# Service difficulty reports: Cessna 425

A list on [Cessna 425](https://openairdocs.org/model/cessna-425.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 5 · 203 reports

- [SDR YN8R2026100600815](https://openairdocs.org/sdr/YN8R2026100600815.md): Mount · cracked · Oct 6, 2026 · N425CC · Cessna 425 · Engine Mount Section
  > DURING THE PHASE 32, SENT THE ENGINE AND NACELLE TRUSSES OUT FOR NDI PER 5-14-22. THE ENGINE MOUNTS ARE NOT CALLED OUT FOR NDI INSPECTIONS DURING ANY PHASE. SENT THE ENGINE MOUNTS FOR NDI AS WELL THOUGH, DUE TO PREVIOUS FINDINGS OF CRACKS IN THE MOUNTS. IT WAS
- [SDR 2026FA0000006](https://openairdocs.org/sdr/2026FA0000006.md): Mount · cracked · Jan 7, 2026 · N353ES · Cessna 425 · Engine Mount Section
  > DURING MINOR PHASE INSPECTIONS, THE RH ENGINE OUTBOARD ENGINE MOUNT P/N: 5951048-2 WAS VISUALLY FOUND TO BE CRACKED. AFTER DEFECT WAS FOUND, ENGINE REMOVAL TOOK PLACE TO INSPECT THE REMAINING TWO ENGINE MOUNTS AND THE FWD. ENGINE TRUSS. NO VISUAL DEFECTS WERE
- [SDR 2024FA0000783](https://openairdocs.org/sdr/2024FA0000783.md): Compressor · failed · Jul 2, 2024 · N425CL · Cessna 425 · Turbine Engine Compressor Section
  > ON 7-2-24, N425CL EXPERIENCE AN INFLIGHT SUDDEN SHUTDOWN OF THE RIGHT-HAND ENGINE. AS THE MECHANIC FOR THIS AIRCRAFT, I REMOVED THIS ENGINE FOR SHIPMENT TO AN OVERHAUL FACILITY. INITIAL INSPECTION SHOWS THAT THE COMPRESSOR SECTION HAD SHED MOST OF THE COMPRE
- [SDR 2023FA0000079](https://openairdocs.org/sdr/2023FA0000079.md): Windshield · cracked · Feb 9, 2023 · N425PJ · Cessna 425 · Windshield/Door Rain/Ice Removal
  > WINDSHIELD OUTER LAYER CRACKED IN FLIGHT
- [SDR 2023FA0000045](https://openairdocs.org/sdr/2023FA0000045.md): Windshield · cracked · Jan 18, 2023 · N74RF · Cessna 425 · Fuselage Main, Structure
  > PILOT SIDE WINDSHIELD OUTER LAYER OF GLASS CRACKED DURING TAKEOFF ROLL, NO EXTERNAL IMPACT WAS REPORTED BY PILOT.
- [SDR 2022FA0000176](https://openairdocs.org/sdr/2022FA0000176.md): Warning Switch · leaking · Mar 16, 2022 · N425JG · Cessna 425 · Fuselage Structure (General)
  > DURING CRUISE FLIGHT PILOT NOTICED A SLIGHT DROP IN OIL PRESSURE. SOON THEREAFTER PILOT NOTICED OIL ON THE NACELLE COMING FROM REAR OF THE LEFT ENGINE COWL. PILOT DECLARED AN EMERGENCY AND LANDED WITH NO ADDITIONAL SYMPTOMS. IT WAS DISCOVERED THAT THE OIL W
- [SDR 2017FA0000390](https://openairdocs.org/sdr/2017FA0000390.md): Bolt · failed · Jan 26, 2017 · N73DW · Cessna 425 · Propeller Blade Section
  > WHILE IN FLIGHT THE PILOT NOTICED A VIBRATION FROM THE RT ENG. AFTER LANDING, INSPECTION OF THE PROPELLER REVEALED THAT THE NR 1 BLADE WOULD SPIN FREELY IN THE HUB. AFTER DISASSEMBLY, IT WAS FOUND THAT THE ACTUATING PIN BOLTS HAD PULLED OUT OF THE BLADE AND
- [SDR 2017FA0000018](https://openairdocs.org/sdr/2017FA0000018.md): Switch · malfunctioned · Jan 19, 2017 · N440H · Cessna 425 · Landing Gear Position and Warning
