# Service difficulty reports: Rearwin 180

A list on [Rearwin 180](https://openairdocs.org/model/rearwin-180.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 2 · 86 reports

- [SDR 2025FA0000531](https://openairdocs.org/sdr/2025FA0000531.md): Piston · disintegrated · Jul 29, 2025 · N9628 · Cessna 180 · Reciprocating Engine Cylinder Section
  > SUPERIOR PISTON ASSY PART # SA640518 INSTALLED. WITHIN 40 HOURS OF INSTALLATION PISTON DISINTEGRATED RESULTING IN EXTREME VIBRATION. ENGINE WAS SHUTDOWN AND LANDING MADE IN FIELD WITHOUT INCIDENT.
- [SDR MPRC202408200001](https://openairdocs.org/sdr/MPRC202408200001.md): Fuel Sys · contaminated · Aug 10, 2024 · N157S · Cessna 180 · Fuel Storage
  > ENGINE STARTED RUNNING ROUGH AT TOD AND STOPPED PRODUCING POWER SHORTLY AFTER. AN EMERGENCY LANDING WAS MADE ON TUNDRA WITH NO DAMAGE. FUEL SUMPS AND GASCOLATOR WERE FOUND TO HAVE WHAT LOOKED LIKE "COTTON OR FILTER LIKE MATERIAL" WHICH WE BELIEVE WAS DRYER LIN
- [SDR 2020FA0000303](https://openairdocs.org/sdr/2020FA0000303.md): Connector · damaged · Jun 13, 2020 · N7620A · Cessna 180 · AC Generator-Alternator
  > LOSS OF ELECTRICAL POWER IN FLIGHT. REWIRED ELECTRICAL CONNECTIONS ON GENERATOR AND TEST RAN ENGINE.
- [SDR 2020FA0000133](https://openairdocs.org/sdr/2020FA0000133.md): Cable · broken · Feb 6, 2020 · N7652A · Cessna 180 · Flight Compartment Equipment
  > DURING FUNCTIONAL CHECK, FOUND CABLE ASSEMBLY COMPLETELY BROKEN. THIS CABLE PART OF CESSNA SK210-174A. PN 505530-405. INVESTIGATION ON THE INTERNET ( YEAH, I KNOW...THE INTERNET) MAKES IT APPEAR TO BE A COMMON PROBLEM.
- [SDR CA190726034](https://openairdocs.org/sdr/CA190726034.md): Bulkhead · chafed · Jul 24, 2019 · Cessna 180 · Fuselage Main, Bulkhead
  > (CAN) DURING ANNUAL INSPECTION, LEFT FUSELAGE TUNNEL BULKHEAD FOUND CHAFED BY LEFT RUDDER RETURN SPRING ARM DUE TO INADEQUATE CLEARANCE. NO INDICATION OF PREVIOUS DAMAGE OR INCORRECT REPAIR WHICH WOULD CAUSE INADEQUATE CLEARANCE. SPRING FOUND INSTALLED CORRECT
- [SDR 2016FA0000234](https://openairdocs.org/sdr/2016FA0000234.md): Axle · failed · May 3, 2016 · N6479X · Cessna 180 · Main Landing Gear Strut/Axle/Truck
  > AXLE FAILURE ON LANDING RESULTING IN GROUND LOOP, PROP STRIKE, AND SUBSTANTIAL DAMAGE TO EMPENNAGE AND LT WING. THE ACFT JUST MODIFIED TO 29 X 11 X 10 AIR HAWKS FROM BUSHWHEELS AND 10" WHEELS. THE AXLE WAS THE STOCK ALUMINUM.
- [SDR CA150205010](https://openairdocs.org/sdr/CA150205010.md): Bulkhead · deformed · Jan 29, 2015 · Cessna 180 · Fuselage Main, Bulkhead
  > (CAN) EVIDENCE OF A HARD LANDING DISCOVERED IN INSPECTION PROCESS. MINOR DEFORMATION OF THE BULKHEAD AND A MINOR WRINKLE IN THE EXTERNAL SKIN WAS EVIDENT. STRUCTURAL REPAIR WAS MADE AND THE AIRCRAFT RELEASED AS REQUIRED.
