Turbomeca ARRIEL-2B1
Service difficulty reports · 757
Newest first. General aviation reporting is voluntary.
Query with SQL
duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE engine_model_key = 'ARRIEL2B1' ORDER BY difficulty_date DESC"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE engine_model_key = 'ARRIEL2B1' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR CA121010008Bracket · broken(CAN) UPPER LT PN 350A23-4222-21, 388.9 TOTAL HOURS. BROKEN IN PIECES. LOWER RT PN 350A23-4223-20, 789.9 TOTAL HOURS. CRACKED UPPER LEFT PN 350A23-4222-21, STOP DRILLED AT 789.9, REPLACED AT 876.7 TOTAL HOURS CRACKED. THIS IS THE FIRST OF 3 SIMILAR BRACKETSDR CA120904002Fitting · cracked(CAN) PN 350A23-4222-20, UPPER, 350A23-4223-20 LOWER STABILIZER ATTACH BRACKETS RT REPLACED. WORK CARRIED OUT BY MFG FIELD SERVICE REPRESENTATIVE.SDR CA110929019Starter Gen · faulty(CAN) WHILE IN CRUISE FLIGHT, THE GENERATOR LIGHT ILLUMINATED 3 TIMES. THE PILOT RESET THE GENERATOR ALL 3 TIMES. TROUBLESHOOTING REVEALED THE STARTER GENERATOR WAS AT FAULT. THE SUBJECT STARTER GENERATOR WILL BE SENT TO A REPAIR FACILITY TO FIND THE CAUSE.SDR HCMA2011F00000Potentiometer · malfunctionedDURING A TOUR FLIGHT WITH 6 PASSENGERS AND THE PILOT ON BOARD, THE ACFT LEFT THE HELIPAD AND 10 MINUTES INTO FLIGHT, THE AMBER "GOV" LIGHT ILLUMINATED ON THE CAUTION PANEL. THE PILOT RETURNED TO THE HELIPORT WITHOUT INCIDENT. THE ACFT WAS SHUTDOWN NORMALLY. SDR PG92011F00010Brake · crackedROTOR BRAKE PAD CRACKED FROM NEW. EDGES FALLING APART WHILE INSTALLED ON ACFT. R & R WITH ONLY 94.7 HRS PART TT. PROBABLE CAUSE MAY BE BAD BATCH. FOUND A 1200T INSPECTION. MFRF0210 CODE.SDR PG92011F00009Servo · wornPILOT FOUND UPPER ROD END BEARING LOOSE, WITHIN SERVO HOUSING. ON FURTHER INVESTIGATION, FOUND THREADS IN SERVO BODY WORN BEYOND LIMITS. COULD HAVE CAUSED A CATASTROPHIC FAILURE.SDR PG92011F00005Sensor · debondedINTERNAL COMPONENTS OF THE NR SENSOR DEBONDED AND EXTRUDED FROM THE SENSOR HSG. THE EXTRUDED PARTS THEN CONTACTED THE ROTATING COG WHEEL OF THE MAIN ROTOR MAST SYS, DAMAGING THE SENSOR, THE ROTATING COG WHEEL ALSO SUSTAINED DAMAGE DUE TO CONTACT AND CAUSED POSDR HCMA20110816001Engine · making metalDURING CRUISE FLIGHT, ENGINE "CHIP" WARNING LIGHT ILLUMINATED. PILOT MADE A PRECAUTIONARY LANDING. UPON INSPECTION OF THE ENGINE MAGNETIC AND ELECTRICAL CHIP PLUGS, SUBSTANTIAL AMOUNTS OF "MAGNETIC" METAL WAS FOUND ON THE MODULE 1 (ENGINE ACCESSORY GEARBOX)SDR RMXA308855ASensor · defectivePILOT REPORTED A LOSS OF NR INDICATION DURING FLIGHT. PILOT ELECTED TO MAKE A PRECAUTINARY LANDING. TECH WAS DISPATCHED BUT DUE TO THE LOCATION AND SECURITY OF THE ACFT, ELECTED TO