# GE CF6-50E2

- Type: Engine model (FAA registry)
- Registry code: 30089
- Manufacturer (registry): GE
- Model: CF6-50E2
- Engine type: Turbo-fan
- Power: 51,800 lb thrust
- Data sheet: [TCDS E23EA](https://openairdocs.org/tcds/E23EA) (OpenAirDocs)
- Holder: General Electric Company
- Installed in: 0 registered aircraft
- Page: https://openairdocs.org/engine/ge-cf6-50e2

Model codes come from the FAA registry's reference file.

## ADs that may apply (OpenAirDocs)

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

- [AD 2023-04-11](https://openairdocs.org/ad/2023-04-11): Turbine Section · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 28, 2023
- [AD 2011-23-04](https://openairdocs.org/ad/2011-23-04): Forward engine mount assembly side links · General Electric CF6-45A, CF6-45A2, CF6-50A and 14 more. Effective Dec 12, 2011
- [AD 2011-07-01](https://openairdocs.org/ad/2011-07-01): Forward and aft centerbodies · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 22, 2011
- [AD 2008-02-17](https://openairdocs.org/ad/2008-02-17): Thrust reverser actuation systems · General Electric CF6-50A, CF6-50C, CF6-50C1 and 16 more. Effective Feb 28, 2008
- [AD 2007-19-06](https://openairdocs.org/ad/2007-19-06): Compressor discharge pressure (CDP) · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Oct 23, 2007
- [AD 2005-26-06](https://openairdocs.org/ad/2005-26-06): Low pressure turbine (LPT) stage 2 interstage seal assemblies · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jan 26, 2006
- [AD 2005-07-05](https://openairdocs.org/ad/2005-07-05): Low pressure turbine (LPT) · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective May 4, 2005
- [AD 2005-08-04](https://openairdocs.org/ad/2005-08-04): Low-cycle-fatigue (LCF) · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 28, 2005
- [AD 2003-09-06](https://openairdocs.org/ad/2003-09-06): Low pressure turbine (LPT) · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Jun 3, 2003
- [AD 2003-02-07](https://openairdocs.org/ad/2003-02-07): Low pressure turbine (LPT) shrouds · General Electric CF6-50A, CF6-50C, CF6-50C1 and 30 more. Effective Mar 3, 2003
- [AD 2002-25-08](https://openairdocs.org/ad/2002-25-08): High pressure compressor rotor · General Electric CF6-45A, CF6-45A2, CF6-50A and 40 more. Effective Jan 23, 2003
- [AD 2002-05-03](https://openairdocs.org/ad/2002-05-03): Life-Limited Rotating Parts · General Electric CF6-45A, CF6-45A2, CF6-50A and 15 more. Effective Apr 12, 2002
- [AD 2002-02-09](https://openairdocs.org/ad/2002-02-09): Low Pressure Turbine Rotor (LPTR) Stage 2 Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Mar 15, 2002
- [AD 2001-12-20](https://openairdocs.org/ad/2001-12-20): Air Ducts and Reworked Mating Hardware · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Jul 26, 2001
- [AD 2001-04-16](https://openairdocs.org/ad/2001-04-16): Low Pressure Turbine (LPT) Nozzle Lock Assembly Studs · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Mar 21, 2001
- [AD 2000-11-12](https://openairdocs.org/ad/2000-11-12): High Pressure Compressor Disk Lock Slots · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Aug 14, 2000
- [AD 98-22-06](https://openairdocs.org/ad/98-22-06): Fan Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 41 more. Effective Nov 23, 1998
- [AD 97-22-14](https://openairdocs.org/ad/97-22-14): (HPCR) 3-9 Spool · General Electric CF6-50A, CF6-50C, CF6-50C1 and 29 more. Effective Nov 17, 1997
- [AD 95-08-03](https://openairdocs.org/ad/95-08-03): High Pressure Turbine Rotor Stage 2 Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jun 12, 1995
- [AD 91-10-03 R1](https://openairdocs.org/ad/91-10-03-R1): High Pressure Compressor · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 28, 1995
- [AD 94-08-05](https://openairdocs.org/ad/94-08-05): Fan Stator Case · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jul 5, 1994
- [AD 94-09-18](https://openairdocs.org/ad/94-09-18): High Pressure Turbine Disk · General Electric CF6-45A, CF6-45A2, CF6-50A and 15 more. Effective Jun 6, 1994
- [AD 93-14-18](https://openairdocs.org/ad/93-14-18): High pressure turbine (HPT) thermal shields · General Electric CF6-45A, CF6-45A2, CF6-50A and 40 more. Effective Oct 4, 1993
- [AD 93-13-10](https://openairdocs.org/ad/93-13-10): Compressor Spools · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Sep 21, 1993
- [AD 91-23-13](https://openairdocs.org/ad/91-23-13): Fan Disks · General Electric CF6-50A, CF6-50C, CF6-50C1 and 12 more. Effective Nov 22, 1991
- [AD 91-15-16](https://openairdocs.org/ad/91-15-16): High Pressure Turbine Thermal Shields · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Sep 4, 1991
- [AD 91-01-04](https://openairdocs.org/ad/91-01-04): Fan Disk · General Electric CF6-45A, CF6-45A2, CF6-50A and 19 more. Effective Jan 22, 1991
- [AD 90-23-15](https://openairdocs.org/ad/90-23-15): Turbine Mid-frame · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Dec 6, 1990
- [AD 90-19-09](https://openairdocs.org/ad/90-19-09): High Pressure Turbine Stage One Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Oct 1, 1990
- [AD 90-12-06](https://openairdocs.org/ad/90-12-06): Low Pressure Turbine · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jun 25, 1990
- [AD 89-01-02](https://openairdocs.org/ad/89-01-02): High Pressure Turbine Stage 2 Disks · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Dec 29, 1988
- [AD 87-23-06](https://openairdocs.org/ad/87-23-06): High Pressure Turbine Impeller Spacer · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Nov 5, 1987
- [AD 86-12-03](https://openairdocs.org/ad/86-12-03): High Pressure Turbine Rotor (HPTR) Stage 1 Disk · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jun 29, 1986
- [AD 84-01-01](https://openairdocs.org/ad/84-01-01): Compressor Assemblies · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Feb 10, 1984
- [AD 82-25-08](https://openairdocs.org/ad/82-25-08): HPT Spacer/Impeller · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Dec 30, 1982
- [AD 82-20-03](https://openairdocs.org/ad/82-20-03): Inspect First Stage HPT Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Oct 31, 1982
- [AD 85-25-56 R1](https://openairdocs.org/ad/85-25-56-R1): Seventh Stage Low Pressure Turbine (LPT) Cooling Air Manifold Tube · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more
- [AD 79-13-09](https://openairdocs.org/ad/79-13-09): Compressor Rotor Spools · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more

