Piper PA-46-310P
Service difficulty reports · 119
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 aircraft_model_key = 'PA46310P' 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 aircraft_model_key = 'PA46310P' 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 2025FA0000670Pump · leakingDURING A PLANNED FLIGHT FROM FORT WORTH MEACHAM (KFTW) TO KENOSHA, WI (KENW), THE PILOT OF A PIPER PA-46-310P MALIBU EXPERIENCED A FUEL SYSTEM ANOMALY. APPROXIMATELY 3 HOURS INTO THE FLIGHT AT FL230, THE PILOT OBSERVED THE INDICATED FUEL QUANTITY DECREASING THSDR 2015FA0000604Selector Valve · failedPILOT REPORTED LANDING GEAR WOULD NOT EXTEND. TROUBLESHOT, FOUND THAT THE HYDRAULIC POWERPACK WOULD CYCLE 5 TIMES, THEN SHUTOFF. ACCORDING TO THE MM THIS IS NORMAL AND IF THIS HAPPENS THE PILOT MUST RESET THE HYD POWERPACK CIRCUIT BREAKER AS THE SYSTEM HAS ASDR DGCA2015042800163Exhaust Pipe · brokenPILOT STATED LOSS OF PRESSURIZATION AND DECREASED MANIFOLD PRESSURE. EXHAUST PIPE BROKEN.SDR 2014FA0000662Lock Nut · detachedTHE LOCKNUT ON THE TURBO COMPRESSOR SHAFT CAME OFF. THE NUT CAUSED DAMAGE TO THE COMPRESSOR FAN BLADES. THE INTER-COOLER WAS REPLACED AS A PRECAUTIONARY MEASURE AFTER IT INGESTED FRAGMENTS FROM THE FAN BLADE AND NUT.SDR H6MR2014121745546Cylinder · separatedAFTER TAKEOFF ACFT WAS CLIMBING THROUGH 8000' WHEN OWNER/PILOT EXPERIENCED A "POP" FOLLOWED BY IMMEDIATE ENGINE ROUGHNESS. PILOT REDUCED POWER AND RETURNED TO DEPARTURE. AFTER SAFE RETURN AND TAXI TO AIRPORT RAMP, PILOT NOTICED A SIGNIFICANT AMOUNT OF OIL COSDR C41R2014071500001Rib · crackedACFT WAS UNDERGOING AN ANNUAL INSPECTION AND SEVERAL RIVETS ON THE BOTTOM OF THE LT AND RT WING WERE FOUND SEEPING FUEL. ACFT WAS DEFUELED AND TANK SEALANT REMOVED FROM AFFECTED RIVETS. AFTER CLEANING AFFECTED AREA SEVERAL CRACKS WERE DISCOVERED IN ATTACHMENTSDR CA140630009Unknown · unknown(CAN) THE ACFT WAS CRUISING AT FL270 AND APPARENTLY DEVIATED FROM ITS ROUTE WHILE IN COMMUNICATION WITH ATC. THE AIRCRAFT THEN CRASHED IN AN OPEN FIELD. SEVERE WEATHER CONDITIONS PREVAILED AT THE TIME. OPEN.SDR C41R201307030001O-Ring · missingTROUBLESHOT ENGINE OIL CONSUMPTION AND LEAKAGE. FOUND OIL LEAK AFTER NUMEROUS ATTEMPTS TO NARROW OIL LEAK TO A CENTRAL LOCATION. DISCOVERED OIL LEAKING FROM AIR CONDITIONER COMPRESSOR ACCESSORY DRIVE PULLEY SHAFT. REMOVED DRIVE PULLEY AND GARLOCK SEAL AND DISCSDR 2013FA0000131Controller · malfunctionedDURING CLIMB, THE