# Service difficulty reports: Cessna T210M

A list on [Cessna T210M](https://openairdocs.org/model/cessna-t210m.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 3 · 110 reports

- [SDR 2024FA0000268](https://openairdocs.org/sdr/2024FA0000268.md): Cylinder Head · separated · Mar 15, 2024 · N732SE · Cessna T210M · Reciprocating Engine Cylinder Section
  > THE PILOT REPORTED A LOSS OF MANIFOLD PRESSURE IN FLIGHT ALONG WITH A REDUCTION IN POWER AND CRUISE SPEED. THE AIRCRAFT SAT UNTIL THE 28TH OF MARCH AWAITING MAINTENANCE. UPON INVESTIGATION, THE CYLINDER HEAD WAS FOUND TO HAVE SEPARATED FROM THE CYLINDER BODY A
- [SDR 2020FA0000377](https://openairdocs.org/sdr/2020FA0000377.md): Ring · broken · Aug 18, 2020 · N761PM · Cessna T210M · AC Generator-Alternator
  > ELECTRICAL SYSTEM FAILURE. FOUND BROKEN RING TERMINAL AT POSITIVE TERMINAL OF ALTERNATOR. FOUND VOLTAGE REGULATOR INOP.
- [SDR 2020FA0000335](https://openairdocs.org/sdr/2020FA0000335.md): Not Reported · corroded · Jul 15, 2020 · N68BM · Cessna T210M · Propeller Assembly
  > EXTREME CORROSION FOUND ON PARTS INSIDE PROP HUB POST OVERHAUL WITH LESS THAN 40 HOURS FROM OVERHAUL. OPERATOR SUSPECTS UNAPPROVED PARTS MAY HAVE BEEN USED AND REPLACEMENT KIT PARTS NOT REPLACED IAW MANDATORY REPLACEMENT KIT MANUAL PROCEDURES.
- [SDR SQPA20190919002](https://openairdocs.org/sdr/SQPA20190919002.md): Bolt · missing · Aug 13, 2019 · N732DW · Cessna T210M · Nose/Tail Landing Gear Strut/Axle
  > NOSE GEAR CAME LOOSE FROM NOSE GEAR FORK. NOSE GEAR BOLT FORK FOUND TO BE MISSING. NO WORK RECENTLY PERFORMED ON NOSE GEAR. NO EMERGENCY MEASURES TAKEN. NO ADS, SBS, STCS OR ICA'S APPLY. BOLT WAS NOT FOUND POST EVENT. SUGGEST PREFLIGHT INSPECTION TO ENSURE BOL
- [SDR SQPA20190919001](https://openairdocs.org/sdr/SQPA20190919001.md): Door · buckled · Aug 13, 2019 · N73TG · Cessna T210M · Landing Gear Doors
  > LT GEAR DOOR BUCKED IN FLIGHT. SUSPECT GEAR DOOR WAS DAMAGED DUE TO OVERSPEED. NO WORK RECENTLY PERFORMED ON LANDING GEAR. NO EMERGENCY ACTIONS TAKEN. NO APPLICABLE ADS, SBS, STCS OR ICAS. SUGGEST VISUAL INSPECTION OF ADHESIVE ATTACHING STRUCTOR TO DOOR EVERY
- [SDR NF2R201812210002](https://openairdocs.org/sdr/NF2R201812210002.md): Lifter · galled · Apr 16, 2015 · N15DA · Cessna T210M · Reciprocating Engine Cylinder Section
  > #1 CYLINDER LOW COMPRESSION 59/80 LEAKING THROUGH EXHAUST VALVE. FOUND LIFTERS SHOWING PITTING AND STRESS.
- [SDR 2014FA0000074](https://openairdocs.org/sdr/2014FA0000074.md): Spar · loose · Feb 14, 2014 · N761GQ · Cessna T210M · Wing Spar
  > DURING ANNUAL INSPECTION, FOUND MOVEMENT IN THE RT WING SPAR FITTINGS, BETWEEN THE RT WING MAIN SPAR ATTACH BRACKETS AND THE FUSELAGE CARRY-THROUGH SPAR ATTACH BRACKETS.
- [SDR 2014FA0000046](https://openairdocs.org/sdr/2014FA0000046.md): Lifter · spalled · May 13, 2013 · N732YK · Cessna T210M · Reciprocating Engine Power Section
  > TWO SPALLED EXHUAST LIFTERS WHICH DAMAGE CAM.
