N852FD
Service difficulty reports · 37
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.
Query with SQL
duckdb -csv -c "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"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
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
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR FDEA202605310656Skin · damagedREQUEST 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 FDEA202602230259Safety Wire · wrong partFOUND INCORRECT SAFETY WIRE ON L1 DOOR SLIDE. AMM: 25-66-01-4 REPLACED SAFETY WIRE WITH CAD COPPER.SDR FDEA202506251045Fitting · corrodedMAIN 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¿½SDR FDEA202506251044Fitting · corrodedMAIN 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>0.002ÏSDR FDEA202506251043Fitting · corrodedMAIN 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 FSDR FDEA202506251042Fitting · corrodedMAIN 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>0.0SDR FDEA202506251041Fitting · corrodedMAIN 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=0.041ÏSDR FDEA202506100881Skin · nickedFOUND 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 47.5SDR FDEA202506060845Floor Panel · crackedMAIN 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 RSDR FDEA202506060844Floor Panel · crackedMAIN 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 ANDSDR FDEA202506060843Skin · dentedLEFT 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 ASDR FDEA202506060842Skin · dentedRIGHT 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-TSDR FDEA202506060841Skin · dentedRH 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 MISDR FDEA202506050839Skin · crackedDURING 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 FDEA202506050838Skin · crackedDURING 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, SRSDR FDEA202107021650Lamp · inoperativePOST-FLT INSP, L-1 DOOR EXTERIOR EMERGENCY LT INOP. RELAMPED, REF AMM: 33-51-04-2. LT TESTS SATIS, ITEM OK FOR SVCSDR FDEA202104170946Line · looseHYD 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 LOOSESDR FDEA202006261367Spar · crackedDURING 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 CHSDR FDEA202006261366Skin · crackedDURING 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 BETWEENSDR FDEA202006261365Skin · crackedDURING 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 BETWEESDR FDEA202006191279Longeron · crackedCRACK 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 STATSDR FDEA202006191278Longeron · crackedCRACK 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 STASDR FDEA2019061101266Wheel · damagedEICAS 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 FDEA2018092522654Tube · damagedREF 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 INSSDR FDEA201809202643Flap · gougedFOUND 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 51-70SDR FDEA2018092502653Tube · severedHYD 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 FDEA2018092502652Tube · severedHYD 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 FDEA2018092102642Spoiler · damagedWHILE 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 FDEA201809202634Hydraulic Line · severedHYD 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 SSDR FDEA201703280996Light · inoperativeDURING PREFLIGHT INSPECTION, L1 DOOR FWD EMERGENCY EXIT LIGHT NOT ILLUMINATED.SDR FDEA201504101210Unknown · malfunctionedEMERGENCY 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 FDEA201406011256Hook And Loop · unsecureCAPTAIN'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 FDEA201302030263Socket · failedEXTERIOR EMERGENCY EXIT LIGHT AT R1 DOOR INOPERATIVE. R & R SOCKET ASSY IAW WDM 33-51-41. OPS CHECK GOOD. ACFT OK FOR SERVICE,SDR FDEA201301290216Lamp · inoperativeRT EMERGENCY LIGHT NEAR R1 DOOR INOPERATIVE. REPLACED LAMP IAW AMM 33-50-00-2, OK FOR SERVICE.SDR FDEA201209113284Skin · crackedLEFT 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 FDEA201101200318Engine · fodDURING 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 VIBSDR FDEA201004181243Hose · failedLT 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
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