U/A Canada PT6A-27

Service difficulty reports · 642

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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 = 'PT6A27'
  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 CA090610002Transmitter · malfunctioned(CAN) DURING INSTALLATION AND LEAK CHECK, FUEL WAS COLLECTING ON THE BASE PLATE. THE MOUNT BOLTS WERE SUBSEUENTLY TIGHTENED AND THE BASE WIPED DRY, WITHIN A MINUTE FUEL HAD AGAIN COLLECTED ON THE BASE PLATE CAUSING A FUEL DRIP. THE FUEL SYSTEM HAD 120 LBS. ONLJun 10, 2009 · Dhav DHC6300 · Fuel Quantity IndicatorSDR CA090706006Feeder Cable · burned(CAN) LT ENG FAILED TO START, NO PWR TO START GENERATOR, WHEN LT INBD L/E WAS OPENED LUG FOR GENERATOR CABLE AT NACELLE FEED THRU WAS BURNED UP, CABLE WAS REPLACED AND ACFT RETURNED TO SERVICE. THIS CONNECTION WAS LAST SECURED WHEN WINGS WERE REINSTALLED DURIMay 20, 2009 · Dhav DHC6300 · Electrical Power System WiringSDR CA090514002Cover · mismanufactured(CAN) NEW FUEL MANIFOLD TUBE DUST COVERS (PN PDMC6PF1054-27) WERE FOUND TO BE DIMENSIONALLY SMALLER THAN THE EXISTING FACTORY-MADE PARTS. THESE COVERS WERE PRODUCED UNDER LOT/PO NR 30322. THE RUBBER COMPOUND THAT THESE ARE CONSTRUCTED OF ALSO APPEARS TO DIFFERMay 14, 2009 · Dhav DHC6300 · Engine Fuel DistributionSDR CA090422001Feeder Cable · wrong part(CAN) DURING INSTALLATION, IT WAS NOTED THAT THE NEW CABLE WAS TOO SHORT FOR OEM MM ROUTING PATH. WHEN COMPARED TO REMOVED SERVICEABLE CABLE IT WAS NOTED THAT THE NEW CABLE WAS 14.5 INCHES SHORTER MINIMUM.Apr 22, 2009 · Dhav DHC6300 · Electrical Power System WiringSDR CA090423010Turbine Blades · failed(CAN) EIR PT6A 2009-08 CT BLADE FAILURE.Apr 21, 2009 · Turbine SectionSDR CA090422002Frame · cracked(CAN) DURING O/H OF ACFT, TECH FOUND SMOKING RIVETS ON THE ACFT FRAME AT VERTICAL FIN ATTACH BRACKET, REMOVED BRACKET AND 6 OF 6 HOLES WERE CRACKED, BRACKET REPAIRED.Apr 20, 2009 · Dhav DHC2MK3 · Vertical Stabilizer, Spar/RibSDR CA090416002Piston · damaged(CAN) WHILE CONDUCTING DISASSEMBLY OF NOSE GEAR FOR OVERHAUL, THE PISTON TUBE WAS FOUND TO HAVE SUBSTANTIAL DAMAGE TO THE UPPER THREADED END BY WHAT APPEARS TO BE ELECTRICAL ARCING. THIS HAS RESULTED IN MATERIAL LOSS AND PISTON TUBE DEEMED UNSERVICEABLE. OTHERApr 16, 2009 · Dhav DHC6300 · Nose/Tail Landing Gear Strut/AxleSDR CA090401006Leg Assy · misinstalled(CAN) A FRESH D-CHECKED GEAR LEG (RT) WAS TO BE INSTALLED ON ACFT. WHEN ATTEMPTING TO MOUNT THE LWR PLATE ASSY TO THE GEAR LEG, IT WAS FOUND THAT 3 OF THE 4 MOUNT HOLES HAD IMPROPERLY INSTALLED HELI-COILS. WHILE ATTEMPTING TO INSTALL BOLTS, THESE HELI-COILS Apr 1, 2009 · Dhav DHC6300 · Main Landing GearSDR 2009F00025Bushing · crackedENGINE OIL PRESSURE WAS LOW DURING ENGINE OPERATION. MAIN OIL FILTER SHOWED METAL. SIGNIFICANT METAL FOUND IN