U/A Canada PT6A-28
Service difficulty reports · 944
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 = 'PT6A28' 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 = 'PT6A28' 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 CA040805010Warning Light · illuminated(CAN) ON START-UP, THE LT FIRE WARNING LIGHT ILLUMINATED BEFORE FUEL WAS INTRODUCED TO THE ENGINE. PILOT ABORTED START. MAINTENANCE CHECKED ALL APPLICABLE SYSTEMS AND FOUND NO FAULTS. NO EVIDENCE OF FIRE WAS FOUND. MULTIPLE STARTS WERE CARRIED OUT AND NO FASDR CA050802004Nut · loose(CAN) AFTER TAKE OFF, THE CREW NOTICED THE LT ENGINE TORQUE WAS OVER RED LINE, POWER WAS REDUCED. MAINTENANCE LATER DISCOVERED THAT PART OF THE LOW PITCH ARM WAS BROKEN OFF. IT WAS DETERMINED THAT THE NUT PN MS21042L4 HOLDING THE PIN PN 100-960036-1 HAD BECSDR CA040816009Bearing · failed(CAN) LT IB WHEEL ASSY INNER BEARING FAILED, ALLOWING WHEEL TO MOVE SUFFICIENT TO ALLOW CONTACT OF THE INNER RIM TO NON ROTATING BRAKE COMPONENTS DAMAGING INNER HALF OF WHEEL ASSY.SDR CA040803008Casting · separated(CAN) ENGINE WAS FOUND SAGGING. UPON INVESTIGATION THE UPPER ENGINE MOUNT WAS FOUND BROKEN OFF. ALL 3 MOUNTS REPLACED AND CHECKED OK NOTE THESE MOUNTS WERE INVOLVED IN A SUDDEN STOPPAGE, 243 HOURS PRIOR.SDR CA040723007Switch · stuck(CAN) ON CLIMB THE PILOT REPORTED THE GEAR IN TRANSIT LIGHT WAS ON. LANDING GEAR WAS EXTENDED WITH NO DIFFICULTIES AND MAINTENNACE WAS CONTACTED. AIRCRAFT RETURNED TO BASE. AIRCRAFT WAS PUT ON JACKS AND THE RT POWER LEVER 70 PERCENT SWITCH WAS FOUND STUCK. SDR CA040719003Relay · intermittentCREWS REPORT THAT DURING CRUISE, THE MAIN ELECTRIC STABILIZER TRIM WOULD NOT TRIM NOSE DOWN. CREW THEN DEACTIVATED THE MAIN TRIM SYSTEM AND ENGAGED STANDBY TRIM SYSTEM. STANDBY SYSTEM FUNCTIONED NORMAL. AIRCRAFT CONTINUED AND LANDED WITH NO FURTHER FAULTS. SDR VDA2004F00000Fan · failedTHE CENTRIFUGAL FAN ASSY CAME APART, SHED ALL THE BLADES. POSSIBLE THAT THE FAN WAS OUT OF BALANCE. POSSIBLE THAT THE FAN WAS THROWN OUT OF BALANCE BY INGESTION OF MATERIAL THROUGH THE AIR RETURN SYSTEM OF THE AIRCRAFT. INSPECTION OF THE VENT RETURN SYSTEM SDR CA040730008Hsi · overheated(CAN) ON CLIMB, BURN ODOR, SMOKE WHERE DETECTED IN COCKPIT. PILOT ADVISED ATC, DIVERTED TO ALTERNATE AIRPORT WHICH HAD VFR CONDITIONS AT TIME. WHILE FLYING INTO HEAVY RAIN, TURBULENT AIR, RT ENG FIRE WARNING LIGHT ILLUMINATED. RT ENG WAS IMMEDIATELY SHUTDOWN.SDR CA040705001Nut · damagedDURING RECTIFICATION OF A SNAG GEAR HANDLE LIGHT STAYING ON WHEN GEAR RETRACTED, A/C JACKED UP AND L/G SWINGS WERE COMPLETED. NOTED THAT LT L/G DOORS WAS HANGING OPEN WITH GEAR RETRACTED. ACT REMOVED DUE TO SUSPICION IT HAD SLIPPED