Cessna 421C

Service difficulty reports · 427

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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 aircraft_model_key = '421C'
  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.

SDR 97ZZZX5162Valve Seat · failedNEW TCM CYLINDER ASSYS INSTALLED AT ENGINE OVERHAUL. DATE STAMPED ON ROCKER BOSS: 7-97. AFTER BREAK-IN FLIGHT AND TEST FLIGHTS, NR 2 CYL ON LT ENGINE WAS NOTED TO HAVE LOW COMPRESSION: 18/80. LEAKAGE DETERMINED TO BE PAST INTAKE VALVE. REMOVAL AND DISASSNov 21, 1997 · N6798V · Cessna 421C · Reciprocating Engine Cylinder SectionSDR 97ZZZX5106Fitting · crackedDURING A 100-HOUR INSPECTION, THE END FITTING ON THE LT ELEVATOR WAS FOUND CRACKED AT THE HOLE FOR THE TAPERED PIN. IT APPEARS THE END FITTING HAD BEEN REMOVED FROM THE AIRCRAFT BEFORE. SUBMITTER STATED THE USE OF PROPER TORQUE WHEN INSTALLING THE TAPERED PINov 20, 1997 · N2656B · Cessna 421C · Elevator StructureSDR CA971110003Crankcase · cracked(CAN) PILOT REPORTED NR 1 ENGINE WAS RUNNING ROUGH. MAINTENANCE FOUND OIL LEAKS AND EVIDENCE OF COMBUSTION DETONATION AT NR 1 CYLINDER. FURTHER INSPECTION FOUND NR 36 STUD WAS PULLED OUT OF THE CRANKCASE THREADS. THE NR 1 CYLINDER BORE IN THE CRANKCASE WAS Oct 30, 1997 · Cessna 421C · Reciprocating Engine Power SectionSDR 97ZZZX4624Tire · failedTHIS TUBE-TYPE MAIN LANDING GEAR TIRE WAS INSTALLED AND OPERATED FOR 390 FLIGHT HOURS. ESTIMATE 290 LANDINGS. THE TIRE WAS FOUND TO HAVE BULGES ON THE EDGE OF THE TREAD AREA. THESE BULGES FEEL LIKE AIR POCKETS BETWEEN THE TREAD AND THE CORD. THE TIRE WAS DOct 22, 1997 · N68670 · Cessna 421C · TireSDR 97ZZZX4326Connecting Rod · brokenENGIEN FAILED EXPLOSIVELY WITH NO PRIOR INDICATIONS NOTED IN MAP, OIL TEMP, OR OIL PRESSURE. ENGINE DISASSEMBLED. INDICATIONS SHOW THAT POSSIBLY THE NR 6 CYLINDER CONNECTING ROD MAY HAVE BROKE CAUSING THE CASE TO BREAK AND COME APART.Sep 9, 1997 · N4162G · Cessna 421C · Reciprocating Engine Power SectionSDR 97ZZZX3699Clamp · crackedOVERBOARD EXHAUST PIPE CLAMP HAD 2 INCH CRACK AROUND CLAMP. REMOVED CLAMP AND INSTALLED NEW ONE.Jul 25, 1997 · N88604 · Cessna 421C · Engine Collector/Tailpipe/NozzleSDR 97ZZZX3495Valve Spring · failedTHE PILOT NOTICED A VIBRATION AT CRUISE POWER AFTER AN HOUR OF FLIGHT. AFTER LANDING, INVESTIGATION REVEALED THE RIGHT ENGINE WOULD INCREASE IN VIBRATION WITH AN INCREASE IN RPM AND NOT DEVELOP FULL RPM. TROUBLESHOOTING REVEALED THE NR 2 CYLINDER HAD BOTH INJul 3, 1997 · N85SC · Cessna 421C · Reciprocating Engine Cylinder SectionSDR 97ZZZX3072Gasket · tornAIRCRAFT CAME IN WITH RIGHT ENGINE LEAKING OIL. FOUND LEAK BETWEEN OIL COOLER AND CASE. WHEN COOLER PULLED AWAY