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 CA100825003Pump · failedENGINE LOSS OIL PRESSURE IN FLIGHT, EMERGENCY AUTO ROTATION TO GROUND STARTED DURING FLARE, LOUD EXPLOSION HEARD, FOLLOWED BY ENGINE STOPPAGE ACFT LANDED WITHOUT FURTHER INCIDENT.SDR CA100806016Ball Joint · seized(CAN) AFTER LIFTING OFF IN A HOVER AND STARTING TRANSLATIONAL LIFT, THE NR DROOPED TO 380. AS THE AIRCRAFT WAS SLOWED DOWN TO PREPARE FOR AN UNSCHEDULED LANDING, THE NR SUDDENLY JUMPED TO 422. THE NORMAL NR RANGE IS 412. THESE SYMPTOMS WERE REPEATED THREE TIMESDR CA100705004Engine · making metalDURING A DI A LARGE QUANTITY OF METAL CHIPS WERE FOUND ON THE MO2 (TURBINE) CHIP DETECTOR. THESE PARTICLES MAY HAVE BEEN GENERATED BY THE MAIN ENGINE BEARINGS. IN SPITE OF THE METAL BRIDGING THE CONTACTS OF THE CHIP DETECTOR THERE WAS NO COCKPIT WARNING LIGHSDR CA101001005Manifold · fumesALSO APPLIES TO LT MANIFOLD PN 0319738340 AND PREFERRED INJECTOR PN 0319738350 ALL TSN 51.5 EXHAUST FUMES IN CABIN RESULTING IN COMPLAINTS OF SORE THROAT, ITCHY EYES AND HEADACHE. REPLACED ALL COMPONENTS OF THE INJECTION MANIFOLD AND THE PROBLEM WAS CORRECTESDR CA091202017Spline · disengaged(CAN) FOLLOWING A SCHEDULED ENGINE CHANGE, ENG PRESS WARNING LIGHT CAME ON DURING A TEST FLIGHT. PILOT LANDED WITHOUT INCIDENT. SUBSEQUENT TROUBLESHOOTING REVEALED DISENGAGEMENT OF THE ENGINE OIL PUMP DRIVE ADAPTER FROM PUMP SLINES. DRIVE ADAPTER APPEARS TO SDR CA091027007Fuel Control · leaking(CAN) DURING DAILY INSPECTION FUEL WAS NOTICED IN ENGINE BAY AREA. FUEL BOOST PUMP WAS TURNED ON TO SEE WHERE LEAK WAS COMING FROM, FUEL WAS NOTICED DRIPPING FROM THE FRONT OF THE F.C.U. TURBOMECA FIELD REP WAS CALLED AND SAW THE LEAK AND ADVISED TO BE REMOVEDSDR CA090918001Valve · sticking(CAN) SERVO CONTROL ISSUES HAVE BEEN RECURRING ON ALL THREE EC120S IN OUR FLEET. THE MOST COMMON PROBLEM OCCURS AFTER INITIAL START UP OF THE DAY WHEN THE PILOT DOES THE HYDRAULIC CUT OFF CHECK (THE SWITCH ON THE COLLECTIVE STICK). THE CYCLIC GOES HARD TO THE SDR CA090812008Servo Control · malfunctioned(CAN) DURING PRE FLIGHT TEST OF HYDRAULIC SYSTEM, THE PILOT OPERATED THE TEST SWITCH ON COLLECTIVE CONROL AND THE CYCLIC CONTRO EXPERIENCED HARD OVER TO THE LEFT. TEST WAS REPEATED WITH SAME RESULT. AIRCRAFT GROUNDED AT 2330 FOR TROUBLESHOOTING IN THE MORNING.SDR CA090702007Electrical Sys · malfunctionedINVESTIGATION 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 SUPPLING 28 VDC TO PIN E OF THE CONNECTION. THIS ERRANT VOLTAGE INS`T ENOUGH TO OPESDR CA090702005Electrical Sys · malfunctioned(CAN) INVESTIGATION 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 SUPPLING 28 VDC TO PIN E OF THE CONNECTION. THIS ERRANT VOLTAGE ISN`T ENOUGH SDR CA090630007Pressure Switch · leaking(CAN) AFTER LANDING, NOTICED A BIT OF OIL ON THE SIDE OF THE ACFT. OPENED THE COWL TO FIND A LOT OF HYD FLUID ON THE DECK. THIS WAS THE SECOND FLIGHT OF THE DAY AND HAD CHECKED ALL THE OILS AND THE DECK WAS DRY BEFORE THE