  > ON APPROACH TO KLUK THE PILOT SELECTED THE GEAR DOWN AND DID NOT GET A GREEN INDICATION FOR THE LEFT MAIN LANDING GEAR. THE AIRCRAFT LANDED SAFELY, AND IT WAS FOUND THAT THE INTERNAL DOWN LOCK INDICATOR SWITCH IN THE LEFT MAIN LANDING GEAR STRUT HAD MALFUNCTIO
- [SDR 2016FA0000393](https://openairdocs.org/sdr/2016FA0000393.md): Fuel Control · defective · Aug 18, 2016 · N1262T · Cessna 425 · Fuel Controlling System
  > ON DECENT THE RIGHT ENGINE WOULD NOT PROPERLY POWER BACK WHEN COMMANDED TO DO SO. THE PILOT ELECTED TO SHUT DOWN THE ENGINE AND DECLARE AN EMERGENCY. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE FUEL CONTROL AND THE FUEL PUMP. RAN AIRCRAFT
- [SDR BIGA20150827007](https://openairdocs.org/sdr/BIGA20150827007.md): Wire · grounded · Aug 25, 2015 · N700WJ · Cessna 425 · Landing Gear System Wiring
  > DURING A TRAINING FLIGHT THE PILOT ATTEMPTED TO EXTEND THE GEAR & HAD THE 5 AMP LG CONTROL CB POP. THE PILOT EXTENDED THE GEAR USING THE NITROGEN BLOW DOWN SYS IAW THE POH & AFM, THE GEAR WAS DOWN & LOCKED WITH 3 GREEN INDICATIONS. THE SYS WAS TROUBLE SHOT &
- [SDR E8JR20150721001](https://openairdocs.org/sdr/E8JR20150721001.md): Control Cable · out of position · Jun 19, 2015 · N425LA · Cessna 425 · Elevator Control System
  > DURING FLIGHT, PILOT FOUND UP ELEVATOR TRAVEL RESTRICTED. GROUND CHECK FOUND ELEVATOR MOVEMENT WAS RESTRICTED TO APPROXIMATELY 1" T/E UP PAST NEUTRAL. OPENED TAIL CONE PANELS AND FUSELAGE LOWER PANEL AFT OF NOSE GEAR WHEEL WELL. INSPECTED AND FOUND NO FAULT
- [SDR 2015FA0000108](https://openairdocs.org/sdr/2015FA0000108.md): Starter · failed · Mar 20, 2015 · N757H · Cessna 425 · APU Start/Ignition System
  > ATTEMPTED START OF APU. NO START. INSPECTION OF APU STARTER NOTED HOLE BURNED THROUGH STARTER CASE. REMOVED STARTER AND PERFORMED INSPECTION ON WIRING, TRU, AND APU START CONTACTOR. NO OTHER DAMAGE OR ARCING NOTED. SUSPECT INTERNAL SHORT AND ARCING INSIDE STA
- [SDR YN8R2015021000001](https://openairdocs.org/sdr/YN8R2015021000001.md): Control Cable · frayed · Feb 10, 2015 · N67BA · Cessna 425 · Rudder Control System
  > DURING PHASE 61 INSPECTION, CHECKED CONTROL CABLES WITH RAGS FOR SNAGS. FOUND BOTH AFT RUDDER CABLES, PN 5200008-28, TO HAVE SEVERAL BROKEN STRANDS WHERE THE CABLES ROLLED OVER THE AFT PULLEYS, PN S378-4 IN THE RUDDER CONTROL SYSTEM, STA 348.00. REPLACED CAB
- [SDR YN8R01302015BH](https://openairdocs.org/sdr/YN8R01302015BH.md): Bellcrank · worn · Jan 30, 2015 · N67BA · Cessna 425 · Elevator Control System
  > DURING PHASE 61 INSPECTION, THE ELEVATOR CONTROL SYS WAS CHECKED PRIOR TO DISASSEMBLY. THE ELEVATORS HAD SIGNIFICANT FREE PLAY BETWEEN EACH ELEVATOR. FOUND THE ELEVATOR BELLCRANK SUPPORT PLATES, PIVOT BOLT HOLES WERE ELONGATED BY WEAR ALLOWING THE BELLCRANK
- [SDR CA141010005](https://openairdocs.org/sdr/CA141010005.md): Blade · distressed · Jul 7, 2014 · Cessna 425 · Turbine Section
  > (CAN) ENGINE CT AND PT BLADE DISTRESS WITH EVIDENCE OF OVERHEATING.
