U/A Canada PT6A-135

Service difficulty reports · 128

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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 = 'PT6A135'
  ORDER BY difficulty_date DESC"

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SDR CA060502004Shroud · distortedDURING HOT SECTION KIT REPAIR OF A PT6A-135 ENG, CT SHROUD SEGMENT-RETAINING RING WAS FOUND LOOSE AND PARTIALLY DISENGAGED FROM CT SHROUD HOUSING RETAINING GROOVE. MINOR SHIFTING OF CT SHROUD SEGMENTS WERE NOTED (SEE PHOTOGRAPH NR 1 AND 2). THE CT SHROUD SEGMApr 24, 2006 · Turbine SectionSDR CA060314004Circuit Breaker · brokenLANDING GEAR FAILED TO EXTEND WHEN SELECTED. POWERPACK C/B OPEN.Mar 13, 2006 · Beech F90 · Landing Gear System WiringSDR CA060227023Motor · unserviceableNOSE GEAR FAILED TO EXTEND CORRECTLY AS INDICATED BY GEAR IN TRANSIT. GEAR EXTENDED MANUALLY AND LANDED WITHOUT INCIDENT. CAUSE UNDER INVESTIGATION AT THIS TIME.Feb 24, 2006 · Beech F90 · Landing Gear Retraction/Extension SystemSDR CA060127003Indicator · failed(CAN) FUEL FLOW INDICATIONS WENT INTERMITTENT THEN FAILED IN FLIGHT. FOUND TRANSMITTER TO HAVE FAILED INTERNALLY. TIME ON UNIT APROX.5000 HRS. (TC NR 20060127003)Jan 19, 2006 · Beech F90 · Fuel Flow SensorSDR CA060130003Shroud · damagedROUTINE BOROSCOPE INSPECTION OF HOT SECTION COMPONENTS REVEALED THAT TWO CT SEGMENTS HAD DROPPED OUT OF PLACE AND CONTACTED CT WHEEL. THE SEGMENT RETAINING RING P/N 3020139 WAS FOUND OUT OF PLACE AND THE CT BLADES HAD WORN BEYOND LIMITS DUE TO HEAVY TIP RUB. Jan 16, 2006 · Beech F90 · Turbine SectionSDR CA060130004Shroud · damagedROUTINE BOROSCOPE INSPECTION OF HSI COMPONENTS FOUND TWO SEGMENTS HAD DROPPED OUT OF POSITION. POWER SECTION REMOVED AND CT COMPONENTS INSPECTED. CT BLADES FOUND TO HAVE CONTACTED SEGMENT ENDS AND RETAINING RING P/N 3020159 FOUND OUT OF PLACE. SEGMENTS REPLJan 16, 2006 · Beech F90 · Turbine SectionSDR CA051012004Arm · crackedWHILE COMPLYING WITH PIPER SL1092, INSPECTION/REPLACEMENT OF MAIN LANDING GEAR RETRACTION ARMS, THE LEFT ARM WAS FOUND CRACKED AT THE INSIDE RADIUS.Oct 11, 2005 · Piper PA31T2 · Landing Gear Retraction/Extension SystemSDR CA050613002Hose · leaking(CAN) OIL PRESSURE DROPPED PASSED 40 PSI IN FLIGHT. SHUTDOWN LT ENGINE. FOUND OIL SUPPLY HOSE FROM OIL COOLER TO TOP OF ENGINE LEAKING. REPLACED WITH NEW. INSPECTED OIL CHIP DETECTOR, FOUND NO FAULTS. ADDED ENGINE OIL TO ENGINE. PERFORMED SATISFACTORY ENGINE Jun 9, 2005 · Piper PA31T2 · Turbine Engine Oil SystemSDR CA050321008Fuel Control · failed(CAN) ENGINE POWER REDUCED TO IDLE ON TAKEOFF. MAINTENANCE