Bell 212

Service difficulty reports · 1,185

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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 CA060118002Engine · malfunctioned(CAN) HELI-SKING: AC DROPPED SKIERS AT TOP, HAD LIFTED OFF MOUNTAIN TO GO TO SKIER PICK UP PAD. AC WAS ON A DESCENDING, SLIDE SLIPPING, PILOT CARRIED OUT A SCAN OF INDICATORS, NOTICE NR AT 99 PERCENT, DESCENDING TO 98 PERCENT, WAS EXPECTING A 101 PERCENT FORJan 16, 2006 · Bell 212 · Engine (Turbine/Turboprop)SDR CA060104009Shaft · crackedPERFORMED MAGNETIC PARTICLE INSPECTION IAW BHT-ALL-SPM, SHAFT P/N 2660-1635-01 WAS FOUND TO BE CRACKED IN KEY WAY, PART HAS BEEN SUBSEQUENTLY SCRAPED. BELL HELICOPTER HAS BEEN NOTIFIED FOR INTEREST AND INFORMATION ONLY.Jan 4, 2006 · Bell 212 · Engine Oil CoolerSDR CA060129016Case · fractured(CAN) DURING APPROACH, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY NOISE AND VIBRATION. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT ISPECTION REVEALED A FRACTURED INLET CASE STRUT. (TC NR 20060129016)Dec 13, 2005 · Bell 212 · Turbine Engine Compressor SectionSDR CA051223005Compressor · damagedDURING A MAINTENANCE CHECK FLIGHT, THE ENGINE EMITTED A LOUND NOISE ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE COMPRESSOR AND INLET AREA. P&WC WILL INVESTIGATE THE EVENT ANNov 14, 2005 · Bell 212 · Turbine Engine Compressor SectionSDR HEEA107314Packing · inoperativeON CLIMB-OUT HEARD A LOUD WHINNING NOISE, HYDRAULIC CAUTION LIGHT CAME ON AND NR 1 HYDRAULIC PRESSURE WENT TO ZERO. STARTED EMERGENCY CHECK LIST AND NOISE STOPPED AND PRESSURE CAME BACK UP. MOMENTS LATER NOISE RETURNED AND PRESSURE DROPPED TO ZERO. MAINTENANov 9, 2005 · N5736J · Bell 212 · Hydraulic System, MainSDR CA051006011Panel · debonded(CAN) DEBONDED BEYOND LIMITS ON LT SIDE BETWEEN STATION 241.22 AND 324.51.Oct 4, 2005 · Bell 212 · Rotorcraft Tail BoomSDR U0GA106181Crossover Tube · brokenDURING NORMAL SHUTDOWN PROCEDURES, THE FORWARD CROSS TUBE BROKE IN HALF CAUSING THE NOSE OF THE AIRCRAFT TO LOWER. NO HARD LANDING WAS REPORTED PRIOR TO THIS FAILURE. INITIAL EXAMINATION OF THE TUBE REVEALS THAT THE TUBE BREAK WAS NOT FRESH. THE ATTACHMENT SASep 27, 2005 · N507EH · Bell 212 · Main Landing Gear Strut/Axle/TruckSDR CA051124003Bearing · unserviceableNEW SPHERICAL BEARING RECEIVED WITH EXCESSIVE AXIAL PLAY. AXIAL PLAY OF THE INNER RACE TO OUTER RACE WAS MEASURES AT 0.032" THE BHT-ALL-SPM LIMIT FOR A USED BEARING IS 0.030". THE BEARING HAS BEEN RETURNED TO BHT FOR WARRANTY WITH A BHT MMIR.Sep 20, 2005 · Bell 212 · Main Rotor GearboxSDR CA051017009Fuel Heater · unserviceableNR 2 ENGINE FUEL HEATER FOUND TOO HOT TO TOUCH FOLLOWING SHUTDOWN. HEATER REPLACED AND A/C RETURNED TO SERVICE.Sep 9, 2005 · Bell 212 · Fuel HeaterSDR CA051025003Gearbox · contaminatedFOUND A BOLT LOCKTAB IN NR 1 RGB CHIP DETECTOR HOUSING WHEN INVESTIGATING AN ENGINE