FLIGHT. THE FIGHT WAS 2.2 HOURS.SDR CA090623007Bolt · broken(CAN) DURING A 100 HOUR INSPECTION ROTATIONAL PLAY WAS NOTED IN THE ROTATING SWASHPLATE. THE DRIVE LINK WAS DISASSEMBLED IAW THE 100 HOUR INSPECTION AND SB 05-009. THE BOLT IN ATTACHING THE DRIVE LINK TO THE MAST WAS FOUND SEIZED IN THE ASSEMBLY. IN ADDITION TSDR CA090417006Switch · intermittentBATTERY WAS LEFT ON. UPON RETURN TO ACFT 2 HOURS LATER, BATTERY WAS TOO LOW TO START ACFT. PILOT THOUGHT BATTERY/EPU SWITCH WAS TURNED OFF, BUT YOU HAVE TO PUSH THE BUTTON UP TO 4 TIMES BEFORE IT STAYS IN SELECTED POSITION. CONFIRMED PILOT`S SNAG. BATTERY/SDR CA090417005Relay · intermittentPILOT REPORTED LANDING LIGHT "STUCK ON". GROUND TESTING, CONFIRMED FAULT. CHECKED WIRINGS, LANDING LIGHT SWITCH AND RELAY INSTALLATION. TAPPED RELAY AND LANDING LIGHT STARTED TO WORK, AS NORMAL. RELAY CONTACTS "STICKY". PARTS ORDERED.SDR CA090407011Chip Detector · illuminated(CAN) FLIGHT CREW REPORTED ENGINE CHIP LIGHT `FLICKERING` ON FINAL LEG OF DAY. ENGINE OIL SYS FLUSHED, OIL COOLERS REPLACED, ENGINE OIL FILTER REPLACED, AND OIL SAMPLES SENT FOR ANALYSIS. ACFT RETURNED TO SERVICE IAW MM.SDR 2009FA0000209Starter Gen · wornGROWLING OR LOUD HOWLING NOISE COMING FROM ENGINE AREA FLUCTUATING WITH POWER CHANGES. VIBRATION TRANSMITTING THROUGH ACFT.SDR CA090210002Window · cracked(CAN) DURING FLIGHT TRAINING, THE FLIGHT CREW NOTICED A LARGE CRACK (4.5 INCHES) LONG IN THE LT WINDSCREEN. FLIGHT CREW LANDED WITHOUT INCIDENT.SDR 2008FA0000917Bearing · unserviceablePILOT COMPLAINED OF A SEVERE ENGINE VIBRATION AND HOWLING NOISE EMANATING FROM THE ENGINE AREA, DURING ALL PHASES OF ENGINE OPERATION. THE STARTER WAS REPLACED AND THE VIBRATION CEASED. (K)SDR CA081218002Rotor Head · damaged(CAN) DURING PREFLIGHT INSP ON NEWLY DELIVERED ACFT, DISCOVERED A .5 INCH COUNTERSINK RESTING UNDER ACFT TRANSMISSION. NO DAMAGE WAS FOUND BUT THE TOOL IS LARGE ENOUGH TO HAVE CAUSED FLIGHT CONTROL INTERFERENCE OR TO HAVE CONTACTED THE ROTOR BRAKE DISK. TOOL WSDR CA081112003Pressure Switch · failedAFTER A LANDING AND COOLDOWN THE PILOT PRESSED THE START/DETENT SWITCH TO MOVE THE TWIST GRIP TO CUTOFF. THE ENGINE IMMEDIATELY FLAMED OUT WHEN THE SWITCH WAS DEPRESSED (TWIST GRIP WAS NOT TURNED). THEN ATTEMPTED TO RECREATE THIS PROBLEM AND IT HAPPENED AT ALSDR CA081031003Control Unit · malfunctioned(CAN) THE ACFT HAS AN ELECTRICAL CONTROL BOX CALLED THE LACU. WHICH CONTROLS COCKPIT LIGHTING AND VARIOUS OTHER SWITCHES INCLUDING BATTERY MASTER, RADIO MASTER, POSITION LIGHTS, AND ANTI-COLLISION LIGHTS AND SO ON. ON A FLIGHT THEY WERE DOING THE CREW BEGAN TOSDR CA080725003Hydraulic System · malfunctioned(CAN) AT GROUND IDLE, THE NORMAL PROCEDURE IS TO TEST ACCUMULATORS BY PUSHING THE ACCUMULATORS BUTTON ON, AND THE HYD LIGHT ILLUMINATES , AND PROCEED TO TEST THE ACTUATORS BY MOVING THE CYCLIC FWD AND AFT, ABOUT 4-5 INCHES TRAVEL, EIGHT TIMES, THEN RT AND LT, SDR 2008FA0000310Engine · making metalENGINE CHIP DETECTOR LIGHT