Lycoming TIO-540-AE2A
Service difficulty reports · 109
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 = 'TIO540AE2A' 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 = 'TIO540AE2A' 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 2008FA0000295Cam · wornBREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START.SDR 2006FA0001061Lifter · brokenLIFTER BROKE. (K)SDR 2006FA0000778Transmitter · unreliableNEW-STYLE FUEL SENDERS UNRELIABLE. HAVE REPLACED 3 TIMES SO FAR.SDR 2006FA0000779Transmission · unreliableNEW-STYLE FUEL SENDERS UNRELIABLE. HAVE REPLACED 3 TIMES SO FAR.SDR CA041216012Tank · cracked(CAN) RIGHT FUEL COLLECTOR TANK WAS LEAKING INSIDE THE WHEEL WELL.FOUND TANK WAS CRACKED ON THE UPPER INBOARD WELD FLANGE.SDR UXCR200400002Hose · flakingDURING CLIMB TO ALTITUDE, THE ENGINE EXHIBITED A ROUGH RUNNING CONDITION THAT NECESSITATED A REDUCTION IN POWER REQUIRING AN UNSCHEDULED LANDING. INSPECTION OF THE ENGINE FUEL INJECTION SYSTEM REVEALED TWO OBSTRUCTED INJECTOR NOZZLES (NR 2 AND NR 4 CYLINDERS).SDR 2004FA0000014Plug · loosePLUG WAS FOUND LOOSE, BEGAN TO LEAK OIL. CONTINUED OPERATION WOULD HAVE CAUSED PLUG TO FALL OUT RESULTING IN EXTREME OIL LOSS. THIS IS THE SECOND TIME THIS PLUG WAS LOOSE.SDR 2003FA0001110Bolt · missingTHE HARDWARE ATTACHING THE TURBOCHARGER SCAVANGE SUMP TO THE TURBOCHARGER BECAME LOOSE ALLOWING LARGE QUANITY OF OIL TO LEAK FROM THE ENGINE OIL SYSTEM. ONE BOLT WAS MISSING. A FORCED LANDING WAS NECESSARY. THIS ENGINE HAD BEEN DISASSEMBLED, REPAIRED AND RESDR 2004F00093Turbocharger · faultyTURBOCHARGER LOW IN PERFORMANCE DURING FLIGHT. TURBOCHARGER SHIPPED TO MFG, FOR INSPECTION. PRELIMINARY EVALUATION: COMPRESSOR RUB.SDR 2002FA0001012Controller · damagedCONTROLLER HAD AXIAL PLAY ON SHAFT FOR CONTROL ARM. ENGINE WAS BACKING.SDR 2002FA0000869Blade · failedPILOT REPORTED LOSS OF POWER AT FLIGHT OF 18,000 FT. REGAINED POWER AT 9,000 FEET AND LANDED. INSPECTED, FOUND EXHAUST SIDE OF TURBO BLADE BROKEN OFF AND TURBO WAS SEIZED.SDR 2002FA0000343Sump · crackedOIL SUMP CRACKED AT TURBOCHARGER MOUNTING BRACKET ATTACHMENT POINT.SDR 2002FA0000378Boss · crackedINSPECTOR FOUND LOOSE RIGHT TURBO BOTTOM ATTACHMENT STUD, CAUSED BY CRACKED MOUNTING BOSS IN MAGNESIUM OIL SUMP ASSEMBLY.SDR J8S2002F00000Crossover Tube · splitCROSSOVER PIPE BETWEEN LEFT AND RIGHT TURBOCHARGERS WAS SPLIT UNDER HEAT SHIELD. ALLOWING HOT EXHAUST TO BLOW ON FORWARD SIDE OF FIREWALL. THE FIREWALL WAS NOT DAMAGED, BUT THE HEAT MELTED THE VINYL TRIM ON THE FORWARD SIDE OF THE NOSE BAGGAGE COMPARTMENT. SDR W452001F00000Probe · failedAFTER INSTALLATION AND CALIBRATION IAW 99-15-04, UNIT LASTED 16.3 HRS. THIS SEEM TO BE A CONTINUING PROBLEM WITH THIS AND SIMILAR UNITS. THIS IS THE 2ND TIME IN 1 WEEK THIS PN FAILED.SDR 2001FA0000170Probe · failedPART FAILED IN 49 HOURS. THIS PART IS REPLACED DURING AN AD REQUIREMENT EVERY 250 HOURS BUT ONLY LASTED 49 HOURS.SDR CA010131016Turbocharger · failed(CAN) PILOT REPORTED LOSS IN MANIFOLD PRESSURE FOUND TURBOCHARGER TURBINE MISSING A BLADE AND TURBO SEIZED.SDR CA010110017Bearing · making metal(CAN) DURING A SCHEDULED OIL/FILTER CHANGE, METAL PARTICLES WERE FOUND IN THE ENGINE OIL SCREEN. IN REFERENCE TO PIPER VSP-127 AND TEXTRON LYCOMINGS SPECIAL ADVISORY 59-800, SAMPLE WAS SENT TO TEXTRON FOR ANALYSIS. AS PER THE SERVICE ADVISORY THE AIRCRAFT WAS SDR CA001228035Harness · frayed(CAN) PILOTS SHOULDER HARNESS FRAYED.SDR 20010125CW005Mount · mismanufacturedLEFT SIDE OF ACTUATOR ATTACH BOSS NOT WELDED ALL THE WAY AROUND. IF NOT DETECTED THIS COULD HAVE CAUSED NOSE GEAR TO COLLAPSE.SDR 20010212CW001Mount · failedLEFT SIDE OF ACTUATOR ATTACH BOSS NOT WELDED ALL THE WAY AROUND. IF NOT DETECTED THIS COULD HAVE CAUSED NOSE GEAR TO COLLAPSE.SDR 20000925SH014Relief Valve · dirtyFOLLOWING TAKEOFF, PILOT NOTED DECREASE IN OIL PRESSURE. PILOT ELECTED TO RETURN TO AIRPORT. UPON LANDING AND TAXI BACK TO RAMP, PILOT KEPT RPM AT APPROX 1,500 RPM TO KEEP OIL PRESS ABOVE READING (LOW END). DUE TO TAXIING AT HIGH RPM, BRAKES WERE OVERHEATEDSDR AU000625Selector Valve · seized(AUS) FUEL SELECTOR VALVE SEIZED. INVESTIGATION FOUND WATER CONTAMINATION IN THE VALVE SPOOL CAVITY. SUSPECT WATER FROZE AND JAMMED SELECTOR. SUBMITTER STATED FUEL SYSTEM HAD BEEN DECONTAMINATED 28 HOURS EARLIER PER AD/GEN/80 AMDT2. (X)SDR 20000911SH019Engine · making metalDURING OIL CHANGE AND OIL FILTER INSPECTION, FOUND METAL IN THE OIL FILTER AND METAL WAS FOUND IN THE SUCTION SCREEN. 50 TO 60 PIECES WERE FOUND IN OIL FILTER AND TWO FLAKES WERE FOUND IN THE SUCTION SCREEN. (X)SDR 20000911SH044Baffle · misalignedENGINE OIL QUICK DRAIN WOULD NOT SHUT OFF DUE TO ONE SHEARED OFF RIVET HEAD, MS 20470-4, BLOCKING HOLE IN DRAIN VALVE. REF LYC SB 489A. OIL SUMP BAFFLE ASSY HAD THE VERTICAL DEFLECTOR FLANGE MISALIGNED TO BAFFLE PLATE AND THE TENSION LOAD POPPED THE RIVET HESDR 20000811SH003Nut · failedINSTALLED LYCOMING FACTORY REBUILT ENGINE IAW PIPER PA-46-310/350 MM 71-00-00, PG 19-22(A) (8). SECURED ENGINE CONTROL WITH SELF-LOCKING NUTS PER PIPER PRACTICES. AFTER LANDING, ON FIRST FLIGHT, THROTTLE CONTROL WAS LOST DUE TO LOSS OF HARDWARE AT THROTTLE TSDR BJ3RE000006Baffle · brokenRIVET HEAD FOUND IN OIL SUCTION SCREEN ON OIL CHANGE. HEAD IS OF THE TYPE USED TO INSTALL THE VERTICAL BAFFLE ON THE OIL SUMP BAFFLE. REFERENCE LYC. SB489A. SUBMITTER STATED AFTER RECEIVING 4 NEW DEFECTIVE OIL SUMP BAFFLES FROM LYCOMING OF THIS PART NUMBER,SDR 20000830SH031Bearing · failedENGINE (106.6 HOURS SINCE NEW) FAILED WHILE AT CRUISE RESULTING IN AN EMERGENCY DESCENT AND LANDING