# N408MC: 1998 Boeing 747-47UF

- Status: Valid registration
- Airframe: [Boeing 747-47UF](https://openairdocs.org/model/boeing-747-47uf) (registry code 1384812, 660 seats)
- Engine: [GE CF6-80 series](https://openairdocs.org/engine/ge-cf6-80-series) (registry code 30025)
- Data sheets: [TCDS E13NE](https://openairdocs.org/tcds/E13NE) (General Electric Company GE Aerospace) (OpenAirDocs)
- Serial number: 29261
- Year built: 1998
- Type: Fixed wing multi engine
- Engine type: Turbo-fan
- Airworthiness: Standard, transport
- Airworthiness date: December 14, 1998
- Certificate issued: May 3, 2021
- Expires: May 31, 2028
- Mode S code: A4CB6F
- Registered owner: [Atlas Air Inc](https://openairdocs.org/faa-owner/ATLAS%20AIR%20INC)
- Location: [Purchase, NY](https://openairdocs.org/faa-place/NY/Purchase)
- Owner type: Corporation
- Owner's area on the map: 41.0382° N, 73.7107° W: Placed by OpenAirDocs at the center of ZIP code 10577, within about a mile (OpenAirDocs). The owner's mailing address, not where the aircraft is based
- FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=408MC
- Page: https://openairdocs.org/aircraft/N408MC

From the FAA registry file of October 24, 2026. ADs below are matched by the registry's airframe and engine model codes. They may apply; each AD's applicability can narrow it by serial number, part number or installed equipment. This is not a compliance determination. The registry lists only the engine series, so ADs for every GE CF6-80 model are included.

## ADs that may apply (OpenAirDocs): 61 in force

### Matched by airframe (Boeing 747-47UF)

None in force.

