# Service difficulty reports: Agusta Bell 212

A list on [Agusta Bell 212](https://openairdocs.org/model/agusta-bell-212.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 24 · 1,185 reports

- [SDR 2026F00200](https://openairdocs.org/sdr/2026F00200.md): Amplifier · failed · Sep 2, 2026 · N815SS · Bell 212 · Rotorcraft Flight Control
  > AS THE COPILOT BROUGHT THE AIRCRAFT TO HOVER, A LATERAL OSCILLATION BEGAN TO DEVELOP. WHILE THE COPILOT STILL HAD CONTROL OF THE AIRCRAFT, I VERIFIED THAT ALL THE APPROPRIATE SYSTEMS WERE STILL ENGAGED. AS THE OSCILLATIONS BEGAN TO INTENSIFY AND WERE BECOMING
- [SDR 2022FA0000450](https://openairdocs.org/sdr/2022FA0000450.md): Hose · leaking · Aug 15, 2022 · N212AH · Bell 212 · Hydraulic System, Main
  > HOSE ASSEMBLY CHAFING DAMAGE RESULTING IN LOSS OF FLUID.
- [SDR DALA2022FA0000429](https://openairdocs.org/sdr/DALA2022FA0000429.md): Link · cracked · Apr 21, 2022 · N212AH · Bell 212 · Fuselage Structure (General)
  > UPON VISUAL INSPECTION OF FRICTION DAMPERS AND TRANSMISSION MOUNTS, FOUND LIFT LINK FITTING CRACK ON THE AFT LUG BUSHING AREA COVERING THE ENTIRE LATERAL (SIDE). TRANSMISSION MOUNTS WERE REMOVED AND INSPECTED FOUND PRESSURE REQUIRED TO DEFLECT MOUNT WAS BEYOND
- [SDR CA190807016](https://openairdocs.org/sdr/CA190807016.md): Compressor · seized · Aug 3, 2019 · Bell 212 · Turbine Engine Compressor Section
  > (CAN) PILOT REPORTED HEARING NOISE AT LEFT REAR OF AIRCRAFT AND CHANGE IN FLIGHT REGIME LIKE SMALL WIND GUST. NO ABMORMAL INSTRUMENT INDICATIONS. AIRCRAFT LANDED AND DISTINCT WHINE NOISE HEARD PRIOR TO SHUT DOWN. ENGINES SHUT DOWN AND BASIC VISUAL INSPECTION C
- [SDR CA190725007](https://openairdocs.org/sdr/CA190725007.md): Indicator · shorted · Jul 19, 2019 · Bell 212 · Engine BMEP/Torque Indicating
  > (CAN) TORQUE GAUGE FAILED AND POPPED CIRCUIT BREAKER. (TC# 20190725007)
- [SDR CA190618013](https://openairdocs.org/sdr/CA190618013.md): Amplifier · false activation · Jun 14, 2019 · Bell 212 · Fire Detection
  > (CAN) THE #2 ENGINE FIRE WARNING LIGHT ILLUMINATED DURING FLIGHT. POST LANDING INSPECTION REVEALED THERE WAS NO FIRE. MAINTENANCE PERSONNEL DISCOVERED THE #2 SIDE FIRE DETECTION AMPLIFIER HAD CAUSED A FALSE FIRE WARNING INDICATION. THE FIRE DETECTION AMPLIFIER
- [SDR CA190622001](https://openairdocs.org/sdr/CA190622001.md): Amplifier · failed · Jun 14, 2019 · Bell 212 · Fire Detection
  > (CAN) IT WAS REPORTED TO BELL:DURING BUCKETING OPERATIONS AT APPROX 300 FEET ABOVE GROUND LEVEL, THE PILOT OBSERVED THAT THE #2 ENGINE FIRE LIGHT HAD ILLUMINATED. HE PILOT FOLLOWED THE EMERGENCY PROCEDURES FOR AN ENGINE FIRE INDICATION AND SUBSEQUENTLY DISCHAR
- [SDR CA190527015](https://openairdocs.org/sdr/CA190527015.md): Engine · malfunctioned · May 19, 2019 · Bell 212 · Engine (Turbine/Turboprop)