AT ALB. RESULTS OF ENGINE SERVICE TEARDOWN INSPECTION AND TECHNICAL REPORTS DATED 7/5/2000 AND 7/27/2000 FROM TEXTRON LYCOMING FOUND THE CRANKSHAFT ROD JOURNALSDR BJ3RE000005Baffle · elongatedON RECEIPT OF A THIRD NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES LIKE THE PREVIOUS UNITS. THIS IS ALSO OF THE NEW (5 RIVETS PER SIDE) DESIGN. SUBMITTER STATED THE HOLES ARE ELONGATED, OVERSIZED, AND NO LONGER SUITABLE FOR THE MS20470AD4-4 RIVESDR BJ3RE000004Baffle · elongatedON RECEIPT OF A SECOND NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES LIKE THE ORIGINAL UNIT AND ITS REPLACEMENT. SUBMITTER STATED THIS IS THE SECOND NEW DESIGN (5 RIVETS PER SIDE) BAFFLE RECEIVED. THE HOLES ARE ELONGATED, OVERSIZED OR FIGURE 8 SHSDR BJ3RE000003Baffle · defectiveON RECEIPT OF A NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES, LIKE THE ONE REMOVED DUE TO FAILED RIVETS. THIS IS ONE OF THE NEW DESIGN WITH 5 RIVETS PER SIDE, INSTEAD OF THE EARLIER 3 RIVET UNIT. RIVET HOLES 1, 3, AND 5 ON EACH SIDE HAVE EITHER SDR 20000511SH015Baffle · misalignedTWO EACH AN470AD RIVET HEADS FOUND IN OIL SUCTION SCREEN. REMOVED SUMP, FOUND BAFFLE HAD 2 RIVETS WITH HEADS MISSING. FURTHER EXAMINATION SHOWED RIVET HOLES COUNTERSUNK ON THE HEAD SIDE. THIS BAFFLE WAS THE NEW STYLE WITH 5 EACH AN470-4-4 AD RIVETS ON EACH BSDR 20000511SH016Gear · wornON REMOVAL OF OIL PUMP, WEAR WAS NOTED ON ALUMINUM GEAR TEETH FACES. IT LOOKED LIKE IMPROPER HARDENING. WEAR ALSO ON TEETH EDGES. DATE CODE: 36/99. (X)SDR BJ3RE000001Rivet · brokenDURING AN OIL CHANGE, TWO RIVET HEADS (AN470) WERE FOUND IN THE OIL SUCTION SCREEN. THE ENGINE WAS REMOVED AND THE OIL SUMP PULLED OFF. TWO RIVET HEADS WERE MISSING FROM THE OIL SUMP BAFFLE. THESE ARE MS20470AD4-4 RIVETS. THE HOLES ON THE DRIVEN SIDE APPEASDR BJ3RE000002Gear · wornUPON REMOVAL OF THE OIL PUMP, TO CHECK FOR POSSIBLE DAMAGE DUE TO TWO RIVET HEADS FOUND IN THE OIL SUCTION SCREEN, IT WAS NOTED THAT THE ALUMINUM OIL PUMP GEAR HAD EXCESSIVE WEAR ON THE DRIVEN SIDE OF EACH TOOTH, AND CHIPS MISSING ON THE OUTER EDGE OF SEVERAL SDR 20000413SH064Bearing · making metalDURING AN ANNUAL INSPECTION, FOUND METAL IN OIL SCREEN. REMOVED ENGINE AND SENT TO LYCOMING FOR REPAIRS. (X)SDR 20000414SH001Bearing · making metalDURING AN ANNUAL INSPECTION, FOUND METAL SHAVINGS IN OIL SCREEN. REMOVED ENGINE AND SENT TO LYCOMING FOR REPAIRS. (X)SDR 99ZZZX4102Engine · making metalOIL SAMPLE SHOWS AMS6270 STEEL FROM CAMSHAFT, EMS-91 CAST IRON FROM TAPPETS AND ALUMINUM ALLOY WORN 5 PERCENT TIN CONTENT FROM BEARING INSERTS. OIL TIME SINCE LAST CHANGE, 20.2 HOURS. RECENT CHANGE OUT OF OIL SUMP AND TURBO SUPPORT BRACKET RIGHT SIDE. SUBMISDR CA010223013Cylinder · broken(CAN) OPERATOR EXPERIENCED HIGH ON CONSUMPTION. NR 5 CYLINDER REMOVED