# Service difficulty reports: N852FD

A list on [N852FD](https://openairdocs.org/aircraft/N852FD.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

- [SDR FDEA202605310656](https://openairdocs.org/sdr/FDEA202605310656.md): Skin · damaged · May 31, 2026 · N852FD · Boeing 777FS2 · Fuselage Main, Plate/Skin
  > 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 TO S-43L. DAMAGED SKIN & STRINGER PERFORMED PERMANENT REPAIR IAW SRM51-10-02-0G. SRM51-20-01-0G.
- [SDR FDEA202602230259](https://openairdocs.org/sdr/FDEA202602230259.md): Safety Wire · wrong part · Feb 23, 2026 · N852FD · Boeing 777FS2 · Passenger/Crew Doors
  > 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.md): Fitting · corroded · Jun 25, 2025 · N852FD · Boeing 777F · Fuselage Main, Attach Fittings
  > MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA1434 RBL6.5. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED: MEASURED THE REWORKED AREA BELONG TO ZONE C,THE MAX ALLOWABLE BLEND OUT IS 0.002, THE MAX CLEAN UP DEPTH IS X=0.058Ï¿½>0.002Ï¿½
- [SDR FDEA202506251044](https://openairdocs.org/sdr/FDEA202506251044.md): Fitting · corroded · Jun 25, 2025 · N852FD · Boeing 777F · Fuselage Main, Attach Fittings
  > MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA1434 LBL6.5. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED: MEASURED THE REWORKED AREA BELONG TO ZONE C, THE MAX ALLOWABLE BLEND OUT IS 0.002, THE MAX CLEAN UP DEPTH IS X=0.022Ï¿½>0.002Ï
- [SDR FDEA202506251043](https://openairdocs.org/sdr/FDEA202506251043.md): Fitting · corroded · Jun 25, 2025 · N852FD · Boeing 777F · Fuselage Main, Attach Fittings
  > MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA1413 LBL6.5. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED: MEASURED THE REWORKED AREA BELONG TO ZONE C,THE MAX ALLOWABLE BLEND OUT IS 0.002. THE MAX CLEAN UP DEPTH IS X=0.022 - 0.002 AND F
- [SDR FDEA202506251042](https://openairdocs.org/sdr/FDEA202506251042.md): Fitting · corroded · Jun 25, 2025 · N852FD · Boeing 777F · Fuselage Main, Attach Fittings
  > MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA 1193 RBL79. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED: MEASURED THE REWORKED AREA BELONG TO ZONE B,THE MAX ALLOWABLE BLEND OUT IS 0.030Ï¿½, THE MAX CLEAN UP DEPTH IS X=0.045Ï¿½>0.0
- [SDR FDEA202506251041](https://openairdocs.org/sdr/FDEA202506251041.md): Fitting · corroded · Jun 25, 2025 · N852FD · Boeing 777F · Fuselage Main, Attach Fittings
  > MAIN DECK CARGO FLOOR FITTING FOUND CORROSION AT STA 1232 RBL79. MAIN DECK CARGO FLOOR FITTING CORROSION REMOVED AND EVALUATED: MEASURED THE REWORKED AREA BELONG TO ZONE Ï¿½BÏ¿½,THE MAX ALLOWABLE BLEND OUT IS 0.030Ï¿½, THE MAX CLEAN UP DEPTH IS X=0.041Ï
- [SDR FDEA202506100881](https://openairdocs.org/sdr/FDEA202506100881.md): Skin · nicked · Jun 10, 2025 · N852FD · Boeing 777FS2 · Fuselage Main, Plate/Skin
  > 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 REPAIR 3 FIGURE 202 REV 47.5. THIS IS A CATEGORY B REPAIR PER B777 SRM 53-00-01-2R REPAIR 3 REV 47.5
- [SDR FDEA202506060845](https://openairdocs.org/sdr/FDEA202506060845.md): Floor Panel · cracked · Jun 6, 2025 · N852FD · Boeing 777FS2 · Fuselage Floor Panel
  > 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 ALLOWABLE DAMAGE 1 REV 47.5 AND REPAIRED AS PER B777 SRM 53-00-50-2R REPAIR 1 REV 47.5.THIS IS A MAJOR R
- [SDR FDEA202506060844](https://openairdocs.org/sdr/FDEA202506060844.md): Floor Panel · cracked · Jun 6, 2025 · N852FD · Boeing 777FS2 · Fuselage Floor Panel
  > 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:L=4.9" DAMAGE OUT OF ALLOWABLE LIMIT AS PER B777 SRM 53-00-50-1A ALLOWABLE DAMAGE 1 REV 47.5 AND
- [SDR FDEA202506060843](https://openairdocs.org/sdr/FDEA202506060843.md): Skin · dented · Jun 6, 2025 · N852FD · Boeing 777FS2 · Trailing Edge Flaps