HAVE THE ACFT TRANSPORTED TO THE MX FACILITY FOR FURTHER TROUBLESHOOTING. THE SDR M7KA201107214340Hmu · failedACFT EXPERIENCED A FORCED LANDING. ON THE FIRST SCHEDULED STRIP TOUR AT DUSK, THE PILOT SUDDENLY NOTED SOME UNUSUAL MODERATE LATERAL VIBRATIONS IN THE AIRFRAME. PILOT IMMEDIATELY DIVERTED BACK TO THE AIRPORT AND JUST SHORT OF FLARING THE ACFT INTO THE HOVER/SDR QMLA2011070211074Unknown · leakingPILOT REPORTED FUEL ODOR IN CABIN/COCKPIT DURING FLIGHT. INSPECTED THE ENGINE, TRANSMISSION AREA, FUEL SYSTEM INCLUDING TANK AREA, UNDERSIDE OF ACFT, BAGGAGE AREA'S, AND COCKPIT/CABIN AREA FOR SIGNS OF FUEL AND/OR FUEL ODOR, LOOSE LINES, OR DAMAGE. NONE FOUNSDR QMLA2011061711067Air Filter · overservicedENGINE INLET FILTER OVER SERVICED, EXCESS OIL ACCUMUATED IN INLET TO ENGINE AND SMOKED WHEN OPERATING TEMPS IN ENGINE BECAME HOT.SDR QMLA2011061711068Shaft · shearedPILOT REPORTED GRINDING SOUND DURING START, FOUND STARTER GENERATOR SHAFT SHEARED. FOUND COMPRESSOR DID ROTATE FREELY WHEN CHECKED. REPLACED WITH SERVICABLE STARTER GENERATOR. CAUSE OF SHAFT FAILURE NOT KNOWN.SDR M7KA20110605#4327Bolt · failedACFT PREPARED TO LAUNCH FOR REVENUE FLT, AN ENGINE CHIP LIGHT ILLUMINATED. ENGINE SHUTDOWN NORMALLY. CHECK OF ELECTRICAL CHIP DETECTOR REVEALED A FEW SMALL METAL SLIVERS BUT SUBSEQUENT INSP REVEALED A SIGNIFICANT NUMBER OF METAL CHIPS ON THE MODULE 5 NON ELSDR CA110610006Pulley · wornDURING THE 100 HR INSP SB 63-005 WAS COMPLETED ON THIS ACFT IAW THE S/B THE PULLEY ASSY WAS FOUND TO BE WORN BEYOND LIMITS AND REQUIRED REPLACING THE PULLEY ASSY AND BEARING. THE BEARING IS NORMALLY A PRESSED FIT REQUIRING HEATING 1 PART AND COOLING THE OTHESDR CA110610007Pulley · wornHYD PUMP PULLEY ASSY WAS FOUND TO BE WORN BEYOND LIMITS AND REQUIRED REPLACING THE PULLEY ASSY AND BEARING. THE BEARING IS NORMALLY A PRESSED FIT REQUIRING HEATING ONE PART AND COOLING THE OTHER BUT ON INSP THE BEARING WAS LOOSE ENOUGH TO FALL OFF THE PULLEY SDR CA110524004Frame · crackedDURING A 100 HR INSP CONDUCTED A 3" CRACK ON ONCS RT CANOPY FRAME ATTACHMENT WEB WAS FOUND. CRACK IS ADJACENT TO THE LOWER RT DOOR ATTACHMENT. MFG WAS CONTACTED AND AN EXISTING FRAME REPAIR WAS PROVIDED. MFG FRAME REPAIR 22 DEG, 130-53-002-08.SDR RMXA383298Blade · damagedUPON APPROACH, ACFT SUSTAINED A BIRD STRIKE ON THE PILOT SIDE WIND SCREEN AND WAS PROJECTED INTO THE TAIL ROTOR DUE TO THE DOWN WASH OF THE MAIN ROTOR SYS TECH INSPECTED WINDSCREEN WITH NO DEFECTS NOTED. TAIL ROTOR BLADE AND SPIDER ASSY HAD EVIDENCE OF THE BIRSDR CA110524006Circuit Card · failedFALSE INDICATION OF "BATTERY HOT" CIRCUIT. LIGHT REMAINED ON.SDR RMXA372672Potentiometer · out of adjustAMBER GOV LIGHT