U/A Canada PT6A-34

Service difficulty reports · 465

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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 = 'PT6A34'
  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 CA021104007Extinguisher · loose(CAN) AT LAST FLIGHT OF THE DAY, PILOT NOTICED PRESSURE VERY LOW ON REAR CABIN HAND FIRE EXTINGUISHER AND REPORTED SNAG. UPON REMOVAL, MAINTENANCE PERSONNEL FOUND UNIT VERY LIGHT, AND PRESSURE ZERO. THE Q.A.CHECKED: BOTTLE LOOSELY UNSCREWED FROM HEAD. NOTE: SEOct 27, 2002 · Emb EMB110P1 · Fire Bottle, PortableSDR CA021028004Torque Link · cracked(CAN) DURING A LANDING GEAR INSPECTION THE TECHNICAIAN FOUND THE CENTER POINT OF TORQUE LINK PART NUMBER 14470 CRACKED.Oct 23, 2002 · Emb EMB110P1 · Landing Gear Retraction/Extension SystemSDR CA021101003Control Cable · frayed(CAN) AIRCRAFT AFTT: 22782.0 HOURS. CABLE FOUND FRAYED DURING INSPECTION OF ELEVATOR CABLE SYSTEM AS PER AD 82-09-08R2 AND SB 110-027-064-R2 AND C2 INSP SHEET, HENCE NECESSITY OF DISCONNECTING CABLES FOR PROPER INSPECTION. PULLEY MS 20220A2 ALSO REPLACED AS SHOct 13, 2002 · Emb EMB110P1 · Elevator Control SystemSDR CA021016037Switch · failed(CAN) GAP SHORT CAUSED BY POSSIBLE LOOSE AIR COLLECTOR WHEN OPEN/SHUT BY PASSENGER, COMING IN CONTACT WITH LIGHT ASSEMBLY. A SMALL PLASTIC TONGUE PROTRUDING FROM SWITCH TO ISOLATE N & P PROBES / LUGS ON SWITCH MAY HAVE BEEN BROKEN. POSSIBLE SIMPLY INSIDEOct 3, 2002 · Emb EMB110P1 · Passenger Compartment LightingSDR CA020917004Case · cracked(CAN) DURING ROUTINE MAINTENANCE THE MAINTENANCE CREW NOTICED TWO SMALL CRACKS ON THE RT ENGINE GAS GENERATOR CASE. THESE CRACKS ARE LOCATED AT THE FIRE SEAL MOUNTING ANGLES. THE ENGINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.Sep 16, 2002 · Emb EMB110P1 · Turbine SectionSDR CA020903002Fuel Nozzle · failed(CAN) AT TERMINATING A ROUTINE 7 DAYS INSPECTION ON THE AIRCRAFT, THE MECHANIC SPOTTED A ROUND DISCOLOURED 'DOT' ON THE ENGINE CASING, TWO FUEL NOZZLES WERE REMOVED TO INVESTIGATE WITH A BORESCOPE TO CONFIR M APPARENT DAMAGE IN THE FUEL COMBUSTION LINER. ENGINAug 12, 2002 · Emb EMB110P1 · Turbine Engine Combustion SectionSDR CA020708010Filter · damaged(CAN) P3 FILTER WAS IN THREE PIECES WHEN REMOVED FROM P3 HOUSING . IT WOULD APPEAR THAT THE BONDING AGENT THAT WAS USED FAILED OR NOT THE RIGHT QUANITY USED.Jul 3, 2002 · Dhav DHC3 · Compressor Bleed ControlSDR CA020621001Liner · cracked(CAN) NEW BRAKE LININGS WERE INSTALLED ONTO BACKING PLATES & PRESSURE PLATES FOR BRAKE CYLINDER ASSY, USING PROPER RIVETS ASSPECIFIED BY CLEVELAND WHEELS & BRAKES. A/C TAXIED FOR CONDITIONING BRAKE LININGS AS PER MANUFACTURE FOR NONASBESTOS ORGANIC LININGS.A/CJun 15, 2002 · Dhav DHC6300 · BrakeSDR CA020613001Fitting · worn(CAN) PUSH PULL ROD ATTACH POINT ON THE FOREFLAP HAD PLAY. UPON INSPECTION WE FOUND THAT THE RIBS