Lycoming IO-540-AB1A5
Service difficulty reports · 138
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 = 'IO540AB1A5' 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 = 'IO540AB1A5' 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 2007FA0000691Alternator · failedAC ARRIVED AT 1R4 WITH A FAILED ALTERNATOR. SYSTEM WAS TESTED TO CONFIRM THAT THE ALTERNATOR WAS THE PROBLEM. ON 6/25/07 THE ALTERNATOR IN QUESTION WAS REMOVED FROM THE AC. UPON REMOVING THE ALTERNATOR THE TECHNICAN FOUND THE SAFETY LOCK WIRE FOR THE ALTERNSDR BUW2007F00001Return Line · looseDURING THE INSPECTION FOR SB 07-71-01 THE FUEL RETURN LINE AT THE FIREWALL BULKHEAD FITTING WAS FOUND LOOSE. (K)SDR 2007FA0000219B-Nut · looseIN THIS CASE, FOUND THAT THE B-NUT CONNECTING TO THE FUEL CONTROL FROM THE SPIDER WAS LOOSE. IT WAS NOT LEAKING, BUT REQUIRED A THIRD OF A TURN TO TORQUE DOWN TO PROPER TORQUE. NO OTHER WORK HAS BEEN DONE TO THE SPIDER OR FUEL CONTROL BECAUSE I HAVE DONE THESDR 2006FA0001235Valve Guide · stuckPERFORMED COMPRESSION CHECK ON ENGINE AND HAD 5/80 PSI ON NR 6 CYL, STAKED EXHAUST VALVE AND GOT 78/80. PERFORMED SB 388C AND HAD TO REAM VALVE GUIDES TO GET WITH-IN LIMITS OF SB. IT WAS ONLY 200 HRS SINCE LAST SB COMPLIANCE.SDR 2006FA0001069Exhaust Valve · stuckSTUCK EXHAUST VALVES ON NR 3 CYLINDER FOUND DURING PHASE 2 INSPECTION.SDR 2006FA0001037Exhaust Valve · stuckDURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (5/80) WITH A STRONG LEAK PASSED THE EXHAUST VALVE. SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN SB 388C REVEALED THE CYLINDER DID NOT MEET THE MEASUREMENT CRITERIA FOR TSDR 2006FA0001060Lifter · brokenLIFTER BROKE. (K)SDR 2006FA0001013Valve Guide · leakingOPERATOR COMPLAINED OF AN OIL LEAK. WHEN COWL WAS REMOVED IT WAS OBVIOUS THAT THE NR3 AND NR4 EXHAUST PUSH RODS AND PUSH ROD HOUSING WERE BENT. SUSPECTED STICKING EXHAUST VALVES. EXHAUST VALVE TO GUIDE CLEARANCE WAS CHECKED ON ALL CYLINDERS IAW SB AND THE PSDR 2006FA0000993Exhaust Valve · stuckDURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (10/80) WITH A STRONG LEAK PASSED THE EXHAUST VALVE. SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN LYCOMING SB 388C REVEALED THAT THE EXHAUST VALVE WAS PARTIALLY STUCK ANSDR 2006FA0000108Control Cable · chafedAT AC STA 22 LWS 3 INCHES, 3.75 INCHES BELOW CABIN FLOOR, ELEVATOR TRIM CONTROL CABLES CHAFING HARD ON BOTTOM SURFACE OF .2500 DIA FUEL TUBE AT LEFT AND AFT OF AIRCRAFT FUEL SELECTOR. IF LEFT CONTROL CABLE WILL CUT THRU FUEL TUBE (CAUSE) NOT SEEN AT FACTORY.SDR AU510001734Fitting · faulty(AUS) LT FORWARD DOORPOST WING STRUT ATTACHMENT FITTING MISSING 2 RIVETS PN MS20470AD6. FITTING AND SURROUNDING STRUCTURE SHOW EVIDENCE OF REWORK DURING MFG.