Lycoming 0-540 series
Service difficulty reports · 107
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 = 'O540' 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 = 'O540' 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 2005FA0000262Rib · crackedLT WING IB FLAP TRACK RIB ASSY, PN 1221010-15, HAS 2 BRACKETS RIVETED TO EITHER SIDE OF IT TO ATTACH FLAP TRACK RIB ASSY TO WING LOWER IB T/E SKIN, REF TO AS FLAP WELL SKIN) PN 0720601-101. ONE OF BRACKETS HAD CRACKED ALLOWING BRACKET TO TWIST SLIGHTLY, DECRESDR 2004FA0000654Strut · failedON MAKING A SLIP TO A LANDING, THE LT GEAR COLLAPSED. IT WAS FOUND THAT THE (VEE ASSEMBLY) PULLED OUT OF THE FITTING ASSEMBLY OF THE SHOCK STRUT. I RECOMMEND THAT THIS BECOME AN INSPECTION POINT FOR POSSIBLE CRACKS. THESE AIRCRAFT MAKE HUNDREDS OF LANDINGS SDR 2004FA0000510Alternator · detachedPILOT REPORTED HE THOUGHT ALTERNATOR THREW THE BELT. REMOVED THE COWLING, FOUND ALTERNATOR LYING IN ENGINE COMPARTMENT, WIRING INTACT, COOLING FINS TORN OFF BELT PULLEY, BELT SHREDDD. AN7-40A MOUNTING BOLT NOT FOUND. BELT ADJUSTMENT BRACKET AN5 ATTACH BOLT SDR 2004FA0000534Nut · missingJUST TURNED FINAL AND WENT TO PULL POWER BACK AND FOUND NO THROTTLE RESPONSE. PILOT WAS ABLE TO LAND USING MAG SWITCH TO ADD AND REDUCE POWER. UPON INSPECTION FOUND LOCK NUT MISSING FROM THROTTLE CONNECTION AND BOLT LAYING HALF OUT OF THROTTLE /TURBO ACTUATOSDR 2004FA0000351Rod · brokenPILOT WAS MOVING FUEL SELECTOR KNOB FROM WING TIP TANKS TO WING TANKS AND THE FUEL SELECTOR ROD BROKE AT THE FUEL SELECTOR VALVE WITH THE FUEL SELECTOR VALVE IN BETWEEN TANK POSITIONS. THE ENGINE STOPPED AND AN EMERGENCY LANDING WAS ACCOMPLISHED. INVESTIGATISDR 2004FA0000353Torque Tube · detachedLT RUDDER BAR TORQUE TUBE ASSEMBLY, PN 2260114-5 FAILURE. FAILURE OCCURRED IN FLIGHT RESULTING IN LT SIDE PILOT'S TOTAL LOSS OF LT RUDDER AND STEERING CONTROL. NATURE OF FAILURE; LT OB RUDDER PEDAL SOCKET ON TORQUE TUBE BROKE AWAY FROM THE TORQUE TUBE. THERE SDR 2004FA0000234Plate · crackedDURING AN INSPECTION, THE BULKHEAD MOUNTING PLATES WERE FOUND CRACKED AND BROKEN AROUND THE HOLES THROUGH WHICH THE PROPELLER MOUNTING STUDS PASS. THIS CONDITION IS FOUND VERY OFTEN AND THE PLATES REALLY NEED TO BE REDESIGNED TO NOT CRACK AS EASILY AS THEY DOSDR CHQA000449Battery · dischargedAFT SECTION OF EMERGENCY LIGHTING OUT. REMOVED AND REPLACED NR 4 EMERGENCY LIGHTING BATTERY IAW EMB 145 AMM II 33-50-04.SDR CHQA000454Connector · brokenONE CONNECTOR FOUND BROKE OFF AT SEAT 14 EMERGENCY PROXIMITY