Continental IO-540 series
Service difficulty reports · 270
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 = 'IO540' 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 = 'IO540' 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 CA051212003Elt · malfunctionedAIRCRAFT WAS IN A TURN WHEN THE ELT WENT OFF. THE PILOT STATED THE TURN WAS NOT OUTSIDE OF A NORMAL MANOUVER. ELT WAS RESET BY REMOTE SWITCH IN THE COCKPIT.SDR CA051207002Housing · wornPITOT LINE WAS FOUND WEARING INTO TRANSMISSION HOUSING. THE WEAR IS ON THE CURVE OF THE HOUSING. THE COMPANY HAS STARTED AN INSPECTION OF THIS AREA FOR ALL R44II IN THE FLEET.SDR 2005FA0001622Downlock Switch · brokenUPON ARRIVING AT DESTINATION GEAR WAS SELECTED DOWN. NOSE GEAR GREEN LIGHT DID NOT ILLUMINATE AND IN TRANSIT LIGHT STAYED ON. INSPECTED AND FOUND NOSE GEAR DOWNLOCK SWITCH ACTUATING ARM BROKEN OFF. DETERMINED CAUSE OF BREAKING WAS TIME IN SERVICE AND WORK SDR 2005FA0001538Pressure Sensor · leakingDURING A 100 HR INSPECTION AN OIL LEAK WAS DETERMINED TO BE ORIGNATING FROM THE HOBBS METER SENSOR AT THE SWEDGED FLANGE. AD CALLS FOR THE REPLACMENT OF SENSOR. JUST THOUGHT IT IRONIC AN AD CALLS FOR HE REPLACEMENT OF ONE LEAKING SENSOR FOR ANOTHER LEAKING SSDR CA051101005Pump · low pressure(CAN) PUMP WAS NOT PROVIDING ENOUGH FUEL TO PRIME THE ENGINE. ELECTRIC PUMP ASSEMBLY REPLACED.SDR QOF2005F00003Blades · out of balanceBLADES CAME OUT OF BALANCE SITTING STATIC OVER A PERIOD OF 4 DAYS, FOR REASON OR REASONS UNKNOWN. (K)SDR 2005FA0001503Window · crackedLT FORWARD SIDE WINDOW. CRACKED AND BROKEN 2 PLACES AROUND SIDE VENT WINDOW CAUSING LARGE SECTION TO BECOME LOOSE. (K)SDR CA050923010Starter Gen · failed(CAN) DURING START UP, THE STARTER WOULD NOT ENGAGE. THE STARTER WAS REMOVED AND REPLACED WITH ANOTHER UNIT AND THE PROBLEM NO LONGER WAS EVIDENT. WE HAVE HAD SEVERAL STARTER PROBLEMS AND ROBINSON ARE TRYING TO SOLVE THE ISSUE.SDR 2005FA0001393Strut · failedUPON LANDING, LT MLG OLEO STRUT FOLDED UPWARDS ALLOWING PROP TO CONTACT GROUND. INVESTIGATION REVEALED MODERATE CORROSION THROUGHOUT STRUT LOWER MOUNT AND BOLT HOLE. SUGGEST INSPECTING AND CLEANING LOWER ATTACH POINTS EVERY 100 HOURS. APPLY CORROSION INHIBISDR CA050916001Magneto · failed(CAN) THE MAGNETO WAS REMOVED DUE TO FAILURE (NOT WORKING) UPON DISASSEMBLY THE BRUSH WAS BROKEN AND THE SPARK WAS NOT MAKING IT OUT OF THE COIL TO THE DISTRIBUTOR. ALSO, FOUND COIL CLAMP BROKEN THIS WILL BE REPAIRED HERE ALONG WITH A FRESH 500 HR INSP. DURISDR CA050916002Bearing · damaged(CAN) MAGNETO WAS REMOVED FOR SCHEDULED 500 HOUR INSPECTION. THE LOWER BEARING LOOKS AS THOUGH IT HAD BEEN SPINNING ON THE SHAFT. THE SPACER WAS ALSO DAMAGED.SDR CA050919001G Switch · failed(CAN) ELT WENT OFF DURING GROUND HANDLING. THE ELT WAS REMOVED FOR FURTHER INVESTIGATION. SUSPECT G-SWITCH.SDR 2005FA0001292Cylinder · damagedDURING ANNUAL INSPECTION, IT WAS DISCOVERED DURING A DIFFERENTIAL COMPRESSION CHECK THAT THE NR 1 CYLINDER ON THIS ENGINE