# Rearwin 180

- Type: Aircraft model (FAA registry)
- Registry code: 2370502
- Manufacturer (registry): REARWIN
- Model: 180
- Aircraft type: Fixed wing single engine
- Category: Airplane
- Engines: 1 · Reciprocating
- Seats: 2
- Weight class: Up to 12,499 lb
- Cruise speed: 86 mph
- Certification: Type certificated
- Data sheet: [TCDS A-729](https://openairdocs.org/tcds/A-729) (OpenAirDocs)
- Holder: Commonwealth Aircraft Inc.
- Registered aircraft: 2
- Page: https://openairdocs.org/model/rearwin-180

Model codes come from the FAA registry's reference file. ADs are matched to them by model name and maker.

## ADs that may apply (OpenAirDocs)

Matched to this model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment.

- [AD 48-06-02](https://openairdocs.org/ad/48-06-02): Jury Struts · Commonwealth 175, 180, 180F and 2 more

## Registered aircraft (2)

- [N37796](https://openairdocs.org/aircraft/N37796): [Allen Ken](https://openairdocs.org/faa-owner/ALLEN%20KEN), [Shelby, NC](https://openairdocs.org/faa-place/NC/Shelby), S/N 1574
- [N37890](https://openairdocs.org/aircraft/N37890): [Hardman Kyle B](https://openairdocs.org/faa-owner/HARDMAN%20KYLE%20B), [Shady Shores, TX](https://openairdocs.org/faa-place/TX/Shady%20Shores), built 1941, S/N 1578

## NTSB investigations

None matched to aircraft with this model.

## FAA accident and incident reports

None matched to aircraft with this model.

## Service difficulty reports (86, newest 50)

As reported by operators and repair stations, by the model named in the report.