Historical (superseded or no longer in force):

- [AD 2012-02-07](https://openairdocs.org/ad/2012-02-07) (historical): LPT rotor stage 3 disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Mar 6, 2012
- [AD 2011-18-01](https://openairdocs.org/ad/2011-18-01) (historical): LPT rotor stage 3 disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 9 more. Effective Sep 26, 2011
- [AD 2011-02-07](https://openairdocs.org/ad/2011-02-07) (historical): Rotor · General Electric CF6-45A, CF6-45A2, CF6-50A and 9 more. Effective Feb 22, 2011
- [AD 2010-12-10](https://openairdocs.org/ad/2010-12-10) (historical): High-pressure turbine (HPT) · General Electric CF6-45A, CF6-45A2, CF6-50A and 9 more. Effective Jun 24, 2010
- [AD 2010-06-15](https://openairdocs.org/ad/2010-06-15) (historical): Low-pressure turbine (LPT) stage 3 disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 9 more. Effective Apr 1, 2010
- [AD 2009-04-17](https://openairdocs.org/ad/2009-04-17) (historical): Long fixed core exhaust nozzle (LFCEN) assembly · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 2, 2009
- [AD 2006-12-24](https://openairdocs.org/ad/2006-12-24) (historical): Five-link forward mount assembly · General Electric CF6-45A, CF6-45A2, CF6-50A and 14 more. Effective Jul 21, 2006
- [AD 2000-20-02](https://openairdocs.org/ad/2000-20-02) (historical): Turbine Nozzle Lock Assemblies · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Oct 17, 2000
- [AD 2000-16-12](https://openairdocs.org/ad/2000-16-12) (historical): High Pressure Compressor Rotor Stage 3-9 Spools · General Electric CF6-45A, CF6-45A2, CF6-50A and 39 more. Effective Sep 5, 2000
- [AD 99-24-15](https://openairdocs.org/ad/99-24-15) (historical): High Pressure Compressor Rotor (HPCR) Stage 3-9 Spools · General Electric CF6-45A, CF6-45A2, CF6-50A and 39 more. Effective Jan 28, 2000
- [AD 99-08-18](https://openairdocs.org/ad/99-08-18) (historical): General Electric CF6-45A, CF6-45A2, CF6-50A and 15 more. Effective May 13, 1999

