# Service difficulty reports: Cessna 182L

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

Newest first. General aviation reporting is voluntary.

- [SDR 2022FA0000027](https://openairdocs.org/sdr/2022FA0000027.md): Screw · missing · Jan 16, 2022 · Cessna 182L · Power Lever
  > THROTTLE CABLE PORT THROUGH FIRE WALL OUTER SLEEVE LOST LOWER SCREW ALLOWING SHIELD FIREWALL GROMMET ATTACHMENT PART (S-352) HOUSING OF SEAL TO WEAR INTO THE CABLE ALMOST 1/2 WAY INTO INTERIOR CABLE, CAUSING INTERIOR CABLE TO BEGIN TO BIND. REPLACED CABLE WIT
- [SDR 2020FA0000500](https://openairdocs.org/sdr/2020FA0000500.md): Oil Filter · loose · Nov 14, 2020 · N42064 · Cessna 182L · Reciprocating Engine Oil System
  > AFTER A FLIGHT FROM CENTRAL ARKANSAS TO SOUTHERN MISSOURI WITH OVERNIGHT STAY, WHILE CONDUCTING A POST FLIGHT INSPECTION THE PILOT REPORTED EXCESSIVE OIL ON THE AIRCRAFT BELLY AND ENGINE COWLING. WHEN QUESTIONED, THE PILOT REPORTED THAT A POST FLIGHT INSPECT
- [SDR 2020FA0000499](https://openairdocs.org/sdr/2020FA0000499.md): Oil Filter · loose · Nov 13, 2020 · N42064 · Cessna 182L · Reciprocating Engine Oil System
  > DURING SCHEDULED OIL CHANGE ON A CONTINENTAL O-470-R RECIPRICATING ENGINE THE MECHANIC NOTED THE TEMPEST OIL FILTER, PART NUMBER AA48110-2, HOUSING APPEARED TO SEPERATING FROM THE BASE AS INDICATED BY A LINE OF UNPAINTED METAL AT THE JUNCTURE OF THE BASE AND H
- [SDR 2018FA0000451](https://openairdocs.org/sdr/2018FA0000451.md): Pump · failed · Oct 26, 2018 · N42045 · Cessna 182L · Vacuum Distribution System
  > NEW VACUUM PUMP FAILURE 3P194-AFC.
- [SDR 2016F00214](https://openairdocs.org/sdr/2016F00214.md): Tube · broken · Sep 19, 2016 · N3311R · Cessna 182L · Elevator Structure
  > WHILE PERFORMING A PART 91 FLIGHT TRAINING, PILOTS EXPERIENCED CONTROL YOKE OSCILLATION. RETURNED TO AIRPORT WITHOUT INCIDENT. DURING INSPECTION, FOUND TRIM TAB TUBE BROKEN AS SECONDARY DAMAGE. BELIEVE PRIMARY FAILURE OF ELEVATOR COUNTER BALANCE WEIGHT ATTAC
- [SDR KC2R20140812002](https://openairdocs.org/sdr/KC2R20140812002.md): Impulse Coupling · cracked · Aug 12, 2014 · N3138R · Cessna 182L · Magneto/Distributor
  > DURING ROUTINE 500 HOUR INSPECTION OF MAGNETO, THE IMPULSE COUPLING WAS FOUND TO BE CRACKED. CRACKS ORIGINATE FROM SHARP CORNERED FEATURE OF IMPULSE COUPLING FLYWEIGHT BASE PLATE. THIS CORNER FORMS THE FULL ADVANCE STOP OF THE IMPULSE COUPLING. CRACK DISCOVERE
- [SDR KC2R20140812001](https://openairdocs.org/sdr/KC2R20140812001.md): Impulse Coupling · cracked · Aug 12, 2014 · N3138R · Cessna 182L · Magneto/Distributor
  > DURING ROUTINE 500 HOUR INSPECTION OF MAGNETO, THE IMPULSE COUPLING WAS FOUND TO BE CRACKED. CRACKS ORIGINATE FROM SHARP CORNERED FEATURE OF IMPULSE COUPLING FLYWEIGHT BASE PLATE. THIS CORNER FORMS THE FULL ADVANCE STOP OF THE IMPULSE COUPLING. CRACK DISCOV
- [SDR 2012FA0000025](https://openairdocs.org/sdr/2012FA0000025.md): Cylinder · peeling · Jan 5, 2012 · N68VT · Cessna 182L · Reciprocating Engine Cylinder Section
  > METAL PARTICLES WERE FOUND IN OIL FILTER DURING OIL CHANGES, APPROX 100 HRS AFTER MAJOR O/H. ALL CYLINDERS WERE REMOVED AND INSPECTED. FOUND NR 5 CYLINDER NICKLE PLATING PEELING AT THE BASE OF THE CYLINDER. PISTON AND RINGS WERE SCUFFING THE PEELING AREA CR
- [SDR MROA20102](https://openairdocs.org/sdr/MROA20102.md): Cylinder · leaking · Nov 26, 2010 · N42801 · Cessna 182L · Reciprocating Engine Cylinder Section
  > ROUTINE DIFFERENTIAL COMPRESSION TEST RESULTING IN A 48/80 READING WAS CAUSED BY A LEAKING EXHAUST VALVE. THE CYLINDER ASSY WAS R & R WITH A NEW CYLINDER ASSY.