INTERNALLY, CAUSING IT TO SDR CA040608002Torque Tube · out of limits(CAN) DURING THE INSTALLATION OF A NEW ELEVATOR TORQUE TUBE, IT WAS NOTICED THAT ONE OF THE TAPERED PINS WAS INSTALLED BEYOND THE MANUFACTURES LIMITS. THE MM 27-30-00 PAGE 202 A, STATES IN PART THE SMALL END OF THE TAPER PIN BODY SHOULD EXTEND .000 TO 0.060 ISDR CA040604009Adapter · cracked(CAN) DURING A ROUTINE HOT SECTION INSPECTION MAINTENANCE FOUND THE P2.5 BLEED ADAPTER (LOCATED AT APPROXIMATELY 1 O'CLOCK ON THE GAS GENERATOR CASE) WITH OBVIOUS CRACKS. THE RETAINING LUGS WERE BOTH CRACKED AND ONE OF THE ADAPTER WELDING JOINTS WAS CRACKED OSDR CA040528009Fitting · crackedAIRCRAFT HAD NO BRAKES AFTER LANDING ON A GRAVEL AIR STRIP. HYDRAULIC FLUID WAS SEEN LEAKING OUT OF THE BRAKE ASSY. ENGINEER WAS FLOWN OUT AND FOUND THE HYDRAULIC FITTING HAD BEEN HIT WITH A ROCK AND WAS BENT AND CRACKED. FITTING WAS REPLACED AND BRAKE SERVSDR CA040520004Bulkhead · cracked(CAN) MAINTENANCE INSPECTION REVEALED CRACKING IN THE LONGITUDINAL BULKHEADS (BOTH) BEHIND EACH ENGINE. THESE BULKHEADS RUN THE LENGTH OF THE NACELLE, FROM THE FIREWALL TO THE TRAILING EDGE OF THE NACELLE. THE CRACKS ARE PRESENT WHERE THE BULKHEADS NARROW TOSDR CA040517003Fitting · cracked(CAN) DURING A ROUTINE DETAILED INSPECTION, MAINTENANCE DISCOVERED A CRACK IN THE LT UPPER FORWARD WING FITTING OF THE WING CENTER SECTION. NDT, USING LPI AND EDDY CURRENT CONFIRMED THIS AS A CRACK. THIS AIRCRAFT HAS FLOWN 513.9 SINCE LAST NDT IAW MFG SIRM. SDR CA040519013Fitting · cracked(CAN) DURING THE ROUTINE COMPLETION OF CF1981-35 SITES NR 1 AND NR 2, A SMALL CRACK WAS DISCOVERED ON THE LOWER RT, IB BATHTUB FITTING. THE CRACK APPEARED TO START ON THE FEATHERED EDGE AT THE CENTER OF THE RADIUS AND PROPOGATE TOWARD THE MATING SURFACE OF THESDR CA040510007Door Frame · cracked(CAN) DURING A PHASE INSPECTION A CRACK WAS FOUND ON THE CABIN DOOR FRAME, WHICH EXTENDED FROM THE CUT-OUT FOR THE UPPER FWD BAYONETTE TO THE BAYONETTE SUPPORT BRACKET SCREW HOLE.SDR CA040510006Fitting · cracked(CAN) DURING A PHASE INSPECTION THE TAIL CONE WAS BEING REINSTALLED WHEN A CRACK WAS NOTICED ON THE LT TORQUE TUBE. THE CRACK EXTENDS FROM THE TAPER PIN HOLE TO THE EDGE OF THE FITTING. THESE FITTINGS ARE NDT EVERY 1000 HRS AND THIS TUBE WAS DONE AT 142.5 HSDR CA040504004Support Bracket · cracked(CAN) DURING AIRCRAFT INSPECTION, IT WAS NOTED THE AFT RT ELEVATOR BELLCRANK SUPPORT BRACKET P/N 115-524058-13 WAS CRACKED. THE CRACK EXTENDED APPROX. 