JASC 5300
Service difficulty reports · 8,206
Reports filed under 5300 · Fuselage Structure (General), 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 = '5300' 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 = '5300' 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 QMLA2022062920036Profile · damagedCUSTOMER REQUEST TO INSPECT FRAME 5 IAW AIR METHODS ENGINEERING ORDER 23-5300-EO-3820 REV - AND ASB 21-01 REV A. VISUAL AND NDT INSPECTIONS CARRIED OUT. THE FOLLOWING DEFECTS WERE DISCOVERED: -LOWER LH DAMAGE OF SHORT PITCH DISTANCE AND EDGE DISTANCE IN U-PROFSDR R61A2022042300295Support · corrodedCENTER FUSELAGE III, LH FLOOR SUPPORT PANEL BETWEEN FR 88-90 FOUND CORRODED BEYOND ALLOWABLE LIMITS. REPLACED IAW SRM 51-42-03SDR IXXA2022041808Angle · crackedCORROSION FOUND ON ANGLE SUPPORT EXTERNAL POWER RECEPTACLE COMPARTMENT. FAS WO N431AZ-01-01 NR 00132SDR R61A2022040700246Seat Track · corrodedCENTER FUSELAGE III, R/H SEAT TRACK CORRODED AT FR 84 TO FR 74. R&R IAW EMB 170 SRM 51-41-01, 51-43-03 AND 51-43-04.SDR CALA2022032100705Skin · crackedSUPPORT TASK- EA5380-01178 REV.A OP.002, 1EA CRACK FOUND BETWEEN BS1660 AND 1670 STR 13AR APPROX. 3/8" IN LENGTH DETAIL REFER FINDING RECORD. TRANSFER WO.643912 AND ORIGINATED BY V906014. SRM 53-80-01-2R-7 RPR 7 TABLE 202 DETAIL XIV FUSELAGE SKIN BS 1660-1670 SDR KCQA20220318Stringer · corrodedPROFILE CORRODED BEYOND LIMITS, FS 6653.1 AND FRAME 19A, STRINGER 20R.SDR EE4Y2022031715259Skin Panel · noneDURING THE ACCOMPLISHMENT OF MAINTENANCE INSPECTION WAS FOUND AT REAR FUSELAGE BETWEEN FR65 AND FR66, BETWEEN STR-33/34RH SKIN WITH TOOL MARKS , NO ALLOWABLE DAMAGE LIMITS WERE FOUND AT SRM A320, DUE TO THIS FACT DETAILS WERE SENT TO AIRBUS ASKING FOR REPAIR SDR 7C7A2022031700004Strap · chafedCHAFE DAMAGE TO TOP STRAP PN 85322331 OF BOTTOM FRAME ASSEMBLY PN 8533086 AT X510 BETWEEN STR. 23S AND 24S. REF. 008.53-22.05SDR 7C7A2022031700003Frame · chafedCHAFE DAMAGE TO THE CENTER FUSELAGE FRAME X253.40 PN 85320575. REF. 008.53-22.03SDR 7C7A2022031700002Frame · chafedCHAFE DAMATE TO RH FRAME X531.50 PN 85330133 INBD FLANGE TO STRAP PN 85322331-179 AT STR. 23S. REF. ECO 008.53-22.04SDR AC2A2022031713901Plate · corrodedCORROSION DAMAGE CAUSING REPLACEMENT OF AFT RIGHT UPPER PLATE.SDR CALA2022031700699Frame · cracked(AD 2018-03-12) L/H FR68 DOOR STOP #4 HAS CRACK INDICATION IN BO T I/B I/B HOLE MARKED AND DOOR STOP #1 BOT I/B HOLE IN RED, REPA IR BEFORE NEXT FLIGHT () IAW SRM 53-41-12-300-010 FIG 001. REINSTALLED #4 DOOR STOP FITTI REPAIRED ZONE AREA 2 INSP THRESHOLD FROMSDR CALA2022031700698Stop · cracked(AD 2018-03-12) R/H FR66 DOOR STOP #7 HAS A CRACK INDICATION IN TOP I/B HOLE MARKED IN RED, REPAIR BEFORE NEXT FLIGHT INSTALLED FREEZE PLUG & WASHER, REINSTALLED #7 DOOR STOP FITTING THRESHOLD FROM TIME OF ADL/REPAIR EMBODIMENT 33000FC FH NOT RELE INSP METHOD SDR CALA2022031700695None · damagedFR16 LH DOUBLE JOGGLE FASTENER HOLES #7, #A, #B, #D, & #E DAMAGE INSPECTION REQUIREMENTS ON LHS HOLES #7, #8, #A AND #B PER BEFORE THE AIRCRAFT REACHES 37,605 TOTAL FLIGHT CYCLES. 