Turbomeca ARRIUS-1A
Service difficulty reports · 25
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 = 'ARRIUS1A' 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 = 'ARRIUS1A' 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 CA160303005Hinge Pin · loose(CAN) AFTER A 30 MINUTE FLIGHT ACFT WAS SHUTDOWN WAITING FOR CREW, DURING A WALK AROUND IT WAS NOTICED THAT THE PIANO HINGE WIRE THAT HOLDS THE ENGINE COWLING ONTO THE ACFT HAD MOVED FORWARD OUT OF THE HINGE AND THAT THERE WAS ONLY ABOUT 3-4 HINGES AND THE 2 BSDR CA150428010Exhaust Stack · loose(CAN) RETENTION CABLE FOUND BROKEN ON EXHAUST STACK. FLIGHT WITH BROKEN RETENTION CABLE NOT PERMITTED IAW EASA AD 2012-0022. INVESTIGATION FOUND STACK NOT MFG TO MFG SPECIFICATIONS PLACING STRAP UNDER TENSION. STRAP RETAINING RIVETS SHOULD HAVE A SPACING OSDR CA150429003Flange · loose(CAN) DURING AN UNRELATED UNSCHEDULED MX CHECK THE OUTPUT FLANGE WAS FOUND TO BE LOOSE, TOTAL LOSS OF TIGHTNESS. THE BEVEL GEARBOX WAS REMOVED, INSPECTED & REINSTALLED. SB 355-63.00.27 WAS COMPLETED WITH NEW FLANGE, STA-LOCK NUT & SECURING WASHER INSTALLED. SDR CA150408035Support · broken(CAN) FOLLOWING AN UNSCHEDULED CLEANING & INSPECTION OF THE OIL COOLER FAN OF OUR AS355N. BOTH BRACKETS PN 355A34-1040-05 & PN 355A34-1041-05 HOLDING THE FAN SHROUD WERE FOUND DAMAGED. BOTH ANGLE ATTACHMENT POINTS EQUIPPED WITH ANCHOR NUTS ON THE RT SIDE BRASDR CA150310008Hinge Pin · weak(CAN) AFTER DOING A TWO HOUR LINE PATROL, LANDED TO REFUEL. WALKED AROUND ACFT TO FIND NR 2 ENGINE COWL STILL LATCHED BUT HANGING OFF THE SIDE OF THE ACFT WITH NO SIGN OF THE TOP PIANO TYPE HINGE PIN. SUSPECTED HINGE DEPARTED IN FLIGHT AND UPON LANDING COWLISDR CA141008014Torque Tube · out of tolerance(CAN) ONE BORE OF HIGH TOLERANCE FLIGHT CONTROL LEVER FOUND TO BE OUT OF TOLERANCE AT NEW. MEASURED AT 8.6 MM, SHOULD BE 8.2MM. IF INSTALLED, THE LEVER WOULD MOST CERTAINLY OF FAILED. PN IS 350A27-2178-0601 FORM TRACKING NUMBER 10769896/13 NEW FROM AIRBUS HELSDR CA140904009Line · worn(CAN) DURING 144 MONTH INSPECTION, LT ENGINE OIL LINE WAS FOUND WORN ALMOST THROUGH AT FIREWALL CLOSEOUT. GROMMETS ARE PROVIDED IN THE AREA FOR PROTECTION, BUT WERE NOT SUFFICIENT IN PROTECTING THE ALUMINUM LINE. IF NOT CORRECTED, ENTIRE LOSS OF LT ENGINE OISDR CA140513004Engine · fire(CAN) AFTERSHUT DOWN THE PILOT NOTICED FLAMES COMING FROM ENGINE NR 2 EXHAUST AND MOTORED THE ENGINE IAW FLIGHT MANUAL TO PUT OUT THE FIRE. THIS ACTUALLY MADE THE FLAMES INCREASE AND THE FIRE WAS PUT OUT WITH THE ONBOARD FIRE EXTINGUSHER.SDR CA140128017Shaft · sheared(CAN) THIS GEAR SHAFT IS SPLINE INSIDE THE LT INTERMEDIATE GEAR OF THE COMBINING GEARBOX AND IS USED TO DRIVE THE LT HYDRAULIC PUMP. DURING A GROUND RUN FOLLOWING MAINTENANCE THE PILOT NOTICED THE HYD 1 LIGHT REMAINING ON. UPON REMOVAL OF THENR 1 LT HYDRAULISDR CA131118029Wire Harness · cracked(CAN) WATER ENTERED THE NR 1 ENGINE HARNESS THROUGH A CRACK IN THE SHIELDING AT THE TORQUEMETER CONNECTOR PLUG. THE WATER MADE ITS WAY DOWN THE HARNESS TO THE CONNECTOR AT THE DECU, DIGITAL ENGINE CONTROL UNIT. THE WATER CAUSED A DECU TO MALFUNCTION AND PUT SDR CA130905006Cable · broken(CAN) DURING 150 HR INSPECTION, EXHAUST RETENTION CABLE FOUND BROKEN. 