- [SDR GNMA20140623001](https://openairdocs.org/sdr/GNMA20140623001.md): Cylinder · activated · Jun 23, 2014 · N425RM · Cessna 425 · Landing Gear Retraction/Extension System
  > AIRCRAFT LEFT HOME BASE & PILOT ATTEMPTED TO RETRACT LG AFTER TAKEOFF & DID NOT GET LG UP & LOCKED INDICATION. PILOT ATTEMPTED TO CYCLE LG & WAS UNABLE TO CYCLE GEAR TO THE UP & LOCKED POSITION. PILOT ENSURED LG WAS DOWN & LOCKED & LANDED BACK AT HOME BASE.
- [SDR YN8R2014042400002](https://openairdocs.org/sdr/YN8R2014042400002.md): Fitting · corroded · Apr 24, 2014 · N425BA · Cessna 425 · Wing, Attach Fittings
  > DURING SID INSPECTION, CORROSION WAS FOUND ON THE LOWER SURFACE OF THE RT FWD WING SPAR LUG FITTING. REPLACED WITH NEW FITTING.
- [SDR YN8R2014042400001](https://openairdocs.org/sdr/YN8R2014042400001.md): Fitting · cracked · Apr 24, 2014 · N425BA · Cessna 425 · Wing, Attach Fittings
  > DURING SID INSPECTION AND SUPPLEMENTAL INSPECTION DOCUMENT 57-10-20, A CRACK WAS FOUND BY EDDY CURRENT INSPECTION IN THE LT AFT WING FITTING. THE CRACK WAS COMING FROM THE INBD AFT BOLT HOLE. NEW FITTING WAS INSTALLED.
- [SDR CA140313011](https://openairdocs.org/sdr/CA140313011.md): Actuator · failed · Feb 28, 2014 · Cessna 425 · Landing Gear Actuator
  > (CAN) THE NLG COLLAPSED ON THE LANDING ROLLOUT, INITIAL FAILURE POSSIBLY DUE TO NOSE GEAR ACTUATOR FAILING TO LOCK, PILOT NOTES THAT HE HAD 3 GREEN INDICATION LIGHTS OF GEAR DOWN AND LOCKED AND THE HYDRAULIC PRESSURE ANNUNCIATOR LIGHT WAS OUT INDICATING HYDRA
- [SDR CA131105005](https://openairdocs.org/sdr/CA131105005.md): Engine · surges · Oct 29, 2013 · Cessna 425 · Engine (Turbine/Turboprop)
  > (CAN) THE PILOT REPORTED AN ENGINE SURGE DURING THE TRANSIT DECENT.
- [SDR FEHR2013FA0000595](https://openairdocs.org/sdr/FEHR2013FA0000595.md): Tube · melted · Oct 18, 2013 · N425DH · Cessna 425 · Navigation System
  > PLASTIC INSTRUMENT AIR TUBE UNDER CO-PILOT'S SEAT MELTED AND SPLIT OPEN. THE CAUSE WAS THE LT BLEED AIR FLOW CONTROL VALVE ALLOWING HIGHER THAN NORMAL TEMPERATURE AIR TO ENTER THE SYSTEM. SB CQB05-1 COVERS THIS PROBLEM BY HAVING YOU INSTALL TEMPERATURE RECORD
- [SDR YN8R201307120001](https://openairdocs.org/sdr/YN8R201307120001.md): Door Frame · cracked · Jul 12, 2013 · N1227J · Cessna 425 · Fuselage Main, Structure
  > FOUND APPROXIMATELY 4 INCH CRACK IN RADIUS OF LOWER CABIN DOOR FRAME AT AFT HINGE.
- [SDR GNMA20130528001](https://openairdocs.org/sdr/GNMA20130528001.md): Engine · low torque · May 28, 2013 · N425RM · Cessna 425 · Engine (Turbine/Turboprop)
  > PILOT PERFORMED PRE-FLIGHT CHECKS AND ALL OPERATIONS GOOD. ACFT STARTED DOWN RUNWAY AND LT ENGINE STARTED TO AUTOFEATHER AND ENGINE WOULD NOT GO TO FULL POWER. TAKEOFF WAS ABORTED AND ACFT WAS GROUNDED FOR FURTHER INVESTIGATION OF ENGINE DISCREPANCY.