HAD ALMOST NO COMPRESSION. IT WAS DISCOVERED THAT THE EXHAUST VALVE GUIDE WAS BAD. ALSO, THE EXHAUST VALVE AND INTAKE VALVE HAD TO BE REPLSDR FYO2005F00000Bar · crackedNOTICED EXCESS PLAY BETWEEN RT AND LT PEDALS DUE TO ELONGATED THRU BOLTS IN ASSY. UPON DISASSEMBLY, FOUND TUBE TO HAVE EXTREME CRACK RADIATING FROM THRU BOLT HOLE AND RADIATING AROUND TO BACK SIDE OF TUBE AND GOING OUT TO EACH SIDE IN A SPIRAL FRACTURE. PARTSDR QOF2005F00001Stringer · crackedTOP FORE AND AFT STRINGER CRACKED AT AFT MOST TAB AT JUNCTURE OF WELD. TURB TO TAB. (K)SDR QOF2005F00002Muffler · crackedMUFFLER SWELLS AND CRACKS AT TAIL PIPE WELD. (K)SDR QOF2005F00000Frame · crackedTOP FORE AND AFT STRINGER CRACKED AT AFT MOST TAB AT JUNCTURE OF WELD. TUBE TO TAB. 2004 MODEL. (K)SDR CA050806001Servo · unserviceable(CAN) DURING TAKEOFF, THE PILOT EXPERIENCED POWER SURGES AND FLUCTUATIONS IN MANIFOLD PRESSURE. THE SERVO COULD NOT BE ADJUSTED EITHER WAY AND BLUE STAINS WERE EVIDENT AT THROAT OF SERVO. ALSO, THE MANIFOLD PRESSURE WAS 2.5 INCHES HIGHER THAN NORMAL AT 100 PSDR 2005FA0001429Wire · chafedTRANSPONDER CIRCUIT BREAKER POPPED AND PILOTS NOTED SMOKE IN CABIN. FLIGHT WAS DISCONTINUED AND DISCREPENCY WAS NOTED. AFTER INSPECTION, CHAFFED WIRE WAS FOUND NEAR THE AVIONICS RACK THAT HAD SHORTED ON THE AIRFRAME. THE WIRES WERE REPAIRED IAW MFG RECOMMENSDR 2005FA0001009Bellcrank · bindingBINDING IN FLAP DR SYS AT BELLCRANKS WHERE ROD ENDS ATTACH. FLAP DR RODENDS WERE FOUND DIGGING INTO BELLCRANK ARMS AS THEY OPERATED, NML TRAVEL AS SHOWN BY RUB MARKS ON RODENDS. BELLCRANK ARMS, EXCESS CLAMPED BY RODEND ATTACH BOLTS, SOME BOLTS NOT TIGHTENED SDR 2005FA0001438Gear · brokenON RESTART IN THE AIR THE STARTER DRIVE GEAR BROKE. THE PILOT WAS UNABLE TO START THE ENGINE. THE GEAR ALSO DAMAGED THE RING GEAR ON THE ENGINE. (K)SDR 2005FA0000856Wheel · crackedAIRCRAFT LANDING SAFELY, WHILE TAXIING, LT TIRE WENT FLAT. ONCE WHEEL FAIRING REMOVED, NOTED IB WHEEL HALF WAS RUBBING BRAKES. PILOT THEN SAID BEEN SMELLING RUBBER AFTER LANDING BRIEFLY. ONCE DISASSEMBLED, WITH BRAKE DISC REMOVED, IB WHEEL HALF CRACKED ALONSDR 2005FA0000613Servo · chafedDURING MFG 200 HOUR INSPECTION FOUND THE AUTOPILOT SERVO CABLE IN THE RT WING RUBBING ON SERVO CABLE GUARD ALMOST RUBBING THRU ONE LEG OF GUARD. INSPECTED CABLE FOUND OK. INSTALLED A NEW GUARD AND CLOCKED TO CORRECT POSITION ON SERVO. (CE07200512741) (K)SDR 2005FA0001061Antenna · inoperativeFOUND LOWER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE. (K)SDR 2005FA0000715Retainer · damagedFLYWEIGHT RETAINING DISC, DAMAGED. (K)SDR 2005FA0000783Retainer · damaged(22209) FLYWEIGHT RETAINING DISC DAMAGED. (K)SDR 2005FA0000625Bushing · splitINNER RUBBER/ PLASTIC MATERIAL NOTED PROTRUDING FROM BOTH SIDES OF BUSHING. MATERIAL INSIDE BUSHING SPLITTING IN SEVERAL AREAS. LT MLG BUSHING ONLY, RT MLG BUSHING APPEARS NORMAL. (K)SDR 2005FA0000610Wire · brokenFOUND ORANGE WIRE FOR THE LOW VOLT ANNUNCATOR FOR THE G-1000 BROKEN INSIDE THE