U/A Canada PT6A-27

Service difficulty reports · 642

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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 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 CA041129018Manifold · malfunctioned(CAN) AFTER REPLACING A SET OF FUEL MANIFOLD ADAPTERS ON A PT6A-27 ENG, A GROUND RUN WAS CARRIED OUT. THE RESULTING GROUND RUN SHOWED SIGNS OF FUEL LEAKAGE FROM THE TRANSFER TUBES P/N 3011155.ENGINE PERFORMANCE DATA SHOWED THAT THE T5 TEMPERATURE AND FUEL FLOWNov 26, 2004 · Engine Fuel DistributionSDR 2005FA0000004Inverter · malfunctionedON CLIMB OUT, RT ENGINE TORQUE DROPPED TO 500. AC RETURNED, WHERE THE TORQUE SYSTEM WAS JET CAL, GAUGES SWAPPED SIDE TO SIDE AND ALL SYSTEMS WORKED AS REQUIRED. MAINTENANCE SUSPECTS AN ELECTRICAL SPIKE FROM THE NR 1 INVERTER. THE GAUGES STUCK ON 500 BUT DRONov 19, 2004 · N326CA · Beech 99A · Engine (Turbine/Turboprop)SDR 2005FA0000005Cable · brokenON CLIMBOUT THE AIRSTAIR DOOR OPENED. AC RETURNED, WHEN AIRSTAIR DOOR OPENED IN FLIGHT, DOOR DAMPER BROKE AND SUPPORT CHAINS BROKE. CHAIN HIT PROPELLER AND CAUSED NOTICEABLE DAMAGE. DOOR ANNUNCIATOR LIGHT WAS NOT ILLUMINATED SO NO INDICATION OF ANY PROBLEMNov 16, 2004 · N153GA · Beech 1900C · Passenger/Crew DoorsSDR CA041112001Powerpack · faulty(CAN) A/C WAS SITTING ON RAMP PARKED, RT MAIN LANDING GEAR COLLAPSED. SUSPECT HYDRAULIC POWER PACK AT FAULT.Nov 8, 2004 · Beech 99A · Landing Gear Retraction/Extension SystemSDR COMA0460590Lamp · inoperativeFLIGHT 5118, EMERGENCY FLOOR PATH LIGHTS INOPERATIVE, ROWS 2 THRU 5. REPLACED STRIP LAMP.Oct 30, 2004 · N403CA · Cndair CL6002B19 · Emergency LightingSDR TIM2005F00001Shear Plate · crackedWHILE INSPECTING THE HORIZONTAL STABILIZER, THE LT SHEAR PLATE WAS FOUND TO HAVE A CRACK RUNNING ACROSS IT. THE ELEVATOR CONTROL HORN IS ATTACHED TO THE SHEAR PLATE WHICH IS ATTACHED TO THE HORIZONTAL STABILATOR. THE CRACK MUST HAVE DEVELOPED UNDER NORMAL CIOct 18, 2004 · N950AA · Beech B99 · Horizontal Stabilizer, Plate/SkinSDR YDA2005F00000Hinge · damagedTHE LT NOSE GEAR DOOR CENTER HINGE AND NOSE GEAR DOOR ACTUATOR LINK QUIDE, BENT. THE NOSE GEAR DOORS WERE DISCONNECTED FOR AN INSPECTION. THE LT MAIN GEAR DOORS WERE RIGGED AND A RETRACTION TEST WAS PERFORMED. A LOAD POPPING NOISE WAS HEARD. UPON INSPECTIOOct 18, 2004 · N99GH · Beech 99A · Landing Gear DoorsSDR CA041001008Barrel Nut · damaged(CAN) WHEN TORQUE CHECK OF ENGINE MOUNT BOLTS PERFORMED OB BOLT CORRECT TORQUE COULD NOT BE ACHIEVED. BARREL NUT REMOVED