Pratt & Whitney PT6T-3B

Service difficulty reports · 480

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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 engine_model_key = 'PT6T3B'
  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 CA130405013Panel · delaminated(CAN) PANEL DELAMINATED.Apr 2, 2013 · Bell 212 · Fuselage Main, Plate/SkinSDR CA130401005Engine · failed(CAN) THE ENGINE SUFFERED AN APPARENT UNCONTAINED EVENT WHERE IT IS REPORTED A TURBINE BLADE EXITED THE SIDE OF THE ENGINE, RESULTING IN A POST DISTRESS FIRE. THE INSPECTION REVEALED A THROUGH GOING HOLD ON THE SIDE OF THE ENGINE. THE ENGINE WILL BE REMOVED Mar 21, 2013 · Engine (Turbine/Turboprop)SDR CA130314014Blower · loose(CAN) DURING HEAVY MAINTENANCE THE IMPELLER RETENTION NUT WAS FOUND TO HAVE NO CLAMP-UP TORQUE ON THE IMPELLER AND THE WASHER BENEATH THE NUT COULD FLOAT FREELY. THE WITNESS MARK ON THE NUT TO THE SHAFT WAS STILL INTACT.Mar 14, 2013 · Bell 212 · Engine Oil CoolerSDR CA130312010Support · broken(CAN) DURING ROUTINE ACFT DAILY INSPECTION, AME WAS INSPECTING THE MAIN TRANSMISSION AND NOTICED THE SUPPORT CASE WAS CRACKED ON THE LT SIDE BY THE AIRFRAME ATTACHMENT BOLT. THE TRANSMISSION WAS REMOVED AND IT WAS FOUND THE SUPPORT CASE LEG WAS BROKEN WITH THMar 9, 2013 · Bell 212 · Main Rotor GearboxSDR CA130401001Engine · failed(CAN) APPROXIMATELY 2 MINUTES AFTER LEVELING OFF AT 300 FT, A NOISE WAS HEARD FROM NR 1 ENGINE ACCOMPANIED BY THE FOLLOWING INDICATIONS: N1 DROOP, ENG 1, N2 DROOP, ENG 2, TORQUE SPLIT, FLICKERING N1, ENGINE CHIP, ENG 1, SMOKE IN COCKPIT AND CABIN COLLECTIVE AMar 8, 2013 · Engine (Turbine/Turboprop)SDR CA130225019Longeron Splice · cracked(CAN) LONGERON SPLICE FOUND CRACKED DURING ANNUAL INSPECTION.Feb 25, 2013 · Bell 212 · Rotorcraft Tail BoomSDR CA130225020Caution Panel · failed(CAN) MASTER CAUTION WILL NOT RESET.Feb 25, 2013 · Bell 212 · Instrument PanelSDR CA130225021Tachometer · slow(CAN) NR 1 NEEDLE SLOW TO COME ON LINE.Feb 25, 2013 · Bell 212 · Main Rotor Indicating SystemSDR CA130225022Indicator · fluctuates(CAN) AMPERE INDICATOR HAD FLUCTUATING INDICATIONS.Feb 25, 2013 · Bell 212 · AC Indicating SystemSDR LCFA20130225001Blade · delaminatedTHE UPPER AND LOWER SURFACES OF THE TRAILING EDGE EXTRUSION ON SUBJECT MAIN ROTOR BLADE HAVE DELAMINATED FROM EACH OTHER. THE OUTBOARD END OF THE DELAMINATION ENDS AT THE INBOARD EDGE OF THE TRIM TAB; THE DELAMINATION OF THE TRAILING EDGE EXTRUSION EXTENDS INFeb 18, 2013 · N16974 · Bell 212 · Main Rotor BladesSDR CA130214022Indicator · failed(CAN) NR 1 ENGINE DUAL TORQUE NEEDLE NOT INDICATING.Feb 14, 2013 · Bell 212 · Engine RPM Indicating SystemSDR CA130214023Window · cracked(CAN) SKY LIGHT WINDOW CRACKED.Feb 14, 2013 · Bell 212 · Flight Compartment WindowsSDR CA130220007Blade · delaminated(CAN) TAIL ROTOR DEBONDED ON DOUBLER AT BS 20.00".Feb 8, 2013 · Bell 212 · Tail Rotor BladesSDR CA130206010Crosstube · broken(CAN) ACFT WAS LANDING WITH GROUP OF SKIERS ON BOARD WHEN PILOT HEARD LOUD BANG AND ACFT STARTED TO SETTLE ON SNOW. PASSENGERS WERE UNLOADED WHILE HOLDING POWER AND ACFT WAS FLOWN BACK TO BASE, LANDED AND PLACED ON JACKS. AFT CROSSTUBE WAS FOUND BROKEN UNDERFeb 5, 2013 · Bell 212 · Main Landing GearSDR CA130212020Engine · fod(CAN) HAD A CHIP CAUTION ON RT ACCESSORIES GEARBOX DURING A FLIGHT. THE CREW SHUTDOWN AND SECURED THE ENGINE. AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE. THE ON GROUND INSPECTION REVEALED DEBRIS ON MAGNETIC CHIP DETECTOR. NO OTHER CONTAMINATION ON OIL FILFeb 4, 2013 · Bell 212 · Engine (Turbine/Turboprop)SDR EOPA20121022397Housing · crackedON INSPECTION, AN OIL LEAK WAS DISCOVERED IN THE COMBINED GEARBOX AREA. ON FURTHER INSPECTION THE NR 1 ENGINE CHIP DETECTOR HSG ATTACHED TO THE GEARBOX WAS FOUND CRACKED.Oct 18, 2012 · N397AL · Bell 412 · Turbine Engine Oil SystemSDR CA120919001Turbine Wheel · fractured(CAN) IN FLIGHT SHUTDOWN. PILOT REPORTED THAT WHILE PULLING POWER, HE HEARD A SERIES OF NOISES, FOLLOWED BY A SHUDDER AND VIBRATION. THE RESULT OF THIS WAS A DECREASE IN ROTOR RPM, FOLLOWED BY A DECAY OF N1. THE FLIGHT OFFICER REPORTED N1 DROPPED TO APPROXIMSep 8, 2012 · Bell 412 · Turbine SectionSDR CA120906013Reservoir · damaged(CAN) INTERNAL COATING BREAKING DOWN AND CONTAMINATING HYDRAULIC FLUID.Sep 4, 2012 · Bell 212 · Hydraulic Reservoir, MainSDR CA120813020Link · failed(CAN) JUST DEPARTED OFF FROM A FOB WITH PASSENGERS, AND WAS IN A SLIGHT LT TURN WITH MAX CONTINUOUS POWER, WHEN A LOUD BANG AND MOMENTARY SHUTTER OCCURRED AND WAS FELT IN THE ACFT. LEVELLED THE ACFT, CROSS CHECKED ENGINE INDICATIONS AND NOTHING ABNORMAL WAS OAug 10, 2012 · Bell 212 · Main Rotor GearboxSDR CA120813013Indication Sys · malfunctioned(CAN) ON AUGUST 4, THE FLIGHT CREW REPORTED A TORQUE SPLIT BETWEEN BOTH ENGINES WITH AN ENGINE OUT WARNING THAT LASTED APPROXIMATELY 5 SECONDS, AND THEN RECOVERED. THE ACFT RETURNED TO BASE. ENGINE ELECTRONIC CONTROL CONNECTORS WERE CLEANED. THE ACFT WAS REAug 6, 2012 · Engine BMEP/Torque IndicatingSDR CA120719010Indicator · erratic(CAN) ERRATIC INDICATION ON OIL PRESSURE.Jul 