N613CZ

Part: SKIN — DENTED (LT NOSE) · airframe 35,474 hrs · 22,265 cycles

TRANSFER FROM EAML 990088 : RAMP CREW INFORMED MAINTENANCE ,THEY FOUND A DENT ON FUSELAGE NOSE SECTION LEFT SIDE ABOUT 1 INCH, SHOWN TO MAINTENANCE TEAM. DENT HAS BEEN DETERMINED TO BE A MAJOR REPAIR PER GMM 3-26 . FORM M-337 WILL BE REQUIRED. (FILED CLOSED) COMPLIED WITH PERMANENT REPAIR TO FWD FUSELAGE SKIN BETWEEN FR08-FR09 AND STGR22L-STGR 23L REF ERJ175 SRM 53-10-01/REPAIR 12P. COMPLIED WITH RII TASK CARD 51-00-00-002-SKY-U STRUCTURAL MAJOR REPAIR. SEE CAMP 25477546 FOR PRESSURIZATION CHECK. / * INSPECTION THRESHOLD & INSPECTION INTERVAL: 20,667 FC OR 27,487 FH, WHICHEVER OCCURS FIRST FROM TAT: 35474.20 AND TAC: 22265

Part: INTERCOSTAL — CORRODED (FRMS 84-85) · airframe 32,772 hrs · 20,425 cycles

L/H O/B INTERCOSTAL AT FR 84 - FR 85 HAS CORROSION AS MARKED. (C-CHECK RO 8/23/21) / REMOVED AND REPLACED LH OB INTERCOSTAL FR 84-85 REF EMB SRM 51-40-08. RESTORED SURFACE PROTECTION AT LH OB INTERCOSTAL FR 84-85 REF EMB SRM 51-23-04, 51-23-05, 51-23-06

Part: SEAT TRACK — CORRODED (FRM 23) · airframe 32,772 hrs · 20,425 cycles

CORROSION IN L/H O/B SEAT TRACK AT FR.23. (C-CHECK RO 8-23-21) REMOVED AND REPLACED LH O/B SEAT TRACK AT FRAME 23. REF SRM 51-40-08 FACTORY REPLACEMENT SEAT TRACK NO CHANGE IN WEIGHT AND BALANCE

Part: SEAT TRACK — CORRODED (FRMS 23-30) · airframe 32,772 hrs · 20,425 cycles

:LH FIRST CLASS SEAT TRACK HAS CORROSION IN SEVERAL SPOTS AS MARKED FR 23-30 (C-CHECK RO 8-23-21) / PERFORMED SEAT TRACK SPLICE REPAIR ON LH FIRST CLASS SEAT TRACK CORROSION IN SEVERAL SPOTS FROM FR 23-30 REPLACED FWD SECTION FROM FR 23 TO FR 30 REF ETD 2021-170-024807. RESTORED SURFACE PROTECTION REF SRM 51-23-06. WEIGHT OF REPAIR PARTS ARE 6.210 OUNCES

Part: SEAT TRACK — CORRODED (FRMS 23-34) · airframe 32,772 hrs · 20,425 cycles

RH FLOOR BEAM SEAT TRACK HAS MULTIPLE SPOTS OF CORROSION AS MARKED FR 23-34 (C-CHECK RO 8/23/21) / REMOVED AND REPLACED RH FLOOR BEAM SEAT TRACK FR 23-34 REF SRM 51-40-08. RESTORED SURFACE PROTECTION REF SRM 51-23-06 PART REPLACEED WITH FACTORE REPLACEMENT PART NO CHANGE TO THE WEIGHT AND BALLANCE.

Part: SEAT TRACK — CHAFED (FRMS 23-33) · airframe 32,772 hrs · 20,425 cycles

CHAFFING ON LH OTBD SEAT TRACK IN 5 SPOTS FR 23-33 AS MARKED. (C-CHECK RO 8-23-21) / REMOVED AND REPLACED LH OB SEAT TRACK FR 23-33 REF EMB SRM 51-40-08 FACTORY REPLACEMENT PART NO CHANGE TO THE WEIGHT AND BALANCE

Part: SEAT TRACK — CHAFED (FRMS 23-34) · airframe 32,772 hrs · 20,425 cycles

CHAFFING ON RH OTBD SEAT TRACK IN 9 SPOTS FR 23-34 AS MARKED. (C-CHECK RO 8-23-21) / REMOVED AND REPLACED RH OTBD SEAT TRACK FR 23-34 WITH FACTORY PART NO CHANGE TO WEIGHT AND BALANCE REF EMB SRM 51-40-08. SEE CONTINUATION CARD FOR WORK PERFORMED.

Part: SEAT TRACK — CHAFED (FRSM 30-34) · airframe 32,772 hrs · 20,425 cycles

LH FLOOR BEAM SEAT TRACK HAS 5 SPOTS OF CORROSION AS MARKED FR 30 - 34. (C-CHECK RO 8-23-21) / REMOVED AND REPLACED LH FLOOR BEAM SEAT TRACK 21-34 IN REF.TO EMB 175 SRM 51-40-08 SEE CONTIUATION CARD FOR WORK PERFORMED.

Part: SKIN — CRACKED (LT WING) · airframe 32,772 hrs · 20,425 cycles

LH WING FIXED LEADING EDGE SKIN EDGE HAS SUSPECTED CRACK AS MARKED AT THE SLAT 2 OTBD TRACK CUTOUT. (C-CHECK RO 8-23-21) CUT OUT LH WING FIXED LEADING EDGE SKIN EDGE CRACK AS MARKED AT THE SLAT 2 OTBD TRACK CUTOUT.REF SRM 57-49-01/REPAIR 06P. RESTORED SURFACE PROTECTION REF SRM 51-23-04, 51-23-05, 51-23-06

Part: WARNING MESSAGE — ACTIVATED (BRAKE SYSTEM) · airframe 32,046 hrs · 19,784 cycles

BRK LH FAULT AND BRK RH FAULT MSGS ON APPROACH AFTER GEAR EXTENSION, FOLLOWED QRH 13.12. MSGS REMAINED ACTIVE AT GATE.