HOLDING THE BRACKET FOR THE PUSH PULL ROD WAS CRACKED AND HAD LOOSE RIVETS.Jun 13, 2002 · Dhav DHC3 · Trailing Edge Flap Control SystemSDR CA020626005Skin · separated(CAN) HINGE SEPARATING FROM SERVO TAB IN FLIGHT. ELEVATO BOTTOM SKIN SEPARATED 24 INCHES ALONG TRAILING EDGE. CENTRE SPAR BROKEN IN 3 PARTS.TAILING SPAR BROKEN IN 2 PIECES.Jun 9, 2002 · Dhav DHC3 · Elevator Tab Control SystemSDR CA020523009Clamp · loose(CAN) PILOT REPORTED THAT FLAPS WOULD NOT OPERATE WHEN SELECTED. MAINTENANCE CONFIRMED THE SNAG ON THE RAMP. INVESTIGATION REVEALED THAT THE AREA AROUND THE FLAP PROTECTION BOX, FLAP MOTOR AND ASSYMETRIC ASSEMBLY WAS VERY WARM. THESE ITEMS ARE LOCATED UNDER THMay 22, 2002 · Emb EMB110P1 · Engine Bleed Air SystemSDR CA020605003Bracket · cracked(CAN) DURING A SCHEDULED INSPECTION THE UPPER RUDDER ATTACHMENT BRACKET WAS FOUND CRACKED.May 5, 2002 · Emb EMB110P1 · Rudder StructureSDR 2002FA0000568Blade · failedDURING TAKE OFF THE ENGINE LOST ALL POWER. ENGINE WAS SHIPPED TO CERTIFIED REPAIR STATION. THE PRELIMINARY ANALYSIS IS IN THE ENGINE TURBINE SECTION: THE COMPRESSOR TURBINE DISC P/N 3013411, S/N 2P609, HAD SEVERAL BLADES (BLADES 9,11 THRU 19, 21, 44, AND 45May 1, 2002 · N9185F · Airtrc AT502 · Turbine Engine Compressor SectionSDR AUS20020572Gearbox · seized(AUS) LH ENGINE REDUCTION GEARBOX SEIZED. METAL CONTAMINATION OF OILSYSTEM.Apr 10, 2002 · Dhav DHC6300 · Turbine Engine Reduction GearSDR CA020326011Hinge · cracked(CAN) THE PILOT REPORTED INTEMITTENT ELEVATOR CONTROL ABNORMALITY. INSPECTION REVEALED THAT THE RT OUTBOARD ELEVATOR HINGE POINT WAS CRACKED. THE EFFECTED PARTS WHERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.Mar 19, 2002 · Emb EMB110P1 · Elevator Tab, Attach FittingsSDR AUS20020236Duct · cracked(AUS) EXHAUST DUCT CONTAINED HAIRLINE CRACKS.Mar 14, 2002 · Emb EMB110P1 · Engine Collector/Tailpipe/NozzleSDR CA020222003Valve · leaking(CAN) 1) AN OVERHAULED PARKING BRAKE VALVE WAS INSTALLED TO REPLACE A UNIT "ROBBED" TO SERVICE ANOTHER AIRCRAFT. NOTE: AIRCRAFT HANGARED MORE THAN TWO (2) DAYS, THUS WARM FLUID AND SYSTEM. 2) OVERHAULED VALVE INSTALLED. 3) UPON FIRST PRESSURE TEST FOLLOWING IFeb 16, 2002 · Emb EMB110P1 · Master Cylinder/Brake ValveSDR AUS20020143Filter · cracked(AUS) HYDRAULIC FILTER HOUSING CRACKED CIRCUMFERENTIALLY IN THREADED AREA. LOSS OF HYDRAULIC FLUID. VENT / DUMP VALVE ALSO FAULTY DUE TO A SPLIT O-RING SEAL.Feb 11, 2002 · Gulstm G73 · Hydraulic Filter, MainSDR CA020225003Engine · deteriorated(CAN) - DETERIORATION INTERNALLY- COATING DETERIORATED ON SMALL EXIT DUCT WHICH CAUSED DAMAGE TO TURBINE BLADES.