- [SDR YN8R04112013BH](https://openairdocs.org/sdr/YN8R04112013BH.md): Oil Filter · ruptured · Apr 11, 2013 · N818PL · Cessna 425 · Engine Oil Distribution (Airframe Furnished)
  > DURING INSPECTION, FOUND LT ENGINE OIL FILTER, TO HAVE FAILED. THE INNER FINGER SCREEN WAS OPEN AT THE END ALLOWING OIL TO BYPASS THE FILTER. LAST FILTER REPLACEMENT WAS 7-13-2010 AT 9394.0 HOURS. LAST OIL CHANGE WAS 08-19-2012 AT 9782.4 HOURS.
- [SDR 2012FA0000746](https://openairdocs.org/sdr/2012FA0000746.md): Flapper Valve · broken · Nov 2, 2012 · N425RM · Cessna 425 · Aircraft Fuel System
  > RIGHT INTERTIA SEPARATOR LOWER AFT VANE BROKEN. RT FUEL FILLER FLAPPER VALVE BROKEN.
- [SDR GNMA2012103100002](https://openairdocs.org/sdr/GNMA2012103100002.md): Hinge · damaged · Oct 30, 2012 · N425RM · Cessna 425 · Nacelle/Pylon Miscellaneous Structure
  > RIGHT HAND COWL FLAP HINGE DAMAMGED.
- [SDR GNMA6640C032712](https://openairdocs.org/sdr/GNMA6640C032712.md): Engine · overtemp · Mar 27, 2012 · N6640C · Cessna 425 · Engine (Turbine/Turboprop)
  > ACFT DEPARTED AND ON DECENT THE RT ENGINE WAS ABRUPT AND VIBRATED. PILOT NOTICED AN INCREASE ON THE INTER-TURBINE TEMPERATURE AND A DECREASE IN ENGINE TORQUE. ENGINE WAS SHUTDOWN AS A PRECAUTIONARY ACTION AND RETURNED TO DEPARTURE AIRPORT WHICH WAS WITHIN 10
- [SDR BIGA2012FA0000128](https://openairdocs.org/sdr/BIGA2012FA0000128.md): O-Ring · leaking · Feb 23, 2012 · N700WJ · Cessna 425 · Master Cylinder/Brake Valve
  > AFTER RETURNING TO DEPARTURE, THE PILOT LOST FULL BRAKING POWER ON THE LT BRAKE AND REPORTED A "SPONGY" CONDITION AND WAS UNABLE TO PUMP UP BRAKE PRESSURE. THE ACFT LEFT MASTER CYLINDER WAS REMOVED AND DISASSEMBLED FOR INSPECTION. THE BRAKE FLUID COMING OUT
- [SDR BIGA2012022301](https://openairdocs.org/sdr/BIGA2012022301.md): Master Cylinder · worn · Feb 20, 2012 · N700WJ · Cessna 425 · Master Cylinder/Brake Valve
  > AFTER RETURNING THE PILOT REPORTED A "SPONGY" LEFT BRAKE AND REDUCED BRAKING DURING TAXI. THE MASTER CYLINDER WAS DISASSEMBLED. THE FLUID OUT OF THE CYLINDER WAS BLACK AND APPEARED TO HAVE BLACK O-RING MATERIAL CONTAMINATING THE FLUID. THE MASTER CYLINDER W
- [SDR CA110803006](https://openairdocs.org/sdr/CA110803006.md): Engine · malfunctioned · Jul 20, 2011 · Cessna 425 · Engine (Turbine/Turboprop)
  > (CAN) DURING REPOSITIONING FLIGHT, THE PILOT NOTED ITT, WF AND NG ALL INCREASING AT FL 270. THE PILOT RETARDED PLA WITH NO RESPONSE. PILOT ELECTED TO SHUTDOWN THE ENGINE AND MADE AN UNEVENTFUL SINGLE ENGINE LANDING. ENGINE IS BEING REMOVED FOR ITT EXCEEDANC
- [SDR YN8R11136](https://openairdocs.org/sdr/YN8R11136.md): Master Switch · defective · Aug 11, 2010 · N828SG · Cessna 425 · DC Power Distribution System
  > AVIONICS MASTER SWITCH WAS FOUND INOP UPON FUNCTIONAL CHECK. PART HAS BEEN RED TAGGED AND REPLACED WITH NEW SWITCH. PART WAS DISASSEMBLED AND UPON FURTHER INSPECTION APPEARS TO HAVE A MFG DEFECT.