## Registered aircraft

None registered with this engine model now.

## NTSB investigations (1)

From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model.

- [NTSB ENG10RA054](https://openairdocs.org/ntsb/ENG10RA054), Sep 23, 2010: Boeing 747 (N758SA), Frankfurt, Germany, incident, minor damage

## FAA accident and incident reports

None matched to aircraft with this engine model.

## Service difficulty reports (401, newest 50)

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

- [SDR Q2SA201209301](https://openairdocs.org/sdr/Q2SA201209301), Sep 30, 2012: BATTERY PACK. DEFECTIVE. EMERGENCY LIGHT IN THE COCKPIT INTERMITTENT. REMOVED AND REPLACED BATTERY PACK AND CHARGER ASSY IAW 33-51-07. SYSTEM OPS CHECK NORMAL.
- [SDR Q2SA20120930197](https://openairdocs.org/sdr/Q2SA20120930197), Sep 30, 2012: BATTERY PACK. DISCHARGED. EMERGENCY FLOOR LIGHTING IN UPPER DECK INOP. REMOVED AND REPLACED BATTERY PACK CARTRIDGE IAW 3-51-04. SYS OPS CHECK NORMAL.
- [SDR Q2SA2012080876504](https://openairdocs.org/sdr/Q2SA2012080876504), Aug 8, 2012: CASE. CRACKED. NORMAL FLAPS 20 TAKEOFF WITH REDUCED THRUST. AT 1000 AGL, NR 3 FIRE WARNING ILLUMINATED AND FIRE BELL SOUNDED. SHUTDOWN ENGINE PER QRH PROCEDURES. REQUESTED AND
- [SDR UIEA2011122700736](https://openairdocs.org/sdr/UIEA2011122700736), Dec 27, 2011: JACKSCREW. BROKEN. DURING WALKAROUND, MX FOUND THE NR 2 LT T/R HALF DAMAGE AND NOTICED A BROKEN JACK SCREW ON THE UPPER ANGLE GEARBOX/BALL SCREW ACTUATOR, BROKEN CASCADE VANES AND
- [SDR UIEA2011122800737](https://openairdocs.org/sdr/UIEA2011122800737), Dec 27, 2011: JACKSCREW. DAMAGED. DURING WALKAROUND, MX FOUND THE NR 2 LT THRUST REVERSER HALF DAMAGE AND NOTICED A BROKEN JACK SCREW ON THE UPPER ANGLE GEARBOX/BALL SCREW ACTUATOR, BROKEN CASCA
- [SDR UIEA2011111800665](https://openairdocs.org/sdr/UIEA2011111800665), Nov 16, 2011: SKIN. DAMAGED. DURING INSPECTION MX FOUND THE NR 2 ENGINE RT THRUST REVERSER CORE COWL INNER SKIN DAMAGED/DELAMINATED. AT APPROX 4 O'CLOCK POSITION WITH SIZE 7.0" X 11.0" AND 
- [SDR UIEA2011082200459](https://openairdocs.org/sdr/UIEA2011082200459), Aug 22, 2011: FRAME. CRACKED. BS 560, S24-S25L FRAME CRACKED. REPAIRED IAW SRM 53-10-04, FIG 35.
- [SDR UIEA2011081800456](https://openairdocs.org/sdr/UIEA2011081800456), Aug 18, 2011: SLEEVE. CRACKED. DURING WALK AROUND CHECK, FOUND SEVERAL CRACKS COMING FROM THE SKIN, ON THE OUTER SLEEVE OF THE LONG FIXED CORE EXHAUST NOZZLE (LFCEN) ON THE NR 4 ENGINE. THE C
- [SDR UIEA2011073100396](https://openairdocs.org/sdr/UIEA2011073100396), Jul 31, 2011: ENGINE. FLAMED OUT. ON TAXI-OUT ENG POSITION 4 FLAMED OUT. ACFT RETURNED TO BLOCKS. FLAMEOUT INSPECTION PERFORMED IAW 71-00-47. REQUIRED ENGINE RUN TO 81.9 WITH ELECTRICAL AND HYD 
