Continental IO-520-D
Service difficulty reports · 283
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 = 'IO520D' 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 = 'IO520D' 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 2009FA0000833Pump · malfunctionedPARTIAL LOSS OF POWER IN CRUISE FLT 2500 MSL ON LEFT TANK. LOSS OF FUEL PRESSURE, SWITCHED TANKS, ENGAGED AUX FUEL PUMP AND REGAINED POWER. MONITORED ENGINE GAUGES, APROX 15 GAL OF 100 LL IN TANK. LANDED ON MECHANICAL PUMP. NO ISSUES ON LANDING. NOTIFIED DIRECSDR CA091005002Throttle Body · obstructed(CAN) THROTTLE WAS JAMMING AFTER INTIAL FLIGHT, FROM BEING PICKED UP AFTER THE PAINT JOB. AFTER ANOTHER GROUND RUN-UP AT AIRPORT, THE THROTTLE JAMMED AGAIN, SO THE ENGINE COWL WAS REMOVED FROM THE ACFT. THROTTLE CABLE WAS REPLACED AT OWNER REQUEST, THEN RAN SDR CA090615005Pushrod · bent(CAN) DURING A CYLINDER CHANGE, PUSHROD WAS FOUND TO BE BENT, REPLACED WITH SERVICEABLE UNIT.SDR CA090402003Screw · missing(CAN) THE PILOT NOTED HIS AILERON CONTROLS WERE SLUGGISH DURING FLIGHT AND THE CONTROL WHEEL WAS OFF CENTER DURING LEVEL FLIGHT. DURING ROUTINE INSP IT WAS FOUND THAT THE UPPER AILERON PULLEY BRACKET SCREW AND NUT WERE MISSING. THE PULLEY BRACKET WAS SLIGHTLY SDR CA081014003Actuator · separated(CAN) ACFT HORIZONTAL STAB TRIM JAM ON LANDING. ELEVATOR CONTROLS BECAME LIGHT. ACFT LANDED WITHOUT INCIDENT. UPON INSPECTION AT THE DOCK, THE PILOT FOUND THE HORIZONTAL STAB WAS COMPLETELY LOOSE, STAB COULD BE MOVED FULL TRAVEL UP AND DOWN WITH NO RESISTANSDR CA080930004Yoke · corroded(CAN) ASSEMBLY WAS FOUND CORRODED WHEN INSPECTED IAW SEB01-3.SDR CA080930005Bracket · broken(CAN) LT FLAPS HAVE EXCESSIVE PLAY WHEN DEPLOYED. SYSTEM INVESTIGATED AND LT SIDE FLAP PULLEY BRACKET FOUND BROKEN.SDR CA080917008Bulkhead · cracked(CAN) DURING A 100 HOUR INSPECTION AN AME FOUND CRACKS IN LOWER LT AND RT CORNER AT REAR FRONT ATTACH, WHICH HAD BEEN PREVIOUSLY REPAIRED AND HAS CRACKED AGAIN.SDR CA080917010Bulkhead · cracked(CAN) DURING A 100 HOUR INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT CORNER AT REAR FLOAT FITTING. CUSTOMER WAS NOTIFIED.SDR CA080917011Bulkhead · cracked(CAN) DURING A NON-ROUTINE INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT AND RT CORNERS AT REAR FLOAT FITTINGS.SDR A3W2008F00000Piston · brokenAT OIL CHANGE, FOUND ALUMINUM CONTAMINATION IN OIL FILTER ELEMENT. INVESTIGATION FOUND BROKEN PISTON SKIRT AND RING PARTS IN OIL PAN FROM NR 4 CYLINDER. NR 4 PISTON SKIRT WAS BROKEN AT LOWEST RING, AT BOTTOM OF PISTON HALF, TOTAL SKIRT WAS BROKEN OFF THIS PISDR CA080229005Bracket · broken(CAN) ON PREFLIGHT INSPECTION, PILOT FOUND WHEN FLAPS EXTENDED, LT FLAP HAD NO TENSION, AND COULD BE LIFTED TO THE RETRACT POSITION, POTENTIALLY CAUSING DISIMILAR LIFT WHEN ACTIVATED IN FLIGHT. INSPECTED AREA, AND FOUND LT BRACKET BROKEN AT F.S. 