JASC 8520
Service difficulty reports · 2,213
Reports filed under 8520 · Reciprocating Engine Power Section, newest first.
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 jasc_code = '8520' 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 jasc_code = '8520' 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 CA070503005Drive Gear · failed(CAN) LT ENGINE FAILED IN CRUISE FLIGHT. AIRCRAFT RETURNED TO BASE. ENGINE REMOVED AND REPLACED. THE ACCESSORY CASE WAS REMOVED AND FOUND THAT THE CRANKSHAFT DRIVE GEAR HAD FAILED (TEETH STRIPPED OFF DRIVE GEAR). (TC NR 20070503005)SDR CA070511003Bushing · worn(CAN) DURING CRUISE PORTION OF THE FLIGHT, THE PILOT NOTICED A VIBRATION FOLLOWED BY A NOISE AND LOSS OF OIL. THE PILOT SHUTDOWN THE ENGINE AND DIVERTED TO A NEARBY AIRPORT AND LANDED SAFELY. THE ENGINE WAS REMOVED AND SENT TO AN ENGINE SHOP FOR A TEARDOWN. SDR CA070518004Case · cracked(CAN) ENGINE WAS OVERHAULED OCT 02,2005, ENGINE WAS REMOVED FROM STEEL SHIPPING CONTAINER FOR INSTALLATION MARCH 25, 2007. CRACKS WERE FOUND ON THE REAR CASE AT THE IB HOLES FOR MAGNETO MOUNTING. THE ENGINE WAS SENT TO APPROVED AMO AND REPAIRED. FOLLOWING REPASDR 2007FA0000277Crankshaft · failedCRANKSHAFT FAILED NDI SB MSB96-10. (K)SDR CA070530003Crankshaft · failed(CAN) ON THE WAY BACK TO THE AIRPORT THE ENGINE DEVELOPED ABNORMAL VIBRATIONS AND THE PILOT DECIDED TO CLIMB TO 2,400 FT, THEN THE ENGINE SUDDENLY STOPPED. THE PILOT DECIDED TO FORCE LAND ON THE AUTO ROUTE IN A WESTERLY DIRECTION. AFTER INSPECTION, IT WAS DETESDR CA070319008Camshaft · worn(CAN) THIS ENGINE WAS JUST PUT ON WING TO REPLACE AN ENGINE THAT HAD CAMSHAFT WEAR. DURING A ROUTINE INSPECTION THE OIL WAS DRAINED AND A SUBSTANTIAL AMOUNT OF FERROUS METAL WAS DISCOVERED IN THE FILTER. AN OIL SAMPLE WAS SENT IMMEDIATELY TO PROGRESSIVE FOR ANSDR CA070313006Crankshaft · broken(CAN) APPROXIMATELY 45 MILES OUT, THE CREW NOTED A VIBRATION FROM THE LT ENGINE. THE CREW SECURED THE ENGINE AND FEATHERED THE PROP IAW THE CHECK LIST. THE FLIGHT CONTINUED TO DESTINATION WITHOUT INCIDENT. WITH COWLING’S REMOVED, NOTED THE CASE HAD BEEN BRSDR 2007FA0000202Crankshaft · corrodedDURING SCHEDULED OVERHAUL, THIS CRANKSHAFT WAS FOUND PITTED IN THE INNER BORE. THIS ENGINE WAS A FACTORY OVERHAUL JULY 2002, AND DID HAVE THE PID COATING. THE COATING DOES NOT SEEM TO BLOCK THE CORROSION. (K)SDR 2007FA0000221Crankshaft · corrodedDURING NORMAL OVERHAUL, CRANKSHAFT FOUND PITTED IN THE INTERNAL BORE. THIS ENGINE WAS LAST OVERHAULED BY THE FACTORY, JULY 2002.. THE PID COATING DOES NOT SEEM TO PREVENT PITTING OR CORROSION. (K)SDR CA070223003Seal · leaking(CAN) DURING A NORMAL WALK AROUND, OIL WAS OBSERVED ON THE COWLING. AN INVESTIGATION INTO THE OIL LEAK REVEALED THE CRANKSHAFT SEAL WAS BLOWN OUT. THE OIL SUMPS WERE DRAINED AND OIL FILTER CHECKED AND FOUND TO CONTAIN LARGE QUANTITIES OF METAL FILINGS. THE ENGSDR 2007FA0000201Crankshaft · corrodedTHIS CRANKSHAFT WAS