- [SDR 2025FA0000531](https://openairdocs.org/sdr/2025FA0000531), Jul 29, 2025: PISTON. DISINTEGRATED. SUPERIOR PISTON ASSY PART # SA640518 INSTALLED. WITHIN 40 HOURS OF INSTALLATION PISTON DISINTEGRATED RESULTING IN EXTREME VIBRATION. ENGINE WAS SHUTDOWN AND LAN
- [SDR MPRC202408200001](https://openairdocs.org/sdr/MPRC202408200001), Aug 10, 2024: FUEL SYS. CONTAMINATED. 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
- [SDR 2020FA0000303](https://openairdocs.org/sdr/2020FA0000303), Jun 13, 2020: CONNECTOR. DAMAGED. LOSS OF ELECTRICAL POWER IN FLIGHT. REWIRED ELECTRICAL CONNECTIONS ON GENERATOR AND TEST RAN ENGINE.
- [SDR 2020FA0000133](https://openairdocs.org/sdr/2020FA0000133), Feb 6, 2020: CABLE. BROKEN. DURING FUNCTIONAL CHECK, FOUND CABLE ASSEMBLY COMPLETELY BROKEN. THIS CABLE PART OF CESSNA SK210-174A. PN 505530-405. INVESTIGATION ON THE INTERNET ( YEAH, I KN
- [SDR CA190726034](https://openairdocs.org/sdr/CA190726034), Jul 24, 2019: BULKHEAD. CHAFED. (CAN) DURING ANNUAL INSPECTION, LEFT FUSELAGE TUNNEL BULKHEAD FOUND CHAFED BY LEFT RUDDER RETURN SPRING ARM DUE TO INADEQUATE CLEARANCE. NO INDICATION OF PREVIO
- [SDR 2016FA0000234](https://openairdocs.org/sdr/2016FA0000234), May 3, 2016: AXLE. FAILED. 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
- [SDR CA150205010](https://openairdocs.org/sdr/CA150205010), Jan 29, 2015: BULKHEAD. DEFORMED. (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. STRUC
- [SDR 2014FA0000152](https://openairdocs.org/sdr/2014FA0000152), Mar 1, 2014: LINE. LEAKING. 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
- [SDR 2014FA0000300](https://openairdocs.org/sdr/2014FA0000300), Feb 11, 2014: ATTACH BRACKET. CRACKED. 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), Sep 2, 2011: FLAP TRACK. CRACKED. (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
- [SDR CA110623006](https://openairdocs.org/sdr/CA110623006), Jun 17, 2011: CONNECTING ROD. CRACKED. 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
- [SDR CA100622023](https://openairdocs.org/sdr/CA100622023), Jun 18, 2010: BARREL. CRACKED. 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
- [SDR 2007FA0000319](https://openairdocs.org/sdr/2007FA0000319), Apr 6, 2007: TRANSDUCER. MALFUNCTIONED. 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 PIT
- [SDR 2007FA0000318](https://openairdocs.org/sdr/2007FA0000318), Apr 6, 2007: TRANSDUCER. MALFUNCTIONED. 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 EI
- [SDR 2007FA0000317](https://openairdocs.org/sdr/2007FA0000317), Apr 6, 2007: TRANSDUCER. MALFUNCTIONED. 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 PIT
- [SDR 2007FA0000316](https://openairdocs.org/sdr/2007FA0000316), Apr 6, 2007: TRANSDUCER. MALFUNCTIONED. 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 E
- [SDR 2007FA0000208](https://openairdocs.org/sdr/2007FA0000208), Mar 1, 2007: BATTERY. LEAKING. 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), Mar 1, 2007: BATTERY. LEAKING. 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), Feb 5, 2007: FUEL LINE. WORN. 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), Jun 15, 2005: ATTACH FITTING. CRACKED. 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 REINFORCEMEN
- [SDR CA050531004](https://openairdocs.org/sdr/CA050531004), May 18, 2005: SUPPORT BRACKET. CORRODED. (CAN) INTERGRANULAR CORROSION FOUND ON INSPECTION.
- [SDR 2005FA0000979](https://openairdocs.org/sdr/2005FA0000979), May 2, 2005: ACTUATOR. DEFECTIVE. 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 R
- [SDR 2004FA0000756](https://openairdocs.org/sdr/2004FA0000756), Jul 19, 2004: GEAR. FAILED. 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 
- [SDR CA040615004](https://openairdocs.org/sdr/CA040615004), Jun 10, 2004: ROCKER BOSS. BROKEN. (CAN) ROCKER BOSSES BROKE OFF, FOR ROCKER SHAFT ON EXHAUST VALVE.
- [SDR 2004FA0000407](https://openairdocs.org/sdr/2004FA0000407), May 20, 2004: CARBURETOR. WORN. 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 TH
- [SDR Z372003F00002](https://openairdocs.org/sdr/Z372003F00002), Oct 23, 2003: CRANKSHAFT. BROKEN. 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 
- [SDR CA030228007](https://openairdocs.org/sdr/CA030228007), Feb 26, 2003: BULKHEAD. CRACKED. (CAN) DURING ANNUAL INSPECTION, IT WAS DICOVERED THE BULKHEAD HAD A SUBSTANDARD REPAIR AT REAR FLOAT FITTING ATTACHMENT BRACKETS. PREVIOUS REPAIR REMOVED TO FAC
- [SDR 2002FA0001371](https://openairdocs.org/sdr/2002FA0001371), Dec 4, 2002: CYLINDER. SEPARATED. 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 BARRE
- [SDR CA030228009](https://openairdocs.org/sdr/CA030228009), Oct 15, 2002: HINGE. SEIZED. (CAN) DURING INSPECTION AILERONS WERE ACTUATED FROM THE CONTROL COLUMN AND AILERON MOVEMENT WAS FOUND TO BE SPRINGY. VISUAL INSPECTION OF BOTH AILERONS CONFIRME
- [SDR CA030228008](https://openairdocs.org/sdr/CA030228008), Oct 15, 2002: BRACKET. CORRODED. (CAN) DURING INSPECTION OUTER GEAR LEG BRACKET FOR LT MAIN GEAR WAS FOUND SEVERELY CORRODED. CORROSION HAD CAUSED SEVERE EXFOLIATION. SUSPECT CORROSION INDUCED 
- [SDR CA010112007](https://openairdocs.org/sdr/CA010112007), Dec 21, 2000: EXHAUST PIPE. CRACKED. (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), Oct 5, 2000: CYLINDER. SEPARATED. DURING WATER TAKEOFF, EXPERIENCED MODERATE ROUGH RUNNING ENGINE, RETURNED TO LAKE. INSPECTION REVEALED ONE CYLINDER HAD SEPARATED BETWEEN BARREL AND HEAD. THESE
- [SDR 20001031SH003](https://openairdocs.org/sdr/20001031SH003), Oct 5, 2000: CYLINDER. SEPARATED. DURING WATER TAKEOFF, EXPERIENCED MODERATE ROUGH RUNNING ENGINE, RETURNED TO LAKE. INSPECTION REVEALED ONE CYLINDER HAD SEPARATED BETWEEN BARREL AND HEAD. THESE
- [SDR 20000817SH017](https://openairdocs.org/sdr/20000817SH017), Aug 17, 2000: CAMSHAFT. MAKING METAL. 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), Aug 10, 2000: DRIVE GEAR. CRACKED. RELEVANT MT INDICATION AROUND GEAR TEETH. (X)
- [SDR 20000602SH005](https://openairdocs.org/sdr/20000602SH005), May 8, 2000: CRANKSHAFT. DAMAGED. PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X)
- [SDR 20000517SH020](https://openairdocs.org/sdr/20000517SH020), Apr 24, 2000: LEVER. FAILED. RELEVANT INDICATION AT CLAMP RETENTION AREA OF CONTROL LEVER. (X)
- [SDR 20000517SH019](https://openairdocs.org/sdr/20000517SH019), Apr 24, 2000: GEAR. CRACKED. RELEVANT INDICATION IN TEETH AREA OF IDLER GEAR. (X)
- [SDR 99ZZZX4556](https://openairdocs.org/sdr/99ZZZX4556), Nov 22, 1999: CAMSHAFT. FAILED. FERROUS MATERIAL FOUND IN OIL FILTER. ENGINE DISASSEMBLED, PROBLEM FOUND TO BE FAILED CAMSHAFT AND LIFTER BODIES.
- [SDR CA991028001](https://openairdocs.org/sdr/CA991028001), Aug 14, 1999: MOUNT. CRACKED. (CAN) ENGINE MOUNT FOUND CRACKED 75 PERCENT THROUGH.
- [SDR 99ZZZX1609](https://openairdocs.org/sdr/99ZZZX1609), Mar 25, 1999: BOLT. WRONG PART. DURING ANNUAL INSPECTION, FOUND INCORRECT HARDWARE INSTALLED ON AFT VERTICAL FIN SPAR ATTACH. BOLTS INSTALLED WERE STANDARD AN HARDWARE. BOLT SHOULD HAVE BEEN A
- [SDR CA990224005](https://openairdocs.org/sdr/CA990224005), Feb 17, 1999: SPIDER. CRACKED. (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), Jan 11, 1999: BLADE. CORRODED. (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
- [SDR 99ZZZX115](https://openairdocs.org/sdr/99ZZZX115), Dec 7, 1998: CLAMP. LOOSE. 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), Nov 1, 1998: HINGE. LOOSE. 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
- [SDR CA981125059](https://openairdocs.org/sdr/CA981125059), Oct 21, 1998: ANGLE. CRACKED. (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 
- [SDR CA981125058](https://openairdocs.org/sdr/CA981125058), Oct 21, 1998: SUPPORT. CRACKED. (CAN) HORIZONTAL STABILIZER RIGHT REAR HINGE REINFORCEMENT BOX FOUND CRACKED FROM EDGE TO BOLT HOLE.
- [SDR CA981007002](https://openairdocs.org/sdr/CA981007002), Sep 28, 1998: BELLCRANK. CORRODED. (CAN) RIGHT HAND CABLE ATTACH POINT FOR THE RUDDER BELLCRANK BROKE DUE TO SEVERE CORROSION WHILE AIRCRAFT WAS DOCKING. ALL RUDDER CONTROL LOST. AIRCRAFT OPERATE
- [SDR CA981007001](https://openairdocs.org/sdr/CA981007001), Sep 28, 1998: FITTING. BROKEN. (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 INT
- [SDR CA980928010](https://openairdocs.org/sdr/CA980928010), Sep 11, 1998: RIB. MISSING. (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.

