Lycoming IO-360-B1B
Service difficulty reports · 46
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 = 'IO360B1B' 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 = 'IO360B1B' 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 2026FA0000879Impulse Coupling · shearedIMPULSE COUPLING FAILED ON SLICK 4373 MAGNETO. MAGNETO HAD 230 HOURS AND 123 START CYCLES SINCE 500 HOUR IRAN. TOTAL TIME ON MAGNETO 765 HOURS. IMPULSE COUPLING WAS REPLACED WITH NEW M3529 SLICK IMPULSE COUPLING AT TIME OF IRAN DUE TO EXCESSIVE WEAR ON EXISTINSDR 2026FA0000186Quick Disconnect · defectiveWHILE IN FLIGHT THE LEFT ENGINE RPM READING BECAME ERRATIC, GOING FROM NORMAL TO PAST RED LINE QUICKLY BACK AND FORTH. PIC PRECAUTIONARY SHUT DOWN ENGINE AND RETURNED TO HOME FIELD. AFTER TROUBLESHOOTING IT WAS FOUND THE LEFT HAND TACH GENERATOR SENSOR PLASTICSDR CA140205005Tube · defective(CAN) DISCOVERED A PIN HOLE IN THE SIDE WALL OF THE INNER TUBE.SDR CA120313002Tappet · spalled(CAN) ENGINE HAD OIL PRESSURE FLUCTUATION ON RUN-UP. OIL FILTER FOUND TO HAVE EXCESSSIVE METAL CONTAMINATION. ENGINE WAS PULLED FOR REPAIR. UPON DISASSEMBLY THE NR 2 CAMSHAFT LOBE WAS FOUND EXTREMELY WORN AND THE NR 1 CAMSHAFT LOBE WAS FOUND DAMAGED AS WELL.SDR CA110416001Landing Gear · deteriorated(CAN) THE SWITCH KEY WAY IS SUCH THAT THE CENTER TERMINAL IS VERY CLOSE TO STRUCTURE. THE INSULATING TAPE THAT WAS INSTALLED DETERIORATED ALLOWING THE SCREW HEAD TO CONTACT STRUCTURE AND SHORT OUT THE LANDING GEAR RELAY C/B.SDR CA110322008Fitting · restricted(CAN) ENGINE WAS RECEIVED FRESH FROM OVERHAUL FACILITY WITH THE ABOVE MENTIONED ENG DRIVEN FUEL PUMP & FITTINGS. POST INSTALL GND RUNS WERE UNABLE TO ACHIEVE TAKEOFF POWER. AFTER 2300 RPM FURTHER POWER LEVER ADVANCEMENT RESULTED IN LOSS OF RPM & INCREASE IN SDR CA101108014Disk · cracked(CAN) DURING REPLACEMENT OF A BLOWN WHEEL AND OVERHAUL OF A WHEEL ASSEMBLY, THE DISK WAS REMOVED, MEASURED FOR WEAR AND INSPECTED FOR DEFECTS. AT THIS TIME A CRACK WAS NOTICED ON THE INNER SIDE OF THE DISK. THIS SIDE IS NOT EASILY VISIBLE DURING SERVICE. THESDR CA090918005Cylinder · cracked(CAN) DURING THE CRUISE PORTION OF FLIGHT, THE RT ENG BEGAN RUNNING VERY ROUGH. CREW REDUCED POWER SETTING ON RT ENGINE AND CONTINUED ON TO DESTINATION. UPON ARRIVAL, AN INSP REVEALED A CRACKED CYL AND LEAKING OIL ON INSIDE OF THE COWLING. MX REPLACED THE CYSDR CA080116022Mount · mismanufactured(CAN) AFTER ENGINE REPLACEMENT FOR OVERHAUL A PRELIMINARY GROUND RUN WAS CARRIED OUT. IT WAS FOUND THAT THE PROPELLER WOULD NOT FEATHER WHEN PERFORMING A GOVERNOR CHECK. THE PROBLEM WAS TRACED TO THE GOVERNOR MOUNT PAD WHICH HAD NOT HAD AN OIL GALLERY COMPLETESDR CA070322011Window · broken(CAN) IN CRUISE FLIGHT, AT 6000 FT, THE MAJORITY OF THE LT SIDE COCKPIT WINDOW DEPARTED THE AC. THE AC BEING CLOSE TO ITS INTENDED DESTINATION CONTINUED ON AND LANDED WITHOUT INCIDENT. A FLIGHT PERMIT WAS ISSUED AND THE AIRCRAFT FLOWN TO MAIN BASE FOR EVALUATISDR CA061117004Cylinder Head · cracked(CAN) DURING A ROUTINE 100 HOUR INSPECTION A CRACK WAS FOUND ON THE RH ENGINE #4 CYLINDER