Turbomeca ARRIEL-1B
Service difficulty reports · 807
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 = 'ARRIEL1B' 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 = 'ARRIEL1B' 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 20001215SH013Vent Line · crackedTUBE, AIR VENT - OIL, CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR 20001215SH015Coupling · wornP2 UNION WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR 20001215SH016Line · wornP2 HOSE WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR CA001103018Transponder · failed(CAN) DURING ANNUAL INSPECTION, THE ELT FAILED BECAUSE OF NO OUTPUT POWER. THE ELT WAS RETURNED TO THE MANUFACTURER FOR REPAIR. THIS IS THE SECOND TIME THAT THIS ELT HAS FAILED ITS ANNUAL INSPECTION DUE TO LACK OF OUTPUT POWER. IT PREVIOUSLY FAILED JUNE 2, 1SDR CA001107011Main Rotor · delaminated(CAN) DELAMINATION DETECTED WITH REFERENCE TO EUROCOPTER AS350 MAINTENANCE WORK CARD 62.20.00.601 PARAGRAPH 4.3 (ILLUSTRATION FIGURE 5, DETAIL A, LOCATION ON PART AT DETAIL N). PENETRATION WITH A 010 INCH FEELER GAUGE TO A DEPTH OF APPROXIMATELY .75 INCH DETSDR CA001107020Stabilizer · cracked(CAN) CRACK FOUND ON UPPER VERTICAL FIN LOWER SECTION OF LEADING EDGE BETWEEN TWO RIVETS, 2.6250 INCHES ABOVE STAMPED FITTING, 2.50 INCHES, LENGTH OF CRACK. (X)SDR 20001108SH030Engine · stalledPILOT COMPLAINT WAS SMALL COMPRESSOR STALLS ''POPPING SOUND'' OCCURRING WHEN THEY WOULD DROP COLLECTIVE. THIS WAS AN INFREQUENT OCCURRENCE THAT WAS HAPPENING OVER A PERIOD OF DAYS PRIOR TO INSPECTION OF THE TURBINE SECTION. FULL INSPECTION OF THE COMPRESSOR,SDR CA010518005Servo · leaking(CAN) SCHEDULED INSPECTION REVEALED EXCESSIVE LEAKAGE FROM MAIN ROTOR SERVO. SERVO REMOVED FOR REPAIR.SDR CA010518007Servo · leaking(CAN) SCHEDULED INSPECTION REVEALED EXCESSIVE LEAKAGE FROM MAIN ROTOR SERVO. SERVO REMOVED FOR REPAIR.SDR CA001016010Brushes · failed(CAN) PREMATURE WEAR OF STARTER BRUSHES AND ARMATURE. THERE APPEARS TO BE NO EXCESS CURRENT DRAW ON GENERATOR. NO OTHER ELECTRICAL ABNORMALITIES ON THIS AIRCRAFT. BRUSH WEAR WAS DETECTED ON 100 HOUR INSPECTION. STARTER GENERATOR WAS SENT TO CANADIAN AERO ACCESSDR CA001013024Blade · cracked(CAN) BLADE CRACKED AT STATION 570, ALSO LEADING EDGE EROSION.SDR CA001205013Bleed Valve · failed(CAN) BLEED VALVE WONT CLOSE.SDR CA000901015Engine · power loss(CAN) HELICOPTER WAS IN A HOVER WHEN A POWER LOSS OCCURRED. UNKNOWN AT THIS TIME WHAT THE CAUSE WAS. TC AWAITING FOLLOW-UP REPORT. (X)SDR CA000906011Blower Motor · failed(CAN) PART RECEIVED WITH A REMOVAL TAG (SERICEABLE). PART (MOTOR) SHAFT VERY HARD TO TURN, AND DENTS IN CASE MADE ME SUSPECT ON INSTALLATION. MOTOR FAILED WITHIN 3 HOURS OF INSTALLATION. TC: REGIONAL PMI INVESTIGATING FURTHER.SDR 20000829SH016Gearbox · making metalWHILE PILOT WAS FLYING ON TOUR FLIGHT, NOTICED MAIN GEARBOX CHIP LIGHT ILLUMINATED. PILOT MADE PRECAUTIONARY LANDING. INSPECTED MAIN GEARBOX CHIP PLUG, FOUND A SMALL METAL FLAKE. CLEANED CHIP PLUG AND PERFORMED OPERATIONAL CHECK, FUNCTIONALLY CHECKED GOOD. SDR CA000824012Bleed Valve · stuck(CAN) BLEED VALVE STUCK CLOSED IN-FLIGHT - COCKPIT INDICATION. EVEN AFTER SHUTDOWN, THE ENGINEER NOTICED IT WAS STILL IN THE