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 = '5700' 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 = '5700' 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 DALA2022061004095Skin · noneSHIP 666 REPAIR TO RH WING UPPER SKIN COMMON TO DRAG FITTING ATTACHMENT REQUIRES SUPPLEMENTAL INSPECTIONS PER ERA 599250-14. CORRECTIVE ACTION: REF ERA 599250-14. (2266999)SDR SWIA202266134Beam · damagedTRANSFER FROM EAML 920632 : TRANSFERRED FROM CAMP 24914026. FOUND LH WING WINGLET BEAM DAMAGED (REF. SRM 57-31-14 ITEM #25) (FILED CLOSED) REMOVED AND REPLACED LH WINGLET BEAM ASSY (REF. SRM 57-31-14 ITEM #25) IN REF TO SRM 51-42-06. COMPLETED 51-900-1003SDR SWIA202266133None · damagedTRANSFER FROM EAML 920630 : TRANSFERRED FROM CAMP 24914020. FOUND LH WING WINGLET DIAPHRAGM DAMAGED (REF. SRM 57-31-14 ITEM #20) (FILED CLOSED) REMOVED AND REPLACED LH WINGLET DIAPHRAGM (REF. SRM 57-31-14 ITEM #20) IN REF TO SRM 51-42-06. COMPLETED 51-900SDR SWIA202266132Beam · damagedTRANSFER FROM EAML 920629 : TRANSFERRED FROM CAMP 24914018. FOUND LH WING WINGLET BEAM DAMAGED (REF. SRM 57-31-14 ITEM #18) (FILED CLOSED) REMOVED AND REPLACED LH WINGLET BEAM (REF. SRM 57-31-14 ITEM #18) IN REF TO SRM 51-42-06. COMPLETED 51-900-1003-SKY SDR IXXA2022060402Cover · erodedSLAT TRACK COVER ERODEDSDR FDEA202206031364Doubler · noneDURING PERFORMING EA TG-5710-T0367832 P2 STEP 11.C.(5), FOUND 01EA ZLJ-8 (BACB30NY8K*) COUNTERSUNK FASTENER AT STA998 STGR35 RHS TOO CLOSE TO EDGE OF MACHINED STEP OF DOUBLER P/N 143W2314Y406, AND WILL RESULT IN KNIFE EDGE WITH MACHINED STEP ON AFT EDGE OSDR FDEA202206031363Doubler · misrepairedDURING PERFORMING EA TG-5710-T0367832 P1 STEP 11.C.(5), FOUND 01EA ZLJ-8 (BACB30NY8K*) COUNTERSUNK FASTENER AT STA998 STGR35 LHS TOO CLOSE TO EDGE OF MACHINED STEP OF DOUBLER P/N 143W2314Y405, AND WILL RESULT IN KNIFE EDGE WITH MACHINED STEP ON AFT EDGE OSDR JR2R20220603515Angle · crackedLH WHEEL WELL STUB ANGLE CRACKED FWD SIDE OF WEB AT FR52SDR DALA2022060603943Skin · noneSHIP 666 REPAIR TO LH WING UPPER SKIN COMMON TO DRAG FITTING ATTACHMENT REQUIRES SUPPLEMENTAL INSPECTIONS PER ERA 599264-14. CORRECTIVE ACTION: REF ERA 599264-14. (2261617)SDR UIEA2022051700486Plate · migratedR/H W/W STA 1350 WING LANDING GEAR SUPPORT BEAM SPLICE LOWER PLATE AFT I/B CORNER SHIM MIGRATED. SHIM MIGRATION INSPECTION PER SRM 51-20-08, MOUNT BOLT TORQUE CHECK PERFORMED PER SRM 51-40-04-0G-0, EDGE SEALEANT APPLIED PER AMM 51-31-01.SDR UIEA2022052200494Attach Plate · corrodedL/H WLG W/W STA 1241 L/H CTR OJ PUMP BONDING ATT SURFACE FOUND CORRODED. CORROSION AREA REMOVED AS PER SRM 51-10-02 AND REPROTECTED AS PER SRM 51-20-01, BLENDED OUT AREA WITHIN SRM 57-10-10-1A-2 ALLOWABLE DAMAGE 2 FIG 101 LIMITS.SDR UIEA2022052300500Panel · crackedLHW TE CAVITY LWR FIXED PANEL CHORD FOUND CRACKED AT WS 1470 CHORD LOCAL FABRICATED AS PER BOEING DWG : 65B08175 AND PART LIST AND CHORD INSTALLED AS PER SRM 51-40-02SDR UIEA2022052300528Flap · chafedLHW O/B FORE FLAP T/E UPR SURFACE O/B AREA FOUND CHAFING AS MARKED (3" TO O/B). PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94 ,FEB 20/2022</P>)SDR UIEA2022052400529Flap · delaminatedLHW O/B FORE FLAP L/E FOUND