STARTING AT THE TOP SPARK PLUG HOLE AND CONTINUING DOWN TO THE EXHAUST PORT. THE CYLINDER WAS REMOVED AND REPLACED. (TC# 20061117004)SDR CA061025007Control Cable · defective(CAN) AFTER A ROUTINE TRAINING FLIGHT THE PILOT REPORTED THAT THE RT PROP CONTROL WAS VERY STIFF AND SPRINGY AND THE PROP WAS SLOW TO FEATHER. THE CONTROL WAS DISCONNECTED FROM THE GOVERNOR AND THE DEFECT WAS CONFIRMED TO BE THE CONTROL CABLE. THE TTSN FOR THESDR CA061025006Spar · cracked(CAN) DUING INSPECTION IAW FAA AD 90-08-14 AND SB53-2269 REV 2 SHORT CRACKS WERE VISUALLY FOUND EMINATING FROM 2 HUCK BOLT LOCATIONS ON THE LT FORWARD WING SPAR CARRY THROUGH WEB FACE. CRACKS WERE CONFIRMED BY LPI. REPAIRED IAW MFG FAA APPROVED DRAWING 58-4000SDR CA050127002Control Horn · cracked(CAN) DURING SHEET METAL REPAIR OF THE RT ELEVATOR ASSY IT WAS NOTED THAT THE ELEVATOR SKIN AT THE CONTROL HORN ATTACH POINT WAS CRACKED. FURTHER INSPECTION OF THE CONTROL HORN ASSY REVEALED A LARGE CRACK PROGRESSSING FROM 1 OF 4 ELEVATOR TO CONTROL HORN MOUNTSDR CA040624006Motor · failed(CAN) UPON REPLACEMENT, TESTING OF LANDING GEAR MOTOR RECEIVED FROM AN APPROVED OH FACILITY IT WAS DETERMINED MOTOR WAS SPINNING IN REVERSE DIRECTION. MOTOR WAS REMOVED AND BENCH TESTED TO ELIMINATE AN AC WIRING PROBLEM. MOTOR ROTATED IN WRONG DIRECTION AGAISDR CA030908004Alternator · failed(CAN) NOTICED NO CHARGE, MINIMIZED ELECTRICAL LOAD TURNED OFF ALTERNATORS RESET ON CHANGED RELAY LT TO RT. NO CHARGE TURNED MASTER OFF, 25 MILES FROM AIRPORT, TURNED MASTER ON AND 1 RADIO GOT ATIS AND CALLED TOWER LOST ALL POWER, CALLED TOWER ON CELL DID A MSDR 2003FA0000665Bolt · shearedRV-8, N9868K, LANDED AND BEGAN ROLLOUT WHEN THE RIGHT MAIN LANDING GEAR ASSEMBLY DEPARTED AIRCRAFT. INVESTIGATION REVEALED THE RIGHT MAIN LANDING GEAR LEG ATTACH BOLT SHEARED/BROKE. FAILED LANDING GEAR PARTS HAVE BEEN SENT FOR ANALYSIS.SDR CA030321004Shaft · cracked(CAN) RT ENGINE WOULD NOT START. DURING TROUBLESHOOTING THE MAGNETO WAS REPLACED. DURING THE INSPECTION OF THE MAGNETO, IT WAS NOTICED THAT THE MAGNETO SHAFT WAS CRACKED AT THE POINT WHERE THE PHENOLIC CAM FOR THE POINTS IS INSERTED INTO THE SHAFT. ALSO EXCESSDR CA020418004Rib · cracked(CAN) THE RIB WAS CRACKED AND BROKEN IN THE NOSE AREA AND THE FORWARD ANCHOR NUT FOR THE FLAP ACTUATOR ATTACH BRACKET WAS BROKEN. WITH THE FLAPS UP THE AME STEPED ON THE FLAP WALKWAY AND A LOUD NOISE WAS HEARD. HE APPLIED UP AND DOWN LOADS TO THE FLAP AT THE TSDR AU001032Blade · separated(AUS) LEFT PROPELLER BLADE SECTION SEPARATED APPROXIMATELY 200 MM (7.87 INCHES) FROM THE BLADE TIP. FAILURE ORIGINATED FROM A PREVIOUS STONE STRIKE THAT HAD NOT BEEN ADEQUATELY BLENDED OUT. (X)SDR CA000328005Pin · missing(CAN) THE LT MAGNETO SWITCH WAS FOUND WITH THE KNOB AND ACTUATOR SEPARATED FROM THE SWITCH. IT APPEARS THE INTERFERENCE FIT PIN INSIDE THE SWITCH THAT HOLDS THE ACTUATOR IN PLACE WAS MISSING. NO EVIDENCE OF THE MISSING PIN WAS FOUND INSIDE THE SWITCH.SDR AU000346Fuel Tank · contaminated(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA)SDR AU000203016Actuator · failed(AU) AFTER