Turbomeca ARRIEL-1D1
Service difficulty reports · 933
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 = 'ARRIEL1D1' 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 = 'ARRIEL1D1' 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 CA090402011Spar · cracked(CAN) ON INSP OF VERTICAL FIN FOUND ONE SMOKING RIVET ATTACHED TO THE SPAR OF THE LOWER VERTICAL FIN. FROM THERE, FOUND THE CRACK ON THE CENTRAL SPAR. REMOVED FIN AND SENT IT OUT FOR REPAIR. THEY INSTALLED A NEW SPAR PN 350A14-1115-22. THE FIN WAS REINSTALLEDSDR CA090323001Bushing · cracked(CAN) CRACKS FOUND IN BUSHING OF TAIL ROTOR PITCH LINKS, PN 350A33-2145-01 DURING ROUTINE INSPECTION.SDR RMX029H3127223Frame · crackedDURING A 500 HR INSP OF THE AIRFRAME THE FUSELAGE AFT FRAME USED FOR TAILBOOM ATTACHMENT WAS INSPECTED. THE TAILBOOM WAS REMOVED BECAUSE OF A SUSPECTED CRACK WHICH WAS FURTHER INSPECTED USING THE DYE PENETRANT INSP METHOD. A CRACK WAS VERIFIED TO HAVE A LENGTHSDR CA090218008Drain Line · disconnected(CAN) DURING ROUTINE MX IT WAS DISCOVERED THAT FUEL WOULD DRAIN OUT OF THE FUSELAGE AFTER DOING A WATER CHECK ON THE MFG AIRFRAME FUEL FILTER BOWL. FURTHER INVESTIGATION REVEALED THAT THE PLASTIC SCUPPER UNDER THE FLOOR WHERE THE FUEL FILTER WAS MOUNTED HAD SNSDR CA090309008Filter · unserviceable(CAN) DURING LAST FLIGHT INSP, THE 3 M/R HYD ACCUMULATORS WERE FOUND EXPANDED BEYOND THEIR NATURAL SHAPE. AT THIS TIME IT WAS ALSO NOTED THAT NUMBEROUS HYD FITTINGS WERE WEEPING FLUID. FROM EXPERIENCE IT WAS DETERMINED THAT THE HYD REGULATOR/FILTER BLOCK (MANISDR QMLA2009020403004Fuel Control · leakingDURING PREFLIGHT FOUND FUEL DRIPPING FROM DRAIN LINE LOCATED ON LOWER LEFT BELLY OF FUSELAGE, DRAIN LINE COVERED AND DRENCHED WITH JET FUEL, AREA FWD OF DRAIN LINE AROUND CROSS TUBE WET ALSO. FWD EDGE OF SX5 HAS A WET RESIDUE ON IT. FIBERGLASS COVER FOR REMOSDR CA090213007Pedal · cracked(CAN) WHILE CARRYING OUT A T-INSPECTION THE RT PEDAL PILOT`S SIDE WAS FOUND TO BE CRACKED. THE LOCATION OF THE CRACK IS AFT SIDE OF PEDAL OR PILOT`S FOOT SIDE IN THE CORNER OF THE RT ANGLE BEND OF PEDAL.SDR HDNA200901230002Windscreen · failedAT CRUISE FLIGHT AT NIGHT, AT APPROX 1500FT ALTITUDE, A SUDDEN BLAST IN THE ACFT WAS FELT. THE PILOT REALIZED THAT HE WAS THEN INJURED DUE TO A BIRD STRIKE THAT PENETRATED THE LT AND RT WINDSCREENS. PILOT REGAINED CONTROL OF THE ACFT AND INITIATED AN EMERGENCYSDR CA090107012Nozzle · unserviceable(CAN) WHILE IS CRUISE FLIGHT A LOUD BANG WAS HEARD AND A LARGE AMOUNT OF INSULATION BLEW OUT OF THE DEFROST SYSTEM. RESIDUAL AIRFLOW WAS SUFFICIENT TO KEEP A PORTION OF THE WINDSHIELD CLEAR AND