Aerospatiale AS350BA
Service difficulty reports · 958
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 aircraft_model_key = 'AS350BA' 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 aircraft_model_key = 'AS350BA' 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 2025FA0000754Capacitor · brokenDURING ROUTINE FLIGHT OPERATION THERE WAS A SUDDEN DECREASE IN ENGINE POWER AND A RISE IN VIBRATION WAS FELT, SO THE AIRCRAFT MADE A PRECAUTIONARY UNSCHEDULED LANDING AND SHUT DOWN WITHOUT INCIDENT. UPON INSPECTION OF THE AIRCRAFT IT WAS FOUND THAT ONE OF TWO SDR 2025FA0000669Module · making metalAFTER LANDING, THE PILOT IDENTIFIED AN ABNORMAL SOUND FROM THE REAR PORTION OF THE ENGINE. THE PILOT RECORDED A VIDEO TO CAPTURE THE SOUND. AFTER THE ROTOR STOPPED SPINNING, THE PILOT CALLED MAINTENANCE TO INVESTIGATE. THE REDUCTION GEAR CHIP PLUG WAS CHECKED,SDR 2020F00027Pump · strippedLOSS OF HYDRAULIC PRESSURE IN FLIGHT, EMERGENCY LANDING OCCURRED. AFTER INSPECTING HYDRAULIC SYSTEM FOUND HYDRAULIC PUMP SPLINES WORN AND NO LONGER FUNCTIONAL.SDR CA190312016Bearing · making metal(CAN) GEARBOX GENERATING METAL FLAKE. GEARBOX REPAIRED BY ORIGINAL EQUIPMENT MANUFACTURER WITHIN 8 HOURS. GEARBOX REMOVED AND RETURNED TO ORIGINAL EQUIPMENT MANUFACTURER COMPONENT SHOP FOR FURTHER INVESTIGATION AND REPAIR.SDR CA190307005Leaf Spring · cracked(CAN) WHILE CREW WAS LOWERING FORWARD BELLY COWLING, INSIDE THE HANGAR, A LOUD BANG OCCURRED AND THE COWLING WAS PULLED OUT OF THEIR HANDS. THE RIGHT HAND ANTI-VIBRATION WEIGHT ASSEMBLY FELL ON THE FLOOR. UPON FURTHER INSPECTION A LEAF WAS FOUND TO HAVE CRACKESDR CA190301007Line · cracked(CAN) AIRCRAFT START WAS ATTEMPTED AND ABORTED DUE TO THE ENGINE HANGING DURING START. UPON INVESTIGATION BY AN ENGINEER IT WAS DISCOVERED THAT THE LEFT HAND START INJECTOR LINE WAS LEAKING AT THE BACK OF THE `B` NUT. ONCE REMOVED A CRACK WAS FOUND IN THE LINESDR 2019F00099Line · rupturedPRIMARY OIL LINE FROM ENGINE RUPTURED SOON AFTER TAKE OFF. PILOT NOTICED OIL PRESSURE LIGHT, AND IMMEDIATLY RETURNED TO BASE. UPON LANDING OIL PRESSURE GAUGE AND TORQUE METER READ ZERO. EXAMINATION OF REMAINING OIL LINE SHOWED SLIGHT PIMPLES ALONG LENGTH OF THSDR 2017F00209Pump · failedHYDRAULIC PUMP AND PULLEY SPLINES WORN BEYOND CAUSING, NO HYDRAULIC PRESSURE TO FAIL.SDR ISH2017F00002Bearing · crackedTHE SET OF 3 SPHERICAL BEARINGS WERE FOUND TO BE CRACKED BEYOND LIMITS. THE PARTS WERE INSTALLED IN 2014 BUT ONLY HAD A TOTAL TIME OF 1562.2 HRS. THE PART HAS A LIFE LIMIT OF 6400 HRS, THUS THE PARTS OPERATED FOR LESS THAN 25% OF THEIR EXPECTANCY. THE DEFECSDR ISH2017F00001Bearing · crackedTHE SET OF 3 SPHERICAL BEARINGS WERE FOUND TO BE CRACKED BEYOND LIMITS. THE PARTS WERE