Rockwell International NA-265-65
Service difficulty reports · 76
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 = 'NA26565' 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 = 'NA26565' 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 2020F00358Ground Wire · failedLIGHT SMOKE IN THE BACK OF PASSENGERS CABIN. DECLARED AN EMERGENCY AND LANDED. INVESTIGATING AFTER LANDING FOUND FAULTY GROUND CONNECTOR GENERATING EXCESSIVE HEAT. REPLACED WIRING.SDR UVVR2020020300049Strut · overservicedDURING LANDING ROLLOUT THE AIRCRAFT DEPARTED THE RIGHT SIDE OF THE RUNWAY AND STOPPED IN THE GRASS. THE FLIGHT CREW REPORTED LOSS OF NOSE STEERING AND BRAKES. AIRCRAFT WAS TOWED TO HANGAR. SUBSEQUENT TESTING IN HANGAR WAS ABLE TO DUPLICATE THE LOSS OF STEERINGSDR UVVR2018060600048Skin · crackedFUSELAGE SKIN WAS FOUND CRACK AT LOWER AFT CORNER OF THE RT OVERWING ESCAPE HATCH OPENING.SDR UVVR2017060900046Unknown · unknownDURING LANDING ROLL, THE ACFT WAS TRACKING TO THE RIGHT. THE PILOT TRIED TO CORRECT IT BY APPLYING MORE LEFT RUDDER AND LEFT BRAKE, THE ACFT STILL CONTINUING TO TRACK TO THE RIGHT. SINCE THE AIRPLANE IS APPROACHING AT THE END OF THE RUNWAY, THE PILOT APPLIEDSDR UVVR2017031500044Skin · corrodedCORROSION WAS DISCOVERED AT LT UPPER WING PLANK BETWEEN WING STATION 146.4 TO 159.0.SDR UVVR2016031500043Flex Line · leakingDURING OPS CHECK OF CREW OXYGEN MASK, FOUND OXYGEN SYSTEM LEAKS BEYOND ALLOWABLE LIMIT WITH A 1 HOUR PERIOD. UPON INVESTIGATION FOUND O2 FLEX TO PILOT SYS OUTLET LEAKING AT 1 END OF CRIMP SECTION. THIS O2 FLEX LINE WAS MFG NEW ON 12/06/2005 WITH LOT 24291 ANSDR UVVR2016020900036Pump · failedAFTER LANDING AND DURING ROLLOUT THE PILOT REPORTED THAT THE BRAKES HAD FAILED. EMERGENCY BRAKING WAS SELECTED AND BRAKING POWER WAS RESTORED. POST LANDING OPS CHECK OF THE NR 1 HYDRAULIC PUMP REVEALED THAT THE PUMP MOTOR WAS SPINNING BUT THE PUMP WOULD NOT SDR UVVR2016020900035Clevis · fracturedON LANDING ROLLOUT THE LT MLG COLLAPSED AND THE LT WINGTIP CONTACTED THE RUNWAY. LANDING GEAR INDICATED DOWN AND LOCKED BEFORE AND AFTER THE GEAR COLLAPSED.SDR UVVR2015091500033Skin · corrodedLEFT WING AT WING 159-171, TOP SKIN BULGING. REMOVED TOP SKIN AND DISCOVERED SIGNIFICANT AREA OF CORROSION MEASURING APPROXIMATELY 3" X 4".SDR 1HYR20141103001Skin · crackedA SKIN CRACK WAS IDENTIFIED IN THE AFT UNPRESSURIZED AREA OF THE FUSELAGE, RT ABOVE, LT PYLON. THE CRACK IS ABOUT 1.375" LONG LOCATED AT APPROXIMATELY FS 390.5 JUST AFT OF FRAME, REF DWG 265-313390. IT RUNS VERTICAL AND IS CENTERED AT APPROX. W/L +7.25". FUSDR UVVR2013101500027Bolt · fracturedBOLT