U/A Canada PT6A-21

Service difficulty reports · 310

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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 = 'PT6A21'
  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 CA060317009Bearing · failedVISUAL INSPECTION CARRIED OUT IAW OPERATION FOUR. NOTICED METAL DUST ON BACK OF THE ACCESSORY GEARBOX AND FOUND IT TO BE MAGNETIC. REMOVED STARTER GENERATOR AND FOUND THE QUILL SHAFT BEARING HAD FAILED. UNIT WAS REMOVED FROM SERVICE.Mar 17, 2006 · Beech C90A · Starter-GeneratorSDR CA060403014Seal · leakingDURING FLIGHT, AN ENGINE OIL LEAK WAS OBSERVED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A LEAKING PROPELLER SHAFT SEAL AND A LOOSE BETA VALVE RETAINING NUT.Mar 16, 2006 · Beech C90A · Propeller AssemblySDR CA060320001Seal · damagedIN CRUISE 16,000 FT, NOTICED OIL LEAK ON TOP RT FWD ENG COWL. LEAK PROGRESSIVELY GOT WORSE, PILOTS ELECTED TO RETURN TO BASE. EVEN THOUGH ENG OIL TEMP AND PRESS NORM, PILOTS SHUTDOWN RT ENG. CREW DECLARED EMERG. BECAUSE QTY OF OIL LOST, PROP SHAFT SEAL SHOULMar 16, 2006 · Beech C90A · Propeller AssemblySDR CA060317008Pump · leakingVISUAL INSPECTION CARRIED OUT IAW SERVICEABILITY CHECK. PRE-DISPATCH CHECK NOTICED FUEL UNDER THE RT ENGINE. INSPECT FUEL FILTER AND DRAINS WITH THE BOOST PUMP ON AND NO LEAKAGE WAS FOUND. REMOVED FUEL PUMP DRAIN HOSE AND A LARGE AMOUNT OF FUEL WAS EXPELLED Mar 15, 2006 · Beech C90A · Engine Fuel PumpSDR CA060130002Windscreen · failedWHILE IN CRUISE FLIGHT AT FL230, THE LT WINDSHIELD INNER PANE SHATTERED. THE WINDSHIELD ANTI-ICE HAD BEEN SELECTED AT NORMAL SINCE DEPARTURE AND THE OAT WAS –38°C. THE CREW CONTACTED ATC TO DECLARE AN EMERGENCY AND REQUESTED RETURN TO AIRPORT. THE CREW THENJan 25, 2006 · Beech C90A · Flight Compartment WindowsSDR CA060125006Shaft Seal · leaking(CAN) WHILE DOING A GROUND RUN TO VERIFY THE COMPASS SYSTEM, TECH NOTICED UNCOMMANDED ACCELERATION AND DECELERATION OF THE RT ENGINE. VISUAL INSPECTION IDENTIFIED BLUE DYE WASHOUT FROM THE FUEL PUMP TO FUEL CONTROL UNIT SEAL AREA AND CONFIRMED A FAULT. THE FUJan 13, 2006 · Beech C90A · Fuel Control/Reciprocating EnginesSDR CA060110001Resistor · overheatedDURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED. INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED. THE SYSTEM WAS DEACTIVATED AND DEFERRED.Jan 6, 2006 · Beech C90A · Flight Compartment LightingSDR CA060110003Resistor · overheatedDURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED. INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED. THE SYSTEM WAS DEACTIVATED AND DEFERRED.Jan 6, 2006 · Beech C90A · Flight Compartment LightingSDR CA051222009Resistor · overheatedVISUAL INSPECTION CARRIED OUT AS PER CAMPAIGN NOTICE 681-33-21-018. RESISTOR VISUAL INSPECTED OKAY. SCORCHING FOUND ON INSULATION BLANKET. SYSTEM CB PULLED AND PLACARDED.Dec 22, 2005 · Beech C90A · Passenger Compartment LightingSDR CA051222006Resistor · overheatedWHILE CARRYING OUT COMPANY CAMPAIGN 681-33-21-018, RESISTOR R145 FOR FLUORESCENT LIGHT CIRCUIT FOUND SHOWING SIGNS OF OVERHEATING. SYSTEM DISABLED AND DEFERRED.Dec 20, 2005 · Beech C90A · Light System WiringSDR CA051222007Resistor · overheatedRESISTOR R145 FOR FLUORESCENT LIGHT CIRCUIT FOUND SHOWING SIGNS OF OVERHEATING WHILE CARRYING OUT COMPANY CAMPAIGN 681-33-21-018. SYSTEM DISABLED AND DEFFERED.Dec 20, 2005 · Beech C90A · Passenger Compartment LightingSDR CA060106002Engine · failedWHILE IN FINAL DESCENT, THE FLIGHT CREW DISCOVERED THAT THEY DID NOT HAVE FULL AUTHORITY OVER THE LEFT ENGINE. THE LEFT ENGINE COULD NOT BE REDUCED BELOW 800 LBS TORQUE. ENGINE CONTROL WAS STILL AVAILABLE IN A RANGE FROM 800 LBS TO MAX TORQUE. FLIGHT CREW OPTDec 20, 2005 · Beech C90A · Engine (Turbine/Turboprop)SDR CA051216003Resistor · overheatedDURING ROUTINE INSPECTION, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED. INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED.Dec 15, 2005 · Beech C90A · Passenger Compartment LightingSDR 2005FA0001575Sense Line · wornP3 AIR LINE CONNECTS COMP TO P3 AIR FLTR. LINE ATTACHES TO GAS OPER CASE AT 5:00 POS LOOKING FWD, CONNECTS TO IS FITTING AT REAR FIREWALL. ENG INSTALLED, LINE RESTS FIRMLY ON ENG TRUSS. SUB ENG HAVE BEEN INSTALLED ON THIS AC FOR 300 HRS. P3 LINE IS ALREADYDec 7, 2005 · N1114Z · Beech C90A · Fuel Controlling SystemSDR 2005FA0001315Downlock Switch · out of adjustON APPROACH THERE WAS NO RT MAIN GEAR INDICATION. CHECKED GEAR RIGGING AND ADJUSTED RT DOWNLOCK SWITCH IAW M/M.Sep 23, 2005 · N502SE · Beech C90 · Landing Gear Position and WarningSDR CA050915004Bolt · broken(CAN) CREW ENTERED DEFECT IN JOURNEY LOGBOOK, (RT ANTI-ICE LIGHT ON. VISUAL INSPECTION INDICATES BY-PASS DOOR FULLY DOWN, DEFLECTOR DOOR HALF WAY DOWN). MAINTENANCE CREW FOUND A BOKEN BOLT IN LINKAGE P/N AN3H-32A. (REFER TO IPC 30-20-02 PAGE 0 ITEM 35) RT ENSep 15, 2005 · Beech C90A · Air Intake Anti/De-Ice SystemSDR CA051005011Engine · failed(CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED INCREASE IN TORQUE AND TEMPERATURE AND WAS SHUTDOWN IN FLIGHT. A SUBSEQUENT RESTART ATTEMPT WAS UNSUCCESSFUL AND A SINGLE ENGINE LANDING WAS ACCOMPLISHED AT POINT OF DESTINATION. WILL MONITOR INVESTIGAug 29, 2005 · Beech C90 · Engine (Turbine/Turboprop)SDR CA050621011Hydromech Unit · damaged(CAN) DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER CHANGE WITH NO SUBSEQUENT RESPONSE TO THROTTLE LEVEL INPUT. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT-OF-DEPATURE. SUBSEQUENT INSPECTION REVEALED A DAMAGED HYDROMECJun 12, 2005 · Beech C90A · Fuel Control/Reciprocating EnginesSDR CA050520001Bushing · migrated(CAN) ON A ROUTINE FLT THE PILOTS COULD HEAR A NOISE IN THE CONTROL COLUMN WHEN MOVING IT BACKWARDS AND FORWARDS. WHEN THE AIRCRAFT RETURNED MAINTENANCE FOUND THE LEFT ELEVATOR TAB BINDING AT THE CONTROL ROD TO TAB HORN ATTACHMENT. THE