AND FOUND TO HAVE DAMAGED THREADS AND WAS OF FIBER LOCK STYLE. BARRREL NUT AND BOLT REPLACED WITH IPC REQUIRED PARTS.Sep 29, 2004 · Dhav DHC6300 · FastenersSDR CA041006007Engine · failed(CAN) ENG REMOVED FROM WING DUE TO INFLT SHUTDOWN CAUSED BY A POWER SECTION SEIZURE. ENG SENT TO ATLANTIC TURBINES FOR INVEST. POWER SECTION, POWER TURBINE & RIB, SUFFERED DAMAGE. POWER TURBINE DISK WAS NO LONGER COUPLED TO RIB INDICATES THAT A POSSIBILE PT OVSep 28, 2004 · Engine (Turbine/Turboprop)SDR AXS2004F00000Bearing · failedON THE TAKEOFF ROLL, 2 MAIN WHEEL ASSEMBLY DEPARTED THE AXLE. PRELIMINARY INVESTIGATION REVEALED THE OUTER WHEEL BEARING RACE HEAVILY DAMAGED AND THE OUTER BEARING DAMAGED BEYOND RECOGNITION. THE MAIN WHEEL AXLE NIT AND HARDWARE WAS FOUND STILL INTACT ON THESep 7, 2004 · N119WA · Beech B99 · Wheel/Ski/FloatSDR CA040730010Bearing · loose(CAN) DURING 100 HR INSPECTION, RT AILERON OUTER PUSHROD WAS FOUND TO HAVE A LOOSE BEARING, ALLOWING ROD END TO FLOAT SIDEWAYS ON BEARING. BEARING REMOVED, ROD END INSPECTED FOR DAMAGE, NONE FOUND. NEW BEARING INSTALLED AND CHECKED SERVICABLE. PUSH ROD ASSYJul 29, 2004 · Pilats PC6BH2 · Aileron Control SystemSDR CA040730011Bearing · loose(CAN) DURING 100 HR INSPECTION - LT IB AILERON CONTROL BELLCRANK WAS FOUND TO HAVE LOOSE FITTING BEARING. ALLOWING AILERON CONTROL ROD TO FLOAT UP AND DOWN, CONTACTING THE BELLCRANK ASSEMBLY. BEARING REMOVED, BELLCRANK AND CONTROL ROD CHECKED FOR DAMAGE, NONJul 29, 2004 · Pilats PC6BH2 · Aileron Control SystemSDR CA040722001Bolt · shearedDURING THE DAILY INSPECTION, IT WAS DETECTED THE TOP BOLT IN THE NOSE GEAR SCISSOR LINK WAS SHEARED. THE GEAR WAS INSPECTED AND NO DEFECTS NOTED. THE BOLT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (HAVE SEEN THIS ONCE BEFORE ON ANOTHER TWIN OTTER ABJul 21, 2004 · Dhav DHC6300 · FastenersSDR CA040712001Cap · leaking(CAN) LANDED BACK TO THE BASE, DUE TO FUEL LEAKAGE FROM FUEL CAP INTO THE CABIN. ON ARRIVAL FOUND SIGN OF FUEL LEAKAGE AT AFT TANK CAP TO THE ADJACENT PAX DOOR INTO THE CABIN. AFT TANK WAS FULL ON DEPARTURE, SUSPECT FUEL SEEPAGE FROM THE TANK CAP DUE TO SEALJun 18, 2004 · Dhav DHC6300 · Fuel StorageSDR CA040611008Bearing · unserviceable(CAN) PILOT DISCOVERED RUDDER MAKING SNAPPING NOISE WHILE CHECKING FREEDOM OF MOVEMENT AND RANGE FOR TRAVEL DURING PRE FLIGHT WALK AROUND. LOWER ATTACH BEARING OF RUDDER, FOUND TO HAVE FAILED ALLOWING RUDDER TO RUB ON ATTACHMENT MOUNT. RUDDER REMOVED AND BEAJun 8, 2004 · Dhav DHC6300 · Rudder/Tab, Attach