Turbomeca ARRIEL-2D
Service difficulty reports · 138
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 = 'ARRIEL2D' 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 = 'ARRIEL2D' 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 QMLA 202608272006Main Rotor · fodJUST PRIOR TO LANDING, A SMALL PLASTIC BAG FLOATED UP AND INTO THE MAIN ROTOR SYSTEM. IT BLEW OUT ALMOST IMMEDIATELY AFTER THE FACT. A NORMAL LANDING AND SHUTDOWN WERE PERFORMED.SDR QMLA2026071820047Bearing · faultedPILOTS REPORT "AFTER ILLUMINATION OF THE HYD2 AND SERVO LIGHTS, NURSE AND MEDIC SAW WHITISH GRAY SMOKE FROM VICINITY IN FRONT OF THE CABIN TDFM RADIO CONTROL HEAD, NEAR THE O2 SHUT-OFF LEVER. I SMELLED A BURNT RUBBER SMELL BUT NEVER SAW ANY SMOKE WHEN I LOOKESDR PG9A2026070600568Hydraulic System · faultedAIRCRAFT WAS DOING LEFT 180 AT QUARTERMASTER CANYON FOR BURNT SPRINGS PILOT STARTED TO NOTICE A STRANGE ODOR IN THE AIRCRAFT. ABOUT 5 SECONDS LATER, A TON OF WHITE SMOKE STARTED TO POUR INTO THE CABIN THROUGH THE A/C VENTS. PILOT IMMEDIATELY TURNED OFF THE A/SDR 9SZA202607100147Terminal · looseENGINE FIRE CAUTION LIGHT INTERMITTENT. FIRE DETECTORS PASSED BENCH TEST PROCEDURES IAW MM. WITH EXCESSIVE VIBRATION AND MOVEMENT, ENG FIRE CAUTION LIGHT INTERMITENT ILLUMINATION.SDR 9SZA202609100148Terminal · looseENGINE FIRE CAUTION LIGHT INTERMITTENT. FIRE DETECTORS PASSED BENCH TEST PROCEDURES IAW MM. WITH EXCESSIVE VIBRATION AND MOVEMENT, ENG FIRE CAUTION LIGHT INTERMITENT ILLUMINATION.SDR 2A6D20260305001Fuel Line · bentWHILE HOVER TAXIING THE AIRCRAFT DURING CHECK FLIGHTS, THE PILOT REPORTED A FUEL P LIGHT AND TURNED THE AIRCRAFT AROUND TO RETURN TO THE RAMP. DURING THE FLIGHT BACK, THE PILOT WAS ALERTED TO AN AMBER GOV LIGHT AND NOTICED THAT THE AIRCRAFT WAS LOSING POWER. TSDR QMLA2025101420105Unknown · odorSTRONG BURNING SMELL IN COCKPIT.SDR 2A6R 09222025743Skin · crackedDURING THE 600 HOUR / 24 MONTH AIRFRAME INSPECTION, A CRACK WAS FOUND ON THE TAILBOOM SKIN (TAILBOOM P/N: 350A2307150002 S/N: TB7538) ON THE UPPER R/H CORNER OF THE BATTERY COMPARTMENT DOOR DOUBLER MEASURING 1.35" IN LENGTH AND STOPPING AT A RIVET HOLE. THIS CSDR JBZA20250710001Elec Connector · arcedDURING FINAL APPROACH TO BASE AN ELECTRICAL SMELL WAS DETECTED COMING FROM THE CENTER CONSOLE TDFM / SKY TRAC PANELS. DURING EVALUATION OF THE SYSTEMS IT WAS DISCOVERED THE CONNECTOR TO THE TDFM WAS THE SOURCE OF THE SMELL. FOUND CONNECTER WITH BROKEN MALE PINSDR 