THE FLIGHT CONTINUED.SDR CA090106008Nozzle · unserviceable(CAN) WINDSHIELD ICED UP IN FLIGHT CAUSING REDUCTION IN PILOTS VISIBILITY DURING FLIGHT AND SUBSEQUENT LANDING. VENTILATION TUBE WAS PINCHED AT A 90 DEGREE ANGLE AND THIS ALLOWED PRESSURE AND HEAT TO BURST SIDE WALL OF VENT TUBE. DEFROST AIR WAS UNABLE TO FLOSDR CA081121012Coupling Sleeve · worn(CAN) DURING DISASSEMBLY FOR OTHER WORK THE HYD PUMP WAS REMOVED AND THE SPLINE DRIVE WAS FOUND EXTREMELY WORN. PART S40 WAS FOUND TO HAVE ALMOST NO SPLINE AT ALL REMAINING AND THE JOINING HYD PUMP PN A5026780 HAD IT`S SPLINES WORN TO HALF THEIR NORMAL WIDTH. SDR CA081117004Bearing Race · cracked(CAN) A 12 YEAR INSP WAS BEING CARRIED OUT ON THE HELICOPTER. 2 CRACKS WERE FOUND ON THE INNER RACE OF A BALL BEARING ASSY. THE CRACKS ORIGNALLY STARTED FROM THE RIVET HOLES. THE BEARING ASSY/SUPPORT ATTACH THE INNER RACE OF BEARING BY 4 RIVETS TO THE PILOT`SSDR CA081202004Control Tube · failed(CAN) EVERY 12 YEARS THE HELICOPTER GOES INTO THE SHOP FOR A MAJOR INSPECTION AS PART OF THE INSP, IS A HARDNESS TEST ON THE COLLECTIVE CONTROL TUBE. THE TUBE IS TESTED AND IT FAILED THE HARDNESS TEST. THE HARDNESS TEST REQUIRED IS 230 HV-5 KG LOAD. THE AVESDR HXS2008F00000Bracket · crackedON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON BOTH THE RT AND LT SIDES, THERE IS A BRACKET THAT IS PART OF THE FOOT PEDAL BELLCRANK ASSY, THE LT BRACKET PN 350A21136324, HAS A CRACK IN IT. THE RT BRACKET, SAME PN, CRACKED ALL THE WAY THROUGH WHICH ALLOWED SDR HXS2008F00001Bellcrank · crackedON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON BOTH THE RT AND LT SIDES, THERE IS A BRACKET THAT IS PART OF THE FOOT PEDAL BELLCRANK PN 350A27-1170-00, TO GO OUT OF ALIGNMENT AND CONTACT THE SURROUNDING SUPPORT STRUCTURE THUS CAUSING A .2500 INCH GROOVE INTSDR HXS2008F00002Bracket · crackedON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-1313-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BSDR HXS2008F00003Bracket · crackedON BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A211183-24, HAS A CRACK IN IT. REMOVED THE BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BESDR HXS2008F00004Bracket · crackedON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-1363-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS SDR HXS2008F00005Bracket · crackedON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-1363-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BSDR HXS2008F00006Bracket · crackedON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-13636-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS SDR