- [SDR 2014FA0000152](https://openairdocs.org/sdr/2014FA0000152.md): Line · leaking · Mar 1, 2014 · N7746A · Cessna 180 · Hydraulic System, Main
  > CENTER HYD SYS LEAK, RT GEAR DOOR CAN'T CLOSE. FOUND RT MLG DOOR UP-LOCK ACTUATOR HYD TUBE CRACK AND CAUSE HYD LEAK. REPAIRED IAW AMM 20-10-09-300-802, REV 70 3. ACFT SYSTEM TEST PASS AND CONDITION CHECK SATISFIED.
- [SDR 2014FA0000300](https://openairdocs.org/sdr/2014FA0000300.md): Attach Bracket · cracked · Feb 11, 2014 · N9009C · Cessna 180 · Elevator Tab, Attach Fittings
  > TWO CRACKS OCCURED AT RIGHT AFT HORIZONTAL STABILIZER ATTACH BRACKET MOUNT BOLT HOLES ON REINFORCEMENT BRACKET ATTACHED TO AFT SPAR.
- [SDR CA110903001](https://openairdocs.org/sdr/CA110903001.md): Flap Track · cracked · Sep 2, 2011 · Cessna 180 · Trailing Edge Flaps
  > (CAN) PILOT COMPLAINED OF FLAPS JAMMING DURING RETRACTION FROM SLOW FLIGHT CONDITION. FLEW ACFT TO BASE TO CHECK OUT PROBLEM. FOUND FLAP BAY SKIN, PN 0720001-27, DEFORMED POSSIBLY DUE TO GROUND HANDLING. REPAIRS COMMENCED, DURING WHICH INBD FLAP TRACK, PN 12
- [SDR CA110623006](https://openairdocs.org/sdr/CA110623006.md): Connecting Rod · cracked · Jun 17, 2011 · Cessna 180 · Reciprocating Engine Power Section
  > NORMAL TAKEOFF AND INITIAL CLIMB BUT CLIMB PERFORMANCE BEGAN TO DECREASE THROUGH 6000 FT. POWER WAS BROUGHT BACK TO 16 INCHES MP AT 8000 FT, RPM TO 2200. ENGINE THEN BEGAN TO RUN VERY ROUGH AND THERE WAS A DECREASE IN OIL PRESSURE AS JUMPERS EXITED THE ACFT.
- [SDR CA100622023](https://openairdocs.org/sdr/CA100622023.md): Barrel · cracked · Jun 18, 2010 · Cessna 180 · Propeller Hub Section
  > DUE TO SUSPECTED PROPELLER STRIKE OR ABNORMAL LOADS, THE PROPELLER HUB CRACKED NEAR THE BLADE RETENTION RADIUS. AS A RESULT OF THIS, INTERNAL PARTS WERE DAMAGED INCLUDING ONE BLADE THRUST WASHER. PROPELLER TO BE O/HD.
- [SDR 2007FA0000319](https://openairdocs.org/sdr/2007FA0000319.md): Transducer · malfunctioned · Apr 6, 2007 · Cessna 180 · Autopilot Main Servo
  > ALTITUDE HOLD WAS INOPERATIVE. WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTAIN ALTITUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FOR TESTING. BOTH UNITS
- [SDR 2007FA0000318](https://openairdocs.org/sdr/2007FA0000318.md): Transducer · malfunctioned · Apr 6, 2007 · Cessna 180 · Autopilot Main Servo
  > ALTITUDE HOLD WAS INOP. WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMEDIATLEY, OR THE A/C WOULD MAINTAIN ALTITUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FO TESTING. BOTH UNITS WERE RETU
- [SDR 2007FA0000317](https://openairdocs.org/sdr/2007FA0000317.md): Transducer · malfunctioned · Apr 6, 2007 · Cessna 180 · Auto Flight System
  > ALTITUDE HOLD WAS INOPERATIVE. WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTAIN ALTITUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FOR TESTING. BOTH UNITS
- [SDR 2007FA0000316](https://openairdocs.org/sdr/2007FA0000316.md): Transducer · malfunctioned · Apr 6, 2007 · Cessna 180 · Auto Flight System
  > ALTITUDE HOLD WAS INOP. WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTAIN ALTITUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC OF TESTING. BOTH UNITS WERE RET
- [SDR 2007FA0000208](https://openairdocs.org/sdr/2007FA0000208.md): Battery · leaking · Mar 1, 2007 · N9198C · Cessna 180 · Battery/Charger System
  > BATTERY ACID LEAKED OR TRANSFERRED TO AFT, LOWEST CELL (AIRCRAFT TAIL WHEEL) AND SPILLED OUT. CORRODED HOLE IN BATTERY BOX AND SPILLED INTO BELLY OF AIRCRAFT.