2A6D20250502001Xmsn Deck · chafedGOUGING- TOOL DAMAGE WAS DISCOVERED ON THE LH SIDE OF THE TRANSMISSION DECK. THE DEPTH IS APPROXIMATELY 0.026". THE MAXIMUM APPROXIMATE LENGTH IS .6 AND WIDTH IS 0.85".SDR EVCA20250502001Structure · crackedCRACK EXCEEDING THE MANUFACTURES LIMITS IN THE HORIZONTAL STABILIZERSDR 2025FA0000130Engine · making metalA CUSTOMER ENGINE WAS RECEIVED AS AN EXCHANGE TO BE INSTALLED IN A AS35B3 HELICOPTER. A PRE-INSTALLATION INSPECTION FOUND SIGNIFICANT METAL CONTAMINATION IN THE OIL SYSTEM, INCLUDING THE FILTER AND MAG PLUGS. THE ENGINE WAS RECEIVED WITH AN 8130-3 INDICATING SDR QMLA2025022520026Fan · damagedAFTER LIFTING GENESIS EAST MED CENTER AND HEADING TO IOWA CITY. THE AV FAN CAME ON FOLLOWED BY A STRONG BURNING SMELL. FOUND INOP AVIONICS FAN RIGHT SIDE UNDER INSTRUMENT PANEL.SDR QMLA2025012920009Bulkhead · crackedDURING SCHEDULED MAINTENANCE FOR THE A 0740 150 HOUR / 12 MONTH AIRFRAME INSPECTION A CRACK WAS FOUND ON THE UPPER RIGHT HAND CORNER OF THE 22 DEGREE BULKHEAD.SDR QMLA2024090620108Engine · power lossON PICKUP I NOTICED THE FLI WAS HIGHER THAN NORMAL, I CAN USUALLY LIFTOFF AT 7/7.5 ON THE FLI AT MGW BUT THIS TIME I WAS 100LBS UNDER MGW AND IT DIDNT LIFT OFF UNTIL OVER 8 ON THE FLI. ON CLIMB-OUT IT FELT SLUGGISH SO I CHECKED MY NUMBERS. I WAS AROUND 98 N1/NSDR 2A6D20240614001Attach Angle · crackedDAMAGE TO THE BAGGAGE COMPARTMENT LH FWD LOWER ANGLE (P/N: 350A210053.28) IN THE FORM OF GOUGE/CRACK. THE GOUGE/CRACK DAMAGE MEASURED TO BE APPROXIMATELY 0.13” IN DIAMETER.SDR 2A6D20240528001Frame · corrodedDAMAGE TO THE AFT UPPER FRAME (P/N: 350A21-1242.35) IN THE FORM OF CORROSION. THE CORROSION DAMAGE IS ON THE UPPER FLANGE OF FRAME AT LH AND RH BOTTOM SIDE NEAR THE AFT LOWER FRAME. THE LH SIDE CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 0.71: X 2.05” AND THSDR 2A6D20240509001Bulkhead · corrodedTHE UPPER 7° BULKHEAD DOUBLER (PN: 350A21-0849.20) IS CORRODED AT THE LOCATION OF A PASS-THRU HOLE. THE DAMAGE AREA WAS REPORTED TO BE 0.80” X 0.50” AND 0.030” DEEP AT THE DEEPEST POINTSDR 2A6D20240509002Bonding Plate · corrodedDAMAGE IS ON THE TAIL BOOM VHF ANTENNA BASE PLATE (P/N: 350A65-1707.00) IN THE FORM OF CORROSION. THE BASE PLATE IS EXCESSIVELY CORRODED AND DEPTH OF THE DAMAGE IS ALL THE WAY THROUGH THICKNESS WHICH RESULTS IN REPLACEMENT OF ANTENNA BASE PLATE.SDR 2A6D20240509003Floorbeam · corrodedDAMAGE IS ON THE LH CABIN FLOOR EDGE FITTING (P/N: 350A214753.20) IN