Textron 208B

Service difficulty reports · 1,669

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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 = '208B'
  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 CA050311005Engine · unknown(CAN) DURING TAKEOFF AND CLIMB OUT PILOT REPORTED A CHANGE IN THE SOUND OF THE ENGINE. AIRCRAFT RETURNED. PILOT REPORTED ENGINE INDICATION NORMAL, NO ENGINE PERFORMANCE ABNORMALITIES. MAINTENANCE INSPECTED THE ENGINE OIL FILTER, NO FINDINGS, ENGINE WAS RUN WIMar 11, 2005 · Cessna 208B · Engine (Turbine/Turboprop)SDR 02021105Brake · unserviceableWHILE TAXIING OUT TO PERFORM A FLIGHT TEST REQUIRED FOR UNRELATED MAINTENANCE (STALL WARNING), THE PILOT EXPERIENCED A LOSS OF ABILITY TO STEER THE AIRCRAFT TO THE RT. UPON INSPECTION OF AIRCRAFT BY MAINTENANCE, THE RT MAIN BRAKE CALIPER WAS FOUND TO BE HANGIMar 11, 2005 · N963FE · Cessna 208B · Landing Gear Brake SystemSDR BSYA200500005Warning Light · illuminatedON ROUTE FROM OMA TO APA, ENGINE CHIP LIGHT CAME ON SHORTLY AFTER DEPARTURE, AIRCRAFT TRIED TO RETURN TO OMA WHEN THE ENGINE FAILED. AN EMERGENCY LANDING ON HIGHWAY. CAUSE UNKNOWN AT THIS TIME.Mar 4, 2005 · N3RY · Cessna 208B · Turbine Engine Oil SystemSDR CA050323004Engine · making metal(CAN) IN CRUISE THE ENGINE EXPERIENCED A POWER LOSS ACCOMPANIED BY A GEARBOX CHIP DETECTOR INDICATION. THE PILOT CARRIED OUT AN EMERGENCY LANDING ON A ROAD-WAY WHICH RESULTED IN DAMAGE TO THE AIRCRAFT. MFG WILL MONITOR THE INVESTIGATION OF THIS INCIDENT AND Mar 3, 2005 · Cessna 208B · Engine (Turbine/Turboprop)SDR CA050223004Nut · fractured(CAN) DURING CPCP AND SID INSPECTION, THE WING LOWER ATTACH STRUT BOLT AND NUT WERE REMOVED FOR INSPECTION AND THE NUT WAS FOUND FRACTURED THROUGH. THE COTTER KEY WILL HOLD THE NUT/BOLT IN PLACE. THE FRACTURE WAS LOCATED THRU THE MFG IDENTIFICATION STAMPS ON TFeb 23, 2005 · Cessna 208B · FastenersSDR PNSA050201Piston · dislodgedON LANDING AT KCG BRAKING WAS LOSS ON LT SIDE. AIRCRAFT ROLLED OUT NORMAL. MAINTENANCE FOUND TWO BRAKE PISTON SEALS ON LT BRAKE CALIPER HAD FAILED CAUSING A LOSS OF FLUID. CALIPER WAS REPLACED AND BRAKES BLED.Feb 21, 2005 · N9310F · Cessna 208B · Master Cylinder/Brake ValveSDR HYTA2005005Relief Valve · malfunctionedINSTRUMENT VACUUM SYSTEM HAD INSUFFICIENT SUCTION. ADJUSTING THE VACUUM REGULATOR HAD NO EFFECT. LOOKING THROUGH THE VACUUM EJECTOR OUTLET REVEALED A FOREIGN OBJECT RESTRICTING THE VENTURI. AN 8-32 NUT WAS RETRIEVED FROM THE VENTURI. THIS NUT CAME FROM INSFeb 18, 2005 · N900WA · Cessna 208B · Vacuum Distribution SystemSDR HSY2005F00003O-Ring · failed(MRR NR 01-020405) DURING DEPARTURE, PILOT NOTICED AN ENGINE POWER LOSS AND FLUCTUATION