LIGHT. SPLICED WIRES BACK TOGETHER IAW CMM 20-21-00 AND OPS CHECKED GOOD IAW AMM 33-50-12.SDR 2004FA0000013Rod · brokenAPPEARS THAT ROD (PN A8268) BROKE JUST ABOVE A921-1 ROD FORK. SUBSEQUENT INVESTIGATION BY PROP REPAIR STATION DID NOT FIND ANY MISALIGNMENT OF GUIDE COLLAR RODS DO NOT APPEAR TO BE BENT OR DAMAGED. COULD NOT FIND ANY REASON FOR ROD TO FAIL.SDR 2004FA0000621Bolt · corrodedDURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS AN175C33A THAT ATTACHES THE SDR 2004FA0000157Gasket · leakingRED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT. OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREWS AND FOLLOWING THE THREADS OUT. ADDITIONAL SEALANT NEEDS TO BE ADDED TOT HE SCREWS DURING INSTALLATION AND PARTICULAR ATTENTION SHOULD BE SDR 2003FA0001114Tube · crackedLANDING GEAR RETRACTION TUBE INBOARD ARM FRACTURED ABOVE THE ATTACHMENT POINTS FOR THE NOSE AND RIGHT MAIN AND NOSE GEAR COLLAPSED ON LANDING. VISUAL INSPECTION OF THE PART INDICATED A PORTION OF THE FRACTURE COULD HAVE OCCURRED AT AN EARLIER DATE. CAUSE OF SDR 2003FA0001259Bulkhead · crackedDURING THE MFG OF THIS AC, THE OPTIONAL FACTORY OXYGEN SYS WAS INSTALLED. IT LOOKS LIKE THIS WAS KNOWN WHEN THE TAIL CONE WAS BUILT AS RIVETS IN THE AREA WHERE THE OXYGEN BOTTLE BRACKETS WERE OMITTED TO PROVIDE FOR INSTALLING THE BRACKETS. ONCE THE BRACKETS SDR AUS20030923Housing · cracked(AUS) LANDING GEAR ACTUATOR BODY CRACKED. FOUND DURING INSPECTION IAW CESSNA SB 01-2 REV1.SDR 2003FA0000904Buckle · crackedTHE LT REAR PASSENGER SEAT BELT BUCKLE ASSY WAS INSPECTED DURING A 100 HOUR INSPECTION AND WAS FOUND TO BE CRACKED. THE CRACK HAD DEVELOPED IN THE STAINLESS STEEL STRAP AT THE BUCKLE TO STRAP RIVIT ATTACH POINTS. THIS STRAP IS FORMED IN A HORSESHOE SHAPE AROSDR 2003FA0000608Control Cable · looseWHEN RUDDER IS DEFLECTED TO THE FAR RIGHT, THE RIGHT RUDDER CABLE GOES SLACK AND HANGS UP UNDER THE NUT FOR THE ELEVATOR PULLEY CLUSTER LOCATED BY THE FUSELAGE RIGHT SIDE ACCESS PANEL. TO PREVENT THIS, INSTALLED A SECOND NUT ON THE BOLT AND INSTALLED AN AN4-1SDR 2003FA0000453Control Cable · frayedELEVATOR UP CABLE FOUND TO HAVE NUMEROUS STRANDS BROKEN WHERE CABLE GOES THROUGH FAIRLEAD IN FUSELAGE AFT TAIL AREA NEAR HORIZONTAL STABILIZER LEADING EDGE / BATTERY AREA. WAS FOUND BY FAA DURING CERTIFICATION OF 137 OPERATOR.SDR 2003FA0000445Eyebolt · incorrectPART ON A/C DID NOT FIT BUSHING ASSY. HOLE IN EYEBOLT IS TOO BIG. ORDERED NEW PART AND HOLE WAS THE SAME. API TECH SAID MFG MUST HAVE MADE BAD BATCH OF PARTS W/HOLE