  > (CAN) PILOT WAS LIFTING A WATER BUCKET FROM A SWAMP NEAR LAC LA BICHE WHEN THE AIRCRAFT KICKED TO THE LEFT AND HE LOOKED OVER AT HIS GUAGES AND NOTICED THAT ENGINE 1 WAS OFFLINE. HE PROCEEDED TO RELEASE THE LONGLINE AND BUCKET, LEAVING THEM IN THE SWAMP AND FL
- [SDR CA190325019](https://openairdocs.org/sdr/CA190325019.md): Battery Pack · leaking · Mar 22, 2019 · Bell 212 · Emergency Locator Beacon
  > (CAN) DURING THE ANNUAL INSPECTION OF THE ELT, UPON OPENING THE UNIT, IT APPEARED EVIDENT AN INTERNAL BATTERY CELL HAD RUPTURED, WAS BULGING AND LEAKING ELECTROLYTE. THE BATTERIES ARE OF LITHIUM ION TECHNOLOGY. THE ELT BATTERY WAS REPLACED WITH A NEW PART, THE
- [SDR CA190308019](https://openairdocs.org/sdr/CA190308019.md): Coupling · damaged · Mar 8, 2019 · Bell 212 · Tail Rotor Drive Shaft
  > (CAN) NEW TAIL ROTOR COUPLING FROM MANUFACTURER PART NUMBER 204040604005S HAS SCORING MARKS IN VALLEY BETWEEN TEETH. MACHINE MARKS THREE COUPLINGS WITH SAME DEFECT
- [SDR CA190219023](https://openairdocs.org/sdr/CA190219023.md): Coupling · gouged · Feb 15, 2019 · Bell 212 · Tail Rotor Drive Shaft
  > (CAN) TRD OUTER COUPLING FOUND WITH POSSIBLE MACHINING MARKING/GOUGES.
- [SDR CA190208024](https://openairdocs.org/sdr/CA190208024.md): Reduction Gb · damaged · Feb 2, 2019 · Bell 212 · Turbine Engine Reduction Gear
  > (CAN) A CHIP LIGHT FOR THE #1 POWERSECTION ILLUMINATED ON THE CAUTION PANEL. PILOT LANDED THE AIRCRAFT. THE AME FOUND METAL ON THE #1 POWERSECTION REAR OIL CHIP PLUG. THE POWERSECTION WAS OVERHAUL AND RECENTLY INSTALLED SO WE SUSPECT THAT THE #5 BEARING IN THE
- [SDR 2018FA0000454](https://openairdocs.org/sdr/2018FA0000454.md): Support · failed · Aug 25, 2018 · N512TA · Bell 212 · Main Rotor Mast/Swashplate
  > THE SWASHPLATE SUPPORT FAILED 83 HOURS PRIOR TO ITS SCHEDULED RETIREMENT LIFE OF 1000 FLIGHT HOURS, FOR UNKNOWN REASONS. THE PILOT WAS UNABLE TO MAKE A SUCCESSFUL EMERGENCY LANDING DUE TO THE TOTAL DISCONNECTION OF HIS PRIMARY FLIGHT CONTROLS. WHILE HALF WAY T
- [SDR 9EKA20160810011](https://openairdocs.org/sdr/9EKA20160810011.md): Rotor Head · misoverhauled · Aug 10, 2016 · N16974 · Bell 212 · Main Rotor Head
  > MAIN ROTOR HEAD REQUIRED REPLACEMENT DUE TO TIME. THE MAIN ROTOR HEAD WAS OVERHAULED. WHEN RECEIVED, THE HEAD THE PAINT AND SEAL WERE NOT CURED AND EXHIBITED IMPROPER MIXTURE. FIXED THE SEAL ISSUES AND ALLOWED THE HEAD TO STAND IN THE HANGAR TO CURE. NOTICE
- [SDR IGAR2016FA0000184](https://openairdocs.org/sdr/IGAR2016FA0000184.md): Blade · corroded · Apr 11, 2016 · N212AH · Bell 212 · Tail Rotor Blades
  > TAIL ROTOR BLADE DEVELOPED DEEP CORROSION PIT AT BLADE ROOT.
- [SDR IGAR2016FA0000183](https://openairdocs.org/sdr/IGAR2016FA0000183.md): Blade · corroded · Apr 11, 2016 · N212AH · Bell 212 · Tail Rotor Blades
  > TAIL ROTOR BLADE DEVELOPED DEEP CORROSION PIT AT BLADE ROOT.
