Bell 212

Service difficulty reports · 1,185

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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 = '212'
  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.

SDR CA040716004Control Unit · malfunctionedGENERATOR WOULDN'T COME ONLINE, NR 1 AND NR 1 SWAPPED FOR TROUBLESHOOTING, CONTROL CONFIRMED TO BE AT FAULT. CONTROL UNIT REPLACED, GENERATOR BALANCING C/O AND A/C RETURNED TO SERVICE. THIS UNIT CONTAINED WATER WHEN REMOVED.Jun 28, 2004 · Bell 212 · DC Power Distribution SystemSDR CA040726009Support · cracked(CAN) PILOT REPORTED THAT THE AIRCRAFT WOULD ENTER INTO PYLON ROCK VERY EASILY. TRANSMISSION MOUNTS AND FRICTION DAMPERS WERE BEING REPLACED WHEN IT WAS FOUND THAT THE FRICTION DAMPER MOUNT SUPPORTS WERE CRACKED AND AS A RESULT NOT ATTACHED TO THE AIRFRAME. SUJun 24, 2004 · Bell 212 · Main Rotor Transmission MountSDR CA040728005Accumulator · leaking0.5 L OF HYDRAULIC FLUID LOST FROM NR 2 SYSTEM IN 1 HOUR OF FLIGHT. LEAK ISOLATED TO NR 2 ACCUMULATOR. ACCUMULATOR REPLACED AND A/C RETURNED TO SERVICE.May 6, 2004 · Bell 212 · Hydraulic Power Accumulator, MainSDR HEEA095227Fire Loop · false indicationAIRCRAFT WAS INBOUND FROM MALONGO WHEN THE NR 2 ENGINE FIRE LIGHT CAME ON. PULLED TEE HANDLE AND FIRE BOTTLE FIRED, BUT LIGHT STAYED ON. FIRED THE RESERVE BOTTLE AND THE LIGHT WENT OUT.May 5, 2004 · N3131S · Bell 212 · Fire DetectionSDR CA050616007Washer · unserviceable(CAN) CONICAL WASHER FOR TRANSMISSION MOUNT BOLT - LT AFT POSITION - FOUND CRACKED. CRACK HAD NOT TRAVELLED COMPETELY THROUGH WASHER, IT HAD STARTED AT OUTBOARD EDGE. WASHER REPLACED.May 1, 2004 · Bell 212 · Main Rotor Transmission MountSDR CA040428001Access Door · cracked(CAN) DURING THE DAILY INSPECTION THE COWL INSPECTION DOOR HINGE WAS FOUND LOOSE ALLOWING THE DOOR TO HANG DOWN. UPON REMOVAL OF THE COWLING IT WAS FOUND THAT THE ATTACH FLANGE FOR THE COWL ACCESS DOOR HINGE WAS CRACKED ACROSS 75 PERCENT OF THE FLANGE LENGTH. Apr 27, 2004 · Bell 212 · Nacelle/Pylon, Main FrameSDR CA040422004Grip · broken(CAN) DURING ROUTINE GREASING AND SERVICING OF MAIN ROTOR COMPONENTS AME ATTEMPTED TO MOVE THE PILOT'S CYCLIC STICK. AS THE MOVEMENT WAS ATTEMPTED, THE GRIP BROKE INTO TWO PIECES. THE FRACTURE OCCURRED BETWEEN THE FORCE TRIM RELEASE SWITCH AND CARGO RELEASE Apr 18, 2004 · Bell 212 · Main Rotor ControlSDR CA040407011Tape · improper part(CAN) ADHESIVE BACKED LEAD TAPE HAD BEEN USED TO BALANCE THE PITCH ERECTION VANES. IAW MANUFACTURER'S SERVICE ADVISORY NR 75, DATED JANUARY 25, 1985, LEAD TAPE SHOULD NOT BE USED TO BALANCE AIM GYROS AS IT CAN FALL OFF AND CAUSE THE GYRO TO BECOME INOPERATIVEApr 7, 2004 · Bell 212 · Attitude and Direction Data SystemSDR CA040407010Pivot Assy · damaged(CAN) ADJUSTABLE PIVOT HAD MOST OF THE ADJUSTMENT SLOT BROKEN AWAY. PREVIOUS