# N852FD: 2010 Boeing 777-FS2

- Status: Valid registration
- Airframe: [Boeing 777-FS2](https://openairdocs.org/model/boeing-777-fs2) (registry code 138527H, 13 seats)
- Engine: [GE GE90-110B1](https://openairdocs.org/engine/ge-ge90-110b1) (registry code 30046)
- Data sheets: [TCDS E00049EN](https://openairdocs.org/tcds/E00049EN) (General Electric Company GE Aviation) (OpenAirDocs)
- Serial number: 37723
- Year built: 2010
- Type: Fixed wing multi engine
- Engine type: Turbo-fan
- Airworthiness: Standard, transport
- Airworthiness date: February 20, 2010
- Certificate issued: March 2, 2010
- Expires: December 31, 2029
- Mode S code: ABAF47
- Registered owner: [Federal Express Corp](https://openairdocs.org/faa-owner/FEDERAL%20EXPRESS%20CORP)
- Location: [Memphis, TN](https://openairdocs.org/faa-place/TN/Memphis)
- Owner type: Corporation
- Owner's area on the map: 35.0351° N, 89.9272° W: Placed by OpenAirDocs at the center of ZIP code 38118, within about 3 miles (OpenAirDocs). The owner's mailing address, not where the aircraft is based
- FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=852FD
- Page: https://openairdocs.org/aircraft/N852FD

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.

## ADs that may apply (OpenAirDocs): 21 in force

### Matched by airframe (Boeing 777-FS2)

None in force.

### Matched by engine (GE GE90-110B1)

- [AD 2025-25-07](https://openairdocs.org/ad/2025-25-07): Turbine Section · General Electric Company GE GE90-90B, GE90-94B, GE90-110B1 and 1 more. Effective Feb 6, 2026
- [AD 2025-07-10](https://openairdocs.org/ad/2025-07-10): Fuel Controlling System · General Electric Company GE GE90-110B1 and GE90-115B. Effective May 21, 2025
- [AD 2024-06-15](https://openairdocs.org/ad/2024-06-15): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective May 14, 2024
- [AD 2023-26-07](https://openairdocs.org/ad/2023-26-07): Turbine Section · General Electric GE90-90B, GE90-94B, GE90-110B1 and 1 more. Effective Feb 27, 2024
- [AD 2023-04-19](https://openairdocs.org/ad/2023-04-19): Turbine Engine Compressor Section · General Electric GE90-110B1 and GE90-115B. Effective Mar 27, 2023
- [AD 2022-23-09](https://openairdocs.org/ad/2022-23-09): Turbine Engine Compressor Section, Turbine Section · General Electric GE90-90B, GE90-94B, GE90-110B1 and 1 more. Effective Jan 17, 2023
- [AD 2022-18-06](https://openairdocs.org/ad/2022-18-06): Turbine Engine Compressor Section, Turbine Section · General Electric GE90-110B1, GE90-115B, GE90-76B and 3 more. Effective Oct 26, 2022
- [AD 2021-26-06](https://openairdocs.org/ad/2021-26-06): Turbine Engine Accessory Drive · General Electric GE90-76B, GE90-85B, GE90-90B and 3 more. Effective Feb 15, 2022
- [AD 2020-21-13](https://openairdocs.org/ad/2020-21-13): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective Nov 17, 2020
- [AD 2020-18-14](https://openairdocs.org/ad/2020-18-14): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective Oct 21, 2020
- [AD 2020-10-04](https://openairdocs.org/ad/2020-10-04): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective May 27, 2020
- [AD 2020-01-55](https://openairdocs.org/ad/2020-01-55): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective Mar 2, 2020
- [AD 2018-20-23](https://openairdocs.org/ad/2018-20-23): Turbine Engine Compressor Section · General Electric GE90-110B1 and GE90-115B. Effective Nov 30, 2018
- [AD 2018-20-22](https://openairdocs.org/ad/2018-20-22): Turbine Section · General Electric GE90-110B1, GE90-113B and GE90-115B. Effective Nov 13, 2018
- [AD 2017-08-06](https://openairdocs.org/ad/2017-08-06): Engine Oil Cooler · General Electric GE90-110B1, GE90-115B, GE90-76B and 3 more. Effective May 22, 2017
- [AD 2013-23-18](https://openairdocs.org/ad/2013-23-18): Variable bypass valve (VBV) actuator fuel supply tube · General Electric GE90-110B1 and GE90-115B. Effective Jan 7, 2014
- [AD 2013-17-07](https://openairdocs.org/ad/2013-17-07): Stage 1 high-pressure turbine (HPT) stator shrouds · General Electric GE90-110B1, GE90-115B, GE90-76B and 3 more. Effective Oct 18, 2013
- [AD 2013-15-20](https://openairdocs.org/ad/2013-15-20): Transfer gearbox assembly (TGB) radial gearshafts · General Electric GE90-110B1, GE90-113B, GE90-115B and 5 more. Effective Aug 21, 2013
- [AD 2011-26-11](https://openairdocs.org/ad/2011-26-11): HPC stages 1-2 seal teeth · General Electric GE90-110B1 and GE90-115B. Effective Feb 3, 2012
- [AD 2009-25-14](https://openairdocs.org/ad/2009-25-14): Blade · General Electric GE90-110B1, GE90-113B and GE90-115B. Effective Jan 19, 2010
- [AD 2007-10-05](https://openairdocs.org/ad/2007-10-05): Turbine Center Frames (TCFs) · General Electric GE90-110B1, GE90-113B and GE90-115B. Effective Jun 14, 2007