- [SDR 2010FA0001154](https://openairdocs.org/sdr/2010FA0001154.md): Piston · cracked · Oct 19, 2010 · N808HC · Cessna 182L · Reciprocating Engine Power Section
  > ACFT WAS IN CRUISE FLIGHT AND EXPERIENCED AN ENGINE FAILURE. THE CASE WAS CRACKED ABOVE THE NR5 CYLINDER AND INSP THROUGH THE OIL FILLER TUBE REVEALED TNE NR5 PISTON WAS COMPLETELY DESTROYED. THIS ENGINE WAS O/H 17 YEARS AGO. INSP REVEALED THE ACFT IS CURRE
- [SDR 2009FA0000721](https://openairdocs.org/sdr/2009FA0000721.md): Attach Fitting · damaged · Jul 10, 2009 · N42154 · Cessna 182L · Vertical Stabilizer, Attach Fittings
  > COMPIED WITH AD72-07-09 DATED 10/17/74 BY INSP AND FOUND SIGNS OF WORKING AT LEFT SIDE AND RIGHT SIDE AFT VERTICAL FIN ATTACHMENT BOLTS. PERFORMED DYE PENETRANT INSP IAW PARA C,1, D, 1 AND 2 WITH NO CRACKS FOUND. CHECKED ATTACHMENT HOLES FOR EXCESSIVE ELONGA
- [SDR 2007FA0000334](https://openairdocs.org/sdr/2007FA0000334.md): Bulkhead · cracked · Apr 2, 2007 · N42053 · Cessna 182L · Fuselage Main, Bulkhead
  > SMALL CRACK AT RUDDER CABLE CUTOUT IB, APPROX.2500 INCH, NO CAUSE.
- [SDR BLB2004F00000](https://openairdocs.org/sdr/BLB2004F00000.md): Starter · failed · Apr 1, 2004 · N42275 · Cessna 182L · Engine Starter
  > TWO OVERHAULED STARTER WERE INSTALLED ON OVERHAULED ENGINE. BOTH STARTERS FAILED TO TURN OVER ENGINE, REINSTALLED OLD STARTER AND ENGINE STARTED AS NORMAL.
- [SDR CA031015010](https://openairdocs.org/sdr/CA031015010.md): Bulkhead · cracked · Sep 29, 2003 · Cessna 182L · Horizontal Stabilizer Structure
  > (CAN) RIVETS LOOSE AT TOP OF ANCHOR DOUBLERS ON BOTH SIDES AND CRACK STARTING ON RIVET ON LEFT SIDE DOUBLER FOR ANCHOR NUT TO RECEIVE HORIZONTAL STAB FRONT ATTACH BOLTS.
- [SDR 2003FA0000375](https://openairdocs.org/sdr/2003FA0000375.md): Bulkhead · cracked · Mar 13, 2003 · N42261 · Cessna 182L · Fuselage Miscellaneous Structure
  > THE AFT FUSELAGE BULKHEAD WAS CRACKED IN THE RADIUS AT THE RUDDER STOP ATTACHEMENT POINTS. BLOCK RUDDER WHEN A/C IS TIED DOWN IN WINDY CONDITIONS.
- [SDR 2003FA0000363](https://openairdocs.org/sdr/2003FA0000363.md): Bulkhead · cracked · Mar 13, 2003 · N42261 · Cessna 182L · Fuselage Main, Bulkhead
  > THE AFT FUSELAGE BULKHEAD WAS CRACKED IN THE RADIUS AT THE RUDDER STOP ATTACHMENT POINTS.