- [SDR 2007FA0000207](https://openairdocs.org/sdr/2007FA0000207.md): Battery · leaking · Mar 1, 2007 · N9198C · Cessna 180 · Battery/Charger System
  > BATTERY ACID LEAKED OR TRANSFERRED TO AFT, LOWEST CELL (AIRCRAFT TAIL WHEEL) AND SPILLED OUT. CORRODED HOLE IN BATTERY BOX AND SPILLED INTO BELLY OF AIRCRAFT.
- [SDR 2007FA0000141](https://openairdocs.org/sdr/2007FA0000141.md): Fuel Line · worn · Feb 5, 2007 · Cessna 180 · Aircraft Fuel Distribution System
  > FLAP CABLE WEARING INTO FUEL LINE. FUEL LINE WAS INCORRECTLY ASSEMBLED. VISUAL INSPECTION OF AREA AT ANNUAL OR 100 HR INSPECTIONS. (K)
- [SDR CA050621007](https://openairdocs.org/sdr/CA050621007.md): Attach Fitting · cracked · Jun 15, 2005 · Cessna 180 · Horizontal Stabilizer, Attach Fittings
  > STABILIZER SPAR P/N 0732602-22, SPAR REINFORCEMENT P/N 0732602-1, SPAR REINFORCEMENT P/N 0732603-1 AFT, ATTACH REINFORCEMENT P/N 0732106 5), ATTACH REINFORCEMENT P/N 0732106-1, HINGE REINFORCEMENT P/N 0732101-4, DURING INSPECTION/REPAIR OF STABILIZER THESE PAR
- [SDR CA050531004](https://openairdocs.org/sdr/CA050531004.md): Support Bracket · corroded · May 18, 2005 · Cessna 180 · Fuselage, Landing Gear Attach Fittings
  > (CAN) INTERGRANULAR CORROSION FOUND ON INSPECTION.
- [SDR 2005FA0000979](https://openairdocs.org/sdr/2005FA0000979.md): Actuator · defective · May 2, 2005 · N3126D · Cessna 180 · Emergency Flotation Section
  > LT MAIN LANDING GEAR FAILED DOWN AND LOCKED POSITION, UPON INSPECTION, O-RING IN ACTUATOR PLUNGER ASSY, MS28775-214 WAS FOUND DEFECTIVE, REPLACED WITH SAME PN RE INSTALLED ACTUATO TO FLOAT ASSY. OPS CHECKED OK, NO DEFECTS NOTED. (AL05200502475) (K)
- [SDR 2004FA0000756](https://openairdocs.org/sdr/2004FA0000756.md): Gear · failed · Jul 19, 2004 · N7714A · Cessna 180 · Reciprocating Engine Power Section
  > THIS ENGINE HAD A COMPLETE FAILURE IN FLIGHT, PILOT WAS ABLE TO GLIDE TO AIRPORT. INITIAL INSPECTION FOUND DAMAGE TO CRANKSHAFT AND CAMSHAFT DRIVE GEARS INSIDE ACCESSORY GEARBOX. INSPECTION WAS NOT COMPLETE TO FIND OUT WHY THIS HAPPENED, DUE TO THE TIME AND
- [SDR CA040615004](https://openairdocs.org/sdr/CA040615004.md): Rocker Boss · broken · Jun 10, 2004 · Cessna 180 · Reciprocating Engine Cylinder Section
  > (CAN) ROCKER BOSSES BROKE OFF, FOR ROCKER SHAFT ON EXHAUST VALVE.
- [SDR 2004FA0000407](https://openairdocs.org/sdr/2004FA0000407.md): Carburetor · worn · May 20, 2004 · N180C · Cessna 180 · Fuel Control/Reciprocating Engines
  > CARBURETOR STICKING AT FULL THROTTLE DUE TO WEAR OF THE FULL THROTTLE STOP. IT WAS ACTUALLY GOING PAST FULL THROTTLE. THE PUMP LEVER ASSEMBLY WOULD TURN PAST THE AIR METERING PIN AND HANG UP THE THROTTLE SHAFT IN WIDE OPEN POSITION.