AND ABORTED THE TAKEOFF. AFTER REDUCING POWER, THE PILOT EXPERIENCED A STRONG FUEL SMELL IN THE COCKPIT. MAINTENANCE FOUND THAT THE NR 10 FUEL NOZZLE TRANSFER TUBE WAS LFeb 4, 2005 · N903FE · Cessna 208B · Engine Fuel DistributionSDR CA050201002Collar · cracked(CAN) DURING ROUTINE MAINTENANCE THE ENGINE MOUNT RING (HORSE COLLAR) WAS FOUND CRACKED AT 2 OF THE 4 CORNERS, INSIDE JOINT. DUE TO THIS BEING A KNOWN PROBLEM, AN ADDITIONAL TASK CARD TO CHECK FOR THIS CONDITION, INITIATED IN 1999, WAS ADDED TO OUR MAINTENANCFeb 1, 2005 · Cessna 208B · Engine Mount SectionSDR VLI2005F00000Spring · crackedPILOT REPORTED, NOSE GEAR COLLAPSED. DURING RUN-UP SPRING NOSE GEAR CRACKED. (SO21200503223)Jan 27, 2005 · N335VL · Cessna 208B · Nose/Tail Landing GearSDR 200501312Adc · malfunctionedPILOT REPORTS 6000 FT, ALTITUDE REPORTING ERROR AT SEA LEVEL. AIR DATA COMPUTER INSTALLED AS PART OF THE CHELTON FLIGHT SYSTEM EFIS-SV SYSTEM UNDER STC NR SA02203AK.Jan 24, 2005 · N332AK · Cessna 208B · Air Data ComputerSDR RNV2005F00001Shaft · shearedWHILE ENROUTE, THE PILOT EXPERIENCED A FAILURE OF THE STANDARD ELECTRICAL POWER SYSTEM FOLLOWED BY FLUCTUATING AND DECREASING OIL PRESSURE. THE PILOT LANDED WITHOUT INCIDENT. MAINTENANCE PERSONNEL FOUND THAT THE AFT END OF THE ACCESSORY DRIVE OF THE ACCESSORJan 20, 2005 · N305PW · Cessna 208B · Turbine Engine Oil SystemSDR RNV2005F00000Drive Shaft · shearedACCESSORY DRIVE SHAFT ON THE EXTERNAL SCAVANGE PUMP SHEARED, RESULTING IN A LOSS OF OIL PRESSURE. PILOT DIVERTED THE FLIGHT. AIRCRAFT COMPONENTS OR SYSTEMS THAT RESULT IN TAKING EMERGENCY ACTIONS DURING FLIGHT (EXCEPT ACTION TO SHUTDOWN AN ENGINE).Jan 19, 2005 · N305PW · Cessna 208B · Turbine Engine Oil SystemSDR CA050120012Actuator · worn(CAN) FLAP ACTUATOR MAKING NOISE DURING FLAP OPERATION. PRIMARY FLAP MOTOR LOADING THROUGH PARTIAL TRAVEL OF FLAPS. SECONARDY FLAP SYSTEM WOULD NOT EXTEND OR RETRACED FLAPS BUT MOTOR STILL RUNNING. FLAP ACTUATOR/MOTOR ASSEMBLY REMOVED AND UPON INSPECTION FOJan 18, 2005 · Cessna 208B · Trailing Edge Flap ActuatorSDR HYTA2M5004Strut · debondedTUBE OF NOSE GEAR STRUT TUBE ASSY PN 26430161, CAME LOOSE FROM UPPER END CAP ALLOWING TUBE TO FLOAT WITH NOSE GEAR STRUT MOVEMENT. VENT TUBE INSIDE STRUT TUBE WAS CRUSHED AND SHOVED TO UPPER END OF TUBE. EXAMINATION OF TUBE AND END CAP REVEALED THAT END CAP Dec 23, 2004 · N32WA · Cessna 208B · Main Landing Gear Strut/Axle/TruckSDR HYTA2005003Seal · looseFELT SEALING STRIP APPROXIMATELY .5 INCH X 7 INCHES WAS COMING LOOSE FROM INSIDE THE ENGINE INDUCTION AIR PLENUM. OFFENDING FELT STRIP WAS REMOVED AS IT SERVES NO PURPOSE. THIS STRIP WAS LOCATED AT ABOUT 4 O’CLOCK ON THE INSIDE SURFACE