# Service difficulty reports: N526EA

A list on [N526EA](https://openairdocs.org/aircraft/N526EA.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Page 1 of 3 · 112 reports

- [SDR VNAA2026050417103](https://openairdocs.org/sdr/VNAA2026050417103.md): Hinge · misinstalled · Apr 29, 2026 · N526EA · Cndair CL6002C10 · Fuselage, Door Hinge
  > GEAR DISAGREE WARNING MSG. T/S & FOUND ALL 3 GEAR TO CYCLE PROPERLY WITH THE NLG AFT DOOR DISCONNECTED UPON FURTHER INVESTIGATION FOUND NLG AFT DOOR LT UPPER HINGE LUG (AIRFRAME SIDE) TO BE INSTALLED UPSIDE DOWN WHICH CAUSED THE HINGE BUSHINGS TO CRACK/BREAK
- [SDR VNAA202509260016](https://openairdocs.org/sdr/VNAA202509260016.md): Drag Angle · damaged · Sep 4, 2025 · N526EA · Cndair CL6002C10 · Vertical Stabilizer Miscellaneous Structure
  > ELONGATE HOLES ON VERTICAL STABILIZER UNDER RH FWD DRAG ANGLE BTW 55.62% STGR DATUM TO 61.56% STGR DATUM. RH FWD DRAG ANGLE BTW 55.62% STGR DATUM TO 61.56% STGR DATUM WAS REPAIRED PER REO 670-55-31-196 REV.-A
- [SDR VNAA202509250011](https://openairdocs.org/sdr/VNAA202509250011.md): Hinge · not reported · Sep 4, 2025 · N526EA · Cndair CL6002C10 · Fuselage, Door Hinge
  > PERM REPAIR - PASSENGER DOOR SURROUND STRUCTURE - HINGE REPLACEMENT REPLACE THE PASSENGER DOOR HINGE IN ACCORDANCE WITH CRJ700 SRM TASK 53-21-23-201-007- A01. PIANO HINGE OF PASSENGER DOOR WAS REPLACED PER CRJ700 SRM 53-21-23-201-007-A01
- [SDR VNAA202509260014](https://openairdocs.org/sdr/VNAA202509260014.md): Frame Angle · corroded · Aug 23, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Frame
  > AFTER ANGLE REINFORCING REMOVAL IN REF NRC 00238, CORROSION ON ANGLE REINFORCING OF FRAME FS879 WAS FOUND. CORROSION WAS REMOVED ON ANGLE REINFORCING OF FRAME FS879 PER CRJ-700 SRM 51-21-06-001-001-A01, EVALUATED OUT LIMTS PER CRJ-700 SRM 53-51-06-101-003-A01
- [SDR VNAA202509260018](https://openairdocs.org/sdr/VNAA202509260018.md): Crossbeam · corroded · Aug 15, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Structure
  > CORROSION WAS FOUND ON LH CROSSBEAM AT FS 280.00. LH CROSSBEAM AT FS280.00 WAS EVALUATED OUT OF LIMITS PER CRJ700 SRM 53-00-01-101-001-A01 AND WAS REPLACED PER CRJ700 SRM 51-42-06-001-001-A01, SRM 51-42-10-001-001-A01 AND SRM 51-42-21-001-001-A01.
- [SDR VNAA202509260013](https://openairdocs.org/sdr/VNAA202509260013.md): Frame · corroded · Aug 15, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Frame
  > AFTER DUCTS REMOVAL IN REF NRC 00236, CORROSION ON FRAME FS969 BTW STGR 26L TO 26R AT INTERNAL FUSELAGE. FRAME FS969 BTW STGR 26L TO 26R AT INTERNAL FUSELAGE. WAS REPLACED PER CRJ 700 SRM 51-42-06-001-001-A01. AND SRM 51-42-21-001-001-A01.
- [SDR VNAA202509260010](https://openairdocs.org/sdr/VNAA202509260010.md): Stringer · worn · Aug 15, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Longeron/Stringer
  > WEAR ON STGR 8 BTW FS1144 TO FS1162 AT AFT EQUIPMENT BAY. WEAR ON STGR 8 BTW FS1144 TO FS1162 AT AFT EQUIPMENT BAY WAS EVALUATED OUT OF LIMITS PER CRJ-700 SRM 53-61-03-101-004-A01 AND WAS REPAIRED PER CRJ-700 SRM 53-00-03-201-002-A01.
