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"

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SDR CA090324006Blade · debonded(CAN) DURING A DAILY INSP, THE ENGINEER NOTICED CRACKS IN THE BONDING SUROUNDING THE EFFECTED TAIL ROTOR TIP CAP. FURTHER INVESTIGATION REVEALED DELAMINTAION OF THE SKIN TO THE TIP CAP ON BOTH SIDES OF THE BLADE. NO ABNORMAL VIBRATIONS WERE REPORTED FOLLOWING Mar 19, 2009 · Bell 212 · Tail Rotor BladesSDR CA090316004Turbine Blades · separated(CAN) HELI SKIING AFTER PASSENGERS DEPLANED, THE PILOT WAS GIVEN THE OK TO DEPART, THE PILOT ROLLED UP THE THROTTLES AND HEARD A NOISE OFF THE NR POWER SECTION AND AN AIRFRAME VIBRATION. SHUTDOWN ENGINE AND VIBRATION AND NOISE WENT AWAY.Mar 14, 2009 · Bell 212 · Turbine SectionSDR CA090105005Rivet · shearedATTACHMENT RIVETS ATTACHING TEE CAP TO OUTBOARD TITAINIUM PANEL P/N 205-030-209-020 UPPER EDGE RIVET P/N MS20470AD4-XX SHEARED.Jan 5, 2009 · Bell 212 · Fuselage Miscellaneous StructureSDR CA090127013Longeron · corrodedCORROSION OF LONGERON AND SPLICE UNDER SPLICE. FOUND WHILE PERFORMING INSPECTION REQUIRED FOR ASB212-90-63. CORROSION WAS VERY SEVERE WHEN SIGNS WERE VISIBLE BECAUSE CORROSION WAS BETWEEN LONGERON AND SPAR SPLICE FAYING SURFACES.Dec 5, 2008 · Bell 212 · Rotorcraft Tail BoomSDR CA081008006Window Frame · cracked(CAN) 10 INCH CRACK FOUND AT UPPER LT CORNER OF WINDOW FRAME.Oct 7, 2008 · Bell 212 · Passenger/Crew DoorsSDR CA080930003Seal · leaking(CAN) DURING CRUISE, THE OIL PRESSURE STARTED TO FLUCTUATE FOLLOWED BY A DROP TO ZERO, WHICH WAS ACCOMPANIED BY A GEARBOX CHIP DETECTOR WARNING FOR NR 2 POWER SECTION. A SINGLE ENGINE LANDING WAS PERFORMED. TROUBLESHOOTING FOUND LITTLE OIL LEFT IN THE ENGINE Aug 31, 2008 · Bell 212 · Turbine Engine Oil SystemSDR CA080924012Engine · failed(CAN) ACFT WAS IN HOVER AND WAS TRANSITIONING TO FWD FLIGHT WHEN THE LT ENGINE ROLLED BACK IN POWER AND SHUTDOWN. PILOT LANDED THE ACFT SUCCESSFULLY ON 1 ENGINE. LT ENGINE WAS REMOVED AND SENT TO MFG FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVAug 15, 2008 · Bell 212 · Engine (Turbine/Turboprop)SDR CA080923006Turbine Wheel · disintegrated(CAN) WHILE HOVERING DURING TAKEOFF, NR1 PWR SECTION LOST POWER (PILOT REPORTED HEARING LOUD BANG). ACFT PUT DOWN WITHOUT FURTHER INCIDENT, NR2 POWER SECTION SHUTDOWN. POWER SECTION REPLACED. ACFT RETURNED TO SERVICE. PRELIMINARY INSP REVEALED FAILURE OF TAug 6, 2008 · Bell 212 · Turbine SectionSDR CA080728010Pilot Valve · chattering(CAN) ACFT ENCOUNTERED VIBRATION, FELT THROUGH FLIGHT