- CORROSION THROUGHOUT ENGINE (UNEXPLAINABLE) INSIDE AND OUT - WHITE POWDER.Feb 11, 2002 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR CA020225004Engine · corroded(CAN) - DETERIORATION INTERNALLY- CORROSION THROUGHOUT ENGINE - WHITE POWDERFeb 11, 2002 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR 2002FA0000153Window · crackedWINDOW CRACKED LOWER FORWARD CORNER FROM STORM WINDOW OPENING TO MOUNTING BOLTS. AIRCRAFT WAS AT CRUISE AND 5PSI WHEN INCIDENT OCCURED.Jan 31, 2002 · N9167Q · Piper PA46350P · Window/Windshield SystemSDR CA011218009Control Cable · frayed(CAN) FOUND THE FORWARD RUDDER CABLE TO BE SHOWING WEAR AT THE LOCATION AT THE FAIRLEAD AT STATION 8.00. THE CABLE WAS REPLACED WITH A NEW UNIT AND THE CABLE RUN WAS CHECKED THROUGH THE FAIRLEAD.Nov 29, 2001 · Dhav DHC2MK1 · Rudder Control SystemSDR AUS20011268Pipe · cracked(AUS) PIPE LOCATED BETWEEN FCU AND START CONTROL VALVE CRACKED AT FITTING.Nov 22, 2001 · Emb EMB110P2 · Engine Fuel DistributionSDR CA011121014Downlock Switch · failed(CAN) DURING DESCENT INTO YMO THE CREW SELECTED GEAR DOWN AND DID NOT GET A LT MAIN GEAR DOWN AND LOCKED INDICATION. THE LANDING GEAR WAS CYCLED A FEW TIMES AND GEAR DOWN AND LOCKED WAS CONFIRMED WITH INDICATION OF DOWN AND LOCKED. AS A PRECAUTION THE CREW ELENov 19, 2001 · Emb EMB110P1 · Landing Gear Position and WarningSDR CA011018013Boot · damaged(CAN) ON APPROACH A VIBRATION WAS FELT BY THE FLIGHT CREW. VISUAL INSPECTION BY THE FLIGHT CREW REVEALED THE OB LEFT HAND WING DEICE BOOT WAS RIPPED AND FLAPING AGAINST THE WING. THE AIRCRAFT LANDED WITH OUT INCIDENT, HOWEVER A PORTION OF THE DEICE BOOT SEPERAOct 17, 2001 · Emb EMB110P1 · Airfoil Anti/De-ice SystemSDR CA011029001Ball Joint · damaged(CAN) ON ROLL OUT FOLLOWING LANDING THE BALL JOIINT ASSEMBLEY PULLED OUT OF THE UPPER TORQUE LINK. THIS CAUSED THE RIGHT MAIN WHEEL TO TURN 180 DEGREES. REPAIRS REQUIRED THE REPLACEMENT OF BOTH THE UPPER TORQUE LINK AND THE BALL JOINT ASSEMBLYOct 14, 2001 · Emb EMB110P1 · Main Landing GearSDR CA011109014Fastener · sheared(CAN) DURING A 12C INSPECTION (7200 HOUR) MAINTENANCE PERSONNEL FOUND SEVERAL SHEARED HILOCKS ON THE LEFT HAND WING AT RIB NR 6.THE LEFT HAND LANDING GEAR WAS REMOVED AND AREA INSPECTED, NO STRUCTURAL DAMAGE WAS FOUND. 22 HILOCKS WERE REPLACED AND GEAR REINSTAOct 13, 2001 · Emb EMB110P1 · Wing Main, Frame StructureSDR AUS20010952Pipe · cracked(AUS) PIPE LOCATED BETWEEN FCU AND START CONTROL VALVE CRACKED AT FITTING.Aug 29, 2001 · Emb EMB110P2 · Engine Fuel DistributionSDR 2001FA0000431Bearing · crackedRELEVANT INDICATION.Aug 28, 2001 · Propeller AssemblySDR CA010622037Light · sparks(CAN) CUSTOMER REPORTED SPARKS FROM LOOSE OVERHEAD LIGHT IN 7TH ROW, LEFT SIDE.Jul 5, 2001 · Emb EMB110P1 · Passenger Compartment LightingSDR CA010621016Pin · making metal(CAN) AT T/O POWER LEVER GOT NOTICIABLY DIFFICULT TO MOVE, EVENTUALLY SEIZING COMPLETELY AT LANDING. APPEARS TO BE MATERIAL FAILURE OF PINJun 1, 2001 · Dhav DHC3 · Power LeverSDR CA010627052Tube · cracked(CAN) DURING CRUISE 300 FT AGL, MAIN TRANSMISSION OIL PRESS WAS NOTICED FLUCTUATING. AN