# Service difficulty reports: Cessna 182P

A list on [Cessna 182P](https://openairdocs.org/model/cessna-182p.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 4 · 179 reports

- [SDR 2026FA0000813](https://openairdocs.org/sdr/2026FA0000813.md): Arm · backed out · Oct 5, 2026 · N7220N · Cessna 182P · Flight Control System
  > NOTED UNUSUAL FEEL IN ELEVATOR CONTROL DURING INSP. PROBLEM DETERMINED TO BE A HEAVY RUB OF THE TORQUE TUBE USED BY THE PITCH SERVO AND THE LOWER ELEVATOR PRIMARY CONTROL CABLE. THE PITCH SERVO CONTROL ARM WAS FOUND TO HAVE ALL FOUR SCREWS THAT SECURE IT TO TH
- [SDR 9WQR202609170736](https://openairdocs.org/sdr/9WQR202609170736.md): Bolt · unsecure · Sep 15, 2026 · N7299 · Cessna 182P · DC Generator-Alternator
  > DURING AN ANNUAL INSPECTION THE ALTERNATOR WAS FOUND TO BE LOOSE BUT STILL WEDGED IN THE MOUNT, AND THE FAN BLADES RUBBING ON THE ENGINE/ALTERNATOR MOUNT. THE ALTERNATOR MOUNTING BOLT WAS FOUND IN THE LOWER COWLING, THE NUT AND WASHER WERE NOT FOUND. IT IS B
- [SDR 2025FA0000360](https://openairdocs.org/sdr/2025FA0000360.md): Rivet · failed · May 16, 2025 · N969R · Cessna 182P · Engine Air Intake System
  > CARB AIRBOX BUTTERFLY VALVE ATTACHMENT TO ACTUATING SHAFT FAILED BY POORLY SHOT RIVET PULLING THROUGH THE BRACKET HOLE ON RIGHT SIDE. LEFT SIDE RIVET IS LOOSE AS WELL BUT HAD NOT FAILED AT THE TIME OF DISCOVERY. VALVE WAS HANGING DOWN AWAY FROM THE SHAFT. OWNE
- [SDR 2023FA0000673](https://openairdocs.org/sdr/2023FA0000673.md): Rocker Boss · broken · Oct 24, 2023 · N8443M · Cessna 182P · Reciprocating Engine Cylinder Section
  > PILOT REPORTED THAT APPROX. AN HOUR INTO FLIGHT AT 3500 FEET AND 30 DEGREES AND ON AUTOPILOT, EXPERIENCED SEVERE ENGINE VIBRATION AND REDUCED POWER. PILOT REDUCED POWER TO AROUND 1700-1800 RPM IN EFFORT TO DECREASE VIBRATION. ULTIMATELY MADE EMERGENCY LANDIN
- [SDR 2026FA0000428](https://openairdocs.org/sdr/2026FA0000428.md): Fuel Cell · leaking · Sep 15, 2023 · N4683K · Cessna 182P · Fuel Storage
  > NEW FFC BLADDER INSTALLED SEPT 2023.. LEAKED.. UNABLE TO RESOLVE LEAKING, BLADDER RETURNED TO FFC FOR INSPECTION AND REPAIR FEB 2024.. REPAIRED BLADDER INSTALLED MAR 2024.. LEAKING CONTINUED.. AGAIN RETURNED TO FFC.. BLADDER REPLACED WITH ANOTHER NEW BLA
- [SDR 2022FA0000518](https://openairdocs.org/sdr/2022FA0000518.md): Seat Track · deformed · May 20, 2022 · N79074 · Cessna 182P · Fuselage, Seat/Cargo Attach Fittings
  > CONDUCT OF AD 2011-10-9, THE AD STATES:"INSPECT THE DIAMETER OF EACH SEAT LOCKING PIN ENGAGEMENT HOLE...THE MOST USED HOLES DO NOT HAVE A "DIAMETER", BUT INSTEAD HAVE A HOLE THAT IS ELLIPTICAL IN SHAPE. THUS, MEASUREMENTS FORE AND AFT AND PORT TO STARBOARD MU
- [SDR 2023FA0000233](https://openairdocs.org/sdr/2023FA0000233.md): Flap · unknown · Mar 1, 2022 · N1392S · Cessna 182P · Trailing Edge Flaps