HXS2008F00007Bracket · crackedON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-13636-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS SDR HXS2008F00008Bracket · crackedON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-13636-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS SDR CA080813012Turbine · failed(CAN) HELICOPTER WAS RETURNING TO AIRPORT, ENGINE CHIP LIGHT CAME ON, FOLLOWED SHORTLY BY A POPPING SOUND FROM ENGINE, A VIBRATION IN AIRFRAME & LOW ROTOR HORN. AN AUTOROTATION INITIATED & WHEN PILOT FLARED TO LAND, NOTICED ENGINE STILL DEVELOPING POWER. ACFTSDR 2008FA0000511Starter Gen · failedWHILE ACFT WAS CIRCLING AT A SCENE CALL, THE CREW WAS STARTING TO DETECT WHAT SEEMED TO BE BURNING PLASTIC FOLLOWED BY A GENERATOR CAUTION LIGHT. AC LANDED BACK AT HOSPITAL PAD WITHOUT INCIDENT. MAINT WAS DISPATCHED. IT WAS FOUND THAT THE STARTER GENERATOR HASDR CA080728009Blade · cracked(CAN) FOUND T/R BLADE CRACKED NEAR TIP OF BLADE AND TRAILING EDGE ON DAILY INSPECTION. BLADE REMOVED FOR EVALUATION BY MFG.SDR CA080724006Fuel Control · failed(CAN) MAIN ROTOR RPM KEPT DECREASING AFTER ADJUSTMENT, OIL ALSO FOUND IN THE INPUT SEAL DRAIN TUBE. NO LONGER ABLE TO ADJUST IAW MM. UNIT REPLACED WITH SERVICEABLE FCU AND DEFECTIVE UNIT SENT TO MFG FOR INVESTIGATION AND WARRANTY REPAIR.SDR CA080722003Gimbal Pin · damaged(CAN) ACFT WAS INSPECTED FOLLOWING A HARD LANDING, MAIN AND TAIL ROTOR STRIKES IAW MET 05.53.00.603, 604 AND 605. GIMBAL PINS (ALL 4 OF THEM) WERE SENT ALONG WITH OTHER PARTS FOR NDT (NO REQUIREMENT TO CHECK THE GIMBAL PINS AFTER AN INCIDENT), AND 3 OF 4 WERESDR CA080722005Stop · cracked(CAN) ON ROUTINE MAST RECONDITIONING AND INSP (6 YEAR INSP REQUIREMENT), THE RING WAS SENT FOR NDT ALONG WITH THE REST OF THE PARTS FROM THE ASSY (NO NDT REQUIREMENT FOR THE RING AT ANY POINT, OR FOR ANY PART OF THE ASSY AT THE 6 YEAR INSP). THERE WAS A STRESSSDR CA080717005Servo · malfunctioned(CAN) ON A EUROCOPTER AS350 B2 DURING HYDRAULIC TEST PROCEDURES FOR FIRST FLIGHT OF THE DAY THE PILOT ENCOUNTERED THE CYCLIC BEING DRIVEN HARD OVER TO THE LT STOP. DURING TROUBLESHOOTING THIS PROBLEM WAS NOT EASILY REPEATABLE EVERYTIME THE TEST WAS COMPLETED.SDR 2008FA0000482Belt · brokenIMMEDIATELY AFTER TAKEOFF AND LEVELING FOR CRUISE, THE AIR CONDITIONER WAS TURNED ON. WITHIN A SHORT TIME A STRONG ACRID SMELL WAS PRESENT IN THE AIRCRAFT. THE SOURCE OF THE SMELL WAS UNKNOWN IN FLIGHT. THE AIRCRAFT WAS IMMEDIATELY LANDED NEXT TO A HARD-SURFSDR CA080707009Diffuser · cracked(CAN) DURING MAINT FOR REPLACEMENT OF THE T2 BLADES AND WHEEL, AFTER REMOVING OUTER CASING OF THE M03 THE OUTSIDE