ID OF .315 INSTEAD OF CORRECT.286. OUR SUPPLIER (KRN) MEASURED THEIR INVENTORY AND FOUND ANSDR 2003FA0000488Yoke · crackedDURING ANNUAL INSPECTION, OWNER REQUESTED YOKES BE CHANGED. BOTH YOKES WERE FOUND TO BE CRACKED ON THE LOWER SIDE, THROUGH THE HOLE FOR THE ROLL PIN. THE CONDITION WAS NOT VISIBLE WIGHOUT REMOVING EMBLEM AND YOKE, AS PLASTIC COATING ON YOKE EXTERIOR HAD NOT SDR 2003FA0000408Control Cable · jammedWHEN THE RUDDER IS DEFLECTED TO THE FAR RIGHT , THE RIGHT RUDDER CABLE GOES SLACK AND HANGS UP UNDER THE NUT FOR THE ELEVATOR PULLEY CLUSTER LOCATED BY THE FUSELAGE RIGHT SIDE ACCESS PANEL. TO PREVENT THIS A GUARD WAS SUGGESTED TO PREVENT THE CABLE FROM SLIPPSDR 2003FA0000709Actuator · crackedCRACK INDICATIONS IN THE 2.28 INCH BORE. CRACK FOUND WHILE INSPECTING ACTUATOR IAW SB 01-2 REV 1. RIGHT MAIN GEAR.SDR 2003FA0000318Control Cable · wornFOUND ELEVATOR DOWN CABLE AT F/W BELCRANK WITH BROKEN STRAND AND WEARING AT POINT OF CONTACT. FOUND WHILE COMPLYING WITH MFG SB NR 64, DURING ANNUAL INSPECTION. REPLACED CABLE WITH NEW PART.SDR 2003FA0000300Light · burned outSPT GLOW STRIPS, INSTALLED CUSTOMER SUPPLIED ELECTROLUMINESCENT LAMPS UNDER INSTRUMENT PANEL GLARE SHIELD, WITHIN 25 HOURS OF AIRCRAFT OPERATION, BOTH LIGHT FAILED. DURING INSPECTION OF THE LAMPS, TURNED POWER ON AND BOTH LAMPS SPARKED AND SMOKE CAME FROM ARESDR 2002FA0001340Latch · crackedCOWL LATCHES ON RIGHT SIDE OF COWL FAILED DURING IFR FLIGHT AND EMERGENCY LANDING MADE SUCCESSFULLY. LATCHES HAD BEEN REPLACED BEFORE THE TRIP. THIS IS THE THIRD SET OF HINGES INSTALLED AND ALL FAILED AFTER A FEW HOURS. THE COWL NOW HAS A SET OF OLD SERVICESDR 2002FA0001300Bolt · misinstalledBOLT WAS INSTALLED BACKWARDS ON SHIMMY DAMPNER. GEAR WAS LOWERED IN FLIGHT AND HUNG UP ON COWL LT V CHANNEL. SUBSEQUENT DAMAGE WAS CAUSE TO CHANNEL AND REAR SUPPORT. TIME SINCE LAST WORK TO SHIMMY DAMPENER MOUNT CLAMP UNKNOWN.SDR 2002FA0001324Coupling · brokenCOUPLING FAILED ON GEAR RETRACTION. COUPLING FROM MOTOR TO GEAR BOX CAUSING COUPLING TAB TO SLIDE OUT OF SLOTS CAUSING GEAR TO LOCK HALF-WAY UP, WOULD NOT EXTEND OR RETRACT. USED EMERGENCY PROCEDURE TO EXTEND GEAR. GEAR CIRCUIT BREAKER POPPED. EMERGENCY SPSDR 2002FA0001307Bolt · failedBOLT (NR 32) IS ONE OF FOUR. THREE APPARENTLY WERE PROBABLY SHEARED FROM PAST ACCIDENT. SAFETY WIRE HELD 211 BOLTS FROM ROTATING. REMAINING BOLT TORE OUT END OF UPPER TUBE, CAUSING COMPLETE DISASSEMBLY OF UPPER PART OF STRUT. UPPER ATTACH BOLT (NR 17) AND SDR GOC2002F00000Strut · damagedBOLT HOLES