4,700 FLIGHT CYCLES THEREAFTER. PART 2A OF THE LATEST REVISION OF EC/RA 5311-027SDR CALA2022031700694Stop · cracked(AD 2018-03-12) L/H FR 68 DOOR STOP #1 HAS A CRACK INDICATION IN BOT I/B I/B HOLE MARKED IN RED, REPAIR BEFORE NEXT FLIGHT () 008 SHEET 01, 02 & 03. INSTALLED FRAME SPLICE & FREEZE PLUG. REI IAW SRI 53-41-12-205-010 REPAIRED ZONE AREA 2 INSP THRESHOLD FRO SUBSSDR CALA2022031700693Stop · cracked(AD 2018-03-12) R/H FR68 DOOR STOP #1 HAS A CRACK INDICATION IN BOT I/B AND TOP O/B HOLE MARKED IN RED, REPAIR BEFORE NEXT FLIGH T. 011 FIG 008 SHEET 01, 02 & 03. INSTALLED FRAME SLPICE & FREEZE P INSP IAW SRI 53-41-12-205-010 REPAIRE ZONE AREA 2 INSP THRESHOLSDR IXXA2022041803Panel Support · corrodedKEEL BEAM STA 889 PANEL SUPPORT CORRODED. FAS WO N431AZ-01-01 NR 00081SDR HNAA2022041300158None · noneE907832 - LEFT HAND LOWER SEAT TRACK CORRODED BETWEEN FRAME 18 TO 23 .... REMOVED AND REPLACED LEFT HAND LOWER #1 SEAT TRACK IAW EMB 145 AMM 53-01-06.SDR 2022FA0000176Warning Switch · leakingDURING CRUISE FLIGHT PILOT NOTICED A SLIGHT DROP IN OIL PRESSURE. SOON THEREAFTER PILOT NOTICED OIL ON THE NACELLE COMING FROM REAR OF THE LEFT ENGINE COWL. PILOT DECLARED AN EMERGENCY AND LANDED WITH NO ADDITIONAL SYMPTOMS. IT WAS DISCOVERED THAT THE OIL WSDR SWIA202265162None · damagedTRANSFER FROM EAML 866485 : CREATED FROM FORWARD DISCREPANCY. PLEASE REFERENCE AML 866344 RT SIDE AT FUSELAGE LOCATED FWD RT BETWEEN FRAME 01 AND FRAME 02 AND STRINGER 17 AND 18 SKIN DAMAGE DUE TO BIRD HIT. THIS DAMAGE HAS BEEN DETERMINED TO BE A / MAJOR REPAISDR JJBA20220316044Not Reported · not reportedRH AFT LAV FLOOR SUPPORT HAS SIGNS OF CORROSION FR 59-61+5 STR 17R. REMOVED AND REPLACED GUSSETSDR CALA2022031700684None · cracked27JUL SFO CF -9 :EXTERNAL FUSELAGE SKIN HAS DOUBLER INSTALLED FRAME 26 A T STR 41 LT. :REINSPECT DOUBLER PER PER SRI-53-00-11-2-003-00 USING AIRBUS NTM 51-10-16 (EDDY CURRENT) B EFORE 48000 FC. OK TO CF PER SRI 53-00-11-2-003-00 AND SFOIQ WAL SH. 13OCT OPB ISDR CALA2022031700683Skin · crackedWHILE ACCOMPLISHING EA 5310-07772 REV. ORIG, OP. 001 AND 004; PRODUCTION REPORTED DAMAGE INDICATIONS AT HOLE #1 AND CRACK INDICATIONS AT HOLES #2 AND #3 IN THE RIGHT HAND FR35 AT STGR30. 135,400 FH OR 67,700 FC, WHICHEVER OCCURS FIRST, PERFORM 5310-07989. INSPSDR CALA2022031700682Skin · cracked(AD2020-20-05) DURING ROTO INSPECTION OF RH FR20 DOUBLE JOGGLE HOLES. CRACK INDICATION WAS NOTED IN HOLE A. REPAIR BEFORE NEXT F LIGHT.() REPAIRED R/H FR20 DOUBLE JOGGLE HOLE #A BY OVERSIZING IAW EC/RA 5311-02774. EMP# V935774 WORK ACCOMPLISHED AT ST ENGINEERISDR CALA2022031700681Skin · cracked(AD2020-20-05) L/H FR 16 DOUBLE JOGGLE HOLES 7,AB, AND D HAVE CR ACK INDICATIONS IN MIDDLE AND AFT LAYERS OF THE HOLES.