U/A Canada PT6A-42
Service difficulty reports · 396
Newest first. General aviation reporting is voluntary.
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 = 'PT6A42' 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.
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 = 'PT6A42' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR CA070103003Engine · malfunctioned(CAN) THE ENGINE WAS REPORTED TO LOSE POWER SHORTLY AFTER TAKEOFF, RESULTING IN A FORCED LANDING AND DAMAGE TO THE AIRCRAFT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103003)SDR 2006FA0001071Web · crackedDURING PHASE 1 THROUGH 4 INSPECTION, AFTER REMOVING MOVING ALL WING INSPECTION PANELS. 4 (EA) CRACKS NOTICED IN WEB FLANGE COMMON TO AND EMITTING FROM RIVETS ON LT IB WING BOX AREA, BL-65.50, (2EA) CRACKS AT WS 65, (1EA) CRACK AT WS 56. (K)SDR 2006F00042Smoke Detector · false indicationLT ENGINE FIRE INDICATION IN DECENT DURING APPROACH PHASE OF FLIGHT. SHUT ENGINE DOWN.INSPECTION OF THE FIRE DETECTION SYSTEM AND DETECTORS PROVED TO HAVE NO ISSUES, COULD NOT DUPLICATE ON GROUND RUN.SDR 2006F00040Engine · fireENGINE SURGE WITH FLAMES OUT OF THE EXHAUST DURING FINAL APPROACH TO LAND.SDR XOR2006F00000Bracket · crackedCRACK AT AIR COMPRESSOR BRACKET DURING ROUTINE POSTFLIGHT INSPECTION. BELT TENSION AND ALIGNMENT WAS INSPECTED AT THE LAST PHASE INSPECTION PERFORMED AT 299.7 HRS. AIRCRAFT TT 3064.5, LANDINGS 3146. UNIT LOCATION IS OB OF RT POWERPLANT NACELLE. SUGGEST ADDSDR XRR2006F00000Windshield · crackedINSIDE LAYER OF PILOTS WINDSHIELD CRACKED WHILE IN CRUISE AT 28,000 FT. AC LANDED AT CDU UNEVENTFULLY. FERRIED AC BACK TO DVN IAW AIRWORTHINESS MANUAL. TALKED TO TECH REP AT MFG TOLD ME THAT PPG HAD PROBLEMS WITH THIS SERIES OF WINDSHIELD MFG AROUND 1999-20SDR CA060227006Fuel Control · malfunctionedTHE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CRUISE AND WOULD NOT RESPOND TO THROTTLE LEVER INPUT. THE PILOT ACTIVATED THE FUEL CONTROL MANUAL OVER-RIDE AND ACCOMPLISHED AN UNSCHEDULED LANDING. GROUND INSPECTION COULD NOT DUPLICATE THE INCIDENT. SDR 2006RC02001Bulkhead · cracked(CAN) PRESSURIZATION ERRATIC IN THE AIR. THE AIRCRAFT WAS TESTED ON THE GROUND AND LEAK WAS DETECTED WITH A 6 INCH CRACK LT OF THE OUTFLOW VALVE. A REPAIR DESIGN WAS CARRIED OUT.SDR CA051103004Web · cracked(CAN) WEB CRACKED HORIZONTALLY APPROX. 