Aerospatiale AS350B
Service difficulty reports · 626
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 = 'AS350B' 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 = 'AS350B' 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 2026FA0000055Meter · inoperativeHOBBS METER STOP WORKING.SDR JBZA20190305001Starter Gen · failedCREW DETECTED A STRONG ELECTRICAL BURNING SMELL DURING FLIGHT BACK TO BASE. NO SMOKE MADE A PRECAUTIONARY LANDING AT KCIC.SDR 2017F00021Air Filter · saturatedAPPROXIMATELY 25 MINUTES AFTER TAKEOFF, THE MED CREW NOTICED SMOKE IN THE CABIN. THEY WERE UNAIDED AT THE TIME AND COULD SEE A LIGHT SMOKE BETWEEN THEM & THE LIGHTING THEY WERE USING FOR PATIENT CARE. THE PILOT WAS UNABLE TO SEE IT UP FRONT UNTIL HE TURNED ONSDR 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 CA140319006Control Lever · malfunctioned(CAN) DURING ALF, AFTER LAST FLIGHT, CHECK, THE TAIL ROTOR CONTROL PITCH LEVER LOWER BUSHING WAS FOUND LOOSE. THIS WAS NOTICED BY EXCESSIVE TWISTING/ROCKING MOVEMENT IN LEVER AROUND THE EXPANSION PIN THAT MOUNTS IT TO THE TAIL ROTOR GEARBOX. LEVER WAS REMOVESDR CA130916012Pump · failed(CAN) DURING FLIGHT THE PILOT NOTED LOW FUEL PRESSURE INDICATION. AS IS NORMAL PROCEDURE IN THIS CASE, THE PILOT LOCATED A SUITABLE LANDING SITE AND LANDED THE ACFT WITH NO INCIDENT. THE FUEL PUMP WAS FOUND TO HAVE FAILED. THIS FAILED PUMP WAS REPLACED PRIOSDR CA130826008Lock Plate · cracked(CAN) LOWER BEARING LOCK PLATE FOUND CRACKED AND DISLODGED, JAMMING INTO SHAFT SPLINES. 1 LOOP OF LOCKWIRE, NON-O/H SHOP, MISSING AT LOCKING FEATURE LOCATION.SDR QMLA2013071713101Unknown · smokeDURING FLIGHT, WITH FAN SWITCH ON, SMOKE CAME OUT OF VENT ON TOP OF GLARESHIELD. WHEN FAN WAS TURNED OFF THE SMOKE STOPPED. REMOVED AND INSTALLED INSTRUMENT PANEL SHROUD IAW AMMS 050-0416. INSPECTED ALL INSTRUMENTS AND WIRE HARNESSES. NO INDICATIONS OF OVERSDR CA120217008Fcu · malfunctioned(CAN) THE PILOT REPORTED DIFFICULTIES RELATING TO HUNG OR HOT STARTS, IN ADDITION TO ROTOR SPEED PROBLEMS. DURING AN INSPECTION AT THE END OF THE DAY, AIR WAS FOUND IN THE AIRFRAME FUEL FILTER SIGHT GLASS. MAINTENANCE TROUBLESHOOTING WAS SYSTEMATICALLY CARRISDR CA120207003Bracket · detached(CAN) VERTICAL STABILIZER ASSY,UPPER WAS INSPECTED DURING A 600 HRS SCHEDULED INSPECTION AND FOUND THAT THE INTERNAL WIRING HARNESS TUBE HOLDER STEEL BRACKET WAS DETACHED FROM THE STRUCTURE AND RUBBED AGAINST THE MAIN SPAR CAUSING EXCESSIVE WEAR THROUGH THE SPSDR CA120116005Spring · corroded(CAN) DURING A 600 HRS INSPECTION, THE COLLECTIVE SPRING ROD ANTICIPATOR WAS FOUND HARD TO OPERATED DUE TO INTERNAL CORROSION.SDR CA111215001Transmitter · leaking(CAN) DURING CHECK AFTER THE LAST FLIGHT OF THE DAY, PRESENCE OF FUEL IS NOTED ON THE LT SIDE OF THE TRANSMISSION DECK. AFTER INVESTIGATION WITH BOOST PUMPS ON, THE LEAK COMES FROM THE PRESS TRANSMITTER, AT THE BASE