ACROSS THE RT END OF TNov 19, 2004 · N976E · Cessna 208B · Turbine Engine Air Inlet SectionSDR HYTA2005002Spring · chafedSHOT PEENED LOWER SURFACE OF MAIN GEAR CENTER SPRING IS BEING DAMAGED BY CONTACT WITH RIVETS AND SCREWS PROTRUDING FROM THE MLG COVER WHICH IS LOCATED BENEATH THE CENTER SPRING. THIS IS THE THIRD AIRCRAFT FOUND IN THIS CONDITION.Oct 29, 2004 · N900WA · Cessna 208B · Main Landing Gear Strut/Axle/TruckSDR 2005FA0000440Adc · malfunctionedNR 2 ADC UNIT REPORTING 350 FEET ERROR. UNIT INSTALLED AS PART OF THE FLIGHT SYSTEMS, INC EFIS-SV SYSTEM UNDER STC NR SA02203AK. (AL05200500174) (K)Oct 28, 2004 · N331AK · Cessna 208B · Air Data ComputerSDR COE2004F00002Relay · burnedENROUTE, PILOT REPORTED THE STANDBY ELECTRIC POWER (ON) AND (INOP) ANNUNCIATOR LIGHTS ILLUMINATED. STANDBY POWER SYSTEM WAS INOPERATIVE. PILOT REPORTED SMELLING SMOKE. NO EMERGENCY WAS DECLARED, HOWEVER, THE EMERGENCY EQUIPMENT RESPONDED. AIRCRAFT LANDED Oct 23, 2004 · N705FX · Cessna 208B · AC Generation SystemSDR CA041103006Fuel Control · failed(CAN) ON ENGINE START UP PRIOR TO DEPARTURE THE ENGINE NG STOPPED ACCELERATING AT 48 PERCENT AND THERE WAS NO RESPONSE TO POWER LEVER MOVEMENT. THE ENGINE RESPONDED TO THE SELECTION OF HIGH IDLE AND THEN IDLED AT THE CORRECT NG OF 52 PERCENT. POWER LEVER RESPOOct 20, 2004 · Cessna 208B · Fuel Control/Turbine EnginesSDR HYTA2005001Spring · chafedFLEXING OF MLG SPRING CAUSES CENTER SPRING TO CONTACT MLG COVER PN 2611103-10 WHICH IS LOCATED BENEATH THE CENTER SPRING. TWO RIVETS HAD WORN INTO THE CENTER SPRING LOWER SURFACE. THESE RIVETS ARE THE CENTER IB RIVETS THAT FASTEN A FAIRING AT EACH END OF THEOct 20, 2004 · N540ME · Cessna 208B · Main Landing GearSDR CA041019003Mount · chafed(CAN) AT ENGINE REPLACEMENT, THE CLAMP WAS FOUND TO BE LOOSE AROUND THE ENGINE MOUNT TUBING. THE CLAMP HAD CHAFFED INTO THE TUBE SIGNIFICANTLY. THE MOUNT WAS REMOVED AND SENT FOR REPAIR IAW THE SRM FOR THE C208B. THE CLAMP AND HARDWARE WAS REPLACED AND SECUREDOct 7, 2004 · Cessna 208B · Engine Mount SectionSDR 4024Odor · detectedAIRCRAFT WAS IN CRUISE, PILOT THOUGHT HE SAW AND SMELLED SMOKE, ARM REST FELT WARM, LANDED A/C SAFELY. AIRCRAFT WAS INSPECTED, NO PROBLEM COULD BE FOUND, TEST FLEW A/C ALL SYSTEMS NORMAL, COULD NOT DUPLICATE PROBLEM.Sep 23, 2004 · N103AN · Cessna 208B · Air Distribution SystemSDR CA040818008Segment · shifted(CAN) WHILE INCREASING POWER FOR CLIMB, THE PILOT NOTICED AN ITT OVERTEMP INDICATION. AIRCRAFT RETURNED TO AIRPORT UNDER REDUCED POWER TO REMAIN BELOW MAXIMUM CONTINUOUS ITT. MAINTENANCE SPLIT THE ENGINE AND FOUND THAT A SHROUD SEGMENT HAD SHIFTED AND CONTACTEAug 12, 2004 · Cessna 208B · Turbine Engine Compressor