# Service difficulty reports: N258PB A list on [N258PB](https://openairdocs.org/aircraft/N258PB.md). Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first. - [SDR HYIA20220413001](https://openairdocs.org/sdr/HYIA20220413001.md): Trunnion · cracked · Apr 9, 2022 · N258PB · Cessna 402C · Fuselage, Landing Gear Attach Fittings > RIGHT MAIN LANDING GEAR TRUNNION UPPER TORQUE LINK TAB BROKE ON LANDING - [SDR HYIA202001210001](https://openairdocs.org/sdr/HYIA202001210001.md): Spar Cap · cracked · Jan 21, 2020 · N258PB · Cessna 402C · Wing Spar > A 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 F - [SDR HYIA20180717002](https://openairdocs.org/sdr/HYIA20180717002.md): Frame · corroded · Jul 12, 2018 · N258PB · Cessna 402C · Fuselage Main, Frame > WHILE 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 REMO - [SDR HYIA20180717001](https://openairdocs.org/sdr/HYIA20180717001.md): Spar Cap · corroded · Jul 12, 2018 · N258PB · Cessna 402C · Wing Spar > WHILE 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 REM - [SDR HYIA20180627001](https://openairdocs.org/sdr/HYIA20180627001.md): Strap · corroded · Jun 21, 2018 · N258PB · Cessna 402C · Wing Miscellaneous Structure > WHILE 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 BLE - [SDR 8PCR20171031001](https://openairdocs.org/sdr/8PCR20171031001.md): Bolt · sheared · Oct 31, 2017 · N258PB · Cessna 402C · Reciprocating Engine Power Section > ENGINE 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 HYIA20170705004](https://openairdocs.org/sdr/HYIA20170705004.md): Rib · cracked · Jul 5, 2017 · N258PB · Cessna 402C · Wing, Rib/Bulkhead > DURING 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 HYIA20170828004](https://openairdocs.org/sdr/HYIA20170828004.md): Fitting · cracked · Jan 12, 2017 · N258PB · Cessna 402C · Nacelle/Pylon, Main Frame > DURING 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 HYIA20170828003](https://openairdocs.org/sdr/HYIA20170828003.md): Fitting · cracked · Jan 12, 2017 · N258PB · Cessna 402C · Nacelle/Pylon, Main Frame > DURING 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 HYIA20141224001](https://openairdocs.org/sdr/HYIA20141224001.md): Governor · defective · Dec 23, 2014 · N258PB · Cessna 402C · Propeller Governor > ON 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 HYIA05032014007](https://openairdocs.org/sdr/HYIA05032014007.md): Beam · chafed · May 1, 2014 · N258PB · Cessna 402C · Nacelle/Pylon Miscellaneous Structure > DURING 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 HYIA05032014006](https://openairdocs.org/sdr/HYIA05032014006.md): Beam · chafed · May 1, 2014 · N258PB · Cessna 402C · Nacelle/Pylon Miscellaneous Structure > DURING 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 FURTHER - [SDR HYIA05032014005](https://openairdocs.org/sdr/HYIA05032014005.md): Spar · cracked · May 1, 2014 · N258PB · Cessna 402C · Wing Spar > DURING 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 SUPPLIED - [SDR HYIA05032014004](https://openairdocs.org/sdr/HYIA05032014004.md): Spar · cracked · May 1, 2014 · N258PB · Cessna 402C · Wing Spar > DURING 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 SUPPLIE - [SDR HYIA05032014003](https://openairdocs.org/sdr/HYIA05032014003.md): Spar · cracked · May 1, 2014 · N258PB · Cessna 402C · Wing Spar > DURING 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 SUPPL - [SDR HYIA05032014001](https://openairdocs.org/sdr/HYIA05032014001.md): Strap · corroded · May 1, 2014 · N258PB · Cessna 402C · Wing Spar > DURING 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 TO - [SDR HYIA20140412001](https://openairdocs.org/sdr/HYIA20140412001.md): Bearing Support · corroded · Apr 10, 2014 · N258PB · Cessna 402C · Rudder Miscellaneous Structure > AT 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 STRUCTU - [SDR HYIA20121221001](https://openairdocs.org/sdr/HYIA20121221001.md): Governor · overspeed · Dec 20, 2012 · N258PB · Cessna 402C · Propeller Governor > PILOT 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 GO - [SDR HYIA20140414024](https://openairdocs.org/sdr/HYIA20140414024.md): Drag Brace · cracked · Oct 19, 2012 · N258PB · Cessna 402C · Landing Gear Retraction/Extension System > AT 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 HYIA20120904005](https://openairdocs.org/sdr/HYIA20120904005.md): Bolt · failed · Sep 1, 2012 · N258PB · Cessna 402C · Main Landing Gear > PILOT 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 HYIA20140415072](https://openairdocs.org/sdr/HYIA20140415072.md): Drag Brace · cracked · Sep 21, 2011 · N258PB · Cessna 402C · Landing Gear Retraction/Extension System > AT 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 IAW - [SDR HYIA258PB](https://openairdocs.org/sdr/HYIA258PB.md): Beam · cracked · Feb 11, 2009 · N258PB · Cessna 402C · Nacelle/Pylon, Main Frame > LEFT ENGINE OUTBOARD SIDE OF CROSSOVER BEAM IS CRACKED. MAINTENANCE TO REMOVE AND REPLACE CROSSOVER BEAM ASSY. - [SDR 135258032308](https://openairdocs.org/sdr/135258032308.md): Axle · cracked · Mar 23, 2008 · N258PB · Cessna 402C · Main Landing Gear Strut/Axle/Truck > ON 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 HYI2002F00008](https://openairdocs.org/sdr/HYI2002F00008.md): Master Switch · failed · Nov 29, 2001 · N258PB · Cessna 402C · Instrument Panel > ON PRE-FLIGHT INSPECTION, AVIONICS SWITCH FAILED. MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE. PTRS 12/12/01 - [SDR HYI2001F00014](https://openairdocs.org/sdr/HYI2001F00014.md): Switch · failed · Nov 2, 2001 · N258PB · Cessna 402C · Electrical Power System Wiring > ON PREFLIGHT INSPECTION, AVIONICS SWITCH FAILED, MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE. - [SDR 97ZZZX1229](https://openairdocs.org/sdr/97ZZZX1229.md): Aileron · weight broken · Feb 25, 1997 · N258PB · Cessna 402C · Ailerons > AILERON 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 ## The whole list in SQL Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS: ```sql 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 ``` This list as a web page: https://openairdocs.org/aircraft/N258PB/reports --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.