OF THE ELEC CONNECTOR. THE NEEDLE OF THE FSDR CA110831007Cable · disconnected(CAN) THE FUEL CONTROL CABLE END (KNOWN AS THE "END EQUIPPED") INADVERTENTLY BECAME DISCONNECTED FROM THE BALL JOINT ON THE FUEL CONTROL ARM . THE SAFETY MECHANISM WAS INSTALLED AT THE TIME.SDR CA110729008Bracket · crackedSTEP BRACKET FOUND CRACKED DURING LAST FLIGHT CHECK. PART FROM STC SH09-38. PART REPLACED BY A NEW ONE AND SENT BACK TO MFG FOR INVESTIGATION.SDR CA110329005Diode · failedACTIVATING THE MASTER CUT OFF SWITCH WILL CAUSE BATTERY FUSE WOULD BLOW CAUSING A LOST OF NR AND T4 INDICATION.SDR CA101015005Transducer · unserviceable(CAN) UPON POWER REDUCTION ON APPROACH THE ENGINE OIL PRESSURE WAS OBSERVED TO FALL TO ZERO. WHEN POWER WAS APPLIED TO FLARE THE INDICATION RETURNED TO NORMAL. NO OIL PRESSURE WARNING LIGHT WAS ILLUMINATED. TRANSDUCER WAS REMOVED AND TESTED. NO INDICATION SDR 2009FA0000906Electrical Box · intermittent25 AMP C/B ON INTEGRATED FLIGHT SYS ELECTRICAL BOX WAS INTERMITTENTLY POPPING. FOUND POOR WIRE ROUTING INSIDE THE BOX (DONE AT TIME OF MFG) CAUSING WIRE TO WEAR AGAINST SOLENOID STUD A/C IS INSTALLED UNDER STC NR SH35095W. (K)SDR 2009FA0000519Elt · failedELT MALFUNCTIONED IN FLIGHT. UPON RETURN TO BASE, WE RESET THE UNIT, PERFORMED A FUNCTION CHECK. WE TOOK THE AIRCRAFT FOR A FLIGHT AND IT FAILED IN FLIGHT AGAIN. WE REJECTED THE UNIT AND INSTALLED A SERVICEABLE UNIT. (K)SDR CA090318001Engine · fod(CAN) PILOT WAS TAKING OFF FROM BASE, REPORTED HEARING ODD WHINING FROM ENGINE DURING TAKEOFF AND POWER CHANGES, ABORTED TAKEOFF AND RETURNED TO STAGING. OPENED ENGINE COWL, NOTED ALUMINUM SHAVINGS ON ENGINE DECK. VISUAL INSP IDENTIFIED THE COMPRESSOR WASH UNISDR 2009FA0000302Tee Fitting · looseHOSE NUT WOULD TORQUE DOWN BUT LINE WAS STILL LOOSE AND LEAKED. A LINE REMOVE FROM ANOTHER HELICOPTER WORKED FINE. NEW LINES INSTALLED AND LINE THAT WAS INSTALLED PRIOR AND LEAKED WAS FITTED TO THE NEW TEE AND WORKED FINE. AT TOTAL OF (3) NEW LINES WERE FITSDR CA090315001Structure · corroded(CAN) UPON ROUTINE INSP, IT WAS FOUND THAT THE RT CABIN RESONATOR STRUCTURE WAS CORRODED AT THE INNER ATTACHMENT FLANGE TO THE POINT THAT BUCKLING OF THE OUTER ATTACHMENT PLATE HAD OCCURED. THE ASSY WAS REMOVED FROM THE ACFT. IT WAS FOUND THAT THE OUTER ATTACHSDR CA090227011Cone · separated(CAN) A/C WAS IN CRUISE AT 5000 FT WHEN A LOUD POP WAS HEARD ACCOMPANIED BY A SINGLE TORQUE OSCILLATION. PILOT REDUCED HIS POWER TO LAND. A BURNING OIL ODOR WAS DETECTED ON THE DESCENT. THE PILOT LANDED NORMALLY WITH FULL POWER AVAILABLE ON LANDING. INVESTIGATSDR CA090127011Bracket · crackedENGINE HIGH PRESSURE FUEL FILTER BRACKET, TOP HOLE CRACKING DUE TO HARMONIC VIBRATION, KNOWN PROBLEM.SDR CA090127012Bracket · crackedENGINE HIGH PRESSURE FUEL FILTER BRACKET, CRACKING AT TOP BOLT HOLE DUE TO HARMONIC VIBRATION, KNOWN PROBLEM.SDR CA081119003Bearing · blocked(CAN) OIL