Part: FAULT LIGHT — ILLUMINATED (BRAKES) · airframe 32,025 hrs · 19,768 cycles

BRAKE LH FAULT AND BRAKE RH FAULT

Part: CROSSBEAM — DAMAGED (FRAME 11) · airframe 31,713 hrs · 19,483 cycles

DURING BASIC CHECK AT EAMS, CORROSION DAMAGE WAS FOUND TO THE FORWARD FUSELAGE FR11 COCKPIT CROSSBEAM. REFERENCE ETD2019-170-122405-A, FIGURE 1 FOR DETAILS. EAMS REQUESTED AND RECEIVED PERMANENT REPAIRS FOR THE DAMAGE IN THE FORM OF ETD2019-170-122405-A WHICH PROVIDES INSTRUCTIONS TO ACCOMPLISH BLEND OUT REPAIR, INSTRUCTIONS TO ACCOMPLISH A DETAILED VISUAL INSPECTION OF THE CORROSION DAMAGE TO VERIFY NO SHARP EDGES, CREASES, CRACKS, OR DISCREPANT FASTENERS ARE PRESENT IN THE BLENDED AREA AND AN NDT HFEC INSPECTION TO VERIFY NO CRACKS EXIST. IF THE BLENDED AREA IS FREE OF DAMAGE, THEN THE BLEND-OUT IS CONSIDERED PERMANENT ALLOWABLE DAMAGE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 31,619 hrs · 19,471 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE ON CONDITION REPLACEMENT OF A DAMAGED OR PREVIOUSLY REPAIRED LT FLOOR BEAM P/N 170-65669-003 (Y = -273) BETWEEN FRAMES 86 AND 89. THE DAMAGED STRUCTURE WILL BE REPLACED BY USING PRODUCTION DRAWINGS. BECAUSE THE TRACK IS A PSE, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. REV 1: ADDS AIRCRAFT S/N 17000218 THRU 17000224 TO THE EFFECTIVITY. REV 2: ADDS AIRCRAFT S/N 17000225 THRU 17000234 TO THE EFFECTIVITY. REV 3: ADDS AIRCRAFT S/N 17000235 THRU 17000264 TO THE EFFECTIVITY. REV 4: ADDS STEP #23 FOR SUBMITTAL OF SDR.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE ON-CONDITION REPAIR OF CORROSION OR OTHER DAMAGE TO THE CENTER FUSELAGE III RT INBOARD SEAT TRACK P/N 170-86082-005 (-003). THE PERMANENT REPAIR WILL BE ACCOMPLISHED BY DIRECT REPLACEMENT OF THE AFFECTED PART IN ACCORDANCE WITH PRODUCTION DRAWINGS LISTED IN TABLE 1, WHICH ARE APPROVED AS PART OF THE TYPE DESIGN, AS WELL AS SRM CHAPTER 51 STANDARD PRACTICES. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED A MAJOR REPAIR BECAUSE THE SEAT TRACK IS PSE AND THE EO IS RESTORING STRENGTH. SINCE THE DAMAGED STRUCTURE IS BEING REPLACED WITH A NEW PART PER THE PRODUCTION DRAWINGS, THE AIRCRAFT STRUCTURE REMAINS IN ITS ORIGINAL CONFIGURATION. THEREFORE, SUPPLEMENTAL FOLLOW UP INSPECTIONS ARE NOT REQUIRED

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE ON-CONDITION REPAIR OF CORROSION OR OTHER DAMAGE TO THE CENTER FUSELAGE III LT LATERAL SEAT TRACK P/N 170-65917-005 (-003). THE PERMANENT REPAIR WILL BE ACCOMPLISHED BY DIRECT REPLACEMENT OF THE AFFECTED PART IN ACCORDANCE WITH PRODUCTION DRAWINGS LISTED IN TABLE 1, WHICH ARE APPROVED AS PART OF THE TYPE DESIGN, AS WELL AS SRM CHAPTER 51 STANDARD PRACTICES. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED A MAJOR REPAIR BECAUSE THE SEAT TRACK IS PSE AND THE EO IS RESTORING STRENGTH. SINCE THE DAMAGED STRUCTURE IS BEING REPLACED WITH A NEW PART PER THE PRODUCTION DRAWINGS, THE AIRCRAFT STRUCTURE REMAINS IN ITS ORIGINAL CONFIGURATION. THEREFORE, SUPPLEMENTAL FOLLOW UP INSPECTIONS ARE NOT REQUIRED.