- [SDR Z372003F00002](https://openairdocs.org/sdr/Z372003F00002.md): Crankshaft · broken · Oct 23, 2003 · N4652B · Cessna 180 · Reciprocating Engine Power Section
  > PILOT FLEW A/C IN FOR GENERATOR REPAIR AND REPORTED TO MAINT THAT THE ENGINE WAS MAKING A CLUNKING NOISE. UPON FURTHER INVESTIGATION WITH A BORESCOPE THE CRANK SHAFT WAS FOUND TO BE BROKE AT APPROX. THE NR 6 PISTON CONNECTING ROD JOURNAL. ENGINE HAS NOT YET
- [SDR CA030228007](https://openairdocs.org/sdr/CA030228007.md): Bulkhead · cracked · Feb 26, 2003 · Cessna 180 · Fuselage Main, Bulkhead
  > (CAN) DURING ANNUAL INSPECTION, IT WAS DICOVERED THE BULKHEAD HAD A SUBSTANDARD REPAIR AT REAR FLOAT FITTING ATTACHMENT BRACKETS. PREVIOUS REPAIR REMOVED TO FACILITATE NEW REPAIR. BULKHEAD WAS FOUND TO BE CRACKED BEYOND REPAIR WITH A TOTAL OF 4 CRACKS WITHIN A
- [SDR 2002FA0001371](https://openairdocs.org/sdr/2002FA0001371.md): Cylinder · separated · Dec 4, 2002 · N2922C · Cessna 180 · Reciprocating Engine Cylinder Section
  > SIX CYLINDER SET INSTALLED ON ABOVE ENGINE AT ENGINE TOTAL TIME OF 3605.0 (TSO 381.5). AT ENGINE TOTAL TIME OF 3989.0 HEAD OF CYLINDER NR 4 SEPERATED FROM BARREL. CYLINDER SENT TCM. TCM REPLACING ALL 6 CYLINDERS.
- [SDR CA030228009](https://openairdocs.org/sdr/CA030228009.md): Hinge · seized · Oct 15, 2002 · Cessna 180 · Ailerons
  > (CAN) DURING INSPECTION AILERONS WERE ACTUATED FROM THE CONTROL COLUMN AND AILERON MOVEMENT WAS FOUND TO BE SPRINGY. VISUAL INSPECTION OF BOTH AILERONS CONFIRMED HINGE PINS WERE SEIZED AND NOT ALLOWING THE HINGE TO MOVE. NEW HINGES INSTALLED.
- [SDR CA030228008](https://openairdocs.org/sdr/CA030228008.md): Bracket · corroded · Oct 15, 2002 · Cessna 180 · Fuselage, Landing Gear Attach Fittings
  > (CAN) DURING INSPECTION OUTER GEAR LEG BRACKET FOR LT MAIN GEAR WAS FOUND SEVERELY CORRODED. CORROSION HAD CAUSED SEVERE EXFOLIATION. SUSPECT CORROSION INDUCED FROM ENGINE EXHAUST ENTERING AREA. OUTSIDE COVER WAS NOT SEALED WHICH ALLOWED EXHAUST TO ENTER AND
- [SDR CA010112007](https://openairdocs.org/sdr/CA010112007.md): Exhaust Pipe · cracked · Dec 21, 2000 · Cessna 180 · Engine Collector/Tailpipe/Nozzle
  > (CAN) ON INSPECTION FOUND PART TO BE CRACKED AT CENTRE OF LOWER SEAM APPROXIMATELY TWO INCHES. PART SENT FOR REPAIR.