INSPECTION REVEALED FUEL CONTROL UNIT FAILURE. REPLACED ENGINE DRIVEN PUMP TO FUEL CONTROL COUPLING AND FUEL CONTROL UNIT. GROUND RUN SERVICEABLE. AIRCRAFT RETURNED TO SERVICE.Mar 11, 2005 · Beech F90 · Fuel Controlling SystemSDR CA050224011Engine · malfunctioned(CAN) THE ENGINE WAS SHUTDOWN IN FLIGHT DUE TO DECREASING ENGINE OIL PRESSURE ACCOMPANIED BY OIL ODOR IN CABIN AND INCREASING OIL AND TURBINE TEMPERATURES. MFG WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE OFeb 16, 2005 · Beech F90 · Engine (Turbine/Turboprop)SDR CA040806009Housing · cracked(CAN) DURING A WALKAROUND, THE PILOT NOTICED THE LT OLEO WAS LOWER THAN THE RT. AT THE MAINTENANCE BASE THE AME INSPECTED THE LT OLEO WHICH WAS COMPLETELY FLATNOW. UPON FURTHER INSPECTION BY THE AME, FOUND HYDRAULIC FLUID IN THE WHEEL WELL AND DOWN THE GEAR LAug 10, 2004 · Piper PA31T2 · Landing Gear Retraction/Extension SystemSDR CA040610007Wire Harness · loose(CAN) ENGINE TEMPERATURE STARTED TO FLUCTUATE IN FLIGHT, MAINTENANCE TROUBLESHOT AND TRACED PROBLEM TO ENGINE, SPLIT THE ENGINE AND FOUND THE TERMINAL END WAS LOOSE. THE FACTORY HAD NOT SOLDERED THE END ON PROPERLY. REPLACED THE HARNESS AND RETURNED PART TO MJun 8, 2004 · Dhav DHC3 · Engine Oil System WiringSDR EWG2004F00000Skin · wrinkledIAW REQUIREMENTS OF FAR 145.63, SUBMITS THIS 8010-4. IN THE PROCESS OF PERFORMING A PHASE 2 AND 3 INSPECTION, DIAGONAL WRINKLES WERE DISCOVERED ON THE TOP LT WING PANEL BETWEEN THE AUX AND AFT SPARS IB OF THE NACELLE. AFTER CONTACT WITH AND REVIEW BY MFG ENGJan 14, 2004 · N6845R · Cessna 425 · Wing, Plate/SkinSDR 2004FA0000078Strut · crackedLOWER END OF STRUT CRACKED BETWEEN INNER AND OUTER ATTACH LUGS (IN THE WEB) FROM BOTTOM OF STRUT UP .7500-1 INCH. THERE WERE NO ABNORMAL CIRCUMSTANCES THAT CAUSED THE CRACK. THE CRACK WAS VERY OBVIOUS, VIEW WAS UNOBSTRUCTED AND EASILY DETECTED DURING 100 HOUNov 20, 2003 · N959PA · Dhav DHC3 · Main Landing Gear Strut/Axle/TruckSDR CA030501007O-Ring · split(CAN) IN CRUISE PILOT OBSERVED OIL SPRAYING ONTO THE WINDSCREEN. AS HE WAS CLOSE TO A MAINTENANCE BASE HE ELECTED TO LAND AND HAVE IT LOOKED AT. AT LANDING HE NOTICED OIL PRESSURE HAD DROPPED TO YELLOW (70 PSI AND THE LOW OIL PRESSURE LIGHT HAD FLICKERED ONCE.Apr 28, 2003 · Dhav DHC3 · Turbine Engine Oil SystemSDR CA030313003Regulator Valve · malfunctioned(CAN) ON APPROACH, THE CREW NOTICED MULTIPLE AVIONICS FAILURES. BOTH VOR SIGNAL STRENGTHS VERY WEAK, NR 1 COMM INOP, MOST NAVIGATION EQUIPMENT INOP. THE PNEUMATIC PRESSURE WAS NOTED AS BEING AT 21 PSI, WHEN IT SHOULD HAVE BEEN AT 18 PSI. THE