CLOSED POSITION. THE ENGINEER PROCEEDED TO START REMOVING THIS BLEED VALVE, WHEN HE HEARD A CLICK AND NOTICED THE BLEED VALVE HAD OPESDR CA000824015Control Unit · intermittent(CAN) A RECURRING DEFECT WAS ATTRIBUTED TO THE FOLLOWING REPAIRED TACH BOXES; FAILURE / INTERMITTENT OUTPUT SIGNAL TO BLEED VALVE, CAUSING AN INTERMITTENT WARNING INDICATION IN THE COCKPIT.SDR CA000719002Line · leaking(CAN) THE LINE GOING TO THE LEFT HAND START INJECTOR FOUND LEAKING DURING A GROUND RUN, AFTER REMOVAL FOUND THE FLARE WAS CRACKED 60 PERCENT AROUND THE CIRCUMFERENCE.SDR CA001005007Cable · failed(CAN) INADVERTENT RELEASE OF CARGO HOOK DURING FLIGHT CAUSED BY THE MANUAL RELEASE CABLE.SDR CA000614064Turbine · failed(CAN) DURING START PROCEDURE STARTER WAS UNABLE TO MOTOR ENGINE. AFTER INSPECTING ENGINE FOR F.O.D. AND REMOVING COMPONENTS ON THE ACCESSORY GEARBOX,, ENGINE WAS DISMANTLED TO ISOLATE THE LOCK UP. LOCK UP WAS FOUND TO BE IN THE GAS PRODUCER ASSEMBLY (M024M0SDR 20001215SH020Probe · inoperativeTEMPERATURE PROBE UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR CA001013018Bearing · failed(CAN) EXCESSIVE PLAY FOUND BETWEEN THE BEARING AND SPIDER HOUSING. ALSO FOUND SIGNS OF OVERHEATING WITH LOSS OF GREASE AND PAINT MELTING.SDR AU000422Bushing · broken(AUS) MAIN ROTOR SWASHPLATE TOP SCISSOR LINK BUSHING BROKEN. THE BROKEN BUSHING WORE INTO THE SCISSOR LINK.SDR AU000483Brush Block · broken(AUS) STARTER/GENERATOR BRUSHES BROKEN.SDR CA000614009Switch · cracked(CAN) PILOT REPORTED THAT THE SWITCH WAS INTERMITTENT (HYDRAULIC CUT-OFF SWITCH ON COLLECTIVE STICK).SDR CA000530015Pump · reads low(CAN) PRIOR TO STARTING AIRCRAFT ENGINE, THE FUEL PRESSURE GAUGE WAS OBSERVED TO BE INDICATING ZERO PRESSURE WITH PUMP SWITCHED ON. WHEN LISTENED TO, THE PUMP SEEMED TO BE WORKING, BUT OBVIOUSLY THE ELECTRIC MOTOR WAS NOT ROTATING THE IMPELLER, AS PROVEN BY DSDR CA001013014Bearing · failed(CAN) DURING A 50 HR INSPECTION ON THIS SPIDER, THE BEARING WAS FOUND TO BE ROUGH. NOTE THE BEARING ONLY REACHED 10 PERCENT OF ITS SERVICE LIFE.SDR CA001103020Brushes · worn(CAN) ON A ROUTINE START-UP BRUSH INSPECTION, IT WAS NOTED THAT THE BRUSHES WERE WORN. STARTER/GENERATION WAS REPLACED. THE SUBJECT STARTER WAS FOR REPAIR. INSPECTION REPORT: PREVIOUS CONDITION (06/14/99) BRUSHES WERE RUN DOWN TO RIVETS CAUSING SEVERE COMMSDR CA000530011Bearing · rough(CAN)WHILE PERFORMING AN INSPECTION OF THE TAIL ROTOR PITCH CHANGE SPIDER BEARINGS FOR ROUGHNESS, DRAG AND TORQUE, (AWD 1999-085-076(A)R2). IT WAS DISCOVERED THAT BEARING WAS VERY ROUGH AND RATCHETY. THE AWD IS A REPETITIVE AWD FOR EVERY 50 HOURS. MANUSDR CA000530016Pump · reads low(CAN) DURING FLIGHT, THE PILOT NOTICED THE FUEL PRESSURE INDICATING ZERO. BEING CLOSE TO THE DESTINATION, THE SHORT FLIGHT WAS COMPLETED WITHOUT INCIDENT. WITH THE ENGINE SHUT DOWN, NOTICED THE PUMP OPERATION SOUNDED CORRECT WITH THE POWER APPLIED, BUT WAS FSDR CA000519006Line · broken(CAN) WHEN STARTING, PILOT NOTICED HE HAD TO MOVE POWER LEVER TO ALMOST HALF THROTTLE TO GET ENGINE STARTED. IN-FLIGHT, LACK OF POWER WAS NOT EVIDENT. UPON LANDING, IT WAS DISCOVERED THE BLEED AIR LINE HAD BROKEN COMPLETELY OFF NEAR THE 90 DEGREE FITTING WHESDR CA000719004Starter