JASC 8520
Service difficulty reports · 2,214
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 99ZZZX307Bolts · misinstalledUPON DISASSEMBLY OF C/CASE FOR PROPELLER STRIKE INSPECTION, MOST OF THE THRU-BOLT NUTS SEEMED TO BE OVERTORQUED. MAJOR EFFORT WAS NEEDED TO BREAK THEM LOOSE AND SEVERAL FELT THEY WERE TWISTING AND THEN BROKE LOOSE WITH A LOUD CRACK. SEVERAL OF THEM, WHEN ROLSDR 99ZZZX306Bolts · misinstalledUPON DISASSEMBLY OF C/CASE FOR PROPELLER STRIKE INSPECTION, MOST OF THE THRU-BOLT NUTS SEEMED TO BE OVERTORQUED. MAJOR EFFORT WAS NEEDED TO BREAK THEM LOOSE AND SEVERAL FELT THEY WERE TWISTING AND THEN BROKE LOOSE WITH A LOUD CRACK. SEVERAL OF THEM, WHEN ROLSDR 99ZZZX305Bolts · misinstalledUPON DISASSEMBLY OF C/CASE FOR PROPELLER STRIKE INSPECTION, MOST OF THE THRU-BOLT NUTS SEEMED TO BE OVERTORQUED. MAJOR EFFORT WAS NEEDED TO BREAK THEM LOOSE AND SEVERAL FELT THEY WERE TWISTING AND THEN BROKE LOOSE WITH A LOUD CRACK. SEVERAL OF THEM, WHEN ROLSDR 99ZZZX182Bolt · mismanufacturedINSPECTED NEW ROD BOLTS OUT OF LYCOMING PACKAGING, FOUND 22 OUT OF 28 BOLTS HAD NOT BEEN MACHINED ON THE HEAD OF THE BOLT, ONLY ON THE THREAD END. LYCOMING CONTACTED AND THE BOLTS RETURNED TO THE FACTORY. SUBMITTER RECOMMENDED INSPECTING ALL NEW PARTS PRIOR SDR 99ZZZX1011Lifter · failedTHE EXHAUST LIFTER, PN 628488, IS CALLED FOR INSTALLATION IN TSIO520C IN TCM MANUAL NR X30579A. SIX NEW LIFTERS WERE INSTALLED AT OVERHAUL OF ENGINE. ONE YEAR AND 112 HOURS LATER, ALL SIX NEW TCM CYLINDER ASSYS HAD WORN OUT EXHAUST VALVES AND GUIDES.SDR 99ZZZX87Crankshaft · brokenENGINE LOST POWER RESULTING IN FORCED LANDING. INVESTIGATION REVEALED THE CRANKSHAFT BROKE AT THE NR 2 CONNECTING ROD JOURNAL.SDR 99ZZZX1046Crankcase · crackedDURING A FLIGHT, RT ENG BEGAN TO RUN ROUGH AND ON THE GROUND, HAD A NOTICEABLE OIL LEAK ALTHOUGH 9.5 QUARTS EXISTED. UPON ENG CHECK, NOTICED COMPOUND FRACTURE AT THE UPPER BASE OF CYL NR 4. ENG REMOVED AND DISASSEMBLED. FOUND FRACTURES THRU THE CASE STUD BOSDR AU981690Crankshaft · cracked(AUS) PRIOR TO HONING CRANKSHAFT TO 49.02 MM (1.930 INCHES) AND ON NDT INSPECTION, A CRACK OR INCLUSION ORIGINATING FROM A PIT WAS FOUND APPROXIMATELY 50.8 MM (2 INCHES) INSIDE FROM THE END.SDR CA981209010Crankcase · cracked(CAN) DURING INSPECTION, THE PRESENCE OF AN OIL LEAK AT THE LOWER FORWARD STUD AT NR 2 