Part: FLOOR SUPPORT — CRACKED (FRAME 66) · airframe 31,713 hrs · 19,483 cycles

AFT WET AREA FLOOR PANEL SUPPORT HAS CRACK AT FR 86

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

CORROSION HAS BEEN FOUND ON THE CABIN RT SEAT TRACK P/N 170-02056-008 DURING BASIC CHECK. SINCE MANUFACTURER CLASSIFIES THIS SEAT TRACK AS PSE, HAS CLASSIFIED REPLACEMENT OF THIS TRACK AS A MAJOR REPAIR. IN LIEU OF CONTINUING TO WRITE INDIVIDUAL EO’S FOR EACH AIRCRAFT. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS FOR THE ON CONDITION REPAIR OF CORRODED OR DAMAGED CABIN SEAT TRACK P/N 170-02056-008 BY PART REPLACEMENT. THE REPLACEMENT IS ACCOMPLISHED USING THE PRODUCTION DRAWINGS AND SRM CHAPTER 51 STANDARD PRACTICES. SINCE THE DAMAGED STRUCTURE IS BEING REPLACED WITH NEW PARTS PER THE PRODUCTION DRAWINGS, THE AIRCRAFT STRUCTURE REMAINS IN ITS ORIGINAL CONFIGURATION. THEREFORE, NO CHANGES TO THE EXISTING INSPECTION PROGRAM ARE REQUIRED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE ON-CONDITION REPAIR OF CORROSION OR OTHER DAMAGE TO THE CENTER FUSELAGE III RT LATERAL SEAT TRACK P/N 170-65917-006 (-004). THE PERMANENT REPAIR WILL BE ACCOMPLISHED BY DIRECT REPLACEMENT OF THE AFFECTED PART IN ACCORDANCE WITH PRODUCTION DRAWINGS LISTED IN TABLE 1, WHICH ARE APPROVED AS PART OF THE TYPE DESIGN, AS WELL AS SRM CHAPTER 51 STANDARD PRACTICES. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED A MAJOR REPAIR BECAUSE THE SEAT TRACK IS PSE AND THE EO IS RESTORING STRENGTH. SINCE THE DAMAGED STRUCTURE IS BEING REPLACED WITH A NEW PART PER THE PRODUCTION DRAWINGS, THE AIRCRAFT STRUCTURE REMAINS IN ITS ORIGINAL CONFIGURATION. THEREFORE, SUPPLEMENTAL FOLLOW UP INSPECTIONS ARE NOT REQUIRED.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE ON-CONDITION REPAIR OF CORROSION OR OTHER DAMAGE TO THE CENTER FUSELAGE III LT LATERAL SEAT TRACK P/N 170-65917-005 (-003). THE PERMANENT REPAIR WILL BE ACCOMPLISHED BY DIRECT REPLACEMENT OF THE AFFECTED PART IN ACCORDANCE WITH PRODUCTION DRAWINGS LISTED IN TABLE 1, WHICH ARE APPROVED AS PART OF THE TYPE DESIGN, AS WELL AS SRM CHAPTER 51 STANDARD PRACTICES. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED A MAJOR REPAIR BECAUSE THE SEAT TRACK IS PSE AND THE EO IS RESTORING STRENGTH. SINCE THE DAMAGED STRUCTURE IS BEING REPLACED WITH A NEW PART PER THE PRODUCTION DRAWINGS, THE AIRCRAFT STRUCTURE REMAINS IN ITS ORIGINAL CONFIGURATION. THEREFORE, SUPPLEMENTAL FOLLOW UP INSPECTIONS ARE NOT REQUIRED.

Part: GUSSET — CORRODED (FRAME 11) · airframe 31,713 hrs · 19,483 cycles

CORROSION AR FR 11 COCKPIT FLORR CROSSBEAM CENTER GUSSET

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

CORROSION HAS BEEN FOUND ON THE LT CABIN SEAT TRACK P/N 170-02056-007 DURING BASIC CHECK. SINCE MANUFACTURER CLASSIFIES THIS SEAT TRACK AS PSE, HAS CLASSIFIED REPLACEMENT OF THIS TRACK AS A MAJOR REPAIR. IN LIEU OF CONTINUING TO WRITE INDIVIDUAL EO’S FOR EACH AIRCRAFT. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS FOR THE ON CONDITION REPAIR OF CORRODED OR DAMAGED CABIN SEAT TRACK P/N 170-02056-007 BY PART REPLACEMENT. THE REPLACEMENT IS ACCOMPLISHED USING THE PRODUCTION DRAWINGS AND SRM CHAPTER 51 PRACTICES. SINCE THE DAMAGED STRUCTURE IS BEING REPLACED WITH NEW PARTS PER THE PRODUCTION DRAWINGS, THE AIRCRAFT STRUCTURE REMAINS IN ITS ORIGINAL CONFIGURATION. THEREFORE, NO CHANGES TO THE EXISTING INSPECTION PROGRAM ARE REQUIRED.

Part: BEAM — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

DURING THE CURRENT B6 BASIC CHECK, CORROSION DAMAGE WAS DISCOVERED ON THE AFT PASSENGER (L2) DOOR LOWER THRESHOLD BEAM (P/N 170-65703-005) AT FASTENER HOLES AROUND THE AFT GIRT BAR FITTING DURING ACCOMPLISHMENT OF EO E175-5300-221.2 FOR A MODIFICATION OF THE CORROSION PROTECTION OF THE BEAM. REFERENCE FIGURE 1 FOR DETAILS OF THE DAMAGE. THE DAMAGE EXCEEDED THE ALLOWABLE LIMITS FROM SRM PART II 53-23-11/AD03, NECESSITATING THE REPLACEMENT OF THE LOWER THRESHOLD BEAM. THIS EO IS BEING ISSUED TO ACCOMPLISH THE PERMANENT REPAIR OF THE L2 DOOR THRESHOLD LOWER BEAM BY REMOVING AND REPLACING THE DAMAGED L2 DOOR THRESHOLD LOWER BEAM WITH A NEW PART. PART REPLACEMENT WILL BE ACCOMPLISHED IN ACCORDANCE WITH DRAWINGS LISTED IN THE REFERENCES AND SRM CHAPTER 51 STANDARD PRACTICES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE PART. BECAUSE THE L2 DOOR THRESHOLD LOWER BEAM (P/N 170-65703-005) IS A PSE AND REPLACEMENT IS COMPLEX, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY ENGINEERING AS A MAJOR REPAIR. EO E175-53MR-444 IS BEING ACCOMPLISHED BY WO 2719869.

Part: SKIN PANEL — DENTED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

BEFORE A FLIGHT OUT OF BIS, A DENT WAS DISCOVERED ON THE FWD FUSELAGE SKIN OF AIRCRAFT, P/N 170-03387-003, BETWEEN S-17L-18L AND CROSSING OVER FR11. ENGINEERING ORIGINALLY RECEIVED RELIEF IN THE FORM OF ETD2017-170-039578, WHICH PROVIDED A 250FC FLYBY PROVIDED THE FOLLOWING WAS ACCOMPLISHED: A DET INSPECTION OF THE DENT TO VERIFY NO SHARP EDGES, CREASES, OIL CANNING OR DISCREPANT FASTENERS WERE PRESENT, A NDT INSPECTION OF THE DAMAGED AREA WAS ACCOMPLISHED WITHIN 25FC, A DET INSPECTION WAS ACCOMPLISHED EVERY 50FC AND THE PERMANENT REPAIR BY REWORK OF THE DENT WAS ACCOMPLISHED WITHIN 250FC. DURING COLD WORKING OF THE DENT PER EA E175-53-901.3, THE SKIN OIL CANNED. EO E175-53MR-352 REV IR WAS ISSUED TO ACCOMPLISH THE REPAIR AT THAT TIME. AT A LATER BASIC CHECK, THE REPAIR INSTALLED BY EO E175-53MR-352 WAS REMOVED. THIS EO IS BEING ISSUED TO INSTALL A REPAIR IN ACCORDANCE WITH SRM PART II 53-10-01/REPAIR 15P. WHILE WORKING THE DOUBLER REPAIR, A FASTENER HOLE WAS DAMAGED, FOR WHICH REQUESTED AND RECEIVED REPAIR DATA IN THE FORM OF ETD2019-170-123489A TO INSTALL FREEZE PLUGS. BECAUSE THE FORWARD FUSELAGE LT LATERAL SKIN PANEL IS A PSE AND THE EO IS RESTORING STRENGTH, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. EO E175-53MR-352.2 IS BEING ACCOMPLISHED BY WO 2721156.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