- [SDR UVVR2010060900013](https://openairdocs.org/sdr/UVVR2010060900013.md): Skin · corroded · Jun 9, 2010 · N111KU · Cessna 425 · Fuselage Main, Plate/Skin
  > (UVVR) EXTERIOR SIDE OF OF FUESELAGE, TOP SKIN CORRODED FS 200.75 TO FS 212.87, BL6R TO BL9.5R. FOUND UPON REMOVAL OF VHF COMMUNICATIONS ANTENNA, MM, ZONE 252.
- [SDR UVVR2010060900012](https://openairdocs.org/sdr/UVVR2010060900012.md): Skin · corroded · Jun 9, 2010 · N111KU · Cessna 425 · Fuselage Main, Plate/Skin
  > (UVVR) EXTERIOR SIDE OF FUSELAGE BOTTOM SKINS CORRODED FS 307.94 - FS 316.94, BL2L TO BL3R. FOUND UPON REMOVAL OF STORMSCOPE ANTENNA, MM, ZONE 311 &N 312.
- [SDR UVVR2010060800011](https://openairdocs.org/sdr/UVVR2010060800011.md): Fork · cracked · Jun 7, 2010 · N111KU · Cessna 425 · Nose/Tail Landing Gear Strut/Axle
  > ((UVVR)) WHILE PERFORMING SUPPLEMENTARY INSPECTION DOCUMENT NR 32-20-02 A.25" CRACK WAS FOUND IN THE RT AXLE BORE OF THE NLG FORK ASSY.
- [SDR UVVR2010060700010](https://openairdocs.org/sdr/UVVR2010060700010.md): Fitting · cracked · Jun 7, 2010 · N111KU · Cessna 425 · Engine Mount Section
  > RT ENGINE OTBD ENGINE MOUNT FITTING WAS FOUND CRACKED APPROX.20 INCHES IN LENGTH DURING INSPECTION.
- [SDR UVVR2010060700009](https://openairdocs.org/sdr/UVVR2010060700009.md): Fitting · cracked · Jun 7, 2010 · N111KU · Cessna 425 · Engine Mount Section
  > RT ENGINE INBD ENGINE MOUNT FITTING WAS FOUND CRACKED APPROX.30 INCHES IN LENGTH DURING INSPECTION.
- [SDR UVVR2010060200008](https://openairdocs.org/sdr/UVVR2010060200008.md): Skin · corroded · Jun 2, 2010 · N111KU · Cessna 425 · Wing, Plate/Skin
  > ((UVVR)) RT OTBD WING L/E SKIN CORRODED UNDER AERODYNAMIC FILLER AT SKIN SPLICE SEAM JUST OTBD OF NACELLE STRUCTURE. CORROSION IS AT LEVEL 3. IT APPEARS THAT MOISTURE HAS SEEPED UNDER DEICE BOOT AT SKIN SPLICE SEAM WHERE THE 2 SECTIONS OF L/E ARE SPLICED TOG
- [SDR CA091021009](https://openairdocs.org/sdr/CA091021009.md): Skin · chafed · Oct 19, 2009 · Cessna 425 · Trailing Edge Flaps
  > (CAN) RT FLAP TRAILING EDGE, NEAR INBOARD SIDE HAS CAUSED CHAFING DAMAGE TO THE WING SKIN WHERE FLAP RETRACTS. LOCAL REPAIR REQUIRED. (TC 20091021009)
- [SDR CA091021008](https://openairdocs.org/sdr/CA091021008.md): Bracket · cracked · Oct 19, 2009 · Cessna 425 · Horizontal Stabilizer Miscellaneous Structure
  > (CAN) WHILE PERFORMING AN EDDY CURRENT INSPECTION TO COMPLY WITH A PHASE 31 SID INSPECTION, A CRACK WAS DETECTED IN THE OUTBOARD BRACKET THAT ATTACHES THE RT ELEVATOR TO THE H STAB. THE CRACK WAS NOT DETECTABLE VISUAL INSPECTION ALONE. (TC 20091021008)
- [SDR CA091021007](https://openairdocs.org/sdr/CA091021007.md): Plate · corroded · Oct 19, 2009 · Cessna 425 · Nacelle/Pylon, Plate/Skin
  > (CAN) DURING DISASSEMBLY OF THE LT NACELLE TO FACILITATE A SID PHASE 32 INSPECTION, IT WAS DISCOVERED THAT THE PLATE CONNECTING THE LT OUTBOARD TRUSS ASSEMBLY TO THE TOP OF THE LT WING SKIN WAS CORRODED. AFTER REMOVING THE CORROSION, THERE WERE PITS LEFT IN T
- [SDR CA090826004](https://openairdocs.org/sdr/CA090826004.md): Nut · missing · Jul 16, 2009 · Cessna 425 · Miscellaneous Hardware
  > CLEVIS BOLT NOT SECURED. RETAINING NUT IS MISSING (AND COULD NOT BE LOCATED IN ACFT) CLEVIS BOLT DID NOT COMPLETLEY SEPARATE FROM THE CLEVIS HSG (ITEM NR 32).