REDUCTION GEARBOX CHIP DETECTOR AND STRAINER. ON TEARDOWN OF REDUCTION GEAR SECTION OF ENGINE, ONE OF THE GEARS IN THE SECOND STAGE REDUCTION GEAR CARMar 25, 2009 · Turbine Engine Reduction GearSDR CA090311009Governor · unserviceable(CAN) AFTER TAKEOFF, ON RETURN TO BASE THE PILOT FOUND THAT HE COULD NOT CONTROL THE LT PROP. THE PROP STAYED IN FULL FINE EVEN WHEN PROP LEVER WAS SELECTED TO FULL COURSE OR TO FEATHER. AFTER LANDING AT BASE MX INSPECTED THE LT ENG RIGGING, AND LT PROP. EVERMar 9, 2009 · Dhav DHC6300 · Propeller GovernorSDR CA090305003Connector · damaged(CAN) WHILE ASSEMBLING THIS CONNECTOR AS PART OF A SATELLITE PHONE INSTALLATION THE TECH NOTED THAT THE PINS WOULD NOT PROPERLY ENGAGE IN ALL THE PLUG SOCKETS. AFTER SEVERAL ATTEMPTS TO COMPLETE THE INSTALLATION THE PINS SEEMED TO ENGAGE, HOWEVER SOME PINS WERMar 5, 2009 · Dhav DHC6300 · Communications System WiringSDR CA090302006Adapter · corroded(CAN) DURING INSP THE REAR SPAR ADAPTER WAS FOUND HEAVILY CORRODED. MORE INFO TO FOLLOW.Mar 2, 2009 · Dhav DHC6300 · Wing SparSDR CA090228001Housing · misinstalled(CAN) DURING SCHEDULED MX, THE LWR BRG HSG ASSY ON THE ELEVATOR LEVER ASSY LOCATED BENEATH THE COCKPIT WAS FOUND TO BE INSTALLED UPSIDE DOWN. SUBSEQUENT RUBBING DAMAGE HAS RESULTED AND THE PART DEEMED UNSERVICEABLE.Feb 28, 2009 · Dhav DHC6300 · Elevator Control SystemSDR CA090205008Thrust Bearing · improper partBECAUSE OF AN ISSUE WITH ANOTHER ACTUATOR OF THE SAME PN THE COMPANY REMOVED THIS ACTUATOR FOR INSP. IT WAS FOUND THAT THRUST BRG ON THIS ACTUATOR WAS OF AN INCORRECT TYPE OR PN. (REF SDR 20090205006) THE TWO ACTUATORS WERE RECEIVED FROM THE SAME COMPANY AT TFeb 4, 2009 · Beech 99 · Landing Gear ActuatorSDR CA090119009Intake · corrodedDURING A STRUT REPAIR, THE TECH FOUND SEVERE CORROSION, LEVEL 3, ON 2 LONGERON INTAKE COWLS, PN C2TEC1001-18 AND C2TEC1001-17. BOTH PARTS WERE REPLACED.Jan 16, 2009 · Dhav DHC2MK3 · Engine Air Intake SystemSDR CA090105010Engine · failed(CAN) EIR PT6A 2008-105 INTERNAL ENGINE FAILURE.Jan 5, 2009 · Engine (Turbine/Turboprop)SDR CA090123004Torque Tube · cracked(CAN) WHILE ACFT WAS IN FOR MAJOR OVERHAUL AND PAINT, THE ELEVATOR BELLCRANK TORQUE TUBE WAS REMOVED FOR ROUTINE MX. THE BELLCRANK ARMS WERE FOUND LOOSE. AFTER THE ARMS WERE REMOVED THE STEEL TORQUE TUBE WAS NDT INSPECTED. CRACK INDICATIONS WERE FOUND ON TWO (Dec 29, 2008 · Beech B99 · Elevator Control SystemSDR CA081209004Mount · worn(CAN) WHILE COMPLETING A 100 HOUR INSPECTION THE UPPER LORD MOUNT WAS FOUND TO BE U/S. BOTH RUBBER HALVES HAD DETERIORATED TO THE POINT THAT RUBBER PIECES WERE CRUMBLING AND FALLING OFF. THERE WERE SMALL PILES OF CRUMBLED RUBBER ON THE TOP OF THE ENGINE. THDec 1, 2008 · Beech 99 · Engine Mount SectionSDR CA081114008Fastener · loose(CAN) DURING INSP, THERE WAS SEVERAL