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

- [AD 2021-15-05](https://openairdocs.org/ad/2021-15-05) (historical): Engine Controls · General Electric GE90-110B1 and GE90-115B. Effective Sep 13, 2021
- [AD 2020-20-17](https://openairdocs.org/ad/2020-20-17) (historical): Engine Controls · General Electric GE90-110B1 and GE90-115B. Effective Oct 23, 2020
- [AD 2017-07-04](https://openairdocs.org/ad/2017-07-04) (historical): Compressor Section · General Electric GE90-110B1 and GE90-115B. Effective Apr 21, 2017
- [AD 2013-24-17](https://openairdocs.org/ad/2013-24-17) (historical): High pressure compressor (HPC) rotor stage 2-5 spools · General Electric GE90-110B1 and GE90-115B. Effective Dec 31, 2013
- [AD 2013-14-51](https://openairdocs.org/ad/2013-14-51) (historical): Failure of a transfer gearbox assembly radial gearshaft · General Electric GE90-110B1 and GE90-115B
- [AD 2013-10-52](https://openairdocs.org/ad/2013-10-52) (historical): Transfer gearbox assemblies (TGBs) · General Electric GE90-110B1 and GE90-115B. Effective Jun 26, 2013

## Information bulletins (advisory)

None matched.

## NTSB investigations

None matched to N852FD.

## FAA accident and incident reports

None matched to N852FD.

