U/A Canada PT6A-21
Service difficulty reports · 310
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 = '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.
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
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 2010FA0000163Powerpack · inoperativeON DECEMBER 27,2009 THE LANDING GEAR FAILED TO EXTEND UNDER NORMAL ELECTRICAL POWER DUE TO A NUISANCE OPENING IN THE 60 AMP UNDERFLOOR CIRCUIT BREAKER. THE PILOT TOOK EMERGENCY ACTION WITH THE CONTROL TOWER TO VISUALLY CHECK THE LANDING GEAR FOR THE DOWN POSISDR CA100108001Intake Duct · cracked(CAN) INTAKE DUCT SKIN CRACKED AT TWO LOCATIONS, LOCATIONS ARE, LEADING EDGE FASTENER ROW, FASTENER HOLES AT 3:00 AND 9:00 O’CLOCK. (TC NR 20100108001)SDR CA091214003Control System · failed(CAN) ACFT REACHED CRUISING ALTITUDE OF FL270, PILOT NOTICED RT ENGINE OIL TEMP INDICATION REACHING RED LINE, AND OIL PRESSURE STARTING TO DECREASE. PILOT REDUCED POWER ON RT ENG AND FEATHERED AFFECTED ENG, HE THEN RETURNED TO BASE AND HAD AN UNEVENTFUL LANDINSDR CA091126001Governor · malfunctioned(CAN) AFTER TAKEOFF THE ENGINE EXPERIENCED AN UNCOMMANDED POWER INCREASE AND WAS SHUT DOWN. INVESTIGATION REVEALED A FAULTY FUEL CONTROL GOVERNOR SECTION. (TC NR 20091126001)SDR CA090904011Petcock · openACFT WAS DEPARTING FOR A LOCAL TRAINING FLIGHT. STUDENT OCCUPIED THE LT SEAT AND WAS PILOT FLYING, INSTRUCTOR WAS PILOT NOT FLYING ON RT SIDE. ON INITIAL CLIMB INSTRUCTOR NOTED THAT STUDENT HAD MISSED CROSSWIND TURN ALTITUDE AND ADVISED SAME. STUDENT CALLED SDR CA090904010Oil Cap · unsecureDURING TRAINING FLIGHT AT APPROX 1 HOUR INTO FLIGHT, FLYING PILOT NOTICED A LWR THAN NORMAL ENG OIL PRESSURE ON LT ENGINE. EMERGENCY CHECKLIST WAS CARRIED OUT AND COMPLETED. LT ENG OIL PRESSURE WARNING LIGHT THEN ILLUMINATED MOMENTARILY (FLICKERED). ENG SHUSDR CA090602009Pin · worn(CAN) ON A SCHEDULED PHASE 4 INSP, A RUBBING SOUND WAS NOTED COMING FROM BENEATH CABIN FLOOR JUST AFT OF THE CABIN ENTRANCE WHEN THE ELEVATOR CONTROLS WERE MOVED. AME NOTING THE SOUND, GAINED ACCESS TO INVESTIGATE IN THIS AREA. IT WAS DISCOVERED THAT A CABLE GSDR CA090526005Oil Filter · damaged(CAN) DURING OPS NR1 INSP, ENG OIL FILTERS WERE REMOVED AND INSPECTED. THERE WAS NO EVIDENCE OF CONTAMINATION ON THE FILTER ELEMENT, HOWEVER, WHEN THE SECONDARY FILTER WAS INSPECTED IT WAS FOUND WITH AN OPEN END. THE SECONDARY FILTER IS CONICAL SHAPED WITH THESDR CA090304014Engine · malfunctioned(CAN) UNCONTROLLED ENGINE ACCELERATION DURING FLIGHT. FLIGHT CONTINUED WITH CLA TO MINIMUM POSITION TO REDUCE POWER. ENGINE IS BEING REMOVED.SDR CA090206007Casting · crackedDURING 72 MONTH INSPECTION IT WAS FOUND THAT THE LOWER CASTING WAS CRACKED AT THE