U/A Canada PT6A-41

Service difficulty reports · 717

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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 = 'PT6A41'
  ORDER BY difficulty_date DESC"

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SDR CA030311017Windshield · cracked(CAN) IN CRUISE THE PILOTS NOTICED A CRACK APPEARED ON THE RIGHT SIDE OF THE PILOTS FRONT WINDOW. MORE CRACKS APPEARED ON DESCENT INTO AIRPORT. ON INSPECTION THE CRACKS WERE FOUND TO BE IN THE OUTSIDE NON-STRUCTURAL GLASS. THE WINDOW WAS REPLACED.Mar 7, 2003 · Beech 200BEECH · Flight Compartment WindowsSDR CA030311008Bungee Cylinder · failed(CAN) NOSE GEAR STEERING FAILED DURING TAXI . THE CREW EXPERIENCED A (THUMP) IN THE RUDDER / STEERING SYSTEM. AFTER THE (THUMP) THE CREW WAS UNABLE TO TAXI THE AIRCRAFT IN A STRAIGHT LINE. INSPECTION REVEALED THAT THE NOSE GEAR STEERING SPRING BUNGEE ASSEMBLY Mar 5, 2003 · Beech 200BEECH · Landing Gear Steering SystemSDR CA040423002Bulkhead · corrodedDURING A SCHEDULED INSPECTION OF THE REAR PRESSURE BULKHEAD A LOCALIZED AREA OF PITTING CORROSION WAS DISCOVERED AROUND THE BULKHEAD FITTING FOR THE RELIEF TUBE CONNECTION. THE AREA WAS CLEANED AND INSPECTED AND AN APPROVED DOUBLER REPAIR CARRIED OUT. THE BUMar 5, 2003 · Beech 200BEECH · Fuselage Main, BulkheadSDR CA030218013Windshield · cracked(CAN) PILOTS WINDOW CRACKED IN FLIGHTFeb 14, 2003 · Beech 200BEECH · Flight Compartment WindowsSDR CA030218011Gearbox · failed(CAN) ENGINE SUFFERED AN IFSD AND WAS REMOVED AND RETURNED FOR INVESTIGATION. CUSTOMER SUSPECTED AN AGB BALL LOCK FAILURE. ENGINE WAS FOUND TO HAVE SIGNIFICANT DAMAGE INSIDE THE AGB WITH MANY GEARSHAFTS & MUTILATED TEETH & INPUT DRIVE FLANGED BEARING COMPLEFeb 11, 2003 · Accessory GearboxesSDR CA030220004Control Cable · sheared(CAN) ON APPROACH AIRCRAFT FLAP ASYMMETRY TRIPPED. ON INSPECTION OF FLAP SYSTEM THE L/H OUTBOARD FLAP CABLE DRIVE AT MOTOR FOUND SHEARED. NEW OUTBOARD L/H FLAP CABLE INSTALLED (P/N 101-380000-5). FLAP SYSTEM FUNCTION TEST CARRIED OUT. TESTED OK.Jan 28, 2003 · Beech 200BEECH · Leading Edge Slat Control SystemSDR CA030124001Tube · broken(CAN) BOTH ENGINES RUNNING WHILE ON THE RAMP. WHEN POWER WAS APPLIED TO THE PORT ENGINE TO TURN THE A/C THE ENGINE RETURNED TO MIN. FLOW OF 38 PERCENT UNCOMMNANDED. THERE WAS NO RESPONSE ON THE POWER LEVER. A/C HANGARED AND PORT ENGINE INSPECTED. THE PY GOVERNJan 24, 2003 · Beech 200BEECH · Engine Fuel DistributionSDR DBCA122D1Uplock Switch · out of rigAFTER DEPARTING MDW PILOT SELECTED LANDING GEAR UP. LANDING GEAR RETRACTED AND LOCKED BUT (IN