CONTROLS. VIBRATION WORSENED RAPIDLY DURING RETURN TO BASE. UPON ARRIVAL TO BASE, ENGINEER INSPECTED ACFT AND FOUND LT CYCLIC SERVO PILOT VALVE TO BE CHATTERING EXCESSIVELY, CAUSING UNCOMMANDED CYCLIC INPUTJul 4, 2008 · Bell 212 · Rotorcraft Servo SystemSDR CA080618002Seat Frame · interference(CAN) DURING THE INSTALLATION OF VERTICAL REFERENCE SEAT KIT, IAW STC SH06-31, IT WAS DISCOVERED THAT THE CYCLIC FLIGHT CONTROL STICK IS INTERFERED WITH DUE TO THE SEAT NOW BEING POSITIONED FURTHER FWD AND ELEVATED BECAUSE OF THE KIT INSTALLATION. AN ELEVATIONJun 16, 2008 · Bell 212 · Flight Compartment EquipmentSDR CA080813011Blade · unknown(CAN) INSP OF T/R HUB AND BLADE ASSY REVEALED AN INTERFERENCE BETWEEN BOTH T/R BLADES AND T/R YOKE AT THE LEADING EDGE/ROOT. T/R BLADES REMOVED AND DRESSED OUT TO PROVIDE .010" CLEARANCE BETWEEN YOKE AND BLADES (IAW PSE). YOKE INSPECTED FOR DAMAGE, NONE FOUND.May 26, 2008 · Bell 212 · Tail Rotor BladesSDR CA080515002Cyclic Control · obstructed(CAN) AFTER INSTALLATION OF THE VERTICAL REFERENCE SEAT KIT LISTED ABOVE, IT WAS DISCOVERED DURING FLIGHT CONTROL CLEARANCE CHECKS THAT THE SEAT IN VARIOUS PLACEMENTS OF IT`S RANGE OF TRAVEL INTERFERED WITH THE FULL MOVEMENT OF THE CYCLIC FLIGHT CONTROL. INCLUMay 15, 2008 · Bell 212 · Main Rotor ControlSDR CA080813009Bellcrank · improper part(CAN) DURING T/R RIGGING CHECK, IT WAS NOTED THAT WHEN FULL LT PEDAL WAS APPLIED, THE COUNTERWEIGHT LINK TO COUNTER WEIGHT ARM HARDWARE WOULD CONTACT T/R CROSSHEAD ASSY. UPON INVESTIGATION THE WRONG P/N OF COUNTERWEIGHT BELLCRANK ASSY`S WERE INSTALLED FOR THE Mar 20, 2008 · Bell 212 · Tail Rotor HeadSDR CA080314014Crosstube · broken(CAN) HELICOPTER WORKING HELI-SKIING. THE PASSENGERS WERE LOADING INTO THE HELICOPTER. ALMOST ALL THE SEATS WERE OCCUPIED WHEN A SUDDEN SETTLING WITH A METALLIC NOISE ON THE REAR OF THE MACHINE OCCURRED. IT WAS NOTED THAT THE REAR CROSS TUBE WAS CRACKED ALL THMar 7, 2008 · Bell 212 · Wheel/Ski/FloatSDR CA080314004Inertia Reel · binding(CAN) CO-PILOT SEAT SHOULDER HARNESS INERTIAL REEL CABLE FOUND BINDING AGAINST VERTICAL REFERENCE SEAT KIT - PLATE ASSY P/N AAL-292-031-001. FOUND TO BE COMMON PROBLEM WHEN CHECKED ON OTHER ACFT. WILL CONTACT MFG.Mar 6, 2008 · Bell 212 · Flight Compartment EquipmentSDR U0GA118933Display · odorWX RADAR DISPLAY STARTED FLICKERING AND GOING BLACK. RADAR TURNED OFF. CIRCUIT BREAKER PULLED AFTER ODOR OF ELECTRICAL BURN WAS NOTICED.Feb 18, 2008 · N508EH · Bell 212 · Weather Radar SystemSDR CA080221004Gearbox · mismanufactured(CAN) MAINT