Eurocopter EC120B
Service difficulty reports · 222
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 = 'EC120B' 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 = 'EC120B' 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 CA190604025Swashplate · damaged(CAN) DURING A 500FH INSPECTION OF THE SWASHPLATE ASSEMBLY, IT WAS NOTED THAT INJECTION OF GREASE INTO THE BALL BEARING WAS NOT POSSIBLE. UPON DISASSEMBLY FOR FURTHER INSPECTION, IT WAS NOTED THAT THE NOTCHES IN THE BEARING WERE NOT ALIGNED AT INSTALLATION WITSDR CA190509010Bearing · rough(CAN) EXCESSIVE HEAT WAS NOTED DURING THE POST MAINTENANCE CHECK FOR HEATING IN THE FORWARD TAIL ROTOR SHAFT BEARING. DURING DISASSEMBLY OF THE BEARING UNIT IT WAS NOTED THE SEALS APPEARED BURNT ALONG WITH THE GREASE HAVING A BURNT SMELL. THE BEARING WAS REMOVSDR CA190423019Bearing · seized(CAN) FOLLOWING A REPORT OF THE COLLECTIVE JAMMING DURING TAKEOFF, THE AIRCRAFT FLIGHT AND ENGINE CONTROLS WERE INSPECTED. THERE WAS NO FAULT FOUND AT FIRST. THE HYDRAULIC CART WAS CONNECTED TO THE AIRCRAFT SERVOS AND THE COLLECTIVE WAS CYCLED UP AND DOWN MULTSDR 2018FA0000077Display · malfunctionedRECEIVED A MODIFIED VEMD. AFTER INSTALLATION, AND INITIAL POWER UP, BOTH SCREENS DISPLAYED LANE FAILURE.SDR 2017FA0000324Wire · chafedTHE MAIN GEAR BOX OIL PRESSURE SWITCH WAS CAUSING MG8 PRESSURE LIGHT TO ILLUMINATE ON CAUTION PANEL. THIS OIL PRESSURE SWITCH ONLY LASTED 21 DAYS WITH 101.6 HRS FLOWN. FURTHER RESEARCH INTO THIS PARTICULAR PART SHOWED INTERNAL WIRES CHAFFED AGAINST MICRO SDR 2017FA0000323Pressure Switch · chafedTHIS MAIN GEAR BOX OIL PRESSURE SWITCH WAS CAUSING MGB PRESSURE LIGHT TO ILLUMINATE ON CAUTION PANEL. FURTHER RESEARCH INTO THIS PARTICULAR PART SHOWED INTERNAL WIRES CHAFFED AGAIN HOUSING CAUSING A SHORT IN WIRES AND ILLUMINATING MGB PRESSURE LIGHT. SUGGESTSDR KW1R20161215005Fire Detector · contaminatedSEVERAL MINUTES AFTER TAKE-OFF "ENG FIRE" WARNING LIGHT ILLUMINATED AND A PRECAUTIONARY LANDING WAS EXECUTED. WARNING LIGHT EXTINGUISHED PRIOR TO LANDING, LIGHT WAS ILLUMINATED FOR APPROX. 30 SECONDS TOTAL. AN INITIAL INSPECTION BY THE FLIGHT CREW AFTER LANDINSDR CA160222001Angle · detached(CAN) REFERENCE SB 53-10 REINFORCEMENT OF XL710 FRAME FOR LATERAL Y VIBRATION DAMPER SUPPORT. SHEARED RIVETS IN ANGLE P/N C533A2103301. DAMAGE APPEARS TO BE FROM IMPROPER INSTALLATION OF THE ANGLE. IT WAS INSTALLED WITH A GAP BETWEEN THE ANGLE AND FRAME X1710.SDR 1HTR2016011300001Pressure Switch · malfunctionedIN FLIGHT ILLUMINATION OF MAIN GEAR BOX PRESSURE CAUTION LIGHT, RED, PILOT MADE AN UNSCHEDULED PRECAUTIONARY LANDING. PRESSURE SWITCH WAS STICKING.SDR KW1R20151228004Valve · bindingP2 HEAT VALVE WOULD NOT TURNOFF WHILE ENGINE WAS RUNNING. P2 VALVE WAS ABLE TO BE TURNED OFF AFTER ENGINE SHUTDOWN.SDR KW1R20151222003Valve · bindingUPON RETURNING FROM A FLIGHT PILOT WAS UNABLE TO SHUTOFF THE P2 HEAT VALVE, CABIN HEAT ON, AIRCRAFT SHUTDOWN.SDR CA151123007Scissor Link · scored(CAN) ON VISUAL DAILY INSPECTION THE COTTER PIN SAFETY DEVICE ON THE FASTENING BOLT/NUT FOR THE SCISSOR ASSEMBLY TO THE MAIN ROTOR MAST WAS FOUND SHEARED OFF ON THE TOP SIDE AND SEVERELY DEFORMED ON THE BOTTOM SIDE. UPON FURTHER INSPECTION THE SCISSOR ASSEMBLYSDR 2015FA0000294Pressure Switch · chafedMAIN GEAR BOX PRESSURE SWITCH CAUSING FALSE READING, LIGHT TO ILLUMINATE. FURTHER RESEARCH SHOWS THAT CAUSE WAS INTERNAL WIRE CHAFING.SDR CA150601007Drive Assy · broken(CAN) HELICOPTER OPERATOR DETECTED ENGINE VIBRATION. TROUBLESHOOTING DETERMINED THE STARTER WAS THE CAUSE. ST/GEN RECEIVED BY O/H AMO FOR INSPECTION/REPAIRS. FOUND THE DRIVE END, ENDBELL BEARING LINER HAS BROKEN LOOSE IN ITS ENDBELL CASTING. BEARING LINER RSDR KW1R20150129002Valve · bindingDUCT TEMPERATURE WARNING LIGHT ILLUMINATED AND PILOT ATTEMPTED TO TURN OFF CABIN HEAT. VALVE WAS BINDING AND WAS DIFFICULT TO SHUTOFF. VALVE WAS JUST INSTALLED 63.6 HRS AGO FOR THE SAME REASON.SDR CA141030006Scissor Link · seized(CAN) MALE BUSHING, SEIZED INTO THE FEMALE BUSHING ON THE SCISSOR LINK BLOCK. THE PARTS IN QUESTION HAVE BEEN REMOVED FROM SERVICE AND QUARANTINED AND THE SCISSOR LINK BLOCK IS GOING TO BE SENT TO MFG TECHNICAL REP IAW HIS REQUEST. THE SCISSOR LINK BLOCK HAD SDR 2014FA0000627Injector · cloggedIN CONJUNCTION WITH LT & RT FUEL INJECTOR MANIFOLDS, ARE CAUSING EXCESSIVE EXHAUST FUMES IN THE COCKPIT. PART TIME ONLY REACHED 215.6 HOURS BEFORE BECOMING CLOGGED INTERNALLY CAUSING THE EXCESSIVE EXHAUST FUMES. PREVIOUS ISSUES HAVE ALSO NOT REACHED ITS 400SDR CA140923008Display · failed(CAN) ENGINE FAILED POWER CHECK PLUS 4 TO BAD, PILOT DID 3 POWER CHECK ALL FAIL BY A FEW DEGREES C. CHANGED THE FDC FILTER AS IT WAS DIRTY AND ALSO DID A COMPRESSOR WASH AND INSPECTED THE COMPRESSOR AND TURBINE BLADES, NO DAMAGE NOTED. WE DID A GROUND RUN TOSDR CA140702013Bushing · seized(CAN) THE ROTATING SCISSOR ASSLY HAS 2 MAIN PARTS, THE SCISSOR LINK BLOCK PN C623A2005103 AND THE BUSHINGS, PN MM2599973, 4 EA. ON A DAILY