10 INCHES. CRACK COINCIDES WITH FLANGE OF UNDERLYING Z CHANNEL. PROBLEM APPEARS TO BE RELATED TO POOR MANUFACTURING PRACTICES. PRC SEALANT BEAD APPLIED TO Z CHANNEL FLANGE CURED BEFORE RIVETING. THE RESULT WAS THAT THE SSDR 2005FA0001447Skin · wrinkledDURING ANNUAL INSPECTION NOTED WING ROOTS, BOTH LT AND RT WRINKLED. AREA OF DEFECT IS FORWARD OF MAIN CARRY THRU SPAR. A SERIES OF 3 WAVES EXTENDING APPROXIMATELY 6-8 INCHES LONG. PROBABLE CAUSE: SEVERE TURBULENCE OR OVER CONTROL OF AIRCRAFT EXCEEDING (G) LSDR CA051003007Motor · failed(CAN) UPON SELECTION OF GEAR DOWN, PILOT NOTICED THAT GEAR WOULD NOT EXTEND AND THAT THE CIRCUIT BREAKER HAD POPPED. HE RESET IT AND SELECTED GEAR DOWN AGAIN WITHOUT ANY SUCCESS. PILOT USED EMERGENCY EXTENSION AND LANDED WITHOUT INCIDENT. UPON INSPECTION OF LASDR CA050912006Pressure Valve · worn(CAN) REMOVED LT PNEUMATIC CHECK VALVE TO INSPECT INTERNAL HINGE OPERATIONS. FOUND HINGE PIN DISLODGED (WORKED) TO ONE SIDE, RESULTING IN OFFSET FLAPPER DOOR MOVEMENT, WEAR AND POOR OPERATION. A LONGER HINGE PIN OR STAKING THE ORIGINAL PIN MAY PREVENT THIS TYPSDR CA050810002Heater · failed(CAN) PILOT REPORTED RT ENGINE HAD NO ACCELERATION RATE AS COMPARED TO LT ENGINE. THE RT ENGINE DID EVENTUALLY ACCELERATE, BUT NOT EQUAL WITH THE LT. TROUBLESHOT AND FOUND RT OIL-TO-FUEL HEATER THERMOSTAT GONE TO (FULL HOT) AND FUEL TEMP WAS SAME AS OIL TEMPSDR CA050621019Windshield · delaminatedDELAMINATION AT WINDSHIELD.SDR 2005FA0000671Fork · crackedFOUND CRACKED NOSE FORK TUBE AT LOWER WELD AREAS WHILE PERFORMING AD 2004-23-02, DURING ROUTINE PHASE INSPECTION. FORK WAS REPLACED WITH MFG KIT NR 101-8030-1, SN 2463.SDR CA050309004Booster · failed(CAN) SHOP TOOL FOR FILLING O2 SYSTEMS. THE OXYGEN BOOSTER DESCRIBED ABOVE WAS BEING USED TO FILL MEDICAL OXYGEN IN TO THE AIRCRAFT LIFEPORT MEDICAL SLED ON BOARD THE AIRCRAFT, WHEN THE UNIT EXPLODED WITH NO WARNING SENDING A TORCHING FLAME WITH HOT SHRAPNEL ASDR CA050309008Hose · leaking(CAN) DURING LANDING, AC PULLED TO RT, FULL LT BRAKING, REVERSE AND RUDDER WERE UNABLE TO KEEP AC ON RUNWAY. AC CAME TO A STOP RT OF LANDING DIRECTION, WITH RT MAIN AND NOSE GEAR OFF OF RUNWAY. DETERMINED THAT RT SIDE BRAKES WERE FROZEN CAUSING WHEELS TO LOCSDR 2005FA0000631Relay · burnedHEAT REMOTE SWITCH MODULE FOR STALL WARNING HEAT (LIFT DETECTOR) HAD SHORTED CAUSING SMOKE IN CABIN/FLIGHT DECK DURING FLIGHT OPERATION. SB 1132 WAS ACCOMPLISHED ON 6/25/2003, AC TT 81.2 HOURS. (K)SDR CA050301004Gas Generator · cracked(CAN) DURING ENGINE INSPECTION USING A VIDEO BORESCOPE, THE HIGH PRESSURE BLEED VALVE TUBE FROM P3 WAS FOUND CRACKED OFF