(MANUFACTURING QUALITY CONTROL ISSUE ) (CASA NR 510001734)SDR AU510001735Screw · defective(AUS) CONTROL COLUMN/ELEVATOR BELLCRANK TORQUE TUBE SUPPORT SCREWS PNO MS35206-228 (2OFF3) DEFECTIVE. SCREWS APPEAR TO HAVE BEEN OVERTORQUED DURING ASSEMBLY. (OTHER CAUSE: MANUFACTURING QUALITY CONTROL ISSUE ) (CASA NR 510001735)SDR 2005FA0001587Actuator · misdrilledMFG MANDATES THE REMOVAL DISASSEMBLY, AND INSPECTION OF THE ELEVATOR TRIM ACTUATOR AT 1000 HRS TT OR 6 YEARS. UPON REMOVAL OF THIS ACTUATOR, FOUND THAT THE GROOVED PIN HOLES IN HOUSING WERE MISDRILLED. THIS CAUSED THE PIN TO WEAR INTO THE ACTUATOR HOUSING. SDR 2005FA0000768Probe · loose"OMEGA" BRAND NAME OF CONNECTORS USED ON THE ALCOR CHT/EGT PROBES. THE SCREWS THAT HOLD THE CONNECTOR AND CONNECTION OF THE WIRE FOR THE PROBES WILL WORK LOOSE CAUSING A FALSE OR NO INDICATION ON THE G-1000 SYSTEM. NEEDS TO HAVE SOMEWAY TO LOCK THE SCREWS INTOSDR CA050407008Brushes · loose(CAN) STARTER FAILED. BRUSHES WERE LOOSE UPON EXAMINATION AND WINDINGS BURNT. SUSPECT THE BRUSHES WERE LOOSE TO START WITH.SDR 2005FA0000158Alternator · failedPILOT DECLARED EMERGENCY, TOTAL ELECTRICAL FAILURE. DIAGNOSTIC INSPECTION REVEALED ALTERNATOR FAILURE. PILOT FAILED TO SEE WARNING LIGHT; DISCHARGE ON AMMETER AND LOW VOLT READING ON VOLT METER. (GL11200505028) (K)SDR CA041012006Switch · overheated(CAN) SWITCH WAS HOT TO THE TOUCH DURING GROUND FUNCTIONAL TEST. SWITCH DID NOT TRIP. SWITCH WENT OPEN CIRCUIT AFTER COUPLE MINUTES.SDR RG42004F00000Attach Bracket · crackedPART FOUND CRACKED DURING 100 HR INSPECTION. CRACK LOCATED AT LOWER LT CORNER OF PART, LT BRACKET. RECOMMEND PART OF STRONGER MATERIAL OR DIFFERENT DESIGN. OBTAINING ENGINEERING APPROVAL FRO MFG TO INSTALL HEAVIER DESIGNED PART, VIA FIELD APPROVAL. (FIRST SDR 2005FA0000101Exhaust Valve · seizedUPON TAKEOFF, PILOT REPORTED POWER LOSS AND ROUGH RUNNING ENGINE. INVESTIGATION FOUND NR 3 CYLINDERS EXHAUST VALVE SEIZED. THIS WAS 4TH OCCURENCE SINCE NEW (1999). INSTITUTED 300 HOUR VALVE GUIDE REAM AND 25 HOUR OIL CHANGE. MFG DENIED REQUEST TO INCREASE SDR AUS20040434Support Bracket · cracked(AUS) BATTERY SUPPORT BRACKETS CRACKED.SDR 2004FA0000005Camshaft · spalledENGINE MAKING METAL, MFG DETERMINED IT TO BE CAMSHAFT/ LIFTER MATERIAL ENGINE RETURNED TO FACTORY FOR REPAIR. THIS IS THE SECOND OCCURRANCE OF CAMSHAFT/ LIFTER SPALLING AND 5TH OCCURANCE OF ENGINES MAKING METAL IN A FLEET OF 5. POSSIBLE MANUFACTURING AND MATSDR AUS20030530Line · cracked(AUS) STAINLESS STEEL FUEL PIPE LOCATED BETWEEN FUEL FILTER BOWL AND BOWL DRAIN VALVE CRACKED BENEATH (B) NUT FERRULE AT DRAIN VALVE END.SDR CA030427001Lock · collapsed(CAN) PILOT WAS PRACTICING A FORCED LANDING AND WAS ON FINAL APPROACH WITH FULL FLAPS, NO POWER AND A LOT OF TRIM TO PRODUCE A 70KT GLIDE. AS FULL THROTTLE WAS APPLIED AND ABORTED LANDING AT 500 FT, THERECLINABLE SEAT BACK COLLAPSED. THE PILOT MANAGED TO USE TSDR CA030414004Skin · cracked(CAN) FUSELAGE SKIN PANEL UNDER REFUELING STEP NOTED HAVING A BULGE AREA UNDER TOP REAR MOUNTING BOLT AREA. SKIN MOVEMENT ALSO WAS EVIDENT WHEN WEIGHT WAS APPLIED TO THE STEP. DETAIL INSPECTION OF AREA FOUND BOTH THE FUSELAGE SKIN AND BULKHEAD WHERE THE STEP SDR CA030414005Skin · cracked(CAN) FUSELAGE SKIN PANEL UNDER REFUELING STEPS NOTED HAVING A BULGE AREA AROUND MOUNTING BOLT. SKIN MOVEMENT ALSO WAS EVIDENT WHEN WEIGHT WAS APPLIED TO THE STEP. DETAIL INSPECTION OF AREA FOUND BOTH THE FUSELAGE SKIN AND BULKHEAD WHERE THE STEPS ARE MOUNTESDR CA030414006Bulkhead · cracked(CAN) FUSELAGE SKIN PANEL UNDER REFUELING STEPS NOTED