Lycoming IO-320-B1A
Service difficulty reports · 76
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 = 'IO320B1A' 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 = 'IO320B1A' 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 EY2R20180320001Screw · backed outPROPELLER FEATHERED ON SHUT-DOWN. ON PROPELLER DISASSEMBLY, THE LATCH ASSEMBLY WAS FOUND LOOSE INSIDE OF CYLINDER. 4 LATCH ASSEMBLY ATTACHING SCREWS HAD BACKED OUT (REASON UNKNOWN).SDR CA151027008Crankcase · cracked(CAN) DURING 100 HR INSPECTION FOUND ALTERNATOR MOUNTING BRACKET AND BOLTS WORN CAUSING A VIBRATION WHICH BROKE ALTERNATOR TIGHTENER MOUNTING BOLT AND CRACKED CRANKCASE BOSS AT THIS LOCATION. ALTERNATOR MOUNTING BOLTS AND ALTERNATOR MOUNTING ATTACH HOLES SEVESDR CA130118012Torque Link · broken(CAN) ON AN APPROACH TO AIRPORT, THE PILOT NOTICED THE ABSENCE OF GREEN LIGHT, AND THE GEAR THAT WAS NOT EXTENDING IAW THE MIRROR VIEW. THE PROBLEM WAS DIAGNOSED VIA RADIO WITH THE HELP OF TECHNICAL CREWS ON THE GROUND, AND CONFIRMED WITH A LOW PASS OVER THE SDR CA120910011Piston Pin · corroded(CAN) THE CORROSION ON THE PISTON PIN WAS FOUND WHEN CYLINDER NR 1 WAS REMOVED FOR AN INTAKE VALVE LEAK. THE PISTON PIN WAS CHECKED AND FOUND WITH DEEP CORROSION PITS ON THE PIN SURFACE. THE OTHER 3 CYLINDERS WERE THEN REMOVED TO CHECK THE REMAINING PISTON PISDR CA110302005Brushes · worn(CAN) AFTER TAKEOFF, THE LANDING GEAR WAS SLOW TO RETRACT. WHEN THE LANDING GEAR WAS SELECTED DOWN, IT ONLY PARTIALLY EXTENDED AND STOPPED. RECYCLING WAS INEFFECTIVE. THE CREW DID A MANUAL GEAR EXTENSION AND LANDED WITHOUT INCIDENT. UPON SUBSEQUENT INSPECSDR 2011FA0000023Washer · brokenDURING A ROUTINE OIL CHANGE, UPON INSP OF THE "FINGER" SCREEN IN THE CRANKCASE OIL SUMP APPROX HALF OF WHAT APPEARED TO BE AN AN-960 WASHER WAS FOUND. NO PART LIKE THIS IS INTERNAL TO THIS MODEL OF ENGINE, BASED ON THE MFG IPC. FURTHER INVESTIGATION REVEALED TSDR CA100217006Hub · damaged(CAN) UPON DISASSEMBLY AND VISUAL INSP OF THE ABOVE HUB, THE PRELOAD SHELFS WERE FOUND TO CONTAIN VISUAL DAMAGE FROM PREVIOUS IMPACT. ACCORDING TO PROP MANUAL 202A VOLUME 6 CHAPTER 1, SPECIAL INSTRUCTIONS,(CURRENT REVISION 29), ANY HUB CONTAINING SIGNS OF PRELSDR CA080903004Housing · cracked(CAN) RT ENGINE OIL FILTER SEPARATED FROM HSG SHORTLY AFTER TAKEOFF. ENGINE SHUTDOWN IN-FLIGHT. ACFT LANDED SAFELY. ACD REMOTE OIL FILTER HSG THREADED STUD FOUND CRACKED. ONE PORTION OF