Lycoming TIO-540-F2BD
Service difficulty reports · 38
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 = 'TIO540F2BD' 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 = 'TIO540F2BD' 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 2017FA0000036Points · closedEXPERIENCED ENGINE ROUGHNESS ON LEFT ENGINE, 5-10 MINUTES AFTER DEPARTURE, AT CRUISE ALTITUDE OF APPROXIMATELY 2,500 FEET MSL. ISOLATED THE PROBLEM TO THE RIGHT SIDE OF LEFT ENGINE DUAL MAGNETO AND CONTINUED THE FLIGHT ON THE LEFT SIDE OF DUAL MAGNETO(RIGHT SISDR JIKA2016092201Engine · making metalTHE PILOT REPORTED DURING CLIMBOUT THAT THE LT ENGINE WAS SURGING AND LACKING IN PERFORMANCE. THE LT OIL PRESSURE WAS LOW BUT STILL IN THE GREEN, THE CYLINDER HEAD TEMPERATURE AND OIL TEMPERATURE WERE HIGH, THE PILOT ENRICHED THE MIXTURE AND FULLY OPENED THE SDR CA090319008Powerpack · mismanufactured(CAN) THE DEFECT WAS NOTICED WHEN RIGGING WAS BEING CONDUCTED OF THE POWER PAK. THE RIGGING HOLE WAS MISSING IN THE LOWER PART OF THE BODY TO ENSURE NEUTRAL IS BEING SET FOR THE SELECTOR ARM. COULD NOT RIG SELECTOR HANDLE CONTROL IAW PA31 MM SEC 6, PARA 6-105 SDR CA090319010Screw · overtorqued(CAN) DURING A TEST FLIGHT FOR THE POWER PAK CHANGE, IT WAS REPORTED THAT THE LANDING GEAR SELECTOR LEVER WAS VERY WEAK AND SLUGGISH IN RETURNING TO NEUTRAL. THE HANDLE WOULD STOP APPROX .2500 BEFORE IT CONTACTED THE NEUTRAL STOP. UPON FURTHER INVESTIGATION ITSDR CA090317004Servo Control · damaged(CAN) DURING FLIGHT THE ENGINE SURGED. MIXTURES COULD NOT BE ADJUSTED. FUEL SERVO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.SDR CA070327005Proximity Switch · failed(CAN) MAINTENANCE COULD NOT DUPLICATE FAULT ON GROUND WITH AIRCRAFT ON JACKS. CYCLED GEAR 20 TIMES FAULT FREE. WIRING CHECKED,OK, RIGGING CHECKED OK, HYDRAULIC POWER PACK CHECKED, OK. CORRECTIVE ACTION TO REPLACE ALL 6 LANDING GEAR PROXIMITY SWITCHES. (TC NR SDR CA080304008Intake Valve · failed(CAN) WHILE IN CRUISE, THE PILOT HEARD A BANG AND EXPERIENCED A LOSS IN POWER ON THE LT ENGINE. AS THE ENGINE REMAINED RUNNING AND THERE WAS NO IMMEDIATE CONCERN FOR SAFETY THE PILOT CHOSE TO LEAVE THE ENGINE RUNNING AND SET DOWN AT THE NEAREST AIRPORT. UPON ESDR CA070127002Control Cable · failed(CAN) LT PROPELLER CONTROL CABLE FAILURE. THE PILOT NOTED THAT THE LT PROPELLER CONTROL WAS STIFF ON APPROACH. THE LT ENGINE AND PROPELLER CONTROLS WERE INSPECTED, MAINTENANCE DETERMINED THE LT PROPELLER CONTROL CABLE IN THE CABIN PEDESTAL HAD FAILED. THE PROPSDR CA061114007Throttle Cable · failed(CAN) RT ENGINE THROTTLE CABLE FAILURE: DURING A ROUTINE FLIGHT, THE PILOT, ENROUTE , NOTED THAT THE RT ENGINE THROTTLE CONTROL WAS STIFF ON APPROACH. THE AIRCRAFT EXPERIENCED A NORMAL LANDING, ONCE ON THE GROUND THE PILOT REPORTED THAT THE RT ENGINE WAS RUNSDR CA060809002Exhaust Duct · cracked(CAN) EXHAUST TRANSITION BETWEEN TURBO AND EXHAUST STACKS FROM CYLINDERS HAD CRACKED AND STARTED TO BLOW A HOLE BELOW THE EGT PROBE HOLE. THE DEFECT WAS NOTICED BY AN EXHAUST STAIN ON THE INSIDE OF THE COWL ON A MAINTENANCE DAILY INSPECTION. THE AIRCRAFT WAS 3SDR CA060530003O-Ring · failed(CAN) O-RING IN HYDRAULIC FILTER BOWL