DELAMINATION (125" TO I/B)(<P>PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94 ,FEB20/2022</P>)SDR UIEA2022052400530Flap · delaminatedLHW O/B FORE FLAP L/E FOUND DELAMINATION (22" TO O/B). PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94 ,FEB20/2022</P>)SDR UIEA2022052400531Flap · delaminatedLHW O/B FORE FLAP L/E FOUND DELAMINATION (145" TO I/B). PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94 ,FEB20/2022</P>)SDR UIEA2022052400532Flap · chafedLHW O/B AFT FLAP T/E FOUND CHAFING (95" TO O/B). PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94, FEB20/2022</P>)SDR UIEA2022052400533Flap · delaminatedLHW O/B MID FLAP L/E FOUND DELAMINATION (140" TO I/B). PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94 ,FEB20/2022</P>)SDR UIEA2022052400534Flap · delaminatedLHW O/B MID FLAP L/E FOUND DELAMINATION (107" TO I/B). PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94 ,FEB20/2022</P>)SDR UIEA2022052400535Flap · delaminatedLHW O/B MID FLAP L/E FOUND DELAMINATION (55" TO I/B). PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94 ,FEB20/2022</P>)SDR UIEA2022052400536Skin · delaminatedLHW I/B FORE FLAP AFTER WEDGE UPPER SURFACE O/B AREA FOUND DELAMINATION (26" TO O/B)(<P>PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94, FEB20/2022</P>)SDR UIEA2022052400537Skin · delaminatedRHW O/B T/E MID FLAP UPR SURFACE AT AFT AREA 135" FROM O/B EDGE FOUND DELAMINATED. PERFORMED COMPOSITE HOTBOND REPAIR AS PER SRM 51-70-07 PAR.5.A REV94, FEB20/2022SDR UIEA2022052900555Housing · crackedRHW I/B FORE FLAP TO MID FLAP MOST O/B LEVER HOUSING FOUND CRACK. LEVER HOUSING REPLACED AS PER SRM 51-10-01 AND NEW HOUSING INSTALLED AS PER SRM 51-40-02SDR UIEA2022052900556Web · crackedRHW I/B FORE FLAP MOST O/B WBL 410.25 O/B RIB ASSY UPPER CHORD & WEB FOUND CRACKED(<P>LOCAL FABRICATE WEB AS PER RI NO.RI-57-00-15623 REV.A AND REPLACED UPPER CHORD AS PER SRM 51-10-02 AND NEW WEB AND UPPER CHORD INSTALLED AS PER SRM 51-40-02</P>)SDR UIEA2022052900557Structure · crackedREFER WO.790016 RI-57-00-15623 REV A HFEC OPEN HOLE INSPECTION FOUND R/H I/B FORE FLAP O/B RIB ASSY AT WBL 410.25 AT I/B WEB, I/B LOWER CHORD & O/B LOWER CHORD CRACKED. LOCAL FABRICATE I/B LOWER CHORD AND O/B LOWER CHORD AS PER BOEING DWG: 65B39038 AND PART SDR REXA2022062101268Hinge · noneRH AILERON CENTER HINGE BEARING LUG BORE D WAS FOUND TO BE OVERSIZED. REPAIRED HINGE FITTING LUG IAW MHIRJ REO 690-57-61-260.SDR REXA2022062101266Hinge · corrodedLH AILERON CENTER HINGE BUSHING LUG BORE C AND F HAVE CORROSION. REPAIRED HINGE FITTING LUG IAW BOMBARDIER REO 670-57-61-237.SDR REXA2022062101265Hinge · noneRH AILERON OB HINGE BEARING LUG BORE H WAS FOUND TO BE OVERSIZED. REPAIRED HINGE FITTING LUG IAW MHIRJ REO 690-57-61-261.SDR SWIA202266111None · crackedWHILE COMPLYING WITH SB 601R-57-046 REV C PART A (LHS) HOLE #15, #17, #18, #19 AND #20 HAS CRACK INDICATIONS. ALL HOLES ARE AT .3305" DIA. (C-CHECK RO 7/9/2022) REPAIRED HOLE #15, #17, #18, #19 AND #20 AT WS 65.75 BETWEEN R/S & AUX SPAR, LHS (DEVIATION SDR SWIA202266110None · crackedWHILE COMPLYING WITH SB 601R-57-046 REV C PART B (RHS) HOLE #4 AND HOLE #14 HAS CRACK INDICATIONS. HOLE #4 IS AT 3305" DIA AND HOLE #14 IS AT .3400" DIA. (C-CHECK RO 7/9/2022) REPAIRED HOLE #4 AND #14 AT WS 65.75 BETWEEN R/S & AUX SPAR, RHS (DEVIATIOSDR REXA2022062101270None · crackedL/H AILERON CENTER HINGE FITTING RIBLET IS CRACKED. REMOVED L/H AILERON CENTER HINGE RIBLET. INSTALLED A SERVICEABLE L/H AILERON CENTER HINGE RIBLET IAW CRJ 900 SRM 51-42-21-001-001-A01, 51-40-11-001-001-A01.SDR A6WA202205208501Skin · noneLEFT-WING LEADING-EDGE SKIN P/N 601R12074-3 SHOWS EROSION/ROUGHNESS OF 0.005" MULTIPLE SPOTS. ******AIRCRAFT REMOVED FROM SERVICE******* REMOVED AND REPLACED LEADING EDGE SKIN P/N 601R12074-3.SDR IXXA2022072604Skin Panel · corrodedLEFT WING UPPER SURFACE L/E CORRODEDSDR REXA2022062101267Hinge · noneR/H AILERON CENTER HINGE BEARING LUG BORE E WAS FOUND TO BE OVERSIZED. REPAIRED R/H AILERON CENTER HINGE BEARING LUG BORE IAW MHIRJ REO 690-57-61-260,REV --, 2022-05-15.SDR REXA2022062001257Hinge · noneR/H AILERON CENTER HINGE FITTINGS AT WING AFT SPAR HAVE 3 EA PREVIOUSLY OVERSIZED LUG BORES. REPAIRED R/H AILERON CENTER HINGE LUG FITTINGS ON WING T/E IAW MHIRJ REO 690-57-51-156,REV --, 2016-11-06.SDR IXXA2022060606Bushing · wornRW INBD FLAP SUPPORT #5 SPLINED BUSSHING WORN AND PITTEDSDR IXXA2022060605Collar · wornRW INBD FLAP #5 COLLAR FITTINGS WORN AND PITTEDSDR IXXA2022060604Torque Tube · wornRW INBD TORQUE TUBE WORN AND PITTEDSDR IXXA2022060603Bushing · wornSPLINED BUSHINGS LW INBD FLAP SUPPORT WORN AND PITTEDSDR IXXA2022060602Torque Tube · wornTORQUE TUBE ON LW INB FLAP WORN AND PITTEDSDR IXXA2022060601Collar · wornCOLLAR FITTING ON LW INB FLAP AT #4 SUPPORT WORN AND PITTEDSDR JR2R8471824Spar Cap · crackedRH WING TIP SPAR 1 CRACKEDSDR JR2R8471823Spar · crackedLH WINGTOP SPAR 1 CRACKEDSDR JR2R8471878Spar · crackedLH WING SPAR 1 CRACKEDSDR A6WA202205098502Skin · noneLH OUTBOARD LEADING EDGE SKIN P/N 601R12074-3 FOUND ERODED BEYOND LIMITS. ******AIRCRAFT REMOVED FROM SERVICE****** REMOVED AND REPLACED SKIN P/N 601R12074-3.SDR CALA2022051101200None · crackedLEFT WW VERTICAL PRESSURE DECK WEB CRACKED APPROX 1.75" LONG BETWEEN LBL 40.0 AND LBL 45.64 -- SEE PHOTO,S REF NDT PART 6. 51-00-00-23. C/W EDCR. VERIFIED CRACK LENGHT 1.9 INCHES. AND MARKED ENDS OF CRACK. IDT-QC :: NEED TO VERIFY CRACK AND MARK ENDS OF CRACK SDR CALA2022051101199None · crackedFLEET CYLCE N/R 9809108 CTR WING VERTICAL PRESSURE WEB CRACKED O N L/H 2 APPOX LBL 35.SDR IPXA2022050681809Stiffener · crackedINSPECTION TYPE:C6CRACK ON CENTER WING TANK STIFFENER(P/N:111T2008-12)ON STA 785.9, RBL 33.REPAIR I.A.W 767-300F SRM. 83.01, UPS EO B767-5740-58151-C.SDR HYIA20220405001Rib · crackedWHILE PERFORMING THE SID 57-10-25 INSPECTION, THREE CRACKS WHERE IDENTIFIED IN THE RIGHT CLOSE-OUT RIB (P/N 5122155-56.) THESE CRACKS WERE FOUND ON THE FORWARD ROW OF AT THE REAR TRUNNION PLATE ATTACH POINT. THERE ARE 6 HI-LOK HOLES ALIGNED VERTICALLY IN THSDR CALA2022050601148Fitting · crackedB737-57-4-1262 SHEAR FITTING AT STATION 540 AND RBL 6.14 IS CRACKED. NSA EMX N/R 00103. REMOVED AND REPLACED SHEAR FITTING AT STATION 540 AND RBL 6.14 U085625, 05/04/2022. DATA WAS TRANSCRIBED FROM NSA EMX N/R 00103 IAW B737-800 SRM 51-40-02 AND BAC DWG 111A20
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