRUISING ALTITUDE THE FUEL FLOW WENT TO 0 & THE PILOT REPORTED TEMP POWER LOSS. THE PILOT WENT THROUGH THE ENG FAILURE CHECKLIST & PLACED THE AUXILIARY BOOST PUMP ON IN THE HIGH SETTING. THE FUEL FLOW WENT TO 170PPH, BUT THE PILOT REPORTED THERE WAS STILL A POWER LOSS. THE PILOT THEN PLACED THE AUXILIARY PUMP IN LOW & THE ENG REGAINED NORMAL POWER INDICATIONS & PERFORMANCE. THE PILOT RETURNED TO DEPARTURE AIRPORT. MAINTENANCE INSPECTED THE ACFT & REPLACED THE RT ENG FUEL FLOW TRANSDUCER IAW THE SIM & SET UP THE RT ENG FUEL FLOW IAW MM 73-20-01. THE ACFT WAS RUN WITH NO DEFECTS OR POWER REDUCTION NOTED. BASED ON THE PILOTS REPORT & MAINTENANCE FINDING THE POWER LOSS WAS LIKELY DUE TO THE AUXILIARY PUMP PLACED ON HIGH CAUSING TOO RICH MIXTURE.
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 A MX EVENT, DAMAGE WAS DISCOVERED ON THE FORWARD CARRY THROUGH SPAR ASSY. DAMAGE INCLUDES FWD LOWER SPAR WEB FLANGE CRACK AND CORRESPONDING VERTICAL STIFFENER CRACKED AT SAME LOCATION. UPON DISCOVERY OF DAMAGE ACFT WAS SUBMITTED TO MRO. MRO REQUESTED AND RECEIVED EO. REPAIRS ARE IN PROCESS.
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 WITHIN ALLOWABLE LIMIT OF MEB91-11R1. THIS UNIT HAS BEEN REPAIRED IAW PROCEDURE OUTLINED IN MEB941-11R1 & RETURNED TO SERVICE.
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.
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.
CREW REPORTED AVIONICS BUSS FAILURE. MX R & R CIRCUIT BREAKER SWITCH. SYS CHECKS OK. ACFT RELEASED BACK TO SERVICE.
RT ENG SURGING AT CRUISE POWER. RESHAPED LEFT NOSE BOWL DUE TO PROP CABLE ROD END CLEARANCE.
PILOT LOG READS THE FOLLOWING: LEFT ENG SMOKES ON APPROACH. MAINTENANCE INSPECTED AND FOUND TURBO TO HAVE FAILED. MAINTENANCE REMOVED AND REPLACED THE TURBO.
AFTER REACHING CRUISE ALTITUDE, CREW NOTICED SMOKE FROM PEDESTAL LIGHTING RHEOSTATS. DAY/NIGHT SWITCH TURNED OFF, CIRCUIT BREAKERS PULLED, SMOKE STOPPED. DIVERTED TO MECHANIC BASE. MECHANIC REMOVED AND REPLACED DIMMER ASSY AND RETURNED AIRCRAFT TO SERVICE.
5 MINUTES INTO CLIMB, CREW REPORTED SMOKE FROM AVIONICS RACK, RETURNED W/O INCIDENT. MECHANIC FOUND A/P PITCH SERVO HARNESS SHORTED, CAUSING A/P COMPUTER TO FAIL INTERNALLY, (TRANSISTORS OVERHEATED AND BURNED) REPAIRED SHORTED HARNESS. REPAIRED A/P COMPUTER, RETURNED MECHANIC TO SERVICE. (NE01200306064)
ON CLIMB OUT, AFTER FIRST POWER REDUCTION, RIGHT ENGINE COST POWER, ATTEMPTED AUX FUEL PUMP, CROSSFEED, NO HELP. SECURED ENGINE AND FEATHERED PROP. RETURNED W/O INCIDENT. MECHANIC FOUND MAIN FUEL LINE TO ENGINE PUMP LOOSE. TIGHTENED LINE, RETURNED A/C TO SERVICE.
ON CLIMB OUT, TOWER REPORTED SMOKE FROM LT ENGINE, CREW REPORTED LOSS OF POWER AFTER AUX BOOST PUMP WAS TURNED ON, ENGINE SHUT DOWN, RETURNED W/O INCIDENT. MECHANIC REMOVED AND REPLACED LT ENGINE DRIVEN FUEL PUMP. RETURNED AC TO SERVICE.