- [SDR 20001108SH039](https://openairdocs.org/sdr/20001108SH039.md): Cylinder · separated · Oct 5, 2000 · N9248C · Cessna 180 · Reciprocating Engine Cylinder Section
  > DURING WATER TAKEOFF, EXPERIENCED MODERATE ROUGH RUNNING ENGINE, RETURNED TO LAKE. INSPECTION REVEALED ONE CYLINDER HAD SEPARATED BETWEEN BARREL AND HEAD. THESE 6 CYLINDERS HAD APPROX 400 HOURS SINCE BEING CHROMED. OWNER REPLACED ALL CYLINDERS WITH NEW SUPE
- [SDR 20001031SH003](https://openairdocs.org/sdr/20001031SH003.md): Cylinder · separated · Oct 5, 2000 · N9248C · Cessna 180 · Reciprocating Engine Cylinder Section
  > DURING WATER TAKEOFF, EXPERIENCED MODERATE ROUGH RUNNING ENGINE, RETURNED TO LAKE. INSPECTION REVEALED ONE CYLINDER HAD SEPARATED BETWEEN BARREL AND HEAD. THESE 6 CYLINDERS HAD APPROXIMATELY 400 HOURS SINCE BEING CHROMED. OWNER REPLACED ALL CYLINDERS WITH N
- [SDR 20000817SH017](https://openairdocs.org/sdr/20000817SH017.md): Camshaft · making metal · Aug 17, 2000 · N9269T · Cessna 180 · Reciprocating Engine Power Section
  > FERROUS MATERIAL FOUND IN OIL FILTER. ENGINE DIS-ASSEMBLED, PROBLEM FOUND TO BE FAILED CHAMSHAFT AND LIFTER BODIES. (X)
- [SDR 20000907SH040](https://openairdocs.org/sdr/20000907SH040.md): Drive Gear · cracked · Aug 10, 2000 · Cessna 180 · Propeller Governor
  > RELEVANT MT INDICATION AROUND GEAR TEETH. (X)
- [SDR 20000602SH005](https://openairdocs.org/sdr/20000602SH005.md): Crankshaft · damaged · May 8, 2000 · N9028C · Cessna 180 · Reciprocating Engine Power Section
  > PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X)
- [SDR 20000517SH020](https://openairdocs.org/sdr/20000517SH020.md): Lever · failed · Apr 24, 2000 · Cessna 180 · Propeller Governor
  > RELEVANT INDICATION AT CLAMP RETENTION AREA OF CONTROL LEVER. (X)
- [SDR 20000517SH019](https://openairdocs.org/sdr/20000517SH019.md): Gear · cracked · Apr 24, 2000 · Cessna 180 · Propeller Governor
  > RELEVANT INDICATION IN TEETH AREA OF IDLER GEAR. (X)
- [SDR 99ZZZX4556](https://openairdocs.org/sdr/99ZZZX4556.md): Camshaft · failed · Nov 22, 1999 · N9269T · Cessna 180 · Reciprocating Engine Power Section
  > FERROUS MATERIAL FOUND IN OIL FILTER. ENGINE DISASSEMBLED, PROBLEM FOUND TO BE FAILED CAMSHAFT AND LIFTER BODIES.
- [SDR CA991028001](https://openairdocs.org/sdr/CA991028001.md): Mount · cracked · Aug 14, 1999 · Cessna 180 · Engine Mount Section
  > (CAN) ENGINE MOUNT FOUND CRACKED 75 PERCENT THROUGH.
- [SDR 99ZZZX1609](https://openairdocs.org/sdr/99ZZZX1609.md): Bolt · wrong part · Mar 25, 1999 · N9240C · Cessna 180 · Vertical Stabilizer, Spar/Rib
  > DURING ANNUAL INSPECTION, FOUND INCORRECT HARDWARE INSTALLED ON AFT VERTICAL FIN SPAR ATTACH. BOLTS INSTALLED WERE STANDARD AN HARDWARE. BOLT SHOULD HAVE BEEN A NAS224-15. CONTACTED CESSNA PARTS DEPT AND FOUND THE PART NUMBER HAD BEEN SUPERCEDED TO MS27039-
- [SDR CA990224005](https://openairdocs.org/sdr/CA990224005.md): Spider · cracked · Feb 17, 1999 · Cessna 180 · Propeller Hub Section
  > (CAN) DURING ROUTINE SIX-YEAR CORROSION INSPECTION, USING LIQUID PENETRATIVE INSPECTION METHOD, BOTH LUGS ON THE SIDE OF THE PROPELLER HUB WERE FOUND CRACKED.