PNEUMATIC REGULATOMar 8, 2003 · Piper PA31T2 · Engine Bleed Air SystemSDR CA030311004Exhaust Stack · cracked(CAN) ON HEAVY MAINTENANCE INSPECTION FOUND BOTH EXHAUST DUCT FLANGES ON LARGE EXIT DUCT CRACKED. THIS IS THE THIRD TIME WE HAVE CHANGED AN EXIT DUCT ON A TURBINE CONVERSION INSTALLATION.Mar 3, 2003 · Dhav DHC3 · Engine Collector/Tailpipe/NozzleSDR CA030211007Spar · cracked(CAN) DURING SCHEDULED 100 HOUR EVENT NR 2 INSPECTION, CRACKS FOUND ON LEFT SIDE STABILIZER SPAR ASSEMBLY AFT BETWEEN RIB STABILIZER LEADING EDGE BL102 AND BL114.Feb 3, 2003 · Piper PA31T2 · Horizontal Stabilizer, Spar/RibSDR CA021217002Wire · broken(CAN) ON FINAL APPROACH, PILOTS SELECTED GEAR DOWN. THREE GREEN INDICATION LIGHTS WERE CONFIRMED. THE GEAR HANDLE WOULD NOT COME BACK TO NEUTRAL. THE CREW CONDUCTED A MISSED APPROACHED AND PROCEEDED TO FOLLOW THE APPROPRIATE CHECKLISTS. THE CREW FLEW OVER Dec 14, 2002 · Piper PA31T2 · Landing Gear System WiringSDR CA021213003Fitting · misaligned(CAN) ON DEPARTURE, THE FLIGHT CREW NOTICED FLUID LEAKING FROM THE RT ENGINE NACELLE. THE CREW RETURNED TO BASE FOR MAINTENANCE INVESTIGATION. MAINTENANCE REPLACED NR 6, 7, 8, 9 & 10 FUEL NOZZLE GASKETS AND TRANSFER TUBE O-RINGS. GROUND RUN WAS FOUND SATISFDec 5, 2002 · Piper PA31T2 · Engine Fuel DistributionSDR CA021024001Socket · loose(CAN) ON FINAL APPROACH, THE CREW NOTICED AN UNSAFE LANDING GEAR INDICATION. THE CREW IMMEDIATELY INITIATED A MISSED APPROACH. THE APPROPRIATE EMERGENCY CHECKLISTS WERE PERFORMED AND WHILE LOOKING FOR THE PROBLEM, THE CREW NOTICED THAT THE EMERGENCY GEAR SOCOct 21, 2002 · Piper PA31T2 · Landing Gear Position and WarningSDR CA020722009Fuel Control · failed(CAN) ON START UP, THE LEFT ENGINE STARTED ACCELERATING OUT OF CONTROL, REGARDLESS OF POWER LEVER POSITION. THE CONDITION LEVER WAS THEN PULLED AND THE ENGINE SHUT DOWN. THE FUEL CONTROL UNIT (FCU) WAS REPLACED WITH AN OVERHAULED UNIT AND A SATISFACTORY RUN UPJul 4, 2002 · Piper PA31T2 · Fuel Control/Reciprocating EnginesSDR CA020729005Hinge · cracked(CAN) DURING SCHEDULED 100 HOUR EVENT NR 2 LANDING GEAR INSPECTION, CRACK FOUND ON LEFT HAND FORWARD MAIN LANDING GEAR OUTBOARD DOOR HINGE. CAUSE DETERMINED TO BE FATIGUE.Jul 3, 2002 · Piper PA31T2 · Landing Gear DoorsSDR CA020510019Bolt · sheared(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN, THE RIGHT MAIN & NOSE GEAR LOCKED DOWN CORRECTLY BUT THE LEFT MAIN DID NOT. THE CREW THEN SELECTED EMERGENCY GEAR EXTENSION AND LANDED SAFELY. UPON INSPECTION THE LEFT ACTUATOR UPPER BOLT WAS FOUND TO BE SHMay 1, 2002 · Piper PA31T2 · Landing Gear