Piper PA-28-180
Service difficulty reports · 194
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 = 'PA28180' 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 = 'PA28180' 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 2024FA0000435Case · crackedON CLIMB TO CRUISING ALTITUDE PIC FELT AN ENGINE VIBRATION AND DECIDED TO TURN BACK TO KARG. ON TURN BACK TO DEPARTURE AIRPORT OIL PRESSURE DROPPED TO "0" AND ENGINE SEIZED. POST EMERGENCY LANDING, ENGINE COWLING WAS REMOVED, HOLE IN CRANKCASE FOUND ON FORWARDSDR 2024FA0000421Screw · looseOWNER COMPLAINED OF A ROUGH RUNNING ENGINE. DIAGNOSIS FOUND THE BEARING CAP ASSEMBLY MOUNTING SCREWS HAS COME LOOSE ON THE RH MAGNETO.ONE SCREW AND RETAINER HAS FALLEN COMPLETELY OUT. THE BEARING CAP ASSEMBLY WAS FREELY ROTATING 5-10 DEGREES ALLOWING THE MAGNESDR 2024FA0000065Piston · failedFOLLOWING A FLT TEST, IN PATTERN WITH ACFT & NEW ENG, DEPARTED KLUD FOR THE 2ND BREAK-IN FLT IAW SERVICE INSTRUCTIONS. MADE A FULL-STATIC POWER RUNUP & INITIATED TAKEOFF IN KLUD. CLIMBOUT NORMAL, ENTERED LT PATTERN & DEPARTED NORTH FROM LT DOWNWIND VFR AT APPRSDR 2023FA0000841Cowling · failedUPPER COWLING BROKE AWAY FROM AIRCRAFT DURING FLIGHT. AFTER INSPECTING THE AIRCRAFT, IT SEEMS THE FRONT PIN BROKE OFF THE COWLING POSSIBLY THE ADESSIVE FAILED AND CAUSED THE PIN TO BREAK AWAY AND THE UPPER COWLING TO ALLOW AIRFLOW TO ENTER THE COWL AND PUT TOOSDR 2023FA0000235Tube · unknownPILOT NOTED SMALL WISPS OF SMOKE IN THE COCKPIT AND CO PILOT NOTICED OIL ON THE LEADING EDGE OF THE RH WING. PILOT RETUNED TO AIRPORT AND BROUGHT THE AIRPLANE TO THE MX HANGAR. I NOTICED OIL ON THE RH SIDE OF THE ENGINE COWLING. UPON REMOVING THE UPPER COWSDR 2023FA0000234Line · unknownTHE B NUT ON THE OIL RETURN LINE FROM THE #1 CYLINDER WAS FOUND TO BE LOOSE. OIL WAS LEAKING FORM THIS LOCATION AND SOME WAS NOTED ON THE LEADING EDGE OF THE RH WING FROM THE AIR FLOW. REMOVED THE UPPER COWLING AND TIGHTEN BUT B NUT. RAN THE ENGINE ON THESDR 2023FA0000023None · noneUNDERSTANDING OF THE 1ST GENERATION FUEL SELECTOR FOR PIPER AIRCRAFT. SEE SB 840A, SAIB CE-14-22, SB 1309A, PIPER SB 355, SA-075. PILOTS ARE INADVERTENTLY SELECTING THE OFF POSITION DUE TO CONFUSION / MISUNDERSTANDING OF THE FUEL SELECTOR POINTER.SDR 2022FA0000422Carburetor · inaccurateFACTORY OVERHAULED ENGINE INSTALLED IN AIRFRAME. PERFORMANCE WAS NORMAL, BUT NOTED THAT CARBURETOR WAS DIFFICULT TO SET AND MAINTAIN LEAN CUTOFF RISE IN RPM DURING SHUTDOWN. SINCE IT DIDN'T AFFECT FLIGHT PERFORMANCE, AIRCRAFT RELEASED TO SEE IF CONDITION WOULDSDR 2021FA0000144Gyro · faultedAIRCRAFT WAS OPERATING UNDER 14 CFR 141 RULES IN IMC CONDITIONS WHEN