REPAIRER HAD 'FIXED' THE PROBLEM BY FLOODING THE AREA WITH EPOXY TO STOP THE PIVOT FROM ROTATING. THE RETAINING SCREW HAD INSUFFICIENT MATERIAL TO HOLD THE PIVOT AS DESIGNED.Apr 7, 2004 · Bell 212 · Instrument PanelSDR CA040318003Coupling · corroded(CAN) DRIVESHAFT UNDERGOING SCHEDULED 600 HR/12 MONTH INSPECTION/LUBRICATION. COUPLING HAS EXCESSIVE CORROSION. PART REPLACED. COUPLING P/N 212-040-688-3.Mar 9, 2004 · Bell 212 · Tail Rotor Drive ShaftSDR CA040318001Ring · burned(CAN) DURING ROUTINE HOT END BORESCOPE INSPECTION, HOT END DISTRESS WAS NOTED. POWER SECTION REMOVED FROM AIRCRAFT, HOT END REMOVED. COMBUSTION CHAMBER CRACKED (MANY) ON NR 2 LOUVERED COOLING RING. SMALL DUCT BURNED/WARPED IN TWO AREAS (VANES). VANE RING ASMar 9, 2004 · Bell 212 · Turbine SectionSDR CA040301007Bearing · disintegrated(CAN) VISUAL INSPECTION REVEALED BEARING RETAINING FAILURE. APRROXIMATELY ONE QUARTER OF RETAINER MISSING. WILL SEND TO PWC FOR EXAMINATION.Feb 29, 2004 · Bell 212 · Turbine Engine Reduction GearSDR CA040130009Cap · cracked(CAN) NOT UNUSUAL FOR THE OLDER STYLE BEAM CAP TO CRACK. THIS IS A REGION THAT IS PART OF OUR INSPECTION PROGRAM. THERE IS A MORE EXTENSIVE INSPECTION AFTER 10,000 HOURS.Jan 30, 2004 · Bell 212 · Nacelle/Pylon, Bulkhead/FirewallSDR CA040203005Tube · cracked(CAN) DURING THE SCHEDULED INSPECTION CARRIED OUT THE BASE, THE AME NOTICED THAT THE TUBE P/N 3023724 WAS CRACKED BEHIND THE B-NUT AREA. THE CRACKED TUBE WAS REMOVED AND REPLACED.Jan 22, 2004 · Bell 212 · Main Rotor GearboxSDR CA040113006Bolt · sheared(CAN) HELISKI OPERATION. PILOT REPORTED BAD VIBRATION IN TURNS AND CONTROLLABILITY CONCERNS, ALSO IN TURNS. RETURNED TO BASE IMMEDIATELY. SHEARED BOLT FOUND WHERE MAIN ROTOR HYDRAULIC DAMPER CONTROL ARM ATTACHES TO STABILIZER BAR CONTROL TUBE ROD END. BOLT WASJan 7, 2004 · Bell 212 · Main Rotor ControlSDR CA031110002Bushing · incorrect(CAN) TWO PITCH HORNS WERE IN FOR REPAIR, ONE HAD BUSHINGS IN HOLES AND BOTH HAD ODD SERIAL NUMBERS. WE CONTACTED OEM AND THEY SAID THAT THE BUSHED HOLES WOULD NOT BE APPROVED BY THEM. AS FOR THE SERIAL NUMBERS, ONE COULD NOT BE CONFIRNED AS BEING MADE BY MNov 7, 2003 · Bell 212 · Tail Rotor HeadSDR EHA2004F00000Quill Assy · worn27 MINUTES INTO THE FLIGHT, STRAIGHT AND LEVEL, TQ 85 PERCENT, ALT 5700 FT, THE TRANSMISSION CHIP LIGHT ILLUMINATED. MIDDLE CAT EYE WAS WHITE. TURNED AROUND, REDUCED POWER TO 65 PERCENT AND RETURNED WITHOUT FURTHER NOTICE.Sep 17, 2003 · N827MS · Bell 212 · Main Rotor BrakeSDR CA030915013Panel · delaminated(CAN) THIS WAS FOUND ON A DAILY INSPECTION. THE TAILBOOM HELICOMB PANEL WAS DELAMINATED JUST AFT OF THE BAGGAGE COMPARTMENT. THIS AIRCRAFT WAS ON FIRES, DOING LOTS OF HOVERING WHICH MAY HAVE CONTRIBUTED TO THE DELAMINATION DUE TO HOT EXHAUST HITTING IT.Sep 12, 2003 · Bell 212 · Rotorcraft Tail BoomSDR