### Matched by engine (GE CF6-80 series)

- [AD 2024-24-03](https://openairdocs.org/ad/2024-24-03): Engine Exhaust · Boeing MD-11, MD-11F and CF6-80C2D1F. Effective Jan 13, 2025
- [AD 2023-20-08](https://openairdocs.org/ad/2023-20-08): Engine (Turbine/Turboprop) · General Electric CF6-80C2B1F, CF6-80C2B2F, CF6-80C2B4F and 4 more. Effective Oct 19, 2023
- [AD 2021-26-22](https://openairdocs.org/ad/2021-26-22): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Mar 14, 2022
- [AD 2022-02-18](https://openairdocs.org/ad/2022-02-18): Engine Mount Section · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 3 more. Effective Feb 25, 2022
- [AD 2021-14-11](https://openairdocs.org/ad/2021-14-11): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 25 more. Effective Aug 27, 2021
- [AD 2021-03-02](https://openairdocs.org/ad/2021-03-02): Fuel Control/Turbine Engines · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Mar 31, 2021
- [AD 2020-22-02](https://openairdocs.org/ad/2020-22-02): Engine Fuel and Control · General Electric CF6-80C2A5F, CF6-80C2B1F, CF6-80C2B2F and 13 more. Effective Dec 3, 2020
- [AD 2018-07-05](https://openairdocs.org/ad/2018-07-05): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 11, 2018
- [AD 2017-11-15](https://openairdocs.org/ad/2017-11-15): Turbine/ Turboprop Engine--Turbine Section · General Electric CF6-80C2L1F. Effective Jul 13, 2017
- [AD 2016-08-10](https://openairdocs.org/ad/2016-08-10): Accessory heat shield · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Jun 1, 2016
- [AD 2014-21-01](https://openairdocs.org/ad/2014-21-01): Fuel manifold · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Nov 28, 2014
- [AD 2013-08-20](https://openairdocs.org/ad/2013-08-20): Fuel tube · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 14 more. Effective May 31, 2013
- [AD 2012-03-12](https://openairdocs.org/ad/2012-03-12): No. 3 bearing packing · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 21 more. Effective Apr 5, 2012
- [AD 2012-04-05](https://openairdocs.org/ad/2012-04-05): Electronic control unit (ECU) · General Electric CF6-80C2B1F, CF6-80C2B1F1, CF6-80C2B1F2 and 8 more. Effective Mar 30, 2012
- [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 2009-21-07](https://openairdocs.org/ad/2009-21-07): Thrust and thrust control · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 21 more. Effective Dec 1, 2009
- [AD 2009-14-08](https://openairdocs.org/ad/2009-14-08): High-pressure compressor rotor (HPCR) stages 11-14 spool/ shafts · General Electric CF6-80C2B5F. Effective Aug 5, 2009
- [AD 2009-08-06](https://openairdocs.org/ad/2009-08-06): Stage 1 high-pressure turbine (HPT) rotor  
 disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 18, 2009
- [AD 2009-07-10](https://openairdocs.org/ad/2009-07-10): High-pressure turbine rotor (HPTR) · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 6, 2009
- [AD 2009-07-03](https://openairdocs.org/ad/2009-07-03): Eddy current inspection (ECI) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Apr 30, 2009
- [AD 2009-04-10](https://openairdocs.org/ad/2009-04-10): Critical life-limited parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 30 more. Effective Mar 30, 2009
- [AD 2008-21-11](https://openairdocs.org/ad/2008-21-11): Low-pressure turbine (LPT) cases · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 25 more. Effective Nov 28, 2008
- [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 2007-24-07](https://openairdocs.org/ad/2007-24-07): Thermal spray coating on certain stage 1 fan disks · General Electric CF6-80C2B1. Effective Jan 2, 2008
- [AD 2007-22-07](https://openairdocs.org/ad/2007-22-07): Electronic control unit (ECU) · General Electric CF6-80C2D1F. Effective Nov 28, 2007
- [AD 2007-21-06](https://openairdocs.org/ad/2007-21-06): Electronic control unit (ECU) · General Electric CF6-80C2A5F. Effective Nov 15, 2007
- [AD 2007-11-20](https://openairdocs.org/ad/2007-11-20): Fuel shroud retaining rings · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 22 more. Effective Jul 10, 2007
- [AD 2007-05-14](https://openairdocs.org/ad/2007-05-14): Cast titanium weld- repaired forward engine mount platforms · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Apr 9, 2007
- [AD 2006-16-06](https://openairdocs.org/ad/2006-16-06): Certain stage 1 high- pressure turbine (HPT) rotor disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Sep 5, 2006
- [AD 2006-06-08](https://openairdocs.org/ad/2006-06-08): Latching system of the fan reverser · General Electric CF6-80C2D1F. Effective Apr 25, 2006
- [AD 2005-17-05](https://openairdocs.org/ad/2005-17-05): High pressure compressor rotor (HPCR) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 25 more. Effective Sep 27, 2005
- [AD 2005-06-07](https://openairdocs.org/ad/2005-06-07): Directional pilot valve (DPV) assembly · General Electric CF6-80A1, CF6-80A3, CF6-80C2A1 and 5 more. Effective Apr 25, 2005
- [AD 2004-22-07](https://openairdocs.org/ad/2004-22-07): Stage 2 nozzle guide vanes (HPT S2 NGVs) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Dec 1, 2004
- [AD 2004-07-13](https://openairdocs.org/ad/2004-07-13): High pressure turbine (HPT) stage 1 disks · General Electric CF6-80C2A5F, CF6-80C2B5F, CF6-80C2B7F and 1 more. Effective May 6, 2004
- [AD 2003-12-08](https://openairdocs.org/ad/2003-12-08): Directional pilot valve · General Electric CF6-80A1, CF6-80A3, CF6-80C2A1 and 5 more. Effective Jul 23, 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 2002-22-12](https://openairdocs.org/ad/2002-22-12): Titeflex hoses · BAE Systems ATP, Avro 146-RJ100A, Avro 146-RJ70A and 122 more. Effective Dec 13, 2002
- [AD 2001-06-09](https://openairdocs.org/ad/2001-06-09): Aft Engine Mount Link Assemblies · General Electric CF6-80A3. Effective May 1, 2001
- [AD 2000-12-08](https://openairdocs.org/ad/2000-12-08): Mount Link Assemblies · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 4 more. Effective Aug 28, 2000
- [AD 2000-03-04](https://openairdocs.org/ad/2000-03-04): General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Apr 10, 2000
- [AD 99-01-01](https://openairdocs.org/ad/99-01-01): Accessory Gearbox (AGB) idler adapters · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Jan 21, 1999
- [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 96-16-07](https://openairdocs.org/ad/96-16-07): Rear Right Hand Mount Link · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 17 more. Effective Aug 28, 1996
- [AD 95-17-16](https://openairdocs.org/ad/95-17-16): Compressor Rear Frame · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective Nov 7, 1995
- [AD 95-10-11](https://openairdocs.org/ad/95-10-11): Fan Reversers · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 17 more. Effective May 31, 1995
- [AD 94-20-06](https://openairdocs.org/ad/94-20-06): Oil System · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Dec 27, 1994
- [AD 94-07-04](https://openairdocs.org/ad/94-07-04): High Pressure Turbine Disk · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 23, 1994
- [AD 94-06-03](https://openairdocs.org/ad/94-06-03): High Pressure Turbine Disk · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Apr 29, 1994