THE FORM OF CORROSION AND CRACKS. THE LH FITTING PLATE IS EXCESSIVELY CORRODED AND THE CRACK DAMAGES AT TWO FASTENER HOLES TO EOP WHICH RESULTS IN REPLACEMENT OF LH FITTING.SDR 2A6D20240508001Crossbeam · corrodedTHE RH X1790 CROSSBEAM (PN: 350A21-0572.20) IS CORRODED IN AN AREA WHERE IT CONTACTS THE RH Y400 BEAM (PN: 350A21-0587.20)SDR 2A6D20240508002Crossbeam · corrodedTHE RH X2244 CROSSBEAM (PN: 350A21-0861.20) IS CORRODED IN AN AREA ON THE LOWER OUTBOARD CORNER OF THE CROSSBEAM. THE DAMAGE WAS REPORTED TO BE 0.572” X 0.179” AND 0.028” DEEPSDR 2A6D20240508003Crosstube · corrodedTHE AFT LANDING GEAR CROSSTUBE FITTING (PN: 350A21-0960.20) IS CORRODED IN MULTIPLE AREAS ON THE LOWER SURFACE. THE DEEPEST DAMAGE AREA WAS REPORTED TO BE 0.022” DEEP AND THE LARGEST AREA IS APPROXIMATELY 0.40” WIDE WITH VARIOUS LENGTHSSDR 2A6D20240425001Web · corrodedDAMAGE TO THE LOWER CENTER WEB IN THE FORM OF CORROSION. THE CORROSION DAMAGE IS TOWARDS THE AFT SIDE OF THE WEB NEAR LIGHTENING HOLES AND MEASURED TO BE THROUGH THICKNESS IN DEPTH.SDR 2A6D20240425002Brace · corrodedDAMAGE TO THE LH VERTICAL ANGLE (PN: 350A62-1148.21) ON THE AFT SECTION FWD LOWER FRAME IN THE FORM OF CORROSION. THE CORRODED AREA IS LOCATED AT THE BOTTOM END OF THE ANGLE, AND WAS MEASURED TO BE APPROXIMATELY 0.875” X 0.875” IN SIZE THROUGH THE FULL THICKNESDR 2A6D20240425003Skin Panel · corrodedFIRST DAMAGE IS ON THE AFT FUSELAGE LH SIDE SKIN PANEL IN THE FORM OF CORROSION. THE LH SIDE SKIN DAMAGE IS NEAR TOP EDGE WHERE ENGINE DECK OVERLAPS AND MEASURED TO BE APPROXIMATELY 0.15” X 0.35” X 0.009”.SDR 2A6D20240425004Skin Panel · corrodedDAMAGE IS ON THE AFT FUSELAGE RH SIDE SKIN PANEL (P/N: 350A210046-21 IN THE FORM OF CORROSION. THE RH SIDE SKIN DAMAGE IS NEAR TOP EDGE WHERE ENGINE DECK OVERLAPS AND MEASURED TO BE APPROXIMATELY 0.15” X 0.20” X 0.011”.SDR 2A6D20240425005Cradle · corrodedTHE LH FWD FUEL CRADLE REINFORCEMENTS HAD DAMAGE IN THE FORM OF CORROSION. THE LH FWD CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 1.0” X 0.80” X 0.008”.SDR 2A6D20240425006Cradle · corrodedRH AFT FUEL CRADLE REINFORCEMENTS HAS DAMAGE IN THE FORM OF CORROSION. THE RH AFT CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 2.1” X