AND A HORIZONTAL CRACK APPROXIMATELY 3 INCHES LONG BELOW BLEED VALVE ATTACH FLANGE WAS NOTED. SOME STAINING INDICATED CRACK WAS PROBABLY NOSDR CA050127007Line · unserviceable(CAN) HYDRAULIC FLUID LEAKING OUT OF THE LT IB L/E. L/E REMOVED AND FOUND RIGID HYDRAULIC BRAKE LINE CHAFFED THROUGH BY ENGINE CONTROL CABLES ABOVE HEAT EXCHANGER. REPLACED LINE. ALL COMPANY AIRCRAFT USING THIS HYDRAULIC LINE VISUALLY INSPECTED AND FOUND DAMASDR CA050117001Frame · cracked(CAN) DURING A ROUTINE INSPECTION A CRACK WAS FOUND PROPAGATING FROM THE OVAL HOLE IN THE RT FRAME AT STATION 207.125 (HALF WAY BETWEEN THE FLOOR AND THE WINDOW). THE CRACK WAS APPROXIMATELY 1 = INCH LONG AND EXTENDED FROM THE 11 O`CLOCK POSITION OF THE LIGHTSDR CA050104002Line · wrong part(CAN) DURING VISUAL INSPECTION AT PWC, WE HAVE IDENTIFIED THAT ONE FUEL PRESSURE HOSE WAS NOT GENUINE BUT WAS FITTED TO THE ENGINE S/N 42372 WHERE THE HOSE P/N 3033736 SHOULD BE FITTED. THIS HOSE IS BUILT IN 3 PIECES, A FLEXIBLE STEEL HOSE COVERED WITH AN ORANSDR 2005FA0000034Relay · failedWHILE THE AIRCRAFT WAS IN FLIGHT, THE FLAPS FAILED TO EXTEND TO THE SELELCTED APPROACH POSITION. THE PILOT CYCLED THE FLAP SELECT SWITCH TO UP AD BACK TO APPROACH AND THE FLAPS EXTENDED. MAINTENANCE INVESTIGATED THE REPORTED PROBLEM AND WAS ABLE TO DUPLICATESDR CA041025002Diode · burned(CAN) EXPERIENCED NR1 DUAL FED BUS FAILURE IN FLT. NR 1 DUAL FEED BUSS EQUIP BECAME DE-ENERGIZED. AC LANDED WITHOUT INCIDENT. MAINT DISCOVERED BOTH DIODES BURNED OPEN ON NR1 DUAL FEED BUSS SYS. REPLACED DIODES WITH NEW, PERFORMED DUAL BUSS CONFORMITY CHECKSDR CA041020010Oil Filter · clogged(CAN) ON ROUTINE INSPECTION IT WAS DISCOVERED THAT A PIECE OF THE SCREEN SECTION WAS SEPERATING FROM THE EXTERNAL SECTION OF THE FILTER. NOT SURE IF IT IS A MANUFACTURING DEFECT OR IF THE FILTER WAS COMING APART IN USE.SDR KNI2004F00000Vane · crackedDURING PHASE INSPECTION, FOUND THE LT ICE VANE CRACKED THRU IN THE CENTER OF THE HINGE. UPON MORE INVESTIGATION, FOUND THE HINGE PIN HAD WORKED ITS WAY OUT OF THE HINGE. EVENTUALLY IT WORE A HOLE THRU THE DUCT SIDE WALL AND PROCEEDED TO COME OUT OF THE HINGESDR CA040922001Snap Ring · out of position(CAN) DURING ENDPLAY CHECK (1000 CYCLES) ON LT MAIN GEAR ACTUATOR, INPUT GEAR WAS FOUND TO HAVE 0.090 INCH ENDPLAY. THIS CHECK USED TO VERIFY THAT THRUST BEARING IS PROPERLY INSTALLED, MAXIMUM ENDPLAY IS 0.050. THESE ACTUATORS ARE OVERHAULED AT 7500 CYCLES, TSDR CA040922005Actuator · worn(CAN) DURING