CA040413005Turbine Wheel · damaged(CAN) WHEN THROTTLES WERE ROLLED TO IDLE FOR COOL DOWN A LOW GROWL WAS HEARD AT IDLE. ENGINES WERE SPUN UP TO 100 PERCENT AND GROWL WENT AWAY. BOTH ENGINES WERE BROUGHT BACK TO IDLE AND NOISE WAS HEARD AGAIN. ENGINES WERE SPOOLED UP SEPARATELY AND PROBLEM WASep 6, 2003 · Bell 212 · Turbine SectionSDR HEEA088965Starter Gen · failedGENERATOR FAILED IN FLIGHT. AFTER SHUTDOWN NOTED LOUD GRINDING NOISE COMING FROM THE STARTER WHEN UNIT WAS MOTORED. REPLACED STARTER GENERATOR. TO BE SENT TO VENDOR FOR REPAIR.Aug 26, 2003 · N27805 · Bell 212 · Starter-GeneratorSDR HEEA088964Starter Gen · failedGENERATOR LIGHT BEGAN FLASHING AFTER LANDING. AFTER SHUTDOWN STARTER WOULD NOT MOTOR. REPLACED STARTER GENERATOR. TO BE SENT TO VENDOR FOR REPAIR.Aug 22, 2003 · N5736D · Bell 212 · Starter-GeneratorSDR CA030828001Hose · ruptured(CAN) DURING FLIGHT THE PILOT NOTICED A LOSS OF HYD PRESSURE ON NR 1 HYDRAULIC SYSTEM. THE SYSTEM WAS DEACTIVATED AND THE PILOT RETURNED TO BASE. AFTER LANDING, SYSTEM NR 1 WAS INSPECTED AND A HYD PRESSURE HOSE WAS FOUND RUPTURED. THE HOSE ASSEMBLY WAS REPLACAug 20, 2003 · Bell 212 · Hydraulic System, MainSDR HEEA088963Starter Gen · damagedSTARTER GEN WILL NOT ENGAGE. ARCING BRUSHES.Aug 1, 2003 · N102PH · Bell 212 · Starter-GeneratorSDR HEEA088962Starter Gen · inoperativeGENERATOR WILL NOT COME ON.Jul 29, 2003 · N102PH · Bell 212 · Starter-GeneratorSDR CA030731020Hose · ruptured(CAN) TRANSMISSION OIL HOSE SWOLLEN AND BLOWN APPROX.6 INCHES FROM FITTING.PILOT HAD LOW OIL PRESSURE WARNING LIGHTCOME ON AND CARRIED OUT PRECAUTIONARY LANDING TO INVESTIGATE. HOSE IS SUBJECT TO TENSION AND TORSION AS TRANSMISSION IS MOUNTED WITH LORD RUBBER Jul 29, 2003 · Bell 212 · Main Rotor GearboxSDR CA030825008Attach Fitting · broken(CAN) DURING CRUISE FLIGHT THE CREW FELT A (POP) ON THE AIRCRAFT WITH NO OTHER INDICATIONS. NO WARNING LIGHTS, NO CONTROL OR HANDLING PROBLEMS. AFTER LANDING, THE ENGINEER CARRIED OUT HIS ROUTINE (BEFORE FLIGHT) INSPECTION. LOOKING AT THE TAILBOOM TO FUSELAGEJul 26, 2003 · Bell 212 · Rotorcraft Tail BoomSDR CA030731019Blade · fractured(CAN) COMPRESSOR TURBINE BLADE FRACTURED CAUSING COMPLETE ENGINE FAILURE AT APPROX. 40KNOTS FORWARD AIRSPEED, PILOT CARRIED OUT EMERGENCY LANDING.ENGINE REMOVED FOR EXAMINATION BY PWC.Jul 17, 2003 · Bell 212 · Turbine Engine Compressor SectionSDR HEEA088058Blade · damagedMAIN ROTOR BLADE SKIN SEPERATION OUTBOARD END LOWER SURFACE FROM TIP INBOARD APPROXIMATELY 2.25 INCHES AND AFT FROM LEADING EDGE APPROXIMATELY 2 INCHES. REPLACED WITH SERVICEABLE PART.Jul 3, 2003 · N27805 · Bell 212 · Main Rotor BladesSDR CA031028009Compressor · failed(CAN) ENGINE FAILURE, ENGINE FIRE, FIRE EXTINGUISHED. - AIRCRAFT LANDED SINGLE ENGINE.Jul 2, 2003 · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA088059Gearbox · making metalMAIN ROTOR TRANSMISSION CHIP LIGHT ILLUMINATED. REPLACED WITH SERVICEABLE PART.Jul 2, 2003 · N3131S · Bell 212 · Main Rotor GearboxSDR CA030708013Line · ruptured(CAN) THE PILOT REPORTED A NOISE (FROM AN UNLOADED HYDRAULIC PUMP) FOLLOWED BY THE ODOR OF HYD FLUID. HYDRAULIC PRESSURE ON SYSTEM NUMBER 2 DROPPED TO ZERO. THE PILOT INITIATED AN UNSCHEDULED LANDINGTO INVESTIGATE THE PROBLEM. AFTER LANDING A CHAFED HYD LINEJul 1, 2003 · Bell 212 · Hydraulic System, MainSDR CA030625001Elbow · cracked(CAN) A HYD LEAK WAS FOUND DURING A GROUND RUN TO CHECK FOR LEAKS AFTER MINOR MAINTENANCE. THE ENGINEER NOTICED HYD FLUID DRIPPING FROM AN ELBOW FITTING ON THE NR 1 HYD PUMP. THE FITTING AND LINE B-NUT WERE CHECKED AND FOUND SECURE. THE FITTING WAS REMOVED ANDJun 23, 2003 · Bell 212 · Hydraulic Pump (Electric/Engine), MainSDR CA030710002Blade · failed(CAN) VOID IN S.S. LEADING EDGE STRIP OUTBOARD BLADE TIP JUNCTION OF BLADE SKIN. VOID AREA APPROXIMATELY 0.175 INCH CHORDWISE X 0.375 INCH SPANWISE. BLADE REMOVED AND SENT FOR REPAIR. SN A-7719.Jun 6, 2003 · Bell 212 · Tail Rotor BladesSDR AGQA088682Contactor · brokenINTERMITTENT, SLOW STARTS, CONTACTOR.Jun 5, 2003 · N8530F · Bell 212 · Starter-GeneratorSDR CA030530001Link · broken(CAN) AFTER THE FLIGHT AN INSPECTION OF THE AIRCRAFT IT WAS DETERMINED THAT PART OF THE LIFT LINK HAD BROKEN OFF NEAR THE UPPER STAKED BEARING BOSS. THE CAUSE OF THE BROKEN PIECE UNDETERMINED AT THIS TIME, INVESTIGATION IS ON GOING.May 26, 2003 · Bell 212 · Main Rotor Transmission MountSDR CA030613009Case · broken(CAN) WHILE CARRYING OUT A DAILY CHECK ON THE AIRCRAFT THE ENGINEER NOTICED THAT THE ONE EAR OF THE LIFT LINK SUPPORT ON THE TRANSMISSION SUPPORT CASE WAS BROKEN OFF. THE TRANSMISSION SUPPORT CASE WAS REPLACEDMay 25, 2003 · Bell 212 · Main Rotor GearboxSDR HEEA086675Hanger Assy · corrodedPITTING ON OUTPUT FLANGE. REPLACED 4 EACH CLAMPS 204-040-811-001 DUE TO CORROSION. REPAIRED.May 22, 2003 · N5736J · Bell 212 · Tail Rotor Drive ShaftSDR HEEA086610Bearing · wornBELLCRANK ASSY HAS WORN BEARINGS. REPLACED BEARING DW-4 DUE TO WORN AND SLEEVE 120-015-4KA DUE TO WORN. REPAIRED.May 21, 2003 · N5736J · Bell 212 · Tail Rotor Control SystemSDR HEEA086609Bearing · wornBELLCRANK HAS WORN BEARINGS. REPLACED BEARING DW-4 DUE TO WORN AND SLEEVE 120-015-4KA DUE TO WORN. REPAIRED.May 21, 2003 · N5736D · Bell 212 · Tail Rotor Control SystemSDR HEEA086597Bushing · wornGUIDE BUSHINGS WORN. REPLACED 2 EACH 204-001-036-001 GUIDES DUE TO WORN AND BEARING MS27643-4 DUE TO WORN. REPAIRED.May 21, 2003 · N5736J · Bell 212 · Main Rotor ControlSDR CA030708011Tube · chafed(CAN) CONTROL TUBE CHAFING IS 0.017 INCH DEEP. TUBE IS STEEL ALLOY. TUBE CHAFED FROM CONTACT WITH FIREWALL BOOT/ALUMINUM FLANGE. TUBE REPLACED.May 15, 2003 · Bell 212 · Main Rotor Drive SystemSDR