() REPAIR BEFORE NEXT FLIGHTSDR CALA2022031700679None · corrodedR2 DOOR SILL HAS SEVERAL AREAS OF CORROSION IN FASTENER HOLES BE TWEEN FR.66-68 PER NR9290764/22764 GEN BY V061742 RMVD AND RPLD R2 DOOR SILL P/N D5348004320701 PO 1101622.9 IAW A 319 SRM 51-72-11 51-42-11 PG 1-2 AND PG 7,8 BY MECH V061742 INSP BY V077960SDR FDEA202203150944Seat Track · corrodedMAIN DECK SEAT TRACK INB LOBE LOCATED BETWEEN STA 1801 AND 1821 AT LBL74 HAS EXFOLIATION CORROSION. NEW SEAT TRACK SECTION PN:AFA7789-543 WAS REPLACED FROM STA 1771 TO 1887 AT LBL 75.25. THIS PRETAINS THE DAMAGED SECTIONS OF SEAT TRACK ON THIS NON-ROUTINE.SDR FDEA202203150943Seat Track · corrodedMAIN DECK SEAT TRACK OUTB LOBE LOCATED AT STA 1841 AT LBL74 HAS EXFOLIATION CORROSION. NEW SEAT TRACK SECTION PN:AFA7789-543 WAS REPLACED FROM STA 1771 TO 1887 AT LBL 75.25. THIS PRETAINS THE DAMAGED SECTIONS OF SEAT TRACK ON THIS NON-ROUTINE. SEE NON-ROSDR FDEA202203150942Seat Track · corrodedMAIN DECK SEAT TRACK INB LOBE AT STA 1782 LBL 74 HAS EXFOLIATION CORROSION NEW SEAT TRACK SECTION PN:AFA7789-543 WAS REPLACED FROM STA 1771 TO 1887 AT LBL 75.25. THIS PRETAINS THE DAMAGED SECTIONS OF SEAT TRACK ON THIS NON-ROUTINE. SEE NON-ROUTINE N00068 WSDR R61A2022033100230Stringer Splice · corroded"SEVERAL AREAS OF CORROSION ON STRINGER 21L FR. 88-89. : PERFORMED PERMANENT REPAIR BY CUTOUT
AND STGR SPLICE REPAIR AT 21L FR. 88-89 IN ACCORDANCE WITH, REF ETD2022-170-009596"SDR VNAA202203159992Frame · corrodedCORROSION ON FRAME STA. 1015.00, BTW STGR.26R ANS STGR.25RH AT AFT BAGGAGE BAY. SDR 2A6R2022031563006Frame · corrodedTHE T-CAP (PN: L533M1028203) ON FRAME 3 AT FUSELAGE STATION 3,150 MM, WHICH SUPPORTS THE CABIN FLOOR STRUCTURE, WAS FOUND TO BE CORRODED ON THE FORWARD HORIZONTAL FLANGE AT THE NUTPLATES BETWEEN LBL 500 MM AND RBL 500 MM.SDR 2A6R2022031563005Deck Plate · corrodedCORROSION DAMAGE WAS NOTED TO THE UPPER SKIN OF THE COCKPIT FLOOR (PN: L533M1014218) ON THE RH SIDE FROM APPROXIMATELY FUSELAGE STATION 1,700MM TO 2,525MM.SDR 2A6R2022031563004Frame · crackedDAMAGE WAS NOTED ON THE LH CABIN FRAME #5 ASSEMBLY (PN: L533M1088103) AND REINFORCEMENT ANGLE (PN: L533M1088218) AT APPROXIMATELY FUSELAGE STATION 4,709MM, WATER LINE 2,350MM. THERE IS ONE CRACK ON EACH STRUCTURE IDENTIFIED ABOVE AT THE LOWER MEDICAL WALL MSDR SWIA202264979None · damagedDURING BIRDSTRIKE INSPECTION FOUND THE FOLLOWING DAMAGE: A DENT JUST FORWARD OF FRAME 3 AND JUST BELOW STRINGER 20R. THE DENT MEASURES 3.5 INCHES WIDE AND 3.5 INCHES LONG AND IS 0.10 INCH DEEP. IT IS 0.125 INCH FROM THE RIVETS ON FRAME 3 AND 4.25 INCHES FROM SDR JJBA20220314037Not Reported · not reportedRH FRAME 62 HAS CRACK ON THE FLOOR SUPPORT AREA. REPLACED DAMAGE FLOOR SUPPORT AND ANGLE AT RH FRAME 62SDR VNAA202203149991Stringer · gougedGOUGES ON STRINGER AND RIVET DAMAGED, STGR. 22 RH BTW FS1126.00/1144.00 CORRECTIVE ACTION. STRINGER AND RIVET. STGR 22RH BTW FS1126.00 / 1144.00 WAS REPAIRED PER EA 22-C7-53-0258 REV, IRSDR CALA2022031400664None · crackedWHILE ACCOMPLISHING EA 5310-07772 REV. ORIG, OP. 001 AND 004; PRODUCTION REPORTED DAMAGE INDICATIONS AT HOLE #1 AND CRACK INDICATIONS AT HOLES #2 AND #3 IN THE RIGHT HAND FR35 AT STGR30. 