- [SDR 2012FA0000716](https://openairdocs.org/sdr/2012FA0000716.md): Pump · leaking · Oct 22, 2012 · N7072 · Cessna T210M · Engine Fuel Pump
  > PILOT WROTE-UP "FUEL FLOW METER INOP" DURING INITIAL START-UP. FOUND NO OR VERY LOW FUEL FLOW INDICATION AT IDLE BUT ENGINE RAN NORMAL, FOUND NORMAL FUEL FLOW INDICATION AT MID TO HIGH POWER SETTINGS WITH ENGINE RUNNING NORMALLY. FOUND GAUGE TO BEOPERATING PRO
- [SDR 2012FA0000672](https://openairdocs.org/sdr/2012FA0000672.md): Engine · power loss · Oct 2, 2012 · N6181N · Cessna T210M · Engine (Turbine/Turboprop)
  > DURING A FINAL APPROACH, PILOT APPLIED THROTTLE TO ARREST HIS SINK RATE BUT THE ENGINE DID NOT RESPOND. POST ACCIDENT INVESTIGATION REVEALED AT LEAST 5 GALLONS WAS AVAILABLE IN EACH WING TANK.
- [SDR 2011FA0000797](https://openairdocs.org/sdr/2011FA0000797.md): Housing · worn · Dec 8, 2011 · N732YK · Cessna T210M · Flight Compartment Equipment
  > COPILOT SEAT ROLLER HOUSING TANG LENGTH WORN BELOW LIMIT OF AD 2011-10-09.
- [SDR 2011FA0000437](https://openairdocs.org/sdr/2011FA0000437.md): Contactor · inoperative · Jul 2, 2011 · N732YK · Cessna T210M · Battery/Charger System
  > BATTERY CONTACTOR FAILED TO OPEN WHEN DEENERGIZED BY MASTER SWITCH.
- [SDR 2010FA0001164](https://openairdocs.org/sdr/2010FA0001164.md): Camshaft · worn · Nov 3, 2010 · N761BT · Cessna T210M · Reciprocating Engine Power Section
  > WORN CAMSHAFT (PN 655384, SN 34962) DISCOVERED DURING CYLINDER CHANGE (LOW COMPRESSION) CYLINDERS NR3 & NR4 INTAKE LOBES ONLY. NEW LIFTERS WERE INSTALLED WITH THE NEW CAMSHAFT AT INSTALLATION. INITIATOR STATES THIS HAS BEEN A PROBLEM MORE THAT A FEW TIMES. MF
- [SDR 2010FA0001170](https://openairdocs.org/sdr/2010FA0001170.md): Hub · failed · Oct 28, 2010 · N732XF · Cessna T210M · Wheel/Ski/Float
  > RT MAIN WHEEL HUB BROKE ON LANDING, AFTER NORMAL TOUCHDOWN WITH NO BRAKING. BROKEN AREA OF WHEEL HAS CORROSION AT BOTTOM OF THREADS. WHEEL TURNED SIDEWAYS DAMAGING BRAKE TORQUE PLATE AXEL AND BRAKE LINE.
- [SDR 2010FA0001215](https://openairdocs.org/sdr/2010FA0001215.md): Fitting · broken · Oct 4, 2010 · N6689B · Cessna T210M · Reciprocating Engine Oil System
  > (GBBR) THE ENGINE SUFFERED CATASTROPHIC FAILURE DUE TO ENGINE OIL STARVATION CAUSED BY THE FAILURE/BREAKAGE OF THE TURBOCHARGER OIL RETURN LINE FITTING AT THE REAR OF THE ENGINE. THE LOSS OF ENGINE OIL ULTIMATELY RESULTED IN AN UNCONTAINED FAILURE OF THE NR4
- [SDR GBBR155E](https://openairdocs.org/sdr/GBBR155E.md): Fitting · broken · Sep 24, 2010 · N6689B · Cessna T210M · Turbine Engine Oil System
  > (GGBR) THE ENGINE SUFFERED CATASTROPHIC FAILURE DUE TO ENGINE OIL STARVATION CAUSED BY THE FAILURE/BREAKAGE OF THE TURBOCHARGER RETURN OIL LINE FITTING AT THE REAR OF THE ENGINE. THE LOSS OF ENGINE OIL ULTIMATELY RESULTED IN THE UNCONTAINED FAILURE OF THE NR 4
- [SDR J7B2010F00001](https://openairdocs.org/sdr/J7B2010F00001.md): Cylinder · leaking · Aug 13, 2010 · N761ST · Cessna T210M · Reciprocating Engine Cylinder Section
  > CYLINDER ASSY IS LEAKING. FUEL, EXHAUST, AND OIL STAIN BETWEEN CYLINDER BARREL AND HEAD. OCCURRED UNDER NORMAL USAGE.