DURING THE B6 BASIC CHECK, CORROSION DAMAGE WAS DISCOVERED IN THE FORWARD FUSELAGE AT THE RT COCKPIT FLOOR DOUBLER (P/N 170-03238-005) DURING INSPECTION IN THE AREA. THE DAMAGE EXCEEDED THE LIMITS PROVIDED IN THE SRM BECAUSE OF ITS DEPTH. EAMS REQUESTED AND RECEIVED APPROVED REPAIR DISPOSITION FROM RTS IN THE FORM OF ETD2019-170-122379A AND ITS CORRESPONDING ANAC DER FORM. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A PERMANENT REPAIR OF CORROSION TO THE RT COCKPIT FLOOR DOUBLER BY SPLICING IN A NEW SECTION OF THE FLOOR DOUBLER PER ETD2019-170-122379A. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR BECAUSE THE RT COCKPIT FLOOR DOUBLER IS A PSE AND THIS EO IS RESTORING STRENGTH. EO E175-53MR-446 IS BEING ACCOMPLISHED BY WO 2719871.

Part: SKIN PANEL — CRACKED (RT WING) · airframe 31,713 hrs · 19,483 cycles

DURING THE B6 BASIC CHECK AT EAMS, THE RT WING LOWER REAR ROOT SKIN, P/N 170-01423-010, WAS DISCOVERED CRACKED DURING INSPECTION AT THE SPAR II AND RIB 4A JUNCTION. THE CRACK WAS VERIFIED AT APPROXIMATELY 0.492 INCHES LONG THROUGH NDT. REFERENCE ETD2019-170-119402 FIGURES 1-3 FOR DETAILS. THE CRACK IS LOCATED APPROXIMATELY 0.5 INCHES OUTBOARD OF THE RIB 4A LOWER SKIN DOUBLER, P/N 170-26653-004. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A TEMPORARY REPAIR OF THE CRACKED RT WING LOWER REAR ROOT SKIN, P/N 170-01423-010, AT THE SPAR II AND RIB 4A JUNCTION, BY CUTOUT AND INSTALLATION OF A SINGLE EXTERNAL REPAIR DOUBLER WITH A FILLER PER ETD2019-170-119402. THE REPAIR DOUBLER, P/N 171-22053-001, IS BASICALLY AN EXTENSION OF THE ORIGINAL DOUBLER P/N 170-26653-004. BECAUSE THE RT WING LOWER REAR ROOT SKIN IS A PSE AND FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY ENGINEERING AS A MAJOR REPAIR DUE TO STRENGTH RESTORATION. EO E175-57MR-015 IS BEING ACCOMPLISHED BY WO 2721589.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

DURING BASIC CHECK, CORROSION DAMAGE WAS DISCOVERED DURING INSPECTION ON THE CENTER FUSELAGE III WASTE BOX SKIN DOUBLER, P/N 170-66931-001, ALONG THE INNER EDGES OF THE DOUBLER (REFERENCE PHOTO 1 FOR DETAILS). THE CORROSION DAMAGE WAS BLENDED WITH THE DEEPEST POST-BLENDOUT AREA MEASURING APPROXIMATELY 2.561 INCHES X 0.842 INCHES TO A MAXIMUM DEPTH OF 0.029 INCHES. THREE BLENDED AREAS EXCEED THE ALLOWABLE DAMAGE LIMITS PROVIDED IN SRM PART II 53-23-60/AD01. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF THE CORRODED CENTER FUSELAGE III WASTE BOX SKIN DOUBLER, P/N 170-66931-001, BY REMOVING AND REPLACING THE CORRODED PART. PART REPLACEMENT WILL BE ACCOMPLISHED IN ACCORDANCE WITH THE DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 STANDARD PRACTICES. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT REQUIRED FOR DIRECT REPLACEMENT OF THE CENTER FUSELAGE III WASTE BOX SKIN DOUBLER. BECAUSE THE CENTER FUSELAGE III WASTE BOX SKIN DOUBLER IS A PSE, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY ENGINEERING AS A MAJOR REPAIR DUE TO THE COMPLEXITY OF ITS REPLACEMENT. EO E175-53MR-447 IS BEING ACCOMPLISHED BY WO 2719873.

Part: BEAM — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

DURING THE CURRENT B6 BASIC CHECK, CORROSION DAMAGE WAS DISCOVERED ON THE AFT SERVICE (R2) DOOR LOWER THRESHOLD BEAM (P/N 170-65639-005) AT FASTENER HOLES AROUND THE AFT GIRT BAR FITTING DURING ACCOMPLISHMENT OF EO E175-5300-221.4 FOR A MODIFICATION OF THE CORROSION PROTECTION OF THE BEAM. REFERENCE FIGURE 1 FOR DETAILS OF THE DAMAGE. THE DAMAGE EXCEEDED THE ALLOWABLE LIMITS FROM SRM PART II 53-23-11/AD03, NECESSITATING THE REPLACEMENT OF THE LOWER THRESHOLD BEAM. THIS EO IS BEING ISSUED TO ACCOMPLISH THE PERMANENT REPAIR OF THE R2 DOOR THRESHOLD LOWER BEAM BY REMOVING AND REPLACING THE DAMAGED R2 DOOR THRESHOLD LOWER BEAM WITH A NEW PART. PART REPLACEMENT WILL BE ACCOMPLISHED IN ACCORDANCE WITH DRAWINGS LISTED IN THE REFERENCES AND SRM CHAPTER 51 STANDARD PRACTICES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE PART. BECAUSE THE R2 DOOR THRESHOLD LOWER BEAM (P/N 170-65639-005) IS A PSE AND REPLACEMENT IS COMPLEX, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY ENGINEERING AS A MAJOR REPAIR. EO E175-53MR-444 IS BEING ACCOMPLISHED BY WO 2719869.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 31,713 hrs · 19,483 cycles

