N258PB
Service difficulty reports · 26
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.
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 n_number = 'N258PB' AND registry_match = 'registration' 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 n_number = 'N258PB' AND registry_match = 'registration' 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 HYIA20220413001Trunnion · crackedRIGHT MAIN LANDING GEAR TRUNNION UPPER TORQUE LINK TAB BROKE ON LANDINGSDR HYIA202001210001Spar Cap · crackedA CRACK WAS IDENTIFIED AT THE RT SIDE OF THE LWR FWD CARRYTHROUGH SPAR CAP (AFT MOST IB FASTENER COMMON TO WING JOINT FITTING) WHILE PERFORMING NDT PROCEDURE AS AMOC FOR AD2018-03-03R1. THE CRACK WAS CONFIRMED WITH BOLT HOLE EDDY CURRENT PROCEDURE AFTER THE FSDR HYIA20180717002Frame · corrodedWHILE CONDUCTION OTHER MAINTENANCE, AN AREA OF CORROSION WAS NOTED ON THE FUSELAGE FRAME ASSEMBLY AT FS 214.00, JUST ABOVE THE 501110-12 STRIKER PLATE FOR THE LOWER PASSENGER DOOR PIN. THE 501110-12 STRIKER PLATE WAS REMOVED FOR FURTHER INSPECTION. UPON REMOSDR HYIA20180717001Spar Cap · corrodedWHILE CONDUCTING OTHER MAINTENANCE, CORROSION WAS NOTED ON THE HORIZONTAL LEG OF THE LOWER LEFT AFT OUTBOARD SPAR CAP, AT WS 222.46. THE CORROSION AREA MEASURED .218 BY .086. THE DEPTH OF THE CORROSION MEASURED AT .022, WHICH IS DEEPER THAN THE ALLOWABLE REMSDR HYIA20180627001Strap · corrodedWHILE CONDUCTING A VISUAL INSPECTION, CORROSION WAS NOTED ON THE LEFT SPAR STRAP. ONE AREA OF CORROSION WAS FOUND AT LWS 127.04 TO 129.04 AT THE AFT ROW OF FASTENERS. CORROSION MEASURED .50 IN WIDTH AT IT'S WIDEST POINT. A SMALL PORTION OF THIS AREA WAS BLESDR 8PCR20171031001Bolt · shearedENGINE DISASSEMBLED FOR OVERHAUL. CRANKSHAFT CLUSTER GEAR BOLTS (6 EACH) SHEARED. NEW PART NUMBER LARGE GEAR (P/N 656991) AND BOLTS (P/N 656990) WERE IN PLACE IAW LATEST SERVICE BULLETINS. LACK OF FRETTING SIGNATURES ON CRANKSHAFT GEARS AND ATTACHING BOLTS SDR HYIA20170705004Rib · crackedDURING A ROUTINE INSPECTION, A CRACK WAS IDENTIFIED IN THE RT CLOSEOUT RIB AT RWS 106.79. ON REMOVAL, IT WAS NOTED THAT THE FASTENER HOLE WHERE THE CRACK STARTED FROM WAS NO LONGER IN TOLERANCE FOR THE LOCK FASTENER THAT WAS PREVIOUSLY INSTALLED THERE.SDR HYIA20170828004Fitting · crackedDURING A ROUTINE INSPECTION, A CRACK WAS DISCOVERED ON THE RT OUTBOARD NACELLE FITTING. THE CRACK WAS FOUND ON THE INBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. THE CRACK MEASURED .171 IN LENGTH.SDR HYIA20170828003Fitting · crackedDURING A ROUTINE INSPECTION, A CRACK WAS DISCOVERED ON THE LT OUTBOARD NACELLE FITTING THE CRACK WAS DISCOVERED ON THE INBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. THE CRACK WAS .108 IN LENGTH.SDR HYIA20141224001Governor · defectiveON CLIMB OUT RT PROP INCREASED RPM BEYOND THE RED, BY ITSELF, HAD NO CONTROL OF RT PROP. ALSO RT PROP WOULD NOT FEATHER. PERFORMED AN AIR RETURN & LANDED WITH NO FURTHER INCIDENT. INSPECTED THE RT PROP CONTROL, REPOSITIONED PROP GOVERNOR CABLE. R & R PROP SDR HYIA05032014007Beam · chafedDURING SCHEDULED INSPECTION, CHAFE DAMAGE WAS NOTED AT RT NACELLE OTBD ENG BEAM AFT OF CORRESPONDING ENG MOUNT. THIS DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIED & SUBSTANTIATED BY DER. A SUPPLEMENT TO THIS SDR WILL BE FORWARDED SEPARATELY FURTHER SDR HYIA05032014006Beam · chafedDURING SCHEDULED INSPECTION, CHAFE DAMAGE WAS NOTED AT LT NACELLE OTBD ENG BEAM AFT OF CORRESPONDING ENG MOUNT. THIS DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIED & SUBSTANTIATED BY DER. A SUPPLEMENT TO THIS SDR WILL