- [SDR J7B2010F00000](https://openairdocs.org/sdr/J7B2010F00000.md): Cylinder · leaking · Aug 13, 2010 · N761ST · Cessna T210M · Reciprocating Engine Cylinder Section
  > CYLINDER ASSY IS LEAKING. FUEL, EXHAUST, AND OIL STAIN BETWEEN CYLINDER BARREL AND HEAD. OCCURRED UNDER NORMAL USAGE.
- [SDR 2010FA0000756](https://openairdocs.org/sdr/2010FA0000756.md): Check Valve · failed · Jul 17, 2010 · N734JC · Cessna T210M · Exhaust Turbocharger
  > P/N S2361-1, LOT 60507, OIL CHECK VALVE FROM TURBOCHARGER, INSTALLED NEW ON 12 APRIL 2010, 60 HOURS IN SERVICE PRIOR TO FAILURE. RECEIVED "LOW OIL PRESSURE" ALERT FROM AURACLE 2100 SYSTEM, IMMEDIATELY TURNED TO NEAREST AIRPORT (KDTS) AND MADE EMERGENCY LANDIN
- [SDR 2009FA0000791](https://openairdocs.org/sdr/2009FA0000791.md): Line · corroded · Jun 17, 2009 · N761BT · Cessna T210M · Aircraft Fuel Distribution System
  > INSP FOUND MINOR FUEL LEAK AT THE FWD FUEL LINE WHERE IT COMES IN CONTACT WITH FRESH AIR VENT DUCTING LOACTED IN WING L/E. AIR DUCTING CAUSES CORROSION PITS TO FORM. LINE WAS REPLACED. INSPECTED (5) OTHER SIMULAR ACFT AND FOUND SAME RESULTS IN ALL EXCEPT (1
- [SDR 2009FA0000005](https://openairdocs.org/sdr/2009FA0000005.md): Hose · burst · Dec 23, 2008 · N732UR · Cessna T210M · Hydraulic System, Main
  > RT NLG DOOR ACTUATOR HOSE FAILED CAUSING COMPLETE HYD FLUID LOSS. RESULTING IN LT MAIN GEAR NOT ABLE TO BE FULLY EXTENDED TO DOWN AND LOCKED POSITION. ACFT MADE EMERGENCY LANDING WITH LT MAIN GEAR PARTIALLY EXTENDED. MINOR DAMAGE. FAILED HOSE APPEARS TO BE
- [SDR GAJ2008F00000](https://openairdocs.org/sdr/GAJ2008F00000.md): Pulley · frozen · Aug 25, 2008 · N7067Z · Cessna T210M · Flight Control System
  > THE COPILOT RETRACTABLE STEP MALFUNCTIONED DUE TO PULLEYS FREEZING. FWD PULLEY IS HARD TO SEE ON AFT NOSE GEAR WELL AND IS IN A VERY DIRTY ENVIRONMENT. THE REAR PULLEY IS IMPOSSIBLE TO SEE. THE REAR PULLEY STOPPED ROTATING (FROZE) CAUSING SEVERE WEAR TO THE CA
- [SDR 2008FA0000085](https://openairdocs.org/sdr/2008FA0000085.md): Line · chafed · Feb 21, 2008 · N761AV · Cessna T210M · Hydraulic System, Main
  > REPLACED HYDRAULIC TUBE (PN 128509-4) DUE TO CHAFFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE. THIS WAS FOUND BY INSPECTION AS DESCRIBED IN SEB07-03 FOR 182 SERIES, AND WHICH 182'S HAVE A SUPERSEDED PN AVAILABLE TO NULLIFY THE POTENTIAL PR
- [SDR 2008FA0000084](https://openairdocs.org/sdr/2008FA0000084.md): Line · chafed · Feb 21, 2008 · N761AV · Cessna T210M · Hydraulic System, Main
  > REPLACED HYDRAULIC TUBE 128509-4 DUE TO CHAFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE. THIS WAS FOUND BY INSPECTION AS DESCRIBED IN MFG SEB07-03 AND WHICH HAVE A SUPERSEDED PN AVAILABLE TO NULLIFY THE POTENTIAL PROBLEM. THIS SERIES AND
- [SDR 2007FA0000817](https://openairdocs.org/sdr/2007FA0000817.md): Alternator · failed · Sep 17, 2007 · N732YK · Cessna T210M · DC Generator-Alternator
  > OVERHAULED DOFF10300B ALTERNATOR FAILED AFTER 458 HOURS IN 35 MONTHS OF USE.
