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 CA030731002Cable · broken(CAN) DURING TAXI OF AIRCRAFT ADVANCING THROTTLE WOULD NOT INCREASE ENGINE RPM. - INVESTIGATION SHOWED THROTTLE CABLE BROKEN IN ENGINE COMPARTMENT BETWEEN WIRE CABLE AT BASE OF SOLID PUSH ROD ON CONTROL ASSEMBLY (THROTTLE).SDR CA030627003Mount · cracked(CAN) ENGINE MOUNT CRACKED AT SUPPORT PADS. REINFORCED TO CARRY 10520 ENGINE AS PER P-PONK STC SA461NW ON JULY 96. MOUNT REPLACED WITH NEW MOUNT PN 4402. NO VIBRATION TO DATE.SDR 2003FA0000630Piston · brokenDISMANTLED ENGINE DUE TO METAL CONTAMINATION FOUND NR 2 PISTON SKIRT BROKEN ON BOTTOM SIDE.SDR CA030521006Bracket · wrong part(CAN) FLAP CABLE IN LT WING AT FLAP PULLEY BRACKET FALL OF THE PULLEY BECAUSE OF THE WRONG SIZE OF PULLEY, PULLEY AND BOLT SHOULD BE USE ON A/C S/N 185-0238 AND ON.SDR CA030501002Support · cracked(CAN) DURING ROUTINE SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE RT AFT HORIZONTAL STABILIZER SUPPORT BRACKET WAS CRACKED. NEW PART 0712302-2 WAS INSTALLED USING CESSNA SERVICE MANUAL D2000-9-13.SDR CA030321010Rib · cracked(CAN) DURING 200 HR INSPECTION THE INBOARD FLAP TRACK BRACKETS FOR THE CLOSING SKIN WHERE FOUND CRACKED. DURING REPLACEMENT OF THESE BRACKETS IT WAS DISCOVERED THAT THE LOWER CORNER OF THE RIBS WHERE ALSO CRACKED. BOTH INBOARD AND OUTBOARD RIBS ON THE FELT INSDR AUS20030353Volt Regulator · unserviceable(AUS) VOLTAGE REGULATOR FAULTY. VIBRATING CONTACTS WELDED CLOSED CAUSING OVER VOLTAGE WHICH DAMAGED SOME AVIONICS EQUIPMENT.SDR CA040210007Blade · scored(CAN) AFTER SHUT-DOWN, PILOT NOTICED ONE PROPELLER BLADE ROOT SNAP RING HAD POPPED OUT OF ITS LOCATION DURING PREVIOUS FLIGHT. IN DOING SO, IT DAMAGED THE BLADE ROOT BY SCORING SURFACE. PROPELLER REMOVED AND SENT FOR REPAIR AT PROPELLER SHOP.SDR CA030204012Wire · overheated(CAN) LUG IMPROPERLY CRIMPED TO WIRE PA-6 AT RADIO MASTER SWITCH CAUSING AN OVERHEAT SITUATION WITH EVENTUAL SEPARATION OF WIRE FROM LUG. WIRE WAS ORIGINAL FROM CESSNA FACTORY INSTALLATION.SDR CA021119011Cylinder · failed(CAN) WHILE CONDUCTING A CYLINDER COMPRESSION TEST, THE FOLLOWING RESULTS WERE DISCOVERED:CYLINDER 1-40PSI, 2-45PSI, 3-0PSI, 4-0PSI,5-40PSI, 6-58PSITHE MEASURE OF THE CYLINDER BARRELS INDICATES THAT THEY SHOULD MEASURE '10 THOU OVERSIZE'. THE EXHAUST VALVES ARSDR 2002FA0001246Bolt · mismanufacturedCRANKCASE UPPER TIE BOLT THREADS WERE NOT CUT PROPERLY. THEY HAD A FLAT PROFILE LIKE THE THREADS WERE NOT CUT DEEP ENOUGH. CONDITION DISCOVERED WHEN ATTEMPTING TO INSTALL NUTS ON THE BOLT.SDR 2002FA0001196Cylinder · crackedA CRACKED CYLINDER HEAD FIN WAS DISCOVERED ON NR 1 CYLINDER FOLLOWING THE ACCEPTANCE RUN AFTER THE ENGINE HAD BEEN OVERHAULED. AN ATTEMPT TO DRESS IT OUT INDICATED THAT THE CRACK EXTENDED ON TO THE BASE OF THE FIN AND POSSIBLY CYLINDER HEAD. CYLINDER WAS REMSDR 2002FA0001184Collar · distortedIN ASSEMBLING A NEW STANDARD GOVERNOR OIL