WAS TROUBLESHOOTING OIL PRESSURE PROBLEMS. THE POWER SECTION ALWAYS APPEARED THAT IT HAD LOTS OF OIL. VISUAL INDICATION. THE OIL PRESSURE FLUCTUATIONS OCCURRED FEB. 5TH. IN THE TROUBLESHOOTING PROCESS A LITTLE OIL WAS BEING DRAINED AND YET THE VISFeb 9, 2008 · Bell 212 · Main Rotor GearboxSDR 2008FA0000124Grease Fitting · blockedDURING LUBRICATION OF A MAIN ROTOR HUB, WE DISCOVERED THAT THE SPRING IN THE GREASE FITTING (NAS516-1A) WAS PRESSED OUT FROM THE FITTING AND BLOCKED THE GREASE PASSAGE. THIS HAPPENED (3) TIMES. WE FOUND THE SPRINGS AFTER EVERY ATTEMPT. THIS COULD RESULT IN Jan 14, 2008 · Bell 212 · Main Rotor HeadSDR CA071204007Balance Weight · incorrect(CAN) INCORRECT WEIGHT FOR PN CAUSED IMBALANCE IN TAIL ROTOR WHICH COULD NOT BE CORRECTED WITHIN BALANCE LIMITS. (TC NR 20071204007)Dec 4, 2007 · Bell 212 · Tail Rotor BladesSDR CA080305015Engine · failed(CAN) DURING APPROACH, VIBRATION WAS NOTED BY THE CREW THROUGH THE FLIGHT CONTROLS. LANDING WAS ABORTED AND AC RETURNED TO BASE. NEARING BASE, VIBRATION LEVEL INCREASED ABD CREW DECLARED AN EMERGENCY. DURING LANDING FLARE, (2) LOUD NOISES WERE HEARD. POST FLIGOct 27, 2007 · Bell 212 · Engine (Turbine/Turboprop)SDR CA071026003Cyclic Stick · corroded(CAN) PILOTS CYCLIC STICK DISASSEMBLED FOR PAINT AND REFURBISH. STEEL RING PN 204-001-369-001 IS RIVETED ON THE CYCLIC STICK. THE STEEL RING IS USED FOR APPLICATION OF FRICTION. THE STEEL RING WAS REMOVED AND EXTREME CORROSION PITTING WAS FOUND IN THE CYCLIC SOct 25, 2007 · Bell 212 · Main Rotor ControlSDR HEEA116677Starter Gen · burnedSMELLED BURNED ELECTRICAL ODOR IN THE COCKPIT. MAINTENANCE REPLACED NR 2 STARTER GENERATOR.Jul 31, 2007 · N27805 · Bell 212 · Starter-GeneratorSDR CA070717003Bracket · broken(CAN) ON APPROACH TO THE LANDING AREA, THE (DOOR LOCK) LIGHT ON CAUTION PANEL ILLUMINATED. AIRCRAFT LANDED SAFELY WITHOUT ANY FURTHER INCIDENT. UPON LANDING THE ENGINEER EXITED THE AIRCRAFT AND PHYSICALY CHECKED ALL DOORS AND PANELS TO ENSURE THAT THEY WERE COJun 29, 2007 · Bell 212 · Passenger/Crew DoorsSDR CA070514062Turbine Blades · fractured(CAN) THE ENGINE CHIP DETECTOR WARNING ACTIVATED IN FLIGHT AND THE ENGINE SHUTDOWN UNCOMMANDED. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED (TC NR 20070514062)Apr 26, 2007 · Bell 212 · Turbine SectionSDR CA070502011Turbine Wheel · damaged(CAN) IN FLIGHT SHUTDOWN OF NR 1 ENGINE. POWER TURBINE WHEEL SHED BLADES. DAMAGE FOUND ON MAIN ROTOR BLADES AND TAIL ROTOR BLADES. LARGE AMOUNTS OF METAL ON CHIP DETECTOR. (TC NR 20070502011)Apr 20, 2007 · Bell 212 · Turbine SectionSDR CA070227001Grip · cracked(CAN) M/R GRIP TANG FOUND CRACK. COMPONENT ACCUMULATE 111 HRS SINCE LAST 150HRS NDT INSPECTION. (TC NR 20070227001)Feb 22, 2007 · Bell 212 · Main Rotor HeadSDR CA070223005Spring · broken(CAN) ENGINEER CARRYING OUT REQUIREMENTS OF CAMP CODE NR 650121 (INSPECT/LUBE T/R DRIVESHAFT FLEX COUPLING). WHEN DISASSEMBLING THE T/R QUILL OUTPUT COUPLING IN SITU ON THE M/R TRANSMISSION. UPON REMOVAL OF RETAINER AND PLATE, A SMALL SECTION OF SPRING PN 20Feb 20, 2007 · Bell 212 · Tail Rotor Drive ShaftSDR CA070227015Gearbox · making metal(CAN) ENGINE NR 1 CHIP DETECTOR CAUTION LIGHT ILLUMINATED WHILE IN CRUISE FLIGHT AND PILOT RETURNED TO BASE. REDUCTION GEARBOX NR 1 SIDE CHIP DETECTOR FOUND WITH SMALL AMOUNT OF METAL. CHIP DETECTOR WAS CLEANED AND AIRCRAFT FLEW ANOTHER 2 HOURS BEFORE SECOND CJan 26, 2007 · Bell 212 · Turbine Engine Reduction GearSDR CA070226007Saddle · cracked(CAN) LT SKID SADDLE WAS FOUND CRACKED. (TC NR 20070226007)Nov 3, 2006 · Bell 212 · Wheel/Ski/FloatSDR CA070228004Splice · corroded(CAN) SPLICE CORRODED,TAIL BOOM REPLACED, A/C RETURNED TO SERVICE. (TC NR 20070228004)Oct 16, 2006 · Bell 212 · Rotorcraft Tail BoomSDR CA061106005Engine · malfunctioned(CAN) DURING GROUND RUNS FOLLOWING EXTENSIVE MAINTENANCE THE POWER SECTION ACCELERATED UNCOMMANDED. POWER WAS REDUCED TO IDE AND THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED. ON SHUT DOWN SMOKE WAS SEEN EMINATING FROM THE EXHAUST. SUBSEQUENT INSPECTION REVOct 15, 2006 · Bell 212 · Engine (Turbine/Turboprop)SDR CA061006004Engine · fire(CAN) DURING FLIGHT THE FIRE WARNING ACTIVATED. THE FIRE BOTTLES WERE DISCHARGED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A PUNCTURED GAS GENERATOR CASE AND FIRE DAMAGE TO THE ENGINE. MFG WILL INVESTIGATE THE EVENT AND Sep 4, 2006 · Bell 212 · Turbine Engine Compressor SectionSDR CA060815003Pressure Switch · leaking(CAN) FLUID LEAK AT UNION OF SWITCH BODY. THE BODY NORMALY HAS A RIVET TO KEEP THE UNIT FROM BEING TAKEN APART, BUT THIS RIVET WAS FOUND TO BE MISSING. THE THREADS HAD DAMAGE WHERE THE RIVET HOLE WAS. A HOLE IS PROVIDED IN THE THREADS TO INSTALL A RIVET. TAug 15, 2006 · Bell 212 · Engine Oil PressureSDR CA061006008Engine · unknown(CAN) ON TRANSITION FROM HOVER, NR 2 POWER SECTION TORQUE DECREASED UNCOMMANDED. AN EMERGENCY LANDING FOLLOWED RESULTING IN AIRFRAME DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006008)Aug 11, 2006 · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA110594Blade · separatedEXPERIENCED