- [SDR 2007FA0000572](https://openairdocs.org/sdr/2007FA0000572.md): Bearing · broken · May 25, 2007 · N808FS · Cessna T210M · Rudder Control System
  > WHILE PERFORMING RUN UP OF AIRCRAFT DURING ANNUAL INSPECTION IT WAS NOTICED THAT PILOT RT RUDDER PEDAL HAD AN UNUSUAL FEEL WHILE BRAKING. DURING THE INSPECTION OF THE RUDDER PEDALS IT WAS FOUND THT THE EACH OF THE PILOT SIDE S1675-1 RUDDER IB BEARING HALF HAD
- [SDR 2006FA0001163](https://openairdocs.org/sdr/2006FA0001163.md): Cable · broken · Aug 23, 2006 · N6169N · Cessna T210M · Entrance Stairs
  > THE PILOT EXTENDED THE LANDING GEAR PRIOR TO LANDING, AND THE NOSEGEAR WOULD NOT EXTEND INTO THE DOWN-AND-LOCKED POSITION (THE MAINS LOCKED). DURING LANDING, THE NOSEGEAR COLLAPSED. POST INCIDENT INSPECTION SHOWED THAT THE PASSENGER STEP CABLE BROKE AT THE F
- [SDR 2006FA0000426](https://openairdocs.org/sdr/2006FA0000426.md): Alternator · failed · Apr 12, 2006 · Cessna T210M · DC Generator-Alternator
  > ALTERNATOR FAILED, PLATE SCREWS FELL OUT. (K)
- [SDR 2005FA0001645](https://openairdocs.org/sdr/2005FA0001645.md): Probe · failed · Dec 29, 2005 · Cessna T210M · Engine Indicating System
  > OUTSIDE AIR TEMP PROBE FAILED SELF TEST INDICATING OPEN.
- [SDR 2005R0124](https://openairdocs.org/sdr/2005R0124.md): Altimeter · binds · Jun 28, 2005 · N732XE · Cessna T210M · Altimeter, Barometric/Encoder
  > ALTIMETER HANDS ARE BENT & INTERFERE WITH EACH OTHER.
- [SDR 2005FA0000836](https://openairdocs.org/sdr/2005FA0000836.md): Circuit Board · loose · Jun 1, 2005 · N6033N · Cessna T210M · Flight Control System Wiring
  > ELECTRIC PITCH TRIM SYSTEM RAN AWAY ON APPROACH. AUTOPILOT/ TRIM DISCONNECT HAD NO EFFECT. PILOT DISENGAGED PITCH TRIM CIRCUIT BREAKER TO STOP THE RUNAWAY. AFTER THE CIRCUIT BREAKER WAS DISENGAGED, THE CONTROL WHEEL VIBRATED ON THE APPROACH AT APPROXIMATELY
- [SDR 2005FA0000024](https://openairdocs.org/sdr/2005FA0000024.md): Bolt · loose · Jan 17, 2005 · N732YK · Cessna T210M · Fasteners
  > 3 OF THE 4 BOLTS THAT ATTACH THE METAL PLATE THAT THE ACTUATOR IS MOUNTED ON TO THE WASTEGATE BODY WERE MISSING. FOURTH BOLT WAS BACKED OUT ABOUT HALF WAY. ALL THREE BOLTS FOUND LOOSE IN ENGINE COMPARTMENT. WASTEGATE ASSEMBLY ONLY 287 FROM OVERHAUL BY MAIN
- [SDR 2005FA0000444](https://openairdocs.org/sdr/2005FA0000444.md): Exhaust Valve · broken · Dec 23, 2004 · N761QK · Cessna T210M · Reciprocating Engine Cylinder Section
  > PILOT REPORTED HEARING A BANG AND NOTICED AN ENGINE VIBRATION AND REDUCTION IN TEMPERATURE ON HIS ENGINE MONITOR. PILOT REPORTED AN EMERGENCY TO ATC AND MADE A SAFE LANDING AT AIRPORT. MAINTENANCE PERFORMED AN ENGINE COMPRESSION TEST AND FOUND CYLINDER NR 1
- [SDR 2005FA0001298](https://openairdocs.org/sdr/2005FA0001298.md): Alternator · failed · Dec 9, 2004 · N732YK · Cessna T210M · AC Generation System
  > OVERHAULED ALTERNATOR FAILED IN FLIGHT AFTER 351 HOURS IN SERVICE.
