Lycoming AEIO-540-D4A5
Service difficulty reports · 61
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 = 'AEIO540D4A5' 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 = 'AEIO540D4A5' 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 CA150504001Control Tube · damaged(CAN) COCKPIT CONTROL TUBE ASSEMBLY RUBBING ON INTERNAL VHF COMM ANTENNA DOUBLER: INVESTIGATION FOUND THAT DUE TO THE LIGHT GAUGE, 0.025", OF BOTTOM AFT PANEL AND UNDERSIZE OF THE VHF COMM ANTENNA DOUBLER, AIR LOAD CAUSES DOUBLER TO CONTACT THE COCKPIT CONTROLSDR CA120530005Pitot Tube · contaminated(CAN) PITOT HEAT CAUTION LIGHT AFTER 20 MINS OF USE. DUE TO HEAVY RAINS, THE PITOT STATIC TUBE ASSY, SUPPORT ASSY, FILLED UP WITH WATER. THE WATER CAUSED A SHORT AT THE CONNECTOR INSIDE THE TUBE. WIRES REPAIRED AND PITOT STATIC TUBE REPLACED. SUGGEST A DRAISDR CA111128005Control Rod · gouged(CAN) ELEVATOR TRIM ROD, 120A-4441, HAS TWO SPOTS WHERE BOLTS FROM THE ELEVATOR CONTROL ROD, 120A-4441, WERE GOUGING INTO THE ROD WHEN THE SYS WAS BEING OPERATED. IN ORDER TO RECTIFY, THE BOLTS AT THE QUADRANT FOR THE ELEVATOR CONTROL ROD, 120A-4441, THE AILESDR CA111021009Fork · cracked(CAN) ON LANDING, THE TAIL WHEEL FORK DEPARTED THE ACFT AS IT CRACKED THE CAST ALUMINUM FORK THAT THE TAIL WHEEL AXLE GOES THROUGH. THE ACFT LANDED WITH NO FURTHER DAMAGE BEYOND THE TAIL WHEEL ASSY.SDR CA110920010Hose · worn(CAN) DURING A LEAK TEST OF THE AIR CONDITIONING, IT WAS DISCOVERED THAT THE MAIN DELIVERY HOSE HAD A LEAK AND REQUIRED REPLACEMENT. THE AFFECTED HOSE IS LOCATED IN THE ENGINE COMPARTMENT AND IN CLOSE PROXIMITY TO THE EXHAUST MANIFOLD AND IS SUBJECT TO HIGH HSDR CA111019019Pump · unsecure(CAN) THE PILOT WAS PERFORMING AN AEROBATIC ROUTINE DURING AN AIRSHOW. WHILE PULLING THE POWER OFF TO PERFORM A TAIL SLIDE THE ENGINE QUIT. THE PILOT DECLARED A MAYDAY TO THE AIR BOSS AND MANAGED TO RESTART THE ENGINE. HE THEN CANCELLED THE REST OF HIS PERFSDR CA101021009Washer · missingDURING A 200 HR INSP ON 2 OTHER ACFT, MSB 1121-109/1 WAS BEING CARRIED OUT AS REQUIRED WHEN IT WAS NOTED THAT THE WASHERS WERE MISSING. THE MFG WAS CONTACTED AND DETERMINED THAT THIS WAS A NON CONFORMANCE TO THE TYPE CERTIFICATE. IT WAS DECIDED THAT THE REMASDR CA090618012Indicator · unserviceable(CAN) DURING PITOT/STATIC GROUND FUNCTION TEST, IT WAS NOTED THAT PILOTS (AFT) AIRSPEED INDICATOR WOULD ACCURATELY INDICATE AN INCREASE IN AIRSPEED BUT WOULD NOT SHOW A DECREASE ONCE PITOT PRESSURE IS RELIEVED AND BROUGHT BACK TO AMBIENT. THIS WOULD CAUSE THESDR CA090515001Tube · damaged(CAN) 4130 N FUSELAGE DIAGONAL TUBE PN 2-2100-241 FOUND DAMAGED BY IMPROPER CLEARANCE OF INSTALLED HARWARE OF THE FORWARD POSITION LT RUDDER PEDAL PIVOT BOLT AND SAFETY COTTER PIN. 74 PERCENT OF TUBE WALL MATERIAL GONE. RUDDER PEDAL FOUND TO BE "HOOKING AROUNDSDR CA090515002Aileron · obstructed(CAN) INSP