CHIP LIGHT. ON FURTHER INVESTIGATION A SECOND LOCKTAB WAS FOUND IN THE VICINITY OF THE CHIP DETECTOR HOUSING. POWER SECTION WAS SEPARATED FROM THE C/BOX TO TROUBLESHOOT THE SSep 6, 2005 · Bell 212 · Turbine Engine Reduction GearSDR ALGA105864Nut · crackedCRACK INDICATION, REPLACED AS REQUIRED.Aug 26, 2005 · Bell 212 · Main Rotor HeadSDR 2005FA0001139Fitting · detachedDURING FLIGHT FITTING BECAME DETACHED CAUSING LOSS OF OIL. FOUND FITTING MADE OF ALUMINUM. NEW FITTING MADE OF STEEL. (K)Aug 8, 2005 · N212AH · Bell 212 · Turbine Engine Oil SystemSDR CA051104019Bleed Valve · stuckCOMPRESSOR STALL CAUSED OSCILLATIONS IN AIRFRAME. ENGINE POWER REDUCED TO IDLE. A SINGLE ENGINE LANDING CARRIED OUT IN NEAR BY FIELD. ENGINE REPLACED WITH SERVICEABLE UNIT. IT WAS FOUND TO BE A STUCK CLOSED, BLEEDVALVE AND 3RD STAGE COMPRESSOR BLADE DAMAGEAug 3, 2005 · Bell 212 · Compressor Bleed ValveSDR CA060329005Engine · failedWHILE IN CRUISE, A LOUD BANG WAS HEARD FOLLOWED BY AIRFRAME SHUDDER. AN EMERGENCY WAS DECLARED AND AIRCRAFT STARTED LANDING PROCEDURES. NR 2 ENGINE INDICATING FAILURE AND ROLLED BACK. AIRCRAFT SUCCESSFULLY LANDED IN A FIELD. POWER RECOVERY OF NR 2 ENGINE AAug 1, 2005 · Bell 212 · Turbine Engine Compressor SectionSDR CA060329003Case · brokenWHILE IN CRUISE, A LOUD BANG WAS HEARD AND AC SHUDDERED. AC SETTLED OUT AND CREW DIVERTED TO AIRPORT. INSPECTION OF AC REVEALED MAIN TRANSMISSIOM SUPPORT CASE BROKEN AT DRAG LINK ATTACHMENT POINT. AC GROUNDED AND MAIN TRANSMISSION REPLACED. AC RELEASED BACJul 30, 2005 · Bell 212 · Main Rotor GearboxSDR CA050816002Plate · mismanufactured(CAN) INK STAMPED NUMBERS ON PART INDICATE THIS IS A BREAKOUT PART ACCORDING TO BELL TEXTRON, MANUFACTURED FOR US ARMY BY MORRIS MANUFACTURING. PURCHASE RECORDS AT BELL HELICOPTERS AS FAR BACK AS 1979 INDICATE THAT MORRIS MANUFACTURING WAS NEVER A SUPPLIER FOJul 25, 2005 · Bell 212 · Main Rotor Mast/SwashplateSDR CA050728010Engine · shutdownTHE ENGINE EXPERIENCED A POWER LOSS IN CRUISE. THE POWER SECTION WAS SHUT DOWN IN FLIGHT. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.Jul 24, 2005 · Bell 212 · Engine (Turbine/Turboprop)SDR CA050826009Fuel Control · malfunctioned(CAN) DURING POST INSPECTION RUN UP, THE NR 2 ENGINE WOULD NOT START. THE AFCU WAS REPLACED AND FURTHER GROUND RUNS CARRIED OUT AND ENGINE STARTED WITH NO FURTHER PROBLEMS. THE AIRCRAFT WAS RETURNED TO THE FLIGHT LINE.Jul 1, 2005 · Bell 212 · Fuel Controlling SystemSDR ALGA105415Blade · corrodedDURING ROUTINE MAINTENANCE INSPECTION CORROSION WAS FOUND ON THE SPAR AT LEADING EDGE SPLICE JOINT / BLADE WAS REMOVED FOR FURTHER INSPECTION, DUE TO EXTENT OF DAMAGE TO SPAR BLADE WAS SCRAPPED!Jun 24, 2005 · Bell 212 · Main Rotor BladesSDR CA050615001Fitting · cracked(CAN) FITTING FOUND CRACKED AT ATTACHMENT BOLT HOLE. DEFECT FOUND BY NDT TECHNICIAN USING EDDY CURRENT INSPECTION METHOD.Jun 