CHERRY MAX RIVETS FOUND TO BE LOOSE ON THE UNDERSIDE OF THE RT WING BETWEEN STATION 35.15 AND 97.50. THE RIVETS WERE ALL LOCATED ON A TRIPLE ROW OF RIVETS AT THE AFT SPAR. FURTHER INSPECTION REVEALED A TOTAL OF 160 RIVETS NNov 13, 2008 · Dhav DHC6300 · Wing, Center BoxSDR TIMA20080006Engine · seizedPILOT FELT A POWER SURGE AND SAW FLAMES OUT THE LEFT ENGINE EXHAUST FOR A MOMENT. LEFT PROPELLER STOPPED TURNING. PILOT SECURED ENGINE, CONTINUED ON AND LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED THAT THE PT BLADES WERE MOSTLY GONE. CT BLADES ARE OK. Oct 27, 2008 · N95WA · Beech 99 · Engine (Turbine/Turboprop)SDR S9BA2008029Turbine · damagedRIGHT ENGINE MAKES NOISE WHEN PROP MOVED BY HAND. REMOVED AND REPLACED RIGHT ENGINE AND PROPELLER AS A QEC ASSEMBLY. SPLIT ENGINE AT C-FLANGE AND FOUND POWER TURBINE RUB.Oct 22, 2008 · N562CP · Dhav DHC6300 · Turbine SectionSDR CA081017002Csu · malfunctioned(CAN) THE ACFT WAS IN CRUISE FLIGHT WHEN THE TORQUE ON THE RT ENGINE SURGED AND THE PROPELLER BEGAN TO FEATHER. AS THE POWER WAS BROUGHT BACK THE PROPELLER STOPPED FEATHERING. A PRECAUTIONARY ENGINE SHUTDOWN WAS PERFORMED AND THE ACFT RETURNED TO BASE WITHOUT Oct 7, 2008 · Dhav DHC6300 · Propeller Controlling SystemSDR CA081010005Attach Fitting · corroded(CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE WING GEAR/STRUT ATTACH FITTING TO BE CORRODED (LEVEL 3).Oct 2, 2008 · Dhav DHC2MK3 · Fuselage, Landing Gear Attach FittingsSDR CA081010006Torque Tube · cracked(CAN) DURING A ROUTINE 100 HOUR INSPECTION A AME FOUND THE ELEVATOR TRIM TORQUE TUBE TO BE CRACKED, PART WAS REPLACED AND CUSTOMER WAS ADVISED.Oct 2, 2008 · Dhav DHC2MK3 · Elevator Tab Control SystemSDR CA081010007Fitting · split(CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE FLOAT FITTING TO HAVE TYPE 3 CORROSION THAT CAUSED FITTING TO SPLIT. FITTING REPLACED WITH NEW PART.Oct 2, 2008 · Dhav DHC2MK3 · Wheel/Ski/FloatSDR CA081010010Screw · corroded(CAN) DURING A 100 HOUR INSPECTION POST RUN UP THE AME FOUND THE IDLE NEEDED TO BE ADJUSTED. UPON LOOSENING IDLE SCREW JAM NUT IDLE SCREW FAILED DUE TO LEVEL 3 CORROSION. FCU REMOVED AND SENT FOR REPAIR.Oct 2, 2008 · Dhav DHC2MK3 · Fuel Control/Turbine EnginesSDR CA081117006Yoke · broken(CAN) DURING A 100 HOUR INSP, THE YOKE LT INTAKE COWL BROKE AT MACHINED LOCKING TAB EAR CUT OUT UPON INSTALLATION WHILE RIVETING, LT YOKE-INTAKE COWL WAS REPLACED.Sep 26, 2008 · Dhav DHC2MK3 · Engine Air Intake SystemSDR CA080924009Attach Fitting · cracked(CAN) DURING THE 12 MONTH INSP OF THE MLG WHICH CONSISTS OF INSPECTING THE WELDS FOR CRACKS, A CRACK WAS DETECTED ON THE BOTTOM OF THE AFT ATTACH TUBE APPROX 5 INCHES FROM THE AFT GEAR ATTACH FITTING.Sep 24, 2008 · Dhav DHC6300 · Main Landing GearSDR CA080924010Leg Assy · cracked(CAN) DURING THE 12 