U/A Canada PT6A-34
Service difficulty reports · 465
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 = 'PT6A34' 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 = 'PT6A34' 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 CA050923007Glide Slope · malfunctionedGLIDESLOPE DEVIATION ON EHSI INVERTED. GLIDESLOPE INFORMATION INTERFACED ON ARINC 429 DATA BUS. EFIS MANUFACTURER ACKNOWLEDGES PROBLEM IS SOFTWARE IN EHSI, AWAITING SOFTWARE FIX FROM MANUFACTURER. DEFECT IS ALSO PRESENT IN EADI WHEN EADI IS IN FORCED COMPOSSDR CA050829001Doubler · cracked(CAN) DURING THE CONTINUING AIRWORTHINESS STRUCTURAL INSPECTION A CRACK WAS FOUND IN THE FLOOR LEVEL DOUBLER FOR THE LT FRAME AT FUSELAGE STATION 207.00, THE CRACK MOVED LATERALLY ACROSS THE DOUBLER FROM THE IB SIDE THOUGH 2 RIVET HOLES AND A BEND. THE PROBABLSDR CA050829003Bulkhead · cracked(CAN) DURING THE CONTINUING AIRWORTHINESS STRUCTURAL INSPECTION CHAFFING DAMAGE WAS FOUND ON THE AFT SIDE OF THE AFT PRESSURE BULKHEAD. THE LOWER CENTER AND THE LOWER RT INTERCOSTALS RUBBING ON THE BULKHEAD DURING PRESSURIZATION CAUSED THE DAMAGE. FURTHER INVESDR CA050823001Support · cracked(CAN) DURING A ROUTINE INSPECTION, MAINTENANCE FOUND A CRACK IN THE RT FLAP ASYMMETRY TELEFLEX CABLE SUPPORT. THIS SUPPORT IS LOCATED ON THE RT FLAP IB SUPPORT AND IS ATTACHING POINT FOR ASYMMETRY DETECTOR TELEFLEX ROD END. FURTHER INVESTIGATION, A SECOND CRACSDR CA050728011Engine · power lossTHE ENGINE WAS REPORTED AS UNABLE TO ACHIEVE REQUIRED TORQUE ON TAKEOFF AND THE TAKEOFF WAS ABORTED. SUBSEQUENT INVESTIGATION WAS REPORTED TO REVEAL COMPRESS OR DAMAGE. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.SDR CA050615005Angle · cracked(CAN) DURING A ROUTINE MAINTENANCE INSPECTION 2 SMALL CRACKS WERE FOUND IN THE LT ELEVATOR TRIM TAB ACTUATOR SUPPORT BRACKET ATTACH POINT AREA. THE CRACKS WERE FOUND IN THE AREA AROUND THE 2 LOWER SUPPORT BRACKET BOLT HOLES. UPON FURTHER INVESTIGATION BOTH THESDR CA050519004Bracket · cracked(CAN) UPON GROUND INSPECTION, THE ELEV TRIM TAB ACTUATOR BRACKET WAS FOUND BROKEN. THE BRACKET WAS REPLACED WITH A NEW AND THE TRIM TAB REINSTALLED AND RIGGED IAW M/M.SDR CA050420003Hinge Bracket · cracked(CAN) DURING A ROUTINE MAINTENANCE INSPECTION, A CRACK WAS FOUND ON THE RUDDER UPPER HINGE BRACKET. THIS BRACKET IS ATTACHED TO THE RUDDER FRONT SPAR AND ATTACHED TO THIS ARE TWO FLANGES FOR THE RUDDER UPPER HINGE BOLT. THE CRACK ON THE BRACKET EXTENDS FROM SDR CA050418013Angle · crackedINSP REVEALED CRACK ON LT ELEVATOR TRIM TAB