IN TOP OF NOSE LANDING GEAR OUTER CYLINDER, (PN 46063), FAILED ALLOWING STEERING STOP TO DEPART THE AIRCRAFT IN FLIGHT. NOSE LANDING GEAR THEN SLIPPED DOWN IN MOUNTING BLOCKS RENDERING NOSE WHEEL STEERING INOPERATIVE. AIRCRAFT WAS ON FINAL LANDINGSDR BTH2002F00003Fitting · crackedBRAKE RESERVOIR (PN 6846400) HAD A CRACKED HOSE ATTACH FITTING LEAKING HYDRAULIC FLUID ON TO DEFROSTER HOSE, CAUSING SMOKE IN COCKPIT. REPLACED BRAKE RESERVOIR WITH A SERVICEABLE PART.SDR 2002FA0000849Stringer · crackedDURNING ANNUAL INSPECTION FOUND RIVETS SHEARED AND MISSING FROM HOLES ON RIGHT REAR WING SPAR ATTACH FITTING ASSY. THIS ASSEMBLY IS ATTACHED TO CENTER SECTION. CARRY THRU UNDER BAGGAGE COMPARTMENT FLOOR. ALSO ON THIS AC THE STRINGER WAS CRACKED AND BUCKLED. SDR CA020507014Points · loose(CAN) THE POINTS THAT OPEN & CLOSE FOR THE ENGINE TACH IS NOT STAKED PROPERLY CAUSING THE POINTS TO OPEN INTERMITTENTLY, IN TURN THE ENGINE TACH BOUNCES & THE GOVERNOR TO GET ERRATIC INPUT AND GIVE BAD OUTPUT. I HAVE RECEIVED 1 OF THESE BAD POINTS FROM AN OVERSDR MAS2002F00000Line · failedDURING FLIGHT EXPERIENCED A NR 2 HYDRAULIC SYSTEM FAILURE IN-FLIGHT. AFTER AN UNEVENTFUL LANDING, MECHANIC WAS CALLED. MECHANIC DISCOVERED THAT THE HYDRAULIC FLEX LINE RUPTURED TO THE SPU PRESSURE SWITCH. MECHANIC REMOVED AND REPLACED THE FLEX LINE. OPS CHSDR 2002FA0001097Bolt · corrodedDURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS (PN AN175C33A) THAT ATTACHES THE STSDR 2004FA0000625Torque Tube · corrodedPRIOR TO ANNUAL INSPECTION. THE RT STABILATOR TIP WAS OBSERVED TO OSCILLATE SEVERAL INCHES. DURING THE ANNUAL INSPECTING THE RT STABILATOR BEARING, PN 4250383 WAS FOUND TO BE LOOSE. THIS PROCESS TOOK THREE PEOPLE SEVERAL HOURS TO COMPLETE. TO ASSIST IN THESDR 2002FA0000401Arm · brokenRUDDER TRIM ARM BROKEN OFF WHERE PILOTS TRIM CONTROL ASSY IS CONNECTED. PEDAL TORQUE TUBE ASSY. HAS EXCESSIVE WEAR AND SCORING AT PIVOT BEARING POINTS DUE TO LACK OF LUBRICATION. BROKEN ARM ASSY. SUGGESTED DUE TO OPERATING TRIM CONTROL ON GROUND PREVENTING NSDR 2002FA0000146Control Cable · looseUPON LANDING, WINDS WERE DOWN RUNWAY AT 15 MPH, THE LEFT RUDDER CABLE CAME LOOSE AT AIRCRAFT NICOPRESS SLEEVE CAUSING AIRCRAFT TO GROUND LOOP. THERE WAS NO EVIDENCE OF CORROSION ON CABLE OR SLEEVE AND SLEEVE WAS PREVIOUSLY INSPECTED FOR CORRECT SWEDGE PER AD.SDR 2002FA0000006Clamp · brokenTHIS CLAMP HOLDS THE SHIMMY DAMPNER IN POSITION ON THE NOSE GEAR BARRELL WITH A PIN WELDED INSIDE THE CLAMP. PIN WAS FOUND BROKEN AND THIS ALLOWED THE