MONTH INSPECTION OF THE MLG WHICH CONSISTS OF INSPECTING THE WELDS FOR CRACKS, A CRACK WAS DETECTED ON THE BOTTOM OF THE AFT ATTACH TUBE APPROX 5 INCHES FROM THE AFT GEAR ATTACH FITTING. (TC NR 20080924010)Sep 24, 2008 · Dhav DHC6300 · Main Landing GearSDR 2008FA0000614Rod · brokenBETA ROD CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K)Sep 9, 2008 · Dhav DHC6300 · Propeller AssemblySDR 2008FA0000615Ring · brokenBETA RING CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K)Sep 9, 2008 · Dhav DHC6300 · Propeller AssemblySDR 2008FA0000695Rod · brokenBETA ROD CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K)Sep 9, 2008 · Dhav DHC6300 · Propeller Controlling SystemSDR 2008FA0000696Beta Ring · brokenBETA RING CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR. (K)Sep 9, 2008 · Dhav DHC6300 · Propeller Controlling SystemSDR CA080807005Hinge Fitting · mismanufactured(CAN) THE HINGE ARM ASSY WAS RECEIVED FROM THE OEM WITH THE BONDING STRAP AND TAB INSTALLED ON THE UPPER ARM OF THE ASSY WHICH IF INSTALLED WOULD RESTRICT TRAVEL OF THE ELEVATOR. THE BONDING STRAP IS A FIXED LENGTH AND RIVETED IN PLACE. ADDITIONALLY TO MAKE THAug 7, 2008 · Dhav DHC6300 · Elevator StructureSDR CA080722007Bushing · missing(CAN) BUSHINGS MISSING FROM WING PICKUP LUGS ON ORIGINAL FRAMES INSTALLED IN ACFT.Jul 18, 2008 · Dhav DHC6 · Wing StructureSDR CA080806009Drive Assy · stripped(CAN) DURING CLIMB OUT AT 800 FEET ALTITUDE THE ACFT SUDDENLY STARTED TO SHAKE VIOLENTLY. THE PILOT ABORTED THE CLIMB, PROCEEDED STRAIGHT AHEAD FOR 4 MILES TO A LANDING STRIP AND LANDED SAFELY WITH NO INJURIES TO PERSONS ON BOARD. UPON INVESTIGATION AS TO THE Jul 18, 2008 · Dhav DHC6300 · Elevator Control SystemSDR CA080704002Rod · worn(CAN) DURING AN INSPECTION ON ACFT, IT WAS DISCOVERED THAT THE LT INBD CHORD-WISE FLAP ROD WAS RUBBING AGAINST THE SPAN-WISE ROD. ONCE THEY WERE REMOVED FROM THE ACFT, IT WAS NOTED THAT THE SPAN-WISE ROD HAD A GROOVE WORN IN IT FROM THE OTHER ROD. A NEW SPAN-WJul 2, 2008 · Dhav DHC6300 · Trailing Edge FlapsSDR S9B2008F00001Compressor · noisyUNUSUAL NOISE NOTED IN COMPRESSOR SECTION NR 2 ENGINE, UPON START UP, REMOVED ENGINE FROM SERVICE WILL CLOSE SDR WHEN SOURCE OF NOISE IS FOUND AND CORRECTED. (K)Jun 20, 2008 · N562CP · Dhav DHC6300 · Turbine Engine Compressor SectionSDR S9BA2008024Blade · wornUNUSUAL NOISE NOTED IN COMPRESSOR SECTION (NR 2 ENG) UPON START UP. REMOVED ENGINE FROM SERVICE, ENGINE RETURNED TO ENGINE SHOP, FOUND 1ST STAGE BLADE RUB. ENGINE PENDING REPAIR. (K)Jun 20, 2008 · N562CP · Dhav DHC6300 · Turbine SectionSDR CA080612003Line · mismanufactured(CAN) A NEW FUEL TUBE ASSY WAS TO BE INSTALLED BETWEEN FUEL CELL NR 4 AND NR 6. THE INSTALLER FOUND THE TUBE ASSEMBLY TO BE .7500 INCHES TOO SHORT FOR THE LOCATION.Jun 12, 2008 · Dhav