FittingsSDR CA040427012Engine · failed(CAN) IN CRUISE FLIGHT THE PILOT HEARD A BANG AND THE RT ENGINE STOPPED TURNING. THE PROP WAS FEATHERED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. AFTER LANDING, THE PROPELLER COULD NOT BE TURNED BY HAND.Apr 26, 2004 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR BAQA094234Pump · leakingFUEL PUMP LEAKING. REPLACED WITH SERVICABLE UNIT. 04/22/2004Apr 22, 2004 · N999G · Beech 100BEECH · Engine Fuel PumpSDR BAQA094035Monitor · intermittentEXCHANGE - CORE RETURN FOR EXCHANGE PO 202350203, INDICATING INTERMITTENT. REPLACED WITH SERVICABLE MONITOR., 04/20/2004Apr 16, 2004 · N999G · Beech 100BEECH · Fuel Quantity IndicatorSDR BAQA094232Load Meter · unserviceableINDICATOR STICKS ON UNIT. REPLACED WITH SERVICABLE UNIT. 04/22/2004Apr 16, 2004 · N999G · Beech 100BEECH · Independent InstrumentsSDR CA040413013Fan · broken(CAN) DURING INSTALLATION OF FAN PN 230481490 AT OVERHAUL, THE CENTER PART OF THE FAN BROKE AWAY FROM THE FAN BODY AND BLADES. THE CAST ALUMINUM FAN WAS BEING ATTACHED TO THE SHAFT, ARMATURE AND BEARING ASSY WHEN IT BROKE CIRCUMFERENTIALLY BEFORE REACHING TARApr 8, 2004 · Dhav DHC6300 · Starter-GeneratorSDR GNL2004F00002Wheel · crackedON PREFLIGHT INSPECTION A DARK HAIR LINE CRACK EXTENDED FROM A BOLT HOLE ON THE IB SIDE OF THE WHEEL HALF. REMOVED WHEEL, APPLIED DYE PENT AND CONFIRMED THE CRACK. THE WHEEL HALF IS CONDEMNED AND REMOVED FROM SERVICE.Mar 26, 2004 · N44GK · Beech E90 · Wheel/Ski/FloatSDR CA040317003Engine · failed(CAN) ENG WAS REMOVED FROM WING, NOTED HIGHER THAN NORMAL OIL TEMP, OIL DISCOLORATION. UPON REMOVAL, EXH DUCT WAS MISSING SECT OF INNER DUCT EXPOSING PT SHAFT HSG TO EXH GASES. IT WAS FOUND THAT REAR SECTION OF EXH DUCT INNER SKI JUMP SECTION, EXTENDING FWMar 9, 2004 · Engine (Turbine/Turboprop)SDR CA040226001Volt Regulator · failed(CAN) AFTER DEPARTURE, THE AIRCRAFT SUFFERED A COMPLETE ELECTRICAL FAILURE. THE CREW NOTICED A BURNING ODOR. THE AIRCRAFT RETURNED WITHOUT FURTHER INCIDENT. UPON INVESTIGATION IT SEEMS LIKE A VOLTAGE SURGE OCCURRED, BOTH GPS ACU'S, BOTH COMM'S, RCR, DME, NR 1 Feb 21, 2004 · Dhav DHC6300 · Electrical Power System WiringSDR CA040211006Oil Cooler · cracked(CAN) AIRCRAFT RETURNED FROM FLIGHT WITH AN EXCESSIVE OIL LEAK ON THE LT ENGINE COWLS. INVESTIGATION DISCOVERED A CRACK IN THE OIL COOLER VERNATHERM INLET/OUTLET HOUSING. THE OIL COOLER WAS REPLACED WITH AZERO TIME UNIT AND CHECKED SERVICEABLE.THE OIL COOLER HFeb 5, 2004 · Dhav DHC6300 · Engine Oil CoolerSDR