## Service difficulty reports (37)

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 FDEA202605310656](https://openairdocs.org/sdr/FDEA202605310656), May 31, 2026: SKIN. DAMAGED. REQUEST A PERMANENT REPAIR ON LT AFT FUSELAGE AT APPROXIMATELY STA 1895 TO 1958 AND S-40L TO S-43L. LT AFT FUSELAGE AT APPROXIMATELY BS 1895 TO 1958 AND S-40L T
- [SDR FDEA202602230259](https://openairdocs.org/sdr/FDEA202602230259), Feb 23, 2026: SAFETY WIRE. WRONG PART. FOUND INCORRECT SAFETY WIRE ON L1 DOOR SLIDE. AMM: 25-66-01-4 REPLACED SAFETY WIRE WITH CAD COPPER.
- [SDR FDEA202506251045](https://openairdocs.org/sdr/FDEA202506251045), Jun 25, 2025: FITTING. CORRODED. MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA1434 RBL6.5. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED : MEASURED THE REWORKED AREA BELO
- [SDR FDEA202506251044](https://openairdocs.org/sdr/FDEA202506251044), Jun 25, 2025: FITTING. CORRODED. MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA1434 LBL6.5. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED : MEASURED THE REWORKED AREA BELO
- [SDR FDEA202506251043](https://openairdocs.org/sdr/FDEA202506251043), Jun 25, 2025: FITTING. CORRODED. MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA1413 LBL6.5. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED : MEASURED THE REWORKED AREA BELO
- [SDR FDEA202506251042](https://openairdocs.org/sdr/FDEA202506251042), Jun 25, 2025: FITTING. CORRODED. MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA 1193 RBL79. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED : MEASURED THE REWORKED AREA BELO
- [SDR FDEA202506251041](https://openairdocs.org/sdr/FDEA202506251041), Jun 25, 2025: FITTING. CORRODED. MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA 1232 RBL79. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED : MEASURED THE REWORKED AREA BELO
- [SDR FDEA202506100881](https://openairdocs.org/sdr/FDEA202506100881), Jun 10, 2025: SKIN. NICKED. FOUND A NICK AT RH LOWER FWD FUSELAGE SKIN AT STA 518.5 S-47R. A NICK AT RH LOWER FWD FUSELAGE SKIN AT STA 518.5 S-47R REPAIRED AS PER B777 SRM 53-00- 01-2R REP
- [SDR FDEA202506060845](https://openairdocs.org/sdr/FDEA202506060845), Jun 6, 2025: FLOOR PANEL. CRACKED. MAIN DECK CARGO FLOOR PANEL P/N:152W8302-31 FOUND CARCKED AT STA1010 LBL85. DAMAGE SIZE:L=4.5" DAMAGE OUT OF ALLOWABLE LIMIT AS PER B777 SRM 53-00-50-1A ALLOWAB
- [SDR FDEA202506060844](https://openairdocs.org/sdr/FDEA202506060844), Jun 6, 2025: FLOOR PANEL. CRACKED. MAIN DECK CARGO FLOOR PANEL P/N:152W8302-34 FOUND CRACKED AT STA 1010 RBL85. MAIN DECK CARGO FLOOR PANEL P/N:152W8302-34 CRACKED AT STA 1010 RBL 85.DAMAGE SIZE:
- [SDR FDEA202506060843](https://openairdocs.org/sdr/FDEA202506060843), Jun 6, 2025: SKIN. DENTED. LEFT WING OTBD FLAP LOWER SKIN FOUND DENT AT 300 MM FROM T/E AND 1700 MM FROM INBOARD SIDE OF FLAP. REPAIRED LH WING OTBD FLAP LOWER SKIN DENT AT 300MM FROM T/E
- [SDR FDEA202506060842](https://openairdocs.org/sdr/FDEA202506060842), Jun 6, 2025: SKIN. DENTED. RIGHT WING OB FLAP LWR SURFACE FOUND MATERIAL MISSING AT 305 IN TO IB AND 3 IN TO AFT EDGE. REPAIRED RH WING OB FLAP LWR SURFAE MATERIAL MISSING AT 305 IN TO IB