CYLINDER LED TO FINDING A CRACK 1.50 INCHES LONG IN THE CRANKCASE, WHICH WAS VERIFIED BY A FLUORESCENT PENETRANT INSPECTION. THE ENGINE WAS REPLACED.SDR CA981207001Crankcase · cracked(CAN) ENGINE LEAKING OIL. INSPECTION FOUND TWO THROUGH BOLTS BROKEN. THIS CAUSED NR 4 CYLINDER TO BECOME LOOSE. THE LOOSE CYLINDER CREATED PULL ON THE CYLINDER HOLD-DOWN STUDS AND CRACKED THE CRANKCASE, WHERE THE STUD WAS PULLED.SDR 98ZZZX4747Crankshaft · out of toleranceWHILE INSPECTING CRANKSHAFT, S/N V21384, PER TEXTRON LYC MSB 475B AND FAA AD 91-14-22, NOTICED CRANKSHAFT COUNTERBORE HAD BEEN FACTORY REPAIRED BY CHROME PLATING PER MSB 475B; CRANK FLANGE MARKED 'L-21884-1', HOWEVER, NEW 13S19646 GEAR MARKED 7189, 29/98, MFR3SDR 99ZZZX635Crankcase · crackedDURING 50 HOUR INSPECTION, AN APPARENT OIL LEAK WAS FOUND ON THE TOP LEFT OF ENGINE CASE. PERFORMED DYE PENETRANT TEST. FOUND CRACK IN CASE ABOVE NR 2 CYLINDER ALONG THE EXHAUST LIFTER BOSS. CRACK WAS APPROXIMATELY 4 INCHES LONG. NO APPARENT REASON FOR DEFSDR 98ZZZX4558Camshaft · wornNR 2 CYLINDER EXHAUST LOBE ON CAMSHAFT WORN.SDR AU981569Tappet · worn(AUS) LT ENGINE NR 6 CYLINDER EXHAUST VALVE HYDRAULIC LIFTER CHIPPED AND PITTED. CORRESPONDING CAM LOBE ALSO BADLY WORN. PART TC: 97.SDR 98ZZZX4763Rod · brokenCONNECTION ROD BROKE .1250 INCH ABOVE WHERE BOLT GOES THROUGH TO CONNECT ROD CAP.SDR 98ZZZX4507Case · crackedCASE CRACKED BELOW NR 3 CYLINDER TOP STUD SECOND FROM THE FRONT. FOUND DURING CYLINDER REMOVAL TO REPLACE BASE SEAL. CRACK ABOUT .50 INCH LONG.SDR CA981207002Crankcase · cracked(CAN) INSPECTION FOUND ENGINE CASE CRACKED AT A NON-CRITICAL AREA, RADIATING OUT FROM CYLINDER HOLD-DOWN STUD.SDR AU981407Crankshaft · damaged(AUS) CRANKSHAFT COUNTERWEIGHT BUSHING P/N 73810 BROKE UP ALLOWING BUSH TO SPIN IN THE BORE AND DAMAGE THE CRANKSHAFT.SDR 98ZZZX4590Lifter · chippedUPON REMOVAL OF CYLINDER NR 1, INSPECTION OF LIFTERS OF CAM LOBES REVEALED CYLINDER LIFTER FACE CHIPPED OUT CAUSING SCRATCHES ON CAMSHAFT LOBE. THIS AIRCRAFT DOES NOT HAVE A HISTORY OF PROLONGED PERIODS WITHOUT FLYING. ENGINE INSTALLED LESS THAN 3 YEARS AGO.SDR AU981358Crankshaft · misinstalled(AUS) RIGHT ROTATION CRANKSHAFT INSTALLED IN LT ROTATION ENGINE. NO TIMING MARKS ON CRANKSHAFT FLANGE. UNAPPROVED PART.SDR 98ZZZX4087Crankshaft · out of toleranceDURING TRIAL ASSY OF NEW CRANKSHAFT