ACTUATOR SUPPORT BRACKET ATTACH POINT REINFORCING ANGLE. CRACK FOUND AT UPPER LT SUPPORT BRACKET BOLT HOLE AND PROPAGATED TO RIVETS DIRECTLY ADJACENT TO HOLE ON BOTH LT AND RT SIDES. UPON FURTHER INVESTIGATION SMSDR CA050321009Combustion Liner · cracked(CAN) 3 INCH BURN THROUGH INNER LINER IN COMBUSTION AREA. ONE SMALL PINHOLE THROUGH PRIMARY SHROUD OR CAP. THE CAP ON THE AFT FACE OF THE UNIT HAD CRACKED ABOUT 120 DEGREES AROUND THE CIRCUMFERENCE. THE BURN THROUGH WAS VISIBLE WITH THE BOROSCOPE INSPECTION SDR CA050309012Duct · cracked(CAN) AT EXHAUST PORT, THE FLANGE THAT PROTRUDES OUT OF THE CASE TO PREVENT EXHAUST GASES FROM EXITING THROUGH THE FLANGE WHERE THE EXHAUST STACK BOLTS ON, WAS CRACKED ABOUT 320 DEGREES AROUND THE CIRCUMFERENCE. THE OPPOSITE PORT WAS DETERMINED TO BE CRACKED TSDR 2005FA0000360Heater · leakingPILOT OBSERVED FLUCTUATING OIL PSI (100-70PSI) BROUGHT POWER BACK TO 200 LBS. TQ AND OIL PSI DROPPED TO 50 PSI. PILOT FEATHERED AND SHUTDOWN EFFECTED ENGINE. AFTER MECH INVESTIGATED THE PROBLEM, FOUND THAT FUEL HAD MIXED WITH THE OIL SUPPLY AND DILUTED IT TOSDR CA050208004Cable · broken(CAN) CABLE BROKE IN THE FORWARD BAY WHERE IT CHANGES DIRECTION. ADDITIONAL NOTE, INSPECTION IN THIS AREA IS ONLY POSSIBLE WITH MIRROR.SDR CA050207002Governor · uncontrollable(CAN) THE AIRCRAFT WAS IN ENROUTE, WHEN THE RT ENGINE PROPELLER RPM DROPPED, UNCOMMANDED, TO 80 PERCENT. THE PROPELLER RPM COULD NOT BE CONTROLLED, NOR COULD THE PROPELLER BE FEATHERED, AND THE RT ENGINE WAS SHUTDOWN AS A PRECAUTION. THE AIRCRAFT RETURNED TOSDR CA050221008Governor · malfunctioned(CAN) DURING FLIGHT, THE PROPELLER SPEED DECREASED TO 80 PERCENT UNCOMMANDED. THE CREW COULD NOT MODULATE THE PROPELLER SPEED AND SHUT THE ENGINE DOWN IN FLIGHT. THE PROPELLER GOVERNOR WAS SUBSEQUENTLY REPLACED.SDR CA041215001Exhaust Duct · cracked(CAN) DURING ROUTINE MAINTENANCE 2 CRACKS WERE FOUND ON THE STARBOARD ENGINE EXHAUSTDUCT. THE CRACKS WERE LOCATED APPROXIMATELY 1.250 INCHES AFT OF THE REDUCTION GEARBOX MOUNTING FLANGE BETWEEN THE 10 AND 11:30 CLOCK POSITIONS. THE ORIGIN APPEARED TO BE FROM TSDR CA041221002Combust Chamber · cracked(CAN) DURING CLIMB THE ENG EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY AUTO-FEATHER. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A FRACTURED COMBUSTOR SMALL EXIT DUCT AND ASSOCIATED CT BLADE AND VANE DAMAGE.SDR CA041210002Latch · inoperative(CAN) NEW PART, DISCOVERED AT INSTALLATION. DOES NOT LATCH. THE SPRING WHICH POSITIVELY PUSHES THE LATCH TO THE LOCK POSITION IS MISSING.SDR CA050117010Engine · failed(CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN UNDER UNKNOWN CIRCUMSTANCES. SUBSEQUENT DISASSEMBLY REVEALED A SEIZED COMPRESSOR ROTOR AND METAL DEBRIS IN THE ENGINE OIL FILTER AND CHIP DETECTOR. MFG WILL MONITOR THE INVESTIGATION OF TSDR BQT2004F00000Display · failedFLIGHT WITH CARGO ON BOARD, PILOT SAID RADAR SCREEN WENT BLANK. SHORTLY AFTER HE SAID THE COCKPIT STARTED TO FILL UP WITH SMOKE. RADIOED TOWER AND DIVERTED FROM INTENDED DESTINATION TO CLOSEST AIRPORT. LANDED WITHOUT INCIDENT WITH THE LOCAL FIRE DEPT STANDISDR CA041029003Engine · failed(CAN) AN OIL PRESSURE FLUCTUATION WAS OBSERVED IN FLIGHT FOLLOWED BY A LOUD NOISE ACCOMPANIED BY A LOSS-OF-GENERATOR AND FIRE INDICATION. THE ENGINE WAS SECURED IN-FIGHT AND THE FIRE WARNING ABATED. A SINGLE-ENGINE LANDING PERFORMED. SUBSEQUENT INSPECTION RSDR CA040813005Arm · missing(CAN) THE AIRCRAFT WAS UNDERGOING A GENERAL INSPECTION MAINTANCE OBSERVED THE VIKING AIR FLUTTER PREVENTION MODIFICATION RUDDER TRIM TAB ARM WAS MISSING THE AIRCRAFT HAD BEEN INSPECETED SOME 50.0 HOURS EARLER WITH NO DEFECTS NOTEDSDR CA040827006Bolt · loose(CAN) ON A WALK AROUND INSPECTION ONE OF FOUR BOLTS FOR THE OB LT FLAP DEFECTER WAS FOUND TO HAVE BACKED OFF.SDR CA040708007Engine · failedDURING CRUISE FLIGHT, THE CREW OBSERVED THE LT ENGINE T5 TEMPERATURE STARTING TOFLUCTUATE FOLLOWED BY A COMPLETE LOSS OF T5 TEMPERATURE INDICATION. ONCE ON THE GROUND, DURING A TROUBLESHOOTING MAINTENANCE RUN, IT WAS ALSO OBSERVED THAT THE ENGINE WAS MAKING ASDR CA040514002Bracket · cracked(CAN) DURING AIRCRAFT DI BY MAINTENANCE THE ELEVATOR TRIM TAB WAS FOUND TO HAVE EXCESSIVE PLAY. INVESTIGATION REVEALED THE ATTACH BRACKET FOR THE TRIM TAB ACTUATOR WAS CRACKED AND THE ACTUATOR BRACKET WAS MOVING WITH THE ACTUATOR ALLOWING THE EXCESSIVE PLAY INSDR CA040309005Lock Pin · wrong part(CAN) INCORRECT PART DISCOVERED DURING SEAT INSPECTION THE PROPER SEAT LOCK PIN HAD BEEN REPLACED BY A GROUND DOWN A/N BOLTSDR AUS20040149Pump · failed(AUS) RT HYDRAULIC PUMP FAILED. INVESTIGATION FOUND A FINE BROWN COATING OVER THE SURFACE OF THE PUMP. SUSPECT PUMP OVERHEATED.SDR CA040219005Control Column · cracked(CAN) CONTROL COLUMN FOUND CRACKED IN THREE LOCATIONS WHEN SB 3/39 CW.SDR CA040203007Ground Wire · failed(CAN) ON STARTING THE ENGINE THERE WAS ARCING AND SPARKS COMING FROM THE STARTER GROUND ATTACHMENT LOCATED UNDERNEATH THE COCKPIT. THE SPARKS CAME FROM THE GROUNDING ATTACHMENT BOLT ANCHOR NUT RIVET. RECOMMEND A BETTER GROUNDING