- [SDR AUS20020716](https://openairdocs.org/sdr/AUS20020716.md): Piston · damaged · Jun 18, 2002 · Cessna 182L · Reciprocating Engine Cylinder Section
  > (AUS) PISTON DAMAGED DUE TO DETONATION. PISTON RINGS BROKEN AND OIL RETURN DRAIN HOLE ENLARGED.
- [SDR 2002FA0000751](https://openairdocs.org/sdr/2002FA0000751.md): Nozzle · loose · Jun 3, 2002 · N42397 · Cessna 182L · Fuel Control/Reciprocating Engines
  > AIRCRAFT MADE AN EMERGENCY LANDING DUE TO LOSS OF POWER. FOUND CARBURETOR MAIN JET VERY LOOSE (REQUIRED TWO COMPLETE FINGER TIGHT TURNS TO TIGHTEN). THE TAB WASHER THAT LOCKS THE MAIN JET HAD NOT BEEN LOCKED, ALL THE TABS WERE FLAT IN A "AS NEW" CONDITION.
- [SDR 2002FA0000012](https://openairdocs.org/sdr/2002FA0000012.md): Valve · worn · Dec 10, 2001 · N42862 · Cessna 182L · Reciprocating Engine Cylinder Section
  > COMPRESSION TEST INDICATED NR 1 AND NR 2 CYLINDERS HAVE EXHAUST LEAKS. REMOVED CYLINDERS AND DIMENSIONALLY INSPECTING VALVES AND GUIDES. SEVERE WEAR OF BOTH GUIDE AND VALVE.
- [SDR 2002FA0000011](https://openairdocs.org/sdr/2002FA0000011.md): Guide · worn · Dec 10, 2001 · N42862 · Cessna 182L · Reciprocating Engine Cylinder Section
  > COMPRESSION TEST INDICATED NR 1 AND NR 2 CYLINDERS HAVE EXHAUST LEAKS. REMOVED CYLINDERS AND DIMENSIONALLY INSPECTING VALVES AND GUIDES. SEVERE WEAR OF BOTH GUIDE AND VALVE.
- [SDR 2002FA0000010](https://openairdocs.org/sdr/2002FA0000010.md): Exhaust Rocker · mismanufactured · Dec 10, 2001 · N42862 · Cessna 182L · Reciprocating Engine Cylinder Section
  > THE INSTALLED EXHAUST ROCKERS WERE PN 534398. THEY EXPLAINED THAT THOSE ROCKERS DID NOT HAVE THE HOLE DRILLED TO SQUIRT OIL ON THE EXHAUST VALVE STEM. THE NEW EXHAUST ROCKER HAS THAT SQUIRTER HOLE TO AID IN LUBRICATION. THIS WAS CAUSE OF FAILURE, PER MFG.
- [SDR 2001FA0000078](https://openairdocs.org/sdr/2001FA0000078.md): Bulkhead · cracked · Jul 10, 2001 · N3301R · Cessna 182L · Fuselage Main, Bulkhead
  > CRACKS IN THE UPPER OUTBOARD CORNERS OF THE RUDDER CABLE CUT-OUTS ON THE 0712616-1 BULKHEAD ASSEMBLY. AREA IN WHICH CRACK OCCURS IS RELATIVELY THIN GAUGE MATERIAL THAT APPARENTLY PROVIDES LITTLE STRUCTURAL STRENGTH. THE FLANGES IN THIS AREA DO LITTLE MORE TH
- [SDR 20010511CW008](https://openairdocs.org/sdr/20010511CW008.md): Bulkhead · cracked · Apr 23, 2001 · N42397 · Cessna 182L · Fuselage Main, Bulkhead
  > FAILED INSPECTION DUE TO CRACKS IN CRITICAL AREAS, REPLACED.
- [SDR CA000414011](https://openairdocs.org/sdr/CA000414011.md): Hub · damaged · Apr 5, 2000 · Cessna 182L · Propeller Hub Section
  > (CAN) PROP HUB DAMAGED IN RETENSION AREA.