PILOT REPORTED A LOSS OF TURBOCHARGING AND CABIN PRESSURIZATION. TROUBLESHOOTING REVEALED THE TURBO CONTROLLER HAD FAILED. THIS WAS THE 4TH FAILED TURBO CONTROLLER IN 12 MONTHS AND APPROX 165 HRS SMOH. THE TURBO CONTROLLER DELIVERED WITH SDR C41R201201240101Master Cylinder · damagedON LANDING ROLLOUT, PILOT HAD NO LT BRAKE. MX REMOVED LT MASTER CYLINDER AND DISCOVERED MASTER CYLINDER END GLAND HAD UNSCREWED ALL BUT 2 THREADS CAUSING FLUID AND PRESSURE LOSS FROM MASTER CYLINDER. REPLACED INTERNAL SEALS AND REASSEMBLED. REINSTALLED AND SDR CA110830005Engine · power loss(CAN) ON AUGUST 6, 2011 AT APPROXIMATELY 1700 EDT, THE ABOVE REFERENCED AIRCRAFT EXPERIENCED A LOSS IN ENGINE POWER SOON AFTER TAKEOFF. THE PILOT REPORTED WHILE TURNING CROSSWIND AT APPROXIMATELY 1,100 FEET ABOVE GROUND HE HEARD A PITCH CHANGE IN THE ENGINE. TSDR CA100819009Mount · crackedCRACK DETECTED IN ENGINE MOUNT ON JCAB REGISTERED ACFT. ENGINE MOUNT SWAPPED FOR MOUNT MODIFIED AND REINFORCED WITH TCCA RDC C-RA03-047. NOTE: ENGINE MOUNT REMOVED FROM ACFT WAS PREVIOUSLY STRENGTHENED WITH FAA-STC SA02779AT. ALTHOUGH COLLAPSE UNLIKELY WITH SDR CA100812019Mount · cracked(CAN) ENGINE MOUNT DETECTED CRACKED BY AMO SENT IN FOR REPAIR. TWO PIECE FOOT STYLE MOUNT WITH CRACK IN TUBES ABOVE MLG ACTUATOR. ENGINE MOUNT WILL BE REPAIRED AND REINFORCED USING TCCA RDC C-RA03-047. THIS IS THE 33RD ENGINE MOUNT THROUGH THE SHOP WITH THISSDR CA100809010Mount · cracked(CAN) ENGINE MOUNT CRACKED AT 2 PIECE ATTACH FOOTING. CRACK IDENTIFIED BY VISUAL INSPECTION AS PER SB1103C. THIS IS THE 31ST ENGINE MOUNT WITH SUCH FAILURE THROUGH THE SHOP. ENGINE MOUNT WILL BE REPAIRED AND RE-INFORCED USING TCCA RDC C-RA03-047. FAILURE TSDR CA100809011Mount · cracked(CAN) CRACK AND CORROSION LEADING TO TUBE DETERIORATION IMMEDIATELY ABOVE THE LANDING GEAR ACTUATOR ATTACHEMENT POINT. NOTE: THIS IS THE "ONE PIECE" STYLE FOOT AS IDENTIFIED BY PIPER SB 1103C. THIS ENGINE MOUNT WAS EXCHANGED WITH STOCK UNIT REPAIRED AND STRENGSDR CA100809013Mount · broken(CAN) CUSTOMER MOUNT WAS SENT IN WITH CRACK IN LANDING GEAR ATTACHMENT. THIS IS THE 29TH ENGINE MOUNT WITH THIS DEFECT TO COME THROUGH OUR SHOP. REPLACEMENT ENGINE MOUNT WAS PROVIDED WITH STRENGTHENED ACTUATOR ATTACH FITTING INSTALLED AS PER RDC C-RA03-047. SDR 2009FA0000907Tube · deterioratedTHE TUBING COVERING THE FUEL QUANTITY WIRING INSIDE THE WING HAS DETERIORATED. SOME SMALL PIECES WERE FOUND NEAR THE