HEAD MISSING FROM UPPER FWD WING SPLICE PLATE. BOLT SHANK AND NUT WERE FOUND INTACT.SDR UVVR2011072500018Attach Fitting · crackedDURING COMPLIANCE OF CAMP CARD 52.006 (521040) INSPECT MAIN ENTRANCE DOOR FOR CORROSION. THE MAIN ENTRANCE DOOR FORWARD HANDRAIL ATTACH FITTING (L-ANGLE) WAS FOUND CRACKED.SDR UVVR2011072200017Skin · corrodedDURING COMPLIANCE OF SB 99-2 INSPECT LT & RT WING TIPS, LT TOP AND BOTTOM AFT WING PLANK CORRODED AROUND NUT PLATE AREAS AT REAR SPAR (RS) 258.371 TO 270.371.SDR DGCA10844Hydraulic System · low pressureLOST MAIN HYD SYS PRESSURE INDICATION. DECLARED AN EMERGENCY LANDING.SDR UVVR2010042800007Skin · corroded(UVVR) WHILE AIRCRAFT WAS STRIPPED FOR A PAINT JOB, VISUAL INSPECTION OF LT WING OVERWING FAIRING WAS DELAMANATED. AFTER FUTHER PANEL REMOVAL, FOUND CORROSION EXTENDING UNDER OVERWING FAIRING. CORROSION EXTENDING THROUGH LT WING PLANK AT W.S. 102.5 TO W.S. 107SDR UVVR2010022600006Floorbeam · corrodedANGLE CORRODED (EXFOLIATED) ON LOWER FS 166.3 FUSELAGE FLOOR SUPPORT WEB RT BP 8-10, ATTACHED TO LOWER FUSELAGE SKIN AND WEB.SDR UVVR2010021500005Skin · crackedFUSELAGE SKIN CRACKED AT LOWER AFT CORNER OF LEFT OVERWING ESCAPE HATCH OPENING.SDR UVVR2010021500004Skin · crackedFUSELAGE SKIN CRACKED AT LOWER FWD CORNER OF RT OVERWING ESCAPE HATCH OPENING.SDR UVVR2010021100001Frame · cracked3 INCH CRACK IN LEFT FUSELAGE SIDE FRAME AT FUSELAGE STATION 257.65 APPROXIMATELY 2 INCHES ABOVE CABIN FLOOR.SDR DGCA10523Circuit Breaker · brokenAIRCRAFT LOST ALL EMERGENCY POWER.SDR DGCA10501Pump · failedHYDRAULIC PUMP FAILURE.SDR DGCA09327Exciter · inoperativeRT ENGINE WOULD NOT START. EXCITER INOPERATIVE.SDR DGCA 09104 11Proximity Switch · defectiveRT MAIN GEAR, DOWN AND LOCKED GREEN INDICATOR LIGHT, WOULD NOT EXTINGUISH.SDR DGC2008F00001Pump · inoperativeON AUGUST 16, 2008, AT APPROXIMATELY 8:30 AM, AFTER LANDING, THE CREW HEARD AUDIBLE WARNING OF HYDRAULIC SYSTEM LOW PRESSURE. THE AC TAXIED TO THE RAMP OF DESTINATION, WITHOUT INCIDENT. UPON INVESTIGATION, THE HYDRAULIC PUMP WAS FOUND TO HAVE FAILED. (K)SDR DGCA175D081867Pump · inoperativeON AUGUST 16, 2008, AT APPROXIMATELY 8:30 AM, ACFT N570R S/N 485-075, AFTER LANDING AT YIP, THE CREW HEARD AUDIBLE WARNING OF HYDRAULIC SYSTEM LOW PRESSURE. THE ACFT TAXIED TO THE RAMP OF DESTINATION, WITHOUT INCIDENT. UPON INVESTIGATION, THE HYDRAULIC PUMP SDR DGC2008F00000Pump · inoperativeHYDRAULIC PRESSURE SYSTEM FAILURE, DISCOVERED PUMP INOPERATIVE. (S)SDR 0805714Proximity Switch · unknownRED LIGHT IN MLG HANDLE.SDR 07060Housing · crackedNOSE LANDING GEAR STEERING ACTUATOR HOUSING DEVELOPED