### Historical (superseded or no longer in force)

- [AD 2020-20-13](https://openairdocs.org/ad/2020-20-13) (historical): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Nov 12, 2020
- [AD 2018-15-04](https://openairdocs.org/ad/2018-15-04) (historical): Turbine/Turboprop Engine--Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Oct 2, 2018
- [AD 2009-05-02](https://openairdocs.org/ad/2009-05-02) (historical): Drainless fuel manifold assemblies · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Mar 31, 2009
- [AD 2007-12-07](https://openairdocs.org/ad/2007-12-07) (historical): Electronic control units (ECUs) · General Electric CF6-80C2B1F, CF6-80C2B2F, CF6-80C2B4F and 5 more. Effective Jul 11, 2007
- [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 2004-04-07](https://openairdocs.org/ad/2004-04-07) (historical): Stage 1 HPT rotor disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Mar 12, 2004
- [AD 2003-01-05](https://openairdocs.org/ad/2003-01-05) (historical): Dovetail slots · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective Jan 28, 2003
- [AD 2002-07-12](https://openairdocs.org/ad/2002-07-12) (historical): Life Limits Section of Continued Airworthiness (ICA) - Selected Critical Life-limited Parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 27 more. Effective May 15, 2002
- [AD 2001-10-07](https://openairdocs.org/ad/2001-10-07) (historical): High Pressure Turbine Rotor Disks · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Jun 18, 2001
- [AD 2000-08-12](https://openairdocs.org/ad/2000-08-12) (historical): Life-limited Parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 10 more. Effective Oct 23, 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 2000-04-14](https://openairdocs.org/ad/2000-04-14) (historical): Fuel tube flange seating · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 12 more. Effective May 1, 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 99-18-20](https://openairdocs.org/ad/99-18-20) (historical): Inadvertent In-flight Thrust Reverser · General Electric Aircraft Engines CF6-50 Series (all), CF6-80A1, CF6-80A3 and 6 more. Effective Nov 2, 1999
- [AD 99-18-19](https://openairdocs.org/ad/99-18-19) (historical): Inadvertent Thrust Reverser · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 7 more. Effective Sep 24, 1999
- [AD 99-08-13](https://openairdocs.org/ad/99-08-13) (historical): General Electric CF6-80A, CF6-80A1, CF6-80A2 and 26 more. Effective May 13, 1999
- [AD 98-15-17](https://openairdocs.org/ad/98-15-17) (historical): Link Assembly · General Electric CF6-80A3. Effective Aug 7, 1998
- [AD 91-20-02](https://openairdocs.org/ad/91-20-02) (historical): Fuel Manifolds · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 12 more. Effective Nov 25, 1991
- [AD 90-26-01](https://openairdocs.org/ad/90-26-01) (historical): Fuel Manifold Systems · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 11 more. Effective Dec 20, 1990

All 80: https://openairdocs.org/aircraft/N408MC/ads.md

## Information bulletins (advisory) (5 in force)

- [SAIB 2023-15](https://openairdocs.org/saib/2023-15): Falsified Forms from AOG Technics. Issued Dec 19, 2023
- [SAIB NE-11-27](https://openairdocs.org/saib/NE-11-27): Fuel Injector Nozzle - CF6-80 Improperly Welded Fuel Nozzles. Issued Apr 5, 2011
- [SAIB NE-10-37](https://openairdocs.org/saib/NE-10-37): Engine Fuel and Control: FADEC Fuel Metering Valve Resolver Feedback Faults. Issued Jul 12, 2010
- [SAIB NE-08-44](https://openairdocs.org/saib/NE-08-44): Engine Thrust Reverser  Transcowl Clevis Pin. Issued Sep 3, 2008
- [SAIB NE-07-01](https://openairdocs.org/saib/NE-07-01): Dual engine flameouts on twin engine airplanes. Issued Oct 12, 2006

## NTSB investigations

None matched to N408MC.

## FAA accident and incident reports (1)

From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model.

- [Incident 20200804013379I](https://openairdocs.org/incident/20200804013379I), Aug 4, 2020: Boeing 747-47UF (N408MC), Shanghai, Minor damage. On August 4, 2020, N408GT, operating as GTI8939, from incheon, south korea (icn) to Shanghai, china (pvg) suffered pod strikes to the #1 ,#2, and #4 engines on…

## Service difficulty reports (206, newest 50)

As reported by operators and repair stations. Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.