VIBRATION DURING TAKEOFF FROM OFFSHORE PLATFORM. THE AIRCRAFT WAS RETURNED TO AND LANDED AT THE SAME PLATFORM. FOUND SKIN SEPERATION FROM LEADING EDGE ABRRASION STRIP AT TIP APPROXIMATELY 1.5 INCHES CHORDWISE X 9.75 INCHES SPANWISE.Aug 2, 2006 · N27805 · Bell 212 · Main Rotor BladesSDR CA060731019Engine · flamed out(CAN) FOLLOWING TAKE-OFF THE ENGINE EMITTED A NOISE AND FLAMED OUT. SUBSEQUENT GROUND INSPECTION REVEALED EXERNAL OIL LEAKAGE. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731019).Jul 22, 2006 · Bell 212 · Engine (Turbine/Turboprop)SDR CA060731017Engine · making metal(CAN) THE ENGINE EMITTED A NOISE IN FLIGHT ACCOMPANIED BY A RISE IN ITT TEMPERATURE. THE ENGINE WAS SHUTDOWN AND AN UNSCHEDULED LANDING CARRIED OUT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE EXHAUST. MFG WILL MONITOR THE INVESTIGATION OF THE EVENT ANJul 19, 2006 · Bell 212 · Engine (Turbine/Turboprop)SDR CA060712007Case · cracked(CAN) THE CRACKED SUPPORT CASE AT THE LIFT LINK FITTING. (TC NR 20060712007)Jul 10, 2006 · Bell 212 · Main Rotor GearboxSDR CA060907004O-Ring · unserviceable(CAN) STARTED NR 2 ENGINE FIRST. SECOND START OF THE DAY. STARTED NR 1 AND BROUGHT IT UP TO IDLE. THE AME CAME RUNNING TO THE COCKPIT AND GAVE THE SIGNAL TO SHUTDOWN THE ENGINE. ENGINE WAS SHUT DOWN AND BOOST PUMP TURNED OFF. HE SAID FUEL WAS STILL LEAKINJun 29, 2006 · Bell 212 · Engine DrainsSDR CA060605012Blade · cracked(CAN) MAIN ROTOR BLADE SMALL DEBOND FOUND ON LOWER SURFACE APPROX 81.5 INCHES FROM BUTT END JUST AFT OF THE STAINLESS STEEL LEADING EDGE STRIP ON DISASSEMBLY. (APRIL 07 2006) BLADE WILL BE INSPECTED WHEN ARRIVING BACK FOR REPAIR EVALUATION. PAINT REMOVED FROM May 25, 2006 · Bell 212 · Main Rotor BladesSDR CA060524007Control Unit · malfunctioned(CAN) TROUBLESHOOTING A FUEL QUANTITY INDICATING A/C SYSTEM DEFECT. WITH BOTH POWER SECTIONS RUNNING THE FUEL QUANTITY INDICATION WOULD CHANGE WITH NO FUEL ADDED. FUEL QUANTITY SELECTOR WOULD BE POSITIONED TO LT TANK AND VERY SLOWLY THE INDICATOR WOULD SHOW THMay 19, 2006 · Bell 212 · Fuel Quantity IndicatorSDR CA060515004Blade · corroded(CAN) AT REASSEMBLY OF T/R BLADES IT WAS NOTED THAT WHITE POWDER WAS PRESENT IN THE CUFF AREA OF THE BLADES. BLADES QTY 2 WERE SENT TO COMPOSITE TECHNOLOGY FOR EVALUATION. BOTH BLADES WERE SCRAPPED DUE TO DEEP CORROSION INSIDE OF UPPER AND LOWER GRIP PLATES. TMay 8, 2006 · Bell 212 · Tail Rotor BladesSDR CA060503001Wire · brokenDURING ROUTINE INSPECTION, THE INDICATOR WAS SHOWING RED INDICATING FILTER BYPASS CONDITION. UPON