Textron 208B
Service difficulty reports · 1,669
Newest first. General aviation reporting is voluntary.
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.
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
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 CA010831007Bolt · damaged(CAN) ON ENGINE REMOVAL, MAINTENACE FOUND ENGINE MOUNT BOLT PART NO. NAS 148A94 (S3461-64) AT LEFT, LOWER ENGINE MOUNT BRACKET. (ITEM 27)- THREADBOUND DUE TO WASHER PART NO. MS20002C8 NOT INSTALLED AT FACTORY ASSEMBLY. MAINTENACE ALSO FOUND INCORRECT WASHERS PSDR CA010726025Relay · unserviceable(CAN) HSI LT/RT DEVIATION REAMINS CENTERED WHEN GPS IS SELECTED WITH NO FAILURE WARNING/INDICATION GPS LAMP REMAINED ON, GPS & TO FROM FLAGS REMAINED VALID). RELAY K2 IN AVIONICS J-BOX #1 FAILED TO ENERGIZE WHEN GPS WAS SELECTED. REPLACED K2. NOTE: TC ENGINEERSDR CA010907020Roll Pin · bent(CAN) IT APPEARS SOMEONE TRIED TO UNLATCH THE UPPER CARGO DOOR WITHOUT PUSHING (ITEM #41) RELEASE KNOB TO RELEASE THE INNER HANDLE FROM THE LOCK PLATE (ITEM #46) EXCESSIVE FORCE WAS APPLIED THUS DAMAGING MECHANISM (ROLL PIN ITEM #2), WITH THIS CONDITION, IF THSDR S8A2001F00000Pin · missingUPON INITIAL 200 HOUR INSPECTION SINCE NEW, AC, FOUND LEFT LOWER LIFT STRUT MISSING THE COTTER PIN THAT SAFETIES THE NUT AND BOLT SECURING THE LIFT STRUT TO THE FUSELAGE. MAINTENANCE MANUAL SPECIFIES SNUG TIGHT THEN ADVANCE TO PIN ALIGNMENT AND SAFETY. THE WSDR CA010625037Washer · broken(CAN) DURING INSPECTION, MAINTENANCE FOUND THE PIN SECURING THE MAIN LANDING GEAR SPRING (LEG) HAD MOVED AFT APPROXIMATELY 3/4 OF AN INCH.MAINTENANCE CONCLUDED WASHER (ITEM 28-FORWARD) WAS DISHED AND FRACTUR ED DUE TO OVERTORQUING OF BOLT (ITEM 30) AND NUT.T HSDR 20010508CW012Line · mismarkedWITHIN THE LEFT WING BEHIND PANEL 603BB THE PITOT AND THE STATIC LINES WERE MISLABELED. THE STATIC LINE WAS MARKED PITOT AND THE PITOT LINE WAS MARKED STATIC FROM THE FACTORY.SDR 20010508CW002Bracket · brokenPRIMARY FLAP MOTOR DRIVE COUPLER FAILED. STAND BY SYSTEM USED TO EXTEND FLAPS. FLAP LIMIT SWITCHES NOT INCORPORATED IN STAND BY SYSTEM. OPERATIONAL SWITCH OF STAD BY SYSTEM HELD TOO LONG AND FLAP MOTOR CONTINUED TO RUN PAST LIMIT SWITCH LOCATION AND TWISTEDSDR CA010529014Bracket · missing(CAN) DURING INSPECTION THE GUIDE PIN/BRACKET ASSEMBLY WHICH IS USED TO KEEP THE CARBON BLOCK IN THE BETA RING WAS FOUND MISSING. WITH ENOUGH PLAY IN THE SYSTEM THIS MIGHT ALLOW THE BLOCK TO COME OUT OF THE RING. THIS WOULD AFFECT PROPELLER OPERATION IN THE BESDR CA010510004Connector · cracked(CAN) THIS CONNECTOR