  > 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 AND 1700MM FROM INBOARD SIDE OF FLAP AS PER B777 SRM 57-53-01-2R-2 & SRM 51-70-04-2R-1 REV 47.5 A
- [SDR FDEA202506060842](https://openairdocs.org/sdr/FDEA202506060842.md): Skin · dented · Jun 6, 2025 · N852FD · Boeing 777FS2 · Trailing Edge Flaps
  > 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 AND 3 IN TO AFT EDGE AS PER B777 SRM 57-53-01-2R-2 & SRM 51-70-04-2R-1 REV 47.5 AND EA:G-5750-T
- [SDR FDEA202506060841](https://openairdocs.org/sdr/FDEA202506060841.md): Skin · dented · Jun 6, 2025 · N852FD · Boeing 777FS2 · Trailing Edge Flaps
  > 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 RH WING OB FLAP LWR SURFACE DENT AT 159 IN TO IB AND 10 IN TO AFT EDGE AND CRACK AND MATERIAL MI
- [SDR FDEA202506050839](https://openairdocs.org/sdr/FDEA202506050839.md): Skin · cracked · Jun 5, 2025 · N852FD · Boeing 777F · Wing, Plate/Skin
  > 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 IN RIB BAY 10 TRAILING EDGE #5 HOLE REPAIRED AS PER B777 SRM 51-40- 02-0G, SRM 51-40-04-0G, SRM
- [SDR FDEA202506050838](https://openairdocs.org/sdr/FDEA202506050838.md): Skin · cracked · Jun 5, 2025 · N852FD · Boeing 777F · Wing, Plate/Skin
  > 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 IN RIB BAY 10 TRAILING EDGE #5 HOLE REPAIRED AS PER B777 SRM 51-40- 02-0G, SRM 51-40-04-0G, SR
- [SDR FDEA202107021650](https://openairdocs.org/sdr/FDEA202107021650.md): Lamp · inoperative · Jul 2, 2021 · N852FD · Boeing 777FS2 · Emergency Lighting
  > 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.md): Line · loose · Apr 17, 2021 · N852FD · Boeing 777FS2 · Hydraulic System, Main
  > 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 SYSTEMS FUNCTIONED NORMALLY ON APPROACH, LANDING AND TAXI. ON BLOCK IN FOUND #5 BRAKE LINE LOOSE
- [SDR FDEA202006261367](https://openairdocs.org/sdr/FDEA202006261367.md): Spar · cracked · Jun 26, 2020 · N852FD · Boeing 777FS2 · Wing Spar
  > 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 AT RIGHT HAND SIDE UNDERWING LONGERON LOWER WING, BUTT STATION 1035, VERTICAL FLANGE OF THE SPAR CH
- [SDR FDEA202006261366](https://openairdocs.org/sdr/FDEA202006261366.md): Skin · cracked · Jun 26, 2020 · N852FD · Boeing 777FS2 · Fuselage Main, Plate/Skin
  > 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 LONGERON AND FUSELAGE SKIN FOUND 01 EACH CRACKS ON THE SKIN APPROXIMATE 0.7" AT STATION 1030 BETWEEN
- [SDR FDEA202006261365](https://openairdocs.org/sdr/FDEA202006261365.md): Skin · cracked · Jun 26, 2020 · N852FD · Boeing 777FS2 · Fuselage Main, Plate/Skin
  > 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 LONGERON AND FUSELAGE SKIN FOUND 01 EACH CRACKS ON THE SKIN APPROXIMATE 0.6" AT STATION 1030 BETWEE
- [SDR FDEA202006191279](https://openairdocs.org/sdr/FDEA202006191279.md): Longeron · cracked · Jun 19, 2020 · N852FD · Boeing 777FS2 · Fuselage Main, Longeron/Stringer
  > 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). TITLE: FUSELAGE - MAINFRAME - INSPECTION AND MODIFICATION OF THE UNDERWING LONGERON AT BODY STAT
- [SDR FDEA202006191278](https://openairdocs.org/sdr/FDEA202006191278.md): Longeron · cracked · Jun 19, 2020 · N852FD · Boeing 777FS2 · Fuselage Main, Longeron/Stringer
  > 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). TITLE: FUSELAGE - MAINFRAME - INSPECTION AND MODIFICATION OF THE UNDERWING LONGERON AT BODY STA
- [SDR FDEA2019061101266](https://openairdocs.org/sdr/FDEA2019061101266.md): Wheel · damaged · Jun 10, 2019 · N852FD · Boeing 777FS2 · Wheel/Ski/Float
  > 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 IS AT 157 PSI AND #10 WHEEL IS AT 204 PSI. CHECK #9 AND #10 TIRE PRESS WITH EXTERNAL