TRANSIT) LIGHT IN GEAR HANDLE REMAINED ILLUMINATED. CREW DIVERTED TO MKE. AIRCRAFT WAS PLACED ON JACKS AND LANDING GEAR RETRACTION TEST WAS ACCOMPLISHED. FOUND LEJan 24, 2003 · N884PG · Beech 200BEECH · Landing Gear Position and WarningSDR CA030123007Hinge · cracked(CAN) WHEN CONDUCTING GEAR RETRACTION AS PART OF PHASE INSPECTION FORWARD PORTION OF RT NOSE GEAR DOOR DID NOT FAIR IN WITH THE FUSELAGE. A MORE DETAILED INSPECTION WAS CARRIED OUT, REVEALING THE FORWARD HINGE CRACKED AT THE FIRST RIVET AS THE FITTING ENTERS Jan 23, 2003 · Beech 200BEECH · Landing Gear DoorsSDR CA030123009Windshield · cracked(CAN) AFTER DEPARTURE THE WINSHIELD HEAT WAS SELECTED ON AT 1500 FEET. AFTER LEVELING AT CRUISE ALTITUDE OF 16,000 FT THE CREW HEARD A POPPING NOISE AND NOTED THAT THE RIGHT WINDSHIELD HAD CRACKED IN THE OUTER PANE. THE CRACK WENT FROM TOP TO BOTTOM AND WAS APJan 20, 2003 · Beech 200BEECH · Flight Compartment WindowsSDR CA030220003Bulkhead · cracked(CAN) CREW REPORTED ON LAST LEG TO AIRPORT, LOW PRESSURIZATION OF 3.2 PSI. DURING TROUBLESHOOTING FOUND A CRACK FOUR INCHES LONG ON BULKHEAD. LOCATION - CENTER OF FUSELAGE AT STATION 227.125.Jan 20, 2003 · Beech 200BEECH · Fuselage Main, BulkheadSDR ZSE2003F00000Engine · failedDESCENDING FOR LANDING, TORQUE DROPPED ON RT ENGINE WITH TEMPERATURE INCREASING. ENGINE SHUT DOWN AND LANDED WITHOUT INCIDENT.Jan 14, 2003 · N498AC · Beech 200BEECH · Engine (Turbine/Turboprop)SDR CA030221004Governor · inoperative(CAN) ON RETURN FLIGHT PILOTS REPORT THAT RT PROPLLER RPM STAYED AT 2100. THEY WERE NOT ABLE TO GOVERN PROPELLER SPEED. AFTER LANDING MAINTENACE CHECKED THE SYSTEM AND DETERMINED THAT REPLACEMENT OF PROP. GOVERNOR WAS REQUIRED. AFTER REPLACEMENT WITH A SERVICAJan 13, 2003 · Beech 200BEECH · Propeller GovernorSDR CA030123006Link · failed(CAN) PILOT PROCEEDED TO TAXI AIRCRAFT, THE NOSE STEERING SYSTEM LOCKED INTO A HARD RT CONDITION. THIS ALSO AFFECTED THE RUDDER SYSTEM, POSITIONING THE RUDDER SYSTEM INTO A RT TURN CONDITION. A TOW BAR WAS ATTACHED AND THE NOSE STEERING SYSTEM EXERCISED, THIS Dec 31, 2002 · Beech 200BEECH · Landing Gear Steering SystemSDR CA021231001Fuel Cap · departed(CAN) AFTER TAKE-OFF FROM YYR THE FLIGHT CREW NOTED THAT THE LEFT MAIN FUEL CAP CAME OFF AND EXITED THE AIRCRAFT. THE AIRCRAFT RETURNED TO BASE. MAINTENANCE INSPECTED THE FUEL FILLER OPENING AND WING CAP FITTING. NO DEFECTS WERE NOTED. THE MISSING FUEL CAP WASDec 17, 2002 · Beech 200BEECH · Fuel StorageSDR GSB2006DEC02Fuel Control · malfunctionedDURING CRUISE FLIGHT RIGHT ENGINE WOULD NOT DEVELOPE POWER, THE ENGINE WAS