TRANSFER COLLAR TO THE CRANKSHAFT IT WAS FOUND TO BIND ON THE JOURNAL. PRIOR TO DIASSEMBLING THE COLLAR HALVES THE INSIDE DIAMETER WAS NOTED TO BE SMOOTH AND COLLAR TO JOURNAL CLEARANCE WITHIN NEW LIMITS. ONCE THE COSDR CA021004008Transmitter · failed(CAN) AT 1/4 FUEL LEVEL TRANSMITTER READS 7/8. NOTE: PROBLEM ONLY EXISTS WHEN TRANSMITTER IS IN FUEL. BENCH CHECK IN DRY CONDITION INDICATES CESSNA RESISTANCE SPEC'S AS NORMAL.SDR 2002FA0001062Tube · defectiveAT ENGINE OVERHAUL, PRIOR TO INSTALLING OIL SUCTION TUBE ASSY'S IN TWO IO-520D ENGINES, BOTH WERE DISCOVERED TO BE DEFECTIVE. ONE TUBE WOULD NOT FIT PROPERLY AND APPEARED TO HAVE NOT BEEN JIGGED PROPERLY IN THE WELDING PROCESS. THE OTHER TUBE HAD SPOT WELDS SDR CA021016026Connecting Rod · broken(CAN) PILOT EXPERIENCED STRANGE NOISE AND VIBRATION FROM ENGINE WHILE IN CRUISE. AIRCRAFT WAS LANDED AND TOWED TO SAFE STORAGE. ENGINE REPLACED.SDR 2002FA0001032Collar · mismanufacturedAT INSTALLATION OF A NEW GOVERNOR OIL TRANSFER COLLAR IT WAS DISCOVERED THAT THE ASSEMBLY HALVES WERE IRREGULAR AT THE PARTING SURFACE. THE INSIDE DIAMETER LOOKED SMOOTH AND REGULAR WHEN REMOVED FROM THE PACKAGE. ONCE DISASSEMBLED AND REASSEMBLED AND TORQUEDSDR 2002FA0001033Rod Bolt · stretchedAT INSTALLATION OF THE NEW CONNECTING ROD BOLT AND NUT IT WAS NOTED THAT PROPER TORQUE WAS NOT ACHIEVED WITH THE SAME AMOUNT OF TURNS AS THE OTHER ROD BOLTS AND NUTS. A VISUAL INSPECTION SHOWED THAT MORE THREADS WERE SHOWING PAST THE NUT THAN OTHER BOLTS ON TSDR CA020829005Bracket · cracked(CAN) AIRCRAFT LANDED IN ROUGH WATER, CAUSING THE BATTERY TO CRACK AT THE BATTERY POSTS. A COMPLETE INSPECTION OF THE AIRCRAFT WAS CARRIED OUT, AND THE CRACK IN THE REINFORCEMENT BRACKET WAS DISCOVERED. NO OTHER DEFECTS WERE FOUND.SDR 2002FA0000978Crankcase · crackedDURING OVERHAUL. THE LIQUID PENETRANT INSPECTION REVEALS CRACKS IN MAIN BEARING BOSSES, CENTER ON LEFT SIDE. DOWN IN OIL CHANNEL RADIUS. THIS CRANKCASE IS PHASE III 7TH STUD STYLE.SDR 2002FA0001114Filter · contaminatedTHE FUEL FILTER SUFFERED CONTAMINATION TO THE POINT OF ENGINE LEANING, REDUCING POWER TO LOW TO MAINTAIN FLIGHT WHILE IN AERIAL APPLICATION WORK. THE ALTITUDE WAS APPROXIMATELY .5000 FT AGL THE SPEED OVER THE CROP WAS 115 MPH. REPOSITIONING THE FUEL FILTER SSDR CA021122002Bracket · cracked(CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THE REINFORCEMENT BRACKETS WERE CRACKED. NEW PARTS 0732101-4 WERE INSTALLED.SDR CA020724009Float · loose(CAN) WHILE CONDUCTING A ROUTINE VISUAL INSPECTION PRIOR TO COWLING INSTALLATION, A SPACE WAS NOTED BETWEEN BOTH HALVES OF THE CARBURETOR OF APPROX 1/32 INCHES. FURTHER INSPECTION REVEALED THAT ALL FLOAT BOWL ATTACHMENT SCREWS WERE FOUND LOOSE. ALL SCREWS WERSDR CA020729006Cover · departed(CAN) UPON LIFTING OFF THE WATER THE RT FLOAT HATCH - DEPARTED THE FLOAT - CREASING RT FUSELAGE SKIN AHEAD OF BULKHEAD AT STATION 108.0 AND HIT RT LEADING