J-BOX WOULD NOT CAUSE THE ANNUNCATOR TO LIGHT UP ON THE PFD (PILOTS FLIGHT DISPLAY). APPEARS WIRE HAVE CHAFED ON J-BOX TO BREAK WIRE. ADDRESSED AND CORRECTED AS REQUIRED. (CE0720SDR 2005FA0000614Connector · looseTACHOMETER INDICATION JUMPS AROUND IN FLIGHT. INSTALLED A NEW TACHOMETER CONNECTOR, IAW MFG SL. OPS CHECK OK. (CE07200512734) (K)SDR 2005FA0000615Probe · inoperativeDURING LEAN FIND FOR G-1000 WOULD NOT INDICATE NR1 AND NR2 ENGINE CYLINDERS. TROUBLESHOT, USED EGT/CHT TESTER AND FOUND PROBES BAD ALSO SHIP SIDE CONNECTOR WAS ALSO BAD, FOUND SCREWS LOOSE INSIDE CONNECTOR. REPLACED NR1 AND NR2 ENGINE CYLINDER PROBES AND COSDR 2005FA0000617Probe · failedDURING FLIGHT, FUEL INDICATIONS WOULD RED-X OUT AND INDICATIONS SHOWING QUANITY JUMPED AROUND LT AND RT SIDE. TROUBLESHOT, AND REPLACED PROBES/ SENDERS IAW MFG. CALIBRATED IAW MFG MM. OPS CHECK OK. NOTE: NEED IMPROVEMENT IN TROUBLESHOOTING PROCEDURES IN MMSDR 18HPControl Unit · defectiveWHILE RUNNING UP AIRCRAFT AFTER MAINTENANCE, IT WAS NOTICED THAT THE FUEL QTY GAGES WERE JUMPING FROM FULL TO EMPTY AND THE LOW FUEL LIGHT WAS FLASHING. BOTH TANKS WERE FULL AT THE TIME. INSTALLED NEW SENDING UNITS IN BOTH WINGS AND IT SEEMED TO REMEDY THE PSDR TZR2005F00014Cylinder · crackedCYLINDER HAS A CRACK IN THE INTAKE VALVE SEAT. (K)SDR 2005FA0000611Pin · looseG-1000-3 PIN CONNECTOR FOR MANIFOLD PRESSURE TRANSDUCER, THE PINS WILL GET LOOSE AND CAUSE THE MANIFOLD PRESSURE INDICATION TO JUMP FROM 7.7 TO 55 MP PSI. TROUBLESHOT, WITH THIS IN THE FUTURE DUE TO VIBRATION OF AIRCRAFT. NOTE: NEVER HAD A RED-X OVER MP INDISDR 2005FA0000612Pin · looseG-1000-3 PIN CONNECTOR FOR OIL PRESSURE TRANSDUCER, THE PINS WILL GET LOOSE AND CAUSE THE OIL PRESSURE INDICATION TO JUMP FROM 45 TO 110 PSI. TROUBLESHOT, RESET PIN TO SHRINK (SHIP SIDE). SUSPECT WILL HAVE PROBLEMS WITH THIS IN THE FUTURE DUE TO VIBRATION OFSDR CA050318002Structure · departed(CAN) AC HAD ITS RT FINLET DEPART. AC CONDUCTING REPEAT LATERAL STABILITY TESTING. DEPARTURE WAS BOTH HEARD AND FELT BY PILOT AND TECH OBSERVER. AC RETURNED TO ITS POINT OF DEPARTURE WITH NO ADVERSE STABILITY ISSUES. UPON DETAILED INSP, IT WAS DETERMINED SDR X6PA200500001Bolt · brokenPILOT'S SEAT BACK ADJUST BOLTS BROKE, ALLOWING SEAT BACK TO RECLINE.SDR 2005FA0000687Indication Sys · inoperativeUNIT WAS INSTALLED IN AIRCRAFT ON 12/20/2004. AFTER APPROX .5 HOURS, PILOT OBSERVED TURN COORDINATOR OFF FLAG, MOMENTS LATER AUTOPILOT DISENGAGED. THIS UNIT REPLACED AN EARLIER INSTALLED OVERHAULED UNIT INSTALLED 7/04. (K)SDR 2005FA0000752Pump · obstructedRECEIVED BOOST PUMP FOR WARRANTY CREDIT WITH A CUSTOMER COMPLAINT OF (BREAKER POPS WHEN FUEL PUMP IS TURNED ON). PRELIMINARY INSPECTION OF THE PUMP REVEALED FOREIGN MATERIAL IN THE INLET PORT. FURTHER INSPECTION OF THE PUMP REVEALED THE FOREIGN MATERIAL TRIESDR 2005FA0000086Pin · out of adjustTRANSIT CUSTOMER HAD RUDDER TRIM STICK IN FULL RT TRIM CONDITION AND COULD NOT TRIM LT. FOUND THAT IF TRIMMED TOO FAR TO RT. THE