OF THE CONTROL SURFACES FOUND THAT AILERONS DO NOT MAKE TRAVEL LIMITS AND PUSH RODS ARE HITTING FWD SPARS OF THE LWR WINGS. ELEVATOR TAB IS UNABLE TO MAKE LIMITS AS STATED. BOTH TRAVEL LIMITS AS STATED IN MM 70206-001 DATED 5-20-1998 PAGE 6 STATE TRSDR R019184Bushing · looseCUSTOMER REMOVED PROP DUE TO OIL LEAKING FROM BLADE. DISASSEMBLY OF THE PROPELLER REVEALED A LOOSE PITCH CHANGE ROD BORE BUSHING CAUSING THE OIL LEAK. THE PC ROD BUSHING WAS FOUND WEDGED BETWEEN THE FORK AND HUB. CENTRAL WEB AREA OF HUB WAS FULL OF OIL. THSDR 2004FA0000229Dope Film · delaminatedALL OF THE DOPE FILM DELAMINATED FROM THE CECONITE 102 FABRIC. AFTER SEVERAL PHONE CALLS, IT WAS DETERMINED THAT IMPROPER APPLICATION METHOD WAS USED. THE RANDOLPH DOPE PROCESS REQUIRES THE USE OF RANDO PROOF PRIMER FOR THE FIRST TWO COATS ON CECONITE FABRICSDR 2003FA0001026Cylinder · wrong partDURING A ANNUAL INSPECTION, FOUND THE NR 1 CYLINDER TO BE INCORRECT FOR THIS INSTALLATION, INCORRECT CYLINDER INSTALLED MFG PRIOR TO INSTALLATION ON AIRCRAFT. CYLINDER WAS FOR SHORT REACH PLUGS, ENGINE USES LONG REACH. CYLINDER FOUND ON 2 ND ANNUAL INSPECTION SDR 2003FA0000731Probe · failedON GROUND RUN-UP EGT INDICATOR FLUCTUATED 25 DEGREES. ON FURTHER INVESTIGATION FOUND CARBON ON END OF PROBE.SDR 2003FA0000392Bearing · failedDURING PROGRESSIVE INSPECTION OF THE AIRCRAFT THERE WAS A STRANGE SOUND FROM THE AILERON SYSTEM. FURTHER INVESTIGATION REVEALED THAT THE BEARING FROM THE LT AILERON ASSEMBLY WAS COMING APART. PROBABLE CAUSE IS DESIGN OF AILERON LEVER ASSEMBLY. THE ANGLE ANDSDR 2003FA0000073Distributor Blk · inoperativeMAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE WEAR. BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT DOWN. BECAUSE THE SDR VJ32003F00004Handle · shortedLANDING GEAR HANDLE COULD NOT BE SELECTED TO THE UP POSITION AFTER PROGRESSIVE INSPECTION WAS PERFORMED ON AIRCRAFT BY MAINTENANCE. BELIEVE THAT HANDLE HAS A SHORT INTERNALLY CAUSED BY THE SHORTING OUT THE HYDRAULIC CONTROL RELAY AND THE RELAY AND DIODES BOASDR VJ32003F00007Motor · inoperativeDURING PROGRESSIVE INSPECTION AND CYCLING THE GEAR THE HYDRAULIC PUMP RCCB CIRCUIT BREAKER WOULD POP. THE HYDRAULIC MOTOR ON THE HYDRAULIC PUMP UNIT WAS PUTTING OUT OVER 75 AMPS.SDR VJ32003F00009Relay · shortedDURING PROGRESSIVE INSPECTION AND CYCLE OF THE LANDING GEAR, WE HAD A FAILURE OCCUR. FOUND A BAD HYD. CONTROL RELAY THAT SHORTED. BECAUSE OF THAT SHORT, IT ALLOWED TOO MUCH CURRENT TO FLOW TO PC BOARD AND SHORT OUT BOARD BETWEEN RELAY K-13 PIN 13 AND 16 TO BSDR VJ32003F00003Shock Mount · damagedDURING PROGRESSIVE INSPECTION OF ENGINE BAY, FOUND LOWER LEFT LORD MOUNT DAMAGED FROM HEAT OF EXHAUST SYSTEM. SUGGEST INSTALLING SOME TYPE OF HEAT SHIELDING OR CHANGING MOUNT TO A MORE HEAT RESISTANT STYLE. PART RETURNED FOR WARRANTY.SDR VJ32003F00005Shock Mount · damagedDURING