0.80” X 0.009”.SDR 2A6D20240425007Attach Angle · corrodedREAR LANDING GEAR ATTACHMENT LOWER ANGLE HAS DAMAGE IN THE FORM OF CORROSION. THE DAMAGE NEAR THE ANGLE OVERLAPS WITH MACHINED FRAME AND AFT LOWER BELLY FAIRING. THE DAMAGE IS ON THE VERTICAL FACE OF THE ANGLE AT PREVIOUS REPAIR LOCATION AND IS MEASURED TO BE SDR 2A6D20240425008Stiffener · corrodedDAMAGE TO THE TAIL BOOM LH FWD STIFFENER MEASURED TO BE APPROXIMATELY 0.85” X 0.85” X 0.0125” IN THE FORM OF CORROSION.SDR 2A6D20240425009Skin Panel · corrodedCORROSION DAMAGE ON THE FWD UPPER SKIN MEASURED TO BE APPROXIMATELY 0.80” X 0.60” X 0.003”SDR M3XA2024012219001B-Nut · loosePILOT REPORTED ON POST FLIGHT INSPECTION, DISCOVERED OIL ON OUTSIDE OF ENGINE COWLING, DRAINING FROM ENGINE DECK DRAIN LINES AND SMOKE COMING OFF OUTSIDE OF EXHAUST DUCT AND OIL ON OUTSIDE OF THE ENGINE. MECHANIC FOUND B-NUT VENT LINE LOOSE AND DISCONNECTED. SDR QMLA202312231222Unknown · unknownDURING CLIMB OUT THE AIRCRAFT HAD SIGNIFICANT INCREASED RIGHT CYCLIC PRESSURE THAT SUDDENLY RELEASED CAUSING THE AIRCRAFT TO SLIGHTLY JOLT TO THE RIGHT. THE FLIGHT WAS ABORTED AND AIRCRAFT SAFELY LANDED BACK AT BASE.SDR QMLA2023092620077Unknown · unknownCOLLECTIVE APPLICATION DURING TAKEOFF CREW NOTICE A SMELL OF BURNING RUBBER. I THOUGHT IT WAS AN AC BELT BURNING, RETURNED TO PAD SHUT DOWN, WENT BACK TO TRANSMISSION AND NOTICED THE AC BELT WAS STILL INTACT. CALLED MX, MAINTENANCE INVESTIGATED AND SMELLED ARESDR EVCA09252023Support · damagedPERFORMED TRANSMISSION SHAFT BEARING SUPPORT 10HR REOCCURRING AD 2022-01-05, DISCOVERED SHEARED RIVET AND CRACKS ON REAR TRANSMISSION SHAFT BEARING SUPPORT.SDR 2A6D20230825001Bulkhead · chafedDAMAGE WAS DISCOVERED ON THE LH SIDE OF THE 15 DEGREE BULKHEAD ON THE AFT FACE. THE CHAFE CORRESPONDS TO AN ANGLE CLIP OF THE SHEET METAL LOX ENCLOSURE RUBBING ON THE AFT WALL. THE CHAFE MEASURES APPROX. 0.029” DEEP, 0.1” LONG AND 0.2” WIDE.SDR QMLA2023082620067Unknown · unknownDEPARTED HELIPAD EN-ROUTE TO AIRPORT FOR FUEL FOR AN INTERFACILITY REQUEST. AFTER HOVER CHECKS AND REPOSITIONING TO THE CENTER OF THE HELIPAD, FLIGHT CREW NOTED VISIBLE LIQUID RANGING IN SIZE FROM A SMALL PUDDLE TO SEVERAL DROPS. FLIGHT CREW CONDUCTED A QUICK SDR FXTA20230926001Motor · failedBLOWER MOTOR MAKING LOUD NOISES DURING OPERATION. WHEN FAN SPUN BY HAND THERE WAS INDICATION OF DRAG OR ROUGHNESS IN MOTOR. MOTOR HAS ONLY BEEN INSTALLED FOR 205.1HRS.SDR 2A6D20230807001Flange · crackedDAMAGE TO THE LH SIDE OF THE 7 DEG BULKHEAD FLANGE (P/N: 350A21-0980.22) IN THE FORM OF A CRACK AND A DENT AT THE FASTENER LOCATION. THE CRACK THROUGH THE FLANGE MEASURED TO BE APPROXIMATELY 0.65” IN LENGTH AND THE DENT DAMAGE