12, 2012 · Bell 212 · Engine Oil Indicating SystemSDR CA120813016Blade · fractured(CAN) DURING LANDING, THE PILOT NOTICED POWER LOSS OF THE NR 2 ENGINE. THE ACFT MADE AN UNEVENTFUL LANDING. A VISUAL INSPECTION OF THE ENGINE SHOWED THE EXHAUST DUCT INNER CRACKED WITH MATERIAL MISSING. THERE WAS NO INDICATION OF FRACTURED PT BLADES. THE POWJul 10, 2012 · Bell 206B · Turbine SectionSDR CA120824005Longeron · cracked(CAN) DURING IMPORT OF THE ACFT, MAINTENANCE WAS CARRYING OUT ASB 212-90-63, THE REPETITIVE TAILBOOM BORESCOPE INSPECTION. IN ADDITION, THE LOWER LONGERONS WERE INSPECTED FOR CONDITION. A CRACK WAS NOTED IN THE LT LOWER LONGERON. THE TAILBOOM WAS REMOVED ANDJun 22, 2012 · Bell 212 · Rotorcraft Tail BoomSDR CA120718001Oil System · leaking(CAN) CUSTOMER REPORTED OIL CONSUMPTION ON A BRAND NEW POWER SECTION ACQUIRED. OIL LEVEL CONTINUOUSLY DROPPING -ESTIMATE .5 TO .7500 LITERS OVER 8 HOURS OF OPERATION. NO EXTERNAL OIL LEAKS. NO LEAKS IN DRAINS. BREATHER LINE VERIFIED, DRY AND NO RESTRICTION Jun 19, 2012 · Turbine Engine Oil SystemSDR CA120608010Shaft · sheared(CAN) COMBINING GEARBOX CHIP LIGHT, NR 2 OIL COOLER BLOWER SHAFT FOUND SHEARED.Jun 5, 2012 · Bell 212 · Engine Oil CoolerSDR CA120605003Blade · fractured(CAN) DURING LOGGING OPERATIONS, AS THE ACFT WAS COMING IN TO DROP, A NOISE WAS HEARD AND A POWER LOSS FOLLOWED ACCOMPANIED BY HIGH TEMPERATURE. THE LOAD WAS LET GO AN A SAFE LANDING FOLLOWED AT THE DROPPING ZONE. INSPECTION FOUND TURBINE BLADE FRACTURES.May 22, 2012 · Bell 212 · Turbine SectionSDR CA120523016Engine · malfunctioned(CAN) ACFT WAS INVOLVED IN LONGLINE OPERATIONS. DURING A MOVE WITH LOAD ON HEADING FOR THE LANDING ZONE UNDER LOW POWER AS THE PILOT BEGAN TO SLOWLY PULL IN POWER TO SLOW THE DECENT A POPPING NOISE WAS HEARD AND A RISE IN THE ITT WAS NOTED ON THE NR 1 ENGINE May 19, 2012 · Bell 212 · Engine (Turbine/Turboprop)SDR CA120505001Blade · failed(CAN) ON FINAL APPROACH NR 2 ENGINE COMPRESSOR STALL OCCURED FOLLOWED BY HIGH PITCH WHINING. PILOT SHUTDOWN ACFT AND AUTOROTATED, LANDED. UPON INVESTIGATION COMPRESSOR BLADE WAS FOUND LYING IN INLET SCREEN. UPON FURTHER INVESTIGATION 1ST STAGE COMPRESSOR WHEMay 3, 2012 · Bell 212 · Turbine Engine Compressor SectionSDR CA120507008Engine · overtemp(CAN) DURING FLIGHT, THE ENGINE STARTED TO SURGE FOLLOWED BY TEMPERATURE RISE AND POWER TURBINE SPEED FLUCTUATION. THE ENGINE THEN SHUT ITSELF DOWN. AN ENGINE RESTART RESULTED IN ENGINE TEMPERATURE OF 880F AT START. THE ENGINE WAS THEN OPERATED AT 70 PERCENApr 27, 2012 · Bell 212 · Engine (Turbine/Turboprop)SDR ALGA2012041801Shaft · shearedOIL COOLER BLOWER HAS A SHEARED SHAFT.Apr 18, 2012 · N9YBCO · Bell 412EP · Engine Oil CoolerSDR CA120409006Drain Valve · leaking(CAN) DURING DI NR 2 POWER SECTION WAS FOUND TO BE LOW ON OIL. AFTER INVESTIGATION LEAKAGE WAS FOUND FROM OIL DRAIN VALVE. UPON REMOVAL SCREWS HOLDING INPUT SPIGOT WERE FOUND PULLED OUT OF VALVE BODY, ALLOWING LEAKAGE PAST THE INTERNAL O-RING. THE SCREWS LOApr 7, 2012 · Bell 212 · Turbine Engine Oil SystemSDR CA120227018Window · missing(CAN) THE ACFT WAS DESCENDING WHEN THE RT FORWARD POP OUT WINDOW WAS LOST IN FLIGHT FROM THE SLIDING, CREW, DOOR.Feb 19, 2012 · Bell 212 · Flight Compartment WindowsSDR CA120217001Link · unserviceable(CAN) DURING CRUISE AT 100 KIAS AT 6500` ASL, ACFT VIOLENTLY PITCHED DOWN 20 DEGREES FROM LEVEL WITH SIGNIFICANT VIBRATIONS. COLLECTIVE WAS LOWERED AS CONTROL OF THE ACFT WAS REGAINED. WHILE TURNING TO RETURN TO BASE THERE WAS AN APPARENT 1:1 VERTICAL AS WEFeb 16, 2012 · Bell 212 · Main Rotor GearboxSDR CA120227012Window · missing(CAN) CREW DOOR RT FORWARD POP OUT WINDOW WAS LOST IN FLIGHT. THE ACFT WAS IN A LEFT DESCENDING TURN. NO DAMAGE TO ACFT. POP OUT WINDOW WAS REPLACED.Feb 15, 2012 · Bell 212 · Flight Compartment WindowsSDR CA120123004Blade · cracked(CAN) ACFT WAS MINUTE INTO FLIGHT AT 200FT AGL WHEN THE PILOT HEARD A LOUD BANG AND FELT A SLIGHT VIBRATION IN THE CYCLIC CONTROL STICK. ACFT LANDED 1 MINUTE LATER WITHOUT FURTHER INCIDENT OR VIBRATION. CRACK IN LOWER BLADE SKIN FOUND 4.5" FROM L/E AND 1.25"Jan 20, 2012 · Bell 212 · Main Rotor BladesSDR CA120119012Ring Gear · cracked(CAN) CRACKS FOUND ON RING GEAR TEETH AFTER TRANSMISSION WAS DISASSEMBLED FOR CRACKED SUPPORT CASE LUG. RING GEAR SENT FOR NDI. INSPECTOR STATES THAT CRACKS WOULD NOT SHOW UP WITH MAGNAFLUX UNDER ANY CIRCUMSTANCE. CRACKS SHOWED UP READILY WITH LIQUID PENETRJan 19, 2012 · Bell 212 · Main Rotor GearboxSDR ALGA13102274112Coupling · wornOUTER COUPLING WORN BEYOND REPAIRABLE LIMITS.Jan 11, 2012 · N9YTSP · Bell 412EP · Tail Rotor Drive ShaftSDR ALGA1973611212Coupling · wornINNER COUPLING WORN BEYOND REPAIRABLE LIMITS.Jan 11, 2012 · N9YTSP · Bell 412EP · Tail Rotor Drive ShaftSDR CA120105011Lug · cracked(CAN) FOUND LT AFT LUG CRACKED ON TRANSMISSION SUPPORT CASE. CRACK FOUND WHEN TRANSMISSION WAS REMOVED FOR NON-RELATED AIRFRAME MAINTENANCE. THIS IS THE THIRD SIMILAR CRACKED CASE WE HAVE OBSERVED.Dec 28, 2011 · Bell 212 · Main Rotor GearboxSDR CA111104008Fitting · cracked(CAN) CRACK FOUND IN BASE OF FITTING. APPEARS