BUSHING HAD MIGRATED SMay 19, 2005 · Beech C90A · Elevator Tab Control SystemSDR CA050519005Clevis · out of rig(CAN) ON INITIAL GEAR EXTENSION DURING APPROACH RT MLG DOWNLOCK LIGHT DID NOT ILLUMINATE. THE PILOTS OPERATED THE EMERGENCY GEAR EXTENSION SYSTEM HOWEVER LIGHT STILL NOT ILLUMINATE. ONLY ONCE AIR SPEED WAS REDUCED JUST PRIOR TO TOUCHDOWN DID LIGHT ILLUMINATE IMay 13, 2005 · Beech C90A · Landing Gear Retraction/Extension SystemSDR CA050506001Windshield · broken(CAN) COPILOT INNER WINDOW PANE SHATTERED (LOUD BANG) DURING CRUISE AT 24,000 FT. IAS WAS 175 KNOTS , O.A.T. -32C. WINDSHIELD ANTI-ICE SELECTED OFF. NO LOSS OF PRESSURIZATION, CREW FOLLOWED CHECKLIST PROCEDURES FOR UNEVENTFUL LANDING. WINDOW HAD DELAMINATIONMay 3, 2005 · Beech C90A · Flight Compartment WindowsSDR CA050527006Coupling · fracturedDURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED TORQUE AND TEMPERATURE INCREASE. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL PUMP COUPLING SHAFT.Apr 21, 2005 · Beech C90A · Engine Fuel PumpSDR CA050408009Case · damaged(CAN) DURING AVIONICS UPGRADE PROCEDURES IT WAS FOUND THAT THE PILOTS RADAR ALTITUDE INDICATOR P/N 622-4160-018 WOULD CHAFE ON THE WINDSHIELD CENTER POST STRUCTURAL DOUBLER P/N 50-420066-281. THE CHAFFING WAS SERIOUS ENOUGH TO DAMAGE THE DOUBLER BEYOND ACCEPTApr 8, 2005 · Beech C90A · Ground Proximity SystemSDR CA050401007Tee Fitting · loose(CAN) TEE FITTING SUPPLYING TORQUE PRESSURE READING TO AIRCRAFT INSTRUMENTS WAS LOOSE, CAUSING AN OIL LEAK. THE TEE FITTING WAS WITNESSED (WIRED) AND APPROX HALF TURN WAS NEEDED TO TIGHTEN. AIRCRAFT ENGINE WAS SHUTDOWN IN FLIGHT AND AIRCRAFT LANDED SAFELY. Mar 24, 2005 · Beech C90A · Fuselage Miscellaneous StructureSDR CA050317001Diaphragm · ruptured(CAN) ENGINE UNABLE TO ACHIEVE TAKEOFF POWER/TORQUE DUE TO BLEED VALVE NOT CLOSING FULLY. COMPRESSOR BLEED VALVE DIAPHRAM FOUND RUPTURED.Mar 14, 2005 · Beech C90 · Compressor Bleed ValveSDR CA050311003Spline · lack of lube(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN AND THE NOSE GEAR DID NOT FULLY EXTEND. AN EMERGENCY EXTENSION PROCEDURE WAS CARRIED OUT AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THAT THE SPLINE COUPLING CONNECTING THE HYDRAULICMar 9, 2005 · Beech C90A · Landing Gear Retraction/Extension SystemSDR CA050307002Fcu · malfunctioned(CAN) DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED INCREASE IN TORQUE AND FAILED TO RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED A FRACTURED FUEL CONTROL COUPLING SHAFT.Feb 3, 2005 · Beech C90A · Fuel Control/Turbine EnginesSDR CA050207005Windscreen · cracked(CAN) PILOTS HEARD A LOUD BANG AND THE CO-PILOTS WINDSCREEN CRACKED. THEY DESCENDED AND BROUGHT CABIN PRESSURE DOWN TO 2 PSI. THEY THEN LANDED AT NEAREST MAINTENANCE BASE.Jan 30, 2005 · Beech C90 · Flight Compartment WindowsSDR CA050120007Windshield · broken(CAN) ENROUTE IN CRUISE FLIGHT AT 16000 MSL, OAT -38C