- [SDR VNAA202509260007](https://openairdocs.org/sdr/VNAA202509260007.md): Hinge Fitting · worn · Aug 15, 2025 · N526EA · Cndair CL6002C10 · Ailerons
  > NICKS ON LUGS OF AILERON HINGE 2 (INB/OUTB LUGS) AND HINGE 3 (INB LUG) AT LH WING REAR SPAR. DAMAGED LUGS OF AILERON HINGE 2 (INB/OUTB LUGS) AND HINGE 3 (INB LUG) AT LH WING REAR SPAR WERE REPAIRED PER REO 670-57-51-629 REV - -.
- [SDR VNAA202509260012](https://openairdocs.org/sdr/VNAA202509260012.md): Fitting · corroded · Aug 14, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Attach Fittings
  > AFTER REMOVAL OF CROSSBEAM, CORROSION WAS FOUND ON FLOOR FITTING BTW INTERCOSTAL RBL 15 - RBL 17 AND BTW FS 280 -295. DUE TO EXCESSIVE DAMAGE ON FLOOR FITTING BTW INTERCOSTAL RBL 15 - RBL 17 AND BTW FS 280 -295 WAS FOUND OUT OF LIMITS PER CRJ700 SRM 53-00-00-
- [SDR VNAA202509260011](https://openairdocs.org/sdr/VNAA202509260011.md): Hinge Fitting · damaged · Aug 14, 2025 · N526EA · Cndair CL6002C10 · Ailerons
  > STANDARD BUSHING FITS FREELY BORE LUG L5 CENTER HINGE AT LH AILERON ASSY. BORE LUG L5 CENTER HINGE AT LH AILERON ASSY WAS REPAIRED PER REO 670-57-61-237 REV. - -
- [SDR VNAA202509260008](https://openairdocs.org/sdr/VNAA202509260008.md): Hinge Fitting · corroded · Aug 14, 2025 · N526EA · Cndair CL6002C10 · Ailerons
  > CORROSION ON BORE LUGS: L1 AND L2 CENTER HINGE 2 AT LH AILERON ASSY. BORE LUGS: L1 AND L2 CENTER HINGE 2 AT LH AILERON ASSY WERE REPAIRED PER REO 670-57-61-237 REV. - -
- [SDR VNAA202509260006](https://openairdocs.org/sdr/VNAA202509260006.md): Bushing · worn · Aug 14, 2025 · N526EA · Cndair CL6002C10 · Ailerons
  > AFTER REMOVAL BUSHINGS, WEAR ON OUTBOARD FACE OF LUGS R5, R6 OF CENTER HINGE FITTING AT RH AILERON. WEAR ON OUTBOARD FACE OF LUGS R5, R6 OF CENTER HINGE FITTING AT RH AILERON. WERE REPAIRED PER REO. 670-57-61-237 REV - -
- [SDR VNAA202509260005](https://openairdocs.org/sdr/VNAA202509260005.md): Hinge Fitting · corroded · Aug 14, 2025 · N526EA · Cndair CL6002C10 · Ailerons
  > CORROSION ON BORE LUG # R1, R2, R4, R5, R6 OF CENTER HINGE FITTING AT RH AILERON. BORE LUG # R1, AND R4, WERE CLEANED PER CRJ700 SRM 51-26-00-001-001-A01, NO CORROSION WAS FOUND AND BORE LUG # R2, R5 AND R6 OF CENTER HINGE FITTING AT RH AILERON WERE REPAIRED
- [SDR VNAA202509260004](https://openairdocs.org/sdr/VNAA202509260004.md): Hinge Fitting · corroded · Aug 14, 2025 · N526EA · Cndair CL6002C10 · Fuselage, Door Hinge
  > CORROSION ON NLG DOOR INTERNAL HOLES OF HINGE FITTINGS (2EAS) LH/RH AT FUSELAGE STRUCTURE WAS FOUND. CORROSION ON NLG DOOR INTERNAL HOLES OF HINGE FITTINGS (2EAS) LH/RH AT FUSELAGE STRUCTURE WERE EVALUATED OUT OF LIMITS PER CRJ-900 SRM 51-10-06-001-001-A01 AN
- [SDR VNAA202509250018](https://openairdocs.org/sdr/VNAA202509250018.md): Skin · corroded · Aug 14, 2025 · N526EA · Cndair CL6002C10 · Passenger/Crew Doors