ActuatorSDR CA020401002Volt Regulator · failed(CAN) LEFT GENERATOR SYSTEM FAILED DURING CLIMB.Mar 28, 2002 · Piper PA31T2 · DC Generating SystemSDR CA020313006Shaft · stripped(CAN) FCU AND FUEL PUMP WAS REMOVED FROM ENGINE. FUEL PUMP TO ENGINE SHAFT WAS FOUND STRIPPED, RESULTING IN FUEL STARVATION.Mar 11, 2002 · Piper PA31T2 · Engine Fuel PumpSDR CA020226014Windshield · cracked(CAN) ENROUTE AT FL210 THE OUTER PANE OF THE LEFT WINDSHIELD CRACKED. CREW MADE NORMAL DESCENT TO LOWER ALTITUDE, REDUCED PRESSURIZATION AND RETURNED TO LAND. PART WAS REPLACED WITH NEW P/N 101-384025-21.Feb 21, 2002 · Beech F90 · Flight Compartment WindowsSDR CA020125001Hydraulic System · contaminated(CAN) LEFT BRAKE WAS DRAGGING DURING AIRCRAFT TAXIING. THE AIRCRAFT WAS TOWED TO HANGAR WHERE THE BRAKE SYSTEM WAS FOUND WORKING NORMALLY. THE BRAKE SYSTEM (CALIPER & MASTER CYLINDER) WAS DISASSEMBLED AND WATER CONTAMINATION WAS FOUND PRESENT IN THE HYDRAULICJan 23, 2002 · Piper PA31T2 · Hydraulic System, MainSDR CA020117001Tire · punctured(CAN) NOSE WHEEL TIRE BECAME FLAT DURING LANDING, CAUSING A SHIMMY NOTICEABLE TO PILOTS.Jan 14, 2002 · Piper PA31T2 · TireSDR CA030416004Actuator · failed(CAN) FROM TSB A01A0112, FOLLOWING TAKE OFF OF A FLOAT EQUIPPED DHC 3T, THE CONTROL COLUMN PITCHED VIOLENTLY FORWARD AND BACK BEFORE RETURNING TO A NEUTRAL POSITION. THE AIRCRAFT THEN PITCHED DOWN AND CONTACTED THE WATER IN A NOSE DOWN, WINGS LEVEL ATTITUDE. Nov 1, 2001 · Dhav DHC3 · Stabilizer ActuatorSDR CA011004005Attach Fitting · cracked(CAN) DURING INSPECTIONS FOUND THAT ELEVATOR SERVO TAB HAD TWO SHEARED OFF RIVETS UPPER FORWARD ENGINE AT ARM ATTACHMENT BLOCK AND CRACK AT LOWER BETWEEN RIVET HOLES ON ELEVATOR SERVO TAB.Sep 27, 2001 · Dhav DHC3 · Elevator, Tab StructureSDR CA010628056Bolt · sheared(CAN) UPON COMPLETION OF THE FLIGHT THE PILOT SHUT DOWN THE ENGINE WITH THE PROPELLOR ON ZERO PITCH. AFTER THE ENGINE HAD COMPLETELY SHUT DOWN AND STOPPED THE PILOT FOUND THAT THE PROPELLER HAD MOVED TOWARDTHE FEATHER POSITION RATHER THAN STAYING IN THE ZERO PJun 7, 2001 · Dhav DHC3 · Propeller Hub SectionSDR CA010625033Bracket · mismanufactured(CAN) SWITCH MOUNT FLANGE NOT BENT PROPERLY PER DRAWING TO OBTAIN 90 DEGREE RELATIONSHIP WITH PIVOT POINT. THIS RESULTS IN A SMALLER RANGE OF ADJUSTMENT. SWITCH P/N 622EN51 (HONEYWELL) INTERNAL SPRING IS SOSTIFF(3-6LBS) THE BRACKET FLEXES EXCESSIVELY AS THE SWMay 18, 2001 · Beech F90 · Landing Gear SelectorSDR CA010507015Rod End · worn(CAN) FOUND ROD END WORN EXCESSIVELY ON INSPECTION 200 HOURS AFTER STC SA99-219/ST01243NY WAS INSTALLED.May 