DURING THE B6 BASIC CHECK, CORROSION DAMAGE WAS DISCOVERED IN THE FORWARD FUSELAGE AT THE RT COCKPIT FLOOR DOUBLER (P/N 170-03238-005) DURING INSPECTION IN THE AREA. THE DAMAGE EXCEEDED THE LIMITS PROVIDED IN THE SRM BECAUSE OF ITS DEPTH. EAMS REQUESTED AND RECEIVED APPROVED REPAIR DISPOSITION FROM RTS IN THE FORM OF ETD2019-170-122379A AND ITS CORRESPONDING ANAC DER FORM. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A PERMANENT REPAIR OF CORROSION TO THE RT COCKPIT FLOOR DOUBLER BY SPLICING IN A NEW SECTION OF THE FLOOR DOUBLER PER ETD2019-170-122379A. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR BECAUSE THE RT COCKPIT FLOOR DOUBLER IS A PSE AND THIS EO IS RESTORING STRENGTH. EO E175-53MR-446 IS BEING ACCOMPLISHED BY WO 2719871.

Part: SKIN — CORRODED (FRAME 88) · airframe 31,713 hrs · 19,483 cycles

DURING BASIC CHECK AT EAMS, CORROSION DAMAGE WAS FOUND TO THE CENTER FUSELAGE III SKIN FORWARD OF THE WASTE DOOR AT FRAME 88 (P/N 170-91883-005). REFERENCE ETD2019-170-120787, FIGURE 1 FOR DETAILS. EAMS REQUESTED AND RECEIVED PERMANENT REPAIRS FOR THE DAMAGE IN THE FORM OF ETD2019-170-120787 WHICH PROVIDE INSTRUCTIONS TO ACCOMPLISH BLEND OUT REPAIR. INSTRUCTIONS TO ACCOMPLISH A DETAILED VISUAL INSPECTION OF THE DENT TO VERIFY NO SHARP EDGES, CREASES, OIL CANNING, OR DISCREPANT FASTENERS ARE PRESENT IN THE DENTED AREA AND AN NDT HFEC INSPECTION TO VERIFY NO CRACKS EXIST. IF THE DENTED AREA IS FREE OF DAMAGE, THEN THE DENT IS CONSIDERED PERMANENT ALLOWABLE DAMAGE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: SHEAR TIE — CORRODED (NOT REPORTED) · airframe 31,713 hrs · 19,483 cycles

DURING BASIC CHECK AT EAMS, CORROSION DAMAGE WAS DISCOVERED ON SHEAR CLIPS IN THE AFT CARGO COMPARTMENT. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF THE CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CARGO SHEAR CLIPS: P/N 170-66867-001 FR83 SHEAR CLIP, P/N 170-66901-001 FR82 SHEAR CLIP. REFERENCE FIGURES 1 AND 2 FOR DAMAGE LOCATIONS AND DETAILS. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2, WHICH ARE APPROVED AS PART OF THE TYPE CERTIFICATE, AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: GUSSET — CORRODED (FRAME 90) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: GUSSET — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: GUSSET — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: GUSSET — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: SHEAR PANEL — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: SHEAR PANEL — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: SUPPORT — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: GUSSET — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING FORWARD CABIN FLOOR STRUCTURE: P/N 170-12118-001 FLOOR DOUBLER, P/N 170-05663-003 RH FLOOR SILL, P/N 170-05661-003 RH SILL. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS A MINOR REPAIR.

Part: DOUBLER — CORRODED (CABIN FLOOR) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING FORWARD CABIN FLOOR STRUCTURE: P/N 170-12118-001 FLOOR DOUBLER, P/N 170-05663-003 RH FLOOR SILL, P/N 170-05661-003 RH SILL. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS A MINOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING FORWARD CABIN FLOOR STRUCTURE: P/N 170-12118-001 FLOOR DOUBLER, P/N 170-05663-003 RH FLOOR SILL, P/N 170-05661-003 RH SILL. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS A MINOR REPAIR.

Part: SUPPORT — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: INTERCOSTAL — CORRODED (ZONE 100) · airframe 31,713 hrs · 19,483 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE BY REPLACEMENT OF THE FOLLOWING AFT CABIN FLOOR STRUCTURE: P/N 170-92856-001 FLOOR DOUBLER, P/N 170-86181-005 RH PANEL SUPPORT, P/N 170-86119-005 FR90 CENTER SPLICE, P/N 170-86139-005 LH PANEL SUPPORT, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 RH IB GUSSET, P/N 170-60261-001 FR90 LH OB GUSSET, P/N 170-60287-001 FR90 ANGLE SUPPORT. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR.

Part: FLASHLIGHT — INOPERATIVE (CABIN) · airframe 29,876 hrs · 17,864 cycles

L1 DOOR FA FLASHLIGHT INOP. R&R L1 DOOR FA FLASHLIGHT IAW AMM 33-51-01. OPS CHECK GOOD. OK FOR SVC.

Part: SEAL — LEAKING (NLG STRUT) · airframe 27,659 hrs · 16,195 cycles

DURING CLIMB OUT, FLIGHT CREW RECEIVED A LANDING GEAR WOW SYSTEM FAIL EICAS MESSAGE. RETURNED TO DEPARTURE. MESSAGE CLEARED AFTER LANDING GEAR DEPLOYMENT. THE CREW DECLARED AN EMERGENCY. PERFORMED STRUT SERVICING IAW AMM 32-21-02. PERFORMED EXTENSION AND RETRACTION OF LANDING GEAR IAW AMM 32-33-02, NO MESSAGES PRESENT. NOSE LANDING GEAR STRUT LEAKING. LANDING GEAR STRUT STILL LEAKING. REMOVED AND REPLACED THE NLG SHOCK STRUCT SEALS IAW AMM 32-21-04. OK FOR SERVICE.