  > SMALL CRACK ON EXTERNAL TOP OF THE RH FLAP, THE CRACK IS NOT LONGER THAN 2 INCHES AND THE INTERNAL RIBS AND AC STRUCTURE WERE UNDAMMAHED. THE CRACK DID NOT PROTRUDE TO ANY FASTENERS AND WAS RELATED TO PREVIOUS FLAP DAMAGE. CESSNA WAS CONTACTED AND VIA PHONE
- [SDR 2021FA0000153](https://openairdocs.org/sdr/2021FA0000153.md): Seal · unsecure · Apr 25, 2021 · N831PZ · Cessna 182P · Engine Air Intake System
  > AIRCRAFT WAS IN CRUISE FLIGHT AND SUDDENLY LOST ENGINE POWER WITH NO PRIOR WARNING. AIRCRAFT PERFORMED EMERGENCY LANDING TO AIRSTRIP WITH NO DAMAGE. UPON INSPECTION IT WAS DETERMINED THAT THE SEAL THAT SURROUNDS THE CONNECTION BETWEEN THE AIR INTAKE AND THE CA
- [SDR 2020FA0000415](https://openairdocs.org/sdr/2020FA0000415.md): Fitting · fractured · Sep 20, 2020 · N8217G · Cessna 182P · Nose/Tail Landing Gear
  > DURING INSPECTION FOUND FITTING SEPARATED ON RIGHT SIDE AND SEPARATION GAP OPEN APPROXIMATELY.75". NO DAMAGE TO FIREWALL FOUND. NO DAMAGE TO CENTER TUNNEL FOUND. NO LOOSE HARDWARE WAS FOUND. METAL IN SEPARATION SHOWS CRACK WAS APPROXIMATELY 1/2 THROUGH ME
- [SDR 2017FA0000081](https://openairdocs.org/sdr/2017FA0000081.md): Capacitor · loose · Mar 1, 2017 · N1245B · Cessna 182P · Magneto/Distributor
  > DURING RUN UP, MAGETO FAILED TEST. LESS THAN 1 HR OPERATION AFTER OVERHAULED MAGETOS INSTALLED. DURING INSPECTION FOUND THE CAPACITOR LOOSE IN HOUSING AND COIL WIRE LOOSE AND MAGETO SET IN E GAP. REMOVED OTHER MAG AS A PRECAUTION AND FOUND ITS COIL WIRE L
- [SDR 2016FA0000039](https://openairdocs.org/sdr/2016FA0000039.md): Elt · false activation · Jan 5, 2016 · N78415 · Cessna 182P · Emergency Locator Beacon
  > OCCURED WHILE ACFT WAS IN HANGER. EMERGENCY LOCATION TRANSMITTER: AK451, 121.5/406 HZ ACTIVATED GIVING FALSE ACCIDENT SIGNAL. COAST GUARD CALLED REGISTERED OWNER AND UNIT WAS TURNED OFF. 70 PERCENT OF THESE UNITS HAVE FAILED IN THIS WAY. CONTACTED FSDO SW
- [SDR LC1R201512225723](https://openairdocs.org/sdr/LC1R201512225723.md): Vent Line · out of position · Dec 22, 2015 · N5723J · Cessna 182P · Fuel Storage
  > REPORTED FUEL WOULD DRAW FROM LT FUEL TANK EVEN WITH THE SELECTOR VALVE POSITIONED IN THE RT TANK POSITION. DISCOVERED THAT SATISFACTORY RESULTS COULD NOT BE OBTAINED FROM THE VENT SYSTEM CHECKS DESCRIBED IN MM SECTION 12-22. FOUND THE LONG RANGE TANK INTERN
- [SDR CA150617019](https://openairdocs.org/sdr/CA150617019.md): Support · damaged · Jun 17, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) DURING ELEVATOR CONTROL MOVEMENT, THE CLEVIS PIN AN21-10, ATTACHED TO THE ARM ASSEMBLY, IS CONTACTING THE SUPPORT ASSEMBLY WEARING A.025 DEEP GROOVE IN THE SUPPORT ASSEMBLY. THIS IS APPROX 50% OF THE MATERIAL THICKNESS. THIS GROOVE EXTENDS DIRECTLY T
- [SDR CA150617013](https://openairdocs.org/sdr/CA150617013.md): Support · damaged · Jun 17, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) AT FULL UP ELEVATOR, WITH THE ELEVATOR RIGGED WITHIN LIMITS, THE ARM ASSEMBLY IS CONTACTING THE SUPPORT ASSEMBLY CAUSING DAMAGE TO THE SUPPORT ASSEMBLY.