- [SDR UIEA2011073100400](https://openairdocs.org/sdr/UIEA2011073100400), Jul 31, 2011: FUEL FILTER. FAILED. DURING CRUISE, NR 2 ENG ROLLED BACK TO IDLE. NO RESPONSE TO THROTTLE MOVEMENTS. APPROX 5 SEC LATER OIL PRESS DROPPED TO ZERO QTY OK. TROUBLESHOT IAW MM FIM 71-0
- [SDR Q2SA2011F00130](https://openairdocs.org/sdr/Q2SA2011F00130), May 31, 2011: SKIN PANEL. CORRODED. DURING MX CHECK, CORROSION WAS FOUND ON UPPER SKIN PANEL OF WING CTR SECTION AT SEVERAL AREAS AROUND: BS 1240 RBL 30 CENTER WING UPPER SKIN, CORROSION BEYOND SR
- [SDR EIAA2011045](https://openairdocs.org/sdr/EIAA2011045), May 29, 2011: GEARBOX. CRACKED. NR 4 ENGINE SHUT DOWN FOR LOSS OF OIL ON APPROACH. FOUND CRACK IN GEAR BOX. REMOVED AND REPLACED NR 4 ENGINE PER EIA W/C F7201 OP'S AND LEAK CHECKED GOOD.
- [SDR UIEA2011052300265](https://openairdocs.org/sdr/UIEA2011052300265), May 23, 2011: ACCESS DOOR. CRACKED. DURING MX WALKAROUND, MX FOUND 1 EA CRACK ON THE NR 1 ENGINE THRUST REVERSER LWR ACCESS DOOR (PN: 9071M77G12). DAMAGE LOCATED AT 6 O'CLOCK POSITION. THE CRACK I
- [SDR UIEA2011051700269](https://openairdocs.org/sdr/UIEA2011051700269), May 17, 2011: NOZZLE. CRACKED. DURING A "C" CHECK OF AIRCRAFT, MX FOUND CRACKS ON THE NR 1 AND NR 2 ENGINE FIXED COWL EXHAUST NOZZLE FWD FLANGE CORE COWL SUPPORT ASSY (REF FIG 1 AND 2 ). (THE
- [SDR UIEA2011032800163](https://openairdocs.org/sdr/UIEA2011032800163), Mar 28, 2011: PANEL. GOUGED. DURING ROUTINE CHECK, GOUGE DAMAGE TO THE RT INBD ELEVATOR LOWER PANEL WAS FOUND. THE DAMAGE OCCUPIES AN AREA OF APPROX 4.5-IN BY 3-IN AND LOCATED AT 23-IN FROM
- [SDR UIEA2011030100135](https://openairdocs.org/sdr/UIEA2011030100135), Mar 1, 2011: RUB STRIP. DAMAGED. ACFT AT SIN D CHECK. THE NR 1 LT FAN COWL WAS ROUTED TO THE COMPOSITE SHOP FOR REPAIRS. DURING INSTALLATION ON THE ACFT THE L/E RUB STRIP MISMATCH (6 O'CLOCK) W
- [SDR UIEA2010121700193](https://openairdocs.org/sdr/UIEA2010121700193), Dec 17, 2010: SLEEVE. CRACKED. DURING MX WALKAROUND OF N517MC, MX FOUND 1 EA CRACK ON THE NR2 ENGINE EXHAUST NOZZLE OUTER SLEEVE, LOCATED AT APPROX 7 O'CLOCK POSITION. THE CIRCUMFERENTIAL CRA
- [SDR Q2SA754009](https://openairdocs.org/sdr/Q2SA754009), Dec 11, 2010: CONNECTOR. DAMAGED. DURING INITIAL CLIMB, THE FIRE ENGINE WARNING BELL FOR NR1 ENGINE SOUNDED BRIEFLY. AT THAT TIME THE CREW PERFORMED AN INSTRUMENT SCAN AND FOUND THE ENGINE INDIC
- [SDR Q2SA815002](https://openairdocs.org/sdr/Q2SA815002), Dec 9, 2010: COOLING DUCT. BROKEN. AFTER LEVEL OFF FROM CLIMB, NR 2 ENGINE "B" LOOP BEGAN OSCILLATING TO TOP OF SCALE AND BACK AND ILLUMINATED THE FIRE DETECTION AMBER LIGHT INTERMITTENTLY; THE "
- [SDR Q2SA753007](https://openairdocs.org/sdr/Q2SA753007), Nov 27, 2010: UNKNOWN. SMOKE. SMOKE IN THE COCKPIT ON DESCENT. INSP ACFT IAW AMM 5-51-50. NO TROUBLE FOUND IN AIR-CONDITIONING SYS. REMOVED ALL PANELS IN F/E AREA P6, P7 AND P12 AND LOOKED F
