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 AUS20040435Clip · cracked(AUS) LT OB FLAP IB TRACK RIVETS LOOSE IN AREA ADJACENT TO LOWER SKIN ATTACHMENT. FURTHER INSPECTION FOUND BUCKLING AND CRACKING OF THE OUTBOARD SHEAR CLIP.SDR CA040324002Battery · discharged(CAN) PILOT REPORTED COMPLETE ELECTRICAL FAILURE AND LANDED WITH GEAR MANUALLY EXTENDED. INSPECTION FOUND STARTER SWITCHES IN THE 'ON' POSITION AND BATTERY DOWN TO 12VOLTS, NO OTHER INDICATION OF FAULT WAS FOUND. I FEEL THAT WITH THE SWITCHES IN THE 'ON' POSITSDR AUS20040213Valve · faulty(AUS) DEFECT REPORT NR WAS CREATED IN LIEU OF DATA BEING ATTACHED TO MDR 04/0176. CANCELLED, DATED 25TH MARCH 2004.SDR AUS20040176Check Valve · faulty(AUS) FUEL SYSTEM CHECK VALVE SUSPECT FAULTY.SDR AUS20040239Frame · cracked(AUS) FUSELAGE FRAMES CRACKED. CRACKS FOUND IN THE FOLLOWING AREAS:-1. INTERCOSTAL CRACKED AT STRINGER NR 72. FUSELAGE FRAME CRACKED AT STATION 326.75, STRINGER NO8 AND NO9 3. FUSELAGE FRAME CRACKED AT STATION 337.75, AT STRINGER NR 9, NR 10 AND NR 114. LT STSDR AUS20040151Engine · fluctuates(AUS) LT ENGINE FUEL FLOW AND ENGINE TORQUE FLUCTUATING BEFORE ENGINE STARTED TO ROLLBACK. INVESTIGATION COULD FIND NO CAUSE FOR THE DEFECT. THE ENGINE WAS GROUND RUN AND THEN TEST FLOWN WITH NO FURTHER REOCCURRENCE.SDR Q2A2004F00000Linkage · lack of lubePILOT REPORTED RT THROTTLE LOCKED IN FLIGHT. NON EVENTFUL LANDING. INSPECTION FOUND DRY FUEL CONTROL LINKAGE CAUSING BINDING. LUBRICATED IAW MM, FUNCTION CHECKS OK. NO PRESENCE OF LUBE SINCE NEW.SDR AUS20040102Shroud · damaged(AUS) RT ENGINE TURBINE SHROUD AND BLADES DAMAGED.SDR AUS20040096Frame · cracked(AUS) FUSELAGE FRAME LOCATED AT RF 265-760 CRACKED IN AREA ADJACENT TO FLOORBEAM. FOUND DURING INSPECTION IAW AD/BEECH200/65.SDR AUS20040093Circuit Breaker · tripped(AUS) RT MAIN LANDING GEAR WOULD NOT EXTEND. CIRCUIT BREAKER (60AMP)FOUND TRIPPED. CB RESET AND RETRACTION TESTS CARRIED OUT WITH NO REOCCURANCE.SDR AUS20040092Skin · delaminated(AUS) LT WING INNER LEADING EDGE SKIN DELAMINATING IN AREA LOCATED ABOVE THE BYPASS DUCT.SDR AUS20040120Structure · cracked(AUS) REAR PRESSURE BULKHEAD CLEAT LOCATED AT STRINGER 7L AND BULKHEAD BEAM AT STRINGER 6L CRACKED. FOUND DURING INSPECTION IAW AD.SDR CA040126002Hinge · worn(CAN) MAINTENANCE INSPECTION DISCOVERED LT ENGINE INLET VANE HINGE PIN WAS WORKING OUT OF THE HINGE AND CONTACTING THE INNER COWL STRUCTURE. MFG ADVISES THE HINGE ENDS ARE CRIMPED TO PREVENT PIN MOVEMENT, HOWEVER ON THIS ASSY THE PIN APPEARS TO HAVE WORN THRSDR SVB2004F00000Engine · making metalON JAN 6, 2004 AIRCRAFT DEPARTED, ABOUT 10 MILES OUT THE PILOT NOTICED A RT ENGINE CHIP LIGHT. PILOT RETURNED TO DEPARTURE AND MADE AN UNEVENTFUL LANDING. AFTER INSPECTION OF THE