Service difficulty reports

1,771,154 reports of malfunctions and defects, newest first. Air carriers must report; general aviation reporting is voluntary.

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'
  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.

SDR IPXA2026090851105Rib · crackedLEFT WING, CENTER FLAP, TOP SKIN RIB FLANGE, 3 EA CRACK INDICATION NOTED AT RIB 26. ACCOMPLISHED PERMANENT REPAIR IAW EO-98405-REQ1 AND EA 300-5750-27-A4600, REV -.Aug 6, 2026 · N147UP · Airbus A300F4622R · Trailing Edge FlapsSDR REXA2026092101853Plate · wornWEAR ON FWD AND AFT PLATE (2EA) OF PASSENGER DOOR. FWD AND AFT NEW PLATE (2EA) OF PASSENGER DOOR WERE REPLACED PER CRJ-900 SRM 51-42-06-001-001-A01; CRJ-900 SRM 51-42-21-001-001-A01 AND CRJ-900 SRM 51-42-13-001-001-A01.Aug 6, 2026 · N480PX · Cndair CL6002D24 · Passenger/Crew DoorsSDR REXA2026092101852Plate · wornWEAR ON FWD AND AFT PLATE (2EA) OF PASSENGER DOOR. FWD AND AFT NEW PLATE (2EA) OF PASSENGER DOOR WERE REPLACED PER SRM 51-42-06-001-001-A01; CRJ-900 SRM 51-42-21-001-001-A01 AND SRM 51-42-13-001-001-A01.Aug 6, 2026 · N480PX · Cndair CL6002D24 · Passenger/Crew DoorsSDR REXA2026092101845Bracket · wornWEAR ON BRACKET RETAINING (2EA) AND MISSING GROMMETS ON BRACKET RETAINING (4EA) OF PASSENGER DOOR. BRACKET RETAINING (2EAS) WERE REPLACED PER CRJ-900 SRM 51-42-21-001-001-A01,GROMMETS ON BRACKET RETAINING (4EA) WERE INSTALLED PER CRJ-900 AMM 52-11-05-350-801.Aug 6, 2026 · N480PX · Cndair CL6002D24 · Passenger/Crew DoorsSDR AALA202609179179Angle · corrodedAIRCRAFT IN BASE MAINTENANCE: CABIN - AFT WET AREA - CORROSION ON ANGLE, AROUND FASTENER HOLE STA 993 AT APPROX. RBL 37. INSTALLED ANGLE IAW DRAWING 147A5700 AND AARD 51-00-05-1.Aug 6, 2026 · N905AN · Boeing 737823 · Fuselage Miscellaneous StructureSDR U2RA2026090700051Tension Tie · crackedDURING FCD 744-53-0025 OPEN HOLE HFEC INSPECTION 1EA HOLE CRACK INDICATION FOUND AT STA 1180 LT TENSION TIE AFT DOUBLER AND FWD CHANNEL. INSTALLED FRAME DOUBLER AND FWD CHANNEL REPAIR PART ON BS 1180 LT TENSION TIE IAW SRM 51-40-02, DWG 65B 01752, MUA-26-0Aug 6, 2026 · N756CA · Boeing 747428 · Fuselage Main, StructureSDR U2RA(20260907)000Tension Tie · cracked2 CRACK INDICATION FOUND (FWD CHANNEL 1EA HOLE AND FRAME AREA 1EA HOLE) DURING OPEN-HOLE HFEC INSPECTION OF THE TENSION TIE AT STA 1120, LEFT HAND SIDE. PER FCD 744-53-0025 R3. REPAIR: REAMED CRACK SIGNAL INDICATION HOLE ON BS 1120 LT FRAME WEB ONLY. UP TO 0.Aug 6, 2026 · N756CA · Boeing 747428 · Fuselage Main, StructureSDR IPXA2026090851282Rib · crackedRIGHT WING, CENTER FLAP, TOP SKIN RIB FLANGE, 2 EA CRACK INDICATIONS NOTED AT RIB 26. ACCOMPLISHED PERMANENT REPAIR IAW EO-98461-REQ1 AND EA 300-5750-27-A4602, REV -.Aug 6, 2026 · N147UP · Airbus A300F4622R · Trailing Edge FlapsSDR IPXA2026090851265Rib · crackedMAJOR REPAIR. RT WING, CENTER FLAP, TOP SKIN RIB FLANGE, 1 EA CRACK INDICATION NOTED AT RIB 11. ACCOMPLISHED PERMANENT REPAIR IAW EO-98461-REQ1 AND EA 300-5750-27-A4602, REV -.Aug 6, 2026 · N147UP · Airbus A300F4622R · Wing, Rib/BulkheadSDR IPXA2026091051162Rib · crackedMAJOR REPAIR, RT WING, CENTER FLAP, TOP SKIN RIB FLANGE, ONE CRACK INDICATION NOTED AT RIB 25. VERIFIED ACCOMPLISHED PERMANENT REPAIR IAW EO-98461-REQ1 (T3F18E009JLB2) AND EA 300-5750-27-A4602, REV -.Aug 6, 2026 · N147UP · Airbus A300F4622R · Trailing Edge FlapsSDR IPXA2026091051256Rib · crackedMAJOR REPAIR, RT WING, CENTER FLAP, TOP SKIN RIB FLANGE, TWO CRACK INDICATIONS NOTED AT RIB 27. ACCOMPLISHED PERMANENT REPAIR IAW EO-98461-REQ1 AND EA 300-5750-27-A4602, REV -.Aug 6, 2026 · N147UP · Airbus A300F4622R · Trailing Edge FlapsSDR IPXA2026091051151Rib · crackedRH WING, CENTER FLAP, TOP SKIN RIB FLANGE, HAD 1 CRACK INDICATION NOTED AT RIB 12. ACCOMPLISHED PERMANENT REPAIR IAW EO-98461-REQ1, AND EA 300-5750-27-A4602, REV -.Aug 6, 2026 · N147UP · Airbus A300F4622R · Trailing Edge FlapsSDR SIMA20260806001Seat Track · corrodedSSI 53-21-005 RH LWR INBD FLOOR BEAM SEAT TRACK JUST FWD OF FR24 HAS CORROSION AT MARKED AREA. (MAJOR REPAIR) (LEVEL 2 CORROSION) PERFORMED PERMANENT REPAIR TO RH LWR INBD FLOOR BEAM SEAT TRACK BETWEEN FR 23 TO FR 26 IAW ERJ 170 SRM 53-00-10/REPAIR 01P.Aug 6, 2026 · N769KW · Emb ERJ170100LR · Fuselage Main, StructureSDR IPXA2026090851082Rib · crackedMAJOR REPAIR, LT WING, CENTER FLAP, TOP SKIN RIB FLANGE, 1 EA CRACK INDICATION NOTED AT RIB 27. ACCOMPLISHED PERMANENT REPAIR IAW EO-98405-REQ1 AND VT-MAE EA 300-5750-27-A4600, REV -.Aug 6, 2026 · N147UP · Airbus A300F4622R · Trailing Edge FlapsSDR REXA2026091101798Former · corrodedPAX DOOR AFT FORMER FOUND TO BE CORRODED. REQUIRES REPLACEMENT REMOVED PAX DOOR AFT UPPER, MID AND LOWER SEAL RETAINERS TO FACILITATE OTHER MAINTENANCE IAW CRJ900 SRM 51-42-06-001-001-A01 REMOVED PAX DOOR AFT SUPPORT ANGLE TO FACILITATE OTHER MAINTENANCE IAW CAug 6, 2026 · N810SK · Cndair CL6002D24 · Passenger/Crew DoorsSDR SWAA2026091083716Floor Panel · pulledPASSENGER CABIN FLOOR PANEL 231XF HAS UPPER SURFACE DAMAGE PASSENGER CABIN FLOOR PANEL 231XF WITH UPPER SURFACE PULLED STRANDS WAS REPLACED WITH A SERVICEABLE FLOOR PANEL IAW SRM 51-10-02-0G-0 PARA 9.A.1 DUE TO AMOUNT OF ALL DAMAGE.Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Floor PanelSDR SWAA2026091004636Floorbeam · corrodedCORROSION FOUND ON TOP & UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT LBL 2 BS 986 WL 208 {MARKED} {PICTURES UPLOADED} EVALUATED CORROSION ON BS986 LBL2 WL208 FLOOR BEAM UPPER FLANGE ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.130" DAMAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091043548Floor Support · corrodedCORROSION FOUND IN (MULTIPLE SPOTS) ON TOP AFT (WET AREA) FLOOR STRUCTURE AT LBL 54 BS 947 - BS 995 WL 208 (MOP-SEAL) CORROSION ON AED INNER CHORD EVALUATED AND FOUND TO BE OUT LIMITS ORIGINAL MATERIAL THICKNESS IS 0.080" LOWEST MATERIAL REMAINING IS 0.067" Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Miscellaneous StructureSDR SWAA2026091059678Floorbeam · corrodedCORROSION FOUND ON TOP & UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT RBL 49 BS 986 WL 208 . REPAIRED FUSELAGE FLOORBEAM UPPER CHORD REPAIR AT BS 986.5 BETWEEN LHS & RHS TERMINATING ENDS AS PER EA 26-153-02137Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091015537Floorbeam · corrodedCORROSION FOUND ON UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT LBL 12 BS 986 WL 208. EVALUATED CORROSION ON BS986 LBL12 WL208 FLOOR BEAM UPPER FLANGE ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.130" DAMAGE FOUND TO BE OUT LIMITS PEAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091035474Web · corrodedCORROSION FOUND ON TOP AFT (WET AREA) FLOOR STRUCTURE AT LBL 38 BS 1006 WL 208 . REMOVE AND REPLACE L/H SHEAR WEB FROM BS986-BS1016 LBL34-LBL42 WL 208 RECORD ON CCN TTG8Q01DKS16 DUE TO OUT LIMIT STATEMENT THEREFORE CORROSION ON TOP AFT (WET AREA) FLOOR STRUCAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Miscellaneous StructureSDR SWAA2026091013321Floorbeam · corrodedCORROSION FOUND ON TOP & UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT RBL 8 BS 986 WL 208. EVALUATED CORROSION ON BS986 RBL8 WL208 FLOOR BEAM UPPER FLANGE ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.090" DAMAGE FOUND TO BE OUT LIMITSAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091033325Floorbeam · corrodedCORROSION FOUND ON TOP & UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT RBL 41 BS 986 WL 208. EVALUATED CORROSION ON BS986 RBL41 WL208 FLOORBEAM UPPER FLANGE ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.110" DAMAGE FOUND TO BE OUT LIMITAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091030945Intercostal · corrodedCORROSION FOUND ON TOP AFT (WET AREA) FLOOR STRUCTURE AT LBL 32 BS 996 WL 208. EVALUATED CORROSION ON BS986-BS1006 LBL34 WL208 INTERCOSTAL AT BS 996 LBL32 WL208 ORIGINAL MATERIAL THICKNESS IS 0.080" LOWEST REMAINING MATERIAL IS 0.056", DAMAGE FOUND TO BE OUAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Miscellaneous StructureSDR SWAA2026091088181Strap · corrodedCORROSION FOUND IN (MULTIPLE SPOTS) ON TOP AFT (WET AREA) FLOOR STRUCTURE AT LBL 3 BS 1006 - BS 1010 WL 208. REMOVED AND REPLACED TENSION STRAP BS 1006-1024 LBL 3 IAW SRM 51-40-02-0G-0 AND SRM 147A5600, REV B.Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Miscellaneous StructureSDR SWAA2026091009965Floorbeam · corrodedCORROSION FOUND ON TOP & UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT RBL 35 BS 986 WL 208 {MARKED} {PICTURES UPLOADED} EVALUATED CORROSION ON BS986 RBL35 WL208 FLOOR BEAM UPPER FLANGE ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.120" DAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091073115Floor Panel · pulledPASSENGER CABIN FLOOR PANEL 241DF HAS UPPER SURFACE DAMAGE PASSENGER CABIN FLOOR PANEL 241DF WITH UPPER SURFACE PULLED STRANDS WAS REPLACED WITH A SERVICEABLE FLOOR PANEL PER SRM 51-10-02-0G-0 PARA 9.A.1 DUE TO AMOUNT OF ALL DAMAGE.Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Floor PanelSDR SWAA2026091070938Strap · corrodedCORROSION FOUND IN (MULTIPLE SPOTS) ON TOP AFT (WET AREA) FLOOR STRUCTURE AT RBL 18 BS 1006 - BS 1014 WL 208. REMOVED AND REPLACED TENSION STRAP BS 1016 - 1028, RBL 18, WL 208 IAW SRM 51-40-02-0G-0 AND SRM 147A5730 REV: C.Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Miscellaneous StructureSDR SWAA2026091043360Sill Drain · corrodedCORROSION FOUND ON TOP & UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT RBL 57 BS 947 - BS 990 (MOP-SILL) CORROSION ON ASD INNER CHORD EVALUATED AND FOUND TO BE OUT LIMITS IN AN AREA OF 4.1"LX1.5"WX0.02"D REMOVED AND REPLACED I.A.W SRM 51-40-02-0G-0 AND BOEING Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, StructureSDR SWAA2026091099550Floorbeam · corrodedCORROSION FOUND ON TOP AFT (WET AREA) FLOOR STRUCTURE AT LBL 42 BS 986 WL 208. EVALUATED CORROSION ON BS986 LBL42 WL208 FLOORBEAM UPPER FLANGE ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.130" DAMAGE FOUND TO BE OUT LIMITS PER SRM 53-7Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091087532Floorbeam · corrodedCORROSION FOUND ON TOP AFT (WET AREA) FLOOR STRUCTURE AT LBL 45 BS 986 WL 208, EVALUATED CORROSION ON BS986 LBL45 WL208 FLOORBEAM UPPER FLANGE ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.130" DAMAGE FOUND TO BE OUT LIMITS PER SRM 53-7Aug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091004217Shear Web · corrodedCORROSION FOUND ON TOP AFT (WET AREA) FLOOR STRUCTURE AT LBL 36 BS 1002 WL 208. REMOVED AND REPLACED L/H SHEAR WEB FROM BS986-BS1016 LBL34-LBL42 WL 208 RECORD ON CCN TTG8Q01DKS16 DUE TO OUT LIMIT STATEMENT THEREFORE CORROSION FOUND ON TOP AFT (WET AREA) FLOAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Miscellaneous StructureSDR SWAA2026091049172Floorbeam · corrodedCORROSION FOUND ON TOP & UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT RBL 45 BS 986 WL 208. EVALUATED CORROSION ON BS986 RBL45 WL208 FLOOR BEAM UPPER FLANGE ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.080" DAMAGE FOUND TO BE OUT LIMITAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR SWAA2026091015597Structure · corrodedCORROSION FOUND IN (MULTIPLE SPOTS) ON TOP AFT (WET AREA) FLOOR STRUCTURE AT LBL 36 BS 989 - BS 995 WL 208 {MARKED} {PICTURES UPLOADED} REMOVED AND REPLACED L/H SHEAR WEB BS986-BS1016 LBL36-LBL48 WL208 I.A.W SRM 51-40-02-0G-0 SOPM 20-50-19 AND BOEING DWG 147AAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Floor PanelSDR SWAA2026090912420Floorbeam · corrodedCORROSION FOUND ON THE TOP AND UNDERSIDE AFT (WET AREA) FLOOR STRUCTURE AT RBL 30, BS 986, WL 208. EVALUATED CORROSION ON BS 986, RBL 30, WL 208 FLOORBEAM UPPER FLANGE, ORIGINAL MATERIAL THICKNESS IS 0.150" LOWEST REMAINING MATERIAL IS 0.120" DAMAGE FOUND TOAug 6, 2026 · N931WN · Boeing 7377H4 · Fuselage Main, Floor BeamSDR IPXA2026090758082Bracket · brokenRIGHT CENTER FLAP, OTBD FACE, AFT BRACKET BROKEN. REMOVED AND REPLACED ONE BRACKET AT RT CENTER FLAP, OTBD FACE IAW SRM 51-40-21-001.Aug 6, 2026 · N147UP · Airbus A300F4622R · Trailing Edge FlapsSDR IPXA2026090758776Bracket · damagedRIGHT WING OTBD FLAP INBD EDGE AFT ANGLE HAS ELONGATED HOLES. REMOVED AND REPLACE NEW ANGLE IAW SRM 51-40-21-001.Aug 6, 2026 · N147UP · Airbus A300F4622R · Trailing Edge FlapsSDR SWAA2026090895787Scuff Plate · crackedCRACKED AFT SCUFF PLATE. REPAIRED AFT SCUFF PLATE IN FWD CARGO IAW SRM 53-30-15-2R-1, REPAIR 1, PARAGRAPH 4. B, STEPS 2 - 7.Aug 6, 2026 · N8652B · Boeing 7378H4 · Fuselage Miscellaneous StructureSDR SWAA2026090818967Support Angle · crackedCRACKED SUPPORT ANGLE LOCATED BS380 TO BS400 AT LEVEL RBL 41 WL 208.1. REPLACED THE SUPPORT ANGLE AND FASTENERS IAW SRM 51-40-02, DWG 143A5400, SHEET 184, REV -, & DWG 143A5400, SHEET 140, REV -.Aug 6, 2026 · N8652B · Boeing 7378H4 · Fuselage Miscellaneous StructureSDR REXA2026090801775Stub Frame · corrodedSTUB FRAME AT FS 581 BETWEEN STR 19L AND STR 18L IS CORRODED. UPON FURTHER EVALUATION, THE STUB FRAME IN FS 581 BETWEEN STR 19L AND STR 18L WAS FOUND TO BE HEAVILY CORRODED AT THE ATTACHED FLANGE AND WEB DUE TO THIS THE PART IS OUT THE LIMITS OF THE SRM 53-3Aug 6, 2026 · N810SK · Cndair CL6002D24 · Fuselage Main, StructureSDR SWAA2026090700470Support Angle · crackedCRACKED SUPPORT ANGLE, BS 380 - 400, RBL 10, WL 208.1. REPLACED THE SUPPORT ANGLE IAW SRM 51-10-02, ITEM 9, SRM 51-40-02, DWG 143A5400, 51-40-02, & DWG 143A5400, SHEET 184, REV -.Aug 6, 2026 · N8652B · Boeing 7378H4 · Fuselage Miscellaneous StructureSDR SWAA2026090754061Scuff Plate · crackedCRACKED FWD