CA040106009Clamp · cracked(CAN) CRACKED CLAMP NOT DISCOVERED UNTIL THE OVERHAUL. PART MPI INSPECTED IAW ASTM-E-1444 WHEN FOUND.Dec 29, 2003 · Dhav DHC6300 · Propeller Hub SectionSDR CA040106010Bearing Race · cracked(CAN) BEARING RACE CRACKED, DISCOVERED AT OVERHAUL, DURING THE NDT PROCESS.Dec 29, 2003 · Dhav DHC6300 · Propeller Hub SectionSDR CA031120012Brake Assy · frozen(CAN) THE AIRCRAFT WAS OPERATING OUT OF A REMOTE STRIP. UPON BACK-TRACK AND TURN-AROUND FOR TAKE-OFF, THE A/C ENCOUNTERED DEEP SNOW AT THE END OF THE STRIP. NORMAL TAKE-OFF PROCEDURES WERE C/O. UPON LANDING AT YVQ, PILOTS EXPERIENCED ABRUPT DECELLERATION. TNov 19, 2003 · Dhav DHC6300 · BrakeSDR CA031029002Oil Filter · damaged(CAN) DURING A ROUTINE OIL FILTER CHANGE, THE NEW FILTER WAS VISUALLY INSPECTED AND FOUND TO HAVE 2 WIRE THREADS PROTRUDING FROM THE FILTER. THE ORIGINAL FILTERS WERE VISUALLY INSPECTED AND WERE FOUND TO BEIN THE SAME CONDITION. REFERENCING OUR STORES, WE ESTAOct 28, 2003 · Dhav DHC6300 · Engine Oil Distribution (Airframe Furnished)SDR CTO13098Pump · failedDURING CRUISE NR 1 FWD ELEC FUEL BOOST PUMP LOW PRESS WARNING LIGHT ILLUM. PULLED C/B. WITHIN MIN, PUMP NR 1 FWD PUMP FAILURE, NR 1 AFT ELEC FUEL BOOST PUMP LOW PRESS WARNING LIGHT ILLUM. PULLED C/B & RETURNED. UPON RESET OF C/B'S, SMOKE OBSERVED COMING FROct 23, 2003 · Dhav DHC6300 · Fuel Boost PumpSDR CA031022004Wheel · failed(CAN) ON THE LANDING ROLL, A BANG WAS HEARD AND THEN THE AIRCRAFT LEANED AND TURNED TOTHE RIGHT A BIT. THE CO-PILOT OBSERVED THE RIGHT MAIN TIRE WAS FLAT. THE A/C WAS SHUT DOWN AND PASSENGERS AND CARGO WERE OFF-LOADED. A PIECE OF THE WHEEL RIM WAS FOUND 100 Oct 11, 2003 · Dhav DHC6300 · Wheel/Ski/FloatSDR BAQA089501Gearbox · malfunctionedGEARBOX BINDING. REPLACED WITH SERVICEABLE UNIT.Oct 4, 2003 · N999G · Beech 100BEECH · Trailing Edge Flap Control SystemSDR BAQA089500Motor · overheatedMOTOR OVERHEATED. REPLACED WITH SERVICEABLE UNIT.Oct 4, 2003 · N999G · Beech 100BEECH · Trailing Edge Flap Control SystemSDR 2003FA0000910Spring · backed outOIL CAP WAS NOT FULLY ENGAGED IN OIL TANK CAUSING LOSS OF APPROX 6 QUARTS OIL DURING CLIMB OUT. DISCOVERED OIL CAP UNLATCH ASSIST SPRING HAD DISENGAGED FROM HOLE IN CAP LATCH BAR. THIS ALLOWED OIL CAP LOCKING TAB TO LOCK WITHOUT OIL CAP FULLY ENGAGED IN OIL TASep 10, 2003 · Dhav DHC6300 · Turbine Engine Oil SystemSDR 08270324Connector · arcedPILOT REPORTED DURING CRUSE FLT SMOKE ENTERED COCKPIT FROM AC ELECTRICAL PANEL AREA. NO SYSTEM MALFUNCTION WAS NOTED. NO