- [SDR UIEA2026100400944](https://openairdocs.org/sdr/UIEA2026100400944), Oct 2, 2026: PCB. DAMAGED. EQUIPMENT COOLING EICAS CAUTION F270 ON CLIMB. CAPT ND BLANK FOR 30", FO PFD FLICKERED ON CLIMB. MESSAGE BLANKED THEN LOST CAPT ND AND FO ND WAS INTERMITTENT. R
- [SDR UIEA2026081200747](https://openairdocs.org/sdr/UIEA2026081200747), Aug 12, 2026: ENGINE. FAULTED. ENGINE 2 OIL TEMP INFLIGHT. ENG 2 IFS. PERFORMED WINDMILLING INSPECTION & NO TROUBLE FOUND IAW AMM 72-00-00/601. PERFORMED ENG MAG CHIP INSPECTION & NO TROUBLE 
- [SDR UIEA2026080700685](https://openairdocs.org/sdr/UIEA2026080700685), Aug 7, 2026: HEAT EXCHANGER. FAULTED. ENG 2 OIL TEMP EICAS MSG. FL 380 MAX OIL TEMP APPROX 194. ENG 2 SHUT DOWN. PERFORMED FIM 79-00, FT FIG 109. R & R FUEL/OIL HEAT EXCHANGER IAW AMM 79-21-01-404-0
- [SDR UIEA2026063000562](https://openairdocs.org/sdr/UIEA2026063000562), Jun 27, 2026: FLAP. DAMAGED. SUSPECTED HARD LANDING. PERFORMED PHASE 1A INSP PER AMM 05-51-05-222-081. DURING INSP, FOUND LH FLAP DAMAGE AT MIDDLE OF FOREFLAP LEVEL. SUBSEQUENT DAMAGE TO TH
- [SDR UIEA2025112901330](https://openairdocs.org/sdr/UIEA2025112901330), Nov 29, 2025: ELEC CONNECTOR. FAULTED. ON DEPARTURE AT 1000' AGL, HYD QTY LOW 4 EICAS ADVISORY MESSAGE, RAN NNC 13.29, SECURED NR 4 HYDRAULIC SYSTEM OFF. T/S PER WDM 29-33-12-2 TO PERFORM WIRING CHKS
- [SDR UIEA2025083001150](https://openairdocs.org/sdr/UIEA2025083001150), Aug 30, 2025: SOLENOID. FAULTED. ENG 4 FUEL VALVE EICAS, ENG 4 FUEL VALVE STATUS, #4 ENG WOULD NOT SHUT DOWN UPON FUEL CONTROL SWITCHING OFF POSN. L13 CB FOUND IN OUT POSITION.(<P>R/R SOLENOID 
- [SDR UIEA2025073001071](https://openairdocs.org/sdr/UIEA2025073001071), Jul 30, 2025: SOFTWARE. FAULTED. L NAV WON'T ENGAGE. RELOADED ALL ASSOCIATED SOFTWARE INTO BOTH LT & RT FMC IAW AMM 34-61-00. ALL GROUND TEST PASSED. VERIFIED ALL SOFTWARE CORRECT CONFIG.
- [SDR UIEA2025060700734](https://openairdocs.org/sdr/UIEA2025060700734), Jun 7, 2025: STARTER. FAULTED. ENG 1 OIL PRESS EICAS MSG. ENG 1 OIL QTY DROPPED ON INITIAL CLIMB, PRESSURE DECREASED STEADILY UNTIL ENG 1 SHUT DOWN IN FLIGHT. ENG WINDMILL FOR 15 MINUTES.(<P>
- [SDR UIEA2025052600695](https://openairdocs.org/sdr/UIEA2025052600695), May 26, 2025: PANEL. DAMAGED. DURING DESCENT, A/C EXPERIENCED HIGH FREQUENCY VIBRATIONS DURING SPEED BRAKE APPLICATIONS. ONCE LANDED IN HKG, STATION NOTICED THE #6 SPEED BRAKE PANEL ASSY DAM
- [SDR UIEA2025020200111](https://openairdocs.org/sdr/UIEA2025020200111), Feb 6, 2025: RIB. CRACKED. EMP HORIZONTAL STABILIZER TIP MOST O/B CLOSURE RIB WEB P/N: 65B03520-60 FOUND CRACKED.(<P>EMP HORIZONTAL STABILIZER TIP MOST O/B CLOSURE RIB WEB P/N: 65B03520-6
- [SDR UIEA2025020200110](https://openairdocs.org/sdr/UIEA2025020200110), Feb 6, 2025: RIB. CRACKED. EMP HORIZONTAL STABILIZER TIP MOST O/B CLOSURE RIB LOWER CHORD P/N: 65B03520-54 FOUND CRACKED.(<P>EMP HORIZONTAL STABILIZER TIP MOST O/B CLOSURE RIB LOWER CHORD
- [SDR UIEA2024052000396](https://openairdocs.org/sdr/UIEA2024052000396), May 23, 2024: DOUBLER. CRACKED. DOOR 1 EXTERIOR LOWER HINGE DOUBLER FOUND CRACK(<P>DOOR 1 LH EXTERIOR LOWER HINGE AREA DOUBLER P/N: 65B22350-7 REPLACED AND INSTALLED IAW SRM 51-40-02 AND BOEIN
