Textron 208

Service difficulty reports · 231

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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 = '208'
  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 CA011029006Actuator · corroded(CAN) WHILE PERFORMING AN ANNUAL INSPECTION ON THIS CESSNA CARAVAN THE ELEVATOR TRIM JACKS WAS NOTED TO HAVE SIGNIFICANT CORROSION ON SEVERAL OF THE PARTS. THE FOLLOWING PARTS REQUIRED REPLACEMENT HOUSING P/N 2661215-2/BEARINGS P/N 6361620-6 AND MS27641-66/PINSep 15, 2001 · Cessna 208 · Elevator Tab Control SystemSDR CA011029005Fitting · corroded(CAN) DURING AN ANNUAL INSPECTION PITTING WAS NOTED ON BOTH OF THE FORWARD AND BOTH OF THE AFT LANDING GEAR ATTACH FITTINGS. WHILE ATTEMPTING TO REMOVE THIS CORROSION THE DAMAGE WAS FOUND TO BE TOO SEVERE TO ATTEMPT. THE LANDING GEAR WAS REMOVED AND MORE CORRSep 15, 2001 · Cessna 208 · Fuselage, Landing Gear Attach FittingsSDR CA011029003Support · corroded(CAN) DURING AN ANNUAL INSPECTION, WHEN THE HORIZONTAL STABALIZER WAS REMOVED TO CARRY OUT A REPLACEMENT OF A SPAR CAP. CORROSION (PITTING) WAS NOTED IN ONE OF THE FORWARD SUPPORTS AND BOTH OF THE AFT SUPPORTS. NO DAMAGE IS ALLOWED TO CASTINGS OR FITTINGS. 3 OSep 15, 2001 · Cessna 208 · Horizontal Stabilizer StructureSDR 2001FA0000207Wire · chafedWIRES LF11 AND LF12 ARE ROUTED THROUGH THE VERTICAL STABILIZER WITHOUT PROTECTION OR SUPPORT. THESE WIRES POWER THE FLASHING RED BEACON MOUNTED ON THE TOP OF THE FIN. BOTH WIRES CHAFED AGAINST THE EDGE OF THE HOLE IN THE STABILIZER RIB THROUGH WHICH THEY WERAug 15, 2001 · Cessna 208 · Light System WiringSDR CA010703012Structure · loose(CAN) DURING INSPECTION FOUND THAT ATTACHMENT RIVETS AT RT SPOILER OUTBOARD ATTACHMENT ARM WERE LOOSE. RIVETS REPLACED 2ND A/C THAT PROBLEM WAS DISCOVERED ON.Jun 21, 2001 · Cessna 208 · Drag Control ActuatorSDR 2001FA0000087Counterweight · crackedDURING MAGNETIC PARTICLE INSPECTION, AN INDICATION WAS FOUND IN THE TRANSITION BETWEEN THE COUNTERWEIGHT ARM AND THE ATTACHMENT AREA, WHERE IT JOINS THE BLADE ROOT. THE CRACK APPEARS LIKE A HAIR LINE BUT STRONG INDICATION, ONCE IT WAS GROUND TO MAXIMUM DEPTH Feb 28, 2001 · Cessna 208 · Propeller AssemblySDR 20001012SH021Control Box · failedFIRE ALARM PUSH-TO-TEST FAILED TO ACTIVATE AUDIBLE HORN. DETERMINED THE FIRE DETECTION CONTROL BOX HAD FAILED. (X)Aug 18, 2000 · N1273E · Cessna 208 · Fire DetectionSDR 20000809SH028Pump · leakingEMERGENCY GEAR HAND PUMP SEEPING HYDRAULIC FLUID. DETERMINED METAL SHAVINGS PRODUCED DURING ACTUATOR PRODUCTION HAD LODGED UNDER AN O-RING. NO GALLING OR DAMAGE WAS FOUND INSIDE THE ACTUATOR. DEBRIS REMOVED AND NEW SEALS INSTALLED. (X)Jul 14, 2000 · N1273E · Cessna 208 · Hydraulic Handpump, MainSDR EY2R49550CBlade · corrodedBLADES HAVE EXFOLIATION, SENT TO MANUFACTURER FOR