14, 2005 · Bell 212 · Rotorcraft Tail BoomSDR CA050706011Blade · debondedBOTTOM SKIN OF BLADE DEBONDED FROM TIP ALONG STAINLESS LEADING EDGE FOR 28 INCHES AND APPROX 3 INCHES PEELED BACK, CAUSING SEVERE VERTICAL VIBRATION. PILOT DECLARED A MAYDAY AND CARRIED OUT PRE-CAUTIONARY LANDING. BLADE WAS REMOVED AND SENT TO CTI AS IT WAS Jun 10, 2005 · Bell 212 · Main Rotor BladesSDR CA050607001Saddle · cracked(CAN) THE RT OUTER SADDLE CRACKED AT THE AFT SPLIT LINE AT THE RIDGE LINE FOLLOWING THE CONTOUR OF THE SKID TUBE AND CROSS TUBE. THE CRACK TURNS 90 DEGREES FROM THE TOP OF THE SADDLE TO THE REAR. THE PART WAS SENT TO HEADQUARTERS FOR INSPECTION.Jun 6, 2005 · Bell 212 · Main Landing Gear Strut/Axle/TruckSDR CA050526006Line · failed(CAN) RAPID LOSS OF HYDRAULIC PRESSURE ON GROUND RUN-UP. FOUND TO BE BLOWN FLEX LINE AT BOTTOM FITTING CRIMP RESULTING IN LOSS OF NR 2 HYDRAULIC PRESSURE & FLUID. PROBABLE CAUSE COMBINATION OF TWISTED LINE & TRANSMISSION MOVEMENT CAUSED LINE TO FATIQUE & RUPTMay 16, 2005 · Bell 212 · Hydraulic System, MainSDR CA050527033Nut · cracked(CAN) THE M/R HUB WAS IN FOR OVERHAUL, AS PART OF THE OVERHAUL THE ACORN NUTS HAD TOBE NDT. ONE NUT PASSED AND THE OTHER REJECTED. TO CONFIRM THE NDT OF THE ACORN NUT WE SENT IT TO ANOTHER NDT AMO. STRIKE TWO THIS ACORN NUT WAS REJECTED DUE TO A CRACK. THE CRAMay 16, 2005 · Bell 212 · Main Rotor HeadSDR ALGA100674Drag Brace · crackedNDT INSPECTION FOUND CRACK OUTSIDE EDGE, BARREL BORE / REPLACED CLEVIS WITH NEW CLEVIS, BY OVERHAUL SHOP.May 5, 2005 · Bell 212 · Main Rotor HeadSDR CA050418015Blade · damagedON DESCENT, HEARD SOUND SIMILAR TO WHISTLE & HEARD SOUNDS DURING RT BANK ON APPR. A/C SHUTDOWN, INSP M/R BLADES & STAB BAR FOR CAUSE OF NOISE. SUSPECT BLADE TAPE ON STAB BAR LOOSE. NO DEFECTS FOUND. NO FURTHER NOISE APPARENT. APPROX 1-2 MINS INTO NEXT FLTApr 12, 2005 · Bell 212 · Main Rotor BladesSDR AU510001454Gearbox · making metal(AUS) COMBINING GEARBOX METAL CONTAMINATION. (CASA# 510001454)Apr 6, 2005 · Bell 212 · Turbine Engine Reduction GearSDR CA050401011Table · wrong part(CAN) MFG 5 MAN SEAT POSITION IS SHOWN AT FS 119. SEAT HAS 2 IN THICK BACK CUSHION AT TRANSMISSION BULKHEAD STA. MM PUTS 5 MAN TROOP SEAT AT FS 117. MIDDLE PASSENGER FOR THAT SEAT CONFIGURATION HAS ITS BACK DIRECTLY AGAINST THE TRANSMISSION BULKHEAD. IT SEEMSApr 1, 2005 · Bell 212 · Passenger Compartment EquipmentSDR CA050228013Engine · unknown(CAN) A/F 18258 HOURS. HELI SKIING OPERATION. PILOT WAS DESCENDING DOWN A HILL AND SETTING UP HIS APPROACH TO LAND HELICOPTER. THE PILOT PULLED IN POWER TO CONTROL HIS DESCENT RATE AND NOTICED THAT THE ENGINES REMAINED IN FLIGHT IDLE. HE CHECKED HIS THROTTLE Feb 24, 2005 · Bell 212 · Engine (Turbine/Turboprop)SDR CA050307001Engine · unresponsive(CAN) ON APPROACH NEITHER ENGINE RESPONDED TO INCREASED COLLECTIVE. THE AIRCRAFT AUTOROTATED TO A HEAVY