JASC 5350
Service difficulty reports · 6,118
Reports filed under 5350 · Aerodynamic Fairings, 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 jasc_code = '5350' 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 jasc_code = '5350' 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 SWAA2025040200520Former · crackedWING TO BODY FAIRING FORMER IS CRACKED BS 500D BETWEEN STRINGER 19 AND 20 R/H<[01] REMOVED AND INSTALLED NEW FAIRING FORMER BS 500D BETWEEN STRINGER 19 AND 20 R/H IAW SRM 51-40-02-0G-0 AND DWG 116A3010 REV: A; 149A7101 REV: -.SDR SWAA2025032498332Bracket · crackedCRACK SUPPORT STRUCTURE WING TO BODY FAIRING BRACKET LOCATED ON BS 500I AT LEVEL STR 18R AT LOWER FUSELAGE 2025-139356<[01] REPLACED SUPPORT STRUCTURE WING TO BODY FAIRING BRACKET LOCATED ON BS 500I AT LEVEL STR 18R AT LOWER FUSELAGE IAW B737-800 SRM 51-40-02 SDR DALA2025022701527Panel · missing(LOG 6892942) DURING WALKAROUND FOUND PANEL 192JL MISSING. PERFORMED TIME LIMITED REPAIR PER ERA 624524-14 REV ORIG SECTION. C/W ER/A 624524-14 REV ORIGINAL SECTION III PERMANENT REPAIR INSTALL OF NEW PANEL 192JL.SDR 2025FA0000125Tail Cone · corrodedAFT FUSELAGE FAIRING SUPPORT CORROSIONSDR SWAA2025032498155Tail Cone · delaminatedDELAMINATION LOCATED ON TAIL CONE BS 1156 AT LOWER POSITION RH SIDE. 2025-139317<[01] TOOL USED: CALIPER P/N 500-197-30; S/N B20189571; DUE DATE: 06-JUN-25.;[02] STEP 3 TOOL USED THERMOGRAPHIC CAMERA P/N:FLIR T300; S/N: 48800502; CAL DUE DATE: 11-OCT-25;[03] TSDR SWAA2025031198536Access Panel · crackedCRACK ACCESS PANEL 191D BODY FAIRING AT FUSELAGE EXTERIOR 2025-151898<[01] TOOL USED CALIPER PN: 500-464; SN: B17030933; DUE DATE: 21/DEC/25.;[02] TOOL USED HOT BONDER PN: HCS8800; SN: 01685794; DUE DATE: 25/APR/25.;[03] REPAIRED ACCESS PANEL 191D BODY FAIRINGSDR SWAA2025022097782Fairing · delaminatedLEFT SIDE PACK PANEL SHOWS SIGNS OF DELAM ON LEADING EDGE<[01] REMOVED AND REPLACED WING TO BODY FAIRING 192BL PER AMM 53-51-21.SDR 2025FA0000120Tail Cone · corrodedTAIL CONE HAS CORROSION SURROUNDING LOWER DATA PLATE.SDR SWAA2025022097185Skin Panel · delaminatedSECTION 43 WING TO BODY FAIRING SKIN PANEL 191FR HAS ONE LAYER OF CARBON FIBER DELAMINATED UP TO FASTENER HOLES<[01] DELAMINATION IS ON THE LEADING EDGE AND MEASURES 2.5? X 3.0? AND EXTENDS TO FASTENERS HOLES.;[02] SRM REF 53-30-70-1A-1;[03] COMPLIED WITH EA 2SDR SWAA2025022097188Skin Panel · delaminatedSECTION 44 WING TO BODY FAIRING SKIN PANEL 192BR HAS ONE LAYER OF CARBON FIBER DELAMINATED UP TO FASTENER HOLE<[01] LENGTH OF DELAMINATION IS 8? X 1.0? AND EXTENDS TO FASTENERS. OUT OF LIMITS PER SRM 53-40-70-1A-1.;[02] COMPLIED WITH EA 25-153-00420 (N8615E- SSDR SWAA2025032496208Support Angle · crackedCRACK ON SUPPORT ANGLE FWD BODY FAIRING STRUCTURE BS 500D AT LEVEL STRINGER 19R LOWER FUSELAGE 2025-136785<[01] REPLACED SUPPORT ANGLE LOCATED AT FWD BODY FAIRING STRUCTURE BS 500D BETWEEN STRINGER 19R AND STRINGER 20 LOWER FUSELAGE IAW B737-700 SRM 51-40-02; SDR DALA2025021801194Cable · out of positionTAILCONE DEPLOYMENT SYSTEM CABLE OUT POSITION OF PULLEY STA 1225 IN 2 O'CLOCK POSITION AT AFT ACCESSORY COMPARTMENT. THIS COULD PREVENT THE PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. SUMMARY OF NRC 00952: CABLE ROSDR JR2R20250211470Angle · corrodedFWD FUSELAGE, AFT OF FRAME 31, AT STRINGER 27L, W2B FAIRING GROUND CLIP CORRODED.SDR JR2R20250211471Angle · corrodedFWD FUSELAGE, AFT OF FRAME 31, AT STRINGER 27R, W2B FAIRING GROUND CLIP CORRODED.SDR HNAA2025031100156Strip · cracked53-2129 RH WING TO BODY FAIRING, STRIP BTW FR48-49 CRACKED. REPAIRED STRIP IAW SRM 53-23-12SDR JR2R20250209260Support Angle · elongatedMID WING TO BODY FAIRING AFT L-SUPPORT ANGLE, RIGHT HAND SIDE TOP SCREWHOLE WAS ELONGATED.SDR SWAA2025021094169Panel · delaminatedLEADING EDGE; EDGE EROSION AND DELAMINATION TO WING TO BODY FAIRING PANEL 192BR EDGE EROSION AND DELAMINATION TO WING TO BODY FAIRING PANEL 192BR LEADING EDGE<[01] REMOVED 3 EA.CAMLOCK FASTENERS AND 1 EA. CAM LOCK GROMET TO F.O.M.;[02] REMOVED DAMAGE AT PANEL SDR JJBA20250213024Fairing · crackedAFT BODY FAIRING ON THE RH SIDE, ONE RIB IS CRACKED. AFT BODY FAIRING ON THE RH SIDE, ONE RIB REMOVED AND REPLACEDSDR DALA2025021000986Skin · damagedSHIP 1812 TAILCONE RH SIDE AT STA 1738 UNDER PANEL 313CRX FOUND FWD SKIN ABRASION. CORRECTIVE ACTION: THE FWD SKIN ABRASION AREA REMOVED AND MEASURED ORIGINAL THICKNESS T:0.080",THE DEPTH OF CLEAN UP IS 0.062">20%T, FOUND OUT OF LIMIT AS PER B767-400 SRM 53-80SDR SWAA2025030493538Former · crackedWING TO BODY FAIRING FORMER IS CRACKED BS 500D BETWEEN STRINGER 19 AND 20 L/H <[01]. REMOVED AND REPLACED WING TO BODY FAIRING FORMER BS 500D BETWEEN STRINGER 19 AND 20 L/H IAW SRM 51-40-02-0G-0; DWG 116A3010 REV:A AND DWG 116A3110 REV:-; [02] VERIFIED CORRECSDR DALA2025022701550Tail Cone · puncturedAIRCRAFT 8122, WHILE IN HCK VISIT @ MSP MAINTENANCE FOUND A PUNCTURE ON THE (PN C03113040-103) FORWARD UPPER TAIL CONE SKIN. THE PUNCTURE IS LOCATED APPROX. 1.00" AFT OF FR88 AND 3.20" INBD OF STGR1R. THE AREA AROUND THE PUNCTURE ALSO CONTAINS A SMALL DENT REPSDR DALA2025020700961Radome · damagedSHIP 3224 DISC: DURING BIRD STRIKE INSPECTION, FOUND DAMAGE TO RADOME. C/A: REMOVED AND REPLACED RADOME PER A320 AMM 53-15. (LP: 6701447)SDR DALA2025020400827Fairing · puncturedSHIP 3101 SMALL PUNCTURE RT BELLY FAIRING. CORRECTIVE ACTION: REPAIRED PANEL 192 KB PER A319 SRM 53-35-11-300-007. (5660427)SDR REXA2025030600266Fairing · corrodedCORROSION ON SETTLEMENT AREA OF THE WING TO FUSELAGE FAIRING 195AL, 195DL, 196AR AND 196DR. CORROSION ON SETTLEMENT AREA OF THE WING TO FUSELAGE FAIRING 195AL, 195DL, 196AR AND 196DR WAS EVALUATED WITHIN LIMITS PER CRJ-900 SRM 53-00-01-101-001 AND SRM 53-51-01SDR CALA2025020200262Angle · crackedLH SIDE VERTICAL WING TO BODY STRUCTURE BRACKET IS CRACKED PER HAECO LCQ N/R 9294125/42125 GEN BY V918855SDR SWAA2025013191303Panel · delaminatedPANEL 193AL HAS DELAMINATION<[01]. EVALUATED DAMAGE ON PANEL 193AL. FOUND PUNCTURE