Part: STRUT — LOW (NLG) · airframe 27,658 hrs · 16,194 cycles

DURING CLIMB, RECEIVED ACARS MESSAGE FROM FLIGHT STATING THEY HAD A LANDING GEAR WOW SYS FAILURE. EMERGENCY HAS BEEN DECLARED. WORKORDER STATES: LG WOW SYS FAIL EICAS MSG ON CLIMB. MSG CLEARED AFTER LANDING GEAR EXTENSION 7 DEPOLYMENT. UPON FURTHER INVESTIGATION, FOUND NLG STRUT TO BE LOW. SERVICE STRUT IAW AMM 12-12-09-03-1-600-801-A OK FOR SERVICE.

Part: RIB — CRACKED (RT WING) · airframe 26,831 hrs · 15,613 cycles

THE RIB THAT IS BEING REPLACED AS PART OF THE SERVICE BULLETIN WAS FOUND CRACKED DURING AN INSPECTION WHILE AT BASIC CHECK. BY ACCOMPLISHING SB 170-57-0047, THIS EO ALSO PROVIDES A REPAIR BY REPLACEMENT OF THE CRACKED RIB. ENGINEERING HAS CLASSIFIED THIS REPAIR AS A MAJOR REPAIR.

Part: SKIN — DENTED (FRAME 11) · airframe 26,211 hrs · 15,227 cycles

BEFORE A FLIGHT, A DENT WAS DISCOVERED ON THE FWD FUSELAGE SKIN BETWEEN STRINGERS 17L - 18L FRAME 11. REPAIRED IAW EA E175-53-901.3, SRM PART II 53-10-01 REPAIR 12P, TABLE 201, AND SRM 51-75-17 TABLE 1.

Part: UNKNOWN — ODOR (CABIN) · airframe 24,939 hrs · 14,464 cycles

FLIGHT REPORTED TO SOC THEY WERE AIR RETURNING TO LAX AND DECLARED AN EMERGENCY. THE ISSUE WAS NOT ELABORATED ON. THE FLIGHT LANDED AND TAXIED TO THE GATE AREA WITH NO ISSUE; THE REASON CONTINUED TO NOT BE GIVEN. ONE HOUR AFTER AIRCRAFT RETURNED TO THE GATE THE CREW REPORTED THAT THE AIR RETURN WAS DUE TO AN UNIDENTIFIABLE SMELL FROM AN UNKNOWN SOURCE IN THE COCKPIT. THE F/AS DID NOT PREPARE THE CABIN NOR DID THEY EXPERIENCE THE SMELL. NO REPORTED PASSENGER DIREST OR OTHER BEHAVIOR. THE CREW REPORT INDICATED THAT THE FO EXPERIENCED A SLIGHT SMELL POSSIBLY FROM THE FORWARD LAVATORY BEFORE TAKEOFF WITH THE CAPTAIN NOT EXPERIENCING THE SMELL. DURING CLIMB THE CREW INDICATED THE SMELL INCREASED AND BECAME CHEMICAL IN NATURE. AT 10,000 FT THE CABIN CREW DONNED O2 MASKS DUE TO SYMPTOMS OF HYPOXIA. THE CABIN CREW REPORTED THAT DONNING THE O2 MASKS DID NOT IMPROVE THE SITUATION. MAINTENANCE PERFORMED FIM TASK 21-20-00-810-801-A. OPS CHECK GOOD. NO SMELL ON COCKPIT. PERFORMED ENGINE RUN IAW EMM 72-00-00. OK FOR SERVICE.

Part: FLASHLIGHT — INOPERATIVE (CABIN) · airframe 23,948 hrs · 13,820 cycles

FA FLASHLIGHT AT R2 DOOR NOT BLINKING. REMOVED AND REPLACED THE FLASHLIGHT IAW AMM 33-51-01. OPS CHECKED GOOD. ACFT OK FOR SERVICE.

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 22,501 hrs · 12,960 cycles

L2 FLIGHT ATTENDANT FLASHLIGHT LED IS NOT FLASHING. R & R L2 FLIGHT ATTENDANT FLASHLIGHT BATTERY IAW AMM 33-51-01. OPERATIONS CHECKED.

Part: CONTROLLER — INOPERATIVE (CABIN PRESSURE) · airframe 21,977 hrs · 12,651 cycles

PRESS AUTO FAULT MSG, ANTI-ICE WING FAIL DURING HEAVY ICING ENG VIB 4.5 NR 1, 4.2 NR 2, CLEARED AFTER LEAVING ICE CONDITIONS. OVERWEIGHT LANDING AT 78.7 300 FEET FERT SPEED. ANTI-ICE WING FAIL DURING HEAVY ICING REF WO 985685. WING THERMAL ANTI-ICING OPERATIONS CHECKED IAW AMM 30-11-00, NO DEFECT ACFT OK FOR SERVICE. PERFORMED ENG VIB CHECKS OF NR 1 & 2 ENGS IAW ESM 71-00-00-760-267, NO DEFECTS NOTED. ACFT OK FOR SERVICE. PRESS AUTO FAULT REF WO 1985685. DEFERRED IAW MEL 21-31-01-1A & TRANSFERRED TO SDI. PLACARD INSTALLED, ACFT OK FOR SERVICE. MEL 21-31-01-1A CAT C. R & R CPCS CONTROLLER IAW AMM 21-31-01 & 21-30-00, OPERATIONS CHECKED NORMAL. CLEARED SDI, REMOVED PLACARD, OK FOR SERVICE. THIS CLEARS DM1986046 MX NOTIFIED.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT CABIN, LT FLOORBEAM PN 170-65669-003, BETWEEN FRAME 87 & 86, Y=260.4 HAS CORROSION, X=23453 - 23865, Y= 260. R & R AFT CABIN, LT FLOORBEAM IAW SRM 51-41-01 & 51-43-01 ON WO 19451292C4 IAW EO E175-53MR-093 REV 3 WO 1832171.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT CABIN, RT FLOORBEAM PN 170-65669-004 HAS CORROSION AT FRAME 87 & 86, Y=+275, X=23453 - 23865, Y= +260. R & R AFT CABIN, RT FLOORBEAM IAW SRM 51-41-01 & 51-43-01 ON WO 19451292D5 IAW EO E175-53MR-094 REV 4 WO 645758.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD FUSELAGE, MAIN CABIN RT FLOOR PANEL SUPPORT PN 170-13939-001, AT FRAME 14, Y=711.2 HAS CORROSION, LD04. WITH 100% MAT LOSS DIMENSION OF CORRODED AREA L=1.0", W=7". REMOVED FWD FUSELAGE MAIN CABIN RT FLOOR PANEL SUPPORT PN 13939-001, AT FRAME 14, Y=711.2 IAW SRM 51-41-01 PARA 4 FIG 1. POSITIONED & DRILLED FLOOR SUPPORT PN 170-13939, BN 0002842468 ON FWD FUSELAGE MAIN CABIN RT FLOOR IAW DWG 170-00800-503 & SRM 51-40-02. INSTALLED FLOOR PANEL SUPPORT ON FWD FUSELAGE MAIN CABIN RT FRAME 14, Y=711.2 IAW DWG 170-00822-503 & SRM 51-41-02. ACCOMPLISHED PERMANENT REPAIR BY REPLACEMENT OF FWD FUSELAGE MAIN CABIN RT FLOOR PANEL SUPPORT PN 170-13939-001, AT FRAME 14, Y=711.2 IAW EO E175-5300-122 REV 1, CONT ON SUPPLEMENT 66192. SUPPLEMENT VOIDED.