LOCATION AND ATTACHMENT.SDR CA031205007Strut · corroded(CAN) WING STRUT WAS REMOVED TO INSPECT/REPAIR SLOPPY STRUT ATACHMENT CONDITION. UPON REMOVING STRUT ASSEMBLY, LUG FACES (FORWARD/AFT) FOUND CORRODED. REF. PSM 1-3-3 FIG 2-1 (DHC-3 REPAIR MANUAL).SDR CA031016001Line · ruptured(CAN) WHILE CARRYING OUT MAINTENANCE IN THE ACCESSORY SECTION AREA OF THE LT ENGINE (PT6A-34) A STRONG FUEL SMELL WAS NOTICED BY MAINTENANCE. A FURTHER INVESTIGATION REVEALED THAT WITH THE AIRFRAME FUEL BOOST PUMPS SELECTED ON THAT THERE WAS FUEL SPRAYING FROSDR CA031014005Control Rod · cracked(CAN) DURING ROUTINE INSPECTION THE FLAP CONTROL ROD (TUNING FORK) WAS FOUND TO HAVE A .70 INCH CRACK RUNNING LENGTHWISE FROM THE THREADED END OF THE ROD.SDR CA030910009Actuator · noisy(CAN) DURING LANDING GEAR EXTENSION THE NOSE GEAR ACTUATOR MADE A LOAD SCREECH NOISE. THE ACTUATOR WAS REPLACED AND THE GEAR SWINGS PERFORMED NORMALLY.SDR CA030716006Strut · cracked(CAN) CRACKED TRAILING EDGE SKIN APROX 9 INCHES LONG AT LOWER END OF STRUT ON THE BOTTOM SIDE.SDR CA030711005Strut · cracked(CAN) DURING A ROUTINE DAILY INSPECTION A 7 INCH CRACK ON THE UPPER SURFACE OF THE LT LOWER WING STRUT IN THE TRAILING EDGE SKIN WAS OBSERVED. 4.2 HOURS OUT OF A 100 HR INSPECTION. THE STRUT WAS GIVEN TO A DAR, WHO IS CONDUCTING AN INVESTIGATION. THE REPORT SSDR CA030609003Chip Detector · cracked(CAN) DURING INSPECTION OF MAGNETIC PLUG, A STRESS CRACK WAS FOUND AT THE BASE OF THE PLUG. UNIT WAS REMOVED FROM SERVICE.SDR CA030505007Spar · cracked(CAN) DURING CHANGE OVER TO FLOATS, CRACKS WERE OBSERVED UNDER THE FORWARD ATTACHMENT POINT. NEW SPAR MANUFACTURED. NO PARTS AVAILABLE FROM MANUFACTURE.SDR CA030505008Spar · cracked(CAN) DURING CHANGE OVER CRACKS WERE OBSERVED UNDER THE FORWARD ATTACHMENT POINT. NEW SPAR MANUFACTURED. NO PARTS AVAILABLE FROM MANUFACTURE.SDR CA030505009Spar · cracked(CAN) DURING CHANGE OVER CRACKS WERE OBSERVED UNDER THE AFT ATTACHMENT POINT. NEW SPAR MANUFACTURED. NO PARTS AVAILABLE FROM MANUFACTURE. POOR PRODUCT SUPPORT.SDR 2003FA0000499Lock Plate · distortedLOCKPLATE WAS DISTORTED AND FAILED TO RETAIN FUEL TRANSFER TUBE IN THE FUEL MANIFOLD ADAPTER. RESULTING, FUEL LEAK CAUSE POWER LOSS/ EMERGENCY LANDING/ CRASH. RECOMMEND LOCKPLATES ARE INSPECTED FOR PROPER SEATING IN TRANSFER TUBES AT 100 HOUR ANNUAL INSPECTISDR YEB2003F00000Slip Ring · failedINSTALLED NEW STANDBY ALTERNATOR MANUFACTURED. ALTERNATOR FAILED AFTER 8.1 HOURS TIME IN SERVICE. TEARDOWN INSPECTION REVEALED THAT THE CARBON BRUSH IN THE AFT POSITION