IMMEDIATE PRECAUTIONARY LANDING WAS CARRIED OUT. A/C WAS INTERMEDIATELY SHUT DOWN. UPON INVESTIGATION TUBE ASSY P/N 212-040-233-001 IN HELL HOLE WAS FOUND LEAKING. TUBE REPMay 19, 2001 · Bell 212 · Main Rotor GearboxSDR CA010622029Exhaust Stack · cracked(CAN) ON A 100 HOUR INSPECTION A CRACK WAS FOUND ON THE LT EXHAUST STACK MOUNTI NG FLANG OF THE TURBINE_EXHAUST DUCT. DUE TO THE FACT THAT THERE WAS SO LITTLE TIME ON THE ENGINE I CALLED P&W AND THEY SENT A REP. & A NEW PART FOR OUR AIRCRAFT. THE REP DID NOT KMay 12, 2001 · Dhav DHC3 · Engine Collector/Tailpipe/NozzleSDR CA010621024Hose · blocked(CAN) BRAKES ON 4TH SIDE WERE REPORTED GRABBING AND OCCASSIONALLY NOT RELEASING PROPERLY. BRAKE UNIT, SHUTTLE VALVE AND BRAKE PRESSURE REDUCER WERE ALL REPLACED WITH NO SUCCESSFUL RESULT. IT WAS DISCOVERED THAT THE ABOVE BRAKE HOSE HAD DETERIORATED INSIDE AND May 8, 2001 · Emb EMB110P1 · BrakeSDR CA010529003Line · broken(CAN) ON LANDING THE PILOT PUMPED THE FLAPS DOWN, WHEN THE FLAPS REACHED THE DOWN POSITION THE HYDRAULIC LINE TO THE FLAP SELECTOR BROKE, LEAKING HYDRAULIC FLUID ON TO THE FLOOR. THE PILOT LANDED THE AIRCRAFT WITHOUT INCIDENT. UPON INVESTIGATION THE AME FOUND May 5, 2001 · Dhav DHC3 · Hydraulic System, MainSDR CA010504005Wheel · separated(CAN) WHILE TAXIING OFF RUNWAY AFTER LANDING LT MAIN WHEEL FAILED. APPROXIMATELY 12 INCHES OF BEAD SEAT SEPARATED FROM INBOARD WHEEL HALF INSTANTLY DEPRESSURIZING TIRE. AIRCRAFT TAXIED TO SAFE ZONE. MAINTENANCE REPLACED WHEEL ON TAXI WAY AND AIRCRAFT WAS RETURApr 11, 2001 · Emb EMB110P1 · Wheel/Ski/FloatSDR CA010508015Line · cracked(CAN) DURING CLIMB, HYDRAULIC FLUID LOW LEVEL WARNING LIGHT ILLUMINATED. MANUAL GEAR EXTENSION PERFORMED, AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND A CRACKED HYDRAULIC LINE IN THE L/H MAIN WHEEL BAY HYDRAULIC LINE REPLACED, HYDRAULIC SYSTEM SERVICED. HYDRAULICMar 30, 2001 · Emb EMB110P1 · Hydraulic System, MainSDR AU010324Door · disconnected(AUS) NOSE LANDING GEAR DOORS DISCONNECTED ON TAKEOFF PREVENTING NOSE LANDING GEAR FROM RETRACTING. SUSPECT DOORS INCORRECTLY ATTACHED. PERSONNEL/MAINTENANCE ERROR.Mar 17, 2001 · Emb EMB110P2 · Landing Gear DoorsSDR CA010411003Taper Pin · corroded(CAN) AIRCRAFT TT: 18965.4 HRS CYC: 24946 PART TT: APP. 7200 HRS. IF REPLACED AT LAST C12 INSP. TAPER PIN CONE BUSHINGS ALSO AFFECTED. PIN DID NOT COME OUT WITH MANUFACTURERS SPECIAL TOOL PRESS. NEW PINS AND CONES REQUIRED. PIN HAD TO BE DRILLED AND CUT BY MAMar 15, 2001 · Emb EMB110P1 · Fuselage, Wing Attach FittingsSDR H1IR069Y02Vane · crackedCOMPRESSOR TURBINE VANE RING OUTER RING ANTI ROTATION LUGS ARE CRACKED OR SEPARATED BEYOND THE MAXIMUM REPAIRABLE LIMIT OF SEVEN. 