LOWER TORQUE KNEE CONTACT POINT.SDR CA080905007Tab · bent(CAN) EMERGENCY EXIT DOOR LATCH APPEARS AS THOUGH THE LATCH TAB HAD BEEN BENT SO THAT IT COULD BE INSTALLED IN THIS MANNER. IN THIS MODE, THE LATCH CAN ALWAYS (EVEN WHEN PRESSURIZED) BE OPENED AS THE TAB PASSES OVER THE SAFETY PLUNGER. THE TAB SHOULD CONTACT SDR 2008FA0000617Blower · failedPILOT DETECTED SMOKE IN CABIN, LANDED. TROUBLESHOT ODOR, CHECK IN ENGINE BAYS, NO DEFECT NOTED. FOUND CABIN VENT BLOWER NOT WORKING, CHECKED BLOWER SYSTEM WIRING, NO DEFECTS NOTED, CHECKED VENT BLOWER UNDER PILOT FLOOR AND FOUND BLOWER MOTOR LOCKED UP. REMOVSDR CA080805002Sleeve · wrong part(CAN) WHILE CARRYING OUT A SCHEDULED HOT SECTION INSPECTION ON THE ABOVE ENGINE, IT WAS DISCOVERED THAT 2 NOZZLE SHEATHS WERE OF AN INCORRECT PART NR FOR THE MODEL OF ENGINE INSTALLED. THE PART NRS ARE BOTH FOR A PT6A-50 ENGINE. EVEN THOUGH WE OPERATE THIS MODSDR CA080624001Compressor · failed(CAN) EIR PT6A 2008-040 OVER TEMPERATURE EVENT OCCURRED AS A RESULT OF COMPRESSOR FAILURE DUE TO LOSS OF STACK RIGIDITY, WHICH RESULTED FROM A LOSS OF STRETCH ON THE COMPRESSOR TIE RODS (P/N 3019371). COMPRESSOR SELF-DESTRUCTED. TIE RODS WERE INSTALLED "NEW" ASDR 2008FA0000437Trim Switch · failedAFTER INSTALLATION OF NEW MFG AUTOPILOT SYS, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT. COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR. TRIM CIRCUITRY FAILED AGAIN AND RETURNED TO MFG. MFG TECH SUPPORT ADVISED REPLACEMENT OF SUSSDR 2008FA0000496Trim Switch · inoperativeAFTER INSTALLATION OF NEW AUTOPILOT SYSTEM, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT, OCT 02, 2007. COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR. TRIM CIRCUITRY FAILED AGAIN AND WAS RETURNED TO MFG ON JAN 18, 2008. MFG TECHSDR 20080101Actuator · crackedRT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE. CRACK RUNS PARALLEL TO TUBE .SDR FAA20080118Actuator · crackedRT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE. CRACK RUNS PARALLEL TO TUBE .SDR IG0R200751070Bellows · damagedENGINE WENT TO IDLE IN FLIGHT. FAILED BELLOWS BENCH TEST. BELLOWS BREACHED. UPON FURTHER INSPECTION THERE WAS NO PHYSICAL DAMAGE TO THE BELLOWS HOWEVER THERE WAS CORROSION ON THE TOP OF THE BELLOWS AND AT THE FIRST CONVOLUTION. REPLACED BELLOWS AND RECALIBRATESDR CA071213002Brushes · burned(CAN) CREW DECLARED EMERGENCY DUE TO SMOKE IN COCKPIT AND LANDED SAFELY. REPAIR PARTY LT FROM ANOTHER BASE. FOUND CAUSE WAS CABIN VENT BLOWER. DISABLED SYSTEM. AIRCRAFT FERRIED TO AIRPORT. MAINTENANCE WILL REPLACE VENT BLOWER. (TC NR 20071213002)SDR CA070706001Relay · corroded(CAN) DURING ANNUAL INSPECTION OF THE HYD LANDING GEAR INSTALLATION THE LANDING GEAR RELAY EXHIBITED SIGNS