65.33, IB MOUSDR CA080225011Control Cable · frayed(CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140 AT THE PHENOLIC BLOCK.SDR 2008FA0000093Hub · crackedPROPELLER HUB CRACKED. (K)SDR CA080225010Control Cable · frayed(CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA140 AT PHENOLIC BLOCK.SDR 2007FA0000925Link Rod · wornTHROTTLE BUTTERFLY (P/N: 625601G) AND THROTTLE BODY (P/N: 639437)ARE WORN, ALLOWING BUTTERFLY SHAFT TO SLIDE SIDE TO SIDE CAUSING THE LINK ROD ASSEMBLY (P/N: 632558A1)TO WEAR CHAFING THE WAVE WASHER AND COTTER PIN. THE COTTER PIN AND WAVE WASHER AT THE THROTTLSDR 2007FA0000930Link Rod · wornTHROTTLE BUTTERFLY (P/N: 625601G) AND THROTTLE BODY (P/N: 639437) ARE WORN, ALLOWING BUTTERFLY SHAFT TO SLIDE SIDE TO SIDE CAUSING THE LINK ROD ASSEMBLY (P/N: 632558A1)TO WEAR CHAFING THE WAVE WASHER AND COTTER PIN. THE COTTER PIN AND WAVE WASHER AT THE THROTTSDR CA071011002Muffler · cracked(CAN) MUFFLER CRACKED AROUND PIPE AFTER BACKFIRE. (TC NR 20071011002)SDR A3W2007F00000Support · crackedWHILE TAXING, ONCE SNOW COVERED GLACIER, THE RT GEAR OUTER SUPPORT CRACKED AND FAILED, DAMAGING THE SUPPORT BULKHEAD. ROUGH SURFACE AND HIGH PART TT IS SUSPECTED AS CAUSE. NO OTHER AIRCRAFT STRUCTURES WERE DAMAGED. (K)SDR 2007FA0000651Fuel Cap · leakingFUEL LEAKING FROM BASE OF NEWLY INSTALLED PREMIUM FUEL CAPS. LOCATION ON WINGS IRRELEVANT. LEAK FROM BOTH IB AND OB CAPS. COMPLIED WITH MFG INSTRUCTIONS IAW VENT LOCATION WITHOUT EFFECT. EVIDENTLY NOT UNCOMMON PROBLEM, AS BLOGS ON MFG CLUB FORUM AND PILOTS ASSDR CA070801004Cylinder · cracked(CAN) DURING INSPECTION FOUND 6 CYLINDER CRACKED AT SPARK PLUG HOLE. (TC NR 20070801004)SDR CA070801005Cylinder · cracked(CAN) DURING INSPECTION FOUND NR 5 CYLINDER CRACKED AT SPARK PLUG HOLE. (TC NR 20070801005)SDR CA070703004Cylinder · cracked(CAN) CYLINDER CRACKED FROM FUEL INJECTOR TO SPARK PLUG HOLE, CRACK FOUND DURING 100 HR INSPECTION (TC NR 20070703004)SDR CA070711001Tube · cracked(CAN) ONE TUBE CRACKED NEAR RT REAR ENGINE LOAD MOUNT. NEW MOUNT INSTALLED. (TC NR 20070711001)SDR OYE2007F00000Leg Assy · brokenAFTER LANDING THE LT GEAR LEG BROKE AT UPPER AXEL BOLTS. THIS CAUSED LOSS OF CONTROL OF AIRCRAFT. IT APPEARED THAT THE LANDING GEAR LEG HAD BEEN CRACKED FOR SOME TIME DUE TO CORROSION NOTED AT BREAK. (K)SDR CA070529005Spar · cracked(CAN) DURING AN ANNUAL/100 HOUR INSPECTION FIN AFT SPAR WAS FOUND CRACKED. MFG SINGLE ENGINE CUSTOMER CARE SERVICE INFORMTION LETTER SE 80-85 ADDRESSES THIS PROBLEM. SERVICE KIT SK 185-25A INSTALLED THIS DATE. (TC NR 20070529005)SDR CA070529006Connecting Rod · destroyed(CAN) DURING FLIGHT, THE ENGINE BEGAN TO RUN ROUGH. THE AIRCRAFT MADE AN UNSHEDULED LANDING FOR INSPECTION. THE CRANKCASE WAS FOUND CRACKED AT THE NR 2 CYLINDER. THE ENGINE WAS REMOVED FROM THE AIRCRAFT. (TC NR 20070529006)SDR CA070504007Tube · leaking(CAN) AIRCRAFT