1.5 INCHES VERTICALLY AROUND THE BELLCRANK PIVOT BOLT ATTACHMENT.SDR CA040428006Aileron · out of rigDURING TROUBLESHOOTING OF A PILOT REPORTED SNAG, THE CONTROL COLUMN IS BANKED SLIGHTLY TO THE LEFT IN ORDER FOR THE AIRCRAFT TO FLIGHT STRAIGHT AND LEVEL, CHECKED THE AILERON RIGGING AND FOUND THAT IF THE PROCEDURES FROM THE MM ARE FOLLOWED THE AIRCRAFT WILL BSDR CA040415006Engine · damagedENG REMOVED AFTER A/C DRIFTED TO LT SIDE OF RWY & HIT A 4 FT SNOWBANK. NLG COLLAPSED & ENG HIT BANK AT MAX PWR. EXHAUST DUCT & GG CASE HAD OUTER SKIN BUCKLING. 2ND STAGE REDUCTION PLANET GEAR CARRIER BENT, PT RUB DAMAGE ON BLADE TIPS. COMP BLADES, STATORS & IMSDR CA040329002Rib · cracked(CAN) ON INSPECTION OF THE HORIZONTAL STABILIZER THE UPPER SKIN WAS FOUND TO BE OIL CANNING. UPON FURTHER INSPECTION IT WAS FOUND THAT 6 RIBS WERE CRACKED INTERNALLY (PN 115-620010-325, 115-620010-210, 115-620010-355, 115-620010-255, 115-620010-215, 115-62001SDR CA040224004Bearing · loose(CAN) ON INSPECTION, THE ROD ENDS WERE FOUND TO BE BADLY WORN ON THE ROD FROM THE START CONTROL TO FUEL CONTROL UNIT.SDR CA040224002Oil System · contaminated(CAN) PILOT REDUCED ENG POWER FOR LANDING AFTER FIRST FLIGHT OF DAY, RT ENGINE PRESSURE DECREASE WAS OBSERVED. TECH DISCOVERED LARGE QUANTITY OF CARBON IN ENGINE OIL FILTER. ENGINE WAS REMOVED AND SENT TO MFG FOR INVESTIGATION. ENGINE WAS DISSEMBLED AT THE SDR CA040209001Blower · seized(CAN) JUST AFTER LEVELING OUT PILOT NOTICED SMOKE IN THE COCKPIT/CABIN AREA. AIRCRAFT WENT TO 10000 FT, DEPRESSURIZED AND ELECTRICAL POWER WAS REMOVED. POWER WAS RESTORED AND AIRCRAFT RETURNED TO BASE WITHOUT FURTHER INCIDENT. UPON INVESTIGATION IT WAS DETERMSDR CA040218007Windshield · cracked(CAN) PILOTS FRONT WINDOW CRACKED ACROSS WINDOW ON OUTER PANE.SDR CA040203010Windshield · cracked(CAN) DURING CRUISE, PILOT HEARD SMALL CRACK SOUND THOUGHT HE DROPPED SOMETHING, WHILE LOOKING AROUND, NOTICED RT WINDSHIELD CRACK DESCENDED AND CARRIED ON. LANDED WITHOUT INCIDENT.SDR CA040104001Fuel Control · failed(CAN) LT ENGINE HAD TO BE SHUT DOWN IN FLIGHT AS FCU THROTTLE ARM WOULD NOT RETURN TO IDLE. DUE TO WEEKEND AND PARTS ON ORDER WE WILL BE REMOVING FCU NEXT WEEK.SDR CA031209005Downlock Switch · broken(CAN) LT MAIN LANDING GEAR NOT INDICATING DOWN AND LOCKED ON APPROACH. AIRCRAFT RETURNED TO BASE. BROKEN WIRE ON DOWN SWITCH FOUND AND REPAIRED. GEAR SWING CARRIED OUT NORMAL FOR TYPE. AIRCRAFT RELEASED FOR RETURN TO SERVICESDR CA031205002Connector · broken(CAN) WHEN REDUCING POWER FOR DESCENT THE PILOT NOTICED A NORMAL REDUCTION IN TORQUE INDICATION, THEN AS POWER FURTHER REDUCED THE TORQUE INDICATION WOULD CLIMB TO REDLINE VALUES. NO OTHER ENGINE PARAMETERS OR AIRCRAFT BEHAVIOR AGREED WITH THIS INDICATION AND SDR CA031203007Bolt · failed(CAN) ON A SIRM INSP OF THE WING BOLTS THE RT FWD UPPER WING BOLT SHOWED REJECTIONABLE INDICATIONS. THE BOLT WAS REPLACED AND A/C RETURNED TO