- [SDR CA150617014](https://openairdocs.org/sdr/CA150617014.md): Support · damaged · Jun 16, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) DURING ELEVATOR CONTROL MOVEMENT, THE CLEVIS PIN AN21-10, ATTACHED TO THE ARM ASSEMBLY, IS CONTACTING THE SUPPORT ASSEMBLY WEARING A GROOVE IN THE SUPPORT ASSEMBLY. THIS GROOVE EXTENDS DIRECTLY THROUGH A HOLE IN THE SUPPORT ASSEMBLY CREATING THE POTENTI
- [SDR CA150616026](https://openairdocs.org/sdr/CA150616026.md): Support · damaged · Jun 16, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) AT FULL UP ELEVATOR, WITH THE ELEVATOR RIGGED WITHIN LIMITS, THE ARM ASSEMBLY IS CONTACTING THE SUPPORT ASSEMBLY CAUSING DAMAGE TO THE SUPPORT ASSEMBLY.
- [SDR CA150616024](https://openairdocs.org/sdr/CA150616024.md): Support · damaged · Jun 16, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) AT FULL UP ELEVATOR, WITH THE ELEVATOR RIGGED WITHIN LIMITS, THE ARM ASSEMBLY IS CONTACTING THE SUPPORT ASSEMBLY CAUSING DAMAGE TO THE SUPPORT ASSEMBLY.
- [SDR CA150616023](https://openairdocs.org/sdr/CA150616023.md): Support · damaged · Jun 16, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) AT FULL UP ELEVATOR, WITH THE ELEVATOR RIGGED WITHIN LIMITS, THE ARM ASSEMBLY IS CONTACTING THE SUPPORT ASSEMBLY CAUSING DAMAGE TO THE SUPPORT ASSEMBLY.
- [SDR CA150616009](https://openairdocs.org/sdr/CA150616009.md): Support · damaged · Jun 15, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) AT FULL UP ELEVATOR, WITH THE ELEVATOR RIGGED WITHIN LIMITS, THE ARM ASSEMBLY IS CONTACTING THE SUPPORT ASSEMBLY CAUSING DAMAGE TO THE SUPPORT ASSEMBLY.
- [SDR 2013FA0000444](https://openairdocs.org/sdr/2013FA0000444.md): Gasket · deformed · May 27, 2013 · N5778J · Cessna 182P · Reciprocating Engine Cylinder Section
  > ENGINE WAS RUNNING ROUGH AND SHOWING SIGNS OF RUNNING LEAN. FOUND ALL INTAKE GASKETS SHRUNK AND DEFORMED CAUSING INTAKE LEAKS AT ALL CYLINDERS.
- [SDR 2013FA0000224](https://openairdocs.org/sdr/2013FA0000224.md): Spark Plug · broken · Apr 9, 2013 · N9335X · Cessna 182P · Spark Plug/Igniter
  > WHILE COMPLETING A 1000 HOUR INSPECTION AND CLEANING THE SPARK PLUGS (XL URHB32S LOT 1269) 1 OF THE PLUGS WAS FOUND TO HAVE THE WIRE ELECTRODE LOOSE AT ITS ATTACHMENT TO THE END OF THE SPARK PLUG. THE WIRE COULD BE ROTATED UP OUT OF ALIGNAMENT WITH THE CENTER
- [SDR 2013FA0000085](https://openairdocs.org/sdr/2013FA0000085.md): Switch · failed · Jan 25, 2013 · N1262S · Cessna 182P · Instrument Panel
  > MFG SWITCHES S-1579-2 COMMONLY USED FOR AUX LIGHTING AND MISC ACCESSORIES COMMONLY FAIL TO OPERATE. FOUND TWO ON SAME AIRCRAFT FOR PITO HEATER AND NAV LIGHTS.