THE AIRCRAFT EXPERIENCED AN INSTRUMENTATION FAILURE OF THE HORIZONTAL SITUATION INDICATOR. INSTRUMENT WAS OPERATING NORMALLY FOR THE FIRST 30 MINUTES OF IFR FLIGHT AND BECAME DEGRADED AFTER ESDR 2020FA0000286Spinner · separatedIN VFR CRUSE FLIGHT WITH ATC, THE PILOT REPORTED HEARING A LOUD BANG AND A SLIGHT ENGINE VIBRATION. A PRECAUTIONARY LANDING WAS MADE, INSPECTION OF THE AIRCRAFT REVEALED THE PROPELLER SPINNER HAD FAILED AND HAD DEPARTED THE AIRCRAFT, AND PORTIONS OF THE FIBESDR 2019FA0000316Selector Valve · stiffFUEL SELECTOR VALVE WAS STIFF AND WOULD JUMP PASS DETENT CAUSING LOSS OF FUEL FLOW FROM RIGHT TANK.SDR 2019FA0000308Volt Regulator · intermittentCUSTOMER COMPLAINED THAT ALTERNATOR WOULD QUIT CHARGING AFTER APPROXIMATELY 20 MINUTE FLIGHT. CONDUCTED TEST FLIGHT OF AIRCRAFT, MONITORED CHARGING VOLTAGE WITH CALIBRATED VOLTMETER, CHARGING VOLTAGE 13.8- 13.9 CONSISTENTLY DURING FLIGHT. CHARGING SYSTEM BEHSDR 2019FA0000227Cable Guard · chafedCABLE PULLEY GUARD CHAFFED IN 3 PIECES BY RUDDER CABLES AT BASE OF CONTROL YOKE. GUARD PLACED IN WRONG HOLE IN CONSOLE. CORRECT HOLE COVERED BY HEAT DUCT MOUNT BRACKETS. TRIMMED BRACKETS AND INSTALLED NEW GUARD. CLEARANCE NORMAL. NO CABLE DAMAGE. NO MAJOSDR 2019FA0000210Turnbuckle · crackedWHILE RETENSIONING THE LOWER STABILATOR TURN BUCKLE AFTER STABILATOR REPLACEMENT THE AFT CABLE END APPEARED BENT. CLOSE INSPECTION SHOWED A CRACK AND PARTIAL PARTING OF THE SWAGED CABLE END. THE CRACK WAS BETWEEN THE THREADS AND SAFETY WIRE HOLE IN THE AREA SDR 2017FA0000516Wing Root · crackedAT INSPECTION, FOUND BOTH R/H WING ROOT SKIN DOUBLER CRACKED. CONTACTED THE MANUFACTURER, FOUND THAT THIS IS A COMMON PROBLEM.SDR 2017FA0000398Skin · crackedDURING AN ANNUAL INSPECTION, A 4.5 INCH CRACK WAS FOUND IN THE SKIN AT THE AFT EDGE OF THE BOTTOM CHANNEL STIFFENER, REAR SPAR LOCATION. STOP DRILLED THE CRACK AND INSTALLED A DOUBLER. AIRFRAME HAS 6261 HRS AND WAS USED FOR FLIGHT TRAINING. REPETITIVE STRSDR 2015FA0000216Pin · shearedFLAP HANDLE WILL NOT CLICK INTO DE-TENT ON LANDING. INSPECTION SHOWED DETENT PIN SHEARED IN HALF THROUGH RETENTION ROLL PIN HOLE. CAUSING FLAP TO RETRACT ON LANDING. ORIGINAL PART IS .1875 DIA, CURRENT PRODUCTION PART IS NOW .2500 DIA.SDR 2015FA0000163Structure · corrodedEXTENSIVE CORROSION IN FUSELAGE AND WINGS, ESPECIALLY THE LEFT WING. THE PLANE WAS SO BADLY CORRODED IT LOOKED AS IF THE PLANE HAD BEEN IMMERSED IN SALT WATER AND THE COST OF THE REQUIRED REPAIRS WOULD EXCEED THE VALUE OF THE PLANE. IN ADDITION, THE LEFT WINGSDR CA141224003G Switch · failed(CAN) WHILE TESTING THE ELT ON ITS ANNUAL CERTIFICATION AS PER CAR 571 APPENDIX G FOUND