EVALUATION. BLADE S/N''''S KF043, KF044, KF046 REMOVED FROM SERVICE.Jun 26, 2000 · Cessna 208 · Propeller Blade SectionSDR PNSA0601Skin · damagedDURING LOADING OF AIRCRAFT, TRUCK BUMPED FUSELAGE JUST AFT OF CARGO DOOR. FLIGHT WAS DELAYED WHILE MAINTENANCE INSPECTED DAMAGE. FOUND MINOR SCRATCH. AIRCRAFT RELEASED FOR SERVICE.Jun 21, 2000 · N9304F · Cessna 208 · Fuselage Main, Plate/SkinSDR EY2R48568Hub · corrodedHUB CORRODED ON MOUNTING SURFACE BEYOND LIMITS. HUB RETIRED FROM SERVICE.Jun 13, 2000 · Cessna 208 · Propeller Hub SectionSDR AU000105Valve · failed(AUS) BLEED AIR SOLENOID VALVE OPEN CIRCUITED. MOVING PARTS CORRODED. SUSPECT MOISTURE INGRESS.Jan 11, 2000 · Cessna 208 · Engine Bleed Air SystemSDR CA991116006Control Cable · frayed(CAN) DURING DAILY INSPECTION, 4 WATER RUDDER CABLES WERE FOUND FRAYED. THE DAMAGE WAS ISOLATED TO THE AREA ABOVE THE SPREADER BAR WHERE THE CABLES TRANSITION TO THE AIRCRAFT FUSELAGE. SUBMITTER STATED THEY CONTACTED THE MANUFACTURER AND STATED A NUMBER OF ONov 2, 1999 · Cessna 208 · Rudder Control SystemSDR 99ZZZX3160Indicator · malfunctionedNOTED UPON INSTALLATION AND ENGINE LEAK/FUNCTIONAL TESTS, THAT OIL PRESSURE/TEMPERATURE INDICATOR WAS INDICATING 'LOW' PRESSURE (SYSTEM WAS BLED PRIOR TO TESTS). INSTALLED "CALIBRATED' DIRECT READING PRESSURE GAUGE FOR CONFIRMATION. ENGINE RUN-UP AND TEST COJul 20, 1999 · N248A · Cessna 208 · Engine Oil PressureSDR CA990125010Clevis · bent(CAN) RIGHT AFT RUDDER CONTROL CABLE SWAGED CLEVIS BENT AND BUCKLED. THIS HAD CAUSED CABLE STRAND SEPARATION AND FRAYING. FURTHER INSPECTION FOUND THE RIGHT CABLE CLAMP P/N 2613397-2 LOOSE ON THE CABLE, LEADING TO A NO-LOCK CONDITION ON THE RIGHT RUDDER CONJan 15, 1999 · Cessna 208 · Rudder Control SystemSDR AU981695Diaphragm · damaged(AUS) SMALL HOLES FOUND IN THE MOVING SECTION OF THE ENGINE BLEED VALVE DIAPHRAGM. PART TC: 247.Dec 26, 1998 · Cessna 208 · Compressor Bleed ValveSDR AU981344Diaphragm · damaged(AUS) ENGINE BLEED VALVE DIAPHRAGM SPLIT. PART TC: 1,622.Sep 30, 1998 · Cessna 208 · Compressor Bleed ValveSDR PNSA980802Igniter Box · inoperativeLOADED PASSENGERS, ENGINE WOULD NOT START. DEPLANED PAX. REPLACED IGNITER BOX, OPS CHECK OK.Aug 25, 1998 · N9481F · Cessna 208 · ExciterSDR 98ZZZX4271Actuator · corrodedNOTED DURING PHASE NR 1 'FLOAT' INSPECTION (SBL AAIP 50 HR), THE LT AND RT MAIN LANDING GEAR EXTEND/RETRACT ACTUATOR CYLINDER (OUTER HOUSING) INDICATED 'CELL CORROSION'. THIS CORROSION WAS NOTED AT THE MANUFACTURER'S ATTACH POINTS OF THE ELECTRICAL HARNESS (NAug 21, 1998 · N248A · Cessna 208 · Landing Gear ActuatorSDR 98ZZZX4270Actuator · corrodedNOTED DURING PHASE NR 1 'FLOAT' INSPECTION (SBL AAIP 50 HR), THE LT AND RT MAIN LANDING GEAR EXTEND/RETRACT ACTUATOR CYLINDER (OUTER HOUSING) INDICATED 'CELL CORROSION'. THIS CORROSION WAS NOTED AT THE MANUFACTURER'S