SURFACE OF THE DIFFUSER WAS FOUND CRACKED FROM ONE SIDE TO THE OTHER. A SERVICEABLE M03 WAS INSTALLED AND THE HELICOPTER WAS RETURN TO SERVICE. DSDR CA080707012Skin · damaged(CAN) THE HELICOPTER EXPERIENCED A HARD LANDING AFTER BEING PUSHED SIDEWAYS BY A GUST OF WIND. THE RT SKID CAUGHT THE GROUND FIRST AND THE HELICOPTER STARTED TO YAW SEVERLY, PILOT DROPPED COLLECTIVE AND LANDED THE HELICOPTER IMMEDIATELY. THE TAILBOOM SUSTAINEDSDR CA080716004Freq Adapter · worn(CAN) WORN TO SERVICEABLE LIMITS, RUBBER DEBONDING FROM ITS METHC SURFACE. REPLACED WITH A NEW SET.SDR QML2008F00001Drain Valve · leakingENROUTE TO SCENE, ONE CREWMEMBER DETECTED A FUEL ODOR. THERE WERE NO UNUSUAL COCKPIT INDICATION SUCH AS EXCESSIVE FUEL CONSUMPTION; BUT, IAW BRIEFING, THE PILOT ABORTED THE FLIGHT AND RETURNED TO BASE. MAINT FOUND A DRAIN VALVE ON THE FUEL FILTER LEAKING. (SDR QML2008F00003Drain Valve · leakingENROUTE TO SCENE, CREW MEMBER DETECTED A FUEL ODOR. THERE WERE NO UNUSUAL COCKPIT INDICATIONS SUCH AS EXCESSIVE FUEL CONSUMPTION, BUT, IAW BRIEFING THE PILOT ABORTED THE FLIGHT AND RETURNED TO BAS. MAINTENANCE FOUND A DRAIN VALVE ON THE FUEL FILTER LEAKING. SDR CA080606008Control Lever · incorrect(CAN) GOVERNOR LEVER P/N 350A57-1476-20 WAS FOUND ON FCU WHERE LEVER P/N 350A57-1472-20 SHOULD HAVE BEEN. UPON CONFIRMATION WITH MFG THIS WAS CONFIMED. AS THIS ACFT CAME TO US, ON B2 S/N 1685 WE ASSUMED THAT THE INSTALLATION WAS CORRECT. THE RIGGIN WAS WAY OUTSDR CA080530003Servo · worn(CAN) STIFF FLIGHT CONTROLS IN ALL RANGE OF TRAVEL, IN HOVER, CRUISE, LANDING.SDR CA080611006Engine · making metal(CAN) WHILE DOING AIRBORNE SURVEY WORK (BIRD TOWING), ENGINE CHIP LIGHT ILLUMINATED. HELICOPTER DESCENDED TO VALLEY BOTTOM AND MADE A PRECAUTIONARY LANDING. UPON LANDING, THE ENGINE MOMENTARILY DECELLERATED AND THEN RE-ACCELERATED. ENGINE WAS SHUTDOWN AND RAPSDR CA080601001Module · noisy(CAN) SQEALING NOISE COMING FROM ENGINE. SHUTDOWN AFTER FLIGHT, SUSPECT TURBINE BLADE RUB. MODULE 2 AND MODULE 3 REMOVED AND SENT TO MFG.SDR IJA2008F00000Bulb · brokenON MAY 17, 2008, THE PILOT REPORTED ELECTRIC SYSTEM FAILURE AND MADE A PRECAUTIONARY LANDING DUE TO THE FAILURE, IN A FIELD. ON INSPECTION OF THE AIRCRAFT, MAINTENANCE FOUND THE AC BATTERY DEAD, INSTALLED NEW/ SERVICEABLE BATTERY. GROUND RAN AIRCRAFT TO TESTSDR IJA2008F00001Circuit Breaker · failedON MAY 17, 2008, THE PILOT REPORTED ELECTRIC SYS FAILURE AND MADE A PRECAUTIONARY LANDING DUE TO THE FAILURE, IN A FIELD. ON INSP OF THE ACFT, MAINT PERSONNEL FOUND THE ACFT BATTERY DEAD, INSTALLED NEW/ SERVICEABLE BATTERY. GROUND RAN AC TO TEST SYS. ON STSDR 