- [SDR CA090826003](https://openairdocs.org/sdr/CA090826003.md): Control Cable · misinstalled · Jul 16, 2009 · Cessna 425 · Rudder Control System
  > BOTH LT AND RT RUDDER CABLES NOT INSTALLLED CORRECTLY. PASSING OVER THE GUARD PINS INSTEAD OF THROUGH THE PULLEYS, RESULTING IN SEVERE CABLE CHAFING. THE LT GUARD PIN FAILED UNDER STRESS AND THUS REDUCING CABLE TENSION. THE RT GUARD PIN REMAINED INTACT, ABB
- [SDR CA090826005](https://openairdocs.org/sdr/CA090826005.md): Retaining Clip · missing · Jul 15, 2009 · Cessna 425 · Autopilot System
  > TURNBUCKLE CLIP WAS NOT ON TURN BUCKLE ALLOWING THE LOWER TURNBUCKLE TO UNSCREW AND SEPARATE FROM THE LWR CLEVIS INFLIGHT INDICATION WAS `PORPOSING O AUTOPILOT IN CRUISE`.
- [SDR 2009FA0000558](https://openairdocs.org/sdr/2009FA0000558.md): Attach Fitting · corroded · Jun 23, 2009 · N425DM · Cessna 425 · Wing, Attach Fittings
  > RT LOWER FWD WING FITTING HAS CORROSION. REPLACE FITTING WITH NEW PART.
- [SDR 2009FA0000557](https://openairdocs.org/sdr/2009FA0000557.md): Attach Fitting · corroded · Jun 23, 2009 · N425DM · Cessna 425 · Wing, Attach Fittings
  > LT LWR FWD WING FITTING IS CORRODED AND HAS OBLONG HOLE - REPLACE FITTING WITH NEW PART.
- [SDR 2009FA0000556](https://openairdocs.org/sdr/2009FA0000556.md): Cable · frayed · Jun 23, 2009 · N425DM · Cessna 425 · Aileron Control System
  > RT WING UPPER AILERON CABLE HAS BROKEN STRANDS. INSTALLED NEW CABLE PN 5000008-94CR.
- [SDR 2009FA0000555](https://openairdocs.org/sdr/2009FA0000555.md): Cable · frayed · Jun 23, 2009 · N425DM · Cessna 425 · Trailing Edge Flap Control System
  > LT UPPER FLAP CABLE HAS SEVERAL BROKEN STRANDS. INSTALLED NEW CABLE PN 5000008-61CR.
- [SDR 2009FA0000554](https://openairdocs.org/sdr/2009FA0000554.md): Spar Cap · damaged · Jun 23, 2009 · N425DM · Cessna 425 · Wing Spar
  > LT WING AFT TRUSS PLATE ATTACH HOLES ARE DRILLED TO LARGE IN TRUSS PLATE AND IN AFT SPAR CAP AT WING STATION 102.1. DETERMINED TO HAVE OCCURRED DURING PRODUCTION. OBTAINED DER APPROVAL FOR DISPOSITION.
- [SDR 2009FA0000553](https://openairdocs.org/sdr/2009FA0000553.md): Coupling · deteriorated · Jun 23, 2009 · N425DM · Cessna 425 · Aircraft Fuel Distribution System
  > LT AND RT NACELLE TO WING FUEL COUPLINGS ARE DETERIORATED, INSTALLED NEW COUPLINGS.
- [SDR 2009FA0000552](https://openairdocs.org/sdr/2009FA0000552.md): Mount · corroded · Jun 23, 2009 · N425DM · Cessna 425 · Engine Mount Section
  > RT LWR OTBD ENGINE MOUNT WING FITTING IS CORRODED- INSTALL SERVICEABLE PART.

Next page: https://openairdocs.org/model/cessna-425/reports.md?page=2

## 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 aircraft_model_key = '425'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/cessna-425/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.