- [SDR Q2SA815001](https://openairdocs.org/sdr/Q2SA815001), Nov 13, 2010: COWLING. DEPARTED. ON WALK AROUND, FOUND DAMAGE TO THE NR 3 ENGINE FIXED COWL. UPON INSPECTION, FOUND EVIDENCE THAT PORTIONS OF THE FIXED COWL DEPARTED CAUSING DAMAGE TO THE RIGHT
- [SDR EIAA2010066](https://openairdocs.org/sdr/EIAA2010066), Oct 13, 2010: ENGINE. FLAMED OUT. NR 4 ENGINE FLAMED OUT IN DESCENT INTO PANC. ABMORMAL PROCEDURES COMPLIED WITH. ENGINE WOULD NOT RESTART, NR 4 THROTTLE/THRUST LEVER REMAINED LOCKED AT IDLE UNT
- [SDR EIAA2010063](https://openairdocs.org/sdr/EIAA2010063), Oct 3, 2010: COMPRESSOR. STALLED. ABORTED TAKEOFF AT 110-115 KNOTS DUE TO 4 STALLS HEARD COMING FROM A/C RIGHT. NO COCKPIT ENGINE INDICATIONS ASSOCIATED WITH STALL, 12 TIRES THERMALED WITH ABORT
- [SDR Q2SA758012](https://openairdocs.org/sdr/Q2SA758012), Sep 24, 2010: ENGINE. FAILED. FLIGHT MAS6145, WHILE PREPARING FOR TAKEOFF, EXPERIENCED AN UNCONTAINED ENGINE FAILURE.
- [SDR Q2SA758011](https://openairdocs.org/sdr/Q2SA758011), Jul 22, 2010: ENGINE. LEAKING. DURING THE TAKEOFF ROLL IN OMDB NR 1 EGT GAUGE BRIEFLY WENT TO 0, THEN RETURNED TO NORMAL. DURING THE CLIMB TO FL 300 IT WAS NOTICED, NR 1 EGT WAS RUNNING SIGNI
- [SDR UIEA2010070200057](https://openairdocs.org/sdr/UIEA2010070200057), Jul 2, 2010: BLADE. DAMAGED. ON POST FLT, FOUND NR1 ENGINE HAD BIRD STRIKE. 3EA FAN BLADES DAMAGED (INSP IAW MM 05-51-14 NO EVIDENCE OF FOD IN COMPRESSOR SECTION OF NR 1 ENG 3 BLADES REPLAC
- [SDR UIEA2010062500032](https://openairdocs.org/sdr/UIEA2010062500032), Jun 25, 2010: RIB. CRACKED. STABILIZER LT L/E OTBD FAIRING LEST 440-496 HAS 4 CRACKS AT RIB ANGLES. INSTALLED 4 FILLERS AND 4 ANGLES. REPAIRED IAW SRM.
- [SDR UIEA2010062400037](https://openairdocs.org/sdr/UIEA2010062400037), Jun 24, 2010: SKIN. CORRODED. DURING C-CHECK IN TLV LEVEL 2 CORROSION WAS FOUND IN THE 65B04142-3 SKIN AT BS 1900 TO BS 1920 S48R. DAMAGE TRIMMED OUT, REPAIRED IAW SRM 53-30-03 FIG 1 AS A CA
- [SDR UIEA2010062400038](https://openairdocs.org/sdr/UIEA2010062400038), Jun 24, 2010: STRINGER. CORRODED. DURING C-CHECK IN TLV LEVEL 2 CORROSION WAS FOUND IN THE STRINGER BETWEEN BS1900 TO BS1920 AND STRINGER 48R. THE DAMAGE WAS CUT OUT, REMOVED AND SPLICED AT BS18
- [SDR UIEA2010062400042](https://openairdocs.org/sdr/UIEA2010062400042), Jun 24, 2010: SKIN. CORRODED. FUSELAGE SKIN CORRODED AT- BS 1241, S10-11R. MAJOR REPAIR PERFORMED IAW THE RAM 177- NRC960 IAW SRM 53-30-03, FIG 47.
- [SDR UIEA2010062200036](https://openairdocs.org/sdr/UIEA2010062200036), Jun 22, 2010: SKIN. DENTED. DURING C-CHECK, A DENT WAS FOUND IN THE SKIN AT BS 360-380 S-38R TO -39R. DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 022 AND SRM 53-30-03, FIG 26.