- [SDR 2004FA0000807](https://openairdocs.org/sdr/2004FA0000807.md): Exhaust Valve · burned · Oct 17, 2004 · N732YK · Cessna T210M · Reciprocating Engine Power Section
  > EXHAUST VALVE LEAKAGE ON COMPRESSION CHECK. BURNED VALVE VERIFIED BORESCOPE INSPECTION. VALVE STEM AND GUIDE WORN BEYOND SERVICE LIMITS.
- [SDR 2004FA0000659](https://openairdocs.org/sdr/2004FA0000659.md): Fuel Strainer · loose · Jun 30, 2004 · N8159M · Cessna T210M · Aircraft Fuel Filter/Strainer
  > AD 2000-06-01 HAS STAND PIPE MEASUREMENT AT 1.68 INCHES. FOUND STAND PIPE LONG AT 1.75.6. REPLACED WITH NEW FUEL STRAINER WITH STAND PIPE AT 1.68 (AT FLIGHT ICE FOUND STAND PIPE LOOSE ON OTHER AND LIKE AIRCRAFT. AC; 8159 TT 3667.
- [SDR 06282004](https://openairdocs.org/sdr/06282004.md): Retaining Ring · worn · Jun 28, 2004 · N121JR · Cessna T210M · Landing Gear Door Actuator
  > A RETAINING RING SEPERATED FROM THE LT MAIN LANDING GEAR DOOR HYDRAULIC ACTUATOR. THIS LEAD TO A LOSS OF HYDRAULIC FLUID AND FAILURE OF THE LANDING GEAR SYSTEM. AIRCRAFT WAS FORCED TO LAND WITH THE NOSE GEAR EXTENDED AND NO MAIN WHEELS. PILOT REPORTED THAT T
- [SDR 2004FA0000800](https://openairdocs.org/sdr/2004FA0000800.md): Latch · failed · Jun 3, 2004 · N7568M · Cessna T210M · Engine Air Intake System
  > DURING THE ANNUAL INSPECTION, FOUND THE PN 1250938-8, MAGNET LATCH ON THE ALTERNATE AIR DOOR WITH ONE OF ITS STEEL BONDED PLATES LOOSE AND READY TO FALL INTO THE TURBO, COULD CAUSE INFLIGHT FAILURE. INSTALLED THE NEW IMPROVED CATCH PN C100200. RECOMMEND MAND
- [SDR 2004FA0000770](https://openairdocs.org/sdr/2004FA0000770.md): Plate · separated · Jun 3, 2004 · N732WP · Cessna T210M · Engine Air Intake System
  > ENGINE ALTERNATE AIR DOOR IS HELD CLOSED WITH A MAGNETIC LATCH ORIGINAL PN 1250938-8. THE MAGNETIC LATCH HAS 2 STEEL SMALL PLATES BONDED TO THE MAGNET THAT MAKE CONTACT WITH THE ALTERNATE AIR DOOR. ONE STEEL PLATE CAME DEBONDED FROM AGE VIBRATION. PLATE WAS
- [SDR PO82004F00000](https://openairdocs.org/sdr/PO82004F00000.md): Alternator · failed · Mar 1, 2004 · N6246B · Cessna T210M · DC Generator-Alternator
  > ALTERNATOR FAILED INFLIGHT AFTER 134 HOURS TSO. UNIT SENT OUT TO A CERTIFIED REPAIR STATION FOR REPAIR. TEARDOWN REPORT STATED ONE BAD BEARING AND A FAILED STATOR. PREVIOUS OVERHAULED ALTERNATOR LASTED FIVE MINUTES BEFORE AND THE OVERHAULED UNIT PRIOR TO TH
- [SDR FPI2004F00001](https://openairdocs.org/sdr/FPI2004F00001.md): Distributor Gear · loose · Feb 17, 2004 · N7398M · Cessna T210M · Magneto/Distributor
  > DISTRIBUTOR GEAR FINGER LOOSENED UP AT SHAFT.
- [SDR 2004FA0000021](https://openairdocs.org/sdr/2004FA0000021.md): Vernatherm · failed · Dec 26, 2003 · N732YK · Cessna T210M · Engine Oil Indicating System
  > VERNATHERM FAILED TO BYPASS OIL COOLER WHEN OIL TEMPS LOW.