CHECK IT WAS DISCOVERED THAT ONE OF THE BUSHINGS WAS SEIZED INTO THE SCISSOR LINK BLOCK. AFTER REMOVAL THE SEIZURE WAS COSDR CA140219001Support Bracket · broken(CAN) DURING HIS DI THE PILOT NOTICED THAT THE T4.5 SUPPORT BRACKET ASSY WAS FOUND TO BE BROKEN AT BOTH MOUNTING HOLES THAT ATTACH IT TO THE ENGINE FLANGE.SDR CA140120002Engine · malfunctioned(CAN) THE PILOT NOTICED A SUDDEN OIL PRESSURE LOSS AND HE ELECTED TO SHUTDOWN THE ENGINE. AN UNEVENTFUL SINGLE ENGINE LANDING FOLLOWED. POST FLIGHT EXAMINATION FOUND A TOTAL LOSS OF OIL AND THE MOUNTING FLANGE TO THE STARTER GENERATOR ADAPTER BROKEN. THE OPESDR 2013FA0000760Bushing · seizedOUTER BUSHING SEIZED ON INNER BUSHING.SDR CA131210002Engine · failed(CAN) AIRFRAME AND ENGINE TOTAL TIME 23.2. DURING AUTOROTATION TRAINING WITH POWER RECOVERY, IN A 3 FOOT HOVER, AN ENGINE CHIP LIGHT INDICATOR ILLUMINATED. AS THE ACFT WAS ON AN ACTIVE RUNWAY IT WAS DECIDED TO MOVE THE ACFT TO THE RAMP AREA. APPROXIMATELY 1.5SDR 2013FA0000762Bushing · scoredROTATING SCISSOR "H" LINK, HAS SCORING ON BUSHINGS.SDR 2013FA0000744Scissor Link · debondedSCISSOR LINK FIXED BUSHING DISBONDED FROM SCISSOR LINK, INNER ROTATING, SLIP BUSHING SEIZED IN OUTER STATIONARY BUSHING.SDR 2013FA0000759Bushing · debondedFIXED BUSHING FROM SCISSOR LINK DISBONDED & SEIZED ON REMOVABLE CARBIDE BUSHING.SDR 2013FA0000761Scissor Link · misoverhauledSCISSOR LINK FAILED CLEARANCE CHECK.SDR CA130823009Bonding Strap · broken(CAN) DURING THE MORNING DAILY PREFLIGHT INSPECTION, THE AME DISCOVERED THE ELECTRICAL BONDING BRAID ON THE RED BLADE HAD BROKEN AT THE BLADE-END LUG. BONDING STRAP, PN 365A31-1937-00 WAS REPLACED AND ACFT RETURNED TO SERVICE.SDR CA130531013Stator Vane · damaged(CAN) DURING AN INSPECTION, THE PAINT ON TWO FENESTRON STATOR VANES HAS BEEN FOUND CRACKED, AND THE SHAPE OF THE VANES "SWOLLEN", ABOUT 1" OF THE L/E.SDR 2013FA0000285Structure · corroded30 DAY CORROSION INSPECTION NOTED A SLIGHT BUBBLE ON THE EDGE OF THE RADAR ALTIMETER MOUNT AND TAIL BOOM JUNCTION. FURTHER INSPECTION REVEALED INTER-GRANULAR AND CORROSION OF ALUMINUM OUTER SKIN OF TAILBOOM STRUCTURE UNDER THE MOUNT. AFTER REMOVAL OF THE CORSDR CA130215006Bushing · scored(CAN) ROTATING SCISSOR ASSY. DURING INSPECTION BUSHING FOUND SCORED. 