7, 2001 · Dhav DHC3 · Elevator Tab Control SystemSDR 2001B4106Rivet · shearedALL RIVETS SECURING MASS BALANCE ARM (INSTALLED PER VIKING AIR LTD. ANTIFLUTTER MOD KIT NO VALTOC1136 AND APPROVED PER STC ST01243NY) SHEARED RESULTING IN SEPARATION OF THE SERVO TAB ACTUATION WITH THE MOVEMENT OF THE ELEVATOR CONTROL. PILOT FELT OSCILLATIONApr 2, 2001 · N50KA · Dhav DHC3 · Elevator Tab Control SystemSDR 20010410AP019Hose · crackedDURING CRUSE FLIGHT THE LT ENGINE LOW OIL PRESSURE WARNING SOUNDED ALERTING THE PILOT TO DROPPING OIL PRESURE. PILOT PERFORMED A PRECAUTIONARY ENGINE SHUTDOWN AND MADE A UNEVENTFUL LANDING. TECHNICICAN INSTALLED A NEW REPLACEMENT INLET OIL COOLER HOSE AND RETUMar 15, 2001 · N410CA · Piper PA31T2 · Engine Oil CoolerSDR CA010314023Window · broken(CAN) - THE AIRCRAFT WAS CLIMBING THROUGH 16,000 FEET WHEN THE CABIN PRESSURIZATION WAS LOST. - THE PILOTS INITIATED EMERGENCY DESCENT TO 10,000 FEET AND DECLARED EMERGENCY. - THE CAUSE FOR DEPRESSURIZATION WAS FOUND TO BE A BROKEN WINDOW IN THE CABIN AREA (3RFeb 23, 2001 · Piper PA31T2 · Passenger Compartment WindowsSDR 20010410AP018Hose · crackedDURING CRUSE FLIGHT THE RIGHT ENGINE OIL PRESSURE LOW WARNING ALERT SOUNDED. PILOT SECURED ENGINE AND RETURNED TO THE AIRPORT. TECHNICAN REMOVED ENGINE COWLING AND NOTED ENGINE OIL DRIPPING FROM THE OIL COOLER HOSE FIRE SLEEVE. THE OIL LINE WAS REPLACED AND AIDec 4, 2000 · N410CA · Piper PA31T2 · Engine Oil CoolerSDR CA001207028Fitting · cracked(CAN) AT SCHEDULED INSPECTION A CRACK WAS FOUND AT THE LOWER BOLT WEB ON THE RT MLG AFT SIDE BRACE FITTING.Nov 15, 2000 · Piper PA31T2 · Main Landing Gear Attach SectionSDR CA000928013Lever · loose(CAN) DURING A ROUTINE 400 HOUR INSPECTION OF THE ELEVATOR SERVO TAB, THE ENGINEER FOUND THAT THE RIVETS SECURING THE LEVER TO THE SERVO TABLWERE LOOSE. THE ENGINEER REMOVED THE TAB, AND REPLACED THE LOOSE RIVET WITH NEW RIVETS. THE SERVO TAB WAS REINSTALLED.Sep 11, 2000 · Dhav DHC3 · Elevator Control SystemSDR CA000829018Screw · loose(CAN) NOT AN SDR - WHILST CARRYING OUT A 100 HOUR INSPECTION, THE ENGINEER NOTICED THAT THE SCREWS ATTACHING THE COUNTERWEIGHT ARM TO THE SERVO TAB WERE LOOSE. THE TRIM TAB WAS OPENED UP, THE SCREWS WERE TIGHTENED, THE TAB WAS CLOSED UP AND THE AIRCRAFT WAS REAug 20, 2000 · Dhav DHC3 · Flight Control SystemSDR CA000829019Rod End · wrong part(CAN) WHEN CARRYING OUT A 100 HOUR INSPECTION, THE ENGINEER NOTICED THAT THE ROD END BEARING ON THE ELEVATOR TRIM TAB ROD LOOKED UNUSUAL. UPON FURTHER INVETIGATION, THE ENGINEER NOTED THAT IT WAS UNLIKE ANY OTHER HE HAD EVER SEEN!THE