- [SDR UIEA2024012500023](https://openairdocs.org/sdr/UIEA2024012500023), Feb 5, 2024: SKIN. PUNCTURED. L/H I/B FLAP FORE FLAP UPPER SURFACE FOUND 1EA PUNCH HOLE DAMAGED AS MARK.(<P>L/H I/B FLAP FORE FLAP UPPER SURFACE PUNCH HOLE DAMAGE AREA. PERFORMED HOT BOND RE
- [SDR UIEA2024012500024](https://openairdocs.org/sdr/UIEA2024012500024), Feb 5, 2024: SKIN. DAMAGED. LHW I/B FORE FLAP LWR SURFACE FOUND DAMAGED AS MARK (156" FROM O/B TO I/B).(<P>LHW I/B FORE FLAP LWR SURFACE 156" FROM O/B TO I/B DAMAGED AREA. PERFORMED HOT BO
- [SDR UIEA2024012500025](https://openairdocs.org/sdr/UIEA2024012500025), Feb 5, 2024: SKIN. DELAMINATED. L/H I/B FLAP MID FLAP MOST O/B LWR SURFACE FOUND DELAMINATION AS MARK (15" TO O/B EDGE).(<P>L/H I/B FLAP MID FLAP MOST O/B LOWER SURFACE (15" TO O/B EDGE) DELAM
- [SDR UIEA2024012500026](https://openairdocs.org/sdr/UIEA2024012500026), Feb 5, 2024: SKIN. DELAMINATED. LHW T/E I/B AFT FLAP L/E 66" FOUND DELAMINATION AS MARKED (COUNT FROM O/B).(<P>LHW T/E I/B AFT FLAP L/E 66" (COUNT FROM O/B) DELAMINATION AREA. PERFORMED HOT BO
- [SDR UIEA2024012500028](https://openairdocs.org/sdr/UIEA2024012500028), Feb 5, 2024: SKIN. DENTED. LHW I/B AFT FLAP LWR T/E SURFACE AT MID AREA FOUND 1EA DENT AS MARK (155" FROM I/B TO O/B).(<P>LHW I/B AFT FLAP LWR T/E SURFACE 155" FROM I/B DENT AREA. PERFORM
- [SDR UIEA2024012500029](https://openairdocs.org/sdr/UIEA2024012500029), Feb 5, 2024: SKIN. PUNCTURED. L/H I/B FLAP AFT FLAP T/E UPPER SURFACE FOUND 1EA PUNCH DAMAGED AS MARK.(<P>LH I/B FLAP AFT FLAP T/E UPPER SURFACE PUNCH DAMAGED AREA. PERFORMED HOT BOND REPAIR
- [SDR UIEA2024012500030](https://openairdocs.org/sdr/UIEA2024012500030), Feb 5, 2024: SKIN. DENTED. LHW I/B AFT FLAP O/B LWR SURFACE FOUND 1EA DENT AS MARK (146" FROM I/B TO O/B).(<P>LHW I/B AFT FLAP O/B LWR SURFACE (146" FROM I/B TO O/B) DENT AREA. PERFORMED 
- [SDR UIEA2024012500031](https://openairdocs.org/sdr/UIEA2024012500031), Feb 5, 2024: SKIN. DELAMINATED. LHW T/E I/B AFT FLAP LOWER SURFACE T/E 130" FOUND DELAMINATION AS MARK. (COUNT FROM I/B TO O/B)(<P>LHW T/E I/B AFT FLAP LOWER SURFACE T/E 130" (COUNT FROM I/B T
- [SDR UIEA2024012500032](https://openairdocs.org/sdr/UIEA2024012500032), Feb 5, 2024: SKIN. DELAMINATED. LHW T/E I/B FLAP FLAP LOWER SURFACE L/E 47" (COUNT FROM I/B) FOUND DELAMINATION AS MARKED.(<P>LHW T/E I/B AFT FLAP LOWER SURFACE L/E 47" (COUNT FROM I/B) DELAMI
- [SDR UIEA2024012500033](https://openairdocs.org/sdr/UIEA2024012500033), Feb 5, 2024: PANEL. DELAMINATED. L/H O/B FLAP MID FLAP O/B CARRIAGE ASSY COVER PANEL FOUND DELAMINATION AS MARK.(<P>L/H O/B FLAP MID O/B CARRIAGE ASSY COVER PANEL DELAMINATION AREA. PERFORMED H
- [SDR UIEA2024012500034](https://openairdocs.org/sdr/UIEA2024012500034), Feb 5, 2024: SKIN. DELAMINATED. RHW T/E I/B AFT FLAP LOWER SURFACE T/E 100" FOUND DELAMINATION AS MARKED (COUNT FROM I/B).(<P>RHW T/E I/B AFT FLAP LOWER SURFACE T/E 100" (COUNT FROM I/B) DELAM
- [SDR UIEA2024012500035](https://openairdocs.org/sdr/UIEA2024012500035), Feb 5, 2024: SKIN. DELAMINATED. RHW T/E I/B AFT FLAP LOWER SURFACE T/E 122" FOUND DELAMINATION AS MARKED (COUNT FROM I/B).(<P>RHW T/E I/B AFT FLAP LOWER SURFACE T/E 122" (COUNT FROM I/B) DELAM
- [SDR UIEA2024012500036](https://openairdocs.org/sdr/UIEA2024012500036), Feb 5, 2024: SKIN. DELAMINATED. RHW T/E I/B MID FLAP LOWER SURFACE L/E 124" FOUND DELAMINATION AS MARKED (COUNT FROM TO I/B).(<P>RHW T/E I/B MID FLAP LOWER SURFACE L/E 124" (COUNT FROM TO I/B)