- [SDR 9EKA20160318004](https://openairdocs.org/sdr/9EKA20160318004.md): Skin · cracked · Mar 18, 2016 · N16974 · Bell 212 · Rotorcraft Tail Boom
  > STRUCTURAL CRACK FOUND ON INTERNAL STIFFENER, IN THE VERTICAL TAIL PYLON FROM PREVIOUS REPAIR FAILURE. 3 INCH CRACK CONNECTING 3 RIVETS ON THE SKIN UNDERNEATH AN EXISTING REPAIR. ON THE INSIDE OF THE SKIN THE FACTORY BELL STIFFENER 212-030-099-028, CRACKED F
- [SDR CA160126003](https://openairdocs.org/sdr/CA160126003.md): Hanger Assy · cracked · Jan 25, 2016 · Bell 212 · Tail Rotor Drive System
  > (CAN) CRACKS WERE FOUND ON EACH BOLT HOLE THAT CONNECTS THE TAIL ROTOR DRIVESHAFT HANGER BEARING AND COUPLING ASSY, PN 212-040-600-009 TO THE TAIL BOOM HANGER FITTING BARREL NUTS.
- [SDR CA160121018](https://openairdocs.org/sdr/CA160121018.md): Seal · worn · Jan 19, 2016 · Bell 212 · Turbine Engine Oil System
  > (CAN) SHORTLY AFTER TAKE OFF. INFORMED PILOT OF ORANGE FLUID ON BELLY OF HELICOPTER. ACFT LANDED AT FUEL CACHE AND SHUTDOWN FOR INSPECTION. BELLY AND TAIL WERE COVERED IN OIL. REPLACEMENT HELICOPTER WAS BROUGHT IN. NR 2 ENGINE OIL COOLER BLOWER SEAL REPLACE
- [SDR CA160112003](https://openairdocs.org/sdr/CA160112003.md): Crosstube · broken · Jan 11, 2016 · Bell 212 · Main Landing Gear
  > (CAN) DURING PREPARATION FOR TAKEOFF, JUST BEFORE PULLING COLLECTIVE, THE PILOT HEARD A LOUD SNAP AND THE ACFT DROPPED TO THE AFT LEFT. PILOT CORRECTED CYCLIC FOR M/R CLEARANCE, SHUTDOWN ENGINES. THE AFT CROSS TUBE BROKE OTBD OF LT RETAINING STRAP. ACFT SET
- [SDR CA151229023](https://openairdocs.org/sdr/CA151229023.md): Crossbeam · sheared · Dec 28, 2015 · Bell 212 · Main Landing Gear
  > (CAN) RETURNED AFTER REFUELING BACK TO THE GROUPS LANDED. SKIDS STILL PENETRATED THE SNOW SURFACE AND THE BELLY OF THE ACFT WAS JUST ABOUT TOUCHING THE SNOW SURFACE. THE LANDING WAS UNEVENTFUL. LAST GUIDE PULLED HIMSELF IN TO THE HELICOPTER THAT IS WHEN A
- [SDR CA151103005](https://openairdocs.org/sdr/CA151103005.md): Cargo Hook · failed · Oct 26, 2015 · Bell 212 · Cargo Compartments
  > (CAN) INADVERTENT RELEASE OF A LOAD DURING LONGLINE OPERATION. SUSPECT THAT THE SWIVEL USED DID NOT OPERATE CORRECTLY AND IN TURN ALLOWED THE LONGLINE TO TWIST AND GAIN ENERGY. SUSPENSION ASSY IS PROTECTED WITH RUBBER ON THE OUTSIDE SURFACE WHERE IT IS DESIGN
- [SDR CA150922013](https://openairdocs.org/sdr/CA150922013.md): Bearing · damaged · Sep 22, 2015 · Bell 212 · Tail Rotor Head
  > (CAN) DURING THE OVERHAUL OF A TAIL ROTOR ASSY THE NEEDLE BEARING ON THE CONTROL LEVER WAS FOUND TO BE DAMAGED DURING INSTALLATION AT THE FACTORY. WE HAVE CHECK ANOTHER LEVER AND FOUND THE SAME ISSUE.
- [SDR CA150818010](https://openairdocs.org/sdr/CA150818010.md): Shaft · sheared · Aug 14, 2015 · Bell 212 · Windshield/Door Rain/Ice Removal
  > (CAN) SHAFT SHEARED DURING FLIGHT. MOTOR ASSEMBLY REPLACED.
- [SDR CA150805008](https://openairdocs.org/sdr/CA150805008.md): Fuel Control · malfunctioned · Aug 3, 2015 · Bell 212 · Fuel Control/Turbine Engines
  > (CAN) FUEL CONTROL CAUSING TORQUE SPLIT AND LOW N1.