PART OF UNKNOWN ORIGIN WASAug 20, 2000 · Dhav DHC3 · Elevator Tab Control SystemSDR CA000720005Tab · loose(CAN) WHILE CARRYING OUT THE 100 HOUR INSPECTION OF THE SERVO TAB, THE ENGINEER NOTICED THAT THERE WAS EXCESSIVE PLAY IN THE ELEVATOR SERVO TAB OPERATING LEVER. UPON FURTHER INVESTIGATION, FOUND THE SERVO TAB HAD TO BE REPLACED DUE TO WEAR ON THE OPERATING LEJul 14, 2000 · Dhav DHC3 · Elevator, Tab StructureSDR CA000720006Control Cable · frayed(CAN) WHILE CARRYING OUT AN INSPECTION OF THE WATER RUDDER CABLES, THE ENGINEER FOUND THE WATER RUDDER STEERING CABLE THAT ATTACHES TO THE RUDDER BELLCRANK BELOW THE PILOTS FLOOR WAS SEVERELY FRAYED WHERE IT CONTACTS THE FORWARD PULLEY ON THE BACKSIDE OF THE FJul 14, 2000 · Dhav DHC3 · Rudder Control SystemSDR CA000720010Switch · out of adj(CAN) - PILOT DID NOT RECEIVE NOSE GEAR DOWN LIGHT INDICATION AFTER CYCLING GEAR DOWN FOR LANDING. MAINTENANCE ADVISED PILOT TO USE RUDDER PEDALS TO ACTIVATE NOSE GEAR DOWN MICROSWITCH. THIS ACTION GAVE NOSE GEAR DOWN INDICATION TO PILOT. THE AIRCRAFT WAJun 28, 2000 · Piper PA31T2 · Landing Gear Position and WarningSDR CA000720015Bolt · sheared(CAN) UPON LANDING THE AIRCRAFT, THE PILOTS NOTICED A PULLING TO THE LEFT. AFTER A BRIEF INSPECTION, THE THREE UPPER AN3 BOLTS, WHICH HOLD THE STEERING ARM AND BRACKET TO THE NOSE GEAR CYLINDER, WERE FOUND TO BE SHEARED.Jun 28, 2000 · Piper PA31T2 · Landing Gear Steering SystemSDR 20000629SH001Valve · leakingINTERNAL LEAK OF FUEL THROUGH GATE VALVE, WITH SHUT-OFF VALVE IN CLOSED POSITION. (I)Jun 23, 2000 · N15 · Beech F90 · Fuel Selector/Shut-Off ValveSDR CA000712015Lock · malfunctioned(CAN) DURING FLIGHT IN ROUGH TURBULENCE, THE REAR CARGO DOOR CAME OPEN. THE FLIGHT CREW ADVISED THAT THE LOCKS HAD BEEN SECURED AND LOCKED. THE AIRCRAFT IS HERE UNDERGOING REPAIR. INSPECTED THE LOCKS AND CAN FIND NO PROBLEM WITH THEM AS OF YET.Jun 21, 2000 · Dhav DHC3 · Cargo/Baggage DoorsSDR CA000712016Breather Tube · leaking(CAN) THE AIRPLANE CONSUMED APPROXIMATELY 5 LITERS OF OIL IN 1 HOUR OF FLIGHT. THE CENTRIFUGAL BREATHER WAS REMOVED FOR INSPECTION AND DEEMED UNSERVICEABLE BY THE PRATT & WHITNEY FIELD REP ON HAND. A REPLACEMENT PART WAS INSTALLED.Jun 21, 2000 · Dhav DHC3 · Turbine Engine Oil SystemSDR CA000606032Trunnion · cracked(CAN) DURING INSPECTION, A CRACK WAS FOUND ON THE AFT RIGHT MAIN LANDING GEAR TRUNNION ASSEMBLY. THE CRACK WAS FOUND TO BE ON THE UPPER REINFORCEMENT RIB. THE PART WAS REPLACED WITH NEW.May 25, 2000 · Piper PA31T2 · Main Landing Gear Strut/Axle/Truck
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