  > CORROSION ON SETTLEMENT AREA OF ACCESS 832FL, 832EL, 832DL, 832CL, 832BL, 832AL, 832AR, AT PASSENGER DOOR. SETTLEMENT AREA ON ACCESS PANELS 832EL, 832DL, 832CL, 832BL, 832AL, 832AR WERE BLEND OUT, MEASURED WITHIN LIMITS PER CRJ-700 SRM 52-11-01-101-001-A01, 5
- [SDR VNAA202509260003](https://openairdocs.org/sdr/VNAA202509260003.md): Hinge Fitting · gouged · Aug 13, 2025 · N526EA · Cndair CL6002C10 · Ailerons
  > AFTER AILERON REMOVAL IN REF CARD 57-60-203_R/H-JIC, GOUGES ON LUG R4 CENTER HINGE FITTING AT RH AILERON. GOUGES ON LUG R4 CENTER HINGE FITTING AT RH AILERON. WERE REPAIRED PER REO 670-57-61-451 REV. - -
- [SDR VNAA202509260002](https://openairdocs.org/sdr/VNAA202509260002.md): Brake · corroded · Aug 12, 2025 · N526EA · Cndair CL6002C10 · Landing Gear Brake System
  > DURING REMOVAL OF MLG RH SHOCK STRUCT IN REFERENCE TASK CARD:32-079-003-19-RH CORROSION WAS FOUN ON BRAKE TAKE OUT RINK MLG RH. PIN, BRAKE TORQUE TAKE-OUT MLG RH WAS VERIFIED (P/N:49231-3 S/N: ACR110787) PER CRJ 700 IPC 32-11-39 AND MUST BE INSTALLED WITH JOB
- [SDR VNAA202509260001](https://openairdocs.org/sdr/VNAA202509260001.md): Skin · mechanic error · Aug 12, 2025 · N526EA · Cndair CL6002C10 · Nacelle/Pylon, Plate/Skin
  > LH PYLON ACCESS PANEL 412HB MISDRILLED. GENERATE NEW RFTS REQUEST AND PROVIDE A DETAILS DAMAGE REPORT REQUESTING PERMANENT DISPOSITION. LT PYLON ACCESS PANEL 412HB MISDRILL WAS REPAIRED PER REO 670-54-51-084 REV.--
- [SDR VNAA202509260019](https://openairdocs.org/sdr/VNAA202509260019.md): Floorbeam · corroded · Aug 11, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Floor Beam
  > AFTER REMOVAL OF FLOOR PANEL SUPPORT ANGLE, CORROSION WAS FOUND ON RH CROSSBEAM AT FS 280.00. CORROSIÓN ON RH CROSSBEAM AT FS 280 ITS OUT OF LIMITS PER CRJ-700 SRM 53-00-01-101-001-A01 AND WAS REPLACED PER CRJ-700 SRM 51-42-06-001-001-A01 SRM 51-42-10-001-0
- [SDR VNAA202509260017](https://openairdocs.org/sdr/VNAA202509260017.md): Seat Track · corroded · Aug 11, 2025 · N526EA · Cndair CL6002C10 · Fuselage, Seat/Cargo Attach Fittings
  > CORROSION ON SEAT RAIL AT RBL9 (02) SEGMENTS: (01) FS679 - FS863. (02) FS863 - FS1005. OF THE PAX CABIN. SEAT RAILS (2EAS) AT RBL9 FS=679 TO FS=1005. OF THE PAX CABIN WERE EVALUATE OUT LIMITS PER CRJ 700 SRM 53-41-49-101-001-A01 AND CRJ 700 SRM 53-51-49-101-0
- [SDR VNAA202509260015](https://openairdocs.org/sdr/VNAA202509260015.md): Support Channel · damaged · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > ELONGATE HOLES ON LOWER CHANNEL FOUND AT RH RUDDER-PEDAL FRONT PIVOT SUPPORT STRUCTURE. LOWER CHANNEL AT RH RUDDER-PEDAL FRONT PIVOT SUPPORT STRUCTURE WAS REPAIRED PER REO 670-53-11-2175 REV.-
- [SDR VNAA202509250033](https://openairdocs.org/sdr/VNAA202509250033.md): Crossbeam · corroded · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CORROSION ON CROSS BEAM ON FS1051.30 BTW LBL28 TO LBL39 AT BAGGAGE BAY FLOOR STRUCTURE. CROSS BEAM ON FS1051.30 BTW LBL28 TO LBL39 AT BAGGAGE BAY FLOOR STRUCTURE WAS REPAIRED PER REO 670-53-61-2549 REV -