- [SDR WGFY2010FA0000495](https://openairdocs.org/sdr/WGFY2010FA0000495), May 25, 2010: STIFFENER. CRACKED. FUSELAGE RT SIDE VERTICAL STIFFENER STA 980, RBL 11,33 WAS CRACKED AND PERFORM HFEC INSPECTION METHOD TO ENSURE CRACK :+/- 20MM. REPLACED VERTICAL STIFFENER IAW
- [SDR UIEA201000188](https://openairdocs.org/sdr/UIEA201000188), May 20, 2010: FRAME. CRACKED. EO 4753A448, A CRACK WAS FOUND IN THE BS 420, S-10R FRAME WEB . THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 500789 AND SRM 53-10-04, FIGURE 11. PART 1 OF TH
- [SDR Q2SA748010](https://openairdocs.org/sdr/Q2SA748010), Apr 30, 2010: ENGINE. MALFUNCTIONED. DURING CLIMBOUT OF FL130 FROM SCEL THERE WAS VIBRATION FOLLOWED BY A LOUD BANG, ACCOMPANIED BY YAW AND HIGH EGT ON NUMBER 3 ENGINE. THE EGT LIGHTS FOR NR 3 CAME
- [SDR UIEA201000149](https://openairdocs.org/sdr/UIEA201000149), Apr 30, 2010: FRAME. DAMAGED. DURING C-CHECK AND INSPECTION IAW EO 4753A521, ADDITIONAL DAMAGE WAS FOUND IN THE BS 2231 FRAME INNER CHORD AT S-25R. THE DAMAGE WAS TRIMMED OUT AND REPAIRED IA
- [SDR UIEA201000150](https://openairdocs.org/sdr/UIEA201000150), Apr 30, 2010: INTERCOSTAL. DAMAGED. DURING C-CHECK, DAMAGE WAS FOUND IN THE 65B07942-26 INTERCOSTAL ON THE NWW SIDEWALL WL 153 STIFFENER BETWEEN BS 260 AND 280.THE INTERCOSTAL WAS REPLACED USING A
- [SDR UIEA201000144](https://openairdocs.org/sdr/UIEA201000144), Apr 29, 2010: SKIN. DAMAGED. DURING C-CHECK, LIGHTNING STRIKE DAMAGE WAS FOUND IN THE 65B07658-1002 SKIN AT BS 160-180, S-45R. THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 094 AND SRM 53
- [SDR UIEA201000151](https://openairdocs.org/sdr/UIEA201000151), Apr 29, 2010: SKIN. DAMAGED. DURING C-CHECK, DAMAGE WAS FOUND IN THE 65B04141-2 SKIN AT BS 1940, S-40L TO -41L.THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 270 AND SRM 53-30-03, FIGURE 1
- [SDR UIEA201000147](https://openairdocs.org/sdr/UIEA201000147), Apr 28, 2010: STRINGER. CRACKED. THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND IN THE BS 370 - 390, S40L STRINGER, CONSISTING OF A CRACK. THE DAMAGE WAS TRIMMED OUT AND REP
- [SDR UIEA201000148](https://openairdocs.org/sdr/UIEA201000148), Apr 28, 2010: SKIN. DAMAGED. THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, CORROSION WAS DETECTED COMMON TO LST SIDE WING INTERSPAR SKIN (65B14451-3 WING UPPER SKIN PANEL NR 1) AFT OF R
- [SDR UIEA201000152](https://openairdocs.org/sdr/UIEA201000152), Apr 28, 2010: CARGO TRACK. DAMAGED. DURING C-CHECK, DAMAGE WAS FOUND IN THE AFT LOWER CARGO COMPARTMENT SEAT TRACK AT RBL 25 BETWEEN BS 1800 AND 1820. THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW N
- [SDR UIEA201000145](https://openairdocs.org/sdr/UIEA201000145), Apr 27, 2010: SKIN. CORRODED. THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, CORROSION WAS DETECTED COMMON TO RT WING LOWER SKIN WS1285 - WS1320 (REF FIG 1). THE CORROSION WAS BLENDED OUT