WAS DETECTED PRIOR TO ACFT LANDING AT BASE. TECH DOWNLOADED VEMD FAIL CODE OF 120 FOR YAW POTENTIOMETER. FOUND YAW POTENTIOMETER SEETINGS ON THE HIGH SIDE OF 53.5 PERCENT. ADJUSTED POTENTIOMETER TO 52.5, AND PERFORMED OPS CHECKS WITH NO DEFECTSDR RMXA383295Display · malfunctionedDURING APPROACH TO AIRPORT, ACFT INDICATED AN AMBER GOV LIGHT. DOWNLOADED VEMD FAIL 1 CODE OF 0008 AND A FAIL 2 CODE OF 0200. AFTER CONTACTING MFG REPRESENTATIVE IT WAS VERIFIED THAT THESE DISTURBANCES ARE KNOWN AS NUISANCE CODES. CONNECTOR PLUGS WERE CLEANEDSDR QMLA2011042011049Unknown · odorSHORTLY AFTER TAKEOFF, RETURNED TO THE BASE, THE MEDIC ANNOUNCED HE SMELLED A STRONG PRESENCE OF FUEL. THE NURSE CONFIRMED THE ODOR AS WELL. THE PILOT IMMEDIATELY BEGAN A COURSE TO THE NEAREST AIRPORT WHERE ON FINAL APPROACH, THE ODOR HAD DISAPPEARED. AFTERSDR QMLA2011041811048Battery · dischargedDURING A NIGHT FLIGHT, FLIGHT INSTRUMENTS BEGAN TO FLICKER AND DIM. NOTED THAT THE GEN SWITCH WAS IN AND THERE WERE NO CAUTION LIGHTS. A COUPLE OF MINUTES LATER THE ENTIRE PANEL WENT OUT, INCLUDING THE VEMD, BOTH GARMIN GPS/RADIS. THE GMX 200 REMAINED ON AND SDR CA110428013Magnetic Seal · leakingTAIL ROTOR GEARBOX INPUT SEAL STARTED LEAKING 21.1 HRS, AFTER INSTALLING THE REPAIRED GEARBOX.SDR CA110418008Blade · brokenFOUND THAT THE STBD HAMMER ATTACHMENT BLADE WAS BROKEN OFF. THIS IS THE 3RD TIME THIS HAMMER HAS BEEN FOUND BROKEN IN 1078.2 HOURS. MFG IS ASSISTING IN INVESTIGATING THE REASON FOR THIS PROBLEM.SDR KBMA2011031802Structure · crackedCRACKED TAIL BOOM.SDR RMXA308855Pump · unserviceableAFTER AIRCRAFT START UP, THE PILOT REALIZED HE DID NOT HAVE HYDRAULIC POWER. THE AIRCRAFT WAS THEN SHUT DOWN. UPON INSPECTION OF THE HYDRAULIC SYSTEM AND CONSULTATION WITH EUROCOPTER TECHNICAL REPRESENTATIVES, IT WAS DISCOVERED THAT THE HYDRAULIC PUMP HAS FAILSDR PG92011F00000Skin · crackedON 3-14-11 DURING A PREFLIGHT INSP BY PILOT, A CRACK WAS DISCOVERED IN THE TAILBOOM SKIN ON THE RT SIDE WHERE THE HORIZ STABILIZER MOUNTS AFT LOWER CORNER. THE CRACK ORIGINATES THERE AND CONTINUES UNDER A SPAR (OVER 1 IN LONG). MFG HAS BEEN CONTACTED AND ALRSDR PG92011F00001Skin · crackedON 3-14-11 DURING THE INSP OF A 600 HR T INSP, A CRACK WAS DISCOVERED IN THE TAILBOOM SKIN ON THE RT SIDE WHERE THE HORZ STAB MOUNTS AFT LOWER CORNER. THE CRACK ORIGINATES THERE AND CONTINUES UNDER A SPAR (OVER 1 INCH LONG). MFG HAS BEEN CONTACTED AND ALREADSDR PG92011F00002Skin · crackedON 3-15-11 DURING A 100 HOUR INSP, A CRACK WAS DISCOVERED IN TAILBOOM SKIN ON THE RIGHT SIDE WHERE THE HORIZ STAB MOUNTS AFT LOWER CORNER. THE CRACK ORIGINATES THERE AND CONTINUES UNDER A SPAR (OVER 1 INCH LONG). MFG HAS BEEN