ATTACH POINTS OF THE ELECTRICAL HARNESS (NAug 21, 1998 · N248A · Cessna 208 · Landing Gear ActuatorSDR 98ZZZX4540Wiper · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR 98ZZZX4539Insert · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR 98ZZZX4538Wiper Felt · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR 98ZZZX4537O-Rings · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR 98ZZZX4536Flange · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR 98ZZZX4535Ring · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR 98ZZZX4534Ram Assy · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR 98ZZZX4533End Cap · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR 98ZZZX4532Cylinder · corrodedWHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE. UPON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA. CHECKED RT SIDE AND FOUND AN IDENTICAL CONAug 19, 1998 · N248A · Cessna 208 · Landing Gear Retraction/Extension SystemSDR PNSA980103Gyro · failedATTITUDE GYRO VERY SLOW TO ERECT. REPLACED GYRO, OPS CHECK OK.Jan 7, 1998 · N9530F · Cessna 208 · Attitude Gyro and Indicating SystemSDR 97ZZZX5202Bearing · defectiveINSPECTION FOUND PROPELLER ASSEMBLY BEARING HAD SHARP INDICATIONS ON BOTH SIDES DIRECTLY ACROSS FROM EACH OTHER APPROXIMATELY .3750 INCH ON ONE SIDE AND .6250 INCH ON THE OTHER SIDE.Dec 1, 1997 · N5NPAN · Cessna 208 · Propeller AssemblySDR PNSA971004Engine · birdstrikeON SHORT FINAL, SUFFERED BIRD STRIKE TO ENGINE INLET AND PROP. LANDING UNEVENTFUL. AIRCRAFT INSPECTED AND RELEASED FOR SERVICE.Oct 23, 1997 · N9304F · Cessna 208 · Engine (Turbine/Turboprop)SDR PNSA971001Screws · looseAILERON JAMMED IN LEFT TURN PILOT WAS ABLE TO FREE-UP CONTROLS AND LAND SAFELY. FURTHER INVESTIGATION REVEALED SCREWS THAT ATTACH AILERON BALANCE WEIGHT TO LEADING EDGE OF AILERON HAD BACKED OUT TO THE POINT OF CATCHING THE TRAILING EDGE OF THE WING GAP FAIOct 18, 1997 · N9304F · Cessna 208 · AileronsSDR PNSA970813Generator · failedGENERATOR FAILED IN FLT. REPLACED GENERATOR, OPS CHECK OK.Aug 29, 1997 · N9530F · Cessna 208 · DC Generator-AlternatorSDR 97ZZZX3668Mount Ring · crackedENGINE MOUNT RING REPAIRED PER CESSNA MM, CHAPER 71-20-00, PAGE 801, APRIL, 1996. ROUGHLY 100 TO 200 HOURS AFTER REPAIR. (TIME IS UNSURE.) CRACK APPEARED ON THE OPPOSITE SIDE OF THE MOUNT RING FROM WHERE THE DOUBLER WAS INSTALLED.Aug 8, 1997 · Cessna 208 · Engine Mount SectionSDR 97ZZZX3667Mount Ring · crackedENGINE MOUNT RING REPAIRED PER CESSNA MM CHAPTER 71-21-00, PAGE 801, APRIL, 1996. ROUGHLY 100 HOURS AFTER INSTALLING DOUBLER PER MANUAL SPECIFICATIONS, THE OPPOSITE SIDE AT THE MOUNT CRACKED IN THE WELD.Aug 8, 1997 · Cessna 208 · Engine Mount SectionSDR CA970731022Press Switch · defective(CAN) DURING NORMAL OPERATIONS, THE GEAR ON THE AMPHIBIOUS FLOATS WAS EXTENDED