- [SDR UIEA201000146](https://openairdocs.org/sdr/UIEA201000146), Apr 27, 2010: SKIN. DENTED. DURING C-CHECK, A DENT WAS FOUND IN THE SKIN AT BS 420-440, S12AL-13L.THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 212 AND SRM 53-30-03, FIG 1. THE SKIN AT T
- [SDR UIEA201000143](https://openairdocs.org/sdr/UIEA201000143), Apr 26, 2010: SKIN. DAMAGED. DURING C-CHECK, DAMAGE WAS FOUND IN THE 65B23675-1 SKIN AND 65B23678-2 DOUBLER AT BS 720, S-40R. THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW RFTA 00694-0004 AND
- [SDR 2010FA0000342](https://openairdocs.org/sdr/2010FA0000342), Apr 15, 2010: STIFFENER. CRACKED. PYLON NR 1, INBD NR 3, STIFFENER CRACK.
- [SDR 2010FA0000343](https://openairdocs.org/sdr/2010FA0000343), Apr 15, 2010: DOUBLER. CRACKED. MAIN ENTRY DOOR NR 1 UPPER OUTER SKIN DOUBLER CRACK, 0.35 INCH AT UPPER HINGE DOOR.
- [SDR 2010FA0000344](https://openairdocs.org/sdr/2010FA0000344), Apr 15, 2010: SKIN. CORRODED. FWD CARGO LOWER FUSELAGE SKIN AT STA 1000 WAS CORRODED LEVEL 2.
- [SDR 2010FA0000345](https://openairdocs.org/sdr/2010FA0000345), Apr 15, 2010: STIFFENER. CRACKED. PYLON NR 2 INBD NR 3 STIFFENER CRACK 0.67 INCH BETWEEN NAC STA 248 AND NAC STA 259 ON THE RT SIDE.
- [SDR 2010FA0000346](https://openairdocs.org/sdr/2010FA0000346), Apr 15, 2010: HINGE FITTING. CRACKED. HORIZ STABILIZER LT 2 PLACES 0.9 INCH AND 0.8 INCH & RT 2 PLACES 1.1 INCH AND 0.85 INCH, HINGE FITTING CRACKED.
- [SDR Q2SA758009](https://openairdocs.org/sdr/Q2SA758009), Apr 12, 2010: STIFFENER. CRACKED. PYLON NR 1 INBOARD NR 3 STIFFENER CRACK.

All 401: https://openairdocs.org/engine/ge-cf6-50e2/reports.md

## STCs that may be installed (OpenAirDocs) (4)

Approved for this engine 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 SE00025EN](https://openairdocs.org/stc/SE00025EN): Installation of International Aerospace Tubes, LLC, Master Drawing List TPC Stage 7 Cooling System , revision NR, dated December 15, 2011, or later FAA-Approved Revisions. United Technologies Corporation, Pratt & Whitney Division
- [STC SA1139NW-D](https://openairdocs.org/stc/SA1139NW-D): Install fireproof blankets on Engine Fan Reverser Intermediate Fireseal in lieu of Fireproof Intumescent Coating. United Airlines Inc
- [STC SE00969CH](https://openairdocs.org/stc/SE00969CH): Install AeroControlex P/N 2605290-001 variable stator feedback control cable. AeroControlex Group TransDigm Inc
- [STC SE00461LA](https://openairdocs.org/stc/SE00461LA): Install fireproof blankets on the engine fan reverser intermediate fireseal, in lieu of fireproof intumescent coating. Hi Temp Insulation Inc

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