Lycoming IO-360-L2A
Service difficulty reports · 994
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 = 'IO360L2A' 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 = 'IO360L2A' 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 2003FA0000272Spark Plug · fouledDURING STALL MANEUVERS, THE ENGINE HESITATED AND RAN ROUGH WHEN POWER WAS BROUGHT TO IDLE. AS ITEMS WERE BEING INSPECTED, THE SPARK PLUGS WERE FOUND WITH HEAVY DEPOSITS. THE PLUGS HAD BEEN CLEANED AND TESTED ABOUT 23 HOURS PREVIOUS TO THE EVENT. TYPICALLY, FOUSDR 2003FA0000273Fuel Control · erraticTHE CREW REPORTED THAT THEY WERE EXPERIENCING A VERY SLOW IDLE DURING PRE TAKEOFF IDLE CHECK. IT WAS ADJUSTED. THIS ENGINE/FUEL CONTROL COMBINATION HAS BEEN THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE CONCERNING UNSTABLE IDLE AS WELL AS VARIOUS SERVICE BULLETINSSDR 2003FA0000274Fuel Control · erraticDURING A PRE TAKEOFF IDLE CHECK, THE ENGINE IDLED VERY SLOW AND BEGAN TO QUIT. THIS ENGINE FUEL CONTROL COMBINATION HAS BEEN DIFFICULT TO MAKE MAINTAIN A STABLE IDLE AND REQUIRES A SIGNIFICANT AMOUNT OF BETWEEN INSPECTION ADJUSTMENTSSDR 2003FA0000271Flow Divider · stickingDURING GROUND OPERATIONS, THE CREW FELT A ROUGH AND UNSTABLE IDLE. AN INSPECTION WAS MADE OFTHE ENGINE AND SYSTEMS. 2 NOZZLES WERE DETERMINED TO HAVE AN IRREGULAR SPRAY PATTERN. AFTER CLEANING, 1 WAS REPLACED. ALSO, THE FUEL FLOW DIVIDER WAS FOUND TO BE STICKISDR 2003FA0000275Fuel Control · erraticDURING THE PRE TAKEOFF IDLE CHECK, THE ENGINE QUIT. THE AIRCRAFT WAS RETURNED TO THE RAMP. AS IS OFTEN THE NEE, THE IDLE SPEED AND MIXTURE WERE ADJUSTED.SDR 2003FA0000276Bulkhead · crackedTHE SPINNER AFT BULKHEAD WAS FOUND CRACKED. IT WAS REPLACED WITH A NEW UNIT...SDR 2003FA0000277Bulkhead · crackedAFT SPINNER BULKHEAD WAS FOUND CRACKED, IT WAS REPLACED WITH A NEW PART.SDR 2003FA0000254Spinner · crackedTHE PROP SPINNER ON THE 172R/S SERIES CRACKS VERY FREQUENTLY. THE CRACKS RADIATE FROM THE CUT OUT FOR THE PROP BLADES.SDR 2003FA0000255Spinner · crackedTHE PROP SPINNER ON THE 172R/S SERIES CRACKS VERY FREQUENTLY. THE CRACKS RADIATE FROM THE CUT OUT FOR THE PROP BLADES.SDR 2003FA0000256Flow Divider · stickingDURING CRUISE THE CREW REPORTED AROUGH ENGINE. AFTER INSPECTING APPLICABLE SYSTEMS, THE FUEL FLOW DIVIDER WAS CHANGED AFTER HAVING BEEN FOUND STICKING INTERNALLY.SDR 2003FA0000257Flow Divider · stickingDURING CRUISE THE CREW REPORTED AROUGH ENGINE. AFTER INSPECTING APPLICABLE SYSTEMS, THE FUEL FLOW DIVIDER WAS CHANGED AFTER HAVING BEEN FOUND STICKING INTERNALLY.SDR 2003FA0000258Flow Divider · stickingDURING CRUISE THE CREW REPORTED A ROUGH ENGINE. AFTER INSPECTING APPLICABLE SYSTEMS, THE FUEL FLOW DIVIDER WAS CHANGED AFTER HAVING BEEN FOUND STICKING INTERNALLY.SDR 2003FA0000259Fuel Control · out of adjustTHE CREW REPORTED A PARTIAL POWER LOSS DURING STALL RECOVERY. THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE REGARDING UNSTABLE