PROGRESSIVE INSPECTION OF ENGINE BAY FOUND LOWER LT MOUNT DAMAGED FROM HEAT OF EXHAUST SYSTEM. SUGGEST INSTALLING SOME TYPE OF HEAT SHIELDING OR CHANGING MOUNT TO A MORE HEAT RESISTANT STYLE.SDR VJ32002F00065Downlock Switch · failedDOWN SWITCH FAILED CAUSING NO DOWN INDICATION OF NOSE GEAR IN THE DOWN POSITION.SDR VJ32002F00066Handle · failedGEAR HANDLE EXPERIENCED INTERNAL FAILURE CAUSING MALFUNCTION OF THE HYDRAULIC GEAR PUMP. WHEN THE PUSH TO TEST BUTTON WAS PRESSED FOR THE ANNUNCIATOR PANEL, THE PUMP WOULD OPERATE.SDR VJ32002F00068Sensor · brokenRPM INDICATION SENSOR RING FOUND BROKEN DURING ROUTINE INSPECTION. THIS SENSOR RING FITS UNDER THE VENT OF THE RIGHT MAGNETO AND PROVIDES ENGINE RPM INDICATIONS. APPEARS TO BE BROKEN DUE TO FLEXING/FATIGUE. PERHAPS A DIFFERENT SENSOR OR OTHER MORE SECURE MOSDR VJ32002F00044Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED.SDR VJ32002F00045Pump · failedIN FLIGHT THE INSTRUMENT VACUUM SYSTEM FAIL. THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUNDED THAT THE ROTOR HAD FROZEN UP AND THE SHAFT HAD SHEARED. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPERATIONAL CHECK OF THE SYSTEM CHESDR VJ32002F00039Rod · chafedAILERON ROD RUBBING AILERON BELL CRANK. REMOVED ROD AND INSTALLED NEW ROD. CONTROL ASSEMBLY WAS SHIMMED TO CORRECT THE PROBLEM.SDR VJ32002F00040Rod · chafedELEVATOR CONTROL ROD RUBBING AILERON CROSS OVER TUBE. REMOVED TUBE AND INSTALLED NEW TUBE. NEW SHIM PLATES INSTALLED, TO CORRECT PROBLEM.SDR VJ32002F00041Clock · brokenLEFT HAND STOP PIN BROKEN OFF. REMOVED AND REPLACED NEW CLOCK.SDR VJ32002F00038Pump · failedIN FLIGHT, THE INSTRUMENT VACUUM SYSTEM FAILED. THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUNDED THAT THE ROTOR HAD FROZEN UP AND THE SHAFT HAD SHEARED. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPERATIONAL CHECK OF THE SYSTEM CSDR VJ32002F00043Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED.SDR VJ32002F00042Pump · burned outLANDING GEAR FAILED, WHEN THE GEAR WAS SELECTED TO THE UP POSITION AFTER TAKE OFF. THE GEAR WAS LOWER AND A SAFE LANDING WAS MADE. INSPECTION OF THE GEAR SYSTEM FOUND THAT THE MOTOR ON THE HYDRAULIC PUMP BURNED OUT. PUMP ASSEMBLY WAS REMOVED AND A NEW PUMP SDR VJ32002F00036Pump · failedIN FLIGHT, THE LANDING GEAR HYDRAULIC PUMP CIRCUIT BREAKER POPPED WITH THE GEAR UP, THE GEAR WAS LOWERED AND A SAFE LANDING WAS MADE. AIRCRAFT WAS PLACED ON JACKS AND THE GEAR SYSTEM WAS OPERATIONAL CHECKED. WITH THE GEAR UP AND LOCKED THE HYDRAULIC PUMP WOUSDR VJ32002F00031Pump · inoperativeAT 800 RPM THE FUEL PRESSURE DROPS BELOW MINIMUM AND THE LOW PRESSURE LIGHT CAME ON AT IDLE. SYSTEM WAS CHECKED AND FOUND THAT THE PUMP OUT PUT WAS LOW. PUMP REMOVED AND A NEW PUMP INSTALLED. GROUND RUN AND FINAL ADJUSTMENTS TO THE PUMP WERE MADE. OPERATIOSDR VJ32002F00032Pump · shearedMETAL SHAFT SHEARED