INDICATOR PIN WOULD JUMP OUT OF TRIM WHEEL TRACK AND COULD LOCK TRIM WHEEL. WE READJUSTED INDICATOR PIN AND CENTERED CONTROLS. SDR CSJ2005F00000Door · departedPILOT REPORTED THAT IN LEVEL CRUISE FLIGHT AFTER ENCOUTERING TURBULENCE THE CABIN DOOR OPEN LIGHT ILLUMINATED. IMMEDIATELY FOLLOWING THE LIGHT THE UPPER CABIN DOOR OPENED AND DEPARTED THE AIRCRAFT. THE PILOT EXECUTED AN EMERGENCY LANDING WITH NO FURTHER INCISDR 2005FA0000172Strut · corrodedPERFORMING ROUTINE SERVICE, THE RT MLG STRUT WAS FOUND LEAKING 5606 HYDRAULIC FLUID. DISCOVERED THAT THE STEEL (4130) ATTACHMENT FOR THE GEAR DOOR HAD CREATED DISSIMILAR METAL CORROSION AND CREATED A PIN HOLE LEAK. THIS PART NEEDS TO BE REMOVED AND CHECKED TSDR BJ3R200400003Pump · defectivePILOT REPORTED, WHEN TURNING ON ELECT FUEL BOOST PUMP TO PREPARE FOR DESCENT, ENG RAN VERY ROUGH AND WAS SIGNIFICANT POWER LOSS. ENG WOULD NOT REMAIN RUNNING WITH FUEL BOOST PUMP ON. WHEN THE BOOST PUMP WAS TURNED OFF THE ENG OP WAS SATISFACTORY. DURING SUBSSDR FYO2004F00000Propeller · malfunctionedPILOT STATED THAT DURING CRUISE FLIGHT, PROPELLER WENT TO FINE PITCH, AND OPERATION OF GOVERNOR CONTROLS HAD NO EFFECT. UPON GROUND RUN UP IT WAS FOUND THAT PROP WOULD NOT CYCLE. REMOVED FROM SERVICE. UNKNOWN CAUSE FOR FAILURE AT THIS TIME. (AL05200401344)SDR CA040913004Hinge · crackedDURING A ROUTINE MX INSPECTION, CRACK WAS DISCOVERED ON THE STABILIZER TRIM HINGE ASSY, (PORT SIDE) P/N: F513-1. TOTAL TIME ON AIRFRAME (AND PART) WAS 802 HOURS. THE CRACK WAS LOCATED BETWEEN THE RADIUS OF THE HINGE ARM AND LIGHTENING HOLE OF HINGE BODY. RESDR 2004FA0000816Stiffener · cracked2 INCH LONG CRACK IN LT AREA OF FIREWALL STIFFENER IN AREA OF THE PARKING BRAKE BRACKET MOUNTING. BELIEVED TO BE CAUSED BY FLEXING OF FIREWALL BY APPLICATION OF PARKING BRAKE. THIS IS THE SECOND AC IN FLEET WITH THIS PROBLEM. THIS AREA NEEDS ADDITIONAL REINSDR 2004FA0000883Starter · intermittentUPON ENGINE START UP, PILOT WENT TO ENGAGE STARTER, STARTER DID NOT ENGAGE. INVESTIGATED STARTER AND FOUND STARTER BENDIX WOULD NOT ENGAGE. SUSPECT FAULTY BENDIX.SDR 2004FA0000759Line · leakingIT APPEARS THAT THE FUEL LINE WAS LEAKING FUEL AT THE ATTACH POINT OF THE STEEL BRAIDED LINE TO THE FITTING. THE FUEL LINE IS ATTACHED AT THE FIRE WALL AND GOES TO THE INLET SIDE OF THE ENGINE DRIVEN FUEL PUMP. (CE07200416055)SDR VJ02004F00000Hose · failedDURING OWNER REQUESTED OIL CHANGE FOUND LW-13175-4-340 HOSE GUSHING FUEL ON TO ENGINE. HOSE FAILED OVER 10 INCH SECTION. INSTALLED NEW TSO-C53A TYPE D HOSE. FAILED HOSE WAS ORIGINAL INSTALLED AT MFG OF AIRCRAFT. HOSE MFG 2Q78, OLD BLACK RUBBER STYLE. IF ASDR MUY2004F00000Pressure Switch · leakingHYDAULIC PRESSURE SWITCH LEAKS INTERNALLY. LEAK IS VERY SLOW. OVER AN EXTENDED PERIOD OF TIME, HYDRAULIC RESEVOIR IS DEPLETED. LACK OF HYDRAULIC FLUID IN RESEVIOR CAUSED LT MAIN GEAR TO REMAIN UNSAFE DURING APPROACH AND LANDING. COMPONENT IS SEALED UNIT AN
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