BE FORWARDED SEPARATELY FURTHERSDR HYIA05032014005Spar · crackedDURING SCHEDULED INSPECTION, MULTIPLE SPAR WEB CRACKS WERE NOTED INITIATING FROM SPAR WEB MOUSE HOLE CUT OUTS AT AFT CARRY THROUGH SPAR ASSEMBLY, PN 5211173-2, AT CTR LOWER SECTION OF FWD & AFT WEBS. THIS DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIEDSDR HYIA05032014004Spar · crackedDURING SCHEDULED INSPECTION, MULTIPLE SPAR WEB CRACKS WERE NOTED INITIATING FROM SPAR WEB, MOUSE HOLE CUT OUTS AT FWD CARRY THROUGH SPAR ASSEMBLY, PN 5211171-2, AT CTR LOWER SECTION OF FWD & AFT WEBS. THIS DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIESDR HYIA05032014003Spar · crackedDURING ROUTINE SCHEDULED INSPECTION, MULTIPLE WEB FLANGE CRACKS WERE NOTED AT AFT FUSELAGE CARRY THROUGH SPAR ASSEMBLY, PN 5211173-2 AT CTR UPPER SECTION FWD & AFT WEBS. THIS DAMAGE WILL BE REPAIRED, REPAIR DEFINITION SUPPLIED & SUBSTANTIATED BY DER. A SUPPLSDR HYIA05032014001Strap · corrodedDURING ROUTINE SCHEDULED INSPECTION, AREAS OF CORROSION WERE FOUND AT LT & RT LOWER WING SPAR CAP STRAPS PREVIOUSLY INSTALLED VIA SK402-47B ON 12/05/2005 TO SATISFY REQUIREMENT OF AD2005-12-13 & MEB02-5. THE CORRECTIVE ACTION TO REMEDIATE CONDITION WILL BE TOSDR HYIA20140412001Bearing Support · corrodedAT SCHEDULED INSPECTION, SEVERE CORROSION WAS FOUND AT LWR RUDDER HINGE BRACKET & ASSOCIATED BEARING BLOCK. CORRECTIVE ACTION WILL BE TO REMOVE AFFECTED PARTS FOR REPLACEMENT WITH NEW IAW MEB00-4 & PERFORM ADDITIONAL DETAILED INSPECTION OF SURROUNDING STRUCTUSDR HYIA20121221001Governor · overspeedPILOT REPORTED THAT ON CLIMBOUT, THE RT PROP BECAME UNCONTROLLABLE AND WOULD OVERSPEED. THE PILOT ELECTED TO RETURN TO THE DEPARTURE AIRPORT. UPON MX INSPECTION, THE RT PROP AND PROP GOVERNOR WERE REPLACED IAW MM CHAPTER 61. THE PROP OPS AND LEAK CHECKED GOSDR HYIA20140414024Drag Brace · crackedAT SCHEDULED INSPECTION, NLG DRAG BRACE, PN 5142002-5 WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE BEYOND LIMIT ALLOWABLE OF MEB91-11R1. THIS UNIT HAS BEEN SCRAPPED & A SDR HYIA20120904005Bolt · failedPILOT REPORTED THAT WHILE TAXIING, A DISCREPANCY WAS NOTED ON THE LT MAIN. ON INSPECTION, IT WAS DISCOVERED THAT THE LT MLG TORGUE LINK CENTER BOLT HAD COME APART. THE TORQUE LINK WAS REASSEMBLED WITH NEW HARDWARE.SDR HYIA20140415072Drag Brace · crackedAT SCHEDULED INSPECTION, NLG DRAG BRACE, PN 5142002-5, WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE WITHIN ALLOWABLE LIMIT OF MEB91-11R1. THIS UNIT HAS BEEN REPAIRED IAWSDR HYIA258PBBeam · crackedLEFT ENGINE OUTBOARD SIDE OF CROSSOVER BEAM IS CRACKED. MAINTENANCE TO REMOVE AND REPLACE CROSSOVER BEAM ASSY.SDR 135258032308Axle · crackedON TAXI AFTER LANDING, PILOT REPORTED RIGHT BRAKE "LOCKED UP". UPON FURTHER INSPECTION BY MAINTENANCE IT WAS FOUND THAT THE RIGHT MAIN LANDING GEAR AXLE WAS CRACKED. MAINTENANCE REMOVED AND REPLACED RIGHT MAIN LANDING GEAR LOWER AXLE ASSEMBLY. AIRCRAFT WAS SDR HYI2002F00008Master Switch · failedON PRE-FLIGHT INSPECTION, AVIONICS SWITCH FAILED. MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE. PTRS 12/12/01SDR HYI2001F00014Switch · failedON PREFLIGHT INSPECTION, AVIONICS SWITCH FAILED, MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE.SDR 97ZZZX1229Aileron · weight brokenAILERON HAS A 4 FOOT LEAD WEIGHT INSTALLED FOR BALANCING. LEAD WEIGHT HAD BROKEN AWAY FROM MOUNT AND WAS LOOSE IN LEADING EDGE OF AILERON. LEADING EDGE WAS REMOVED AND BALANCE WEIGHT WAS RE-ATTACHED TO AILERON. FLIGHT CONTROL WAS RE-BALANCED AND RETURNED TO
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