OF HEAVY PITTING AND METAL TRANSFER. THE LANDING GEAR RELAY WAS REPLACED. (TC NR 20070706001)SDR 2007FA0000269None · unknownAIRCRAFT HAS RAISEBECK STC SA3593NM INSTALLED WHICH STATES THE PROPS ARE NOT TO BE OPERATED BELOW THE SET MINIMUM RPM. PRE PHASE INSPECTION RUNS REVEALED THIS CONDITION. IAW MFG SERVICE LETTER 61-254 THIS CAN CAUSE NO REACTION MODE VIBRATORY RESONANCE AND MASDR HSRA3132007Skin · crackedFOUND CRACKS IN THE WING SKIN ON THE LT WING UPPER CENTER SECTION WHERE IT IS RIVETED TO THE ATTACH FITTING. THE FORWARD OB FAIRING NEXT TO THE NACELLE MUST BE LIFTED TO SEE THE CRACKS. LIKELY CAUSED BY LANDING CYCLES AND FATIGUE. SUBMITTER ADVISES THAT MFGSDR CA070221004Buckle · damaged(CAN) COMPLIED WITH COMPANY CAMPAIGN NOTICE 010-25-10-011, NM-06-29. THE CREW SEATBELT ROTARY LATCH CAN BE CONTACTED WITH THE CONTROL YOKE WITH THE SEAT FULL FORWARD AND THE YOKE FULL AFT. IT IS POSSIBLE TO UNLATCH THE SEATBELT BY ROTATING THE YOKE AND MAKINGSDR CA070209001Buckle · damaged(CAN) WITH A COCKPIT CREW MEMBER STRAPPED INTO THEIR SEAT WITH THE SEAT FULLY FORWARD, INTERFERENCE BETWEEN THE CONTROL COLUMN YOKE AND THE ROTARY SEAT BELT BUCKLE FINS OCCURS WHEN THE CONTROL YOKE IS PULLED FULLY AFT AND ROTATED. THE POSSIBILITY EXISTS THAT TSDR CA070207003Buckle · damaged(CAN) CAMPAIGN NOTICE 010-25-10-011 / FAA SAIB NM-06-29. CREW SEAT BELT ROTARY LATCH IS CONTACED BY THE CONTROL YOKE AND THE POSSIBLITY EXISTS TO RELEASE THE BELT WITH ROTATION OF THE CONTROL YOKE WHEN FUNCTIONAL TEST WAS CARRIED OUT IAW SAIB. (TC NR 20070207SDR CA070221003Buckle · malfunctioned(CAN) COMPLIED WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 NM-06-29. THE CREW SEATBELT ROTARY LATCH CAN BE CONTACTED WITH THE CONTROL YOKE WITH THE SEAT FULL FORWARD AND THE YOKE FULL AFT. IT IS POSSIBLE TO UNLATCH THE SEATBELT BY ROTATING THE YOKE AND MAKING SDR CA070202015Fire Detector · malfunctioned(CAN) DURING A ROUTINE MISSION, THE RT FIRE WARNING ANNUNCIATOR LIGHTS ILLUMINATED. THERE WAS NO VISUAL INDICATION OF FIRE. THE PILOT`S SECURED THE ENGINE IAW PUBLISHED PROCEDURES, ACTIVATED THE FIRE SUPPRESSION SYSTEM AND RETURNED TO THE BASE. MAINTENANCE WASSDR CA070202016Gasket · damaged(CAN) PILOTS NOTICED FUEL (STREAMING) FROM THE RT NACELLE TOP COVER SHORTLY AFTER TAKEOFF. THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT. THIS HAPPENED (3) TIMES BEFORE THE PROBLEM WAS CORRECTED. 