AND FOUND BROKEN ON CONTROL RING. CYLINDER/PISTON AND RING ASSEMBLY REPLACED.SDR 99ZZZX1645Piston Pin · peeledENGINE FAILURE. HIGH AMOUNTS OF FERROUS AND NON-FERROUS METALS FOUND IN OIL FILTER. FOUND THAT UP TO .1250 INCH OF METAL PEELED FROM NR 1, NR 2, AND NR 6 PISTON RING PLUGS. ALL 6 ROD BEARINGS SEVERELY SCORED FROM FOREIGN METAL. FRONT MAIN BEARING ALSO SEVESDR CA991209026Actuator · failed(CAN) NOSE GEAR SEQUENCE ACTUATOR FAILED, CAUSING MAJOR LEAK IN HYDRAULIC SYSTEM,.THIS CAUSED THE GEAR TO NOT FULLY EXTEND.SDR 99ZZZX292Bracket · crackedDURING A ROUTINE MAINTENANCE CHECK, DISCOVERED THE RIGHT TURBOCHARGER MOUNT CRACKED. THE CRACK OCCURRED JUST BELOW THE UPPER ATTACH STUD BOSS.SDR 99ZZZX293Mount · crackedDURING AN ANNUAL INSPECTION, DISCOVERED A CRACK ON THE ENGINE MOUNT. THE CRACK IS LOCATED ON THE RIGHT SIDE OF THE AFT NOSE GEAR ACTUATOR MOUNT. THIS IS AN AREA OF HIGH STRESS AS IT SERVES AS BOTH ACTUATOR MOUNT AND NOSE GEAR DRAG BRACE SUPPORT.SDR 98ZZZX3884Turbocharger · looseTURBO ON RT SIDE HAD ATTACH NUTS LOOSE. THIS ALLOWED VIBRATION OF TURBO CAUSING SUPPORT CLAMP TO BREAK AND VIBRATION ON MOUNT STUDS. VIBRATION ON STUDS ALLOWED UPPER STUD ON INTAKE OIL SUMP TO CARRY ALL THE TURBO WEIGHT AND CRACK SUMP. SUMP WAS REPLACED. TSDR 99ZZZX962Arm · brokenARM BROKE. REPLACED ARM. SYSTEM OPERATED NORMALLY. ARM COMES AS PART OF CONTROLLER.SDR 99ZZZX192Cam · wornENGINE WOULD NOT START. REMOVED MAG, FOUND CAM FOR POINTS WAS ROUNDED FLAT AND GEARS INSIDE WERE WORN BAD. TALKED TO TECH REP WITH UNISON AND WAS TOLD ON A PRESSURED MAG, 238 HRS WAS MORE THAN THE MFG EXPECTS TO GET OUT OF THE PART. THE NYLON REACTS TO THE SDR 98ZZZX2048Oil Jet · faultyREPETITIVE OIL ANALYSIS REVEALED HIGH WEAR METAL LEVELS FROM CYLINDER AREA WEAR (PISTON, RINGS, LINER). REMOVED AND REPLACED CYLINDERS WITH FACTORY NEW CYLINDER KITS. WHILE CYLINDERS WERE REMOVED, PISTON COOLING OIL JETS WERE REMOVED AND TESTED. FIVE OUT OFSDR 98ZZZX1131Pump · leakingOWNER NOTICED FUEL STAIN ON BELLY OF NEW AIRCRAFT. AFTER INVESTIGATION, FOUND THAT ENGINE DRIVEN FUEL PUMP SEAL HAD EXTRUDED AND FUEL WAS LEAKING. LOG BOOKS INDICATED THE SCREWS HOLDING THE CAP AND SEAL IN PLACE HAD BEEN TORQUED IAW LYCOMING SB 529. ALL SCRSDR 98ZZZX848Pump · leakingFUEL PUMP GASKET BLOWN OUT AND PUMPS LEAK AT THE ADJUSTMENT VALVE PARTING SURFACE GASKET. SUBMITTER STATED THIS IS THE SECOND PUMP FAILURE ON THIS MODEL AIRPLANE, AND BOTH WERE NEW AIRCRAFT.SDR 97ZZZX4963Magneto · wornPILOT REPORTED HIGH MAG DROP ON LEFT MAG. RUN-UP INDICATED NEARLY COMPLETE MAG FAILURE. DURING DISASSEMBLY, A LARGE AMOUNT OF DUST WAS NOTED IN THE AREA OF THE CONTACT ASSEMBLY AND CONTACTS WERE BARELY OPENING. THE CAM WAS FOUND SEVERELY WORN. NO REASON FO
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