LENGTH .5''; WIDTH .3''; DEPTH 0.05''. APPLIED TEMPORARY SEAL PER SRM 53-40-70-1A-1. INSPECTED PER [SRM 53-40-70-1A-1-B00369 (DAMAGE NOT MORE THAN 1 PLY DEEP - SEAL WITH SPEEDSDR QXEA2025021900043Fairing · damagedBELLY FAIRING 192DL AFT EDGE HAS COMPOSITE DAMAGE - ELONGATED FASTENER HOLES. REPAIRED THE ELONGATED HOLES ON PANEL 192DL. REFERENCE SRM 53-04-00/AD01 FIGURE 104 SHEET 2 AND SRM 51-71-09. PO# 326049(ADHESIVE), 283594(CARBON GRAPHITE).SDR VNAA20250329017Angle · corrodedCORROSION ON JOINT ANGLE AT WING TO FUSELAGE FAIRINGSUPPORTFS939BTWSTGR26L-26R. EVALUATED, DUE TO EXCESSIVE ALLOWABLE DAMAGE ON JOINT ANGLE AT WING TO FUSELAGE FAIRING SUPPORT FS939 BTW STGR 26L-26R PER CRJ-700 SRM 53-00-01-101-001-A01 AND REPLACED PER CRJ-7SDR JR2R20250128182Splice Strap · corrodedAFT WING TO BODY, FUSELAGE FAIRING STRAP SPLICE IS CORRODED.SDR SWIA202503240126Support Angle · crackedCRACK AT BOTTOM OF CORNER ANGLE SUPPORT BRACKET FOR AFT FAIRING AT FS909.0 STGR 25LH. (C-CHECK RO 03/22/2024)PERFORMED REPAIR AT AFT FAIRING SUPPORT FS 909.00 LBL 17.63 IAW REO 670-53-82-478 REV -A DATED 2014-11-12PERFORMED NDT ET INSPECTION BY BARON NDT,LLC FSDR DALA2025012400586Support · crackedSHIP 3136 FINDING CRACK SUPPORT WEB BELLY FAIRING STRUCTURE AT FR52 LH SIDE LOWER FUSELAGE. CORRECTIVE ACTION: COMPLIED WITH ER/A 623195-14. (0775586)SDR DALA2025012200514Radome · delaminatedSHIP 3148 FOUND NOSE RADOME INTERIOR DELAMINATED. CORRECTIVE ACTION: REPLACED RADOME PER A319 AMM 53-52. (6409219)SDR AALA202502109992Panel · crackedAIRCRAFT IN BASE MAINTENANCE: WING TO BODY PANEL 192AL HAS A CRACK AROUND FASTENER HOLE. ACCOMPLISHED PERMANENT REPAIR ON WING TO BODY PANEL 192AL. PER B737-NG SRM53-40-70-2R-1 SRM 51-70-05-2R REPAIR GENERAL AND SRM 51-70-05-2R-8.SDR DALA2025012300565Longeron · crackedWTBF RHS LONGERON ASSEMBLY. PN: C02383111-002 HAS CRACK. REMOVED RHS LONGERON ASSEMBLY P/N: C02383111-002 IAW W/C 5352-01038- 07B H. MOORE 1943566. MOCK INSTALLED LONGERON P/N: C02383111-002 IAW W/C 5352-01038-07B. RIVETS AND SEALANT STILL REQUIRED. APPLIED FASDR IPXA2025021567101Support Bracket · corrodedCORROSION SUPPORT BRACKET, WING TO BODY FAIRING INTERNAL STA 1078 LBL 9. (REPLACE). FABRICATE P/N:149U1070-47 PER BOEING DWG NO.149U7010 SH6 REV."A", PL REV."AC" AND EGAT WORK SHEET NO.50109 AND ORIGINAL PART AS A SAMPLE I.A.W GMM-MTX CH9.08 REV.10 REQUIREMENSDR VNAA20250116042Support · corrodedFS 879 LBL 10- RBL 28 WING TO FUSELAGE SUPPORT STRUCTURE FLANGE FAYING SURFACE (BOTTOM) IS CORRODED ALONG LENGTH AND REQUIRES EVALUATION CORRECTIVE ACTION: REMOVED CORRODED STRAPS AND INSTALLED (2) STRAPS P/N: (SH670-39333-9) ON FS 879 LBL 10- RBL 28 WING TO FSDR CALA2025011401906Panel · brokenPDA 2 192MB FOUND OPEN UPON ARRIVAL. 