1ST NOTICE, AFT 86.9 HRS. MAINTENANCE ATTRIBUTED THE EXCESS FUESDR 2007F00018Blower Motor · seizedVENT BLOWER ASSEMBLY SEIZED DURING FLIGHT CAUSING SMOKE IN THE COCKPIT. UNIT IS A PART THAT IS CHANGED (ON CONDITION). PART HAS BEEN ON AIRCRAFT SINCE NEW.SDR C90ABushing · missingFOUND VERY SLIGHT MOVEMENT IN RT MLG OB PART OF MLG STRUT. UPON FURTHER INVESTIGATION, FOUND THAT PN 10574X-YR1145 BUSHING WAS NOT INSTALLED IN MLG STRUT. FURTHER INVESTIGATION FOUND THAT THIS AREA HAD NOT BEEN THOROUGHLY INSPECTED SINCE DECEMBER 2004 DURING 6SDR QVFA001Bushing · missingFOUND VERY SLIGHT MOVEMENT IN RT MLG OB PART OF MLG STRUT. UPON FURTHER INVESTIGATION, FOUND THAT P/N 10574X-YR1145 BUSHING WAS NOT INSTALLED IN MLG STRUT. FURTHER INVESTIGATION FOUND THAT THIS AREA HAD NOT BEEN THOROUGHLY INSPECTED SINCE DECEMBER 2004 DURING SDR 2006FA0001082Tube · crackedTHE TUBES ARE CRACKING ALONG THE WELDS, WHICH CONNECT THEM TO THE INLET LIP ASSEMBLY. REQUIRES REMOVAL OF INLET LIP ASSY AND REPAIR OF THE CRACKED WELDS. (K)SDR CA060922001Bearing · destroyed(CAN) MAINTENANCE NOTICED FLUID LEAKING FROM THE RT MLG BRAKE ASSY. INVESTIGATION REVEALED THAT THE BRAKE ASSY. PISTON RETENTION BOLT WAS THE SOURCE OF THE LEAK. A MORE DETAILED INSPECTION DISCOVERED THAT THE RT MAIN WHEEL INNER WHEEL HALF CONE AND BEARING HADSDR CA061108003Floor Support · cracked(CAN) FLOOR SUPPORT ANGLE P/N UNKNOWN FOUND CRACKED. ANGLE IS PART OF BULKHEAD ASSY. P/N 50420028-15. ANGLE IS LOCATED UNDER CENTRE FLOOR PANEL. (TC NR 20061108003)SDR 2006FA0000890Control Cable · out of adjustDURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTIONS NOTED ELEVATOR CONTROL SYSTEM CABLE TENSIONS OUT OF MM SERVICE LIMITS. FOUND ELEVATOR NEUTRAL POSITIONS OUT OF LIMITS FOLLOWING CABLE TENSION ADJUSTMENTS (WITH FORWARD AND AFT RIG PINS INSTALLED). FOUND FOSDR 2006FA0000892Mount · distortedDURING FIRST SCHEDULED 1ST AND 2ND PHASE INSPECTIONS NOTED SQUEAKING AND METAL TO METAL CONTACT NOISES WHEN RUDDER MOVED SIDE TO SIDE. FOUND RUDDER SERVO CABLE RUBBING ON SMT-65 SERVO MOUNT CABLE DRUM COVER. REPLACED SMT-65 UNIT AND REINSTALLED, RIGGED SERVOSDR 2006FA0000893Fastener · overtorquedFOUND OTHER LT SIDE RUDDER CONTROL ATTACHING HARDWARE TIGHT OR OVERTIGHTENED. EXAMINED LT RUDDER CONTROL SYSTEM HARDWARE FOR SERVICEABILITY AND REINSTALLED AS REQUIRED WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED WITH NORMAL RECOMMENSDR 2006FA0000894Bolt · overtorquedDURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTION INVESTIGATED PILOT COMPLAINT OF STIFF NOSEWHEEL STEERING. VERIFIED COMPLAINT, FOUND NOSEWHEEL STEERING STIFF AND LOUD POPPING NOISES COMING FROM COCKPIT UNDER FLOOR AREA WHEN TAXIED FROM COPILOTS POSITION. SDR CA061006006Drive Shaft · fractured(CAN) THE FUEL CONTROL DRIVE SHAFT WAS FOUND FRACTURED. THE FUEL CONTROL MID LIFE INSPECTION WAS DETERMINED NOT TO HAVE BEEN PERFORMED. (TC NR 20061006006)SDR CA060627001Snap Ring · missing(CAN) WHILE TURNING PROPELLER DURING MAINTENANCE, A METAL-ON-METAL GRINDING NOISE WAS COMING FROM INSIDE L/H ENGINE