HAS BEEN FOUND TO BE EASILY DAMAGED WHEN IT IS REQUIRED TO REMOVE OR INSERT A CONTACT IN IT. NEW REPLACEMENT PARTS OFTEN ARRIVE DAMAGED AS WELL. WHILE NOT A PROBLEM IN TYPICAL OPERATION IT DOES ALLOW FOR THE POSSIBILITY AT THE TERMINAL BEISDR 2001F00274Controller · defectiveFLT 7769 - GTF - PILOT REPORTED 'ENGINE FIRE LIGHT CAME ON DIMLY IN FLIGHT'. NO AURAL WARNING, ONLY PARTIAL DIM LIGHT INDICATION. INTERNAL MALFUNCTION OF THE FIRE DETECTION CONTROLLER. REMOVED AND REPLACED THE FIRE DETECTION CONTROLLER. PERFORMED FUNCTIONASDR 20010411CW004Counterweight · damagedAIRCRAFT ENCOUNTERED SEVERE VIBRATION ON CLIMB OUT. REQUESTED TO RETURN TO AIRPORT AND LANDED WITHOUT COMPLICATIONS. INSPECTION OF VIBRATION FOUND THAT THE COUNTERWEIGHT FROM NR 2 PROP BLADE HAD COME LOOSE. INSPECTION SHOWED BOLT THAT HOLDS COUNTERWEIGHT HASDR H1IR069Y01Vane · crackedCOMPRESSOR TURBINE VANE RING OUTER RING ANTI ROTATION LUGS ARE CRACKED OR SEPARATED BEYOND THE MAXIMUM REPAIRABLE LIMIT OF SEVEN. 11 LUGS SEPARATED AND 1 EA CRACKED FROM A TOTAL OF 14. EXPERIENCE INDICATES NORMAL AS REMOVED VANE RINGS WITH THIS TOTAL TIME SHSDR CA010222016Roll Pin · broken(CAN) DURING THE ROUTINE 100 HOUR INSPECTION THE AIRCRAFT ENGINEER FOUND THAT THE ROLL PINS, QUANTITY 4, SECURING THE BELL CRANK TO THE AIR BYPASS DUCT FOR THE ENGINE, WERE LOOSE. UPON RMEOVAL WE FOUND THAT ALL FOUR PINS WERE BROKEN. PIN REPLACED WITH NEW.SDR CA010222015Transmission · failed(CAN) AFTER LANDING THE PILOTS SELECTED FLAPS TO THE UP POSITION AND THE FLAP CIRCUIT BREAKER POPPED. THE FLAP CIRCUIT BREAKER WAS RESET AND THE FLAPS WERE SELECTED UP NORMALLY. WHEN THE FLAPS WERE RESELECTED TO THE DOWN POSITION THE CIRCUIT BREAKER POPPED AGASDR 20010222AP003Light · misinstalledLEFT WING POSITION/STROBE LIGHT ASSY INSTALLED INCORRECTLY(BACKWARDS). RED LIGHT FACING AFT AND STROBE FACING FOWARD. LIGHT ASSY CAN BE INSTALLED INCORRECTLY AT FACTORY OR BY MECHANIC IN THE FIELD.SDR 20010222AP002Light · misinstalledRIGHT WING POSITION/STROBE LIGHT INSTALLED INCORRECTLY(BACKWARDS). GREEN LIGHT FACING AFT AND STROBE FACING FOWARD. LIGHT ASSY CAN BE INSTALLED INCORRECTLY AT FACTORY OR BY MECHANIC IN THE FIELD.SDR 20010222AP001Light · misinstalledLEFT WING POSITION LIGHT/STROBE ASSY INSTALLED INCORRECTLY(BACKWARDS). RED LIGHT FACING AFT AND STROBE FACING FOWARD. ASSY CAN BE INSTALLED INCORRECTLY AT FACTORY OR BY MECHANIC IN THE FIELD.SDR 20010326CW002Resistor · burnedFOUND PROP DEICE VARIABLE RESISTOR BADLY BURNED AT CONNECTOR. REPLACEMENT OF VARISTOR CALLED FOR WITH NEW PN2670069-9 WHICH USES SPLICES