ROUTINE 1000 CYCLE ENDPLAY CHECK OF THE NOSE GEAR ACTUATOR, THE ACTUATOR FAILED WITH 0.020 OF AN INCH ENDPLAY THE MAX ALLOWABLE IS 0.016. THIS UNIT ONLY HAD 997 CYCLES SINCE OVERHAUL (OVERHAUL DUE AT 7500 CYCLES). THE ACTUATOR WAS REMOVED FROM SESDR VIBA20040916Fuel Control · failedTHE FUEL PUMP DRIVE SHAFT BEARING ASSEMBLY APPARENTLY FAILED OVER AN UUNDETERMINED PERIOD OF TIME, LEADING TO SHAFT LOCK UP AND SHEARED THE DRIVE COUPLING. BLACK RESIDUE FROM THE BEARING FAILURE WAS FOUND TO BE EMITTING FROM THE GANG DRAIN AND STREAKING BACK SDR CA040908003Glide Slope · erratic(CAN) RT GLIDESLOPE INDICATION VERY ERRATIC AND NO WARNING FLAP IN VIEW TELLING PILOT SIGNAL INVALID. MEL'ED SYSTEM AND TROUBLESHOOTING IN PROGRESS.SDR CA040831021Gps · out of adjust(CAN) PILOT REPORTS GPS 60 DEGREES OFF TRACK. T/S INDICATES CALIBRATION OF UNIT 60 DEGREES OUT. RECALIBRATED.SDR 2004FA0000695Fuel Control · seizedPILOT NOTED UNCOMMANDED LEFT ENGINE TORQUE AND ITT INCREASE IN FILGHT ON INITIAL APPROACH TO MKE. NO RESPONSE TO POWER LEVER INPUT. PILOT SHUTDOWN ENGIEN AND DIVERTED TO RFD. DURING REMOVAL OF FCU FOR TROUBLESHOOTING NOTED FCU INPUT SHAFT COUPLING SHEARED, SDR CA040805016Sensor · faulty(CAN) UPON REGULAR PHASE INSPECTION, THE FIRE DETECTION SYSTEM FAILED TO TEST CORRECTLY ON RT ENGINE. TROUBLESHOT AND FOUND SENSOR AT FAULT. REPLACED SENSOR, OPERATION RESTORED TO NORMAL.SDR G9C2004F00000Mount · crackedWHILE INSPECTING THE ENGINE MOUNT IAW THE INSTRUCTIONS OF PART 1, MFG SB 1103B, DATED NOV 11, 2003, CRACKS WERE DISCOVERED IN TWO OF THE ENGINE MOUNT TUBE MEMBERS ATTACHED TO THE RT NOSE GEAR ACTUATOR ATTACHMENT FOOT. THE SB SPECIFIES TO INSPECT THE ENGINE MSDR CA040628008Skin · cracked(CAN) COMBINATION VHF/GPS ANTENNA DOUBLER AND FUSELAGE SKIN CRACKED UNDER ANTENNA WHICH WAS ENGINEERED AND INSTALLED IAW LSTC NR C-LSA01-625/D. FUSELAGE REPAIRED AND ANTENNA REMOVED. NEW REPAIR DOUBLER INSTALLED.SDR CA040628009Skin · cracked(CAN) COMBINATION VHF/GPS ANTENNA DOUBLER AND FUSELAGE SKIN CRACKED UNDER COMANT ANTENNA WHICH WAS ENGINEERED AND INSTALLED IAW LSTC NR C-LSA01-625/D. FUSELAGE REPAIRED AND ANTENNA REMOVED. NEW REPAIR DOUBLER INSTALLED.SDR CA040624001Mount · mismanufactured(CAN) DURING ENGINE MOUNT REPLACEMENT IT WAS NOTICED THAT THE NEW MOUNTS WERE MANUFACTURED WITH THE BEVEL ON THE WRONG SIDE OF THE METAL PART OF THE CORE (R20700-11). THE CORE IS MADE OF RUBBER SANDWICHED BETWEEN TWO PIECES OF METAL. THE BEVEL IS THERE TO ALLSDR CA040621006Receptacle · corrodedCOURTESY AND ENTRANCE DOOR LIGHTS REPORTED U/S. TROUBLESHOOTING LED TO CONNECTOR P406 LOCATED IN THE AIRCRAFT SIDEWALL FORWARD OF THE ENTRANCE DOOR. FOUND CONNECTOR PINS CORRODED, PRIMARILY PIN 7 THATSUPPLIES 28VDC TO THE CIRCUIT. WIRING REPAIRED AND AIRCRASDR AUS20040504Seal · leaking(AUS) ENGINE STARTER-GENERATOR OIL SEAL LEAKING.SDR AUS20040433Seal · worn(AUS) ENGINE ACCESSORY GEARBOX STARTER-GENERATOR DRIVE SHAFT SEAL WORN. LOSS OF ENGINE OIL.SDR CA040519004Rudder Pedal · worn(CAN) RUDDER PEDAL ATTACH POINT BROKEN AT BUSHING ATTACH.SDR AUS20040400Turbine Blades · cracked(AUS) COMPRESSOR TURBINE BLADES (3 OFF) CRACKED. CRACKS EMANATE FROM BLADE TIP RADIALLY TOWARDS BLADE ROOT. CRACK LENGTHS UP TO APPROXIMATELY 7MM (0.27IN). FOUND DURING BOROSCOPE INSPECTION.SDR CA040505002Hose · ruptured(CAN) BRAKE DEICE HOSE RUPTURED AND CAUSED BLEED AIR FAILURE SYSTEM TO ACTIVATE LIGHT. HOSE WAS REMOVED AND LINE CAPPED, WARNING SYSTEM REPAIRED IAW MFG MM. CH 21 BRAKE HOSE ORDERED AND SYSTEM PLACARDED AND MADE INOPERATIVE.SDR CA040423006Switch · shorted(CAN) PILOT REPORTED THAT THE STALL HEAT APPEARED TO BE ON (HIGH) MODE ON THE GROUND WHEN A WALK-AROUND WAS CONDUCTED. MAINTENANCE CONFIRMED BY RESEARCHING WIRING DIAGRAM AND SYSTEM OPERATION. TROUBLESHOT AND FOUND LT MAIN GEAR SAFETY SWITCH P/N 101-364628-3SDR CA040428003Exhaust Stack · cracked(CAN) DURING ROUTINE INSPECTION A CRACK WAS NOTED AT THE LIP HEAT WELD TO THE FORWARD SECTION OF THE EXHAUST STACK. EXHAUST UNIT WAS ORDERED AND INSTALLED WITHOUT ANY INCIDENT.SDR AUS20040308Engine · surges(AUS) NR 2 ENGINE POWER SURGE. DURING GROUND RUN TORQUE BLED OFF. INVESTIGATION FAILED TO FIND ANY CAUSE AND THE ENGINE WAS REMOVED.SDR AUS20040454Engine · overheated(AUS) RT ENGINE OVERTEMPED ON START. ENGINE REMOVED.SDR 2004FA0000349Switch · shortedAUTO START SYSTEM WOULD NOT DISENGAGE AUTOMATICALLY AT 56 PERCENT NG. FOUND ELECTRONIC CONTROL MODULE 1012 (P/N 688-499) INTERNALLY SHORTED CAUSING POWER TO CONSTANTLY FLOW REGARDLESS OF COMMANDS.SDR AUS20040252Pushrod · corroded(AUS) RUDDER PUSHROD CONTAMINATED WITH WATER CAUSING CORROSION OF THE INTERNAL BORE.SDR CA040426003Window · warped(CAN) DURING A ROUTINE DAILY INSPECTION IT WAS NOTED THE RT AFT CABIN WINDOW HAD A INWARD CONCAVE APPEARANCE ACROSS THE CENTER FROM TOP TO BOTTOM. UPON REMOVAL WITH THE USE OF A STRAIGHT EDGE IT WAS WARPED ACROSS THIS AREA. NO FURTHER DEFECTS IN THE FORM OF CR
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