- [SDR VNAA202509250032](https://openairdocs.org/sdr/VNAA202509250032.md): Floor Support · corroded · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CORROSION ON FLOOR BEAM BTW FS985.00 TO FS1088.20 AND LBL27 AT AFT BAGGAGE BAY FLOOR STRUCTURE. DUE TO NO DAMAGE IS ALLOWED ON FLOOR BEAM BTW FS 1008 TO FS 1080 AND LBL 27 AT AFT BAGGAGE BAY FLOOR STRUCTURE WAS REPLACED PER SRM 53-61-43-101-001-A01 AND SRM 5
- [SDR VNAA202509250031](https://openairdocs.org/sdr/VNAA202509250031.md): Floor Support · corroded · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CORROSION ON FLOOR BEAM BTW FS985.00 TO FS1088.20 AND LBL9 AT AFT BAGGAGE BAY FLOOR STRUCTURE. DUE TO NO DAMAGE IS ALLOWED ON FLOOR BEAM BTW FS 985.00 TO FS 1088.20 AND LBL 9 AT AFT BAGGAGE BAY FLOOR STRUCTURE WAS REPLACED PER CRJ700 SRM 53-61-43-101-001-A01
- [SDR VNAA202509250030](https://openairdocs.org/sdr/VNAA202509250030.md): Frame · corroded · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Structure (General)
  > CORROSION ON FRAME BTW FS909 STGR 26R TO STGR 26L AT INTERNAL FUSELAGE. CORROSION ON FRAME BTW FS909 STGR 26R TO STGR 26L AT INTERNAL FUSELAGE WAS REMOVED PER CRJ-700 SRM 51-21-06-001-001-A01. AND AREA OUT LIMITS PER CRJ-700 SRM 53-00-00-101-001-A01 AND WAS
- [SDR VNAA202509250029](https://openairdocs.org/sdr/VNAA202509250029.md): Frame · corroded · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Frame
  > CORROSION ON FRAME BTW FS 879 STGR 26R TO STGR 26L AT INTERNAL FUSELAGE. CORROSION ON FRAME BTW FS 879 STGR 26R TO STGR 26L AT INTERNAL FUSELAGE WAS EVALUATE OUT OF LIMITS PER CRJ-700 SRM 53-51-06-101-003-A01 AND REPLACED PER CRJ-700 SRM 51-42-06-001-001-A01
- [SDR VNAA202509250028](https://openairdocs.org/sdr/VNAA202509250028.md): Static Wick · corroded · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Vertical Stabilizer
  > CORROSION AT STATIC DICHARGER BASE, ACCESS PANEL 343BR. STATIC DICHARGER BASE ON ACCESS PANEL 343BR WAS REPLACED PER CRJ700 AMM 55-00-28-960-801 (CONFIG A01) AND SRM 51-42-06-001-001-A01
- [SDR VNAA202509250027](https://openairdocs.org/sdr/VNAA202509250027.md): Frame · corroded · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Frame
  > CORROSION ON FRAME BTW FS 863 STGR 26R TO STGR 26L AT INTERNAL FUSELAGE. FRAME BTW FS 863 STGR 21R TO STGR 21L AT INTERNAL FUSELAGE WAS EVALUATED OUT LIMITS PER CRJ-700 SRM 53-00-00-101-001-A01 AND FRAME WAS REPLACED PER CRJ/700 SRM 51-42-21-001-001-A01 AND
- [SDR VNAA202509250026](https://openairdocs.org/sdr/VNAA202509250026.md): Floor Support · cracked · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CRACK ON FLOOR BEAM RBL 12.0 BTW FS 221.73 TO FS 229.00 AT FWD FUSELAGE INTERNAL STRUCTURE (FLIGHT COMPARTMENT FLOOR STRUCTURE BELOW WL79.50). CRACK ON FLOOR BEAM RBL 12.0 BTW FS 221.73 TO FS 229.00 AT FWD FUSELAGE INTERNAL STRUCTURE WAS REPAIRED PER 670-53-1