BLEW OUT SIDE BETWEEN THE BOWL SEATS. THERE ARE 2 DIFFERENT TYPES SIZES OF O-RING FOR THIS SET UP AS THERE ARE 2 SLIGHTLY DIFFERENT BOWL TYPES. THE O-RINGS ARE THE SAME COLOR AND VERY CLOSE IN SIZE MAKING IT REAL EASY TO PSDR 2005F00092Stud · brokenAFTER DEPARTURE, @ APPROX 500'AGL, ENGINE LOST POWER. THROTTLE REDUCTION TO 31"MP, RAN SMOOTHLY. RETURN FOR LANDING, DISCOVER 7 OF #2 CYLINDER HOLD DOWN STUDS BROKENSDR CA050817006Skin · damaged(CAN) WHILE IN CRUISE FLIGHT THE NR 2 COMM ANTENNA DEPARTED THE AIRCRAFT. THE PILOT HEARD THE ANTENNA DEPART AND LANDED AT THE NEAREST AIRPORT. A FERRY PERMIT WAS OBTAINED AND FOLLOWING INSPECTION THE AIRCRAFT WAS FERRIED TO FLY WERE IT WAS RECENTLY REPAIRED. SDR 2005FA0000767Camshaft · brokenTHE LT ENGINE STOPPED IN CRUISE FLIGHT. AFTER INVESTIGATION IT WAS FOUND THE CAM HAD FAILED JUST FORWARD OF THE NR 5 AND NR 6 CYLINDERS AND CRACKED THE LT CASE HALF. TBO IS 1800HRS, COMPONENT TIME IS 1413.3 TSMOH.SDR CA050531002Turbocharger · leaking(CAN) ENGINE WAS SEEN TO BE SMOKING AT STARTUP AND LOW POWER. AN INSPECTION OF THE TURBO CHARGER REVEALED THAT OIL WAS GETTING BY THE SEALS INTO THE TURBINE SECTION. THE TURBO CHARGER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. THIS ENGINE IS ON CONSDR CA050222009Magneto · failed(CAN) ENGINE WOULD NOT START. THE PROBLEM WAS TRACED TO THE MAG. THIS OVERHAULED MAGNETO HAD BEEN IN SERVICE FOR 34 HRS.SDR 2005FA0000310Engine · failedTHE PILOT ATTEMPTED TO START THE RT ENGINE, WHILE DOING SO, HE HEARD A LOUD BANG THE ENGINE STARTED, AFTERWARDS, SHUTDOWN THE ENGINE AND EXITED THE AIRCRAFT. UPON INVESTIGATION, OBSERVED SKIN DAMAGE BETWEEN THE INSIDE NACELLE AND FUSELAGE, THE WING LOCKER SUFSDR CA050124008Hsi · stuck(CAN) NR1 HSI NEEDLE STUCK ON NORTHERN HEADING. NR1 ENGINE STARTED TO SURGE. ENGINE DROPPED TO 20 INCHES OF MANIFOLD PRESSURE. AIRCRAFT RETURNED TO BASE SAFELY.SDR AUS20040425Rod End · failed(AUS) LT MAIN LANDING GEAR ACTUATOR ROD END FAILED. AIRCRAFT LANDED WITH LT MAIN LANDING GEAR FULLY RETRACTED.SDR CA031201005Bearing · failed(CAN) AFTER TAKEOFF ENGINE MANIFOLD PRESS DROPPED TO 23 INCHES, THE PILOT TURNED AND LANDED BACK AT AIRPORT. MANTENANCE FOUND THE TURBO BEARINGS FAILED. ENGINE WAS FLUSHED AND NEW FILTER AND OIL INSTALLED WITH THE TURBO BEING REPLACED. A/C WAS GROUND RUN AND TSDR 2003FA0001112Torque Tube · corrodedSB 1105, RUDDER TORQUE TUBE INSPECTION RUST AND CORROSION.SDR AUS20030435Spar · cracked(AUS) LT TAILPLANE OUTBOARD SPAR CRACKED AT HINGE POINT. FOUND DURING INSPECTION IAW AD.SDR 2003F00101Line · leakingDEVELOPED OIL LEAK FROM LT ENGINE DURING RETURN FLIGHT. OIL TEMP WAS HOLDING, BUT OIL PRESSURE HAD STARTED TO DECAY. PILOT SHUT ENGINE DOWN AND FEATHERED AS A PRECAUTIONARY MEASURE. FOUND PIN HOLE IN TURBOCHARGER OIL SUPPLY LINE AND REPLACED WITH NEW ON 1/2SDR CA021219002Uplock Hook · lack of lube(CAN) LT MLG DOWNLOCK INDICATION FAILED TO COME ON AFTER GEAR SELECTION. MLG HANDLE DID NOT NEUTRALIZE AND RED MLG UNSAFE LIGHT WAS ON. AFTER UNEVENTFUL LANDING, THE MLG DOWNLOCK HOOK WAS FOUND TO BE NOT ENGAGED. MLG HOOK DID NOT FREELY ROTATE ON THE MOUNTISDR AUS20020909Downlock · seized(AUS) LH MAIN LANDING