EDGE OF HORIZONTAL STABILIZER.SDR CA020626003Snap Ring · missing(CAN) PROPELLER RECEIVED FROM CUSTOMER AFTER LOSS OF SNAP RING. PROPELLER WAS DISMANTLED, BLADES DRESSED, PAINTED AND ASSEMBLED.SDR CA020619012Gear · broken(CAN) AT THE MOMENT OF ACCIDENT, THE MOTOR DID A "KICK BACK". TWO TEETH OF THE CRANKSHAFT GEAR THAT WERE IN CONTACT WITH THE STARTER CLUTCH SHAFT GEAR BECAME BROKEN AND FELL INTO THE OIL PAN. THIS MODEL OF THE STARTER CLUTCH CAN STICK IF IT IS TURNED COUNTER-CSDR CA020606008Angle · cracked(CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE ANGLE - TAILCONE REINFORCEMENT RT IN THE TAILCONE BULKHEAD ASSEMBLY WERE CRACKED. NEW PARTS 0712048-7 (LT) AND 0712048-6 (RT) WERE INSTALLED USING THE EXISTING RIVET SIZE AND PATTERN.SDR CA020530008Pulley Bracket · broken(CAN) WHEN SELECTING FLAPS FOR LANDING, LEFT FLAP WOULD NOT COME DOWN. AIR PRESSURE KEPT IT UP. PILOT SELECTED FLAPS UP, AND LANDED.SDR CA020523017Fork · cracked(CAN) BOTH BOW WHEEL FORKS HAVE TWO CRACKS EACH UP TO 1.5 INCHES LONG LOCATED ON THE AFT UPPER EDGE OF FORK. THE CRACKS ARE RUNNING FROM EDGE OF THE FORK FORWARD THE TWO 5/16 INCH REAR MOUNTING BOLT HOLES. ONE OF THE CRACK HAD GONE BEYOND THE HOLE.SDR CA040622004Crankcase · cracked(CAN) WHILE CONDUCTING PRE-FLIGHT CHECK, OIL DRIPS WHERE NOTICED. AFTER VERIFICATION BY AN AMO, IT WAS DETERMINED THAT THERE WAS A SMALL CRACK IN THE CRANKCASE. ENGINE DISASSEMBLED AND CRANKCASE WAS REPLACED.SDR CA020510016Cylinder · worn(CAN) ENGINE INDICATING SYS & PARAMETERS WERE OP NORMALLY.AT 164.1 HRS OF OP, A CYLINDER DIFFERENTIAL CHECK WAS CARRIED OUT. ALL CYLINDERS WERE FOUND TO BE IN 60/80 RANGE. A/C CONTINUED TO FLY & AT 260.6 HRS OF OP, A 2ND DIFFERENTIAL CHECK SHOWED READINGS OF SDR CA020606009Counterweight · separated(CAN) ROLLER RETAINING PLATE VIBRATED THROUGH SIDE OF COUNTERWEIGHT ALLOWING ROLLER TO FALL OUT. COUNTERWEIGHT THEN STRUCK CRANKCASE CAUSING NOISE. CRANKSHAFT CRACKED AT OPPOSITE BUSHING FROM OVERLOAD. CRANKCASE AND TWO PISTONS DESTROYED.SDR AUS20020434Hub · corroded(AUS) PROPELLER HUB CORRODED IN AREA OF BLADE SOCKETS AND ON SHIM FACES.SDR AUS20020345Fitting · faulty(AUS) LH WING ATTACHMENT FITTING CONTAINED A SUBSURFACE DEFECT IN THE AREA ADJACENT TO BUT NOT INTO THE MAIN WING ATTACHMENT BOLT HOLE. FOUND DURING EDDY CURRENT INSPECTION.SDR CA011116002Control Arm · misinstalled(CAN) GOVERNOR WOULD NOT CYCLE PROP BELOW 1500 RPM. CONTROL ARM INSTALLED IN THE INCORRECT POSITION ON CONTROL SHAFT.SDR CA011116014Pump · failed(CAN) DURING CLIMB AFTER TAKEOFF FROM RUNWAY 16 AT YYC WHEN THE PILOT ADJUSTED THROTTLE AND MIXTURE THE ENGINE STOPPED PRODUCING POWER. AN EMERGENCY LANDING WAS CARRIED OUT ON THE END OF RUNWAY 16.SDR CA011017007Valve Seat · cracked(CAN) - NR 6 CYLINDER ASSEMBLY CRACKED FROM EXHAUST VALVE SEAT TO INJECTOR PORT TO INTAKE VALVE SEAT. - INJECTOR AND FUEL FLOW AND PRESSURE NORMAL SO CAUSE UNKNOWN.