ELECTRICAL POWER WAS LOST. ONCE ON GROUND DC POWER COULD NOT BE TURNED OFF THROUGH NORMAL SWITCHING. BATTERY WAS DISCONNECTED TO REMOVE DCAug 27, 2003 · N122SA · Dhav DHC6 · Electrical Power System WiringSDR CA031008005Line · burst(CAN) THE PILOTS HAD THE BETA BACKUP SYSTEM ON THE RT ENGINE FAIL IN FLIGHT. IT WAS DISCOVERED BY THE ENGINEER THAT THE BLEED AIR LINE HAD RUPTURED IN THE BRADED AREA WHERE IT LEAVES THE ENGINE COMPARTMENT AND GOES INTO THE WING. THE WIRE BUNDLE SUSTAINED DAMAAug 27, 2003 · Dhav DHC6300 · Engine Bleed Air System WiringSDR CA030908009Duct · damaged(CAN) RT BLEED AIRS LINE RUPTURED IN THE BRADED FLEX AREA. THE BLEED AIR THEN MELTED THE WIRE BUNDLE RUNNING FROM THE ENGINE INTO THE WING. THE ONLY INDICATION WAS THAT THE BETA BACKUP SYSTEM MALFUNCTIONED. ALL THE WIRES EXCEPT FOUR HAD DAMAGE WHEN REMOVED.Aug 27, 2003 · Dhav DHC6300 · Engine Bleed Air SystemSDR CA030819002Blade · fractured(CAN) ENGINE WAS SHUTDOWN IN CRUISE DUE TO TORQUE INDICATION DROPPING OFF AND ITT CLIMBING TO 6900C. DISMANTLE INVESTIGATION HAS REVEALED THAT CT DISK ASSEMBLY EXHIBITED ONE FRACTURED CT BLADE AT THE ROOT OF THE AIRFOIL OR BLADE PLATFORM. THE FRACTURED AIRFOIAug 14, 2003 · Turbine Engine Compressor SectionSDR AUS20030827Turbine Wheel · seized(AUS) ENGINE POWER SECTION SEIZED.Aug 7, 2003 · Dhav DHC6300 · Turbine SectionSDR CA030723003Rudder Pedal · broken(CAN) THE CAPTAIN'S RUDDER PEDAL BROKE OFF THE AXLE WHEN APPLYING THE BRAKES TO RELEASE THE PARKING BRAKE. WHEN EXAMINING THE PEDAL A DARKENED AREA IN THE AREA OF THE BREAK IS VISIBLE INDICATING IT WAS PREVIOUSLY CRACKED PRIOR TO THE FAILURE. THE RUDDER PEDAL Jul 21, 2003 · Dhav DHC6300 · Rudder Control SystemSDR CA030903003Blade · failed(CAN) RT ENGINE SHUTDOWN DUE TO LOW TORQUE 10 PSI AND RISING T5 SHUTDOWN AT 690 DEGREES C. PILOT WAS IN CRUISE ABOUT 9 MINS AFTER TAKEOFF FROM GJOA HAVEN. AIRCRAFT RETURNED TO GJOA HAVEN AND PERFORMED AN UNEVENTFUL LANDING. MAINTENANCE DISCOVERED A FUEL LINEJul 17, 2003 · Dhav DHC6300 · Turbine Engine Compressor SectionSDR AUS20030768Adapter · cracked(AUS) FORWARD VERTICAL FIN ATTACHMENT BRACKET CRACKED THROUGH BOLT MOUNTING HOLE.Jul 14, 2003 · Dhav DHC6300 · Vertical Stabilizer, Attach FittingsSDR CA030628001Relay · shorted(CAN) DURING FLT, CREW SMELLED ELECTRICAL BURNING ODOR. SYS SYSTEMATICALLY SHUT DOWN INCLUDING, AVIONICS & AIRCRAFT MASTER, ODOR DISSIPATED. ALL RADIOS WERE SWITCHED OFF IN AN ATTEMPT TO SECURE OPERATION OF ONE RADIO FOR COMMS. A/C & AVIONICS MASTER WERE