- [SDR UIEA2024012500037](https://openairdocs.org/sdr/UIEA2024012500037), Feb 5, 2024: FRAME. CRACKED. FX STA 1480 RH BULKHEAD FRAME WEB FOUND CRACK(<P>FRAME WEB REPAIRED AS PER SRM 53-40-08-2R-1 REPAIR 1 FIG 201. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024012500038](https://openairdocs.org/sdr/UIEA2024012500038), Feb 5, 2024: SKIN. DELAMINATED. RHW T/E I/B AFT FLAP LOWER SURFACE T/E 48" FOUND DELAMINATION AS MARKED (COUNT FROM I/B).(<P>RHW T/E I/B AFT FLAP LOWER SURFACE T/E 48" (COUNT FROM I/B) DELAMIN
- [SDR UIEA2024012500039](https://openairdocs.org/sdr/UIEA2024012500039), Feb 5, 2024: SKIN. DELAMINATED. RHW T/E I/B MID FLAP L/E 2" (COUNT FROM I/B) FOUND DELAMINATION AS MARK.(<P>RHW T/E I/B MID FLAP L/E 2" (COUNT FROM I/B) DELAMINATION AREA PERFORMED REPAIR AS P
- [SDR UIEA2024012500040](https://openairdocs.org/sdr/UIEA2024012500040), Feb 5, 2024: PANEL. DELAMINATED. R/H I/B T/E FLAP MID FLAP O/B CARRIAGE ASSY UPPER COVER APNEL FOUND DELAMINATION AS MARK.(<P>R/H I/B T/E FLAP MID FLAP O/B CARRIAGE ASSY UPPER COVER PANEL DELAM
- [SDR UIEA2024012500041](https://openairdocs.org/sdr/UIEA2024012500041), Feb 5, 2024: SKIN. DELAMINATED. RHW T/E I/B AFT FLAP LOWER SURFACE T/E 155" FOUND DELAMINATION AS MARKED (COUNT FROM I/B).(<P>RHW T/E I/B AFT FLAP LOWER SURFACE T/E 155" (COUNT FROM I/B) DELAM
- [SDR UIEA2024012500042](https://openairdocs.org/sdr/UIEA2024012500042), Feb 5, 2024: FAIRING. DELAMINATED. RHW O/B FWD FLAP FWD FAIRING 48" FOUND DELAMINATION AS MARKED (COUNT FROM O/B).(<P>RHW O/B FWD FLAP FWD FAIRING 48" (COUNT FROM O/B) DELAMINATION AREA. PERFORME
- [SDR UIEA2024012800046](https://openairdocs.org/sdr/UIEA2024012800046), Feb 5, 2024: SEAT TRACK. DAMAGED. M/D STA 1890 RBL 11 SEAT TRACK CTR GUIDE STOP HOLE FOUND ELONGATED(<P>SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12 REPAIR 12. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024012800047](https://openairdocs.org/sdr/UIEA2024012800047), Feb 5, 2024: TENSION TIE. CRACKED. LH BS 840 UPPER DECK TENSION TIE 1EA CRACK FOUND AT AFT CHANNEL(<P>TENSION TIE REPAIRED AS PER SRM 53-20-30-2R-1 REPAIR. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024012800048](https://openairdocs.org/sdr/UIEA2024012800048), Feb 5, 2024: TENSION TIE. CRACKED. LH BS 880 UPPER DECK TENSION TIE 1EA CRACK FOUND AT AFT CHANNEL(<P>TENSION TIE REPAIRED AS PER SRM 53-20-30-2R-1 REPAIR 1. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024012800049](https://openairdocs.org/sdr/UIEA2024012800049), Feb 5, 2024: TENSION TIE. CRACKED. RH BS 840 UPPER DECK TENSION TIE 1EA CRACK FOUND AT 1 O/C POSITION OF THE AFT CHANNEL(<P>TENSION TIE REPAIRED AS PER SRM 53-20-30-2R-1 REPAIR 1. NO FURTHER DEFE
- [SDR UIEA2024012800050](https://openairdocs.org/sdr/UIEA2024012800050), Feb 5, 2024: CHANNEL. CRACKED. LH BS 900 UPPER DECK TENSION TIE AFT CHANNEL 1EA HOLE FOUND CRACK(<P>TENSION TIE REPAIRED AS PER SRM 53-20-30-2R-1 REPAIR 1. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024012800051](https://openairdocs.org/sdr/UIEA2024012800051), Feb 5, 2024: SKIN. CORRODED. FUSELAGE SKIN AT LOWER LOBE CIRCUMFERENTIAL SPLICE LOCATION STA 1715 S45R FOUND CORROSION APPROX 1" X 1"(<P>SKIN REPAIRED AS PER SRM 53-00-01-2R-1 REPAIR 1 FIG 