- [SDR 98ZZZX2230](https://openairdocs.org/sdr/98ZZZX2230.md): Muffler · failed · Jun 2, 1998 · N33DM · Cessna 182L · Engine Noise Suppressor
  > THE MUFFLER WAS OBTAINED FROM THE MANUFACTURER IN JUNE, 1996. IT WAS INSTALLED ON THE AIRCRAFT JUNE 5, 1996. MAY 30, 1998, AT ANNUAL INSPECTION, THIS MUFFLER WAS FOUND TO HAVE ONE OF THE INTERNAL CONES MORE THAN 50 PERCENT BURNED OUT. THE CALENDAR TIME WAS
- [SDR 98ZZZX1178](https://openairdocs.org/sdr/98ZZZX1178.md): Bulkhead · cracked · Mar 5, 1998 · N42279 · Cessna 182L · Fuselage Main, Bulkhead
  > BULKHEAD FOUND CRACKED AT RIGHT RUDDER STOP APPROXIMATELY.50 INCH LONG. REMOVED AND REPLACED BULKHEAD ASSY. THIS REPORT SUBMITTED IN C/W AD 72-07-09.
- [SDR 97ZZZX4872](https://openairdocs.org/sdr/97ZZZX4872.md): Points · weak · Nov 1, 1997 · N42818 · Cessna 182L · Magneto/Distributor
  > FOUND POINTS WITH VERY LOW SPRING TENSION. CAUSED ENGINE TO RUN ROUGH AND QUIT IN FLIGHT AT HIGHER RPM'S.
- [SDR 96ZZZX5913](https://openairdocs.org/sdr/96ZZZX5913.md): Mount · corroded · Nov 5, 1996 · N42036 · Cessna 182L · Engine Mount Section
  > DURING ANNUAL INSPECTION, FOUND HEAVY CORROSION AT FORWARD END OF ENGINE MOUNT MAIN BEAMS AND DIAGONAL BRACE TUBES ON BOTH SIDES. CAUSE OF CORROSION-PROXIMITY OF EXHAUST COLLECTORS TO MOUNT. CORRECTIVE ACTION-INSTALL HEAT SHIELDS AFTER PAINTING WITH HEATPROO
- [SDR 96ZZZX3206](https://openairdocs.org/sdr/96ZZZX3206.md): Fuel Cap · water leak · Mar 31, 1996 · N42876 · Cessna 182L · Fuel Storage
  > FUEL CAPS LEAKING WATER INTO FUEL TANKS WHEN EXPOSED TO RAINY WEATHER. CORRECTED BY INSTALLING CESSNA 182L, SN 59229, (WW OVAL PLATES) FROM MONARCH AIR AND DEVELOPMENT, INC.
- [SDR 95ZZZX4473](https://openairdocs.org/sdr/95ZZZX4473.md): Reinforcement · corroded · Aug 16, 1995 · N42072 · Cessna 182L · Fuselage Miscellaneous Structure
  > ANNUAL INSPECTION FOUND SEVERE CORROSION AT STA 65.33 BELOW FLOORBOARDS. STEEL REINFORCEMENT HAD CORRODED BADLY. SURROUNDING STRUCTURE STARTED TO CORRODE. REINFORCEMENT IS MAJOR STRUCTURE FOR LANDING GEAR BULKHEAD, PN 0710600, AND IS FASTENED WITH HI-SHEAR
- [SDR 95ZZZX4431](https://openairdocs.org/sdr/95ZZZX4431.md): Cylinder · cracked · Aug 16, 1995 · N42072 · Cessna 182L · Reciprocating Engine Cylinder Section
  > CYLINDER SHOWED LOW COMPRESSION. DETAILED INSPECTION REVEALED CRACK IN EXHAUST VALVE AREA ON HEAD NEAR VALVE EXHAUST PORT. CYLINDER WAS PREVIOUSLY WELDED IN THIS AREA. CYLINDER SCRAPPED. EXCHANGE UNIT INSTALLED. NO WAY OF KNOWING TIME SINCE NEW ON THIS CY
- [SDR 95ZZZX4429](https://openairdocs.org/sdr/95ZZZX4429.md): Bulkhead · cracked · Aug 16, 1995 · N42072 · Cessna 182L · Propeller Spinner Section
  > DURING ANNUAL INSPECTION OF AIRCRAFT, NOTED WHAT APPEARED TO BE VERY SMALL CRACKS RADIATING FROM PROP SPINNER BULKHEAD FASTENER HOLES. CRACKS VERY SMALL. CONFIRMED USING EDDY CURRENT INSPECTION AND ZYGLO. SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS AREA. N

## 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 = '182L'
ORDER BY difficulty_date DESC
```

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

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