WAS COMING OUT OF TURBINE EXHAUST AND M03 BEARING VENT TUBE ON START UP. DISASSEMBLED THE ENGINE AND FOUND M03 REAR BEARING CAKED WITH BURNED OIL. M03 REAR BEARING OIL RETURN TUBE PARTIALLY BLOCKED WITH BURNED OIL.SDR CA080115009Ground Wire · failed(CAN) IN THE PROCESS OF DOING RECURRENT TRAINING FLIGHT. AFTER SEVERAL SIMULATED HYD FAILURES IN AND OUT OF GROUD EFFECT HOVER, PROCEEDED TO PRACTICE THE SIMULATED HYD FAILURE. THE SIMULATED PROCEDURE WAS INITIATED FROM 100 FOOT HOVER WITH A VERBAL WARNING THASDR CA080104003Trim Tab · unserviceable(CAN) WHILE PERFORMING A BRIDGING INSPECTION ON AN A/C PREVIOUSLY LEASED TO A DIFFERENT COMPANY, AD 2007-0138-E WAS BEING C/O. SECTION OF MISSING PAINT NOTED ON AREA REQUIRING INSPECTION IAW ASB 05-00.40( IB ATTACHMENT POINT OF T/E TAB). A CRACK WAS NOTED THROSDR CA070118011Servo · unserviceable(CAN) DURING HYDRAULIC PRE-FLIGHT CHECK CAUSED CYCLIC TO MOVE 4-5 INCHES TOWARDS 8 O’CLOCK POSITION. SERVO REMOVED SERVICEABLE UNIT INSTALLED. SERVO SENT OUT FOR REPAIR AWAITING TEARDOWN REPORT. (TC NR 20070118011)SDR LBG2007F00001Wire Harness · chafedON A TOUR FLIGHT THE PILOT LOST GENERATOR OUTPUT. HE TURNED AROUND AND MADE A SAFE LANDING AT THE AIRPORT. THE GENERATOR WIRES WERE RUBBING ON THE CARBON FIBER ENGINE COWLING AND SHORTED TO AIRFRAME GROUND. THIS IS A PROBLEM WITH THE STC SH3324NM CONVERSIONSDR LBG2007F00000Wire Harness · chafedON A TOUR FLIGHT, THE PILOT LOST GENERATOR OUTPUT. TURNED AROUND AND MADE A SAFE LANDING AT THE AIRPORT. THE GENERATOR WIRES WERE RUBBING ON THE CARBON FIBER ENGINE COWLING AND SHORTED TO AIRFRAME GROUND. THIS IS A PROBLEM WITH THE STC SH3324NM CONVERSION KSDR 2006FA0000496Blade · crackedCRACK FOUND ON LOWER SURFACE OF MAIN ROTOR BLADE NEAR STATION 1000. EXACT CAUSE OF CRACK WOULD ONLY BE SPECULATIVE. (K)SDR KBM2005F00351Battery · inoperativeUNIT STARTS SLOW. REMOVED AND REPLACED BATTERY. (K)SDR CA051128012Transmitter · unserviceableA RESISTANCE CHECK OF THE TRANSMITTER WAS CARRIED OUT. IT REVEALED AN OPEN CIRCUIT. TX ORDERED AOG. PREVIOUS LOG ENTRY REVEALED THIS TRANSMITTER WAS JUST INSTALLED AUG 30 05.SDR CA050919007Shock Absorber · cracked(CAN) REMOVED FROM AIRCRAFT FOR MANUFACTURER 2500 HOUR INSPECTION AND 2 COILS OF THE SAME PN WERE FOUND TO BE CRACKED.SDR CA050819005Igniter · damaged(CAN) INSULATION TIP LOOSE. HASN'T FALLEN OUT YET. ANOTHER OPERATOR HAS HAD TWO OCCURANCE'S WERE THE CERAMIC INSULATOR CAME RIGHT OUT.SDR CA050819004Igniter · damaged(CAN) INSULATION TIP LOOSE. HASN'T FALLEN OUT YET. ANOTHER OPERATOR HAS HAD TWO OCCURANCE'S WHERE THE CERAMIC INSULATOR CAME RIGHT OUT.SDR HXSA0508001Turbine Wheel · failedAS-350 CRASHED IN BOGGY TERRAIN WHILE DEPARTING JUNEAU AIRPORT. AIRCRAFT HAD SUBSTANTIAL DAMAGE. IT APPEARS THAT AFTER TAKEOFF THE TURBINE BLADE OR BLADES CAME APART IN THE ENGINE AND SMOKE/FIRE WAS OBSERVED FROM PERSONS ON THE GROUND