WING STRAINERS. THE CONDITION WAS FIRST DISCOVERED LOOKING THROUGH THE FUEL FILL PORT. ADDITIONALLY THE MFG CALLS OUT FOR INSPECTING THE FUELSDR CA090505001Hinge Bracket · loose(CAN) AS PART OF A 500 HR AILERON BEARING INSP, IT WAS NOTICED THAT THE AILERON HINGES WERE LOOSE WHERE THEY ATTACHED TO THE BRACKETS THAT ATTACHED THEM TO THE WING. THE RIVETS HAD LOOSENED UP OVER TIME AND ALLOWED THE HINGE TO MOVE SLIGHTLY IN ATTACH BRACKETSSDR CA090310009Rod Bearing · broken(CAN) ENG RECEIVED FOR CYL CHANGE, FOUND CAMSHAFT WITH SOME PITS. ON DISASSEMBLY OF ENG TO REPAIR CAMSHAFT FOUND NR 4 CONNECTING ROD BRG SHELL ON ROD END SPLIT IN HALF. OTHER CONNECTING ROD BRG WERE ALSO SHOWING SIGNS OF WEAR. TSN APPROX 1400 HOURS NORMAL TBSDR 2008FA0000097Crankshaft · brokenCRANKSHAFT BROKE JUST AFT OF PROPELLER MOUNTNG FLANGE. (K)SDR 2007FA0000948Centering Mech · failedUPON TOUCHDOWN AIRCRAFT VEERED LT ABRUPTLY AND DEPARTED RUNWAY SURFACE. GEAR EXTENSION AND INDICATION WERE NORMAL. INVESTIGATION REVEALED THAT UPON TOUCHDOWN THE NOSE LANDING GEAR HAD FAILED TO CENTER CORRECTLY DURING EXTENSION.SDR R019692Rod · wornTHE AREA OF THE PITCH CHANGE ROD THAT IS GUIDED THROUGH THE ENGINE SIDE HUB HALF BORE HAS WORN THROUGH THE CHROME PLATING BEFORE FIRST OVERHAUL.SDR 2005FA0001045Collector Ring · defectiveTHIS IS THE COLLECTOR THAT MOUNTS TO THE TOP OF THE LT TURBO. FOUND HOLES ON BOTH SIDES OF WELDS ON THE AFT END NEAR THE SMALL BALANCE TUBE. (K)SDR 2005FA0001011Points · brokenCONTACT SPRING BROKNE IN 311.1 HOURS OF OPERATION. (K)SDR 2005FA0001010Points · brokenCONTACT SPRING BROKEN IN 300.7 HRS OF OPERATION. (K)SDR CA040326006Mount · cracked(CAN) ENGINE MOUNT CRACKED AT AREA DESCRIBED IN MFG SB NR 1103 REV.B NOTE: THIS SHOULD BE NOTIFIED TO ALL OWNERS BY AN AIRWORTHINESS DIRECTIVE.SDR 2004FA0000052Fitting · looseDURING A RECENT INSPECTION IT WAS NOTED THAT THE LOCK FASTENERS SECURING THE STEEL LOWER ENGINE MOUNT ATTACH FITTINGS, INBOARD AND OUTBOARD, TO THE FUSELAGE WERE EXTREMELY LOOSE. ALL OF THE LOCK FASTENERS WERE CHANGED TO THE NEXT SIZE UP. ACCESS TO AREA MAKES SDR 2004FA0000051Fastener · looseDURING A RECENT INSPECTION IT WAS NOTED THAT ALL OF THE LOCK FASTENERS THAT SECURE THE STEEL ATTACH FITTINGS TO THE AIRFRAME FOR THE ENGINE MOUNT LOWER ATTACH POINTS WERE VERY LOOSE (COULD BE TURNED BY HAND). ACCESS TO THE AREA MAKES IT DIFFICULT TO INSPECT. SDR CA030828002Exhaust Valve · broken(CAN) CRUISING AT 