THREADED STUD REMAINED IN FILTER AND THE OTHER HALF REMAINED IN THE FILTERSDR CA070312007Wheel Half · destroyed(CAN) SUSPECT HARD LANDING WITH SIDE MOVEMENT STRESSED WHEEL HALF CASTING. THE BACK STOP PORTION OF HUB CASTING HAS A NEW CLEAN BREAK. WITH RACE BROKEN, BEARING CONE FAILED. WHEEL ASSEMBLY TIPPED IN MOUNTING FORK AND RODE ON BRAKE CALIBER TORQUE PLATE. BRAKE DSDR CA060116003Cylinder · crackedIN RESPONSE TO AD 2005-26-10 ISSUED BY THE FAA, INSPECTED AIRCRAFT TO DETERMINE IF ANY OF SUSPECT SN CYLINDERS INSTALLED. FOUND 2 CYLINDERS ON LT ENGINE WERE PART OF THE AD REQUIREMENT FOR REPLACEMENT. ON CLOSER EXAMINATION OF ONE OF THESE CYLINDERS (NR 3), FSDR AU510002032Bearing · looseLT ENGINE ALTERNATOR DRIVE END BEARING SPINNING IN HOUSING. ALTERNATOR ROTOR RUBBING ON STATOR. LOSS OF BEARING GREASE.SDR CA051116004Arm · failedDURING FLIGHT TRAINING, GEAR RETRACTION CAUSED UNUSUAL NOISE AND GEAR FAILED TO RETRACT. ON SELECTING GEAR DOWN, 3 GREEN LIGHTS WERE NOTED BUT VISUAL INSPECTION OF NOSE GEAR IN MIRROR SHOWED NOSE WHEEL RANTED 5-10" TO LEFT. A LANDING AT AIRPORT WAS CARRIED OSDR CA050503009Nozzle · failed(CAN) ON CLIMB OUT AFTER TAKEOFF, A HIGH FUEL PRESSURE READING ON THE LT ENGINE WAS NOTICED (NEEDLE TO THE REDLINE). REDUCED POWER/CALLED ATC/RETURNED FOR LANDING. (SUSPECT CLOGGED FUEL INJECTOR NOZZLE.)SDR CA041029007Hub · corrodedPROPELLER REMOVED FROM AIRCRAFT FOR 10 YR O/H. UPON VISUAL INSPECTION OF HUB, CORROSION BEYOND REPAIRABLE LIMITS WAS FOUND IN THE BLADE 'O' RING GROOVES. MANUFACTURERS RECOMMENDED TBO IS 2000 HRS OR 72 MONTHS. THIS PROPELLER HAS EXCEEDED THE CALENDAR TBO BYSDR CA041029008Hub · corroded(CAN) PROPELLER REMOVED FROM AC FOR 10 YR. O/H. UPON VISUAL INSPECTION OF THE HUB CORROSION WAS FOUND ON THE MOUNTING FLANGE AND O-RING GROOVE OF THE REAR HUB HALF. THIS CORROSION IS BEYOND REPAIRABLE LIMITS. MANUFACTURERS RECCOMENDED TBO IS 2000 HOURS OR 72SDR CA040202001Seal · blown(CAN) PILOT NOTICED ENGINE SEEPING FROM LT ENGINE COWL, THEY WERE NEAR THE AIRPORT AND DECIDED TO SHUTDOWN LT ENGINE TO PREVENT ENGINE DAMAGE. IT WAS DETERMINED ON THE GROUND BY MAINTENANCE THAT THE LT PROP SEAL HAD BLOWN DUE TO A FROZEN BREATHER. IT WAS DETERSDR CA030730010Housing · cracked(CAN) FLUID LEAK FROM HOUSING ASSEMBLY. CRACK DETECTED.SDR CA030610004Conduit · failed(CAN) RT MAIN GEAR CONDUIT FLEXIBLE OUTER SLEEVE MOVED WITH INNER CABLE EXPOSING 11.0 INCHES OF INNER