IDLE/MIXTURE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONLY DURING INSPECTION SDR ZDU2003F00000Elt · failedDURING ROUTINE MECHANIC CHECK, ELT REMOTE SWITCH FOUND INOPERATIVE, FAILURE TRACED TO ELT ITSELF. ALL UNITS FAILED REMOTE TEST BETWEEN 400-600 HOURS. ALL OTHER ELT FUNCTIONS, NORMAL.SDR CA030131007Wire · chafed(CAN) CREW REPORTED INSTRUMENT PANEL LIGHTS WOULD OPERATE INTERMITTANTLY IN FLIGHT. CONDITION ONLY SEEMED TO OCCUR WHEN PILOT OPERATED THROTTLE CONTROL. MAINTENANCE INVESTIGATING DEFECT DETERMINED THE AIRCRAFT WIRING BUNDLE BEHIND THE PANEL WAS POSITIONED IN SSDR 2003FA0000098Crankshaft · damagedTHIS CRANKSHAFT ALONG WITH FOUR OTHERS OF SAME KIND AND AGE, HAVE EXTREMELY HEAVY GRAINULAR INDICATIONS ON JOURNALS, RADII, FLANGE RADIUS AND SEAL SURFACE WHEN VIEWED UNDER MAGNETIC PARTICLE INSPECTION, WET METHOD. THESE INDICATIONS ARE EXTREMELY RARE WITH CRASDR 2003FA0000099Crankshaft · damagedTHIS CRANKSHAFT ALONG WITH FOUR OTHERS OF SAME KIND AND AGE, HAVE EXTREMELY HEAVY GRAINULAR INDICATIONS ON JOURNALS, RADII, FLANGE RADIUS AND SEAL SURFACE WHEN VIEWED UNDER MAGNETIC PARTICLE INSPECTION, WET METHOD. THESE INDICATIONS ARE EXTREMELY RARE WITH CRASDR CA030117002Check Valve · unserviceable(CAN) THE VACUUM SYSTEM CHECK VALVE MANIFOLD WAS DETERMINED TO BE UNSERVICEABLE DUE TO LEAKS PAST THE CHECK VALVE DISC. THIS FINDING WAS DETERMINED BY FOLLOWING THE INSPECTION CRITERIA CONTAINED IN CESSNA SB 02-37-04. THE PART WAS REMOVED FROM SERVICE AND A RESDR CA030117001Check Valve · unserviceable(CAN) THE VACUUM SYSTEM CHECK VALVE MANIFOLD WAS DETERMINED TO BE UNSERVICEABLE DUE TO LEAKS PAST THE CHECK VALVE DISC. THIS FINDING WAS DETERMINED BY FOLLOWING THE INSPECTION CRITERIA CONTAINED IN CESSNA SB02-37-04. THE PART WAS REMOVED FROM SERVICE AND A RESDR W6N2003F00000Static Port · contaminatedTHE PILOT HAS BEEN COMPLAINING ABOUT THE VSI AND THE ALTIMETER JUMP APPROX 100-200 FEET AND THEN SETTLE DOWN. THIS ONLY HAPPENS DURING A LIGHT RAIN OR HEAVY MIST (NO ICE). WHEN HE TURNS THE ALTERNATE STATIC ON, THE PROBLEM GOES AWAY. THE STATIC PORT HAS BEESDR 2003FA0000010Bearing · delaminatedBEARING DELAMINATED PART DEFECT REQUEST PART BE ANALYSED BY MANUFACTURER OR FAA.SDR CA021118007Tank · cracked(CAN) HEADER TANK FOUND LEAKING. UPON REMOVAL, TANK HAS A 1 INCH CRACK ON TOP OF WELD AROUND BOTTOM AFT SIDE OF TANK.SDR 2002FA0001272Lifter · brokenWHILE DRAINING OIL, FOUND A PIECE OF STEEL WITH A ROUNDED EDGE. ALSO FOUND METAL IN THE OIL FILTER. REMOVED NR 2 CYLINDER AND FOUND THE INTAKE VALVE LIFTER HAD PIECES FRACTURED OFF OF THE EDGE. THE CAM WAS SPALLED AND THE NR1 CYLINDER INTAKE VALVE LIFTER WASDR CA021022008Starter · failed(CAN) STARTER NOT ENGAGING. STARTER REPLACED WITH SERVICEABLE UNIT.SDR 2002FA0001267P-Lead · failedREPORTS OF INTERMITTENT LT MAG FAILURE. TROUBLESHOT AND REMOVED ENTIRE P-LEAD ASSEMBLY. FOUND SHIELDING SOLDER / CRIMP AT SWITCH END CUT INTO CENTER CORE VERY SLIGHTLY. REPLACED