INSTALLED IN 2014 BUT ONLY HAD A TOTAL TIME OF 1562.2 HRS. THE PART HAS A LIFE LIMIT OF 6400 HRS, THUS THE PARTS OPERATED FOR LESS THAN 25% OF THEIR EXPECTANCY. THE DEFECSDR ISH2017F00000Bearing · crackedTHE SET OF 3 SPHERICAL BEARINGS WERE FOUND TO BE CRACKED BEYOND LIMITS. THE PARTS WERE INSTALLED IN 2014 BUT ONLY HAD A TOTAL TIME OF 1562.2 HRS. THE PART HAS A LIFE LIMIT OF 6400 HRS, THUS THE PARTS OPERATED FOR LESS THAN 25% OF THEIR EXPECTANCY. THE DEFECSDR CA151105002O-Ring · cut(CAN) ACFT HAD A CHIP INDICATION IN FLIGHT, THE PILOTS LANDED AT THE COMPANY BASE. THE ENGINEERS INVESTIGATED AND FOUND MINOR FUZZ ON THE ADC SCAVENGE OIL FILTER CHIP PLUG. THE CHIP PLUG WAS CLEANED AND THE ACFT RETURNED TO SERVICE IAW MM. THE ACFT WENT OUT SDR CA150925012Hydraulic Line · leaking(CAN) PILOT NOTICED THE LINE WAS LEAKING AT THE LOWER END, THE ENGINEER ORIGINALLY SUSPECTED THE B-NUT AND TIGHTENED THE LINE. THIS DID NOT STOP THE LEAK SO THE ENGINEER HAD A MORE DETAILED LOOK AT THE LINE AND FOUND THE HYDRAULIC FLUID WAS COMING OUT OF THESDR CA150925006Fuel Control · faulty(CAN) ACFT WAS STARTED FOR A COMPANY FLIGHT. DURING RUN UP CHECKS, THE EOS, ELECTRONIC OVERSPEED SENSOR, CHECK WAS COMPLETED SATISFACTORILY. HOWEVER, UPON RETURNING THE EOS SWITCH TO THE OFF, NORMAL, POSITION, THE ENGINE AND NR SPEEDS RAPIDLY SURGED TO APPROXISDR CA150721003Bolt · loose(CAN) THE MAST CHIP PLUG, REQUIRED MORE FORCE THEN ORDINARY TO BE PULLED OUT. THE TIP OF THE CHIP PLUG WAS FOUND CHOPPED OFF AND THE INTERNAL MAGNET OF THE CHIP DETECTOR WAS APPARENT. THE AICFT WAS THEN GROUNDED. THE TRANSMISSION WAS OPENED ON SITE. RIGHT AFSDR 2014FA0000542Capacitor · brokenPILOT NOTICED N1 DROOPING AFTER TAKEOFF, LANDED BACK ON THE PAD, VISUAL INSPECTION OF THE ENGINE WAS PERFORMED, NOTICED THE SMALL CAPACITOR LOOKED SLIGHTLY OFF CENTER, SHOULD LOOK PERPENDICULAR TO THE ENGINE, AS A SLIGHT HAND PRESSURE WAS APPLIED THE UNIT BROSDR CA140808009Engine · power loss(CAN) ON DEPARTURE, AT AN ELEVATION OF 900FT AGL PILOT NOTICED LOSS OF POWER AND SUBSEQUENT LOW ROTOR HORN ALARM. PILOT ENTERED AUTO-ROTATION, A/C LANDED WITH MINOR DAMAGE AND NO INJURY TO THE PILOT. PLUMES OF WHITE SMOKE WERE SEEN BY WITNESSES COMING FROM EXSDR CA140724011Armature · shorted(CAN) WHILE BUCKETING WATER, PILOT SMELLED ELECTRICAL BURNING AND THE GENERATOR FAIL LIGHT ILLUMINATED, LANDED. NOTICED BURNED GROUND WIRE BETWEEN STARTER GEN AND FIREWALL GROUND LUG. NEW STARTER GEN INSTALLED, NO DEFECTS NOTED. SENT FAILED STARTER GEN TO ASDR CA140626002Shaft · worn(CAN) WHEN THE TAIL ROTOR WAS ROTATED CLOCKWISE OR COUNTER CLOCKWISE, A NOISE WAS DETECTED. AFTER INVESTIGATION, IT WAS DISCOVERED THAT A PLAY EXISTED AT THE ASSY POINT OF THE FRONT