G SWITCH IN UNIT WOULD NOT ACTIVATE & OUTPUT POWER LOW. UNIT REMOVED FROM SERVICE.SDR KC2R1010201449428Impulse Coupling · crackedDURING ROUTINE 500 HOUR INSPECTION, DISCOVERED IMPULSE COUPLING CRACKED AT FULL ADVANCE STOP ON FLYWEIGHT BASE PLATE. CRACKS DETECTED USING MAGNETIC PARTICLE NDT METHOD. HAVE SEEN THIS SAME ISSUE WITH MANY OTHER MAGNETOS. CRACKS APPEAR TO BE ORIGINATING FROM ASDR 2014FA0000559Control Cable · frayedTRIM CABLE FRAY AND BROKEN, STRANS AT TRIM BARREL AT STABILIZER.SDR 2014FA0000452Muffler · blockedTHE FORWARD MUFFLER WAS REMOVED FROM THE NR 1 AND NR 2 CYLINDERS. THE INTERIOR SURFACES OF THE LT AND RT RISERS REVEALED WHITE AND GRAY DEPOSITS CONSISTENT WITH NORMAL OPERATION. A VISUAL INSPECTION REVEALED THE MUFFLER BAFFLING HAD SEPARATED FROM ITS LT SIDSDR 2014FA0000048Spar · corrodedCORROSION FOUND DURING A ANNUAL INSPECTION, ON INBOARD LOWER RT WING SPAR WS 44.2.SDR 2014FA0000028Skin · crackedCRACK NEAR AFT WING SPAR SPLICE, LOWER WING SKIN, FWD INBD END, LT AND RT.SDR 2013FA0000301Shaft · mismanufacturedNEW SHAFT FROM MFG IS .010 UNDER DIAMETER. PART IS USED TO COMPLY AD10-15-10.SDR 2014FA0000123Cylinder Head · fracturedALUMINUM CYLINDER HEAD FRACTURED CIRCUMFERENTIALLY ADJACENT TO UPPER EDGE OF STEEL CYLINDER BARREL ON 4/28/13 DESPITE A SATISFACTORY COMPRESSION CHECK (79/80) 4 DAYS PRIOR 4/25/13, WITH NO USE IN THE INTERIM. HEAD SEPARATION OCCURRED AT HIGH POWER SETTING, TASDR 2013FA0000113Distributor Blk · inoperativePILOT COMPLAINED OF ROUGH ENGINE & LOSS OF POWER. GROUND RUN DETERMINED THAT THE RT MAGNETO WAS CAUSING PROBLEM. ENSURED RT WAS CORRECT POSITION ON SWITCH. PULLED AND CLEANED ALL SPARK PLUGS FOR RT MAGNETO. PULLED RT MAGNETO, TESTED CONDENSER, AND COIL BOTSDR CA120625002Leg Assy · cracked(CAN) DURING INSPECTION IAW SB 1131, RT MLG LEG WAS FOUND CRACKED AT THE UPPER INBD TORQUE LINK ATTACH LUG. THIS LG STRUT CYLINDER WAS CAST TYPE.SDR 2012FA0000338Line · leakingOIL LEAK ON BACK SIDE OF FIREWALL, UNDER THE PANEL ON THE ENGINE OIL PRESSURE HARD LINE AFTER COMPLETING ENGINE CHANGE DURING FIRST ENGINE RUN-UP, FOUND EXCESSIVE CORROSION ON THE LINE WHERE IT PASSES THRU THE FIREWALL INSIDE THE FIREWALL GROMMENT - SUSPECT LISDR REXA201200065Light · unknownFLOOR TRACK LIGHTING ASSEMBLIES IN FRONT OF LT FORWARD GALLEY NEEDS REPLACEMENT. REMOVED AND REPLACED FLOOR TRACK LIGHTING IN FRONT OF LT FORWARD GALLEY IAW CRJ900 AMM 33-51-01. ALL CHECKS GOOD.SDR 2012FA0000224Transmitter · erraticDURING ALL OPERATIONS, NOTICED VERY ERRATIC FUEL QUANTITY INDICATIONS FROM BOTH TANKS. DURING ANNUAL INSPECTION, MECHANIC DISCOVERED THAT THE BOTH FUEL QUANTITY SENDERS RESISTANCE WAS VERY