LANDING. MFG WILL MONITOR THE INVESTIGATION INTO THIS EVENT AND WILL SUPPLIMENT THIS REPORT TO REFLECT ROOT CAUSE, ONCE ESTABLISHED.Feb 24, 2005 · Bell 212 · Engine (Turbine/Turboprop)SDR CA050209006Fitting · cracked(CAN) UPPER RT TAILBOOM ATTACH FITTING ON FUSELAGE FOUND CRACKED FROM LOCK FASTENER HOLE.Feb 9, 2005 · Bell 212 · Rotorcraft Tail BoomSDR CA050125017Collective Stick · broken(CAN) THE ENGINEER WAS ABOUT TO GREASE THE SWASHPLATE. TO GREASE SOME OF THE ZERK FITTINGS IT IS EASIER TO LIFT THE COLLECTIVE CONTROL STICK UP. THE ENGINEER WAS MOVING THE COLLECTIVE CONTROL STICK UP WHEN THE RIDGED TUBE BENT AND BROKE IN TWO. THE BREAKAGE Jan 25, 2005 · Bell 212 · Main Rotor ControlSDR CA050112006Line · fractured(CAN) THE ENGINE NO.2 POWER-SECTION EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CRUISE, FALLING BELOW GROUND IDLE.THE POWER-SECTION WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO BASE. SUBSEQUENT INSPECTION REVEALED A FRACTURED P3 PNEUMATIC TUBE LEADINGJan 7, 2005 · Bell 212 · Pneumatic Distribution SystemSDR CA050110003Coupling · corroded(CAN) DURING SCHEDULED INSPECTION PITTING CORROSION IN EXCESS OF .005 INCH HAS BEEN DISCOVERED. THE PATTERN AND LOCATION OF CORROSION PITTING CONFORMS TO PROCESS STAMP IMPRESSION (186). IT IS LIKELY THAT IMPROPER INK HAS BEEN USED DURING SHAFT OVERHAUL. OVEJan 5, 2005 · Bell 212 · Engine/Transmission CouplingSDR HEEA108771Window · departedLH CARGO DOOR FWD WINDOW DEPARTED IN FLIGHT. MAINTENANCE INSPECTED AIRCRAFT FOR DAMAGE AND INSTALLED A NEW WINDOW.Dec 8, 2004 · N5736J · Bell 212 · Door WindowsSDR CA041007008Control Tube · cracked(CAN) WE ARE PRESENTLY DOING A 3000 HOUR AIRFRAME INSPECTION. THIS VERTICAL UPPER SERVO CONTROL TUBE WAS SENT TO A NDT SHOP FOR INSPECTION. THE NDT SHOP STATED THAT THEIR WAS A LONGDITUDANAL CRACK ON THE UPPER END OF CONTROL TUBE. SINCE THE LAST INSPECTION TOct 7, 2004 · Bell 212 · Main Rotor ControlSDR CA040901008Panel · cracked(CAN) DURING ROUTINE INSPECTION AME DISCOVERED A CRACK SURROUNDING ELEVATOR CONTROL SUPPORT (P/N 205-001-920-001) IN A FWD AND AFT SKIN OF TAILBOOM PANEL (205-032-819-3). PANEL REPLACED, A/C RETURNED TO SERVICE.Sep 29, 2004 · Bell 212 · Rotorcraft Tail BoomSDR CA041109008Wire · arced(CAN) FUEL QUANTITY REPORTED AS FLUCTUATING. DURING TROUBLESHOOTING PROCESS ONE OF THE WIRES ON THE RT TANK FORWARD FUEL PROBE WAS FOUND ARCING. PROBE REPLACED.Sep 27, 2004 · Bell 212 · Fuel System WiringSDR CUC2004F00000Bearing · inoperativeNR 1 POWER SECTION, NR 6 BEARING KEY WASHER WAS FOUND DISTORTED WITH OPEN FRACTURE AT THE STAKING LOCATIONS OF THE WASHER. MISSING WASHER PARTS FOUND ON CHIP PLUG. TIME SINCE LAST GEARBOX REPAIR 767.3 HOURS.Sep 27, 2004 · N911KW · Bell 212 · Accessory GearboxesSDR CA040910002Hose · burstBEFORE FIRST FLIGHT DURING HYDRAULIC TESTING, PILOT SWITCHED 'OFF' NR 2 HYDRAULIC SYSTEM. AFTER THE SYSTEM