A CRACK AND LEAKED HYDRAULIC FLUID ON THE RAMP.SDR DGCA06233Pin · crackedRT EMERGENCY EXIT, LOWER AFT ALIGNMENT PIN CRACKED.SDR DGCA06009Carbon Seal · failedAFTER DEPARTURE, PLTS NOTICED RT ENG OIL PRESSURE WAS ABOVE THE GREEN ARC INTO THE YELLOW. PULLED BACK ON THE THROTTLE AND THE OIL PRESSURE FOLLOWED THE THROTTLE MOVEMENT, AT THAT TIME THE ENGINE BEGAN TO SURGE AND THEY HEARD A POP FROM THE REAR OF THE A/C. SDR DGCA06002Proximity Switch · brokenWHEN DEPARTING FROM SPIRIT OF ST. LOUIS AIRPORT S.U.S., THE CREW RETRACTED THE MAIN GEAR, UPON COMPLETION OF THE UP CYCLE THE CREW HEARD A KNOCKING NOISE FROM THE BELLY OF THE AIRCRAFT, AND THEN GOT A RED LIGHT IN THE GEAR HANDLE. THEY PUT THE GEAR DOWN AND HSDR DGCA05020Control Box · malfunctionedDC VOLTAGE "SPIKE", CAUSING MULTIPLE COMPONENT/SYSTEM FAILURES, CIRCUIT BREAKERS POPPING.SDR JV2R200400003Eec · defectiveOPERATOR REPORTED LEFT DIGITAL ELECTRONIC ENGINE CONTROL COMPUTER FAIL LIGHT ILLUMINATED DURING CLIMB PUTTING THE SYSTEM IN MANUAL. THE OPERATOR REPORTED ATTEMPTING RESET ONE TIME, SYSTEM FAILED AGAIN AND OPERATOR RETURNED TO BASE. HONEYWELL WAS CONTACTED.SDR JV2R200400001Computer · failedDURING MAINTENANCE ENGINE RUN, THE LT COMPUTER FAIL LIGHT ILLUMINATED AT 92 PERCENT AND THE SYSTEM WENT TO MANUAL. THE ENGINE OPERATOR RESET THE SYSTEM PER MANUAL AND PERFORMED A SECOND ENGINE RUN. LEFT COMPUTER FAIL LIGHT ILLUMINATED AT IDLE ON THE SECOND ESDR WK42004F00002Tire · damagedCENTER TREAD CHUNKED AFTER 54 LANDINGS ON LT TIRE.SDR JV2R20040001Tire · separatedTIRE TREAD SEPARATION FROM TIRE CASING. EACH TIRE REPORTED HAS LESS THAN TWENTY LANDINGS ON IT. THIS PROBLEM REPORTED TO TIRE MFG. SAMPLES OF DISCREPANT UNITS FORWARDED TO MFG FOR EVALUATION. THIS IS THE FIRST OF NINE KNOWN FAILURES OF THESE TIRES. ONE OTSDR WK42004F00000Tire · damagedCENTER TREAD CHUNKED AFTER 19 LANDINGS ON LEFT LAND TIRE.SDR JV2R200300001Frame · crackedCRACK FOUND UPON ROUTINE INSPECTION. CRACK IS APPOXIMATLY FOURTEEN INCHES INTO FRAME. APPOXIMATE LOCATION OF FRAME IS FS 264.SDR 2003F00513Bellcrank · crackedAFTER FINDING THE LT AFT ELEVATOR BELLCRANK PN 265-5221313 FS457 CRACKED AT LOWER BEARING BOSS AREA ON A DIFFERENT NA 265-65 AIRCRAFT WE PERFORMED INSPECTIONS ON 5 EA. ADDITIONAL NA 265-65 AIRCRAFT THAT WERE IN HOUSE. THIS INSPECTION UNCOVERED A CRACKED BELLSDR 032031ARestrictor Valve · bypassingDURING PREFLT INSP, MAINT CREW NOTED THAT SPOILERS FULLY DEPLOYED IN LESS THAN 1 SECOND WITH SPOILER SWITCHES SET TO "IN-FLT" MODE. NORMAL DEPLOY TIME IN THIS MODE IS 6-10 SECONDS WHEREAS "GROUND AUTO-DEPLOY" MODE FOR