LANDED, DURING TAXI RT MAIN WHEEL WENT FLAT AIRCRAFT WAS REMOVED FROM RUNWAY WHEEL ASSY REMOVED, TUBE FOUND TO HAVE A PIN HOLE, TUBE REPLACED, AIRCRAFT RETURNED TO SERVICE (TC NR 20070504007)SDR CA070528003Hub · cracked(CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, FOUND HUB THREADS CRACKED, FOUND ONE BLADE THREAD CRACKED, FOUND ONE BLADE RETENTION NUT CRACKED. FAA AD 91-15-04 APPLIED TO THIS PROPELLER FOR INITIAL INSPECTION AND MODIFICATION WHICH HAD BEENSDR CA070528005Hub · cracked(CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, AT THAT TIME THE PROPELLER HAD BEEN INSPECTED IAW AIRWORTHINESS MANUAL PART VI APPENDIX C (4). THE LAST OVERHAUL COMPLETED WAS JUNE 1987. THE PROPELLER HAD EXCEEDED THE MFG HARD TIME OF 1,500 HSDR CA070528006Blade · cracked(CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, AT THAT TIME THE PROPELLER HAD BEEN INSPECTED PER AIRWORTHINESS MANUAL PART VI APPENDIX C (4). THE LAST OVERHAUL COMPLETED WAS OCTOBER 1991. FOUND BOTH BLADE THREADS CRACKED. FAA AD 91-15-04 APSDR CA070228003Control Arm · defective(CAN) THE SUBJECT AIRCRAFT WAS CLIMBING OUT AFTER TAKEOFF AND EXPERIENCED A SIGNIFICANT LOSS OF CLIMB POWER RELATED TO A DROP IN ENGINE RPM FROM 2700 RPM TO 1600 RPM. THE PILOT EXECUTED ALL APPROPRIATE EMERGENCY PROCEDURES/ACTIONS WITH NO IMPROVEMENT. THE PILSDR CA070222003Bracket · cracked(CAN) HORIZONTAL STABILIZERS REMOVED FOR REPAIR. AFT ATTACHMENT POINT REINFORCEMENT BRACKETS PN 0732101-4 REPLACED WITH NEW. ADJACENT RIVETS REPLACED. TAIL RE-ASSEMBLED. DUAL INSPECTED. (TC NR 20070222003)SDR CA070731004Bellcrank · cracked(CAN) BELLCRANK HAS CRACKS ADJACENT TO AN3 BOLT HOLES. (TC NR 20070731004)SDR CA061025004Stud · unserviceable(CAN) WHILE INSTALLING THE MCCAULEY MODEL D3A34C403-B PROPELLER ONTO A CESSNA 185, THE ENGINEER WAS TIGHTENING THE FIBER LOCK NUTS ONTO THE PROPELLER MOUNTING STUDS, WHEN ONE OF THE NUTS KEPT ON TURNING AND DID NOT SEEM TO BE GETTING ANY TIGHTER. HE TRIED ANOTSDR CA061005002Rivet · loose(CAN) THE AIRCRAFT WAS DISASSEMBLED. IT WAS NOTED THAT THERE WERE SEVERAL LOOSE AND SMOKING FASTENERS THROUGH RT AFT WING FITTING BRACKET IN FUSELAGE. REFERENCED MFG PART MANUAL P527-12 FIGURE 30 INDEX NR 99. (TC NR 20061005002)SDR CA061010001Bulkhead · damaged(CAN) AT INSPECTION, SMOKING FASTENERS AT THE LT WING AFT FITTING WERE FOUND. FASTENERS WERE REPLACED AS REQUIRED. (TC NR 20061010001)SDR ERH2006F00002Reinforcement · unserviceableTHE AFT ATTACH POINTS OF THIS HORIZONTAL STABILIZER ARE STRUCTURALLY REINFORCED WITH AN INTERNAL REINFORCEMENT TRIANGLE BRACKET, PN 0732106 AND 0732106-1. CRACKS IN THESE REINFORCEMENTS WERE FOUND AROUND THE WASHERS OF THE ATTACH HARDWARE, AND IN THE RADIUS OSDR CA060825002Hinge · cracked(CAN) HINGE ASSEMBLY FOR STABILIZER OB BEARING WAS FOUND CRACKED FOR BOTH ELEVATORS. ELEVATORS REMOVED. SEVERAL CRACKS WERE FOUND ON EACH