CABLE. INNER CABLE LOOPED OUT OF EXPOSED AREA. NOW WITH CABLE BEING BENT RT GEAR COULD NOT OVER CENTER FOR DOWN AND LOCKED.SDR CA030627016Attach Fitting · broken(CAN) GEAR WOULD NO EXTEND WHEN SELECTED DOWN. EMERGENCY GEAR EXTENSION CARRIED OUT. LUG WAS FOUND BROKEN. THIS RESULTED IN JAMMING OF THE RETRACTION MECHANISM. THIS PART SHOULD BE INSPECTED FOR CRACKS AT INSPECTION. ALSO ATTENTION SHOULD BE PAID TO THIS AREA SDR AUS20021362Spar Cap · corroded(AUS) RH WING MAIN LOWER SPAR CAP CORRODED. CORROSION IS LOCATED AT WS62 AS INDICATED IN AWB/51-4 ISSUE 1.SDR AUS20021363Spar Cap · corroded(AUS) LH WING MAIN LOWER SPAR CAP CORRODED. CORROSION IS LOCATED AT WS62 AS INDICATED IN AWB/51-4 ISSUE 1.SDR AUS20021335Spar · corroded(AUS) LH WING SPAR CONTAINED LIGHT CORROSION AND MINOR PITTING LOCATEDIN AREA JUST ABOVE LOWER SPAR CAP RADIUS. AREA OF CORROSION APPROXIMATELY 25MM (1IN) LONG BY 6MM (0.236IN) WIDE. FOUND DURING INSPECTION IAW AWB51-4.SDR AUS20021315Pin · broken(AUS) LANDING GEAR TRANSMISSION ASSEMBLY MOTOR RELEASE LINK PIN BROKEN AND JAMMING MECHANISM.SDR AUS20020928Spar · corroded(AUS) LH WING INBOARD SPAR LOWER SPAR CAP ASSEMBLY SEVERELY CORRODED. CORROSION IS INITIATED BY INGRESS OF EXHAUST GASSES THROUGH A FUEL DRAIN HOLE IN A PANEL FORWARD OF THE SPAR. THE FUEL DRAIN IS PART OF CANCELLED AD/PA30&39/20.SDR AUS20021016Hub · damaged(AUS) PROPELLER HUB DAMAGED IN AREA OF PRELOAD PLATE SHELF. SUSPECT PROPELLER HAD SUFFERED A GROUND STRIKE AND THE DAMAGED AREA HAD BEEN REMOVED BY WHAT APPEARS TO BE SCRAPING. UNAPPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR.SDR AUS20021017Hub · damaged(AUS) PROPELLER HUB DAMAGED IN AREA OF PRELOAD PLATE SHELF. SUSPECT PROPELLER HAD SUFFERED A GROUND STRIKE AND THE DAMAGED AREA HAD BEEN REMOVED BY WHAT APPEARS TO BE SCRAPING. UNAPPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR.SDR IK82002F00000Drive Unit · shearedWHEN CASE WAS REMOVED PN 78368 ON TACH DRIVE WAS FOUND TO BE SHEARED. IF ACCY CASE HAD NOT BEEN REMOVED AT THIS TIME, WE WOULD HAVE HAD A MAJOR FAILURE OF LT ENGINE. HALF OF THE ROLL PINS WERE SHEARED AND FLOATING INSIDE TACH RING ON END OF CAMSHAFT. NEW REPSDR AUS20011186Bearing · failed(AUS) CONNECTING ROD BIGEND BEARING MATERIAL SEPARATED FROM BEARING SHELL.SDR 2001FA0000305Seal · failedDURING A CROSS-COUNTRY FLIGHT BETWEEN CNO AND SPF (31 AUG 01 THRU 3 SEP 01), OIL STREAKS FROM THE NOSE BOWLS OF BOTH ENGINES INCREASED