FROM CASE, GASKET HAD A STRAIGHT LINE TEAR AND PART 'OF 1 SIDE OF GASKET ON CASE, OTHER ON COOLER. THE REST OF THE GASKET HAD UNEVEN MARKS LIKE BJun 25, 1997 · N321FL · Cessna 421C · Engine Oil CoolerSDR AU971646Control Cable · broken(AUS) FLAP CABLE SNAPPED.Jun 8, 1997 · Cessna 421C · Trailing Edge Flap Control SystemSDR AU970731Alternator · failed(AUS) LH ALTERNATOR FAILED - INSPECTION FOUND THAT THE FAILURE WAS DUE TO THE DIODE PLATE GROUND WIRE BEING LOOSEJun 1, 1997 · Cessna 421C · DC Generator-AlternatorSDR CA970609022Hub · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER HUB AND BLADES SUFFERED EXTENSIVE CORROSION. HUB REPLACED (NEW HUB S/N 961650) AND PROPELLER OVERHAULED.May 28, 1997 · Cessna 421C · Propeller Hub SectionSDR CA970609021Hub · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. HUB AND PROPELLER BLADES FOUND BADLY CORRODED. HUB REPLACED BY HUB S/N 961729 AND PROPELLER OVERHAULED.May 28, 1997 · Cessna 421C · Propeller Hub SectionSDR 97ZZZX2083Lug · brokenAFTER TAKEOFF ON TEST FLIGHT FOR REPLACEMENT OF CYLINDER ON LEFT ENGINE WHEN THE LANDING GEAR WAS RETRACTED, A LOUD NOISE WAS HEARD IN THE NOSE WHEEL AREA. THE LANDING GEAR WAS EXTENDED AND ALL INDICATIONS FOR DOWN AND LOCKED WERE PRESENT. AIRCRAFT LANDED WIMay 2, 1997 · N4162G · Cessna 421C · Landing Gear ActuatorSDR 97ZZZX2044Cylinder · separatedACFT LOST NR 5 CYLINDER IN CRUISE FLIGHT TO JBR. CYLINDER SEPARATED ABOUT 1 INCH INBOARD OF THREADED AREA IN STEEL SLEEVE. AREA CRACKED IS 360 DEGREES AND EXPOSED TOP RINGS ON PISTON CAUSING METAL CONTAMINATION IN ENGINE. OIL PRESSURE WAS LOST 4 MINUTES BEFApr 22, 1997 · N421FC · Cessna 421C · Reciprocating Engine Cylinder SectionSDR 97ZZZX1919Gear · failedNEW CRANKSHAFT GEAR P/N 653580 INSTALLED AT TIME OF ENGINE OVERHAUL IN CONJUNCTION WITH TCM SB CSB 94-4 IN KIT EQ6642. ENGINE FAILED APROXIMATELY 400.0 HOURS LATER. ENGINE DISASSEMBLY REVEALED THE POSSIBILITY THE GEAR BROKE FIRST CAUSING DAMAGE TO VALVE TRAINApr 22, 1997 · N6867L · Cessna 421C · Reciprocating Engine Power SectionSDR AU970360Nut · broken(AUS) ALTERNATOR DRIVE CLUTCH ASSEMBLY SEPARATED FROM ALTERNATOR DUE TO FAILURE OF THE SLOTTED HOLDING NUT - DAMAGE TO ENGINE GEARS AND CRANKCASE ASSEMBLY - METAL CONTAMINATION OF ENGINEApr 4, 1997 · Cessna 421C · Alternator-Generator DriveSDR 97ZZZX1712Adapter Gear · failedENGINE FAILED TO START. INSPECTION REVEALED FAILED STARTER ADAPTER. REMOVED ADAPTER AND FOUND DRIVE GEAR AND CRANKSHAFT GEAR DEFECTIVE. INSPECTION OF OIL FILTER REVEALED METAL CONTAMINATION OF ENGINE OIL SYSTEM. ENGINE TSOH: 1,067 HOURS. SUBMITTER RECOMMApr 4, 1997 · N999VE · Cessna 421C · Reciprocating Engine Rear SectionSDR 