SectionSDR 4018Warning Light · false activationON TAKEOFF OUT OF BTR HAD ENGINE FIRE DETECT LIGHT COME ON, ABORTED TAKEOFF. MAINT CHECKED FOR BLEED AIR LEAKS, CHECKED FIRE LOOP FOR RUBBING NO DEFECTS NOTED, RAN AIRCRAFT AT FULL POWER COULD NOT DUPLICATE FIRE LIGHT.Aug 4, 2004 · N108AN · Cessna 208B · Fire DetectionSDR HYTA2004007Spar · chafedLOWER SURFACE OF LT AND RT FORWARD WING SPARS AND LIFT STRUT ATTACH FITTINGS HAVE BEEN CHAFED BECAUSE OF CONTACT WITH THE LIFT STRUT UPPER FAIRING/COVER. WORST DAMAGE WAS LESS THEN .005 INCH IN DEPTH AND WAS EASILY BLENDED OUT. APPLIED VINYL CHAFE TAPE TO SPAug 2, 2004 · N976E · Cessna 208B · Wing SparSDR CA040810005Shimmy Dampener · broken(CAN) SHIMMY DAMPENER BARREL END ENTIRELY BROKE OFF AT CIRCLIP GROOVE. ALL FLUID LOST,CIRCLIP MISSING, BROKEN PIECE MISSING. NO EVIDENCE OF PRIOR OVERSTEER.Jul 19, 2004 · Cessna 208B · Shimmy DamperSDR 2004F00320Fire Loop · looseENGINE FIRE LIGHT AND HORN CAME ON IN LEVEL FLIGHT. INDICATIONS CEASED ON APPROACH TO LANDING. ALL OTHR INDICATIONS NORMAL. PILOT DECLARED AN EMERGENCY. AIRCAFT LANDED WITHOUT INCIDENT. PILOT NOTED THAT NO FIRE EXISTED AND IT WAS A FALSE INDICATION. MECHJul 14, 2004 · N880FE · Cessna 208B · Fire DetectionSDR 2004F00279Adc · faultyUNIT WAS REPORTING 400 PLUS FEET OFF FROM ACTUAL. PROGRESSIVE REPORTING ERROR OVER ONE MONTH TIME FRAME. (M)Jul 9, 2004 · N331AK · Cessna 208B · Altimeter, Barometric/EncoderSDR 761003Support · damagedNLG DRAG LINK SUPPORT DAMAGED. (K)Jul 8, 2004 · N748FX · Cessna 208B · Main Landing Gear Attach SectionSDR PNSA040604Hub · damagedSLUGGISH RESPONSE TO TAKEOFF POWER AND RPM/TORQUE DROPPED OFF AT FLIGHT IDLE POWER SETTINGS. AIRCRAFT MADE NORMAL LANDING WITH POWER LEVER FURTHER FORWARD THAN NORMAL. MAINTENANCE FOUND PROPELLER BLADE ANGLE IN HUB 2 DEGREES OFF AND BETA RING BENT. AT TEARDOWJun 28, 2004 · N9820F · Cessna 208B · Propeller Hub SectionSDR CA040614004Bellcrank · mismanufactured(CAN) DURING COMPLETION OF MFG BULLETIN CAB03-4 ONE WELD WAS FOUND TO BE MISSING. THE MISSING WELD WAS ON THE LOWER ARM INNER SURFACE DESCRIBED AS ITEM 6 IN FIGURE 1 OF CAB03-4. ALL OTHER WELDS WERE PRESENT AND THE BELLCRANK SHOWED NO OBVIOUS DAMAGE OR DISTOJun 10, 2004 · Cessna 208B · AileronsSDR FXT2004F00000Vane · wornCT-VANE SEGMENTS SLIPPED AND RUBBED INTO THE CT-DISK, CAUSING ABNORMALLY HOT OPERATION OF THE ENGINE. A NEW HOT SECTION WAS IN STALLED AND THE PROBLEM WAS FIXED ALL OPERATING TEMPERATURES WERE NORMAL. THE FIRST TIME THIS HAPPENED WAS IN NOV OF 2003. AT THATJun 8, 2004 · N1263Y · Cessna 208B · Turbine SectionSDR UNI2004F00000Flap Track · corrodedUPON PERFORMANCE OF INSPECTION OPERATION MD OF MFG MM, SEVERE