INSTEAD OF PUSH ON CONNECTORS.SDR CA010322008Brushes · worn(CAN) OUR STANDBY ELECTRICAL POWER INOP LIGHT WAS FADING IN AND OUT AT APPROX 65 - 67 PERCENT NG. THE RESISTOR WAS CHECKED OUT AT 110 OHMS AND THEN THE FIELD BRUSHES WERE CHECKED - FOUND THAT TO BE WORN PAST THE POINT OF MAKING CONTACT WITH THE SLIP RINGS. NEWSDR 20001205SH002Liner · looseNOSE GEAR SPRING SUPPORT LINER BACKED OUT APPROX .750 INCH AFT OUT OF SUPPORT ASSY. LINER WAS STOPPED BY CONTACT WITH CARGO POD. (X)SDR CA001218012Wire · chafed(CAN) ARCING OF CHAFED WIRES WAS DISCOVERED BEHIND THE LT PANEL FORWARD OF THE MAIN CCT BREAKER PANEL (P/N 2613181-18). THE WIRE BUNDLE WAS RUBBING AGAINST THE PRIMARY STRUCTURE BEAM WHICH RUNS BETWEEN THE FIREWALL AND THE DOOR SILL ON A 45 DEGREE ANGLE. THE WSDR CA001206013Support Bracket · cracked(CAN) PILOT REPORTED CIRCUIT BREAKER TRIPPED DURING FLAP SELECTION. MAINTENANCE FOUND FLAP MOTOR AND ACTUATOR MOUNTING STRUCTURE BENT AND CRACKED. REPLACED SUPPORT ASSEMBLY 2611144-1 AND FLAP MOTOR/ACTUATOR ASSY 9910586-3. NEW PARTS RIGGED, FLAPS AND TESTEDSDR 20001109SH038Skin · corrodedHNL - MAINTENANCE FOUND FUSELAGE SKIN PANEL, UPPER CENTER FORWARD, CORRODED. PANEL CORRODED BEYOND LIMITS FOR 2024T3, .032 INCH THICK. REMOVED AND REPLACED PANEL ASSEMBLY IAW C208 SRM 53-10-10 AND SRM 51-40-00. (X)SDR CA010110015Connector · melted(CAN) THE CONNECTOR WAS FOUND BURNED/MELTED WHILE COMPLYING WITH SB CAB00-11.SDR 20001026SH013Fuel Line · chafedBOLT HOLDING SEAL TO LONGERON HAD THE END RUBBING AGAINST THE FUEL LINE THAT FEEDS THE RESERVOIR. (X)SDR 20010502CW006O-Ring · wornPILOT REPORTED LOST RIGHT BRAKE AFTER LEAVING BLOCKS. PILOT SIDE, RIGHT BRAKE MASTER CYLINDER ORING LEAKING/BYPASSING HYDRAULIC FLUID. RIGHT BRAKE PISTO O-RINGS LEAKING. REPLACE O-RING SEAL IN THE PILOTS SIDE RIGHT BRAKE MASTER CYLINDER. REPLACED THE O-RISDR 20001108SH038Pin · shearedTHE ROLL PIN THAT HOLDS THE LOCK MECHANISM FOR THE CARGO TIE-DOWN FITTING, PN 22555-71, SHEARED CAUSING THE CARGO STRAP TO COME LOOSE AND THE LOAD TO SHIFT. THE LOAD SHIFT CAUSED THE AIRCRAFT IN QUESTION TO FALL ONTO THE TAIL TIE-DOWN AFTER THE ENGINE WAS SHUSDR CA000829024Bolt · sheared(CAN) ON LANDING THE PILOT APPLIED BRAKES AND FELT SHUDDERING. REVERSE PITCH WAS MOSTLY USED TO BRING THE AIRCRAFT TO A STOP. THE LEFT HAND BRAKE CALIPER WAS FOUND TO BE COMPLETELY DETACHED FROM THE AIRCRAFT.THE PILOT FOUND THE BRAKE ON THE RUNWAY, RETURNING ISDR 20000914SH004Fitting · leakingAIRCRAFT ARRIVED WITH OIL LEAK. ACFT LOST 1/2 QUART OF OIL DURING A 3.5 HOUR FLIGHT. T/S REVEALED OIL