INVESTIGATION BY AME NONE OF THE FILTERS HAD BYPASSED ON THE INTEGRATED VALVE AND FILTER ASSEMBLY. AT THIS TIME IT WAS DETERMINED THAT THE CLOGGING INDICATOR WAApr 26, 2006 · Bell 212 · Hydraulic Power System WiringSDR CA060531010Rotor · malfunctioned(CAN) FOLOWING CLIMB THE MAIN ROTOR SPEED DECREASED UNCOMMANDED AND THE LOW ROTOR RPM WARNING ACTIVATED. AN EMERGENCY LANDING WAS CARRIED OUT RESULTING IN AIRFRAME DAMAGE. NR WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR20Apr 4, 2006 · Bell 212 · Main Rotor SystemSDR CA060410008Rod End · damaged(CAN) DURING A SCHEDULED INSPECTION OF THE ROD ENDS, IT WAS NOTED THAT THE BEARING WAS SHOWNING EVIDENCE OF MOVEMENT. BEARING WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060410008)Apr 2, 2006 · Bell 212 · Flight Control SystemSDR CA060601006Detector · failed(CAN) ENGINE OUT LIGHT STAYS ON AFTER ENGINES STARTED. RPM LIGHT INTERMITTENT WITH RPM IN NORMAL OPERATING RANGE.THE RELIABILITY OF THESE UNITS ARE NOT GOOD.IN OUR FLEET OF 4 BELL 212'S WE GO THROUGH 6 RPM BOXES IN 1 SUMMER (TC NR 20060601006)Mar 27, 2006 · Bell 212 · Engine RPM Indicating SystemSDR CA060614004Fitting · cracked(CAN) PILOT REPORTED A FORE-AFT KICK IN THE CYCLIC, AT THE SAME TIME THEY HEARD A NOISE. ON ARRIVAL OF THE AC, INSPECTED THE M/R SYSTEM, SWASHPLATE, SCISSORS AND SLEEVE, TRANSMISSION MOUNTS AND NO DAMAGE WAS FOUND. A/C WAS FLOWN AGAIN AND THE PILOT REPORTED ANFeb 24, 2006 · Bell 212 · Main Rotor GearboxSDR 2006FA0000237Debris Monitor · debondedAFTER REMOVAL OF DEBRIS MONITOR FOR 50 HR, CLEAN AND INSP, THE SCAVENGE CUP/SCREEN TUBE ASSY (PN A8858 IS UNSCREWED FROM UNIT. THE O-RING FLANGE RING GLUED ONTO SCREEN TUBE SHEARS OFF OF SCREEN GLUE LINE, AND STAYS IN THE MAIN UNIT. FIX MAYBE TO APPLY GLUE TFeb 17, 2006 · N911KW · Bell 212 · Aircraft Fuel SystemSDR CA060313011Collective Stick · brokenTHE AME WAS MANIPULATING THE COLLECTIVE STICK TO EXPOSE GREASE FITTINGS ON THE SWASHPLATE DURING A ROUTINE SERVICING OPERATION. WHEN THE COLLECTIVE STICK WAS PULLED UP, STICK ASSY DETAIL P/N 212-001-181-001 BROKE AND SEPARATED AT THE SLOT WHERE THE NR 2 THROTFeb 2, 2006 · Bell 212 · Main Rotor ControlSDR HEEA107921Pump · lowDURING CRUISE FLIGHT THE NR 2 BOOST PUMP LIGHT ILLUMINATED FOR 10 SECONDS AND FUEL PRESSURE DROPPED TO ZERO. PRESSURE CAME BACK UP AND LIGHT WENT OUT FOR 5 SECONDS. LIGHT CAME BACK ON AND PRESSURE DROPPED TO ZERO AGAIN. PLACED INTERCONNECT SWITCH TO OPEN IJan 18, 2006 · N3208H · Bell 212 · Fuel Boost Pump
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