LANDING IS LESS THAN ONE SECOND. IN PROCSDR 032031Restrictor Valve · bypassingMAIN ACCOMPLISHED PREFLT INSP AND THEN PILOTS PROCEEDED TO DO THEIR PREFLT INSP. UPON NORMAL EXTENSION OF SPEED BRAKE PANELS, THEY RETRACTED WITH HIGH SPEED AS THOUGH SWITCHES WERE IN THE "GROUND AUTO DEPLOY" POSITION. DISASSEMBLLY OF RESTRICTOR VALVE SHOWEDSDR ROCK012303Switch · inoperativePILOT'S TRIM SWITCH BECAME INTERMITTENT AND THEN FAILED TO OPERATE COMPLETELY IN FLIGHT. CO-PILOT AND ALTERNATE TRIM SYSTEMS BOTH REMAINED FUNCTIONAL. TESTED AND REPLACED PILOT'S TRIM SWITCH AT DESTINATION. SYSTEM FUNCTIONED PROPERLY AFTER REPLACMENT OF SWISDR JV2R200200004Line · nickedWHEN COMPLYING WITH CAMP CARDS, A VISUAL INSPECTION OF THE ENGINE WAS PERFORMED AND FOUND THE OIL LINE HAD NICKS IN THE LINE CAUSE BY THE CLAMPS, THAT HAD THE TEFLON WORN CAUSING METAL TO METAL CONTACT. REPLACED LINE AND CLAMPS.SDR JV2R200200003Line · nickedWHEN COMPLYING WITH CAMP CARDS, A VISUAL INSPECTION OF THE ENGINE WAS PERFORMED AND FOUND THE OIL LINE HAD NICKS IN IT CAUSE BY THE CLAMPS THAT HAD THE TEFLON WORN CAUSING METAL TO METAL CONTACT. REPACED LINE AND CLAMPS.SDR 02341Bearing · failedPILOT BEGAN FEELING VIBRATION FROM LEFT ENGINE, LEFT GENERATOR HOT LIGHT CAME ON, FOLLOWED BY GENERATOR FAILURE.SDR 2002FA0001066Bracket · brokenDURING GEAR RETRACTION TEST, LT MLG DOOR ACTUATOR ATTACH BRACKET BROKE AT GEAR DOOR.SDR UVVR200200001Gasket · failed"AFT FUSELAGE HOT" LIGHT CAME ON IN FLIGHT. CREW MADE LANDING AT SUS. AVMATS TROUBLESHOT PROBLEM, FOUND APU START BYPASS VALVE GASKET BLOWN - CAUSING HOT BLEED AIR TO TRIP THERMAL SWITCH, ILLUMATING WARNING LIGHT. REMOVED AND REPLACED GASKET WITH NEW GASKET.SDR I5W2002F00000Fitting · brokenLANDING GEAR WOULD NOT RETRACT AFTER TAKE-OFF. THE MAIN GEAR INNER DOOR ACTUATOR SUPPORT FITTING PN 2823330511 BROKE AT THE ACTUATOR ATTACH POINT. MANUALLY RETRACTED THE RIGHT GEAR DOOR AND INSPECTED THE AIRCRAFT AND DEEMED THE AIRCRAFT SAFE FOR THE FERRY FLSDR 029041702Line · crackedPILOTS STARTED TAXI OUT TO TAKEOFF. IN PROCESS CONDUCTED THE LANDING SPOILER EXTENSION OPERATIONAL TEST WHICH SURGES AND SLAMS THE HYDRAULIC SYSTEM FAIRLY HARD. WITHIN A FEW SECONDS RECEIVED MASTER WARNING CAUTION LIGHT AND NOTICED LOW HYDRAULIC PRESSURE. SDR 2001112329Line · crackedMAINTENANCE PERSONNEL NOTICED FLUID LEAKAGE FROM BELLY PANEL AFT OF LANDING GEAR FOLLOWING PILOT'S COMPLETION OF "SPOILER AUTO EXTEND" PREFLIGHT CHECK BY FLIGHT CREW. VISUAL INSPECTION DETERMINED SPOILER AUTO EXTEND LINE ASSEMBLY TO BE LEAKING PAST B-NUT AND
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