- [SDR UIEA2024012900052](https://openairdocs.org/sdr/UIEA2024012900052), Feb 5, 2024: SKIN. CORRODED. LHW I/B AFT FLAP FOUNDÂ BULGE UP(<P>PERFORMED REPAIR AT BULGE UP AREA IAW RI-57-53-16705. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024013000053](https://openairdocs.org/sdr/UIEA2024013000053), Feb 5, 2024: SKIN. DENTED. LHW O/B T/E AFT FLAP O/B PANEL UPPER SURFACE FOUND SEVERAL AREA DENT MARK AS MARKED.(<P>METAL HOT BOND REPAIR CARRIED OUT AS PER RI-57-51-16699 REV.A. NO FURTHE
- [SDR UIEA2024013000054](https://openairdocs.org/sdr/UIEA2024013000054), Feb 5, 2024: SKIN. DENTED. RHW O/B T/E AFT FLAP O/B PANEL UPPER SURFACE FOUND SEVERAL AREA DENT MARK AS MARKED.(<P>METAL HOT BOND REPAIR CARRIED OUT AS PER RI-57-51-16700 REV.A. NO FURTHE
- [SDR UIEA2024013100055](https://openairdocs.org/sdr/UIEA2024013100055), Feb 5, 2024: FRAME. CRACKED. LH BS 2598 B/HEAD INNER CHORD 1EA HOLE FOUND CRACK AT 3ND LAYER (COUNTING FROM AFT) AT 5 O'CLOCK POSITION APPROX 0.050" IN DEPTH(<P>INNER CHORD CRACK AREA REPAI
- [SDR UIEA2024013100057](https://openairdocs.org/sdr/UIEA2024013100057), Feb 5, 2024: LONGERON. CRACKED. FUS - 2EA CRACKS WERE FOUND ON RH BS 1480-1540 STR 32-33 LONGERON EXTENSION FITTING(<P>LONGERON EXTENSION FITTING REPLACEMENT CARRIED OUT AS PER ATLAS AIR EO 44
- [SDR UIEA2024013100058](https://openairdocs.org/sdr/UIEA2024013100058), Feb 5, 2024: PANEL. CRACKED. M/D STA 1720 L/H DADO PNL FOUND CRACK(<P>DADO PNL CRACK AREA REPAIRED AS PER RI-25-21-16675 REV.A. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024020100059](https://openairdocs.org/sdr/UIEA2024020100059), Feb 5, 2024: LADDER. CRACKED. M/D CREW LADDER I/B SIDE #7 & 10 STEP FOUND CRACK(<P>#7 AND #10 STEP CRACK AREA REPAIRED AS PER RI-25-50-16667 REV.A. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024020100060](https://openairdocs.org/sdr/UIEA2024020100060), Feb 5, 2024: SKIN. CORRODED. FX R/H AIRCON BAY STA 1000-1003 CENTER SECTION LOWER SURFACE CORR. AT RBL 15" - RBL 29"(<P>SKIN CORROSION AREA REPAIRED AS PER RI-57-10-16703 REV.A. NO FURTHER 
- [SDR UIEA2024020100061](https://openairdocs.org/sdr/UIEA2024020100061), Feb 5, 2024: BRACKET. DAMAGED. APU COMPT L/H FRAME STA 2674 WIRE BRACKET AND ATT FRAME RIVET HOLES FOUND ELONGATED(<P>WIRE BRACKET REPLACED AS PER SRM 51-10-02, NEW BRACKET HOLES TRANSFERRED 
- [SDR UIEA2024020100062](https://openairdocs.org/sdr/UIEA2024020100062), Feb 5, 2024: SKIN. CRACKED. FX - FUSELAGE SKIN STA 1680 STR 41R FOUND CORR CRACK(<P>SKIN REPAIRED AS PER RI-53-61-16685 REV.A. NO FURTHER DEFECTS NOTED.</P>)
- [SDR UIEA2024020100063](https://openairdocs.org/sdr/UIEA2024020100063), Feb 5, 2024: SUPPORT. CRACKED. LHW L/E CAVITY HOLES 1300 FIXED PNL SUPPORT CRACK (AFT OF #4 V/C FLAP)(<P>SUPPORT BEAM REPAIRED AS PER RI-57-41-16684 REV.A. NO FURTHER DEFECTS NOTED</P>)
- [SDR UIEA2024020100064](https://openairdocs.org/sdr/UIEA2024020100064), Feb 5, 2024: CLOSEOUT PANEL. CRACKED. M/D STA 1241 LBL 77-99 CLOSURE PNL FOUND CRACK.(<P>CLOSURE PNL REPLACED AS PER SRM 51-10-02, NEW PNL HOLES TRANSFERRED AS PER SRM 51-40-05 AND NEW PNL INSTALLED
- [SDR UIEA2024020100065](https://openairdocs.org/sdr/UIEA2024020100065), Feb 5, 2024: NONE. NONE. ACCOMPLISHMENT OF EO 4453A301 REV.11, WE FOUND ONE EACH FREEZE PLUG INSTALLED ON UPPER DECK R/H STA 880 FRAME AREA.(<P>FRAME REPAIRED AS PER RI NO. RI-53-20-167