THE LT WINDSHEILD SHATTERED. THE WINDSHIELD HEAT WAS OFF AND HAD NOT BEEN USED DURING THE FLIGHT. THE DEFOG AIR WAS ALSO OFF. THE CREW DECLARED AN EMERGENCY AND REQUESTED CLEARENCE AND IMMEDIATE DECENT TOJan 17, 2005 · Beech C90A · Flight Compartment WindowsSDR CA050308007Bushing · failed(CAN) BOLT, P/N 130909B172, ATTACHING RUDDER PEDAL TO RUDDER PEDAL ARM WILL NOT FIT PROPERLY THROUGH BUSHING. THE RUDDER PEDAL MUST THEN TURN ON THE BOLT AND THE BUSHING MUST TURN WITHIN THE RUDDER PEDAL ARM CAUSING PREMATURE WEAR AND/OR POSSIBLE FAILURE.Jan 13, 2005 · Beech C90A · Rudder Control SystemSDR CA041123001Pin · missing(CAN) THE PRIMARY CABLE FOR THE ELEVATOR CONTROL HAD JUMPED OUT OF THE PULLEY. THE (SPRING PIN) THAT PREVENTS THIS FROM HAPPENING WAS OUT OF POSITION (UNABLE TO STOP THE CABLE FROM LEAVING THE PULLEY). ABRASION OF THE ELEVATOR CABLE AT THE PULLEY AND ON SUPPORNov 19, 2004 · Beech C90A · Elevator Control SystemSDR CA041015004Torque Knee · cracked(CAN) DURING A 8000 CYCLE TORQUE KNEE NDT INSPECTION IT WAS DETECTED THAT THE RT LOWER TORQUE KNEE ATTACH PIN, PN 50-810035-2 WAS CRACKED IN NUMBER OF PLACES. THE TORQUE KNEE IS POST S/B 32-3116 - IMPROVED STEEL. PRESENTLY THE PIN IS PLACED IN QUARANTINE. THEROct 15, 2004 · Beech C90A · Landing Gear Retraction/Extension SystemSDR CA040910001Fixture · meltedPLASTIC HOUSING OF THE LIGHT SHIELD P/N 101-530764-1 HAS MELTED DUE TO THE HEAT PRODUCED BY THE HIGH WATTAGE RESISTOR MOUNTED ON THE LIGHT ASSY PRINTED CIRCUIT BOARD P/N PW2014. IT HAD MELTED ENOUGH TO DISFIGURE THE SHIELD AND PRODUCE AN ELONGATED HOLE THE LENSep 9, 2004 · Beech C90A · Passenger Compartment LightingSDR CA040917004Switch · failed(CAN) LANDING GEAR FAILED TO EXTEND WHEN SELECTED DUE TO FAILURE OF SWITCH IN LANDING GEAR CONTROL HANDLE.Aug 30, 2004 · Beech C90A · Landing Gear SelectorSDR CA040917003Cell · reversed(CAN) AIRCREW REPORTED LOAD METERS NOT INDICATING BATTERY CHARGE FOR NORMAL PERIOD OF TIME OR NORMAL LEVEL OF CHARGE. UPON INSPECTION NR 9 CELL FOUND INSTALLED IN REVERSE POLARITY ORIENTATION.Aug 30, 2004 · Beech C90A · Battery/Charger SystemSDR CA040713001Shutoff Valve · failed(CAN) FAILED FUNTIONAL TEST IAW PILOTS CHECK LIST. REPLACEDJul 12, 2004 · Beech C90A · Fuel Selector/Shut-Off ValveSDR CA040705006Shutoff Valve · failed(CAN) DURING PILOTS START CHECKS RT HAND FUEL SHUT-OFF VALVE FAILED IN OPEN POSITION. UNABLE TO TURN LOW PRESSURE LIGHT ON. REPLACED VALVE. AIRCRAFT RETURNED TO SERVICE.Jun 30, 2004 · Beech C90A · Fuel Selector/Shut-Off ValveSDR CTU2004F00000Windscreen · crackedLT WINDSCREEN CRACKED DURING CRUISE, AT AN ALTITUDE OF BETWEEN 12,000 AND 16,000 FEET. FLIGHT WAS CONDUCTED AT NIGHT TIME WHILE ON AN IFR FLIGHT PLAN. AIRCRAFT WAS BEING OPERATED AS A LIFE FLIGHT. FLIGHT WAS CONDUCTED NORMALLY TO THE DESTINATION AIRPORT, NOJun 29, 2004 · N502SE · Beech C90 · Flight Compartment WindowsSDR CA040503001Shutoff Valve · failed(CAN) DURING