- [SDR CA120827011](https://openairdocs.org/sdr/CA120827011.md): Gear · failed · Aug 21, 2012 · Cessna 182P · Reciprocating Engine Power Section
  > (CAN) WHILE TURNING THE PROPELLER BY HAND, THE OWNER/PILOT FOUND THAT THE ENGINE LOCKED UP. THE AME WORKING ON THE ACFT REMOVED AN ENGINE ACCY TO GAIN ACCESS TO THE INTERNAL GEARS AND FOUND THAT THERE WERE 2 TEETH MISSING FROM THE CRANKSHAFT GEAR. THE ENGINE
- [SDR CA120507021](https://openairdocs.org/sdr/CA120507021.md): Bellcrank · cracked · May 7, 2012 · Cessna 182P · Flight Compartment Equipment
  > (CAN) BELLCRANKS FOUND CRACKED. PINS THAT SECURED THE BELLCRANK ON THE LT SIDE HAD PARTIALLY SHEARED PLACING THE LOAD ON 2 OF THE 4 HOLES AND APPEARED TO CAUSE CRACKS TO SPREAD OPEN. DAMAGE TO THE RT BELLCRANK WAS LESS SEVERE AND PINS WERE INTACT. COMPLETE
- [SDR EVGR20120326001](https://openairdocs.org/sdr/EVGR20120326001.md): Skin · corroded · Mar 26, 2012 · N91222 · Cessna 182P · Fuselage Main, Plate/Skin
  > CORROSION WAS FOUND UNDER THE BLACK SOUND DEADENING PATCHES ON THE INSIDE OF THE ACFT SKIN, AND WAS NOT DETECTED UNTIL THE PATCHES WERE REMOVED.
- [SDR CA120103015](https://openairdocs.org/sdr/CA120103015.md): Nut · failed · Jan 2, 2012 · Cessna 182P · Reciprocating Engine Cylinder Section
  > (CAN) UPON INSPECTION IT WAS NOTED THAT THE NUT LOCATED ON THE NR 6 CYLINDER TOP FWD THRU STUD WAS CRACKED. REQUIRED INSPECTION WERE CARRIED OUT WITH NO DEFECT FOUND, NUT WAS REPLACED & A COMPLETE ENGINE TORQUE SEQUENCE WAS CARRIED OUT. NO OTHER NUTS WERE FO
- [SDR HYIA20110607001](https://openairdocs.org/sdr/HYIA20110607001.md): Strap · corroded · Jun 7, 2011 · N52836 · Cessna 182P · Wing Miscellaneous Structure
  > DURING HEAVY CHECK INSPECTION, CORROSION WAS FOUND ON THE UPPER SURFACE OF THE RT WING STRIP STRAP OF RIB 20 AT WS 7900. THE CORROSION WAS REMOVED IAW SRM 51-21-58 AND EXCEEDED THE LIMITS OF THE SRM. REPAIRED IAW WITH EA 12-2011-014.
- [SDR 2010FA0001255](https://openairdocs.org/sdr/2010FA0001255.md): Cylinder Head · broken · Dec 22, 2010 · N21140 · Cessna 182P · Reciprocating Engine Cylinder Section
  > IN CRUISE FLIGHT, ENGINE STARTED TO LOSE POWER AND BACKFIRE. PILOT MADE AN EMERGENCY LANDING IN FIELD WITH NO DAMAGE TO ACFT. VISUAL INSP OF THE ENGINE WAS ACCOMPLISHED. THE NR 6 CYLINDER WAS FOUND TO HAVE FAILURE OF EXHAUST ROCKER ARM BOSS RESULTING IN THE
- [SDR 2010FA0001216](https://openairdocs.org/sdr/2010FA0001216.md): Bulkhead · cracked · Dec 3, 2010 · N20733 · Cessna 182P · Fuselage Main, Bulkhead
  > DURING ANNUAL INSPECTION AD 72-07-09 WAS DUE FOR RE-INSPECTION, DURING INSPECTION FOUND THAT THE AFT BULKHEAD WAS CRACKED ON THE LEFT AND RIGHT SIDE FROM THE RUDDER CUT OUT TO THE BULKHEAD FLANGE.AS SHOWN IN CESSNA SERVICE LETTER SE72-3 FIG 1. THE CRACKS WERE
- [SDR CA111117003](https://openairdocs.org/sdr/CA111117003.md): Strut · damaged · Nov 19, 2010 · Cessna 182P · Wheel/Ski/Float
  > (CAN) FLOAT STRUT LOWER BOLT HOLE ELONGATED UPON VISUAL INSPECTION.