97ZZZX2030Spring · brokenRIGHT ENGINE WOULD NOT TURN OVER TO START. FOUND CLUTCH SPRING INSIDE THE STARTER ADAPTER BROKEN. REPLACED STARTER ADAPTER. NOTE: THIS ENGINE AND STARTER ADAPTER IS NOT REQUIRED TO BE INSPECTED BY TCM BULLETIN CSB94-4A.Apr 1, 1997 · N234CN · Cessna 421C · Reciprocating Engine Rear SectionSDR AU970211Pump · faulty(AUS) ENGINE FUEL PUMP FAULTY - SUSPECT INTERNAL STICKING IN SOLENOID - PUMP HAD COMPLETED 4.8 HOURS TIME SINCE OVERHAULMar 5, 1997 · Cessna 421C · Engine Fuel PumpSDR 97ZZZX1916Oil Cooler · malfunctionedWHILE AT CRUISE FL 210 OAT 45 DEGREES FAHRENHEIT, LEFT ENGINE OIL TEMP WENT UP WHILE OIL PRESSURE WENT DOWN, BOTH STILL IN 'GREEN'. AFTER PRECAUTIONARY LANDING AND INSPECTION, FURTHER FLIGHT WAS NORMAL. APPEARS OIL COOLER HAD CONGEALED DUE TO COLD WEATHER.Mar 1, 1997 · N18TC · Cessna 421C · Engine Oil CoolerSDR AU970385Pump · faulty(AUS) ELECTRICAL BOOST PUMP FAULTY - INVESTIGATION FOUND CHIPPED VANE WHICH CAUSED IMPELLER UNBALANCE AND WEAR TO THE VANES AND PUMP CAVITYFeb 27, 1997 · Cessna 421C · Fuel Boost PumpSDR 97ZZZX1052Control Cable · wornEXTREME CABLE WEAR (FLAP EXTEND) AT PULLEY JUST OUTBOARD OF THE FLAP MOTOR AND TRANSMISSION ASSY. PULLEYS MUST BE REMOVED IN ORDER TO SEE THIS TYPE OF WEAR. SUBMITTER RECOMMENDED 100 PERCENT INSPECTION OF FLAP CABLES (BY REMOVAL AND REPLACEMENT) AT 4,000 HOUJan 27, 1997 · N746CA · Cessna 421C · Trailing Edge Flap Control SystemSDR 97ZZZX1049Starter Drive · wornSTARTER DRIVE GEAR WEAR UNACCEPTABLE IAW TELEDYNE CONTINENTAL CSB 94-4 EVEN THOUGH THE SERVICE KIT REQUIRED BY TCM CSB 94-4 HAD BEEN PREVIOUSLY INSTALLED AT ENGINE OVERHAUL. SUBMITTER SUGGESTED CSB 94-4 MAY NOT BE SUFFICIENT. RECOMMENDED FLEET DATA BE EXAMINJan 27, 1997 · N411MZ · Cessna 421C · Reciprocating Engine Rear SectionSDR 97ZZZX820Pick Up · pluggedPILOT REPORTED THE RT ENGINE OIL PRESSURE WAS HIGH ON THE GROUND NEAR RED LINE, BUT WOULD FALL IN PRESSURE AT ALTITUDE, THE HIGHER THE ALTITUDE, THE LOWER THE OIL PRESSURE WOULD FALL REACHING BOTTOM RED LINE AT 12,000 FEET. THE OIL PRESSURE SPRING WAS REPLACEJan 18, 1997 · N307FM · Cessna 421C · Reciprocating Engine Oil SystemSDR CA970114010Cylinder · separated(CAN) #1 ENGINE RUNNING ROUGH ON TAKEOFF. AIRCRAFT RETURNED TO BASE. POST FLIGHT INSPECTION FOUND #5 CYLINDER HEAD SEPARATED FROM THE BARREL, WITH A THREE INCH CRACK FROM THE INTAKE VALVE TO THE INTAKE PORT.Dec 29, 1996 · Cessna 421C · Reciprocating Engine Cylinder SectionSDR 97ZZZX606Coupling · failedON CLIMB-OUT THE RIGHT ALTERNATOR WENT OFF LINE. SOON AFTER THE OIL PRESSURE STARTED TO DECREASE AND THE OIL TEMP STARTED TO INCREASE, THE PILOT FEATHERED THE RIGHT ENGINE AND LANDED AT NEXT