EXFOLIATION, CORROSION WAS FOUND ON BOTH OB FLAP TRACKS. AREAS ON FLAP TRACK WHERE CORROSION WAS DISCOVERED INCLUDE: AFT RECESSED WEB AREA AND ADJACENT UPPER AND LOWER PORTIONS OF TRACK. CONTRIBUMay 17, 2004 · N127HA · Cessna 208B · Trailing Edge FlapsSDR HSY2004F00000Transmitter · malfunctionedUPON REMOVAL OF RT WING NR 3 OB FUEL TRANSMITTER, PART WAS FOUND MISSING THE ROLL PIN THAT SECURES THE FLOAT ARM TO THE TRANSMITTER ASSY. FUEL TRANSMITTER INSPECTION WAS PERFORMED ON 2/19/04. THE SERIAL NR OF THIS TRANSMITTER WAS NOT APPLICABLE TO THE SERIALApr 30, 2004 · N730FX · Cessna 208B · Fuel Quantity IndicatorSDR AUS20040377Support · cracked(AUS) FLAP ACTUATOR SUPPORT ASSEMBLY CRACKED.Apr 24, 2004 · Cessna 208B · Fuselage Main, Attach FittingsSDR HYTA2004006Longeron · crackedLT LONGERON 261310531 AND RT LONGERON 261310528 WERE FOUND CRACKED AT THE LOWER AFTER CORNERS OF THE CUT-OUTS FOR THE CONTROL COLUMN TORQUE TUBE. THESE CUT-OUTS ARE LOCATED JUST FORWARD OF THE NOSE GEAR SPRING SUPPORT FITTINGS 26430633. RT LONGERON HAS ONE CApr 23, 2004 · N4365U · Cessna 208B · Fuselage Main, Longeron/StringerSDR 2004FA0000560Latch · inoperativeCARGO DOOR OPENED IN FLIGHT. INSPECTED DOOR AND ADT LATCH.Apr 15, 2004 · N303PW · Cessna 208B · Cargo/Baggage DoorsSDR CA040413011Pump · failed(CAN) DURING ROUTINE INSPECTION ALUMINUM PARTICLES WERE FOUND IN THE AIRFRAME FUEL FILTER DOWNSTREAM OF THE FUEL BOOST PUMP. RUNNING THE BOOST PUMP SHOWED THAT WHILE IT MAINTAINED OPERATING PRESSURE AN INTERMITTENT GRINDING NOISE COULD BE HEARD. DISSASEMBLY OApr 9, 2004 · Cessna 208B · Engine Fuel DistributionSDR CA040414001Retaining Ring · collapsed(CAN) THE HOT SECTION WAS DISMANTLED FOR A SCHEDULED CT DISK REPLACEMENT. CT SHROUD SEGMENTS HAD SHIFTED AXIALLY. THE RETAINING RING HAD COME OUT OF THE GROOVE. THIS PROBLEM HAS BEEN DOCUMENTED ON OTHER ENGINES. MFG HAS ISSUED P/N 3110741-02 RETAINING RINGApr 1, 2004 · Cessna 208B · Turbine Engine Compressor SectionSDR 2004F00169Warning Light · interferenceENGINE FIRE LIGHT BLINKED ON TWICE FOR ONE SECOND AND EACH TIME THAT HAPPENED THE HORN CHIRPED. PILOT RETURNED TO MFR WITHOUT INCIDENT. NO EMERGENCY WAS DECLARED. AIRCRAFT WAS INSPECTED WITH NO DEFECTS FOUND. FIRE WARNING SYSTEM TESTED GOOD. AIRCRAFT WAS Mar 26, 2004 · N880FE · Cessna 208B · Fire DetectionSDR HYTA2004005Spring · wornFLEXING OF MLG CENTER SPRING PN 2641014-3 CAUSES CENTER SPRING TO CONTACT MLG COVER PN 2611103-10 WHICH IS LOCATED BENEATH THE CENTER SPRING. CHAFING HAD WORN THROUGH THE PAINT ON THE LOWER SURFACE OF CENTER SPRING. TWO RIVETS HAD WORN INTO THE LOWER SURFACEMar 17, 2004 · N4365U · Cessna 208B · Main Landing GearSDR HYTA2004004Wire · misroutedFLASHING