- [SDR CA100218008](https://openairdocs.org/sdr/CA100218008.md): Cylinder · damaged · Feb 18, 2010 · Cessna 182P · Reciprocating Engine Cylinder Section
  > (CAN) DURING A 100 HOUR INSP, A ROUTINE COMPRESSION TEST WAS CARRIED OUT AS PART OF ENGINE ON CONDITION PROGRAM IAW AN B041. A LEAK WAS NOTED ASSOCIATED WITH LOW COMPRESSION ON THE NR 5 CYL ASSY AT TOP DEAD CTR. THE PISTON WAS THEN PLACED AT BOTTOM DEAD CTR AN
- [SDR 2010FA0000098](https://openairdocs.org/sdr/2010FA0000098.md): Nut · broken · Jan 28, 2010 · N21462 · Cessna 182P · Vertical Stabilizer
  > ONE OF THE 4 BOLTS HOLDING THE REAR ATTACHMENT BRACKET ON VERTICAL STABILIZER, HAD A BROKEN/ SPLIT NUT. PROBABLE CAUSE COULD HAVE BEEN FROM CORROSION FOUND BETWEEN THE NUT AND WASHER CAUSING STRUCTURAL LOSS OF THE NUT. INSPECTED NUTS FOR CORROSION AND REPALC
- [SDR 2010FA0000188](https://openairdocs.org/sdr/2010FA0000188.md): Impulse Coupling · loose · Jan 14, 2010 · N52600 · Cessna 182P · Magneto/Distributor
  > DISCOVERED DURING FINAL TORQUING OF THE MAGNETO HOLD DOWN NUTS, THE IMPULSE COUPLING WOULD BOTTOM OUT IN THE ENGINE GEAR HSG. THIS WOULD LOCK THE COUPLING, CAUSING IT TO NOT WORK. IF THE COUPLING WAS PARTIALLY ENGAGED, IT WOULD HOLD THE DISPLACED TIMING BETW
- [SDR CA090915006](https://openairdocs.org/sdr/CA090915006.md): Cylinder · wrong part · Jul 31, 2009 · Cessna 182P · Reciprocating Engine Cylinder Section
  > (CAN) DURING ROUTINE MAINTENANCE THE NR 1 AND 3 CYLINDERS WERE FOUND TO HAVE LOW COMPRESSION. THE CYLINDERS AND PISTONS WERE REMOVED AND SENT IN FOR REPAIR. AFTER RECEIVING THE CYLINDERS AND PISTONS, DISCOVERED THAT THE PISTONS PART NUMBERS WERE THAT OF A "U"
- [SDR 2009FA0000452](https://openairdocs.org/sdr/2009FA0000452.md): Tube · split · Apr 24, 2009 · N134LS · Cessna 182P · Tire Tube
  > SPLIT IN SIDE OF NOSE WHEEL TUBE CAUSING FLAT TIRE. THIS SEEMS TO BE A PROBLEM WITH SYNTHETIC TUBES. (K)
- [SDR 2009FA0000073](https://openairdocs.org/sdr/2009FA0000073.md): Connector · burned · Feb 10, 2009 · N1403S · Cessna 182P · Light System Wiring
  > PILOT REPORTED SMOKE IN COCKPIT AFTER TAKEOFF AND RETURNED TO THE AIRPORT MAKING AN UNEVENTFUL LANDING. MX INSPECTED THE ACFT AND FOUND A LOOSE CONNECTION AT THE LANDING LIGHT SWITCH WITH BURNED WIRING INSULATION. INSTALLED NEW WIRING AND CONNECTOR AS NEEDED