192MB WAS MANUALLY REMOVED FROM THE AIRCRAFT PANEL 192LB VIA CDL 28B AND STORED IN THE FLIGHT DECK.ACCESS PANEL RIGHT SIDE OF FUESLAGE WAS FOUND OPEN DURING POST WALK VISIBLE DAMAGE NOTED REMOVED DOOR 192MB. UPLOADED PHOTOSSDR SWAA2025011385376Panel · delaminatedWING TO BODY PANEL #194 CR HAS DELAMINATION 7' AFT OF THE LEADING EDGE AND 12' FROM THE UPPER EDGE MEASURING 1.4' X 1.0'<[01] R&R 194CR PANEL PER AMM 53-51-21SDR DALA2025011400324Longeron · crackedRHS LONGERON CRACKED IN WTB FAIRING R/R WTB RHS LONGERON P/N53-1111-502 PER AMDS WC 5352-01038-01A. (LP# 6421197)SDR DALA2025011300240Support · crackedSHIP 3147 SECONDARY FINDING CRACK SUPPORT WEB BELLY FAIRING REAR AT LEVEL OF FR52 LH SIDE. CORRECTIVE ACTION: COMPLIED WITH ER/A 622828-14. (0757745)SDR IPXA2025020543514Tee Angle · corrodedFAULT-STR-ZONE 100. LH MID WING TO BODY STRUCTURE, T-CHORD AT STA 1080-1200, LBL 60 HAS CORROSION. DOT 28-01. INSTALLED NEW T-CHORD AT STA 1080-1200, LBL 60 IAW B757-200 SRM 51-40-02. REVIEWED.SDR IPXA2025020543758Tee Angle · corrodedRH WING TO BODY STRUCTURE, T-CHORD AT STA 1260, RBL 10 HAS LIGHT CORROSION. DOT 28-05. NEW T-CHORD IT IS FOUND TO BE INSTALLED IAW B757-200 SRM 51-40-02-0G-0.SDR IPXA2025020443836Tee Angle · corroded.LH WING TO BODY STRUCTURE, T-CHORD AT STA 1020-1040, LBL 30 HAS LIGHT CORROSION. DOT 28-08. INSTALLED 8 NUTPLATE AND T-CHORD AT STA 1020-1040, LBL 30 IAW B757-200, SRM 51-40-02.SDR IPXA2025020444064Tee Fitting · corrodedFAULT-STR-ZONE 100. RH WING TO BODY STRUCTURE, T-CHORD AT STA 900-920, RBL 60 HAS CORROSION. DOT 28-10. INSTALLED T-CHORD AT STA 900-920 RBL 60 IAW B757 SRM51-40-02 HL P/N BACB30NX6K2 BACH #4244109 COLLAR P/N BACC30BL6 BACH # 4207142. REVIEWEDSDR IPXA2025020443668Tee Fitting · corrodedLH WING TO BODY STRUCTURE, T-CHORD AT STA 1040-1060, LBL 57 HAS LIGHT CORROSION . DOT 28-04. INSTALLED T-CHORD AT STA 1040-1060, LBL 57 LH WING TO BODY STRUCTURE, IAW B757-200, SRM 51-40-02.SDR IPXA2025013043970Tee Fitting · corrodedLH WING TO BODY STRUCTURE, T-CHORD AT STA 1020-1040, LBL 50 HAS 10 NUTPLATES CORRODED. DOT 28-09. INSTALLED T-CHORD AT STA 1020-1040, LBL 50 IAW B757-200, SRM 51-40-02. OSD: 1/31/2025SDR SWAA2025021884802Former · crackedR/H WING TO BODY FAIRING FORMER IS CRACKED BS 500D STRINGER 19 R/H<[01] FAIRING FORMER R/H IS CRACKED AT BS 500D IN L=2' NOT FOUND ALLOWABLE LIMITS ON SRM WILL BE REPAIRED BY REPLACEMENT OF PART PER SRM 51-10-02. PAR 9.;[02] VERIFIED CORRECTIVE ACTION 1;[03] RSDR SWAA2025021184634Support Angle · crackedCRACK ANGLE SUPPORT STRUCTURE WING TO BODY FAIRING LOCATED BS 540 AT LEVEL S-22L FUSELAGE EXTERIOR 2024-779430<[01] REPLACED ANGLE SUPPORT STRUCTURE WING TO BODY FAIRING LOCATED BS 540 AT LEVEL S-22L FUSELAGE EXTERIOR I.A.W B737-800 SRM 51-40-02; SRM 51-10-02 SDR SWAA2025011384163Fairing · crackedLOWER BODY FAIRING 193D HAS DAMAGE. REMOVED PANEL 193D IAW AMM 53-51-21. INSTALLED PANEL 193D REF AMM 53-51-21.SDR DALA2025010900177Pin · out of positionTAIL CONE EXIT RELEASE CAM PIN IS NOT 34.5 TO 38.5 DEGREES FROM THE CENTERLINE OF THE BASE AT AFT ACCESORIES COMPARTMENT. THIS COULD PREVENT THE PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. SUMMARY OF NRC 00899: REL
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