- [SDR 2003FA0001119](https://openairdocs.org/sdr/2003FA0001119.md): Exhaust Valve · worn · Sep 19, 2003 · N732YK · Cessna T210M · Reciprocating Engine Cylinder Section
  > CYLINDER FAILED COMPRESSION CHECK DUE TO EXHAUST VALVE LEAKAGE. VISUAL INSPECTION REVEALED BURNED EXHAUST VALVE WITH NO SIGNS OF OVER TEMP OR CARBON BUILD UP. VALVE STEM AND GUIDE WORN BEYOND SERVICE LIMITS. EXHAUST VALVES IN CYLINDERS 4 AND 5 EXPERIENCE ID
- [SDR CA030916002](https://openairdocs.org/sdr/CA030916002.md): Points · broken · Sep 15, 2003 · Cessna T210M · Magneto/Distributor
  > (CAN) POINT ASSEMBLY CONTACT ARM FAILED.
- [SDR RCO2003F00000](https://openairdocs.org/sdr/RCO2003F00000.md): Alternator · broken · Jun 6, 2003 · N732XE · Cessna T210M · AC Generator-Alternator
  > WHILE INSTALLING A 135 AMP ALTERNATOR KIT UNDER A STC FROM MFG, IT LOOKED LIKE THE COOLING FAN PN 8-4 HAD A SMALL CRACK IN IT. THIS PULLEY IS A ONE-PIECE CAST ASSEMBLY MADE OF ALUMINUM. WHEN THE ALTERANTOR WAS REMOVED FOR CLOSER INSP, THE PULLEY WAS FOUND TO
- [SDR 2003FA0000360](https://openairdocs.org/sdr/2003FA0000360.md): Alternator · seized · Apr 1, 2003 · N6246B · Cessna T210M · AC Generator-Alternator
  > UPON FIRST START OF THE DAY A LOUD SQUEALING NOISE WAS HEARD ALONG WITH WHITE SMOKE EXITING THE COWL FLAPS AND THE PILOT SHUT DOWN ENGINE. UPON REMOVING THE COWLING IT BECAME OBVIOUS THAT THE ALTERNATOR HAD SEIZED AND THAT THE BELT WAS BADLY BURNED. LATER EXA
- [SDR FLTICE0303002](https://openairdocs.org/sdr/FLTICE0303002.md): Control Panel · erratic · Mar 18, 2003 · N77CF · Cessna T210M · Airfoil Anti/De-ice System
  > CPS-OWNER FOUND THAT THE TKS QUANTITY INDICATOR FLUCTUATES IN FLIGHT FROM 9.8 TO LOWER LEVELS. THIS PROBLEM IS INTERMITTENT. REPLACED QUANTITY INDICATOR.
- [SDR BYK2002F00000](https://openairdocs.org/sdr/BYK2002F00000.md): Turbocharger · fod · Nov 19, 2002 · N761HS · Cessna T210M · Exhaust Turbocharger
  > TOTAL FAILURE OF TURBO CHARGER DURING TAKE OFF ROLL DUE TO THE STEEL STRIP FOR INDUCTION ALTERNATE AIR DOOR MAGNET WEDGED INTO TURBO INLET BLADES. LEADING EDGES OF ALL INTAKE TURBINE BLADES DAMAGED. DISSIMILAR METAL CORROSION OF STEEL STRIP ATTACHMENT ALUMIN
- [SDR 2002FA0000508](https://openairdocs.org/sdr/2002FA0000508.md): Switch · failed · Mar 30, 2002 · N732YK · Cessna T210M · Landing Gear Position and Warning
  > GEAR FAILED TO INDICATE UP AND LOCKED ON RETRACTION.
- [SDR 2001FA0000459](https://openairdocs.org/sdr/2001FA0000459.md): Cylinder · out of tolerance · Sep 28, 2001 · N761RD · Cessna T210M · Reciprocating Engine Cylinder Section
  > CUSTOMER COMPLAINED OF INTERMITTENT ROUGHNESS. REMOVAL OF CYLINDERS REVEALED STICKING INTAKE VALVES. GUIDE TO VALVE TOLERANCE TOO TIGHT, BELOW MFG MINIMUM LIMITS. MFG CLAIMS TOLERANCE TOO TIGHT FROM NORMAL OPERATION. NO BUILD UP NOTED OF ANY KIND ON VALVE

Next page: https://openairdocs.org/model/cessna-t210m/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 = 'T210M'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/cessna-t210m/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.