WAS COMPLETELY WORN OUT AND THE BRUSH SPRING HAD WRAPPED AROUND THE SLIP RING AND SHAFT SDR CA030318004Spar · cracked(CAN) 6 CRACKS BETWEEN RIVETS ON VERTICAL FLANGES. BETWEEN WING STA. 35.15 AND 60.0 CRACKS VISUALLY DISCOVERED - CONFIRMED NDT.SDR CA030318014Actuator · failed(CAN) SHIMMY WHEN TAXIING & NECESSARY TO CENTRE THE NOSE GEAR MANUALLY IN ORDER TO GET THE GEARS TO RETRACT ON TAKEOFF. AFTER INVESTIGATION IN COLLABORATION WITH THE O/H FACILITY (THE GEAR WAS FRESHLY O/H), WE FOUND THAT IN THE NOSE STEERING RACK ACTUATOR, BSDR ZKG2003F00002Bellcrank · brokenPILOT REPORTED A ROLL OF THE AIRCRAFT WHEN THE FLAPS WERE SELECTED DOWN, INSPECTION FOUND LEFT FLAP BELLCRANK BROKEN. THE FAILED PART WAS PREVOUSLY INSPECTED IAW MFG SB 1062 AND FOUND TO BE IN COMPLIANCE. THE BRAKE WAS NOT IN THE AREA OF INSPECTION OF THE SB.SDR CA030120007Starter Gen · failed(CAN) DURING A ROUTINE MAINTENANCE INSPECTION IN THE AREA AT THE REAR OF THE RT ENGINE COMPARTMENT IT WAS NOTICED THAT THERE WAS AN ABUNDANCE OF METALLIC DUST IN THE AREA SURROUNDING THE REAR OF THE STARTER GENERATOR. A THOROUGH INVESTIGATION REVEALED THE DUSTSDR CA030113005Spline Adapter · cracked(CAN) DURING INSPECTION, THE TRAILING EDGE SPLINE ON THE ELEVATORS, THE SPLINES WERE FOUND CRACKED AT SEVERAL LOCATIONS, THIS IS THE 7TH SDR REGARDING THESE SPLINES AND A TOTAL OF 11 SPLINES FOUND CRACKED. THE ELEVATORS WERE REPLACED AND THE AIRCRAFT RETURNED SDR CA030318012Strut · broken(CAN) SHIMMY FROM NOSE GEAR WHEN TAXIING. AFTER DISASSEMBLING THE NLG OLEO STRUT ASSEMBLY, IT HAD BEEN FOUND BROKEN. (THE THREADED SECTION AT THE TOP WHERE NUT P/N 15134 SCREW ON.)CORRECTION: REPLACING NOSE GEAR ASSEMBLY FIXED THE PROBLEM. NO CAUSE HAVE BEEN SDR CA021115006Attach Angle · worn(CAN) DURING A SCHEDULED INSPECTION EVENT EXCESSIVE WEAR WAS NOTED AROUND THE BOLT HOLE OF THE UPPER RUDDER ATTACH BRACKET. THE RIVETS SECURING THE BUSHING BOSS IN THE BRACKET WERE ALSO WORKING.THE RUDDER ATTACH BRACKET ASSEMBLY PART NUMBER 4A-3441 WAS REPLACESDR CA021105007Starter Gen · failed(CAN) STARTER/GENERATOR SHAFT SHEARED WHILE MOTORING THE RT ENGINE FOR START. THE SHAFT BROKE AT 1/8 INCH BELOW THE SPLINE. INSTALLED NEW STARTER/GENERATOR ON RT ENGINE. GROUND RUN SERVICEABLE. AIRCRAFT RETURNED TO SERVICE.SDR CA021030006Wheel · fractured(CAN) INNER WHEEL HALF BEAD SEAT FAILED AROUND APPROXIMATELY HALF THE CIRCUMFRENCE OF THE WHEEL DURING LANDING PHASE. WHEEL WAS REPLACED AND NO OTHER DAMAGE REPORTED OR FOUND.
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