CONTACTED AND ALREADY HAS A REPASDR RMXA110314194936Swashplate · dirtyPILOT EXPERIENCED A BINDING OR HARD POINT PREVENTING CYCLIC TRAVEL IN THE AFT LT QUADRANT OF TRAVEL DURING HOVER TAXI/FWD FLIGHT IN GROUND EFFECT. THE PILOT PERFORMED A RUN ON LANDING. THE PILOT SELECTED IDLE AND PERFORMED A CONTROL FREEDOM CHECK WITH CYCLICSDR RMXA363942Potentiometer · malfunctionedACFT INDICATED AN AMBER GOV LIGHT IN FLIGHT, WITH NO ENGINE, MAIN ROTOR, OR TAIL ROTOR FLUCTUATIONS IN FLIGHT. TECH RETRIEVED AN INTERMITTENT FAILURE CODE 122 FOR THE COLLECTIVE POTENTIOMETER. WHEN THE ACFT WAS POWERED BACK UP AFTER LANDING THE AMBER GOV LIGHTSDR CA110816006Windshield · cracked(CAN) CENTER WINDSCREEN CRACKED 21.5 CM FROM UPPER SCREW HOLE OF TURN & SLIP INDICATOR.SDR CA110222012Shaft · damaged(CAN) THIS HELICOPTER HAS BEEN WORKING FOR THE PAST 11 DAYS. THE HELICOPTER HAS BEEN PARKED OUTSIDE WITH ALL THE NECESSARY COVERS AND HEATERS INSTALLED. THERE HAD BEEN BLOWING SNOW FOR THE PAST DAY PRIOR TO THIS INCIDENT. ON THE FIRST FLIGHT OF THE DAY THE HSDR 2011F00050Pressure Switch · faulty10 MINUTES INTO A TOUR FLIGHT, HYD LIGHT ILLUMINATED. PILOT RETURNED TO BASE, WHERE THE HYD LIGHT WENT OUT PRIOR TO LANDING. RT HYD PRESSURE SWITCH WAS CHANGED. THE RT PRESSURE SWITCH WAS CHOSEN DUE TO THE FACT THAT THE RT HYD MANIFOLD INCLUDING THE PRESSURSDR CA110214018Plug · damagedDURING THE 600 HR/24 MONTHS INSPECTION ON ENGINE AND AIRFRAME, FOUND MISSING RIVETS ON COMPRESSOR WASH NOZZLE PLUG. REMOVED DEFECTIVE PARTS AND FOUND METAL FROM RIVET SHAVINGS IN COMPRESSOR WASH NOZZLE. SUSPECT METAL MAY HAVE PASSED THRU COMPRESSOR WASH NOZZLESDR CA110214015Windshield · deformedDURING FLIGHT, PILOTS DISCOVER DEFORMATION OF THE CTR WINDSHIELD IAW AD`S 2007-0219-E AND 2010-0258 INSPECTION/REPLACEMENT WINDSHIELD REPLACED BY PN 350A25-9045-20.SDR CA110214017Windshield · crackedACFT WAS OUTSIDE AT -32C. WHEN PILOTS C/OUT PREFLIGHT CHECK, NO DAMAGE FOUND. PILOTS TAKEOFF AND DURING FLIGHT AT -32C, CRACK START ON LT TOP WINDSHIELD. PILOTS REDUCED SPEED AND LANDED .SDR QMLA2011012711016Potentiometer · failedIN CRUISE FLIGHT, PILOT NOTICED YELLOW GOV LIGHT ILLUMINATED. LANDED, SHUTDOWN ACFT. MECHANIC REVIEWED VEMD FAILURE PAGE ON MX MENU OF VEMD. VEMD INDICATED FAILURE, TEST REF 120, LRU "NF TRIM POT" IN RED. REMOVED YAW ANTICIPATOR POTENTIOMETER AND REPLACED SDR QMLA2011012511013Potentiometer · failedUPON SHUTDOWN AND COLLECTIVE ROLLED TO IDLE, PILOT NOTICED FLASHING YELLOW GOV LIGHT ILLUMINATED. PILOT SHUTDOWN ACFT. MECHANIC REVIEWED VEMD FAILURE PAGE ON MX MENU OF VEMD. VEMD INDICATED FAILURE, TEST REF 120, LRU "NF TRIM POT" IN RED. REMOVED NF TRIM SDR QMLR20110126Structure · damagedDURING INSTALLATION OF MED EQUIPMENT RAILS IAW DWG 749-1035-002: RT UPPER MED RAIL LOCATION IN AFT WALL WAS MISDRILLED AT 9.5 AND NOT AT 9.95 IAW ECO 9485. LOWER MED MOUNT RAIL LOCATIONS IN AFT WALL WERE MISDRILLED FOR INCORRECT NUT-PLATE.SDR QMLA2011011611010Windshield · crackedWHILE COMING UP TO A 2 FT HOVER, A CRACK APPEARED ON THE LT PILOTS WINDSHIELD BEGINNING AT THE RT CTR OF WINDOW, CRACK GREW TO APPROX 8 INCHES IN LENGTH, MOVING TOWARD THE LT SIDE OF WINDOW, ALMOST EYE LEVEL, ABORTED TAKEOFF, LANDED BACK ON HELIPAD.SDR RMXA350481Potentiometer · bindingACFT WAS LEAVING AIRPORT, DURING FLIGHT ACFT HAD A YAW FLUCTUATION. AFTER SEVERAL YAW FLUCTUATIONS THE WARNING INDICATION PANEL DISPLAYED AN AMBER GOV LIGHT. DURING THIS TIME OF OCCURANCE THE PILOT REPOSITIONED THE ACFT TO AIRPORT AND LANDED WITHOUT INCIDENTSDR CA110114001Fuel Tank · chafed(CAN) DURING A 600 HR INSPECTION, ON REMOVAL OF THE AUXILIARY FUEL TANK. THE BOTTOM OF THE FUEL TANK HAD CHAFING MARKS FROM THE RIVETS ON THE LT BAGGAGE FLOOR. IF LEFT THIS WOULD HAVE LEAD TO A HOLE IN THE AUXILIARY FUEL TANK CAUSING A FUEL LEAK.SDR CA110105002Magnetic Seal · leakingLEAKING, THIS LEAK IS WELL WITHIN LIMITS BUT THIS CAUSES UNNECESSARY CONTAMINATION ON TAILBOOM AND ASSOCIATED PARTS. THE OIL VENTS OUT OF THE GEARBOX (AS IT SHOULD), BUT THE EXTRA THAT CAN’T BE BURNT IN THE EXHAUST IS VENTED ON THE TAILBOOM AND TAIL ROTOR CAUSDR QMLRMD9951Support Frame · mislocated(QMLR) 2 EA, 190 DIA BRACKET INSTALLATION HOLES WERE MISLOCATED ON THE OEM SUPPORT FRAME DURING INSTALLATION OF A SUPPORT BRACKET.SDR 2010FA0001264Oil Cap · detachedTHE ENGINE OIL RESERVOIR CAP CAME OFF IN FLIGHT RESULTING IN SIGNIFICANT OIL LOSS. HELICOPTER RETURNED TO BASE WITH NO PROBLEMS ENCOUNTERED. THE ISSUE IS MANUFACTURER`S "UNIQUE" RETAINING MECHANISM FOR CAP. RETAINING MECHANISM IS EASILY DISLODGED AND YET STILLSDR CA110105003Seal · leaking(CAN) MAIN ROTOR TRANSMISSION INPUT SEALS LEAK. WITHIN LIMITS BUT OIL LEAKING CAUSES PREMATURE LIFE OF ELASTOMERIC COMPONENTS. THIS LEAK IS MOST COMMON WHEN CHANGING FROM WINTER OIL TO SUMMER OIL. AS WELL AS SUMMER OIL TO WINTER OIL.SDR CA101223005Bearing · out of balance(CAN) WHILE CARRYING OUT A BALANCE CHECK ON BEARING NR 1 AFTER ROUTINE MAINTENANCE (200 HOUR INSPECTION) BEARING NR 1 WAS FOUND TO HAVE AN IMBALANCE OF 6.84 IPS. THE VIBRATION WAS FELT THROUGH THE HELICOPTER. SQUARENESS CHECK OF NR 1 BEARING WAS CARRIED OUT, FSDR QMLDMG1502Skin · crackedWHILE PERFORMING AN INSP OF THE FUSELAGE, FOUND A CRACK IN THE SKIN BEHIND THE LT SLIDING DOOR TRACK. CONTACTED MFG IAW THE SRM FOR A REPAIR SCHEME.
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