- [SDR FDEA202506060841](https://openairdocs.org/sdr/FDEA202506060841), Jun 6, 2025: SKIN. DENTED. RH WING OB FLAP LWR SURFACE FOUND DENT AT 159 IN TO IB AND 10 IN TO AFT EDGE AND CRACK AND MATERIAL MISSING, TOTAL DAMAGE SIZE 10 INCHES BY 10 INCHES. REPAIRED 
- [SDR FDEA202506050839](https://openairdocs.org/sdr/FDEA202506050839), Jun 5, 2025: SKIN. CRACKED. DURING PERFORM UT & OPEN HOLE HFEC INSPECTION OF THE LEFT UPPER WING SKIN COMMON TO FASTENERS 0-5 AND FOUND 01EA CRACK AT HOLE #5 AS MARKED. LH WING UPPER SKIN 
- [SDR FDEA202506050838](https://openairdocs.org/sdr/FDEA202506050838), Jun 5, 2025: SKIN. CRACKED. DURING PERFORM UT & OPEN HOLE HFEC INSPECTION OF THE RIGHT UPPER WING SKIN COMMON TO FASTENERS 0-5 AND FOUND 01EA CRACK AT HOLE #5 AS MARKED. RH WING UPPER SKIN
- [SDR FDEA202107021650](https://openairdocs.org/sdr/FDEA202107021650), Jul 2, 2021: LAMP. INOPERATIVE. POST-FLT INSP, L-1 DOOR EXTERIOR EMERGENCY LT INOP. RELAMPED, REF AMM: 33-51-04-2. LT TESTS SATIS, ITEM OK FOR SVC
- [SDR FDEA202104170946](https://openairdocs.org/sdr/FDEA202104170946), Apr 17, 2021: LINE. LOOSE. HYD QTY LOW C AT 4:21 INTO FLIGHT FOLLOWED BY RESERVE BRAKES/STRG. HYDRAULIC QUANTITY CENTER DECREASED FROM .41 AT TIME OF EICAS TO .30 BY END OF FLIGHT. ALL SY
- [SDR FDEA202006261367](https://openairdocs.org/sdr/FDEA202006261367), Jun 26, 2020: SPAR. CRACKED. DURING ULTRASONIC INSPECTION ON THE VERTICAL FLANGE OF THE SPAR CHORD AND HIGH FREQENCY EDDY CURRENT OPEN HOLE INSPECTION CARRIED OUT ON REMOVED FASTENER HOLES 
- [SDR FDEA202006261366](https://openairdocs.org/sdr/FDEA202006261366), Jun 26, 2020: SKIN. CRACKED. DURING HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT ON EXTERNAL SURFACE OF FUSELAGE WITHIN A 2 INCH RADIUS OF ALL HOLES COMMON TO THE LEFT HAND UNDERWING 
- [SDR FDEA202006261365](https://openairdocs.org/sdr/FDEA202006261365), Jun 26, 2020: SKIN. CRACKED. DURING HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT ON EXTERNAL SURFACE OF FUSELAGE WITHIN A 2 INCH RADIUS OF ALL HOLES COMMON TO THE RIGHT HAND UNDERWING
- [SDR FDEA202006191279](https://openairdocs.org/sdr/FDEA202006191279), Jun 19, 2020: LONGERON. CRACKED. CRACK INDICATION FOUND DURING ULTRASONIC INSPECTION ON LEFT HAND SIDE UNDERWING LONGERON FITTING AT BODY STATION 1035. COMPLIANCE WITH EO G-5310-E0332629 G (P5)
- [SDR FDEA202006191278](https://openairdocs.org/sdr/FDEA202006191278), Jun 19, 2020: LONGERON. CRACKED. CRACK INDICATION FOUND DURING ULTRASONIC INSPECTION ON RIGHT HAND SIDE UNDERWING LONGERON FITTING AT BODY STATION 1035. COMPLIANCE WITH EO G-5310-E0332629 G (P6
- [SDR FDEA2019061101266](https://openairdocs.org/sdr/FDEA2019061101266), Jun 10, 2019: WHEEL. DAMAGED. EICAS STATUS " TIRE PRESSURE" #10 TIRE PRESSURE BEFORE LANDING 157 EICAS STATUS " TIRE PRESSURE" #9 TIRE PRESSURE BEFORE LANDING 204 PER CREW DEBRIEF, #9 WHEEL 
- [SDR FDEA2018092522654](https://openairdocs.org/sdr/FDEA2018092522654), Sep 22, 2018: TUBE. DAMAGED. REF WRI 29-02/8711 NEED TO INSTALL FLEX LINE IN PLACE OF SEVERED RIDGID HYD PRESSURE LINE ON THE #12 SPOILER PCU PRESSURE LINE . NUMBER 12 SPOILER HAS TEMP FLEX
- [SDR FDEA201809202643](https://openairdocs.org/sdr/FDEA201809202643), Sep 20, 2018: FLAP. GOUGED. FOUND DAMAGE ON LEADING EDGE OF OUTBOARD FLAP ADJACENT TO NR 12 SPOILER ACTUATOR. REF WRI 29-02/8711 LEADING EDGE FLAP GOUGE IS OUT OF LIMITS REF SRM 57-53-01-1
