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.

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 COMPOSSep 13, 2005 · Dhav DHC6300 · Flight Management Computing Software SystemSDR 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 PROBABLAug 25, 2005 · Beech A100 · Fuselage Main, FrameSDR 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 INVEAug 25, 2005 · Beech A100 · Fuselage Main, BulkheadSDR 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 CRACAug 22, 2005 · Emb EMB110P1 · Trailing Edge FlapsSDR 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.Jul 22, 2005 · Emb EMB110* · Turbine Engine Compressor SectionSDR 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 THEJun 12, 2005 · Emb EMB110P1 · Elevator Tab, Attach FittingsSDR 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.May 10, 2005 · Emb EMB110* · Elevator, Tab StructureSDR 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 Apr 18, 2005 · Emb EMB110P1 · Rudder StructureSDR 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 SMApr 15, 2005 · Emb EMB110P1 · Elevator Miscellaneous StructureSDR 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 Mar 19, 2005 · Dhav DHC3 · Turbine Engine Combustion SectionSDR 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 TMar 6, 2005 · Dhav DHC3 · Engine Collector/Tailpipe/NozzleSDR 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 TOFeb 24, 2005 · N83BA · Emb EMB110P1 · Fuel HeaterSDR CA050208004Cable · broken(CAN) CABLE BROKE IN THE FORWARD BAY WHERE IT CHANGES DIRECTION. ADDITIONAL NOTE, INSPECTION IN THIS AREA IS ONLY POSSIBLE WITH MIRROR.Feb 4, 2005 · Dhav DHC3 · Landing Gear Steering SystemSDR 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 TOFeb 2, 2005 · Emb EMB110P1 · Propeller GovernorSDR 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.Feb 2, 2005 · Emb EMB110P1 · Propeller GovernorSDR 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 TDec 14, 2004 · Emb EMB110P1 · Engine Collector/Tailpipe/NozzleSDR 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.Dec 13, 2004 · Emb EMB110* · Turbine Engine Combustion SectionSDR CA041210002Latch · inoperative(CAN) NEW PART, DISCOVERED AT INSTALLATION. DOES NOT LATCH. THE SPRING WHICH POSITIVELY PUSHES THE LATCH TO THE LOCK POSITION IS MISSING.Dec 9, 2004 · Dhav DHC3 · Emergency EquipmentSDR 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 TDec 4, 2004 · Emb EMB110* · Engine (Turbine/Turboprop)SDR 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 STANDISep 10, 2004 · N49BA · Emb EMB110P1 · Weather Radar SystemSDR 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 RSep 10, 2004 · Emb EMB110* · Engine (Turbine/Turboprop)SDR 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 NOTEDAug 13, 2004 · Dhav DHC3 · Elevator Tab Control SystemSDR CA040827006Bolt · loose(CAN) ON A WALK AROUND INSPECTION ONE OF FOUR BOLTS FOR THE OB LT FLAP DEFECTER WAS FOUND TO HAVE BACKED OFF.Jul 9, 2004 · Emb EMB110P1 · Trailing Edge FlapsSDR 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 AJul 6, 2004 · Emb EMB110P1 · Engine (Turbine/Turboprop)SDR 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 INMay 10, 2004 · Emb EMB110* · Elevator Tab Control SystemSDR 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 BOLTMar 9, 2004 · Dhav DHC3 · Passenger Compartment EquipmentSDR AUS20040149Pump · failed(AUS) RT HYDRAULIC PUMP FAILED. INVESTIGATION FOUND A FINE BROWN COATING OVER THE SURFACE OF THE PUMP. SUSPECT PUMP OVERHEATED.Mar 2, 2004 · Gulstm G73 · Hydraulic Pump (Electric/Engine), MainSDR CA040219005Control Column · cracked(CAN) CONTROL COLUMN FOUND CRACKED IN THREE LOCATIONS WHEN SB 3/39 CW.Jan 29, 2004 · Dhav DHC3 · Control Column SectionSDR 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.Jan 22, 2004 · Dhav DHC3 · Starter-GeneratorSDR 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).Dec 1, 2003 · Dhav DHC3 · Wing Main, Frame StructureSDR 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 FROOct 15, 2003 · Emb EMB110P1 · Engine Fuel DistributionSDR 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.Oct 3, 2003 · Dhav DHC3 · Trailing Edge Flap Control SystemSDR 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.Sep 8, 2003 · Beech A100 · Landing Gear ActuatorSDR CA030716006Strut · cracked(CAN) CRACKED TRAILING EDGE SKIN APROX 9 INCHES LONG AT LOWER END OF STRUT ON THE BOTTOM SIDE.Jul 13, 2003 · Dhav DHC3 · Wing, Attach FittingsSDR 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 SJul 2, 2003 · Dhav DHC3 · Wing, Attach FittingsSDR 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.Jun 6, 2003 · Dhav DHC6300 · Engine Oil Indicating SystemSDR CA030505007Spar · cracked(CAN) DURING CHANGE OVER TO FLOATS, CRACKS WERE OBSERVED UNDER THE FORWARD ATTACHMENT POINT. NEW SPAR MANUFACTURED. NO PARTS AVAILABLE FROM MANUFACTURE.May 5, 2003 · Dhav DHC6300 · Vertical Stabilizer Miscellaneous StructureSDR CA030505008Spar · cracked(CAN) DURING CHANGE OVER CRACKS WERE OBSERVED UNDER THE FORWARD ATTACHMENT POINT. NEW SPAR MANUFACTURED. NO PARTS AVAILABLE FROM MANUFACTURE.May 5, 2003 · Dhav DHC6300 · Vertical Stabilizer Miscellaneous StructureSDR 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.May 5, 2003 · Dhav DHC6300 · Vertical Stabilizer, Spar/RibSDR 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 INSPECTIApr 17, 2003 · Engine Fuel DistributionSDR 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 Apr 1, 2003 · N881DB · Piper PA46350P · AC Generator-AlternatorSDR CA030318004Spar · cracked(CAN) 6 CRACKS BETWEEN RIVETS ON VERTICAL FLANGES. BETWEEN WING STA. 35.15 AND 60.0 CRACKS VISUALLY DISCOVERED - CONFIRMED NDT.Mar 11, 2003 · Dhav DHC6300 · Wing SparSDR 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, BMar 6, 2003 · Emb EMB110P1 · Nose/Tail Landing Gear Strut/AxleSDR 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.Feb 24, 2003 · N9100Z · Piper PA46310P · Trailing Edge Flap Control SystemSDR 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 DUSTJan 17, 2003 · Emb EMB110P1 · Starter-GeneratorSDR 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 Jan 10, 2003 · Beech A100 · Elevator StructureSDR 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 Nov 20, 2002 · Emb EMB110P1 · Nose/Tail Landing Gear Strut/AxleSDR 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 REPLACENov 13, 2002 · Emb EMB110P1 · Rudder/Tab, Attach FittingsSDR 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.Oct 30, 2002 · Emb EMB110P1 · Starter-GeneratorSDR 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.Oct 28, 2002 · Emb EMB110* · Wheel/Ski/Float
Back to U/A Canada PT6A-34