- [SDR CA990129014](https://openairdocs.org/sdr/CA990129014.md): Blade · corroded · Jan 11, 1999 · Cessna 180 · Propeller Blade Section
  > (CAN) DURING THE 6-YEAR CORROSION INSPECTION, CORROSION WAS FOUND IN THE BLADE BALANCE LEAD HOLE, THE CORROSION WAS REMOVED IAW MANUFACTURER'S INSTRUCTIONS. THE SUBMITTER SUGGESTS THAT PROPELLERS SHOULD BE OVERHAULED EVERY 5 YEARS PER THE MANUFACTURER'S RECOM
- [SDR 99ZZZX115](https://openairdocs.org/sdr/99ZZZX115.md): Clamp · loose · Dec 7, 1998 · N6560A · Cessna 180 · Mixture Control
  > ENGINE HAS HIGH BURN RATE DURING CRUISE. FOUND MIXTURE CONTROL CABLE HOUSING VERY LOOSE. INSTALLED TWO NEW CLAMPS.
- [SDR 98ZZZX4513](https://openairdocs.org/sdr/98ZZZX4513.md): Hinge · loose · Nov 1, 1998 · N2244C · Cessna 180 · Elevator Structure
  > UPON INSPECTION OF RUDDER AND LT ELEVATOR, FOUND EXCESSIVE PLAY AT RUDDER AND ELEVATOR TIP WHEN MOVING CENTRAL SURFACE FROM STOP-TO-STOP. OPENED UP ELEVATOR AND FOUND BROKEN RIVET AT OUTBOARD HINGE POINT. REPLACED RIVET AND CLOSED UP SKIN. MOVEMENT GONE.
- [SDR CA981125059](https://openairdocs.org/sdr/CA981125059.md): Angle · cracked · Oct 21, 1998 · Cessna 180 · Fuselage Miscellaneous Structure
  > (CAN) THE LEFT FUSELAGE TAIL CONE REINFORCEMENT ANGLE WAS FOUND CRACKED AT THE STABILIZER REAR HINGE ATTACH HOLE. THIS ANGLE RUNS APPROXIMATELY FROM STA 172 TO STA 230. NEW ANGLE P/N 0712048-7 INSTALLED.
- [SDR CA981125058](https://openairdocs.org/sdr/CA981125058.md): Support · cracked · Oct 21, 1998 · Cessna 180 · Horizontal Stabilizer Structure
  > (CAN) HORIZONTAL STABILIZER RIGHT REAR HINGE REINFORCEMENT BOX FOUND CRACKED FROM EDGE TO BOLT HOLE.
- [SDR CA981007002](https://openairdocs.org/sdr/CA981007002.md): Bellcrank · corroded · Sep 28, 1998 · Cessna 180 · Rudder Control System
  > (CAN) RIGHT HAND CABLE ATTACH POINT FOR THE RUDDER BELLCRANK BROKE DUE TO SEVERE CORROSION WHILE AIRCRAFT WAS DOCKING. ALL RUDDER CONTROL LOST. AIRCRAFT OPERATED IN SALT WATER ENVIRONMENT AND THE FITTING WAS STEEL BUSHING IN AN ALUMINUM PIECE.
- [SDR CA981007001](https://openairdocs.org/sdr/CA981007001.md): Fitting · broken · Sep 28, 1998 · Cessna 180 · Instrument Panel
  > (CAN) PILOT NOTED A DRASTIC LOSS OF ELEVATOR CONTROL. THE RADIO STACK IN THE CENTER OF THE INSTRUMENT PANEL HAD BROKEN AT THE TOP FITTING AND THE STACK FELL INTO THE PANEL. THE ELEVATOR CONTROL THEN GOT STUCK, AS THE TRANSPONDER TRAY WAS RESTRICTING UP TRAVE
- [SDR CA980928010](https://openairdocs.org/sdr/CA980928010.md): Rib · missing · Sep 11, 1998 · Cessna 180 · Rudder, Spar/Rib
  > (CAN) WHILE INVESTIGATING MINOR SKIN DIAMAGE, IT WAS NOTED THAT RIBS 073100-49 AND -50 WERE MISSING. ALL OF THE RIVET HOLES WERE PLUGGED WITH RIVETS.

Next page: https://openairdocs.org/model/rearwin-180/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 = '180'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/rearwin-180/reports

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