- [SDR C2X2008F00049](https://openairdocs.org/sdr/C2X2008F00049.md): Rotor · eroded · Jul 2, 2008 · N21145 · Cessna 182P · Turbine Section
  > THE CREW REPORTED ENGINE NR 1 HP INDICATION IN YELLOW RANGE AFTER TAKEOFF, THE ACFT RETURNED TO DEPARTURE AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED AND REPLACED THE NR 1 ENGINE. OPERATIONAL CHECKS WERE GOOD. SUPPLEMENT TO FOLLOW: CONDITION REPORT FROM
- [SDR 2008FA0000231](https://openairdocs.org/sdr/2008FA0000231.md): Line · leaking · Mar 31, 2008 · N20935 · Cessna 182P · Aircraft Fuel Distribution System
  > FUEL LEAKING FROM GAS COLATOR BOWL, TIGHTENED AT FACTORY DURING ACCEPTANCE FLIGHT (5.0 HOURS). FUEL LEAKING FROM GAS COLATOR INLET LINE (10 HOURS SINCE NEW) RESULTED IN OFF-AIRPORT LANDING DUE TO FUEL QUANTITY. (K)
- [SDR EA25070193](https://openairdocs.org/sdr/EA25070193.md): Landing Gear · departed · Oct 19, 2007 · N6506M · Cessna 182P · Nose/Tail Landing Gear
  > AIRCRAFT ALTERED IAW STC SA02031NY INSTALLATION OF 3400 AMPHIBIOUS FLOATS APPROXIMATELY 36 HOURS PRIOR TO OCCURRENCE. ON TAKEOFF FROM HARD SURFACE RUNWAY, RT FORWARD WHEEL AND SUPPORT ASSY DEPARTED LANDING GEAR STRUT. WHEEL AND SUPPORT ASSY LT GEAR STRUT CLEAN
- [SDR 2007FA0000797](https://openairdocs.org/sdr/2007FA0000797.md): Fuel Cap · venting · Aug 9, 2007 · N58776 · Cessna 182P · Fuel Storage
  > FUEL CAPS WERE INSTALLED ON AIRCRAFT IAW STC SA2376CE AND HAD BEEN IN SERVICE FOR ABOUT 40 HOURS IN A 4 MONTH PERIOD. THEY BEGAN VENTING FUEL FROM BOTH TANKS RESULTING IN A FORCED EMERGENCY LANDING DUE TO FUEL STARVATION.
- [SDR 2006FA0000441](https://openairdocs.org/sdr/2006FA0000441.md): Oil Filter · mismanufactured · Apr 17, 2006 · N58946 · Cessna 182P · Reciprocating Engine Oil System
  > MOUNTING STUD TOO LONG, APPROX.200 LONGER. INSTALLED OIL FILTER AFTER OIL CHANGE, RAN ENGINE TO LEAK CHECK AND LOST ALMOST 2 QTS OF OIL. INVESTIGATION FOUND THAT THE OIL FILTER STUD WAS TOO LONG CAUSING THE FILTER TO TORQUE BEFORE SEAL TOUCHED FLANGE, LEAVI
- [SDR AU510001572](https://openairdocs.org/sdr/AU510001572.md): Exhaust Valve · worn · Dec 12, 2005 · Cessna 182P · Reciprocating Engine Cylinder Section
  > NR 3 CYLINDER EXHAUST VALVE STEM WORN EXCESSIVELY. WEAR WAS APPROXIMATELY 3.175MM (0.125IN). SUSPECT INCORRECT VALVE GUIDE/VALVE COMBINATION.