Part: DOOR FRAME — CORRODED (R2 DOOR) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

CPCP UPON REMOVAL OF R2 DOOR CUTOUT LWR FWD AND AFT FITTINGS FOUND CORROSION ON BEAM 1. REMOVED CORROSION ON R2 DOOR LOWER BEAM FWD FITTING EDGE AREA L= 1.5 W= .045 D= .100 IAW E175 SRM 51-12-01 PG. 1-4 AND E175 SRM 51-10-03 PG. 1-10. FOUND MORE CORROSION. PERFORMED DVI OF R-2 LWR BEAM AND SURROUNDING STRUCTURE AND FOUND NO FURTHER DAMAGE IAW E175 NDT MANUAL FRONT MATTER INTRO. LOCATED AND DRILLED R2 DOOR LOWER BEAM PN 170-65639-005 BATCH 0002843145 IAW DRAWING 170-65540-433. ACCOMPLISHED THE PERMANENT REPAIR OF THE R2 SERVICE DOOR THRESHOLD BEAM BY REPLACEMENT PER EO E175-53MR-212 REV IR.

Part: GUSSET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN LT INBD UPPER GUSSET PN 170-60257-001 AT FRAME 90 Y=-260.4 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR BY REPLACEMENT OF AFT MAIN CABIN LT INBD UPPER GUSSET PN 170-60257-001 AT FRAME 90 Y=-260.4 IAW EO NO E175-5300-123 REV IR WO 1958236 & 19451292C7.

Part: RETAINER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

CENTER FUSELAGE III AFT WASTE PAN RETAINER CORRODED, BETWEEN 22270.0 & 22680.0 AT STRINGER 26R. ACCOMPLISHED THE MODIFICATION OF WASTE BOX RETAINING DOUBLERS PN 170-86654-003 & 170-86655-003 IAW EO E17X-5300-004 REV IR WO 694221 & 19451311E2.

Part: GUSSET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN, LT OTBD UPPER GUSSET PN 170-60261-001 AT FRAME 90 Y=489.0 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR BY REPLACEMENT OF AFT MAIN CABIN LT OTBD UPPER GUSSET PN 170-60261-001 AT FRAME 90 Y=-489.0 IAW EO NO E175-5300-123 REV IR ON WO 1958236 & 19451292C6.

Part: RETAINER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

CENTER FUSELAGE III AFT WASTE PAN RETAINER CORRODED, BETWEEN 22270.0 & 22680.0 AT STRINGER 26R. ACCOMPLISHED THE MODIFICATION OF WASTE BOX RETAINING DOUBLERS PN 170-86654-003 & 170-86655-003 IAW EO E17X-5300-004 REV IR WO 694221 & 19451311E2.

Part: RETAINER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

CENTER FUSELAGE III AFT WATER PAN RETAINER CORRODED AT 21263.0 - 21675.0, STRINGER 27L - 29L. ACCOMPLISHED THE MODIFICATION OF THE WATER BOX RETAINING DOUBLERS PN 170-86656-001 & 170-86657-001 IAW THE EO E17X-5300-004 REV IR WO 694221 & 19451311E3.

Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN LT SHEAR PANEL PN 170-65927-007, BETWEEN FRAME 87 & 88, FROM Y=-304.8 - Y=-1041.4 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-123 REV IR WO 195823 & 19451292C2.

Part: SEAT TRACK — CORRODED (FRAMES 53-55) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

CENTER FUSELAGE RT LATERAL SEAT TRACK BETWEEN FRAMES 53-55 GOUGED & CORRODED. R & R THE SEAT TRACK IAW SRM 51-41-01 & 51-43-01.

Part: GUSSET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN RT GUSSET PN 170-60259-001 HAS CORROSION AT FRAME 90 Y=+560. ACCOMPLISHED PERMANENT REPAIR BY REPLACEMENT OF AFT FUSELAGE MAIN CABIN RT GUSSET PN 170-60259-001 AT FRAME 90 Y=+560 IAW EO NO E175-5300-123 REV IR WO 1958236 & 19451292D2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD FUSELAGE MAIN CABIN LT FLOOR PANEL SUPPORT PN 170-14734-001 AT FRAME 18, Y=-749.3 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-122 REV 1 WO 1957702 & 19451282A8.

Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN RT SHEAR PANEL PN 170-91919-001 HAS CORROSION, BETWEEN FRAME 87 & 88, Y=+300 - Y=+1040. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-123 REV IR WO 1958236 & 19451292D4.

Part: UPPER SHEET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN RT UPPER SHEET PN 170-86101-001 HAS CORROSION, BETWEEN FRAME 84 & 86, Y=+275. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-123 REV IR WO 645758 & 19451292D7.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD FUSELAGE MAIN CABIN RT FLOOR PANEL SUPPORT PN 170-04071-001 AT FRAME 16 Y=711.2. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-122 REV 1 WO 1957702 & 19451282A9.