DHC6300 · Aircraft Fuel Distribution SystemSDR CA080612004Line · mismanufactured(CAN) A NEW FUEL TUBE ASSY WAS TO BE INSTALLED BETWEEN FUEL CELL NR 5 AND NR 8 AS PART OF THE MOTIVE FLOW SYS. THE INSTALLER FOUND THE TUBE ASSY TO BE ONE INCH TOO LONG FOR THE LOCATION.Jun 12, 2008 · Dhav DHC6300 · Aircraft Fuel Distribution SystemSDR CA080602005Exhaust Duct · cracked(CAN) DAMAGED EXHAUST DUCT, PRIMARY FAILURE WAS TO THE INNER CONE OF THE EXHAUST DUCT, APPEARED TO CRACK AT NR 3 BEARING END AND EVENTUALLY DAMAGED THE T/E OF THE PT ROTOR BLADES. (TC NR 20080602005)May 16, 2008 · Engine Collector/Tailpipe/NozzleSDR 2008FA0000488Housing · brokenABOUT 12 INCHES OF THE RGB FRONT HOUSING SPLINES WERE FOUND BROKEN OFF DUE TO FATIGUE CRACK. (K)Apr 23, 2008 · Turbine Engine Reduction GearSDR CA080418004Plate · damaged(CAN) RECEIVED A CALL REGARDING DAMAGE THAT OCCURRED TO THE PROP BACKING PLATED ON A TURBO BEAVER WE COMPLETED REG, C-FOEU. THIS DAMAGE IS THE RESULT OF OUR INSTALLATION OF OUR PROP POSITION TRANSMITTER MOD STCSA 98-46, VT2E 1623. IDENTIFIED THE PROBLEM TO BEApr 17, 2008 · Dhav DHC2MK3 · Propeller Spinner SectionSDR CA080414005Duct · damagedMETAL SWARF FOUND INSIDE COOLING PASSAGES OF DUCT ASSY.Apr 11, 2008 · Turbine Engine Compressor SectionSDR 2008FA0000285Pump · failedBOOST PUMP FAILS AT 11,000 TO 12,000 FT OF ALTITUDE. WORKS FINE ON GROUND. (K)Apr 2, 2008 · N359AR · Dhav DHC6300 · Fuel Boost PumpSDR S9BA200800015Longeron · damagedDURING SCHEDULED 125HR INSPECTION FOUND: RT ENGINE NACELLE IB LONGERON DAMAGED FORWARD OF LEADING EDGE AT STATION 60.8. REMOVED AND REPLACED RT NACELLE IB LONGERON ASSY IAW AC 43-131B CHP7 EMERGENCY MEASURES EXECUTED: NO AIRCRAFT. GROUNDED: BEING REPAIRED DURMar 25, 2008 · N562CP · Dhav DHC6300 · Nacelle/Pylon, Longeron/StringerSDR S9BA200800013Control Rod · corroded125 HR INSPECTION, EMERGENCY MEASURES EXECUTED, NO, AC GROUNDED. NO CORROSION FOUND ON RT FLAP INTERCONNECT ROD UNDER FLEXIBLE BOOT. ON IB END. REMOVED AND REPLACED CONTROL ROD.Feb 22, 2008 · N888PV · Dhav DHC6300 · Trailing Edge Flap Control SystemSDR CA080220001Rod End · bent(CAN) THE PILOT REPORTED A DEFECT NR 2582A: ABOUT 10 MINUTES AFTER TAKEOFF, THE RT ENGINE NR 2 THROTTLE LEVER WAS STUCK. WORKED THE THROTTLE BACK AND FORTH IN CRUISE 3 - 4 TIMES AND FOUND OK. ON FINAL APPROACH INTO ARRIVAL AIRPORT, THE NR 2 THROTTLE WAS DIFFeb 19, 2008 · Dhav DHC6300 · Power LeverSDR CA080222006Line · puncturedHYDRAULIC PUMP SUPPLY LINE IN THE COCKPIT DEVELOPED A PIN-HOLE FAILURE IN THE WALL OF THE TUBING. THE HYDRAULIC FLUID AT A PRESSURE OF 1650 PSI WAS RELEASED INTO THE CABIN, ATOMIZING AS IT DID SO, THE DIRECTION OF THE SPRAY WAS DIRECTLY AT THE PILOT. THE POWFeb 19, 2008 · Dhav DHC2MK3 · Hydraulic System, Main
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