78.8 HRS TTSN.SDR CA120813019Metering Unit · malfunctioned(CAN) RED "GOV" LIGHT CAME ON IN FLIGHT. FOLLOWED EMERGENCY PROCEDURES. RETURNED TO TAKEOFF ORIGIN, 5 MIN FLIGHT. AFTER LANDING THAT RED "GOV" LIGHT ILLUMINATED ON 4 ALPHA WARNING PANEL. UPON LANDING, THE FAILURE PANEL HAS CODE "FUEL", A-6020 AND B-003. SDR CA101110007Nut · loose(CAN) PILOT MADE PRECAUTIONARY LANDING SHORTLY AFTER TAKEOFF FROM BASE IN AIRPORT INFIELD DUE TO A SUDDEN ABNORMAL VIBRATION. UPON INSPECTING THE AIRCRAFT IT WAS DETERMINED THAT THE INPUT PINION/ROTOR BRAKE FLANGE NUT HAD BECOME LOOSE. FURTHER INSPECTION REVSDR ASMF201007003Access Door · damagedDURING TRANSIT CHECK A BIRD STRIKE WAS DETECTED BETWEEN SLAT NR 9 AND 10. MX PERFORMED A BIRD STRIKE INSP IAW 05-51-18 DETECTING DAMAGES IN ANTI ICE RELEASE ACCESS DOORS SLAT. THE RT WING SLAT LEADING EDGE NR 9 WAS REPLACED IAW DWG NR 114W4565 AND INSTALLED FASDR CA090702004Electrical Sys · malfunctioned(CAN) INVESTIGATION INTO INADVERTENT LOSS OF 2 SLUNG LOADS CLOSE TO GROUND WITH NO DAMAGE, REVEALED THAT THE CAROUSEL RELAY PROVIDES AN UNANTICIPATED 6 TO 9 VOLTS VDC TO PIN C OF THE UTILITY CONNECTION ON THE BELLY OF THE AIRFRAME WHEN IT SHOULD ONLY BE SUPPLISDR 2008FA0000891Coupling · misinstalledENGINE TO MAIN TRANS COUPLINGS FOUND TO BE INCORRECTLY ASSEMBLED. THS WAS FOUND DURING A PRE-FLIGHT INSP. THE COUPLINGS HAVE NOW BEEN ASSEMBLED CORRECTLY. (K)SDR IJA2006F00000Bearing · failedAC ON NORMAL FLIGHT. AT END OF FIRST LEG OF FLIGHT, PILOT SHUTDOWN THE ENGINES. PILOT THEN NOTICED A NOISE NEAR THE REAR OF AC. MAINT WAS NOTIFIED AND AC WAS GROUNDED UNTIL FURTHER NOTICE. AC WAS MOVED BY TRUCK TO HANGER. DISASSEMBLY WAS CONTINUED AND FOLLSDR IJA2005F00000Starter Gen · vibrationSTARTER GEN VIBRATION WAS CHECKED AFTER A NR 1 ENGINE EXHAUST PIPE WAS FOUND CRACKED. VIBRATION WAS ABOVE LIMITS AND THE STARTER WAS REMOVED AND THE STARTER GEN ADAPTER WAS FOUND TO HAVE 2 MOUNTING FLANGES BROKEN OFF AND ONE CRACKED. THINK THAT THE STARTER GSDR IJA2005F00002Exhaust Pipe · vibrationSTARTER GEN VIBRATION WAS CHECKED AFTER A NR 1 ENGINE EXHAUST PIPE WAS FOUND CRACKED. VIBRATION WAS ABOVE LIMITS AND THE STARTER WAS REMOVED AND REPLACED WITH O/H STARTER GEN. SERVICEABLE EXHAUST PIPE WAS INSTALLED. (CE07200506287) (K)SDR IJA2005F00003Starter Gen · vibrationSTARTER GEN VIBRATION WAS CHECKED AFTER A NR 1 ENGINE EXHAUST PIPE WAS FOUND CRACKED. VIBRATION WAS ABOVE LIMITS AND THE STARTER WAS REMOVED AND REPLACED WITH O/H STARTER GEN. (K)SDR IJA2005F00001Exhaust Pipe · failed(3) OUT OF (4) STRUTS THAT HOLD THE OUTSIDE PART OF THE EXHAUST ON FAILED. TT OF THE PART IS UNKNOWN. MFG THINKS THE PROBLEM IS RELATED TO A HIGH VIBRATION IN THE STARTER GEN. THE VIBRATION LEVEL WAS .04 WHICH IS WELL BELOW THE LIMIT. (CE07200502200) (K)SDR BAQA094141Clock · intermittentCLOCK WORKS INTERMITTENTLY AND THEN STOPS, WORKS THEN STOPS. REPLACED WITH SERVICABLE UNIT, 04/19/2004.SDR BAQA093734Indicator · ratchetingINDICATOR IS RATCHETY AND STICKY. REPLACED WITH SERVICABLE UNIT. 03/11/2004SDR HEEA088385Fuel Control · malfunctionedFUEL CONTROL PRODUCING HARD START. TO BE SENT TO VENDOR.SDR ALG2003F00023Sensor · malfunctionedDURING TAKE OFF, TWO MINUTES AFTER TAKEOFF FROM BASE, NR 1 ENGINE OVERSPEED CAUTION LIGHT FLICKERED REPEATEDLY (BRIGHT NOT DIM). AIRCRAFT WAS RETURNED TO BASE. UPON LANDING THE MECHANIC REMOVED AND REPLACED THE NR 1 ENGINE SPEED SENSOR. AIRCRAFT WAS FUNCTIO
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