Gen · failed(CAN) STARTER/GENERATOR FOUND TO BE CAUSING EXCESSIVE ENGINE VIBRATION. UNIT REPLACED.SDR R7MR33303Generator · inoperativeHE GENERATOR, UNIT INOPERATIVE. LOW ENERGY AND LOW FREQUENCY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR R7MR33304Generator · inoperativeHE GENERATOR, UNIT INOPERATIVE. LOW ENERGY AND LOW FREQUENCY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR CA001013012Blade · failed(CAN) MAIN ROTOR BLADE AFTER BALANCING SEVERAL TIMES WINDS UP FLYING OUT OF TRACK, CAUSING A CYCLIC STICK FEEDBACK WHEN THE HYDRAULICS ARE OFF.SDR 20000621SH006Exciter · inoperativeHE GENERATOR INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR CA001013009Fuel Control · failed(CAN) THE ROTOR RPM WAS ADJUSTED SEVERAL TIMES OVER THE COURSE OF A MONTH, AT WHICH TIME THE UNIT FAILED THE CHARACTERISTICS CHECK. UNIT REPLACED. (X)SDR CA001013008Blade · cracked(CAN) CRACKED AT STATION 570, ALSO LEADING EDGE EROSION. BLADE REPLACED.SDR CA001013006Bleed Valve · failed(CAN) INTERMITTENT FAILURE TO CLOSE.SDR CA000404015Tachometer · failed(CAN) TACHOMETER BOX FAILED TO SEND SIGNAL TO BLEED VALVE, CAUSING VALVE NOT TO CLOSE.SDR CA000519007Attach Fitting · cracked(CAN) CRACK FOUND ON THE FUSELAGE TO TAILBOOM ATTACHMENT FLANGE. CRACK LOCATED (LOOKING FORWARD) AT 2:30 POSITION ON RIGHT SIDE. CRACK LENGTH WAS APROXIMATELY 3.5 CM LONG AND ABOUT 2 MM FROM EDGE. THE TORQUE ON FUS/TAILBOOM ATTACH BOLTS WERE UNKNOWN AT THE SDR CA001013004Support Bracket · cracked(CAN) AFTER THE FUEL CELL WAS REMOVED FOR INSPECTION, CRACKS WERE DETECTED IN THE AREA OF THE UPPER TWO BOLT HOLES FOR THE FUEL CELL SUPPORT SADDLES. CRACKED WERE REPAIRED AS PER MRR 53-10-21-777.SDR CA001013005Shim · missing(CAN) DURING THE MAIN ROTOR BLADE REMOVAL, NOTICED THAT THE BLADE PINS WERE HARD TO REMOVE. AFTER INSPECTION, FOUND THAT THE SHIMS WERE MISSING FROM THE FREQUENCY ADAPTERS. ONCE THE SHIMS WERE INSTALLED THE BLADE PIN INSTALL WAS NORMAL.SDR CA000518014Bleed Valve · stuck(CAN) UNIT STICKS CLOSED INTERMITTENTLY.SDR CA000329015Bolt · sheared(CAN) SLIGHT VIBRATIONS NOTICED DURING FLIGHT (3 PER). UPON LANDING, A SHEARED BOLT WAS FOUND ON THE VERTICAL STABILIZER ATTACHMENT. BOLT REPLACED AND ROTORCRAFT TEST FLOWN WITH NO VIBRATIONS.SDR CA000322006Belt · failed(CAN) DURING 100 HOUR INSPECTION WHILE RE-INSTALLING THE HYDRAULIC PUMP, THE BELT BROKE WHILE TRYING TO STRETCH IT TO THE REQUIRED 102 MM ADJUSTMENT CRITERIA.SDR CA000410036Line · cracked(CAN) ENGINE FAILED TO START, MAINTENANCE FOUND SPRAY OF FUEL BETWEEN THE LEFT HAND FITTING TO THE START INJECTOR. THE LINE WAS REMOVED AND FOUND CRACKED AT BASE OF THE FLARE.SDR CA000518012Heater · corroded(CAN) LINE FOUND TO BE CORRODED AND CRACKED BY THE UNION.SDR CA000518009Tachometer · unserviceable(CAN) ENGINE BLEED VALVE WHICH IS CONTROLLED BY THE TACHOMETER BOX INADVERTENTLY OPENED TWICE AT 98 PERCENT NG. OPERATOR WAS NOT ABLE TO DUPLICATE. POSSIBLE CAUSE WAS A SHORT IN THE TACHOMETER BOX.SDR CA000518010Transmitter · incorrect(CAN) TORQUE TRANSMITTER WAS INSTALLED THE DAY BEFORE AND SET TO PROPER PRESSURE. CHECKED LATER AND FOUND TO BE OFF BY 3% PERCENT. UNIT RE-ADJUSTED.
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