HAVING A BULGE AREA AROUND MOUNTING BOLT. SKIN MOVEMENT ALSO WAS EVIDENT WHEN WEIGHT WAS APPLIED TO THE STEP. DETAIL INSPECTION OF AREA FOUND BOTH THE FUSELAGE SKIN AND BULKHEAD WHERE THE STEP IS MOUNTED SDR WDA2003F00000Fork · inoperativeDURING AN ANNUAL INSPECTION, WE REMOVED THE NOSE WHEEL PANT TOP ATTACHING BOLT AND THE LOWER FORK WITH THE TIRE ON IT FELL OFF OF THE STRUT ASSEMBLY. WE CALLED MFG TO VERIFY THAT FORK IS PRESSED ON THE STRUT ASSEMBLY. MFG REQUESTED THE FORK ASSEMBLY FOR FURTSDR 2004FA0000167Magneto · failedIT APPEARS THAT THE IMPULSE COUPLING FAILED, THEREFORE SEIZING THE MAGNETO AND SHEARING GUIDE SHAFT OF RETAINER GEAR ASSEMBLY AND BREAKING APART (INTO PIECES) THE RETAINER ASSEMBLY, ITSELF. SENDING PIECES OF METAL INTO THE ACCESSORY CASE AND POSSIBLY INTO THESDR 2002FA0001046Valve Guide · seizedNR 2 CYLINDER EXHAUST VALVE SIEZED IN VALVE GUIDE POSSIBLY DUE TO CARBON BUILD UP. NR 2 PUSHROD AND PUSHROD SHROUD WERE BENT. NR 2 EXHAUST PLUNGER ALSO REPLACED AT MFG RECOMMENDATION.SDR 2002FA0000912Retainer · missingNR 3 CYLINDER PUSH ROD BENT, REMOVED THE NR 5 CYLINDER VALVE COVER FOR FURTHER INSPECTION AND FOUND PUSH ROD RETAINING CLIP MISSING AND ASSOCIATED HARDWARE. NO DAMAGE OR PARTS FOUNDSDR CA020617003Connecting Rod · broken(CAN) CONNECTING ROD APPEARS TO HAVE BROKEN 1 INCH OUT FROM CRANKSHAFT JOURNAL. THIS WRAPPED ITSELF AROUND UNTIL THE CONNECTING ROD CAP DEPARTED AND THE PIECES BROKE THE CASE 60 PERCENT OF THE WAY AROUND THE ENTIRE CASE AND DESTROYED THE CAMSHAFT AND JAMMED UPSDR 2001FA0000577Fuel Line · chafedDURING 100 HOUR INSPECTION, DISCOVERED NR2 CYLINDER FUEL INJECTION LINE LEAKING WHILE ACCOMPLISHING MFG SB. FUEL LINE SUPPORT CLAMP HAD BECOME LOOSE AND CAUSED LINE TO CONTACT NR2 CYLINDER FINS, WHICH WORE 6 GROOVES IN LINE.SDR 2001FA0000489Main Bearing · delaminatedFRONT MAIN BEARING DELAMINATION. DEFECT AREA WAS ABOUT THE SIZE OF A DIME. THERE WAS EVIDENCE OF SUBSURFACE FLAWS IN THE SURROUNDING AREA. THE CAUSE WOULD BE IMPROPER MANUFACTURING.SDR 2001FA0000182Gasket · missingWHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, AND OIL LEAK WAS NOTICED COMING FROM THE LOWER VACUUM PUMP DRIVE PAD. FURTHER INSPECTION REVEALED THAT THE GASKET FOR THE PUMP WAS MISSING. A NEW GASKET WAS INSTALLED AND A LEAK CHECK WAS PERFORMED.SDR 20010612CW003Spar · crackedREAR STABILIZER/ REAR SPAR LEFT SIDE/ CRACKED.SDR AUS20010665Cylinder · leaking(AUS) RH BRAKE MASTER CYLINDER LEAKING AT ELBOW FITTING. INVESTIGATIONFOUND THAT THE ELBOW HAD NOT BEEN FULLY SCREWED IN AND THESEALING O' RING WAS DISPLACED ONTO THE THREADS OF THE ELBOW INSTEAD OF FITTING INTO THE SEAL RECESS DUE TO THE B' NUTCOVERING THE RSDR AU010029Flow Divider · corroded(AUS) ENGINE FUEL FLOW DIVIDED CORRODED. PARTICLES OF CORROSION BLOCKING FUEL INJECTORS. AIRCRAFT HAD BEEN CONTAMINATED WITH EDAAND DECONTAMINATED IAW AD/GEN/80 AND MANUFACTURERS INSTRUCTIONS.SDR 20000516SH011Guide · failedEXHAUST VALVE STUCK, BENDING PUSH ROD AND HOUSING. SEE LYC SI 1425H, 1485. SB388B. FOUND 3 OTHER CYLINDERS WITH STUCK VALVES. SUBMITTER SUGGESTED AD BE ISSUED. (X)
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