ERRATIC AND DID NOT APPEAR TO BE WITHIN TOLERANCE. FUEL QUANTITY SENDSDR 2012FA0000135Cylinder · crackedDURING ANNUAL COMPRESSION TEST, CYLINDER WAS FOUND TO HAVE NO COMPRESSION. UPON FURTHER INVESTIGATION AIR WAS FOUND LEAKING FROM THE BACK OF CYLINDER ASSY AT THE POINT WHERE THE FINS STEP UP TO THE NEXT SIZE. WITH AN INSPECTION MIRROR HELD BETWEEN THE BAFFLISDR 2012FA0000115Selector Valve · wornTHE FUEL TANK SELECTOR VALVE, WHEN THE VALVE WAS ROTATED, IT WAS STIFF TO MOVE AND COULD NOT FEEL THE DETENT AT EACH POSITION. A TEARDOWN OF THE VALVE SHOWED THAT THE VALVE WAS VERY DIRTY INSIDE AND THE DETENT RING WAS WORN. DEFECT LED TO IMPROPER FUEL SELECSDR 2011FA0000524Skin · buckledRT WING HAS BUCKLING ON BOTTOM INBD PANELS. INSP OF INSIDE OF WING ROOT REVEALED MISSING AND INCOMPLETE BUCKED RIVETS.SDR 2011FA0000190Cylinder · brokenRT MLG LOWER STRUT FELL OFF WHEN ACFT LIFTED OFF THE RUNWAY AT 2H2. STUDENT PILOT FLEW AND LANDED RESULTING IN DAMAGE TO THE UPPER LANDING GEAR STRUT HSG. WHEN LOWER STRUT DEPARTED UPPER HSG, IT STRUCK THE FLAP, DAMAGING FLAP SKIN. RT MLG UPPER TORQUE LINK SDR CA100813008Hub · corroded(CAN) PROPELLER RECEIVED FOR COMPLIANCE WITH CARS, PART 6, STANDARD 625, APPENDIX C. 6. FIRST THING NOTICED WAS WHITE CORROSION POWDER IN THE 6 BOLT HOLE COUNTERBORES. GLASS CLEANED THE AREA AND FOUND PITTING. PROPELLER TAGGED UNSERVICEABLE. REQUESTED TO COSDR 2010FA0000529Torque Link · brokenLT MLG TORQUE LINK BROKE ABOUT 1" BELOW UPPER MOUNT AFTER LANDING. TORQUE LINK WAS SENT TO NTSB FOR TESTING WITH THE FOLLOWING REPORT. THE FATIGUE ORIGIN AREAS CONTAINED NO EVIDENCE OF GOUGE DAMAGE OR CORROSION DAMAGE. ON ONE SIDE OF THE LINK THE FATIGUE CRACKSDR C2XA10IA142Relay · inoperativeIAH, FLIGHT 2170, THE CREW REPORTED EICAS MESSAGES ON ROTATION FOR ELECTRIC ABNORMAL, AND EMERGENCY LIGHTS NOT ARMED, AND ELECTRICAL SURGING ON THE FLIGHT DECK AND CABIN FOR APPROXIMATELY THREE SECONDS. THE AIRCRAFT RETURNED TO IAH WHERE IT LANDED WITHOUT INCISDR CA081106005Baffle · failed(CAN) POWER LOSS ON TAKEOFF DUE TO BAFFLE FAILURE INSIDE MUFFLER WHICH RESTRICTED EXHAUST OF ENGINE CAUSING PARTIAL POWER LOSS.SDR 2008FA0000725Rib · corrodedDURING ANNUAL INSPECTION FOUND ALL FLAPS, LEADING EDGE RIBS WERE SEVERELY CORRODED. DETECTION METHOD WAS TO TAKE THE FOREFINGER AND THUMB AND SQUEEZE LEADING EDGE AT THE RIB, GOT A CRUNCHING FEEL AND SOUND.SDR CA080919001Mount Bracket · cracked(CAN) THE EXISTING ELT MOUNTING BRACKET WAS INSPECTED PRIOR TO REPLACEMENT OF THE VHF ELT WITH A 406 MHZ ELT. UPON REMOVING THE NARCO ELT10 MOUNTING TRAY, IT WAS DISCOVERED THAT ACFT ELT MOUNTING BRACKET WAS CRACKED AT EACH MOUNTING