AND THE CREW NOTED A LONGER THAN NORMAL EXTENSION PERIOD. MAINTENANCE FOUND THAT ONE PUMP ONLY WAS BEING UTILIZED DUE TO A FAULTY PRESSURE SWITCH.Jul 23, 1997 · Cessna 208 · Hydraulic Pressure SensorSDR 97ZZZX3412Blade · damagedPROPELLER DE-ICE BOOT BURNED OUT AND DAMAGED PROPELLER BLADE AT STA 24. SUBMITTER STATES A POSSIBLE CAUSE, ROCK NICK ON BOOT.Jul 17, 1997 · N192AV · Cessna 208 · Propeller Blade SectionSDR CA970527014Propeller · mis ohauled(CAN) PROPELLER RECEIVED FOR BENCH CHECK. NUMEROUS FAILURES FOUND INCLUDING: WRONG TYPE OF DE-ICER BOOT; BULKHEAD INSTALLED ON WRONG SIDE OF SLIP RING; LOW STOP COLLAR INSTALLED IN WRONG POSITION; LOW STOP COLLAR RUNOUT WAS GREATER THAN MAX ALLOWABLE; SLIP RINMay 21, 1997 · Cessna 208 · Propeller AssemblySDR AU970100Torque Tube · cracked(AUS) LH ELEVATOR ASSEMBLY TORQUE TUBE CRACKED LONGITUDINALLY THROUGH RIVET HOLE 60MM (2.36IN) FROM INBOARD END - CORROSION FOUND BETWEEN TUBE AND END FITTING WHICH CAUSED THE TUBE TO EXPAND AND CRACK - SUSPECT INADEQUATE TREATMENT DURING ASSEMBLY - AIRCRAFT OJan 22, 1997 · Cessna 208 · Elevator Control SystemSDR PNSA970103Fuel Control · malfunctionedWHEN POWER WAS APPLIED TO TAXI, ENGINE WOULD START TO ACCELERATE AND THEN RETURN TO IDLE.Jan 17, 1997 · N9316F · Cessna 208 · Fuel Controlling SystemSDR 97ZZZX569Indicator · malfunctionAIRCRAFT WAS FLYING AT 3,000 FEET, REPORTED TEMP OF 22 DEGREES FAHRENHEIT. AIRCRAFT DID NOT GET RIGHT MAIN LANDING GEAR DOWN AND LOCKED LIGHT. INVESTIGATION DETERMINED LANDING GEAR MAGNETIC POSITION INDICATOR WAS FROZEN. AFTER AIRCRAFT WARMED UP, INDICATOR Jan 17, 1997 · N208RD · Cessna 208 · Landing Gear Position and WarningSDR PNSA961206Gcu · malfunctionedENGINE WOULD NOT CRANK. REPLACED GCU, OPS CK OK.Dec 27, 1996 · N9602F · Cessna 208 · DC RegulatorSDR EY2R9601305Cylinder · corrodedCYLINDER CORRODED.Dec 1, 1996 · Cessna 208 · Propeller AssemblySDR EY2R9601304Screw · corrodedSCREW CORRODED.Dec 1, 1996 · Cessna 208 · Propeller AssemblySDR CA961216027Bolt · pitted(CAN) THE UPPER LEFT ATTACHMENT BOLT ON THE ENGINE MOUNT FOUND SEVERELY PITTED. THE BOLT WAS CORRODED THE COMPLETE LENGTH OF THE SHANK. NO CORROSION OF MOUNT. NO LUBE FOUND ON BOLTS WHEN REMOVED.Nov 25, 1996 · Cessna 208 · Engine Mount SectionSDR 97ZZZX154Propeller Assy · corrodedINSPECTION FOUND PROPELLER ASSY P/N D5010 CORRODED.Nov 5, 1996 · Cessna 208 · Propeller AssemblySDR 97ZZZX153Propeller Assy · corrodedINSPECTION FOUND PROPELLER ASSY P/N 35177 CORRODED.Nov 5, 1996 · Cessna 208 · Propeller AssemblySDR 97ZZZX138Prop Assy · corrodedINSPECTION FOUND PROPELLER ASSY P/N B5177 CORRODED.Nov 5, 1996 · Cessna 208 · Propeller AssemblySDR EY2R9601663Cylinder · defectivePROP ASSY CYLINDER PLATING BLISTEREDNov 1, 1996 · Cessna 208 · Propeller Assembly
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