WITH EACH LEG. UPON RETURN TO CNO, COWLS AND PROPELLERS HAVE BEEN REMOVED. DURING INSPECTION OF ENGINE NOSE SEALS, BOTH SEASDR CA011105018Structure · galled(CAN) IT WOULD APPEAR, UPON INVESTIGATION THAT A PIECE OF MATERIAL FROM THE INNER ATTACHMENT (TELEFLEX) BROKE AND BECAME LODGED BETWEEN IT AND THE OUTER PORTION (SLIDE) AND CAUSED GALLING/SCORING WHICH JAMMED THE U/C AND WOULD NOT ALLOW GEAR TO EXTEND. AFTER MSDR CA010628045Control Cable · failed(CAN) THROTTLE CONTROL CABLE BROKE AT ENGINE END RESULTING IN LOSS OF ENGINE POWER SELECTION CAPABILITY. SUBSEQUENTLY, ALL ENGINE CONTROL /CABLES ON BOTH ENGINES WERE REPLACED.SDR 2001FA0000155Gear · damagedDURING COMPLICANCE WITH AD 96-09-10 - COMPLIED ALSO WITH AD 91-14-22 CRANKSHAFT GEAR RETAINING BOLT. ORDERED NEW CRANKSHAFT GEARS PN SL13S19464 FOR LH AND RH ENGINES. WHEN INSTALLING NEW GEARS IT WAS DISCOVERED ONE HAD THE TIMING MARK ON THE CORRECT TOOTH ANDSDR CA010523017Release Cable · stiff(CAN) - LANDING GEAR FAILED TO RETRACT ON CLIMB OUT & BREAKERS POPPED.- GEAR FAILED TO EXTEND WHEN BREAKER RESET & SELECTED DOWN, NO GREEN LIGHT TO INDICATE GEAR DOWN AND LOCKED.- PILOT COULD NOT RELEASE EMERGENCY GEAR EXTENSION HANDLE.- RT GEAR COLLAPSED ON RSDR 20010525CW001Rudder Horn · crackedREMOVED HORN DUE TO WEAR BETWEEN HORN AND RUDDER. FOUND CRACKS FROM MOUNT HOLES TO TOP OF RUDDER HORNS OF SAME PART NUMBER TO BE CRACKED IN A SIMILAR FASHION .SDR 20010228CW002Crankcase · crackedDURING ANNUAL INSPECTION, OIL LEAK NOTED AT CRANKCASE AREA FORWARD OF NR2 CYLINDER. AFTER CLEANING AN OBVIOUS 1.5 IN CRACK WAS NOTED. ENGINE WAS REMOVED FOR REPAIRS. LT ENGINE TSMOH 1098.41, 1992 FIREWALL FORWARD, INC.SDR CA010119006Rod · corroded(CAN) INSPECTION OF NOSE GEAR PUSH/PULL ROD FOUND PIT MARKS THROUGH LENGTH OF ROD ASSY. FURTHER INVESTIGATION SHOWED HOLES CORRODED WITH ONE AREA HAVING A HOLE, WHEN CLEANED OUT, OF APPROXIMATELY 1/8 INCH & 3/16 INCH. THERE WAS A LARGE AMOUNT OF CORROSION, INSDR AU000941Wire · cracked(AUS) RIGHT ALTERNATOR FIELD WIRING CRACKED ALLOWING SHORT CIRCUIT. (X)SDR CA000724023Hub · damaged(CAN) DAMAGE BEYOND LIMIT TO HUB SHELF DUE TO A PREVIOUS PROPELLER STRIKE.SDR 20000802SH018Exhaust Valve · shearedDURING FLIGHT, PILOT HEARD BANG AND NOTICED DIMINISHED POWER. PILOT LANDED WITH BOTH ENGINES RUNNING. ON GROUND, INSPECTION FOUND ''O'' COMPRESSION ON LEFT ENGINE, NR 2 CYLINDER. ON FURTHER INSPECTION, TOP OF EXHAUST VALVE