SHUTDOWN, THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. THE CAUSE OF THE ENGINE POWER LOSS WAS DETERMINED TO BE POSSIBLE (FUEL CONTROL UNIT) INTERNAL MALFUNCTION. THE FCU WAS REPLACEDDec 16, 2002 · N90PB · Beech 200BEECH · Fuel Control/Turbine EnginesSDR CA030306001Windshield · failed(CAN) IN FLIGHT THE WINDOW SUDDENLY SHATTERED WITH A LOUD BANG.Dec 15, 2002 · Beech 200BEECH · Flight Compartment WindowsSDR CA030103005Rivet · failed(CAN) LT AND RT SIDE FRAME PN 10143002611 TO LONGERON ATTACH CLIP RIVETS (3 EACH SIDE) FAILED. SOME RIVETS COMPLETELY GONE, SOME HEADS POPPED OFF. RAYTHEON FIELD REPAIR FR-KA-00814 CARRIED OUT. FAILED RIVETS REPLACED.Dec 12, 2002 · Beech 200BEECH · FastenersSDR CA030103006Rivet · failed(CAN) WHILE CONDUCTING A STRUCTURAL INSPECTION A RIVET HEAD WAS FOUND MISSING AT STN 187.3 RT ATTACH CHANNEL TO SPAR CAP ATTACHMENT CLIP. RIVET REPLACED IN ACCORDANCE WITH RAYTHEON FIELD REPAIR FR-KA-00807.Dec 12, 2002 · Beech 200BEECH · FastenersSDR CA030103007Bulkhead · cracked(CAN) WHILE CONDUCTING A STRUCTURAL INSPECTION, BULKHEAD AT STATION 236.5 WAS FOUND CRACKED WHERE IT JOINS WITH RT SIDE FRAME BETWEEN RT STRINGER NR 12 AND 13. FRAME/BULKHEAD REPAIR CARRIED OUT IN ACCORDANCE WITH RAYTHEON FIELD REPAIR FR-KA-00814.Dec 12, 2002 · Beech 200BEECH · Fuselage Main, BulkheadSDR 2004F00258Fuel Control · malfunctionedDURING CRUISE FLIGHT, WOULD NOT DEVELOP POWER, THE ENGINE WAS SHUTDOWN AND SECURED PER PUBLISHED EMERGENCY PROCEDURE. THE AIRCRAFT LANDED AT ANCHORAGE INTERNATIONAL AIRPORT WITHOUT FURTHER INCIDENT. THE CAUSE OF THE POWER LOSS WAS DETERMINED TO BE POSSIBLE FDec 6, 2002 · N90PB · Beech 200BEECH · Fuel Controlling SystemSDR CA021204011Engine · failed(CAN) ENGINE RECENTLY OVERHAULED AND WAS BEING USED AS A RENTAL WHEN REPORTED ENGINE MAKING NOISE AND HIGH VIBRATION AFTER LAST LANDING. ENGINE HAS BEEN REMOVED AND SENT IN FOR INVESTIGATION AND REPAIR. COMPRESSOR ASSY WAS OUT OF BALANCE & COMPRESSOR BOLT STRENov 28, 2002 · Turbine Engine Compressor SectionSDR CA021230006Blade · fractured(CAN) AS POWER WAS APPLIED TO THE ENGINE DURING TAXI TO TAKE-OFF POSITION, A LOUD NOISE WAS HEARD AND THE ENGINE PARAMETERS BEGAN TO SPOOL DOWN. ENGINE WAS IMMEDIATELY SHUTDOWN. NO FURTHER INCIDENT OCCURRED AND THE CREW DEPLANED. A VISUAL INSPECTION OF THE ENGNov 25, 2002 · Beech 200BEECH · Turbine Engine Compressor SectionSDR CA030102007Control Cable · twisted(CAN) LT INBOARD FLAP CABLE FOUND DRIVE END AT ACTUATOR TWISTED, FLAP SAFETY FUSE PULLED OUT ON LT FLAPS. NEW INBOARD LT FLAP CABLE INSTALLED. FLAP SAFETY FUSE RESET AND FUSE PULL WIRE