GEAR P/N 13S19646, MARKED 7/89, 27/98, MFR 30620, NOTED THAT GEAR WOULD NOT START INTO CRANKSHAFT COUNTERBORE DUE TO INTEFERENCE WITH THE COUNTERBORE ID AND/OR STD-1065 DOWEL. CRANKSHAFT WOULD BE ASSEMBLED WITH EARILIER 611SDR 98ZZZX4083Crankshaft · out of toleranceDURING TRAIL ASSY OF NEW 13S19646 GEAR, MARKED 7/89, 27/98, MFR 30620, IN CONJUNCTION WITH FAA AD 91-14-22 INSPECTIONS, THE GEAR WOULD NOT START INTO THE CRANKSHAFT COUNTERBORE. INTERFERENCE WAS FOUND BETWEEN THE CRANKSHAFT COUNTERBORE ID AND THE P/N STD-1065SDR 98ZZZX4079Crankshaft · out of toleranceCRANKSHAFT REMOVED FROM ENGINE AT TBO. JOURNALS REQUIRED GRINDING AND RENITRIDED DUE TO WEAR. INSPECTION OF GEAR COUNTERBORE PER AD 91-14-22 REVEALED DOWL HOLE HAD BEEN FACTORY REPAIRED BY INSTALLATION OF SLEEVE. TEXTRON LYCOMING SB 475 HAS NO DATA FOR SLEESDR CA990226008Gear · sheared(CAN) PILOT REPORTED SUDDEN STOPPAGE. POST-FLIGHT INSPECTION FOUND THE CRANK GEAR MOUNTED ON THE CRANKSHAFT HAD SHEARED AND SPLIT. IT DID A 180 DEGREE ROTATION AND REPLACED ITSELF, CAUSING THE ENGINE TO BE 180 DEGREES OFF TIMING.SDR CA981109010Crankcase · cracked(CAN) THE REAR ENGINE OF A 337G SKYMASTER WAS REPORTED AS RUNNING ROUGH. INSPECTION FOUND THE SPARK PLUGS FOULED, SO THE PLUGS WERE REPLACED. THE ENGINE RAN SMOOTH AND IT WAS RELEASED FOR RETURN TO SERVICE. ON THE SECOND FLIGHT WHEN POWER WAS REDUCED, THE ENSDR AU981426Lifter · damaged(AUS) HYDRAULIC EXHAUST VALVE LIFTER DAMAGED WITH SURFACE HARDENING CHIPPING AWAY. PART TC: 670.SDR 98ZZZX3854Rod · failedAIRCRAFT WAS HOVERING. LOUD BANG WAS HEARD, FOLLOWED BY ENGINE SUDDEN STOPPAGE. AIRCRAFT CONTACTED GROUND HARD CAUSING LANDING GEAR DAMAGE. SUBMITTER STATED IT APPEARED THE NR 3 CYLINDER PISTON CONNECTING ROD FAILED. ENGINE WAS DUE OVERHAUL IN APPROXIMATELSDR CA981109022Crankcase · cracked(CAN) PILOT REPORTED OIL LEAK ON NR 2 ENGINE. ENGINE WAS WASHED DOWN AND RUN-UP. INSPECTION FOUND A 1.5 INCH CRACK JUST BELOW THE FORWARD TOP THROUGH-BOLT AREA, NEAR THE THRUST BEARING AREA OF THE FRONT OF THE CRANKCASE. THE ENGINE WAS REMOVED AND SENT FOR SDR AU981383Crankcase · cracked(AUS) CRANKCASE CRACKED FROM NR 5 CYLINDER LOWER FRONT STUD.SDR AU981267Crankcase · damaged(AUS) ENGINE CRANKCASE BEARING MOVEMENT. CAMSHAFT LOBES DAMAGED. TWO CONNECTING RODS CRACKED.SDR 99ZZZX679Rod · separatedENGINE DEVELOPED