HINGE ASSEMBLY. HINGE ASSEMBLIES REPLACED ON STABILIZER. ALL PARTS INSTALLED USING NEW (AN) HARDWARE. INDEPENDENT CONTSDR CA060808006Fitting · cracked(CAN) DURING A 100 HOUR INSPECTION LOOSE RIVETS WERE NOTICED AROUND THE LT MAIN GEAR. ONCE THE FLOOR WAS LIFTED TO PERFORM THE REPAIRS, THE LT MAIN GEAR OB FITTING WAS FOUND TO BE CRACKED PROPOGATING FROM THE AFT END OF THE GEAR LEG OPENING TOWARDS THE AFT ENSDR CA060710003Throttle Control · separated(CAN) DURING A SCHEDULED 50 HOUR INSPECTION THE THROTTLE CONTROL WAS FOUND TO BE SEPARATED AT THE SWAGE AREA JUST AFTER THE CLAMP AREA ON THE ROD END END ALLOWING THE CONTROL GUIDE TO MOVE ALONG WITH THE CONTROL END POSSIBLY RESULTING IN CONTROL JAMMING. (TC NSDR CA060717003Mount · cracked(CAN) DURING ROUTINE INSPECTION, IT WAS DISCOVERED THAT THE FWD LT MOUNT PAD WAS CRACKED. THIS ENGINE MOUNT WAS INSTALLED 44.8 HRS AGO. REPLACED ENGINE MOUNT WITH SERVICEABLE P/N 075-1003-31, AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060717003)SDR CA060705005Rheostat · malfunctioned(CAN) AIRWORTHINESS DIRECTIVE SEARCH ON TRANSPORT CANADA`S WEB SITE DID NOT SHOW 93-24-15 APPLYING TO THIS AIRCRAFT. IT APPEARS THAT THE MODEL APPLICABILITY SECTION OF THE FAA AIRWORTHINESS DIRECTIVE IS INCORRECT. (TC# 20060705005)SDR CA060608003Shaft · damaged(CAN) ON INSP, IT WAS FOUND THAT THE RT AND LT CONTROL WHEELS WERE LOOSE ON THE CONTROL SHAFTS. AVION RESEARCH STC 00709LA HAD PREVIOUSLY BEEN INSTALLED TO REPLACE THE CONTROL WHEELS, HOWEVER, THE INSTALLATION INSTRUCTIONS CW-8001 REV1 FEB26/98 DO NOT ADDRESS SDR CA070502013Control Cable · broken(CAN) THE BOLT THAT ATTACHES THE LT FORWARD RUDDER CABLE TO THE RUDDER PEDAL SETUP WAS ORIGINALLY TOO TIGHTLY DONE UP. THE CABLE ATTACHMENT FORK WAS NOT ABLE TO MOVE FREELY ON END, IN THE FORK, AND BREAK UNDER LOAD. (TC NR 20070502013)SDR CA060526004Impulse Coupling · brokenDURING FLT, PILOT NOTICED A VERY SLIGHT RPM DROP AND SLIGHT ROUGHNESS. UPON LANDING A GROUND RUN WAS PERFORMED AND WHEN THE IGNITION SWITCH WAS SELECTED TO RT MAG, ENGINE DIED OFF BEFORE SELECTING BACK TO LT OR BOTH. WHEN COWLS WERE REMOVED IT WAS EVIDENT THSDR CA060516004Reinforcement · crackedEXCESSIVE MOVEMENT FOUND AT AFT LT HINGE ASSY, INSIDE REINFORCEMENT P/N 0732106-1, ALSO FOUND CRACKED.SDR CA060518003Strut · shearedDURING TOUCH DOWN, INSTRUCTOR HEARD THE VOICE ADVISORY SYSTEM WITH THE MESSAGE "CHECK GEAR" AND LOST THE LIGHT ON THE BLOCK INDICATOR P/N 2A11179-001 ON THE RIGHT AND SIDE. DECIDED TO LAND ON LAKE WITH SMALLER WAVE WITH NO PROBLEM. THE INSTRUCTOR FOUND THE SDR CA070716004Cylinder · cracked(CAN) NR 4 CYLINDER FOUND CRACKED DURING INSPECTION (TC IN20070716004)SDR CA060509001Flap Track · cracked(CAN) LT IB FLAP TRACK, FWD ANGLES, AGAINST SPAR FOUND CRACKED AT BEND RADIUS, LOWER END. (TC NR 20060509001)
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