CLAMP TO SHIFT WHICH CAUSED THE SHIMMY DAMPNER TO HIT THE GEAR WELL AND SOME TIMES LOCK THE GEAR IN THE UP PSDR 2001FA0000593Wheel · crackedCRACK, 1.25 INCHES IN LENGTH, EMANATING FROM BOLT HOLE.SDR 2001FA0000492Blade · crackedCRACK FOUND IN BLADE SHANK BETWEEN TWO SHOULDERS APPROX 2 INCHES IN LENGTH. THREE HUNDRED HOURS EST SINCE LAST INSPECTION.SDR 2001FA0000416Clamp · bentNOSE GEAR FAILED TO EXTEND, BUT FELL OUT WHEN AIRCRAFT WAS LIFTED FROM RUNWAY. ON JACKS, GEAR OPS WAS NORMAL. THIS CLAMP WAS BENT WHICH MAY HAVE ALLOWED SHIMMY DAMPENER TO JAM THE GEAR. MAY HAVE BEEN DAMAGED FROM TUG OVER TURNING THE GEAR.SDR 2001FA0000414Fuel Strainer · backed outDURING ANNUAL INSPECTION NOTICED FUEL STRAINER STANDPIPE HAD BACKED OUT AND WAS ABLE TO PULL IT OUT OF TOP ASSEMBLY WITH FINGERS.SDR 2001FA0000311Contactor · failedCONTACTOR FAILED/ CLOSED CAUSING STARTER TO BURN OUT. THIS IS SECOND FAILURE OF A NEW CONTACTOR IN LESS THAN 140 HOURS. (ONE STARTER CONTACTOR, ONE MASTER CONTACTOR)SDR BIER0056Thrust Plate · brokenAT 400 HR VALVE INSPECTION FOUND ROCKER ARM SHAFT THRUST BUTTONS BRITTLE AND CRACKED. SUBMITTER RECOMMENDATION: STRESS THE IMPORTANCE OF THE 400 HR VALVE INSPECTION.SDR 20010413CW011Gear · brokenHAVE FOUND 3 GEARS WITH 1 TOOTH BROKEN. WERE FOUND A 500 HOUR MAG INSPECTION AFTER ENGINE QUIT ON LANDING. FOUND 2 MORE GEARS WITH SEVERAL TEETH MISSING. MAGNETO JUMPED INTERNAL TIME.SDR 20010425CW007Tube · looseDURING ANNUAL INSPECTION THE TWO ALUMINUM RIVETS SECURING THE FORWARD END OF SHAFT WERE FOUND LOOSE AND THE BUCK TAILS MISSING . THE SQUARK TUBE PORTION OF ASSEMBLY APPEARS TO BE ALUMINUM. THE FORWARD THREADED END IS STEEL. THE FIT OF THE TWO PARTS IS NOT VSDR 20010321CW005Plate · missingWHILE IN FLIGHT, THE C50462 SPINNER MOUNTING PLATES FAILED, RELEASING THE SPINNER FROM THE AIRCRAFT. THE PROPELLER BECAME LOOSE ON THE CRANKSHAFT DUE TO THE MISSING PLATES. WAS DAMAGED BEYOND REPAIR DUE TO SEVERE FRETTING. A NUMBER OF THE ATTACHING STUDS WESDR 20010406CW009Pump · failedFUEL LEAK IN AREA OF FUEL PUMP ABOVE INJECTOR. CAUSED FIRE. HOSES WERE NOT REMOVED TO DETERMINE EXACT CAUSE.SDR 20010412CW005Spar · corrodedINSPECTION REVEALED MISSING RIVET HEADS, RUST. CORROSSION ON REAR SPAR AT CENTER SECTION JUNCTION.SDR 20010412CW007Spar · corrodedAFT CARRY THROUGH SPAR AND BAGGAGE DOOR FRAME AND OPPOSITE SIDE ARE RUSTING AND CORRODING AND STEEL FITTINGS UNDER BAGGAGE COMPARTMENT FLOOR. PN 62448-00 PN 62448-01 PN 62618-00 PN 62619-00 PN 62529-00 65383-00 .
Back to Lycoming 0-540 series