TRAY SCREW HOLE LOCATION. SDR 2007FA0000820Bearing · destroyedBEARING LW14227 CAGE DESTROYED AND APPROXIMATELY 50 PERCENT MISSING. THIS IS THE ENGINE SIDE BEARING OF THE LW15416 MAGNETO DRIVE ADAPTER (MAGNETO ISOLATION DRIVE FOR RIGHT HAND MAGNETO). ENGINE HAS 857 HOURS SINCE FACTORY OVERHAUL IN 2000.SDR 2007FA0000819Bearing · destroyedBEARING LW14227 CAGE DESTROYED AND APPROXIMATELY 50 PERCENT MISSING. THIS IS THE ENGINE SIDE BEARING OF THE LW15416 MAGNETO DRIVE ADAPTER (MAGNETO ISOLATION DRIVE FOR RT MAGNETO)ENGINE HAS 857 HOURS SINCE FACTORY OVERHAUL IN 2000.SDR 2007FA0000526Terminal · loose217 HOURS AFTER OVERHAUL, THE OUTPUT TERMINAL BECAME LOOSE IN THE BUSS STRAP INSIDE THE ALTERNATOR, CAUSING COMPLETE FAILURE. LIKELY THIS FIT (NORMALLY A PRESS FIT) WAS NOT AS TIGHT AS IT NEEDED TO BE WHEN THIS UNIT LEFT KELLY.SDR 2007FA0000075Bulkhead · corrodedTHE BULKHEAD, BRACKETS, AND DOUBLERS AT STA. 228.3 WERE SEVERELY CORRODED. THIS BULKHEAD IS THE FRONT SUPPORT FOR THE VERTICAL STABILIZER/RUDDER ASSEMBLY. THE CORROSION COVERED AN AREA APPROXIMATE THE SIZE OF THE FRONT RUDDER ATTACHMENT BRACKET THAT IS PART OFSDR 2007FA0000074Bulkhead · corrodedTHE BULKHEAD, BRACKETS, AND DOUBLERS AT STA. 228.3 WERE SEVERELY CORRODED. THIS BULKHEAD IS THE FRONT SUPPORT FOR THE VERTICAL STABILIZER/RUDDER ASSEMBLY. THE CORROSION COVERED AN AREA APPROXIMATE THE SIZE OF THE FRONT RUDDER ATTACHMENT BRACKET THAT IS PART OFSDR 2006FA0000904Pump · leakingUPON RETURNING FROM A TRAINING FLIGHT, A FAINT SMELL OF GAS WAS NOTED. SINCE THE ELECTRIC PUMP WAS ON, IT WAS TURNED OFF. NO ENGINE PERFORMANCE PROBLEMS WERE NOTED AND LANDING WAS NORMAL. UPON LANDING IT WAS NOTICED THAT FLUID WAS DRAINING FROM THE FUEL PUMP SDR 2006FA0000905Diaphragm · rupturedUPON RETURNING FROM A TRAINING FLIGHT, A FAINT SMELL OF GAS WAS NOTED. SINCE THE ELECTRIC PUMP WAS ON, IT WAS TURNED OFF. NO ENGINE PERFORMANCE PROBLEMS WERE NOTED AND LANDING WAS NORMAL. UPON LANDING IT WAS NOTICED THAT FLUID WAS DRAINING FROM THE FUEL PUMP SDR CA061011002Connector · broken(CAN) WHEN MANUAL RUDDER TRIM WAS APPLIED IN CLIMB THERE WAS NO RESPONSE. SUBSEQUENT INSPECTION FOUND THAT THE ARM THAT CONNECTS THE TRIM ACTUATOR TO THE RUDDER CONTROL ASSEMBLY HAD BROKEN OFF THE ASSEMBLY AT THE EDGE OF THE WELD. THE COMPLETE RUDDER TRIM ARMSDR CA060925003Connector · broken(CAN) WHEN MANUAL RUDDER TRIM WAS APPLIED THE RUDDER FAILED TO RESPOND. SUBSEQUENT INSPECTION FOUND THAT THE ARM THAT CONNECTS THE TRIM ACTUATOR TO THE RUDDER CONTROL ASSEMBLY HAD BROKEN OFF THE ASSEMBLY AT THE EDGE OF THE WELD. THE COMPLETE RUDDER TRIM ARM AS
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