IN PUMP. REMOVED AND INSTALLED NEW PUMP, SYSTEM OPERATIONAL CHECKED NORMAL. PUMP SENT IN FOR WARRANTY.SDR VJ32002F00033Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. PART SENT IN FOR WARRANTY.SDR VJ32002F00034Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. PART SENT IN FOR WARRANTY.SDR VJ32002F00029Bracket · crackedALTERNATOR SUPPORT BRACKET CRACKED. PART REMOVED AND A NEW SUPPORT BRACKET INSTALLED. PART SENT IN FOR WARRANTY.SDR 2002FA0000515Pump · failedTHE LANDING GEAR WAS SWLECTED IN FLIGHT TO THE DOWN POSITION; THE RIGHT MAIN GEAR LIGHT FAILED TO COME ON IN THE DOWN AND LOCKED POSITION. THE AIRCRAFT WAS YAWED AND THE DOWN AND LOCK GEAR LIGHT CAME ON. A SAFE LANDING WAS MADE. AIRCRAFT WAS TAKEN TO MAINTESDR 2002FA0000514Handle · failedLANDING GEAR WAS CYCLED TO THE DOWN POSITION IN FLIGHT, BOTH MAIN GEAR DOWN LIGHTS CAME ON AND THE NOSE GEAR DOWN LIGHTS CAME ON AND THE NOSE GEAR DOWN LIGHTS FAILED TO COME ON. THE SYSTEM WAS TESTED IAW FLIGHT MANUAL PROCEDURES AND THE LIGHTS FOR THE NOSE GESDR 2002FA0000484Audio Panel · failedAUDIO PANEL FAIL INTERNALLY GIVING AND UNSAFE GEAR INDICATION LIGHT, AND WHEN THE THROTTLE WAS PULLED TO IDLE, THE HYDRAULIC PUMP WOULD START TO RUN. REMOVED AND INSTALLED NEW AUDIO PANEL. THE LANDING GEAR OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANSDR 2002FA0000474Switch · failedMAGNETO SWITCH FAILED TO START ENGINE, FOUND BAD SWITCH. NEW SWITCH INSTALLED, OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANTY.SDR 2002FA0000481Actuator · failedNOSE LANDING GEAR HYDRAULIC ACTUATOR BOTTOM SEAL AROUND SHAFT BLOW OUT AND LEAKING FLUID FROM CYLINDER. ACTUATOR REMOVED AND A NEW ACTUATOR INSTALLED. ACTUATOR SENT IN FOR WARRANTY.SDR 2002FA0000477Pin · brokenLEFT HAND STOP PIN BROKEN OFF, REMOVED AND INSTALLED NEW CLOCK. PART SENT IN FOR WARRANTY.SDR 2002FA0000478Pump · damagedMETAL SHAFT SHEARED IN PUMP. REMOVED AND INSTALLED NEW PUMP, SYSTEM OPERATIONAL CHECKED NORMAL. PUMP SENT IN FOR WARRANTY.SDR 2002FA0000480Servo · stickingTRIM SERVO STICKING IN OPERATION AND FAILS TO MOVE THE AILERON TRIM TAB. REMOVED AND INSTALLED NEW TRIM SERVO ASSEMBLY. PART SENT IN FOR WARRANTY.SDR 2002FA0000482Pump · inoperativeELECTRIC MOTOR SLOW IN FLIGHT, OVER 25 TO 30 SECONDS TO RETRACT AND EXTENT THE LANDING GEAR. NEW HYDRAULIC PUMP ASSEMBLY INSTALLED, CYCLED GEAR IAW MAINTENANCE MANUAL, LANDING GEAR OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANTY.SDR 2002FA0000483Filter · inoperativeFEED BACK IN THE RADIOS, NEW FILTER INSTALLED, OPERATIONAL CHECK NORMAL. PART SENT IN FOR WARRANTY.SDR 2003FA0001092Flange · crackedFOUND CRACKED CRANKSHAFT FLANGE. INSTALLED 3 BLADE MT PROP TO DECREASE STRESS ON CRANKSHAFT.(K)SDR 2003FA0001091Flange · crackedFOUND CRACKED CRANKSHAFT FLANGE. INSTALLED 3 BLADE PROP TO DECREASE STRESS ON CRANKSHAFT.
Back to Lycoming AEIO-540-D4A5