LAST INSPECTED AND PID COATED AT THE FACTORY APRIL 23, 2002, YET 6 YEARS AND 2196 HOURS LATER, IT WAS PITTED, AND REQURIED FURTHER MACHINING. THE PID COATING DOES NOT SEEM TO HOLD UP, OR BLOCK THE CORROSION. (K)SDR CA070226006Camshaft · worn(CAN) EXCESSIVE WEAR ON NR 1 AND NR 2 INTAKE LOBE. CAUSED EXCESSIVE PITTING ON ALL LIFTER BODY ASSEMBLIES. (TC NR 20070226006)SDR NACA20070006Clutch · failedNR 2 ENGINE DROP IN BMEP, MAP DROPPED TO BAROMETRIC PSI, PRECAUTIONARY ENGINE SHUT DOWN. REPLACED NR 2 ENGINE DUE TO CLUTCH FAILURE REF: DC-6MM SECT V PG. 3-8.SDR FCPR20070003Gear · brokenENGINE FAILED IN FLIGHT. FOUND 13 TEETH MISSING FROM CAMSHAFT GEAR P/N 655516.SDR PAI52007S4448Stud · brokenDURING ANNUAL INSPECTION FOUND 5 BROKEN HOLD DOWN STUDS ON NR 4 CYLINDER. ENGINE WAS MODIFIED IAW RAM STC SE3630SW AND SE3631SW AT PREVIOUS OVERHAUL.SDR 20070125Gear · wornDURING INSPECTION OF THE ENGINE WHILE REPLACING THE CRANKSHAFT IAW SB 569A, IT WAS OBSERVED THAT (PN 13519647) CRANKSHAFT GEAR WAS EXCESSIVELY WORN. THE GEAR WAS REPLACED WITH A NEW PART.SDR 2007FA0000095Crankshaft · brokenENGINE BEGAN RUNNING ROUGH AND BECAME SMOOTH AGAIN DURING DESCENT. TROUBLESHOOTING FIRST FOUND BRASS METAL PARTICLES IN AIR FILTER AND OIL. CRANKSHAFT WAS APPARENTLY BROKEN OR CRACKED BUT STILL TOGETHER. AFTER NUMEROUS GROUND RUSN AND KNOCKING NOISES HEARD,SDR 2007FA0000031Crankshaft · corrodedTHE ENGINE CURRENTLY UNDERGOING ITS FIRST OVERHAUL SINCE NEW. THE CRANKSHAFT WAS CLEANED, URETHABOND 104 COATING REMOVED AND CORROSION PITTING WAS DISCOVERED BENEATH COATING. THE PITTING EXCEEDED (SERVICEABLE LIMITS) AS STATED IN SB NR 505B. THIS CAUSED THESDR 2007FA0000036Lifter · deterioratedAFTER DRAINING OIL AND INSPECTING FILTER, LARGE FLAKES OF METAL WERE FOUND. DISASSEMBLED VALVE TRAIN AND FOUND SPALLING ON CYLINDER NR 6 INTAKE LIFTER. DAMAGE OCCURRED TO THE CORRESPONDING CAM LOBE AND CLYINDER NR 5 INTAKE LIFTER DUE TO DETERIORATION OF CYLISDR 2007FA0000093Crankshaft · brokenCRANKSHAFT IS BROKEN IN AREA OF NR6, NR5 ROD JOURNAL. CRANKSHAFT BROKE ON APPROACH TO LANDING AS PROP RPM CONTROL WAS ADVANCED ON SHORT FINAL. ENGINE POWER UNDER VERY LOW POWER. ENGINE HAS NOT BEEN DISASSEMBLED YET. THERE IS ALREADY AN AD NOTE TO TAKE THESSDR CA061227005Crankshaft · cracked(CAN) LT ENGINE DEVELOPED AN OIL LEAK FROM CRANKSHAFT SEAL. DURING SEAL REPLACEMENT, IT WAS NOTICED THAT THE CRANKSHAFT FLANGE WHERE PROPELLER BOLTS ON, WAS CRACKED FROM ONE LIGHTNING HOLE TO THE OTHER. IT LOOKED AS IF THERE WAS AN INDENTATION ON THE BACK SIDSDR 2006FA0001234Piston · stuckENGINE QUIT IN FLIGHT, FOUND NR 3 CYLINDER PISTON NOT MOVING IN CYLINDER WHEN TURNING PROP. (K)SDR YYB2006F00000Crankshaft · corrodedINSIDE DIAMETER WAS FOUND TO BE PITTED AFTER REMOVAL OF THE COATING CALLED URETHABOND 104. THIS COATING WAS APPLIED IN THE FIELD. THE CAUSE FOR THE CORROSION IS UNCERTAIN. THEREFORE A SUGGESTION FOR PREVENTION IS NOT POSSIBLE. MY SPECULATION WOULD BE THAT SDR CA061109008Piston · cracked(CAN) HIGH OIL TEMPERATURE AND BURNING ODOR IN CABIN PROMPTED RETURN TO AIRPORT. COMPRESSION CHECK REVEALED LOW COMPRESSION NR 3 CYLINDER, REMOVAL REVEALED A PORTION OF THE SECOND RING LAND APPROX. 