GEAR DOWNLOCK PARTIALLY SEIZED PREVENTING POSITIVE LOCKING.SDR CA020522000Plate · cracked(CAN) THE BULKHEAD REINFORCEMENT PLATE (KIT P/N 764 028)WAS FOUND CRACKED AT AFT FUSELAGE STA 317.75 WITHIN THE SAME INSPECTION AREA OUTLINED ON PIPER SB 636A. THE REINFORCEMENT PLATE IS A PART OF PIPER KIT 764 028 INSTALLED UNDER AD96-12-12 WITH ABOUT 2000 HSDR CA020611005Case · damaged(CAN) ON ENGINE BUILD-UP TO INSTALL THE PROP DEICE BRUSH BLOCK BRACKET ASSEMBLY. ONE OF THE BOLTS THAT GO THROUGH THE CASE HAD TO BE REMOVED. THE THREADS OF THE BOLT WERE MARKED UP. ON FURTHER INVESTIGATION IT WAS FOUND THAT THE BOLT HAD BOTTOMED OUT IN THE HESDR CA000410010Line · broken(CAN) OIL LINE FAILURE AT FITTING FEEDING TURBOCHARGER SECONDARY DAMAGE TO CONNECTING ROD BEARING CAUSING ROD FAILURE.SDR CA990401011Turbocharger · leaking(CAN) ON LANDING OIL SEAL LEAK FROM TURBOCHARGER IGNITED. WHEN THE ENGINE WAS RETARDED TO IDLE, THERE WAS NO DAMAGE TO THE AIRCRAFT OR ENGINE COMPONENTS.SDR CA990330023Rod · broken(CAN) DURING FLIGHT, THE NR 1 ENGINE BEGAN TO LOSE POWER. THE AIRCRAFT WAS DIVERTED AND LANDED WITHOUT INCIDENT. POST-FLIGHT INSPECTION FOUND THE NR 6 CYLINDER PISTON NOT MOVING. FURTHER INVESTIGATION FOUND THE CONNECTING ROD BROKEN. THE ENGINE WAS REPLACESDR CA981214001Shaft · cracked(CAN) THE SHAFT JOINING THE TWO IMPELLERS IN THE TURBOCHARGER WAS FOUND CRACKED. THIS ALLOWED THE EXHAUST SIDE IMPELLER TO SEPARATE FROM THE SHAFT. THE INTAKE IMPELLER STAYED IN PLACE, BUT DUE TO IMBALANCE, SUSTAINED SOME BLADE DAMAGE.SDR CA981109004Control Cable · sheared(CAN) DURING PRE-FLIGHT, PILOT NOTED PROP LEVER WAS TOO LOOSE AND THE PROP DID NOT RESPOND. AIRCRAFT SHUT DOWN. INSPECTION FOUND THE PROP CABLE AT THE CONTROL COLUMN LEVER, THE CABLE STRANDS WERE ALL BROKEN. BREAK AT END WHERE CABLE IS SWAGED ON TO CABLE ESDR CA980311012Engine · friction(CAN) UNKNOWN CAUSE OF FRICTION IN THE CRANKCASE. ENGINE SENT FOR INVESTIGATION AND REPAIR.SDR AU970581Camshaft · cracked(AUS) ENGINE CAMSHAFT LOBE CASE HARDENING CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTIONSDR 96ZZZX2868Valve Seat · dislodgedON A SHORT FLIGHT, A ROUGHNESS DEVELOPED IN THE LEFT ENGINE. NO EMERGENCY ACTION WAS REQUIRED. AFTER PERFORMING A COMPRESSION CHECK, FOUND THE EXHAUST VALVE SEAT ON NR 2 CYLINDER HAD BECOME DISLODGED CAUSING THE EXHAUST VALVE TO REMAIN PARTIALLY OPEN. THE CSDR AU960492Fitting · loose(AUS) HORIZONTAL STABILISER WAS REMOVED DUE TO EXCESSIVE MOVEMENT - INVESTIGATION FOUND THAT EACH OF THE TWO FORWARD ATTACHMENT FITTINGS HAD FOUR OF THE FIVE RIVETS SHEARED - SUSPECT INCORRECT GROUND HANDLING TECHNIQUESDR 95ZZZX5125Coupling Clamp · crackedDURING 100-HOUR INSPECTION, FOUND LEFT ENGINE TURBO EXHAUST COUPLING CLAMP CRACKED IN V-BAND SEGMENT. THIS CLAMP IS THE NEW IMPROVED COUPLING CLAMP. REF PIPER SB644D.SDR 95ZZZX2952Turbocharger · leakingSHORTLY AFTER TAKEOFF, RT ENGINE LOST POWER. MAP DROP TO 15 INCHES. AIRCRAFT RETURNED TO FARGO. INSPECTION REVEALED OIL LEAKING FROM INTAKE DRAIN. FOUND OIL SEAL RUPTURE IN TURBOCHARGER AND FLOODED OUT INTAKE SYSTEM. EST 1 QUART OF OIL IN INTAKE SYSTEM, A
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