RESULTING IN AUTOROTATISDR CA050417006Igniter · damaged(CAN) CENTER CERAMIC MISSING, BOROSCOPE OF ENGINE FOUND NO DAMAGE, IGNITER REPLACED.SDR CA050215009Switch · defective(CAN) PILOT COULD NOT TURN HYD OFF DURING FLIGHT BY PRESSING BUTTON ON COLLECTIVE STICK. TROUBLESHOOTING DETERMINE THE SWITCH WAS DEFECTIVE AND NOT SUPPLYING VOLTAGE TO SOLENOIDS. NEW SWITCH INSTALLED.SDR CA041209005Servo · malfunctioned(CAN) PILOT REPORTED THAT CYCLIC WAS STIFF WHEN MOVED TO LEFT AND IT WANTED TO MOVE RIGHT WHEN COLLECTIVE LOWERED (NO PROBLEMS WHEN COLLECTIVE WAS RAISED). LEFT MAIN SERVO WAS CHANGED AND DEFECT WAS CURED.SDR VY12008F00000Gearbox · destroyedPERFORMED A PRELIMINARY REVIEW OF THE SERVICE HISTORY OF THE GEARBOX THAT WAS RECEIVED FOR OVERHAUL. IT WAS DETERMINED THAT THE GEARBOX WAS INVOLVED IN AN ACCIDENT. BASED ON THE ACCIDENT THAT OCCURRED ON 9 NOV 2004, MFG HAS DETERMINED THAT ALL DYNAMIC COMPONENSDR CA041105006Fuel Control · failed(CAN) ON P2 CHAMBER INSPECTION AND CLEANING OF FCU. WHEN BELLOWS WERE REMOVED WE FOUNDTHAT THE PIN THAT HOLDS THE METERING VALVE IN PLACE WAS BROKEN OFF AND HALF OFTHE PIN WAS FOUND IN THE CHAMBER.SDR CA041110016Servo · malfunctionedWHEN HYDRAULIC POWER IS RE-ESTABLISHED AFTER DOING HYDRAULIC ACCUMULATOR PREFLIGHT CHECK, THE CYCLIC STICK WOULD GO HARD LEFT, BUT WAS ABLE TO BE OVERCOME AND WOULD ONLY LAST BRIEFLY. LEFT HAND SERVO WAS REPLACED FOR TROUBLESHOOTING AND PROBLEM WAS RECTIFIED.SDR CA040916007Switch · malfunctionedSHORTLY AFTER T/O, WARNING HORN & NOTICED 'HYD CAUTION LIGHT' ON. A FEW SECONDS LATER, ERRATIC CYC MOVEMENT FELT. RETURNED & LANDED W/O INCIDENT. MX INSPECT DID NOT ISOLATE CAUSE FOR MALFUNCTION. HYD SYS CK APPEARED TO BE NORM. HYD PUMP SPLINES INSPECTED & SDR CA041022003Turbine Wheel · unserviceable(CAN) DURING A SCHEDULED CHECK OF THE SECOND STAGE TURBINE BLADES (T2 ) IAW TURBOMECA ASB 292-72-0807 AND AD2004-047 IT WAS DETERMINE THE BLADE SHIFT HAD FAILED THE CHECK. THE GAS GENERATOR WAS REPLACEDSDR CA040805011Casting · cracked(CAN) CRACK FOUND ON WEB CASTING DURING A 100 HOUR INSPECTION. (BUTTERFLY) PLATE VERY LOOSE (WORN OUT END BUSHINGS).SDR CA040805013Relay · faulty(CAN) WHEN START BUTTON PRESSED THE STARTER RELAY WOULD ONLY CHATTER. TROUBLESHOOTING DETERMINED A FAULTY RELAY 23K. PRINTED CIRCUIT BOARD REPLACED.SDR CA040803006Battery · unserviceable(CAN) A/C BATTERY IS WEAK. IT WILL NOT START THE A/C TWICE WITHIN 5 MINUTES. BATTERY HAS ONLY AVERAGED 115 HOURS OF LIFE IN THE LAST 6 INSTALLSDR CA040803004Engine · failed(CAN) ENGINE START CYCLE INCONSISTANT AFTER OVERHAUL. MANY FUEL SYSTEM COMPONENTS CHANGED WITH NO CONSISTANT RESULTS.SDR HXS2004F2004ACompressor · fodENGINE WAS FOUND TO HAVE INGESTED A ROCK THROUGH THE INTAKE AND DAMAGED TO INLET COMPRESSOR. FOD DAMAGE. THIS ENGINE IS TO BE SENT FOR EVALUATION AND REPAIR.
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