CA030708010Shaft · stripped(CAN) DURING ATTEMPTED DISASSEMBLY, WE WERE UNABLE TO REMOVE THREADED SLEEVE PN 209011719003. FOUND INCORRECT HARDWARE STARKUP (WASHER PN 212010714003 MISSING). PRESUME SLEEVE BOTTOMED OUT, NUT MS14145L8 ALSO, AND HENCE THREADS STRIPPED ON TORQUE UP. HAD TO HMay 15, 2003 · Bell 212 · Tail Rotor GearboxSDR CA030708009Control Arm · chafed(CAN) CONTROL TUBE AT PRIOR MAINTENANCE EVENT WAS INSTALLED BACKWARDS (180 DEGREES OUT). TUBE HAD NYLATRON SLEEVES BUT REVERSED POSITION CAUSED WEAR AT AFT FAIRLEAD. TUBE WORN 0.013. TUBE WALL THICKNESS IS 0.035. PART REPLACED.May 1, 2003 · Bell 212 · Tail Rotor SystemSDR CA030708008Hanger Assy · corroded(CAN) DEFECTS FOUND DURING ROUTINE INSPECTION/LUBRICATION. PROBLEM MAY HAVE EXISTED ATPRIOR INSPECTIONS BUT NOT DISCOVERED. 4 INNER, 4 OUTER COUPLINGS REPLACED. CORROSION PITS/SPALLING WERE ON SEVERAL TEETH OF EACH COUPLING.May 1, 2003 · Bell 212 · Tail Rotor Drive ShaftSDR CA030530003Blade · cracked(CAN) DURING ANNUAL M/R BLADE INSPECTION AME DISCOVERED A SMALL CORROSION PIT IN BLADESKIN LOCATED AT BLADE STATION 13.7 & 5.5 FROM LEADING EDGE.(SEE ATTACHED PHO TOS)FOUR CRACKS WERE FOUND ORIGINATING FROM THE PIT.THE LONGEST CRACK WAS 14 INCH CHORDWISE, TWO Apr 28, 2003 · Bell 212 · Main Rotor BladesSDR CA030416003Bellcrank · failed(CAN) DURING APPROACH THE DROOP COMPENSATOR SYSTEM FAILED TO RESPOND AND ENGINE RPM INCREASED AS THE COLLECTIVE WAS LOWERED. PILOT ADJUSTED ENGINE RPM USING THE ELECTRICAL TRIM SYSTEM, (BEEP SWITCH). SUBSEQUENT INSPECTION FOUND THAT THE ENGINE GOVERNOR CONTROLApr 6, 2003 · Bell 212 · Fuel Controlling SystemSDR EHI0404Spring · failedHYDRAULIC SYSTEM FEEDBACK FELT AND AUDIBLY OBSERVED WHILE IN ALL OPERATIONAL GROUND AND FLIGHT PROFILES. DURING MAINTENANCE TROUBLESHOOTING THE SUBJECT SERVO SPRING WAS FOUND FATIGUED/BROKEN.Apr 4, 2003 · N59633 · Bell 212 · Hydraulic System, MainSDR CA030425003Bearing · making metal(CAN) DURING 600 HR TRANSMISSION INSPECTION INPUT QUILL WAS REMOVED TO FACILITATE MAINTENANCE. BEARING DEFECTS WERE IDENTIFIED THAT REQUIRED REPLACEMENT PRIOR TO AIRCRAFT WAS RETURNED TO SERVICE.Mar 31, 2003 · Bell 212 · Main Rotor GearboxSDR HEEA085017Tach Generator · contaminatedTRANSMISSION RPM LIGHT FLASHING AND AUDIO HORN GOING OFF. FOUND TACH GEN FULL OF OIL AND WATER ON SEAL AROUND BACKPLATE. REPLACED WITH SERVICEABLE PART.Feb 27, 2003 · N27805 · Bell 212 · Engine RPM Indicating SystemSDR CA030220001Window · missing(CAN) HELI SKIING: HELICOPTER WAS UP IN AN ALPINE LANDING PAD. THE PASSENGERS HAVE BEEN ON LOADED FROM THEHELICOPTER. THE HELICOPTER SKIING GUIDE ON THE RIGHT SIDE OF THE HELICOPTER GAVE THE SIGNAL TO TAKE OFF. THE HELICOPTER TOOK OFF AND DESCENDED DOWN THE HIFeb 14, 2003 · Bell 212 · Passenger Compartment Windows
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