AIRPORT. INVESTIGATION REVEALED THAT THE ALTERNATOR HAD FAILED INTEDec 26, 1996 · N421HP · Cessna 421C · Alternator-Generator DriveSDR 97ZZZX192Air Filter · failedCABIN PRESSURIZATION WEAK, INSPECTED PRESSURIZATION HEAT EXCHANGER IN WING. BOTH EXCHANGERS PLUGGED WITH FELT MATERIAL. SUSPECT FELT MATERIAL CAME FROM ENDS OF PAPER AIR FILTERS. VACUUM AND CLEANED HEAT EXCHANGERS, TEST FLIGHT CHECK, AND NORMAL.Dec 16, 1996 · N88604 · Cessna 421C · Cabin Pressure Control SystemSDR CA961223004Cylinder · separated(CAN) DURING CLIMBOUT THE #1 ENGINE HAD A LOSS OF POWER FOLLOWED BY ROUGH RUNNING. ON RETURN TO THE AIRPORT OIL WAS NOTICED ESCAPING THROUGH THE #1 ENGINE COWLING. POST FLIGHT INSPECTION FOUND THE #1 CYLINDER HEAD LYING IN THE COWLING. THE CYLINDER WAS REMOVEDDec 3, 1996 · Cessna 421C · Reciprocating Engine Cylinder SectionSDR 97ZZZX3484Washer · failedON LANDING ROLL-OUT, RT MAIN LANDING GEAR ROTATED 90 DEGREES AND BACK AGAIN. INVESTIGATION FOUND MAIN GEAR SCISSOR CENTER BOLT AND BUSHING RETAINING WASHER FAILED AND ALLOWED BUSHING TO 'WALK' AND SCISSOR TO DISCONNECT, ALLOWING TIRE TO ROTATE. NEW P/N S145Dec 2, 1996 · N234CN · Cessna 421C · Main Landing Gear Strut/Axle/TruckSDR 97ZZZX364Separator · failedENGINE OIL PUMPING OVERBOARD. FOUND OIL AIR SEPARATOR INTERNAL SCREEN (SMALL) FAILED AND WAS BLOCKING OIL RETURN TO CRANKCASE. ENGINE DAMAGE AT THIS TIME UNKNOWN. SEPARATOR INSTALLED 411 HRS AGO NEW. ONLY SERVICES WET VACUUM PUMP. WENT TO DRY PUMP.Dec 1, 1996 · N726RT · Cessna 421C · Reciprocating Engine Oil SystemSDR 96ZZZX6160Drive Adapter · wornSTARTER DRIVE GEAR WEAR UNACCEPTABLE IAW TELEDYNE CONTINENTAL CSB 94-4 EVEN THOUGH THE SERVICE KIT REQUIRED BY TCM CSB 94-4 HAD BEEN PREVIOUSLY INSTALLED AT THE ENGINE OVERHAUL. SUSPECT CAUSE: CSB 94-4 MAY NOT BE SUFFICIENT. SUBMITTER RECOMMENDS FLEET DATA Nov 16, 1996 · N749CA · Cessna 421C · Reciprocating Engine Rear SectionSDR 97ZZZX158Blade · corrodedINSPECTION FOUND PROPELLER BLADE ASSY B4426 CORRODED.Nov 5, 1996 · Cessna 421C · Propeller Blade SectionSDR 97ZZZX157Bearing · corrodedINSPECTION FOUND BLADE BEARING CORRODED.Nov 5, 1996 · Cessna 421C · Propeller Blade SectionSDR 97ZZZX156Blade · corrodedINSPECTION FOUND PROPELLER BLADE CORRODED.Nov 5, 1996 · Cessna 421C · Propeller Blade SectionSDR 97ZZZX155Propeller · wornINSPECTION FOUND PROPELLER ASSY P/N 3474 WORN.Nov 5, 1996 · Cessna 421C · Propeller AssemblySDR 97ZZZX143Prop Assy · wornINSPECTION FOUND PROPELLER ASSY P/N D3474 WORN.Nov 5, 1996 · Cessna 421C · Propeller AssemblySDR 97ZZZX142Prop Assy · corrodedINSPECTION FOUND PROPELLER ASSY P/N D5878/C501 CORRODED.Nov 5, 1996 · Cessna 421C · Propeller AssemblySDR 97ZZZX141Propeller