SHAFT AND THE FRONT FLANGE.SDR CA140505012Fuel Control · malfunctioned(CAN) FCU INSTALLED AND ADJUSTED IAW MFG RECOMMENDATIONS DURING GROUND RUNS. LEAK TESTS CARRIED OUT SATISFACTORILY. FLIGHT TESTING CARRIED OUT FOR POST-MAINTENANCE CHECKS. DURING THIS TESTING PERIOD, THE ACFT WAS SHUTDOWN AT ONE POINT AND FAILED TO RESTART. SDR CA131107007Rod · cracked(CAN) DURING A VISUAL INSPECTION, A CRACK WAS FOUND AT THE AFT END OF THE TAIL ROTOR ACTUATING ROD, WHERE THE BEARING IS SWAGED.SDR CA131107005Reservoir · contaminated(CAN) WATER AND ICE CONTAMINATION WAS FOUND IN THE HYDRAULIC RESERVOIR TAPERED FILTER.SDR CA131107004Reservoir · contaminated(CAN) WATER AND ICE CONTAMINATION WAS FOUND IN THE HYDRAULIC RESERVOIR TAPERED FILTER.SDR CA131107009Starflex · cracked(CAN) VISUAL ROUTINE INSPECTION REVEALED CRACK ON ONE STARFLEX END-BUSHING SEALER.SDR CA131007026Power Supply · failed(CAN) THE STROBE LIGHT WAS NOTED AS BEING INTERMITTENT BY THE PILOT. UPON INVESTIGATION THE STROBE POWER SUPPLY HAD FAILED INTERNALLY. THE CIRCUIT BOARD APPEARS TO HAVE CAUGHT IN FIRE. THE WIRING TO THE STROBE LIGHT WAS INSPECTED FOR DAMAGE AND A NEW POWESDR CA130814002Transmitter · intermittent(CAN) ENGINE OIL PRESSURE GAUGE WAS INTERMITTENT. RESISTANCE CHECK OF TRANSMITTER FOUND IT TO BE OPEN CIRCUIT. REMOVED TRANSMITTER CASE TO FIND THAT INTERNAL WIRE WAS MISROUTED CAUSING IT TO BE PINCHED AND EVENTUALLY CUT THROUGH. TRANSMITTER REPLACED.SDR CA130624004Modulator · cracked(CAN) WHILE PERFORMING A 100 HRS INSPECTION, IT WAS NOTICED THAT THE BOTTOM ATTACHMENT ARM ON THE AIRFLOW MODULATOR WAS CRACKED. ONCE THE UNIT WAS REMOVED, THE ARM BROKE OFF WITH FINGER FORCE ONLY.SDR CA130621004Wire Harness · chafed(CAN) ENGINE POWER TURBINE MODULE INDICATING HARNESS WAS FOUND WORN BEYOND REPAIR DUE TO CHAFING AGAINST THE FDC/AEROFILTER INLET HOUSING. THERE WERE NO REPORTS OF INACCURATE OR LOST OF T4 INDICATION BY THE PILOT.SDR CA130318024Servo · contaminated(CAN) THE OPERATION HAD TO CONDUCT PILOT TRAINING WITH ACFT WHICH WAS PARKED OUTDOORS FOR THE LAST 4 DAYS. AFTER THE START WAS COMPLETED THE PILOT IN COMMAND FOUND THAT THE FORE AND AFT MOVEMENT OF THE CYCLIC SERVO WAS RESTRICTED IN THE FORWARD MOVEMENT. THSDR CA130318022Servo · malfunctioned(CAN) THE OPERATION HAD TO CONDUCT PILOT TRAINING, WHICH WAS PARKED OUTDOOR FOR THE LAST 4 DAYS. AFTER THE START WAS COMPLETED THE PILOT IN COMMAND FOUND THAT THE FORE AND AFT MOVEMENT OF THE CYCLIC SERVO WAS RESTRICTED IN THE FORWARD MOVEMENT. THE ACFT WAS SDR CA130306004Fuel Control · disconnected(CAN) FUEL LEVER WAS DISCONNECTED AT LINKAGE. LEVER POSITIONED IN OPEN POSITION DURING RIGGING REQUIREMENTS. LINKAGE RECONNECTED. AT NO TIME WAS THE FUEL SYSTEM FUEL LINES