- [SDR VNAA202509250025](https://openairdocs.org/sdr/VNAA202509250025.md): Floor Support · corroded · Aug 7, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CORROSION ALONG EXTERNAL FACE OF FLOOR SILL BTW FS1000-FS1051.30 AT SURROUND STRUCTURE OF AFT BAGGAGE-BAY DOOR. DUE TO EXCESSIVE CORROSION MUST BE REPLACED PER CRJ 700 SRM 51-21-06-001-001-A01 AND SILL, LOWER BTW FS1000-FS1051.30 AT SURROUND STRUCTURE OF AFT
- [SDR VNAA202509250038](https://openairdocs.org/sdr/VNAA202509250038.md): Support Angle · cracked · Aug 6, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CRACK ON SUPPORT ANGLES OF PANEL 542AZ/642AZ AT LH/RH MLG SHOCK STRUT BAY. SUPPORT ANGLES OF PANEL 542AZ/642AZ AT LH/RH MLG SHOCK STRUT BAY WERE REPLACED PER CRJ-700 SRM 51-42-21-001-001-A01.
- [SDR VNAA202509250034](https://openairdocs.org/sdr/VNAA202509250034.md): Seat Track · corroded · Aug 6, 2025 · N526EA · Cndair CL6002C10 · Fuselage, Seat/Cargo Attach Fittings
  > CORROSION AT SEAT RAIL LBL 9 (02) SEGMENTS: (01) FS679 - FS863. (02) FS863 - FS1005. AT PAX CABIN. CORROSION AT SEAT RAIL LBL 9 (02) SEGMENTS: (01) FS679 - FS863. (02) FS863 - FS1005. AT PAX CABIN WAS EVALUATED OUT OF LIMITS PER PER CRJ-700 SRM 53-41-49-101-0
- [SDR VNAA202509250024](https://openairdocs.org/sdr/VNAA202509250024.md): Hinge Fitting · excess play · Aug 6, 2025 · N526EA · Cndair CL6002C10 · Vertical Stabilizer
  > DURING INSPECTION OF TASK CARD:55-30-203-JIC GVI OF THE VERTICAL STABILIZER INTERNAL AREA AROUND RUDDER POWER CONTROL UNIT WAS FOUND FREEPLAY ON BEARING OF LOWER HINGE FITTING AT REAR SPAR OF VERTICAL STABILIZER. HINGE FITTING #3 (P/N: AV670-21081-013) WAS
- [SDR VNAA202509250022](https://openairdocs.org/sdr/VNAA202509250022.md): Seat Track · corroded · Aug 6, 2025 · N526EA · Cndair CL6002C10 · Fuselage, Seat/Cargo Attach Fittings
  > CORROSION AT SEAT RAIL LBL 9 (03) SEGMENTS: (01) FS375 - FS485. (02) FS485 - FS581. (03) FS581 - FS677. AT PAX CABIN. SEAT RAILS LBL 9 (03) SEGMENTS: (01) FS375 - FS485. (02) FS485 - FS581. (03) FS581 - FS677. AT PAX CABIN. WERE EVALUATES OUT LIMITS PER CRJ 7
- [SDR VNAA202509250021](https://openairdocs.org/sdr/VNAA202509250021.md): Seat Track · corroded · Aug 6, 2025 · N526EA · Cndair CL6002C10 · Fuselage, Seat/Cargo Attach Fittings
  > CORROSION ON RH SIDE SEAT RAIL (STRG 15R) (05) SEGMENTS: (01) FS573 - FS661. (02) FS679 - FS704. (03) FS704 - FS763. (04) FS783 - FS861. (05) FS861 - FS969. AT PAX CABIN. RH SIDE SEAT RAIL STRG 15R (FS573 - FS661) WAS CLEANED PER CRJ-700 SRM 51-26-00-001-001-
- [SDR VNAA202509250020](https://openairdocs.org/sdr/VNAA202509250020.md): Seat Track · corroded · Aug 6, 2025 · N526EA · Cndair CL6002C10 · Fuselage, Seat/Cargo Attach Fittings
  > CORROSION ON LH SIDE SEAT RAIL (STRG 15L) 04 SEGMENTS: (01) FS573 - FS679. (02) FS679 - FS704. (03) FS704 - FS763. (04) FS783 - FS861. AT PAX CABIN. CORROSION ON LH SIDE SEAT RAIL (STRG 15L) 04 SEGMENTS: (01) FS573 - FS679. (02) FS679 - FS704. (03) FS704 - FS