TAKEOFF, THE LANDING GEAR FAILED TO RETRACT. THE AIRCRAFT RETURNED AND A SUBSEQUENT INSPECTION REVEALED THAT THE LANDING GEAR MOTOR HAD FAILED THE MOTOR WAS REPLACED. THE SUBMITTER STATES THAT THE AIRCRAFT IS PRIMARILY USED FOR FLIGHT TRAINING SO SDR CA000203016Actuator · failed(CAN) AFTER TAKEOFF, THE LANDING GEAR FAILED TO RETRACT.THE AIRCRAFT RETURNED AND A SUBSEQUENT INSPECTION REVEALED THAT THE LANDING GEAR MOTOR HAD FAILED.THE MOTOR WAS REPLACED. THE SUBMITTER STATES THAT THE AIRCRAFT IS PRIMARILY USED FOR FLIGHT TRAINING SO ISDR CA000118001Brace · cracked(CAN) THE AIRCRAFT WAS IN FOR A 100 HR. INSPECTION. WHEN THE COWLS WERE REMOVED FROM THE RT ENGINE IT WAS NOTICED THAT AN O/B DIAGONAL BRACE WAS BROKEN. THE MOUNT WAS REMOVED AND SHIPPED TO AN APPROVED AMO FOR WELDING REPAIRS AND TUBE REPLACEMENT.SDR AU990459Strut · cracked(AUS) LEFT AND RIGHT MAIN LANDING GEAR CYLINDERS P/N 35815246-1 (LT) AND P/N 35815246-3 (RT) CRACKED IN THE RADIUS OF THE LOWER BRACE ATTACHMENT FITTINGS.SDR AU990416026Switch · failed(AU) ON APPROACH, THE LANDING GEAR FAILED TO EXTEND ELECTRICALLY. THE LANDING GEAR MOTOR WAS REPLACED. SEVERAL FLIGHTS LATER THE SAME FAULT OCCURRED AGAIN. ON A SUBSEQUENT TEST, THE SELECTOR SWITCH WAS FOUND TO BE THE CAUSE.SDR CA990311002Switch · failed(CAN) AFTER LEFT ENGINE WAS STARTED AND DURING THE MAG DROP TEST, ELECTRICAL SMELL WAS DETECTED AND ARCING COULD BE HEARD. THE MAGNETO SWITCH WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. A SUBSEQUENT INSPECTION OF A MAGNETO SWITCH REVEALED THAT IT WAS SDR AU980859Skin · cracked(AUS) RUDDER CONTAINED FOUR CRACKS IN THE AREA OF THE TOP PIVOT. FURTHER INVESTIGATION FOUND DELAMINATION AND LOW STRENGTH IN THE MATERIAL. SUSPECT CAUSED BY THE USE OF TIME EXPIRED MATERIALS. PART TOTAL CYCLES: 397.SDR CA980602058Motor · failed(CAN) LANDING GEAR FAILED TO EXTEND USING THE NORMAL ELECTRICAL EXTENSION SYSTEM. THE LANDING GEAR WAS EXTENDED MANUALLY AND AIRCRAFT LANDED WITHOUT INCIDENT AFTER CONFIRMATION GEAR DOWN AND LOCKED. SUBSEQUENT INVESTIGATION REVEALED THE LANDING GEAR ELECTRICSDR CA980407006Drag Brace · cracked(CAN) NOSE LANDING GEAR UPPER DRAG BRACE FOUND CRACKED ON INSPECTION.SDR CA980311005Motor · failed(CAN) LANDING GEAR FAILED TO COMPLETELY RETRACT AFTER TAKEOFF. GEAR SELECTED DOWN AND NO MOVEMENT. GEAR RESELECTED UPN AND GEAR CIRCUIT BREAKER POPPED. FLY BY INDICATED GEAR DOWN. AIRCRAFT LANDED. GEAR RETRACT MOTOR REPLACED. ARMATURE BADLY ERODED, BRUSHES SHOSDR CA970904034Stud · sheared(CAN) ON DAILY INSPECTION THE UPPER FORWARD CYLINDER BASE STUD ON THE NR2 CYLINDER WAS FOUND SHEARED OFF. THE STUD WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.SDR CA970421061Dry Air Pump · loose(CAN) DURING TRAINING THE RIGHT HAND ENGINE OIL PRESSURE BEGAN TO DROP. ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED SAFELY. INSPECTION FOUND THE DRY AIR PUMP LOWER ATTACHING HARDWARE WAS NOT TIGHT, CAUSING A SUBSTANTIAL OIL LEAK. THE HARDWARE WAS SECURED AND SDR CA960924025Magneto · shaft sheared(CAN) THE RIGHT ENGINE WOULD NOT START. INSPECTION REVEALED THE #2 ENGINE LEFT HAND MAGNETO HAD SEPARATED FROM THE CASE BREAKING THE MAG CASTING AT THE MOUNTING FLANGES & THE MAGNETO SHAFT WAS BENT. FURTHER INVESTIGATION FOUND THE FUEL PUMP, CAMSHAFT, VACUUM PSDR CA960909026Bracket · slipped(CAN) AFTER TAKEOFF, THE LANDING GEAR FAILED TO RETRACT, THE AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT. A SUBSEQUENT INSPECTION REVEALED THAT THE LANDING GEAR SAFETY SWITCH HAD SLIPPED THUS NOT ACTUATING THE SWITCH WHEN THE GEAR WAS FULLY EXTENDED. THE SAFSDR CA960826044Crankcase · cracked(CAN) DURING A SCHEDULED INSPECTION A CRACK WAS FOUND ON THE RH ENGINE BETWEEN #2 AND #4 CYLINDERS, APPROXIMATELY 4" LONG PROPAGATING FROM THE #4 CYLINDER FLANGE. THE ENGINE WAS REPLACED.SDR CA960723009Distributor Gear · loose electrode(CAN) THE MAGNETO WAS SENT IN FOR WARRANTY REPAIR. A TEST FOUND THAT THE UNIT WAS FIRING ON ONE CYLINDER. INSPECTION FOUND THAT THE ELECTRODE HAD BROKEN FREE OF ITS MOUNTING. THE UNIT WAS GIVEN A 500 HOUR SERVICE AND THE DEFECTIVE PART REPLACED AND THE UNIT RESDR CA960709003Bushing · oversized(CAN) RIGHT HAND MAIN LANDING GEAR BUSHING PURCHASED NEW FROM BEECHCRAFT FOUND TO BE OUTSIDE THE TOLERANCE OF THE MAINTENANCE MANUAL. THE BUSHING WAS RETURNED FOR A CREDIT.SDR 96ZZZX3700Rotor · shaft failedENGINE NO START. TROUBLESHOOTING ISOLATED TO MAGNETO. OPENED MAGNETO HOUSING TO INSPECT. REMOVED DISTRIBUTOR BLOCK AND GEAR ASSEMBLY. NOTICED ROTOR GEAR APPEARED DETACHED. REMOVED GEAR AND FOUND SHAFT HAD BROKEN AT AREA BELOW POINT CAM SLOT. SLOTTED PORTSDR CA960626002Crankcase · cracked(CAN) WHILE REMOVING THE #2 ENGINE TO FACILITATE REPLACEMENT OF A CRACKED ENGINE MOUNT, A 6" CRACK WAS FOUND ON THE CRANKCASE, JUST AFT OF THE PROP UNDER THE FORWARD BAFFLE. THE ENGINE WAS REPLACED.SDR CA960515002Static Sensor · leak(CAN) PIEZO STATIC SENSOR HOUSING LEAKING IN EXCESS OF LIMITSSDR CA960502006Distributor Gear · loose electrode(CAN)THE MAGNETO WAS SENT IN FOR OVERHAUL, 215 HOURS AFTER A 500 HOUR INSPECTION. THE CUSTOMER HAD SNAGGED IT FOR NOT FIRING. INTERNAL INSPECTION FOUND THAT THE ELECTRODE AND AXLE ASSEMBLY HAD COME LOOSE F ROM THE GEAR ITSELF. THE GEAR IS OF THE NEWEST TYPE ANSDR CA960321012Alternator · shorted field(CAN)DURING CLIMB BOTH ALTERNATORS WENT OFF LINE. AN INSPECTION REVEALED THAT THE RIGHT HAND COOLING FAN HAD SEPARATED FROM THE ALTERNATOR AND SOME OF THE PIECES WERE FOUND INSIDE THE ALTERNATOR THUS SHORTING THE FIELD. THE SHORTED FIELD CAUSED A VOLTAGE REGULSDR CA960212015Vane · stuck(CAN)ON TAKEOFF THE LEFT HAND ENGINE WOULD NOT DEVELOP FULL POWER. INSPECTION REVEALED THE ALTERNATE AIR DOOR CABLE TO BE OUT OF RIG, CAUSING THE AFT VANE TO JAM IF THE CONTROL CABLE WAS PUSHED TOO FAR TOWARDS THE FILTER POSITION. THE ALTERNATE AIR CONTROL WASSDR CA960212013Vane · frozen(CAN)DURING TAKEOFF ROLL A LEFT YAW WAS NOTICED AND ONCE AIRBORNE THE FUEL FLOW AND MANIFOLD PRESSURE ON THE LEFT ENGINE WAS NOTED TO BE LOW. THE ALTERNATE AIR CONTROL WAS NOTED IN THE HEAT POSITION. WHEN THE ALTERNATE AIR WAS RETURNED TO THE FILTER POSITION
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