WAS SWITCHED BACK 'ON' PRESSURE INDICATION FELL OFF TOZERO. A/C WAS SHUTDOWN. SUBSEQUENT INSPECTION REVEALED THAT THE BRAIDED NR 2 HYDRAULIC HOSE FROMAug 24, 2004 · Bell 212 · Hydraulic System, MainSDR KHS2004F00000O-Ring · cutNR 1 HYD SYSTEM ACCUMULATOR O-RING (PN MS28775-212) FAILURE, CAUSING LOSS OF HYDRAULIC FLUID IN THAT SYSTEM. NR 1 SYSTEM WAS SHUT OFF AND AIRCRAFT RETURNED TO AIRPORT ON NR 2 SYSTEM WITH NO FURTHER INCIDENT. NR 1 HYDRAULIC ACCUMULATOR O-RING, (PNMS28775212).Aug 23, 2004 · N144WA · Bell 212 · Hydraulic Power Accumulator, MainSDR CA040908005Turbine · failedDURING HIGH HOVER (LONG LINE) TO PICK UP LOAD, NR 1 POWER SECTION FAILED. INITIAL COMPRESSOR INLET INSPECTION (PLENUM AREA) REVEALED MOLTEN PARTICLES. FURTHER INVESTIGATION WILL COMMENCE ON POWER SECTIONREMOVAL/TEARDOWN INSPECTION. (ALTSN-6421.0).Aug 19, 2004 · Bell 212 · Turbine SectionSDR CA040831005Engine · failed(CAN) DURING HIGH HOVER (LONG LINE) TO PICK UP LOAD, NR1 POWER SECTION FAILED. INITIAL COMPRESSOR INLET INSPECTION (PLENUM AREA) REVEALED MOLTEN PARTICLES. FURTHER INVESTIGATION ON POWER SECTION REMOVAL/TEARDOWN INSPECTION.Aug 19, 2004 · Bell 212 · Engine (Turbine/Turboprop)SDR CA041123008Line · broken(CAN) LINE BROKE. A/C RETURNED TO BASE. LINE WAS REPLACED. A/C WAS RETURNED TO SERVICE. NO FURTHER DEFECTS.Jul 20, 2004 · Bell 212 · Engine Bleed Air SystemSDR CA040812006Angle · corroded(CAN) DURING IMPORT INSPECTION, RT FUEL CELL CAVITY AFT CAP ANGLE FOUND BADLY CORRODED (EXFOLIATION). PART REPLACED.Jul 19, 2004 · Bell 212 · Fuel StorageSDR CA040812003Bulkhead · cracked(CAN) BULKHEAD FRAME CRACKED ADJACENT TO RT UPPER TAILBOOM ATTACH BOLT. FRAME REPLACED.Jul 19, 2004 · Bell 212 · Rotorcraft Tail BoomSDR CA040928016Line · broken(CAN) UNCOMANDED DECEL TO IDLE. PART CHANGED, ENGINE RETURNED TO NORMAL OPS.Jul 19, 2004 · Bell 212 · Turbine SectionSDR EHA2004F00003Line · chafedHYDRAULIC LEAK FROM AREA OF CARGO HOOK. TRACED TO TAIL ROTOR SAS LINK HYDRAULIC LINE CHAFED BY FUEL VENT LINE. REPLACED LINE, REROUTED AND SECURED FUEL VENT LINE. LEAK CHECKED AND MOC FLIGHT GOOD. (AL03200404250)Jul 13, 2004 · N398EH · Bell 212 · Hydraulic System, MainSDR CA041123011Case · broken(CAN) PILOT REPORTED HEARING A LOUD BANG AND THOUGHT PIECES OF THE HELICOPTER FELL FROM THE BELLY. PILOT WAS FLYING VERTICAL REFERENCE WITH A BAMBI BUCKET. UPON IMMEDIATE RETURN TO THE PAD, THE HELL HOLE SIDE INSPECTION PANELS WERE REMOVED AND THE SUPPORT CAJul 12, 2004 · Bell 212 · Main Rotor GearboxSDR CA041123012Fuel Cell · split(CAN) LOW FUEL LIGHT COMING ON WITH 250-300 LBS INDICATED IN LT LOWER FUEL CELL. INVESTIGATION FOUND SPLIT IN FUEL CELL INTERNALLY ACROSS BAFFLE, WHICH ACTED LIKE A ONE WAY VALVE. THIS WOULD PUMP FUEL AWAY FROM BOOST PUMP WHEN A/C IS IN UNUSUAL ATTITUDES (HOVJul 7, 2004 · Bell 212 · Fuel Storage
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