- [SDR CA051220005](https://openairdocs.org/sdr/CA051220005.md): Rod · broken · Dec 2, 2005 · Cessna 182P · Rudder Control System
  > DURING TAXI (AFTER HARDWIND DURING THE DAY WITH THE AIRCRAFT PARKED WITH TAIL TO THE WIND), AT THE END OF THE DAY THE PILOT HAD NO CONTROL ON PEDALS FOR TAXIING. THE PILOT SIDE RT PEDAL WAS JAMMED IN PLACE. AFTER EVALUATION OF PROBLEM, FOUND A BROKEN ROD END
- [SDR 2005FA0001477](https://openairdocs.org/sdr/2005FA0001477.md): Support Bracket · cracked · Oct 10, 2005 · N888SR · Cessna 182P · Wing, Attach Fittings
  > WING T/E SKIN SUPPT BRKT CRACKED CAUSED FLAP INTERFERENCE AND FAILURE. BRKT IS ATTACHED TO EACH FLAP TRACK RIB INSIDE T/E OF WING, SUPPT T/E WING SKIN IN FLAP BAY. PART CRACKED, ALLOWED FLAP SUPPT TO GET CAUGHT DURING FLAP RETRACTION, BINDING FLAP. FLAP STR
- [SDR 2005FA0000976](https://openairdocs.org/sdr/2005FA0000976.md): Magneto · cracked · Jul 21, 2005 · N113SG · Cessna 182P · Magneto/Distributor
  > FOUND AN OIL LEAK COMING FROM THE BASE OF THE LEFT MAGNETO. REMOVED MAG TO REPLACE GASKET. FELT SOMETHING ON THE MOUNTING FLANGE OF THE MAG. FOUND A SECTION OF THE FLANGE ABOUT 1 1/4 INCH CRACKED WHERE THE HOLD DOWN CLIP CLAMPS THE MAG TO THE ENGINE CASE. A LI
- [SDR 2005FA0000975](https://openairdocs.org/sdr/2005FA0000975.md): Magneto · cracked · Jul 21, 2005 · N113SG · Cessna 182P · Magneto/Distributor
  > FOUND AN OIL LEAK COMING FROM THE BASE OF THE LEFT MAGNETO. REMOVED MAG TO REPLACE GASKET. FELT SOMETHING ON THE MOUNTING FLANGE OF THE MAG. FOUND A SECTION OF THE FLANGE ABOUT 1 1/4 INCH CRACKED WHERE THE HOLD DOWN CLIP CLAMPS THE MAG TO THE ENGINE CASE. A LI
- [SDR 2005FA0000974](https://openairdocs.org/sdr/2005FA0000974.md): Magneto · cracked · Jul 21, 2005 · N113SG · Cessna 182P · Magneto/Distributor
  > FOUND AN OIL LEAK COMING FROM THE BASE OF THE LEFT MAGNETO. REMOVED MAG TO REPLACE GASKET. FELT SOMETHING ON THE MOUNTING FLANGE OF THE MAG. FOUND A SECTION OF THE FLANGE ABOUT 1 1/4 INCH CRACKED WHERE THE HOLD DOWN CLIP CLAMPS THE MAG TO THE ENGINE CASE. A LI
- [SDR 2005FA0001109](https://openairdocs.org/sdr/2005FA0001109.md): Control Cable · worn · Jul 8, 2005 · N52389 · Cessna 182P · Aileron Control System
  > CABLES WORN BEYOND LIMITS AT A CABLE RUB STRIP IN RT WING BY AUTOPILOT SERVO AT STA RBL 102. (K)
- [SDR CA041019005](https://openairdocs.org/sdr/CA041019005.md): Hub · corroded · Oct 19, 2004 · Cessna 182P · Propeller Hub Section
  > (CAN) PROP RECEIVED FOR 10 YR. CALENDAR O/H. AFTER PAINT REMOVAL FROM HUB CORROSION WAS FOUND ON THE EXTERNAL SURFACES. THIS CORROSION CANNOT BE REMOVED WITHIN THE MANF.'S MINIMUM SPEC'S. THIS PROPELLERHAS EXCEDED THE MANF'S RECOMMENDED CALENDAR TBO BY 60 MONT
- [SDR 2004FA0000787](https://openairdocs.org/sdr/2004FA0000787.md): Valve Guide · worn · Aug 12, 2004 · N5823J · Cessna 182P · Reciprocating Engine Power Section
  > ON DOING A COMPRESSION CHECK, 3 OUT OF 6 CYLINDERS HAD VALVES LEAKING. WHEN REMOVED FOR REPAIR, DISCOVERED GUIDES WORN BEYOND MAX SERVICE LIMIT. (NM09200412745)

Next page: https://openairdocs.org/model/cessna-182p/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 = '182P'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/cessna-182p/reports

---
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