ADJUSTED. FUNCTION TEST OF FLAP SYSTEM CARRIED OUT SERVICEABLE.Nov 13, 2002 · Beech 200BEECH · Leading Edge Slat Control SystemSDR CA030106007Stator · failed(CAN) AT TAKEOFF POWER, SMOKE WAS NOTED IN THE COCKPIT & TAKEOFF WAS ABORTED, ENGINE SHUTDOWN AND TOWED BACK TO MAINTENANCE FACILITY. OIL WAS EVIDENT ON THE COWLINGS, AFTER EXTENSIVE TROUBLESHOOTING, THE ENGINE WAS REMOVED AND SENT TO AN OVERHAUL FACILITY. THENov 12, 2002 · Beech 200BEECH · Turbine Engine Compressor SectionSDR AUS20021272Bolt · separated(AUS) LT MAIN LANDING GEAR OLEO STRUT PISTON SEPARATING FROM AXLE. SHEAR BOLT HAD SHEARED AND THE PISTON HAD MIGRATED OUT BY APPROXIMATELY 25MM (0.98IN).Oct 30, 2002 · Beech B200C · Main Landing Gear Strut/Axle/TruckSDR CA021029009Bearing · failed(CAN) DURING ROUTINE MAINTENANCE, VISUAL INSPECTION OF THE NR 1 ENGINE REDUCTION GEARBOX CHIP DETECTOR PLUG AND STRAINER WAS CARRIED OUT. FOUND NUMEROUS BALL BEARINGS APPROX.0.039 INCHES IN SIZE AND SOME PLASTIC & RUBBER DEBRIS CAUGHT IN THE STRAINER. ENGINE MOct 26, 2002 · Beech 200BEECH · Turbine Engine Reduction GearSDR JEM2002F00008Thru Bolt · loosePILOT REPORTED UNUSUAL NOISE COMING FROM LT ENGINE. TECH INVESTIGATED AND COULD NOT DETERMINE SOURCE OF NOISE. DECISION WAS MADE TO REMOVE ENGINE AND SEND TO ENGINE SHOP FOR FURTHER TEAR DOWN AND EVALUATION. ENGINE SHOP FOUND ENGINE THRU BOLT LOOSE.Oct 25, 2002 · N366EA · Beech 200BEECH · Engine (Turbine/Turboprop)SDR FTU2002F00000Bracket · mismanufacturedRECEIVED TWO NEW MAIN LANDING GEAR DOWN LOCK PIVOT BRACKETS, FOUND THE SLOT SUED TO CREATE THE PIVOT CAPABILITY WAS IMPROPERLY MACHINED. WHEN INSTALLED ON THE AIRCRAFT, THE PART WOULD NOT PIVOT DUE TO CLEARANCE PROBLEM REPLACEMENT ITEM ON THIS AIRCRAFT, ALONGOct 22, 2002 · N444SC · Piper PA42 · Main Landing Gear Attach SectionSDR 2002FA0001269Screen · crackedDURING A SCHEDULED EVENT INSPECTION, BOTH ENGINE AIR INLET SCOOP SCREENS WERE FOUND CRACKED IN BOTH FORWARD CORNERS FOR EACH ENGINE. REPAIR WAS NOT FEASABLE DUE TO THE LOCATION DAMAGE. BOTH INLET SCREEN HAD TO BE REPLACED WITH NEW PARTS.Oct 21, 2002 · N444SC · Piper PA42 · Engine Air Intake SystemSDR 2002FA0001275Windshield · crackedWINDSHIELD SHATTERED IN FLIGHT, FROM UNKNOWN CAUSES.Oct 18, 2002 · N366EA · Beech 200BEECH · Flight Compartment WindowsSDR JEM2002F00009Windshield · crackedFLIGHT ELEVATION OF 28,000 FT. AIRCRAFT HAD DEPARTED, PILOTS REPORTED THAT THE WINDSHIELD HEAT WAS ON, WHEN THE RT WINDSHIELD SUDDENLY CRACKED. AIRCRAFT PRESSURE WAS NOT AFFECTED. FLIGHT CREW DECIDED TO RETURN AND AN UNEVENTFUL LANDING WAS MADE.Oct 16, 2002 · N366EA · Beech 200BEECH · Flight Compartment WindowsSDR AUS20021192Bulkhead · cracked(AUS) LH ENGINE NACELLE BULKHEAD CRACKED.Oct 5, 2002 · Piper PA42 · Nacelle/Pylon, Bulkhead/FirewallSDR AUS20021193Trunnion · cracked(AUS) LANDING GEAR TRUNNION CRACKED THROUGH VERTICAL WEB. CRACK LENGTHAPPROXIMATELY 12.7MM (0.5IN). AIRCRAFT OPERATES FROM ROUGHSTRIPS.Oct 5, 2002 · Piper PA42 · Main Landing Gear Attach SectionSDR AUS20021150Transducer · leaking(AUS) RH ENGINE FUEL FLOW TRANSDUCER OUTLET FITTING LOOSE AND LEAKING FUEL. TRANSDUCER IS MANUFACTURED BY SHADIN.Oct 4, 2002 · Beech 200BEECH · Fuel Flow IndicatingSDR CA021106002Bearing · worn(CAN) DURING CRUISE PILOT NOTICED LT ENGINE NG SLOWLY INCREASING. PILOT INCREASED THROTTLE TO COMPENSATE.STABILIZED AT ONE THROTTLE KNOB FORWARD OF RT THROTTLE. LANDED WITH NO FURTHER INCIDENT. FCU REMOVED FOR REPLACEMENT (NO OTHER DISCREPANCIES FOUND). FOUNDSep 27, 2002 · Beech 200BEECH · Fuel Control/Reciprocating EnginesSDR CA021003005Engine · making metal(CAN) DURING CRUISE FLIGHT, THE PILOT WAS ALERTED BY A RT ENGINE CHIP LIGHT. THE PILOT SHUTDOWN THE ENGINE AND ARETURNED TO THE AIRPORT. UPON INSPECTION OF THE MAGNETIC CHIP DETECTOR, METAL CONTAMINATION WAS FOUND, ENGINE REMOVED FOR REPAIR.Sep 16, 2002 · Beech 200BEECH · Engine (Turbine/Turboprop)SDR CA020905006Engine · failed(CAN) THE ENGINE WAS SENT TO ATI FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED THAT ENGINE WAS SHUT DOWN IN FLIGHT.THE OPERATOR REPORTED THAT DURING THE FLIGHT THE PILOT HEARD A LOUD BANG FOLLOWED BY POWER LOSS AND EXTREME RISE IN ITT. THE PILOT SHUAug 26, 2002 · Engine (Turbine/Turboprop)SDR CA020828011Control Arm · obstructed(CAN) ON APPROACH, PILOT BROUGHT BACK POWER LEVERS, NR 2 ENG REACTED NORMALLY, THE NR 1 ENG INCREASED. THE PILOT MOVED THE NR 1 ENG POWER LEVER FWD AND ENG WENT BACK TO WHAT THEY HAD BEEN BEFORE APPROACH. NR 1 POWER LEVER MOVED SEVERAL TIMES, EACH TIME THEAug 9, 2002 · Beech 200BEECH · Fuel Controlling SystemSDR B3OR20020018Rivet · missingTRIM TAB WAS REPLACED DUE TO CORROSION, WHEN PART WAS INSTALLED IT WAS NOT NOTICED THAT THE RIVETS ALONG THE LEADING EDGE AND AROUND THE PITCH HORN WERE NOT INSTALLED.Aug 7, 2002 · N7074G · Beech A200 · Elevator Tab Control SystemSDR AUS20020746Spacer · damaged(AUS) ENGINE FIRST STAGE COMPRESSOR SPACER DAMAGED DUE TO RUBBING ONTHE FIRST STAGE COMPRESSOR STATORS.Jul 24, 2002 · Beech 200BEECH · Turbine Engine Compressor SectionSDR CA020726005Fire Detector · malfunctioned(CAN) CREW REPORTED A RIGHT ENGINE FIRE LIGHT IN FLIGHT.THE WARNING LIGHT ILLUMINATED, WENT OUT FOR A