- [SDR CA150814006](https://openairdocs.org/sdr/CA150814006.md): Boot · torn · Jul 31, 2015 · Bell 212 · Main Rotor System
  > (CAN) THIS DRIVE SHAFT WAS INSTALLED AS A REPLACEMENT FOR THE PREVIOUS DRIVE SHAFT THAT HAD A LEAKING BOOT. THERE WAS NO GREASE LEAKAGE AFTER THE MANDATORY GROUND RUN LEAK CHECK. THE ACFT HAD A 1.2 HR FERRY FLIGHT AND ON A POST FLIGHT INSPECTION THE ENGINEER
- [SDR CA150813007](https://openairdocs.org/sdr/CA150813007.md): Boot · torn · Jul 31, 2015 · Bell 212 · Engine/Transmission Coupling
  > (CAN) ON A POST FLIGHT INSPECTION IT WAS NOTED THE FWD COUPLING BOOT, M/R TRANSMISSION END, HAD SOME SLIGHT GREASE LEAKAGE. THE DRIVE SHAFT WAS REPLACE WITH ANOTHER DRIVE SHAFT. THE BOOT WAS INSTALLED NEW ON FEB 14 2012 AND THE MFG DATE ON THE BOOT WAS FEB 5
- [SDR CA150701012](https://openairdocs.org/sdr/CA150701012.md): Compressor Blade · unserviceable · Jun 17, 2015 · Bell 212 · Turbine Engine Compressor Section
  > (CAN) AIRCRAFT WAS PERFORMING GND RUN BEFORE FLIGHT WHEN THE PILOT NOTICED THAT THE TEMP ON THE RT ENG WAS SIGNIFICANTLY HIGHER. UNUSUAL NOISE WAS ALSO HEARD FROM THE ENG WHILE HOVERING. THE FLIGHT WAS ABORTED. CUSTOMER PERFORMED BORESCOPE INSPECTION & FOUN
- [SDR CA150602026](https://openairdocs.org/sdr/CA150602026.md): Bracket · worn · May 30, 2015 · Bell 212 · Cargo Compartments
  > (CAN) INADVERTENT IN FLIGHT CARGO RELEASE CAUSED BY INTERNAL WEAR IN BRACKET, PN 204-070-999-001. MANUAL RELEASE CABLE WAS FOUND INTERMITTENTLY NOT ABLE TO RESET TO NORMAL POSITION DUE TO RETURN SPRING GUIDE, PN 204-070-997-001 GETTING STUCK IN THE INTERNAL W
- [SDR CA150529005](https://openairdocs.org/sdr/CA150529005.md): Crosstube · broken · May 27, 2015 · Bell 212 · Main Landing Gear
  > (CAN) CROSS TUBE BROKE AT LT AIRFRAME SUPPORT, UNDER THE STEEL WEAR PLATES.
- [SDR CA150520017](https://openairdocs.org/sdr/CA150520017.md): Control Tube · corroded · May 18, 2015 · Bell 212 · Rotorcraft Flight Control
  > (CAN) CORROSION FOUND NEAR END OF TUBE ASSY COMING THRU THE PAINT, PITTING BEYOND LIMITS, PART HAD TO BE REPLACED.
- [SDR CA150520018](https://openairdocs.org/sdr/CA150520018.md): Pump · failed · May 15, 2015 · Bell 212 · Hydraulic Pump (Electric/Engine), Main
  > (CAN) HYDRAULIC FLUID TURNING DARK, FLUID TESTED & CONTAMINATION DETERMINED TO BE COMING FROM PUMP. PUMP REPLACED.