ILLUMINATED. INSPECTED CHIP DETECTORS, AND FOUND METAL SLIVERS ON MODULE NR 1 CHIP DETECTOR. ENGINE REMOVED FROM SERVICE.SDR CA080407001Housing · cracked(CAN) CRACK INDICATION FOUND ON UPPER RT AREA OF INPUT HOUSING BOSS. THIS WAS FOUND DURING OVERHAUL OF THE MODULE. PART SENT TO MFG FOR EVALUATION.SDR 2008FA0000148Housing · wornINPUT BOX HOUSING BEARING WORN. (SHOULDER)SDR CA080317003Cooling Fan · separated(CAN) DURING THE ENGINE START SEQUENCE, AN UNUSUAL NOISE WAS HEARD BY THE PIC. THE NOISE WAS MOMENTARY AND OCCURRED SEVERAL SECONDS AFTER STARTER GENERATOR ENGAGEMENT AND JUST PRIOR TO ENGINE LIGHT OFF. ENGINE PARAMETERS REMAINED NORMAL SO THE START SEQUENCE WSDR CA080215012Display · malfunctioned(CAN) THERE HAS BEEN REPORTS OF NUMEROUS SYS FAILURE REPORTS FROM THE VEMD SUCH AS NF/NR, MODULE, OVERLIMITS, LANE FAILURES AND LIGHTING FAILURES AND NONE OF THESE FAILURES ACTUALLY OCURRED. THIS IS A PROBLEM WITH THE SOFTWARE AND HAS BEEN A PROBLEM ON THESE SDR 2008FA0000114Starter Gen · failedSTARTER/GENERATOR FAILED TO ENERGIZE.SDR 2008FA0000078Hydraulic System · contaminatedHYD POWER PACK PRE-CLOGGING INDICATOR IS DISPLAYED BEFORE FLIGHT.SDR 2008FA0000058Engine · making metalON 10, OCT. 2007 THE PILOT REPORTED THE ENGINE CHIP WARNING LAMP ILLUMINATED. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. THIS WAS THE FOURTH OCCURRENCE IN 10.9 HOURS. THE ENGINE WAS REMOVED AND RETURNED TO MFG FOR EVALUATION AND REPAIR.SDR CA080118002Battery Box · broken(CAN) DURING DAILY INSPECTION FOUND (2) BROKEN HEAD OF RIVETS ON BATTERY TRAY. RIVETS REPLACED AND AIRCRAFT, SERVICEABLE (TC NR 20080118002)SDR 2008FA0000029Warning Light · false activationENGINE CHIP LIGHT IN CRUISE FLIGHT. INSPECTED BOTH MAGNETIC PLUGS FOR FOREIGN MATERIAL, NONE WAS NOTED. INSPECTED AND TESTED MAGNETIC PLUG HEADS IAW 79-38-00-750-801, INSPECTION AND OPS CHECKS WERE GOOD. REMOVED AND REPLACED ENGINE OIL AND RETURN FILTER IAWSDR 2008FA0000022Oil Jet · leakingENGINE EXPERIENCING INTERNAL OIL LEAKAGE. MFG CONDEMNED ENGINE. ENGINE REMOVED SERVICE, AND RETURNED TO MFG FOR REPAIR.SDR CA071130012Brake · damaged(CAN) MECHANICAL DAMAGE TO ROTOR BRAKE GRID ASSEMBLY, DUE TO IMPROPER OPERATION. TRIGGER WAS NOT DEPRESSED PRIOR TO ENGAGING ROTOR BRAKE HANDLE CAUSING MECHANICAL DAMAGE TO GRID ASSEMBLY. NEW GRID ASSEMBLY INSTALLED (TC NR 20071130012)SDR CA080318005Reservoir · leaking(CAN) THE RESERVOIR SECTION OF THE HYDRAULIC PUMP ASSEMBLY BEGAN TO LEAK HYDRAULIC FLUID. THE LEAK WAS NOTED ON A PREFLIGHT INSPECTION WHERE THERE WAS A PUDDLE OF HYDRAULIC FLUID ON THE TRANSMISSION DECK OF THE HELICOPTER. THE FLIGHT WAS CANCELLED. THE LEAK WASDR 2008FA0000024Engine · making metalENGINE CHIP DETECTOR ILLUMINATED. BOTH CHIP DETECTORS HAD METAL CONTAMINATION. SAMPLES TAKEN, AND MFG CONDEMNED ENGINE. ENGINE REMOVED FROM SERVICE, AND RETURNED TO MFG FOR REPAIR.SDR 2008FA0000020Engine · making metalON GROUND RUN, ENGINE CHIP DETECTOR ILLUMINATED. BOTH DETECTORS HAD METAL SLIVERS. SAMPLES TAKEN, AND