9 OF 14 LUGS FOUND SEPARATED.Mar 5, 2001 · Turbine Engine Compressor SectionSDR CA010222007Light · failed(CAN) IN FLT AFTER LEVELING OFF AT 9000 ODOUR STARTED COMING FROM HEATING VENTS. CREW OPTED TO SHUT AIR-COND SYS OFF TO FIND OUT WHERE SMELL COMING FROM. AT SAME TIME CREW CHECKED OP OF SMOKE ALARMS. THEY FUNCTIONED NORMALLY. CREW HAD THOUGHT THAT GLYCOL COULDFeb 7, 2001 · Emb EMB110P1 · Flight Compartment LightingSDR AU010224Relief Valve · contaminated(AUS) RT ENGINE OIL PRESSURE RELIEF VALVE CONTAMINATED BY A PIECE OF O-RING SEAL.Feb 2, 2001 · Emb EMB110P1 · Turbine Engine Oil SystemSDR CA010212007Control Column · cracked(CAN) WHILE CARRYING OUT AIRWORTHINESS DIRECTIVE CF-82-34 WE FOUND A CRACK IN THE LOWER WELD ASSEMBLY OF THE AILERON CONTROL COLUMN LOCATED AT THE CUT HOLE FOR THE AILERON CHAIN. THE CRACK WAS APPROXIMATELY 1/4 INCH LONG.Jan 25, 2001 · Dhav DHC3 · Control Column SectionSDR CA010307006Engine · failed(CAN) WHILE IN LEVEL CRUISE AT 500 AGL THE RT ENGINE FAILED. FIRST OBSERVATION WAS DROPPING OIL PRESSURE, PROPELLER AUTO-FEATHERING AND AIRCRAFT YAWING TO RIGHT. RT ENGINE WAS SECURED AND AIRCRAFT RETURNED TO BASE. UPON EXAMINATION AT BASE, THE POWER TURBINE WJan 24, 2001 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR AU010191Engine · damaged(AUS) ENGINE SKI JUMP SEVERELY CRACKED AND DISTORTED IN AREA AROUND NR 3 BEARING COVER. SOME PIECES OF THE EXHAUST CASING HAVE COMPLETELY BROKEN AWAY CAUSING DAMAGE TO THE POWER TURBINE DISC AND BLADES. POWER TURBINE STATOR CRACKED THROUGH THE INNER BAND.Jan 10, 2001 · Emb EMB110P1 · Turbine SectionSDR CA001214016Bracket · cracked(CAN) THE HORIZONTAL STABILIZER UPPER AND LOWER SKIN AT THE RIGHT HAND ELEVATOR ATTACH BRACKET WERE FOUND DENTED AND CRACKED. THE DAMAGED AREA WAS OUT AWAY AND REPAIRED BY INSTALLING AN INNER SPLICE PLATE AND AN EXTERNAL DOUBLERS PLATE PATCH OF 2024T3 ALUMINUMDec 4, 2000 · Emb EMB110P1 · Horizontal Stabilizer StructureSDR CA001106016Bushing · cracked(CAN) DURING AD CF-82-26R1, FOUND THAT TIE BAR BUSHINGS WERE NOT OF NORMAL TYPE PER PARTS MANUAL. TIE BAR BUSHINGS WERE REMVD&VISUAL&DYE CHECK INSP CARRIED OUT ON END FITTING. DURING NDT INSPE CTION, IND.S WERE THAT CRACK RADIATING FROM BUSHING HOLE ON TOP INOct 31, 2000 · Dhav DHC3 · Fuselage, Wing Attach FittingsSDR CA001005008Pin · broken(CAN) BROKEN PIN HEAD ON ADJUSTER ASSEMBLY. CAUSED ADJUSTER TO LOOSEN.Sep 1, 2000 · Emb EMB110P1 · BrakeSDR AU000760Wheel · cracked(AUS) LT MAIN WHEEL INNER HALF CRACKED IN THE TIRE BEAD SEAT AREA RESULTING IN A SECTION BREAKING AWAY AND CAUSING THE TIRE TO DEFLATE.Aug 28, 2000 · Emb EMB110P1 · Wheel/Ski/FloatSDR CA000928028Connector · loose(CAN) AIRCRAFT WAS UNABLE TO TRANSMIT ON ANY OF THE 3 COMMS. MAINTENANCE DISCOVERED THE CONNECTOR TO BACK OF THE RADIO RACK LOOSE. THE CONNECTOR WAS CONNECTED, COMMS TESTED, AND THE AIRCRAFT RETURNED TO SERVICE. AVIONICS HAS ADVISED THAT THESE CONNECTORS CAN BAug 26, 2000 · Beech A100 · VHF Communications System
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