Assy · wornINSPECTION FOUND PROPELLER ASSY P/N D3474 WORN.Nov 5, 1996 · Cessna 421C · Propeller AssemblySDR 97ZZZX140Propeller Assy · corrodedINSPECTION FOUND PROPELLER ASSY P/N A4191 CORRODED.Nov 5, 1996 · Cessna 421C · Propeller AssemblySDR 97ZZZX139Prop Assy · corrodedINSPECTION FOUND PROPELLER ASSY P/N A1896 CORRODED.Nov 5, 1996 · Cessna 421C · Propeller AssemblySDR 96ZZZX5643Control Cable · frayedUPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED. ALSO NOTE THAT LOCATION OF DAMAGE AREAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL. BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERNAL VISUAL INSPECTIONNov 4, 1996 · N247CB · Cessna 421C · Trailing Edge Flap Control SystemSDR 96ZZZX5642Control Cable · frayedUPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED. ALSO NOTE THAT LOCATION OF DAMAGE AREAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL. BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERNAL VISUAL INSPECTIONNov 4, 1996 · N247CB · Cessna 421C · Trailing Edge Flap Control SystemSDR 96ZZZX5641Control Cable · frayedUPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED. ALSO NOTE THAT LOCATION OF DAMAGE AREAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL. BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERNAL VISUAL INSPECTIONNov 4, 1996 · N247CB · Cessna 421C · Trailing Edge Flap Control SystemSDR 96ZZZX5708Control Cable · wornALL FLAP SYSTEM CABLES WERE REMOVED AS A PRECAUTIONARY MEASURE FOR A VISUAL INSPECTION. BOTH FLAP EXTEND CABLES WERE FOUND TO HAVE A GREAT DEAL OF INTERNAL WEAR AT PULLEY LOCATIONS. SUBMITTER SUGGESTS LIFE LIMIT ON CABLES.Oct 30, 1996 · N782LC · Cessna 421C · Trailing Edge Flap Control SystemSDR 96ZZZX5707Control Cable · wornALL FLAP SYSTEM CABLES WERE REMOVED AS A PRECAUTIONARY MEASURE FOR A VISUAL INSPECTION. BOTH FLAP EXTEND CABLES WERE FOUND TO HAVE A GREAT DEAL OF INTERNAL WEAR AT PULLEY LOCATIONS. SUBMITTER SUGGESTS LIFE LIMIT ON CABLES.Oct 30, 1996 · N782LC · Cessna 421C · Trailing Edge Flap Control SystemSDR 96ZZZX5554Trunnion Assy · crackedINSP FOUND RT MLG TRUNNION ASSY UPPER BARREL CRACKED.Oct 23, 1996 · N148MA · Cessna 421C · Main Landing Gear Strut/Axle/TruckSDR EY2R9601637Piston Rod Assy · wornPISTON ROD ASSY WORNOct 1, 1996 · Cessna 421C · Propeller AssemblySDR EY2R9601636Piston Rod Assy · wornPISTON ROD ASSY WORNOct 1, 1996 · Cessna 421C · Propeller AssemblySDR EY2R9601119Hub · corrodedHUB FOUND CORRODED.Oct 1, 1996 · Cessna 421C · Propeller Hub SectionSDR EY2R9601118Rod · corrodedPISTON ROD ASSY FOUND WITH CORROSION.Oct 1, 1996 · Cessna 421C · Propeller Assembly
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