CHIP DETECTOR BY MAINT IT WAS FOUND TO HAVE A PIECE OF GEAR TOOTH ON IT. FURTHSDR CA040203006Windshield · broken(CAN) IN CRUISE RT WINDSHIELD HEAT ON, WINDOW SHATTERED, DESCENDED TO 12,000 FT, REDUCED AIR SPEED AND CABIN PRESSURE AND RETURNED TO BASE.SDR CA031205001Windshield · cracked(CAN) WHILE IN CRUISE FLIGHT THE PILOT HEARD A 'CLAP' AND THEN NOTICED A CRACK IN THE RT WINDSHIELD. THE AIRCRAFT RETURNED TO BASE. INSPECTION DETERMINED CRACK TO BE IN THE EXTERIOR PANE, LIKELY ORIGINATING FROM A SMALL STONE BRUISE. WINDSHIELD TO BE REPLACED.SDR CA031117014Cable · frayed(CAN) DURING INSPECTION OF CABIN DOOR CAM LOCK LATCHES, THE DOOR LATCHING CABLE WAS FOUND TO HAVE HALF TO THREE QUARTERS OF THE CABLE STRANDS BROKEN. IF THIS CABLE WOULD HAVE BROKEN COMPLETELY IT COULD HAVE CAUSED ONE COMPLETE SIDE OF DOOR TO BECOME UNLATCHEDSDR CA031031010Duct · cracked(CAN) DISCOVERED COWL DUCT CRACKING DURING ROUTINE MAINTENANCE INSPECTION. MFG HAS PREVIOUSLY IDENTIFIED THIS PROBLEM AND DESIGNED A FIELD REPAIR TO RECTIFY IT. INCORPORATED FIELD REPAIR FR-KA-00038 TO BOTH ENGINE COWLS. DUCT PN 101-910049-12 ALSO AFFECTEDSDR CA040902008Antenna · vibrationA/C ORIGINALLY EQUIPPED WITH ANTENNA MOD CI4510-700 IAW LSTC NR C-LSA02-377/D. ANTENNA LATER RECALLED BY MANUFACTURER. REPLACEMENT ANTENNA MOD CI2480-100. DURING FLT, REPLACEMENT ANTENNA VIBRATED LOUD ENOUGH TO BE HEARD IN COCKPIT. ANTENNA REMOVED. INSTALSDR CA040325001Windshield · failed(CAN) INNER PLY ON CAPTAINS WINDSHIELD INSTANTLY SHATTERED AT APPROXIMATELY 28,000 FT, CAUSING THE CREW TO COMMENCE AN EMERGENCY DESCENT AND LANDING. WEATHER WAS FAIR AT THE TIME AND THERE WAS NO WINDSHIELD HEAT ON.SDR CA030925005Pad · loose(CAN) DURING LANDING THE AIRCRAFT WAS PULLING TO THE LEFT SIDE OF THE RUNWAY. UPON APPLICATION OF THE BRAKE ON THE LEFT SIDE AIRCRAFT STARED TO VIBRATE. THE BRAKE WAS ALSO NOTED TO BE SOFT AND INEFFECTIVE. MAINTENANCE INSPECTED IT AND FOUND THE LT OUTBOARD SDR AUS20030915Relay · corroded(AUS) EFIS RELAY PN 3921K10 CORRODED. INVESTIGATION FOUND EXTENSIVE CORROSION THROUGHOUT THE RELAY MODULE.SDR AUS20030893Bolt · cracked(AUS) LT AFT UPPER WING ATTACHMENT BOLT CRACKED IN THREADED AREA.SDR AUS20030943Windshield · failed(AUS) RT WINDSHIELD INNER PANE SHATTERED.SDR CA030827013Hose · deteriorated(CAN) BRAKE DE-ICE HOSE WAS FOUND TO BE BLOCKED DUE TO DETERIORATION OF THE INSIDE OF HOSE. THE UPPER FLEXIBLE HOSE WAS FOUND TO PASS SHOP AIR THROUGH AN AIR NOZZLE BUT WAS NOT FOUND TO PASS THE VOLUME SUPPLIED BY THE ENGINE BLEED AIR. THE LARGE VOLUME OF AIRSDR 2003FA0000916Heater · crackedTROUBLESHOT NR 2 ENGINE OIL LEAK. FOUND A HAIRLINE CRACK NEAR UPPER INBOARD WELD OF PARTS MAIN BODY. LOCATED JUST UNDER WELD AND APPROX .7500 INCH IN LENGTH.SDR