MFG CONDEMNED ENGINE. ENGINE REMOVED FROM SERVICE, AND RETURNED TO MFG FOR REPAIR.SDR CA071114007Chip Detector · shorted(CAN) MAIN GEARBOX MAGNETIC CHIP PLUG SHORTED INTERNALLY. (TC NR 20071114007)SDR CA071005002Servo Control · unlocked(CAN) PILOT REPORTED, WHEN PREFLIGHT HYDRAULIC TEST ACTIVATED, CYCLIC MOTORED RT. CYCLIC SHOULD STAY CENTERED DURING HYD TEST. SERVO REPLACED WITH O/H UNIT. GROUND TESTED, SERVICEABLE. AFTER REMOVAL OF SERVO, NOTICED THAT INPUT LEVER WAS SLIGHTLY LOOSE. AFTERSDR CA070717006Wire Harness · burned(CAN) DURING CRUISE FLIGHT, PILOT NOTED THE V/A INDICATION ON THE VEMD WAS OSCILLATING INTERMITTENTLY BETWEEN PARAMETERS, AS WELL, THE LOW ROTOR AURAL WARNING WAS INTERMITTENTLY SOUNDING AND AT TIMES WAS ON STEADY. AT NO TIME WERE ANY ANOMOLIES NOTICED IN THE SDR CA070621001Bushing · failed(CAN) FACTORY NON- FIELD REPLACEABLE BUSHING BOND FAILED IN THE SCISSOR LINK, BROKE FREE AND WORE INTO THE SISSOR LINK. EXCESSIVE PLAY AND "SMOKE" WAS EVIDENT. (TC NR 20070621001)SDR CA070622007Scissor Link · failed(CAN) (1) OF (4) BONDED BUSHINGS FAILED, RESULTING EXCESSIVE PLAY/SMOKING. BUSHING CONTINUED TO WEAR INTO SCISSOR LINK UNTIL CAUGHT AT FIRST 100 HOUR INSPECTION (SINCE NEW). (TC NR 20070622007)SDR PG9A114592Tie Rod · brokenDURING A 100HR INSPECTION, FOUND TWO TT BARS WITH BROKEN LAMINATES. REPLACED WITH NEW.SDR CA070309002Blade · cracked(CAN) BLADE CRACKED BY TRAILING EDGE OF TRIM TAB, IB SIDE. (TC NR 20070309002)SDR CA070307011Cyclic Control · malfunctioned(CAN) CYCLIC CONTROLS JAMMED IN NEUTRAL POSITION, CYCLIC WAS ABLE TO MOVE AFT, FWD, AND LT BUT WAS UNABLE TO MOVE CYCLIC TO THE RT DURING LEVEL CRUISE AT 2500 FT AGL. REDUCED AIRSPEED TO 65 KNOTS AND CONTROLS BROKE FREE AND OPERATED NORMALLY. THEN FLEW BACK TSDR CA070214002Cable · failed(CAN) THROTTLE FROZEN IN THE FULL OPEN POSITION. FUEL FIRE WALL SHUT OFF USED TO CONTAIN ENGINE. (TC NR 20070214002)SDR U0GA114202Tail Boom · crackedTAILBOOM TO FENESTRON AREA HAS 1 INCH CRACK. REMOVED FENESTRON FROM TAILBOOM. REMOVED TAILBOOM FROM AIRCRAFT TO FURTHER INSPECT. UPON FURTHER INSPECTION THE ATTACHMENT FLANGE WAS CORRODED AND FOUND NOT REPAIRABLE. TAILBOOM ASSEMBLY WAS SCRAPPED.SDR PG9A111542Drive Shaft · out of toleranceDURING INSPECTION, THE DRIVE SPLINES OF THE T/R DRIVE SHAFT CENTER SECTION, WERE FOUND TO BE WORN AND OUT OF LIMITS SPECIFIED IN THE MM CH 65-11-00, 6-2. SHAFT WAS REPLACED WITH A NEW SHAFT.SDR CA060328001Fcu · leaking(CAN) DURING ROUTINE DAILY INSPECTION AFTER A FLIGHT, FUEL LEAK NOTICED AT THE MAIN FUEL OUTLET FITTING (NIPPLE) ON THE FCU. SUSPECT O-RING P/N 9794099203 DEFECTIVE. (TC NR 20060328001)SDR 2006FA0000362Plate · unbondedLOWER DROOP RING WEAR PLATE BECAME UNBONDED AND CAME OFF THE MAIN ROTOR HUB. THE ENTIRE PLATE WAS FOUND APPROXIMATELY 20 FT FROM THE AIRCRAFT. IT IS NOT CLEAR WHETHER THE PART FELL OFF DURING ENGINE START UP OR SHUTDOWN. WE BELIEVE THE UNBONDING TO BE THE R
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