BRIEF PERIOD AND THEN CAME ON AGAIN. THERE WAS NO PHYSICAL EVIDENCE OF A FIRE AND ALL ENGINE PARAMETERS WERE NORMAL. THE ENGINE WAS SHUT DOWN AND THE FIRE BOTJul 24, 2002 · Beech 200BEECH · Detection SystemSDR CA020722017Detector · malfunctioned(CAN) CREW REPORTED NR 1 ENGINE FIRE WARNING ILLUMINATED IN FLIGHT. AIRCRAFT HEADING CHANGED AND WARNING STILL ILLUMINATED. EMERGENCY CALL MADE AND ENGINE SHUT DOWN IN FLIGHT. NR 1 ENGINE FORWARD UPPER FLAME DETECTOR REPLACED WITH NEW. GROUND FUNCTION CHECKED.Jul 21, 2002 · Beech 200BEECH · Fire DetectionSDR CA020725013Frame · cracked(CAN) TWO CRACKS STARED FROM THE RADIUS OF THE LOWER FLANGE. THE FORWARD CRACKED ENDED AT LIGHTNING HOLE WHILE THE OTHER CRACK ENDED BEHIND THE AFT LIGHTNING HOLE. IPL 53-10-10-37Jul 17, 2002 · Beech 200BEECH · Fuselage Main, FrameSDR CA020722002Bellcrank · bent(CAN) DOOR, FWD UPPER HOOK BELLCRANK FOUND TO HAVE A BENT SHAFT, AND ARMS TO BE APPROX 45 DEGREES ANGLE TO EACH OTHER - DOOR, AFT UPPER HOOK BELLCRANK FOUND TO HAVE A BENT SHAFT WITH NOT SO SEVERE ANGLE OF DIS-AUGMENT WITH ARM ANGLES APPROX 80 DEG. TO EACH OTHJul 4, 2002 · Beech 200BEECH · Entrance StairsSDR AUS20020881Bleed Valve · contaminated(AUS) NO2 ENGINE HP BLEED VALVE PISTON CONTAMINATED WITH GRIME.Jul 2, 2002 · Beech 200BEECH · Compressor Bleed ValveSDR CA020619013Fire Detector · malfunctioned(CAN) AFTER TAKE-OFF, RT ENGINE FIRE ANNUNCIATOR ILLUMINATED, THEN EXTINGUISHED. CREW VIEWED ENGINE FOR ANY SIGNS OF FIRE AND VERIFIED ALL ENGINE PARAMETERS NORMAL. CREW DECIDED TO RETURN TO BASE. MAINTENANCE FOUND RT ENGINE ,FOWARD TOP FIRE DETECTOR FAULTY. RJun 17, 2002 · Beech 200BEECH · Fire DetectionSDR CA020702004Engine · failed(CAN) THE ENGINE WAS SENT TO ATI FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED COMPRESSOR FOD. THE ENGINE WAS DISASSEMBLED & THE COMPRESSOR ROTOR ASSY WAS DETACHED FROM THE GG CASE.AFTER DE-MATING THE ENGINE COMPRESSOR ITWAS APPARENT THA THE ROTOR BJun 14, 2002 · Turbine Engine Compressor SectionSDR T4O2002F00002Actuator · failedFOUND DURING PHASE INSPECTION LANDING GEAR RETRACTION TEST; THE LEFT LANDING GEAR RETRACT ACTUATOR JACKSCREW NUT ASSEMBLY BROKE (THREADED SCREW DISCONNECTED FROM CHROME TUBE), AND THE LEFT LANDING GEAR FELL DOWN, BUT NOT LOCKED. PROBABLE CAUSE: BAD ACTUATORJun 12, 2002 · N266RH · Beech 200BEECH · Landing Gear ActuatorSDR CA020523007Frame · cracked(CAN) FUSELAGE LT FRAME AT STATION 167.625 STRINGER 9 CRACKED. TO BE REPAIRED PRIOR TO FURTHER FLIGHT.May 22, 2002 · Beech 200BEECH · Fuselage Main, Frame
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