MEASURED TO BE APPROXIMATELY 0.5”SDR 2A6D20230807002Bulkhead · chafedDAMAGE TO THE AFT BULKHEAD PANEL (P/N: 350A21-1570.20) IN THE FORM OF MULTIPLE CHAFED AREAS IN THE PART, MOST OF WHICH ARE FOUND ON THE TOPS OF THE STIFFENING FEATURES. THE LARGEST CHAFE WAS MEASURED TO BE APPROXIMATELY 1.40” X 0.70” AND 0.0075” DEEP.SDR QMLA2023072520054Stabilizer · crackedUPON DAILY INSPECTION, THE HORIZONTAL STABILIZER WAS FOUND CRACKED ON THE RIGHT HAND SIDE OF THE UPPER SKIN JUST PAST THE UPPER REINFORCEMENT SPAR.SDR QMLA2023060420046Cover · handler errorAIRSPEED INDICATOR FAILURE DUE TO PITOT TUBE COVER REMAINING ON PITOT TUBE. COVER REMAINS ON THE TUBE DURING THE DAY WHEN HELICOPTER NOT IN SERVICE TO PREVENT BUGS FROM ENTERING THE PITOT TUBE WHILE ON GROUND, WHICH HAS OCCURRED IN IMMEDIATE HISTORY.SDR QMLA2023031520014V-Belt · unknownPL DUE TO ILLUMINATION OF SERVO AND HYD2 CAUTION LIGHT. CAUTION LIGHTS ILLUMINATED WHILE AT CRUISE FLIGHT. PL CONDUCTED TO THE NEAREST AIRPORT. POST FLIGHT INSPECTION REVEALED THE BELT FOR THE BELT-DRIVEN HYDRAULIC PUMP HAD SEPARATED.SDR EVCA202212280001Floor Support · crackedTHERE IS AN APPROX 1/2 INCH CRACK ON LH RIB AT INBOARD OUTER EDGE OF THE FLOOR SUPPORT.SDR 2025FA0000124Elec Connector · fodVISUAL FOD DAMAGE TO THE AXIAL COMPRESSOR/MODULE M02 ON ARRIEL 2D ENGINE. UNKNOWN DAMAGE TO REST OF ENGINE MODULES PENDING INSPECTION. DONALDSON INLET BARRIER FILTER, MANUFACTURER PART # 121003-101, SERIAL # 0395. A SCREW FROM THE BYPASS SECTION OF THE INLESDR 2022FA0000493Belt · failedDURING FINAL APPROACH TO THE HOSPITAL IN LOVELAND CO, THE CREW REPORTED THE SMELL OF BURNT RUBBER. AFTER LANDING, THE PILOT INVESTIGATED AND FOUND THE A/C COMPRESSOR BELT SHREEDED. HE ALSO NOTED THAT THE DAMAGED A/C BELT CAUSED SIGNIFICATE DAMAGE TO THE HYRDAUSDR QMLA2022083020060None · noneCRACK FOUND AT L/H FRWARD CANOPY FRAME ATTACHMENT STRUCTURE. CRACK IS IN THE AREA "A" IDENTIFIED IN EC130T2 AMM TASK 53-21-00, 6-1. CRACK IS ROUGHLY 15MM (.59IN). FIELD LOCATION. NOT CURRENTLY EQUIPPED TO PERFOM REQUIRED REPAIR PER SAME AMM TASK 53-10-00,8-19.SDR 2022FA0000420Strainer · brokenAIRCRAFT FUEL FILLER STRAINER BROKE OFF AT SPOT-WELDS AROUND STRAINER RETAINING COLLAR CAUSING STRAINER BODY TO FALL INTO AIRCRAFT FUEL TANK.SDR EVCA202207070001Fan · fodBURNING RUBBER SMELL IN CABIN COMPARTMENT. FOUND SMALL BIRD INGESTED INTO CABIN COMPARTMENT BLOWER ASSEMBLY.
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