20 HRS TOTAL TIME ON BUSHING.SDR CA121227002Adapter · damaged(CAN) ON A FLIGHT ON DECEMBER 21, 2012, THE FLIGHT CREW NOTED A LATERAL VIBRATION THAT BECAME MORE PRONOUNCED DURING DECENT. THE FLIGHT CREW TERMINATED THE FLIGHT AND RETURNED TO BASE. A SUBSEQUENT VISUAL INSPECTION OF THE MAIN ROTOR HEAD FREQUENCY ADAPTERS SDR 2013FA0000017Outlet · burnedDURING SCHEDULED INSPECTION, MECHANIC NOTED BURNING AROUND THE AREA OF THE EXHAUST OUTLET. IT WAS NOTED THAT THE BURNING, CRACKING AND DEBONDING HAD TAKEN PLACE IN A 12 X 9 AREA. FURTHER INSPECTION REVEALED THE CAUSE COULD BE FROM AN ENGINE BREATHER TUBE THASDR 2012FA0000494Torque Tube · wornACFT UNDERGOING 1500 HR INSPECTION AT A TOTAL AIRFRAME TIME OF 1501.4 HRS. THE MECHANIC FOUND THE THE WEAR ADHESIVE TAPE ON THE ORIGINAL ASSY HAD DEBONDED AND CAUSED AN ABNORMAL AMOUNT OF WEAR TO THE SHAFT (.008").SDR CA120604007Rail · worn(CAN) IT WAS BECOMING DIFFICULT TO OPEN OR CLOSE THE SLIDING DOOR. THE BOTTOM RAIL WAS WORN AND SOME AREAS WERE BROKEN. THE ROLLERS WERE NOT MAINTAINED PROPERLY IN THE RAIL. REPLACEMENT OF THE BOTTOM RAIL C/O, DOOR ADJUSTED, NO MORE PROBLEMS.SDR CA111016001Magnetic Plug · damaged(CAN) IN CRUISE FLIGHT, PILOT SEES "GB CHIP" LIGHT FLASHING INTERMITTENTLY. HE LANDS SAFELY AND AFTER SHUTDOWN, DISCOVERS THE TAIL GEARBOX CHIP DETECTOR OUT OF ITS RECEPTACLE, HANGING BY THE ELECTRICAL CABLE. OIL LEVEL IN THE GEARBOX IS NORMAL, NO LEAK. THE SDR CA110829001Panel · departed(CAN) WHILE FLYING WITH ALL DOORS OFF, THE COMMUNICATION PANEL (THE PANEL THAT OPENS THE CABIN TO THE REAR CARGO HOLD) FLEW OUT OF THE CABIN. NO DAMAGE WAS FOUND ON THE REST OF THE ACFT. THE PANEL HAD RECENTLY BEEN MODIFIED FOR A STRETCHER KIT INSTALLATION ISDR CA110610009Freq Adapter · failedDURING A MAJOR INSPECTION, DISCOVERED THE FREQUENCY ADAPTER WAS INCORRECT (TOO LONG). PILOT HAD JUST REPORTED A SERIOUS VIBRATION ON THE GROUND. REMOVED THE FREQUECY ADAPTER AND FOUND THAT 1 OF THEM HAD STRETCHED AND REQUIRED A COMPLETE TURN IN ON THE RODSDR 2011FA0000311Skin · chafedDURING THE INSTALLATION OF A TAIL BOOM ON THE SAME MODEL ACFT THAT HAD BEEN REPAIRED FOR CRACKING IN THE LT FWD VOR ANTENNA MOUNT THE MECHANIC NOTED CHAFING ALONG THE BOTTOM OF THE INNER TAIL BOOM SKIN UNDER THE WIRE HARNESSES. IN SOME CASES IT HAD PENETRATEDSDR 2011FA0000310Skin · chafedDURING THE INSTALLATION OF A TAIL BOOM ON THE SAME MODEL ACFT THAT HAD BEEN REPAIRED FOR CRACKING IN THE LT FWD VOR ANTENNA MOUNT THE MECHANIC NOTED CHAFING ALONG THE BOTTOM OF THE INNER TAIL BOOM SKIN UNDER THE WIRE HARNESSES. IN SOME CASES IT HAD PENETRATEDSDR 2011FA0000309Structure · crackedDURING THE VALVE CHECK A MECHANIC NOTED A CRACK EXTENDING LONGITUDINALLY FROM THE LT