SERVICE.SDR CA031203008Bolt · failed(CAN) ON INSP OF A/C AT SIRM INSP FOUND REJECTIONABLE INDICATIONS ON THE FORWARD UPPER RT WING BOLT. REPLACED AND A/C RETURNED TO SERVICE. PART WAS 9 YEARS OLD.SDR CA031203009Bolt · failed(CAN) ON DOING A SIRM WING BOLT INSP THE FWD UPPER RT WING BOLT SHOWED REJECTIONABLE INDICATIONS. BOLT WAS CHANGED AND RETURNED TO SERVICE. BOLT LIFE WAS 9YEARS.SDR CA031126008Strut · cracked(CAN) AFTER FINDING THE RT MAIN GEAR BRACE CRACKED WE INSPECTED THE LT GEAR AND FOUND A SMALL CRACK AT THE UPPER END OF THE RADIUS OF THE UPPER TORQUE KNEEBOSS. LIQUID PENETRANT WAS REQUIRED TO CONFIRM THE CRACK. IT STARTED AT THE TOP OF RADIUS AND TRAVELED DOSDR CA031127001Brace · cracked(CAN) AFTER FINDING TWO OTHER GEAR BRACES CRACKED (SDR 20031126008, 20031126004) WE INSPECTED THE LT GEAR AND FOUND A POSSIBLE CRACK AT THE UPPER END OF THE RADIUS OF THE UPPER TORQUE KNEEBOSS. LIQUID PENETRANT WAS REQUIRED TO CONFIRM THE CRACK. IT STARTED AT SDR CA031127003Attach Fitting · cracked(CAN) DURING AN UNSCHEDULED INSPECTION A SMALL CRACK WAS FOUND IN THE UPPER FORWARD WING ATTACH FITTING, THE CRACK WAS APPROXIMATELY .0625 OF AN INCH LONG STARTING AT THE TOOLING HOLE HEADING TOWARD THE TUB. THE AIRCRAFT IS GROUNDED WAITING FOR WING SPAR REPLSDR CA031224003Engine · making metal(CAN) ENGINE S/N PCE40252 WAS SENT FOR METAL IN OIL. ENGINE WAS DISSASSEMBLED AND IT WAS FOUND THAT THE NR 2 BEARING ROLLER CAGE SILVER PLATE HAD FLAKED OFF. MFG HAS A SIL NR PT6A-106 ON THIS CONDITION. THIS ENGINE WAS REPAIRED IAW MFG LATEST SPECIFICATIONS ASDR CA031126004Strut · cracked(CAN) AFTER A PILOT REPORTING THE RT MAIN GEAR OLEO WAS LOW, MAINTENANCE ATTEMPTED TO INFLATE THE OLEO WITH NITROGEN. THE NITROGEN IMMEDIATELY STARTED TO LEAK FROM A LARGE CRACK AROUND THE UPPER TORQUE KNEEBOSS ON THE BRACE ASSEMBLY. THE CRACK WAS APPROXIMATELSDR CA031120006Latch · unsecure(CAN) NOTICED BAGGAGE DOOR LITE ON AFTER TAKEOFF, RETURNED TO BASE FOUND LATCH UNDONE. LATCH CLOSED. AIRCRAFT RETURNED TO SERVICE.SDR CA031107014Windshield · broken(CAN) PILOTS REPORTED THAT WHILE CRUISING AT 23 000 FT THEY A HEARD CRACKLING SOUND. SOON AFTER THEY DETECTED THIS SOUND, THE INTERIOR PANE OF THE LEFT WINDSHIELD SHATTERED. HEAT WAS NOT IN USE, AND THE AMBIENT TEMPERATURE WAS -30 C. THE PILOTS IMMEDIATELYSDR CA031105004Lever · cracked(CAN) UPON INSPECTION OF THE REVERSING LEVER GUIDE PIN BRACKET FOR WEAR DURING AN ENGINE BUILD UP IT WAS NOTICED THAT THE BRACKET PLATE THAT THE GUIDE PIN IS WELDED TO WAS CRACKED. THE CRACK WAS ADJACENT TO THE PIN WELD AND ON THE FORWARD SIDE OF THE PLATE. TOSDR CA031028003Pinion Gear · cracked(CAN) DURING GEAR SWING LT HAND MAIN LANDING GEAR WAS SHUTTERING