1.5 INCHES LONG BROKEN OFF THE PISTON AT THE 10 O`CLOCK POSITISDR 2006FA0001076Connecting Rod · failedENGINE FAILED ON CIRCLING CLIMB FROM AIRPORT. ROD CAME THRU ENGINE BLOCK. (INCIDENT ISW1107003) (K)SDR 2006FA0001061Lifter · brokenLIFTER BROKE. (K)SDR 2006FA0001060Lifter · brokenLIFTER BROKE. (K)SDR 2006FA0001059Lifter · brokenLIFTER BROKE. (K)SDR 2006FA0001027Rod · failedCYLINDER NR 2 PISTON ROD FAILED WHILE AIRCRAFT WAS IN CRUISE FLIGHT. PROP WAS FEATHERED. AIRCRAFT LANDED WITHOUT INCIDENT. (K)SDR FAA1023001Exhaust Valve · separatedPILOT REPORTED ENGINE VIBRATION FOLLOWED BY PROGRESSING LOSS OF POWER WHICH EVENTUALLY LED TO COMPLETE LOSS OF POWER AND ENGINE FAILURE. PILOT EXECUTED AN UNEVENTFUL EMERGENCY LANDING ON A PAVED STATE HIGHWAY. NO DAMAGE TO AIRCRAFT UPON LANDING. RESULTS OF ESDR CA061023005Case · cracked(CAN) THE ENGINE HAD A SMALL OIL LEAK. AFTER REMOVING THE DIP STICK ASSEMBLY, A CRACK WAS FOUND BETWEEN NR 2 AND NR 4 CYLINDERS. THE ENGINE WAS REMOVED FOR OVERHAUL. (TC NR 20061023005)SDR CA061018007Piston · cracked(CAN) ENGINE WAS TORN DOWN FOR INSPECTION DUE TO SMALL AMOUNT NON FERROS METAL IN FILTER. ENGINE TIME 2,707 HOUR. FRONT BEARING SLIGHT WEAR AND FLAKING (NORMAL FOR HIGH TIME ENGINE). NR 1 PISTON SKIRT CRACKED AT 1,100 HOURS. NOTE: THIS IS THE 4TH PISTON TSDR 2006FA0001199Screw · failedA POST ACCIDENT INVESTIGATION IDENTIFIED THAT THE CRANKSHAFT IDLER GEAR WAS MISSING SEVERAL TEETH. FURTHER EXAMINATION REVEALED THAT THE SCREWS HOLDING THE CRANKSHAFT IDLER GEAR SHAFT HAD FAILED. (K)SDR 2006FA0001062Crankshaft · corrodedINSIDE DIAMETER WAS FOUND TO BE PITTED AFTER REMOVAL OF THE COATING CALLED URETHABOND 104. THIS COATING WAS APPLIED BY MFG. THE SURFACE APPEARED TO BE VERY ROUGH, ALMOST THREADED. THE CAUSE FOR THE CORROSION IS UNCERTAIN. A SUGGESTION FOR PREVENTION IS NOTSDR CA061004006Bearing · broken(CAN) THE AIRCRAFT DEPARTED THE RUNWAY FOR A 1 HOUR TRIP. APPROXIMATELY 17 MINUTES INTO THE CRUISE PORTION OF FLIGHT THE PILOT NOTICED A LOSS IN OIL PRESSURE FOLLOWED BY NOISE FROM THE RT ENGINE. THE PILOT IMMEDIATELY FEATHERED THE PROP AND SHUTDOWN THE ENGINESDR 2006FA0000961Crankcase · leakingPOROSITY IN CRANKCASE NOSE SECTION ON THE RT SIDE BY THE OIL GALLEY PLUG. LEAKS OIL, MFG HAS BEEN NOTIFIED. (K)SDR CA060920013Crankshaft · broken(CAN) AT APPROXIMATLY 300 FEET AGL ON TAKE OFF THE PILOT REDUCED POWER FOR FULL POWER TO CLIMB POWER. A BANG WAS HEARD AND THE ENGINE LOST POWER. THE AIRCRAFT WAS OPERATING ON FLOATS AND WAS LANDED STRAIGHT AHEAD BACK ON TO THE LAKE IT HAD DEPARTED FROM. INVESDR CA060925004Piston · cracked(CAN) DURING REGULAR INSPECTION LOW COMPRESSION WAS NOTED ON NR 1 CYL. CYLINDER WAS REMOVED AND PISTON WAS