- [SDR CA150602008](https://openairdocs.org/sdr/CA150602008.md): Engine · failed · May 13, 2015 · Bell 212 · Engine (Turbine/Turboprop)
  > (CAN) WHILE PULLING THE BUCKET LOAD FROM WATER, THE PILOT HEARD A COMPRESSOR STALL, FOLLOWED BY A YAW AND LOAD GROWLING NOISES. PILOT LOOKED AT THE GAUGES AND NOTICED NG DROPPING AND ITT CLIMBING. PILOT RELEASED THE LOAD, ROLLED THE ENGINE DOWN TO IDLE AND M
- [SDR CA150520016](https://openairdocs.org/sdr/CA150520016.md): Turbine Wheel · failed · May 13, 2015 · Bell 212 · Turbine Section
  > (CAN) DURING WATER BUCKET OPERATION, PILOT HEARD THE ENGINE RUMBLING AND A RAPID STALLING, ABORTED PICK UP, THE NR 1 ENGINE SURGED & LOST POWER. THE PILOT IMMEDIATELY LANDED WITHOUT INCIDENT. DURING INSPECTION, ONE OF THE TURBINE WHEELS HAD THROWN SOME BLAD
- [SDR CA150511013](https://openairdocs.org/sdr/CA150511013.md): Blade · out of balance · Apr 30, 2015 · Bell 212 · Main Rotor Blades
  > (CAN) NEW MAIN ROTOR BLADE WAS INSTALLED. WE WERE NOT ABLE TO BALANCE. MFG SENT OVER A TECH REP TO BALANCE WITH A MASTER BALANCER. THIS ALSO DID NOT WORK. A NEW BLADE WAS INSTALLED AND THE ACFT WAS BALANCED.
- [SDR CA150326007](https://openairdocs.org/sdr/CA150326007.md): Bolt · mismanufactured · Mar 26, 2015 · Bell 212 · Main Rotor System
  > (CAN) MISMANUFACTURED BLADE BOLT LOCK WIRE SAFETY LOCATION DRILLED IN WRONG LOCATION. RETURED TO VENDOR THE HOLE FOR THE LOCK WIRE SHOULD BE COMING OUT TO SIDE NOT DRILLED STRAIGHT THROUGH.
- [SDR 9EKA20150125001](https://openairdocs.org/sdr/9EKA20150125001.md): Web · cracked · Jan 25, 2015 · N16973 · Bell 212 · Fuselage Miscellaneous Structure
  > A CRACK IN THE AFT FUSELAGE TAIL SERVO ACCESS AREA AROUND STATION 238.29, BL 14.29 & WL 56.97. CRACK IS APPROX 5/8 INCHES LONG.
- [SDR CA150123005](https://openairdocs.org/sdr/CA150123005.md): Window · cracked · Jan 21, 2015 · Bell 212 · Flight Compartment Windows
  > (CAN) WINDOW MOUNTING FLANGE CRACK AT 1 BOLT HOLE LOCATION. 12:00 O`CLOCK, THERE ARE 26 BOLT HOLES.
- [SDR CA150123004](https://openairdocs.org/sdr/CA150123004.md): Window · cracked · Jan 21, 2015 · Bell 212 · Flight Compartment Windows
  > MOUNTING FLANGE CRACKS AND CRAZING AT SEVERAL BOLT HOLE LOCATIONS. THERE ARE 26 BOLT HOLES, 2 WITH CRACKS, 7 WITH STAR-BURST, CRAZING, CRACKING.
- [SDR CA141216003](https://openairdocs.org/sdr/CA141216003.md): Support · mismanufactured · Dec 15, 2014 · Bell 212 · Nacelle/Pylon Miscellaneous Structure
  > (CAN) A STRUCTURES TECH WAS REPLACING DAMAGED PART WITH A NEW BELL SUPPLIED PART ND NOTICED THE PART IS SMALLER THAN THE ORIGINAL FOUND INSTALLED AND DID NOT HAVE SUFFICIENT EDGE DISTANCE FOR FASTENERS.
- [SDR CA141126008](https://openairdocs.org/sdr/CA141126008.md): Barrel · cracked · Nov 26, 2014 · Bell 212 · Main Rotor Head
  > (CAN) CRACK FOUND IN THREADS ON DRAG BRACE BARREL DURING NDT INSPECTION.
- [SDR CA141202017](https://openairdocs.org/sdr/CA141202017.md): Compressor · damaged · Nov 8, 2014 · Bell 212 · Turbine Engine Compressor Section
  > (CAN) ACFT CAME BACK FROM A FLIGHT FOR REFUEL. ENGINE START AFTER THE REFUEL WAS OK. AS THE PILOT STARTED PULLING THE COLLECTIVE, THE LT PS WAS SURGING/VIBRATION WAS FELT, ITT WENT HIGH, PILOT SHUTDOWN THE ENGINE. COMPRESSOR DAMAGE WAS OBSERVED. CUSTOMER ALR
- [SDR IGAA2014121200002](https://openairdocs.org/sdr/IGAA2014121200002.md): Blade · cracked · Oct 16, 2014 · N212AH · Bell 212 · Main Rotor Blades
  > DURING ROUTINE MAINTENANCE, CONDUCTING AD2011-23-02 FOR CRACKS AND CORROSION, FOUND A VOID IN THE M/R BLADE AT ABOUT STATION 29.5 ON THE TOP SIDE OF THE BLADE DOUBLER. BLADE WAS REMOVED FROM SERVICE.