- [SDR FDEA2018092522654](https://openairdocs.org/sdr/FDEA2018092522654.md): Tube · damaged · Sep 22, 2018 · N852FD · Boeing 777FS2 · Drag Control System
  > 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 LINE INSTALLED PER MM-NEEDS RE-INSPECT EVERY 7 DAYS AND FINAL REPAIR AT NEXT B CHECK INS
- [SDR FDEA201809202643](https://openairdocs.org/sdr/FDEA201809202643.md): Flap · gouged · Sep 20, 2018 · N852FD · Boeing 777FS2 · Trailing Edge Flaps
  > 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 57-53-01-1A. COMPLIED WITH EA G-2750-T0342462 PART1. REPAIRED RT WING OUTBOARD FLAP LEADING EDGE PER SRM 51-70
- [SDR FDEA2018092502653](https://openairdocs.org/sdr/FDEA2018092502653.md): Tube · severed · Sep 20, 2018 · N852FD · Boeing 777FS2 · Hydraulic System, Main
  > 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. ACTUATOR MOUNT BOLTS SHEARED IN ATTACH FITTING. REMOVED AND REPLACED #12 SPOILER PCU REF MM 27-61-
- [SDR FDEA2018092502652](https://openairdocs.org/sdr/FDEA2018092502652.md): Tube · severed · Sep 20, 2018 · N852FD · Boeing 777FS2 · Hydraulic System, Main
  > 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. ACTUATOR MOUNT BOLTS SHEARED IN ATTACH FITTING. REMOVED AND REPLACED #12 SPOILER PCU REF MM 27-61-
- [SDR FDEA2018092102642](https://openairdocs.org/sdr/FDEA2018092102642.md): Spoiler · damaged · Sep 20, 2018 · N852FD · Boeing 777FS2 · Spoilers
  > 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 27-61-11-4.
- [SDR FDEA201809202634](https://openairdocs.org/sdr/FDEA201809202634.md): Hydraulic Line · severed · Sep 20, 2018 · N852FD · Boeing 777FS2 · Hydraulic System, Main
  > 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 NEW SPOILER ACTUATOR ASSY ACTUATOR MOUNT BOLTS SHEARED IN ATTACH FITTING REF IPC 57-52-51-38 FIG 38 S
- [SDR FDEA201703280996](https://openairdocs.org/sdr/FDEA201703280996.md): Light · inoperative · Mar 28, 2017 · N852FD · Boeing 777FS2 · Emergency Lighting
  > DURING PREFLIGHT INSPECTION, L1 DOOR FWD EMERGENCY EXIT LIGHT NOT ILLUMINATED.
- [SDR FDEA201504101210](https://openairdocs.org/sdr/FDEA201504101210.md): Unknown · malfunctioned · Apr 10, 2015 · N852FD · Boeing 777FS2 · Central Display
  > 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. ACFT OK FOR SERVICE.
- [SDR FDEA201406011256](https://openairdocs.org/sdr/FDEA201406011256.md): Hook And Loop · unsecure · Jun 1, 2014 · N852FD · Boeing 777FS2 · Emergency Equipment
  > 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.md): Socket · failed · Feb 3, 2013 · N852FD · Boeing 777FS2 · Emergency Lighting
  > 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.md): Lamp · inoperative · Jan 29, 2013 · N852FD · Boeing 777FS2 · Emergency Lighting
  > 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.md): Skin · cracked · Sep 11, 2012 · N852FD · Boeing 777FS2 · Leading Edge Devices
  > 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 GMM 6-2-100 REVISION 115.
- [SDR FDEA201101200318](https://openairdocs.org/sdr/FDEA201101200318.md): Engine · fod · Jan 20, 2011 · N852FD · Boeing 777FS2 · Engine (Turbine/Turboprop)
  > 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 TO RTB PANC, NO FUEL DUMP REQUIRED. MODERATE AIRFRAME VIBRATION ASSOCIATED WITH THE RT ENGINE VIB
- [SDR FDEA201004181243](https://openairdocs.org/sdr/FDEA201004181243.md): Hose · failed · Apr 18, 2010 · N852FD · Boeing 777* · Hydraulic System, Main
  > 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 SWIVEL ASSY AND THE NR 5 BRAKE LINE. R & R LT MLG BRAKE ASSEMBLIES IAW MM 32-45-07-4-0. BLEED

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
WHERE n_number = 'N852FD' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N852FD/reports

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