PILOTS PREFLIGHT CHECK THE RT FUEL SHUTOFF VALVE FAILED. THE VALVE WAS REPLACED. TSO 75.4 HOURSApr 29, 2004 · Beech C90A · Fuel Selector/Shut-Off ValveSDR CA040405006Hose · cracked(CAN) DURING PHASE 3 INSPECTION THE RT ENGINE IB INLET ANTI-ICE TUBE WAS FOUND CRACKED. UNIT REPLACED WITH NEW.Mar 30, 2004 · Beech C90A · Engine Anti-Icing SystemSDR CA040405007Cowling · cracked(CAN) DURING PHASE 3 INSPECTION THE LT ENGINE LOWER AFT COWL WAS FOUND CRACKED A LONG A SEAM WELD. UNIT WAS REPAIRED IAW COMPANY PROCEDURE ASSY 681-71-10-0093.Mar 30, 2004 · Beech C90A · Engine Cowling SystemSDR CA040319002Anti-Ice System · cracked(CAN) AIR INTAKE ANTI-ICE LIP WAS FOUND CRACKED AT THE WELDED ATTACH JOINTS AT BASE OF EXHAUST INLET/OUTLET TUBES.Mar 9, 2004 · Beech C90A · Air Intake Anti/De-Ice SystemSDR CA040315008Shutoff Valve · failed(CAN) DURING PRESTART CHECKS FLIGHT CREW COULD NOT EXTINGUISH (LOW FUEL PRESSURE) WARNING LIGHT. FLIGHT CANCELLED. INSPECTION FOUND RT FUEL SHUT OFF VALVE HAD FAILED IN THE CLOSED POSITION. VALVE HAD BEEN RECENTLY OVERHAULED.Mar 2, 2004 · Beech C90A · Fuel Selector/Shut-Off ValveSDR CA040220008Hose · cracked(CAN) LT COWL ANTI ICE FLEX HOSE FOUND CRACKED DURING OPS 1 INSPECTION.Feb 18, 2004 · Beech C90A · Engine Anti-Icing SystemSDR CA040220009Duct · cracked(CAN) LOWER FORWARD COWL AIR INLET DUCT CRACKED. REPAIR TO BE ACCOMPLISHED IAW MFG FIELD REPAIR PROCEDURE.Feb 2, 2004 · Beech C90A · Turbine Engine Air Inlet SectionSDR CA040220010Windscreen · damaged(CAN) AIR CREW REPORTED THAT THE PILOTS WINDSCREEN WAS DISCOLOURED AT THE OB EDGES AND HAD A MILKY APPEARANCE. THE WINDSCREEN HAD PREVIOUSLY BEEN REPAIRED BY THE MFG. THE WINDSCREEN WAS REPLACED WITH A NEW UNIT AND THE DAMAGED UNIT WAS RETURNED TO THE MFG FOR Feb 2, 2004 · Beech C90A · Flight Compartment WindowsSDR CA040211005Windshield · failed(CAN) DEFECT REPORTED AS, RT OUTER WINDSHIELD SHATTERED IN FLIGHT. AIRCRAFT WAS ENROUTE AT FL250 WHEN THE WINDSHIELD SHATTERED WITH NO PRIOR INDICATIONS AND NO WINDSHIELD HEAT SELECTED, OAT WAS 41C. THE AIRCRAFT DIVERTED TO HOME BASE. UPON INSPECTION IT WJan 23, 2004 · Beech C90A · Flight Compartment WindowsSDR CA040211007Windshield · cracked(CAN) RT WINDSHIELD INNER LAYER CRACKED IN FLIGHT AT FLIGHT LEVEL 240. REPORTED OAT -45C.Jan 22, 2004 · Beech C90A · Flight Compartment WindowsSDR CA040211008Windshield · cracked(CAN) DURING SERVICING THE LT WINDSHIELD WAS FOUND CRACKED IN THE OUTER PLY. REPORTED OAT FOR THE PREVIOUS FLIGHT WAS -45C.Jan 22, 2004 · Beech C90A · Flight Compartment WindowsSDR AKG2004F00000Fuel Control · malfunctionedAFTER TAKEOFF AND SHORTLY INTO FLIGHT THE LT ENGINE ROLLED BACK TO IDLE WITH THE POWER LEVER NOT BEING MOVED. MAKING A GROUND RUNUP, FOUND THAT THE FCU WAS VERY UNSTABLE AND NOT RESPONSIVE TO POWER LEVER CONTROL INPUTS.Jan 16, 2004 · N475JA · Beech C90A · Fuel Control/Turbine Engines
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