EXHAUST DUCT. MAINTENANCE REACHED IN THRU EXHAUST STACK OPENING AND TAPPED EXHAUST DUCT "SKI SLOPE" AREA AND HEARD A RATTLE SOUND. ENGINE SPLIT,SDR CA060619004Channel · cracked(CAN) THE P/N 109-910053-15 AND -16 COWL SUPPORT CHANNELS WERE FOUND CRACKED IN THE LOWER FLANGE AREA, AND SUBSEQUENTLY REPAIRED. MANY OF THE REPAIRS HAVE ALSO FAILED. IT APPEARS THAT A SUBSTANTIAL AMOUNT OF COWLING WEIGHT RESTS ON THESE CHANNELS. THE REPEAT DSDR CA060615001Relay · burned(CAN) AIRCRAFT WAS ON A OPS 1 INSPECTION BASE . WHILE WORKING ON SNAG 1769A (OIL COMING FROM A/C COMPRESSOR). AFTER REMOVING THE UNSERVICEABLE A/C COMPRESSOR A VISUAL OF THE SURROUNDING AREA REVEALED THAT THE AIR CONDITIONER START RESISTOR PHENOLIC P/N 100-364SDR CA060619002Tab · cracked(CAN) CRACK DISCOVERED ON LOWER TAB SURFACE SKIN ADJACENT TO TAB HORN ATTACH RIB. SEE PICTURES ATTACHED.TRIM TAB ASSEMBLY P/N 50-610017-36 REPLACED WITH NEW. ELEVATOR AND TAB ASSEMBLY BALANCED (21.33 IN LBS TAIL HEAVY) AND REINSTALLED. INDEPENDENT CHECK ON R/HSDR CA060530008Line · cracked(CAN) AIRCRAFT HAD TAXIED TO RUN-UP AREA PRIOR TO TAKEOFF. WHILE COMMENCING ENGINE RUN-UP NOTICED THAT THERE WAS NO THROTTLE RESPONSE ON THE RT ENGINE. CREW CONTACTED MAINTENANCE AND REQUESTED A TOW BACK TO THE HANGER. MAINTENANCE FOUND THAT THE FUEL FEED LINESDR CA060531020Engine · malfunctioned(CAN) DURING CLIMB THE ENGINE WAS REPORTED TO EMIT A NOISE AND WAS SHUT DOWN IN FLIGHT. AN EMERGENCY WAS DECLARED AND THE AIRCRAFT DIVERTED. THE AIRFRAME WAS DAMAGED IN THE SUBSEQUENT LANDING (OVERSHOOT). MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CASDR CA060704004Turbine Blades · fractured(CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT. THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING WHICH RESUTED IN AIRFRAME DAMAGE. SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES. P&WC WILL MONITOR INVESTIGSDR CA060509000Skin · worn(CAN) SKIN P/N 50-120156-82 (PRESSURE VESSEL) EXIBITING WEAR MARK ALONG FASTENER ROW ATTACHING FILLET P/N 50-420023-24 TO IT. WEAR MARK NOT READILY VISIBLE WITHOUT PULLING AWAY FILLET FROM SURFACE OF SKIN. WEAR MARK IS CAUSED BY LOOSENING OF FILLET TO SKIN FASSDR DYV2006F00001Bearing · damagedTHE ROLLER BEARINGS HAVE VERY LITTLE SIDE CLEARANCE BETWEEN THE BEARING AND THE FLAP RIBS. AS THE BEARING WEARS SIDE PLAY INCREASES TO THE POINT WHERE THE BEARING FLANGE CONTACTS THE RIB. MDG HAS NOT PROVIDED ANY CHAFE PROTECTION ON THIS SIDE OF THE BEARING,SDR CA060425009Engine · malfunctionedON APPROACH, ENGINE TORQUE AND FUEL FLOW WERE SEEN TO FLUCTUATE. THE ENGINE WAS SUBSEQUENTLY SHUT DOWN IN FLIGHT. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.
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