FWD NAV/VOR ANTENNA MOUNT. MFG HAS PREVIOUS KNOWLEDGE OF THIS DEFECT AND HAS DEVISED A REPAIR SCHEME FOR THIS DEFECT. RDAS (REPAIR DESIGN APPLICATION SHEET) NR RDAS-AE11-014SDR 2011FA0000308Skin · chafedDURING THE INSTALLATION OF A TAILBOOM ON THE SAME MODEL ACFT THAT HAD BEEN REPAIRED FOR CRACKING IN THE LT FWD VOR ANTENNA MOUNT THE MECHANIC NOTED CHAFING ALONG THE BOTTOM OF THE INNER TAIL BOOM SKIN UNDER THE WIRE HARNESSES. IN SOME CASES IT HAD PENETRATED SDR 2011FA0000307Skin · chafedDURING THE INSTALLATION OF THE TAILBOOM THAT HAD BEEN REPAIRED FOR CRACKING IN THE LT FWD VOR ANTENNA MOUNT THE MECHANIC NOTED CHAFING ALONG THE BOTTOM OF THE INNER TAILBOOM SKIN UNDER THE WIRE HARNESSES. IN SOME CASES IT HAD PENETRATED THE COMPOSITE MATERIASDR 2011FA0000201Skin · crackedDURING THE QC FINAL INSP PHASE OF A 100 HR INSP THE INSPECTOR NOTED A CRACK EXTENDING LONGITUDINALLY FWD AND AFT FROM THE LT FWD NAV/VOR ANTENNA MOUNT. PHOTO`S AND INFOR SENT TO MFG FOR DETERMINATION. MFG SUGGEST REMOVAL AND REPAIR BY MFG. BELIEVE PART TO BSDR CA110402001Probe · failed(CAN) PILOT LOST FUEL QTY INDICATION IN FLIGHT. TROUBLESHOOTING C/O AFTER LANDING. LOWER FUEL PROBE REPLACED, FAILURE CLEARED. ACFT RELEASED.SDR CA110203009Block · dislodgedLIP SEAL OF BEARING BLOCK ASSY DISLOGED.SDR 2011FA0000042Control Unit · misalignedFOUND MIXER UNIT MISALIGNED CAUSING THE CYCLIC STICK TO RISE UNCOMMANDED DURING GROUND CHECKS AND ALSO CAUSED THE STRESS OF OTHER FLIGHT CONTROL COMPONENTS IN THE SYS CAUSING RIVETS TO WORK WHEN THE ACFT WAS SHUTDOWN AND THE CYCLIC IN THE LOCKED POSTION.SDR CA101116012Seal · failed(CAN) SEALS AND SPHERICAL JOINTS REPLACED DUE TO SEAL POPPED OUT OF JOINT ON BEARING P/N 593278 ON BOX EQUIPPED P/N C651A1107101 BUT WHEN GREASE IS APPLIED TO NEW SEALS THEY ALSO POP OUT OF JOINT RELEASING GREASE PROCDURE IN MAINTENANCE MANUAL EC120B AMM 65-1SDR CA101019003Engine · making metal(CAN) DURING FLIGHT ENG CHIP LIGHT WENT ON. KNOWING THE CASE HISTORY OF THIS TYPE OF WARNING ON ENGINES, THE COLLECTIVE WAS LOWERED TO MINIMUM, AUTO ROTATION SPEED ESTABLISHED, DESCENT TO VALLEY BOTTOM WAS PERFORMED, FLARE AND CUSHION LANDING WITH POWER ON (LOSDR CA101024001Servo Control · failedHYD SERVO WHICH CONTROLS FORE/AFT CYCLIC MOVEMENT WOULD NOT SHUTOFF WHEN COLLECTIVE "HYD SHUTOFF" SWITCH IS ACTIVATED. THE SERVO CONTINUED TO OPERATE ON ACCUMULATOR PRESSURE FOR APPROX 20 SECONDS UNTIL ACCUMULATOR WAS DEPLETED. IN THE EVENT OF A FLIGHT CONTRO
Back to Eurocopter EC120B