- [SDR VNAA202509250010](https://openairdocs.org/sdr/VNAA202509250010.md): Access Panel · damaged · Aug 6, 2025 · N526EA · Cndair CL6002C10 · Nacelle/Pylon, Plate/Skin
  > PYLON ACCESS PANEL 412HB DAMAGED FASTENER LOCATION WITHIN 1193.53 FLIGHT HOURS AFTER COMPLETION OF SECTION I, ACCOMPLISH A PERMANENT REPAIR AT DISCREPANT LOCATION IN ACCORDANCE WITH APPROVED PROCEDURES OR REPLACE PART// ENGINEERING COMMENTS. PYLON ACCESS PANE
- [SDR VNAA202509250039](https://openairdocs.org/sdr/VNAA202509250039.md): Intercostal · corroded · Aug 5, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CRACK ON INTERCOSTALS OF TIRE BURST SUPPORT STRUCTURE (SUPPORT FOR 542AZ/642AZ) AT LH/RH MLG SHOCK STRUT BAY. INTERCOSTALS OF TIRE BURST SUPPORT STRUCTURE (SUPPORT FOR 542AZ/642AZ) AT LH/RH MLG SHOCK STRUT BAY WERE REPLACED PER CRJ-700 SRM 51-42-06-001-001-A
- [SDR VNAA202509250037](https://openairdocs.org/sdr/VNAA202509250037.md): Angle · corroded · Aug 5, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CORROSION ON ANGLE MID CAP BTW FS310.00 TO FS349.00 AT PASSENGER SURROUND STRUCTURE. ANGLE MID CAP BTW FS310.00 TO FS349.00 AT PASSENGER SURROUND STRUCTURE WAS EVALUATED OUT OF LIMTS PER CRJ-700 SRM 53-00-00-101-001-A01 AND IT WAS REPLACED PER CRJ-700 SRM 51-
- [SDR VNAA202509250036](https://openairdocs.org/sdr/VNAA202509250036.md): Fitting · corroded · Aug 5, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Attach Fittings
  > CORROSION ON SUPPORT OF ACTUATOR ROD ASSEMBLY BTW FS310.00 TO FS319.70 AND STGR18LH AT LOWER SURROUND STRUCTURE OF PASSENGER DOOR. SUPPORT OF ACTUATOR ROD ASSEMBLY BTW FS310.00 TO FS319.70 AND STGR18LH (FITTING) AT LOWER SURROUND STRUCTURE OF PASSENGER DOOR W
- [SDR VNAA202509250014](https://openairdocs.org/sdr/VNAA202509250014.md): Stringer · corroded · Aug 5, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Longeron/Stringer
  > CORROSION ON STGR 26RH BTW FS 349-364 AT MAIN AVIONICS BAY. CORROSION ON STGR 26RH BTW FS 349-364 AT MAIN AVIONICS BAY DUE TO EXCESS DAMAGE WAS EVALUATED OUT OF LIMITS PER CRJ-700 SRM 53-21-03-101-006-A01 AND REPLACED PER CRJ 700 SRM 51-42-21-001-001-A01 AND
- [SDR VNAA202509250013](https://openairdocs.org/sdr/VNAA202509250013.md): Frame · corroded · Aug 5, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Frame
  > CORROSION ON FRAME FS 319.70 BTW STGR 20LH TO 21LH AT MAIN AVIONICS BAY. CORROSION ON FRAME FS 319.70 BTW STGR 20LH TO 21LH AT MAIN AVIONICS BAY. WAS REMOVED PER CRJ-700 SRM 51-21-06-001-001-A01 AND EVALUATE WITHIN LIMITS PER CRJ-700 SRM 53-21-06-101-002-A01
- [SDR VNAA202509250012](https://openairdocs.org/sdr/VNAA202509250012.md): Floorbeam · corroded · Aug 5, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Floor Beam
  > CORROSION ON POST LOWER CORNER OF FS 280 STGR 25LH OF AT MAIN AVIONICS BAY. POST BTW FS 280/ STGR 25LH WAS REPLACED PER CRJ-700 SRM 51-42-06-001-001-A01 STEP 6.C, SRM 51-42-10-001-001-A01 STEP 8.C AND SRM 51-42-21-001-001-A01 STEP 6.C