25,000 FT, MANIFOLD PRESS DROPPED BY 5 INCHES, DID NOT RECOVER UNTIL BELOW 10,000 FT. MAINT CHECKS ON GROUND DETERMINED NO (ZERO) COMPRESS ON NR 6 CYL UPON REMOVAL OF CYL EXHAUST VALVE WAS DISCOVERED TO HAVE .2500 OF VALVE FACE MISSING. PIECESDR AUS20030446Crankshaft · cracked(AUS) CRANKSHAFT CRACKED RADIALLY IN AREA LOCATED BEHIND THE PROPELLER FLANGE. CRACK LENGTH APPROXIMATELY 50.8MM (2IN).SDR SL52003F00000Exhaust Gate · crackedDURING MAINTENANCE, CHECKING EXHAUST FOR POSSIBLE LEAKS, FOUND RIGHT HAND EXHAUST TEE ABOVE RIGHT TURBOCHARGER CRACKED HALF WAY AROUND, THE CRACK IS NOT VISIBLE FROM OUTSIDE AND WAS FOUND BY PRESSURIZING EXHAUST AND SOAP AND WATER.SDR 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 2002FA0001379Collar · looseLEFT WING REAR ATTACH FITTING COLLAR FOUND IN RECESS BELOW FITTING. RIVET LOOSE IN HOLE. REPLACED WITH OVERSIZE FASTENER AND TORQUED COLLAR. DISCOVERED DURING ALTERATION FOR ENGINE INSTALLATION.SDR ECWR200201Screen · failedINDUCTION AIR FILTER METAL PROTECTIVE SCREEN FAILED AND THE METAL FROM THE SCREEN WAS INDUCTED INTO THE TURBOCHARGER ASSEMBLY AND INTAKE AIR OF THE ENGINE. THE ENGINE OIL FILTER WAS REMOVED AND IT WAS DISCOVERED TO HAVE MAJOR METALLIC CONTAMINATION AS A RESULSDR 200202Relay · chafedDURING AVIONICS TROUBLE SHOOTING, AN INSPECTION PANEL WAS REMOVED FROM THE COCKPIT FLOOR IN THE AREA JUST FORWARD OF THE CO PILOT'S SEAT TO GAIN ACCESS TO A SWITCHING RELAY MOUNTED ON THE UNDERSIDE OF THAT SAME PANEL. ONCE REMOVED, IT WAS NOTED THAT THE "SWITCSDR 2002FA0000682Valve · brokenDE-ICE BOOTS INOPERATIVE, FOUND AIRBORN MANIFOLD VALVE BROKEN IN TWO.SDR 2002FA0000180Magneto · failedPILOT REPORTED FAILED RT MAGNETO. REMOVED MAGNETO FROM ENGINE AND DISASSEMBLED. FOUND ONE OF THE COIL ANCHOR WEDGES WAS DISPLACED AND HAD MIGRATED ONTO THE SECONDARY TOWER. THE TOWER WAS BURNED AND MELTED AND THERE WAS OBVIOUS SIGNS OF A DIRECT SHORT AT THESDR 2001FA0000128Rod · corrodedELEVATOR PUSH PULL CONTROL ROD VERY RUSTY AND PITTED. LOCATED IN TAIL SECTION WHERE MOISTURE AND CONTAMINATION ACCUMULATE.SDR SW15200111824Knob · inoperativeMANUAL OVER RIDE (MOR) CONTROL LEVER KNOB CAME APART CAUSING THIS SYSTEM TO BE RENDERED INOPERATIVE AND A CERTAIN SAFETY ISSUE. PROBLEM CAN BE SOLVED WITH PROPER INSTALLATION. THIS AIRCRAFT JUST COMPLETED A PHASE I AND II INSPECTION.SDR 2001F00048Mount · damagedFOUND ENGINE CONTROL CABLES CHAFFING ON THE ENGINE MOUNT DURING ENGINE