- [SDR FDEA2018092502653](https://openairdocs.org/sdr/FDEA2018092502653), Sep 20, 2018: TUBE. SEVERED. HYD PRESS SYS, R HYD QUANITY 0. FOUND #12 SPOILER ACTUATOR TUBE SEVERED. ALSO FOUND ACTUATOR MOUNT BRACKETS BROKEN. WILL NEED NEW SPOILER ACTUATOR ASSY. ACTUATO
- [SDR FDEA2018092502652](https://openairdocs.org/sdr/FDEA2018092502652), Sep 20, 2018: TUBE. SEVERED. HYD PRESS SYS, R HYD QUANITY 0. FOUND #12 SPOILER ACTUATOR TUBE SEVERED. ALSO FOUND ACTUATOR MOUNT BRACKETS BROKEN. WILL NEED NEW SPOILER ACTUATOR ASSY. ACTUATO
- [SDR FDEA2018092102642](https://openairdocs.org/sdr/FDEA2018092102642), Sep 20, 2018: SPOILER. DAMAGED. WHILE INSPECTION OF DAMAGE ON WRI 29-02/8711. ALSO FOUND NR 12 SPOILER TRAILING EDGE DAMAGE AT 5 DIFFERENT LOCATIONS. REMOVED AND REPLACED NR 12 SPOILER REF AMM
- [SDR FDEA201809202634](https://openairdocs.org/sdr/FDEA201809202634), Sep 20, 2018: HYDRAULIC LINE. SEVERED. HYD PRESS SYS, R HYD QUANTITY 0. FOUND NR 12 SPOILER ACTUATOR TUBE SEVERED. REF IPC 27-11-05-66 ITEM 455. ALSO FOUND ACTUATOR MOUNT BRACKETS BROKEN. WILL NEED N
- [SDR FDEA201703280996](https://openairdocs.org/sdr/FDEA201703280996), Mar 28, 2017: LIGHT. INOPERATIVE. DURING PREFLIGHT INSPECTION, L1 DOOR FWD EMERGENCY EXIT LIGHT NOT ILLUMINATED.
- [SDR FDEA201504101210](https://openairdocs.org/sdr/FDEA201504101210), Apr 10, 2015: UNKNOWN. MALFUNCTIONED. EMERGENCY LIGHT LINE ON SHUTDOWN CHECKLIST REMAINS WHITE WITH SWITCH IN OFF POSITION. CYCLED EMER LIGHT SWITCH, CHANGED TO GREEN SEVERAL TIMES IAW MM 31-61-00-2
- [SDR FDEA201406011256](https://openairdocs.org/sdr/FDEA201406011256), Jun 1, 2014: HOOK AND LOOP. UNSECURE. CAPTAIN'S LIFE VEST POUCH HOOK AND LOOP HAS COME OFF OF SEAT. SECURED CAPTAIN`S LIFE VEST POUCH HOOK AND LOOP IAW SMP. OK FOR SERVICE.
- [SDR FDEA201302030263](https://openairdocs.org/sdr/FDEA201302030263), Feb 3, 2013: SOCKET. FAILED. EXTERIOR EMERGENCY EXIT LIGHT AT R1 DOOR INOPERATIVE. R & R SOCKET ASSY IAW WDM 33-51-41. OPS CHECK GOOD. ACFT OK FOR SERVICE,
- [SDR FDEA201301290216](https://openairdocs.org/sdr/FDEA201301290216), Jan 29, 2013: LAMP. INOPERATIVE. RT EMERGENCY LIGHT NEAR R1 DOOR INOPERATIVE. REPLACED LAMP IAW AMM 33-50-00-2, OK FOR SERVICE.
- [SDR FDEA201209113284](https://openairdocs.org/sdr/FDEA201209113284), Sep 11, 2012: SKIN. CRACKED. LEFT WING NR 7 SLAT OUTER SKIN INBD AREA FOUND CRACKED. REPAIRED IAW SRM 57-43-01 FIGURE 201 REPAIR 8 AND EA G-5750-159900. REPAIR CLASSIFIED AS MAJOR AS PER GM
- [SDR FDEA201101200318](https://openairdocs.org/sdr/FDEA201101200318), Jan 20, 2011: ENGINE. FOD. DURING CLIMB & LEVEL OFF, VIBRATION SHOWED 4.0 LT & 5.0 RT ABLE TO REDUCE LT TO 1.3 BUT UNABLE TO REDUCE RT. AFTER CONSULT WITH MOCC & FLT OPS WERE INSTRUCTED T
- [SDR FDEA201004181243](https://openairdocs.org/sdr/FDEA201004181243), Apr 18, 2010: HOSE. FAILED. LT MLG TIRES DEFLATED DURING TAXI CHECK. SHOWS EVIDENCE OF FIRE/OVERHEAT AND FIRE SUPPRESSION AGENTS. R & R THE NR 1 FWD BRAKE LINE, THE NR 1 AFT BRAKE LINE AND

## STCs that may be installed (OpenAirDocs)

None matched to this aircraft's models.

## Related

- Other Boeing 777-FS2 aircraft: https://openairdocs.org/model/boeing-777-fs2/aircraft.md
- The GE GE90-110B1 engine: https://openairdocs.org/engine/ge-ge90-110b1.md

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