CRACKED. CYLINDER ASSY WAS REPLACED. AIRCRAFT GROUND RUN WAS CARRIED OUT SATISFACTORY. (TC NR 20060925004)SDR 2006FA0000917Gear · brokenAC FLEW A SHORT LEG TO AN ISLAND 25 NM OFFSHORE. AFTER START-UP THE PILOT HEARD AN UNUSUAL NOISE THAT SOUNDED LIKE A LOOSE VALVE TRAIN. THE PILOT QUICKLY SHUT THE POWERPLANT DOWN AND DECIDED IT WOULD NOT BE SAFE TO COMPLETE THE TRIP BACK TO MAINLAND. MECHANSDR 2006FA0000906Bolt · shearedCRANKSHAFT GEAR BOLTS SHEARED/BROKE CAUSING ENGINE FAILURE. (ENGINE FIALED ON GROUND, DURING STARTING) (K)SDR 135N6813JLENGConnecting Rod · destroyedPILOT REPORTED RPM/POWER LOSS, SHUT ENGINE AS A PRECAUTIONARY MEASURE, RETURNED TO DEPARTURE AIRPORT.SDR CA060817007Bearing · damaged(CAN) PILOTS NOTICED SMOKE COMING FROM THE LT ENGINE AFTER SHUTDOWN. THEY ALSO NOTICED AN OIL LEAK. FURTHER INVESTIGATION REVEALED THAT ONE CRANKSHAFT BEARING HAD BEEN MOVED FROM ITS ORIGINAL PLACE AND WAS NOW LOOSE. THE ENGINE IS BEING REMOVED FOR REPLACEMENTSDR CA060731003Crankcase · cracked(CAN) DURING A ROUTINE INSPECTION AN AME VISUALLY DISCOVERED A CRACK 2-3 INCHES IN LENGTH. THE CRACK IS LOCATED BETWEEN CYLINDERS 3 AND 5 IN THE VICINITY OF THE LOWER RIB. PREVIOUSLY NO DISCREPANCIES HAD BEEN NOTED. THE ENGINE WAS SUBSEQUENTLY REMOVED FOR REPASDR 2006FA0000710Crankcase · crackedENGINE CASE CRACKED NEAR (7TH) STUD BETWEEN CYLINDERS 2 AND 4. PROBLEM FOUND WHEN INVESTIGATING OIL LEAK.SDR 2006FA0000682Crankcase · crackedFOUND A CRACK IN BOTH CASE HALF AT THE FOURTH AFT BOLT HOLE FROM FRONT OF CASE AT 12 O'CLOCK POSITION. CRACKS WERE FOUND ON AN INSPECTION OF ENGINE.SDR 2006FA0000683Crankcase · crackedFOUND A CRACK IN BOTH CASE HALVES AT THE FOURTH AFT BOLT HOLE FROM FRONT OF CASE AT 12 O'CLOCK POSITION. CRACKS WAS FOUND ON AN INSPECTION OF ENGINE.SDR CA060808004Bearing · broken(CAN) CONNECTING ROD BEARINGS ON NR 1,3, AND 5 RODS HAD SIGNIFICANT SURFACE DELAMINATION. BROKEN PIECES .5 INCH L X .1250 INCH W FOUND IN BETWEEN CONNECTING ROD BEARING AND CRANKSHAFT. (TC INCH 20060808004)SDR 2007FA0000213Crankcase · crackedDURING 100 HOUR INSPECTION A CRACK WAS DISCOVERED ON RT CRANKCASE HALF. THE CRACK (APPROXIMATELY 1 INCH) ORIGINATED FROM A LOWER PARTING FACE BOLT HOLE AND SHOWED EVIDENCE OF OIL LEAKAGE ONTO MUFFLER SHROUD (BURNED OIL). SPECIFIC CAUSE OF CRACK UNKNOWN.SDR 2006FA0000860Crankshaft · damagedPILOT REDUCED POWER FOR LANDING, PUSHED NOSE OF AC OVER TO DESCEND, LF ENGINE RPM INCREASED. PULL NOSE OF AC UP, RPM DECREASED. THEN PILOT REPORTED SLIGHT VIBRATION AND THE BANG. LT ENGINE WAS SHUTDOWN. AIRCRAFT LANDED WITHOUT INCIDENT. INSPECTION OF LT SDR 2006FA0000995Crankcase · brokenWHEN OUR ENGINE NEEDED A MAJOR OVERHAUL THE CRANKCASE WAS SENT TO DIVCO IN TULSA, OKLAHOMA FOR INSPECTION AND FAA AIRWORTHINESS CERTIFICATION. DIVCO DID REPAIRS AND MACHINE WORK AND CERTIFIED THE CRANKCASE AS AIRWORTHY ON FAA FORM 8130 PER 14 CFR § 43.13 (B).
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