OPENED. THE NEXT ENGINE START ATTEMPT RESULTED IN FAILED START ATTEMPT. THE SYSTEM WASDR CA130131004Idler Gear · unsecure(CAN) DURING THE SCHEDULED 1800 HRS INSPECTION, THE 8 BOLTS ON THE TORQUE IDLER GEAR WERE FOUND LOOSE. THE GEAR ASSY AS TO BE REMOVED AND SENT FOR DETAILED INSPECTION. A PREVIOUS SDR WAS SUBMITTED DUE TO SIMILAR PROBLEM CAUSING AN EMERGENCY LANDING, WERE THESDR CA130205002Idler Gear · damaged(CAN) IN FLIGHT OPERATION INDICATION OF FIRST POSSIBLE LOW TORQUE AND THEN ENGINE CHIP AND OIL FILTER CHIP, FOLLOWED BY AS SOON AS POSSIBLE LANDING. 01-19-2013 TO DISCOVER BOTH CHIP PLUGS COVERED WITH METAL PARTICLES. ACFT WAS GROUNDED AND TRUCKED BACK TO MASDR CA121102002Servo · frozen(CAN) AFTER DEPARTING AIRPORT ON A LOCAL FLIGHT TO THE FORESTRY PAD, PARTIAL CONTROL LOSS WAS EXPERIENCED. THE FORWARD CYCLIC MOVEMENT WAS IMPEDED AND IT WAS NOT POSSIBLE TO MOVE THE CYCLIC INTO THE FORWARD QUADRANT OF ITS MOTION. SUSPECTING ICE ON THE CYCLISDR CA120926010Bolt · sheared(CAN) WHILE CONDUCTING A 600 HR DETAILED CHECK OF THE M/R HEAD AND M/R HEAD STARFLEX. REPLACEMENT 1 OF THE M/R ATTACH BOLTS WAS FOUND SHEARED AND CORRODED. BOLT HAS A LIFE OF 3000 HRS, TTSN = 2393.4, ALL 12 BOLTS REPLACED WITH NEW.SDR CA120622003Bushing · worn(CAN) WHEN THE TAIL ROTOR BLADES WERE REMOVED FOR SCHEDULED MX. THE CONTROL SPIDER ASSEMBLY WAS FOUND TO BE MOVING LOOSELY ON THE SHAFT. AFTER FURTHER INVESTIGATION IT WAS FOUND THAT THE SPHERICAL BEARING AT THE END OF THE TAIL ROTOR CONTROL TUBE WAS LOOSE. SDR CA120523011Bearing · leaking(CAN) EXCESSIVE GREASE LEAKAGE FROM MAIN ROTOR SWASHPLATE BEARING FOUND AT ALF AFTER LAST FLIGHT, INSPECTION. SWASHPLATE CHECK FOR OVERTEMP, NO ABNORMAL TEMPERATURE AFTER 15 MINUTE GROUND RUN. SWASHPLATE BEARING ROTATION CHECK FOR ABNORMAL FRICTION/ROUGHNESSSDR QMLA2012050512073Unknown · unknownAFTER DEPARTING, LEVELED OFF AT 1500 MSL, ENGINE TEMPERATURE APPROXIMATELY 600 DEGREES, ROTOR & ENGINE IN GREEN RANGE. HEARD A LOUD BANG FOLLOWED BY AN IMMEDIATE SHUTTER AND RT YAW. LOWERED COLLECTIVE IMMEDIATELY AND TURNED BACK TOWARD DEPARTURE, REGAINED ASDR QMLA2012041612061Bleed Valve · failedIN CRUISE, AT APPROX 78 PERCENT TORQUE, 110 KIAS, AND 2000 FT MSL, EXPERIENCED A VERY LOUD NOISE & HARD JERK IN YAW AXIS OF AT LEAST 45 DEGREES TO RT. REPLACED ENGINE BLEED VALVE. TEST FLIGHT ACCOMPLISHED. NO DEFECTS REPORTED, ACFT RETURNED TO BASE.SDR CA120403001Magnetic Seal · leaking(CAN) LEAK DISCOVERED DURING ALF INSPECTION, ENGINE DECK COVERED WITH ENGINE OIL, COMING FROM REAR OF ENGINE, MODULE 5 MAG SEAL. OIL CONSUMPTION STILL WITHIN LIMITS, BUT MAG SEAL REPLACED, PROBLEM SOLVED.SDR CA120322001Pump · failed(CAN) AFTER SUCCESSFUL GROUND TEST OF ACCUMULATORS AT 70 PERCENT