EXTREME VIBRATION CLIMBING THROUGH 2,500 FEET MSL. OIL OBSERVED COMING FROM COWLING. ENGINE SHUT DOWN AND SECURED. POST-FLIGHT INSPECTION REVEALED NR 4 CYLINDER CONNECTING ROD EXITED THROUGH CRANKCASE. PISTON BROKEN. SEVERAL INTERNAL PARTSDR 99ZZZX111Crankshaft · misoverhauledDURING DISASSY OF CORE ENGINES RETURNED TO TEXTRON LYC, NOTICED ON SEVERAL INSTANCES, 7 AS OF THIS DATE, WHERE CRANKSHAFTS ARE BEING GROUND OR POLISHED IN THE CHEEK AREAS BY OVERHAULING AGENCIES, PRESUMABLY TO BALANCE THE UNIT. TEXTRON LYC HAS NO APPROVED DATSDR AU981266Crankshaft · cracked(AUS) ENGINE CRANKSHAFT CRACKED. CRANKCASE SADDLES FRETTED. CAMSHAFT LOBE DAMAGED.SDR 98ZZZX4363Thru-Bolt · brokenTHRU-BOLT IN CRANKCASE FOUND BROKEN.SDR CA981006002Rod · failed(CAN) DURING CRUISE, THE PILOT NOTED THE NR 1 ENGINE WAS RUNNING ROUGH. THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT RETURNED TO BASE. POST-FLIGHT INSPECTION REVEALED A HOLE IN THE ENGINE CASE, IT WAS ALSO NOTED THAT A CONNECTING ROD HAD FAILED. THE ENGINE WASSDR 98ZZZX3813Bolt · mismanufacturedWHILE CONDUCTING PRE-ASSEMBLY INSPECTION OF PARTS DURING ENGINE OVERHAUL, NOTICED THE CONNECTING ROD NUT WOULD NOT THREAD COMPLETELY ON ONE CONNECTING ROD BOLT. THE THREAD MAJOR DIAMETER ON THE DEFECTIVE BOLT WAS FOUND TO BE .378 INCH WHICH RESULTED IN AN INSDR CA980930013Crankshaft · cracked(CAN) REPORT OF PROBLEMS WITH CRANKSHAFT BALANCING R & O SHOP LED OWNER TO GROUND HIS AIRCRAFT AND REMOVE THE CRANKSHAFT FOR MPI INSPECTION. CRACKS WERE FOUND AROUND CRANKPIN RADIUS. THE CRANKSHAFT WAS REPLACED.SDR CA980930012Crankshaft · cracked(CAN) REPORT OF PROBLEMS WITH CRANKSHAFT BALANCING R & O SHOP LED OWNER TO GROUND HIS AIRCRAFT AND REMOVE THE CRANKSHAFT FOR MPI INSPECTION. CRACKS WERE FOUND AROUND 80 PERCENT OF THE NR 4 CRANKPIN RADIUS. SIGNS OF OVERHEATING WERE ALSO PRESENT ON THE SURFACSDR 98ZZZX4478Crankshaft · shearedJUST AFTER TAKEOFF, THE ENGINE STARTED TO RUN ROUGH AND LOST POWER. PILOT RETRACTED GEAR AND LANDED IN FIELD. INVESTIGATION REVEALED THE CRANKSHAFT FAILED BETWEEN NR 2 AND NR 3 CYLINDERS NTSB NR CHI98LA360. THE ENGINE IS STILL INSTALLED ON AIRCRAFT AWAITINGSDR AU981296Crankshaft · corroded(AUS) CRANKSHAFT CONTAINED MINOR CORROSION PITTING. FOUND DURING INSPECTION IAW AD/LYC/102 AMDT 2.SDR AU981200Crankshaft · failed(AUS) CRANKSHAFT FAILED TO