LEAKING FROM THE TOP OF THE TORQUE LINE ADAPTER, PN 5950034-7, MOUNTED AT THE FRONT OF THE ENG. INSP REVEALED FITTING, PN 5950034-7, HAD DRILLED TO ALLOW ASDR 20001012SH023Angle · crackedFORWARD ANGLE ON LEFT NOSE CAP FOR INDUCTION AIR PLENUM ATTACHMENT CRACKED. (X)SDR PNSA0804Fuel Control · failedDURING CRUISE, ENGINE WENT TO MAX POWER AND WAS UNCONTROLLABLE. ENGINE WOULD NOT RESPOND TO POWER LEVER OR EMERGENCY POWER LEVER. ENGINE WAS CONTINUOUSLY OVER TORQUE AND OVER TEMP LIMITS FOR 7 MINUTES. AIRCRAFT WAS FLOWN TO NEAREST AIRPORT BY CYCLING THE PRSDR CA000808009Selector Valve · leaking(CAN) IN FLIGHT PILOT NOTICED A DISCREPANCY BETWEEN COPILOT AND PILOT AIR SPEED AND ALTIMETER. PILOT RETURNED TO MAINTENANCE BASE AND FOUND BODY OF SELECTOR VALVE SPARATED FROM DASH MOUNT PLATE CAUSING LARGE STATIC LEAK. VALVE WAS REMOVED, REASSEMBLED USING ORSDR CA000824032Line · worn(CAN) BLEED AIR LINE LOCATED AT THE FRONT OF THE FIREWALL FOUND TO BE WORN, BY STARTER GENERATOR COOLING DUCT. LINE WAS REPLACED. BOTH OTHER COMPANY 208S WERE INSPECTED, ONE WAS FOUND TO HAVE CONTACT IN THE SAME AREA. DUCT WAS SECURED AWAY FROM THE BLEED AIR SDR 20001012SH022Angle · crackedFORWARD ANGLE ON LEFT NOSE CAP FOR INDUCTION AIR PLENUM ATTACHMENT CRACKED. (X)SDR CA000712017Bolt · sheared(CAN) WHILE CARRYING REGULAR MAINT ON A/C, NOTICED ONE NUT WAS MISSING FROM WHEEL HUB BOLTS. UPON FURTHER INVESTIGATION, FOUND THAT BOLT HAD SHEARED AND NUT HAD FALLEN OFF, AT WHICH POINT, BOLT BACKED OUT OF HUB AND HIT BRAKE TORQUE PLATE, BENDING BOLT AND SCSDR 20000714SH033Switch · shortedPILOT REPORTED AFTER REPEATED ACTUATIONS OF FIRE DETECTION WARNING TEST SWITCH, SWITCH BUTTON DETACHED FROM SWITCH BODY CAUSING SWITCH TO SHORT AND ACTIVATE WARNING HORN. PILOT DECLARED AN EMERGENCY AND DIVERTED TO BUR AIRPORT WITHOUT INCIDENT. (X)SDR 20000713SH006Paint · looseDURING THE FIRST PHASE 1 INSPECTION, AN AREA APPROXIMATELY 3 INCHES SQUARE ON THE INSIDE BOTTOM OF THE INERTIAL SEPARATOR HAD LOOSE EPOXY PAINT PEELING LOOSE. 15 GRAMS OF CHIPS REMOVED WITH FINGERNAIL. AN UNKNOWN MOUNT WAS MISSING AND PRESUMABLY WENT THROUGHSDR 20000720SH021Actuator · shearedSTANDBY FLAP MOTOR INOPERATIVE. ACTUATOR SHAFT ROLL PIN SHEARED. JACKSCREW CONTAMINATED WITH METAL PARTICLES, MOTOR INOPERATIVE. UPON REPLACEMENT OF TRANSMISSION ASSY, ALSO DISCOVERED ELECTRICAL PIN IN PRIMARY FLAP MOTOR POWER CONNECTOR PARTIALLY DISENGAGED SDR AU000449Bracket · failed(AUS) FLAP MOTOR SUPPORT BRACKETS PN 2611144-6 AND PN 2611144-7 TORN FROM FUSELAGE STRUCTURE.SDR AU000436Bracket · failed(AUS) STANDBY