NG, AND ENGINE BROUGHT UP TO FLIGHT IDLE, HORN AND LOW HYDRAULIC PRESSURE LIGHT ILLUMINATED AND LOSS BOOSTED CONTROL WAS NOTED BY FLIGHT CREW. ACFT SHUTDOWN. SUBSEQUENT INSPECTION FOUND HYD PUMSDR CA120314004Servo · leaking(CAN) AFTER A FLIGHT, DURING THE ALF CHECK, THE PILOT DISCOVERS PRESENCE OF HYDRAULIC FLUID AROUND THE LT MAIN ROTOR SERVO. AFTER CLEANING, IT IS DISCOVERED DURING A RUN-UP THAT THE FLUID COMES FROM THE INTERFACE BETWEEN THE MAIN BODY AND THE UPPER ARM, 3 ALLSDR CA120227017O-Ring · damaged(CAN) 4TH EVENT WHERE THE INTERNAL O-RING FROM THE CHIP PLUG HOUSING IS DAMAGED AND FLOW OF ENGINE OIL LEAKING FROM CHIP PLUG ASSY. O-RING WAS REPLACED AND ACFT BACK IN SERVICE. EFFECTIVE APRIL 6, 2010, STC SH07-32 NOW REPLACES STC LSH07-117/D.SDR CA120127002Pickup · failed(CAN) NG INDICATION STARTED TO FLUCTUATE IN FLIGHT, WITH NO REAL FLUCTUATION OF ENGINE SPEED. AFTER LANDING, INVESTIGATION SHOWS THAT PICK-UP RESISTANCE VARIES FROM 134 OHMS, NORMAL, TO INFINITE. REPLACED NG PICKUP BY NEW. SYSTEM TESTED SERVICEABLE.SDR CA120125019Bolt · sheared(CAN) DURING A FERRY FLIGHT THE PIC HAD A WARNING INDICATION FOR ENGINE CHIPS. PIC LANDED THE ACFT, CLOSEST LANDING POSSIBLE, FOR FURTHER INVESTIGATION. AFTER INSPECTING ALL THE ENGINE CHIP PLUGS BY A COMPANY AME IT WAS DETERMINED THAT THE ENGINE HAD SUFFER SDR CA111209009Longeron · cracked(CAN) NOISE WAS HEARD BY ENGINEER DURING MX WHILE MOVING CYCLIC FROM SIDE TO SIDE. AFTER THE BELLY SKIN WAS REMOVED A 5 INCH CRACK WAS FOUND IN ONE OF THE MAIN LONGERONS OF THE CABIN FLOOR. JUST BELOW WHERE THE CYCLIC MIXING UNIT ATTACHES. CRACK SEEMS TO HASDR CA111031002Skin · cracked(CAN) DURING SCHEDULED 12 YEARS INSPECTION, A CRACK WAS FOUND ON VERTICAL STABILIZER T/E SKIN. A SMALL PORTION STARTED TO EMERGE (.50" LONG) BUT AFTER DISASSEMBLY FOUND (6.0" LONG). THE CRACK STARTING AREA BETWEEN 2 PARTS (FIN SPAR & SPLICING PLATE) AND WAS NSDR QMLA2011100311096Fuel Sys · leakingTHE PILOT AND MEDICAL CREW SMELLED FUEL IN THE CABIN SHORTLY AFTER TAKEOFF. THE ODOR APPEARED TO BE MORE SIGNIFICANT IN THE AFT CABIN AREA. THE PILOT IMMEDIATELY DECIDED TO LAND IN A CLEAR LANDING AREA. THE MECHANIC WAS CALLED TO THE LOCATION WHERE HE INSPESDR 2011FA0000651Damper · crackedPART FOUND CRACKED AT INSPECTION. CRACK RUNS ALONG WITH METAL GRAIN ALONG THE INBD SECTION NEXT TO WELDED NIPPLE. FAILURE OF THIS PART WILL CAUSE ENGINE FAILURE.SDR CA110926004Modulator · unserviceable(CAN) PILOT REPORTED INCREASE IN COMPRESSOR SPEED AND DROP IN ROTOR RPM ON APPROACH. PILOT MANAGED TO LAND WITHOUT INCIDENT. MAINTENANCE PERSONNEL FOUND THE AIRFLOW MODULATOR DEFECTIVE DUE TO A BROKEN BLEED AIR TRANSFERT TUBE.
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