CA030718002Wheel · cracked(CAN) DURING WHEEL OVERHAUL THE NDT FACILITY DISCOVERED 3 CRACKS IN THE OUTER-HALF OF THE WHEEL ASSEMBLY. CRACKING WAS IN THE WEB AREA BETWEEN THE BEARING BOSS AND THE BEAD SEAT FLANGE. THE INBOARD HALF WAS NOT DAMAGED. OUTBOARD WHEEL HALF SCRAPPED AND REPLACESDR AUS20030673Engine · fluctuates(AUS) LT ENGINE TORQUE FLUCTUATING. ITT 900 DEGREES C.SDR AUS20030629O-Ring · wrong part(AUS) ENGINE OIL SYSTEM CHECK VALVE O' RING JAMMED CHECK VALVE IN OPEN POSITION. SB3178R2 DELETES THE O' RING FROM THE CHECK VALVE. PERSONNEL/MAINTENANCE ERROR. ENGINE SERIAL NUMBER PCE-93117.SDR AUS20030630O-Ring · wrong part(AUS) ENGINE OIL SYSTEM CHECK VALVE O' RING JAMMED CHECK VALVE IN OPEN POSITION. SB3178R2 DELETES THE O' RING FROM THE CHECK VALVE. PERSONNEL/MAINTENANCE ERROR. ENGINE SERIAL NUMBER PCE-93183. SEEALSO MDR 03/0629 FOR SIMILAR DEFECT ON OTHER ENGINE OF SAME AIRCSDR CA030703008Stringer · cracked(CAN) 600 HR INSPECTION REVEALED 2 CRACKED STRINGERS (NR 9 RT HYD TSB 2472 REV.II.)SDR CA030703009Bulkhead · cracked(CAN) NACELLE BULKHEAD CRACKED FROM LOWER RT BOLT HOLE TO EDGE OF BULKHEAD. NEW BULKHEAD INSTALLED ON BOTH NACELLES. PROBLEM ATTRIBUTED TO AIRCRAFT AGE AND NUMBER OFCYCLES.SDR CA030627010Plate · leaking(CAN) DURING SCHEDULED INSPECTION, FOUND EXHAUST SEAL PLATE FROM LT ENGINE OUTBOARD EXHAUST STACK TO THE HEATED ENGINE INTAKE ANTI-ICE LIP WITH ONE BOLT MISSING AND THE REMAINING BOLTS LOOSE. THE RESULTING EXHAUST LEAK HAS CAUSED SOOT TO BUILDUP ON THE ENGINE SDR CA030702003Fire Detector · malfunctioned(CAN) AFTER TAKEOFF AIRCRAFT CLIMBED OUT, AND A RT ENGINE FIRE WARNING LIGHT CAME ON. COULD NOT SEE SMOKE, ENGINE FUNCTIONED NORMAL.. RETURNED TO MAINTENANCE FACILITY.SDR CA030610005Bolt · loose(CAN) UPON INSPECTION THE TRIM TAB ACTUATOR WAS FOUND TO HAVE 2 BOLTS, P/N 130909B38, LOOSE. THE ACTUATOR SHOWED NO INDICATIONS OF DAMAGE OR MALFUNCTION, TRIM TAB FREE PLAY INSPECTION WAS WELL WITHIN TOLERANCE. BOLTS WERE TORQUED AND ANTI SABATOGE LAQUER WASSDR CA030610006Regulator · failed(CAN) PNEUMATIC REGULATOR FAILURE IN CRUISE FLIGHT OCCURRED. PILOTS HAD TWO BLEED AIR FAIL LIGHTS, LEFT AND RIGHT, AND ALSO NOTED LOSS OF SUCTION AND PNEUMATIC PRESSURES CONFORMING LIGHT INDICATION. PILOTS RETURNED TO BASE. UPON INSPECTION THE REGULATOR FOUND SDR CA030610007Actuator · misinstalled(CAN) FLAP ACTUATOR WAS FOUND TO HAVE BEEN INSTALLED INCORRECTLY WITH LUBRICANT VENT HOLE DOWN WHICH RESULTS IN LOSS OF LUBRICANT. ACTUATOR WAS REMOVED AND FOUND TO BE UNSERVICEABLE DUE TO HAVING TOO MUCH END PLAY. THE ACTUATOR WAS SENT FOR REPAIR, RE-INSTALLSDR CA030609004Pressure Switch · failed(CAN) AIRCRAFT FLEW UNEVENTFUL. UPON TAKEOFF, THE CREW SELECTED GEAR UP. THE NOSE AND RT MAIN GEAR BEGAN