FLAP MOTOR SUPPORT BRACKETS PN 2611144-6 AND PN 2611144-7 FAILED.SDR AU000437Bleed Valve · faulty(AUS) ENGINE BLEED VALVE DIAPHRAGM HOLED AND SEAT BADLY WORN DUE TO CHATTERING.SDR CA000614022Ring Assembly · cracked(CAN) DURING HOT SETION INSP PROCEDURES OF A/C ENGINE. ROUTINE INSP OF ENG MOUNT REVEALED A ONE INCH LONG CRACK IN ENG MOUNT RING LOWER (AFT) CORNER, RT SIDE. CRACKING OF RING SUBJECT OF AWD 90-05-04 AND CESSNA S/B CAB 88-14 INVOLVING A/C S/NS 208B0001 THRU S/SDR 20000721SH040Hose · leakingHNL - FLT 8666 - ON CLIMB-OUT, PILOT REPORTED ''FUEL FUMES IN COCKPIT''. AIR TURNBACK TO HNL. FUEL ACCUMULATION IN ENGINE COWL DUE TO LOOSE FUEL LINE CONNECTION AT FIREWALL FUEL FILTER. TIGHTENED THE NOSE FITTING, FLUSHED COWLING WITH SOAP AND WATER. PERFOSDR 20000720SH022Bleed Valve · failedMANUFACTURER RECALLED THIS SPECIFIC COMPRESSOR BLEED VALVE FOR TESTING OF INTERNAL PACKING FOR DEFECTS. BLEED VALVE SERIAL NUMBER FELL OUTSIDE OF ANY AD OR SB. (X)SDR 20000720SH020Transmitter · shortedLEFT FUEL QUANTITY INDICATOR INACCURATE AND ERRATIC. REPLACED DEFECTIVE CENTER OUTBOARD FUEL SENDING UNIT. (X)SDR CA000412009Bellcrank · broken(CAN) DURING APPROACH ,THE FLAPS FULLY RETRACTED. MAINTENANCE PERSONNEL FOUND THAT THE RIGHT FLAP BELLCRANK HAD BROKEN AT THE ARM CONNECTED TO THE INPUT DRIVE SHAFT FROM THE FLAP TRANSMISSION. THE BREAK OCCURRED AT THE WELD WHERE THE DOUBLER ENDS. THE BELLCSDR 20000510SH005O-Ring · cutDURING A POST-FLIGHT INSPECTION, THE PILOT NOTED EXCESSIVE OIL ON THE LOWER COWL AND DOWN THE LEFT SIDE OF THE AIRCRAFT. UPON FURTHER INSPECTION, DETERMINED A NR 2 BEARING OIL SCAVENGETUBE COUPLING O-RING LOCATED AT C-FLANGE WAS LEAKING. UPON REMOVAL OF THE SDR 20000428AP010Wire · chafedSMOKE FROM UNDER INSTRUMENT PANEL AFTER TURNING ON PROPELLER HEAT. MAINTENANCE FOUND CHAFFED WIRE DUE TO CONTACT WITH THE BACKSHELL OF A CANNON PLUG. THE WIRE WAS REPAIRED AND TEH WIRE BUNDLE WAS REPOSITIONED TO PREVENT REOCCURRANCE. THE A/C WAS RETURNED TOSDR CA000511013Screw · misinstalled(CAN) DURING A PHASE 1 INSPECTION, INCORRECT LENGTH SCREWS WERE FOUND INSTALLED AT WING ACCESS PANELS FOR THE AILERON BELLCRANK. THE SCREWS WERE RUBBING ON THE BELLCRANK AND THE SUBMITTER STATED THAT THE ENDS OF THE SCREWS WERE FOUND WORN OFF.SDR CA000309004Support Bracket · loose(CAN) THE PILOT REPORTED A THUMP WHEN POWER WAS INCREASED OR DECREASED. MAINTENANCE TRACED THE PROBLEM TO A LOOSE LINER IN THE FORWARD NOSE GEAR SPRING (DRAG LINK) SUPPORT. THE LINER COULD BE SEEN TO MOVE FORWARD AND AFT WITH THE APPLICATION OF POWER.
Back to Textron 208B