BEACON WIRE IN TAILCONE WAS ROUTED OVER THE BALLAST RESISTOR WHERE THERE IS LESS THAN .5 INCH CLEARANCE TO STRUCTURE. WIRE WAS NOT TOUCHING BALLAST RESISTOR OR AIRPLANE STRUCTURE, BUT INSULATION WAS BURNED CLEAR THROUGH TO BARE WIRE. WIRE SHOULD HAVMar 17, 2004 · N4365U · Cessna 208B · Light System WiringSDR HYTA2004003Bolt · corrodedWHILE CONDUCTING INITIAL INSPECTION, BOTH AFT WING TO FUSELAGE ATTACH BOLTS WERE FOUND SLIGHTLY RUSTED. DAMAGE WAS NEGLIGIBLE. THESE BOLTS AS WELL AS FORWARD ATTACH BOLTS AND UPPER AND LOWER STRUT ATTACH BOLTS WERE APPARENTLY INSTALLED DRY. THIS HARDWARE SHMar 17, 2004 · N4365U · Cessna 208B · FastenersSDR CA040217003Relay · burned(CAN) DURING TROUBLESHOOTING OF THE WINDSHIELD HEAT AUTO FUNCTION, THE AUTO RELAY WAS FOUND TO BE INTERNALLY SHORTED AND HAD MELTED THE CLEAR CASE. THE RELAY WAS REPLACED AND THE AIRCRAFT RELEASED.Feb 17, 2004 · Cessna 208B · Windshield/Door Rain/Ice RemovalSDR CA040217001Mount · cracked(CAN) DURING ROUTINE MAINTENANCE THE ENGINE MOUNT RING (HORSE COLLAR) WAS FOUND CRACKED AT TWO OF THE FOUR CORNERS, INSIDE JOINT. DUE TO THIS BEING A KNOWN PROBLEM, AN ADDITIONAL TASK CARD TO CHECK FOR THIS CONDITION, INITIATED IN 1999, WAS ADDED TO OUR MAINTFeb 17, 2004 · Cessna 208B · Engine Mount SectionSDR CA040210005Hinge · torn(CAN) ON SHORT FINAL THE PILOT HEARD A LOUD BANG AT THE BEGINNING OF THE FLARE. THE PILOT TAXIED THE AIRCRAFT TO THE CARGO RAMP. AFTER THE PILOT GOT OUT OF THE COCKPIT HE NOTICED THAT THE FWD LOWER POD CARGO DOOR WAS MISSING. THE CARGO DOOR WAS FOUND ON TOP OFFeb 10, 2004 · Cessna 208B · Cargo/Baggage DoorsSDR CA040210003Ring · cracked(CAN) DURING ROUTINE MAINTENANCE THE ENGINE MOUNT RING (HORSE COLLAR) WAS FOUND CRACKED AT TWO OF THE FOUR CORNERS, INSIDE JOINT. DUE TO THIS BEING A KNOWN PROBLEM, AN ADDITIONAL TASK CARD TO CHECK FOR THIS CONDITION, INITIATED IN 1999, WAS ADDED TO OUR MAINTEFeb 8, 2004 · Cessna 208B · Engine Mount SectionSDR EPUA300104ASupport · crackedPILOT REPORTED WHEN RETRACTING FLAPS ON ROLL-OUT THE FLAP CIRCUIT BREAKER TRIPPED. MX INSPECTED AND FOUND THE FLAP TRANSMISSION SUPPORT ASSY. CRACKED AND BUCKLED. THERE WAS NO EVIDENCE OF THE STANDBY FLAP SYSTEM BEING ACTIVATED.Jan 30, 2004 · N407GV · Cessna 208B · Fuselage Main, Attach FittingsSDR CA040130003Retainer · collapsed(CAN) THE HOT SECTION WAS GIVEN A SCHEDULED HOT SECTION INSPECTION. FOUR CT SHROUD SEGMENTS HAD SHIFTED SLIGHTLY. THE RETAINING RING HAD COME OUT OF THE GROOVE. THIS PROBLEM HAS BEEN DOCUMENTED ON OTHER ENGINES. PWA HAS ISSUED P/N 3110741-02 RETAINING RING ON Jan 26, 2004 · Cessna 208B · Engine (Turbine/Turboprop)
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