WAS SHEARED OFF STEM. STEM WAS SSDR AU000404Lever · fouled(AUS) LANDING GEAR MANUAL EXTENSION SYSTEM LEVER OBSTRUCTED BY THE SEAT MOUNTED PORTABLE FIRE EXTINGUISHER IN SOME SEAT POSITIONS.SDR AU000408Rotor · shorted(AUS) LEFT ALTERNATOR SHORT CIRCUITED. COMPLETE ELECTRICAL FAILURE. A PROBLEM LOWERING THE LANDING GEAR RESULTED IN A GEAR UP LANDING CAUSING DAMAGE TO THE AIRCRAFT. SEE SDR AU000404 FOR ADDITIONAL INFORMATION.SDR AU000300Bungee Cylinder · faulty(AUS) LANDING GEAR BUNGEE FAULTY.SDR AU000250Valve · contaminated(AUS) RIGHT ENGINE FUEL DISTRIBUTOR VALVE VENT HOLE BLOCKED BY A GREASE TYPE SUBSTANCE APPLIED TO THE DIAPHRAGM SPRING.SDR CA000301050Guide · damaged(CAN) PILOT REPORTED LANDING GEAR CIRCUIT BREAKER TRIPPED ON LANDING. MAINTENANCE FOUND THE NOSE WHEEL ALIGNER GUIDE WAS DAMAGED ALLOWING THE GUIDE ROLLER TO JAM ON DAMAGED PORTION OF ALIGNER GUIDE, WHEN FULL LEFT RUDDER WAS APPLIED AND GEAR SELECTED UP. ONCSDR CA000118054Brushes · failed(CAN) DURING CLIMB, SMOKE AND SPARKS WERE NOTICED COMING FROM THE VENTILATION DUCTS AND FROM THE NOSE ACCESS PANEL. FOUND VENT BLOWER MOTOR AND RELATED WIRING BURNT, INSPECTION OF MOTOR FOUND BRUSHES COMPLETELY WORN OUT ALLOWING TENSION SPRINGS TO CONTACT COMSDR CA000120036Piston · broken(CAN) NO INDICATION AT COMPRESSION TEST OR IN OIL FILTER BUT OIL WOULD NOT DRAINFROM THE SUCTION SCREEN. PIECES OF PISTON SKIRT FOUND WHEN SUMP REMOVED.SDR CA991230046Line · cracked(CAN) PILOT DISCOVERED LT MANIFOLD PRESSURE GAUGE NOT RESPONDING APPROPRIATELY TO THROTTLE SETTINGS. MAINTENANCE DISCOVERED A CRACK IN THE LT ENGINE SENSE LINE ABOUT 2 INCH FORWARD OF THE FIREWALL.SDR AU991062Crankshaft · failed(AUS) CRANKSHAFT BROKEN AT NR 1 CONNECTING ROD POSITION. NR 1 CONNECTING ROD BEARING SPINNING. CRANKCASE THRUST FACE WORN. INVESTIGATION FOUND THAT THE FAILURE WAS A RESULT OF FATIGUE INITIATING FROM A SMALL DEFECT ON THE CRANKSHAFT CHEEK ADJACENT TO THE SLUSDR CA990907040Line · broken(CAN) LOST FUEL FLOW INDICATION ON LEFT ENGINE. FOUND FUEL FLOW SENSE LINE AFT OF ENGINE FIREWALL IN NACELLE BROKEN OFF. CAUSE MOST LIKELY FROM VIBRATION/FLEXING OF LINE. LINE REPAIRED.SDR CA990907038Brushes · worn(CAN) GEAR WOULDN'T COME UP. CIRCUIT BREAKER DID NOT TRIP. WARNING HORN WENT OFF WHEN MANIFOLD PRESSURE AT 15. NOTICED NOSE GEAR PARTIALLY DOWN IN MIRROR. CYCLED GEAR A FEW TIMES, GEAR CAME DOWN AND LOCKED SHOWING GREEN LIGHT.
Back to Lycoming IO-320-B1A