# N268CA: 1992 Embraer EMB-120RT, registration cancelled 2007-05-11 - Type: Cancelled registration (FAA registry, deregistered aircraft) - Cancelled: May 11, 2007 - Exported to: South Africa - Status when cancelled: Sale reported - Airframe: [Embraer EMB-120RT](https://openairdocs.org/model/embraer-emb-120rt) (registry code 3260202) - Engine: [Pratt & Whitney Canada PW118](https://openairdocs.org/engine/pratt-whitney-canada-pw118) (registry code 52116) - Data sheets: [TCDS A31SO](https://openairdocs.org/tcds/A31SO), [TCDS E20NE](https://openairdocs.org/tcds/E20NE) (OpenAirDocs) - Serial number: 120.262 - Year built: 1992 - Type of aircraft: Fixed wing multi engine - Engine type: Turbo-prop - Airworthiness: Standard, transport - Airworthiness date: March 28, 1992 - Last registry action: April 4, 2007 - Mode S code: A29CE8 - Location: Johannesburg, South Africa - Owner type: Individual - The mark today: https://openairdocs.org/aircraft/N268CA - FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=268CA - Page: https://openairdocs.org/deregistered/N268CA-2007-05-11 From the FAA registry file of November 3, 2026, cancelled registrations. Owners' street addresses are left out. The Mode S code belongs to the N-number, not the airframe. ADs and bulletins for the Embraer EMB-120RT: https://openairdocs.org/model/embraer-emb-120rt.md ## Service difficulty reports (93, newest 50) Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. - [SDR COMA0210025](https://openairdocs.org/sdr/COMA0210025), Jun 6, 2002: CIRCUIT BREAKER. FLIGHT 5061 "TRIM" AURAL WARNING DURING T/O.RESET AURAL WARNING CIRCUIT BREAKER - SYSTEM CHECK NORMAL. - [SDR COMA0210021](https://openairdocs.org/sdr/COMA0210021), May 21, 2002: LIGHT. BROKEN. FLIGHT 5063 DURING INSPECTION FOUND EMERGENCY EXIT SIGN AT 5A LOCATION INOPERATIVE.REPLACED THE EMERGENCY LIGHT ASSEMBLY. - [SDR COMA0210017](https://openairdocs.org/sdr/COMA0210017), May 3, 2002: ENGINE. FLIGHT 5075 T6 WARNING DURING T/O.COMPLIED WITH COMPRESSOR WASH, ENGINE PERFORMANCE RUNS WERE WITHIN LIMITS. - [SDR COMA0210006](https://openairdocs.org/sdr/COMA0210006), Feb 16, 2002: BOOT. PERFORATED. FLIGHT 5059 HORZ STAB AND VERT FIN DEICE FAILED.REPLACED THE VERT STABILIZER DEICE BOOT. - [SDR COMA0110165](https://openairdocs.org/sdr/COMA0110165), Dec 21, 2001: ROLLER. WORN. FLIGHT 5061 - FLAP DISAGREEMENT WARNING WHEN FLAPS SELECTED UP.REPLACED THE R/H OUTBD FLAP SECTION ROLLERS. - [SDR COMA0110147](https://openairdocs.org/sdr/COMA0110147), Sep 30, 2001: WIRE. BROKEN. FLIGHT 5025. OVERHEAD EMERGENCY LIGHT AT ROW 8 IS INOP. REPAIRED BROKEN WIRE AT LIGHT FIXTURE. OPERATIONAL CHECK SATISFACTORY. - [SDR COMA0110151](https://openairdocs.org/sdr/COMA0110151), Sep 26, 2001: LIGHT. FLIGHT #5057. DURING INSPECTION; FOUND THE EMERGENCY EXIT SIGN ON OVERHEAD BIN INOPERATIVE.REPAIRED WIRING AT THE EMERGENCY EXIT SIGN ASSEMBLY. - [SDR COMA0110149](https://openairdocs.org/sdr/COMA0110149), Sep 26, 2001: LIGHT. FLIGHT #5057. DURING INSPECTION; FOUND THE EMERGENCY EXIT SIGN ON OVERHEAD BIN INOPERATIVE.REPAIRED WIRING AT THE EMERGENCY EXIT SIGN ASSEMBLY. - [SDR COMA0110033](https://openairdocs.org/sdr/COMA0110033), Feb 4, 2001: SHEAR TIE. CRACKED. DURING 400 FLIGHT CYCLE CHECK, A CRACKED RIVET HEAD WAS DISCOVERED ON THE RIGHT SIDE OF AIRCRAFT FUSELAGE ALONG FRAME 9. UPON FURTHER INVESTIGATION, THE SKIN SU - [SDR COMA0110001](https://openairdocs.org/sdr/COMA0110001), Dec 29, 2000: WARNING SYSTEM. FALSE ACTIVATION. "BRAKES" MESSAGE ON MAP AFTER T/O. COULD NOT DUPLICATE. INSPECTED ANTI-SKID SYSTEM, FOUND NO DEFECTS. - [SDR COMA0010436](https://openairdocs.org/sdr/COMA0010436), Dec 12, 2000: SKIN. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 191/192 01Z THE LOWER FUSELAGE SKIN WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPAIRED I/A/W EMB-120 STRUCTURAL REPAIR MA - [SDR COMA0010435](https://openairdocs.org/sdr/COMA0010435), Dec 12, 2000: FRAME. CRACKED. UPON COMPLIANCE 2C INSPECTION TASK 163/164 - 01Z THE HALF FRAME 46A WAS FOUND TO BE CRACKED.THE DAMAGED PART WAS REPAIRED I/A/W EMB-120 STRUCTURAL REPAIR MANUAL - [SDR COMA0010434](https://openairdocs.org/sdr/COMA0010434), Dec 12, 2000: PIN. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 151-152-01Z THE LOWER ANGLE AND P/N RECEPTACLES AT ROW 8 WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 - [SDR COMA0010433](https://openairdocs.org/sdr/COMA0010433), Dec 12, 2000: BUTTSTRAP. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 131/132 - 01Z THE RH #1 BUTT STRAP WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR MAN - [SDR COMA0010432](https://openairdocs.org/sdr/COMA0010432), Dec 12, 2000: BUTTSTRAP. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 131/132-01Z THE LH #1 BUTTSTRAP WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR MANUAL - [SDR COMA0010431](https://openairdocs.org/sdr/COMA0010431), Dec 12, 2000: BUTTPLATE. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 131/132-01Z THE CENTER BUTT PLATE WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPAIRED I/A/W EMB-120 STRUCTURAL REPAIR MANU - [SDR COMA0010430](https://openairdocs.org/sdr/COMA0010430), Dec 12, 2000: SILL. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 131/132 - 01Z THE LEFT HAND FORWARD #1 CABIN SILL WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCT - [SDR COMA0010429](https://openairdocs.org/sdr/COMA0010429), Dec 12, 2000: SILL. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 131/132-01Z THE RH FWD #1 CABIN SILL WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR M - [SDR COMA0010428](https://openairdocs.org/sdr/COMA0010428), Dec 12, 2000: SHEAR TIE. CRACKED. UPON COMPLIANCE 2C INSPECTION TASK 5720-651-01I THE RIGHT WING SKIN SUPPORT ON RIB 20 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPPLACED I/A/W EMB-120 STRU - [SDR COMA0010420](https://openairdocs.org/sdr/COMA0010420), Dec 12, 2000: CROSSBEAM. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 151/152 - 01Z THE FRAME 36 CROSSBEAM - RT WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REP - [SDR COMA0010427](https://openairdocs.org/sdr/COMA0010427), Dec 12, 2000: SHEAR TIE. CRACKED. UPON COMPLIANCE 2C INSPECTION TASK 5310-221/222 - 05I THE SKIN SUPPORT BEHIND DU WINDOW - LEFT WAS FOUND TO BE CRACKED.THE DAMAGED PART WAS REPLACED I/A/W EMB-1 - [SDR COMA0010426](https://openairdocs.org/sdr/COMA0010426), Dec 12, 2000: FLOORBEAM. CRACKED. UPON COMPLIANCE 2C INSPECTION TASK 5310-121/122 - 01I THE LT AND RT FRAME 13 FLOORBEAMS WERE FOUND TO BE CRACKED. THE DAMAGED PART WAS REPAIRED IAW EMB-120 STRU - [SDR COMA0010425](https://openairdocs.org/sdr/COMA0010425), Dec 12, 2000: BUTTSTRAP. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 141/142 - 01Z THE LEFT AND RIGHT NR 2 BUTTSTRAPS WERE FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUC - [SDR COMA0010424](https://openairdocs.org/sdr/COMA0010424), Dec 12, 2000: BUTTSTRAP. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 141/142 - 01Z THE RT NR 3 BUTTSTRAP WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR MA - [SDR COMA0010423](https://openairdocs.org/sdr/COMA0010423), Dec 12, 2000: BUTTSTRAP. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 131/132 01Z THE CENTER #1 BUTT STRAP WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR M - [SDR COMA0010422](https://openairdocs.org/sdr/COMA0010422), Dec 12, 2000: SILL. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 161/162 - 01Z THE CARGO BAY FWD SILL WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR M - [SDR COMA0010421](https://openairdocs.org/sdr/COMA0010421), Dec 12, 2000: CROSSBEAM. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 151/152 - 01Z THE FRAME 33 RH CROSSBEAM WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAI - [SDR COMA0010419](https://openairdocs.org/sdr/COMA0010419), Dec 12, 2000: SHEAR TIE. CRACKED. UPON COMPLIANCE 2C INSPECTION TASK 231/232 - 01Z THE FRAME 13A SKIN SUPPORT WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPAIRED I/A/W EMB-120 STRUCTURAL REPA - [SDR COMA0010418](https://openairdocs.org/sdr/COMA0010418), Dec 12, 2000: STRINGER. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 5310-131/132 - CO1I (2 YR CORROSION SK) THE STRINGERS 18L AND 19L WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPAIRED I/A - [SDR COMA0010412](https://openairdocs.org/sdr/COMA0010412), Dec 12, 2000: STRUCTURE. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 131/132-01Z THE FRAME 13 Z SECTION WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR MAN - [SDR COMA0010411](https://openairdocs.org/sdr/COMA0010411), Dec 12, 2000: BUTTPLATE. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 131/132-01Z THE LEFT FORWARD BUTTPLATE WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR - [SDR COMA0010417](https://openairdocs.org/sdr/COMA0010417), Dec 12, 2000: CROSSBEAM. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 141/142 - 01Z THE FRAME 23 RT CROSSBEAM WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAI - [SDR COMA0010416](https://openairdocs.org/sdr/COMA0010416), Dec 12, 2000: SHEAR TIE. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 141/142 - 01Z THE FRAME 23 SKIN SUPPORT WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAI - [SDR COMA0010415](https://openairdocs.org/sdr/COMA0010415), Dec 12, 2000: SHEAR TIE. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 5310-131/132 - CO1I (2 YR CORROSION TASK) THE SKIN SUPPORT FRAME 19 WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED I - [SDR COMA0010414](https://openairdocs.org/sdr/COMA0010414), Dec 12, 2000: BRACKET. CRACKED. UPON COMPLIANCE 2C INSPECTION TASK 261/262 - 01Z THE CARGO DOOR TRACK BRACKET WAS FOUND TO BE CRACKED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REA - [SDR COMA0010413](https://openairdocs.org/sdr/COMA0010413), Dec 12, 2000: SEAT TRACK. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK ZONE 200 THE SEAT TRACKS - ALL WAS FOUND TO BE CORRODED.THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STRUCTURAL REPAIR MANUAL - [SDR COMA0010410](https://openairdocs.org/sdr/COMA0010410), Dec 12, 2000: SKIN. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 811-02Z THE PAX DOOR INNER SKIN WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPAIRED I/A/W EMB-120 STRUCTURAL REPAIR MANUA - [SDR COMA0010409](https://openairdocs.org/sdr/COMA0010409), Dec 12, 2000: FITTING. CORRODED. UPON COMPLIANCE 2C INSPECTION TASK 811-02Z THE PAX DOOR BOTTOM CHANNEL AND END FITTING WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED I/A/W EMB-120 STR - [SDR COMA0010406](https://openairdocs.org/sdr/COMA0010406), Nov 25, 2000: BATTERY. DISCHARGED. EMERGENCY LIGHTS ARE INOPERABLE. REPLACED THE NR 2 EMERGENCY BATTERY. - [SDR COMA0010405](https://openairdocs.org/sdr/COMA0010405), Nov 22, 2000: BATTERY. DISCHARGED. EMERGENY LIGHTS ARE INOPERABLE.REPLACED EMERGENCY BATTERY. - [SDR COMA0010403](https://openairdocs.org/sdr/COMA0010403), Nov 21, 2000: LIGHT. INOPERATIVE. EMERGENCY LIGHTS AT ROW 8 ARE INOPERABLE. COULD NOT DUPLICATE. ALL LIGHTS FUNCTION. - [SDR COMA](https://openairdocs.org/sdr/COMA), Oct 6, 2000: WARNING LIGHT. ILLUMINATED. T6 WARNING DURING T/O. REPLACED THE RIGHT ENGINE. - [SDR COMA0010326](https://openairdocs.org/sdr/COMA0010326), Aug 31, 2000: ANGLE. CRACKED. DURING A 1C INSPECTION TASK 193-01Z, THE WING TO FUSELAGE FAIRING (193) LOWER ATTACH ANGLE WAS FOUND TO BE CRACKED. THE ANGLE WAS REPLACED WITH A SERVICEABLE AN - [SDR COMA0010325](https://openairdocs.org/sdr/COMA0010325), Aug 31, 2000: ANGLE. CRACKED. DURING A 1C INSPECTION TASK 194-01Z, THE WING TO FUSELAGE FAIRING (194) LOWER ATTACH ANGLE WAS FOUND TO BE CRACKED. THE ANGLE WAS REPLACED WITH A SERVICEABLE AN - [SDR COMA0010324](https://openairdocs.org/sdr/COMA0010324), Aug 31, 2000: ANGLE. CRACKED. DURING A 1C INSPECTION TASK 194-01Z, THE WING TO FUSELAGE FAIRING (194) LOWER ATTCH ANGLE WAS FOUND TO BE CRACKED. THE ANGLE WAS REPLACED WITH A SERVICEABLE ANG - [SDR COMA0010317](https://openairdocs.org/sdr/COMA0010317), Aug 11, 2000: SKIN. CORRODED. ON AN OVERNIGHT, MECHANIC NOTICED A BULGE ON EXTERNAL SKIN AT FRAME 21 LOWER RIGHT SIDE. UPON FURTHER INSPECTION, FOUND STRINGER 21R HAD CORROSION BETWEEN FRAME - [SDR COMA0010160](https://openairdocs.org/sdr/COMA0010160), Jun 8, 2000: SHUTOFF VALVE. MALFUNCTIONED. CABIN PRESSURE INCREASES AND DECREASES WITH POWER LEVER MOVEMENT. REPLACED THE PRSOV. - [SDR COMA0010063](https://openairdocs.org/sdr/COMA0010063), May 8, 2000: BULB. FAILED. AFT, CEILING EMERGENCY LIGHT IS INOPERABLE. REPLACED LIGHT BULB. - [SDR COMA0010057](https://openairdocs.org/sdr/COMA0010057), Apr 24, 2000: ANGLE. CRACKED. WHILE PERFORMING OTHER MAINTENANCE TO THE PASSENGER DOOR, THE FUSELAGE ENTRY WAY DOOR SILL ANGLE WAS FOUND CRACKED. THE ANGLE WAS REPLACED PER EMB 120 SRM STAND - [SDR COMA0010056](https://openairdocs.org/sdr/COMA0010056), Apr 24, 2000: ANGLE. CORRODED. WHILE REPLACING THE FUSELAGE PASSENGER DOOR ENTRYWAY LOWER SILL ANGLE, THE SUPPORT ANGLE UNDERNEATH WAS FOUND SEVERELY CORRODED. THE ANGLE WAS REPLACED PER EMB1 All 93: https://openairdocs.org/deregistered/N268CA-2007-05-11/reports.md ## Other aircraft with N268CA - [Registered now](https://openairdocs.org/aircraft/N268CA): Beech C90, S/N LJ-759, built 1978 --- 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.