CHANGE. DAMAGE WAS FOUND TO BE BEYOND LIMITS. SENT MOUNT FOR REPAIR. ENGINE MOUNT WAS FOUND TO HAVE 6 CRACKS AND CORROSION BEYOND LIMITS .SDR 20000802SH017Rod End · corrodedDURING ANNUAL INSPECTION, TUBE WAS FOUND WITH EXTERIOR CORROSION ON BOTTOM AFT SURFACE. FLAKED OFF LOOSE PAINT FOUND A DEEP PIT. ABLE TO PASS THIS TUBE WITH AN AWL. WAS ABLE TO PUSH THROUGH A SECOND AREA OF TUBE THAT DID NOT HAVE SIGNS OF CORROSION EXTERNASDR CA991209064Bolt · wrong part(CAN) ONE BOGUS PART (HUB BOLT) FOUND.SDR CA991209039Control Shaft · cracked(CAN) DURING INSPECTION NDT PROCESS REVEALED A CRACK IN THE CONTROL SHAFT.SDR CA991209040Blade · corroded(CAN) CORROSION FOUND UNDERDEICE BOOTS.SDR 99ZZZX2477Spring · weakNOSE GEAR EMERGENCY EXTENSION SPRING UNABLE TO EXTEND NOSE GEAR AND LOCK IN-FLIGHT. AFTER LANDING AND ROLL-OUT ON MAINS HOLDING NOSE OFF, NOSE GEAR LOCKED AT 30 KNOTS AIRSPEED. NEW PART WAS 2 INCHES LONGER THAN OLD PART. SUBMITTER RECOMMENDED TIME-LIFE CYCLSDR 99ZZZX976Gear Dist · failedPILOT REPORTED LOSS OF POWER AND A ROUGH RUNNING ENGINE. AFTER COMPLETING MAGNETO CHECK, A DEAD LT MAGNETO WAS DISCOVERED. THE MAGNETO WAS DISASSEMBLED AND THE DISTRIBUTOR GEAR WAS DISASSEMBLED AND THE DISTRIBUTOR GEAR WAS FOUND TO HAVE 15 TEETH THAT WERE LISDR CA990119044Bolt · fractured(CAN) THE NR 2 CYLINDER ROCKER COVER HOLD-DOWN BOLTS BROKE, SENDING INTAKE BOLT UPPER BROKEN HALF THROUGH THE ROCKER COVER. THE CYLINDER WAS REMOVED AND SENT FOR REPAIR. NO OTHER DAMAGE WAS FOUND TO THE CYLINDER OR THE PISTON. ALL OTHER HOLD-DOWN BOLTS WERE SDR AU981663Actuator · leaking(AUS) AFTER TAKEOFF AND LANDING GEAR RETRACTED, THE HYDRAULIC PRESSURE CYCLED AND TRIPPED THE HYDRAULIC MOTOR CIRCUIT BREAKER. THE LANDING GEAR THEN PARTIALLY EXTENDED BY ITSELF. AN EMERGENCY EXTENSION DID NOT FULLY EXTEND THE NOSE GEAR. BY STEEP TURNING ATSDR AU981655Engine · deteriorated(AUS) DURING SCHEDULED ENGINE MAINTENANCE, THE FOLLOWING PROBLEMS WERE FOUND: 1. ENGINE OIL FILTER INSPECTED AND FOUND (EXCESSIVE) HIGH LEVELS OF COPPER. 2. TWO CYLINDERS REMOVED DUE TO LOW COMPRESSION. 3. SUMP REMOVED - MINOR METAL PARTICLES FOUND. 4. SDR 98ZZZX4224Bellcrank · failedON APPROACH, THE PILOT NOTICED THE RIGHT FLAP DID NOT EXTEND. THE LEFT FLAP WAS PROMPTLY RETRACTED AND A SAFE LANDING WAS MADE WITHOUT INCIDENT. THE INVESTIGATION FOUND THE RIGHT INBOARD FLAP BELLCRANK P/N 82905-03 WAS COMPLETELY BROKEN THROUGH THE TUBE PORT
Back to Piper PA-46-310P