All 86: https://openairdocs.org/model/rearwin-180/reports.md

## STCs that may be installed (OpenAirDocs) (20)

Approved for this model: the STC's model list names it on its data sheet, or a series that includes it. In force first, then newest. The registry doesn't record which STCs an aircraft has.

- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less. Airwolf Filter Corporation
- [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system. Shady Aviation LLC
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts. Andrew D. Humphrey
- [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric. Aviation Products Systems Inc
- [STC SA01944CH](https://openairdocs.org/stc/SA01944CH): Modify airplane to fly on unleaded automotive gasoline, 87 minimum antiknock index, per ASTM Specification D-439 or D-4818 of any volatility class, A through E, or 82UL AVGAS per ASTM D-6227. Experimental Aircraft Association Inc
- [STC SA905GL](https://openairdocs.org/stc/SA905GL): Superseded by STC SA01944CH. Modify airplane to fly on unleaded automotive gasoline, 87 minimum antiknock index. EAA Aviation Foundation
- [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material. Poly-Fiber Inc
- [STC SA489EA](https://openairdocs.org/stc/SA489EA): Installation of ARP Inc. carburetor ice detection system. Aircraft & Rotorcraft Products (ARP) Inc
- [STC SA167CH](https://openairdocs.org/stc/SA167CH): Surrendered and incorporated into STC SA00478CH. Cooper Aviation Supply Company, Inc
- [STC SA5755NM](https://openairdocs.org/stc/SA5755NM): Installation of a propeller anti theft device. Davis Ray G
- [STC SA4-302](https://openairdocs.org/stc/SA4-302): Installation of BN-1 propeller spinner. ACS Products Co, Inc
- [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc
- [STC SA4-1210](https://openairdocs.org/stc/SA4-1210): Installation of Eonnex cover on aircraft surfaces. Ceconite, Inc
- [STC SA3976WE](https://openairdocs.org/stc/SA3976WE): Installation of McCauley 1B90CM7038 propeller on aircraft equipped with Continental A-80-9 engine. Daugherty John E
- [STC SA308EA](https://openairdocs.org/stc/SA308EA): Installation of carburetor ice detection system 105AP in single and twin engine aircraft and single engine helicopters powered by Continental, Franklin, and Lycoming type engines equipped with Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-6 and HA-6 series carburetors. (Normal,Utility and Acrobatic Category airplanes and helicopters equipped with engines and carburetors as described.). Alfred R Puccinelli
- [STC SA4-1208](https://openairdocs.org/stc/SA4-1208): Ceconite covering of complete aircraft. Cooper Engineering Corporation

## The same model under other registry codes

Amateur-built copies and renamed makers get their own codes.

- [Cessna 180](https://openairdocs.org/model/cessna-180): 1,177 registered aircraft, registry code 2072602
- [Commonwealth REARWIN 180](https://openairdocs.org/model/commonwealth-rearwin-180): 1 registered aircraft, registry code 2370506

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