- CYLINDER REPLACED.SDR CA011003014Bracket · broken(CAN) FLAPS WOULD NOT EXTEND PROPERLY FOR TAKEOFF. PILOT LEFT FLAPS IN UP POSITION AND RETURNED TO BASE. BRACKET IS MOUNTED TO LOWER BULKHEAD USING 4 SCREWS AND LOCKNUTS ON THE 4 MOUNT TABS. BOTH INBOARD TABS ON BRACKET HAD FAILED AT THE BEND RADIUS, ALLOWING SDR AUS20010779Structure · damaged(AUS) HORIZONTAL STABILISER TIP DAMAGED.SDR CA010724023Arm · broken(CAN) RUDDER PEDAL PEDASTAL BROKEN ON LANDING. FOUND THE PEDAL ARM BROKEN DUE TO CORROSIONSDR CA011211004Control Cable · frayed(CAN) FWD (CARRY-THROUGH) CABLE REMOVED TO CARRY OUT AN INSPECTION ON IT'S CONDITION DUE TO THE FACT THAT IT IS IMPOSSIBLE TO FEEL OR SEE MOST OF THE CABLE AS IT'S INSTALLED IN THE A/C. INSPECTION REVEALED FRAYED SECTION WHERE CABLE GOES AROUND THE PULLEY SUGGSDR CA010622033Pump · leaking(CAN) THE PILOT NOTED FUEL DRIPPING FROM THE OVERBOARD DRAIN TUBE. MAINTENANCE DISCOVERED FUEL COMING FROM THE FUEL PUMP SEAL DRAIN. THERE IS A CRITICAL SERVICE BULLETIN C53 01-01. ALTHOUGH THE PART NUMBER DID NOT MATCH THE BASIC FUEL PUMP WAS IDENTIFIED BY THSDR CA010626006Switch · failed(CAN) ON GEAR EXTENSIONFOR LANDING IN PRINCE ALBERT SASK. THE RH MAIN GEAR DOWN INDICATOR LIGHT DID NOT ILLUMINATE. AFTER TESTING THE SYSTEM AND HAVING THE SAME RESULTS, THE PILOT ELECTED TO LAND AND DID SOWITHOUT INCIDENT. ON THE GROUND, TESTING REVEALED THATSDR CA011211005Channel · cracked(CAN) CHANNEL FOUND CRACKED DIRECTLY BEHIND LT STAB HINGE REINFORCEMENT, WHICH WAS ALSO CRACKED. FURTHER INVESTIGATION REVEALED CRACKED SPAR ALSO IN SAME AREA.SDR CA011219006Bulkhead · cracked(CAN) CRACK NOTED ON LT BULKHEAD DURING INSPECTION WITH MIRROR. BULHEAD IS LOCATED DIRECTLY ADJACENT TO BAGGAGE DOOR.SDR CA011221001Bracket · cracked(CAN) CRACK NOTED FROM RETAINER'S EDGE TO INBOARD ATTACHMENT SCREW HOLE AS VIEWED FROM THE LT SIDE OF A/C. ANOTHER CRACK NOTED IN BOTTOM BEND RADIUS OF BRACKET AND EXTENDING ALONG THE BEND FOR APPROX. 1 INCH. PROBABLE CAUSE IS FROM CARRYING EXTERNAL LOADS ON SDR CA010628022Channel · cracked(CAN) PREVIOUS FILED SDR FOR CRACKED STABILIZER- HINGE REINFORCMENT P/N 0732101-4 AFTER REMOVAL OF THE REINFORCEMENT CH-RT WAS FOUND CRACK IN P/N 0732602-2/1232114-1 CRACK IN 07323603-1. LOWER RADIUS LT SIDE STA 6 INCH. LENGTH OF COACH I".SDR CA010628029Spar · cracked(CAN) DURING ANNUAL INSPECTION FOUND PLAY IN HORIZONTAL STABILIZER TO ELINMINATE PLAY REPLACE ALL HARDWARE AND BUSHING IN ASS. DURING LUBRICATING OF ELEVATOR HINGES DISCOVERED CRACK ON STABILIZER HINGE REINFORCEMENT. THIS REINFORCEMENT IS RIVETED ON MAIN SPARESDR CA011211019Rib · corroded(CAN) LEAD BALANCE WEIGHT ATTACHES TO AFFECTED RIB AND CORROSION FORMED DUE TO DISSIMILAR METAL. AREA IMPOSSIBLE TO INSPECT UNLESS ELEVATOR TIP SKIN IS REMOVED TO ACCESS RIB. UPON REPLACEMENT OF RIB,SDR AUS20010456Bracket · corroded(AUS) MAIN LANDING GEAR ATTACHMENT BRACKET SEVERELY CORRODED.
Back to Continental IO-520-D