P-LEAD ASSEMBLY. NO ADDITIONAL REPORTS OF MAG FAILURE.SDR CA021009026Pressure Switch · failed(CAN) PILOT NOTICED LOW OIL PRESSURE LIGHT AND HOBBS METER HAD STOPPED. INVESTIGATION REVEALED THAT SWITCHP/N 83278 HAD FAILED INTERNALLY ALLOWING OIL TO COME UP THROUGH THE SWITCH AND CONNECTOR.SDR CA021010004Impulse Coupling · cracked(CAN) OUR MAINTENANCE SCHEDULE APPROVAL FOR 172R CALLS FOR MAG OVERHAUL AT 700 HOURS +/- 10 HOURS. AT 657.9 HR MAGS WERE CHANGED FOR ROUGH ENGINE (2-3 SEC) SNAG. AT OVERHAUL MAG IMPULSE COUPLINGS FOUND CRACKED AT HUB.SDR CA021022007Starter · shorted(CAN) PILOT REPORTED DURING PRE-TAKE-OFF RUN-UP: 'OVERCHARGING DURING RUN UP, COMPLETE ELECTRICAL MALFUNCTION 30 SEC. THEN COMPLETE ELECTRICAL FAILURE BURNING SMELL (PALASTIC RUBBER). CYCLED MASTER NO EFFECT, SHUTDOWN.' STARTER FOUND BURNED UP AND SHORTED, STSDR 2002FA0001084Manifold · malfunctionedTHE CREW REPORTED A MOMENTARY POWER ROUGHNESS. THE AIRCRAFT FUEL CONTROL SYSTEM AND IGNITION SYSTEM WERE INSPECTED. THE FUEL MANIFOLD WAS REPLACED ALONG WITH 2 INJECTOR NOZZLES. A GROUND OPERATIONAL CHECK WAS PERFORMED. FOLLOWING THAT A FUNCTIONAL CHECK FLIGHTSDR 2002FA0001065Pump · looseBOLTS LOOSE IN FUEL PUMP DIAPHRAGM.SDR 2002FA0001088Engine · roughDURING FLIGHT, THE CREW REPORTED A ROUGH ENGINE. THE FLIGHT WAS TERMINATED AND MAINTENANCE WAS PERFORMED. THE SPARK PLUGS WERE CLEANED AND THE INJECTOR NOZZLES INSPECTED..SDR CA021022005Starter · stuck(CAN) STARTER NOT ENGAGING. STARTER REPLACED WITH SERVICEABLE UNIT. AFTER SENDING THE UNIT TO LAMAR FOR WARRANTY CONSIDERATION, AND TO DISCOVER WHAT WAS ACCTUALLY WRONG WITH THE UNIT, WE WERE INFORMED THE THE WARRANTY WILL NOT BE HONOURED. LAMAR DESCRIBED THASDR 2002FA0000982Bearing · separatedCONTAMINATION FOUND IN SUCTION SCREEN. DISASSEMBLY OF ENGINE FOUND ONE OF THE CENTER MAIN BEARINGS BABBIT MATERIAL STARTED TO SEPARATE FROM SHELL. DATE CODE ON BEARING IS (07-2000).SDR MNZA0207008Reservoir · crackedUPON INSPECTION, IT WAS NOTED THAT A FUEL STAIN WAS EVIDENT ON THE UNDERBELLY OF THE AIRCRAFT IN THE VACINITY OF THE FUEL SELECTOR VALVE. CABIN FLOORING AND UPHOLSTERY WAS REMOVED AND THE FUEL SELECTOR AND FUEL RESERVOIR WAS REMOVED AND INSPECTED. THE RESEVOISDR CA020729008Servo · failed(CAN) PILOT REPORTED THAT THE ENGINE QUIT WHEN LANDING AND THROTTLE PULLED TO FULL IDLE. GROUND RUN CONFIRMED PROBLEM. MIXTURE CONTROL ADJUSTED TO GET PROPER RISE AT IDLE CUT-OFF - RUN UP AND FULL IDLE OPERATION NOW NORMAL.SDR 2002FA0000868Servo · inoperativeAFTER RECEIVING THE ENGINE BACK FROM MFG, YELLOW TAGGED, STICKERED IN THE LOG BOOK AIRWORTHY, REINSTALLED ENGINE. GROUND RUN FOR LEAKS BUT WOULD NOT IDLE SMOOTH UNTIL IDLE/MIXTURE WAS SET AT 625 RPM. OK`D TEST FLIGHT AND IT QUIT ON LANDING. THIS AIRCRAFT DSDR 2002FA0000818Washer · brokenDURING SCHEDULED TIME CHANGE OF THE ENGINE-DRIVEN FUEL PUMP, THE SMALL RETAINING WASHER FOR THE PUMP SHAFT SPRING WAS FOUND BROKEN.SDR CA020619002Shaft · sheared(CAN) INVESTIGATION OF A SEVERE NOSEWHEEL SHIMMY REPORT REVEALED THAT THE SHIMMY DAMPENER SHAFT HAD SHEARED. BOTH HALVES OF THE ASSEMBLY REMAINED ATTACHED BUT THE UNIT COULD NO LONGER FUNCTION AS DESIGNED. THE FAULTY UNIT WAS REMOVED FROM SERVICE AND REPLACED SDR 2002FA0000731Alternator · failedCHARGING SYSTEM CEASED TO FUNCTION. DIAGNOSIS WAS ALTERNATOR FAILURE, PROBABLY BREAKDOWN OF DIODES. NO EXTERNAL SIGNS OF FAILURE.SDR CA020606017Bulkhead · cracked(CAN) AFT SPINNER BULKHEAD FAILED AT RADIUS OF FLANGE AT CUTOUT FOR PROPELLER. SPINNER DISTORTED AS RESULT OF THE BULKHEAD FAILURE.SDR CA020610004Pump · failed(CAN) FOLLOWING THE SB OF THE CESSNA 01-73-01A, A NEW MECHANICAL FUEL PUMP WAS INSTALLED. WE BELIEVE THE PUMP WAS DEFECTIVE, BECAUSE IT WAS NOT POSSIBLE FOR US TO HAVE RPM HIGHER THAN 1900. MOREOVER, AT 1900 RPM, A REDUCTION IN FUEL FLOW WAS NOTICED. FOR NOW, SDR 2002FA0000977Bulkhead · crackedDURING A PRE-FLIGHT INSPECTION THE PILOT NOTED THAT SPINNER BULKHEAD WAS CRACKED.SDR 2002FA0000399Manifold · detachedTHIS AIRCRAFT USES DUAL VACUUM PUMPS. THESE PUMPS ARE CONNECTED TO THE VACUUM SYSTEM VIA A MANIFOLD ASSEMBLY. THIS MANIFOLD PERFORMS TWO IMPORTANT FUNCTIONS, ONE TO ALLOW FOR A COMBINED SOURCE OF VACUUM FROM THESE TWO PUMPS, AS WELL AS PROVIDE AN ISOLATION FUNSDR CA020301004Bulkhead · cracked(CAN) SPINNER WAS NOTICED DEFORMED DURING GROUND HANDLING.SPINNER BULKHEAD FOUND CRACKED AND FLANGE SEPERATED CAUSING SPINNER DEFORMATION.SDR 2002FA0000278Servo · malfunctionedREPORTED ENGINE LOST POWER TWICE (ENG RUNNING 1 HOUR).SDR 2002FA0000152Pin · shearedWHILE REMOVING THE TRIM TAB ACTUATOR FOR SERVICE, BOTH GROOVE-PINS (P/N 3/32X.38TYPE3) WHICH ATTACH THE ROLL CHAIN SPROCKET, (P/N 0310332-0) TO THE SCREW-INTERNAL THREADS (P/N 1260049-1) OF THE TRIM TAB ACTUATOR WERE FOUND TO HAVE SHEARED. THIS ALLOWED THE SDR CA011123001Plate · broken(CAN) THE CORNER SECTION OF SPINNER AT LEADING EDGE OF PROPELLER BLADE CUT-OUT BADLY BENT (PEELED BACK) BY CENTRIFUGAL FORCE. THIS WAS CAUSED BY THE ADJACENT CORNER SECTION OF THE BACKPLATE (AROUND ANCHOR NUT) BREAKING OFF DURING OPERATION. CESSNA HAS RECOGNIZSDR 2001FA0000395Injector · cloggedPILOT REPORTED THAT DURING CLIMBOUT THE ENGINE BEGAN RUNNING ROUGH, AT WHICH TIME HE RETURNED TO THE AIRPORT (PHX). TECHNICIAN COULD NOT DUPLICATE THE MALFUNCTION ON A GROUND RUN UP. THE FUEL INJECTOR NOZZLES WERE REMOVED & INSPECTED AND THE NR 2 INJECTOR WASSDR 2001FA0000309Injector · malfunctionedENGINE FAILED TO DEVELOP FULL POWER AFTER LONG POWER OFF DECENT AT HIGH DENSITY ALTITUDE CONDITIONS. CORRECTIVE ACTIONS TAKEN: FUEL INJECTOR SERVO REPAIRED BY CRS/NE2R WO R01-042240. FLOW DIVIDER MODIFIED IAW SI. C/W SI AND SB.SDR CA010831013Brushes · broken(CAN) - AIRCRAFT ALTERNATOR FAILED. - ALTERNATOR INTERIOR INSPECTION REVEALED A BROKEN BRUSH BLOCK ASSEMBLY CAUSED BY A INCORRECT INSTALLATION
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