ON RETRACTION. REMOVED ACTUATOR AND REPLACED WITH OVERHAULED PART.TOOK ACTUATOR TO OVER HAUL FACILITY AND DISASSEMBLED AND DISCOVERED DEFECT.SDR CA031022006Counterweight · loose(CAN) ON PRE-FLIGHT INSPECTION, THE LT ELEVATOR WAS MOVED AND A RATTLING NOISE WAS HEARD.FURTHER INSPECTION REVEALED THE INBOARD BALANCE WEIGHT, OUTBOARD BALANCE WEIGHT SUPPORT WAS LOOSE. THE THREE ATTACHING BOLTS PN AN174-6 WERE FOUND BACKEDOUT APPROX. 1/8 INSDR CA031017009Check Valve · failed(CAN) AFTER PILOTS HAD DEPLANED PASSENGERS AND BAGGAGE AT A SCHEDULED STOP THEY NOTICED FUEL COMING OUT OF THE FUEL VENT. MAINTENANCE TOWED THE A/C TO THE HANGER AND DEFUELED THE A/C. THEY FOUND THAT THE ONEWAY VALVE GOING TO THE AUX TANK, SOMETHING HOLDING SDR CA031027004Controller · malfunctioned(CAN) TAKE-OFF WAS REJECTED IN YXY DUE TO AUTO FEATHER FAILING TO ARM ON THE RIGHT SIDE A/C GROUND RUN TESTED-NORMAL-NO FAULT FOUND A/C RELEASED FOR RETURN TO SERVICESDR CA031008001Switch · separated(CAN) RECENTLY BEECH ADDED FIRE EXTINGUISHER ACTIVATION CHECK TO PHASE 2 INSPECTION, UPON COMPLETION THIS INSPECTION, FOUND BOTH LT AND RT FAILED TEST. WITH FURTHER INVESTIGATION WE FOUND THE BACK PART OF THE SWITCHES HAD FALLEN OFF. SWITCH IS A 2 PART SWITCHSDR CA031022008Hinge · loose(CAN) DURING VERTICLE STAB. DE-ICE BOOT REPLACEMENT, IT WAS NOTED THAT THREE OF THE SIX JO-BOLT FASTENERS THAT ATTACH THE UPPER RUDDER HINGE BRACKET TO THE SPAR WERE LOOSE.THESE FASTENERS WERE REPLACED WITH NEW.SDR CA031001004Fuel Tank · contaminated(CAN) WHILE INSPECTING THE INSIDE OF THE BLADDER TANKS FOR LOOSE PATCHES BECAUSE OF LOOSE PATCHES FOUND ON ANOTHER AIRCRAFT. MAINTENANCE FOUND A BABY SLEEPER INSIDE AFT MIDDLE FUEL TANK. THIS AIRCRAFT CAME INTO THE FLEET 3 YEARS AGO AND AS THIS COMPANY DOES SDR CA030915009Pump · failed(CAN) WHILE CLIMBING AFTER TAKEOFF, NOTICED LOSS OF TORQUE AND OIL PRESSURE. SECURED THE LT ENGINE. FAILURE TROUBLE SHOT TO LOSS OF FUEL FLOW. HIGH PRESSURE FUEL PUMP AND FUEL CONTROL UNIT REMOVED AND EXAMINED. FOUND THE INPUT GEAR OF THE PUMP HAD STRIPPED SPLSDR CA030903004Line · blocked(CAN) AIRCRAFT HAD LT ENGINE SHUTDOWN IN FLIGHT. AFTER EXTENSIVE TROUBLESHOOTING FOUND THAT AN INTERNAL PATCH ON FUEL BLADDER HAD COME OFF AND BLOCKED THE LINE TO NACELLE TANK. ALL TANKS WERE INSPECTED AND 2 OTHER TANKS HAD INTERNAL PATCHES. FUEL CELL REPAIRSDR CA030826017Engine · failed(CAN) ENGINE CONTINUED TO BE OPERATED FOR APPROXIMATELY ONE HOUR BEFORE SEIZING TO A STOP, AFTER A 'LOW OIL LEVEL' INDICATOR ILLUMINATED IN THE COCKPIT. ENGINE WAS REMOVED AND SHIPPED TO REPAIR STATION TO REVIEW ENGINE AND DETERMINE REQUIRED WORKSCOPE. ATLANT
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