MEET DIMENSIONAL LIMITS FOLLOWING REWORK IAW AD/LYC/102 AMDT 1 (LYC SB 05) (HAWKER PACIFIC ENGINEERING ORDER ENG 1627/2).SDR AU981165Crankshaft · corroded(AUS) CRANKSHAFT INTERNAL INSPECTION FOUND THAT THE CRANKSHAFT WAS CORRODED BEYOND LIMITS. FOUND DURING INSPECTION IAW AD/LYC/102AMDT 1.SDR 99ZZZX269Bolt · failedHEAD SEPARATED FROM ROD BOLT. SUBMITTER STATED CONTINENTAL ALSO ALLOWED RE-USE. CRUISE FLIGHT FAILURE. SUBMITTER SUGGESTED CONTINENTAL SPECIFY MANDATORY ROD BOLT REPLACEMENT WITH NEW AT OVERHAUL.SDR CA980928003Crankshaft · pitted(CAN) TO COMPLY WITH AD 98-02-08, IN ACCORDANCE WITH LYCOMING SERVICE BULLETIN 505B, PITTING WAS NOTED ON THE INTERNAL BORE OF THE CRANKSHAFT. FPI CARRIED OUT, NO CRACKS WERE FOUND.SDR CA980916029Bolt · sheared(CAN) PILOT EXPERIENCED TOTAL ENGINE FAILURE. AFTER A SUCCESSFUL FORCED LANDING, INVESTIGATION REVEALED CAMSHAFT WAS NOT TURNING WITH PROP ROTATION. THE REMOVAL REAR CASE SHOWED CRANKSHAFT GEAR ATTACHMENT BOLT AND DOWEL WERE SHEARED. THE GEAR WAS OUT OF MESSDR 2000ZZZX270Piston Pin · brokenC/W ROUTINE 50-HOUR OIL CHANGE. FOUND CHUNK OF ALUMINUM IN DRAIN PLUG, ALUM FND IN OIL SCREEN, FILTER. PULLED ALL SPARK PLUGS, FOUND OIL ON NR 4 CYL PLUGS. PULLED NR 4 CYL. FOUND NO PISTON PIN CAPS IN PLACE AND A LARGE CHUNK OF MATERIAL BROKEN OFF INSIDE OSDR CA980915023Crankshaft · disconnected(CAN) NR 2 ENGINE SUDDENLY STOPPED DURING FLIGHT. POST-FLIGHT INSPECTION FOUND THE CAMSHAFT AND THE ACCESSORY GEARBOX WERE NO LONGER DRIVEN BY THE CRANKSHAFT. A FOLLOW-UP REPORT WILL BE SUBMITTED.SDR CA980915003Ring · damaged(CAN) AFTER LANDING, THE PILOT NOTICED THE ENGINE WAS RUNNING ROUGH AND POPPING AT IDLE. INVESTIGATION FOUND THE CAM RING WAS DAMAGED. THE ENGINE WAS REMOVED AND SENT FOR REPAIR.SDR AU981463Camshaft · worn(AUS) NR 5 CYLINDER EXHAUST CAM LOBE WAS WORN BEYOND MANUFACTURER'S SPECIFICATIONS. THE LOBE WAS EXCESSIVELY WORN FROM WHAT APPEARS TO BE METAL FATIGUE. FAULT FOUND DURING SCHEDULED 1000 HOUR INSPECTION. THE ENGINE WAS FACTORY OVERHAULED ON THE 15NOV96.SDR CA990111058Camshaft · worn(CAN) THE ENGINE WAS REMOVED DUE TO METAL CONTAMINATION IN THE OIL. DURING DISASSEMBLY OF THE ENGINE, PREMATURE WEAR WAS NOTICED OF THE LIFTER BODY FACE AND OF THE INTAKE AND EXHAUST VALVES OF NR 1 CYLINDER; OF THE INTAKE VALVE OF NR 3 CYLINDER IN THE FORM OF
Back to JASC 8520