135,400 FH OR 67,700 FC, WHICHEVER OCCURS FIRST, PERFORM 5310-07989. INSPSDR CALA2022031400663Keelbeam · damagedWHILE ACCOMPLISHING INSPECTIONS PER FCD 5330-05575D, PRODUCTION REPORTED MULTIPLE DISCREPANT/OVERSIZED HOLES IN THE RH KEEL BEAM MLG ATTACHMENT STRUCTURE. ECRA 5330-06914. ACCOMPLISH A PERMANENT REPAIR PER LATEST REVISION OF EC/RA 5330-06914 ON OR BEFORE 24-FESDR IXXA2022060809Floor Panel · crackedUPPER CARGO FLOOR PANEL 241M DAMAGED HONEYCOMBSDR SWIA202265265None · scratchedREAR FUSELAGE L/H LOWER EXTERNAL SKIN DIRECTLY ABOVE ACCESS PANELS 351GL AND 351HL HAS NUMEROUS SCRATCHES TO THE PAINT AND BARE METAL EXPOSED. (C-CHECK RO 4/2/2022) REPAIRED REAR FUSELAGE L/H LOWER SKIN AS REQUIRED REF ETD2022-170-010449 AND DOCUMENT:CVSDR R61A2022033100231Shear Angle · corroded"RH FLOOR SUPPORT CORRODED AT FRAME 84 FROM CENTER LINE TO STRINGER 29R. REMOVED AND REPLACED SHEAR CLIP AT FRAME 84 FROM CENTER LINE TO STRINGER 29R. REF SRM
51-40-08."SDR R61A2022033100229Shear Angle · corrodedSHEAR CLIP CORRODED ON FRAME 82 FROM STRINGER 27L TO 28L.REMOVED AND REPLACED DAMAGED SHEAR CLIP ON FRAME 82 FROM STRINGER 27L TO 28L.REF SRM 51-40-08,SDR R61A2022033100228Shear Angle · corrodedSHEAR CLIP CORRODED ON FRAME 85 FROM STRINGER 27L TO 28L. REMOVED AND REPLACED SHEAR CLIP ON FRAME 85 FROM STRINGER 27L TO 28L. REF SRM 51-40-08.SDR R61A2022033100227Shear Angle · corrodedSHEAR CLIP CORRODED ON FRAME 84 FROM STRINGER 27L TO 28L. REMOVED AND REPLACED DAMAGED SHEAR CLIP. REF SRM 51-40-08SDR P5CA2022022100062None · noneM/D STA 1778-1800 LBL 33 SEAT TRACK FOUND CORROSION.(<P>M/D STA 1778-1800 LBL 33 SEAT TRACK CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECKED WITHIN SRM 53-00-52 ALLOWABLE DAMAGE 1 FIG 101 LIMIT.</P>)SDR P5CA2022022100044None · noneM/D STA 850 - 809 LBL 11.33" SEAT TRACK FOUND CORROSION(<P>M/D STA 805 - 809 LBL 11.33" SEAT TRACK CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECKED WITHIN SRM 52-00-52 ALLOWABLE DAMAGE. 1 FIG 101 LIMIT</P>)SDR P5CA2022022100045None · noneM/D - STA 1920 RBL 75.92 SEAT TRACK FOUND CORROSION.(<P>M/D - STA 1920 RBL 75.92 SEAT TRACK CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECKED WITHIN SRM 53-00-52 ALLOWABLE DAMAGE 1 FIG 101 LIMIT.</P>)SDR P5CA2022022100046None · noneM/D - STA 1920 RBL 99 SEAT TRACK FOUND CORROSION(<P>M/D - STA 1920 RBL 99 SEAT TRACK CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECKED WITHIN SRM 53-00-52 ALLOWABLE DAMAGE 1 FIG 101 LIMIT.</P>)SDR P5CA2022022100047None · noneM/D - STA 1900 RBL 99 SEAT TRACK FOUND CORROSION(<P>M/D - STA 1900 RBL 99 SEAT TRACK CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECKED WITHIN SRM 53-00-52 ALLOWABLE DAMAGE 1 FIG 101 LIMIT.</P>)
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