SWITJun 26, 2003 · Dhav DHC6300 · Electrical Power System WiringSDR CA030613005Rib · worn(CAN) EXCESSIVE LOOSENESS BETWEEN THE TWO HALVES OF THE FLAP AT THE CENTER HINGE ARM POSITION. THE RIBS ON EITHER SIDE OF THE HINGE ARM ARE ASSEMBLED TO THE ARM BY THE USE OF MS20470AD5-24 SOLID RIVETS. IT WOULD APPEAR THAT THERE HAS BEEN SOME WORKING BETWEENJun 5, 2003 · Dhav DHC6300 · Trailing Edge FlapsSDR CA030527011Pin · loose(CAN) PILOT REPORTED THAT HE RAN OUT OF NOSE DOWN ELEVATOR TRIM WITH FLAPS 30 DEGREES. INSPECTED FLAP TRIM INTERCONNECT AND FOUND NO FAULTS. INSPECTED ELEVATOR TRIM AND FOUND THAT NOSE DOWN TRIM WAS LIMITED BY A STOP IN THE COCKPIT TRIM WHEEL. FOUND THAT PIN TApr 29, 2003 · Dhav DHC6300 · Elevator Tab Control SystemSDR CA030318007Stator Vane · fractured(CAN) PILOT REPORTED A LOUD BANG AND TORQUE DROPPING OFF ON LANDING. THE SUBJECT ENGINE WAS REMOVED FROM SERVICE AND SENT FOR INVESTIGATION AND REPAIR. INVESTIGATION RESULTED IN THE FINDING OF ONE MISSING FIRST STAGE STATOR VANE (I.E. 1 OF 44) FROM THE 1ST SMar 6, 2003 · Dhav DHC6300 · Turbine Engine Compressor SectionSDR AUS20030320Hinge · corroded(AUS) LEVEL 1 CORROSION WAS FOUND ON EXTERNAL SURFACES IN VARIOUS LOCATIONS. LEVEL 2 CORROSION WAS FOUND ON FLAP HINGE ARMS,VERTICAL AND HORIZONTAL FORWARD ATTACHMENT FITTINGS. FOUND DURING INSPECTION IAW AD/DHC-6/69, LEVEL 1 AND LEVEL 2 CORROSION WAS FOUND ASFeb 7, 2003 · Dhav DHC6300 · Trailing Edge FlapsSDR CA030205001Bracket · cracked(CAN) DURING CHANGEOVER FROM FLOATS TO WHEELS A CRACK WAS FOUND ON THE TAIL WHEEL ATTACHMENT LUG. THE CRACK WAS ON THE LT FORWARD ATTACH POINT OF THE TAIL WHEEL. THIS BRACKET ALSO ATTACHES THE HORIZONTAL STABILIZER ON THE UPPER PICKUPS. BRACKET WAS REPLACED WIFeb 5, 2003 · Dhav DHC2MK3 · Horizontal Stabilizer, Attach FittingsSDR CA030205006Cam · cracked(CAN) DURING INSPECTION CRACKS WERE FOUND ON THE CAM ASSY FOR THE PROP GOVERNOR. THE CRACKS WERE LOCATED WHERE THE SCREWS ATTACH THE BRACKET ASSY TO THE ENGINE FIRE WALL. FIG 76 ITEM 24 IN THE TURBO BEAVER IPC. BRACKET WAS REPLACED WITH A NEW UNIT FROM VIKING Feb 5, 2003 · Dhav DHC2MK3 · Propeller GovernorSDR CA030211001Rib · cracked(CAN) CRACKED RIB FLANGE OUTBOARD MOST RIB WING STATION 376.20.Feb 4, 2003 · Dhav DHC6300 · AileronsSDR CA030211002Bracket · cracked(CAN) OIL COOLER BRACKET IS A WELDED ASSEMBLY FROM FACTORY. CRACKS ORIGINATED FROM MOUNTING HOLES AND 'RELIEF' AREA.Feb 4, 2003 · Dhav DHC6300 · Engine Oil Cooler
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