All 206: https://openairdocs.org/aircraft/N408MC/reports.md

## STCs that may be installed (OpenAirDocs) (6)

Approved for this aircraft's airframe or engine model, in force first, then newest. The registry doesn't record which STCs an aircraft has; its records do.

### Approved for the engine (GE CF6-80 series)

- [STC SE01543CH](https://openairdocs.org/stc/SE01543CH): Replace Hamilton Sundstrand P/N 778839-13, 778839-14, 778839-19, 778839-20, 778839-37, 778839-38, 816682-1, 840618-2, 880724 carbon bushings with Cook Airtomic P/N AIR22947 Slotted Entry Busing in the High Pressure Shutoff Valve. Cook Airtomic. Lists CF6-80A
- [STC SE01478CH](https://openairdocs.org/stc/SE01478CH): Installation of Cook Airtomic alignment joint p/n AIR 22912. Cook Airtomic. Lists CF6-80C2 Series
- [STC SE00969CH](https://openairdocs.org/stc/SE00969CH): Install AeroControlex P/N 2605290-001 variable stator feedback control cable. AeroControlex Group TransDigm Inc. Lists CF6-80A
- [STC SE01471AT](https://openairdocs.org/stc/SE01471AT): Replace right and left side Rohr, Inc. fire detection harness on GE CF6-80C2 engine. Unison Industries. Lists CF6-80C2 Series
- [STC SE00463LA](https://openairdocs.org/stc/SE00463LA): Install fireproof blankets on the engine fan reverser intermediate fireseal, in lieu of fireproof intumescent coating. This STC is jointly by owned by Hi Temp Insulation and MRA Systems acting through Middle River Aircraft Systems, 103 Chesapeake Park Plaza, Baltimore, MD 21220. Hi Temp Insulation Inc. Lists CF6-80C2A1
- [STC SA2227SO](https://openairdocs.org/stc/SA2227SO): Installation of wiring and associated components for utilization of the Rolls Royce, Inc., ARINC, interface/readers UT1317 or UT1317/1, for the purpose of acquisition, recording, and analysis in real time of engine/aircraft/ systems. (767 SERIES POWERED BY RR RB-11-524 SERIES. Rolls Royce, Inc

## Related

- Other Boeing 747-47UF aircraft: https://openairdocs.org/model/boeing-747-47uf/aircraft.md
- The GE CF6-80 series engine: https://openairdocs.org/engine/ge-cf6-80-series.md

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