- [SDR CA141031011](https://openairdocs.org/sdr/CA141031011.md): Crosstube · broken · Oct 11, 2014 · Bell 212 · Main Landing Gear
  > (CAN) DURING GROUND MOVEMENT OF HELICOPTER, CROSS-TUBE BROKE AND ACFT BELLY IMPACTED GROUND. DAMAGE TO ACFT STRUCTURE OCCURRED.
- [SDR CA141014009](https://openairdocs.org/sdr/CA141014009.md): Crosstube · collapsed · Oct 11, 2014 · Bell 212 · Main Landing Gear
  > (CAN) WHEN MOVING THE MACHINE FROM THE HANGAR TO THE FLIGHT LINE THE AFT CROSS TUBE COLLAPSED. NO INJURIES TO GROUND HANDLING PERSONNEL AND DAMAGE TO THE AIRFRAME IS BEING ASSESSED.
- [SDR CA140917001](https://openairdocs.org/sdr/CA140917001.md): Pressure Switch · leaking · Sep 16, 2014 · Bell 212 · Turbine Engine Oil System
  > (CAN) DURING POST FLIGHT INSPECTION NR 1 ENGINE DECK WAS FOUND TO HAVE FOIL/OIL RESIDUE ON IT BUT NO SOURCE OF THE LEAK WAS FOUND. WITH THE INDUCTION COWL REMOVED AND BOOST PUMP PRESSURE APPLIED FUEL WAS FOUND SEEPING OUT THE DIFFERENTIAL PRESSURE SWITCH AND R
- [SDR CA140805008](https://openairdocs.org/sdr/CA140805008.md): Windshield · cracked · Aug 1, 2014 · Bell 212 · Flight Compartment Windows
  > (CAN) FOLLOWING WATER BUCKETING MISSION PILOT NOTICED 5" CRACK AT UPPER OTBD CORNER OF GLASS WINDSHIELD. CAUSE UNKNOWN AT THIS TIME. WINDSHIELD REPLACED WITH NEW PART.
- [SDR CA140721023](https://openairdocs.org/sdr/CA140721023.md): Fitting · cracked · Jul 19, 2014 · Bell 212 · Main Rotor Head
  > (CAN) WHILE PERFORMING A DAILY INSPECTION OF THE ACFT, THE AME NOTICED A THIN BLACK LINE ON THE OUTER END OF THE DRAG BRACE FITTING. AFTER FURTHER INVESTIGATION INCLUDING PAINT REMOVAL FROM THE AFFECTED AREA, THE AME DETERMINED THE FITTING TO BE CRACKED. THE
- [SDR CA140716009](https://openairdocs.org/sdr/CA140716009.md): Crosstube · cracked · Jul 13, 2014 · Bell 212 · Main Landing Gear
  > (CAN) PILOT ON FIRE FIGHTING OPERATIONS HEARD LOUD SNAP SOUND ON LANDING AND ABORTED THE TAKE-OFF. HIGH FORWARD CROSSTUBE FOUND CRACKED OTBD OF LT SADDLE FITTING. COMPONENT TIMES KEPT IAW ACCESSORIES AERT SB AA-08055, REV B AND ALERT SB 212-09-132, REV A, LAN
- [SDR SAJF2014062603020](https://openairdocs.org/sdr/SAJF2014062603020.md): Engine · leaking · Jun 16, 2014 · N398EH · Bell 212 · Engine (Turbine/Turboprop)
  > DURING FLIGHT AFTER 5 HOURS AFTER TAKEOFF, THE PILOT OBSERVED LOW OIL QTY ON NR 2 ENG & NORMAL OIL PRESS WAS MAINTAINED. AFTER INTERVAL DISCUSSION, PILOT CHOSE TO DIVERT FOR AN UNEVENTFUL LANDING. DURING GND INSPECTION, OBVIOUS OIL LEAKAGE UNDER COMPRESSOR R

Next page: https://openairdocs.org/model/agusta-bell-212/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
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
```

This list as a web page: https://openairdocs.org/model/agusta-bell-212/reports

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