TO HAVE BEEN CRACKED AT MFG AS THE BELL HELICOPTER INSPECTORS MARK ENGRAVED IN THE PART HAS DISPLACED METAL INTO THE CRACK.Nov 4, 2011 · Bell 212 · Main Rotor GearboxSDR CA111030005Engine · power loss(CAN) THE ACFT WAS TRANSPORTING BACK TO BASE FIREFIGHTERS THAT HAD BEEN WORKING A FOREST FIRE WHEN THE PILOT NOTED ENGINE FLUCTUATIONS FOLLOWED BY A LOSS OF MAIN ROTOR SPEED. HE RETARDED BOTH ENGINES TO IDLE AND HE MADE AN AUTOROTATION IN A FIELD. THE HELO TOct 18, 2011 · Bell 212 · Engine (Turbine/Turboprop)SDR CA111018004Crosstube · failed(CAN) WHILE RELOADING ACFT AT A FOB, AFT CROSSTUBE FAILED JUST INBD OF THE OUTER EDGE OF LT SADDLE BRACKET AND CLAMP ASSY. ON INVESTIGATION, SOME PITTING CORROSION WAS NOTED UNDER THE SADDLE AREA AT A POINT WHERE THE FRACTURE SEEMS TO HAVE ORIGINATED. ADDITIOct 14, 2011 · Bell 212 · Main Landing GearSDR CA090929004Bearing · loose(CAN) BEARING SLEEVE FOUND LOOSE DUE TO IMPROPER ADHESIVE USE AND IMPROPER STAKING OF BEARING ASSY.Aug 26, 2011 · Bell 212 · Main Rotor Mast/SwashplateSDR CA110803029Fitting · crackedLIFT LINK FITTING AFT LUG FOUND CRACKED BY MECHANIC DURING DAILY INSP. CAUSE WAS FOUND TO BE WRONG P/N BOLT INSTALLED. TB 212-91-132 HAD BEEN COMPLETED WHICH INCORPORATES IMPROVED LIFT LINK FITTING P/N 212-030-154-101 THAT REQUIRES LARGER DIAMETER BOLT P/N 41Aug 2, 2011 · Bell 212 · Main Rotor GearboxSDR CA110707014Seal · leakingHYDRAULIC PUMP LEAKING FROM INPUT SEAL.Jul 2, 2011 · Bell 212 · Hydraulic Pump (Electric/Engine), MainSDR CA110707015Actuator · seizedDROOP COMPENSATOR ACTUATOR SEIZED, WILL NOT EXTEND OR RETRACT.Jul 2, 2011 · Bell 212 · Turbine GovernorSDR CA110707016Selector Valve · intermittentFUEL VALVE, INTERMITTENT OPERATION.Jun 29, 2011 · Bell 212 · Fuel Selector/Shut-Off ValveSDR CA110611004Lock Plate · bentFUEL TRANSFER TUBE DISENGAGED FROM FUEL NOZZLE ALLOWING UN-RESTRICTED HIGH PRESSURE FUEL LEAKAGE. THE FUEL TRANSFER TUBE LOCK PLATE AT THE NR 6 FUEL NOZZLE LOCATION ON THE NR 1 ENGINE HAD NOT BEEN CORRECTLY INSTALLED 353.2 HOURS PREVIOUS DURING A SCHEDULED NOJun 7, 2011 · Bell 212 · Engine Fuel DistributionSDR CA110707012Oil Cooler · leakingHEATER LEAKING OIL FROM A WELD SEAM.Jun 7, 2011 · Bell 212 · Engine Fuel/Oil CoolerSDR CA110603008Fitting · crackedTHIS PART WAS INSPECTED IAW MFG ASB 212-10-142 B. DURING THE NDT INSP A CRACK WAS FOUND IN THE AREA HIGHLIGHTED BY THE ASB. THE PART HAS BEEN REMOVED FROM SERVICE AND IS WAITING FOR EVALUATION.Jun 2, 2011 · Bell 212 · Main Rotor Head
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