- [SDR VNAA202509250008](https://openairdocs.org/sdr/VNAA202509250008.md): Skin · scratched · Aug 5, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Plate/Skin
  > 3250FH PERM REPAIR - SCRATCH DAMAGE ON FUSELAGE SKIN BETWEEN FS1031.00-FS1051.30 THE SUBJECT CONDITION IS STRUCTURALLY ACCEPTABLE FOR 3250 FLIGHT HOURS FROM TIME OF INCORPORATION OF THIS REO AT REV -. ENGINEERING COMMENTS: COMPLY WITH STEP 5 OF REO 670-53-61-2
- [SDR VNAA202509250035](https://openairdocs.org/sdr/VNAA202509250035.md): Floorbeam · corroded · Aug 4, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Floor Beam
  > CORROSION AND WRONG INSTALLED FASTENERS (4EAS) ON FLOOR PANEL SUPPORT ANGLE AT FS280. FLOOR PANEL SUPPORT ANGLE AT FS280.00 WAS REPLACED PER CRJ-700 SRM 51-42-06-001-001-A01. AND SRM 51-42-21-001-001-A01.
- [SDR VNAA202509250007](https://openairdocs.org/sdr/VNAA202509250007.md): Floor Support · corroded · Aug 4, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > CORROSION ON FLOOR SUPPORTS (2EAS), PLATE (1EA), BRACKET MACHINED (2EAS) BTW FS 533 TO FS 581 STGR 26LH TO STGR 21LH AT FWD CARGO COMPARTMENT. CORROSION ON FLOOR SUPPORTS (2EAS), PLATE (1EA), MACHINED BRACKET (2EAS) BTW FS 533 TO FS 581 STGR 26LH TO STGR 21LH
- [SDR VNAA202509250006](https://openairdocs.org/sdr/VNAA202509250006.md): Web · gouged · Aug 4, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > GOUGES ON WEB FROM THE FWD EDGE AND LOWER EDGE AT DOOR SURROUND STRUCTURE AT FWD BAGGAGE BAY. GOUGES ON WEB FROM THE FWD EDGE AND LOWER EDGE AT DOOR SURROUND STRUCTURE AT FWD BAGGAGE BAY WERE BLENDED OUT PER CRJ-700 SRM 51-12-00-001-001-A01 AND EVALUATED WITH
- [SDR VNAA202509250005](https://openairdocs.org/sdr/VNAA202509250005.md): Web · mechanic error · Aug 4, 2025 · N526EA · Cndair CL6002C10 · Fuselage Miscellaneous Structure
  > MISDRILL ON LOWER SURROUND STRUCTURE OF FWD COMPARTENT DOOR. REPAIRED PER REO 670-53-31-1078 REV --
- [SDR VNAA202509250004](https://openairdocs.org/sdr/VNAA202509250004.md): Skin · worn · Aug 4, 2025 · N526EA · Cndair CL6002C10 · Fuselage Main, Plate/Skin
  > WEAR ON LOWER SKIN OF AFT FUSELAGE ON FS970.00 TO FS 977.00 AND STG 27. LOWER SKIN OF AFT FUSELAGE ON FS970.00 TO FS 977.00 AND STG 27 WAS REPAIRED PER REO 670-53-00-789 REV.--
- [SDR VNAA202509250017](https://openairdocs.org/sdr/VNAA202509250017.md): Drag Angle · cracked · Aug 3, 2025 · N526EA · Cndair CL6002C10 · Vertical Stabilizer Miscellaneous Structure
  > CRACK ON FWD AND AFT RH DRAG ANGLE BTW UNION OF VERTICAL STABILIZER AND FUSELAGE (67.5% REAR SPAR DATUM). FWD AND AFT DRAG ANGLE WERE REPAIRED PER CRJ700 SRM 55-31-00-201-001-A01

Next page: https://openairdocs.org/aircraft/N526EA/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
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 = 'N526EA' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N526EA/reports

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