CORNER SCUFF PLATE AT FWD CARGO BAY. REPAIRED THE SCUFF PLATE IAW SRM 53-30-15-2R-1, REPAIR 1, PARAGRAPH 4. B, STEPS (2 TO 7), FIGURE 203.Aug 6, 2026 · N8652B · Boeing 7378H4 · Fuselage Miscellaneous StructureSDR SWAA2026090345661Rib · crackedCRACKED INSPAR RIB, HSS 129.50 AND 27 INCHES FROM FRONT SPAR. REPAIRED THE INSPAR RIB IAW SRM 55-10-09-2R-4, REPAIR 4.Aug 6, 2026 · N954WN · Boeing 7377H4 · Horizontal Stabilizer, Spar/RibSDR SWAA2026090322253Strap · crackedCRACK INDICATION FOUND ON THE BS 639, LBL45.57 STUB BEAM STRAPS. REPLACED THE STRAP ASSY IAW SRM 51-40-02-0G-0, SRM 51-10-02-0G-0, PARA 9, & DWG 144A1715, SHEET 9, REV A.Aug 6, 2026 · N954WN · Boeing 7377H4 · Fuselage Miscellaneous StructureSDR SWAA2026090257730Crossbeam · crackedCRACKED PANEL BREAK AT BS 540 RBL 3 TO RBL 25 WL 208 REMOVED AND REPLACED PANEL BREAK BS540 BL0 TO RBL25 WL208 IAW SRM 51-40-02 ANG DWG# 143A5240 REV -. VERIFIED CORRECTIVE ACTION 1Aug 6, 2026 · N8709Q · Boeing 7378 · Fuselage Main, StructureSDR SWAA2026090220226Crossbeam · crackedCRACKED PANEL BREAK AT BS 540 LBL 3 TO LBL 25 WL 208 REMOVED AND REPLACED PANEL BREAK BS540 BL0 TO LBL25 WL208 IAW SRM 51-40-02 ANG DWG# 143A5240 REV -. VERIFIED CORRECTIVE ACTION 1Aug 6, 2026 · N8709Q · Boeing 7378 · Fuselage Main, StructureSDR SWIA2026080677074Seat Track · gougedCF III CABIN FLOOR STRUCTURE LEFT OUTBOARD SEAT TRACK SECTION FR 74 - 84 HAS GOUGING AT FRS 74, 78, 80, 82 AND 83. (C-CHECK RO 08/30/2026)REMOVED AND REPLACED CF III CABIN FLOOR STRUCTURE LEFT OUTBOARD SEAT TRACK SECTION FR 74 - 84. REF: SRM 51-40-08. REPLAAug 6, 2026 · N277SY · Emb ERJ170200LL · Fuselage, Seat/Cargo Attach FittingsSDR HNAA2026090100851Support · corrodedRIGHT INBD FLAP, OTBD FLAP SHROUD SUPPORT, PITTED ON MATING SURFACE. REMOVED THE CORROSION ON RT INBD FLAP, OTBD FLAP SHROUD SUPPORT BY BLENDING. DAMAGE FOUND TO BE OUT OF LIMITS IAW SRM 51-10-05-PR, STEP 3. REPLACED THE SHROUD SUPPORT WITH NEW.Aug 6, 2026 · N664MS · Emb EMB145LR · Trailing Edge FlapsSDR REXA2026083101764Cleat · corrodedFOUND PAX DOOR DD4 FWD CLIP, FS 320.163 SIDE, TO BE CORRODED. REQUIRES REPLACEMENT. REMOVED UNSERVICEABLE PAX DOOR DD4 FWD CLIP IAW SRM 51-42-06-001-001-A01. NEW SERVICEABLE PAX DOOR DD4 CLIP P/N: 600-31902-269 HAS BEEN LOCATED AND DRILLED IAW SRM 51-40-11-001Aug 6, 2026 · Cndair CL6002D24 · Passenger/Crew DoorsSDR REXA2026083101763Frame · corrodedFOUND PAX DOOR FORMER FS 320.00 TO BE CORRODED. REMOVED UNSERVICEABLE PAX DOOR FORMER F.S. 320.00 IAW SRM 51-42-06-001-001-A01 AND 51-42-21-001-001-A01 INSTALLED NEW SERVICEABLE PAX DOOR FORMER F.S. 320.00 IAW SRM 51-42-06-001-001-A01 AND 51-42-21-001-001-A01 Aug 6, 2026 · N810SK · Cndair CL6002D24 · Fuselage Main, Structure