TO RETRACT. THE LT MAIN GEAR REMAINED DOWN AND LOCKED. CREW SELECTED GEAR DOWN AND RETURNED TO 3 GREEN. ONCE AGAIN, CREW SELECTED GEAR UP. GEAR DID NOT MSDR CA030606009Flow Divider · wrong part(CAN) ENG WAS SHUTOFF IN FLT FOLLOWING HIGH T-5 OCCURRENCE. NO DAMAGE EXTERNALLY & ONLY DAMAGE FOUND INTERNALLY RUBBING CONTACT BETWEEN COMP TURBINE BLADE TIPS & CT SHROUD SEG. NO EVIDENCE OF OVERTEMP, OR ANY BUILD ERRORS IN THE ENG. FLOW DIVIDER HAS WRONGLYSDR AUS20030672Structure · cracked(AUS) REAR BULKHEAD BEAM EXTENSION CLEATS LOCATED AT STRINGER 5,STRINGER 7, STRINGER 8 AND STRINGER 11 CRACKED. CLEATS ARE INSTALLED DUE TO WIDENING OF THE REAR FUSELAGE FOR STC SA2192CE. FOUND DURING INSPECTION IAW AD/BEECH200/55 AMDT1 AND AD/BEECH200/21 AMDSDR AUS20030796Fire Detector · faulty(AUS) LT ENGINE FIRE WARNINGS. EXTINGUISHER DISCHARGED. NO EVIDENCE OF FIRE FOUND. FAULTY FIRE DETECTORS PN 302158 AND PN 473275.SDR AUS20030431Insulator · failed(AUS) WIRE SEPARATED FROM AIRCRAFT AT FEED THROUGH INSULATOR. LONG WIRE IS USED FOR MILITARY OPERATIONS.SDR AUS20030427Bulkhead · damaged(AUS) REAR PRESSURE BULKHEAD DAMAGED. A SMALL DENT APPROXIMATELY 10.1MM (0.4IN) LONG CONTAINING A SHARP INDENT WAS FOUND TO BE CRACKED. SUSPECT CAUSED DURING EQUIPMENT LOADING SOME TIME PREVIOUSLY.SDR CA030424006Actuator · leaking(CAN) DURING A POST FLIGHT WALK AROUND, THE PILOT NOTICED HYDRAULIC FLUID LEAKING FROM THE NOSE GEAR ACTUATOR P/N 112-280022-21. THE FLUID WAS COMING FROM ABOVE THE RETAINER. THE ACTUATOR WAS REPLACED WITH A OVERHAULED UNIT. DURING THE RIGGING PROCESS THE POSISDR CA030417010Bearing · failed(CAN) DURING DESCENT THE CREW NOTICED AN ELECTRICAL SMOKE ODOR IN THE CABIN WITH NO VISIBLE SIGNS OF SMOKE, THE CREW ACTIONED THE EMERGENCY CHECKLIST AND LANDED THE AIRCRAFT WITHOUT INCIDENT. MAINTENANCE FOUND THAT THE FORWARD BLOWER ASSEMBLY WAS A LITTLE NOISSDR AUS20030349Doubler · worn(AUS) DOUBLER WORN THROUGH BY LT WINDSHIELD DEMIST DUCT.SDR 2004FA0000582Check Valve · stuckCHECK VALVE, GRAVITY/SUPPLY LINE FOUND STUCK OPEN ALLOWING FUEL DISPLACEMENT FROM HEADER TANK. AIRCRAFT INVOLVED IN FATAL ACCIDENT 03/07/03SDR 2004FA0000592Check Valve · stuckCHECK VALVE ASSY. GRAVITY/SUPPLY LINE FOUND STUCK OPEN ALLOWING FUEL DISPLACEMENT FROM HEADER TANK.SDR 2004FA0000593Check Valve · stuckCHECK VALVE ASSY. GRAVITY/SUPPLY LINE FOUND STUCK OPEN ALLOWING FUEL DISPLACEMENT FROM HEADER TANK.SDR CA030425005Resistor · loose(CAN) CREW REPORTED TOTAL LOSS OF ENGINE TEMPERATURE INDICATION DURING TAXI OPERATIONS. ALL TROUBLESHOOTING PROCEDURES WERE FOLLOWED IN THE ENGINE AND AIRFRAME MANUFACTURER'S MAINTENANCE MANUALS. AIRFRAME WIRING HARNESS WAS CONNECTED TO MULTIMETER FOR TESTS. O
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