436905162008Control Lever · misalignedTHE PILOT RAN THE HELICOPTER UP FOR NEARLY 20 MINUTES TESTING THE NEW RADIOS, AND THE AIR CONDITIONING UNIT. JUST AFTER DEPARTURE, AND IN CLOSED TRAFFIC, I STARTED TO SMELL AND SEE SMOKE IN THE COCKPIT. I RETURNED TO THE RAMP AND SHUTDOWN. SOURCE OF THE SMOKE SDR CA080516013Stop · broken(CAN) SUPPORT WAS FOUND BROKEN DURING THE AFTER LAST FLIGHT INSPECTION BY THE PILOT. NO SIGN OF FLIGHT CONTROL PROBLEM, VIBRATION OR NOISE WAS NOTICED. WORST CASE SCENARIO, IF THE DROOP RING GOT STUCK BETWEEN ONE BLADE AND THE MAST, IT COULD BE FATAL SINCE ONLSDR 401104242008Blower · burnedWHILE IN CRUISE FLIGHT, RETURNING TO BASE (WITH NO PATIENT ON BOARD) THE MED CREW REPORTED A SMELL OF BURNING RUBBER COMING OUT OF THE AIR CONDITIONING VENTS. PILOT PERFORMED A PRECAUTIONARY LANDING WITHOUT INCIDENT IN A FIELD. MAINT INSPECTED THE A/C SYSTEM ASDR KNK2008F00000Manifold · cokedFUEL COKING DEPOSITS FORMED IN FUEL INJECTION MANIFOLD AIR/FUEL LABRYNTH SEAL, CAUSING DRAG ON AXIAL ROTATING COMPONENTS OF THE ENGINE ASSY, PREVENTING THE START SEQUENCE OF THE ENGINE. (K)SDR LV62008F00000Spacer · damagedRETAINING RING "SPACER" APPARENTLY BROKE AND AS IT SPUN AROUND, CAUGHT M/R SHAFT CHIP DETECTOR AND BROKE THE END OF IT OFF THUS TURNING ON "CHIP LIGHT" IN COCKPIT. AC TURNED AROUND AND LANDED AT BASE. FOUND CHIP DETECTOR BROKEN, TRANSMISSION APART AND SUBSSDR 2008040423235Fuel Control · faultyTHE PILOT STATES THAT THE AC LIFTED OFF AND BEGAN A CLIMB TO CLEAR OBSTACLES AND UPON REACHING 100 FEET AGL, A DISTINCT CHANGE IN ENGINE SOUND WAS DETECTED ALONG WITH A SLIGHT YAW TO THE RT FROM THE LOSS OF POWER. THE PILOT IMMEDIATELY LOWERED THE COLLECTIVE TSDR CA080219002Servo · malfunctioned(CAN) ALSO APPLIES TO SERVO SC5081-1 S/N 229 TSN 8917.4 TSO 2342.6 AND SERVO SC5082-1 S/N 361 TSN 5634.5 TSO 2345.1. A/C WAS APPOACHING FOR LANDING AND WHEN THE COLLECTIVE WAS REDUCED THERE WAS A VIOLENT VIBRATION, SEVERE ENOUGH TO CAUSE CONCERN ABOUT LOSS OF SDR B3OR2008030Fcu · leakingFUEL CONTROL UNIT IS LEAKING FUEL FROM A DIAPHRAM BREATHER HOLE IN THE CASING. THE LEAKING HOLE IS LOCATED BELOW AND SLIGHTLY IB OF THE PRESSURE REDUCING VALVE ATTACHED TO THE FCU.
FUEL LEAK WAS INITIALLY OBSERVED AS A SEEP, PROGRESSING TO A LOW PRESSURE STESDR CA080205005Ball Joint · worn(CAN) WHEN THROTTLE WAS RETARDED DURING ENGINE START, T4 CONTINUED TO INCREASE. EMERGENCY SHUTOFF PULLED AND ENGINE MOTORED AS T4 REACHED 900C FOR 2 SECONDS. INVESTIGATION FOUND THE THROTTLE LINK DISCONNECTED BUT THE LOCKING PIN WAS PROPERLY ENGAGED AND IN TH
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