Part: SEAL REST — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD CARGO DOOR CUT OUT, FWD LOWER CORNER SEAL REST HAS CORROSION. R & R FWD LOWER CORNER SEAL REST 170-66803-402 IAW SRM 51-41-01 & 51-43-01 ON WO 14751771H7 IAW EO E175-53MR-108 REV 2 WO 903876. RESUBMITTING WITH CORRECTED CONTROL NUMBER.

Part: RETAINER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

CENTER FUSELAGE III AFT WATER PAN RETAINER CORRODED AT 21263.0 - 21675.0, STRINGER 27L - 29L. ACCOMPLISHED THE MODIFICATION OF THE WATER BOX RETAINING DOUBLERS PN 170-86656-001 & 170-86657-001 IAW THE EO E17X-5300-004 REV IR WO 694221 & 19451311E3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD FUSELAGE MAIN CABIN RT FLOOR PANEL SUPPORT PN 170-13939-001 AT FRAME 14, Y=711.2. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-122 REV WO 1957702 & 19451282A8.

Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN CTR SHEAR PANEL PN 170-65928-001, BETWEEN FRAME 87 & 88, FROM Y=-222.3 - Y=222.3 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-123 REV IR WO 195823 & 19451292C3.

Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD FUSELAGE MAIN CABIN RT FLOOR SILL PN 170-05663-003, BETWEEN FRAME 12 & 14, Y=914.4 THROUGH 1219.2 HAS CORROSION. R & R RT FLOOR SILL PN 170-05663-003 IAW SRM 51-41-01 & 51-43-01.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN LT GALLEY SUPPORT PN 170-86132-003 AT FRAME 90, Y=-958.9. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-53MR-093 REV 3 WO 1832171 & 19451291C4.

Part: SEAL REST — CORRODED (FWD CARGO) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD CARGO DOOR CUT OUT, LOWER CTR SEAL REST HAS CORROSION. R & R THE SEAL REST IAW SRM 51-41-01 & 51-43-01.

Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD FUSELAGE MAIN CABIN LT FLOOR SILL PN 170-03275-005 AT FRAME 16, Y=-1149.4 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-122 REV I.

Part: GUSSET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN RT GUSSET PN 170-60257-001 HAS CORROSION AT FRAME 90 Y=+275. ACCOMPLISHED PERMANENT REPAIR BY REPLACEMENT OF AFT MAIN CABIN RT GUSSET PN 170-60257-001 AT FRAME 90 Y=+275 IAW EO NO E175-5300-123 REV IR WO 1958236 & 19451292D3.

Part: PANEL SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN RT PANEL SUPPORT PN 170-86181-005 AT FRAME 89 Y=+120 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR BY REPLACEMENT OF AFT MAIN CABIN RT PANEL SUPPORT PN 170-86181-005 AT FRAME 89 Y=+120 IAW EO NO E175-5300-123 REV IR WO 1958236 & 19451292D1.

Part: UPPER SHEET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN LT UPPER SHEET PN 170-86101-001, BETWEEN FRAME 85 & 86, Y=-260.4 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-123 REV IR WO 1958236 & 19451292B9.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD MAIN CABIN LT FLOOR DOUBLER PN 170-12118-001 AT FRAME 16 FROM Y=-304 - Y=-914.4 HAS CORROSION. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-122 REV 1 WO 1957702 & 19451282A8.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD FUSELAGE MAIN CABIN LT FLOOR DOUBLER PN 170-07311-001 AT FRAME 19, BETWEEN Y=-304.8. ACCOMPLISHED PERMANENT REPAIR IAW EO NO E175-5300-122 REV 1 WO 1957702 & 19451282A8.

Part: BEAM — CORRODED (FUSELAGE) · airframe 21,481 hrs · 12,356 cycles

DURING BASIC CHECK, INSPECTION DISCOVERED THE AFT FUSELAGE R2 SERVICE DOOR THRESHOLD BEAM, PN 170-65639-003 -005 TO HAVE CORROSION DAMAGE. THE CORROSION DAMAGE IS LOCATED IN MULTIPLE LOCATIONS, REF FIGURE 1 FOR DAMAGE DIMENSIONS & LOCATIONS. THE PERMANENT REPAIR ACCOMPLISHMENT BY REPLACEMENT OF THE CORRODED THRESHOLD BEAM, PN 170-65639-003 -005, WILL BE ACCOMPLISHED IAW ORIGINAL PRODUCTION DWGS & SRM STANDARD PRACTICES. SUPPLEMENTAL FOLLOW UP INSPECTIONS ARE NOT REQUIRED DUE TO DIRECT REPLACEMENT OF THE PART. ENGINEERING HAS CLASSIFIED THIS REPAIR AS A MAJOR REPAIR. ACCOMPLISHMENT OF THIS MAJOR REPAIR WAS ON EO E175-53MR-212 UNDER WO 1957719.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD FUSELAGE MAIN CABIN LT FLOOR TRACK, PN 170-03264-001, HAS MULTIPLE AREAS OF CORROSION, BETWEEN FRAME 13 & 19, Y=260.4, ZONE 200, BL 260. R & R LT FLOOR TRACK IAW SRM 51-41-01 & 51-43-01 ON WO 19451282B2 IAW EO E175-53MR-061 REV 5 WO 1955089.

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN, RT BEAM, PN 170-65669-004, HAS MULTIPLE AREAS OF CORROSION, BETWEEN FRAME 86 - 87, Y=275, ZONE 200, BL 260. R & R FWD CABIN RT MAIN CABIN BEAM IAW SRM 51-41-01 & 51-43-01 ON WO 19451292D5 IAW EO E175-53MR-094 REV 4 WO 645758.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

FORWARD MAIN CABIN, RT SEAT TRACK, PN 170-03263-001, HAS MULTIPLE AREAS OF CORROSION, BETWEEN FRAME 13 - 20, Y=260.4, ZONE 200, BL 260. R & R FWD CABIN RT SEAT TRACK IAW SRM 51-41-01 & 51-43-01 ON WO 19451282B1 IAW EO E175-53MR-062 REV 5 WO 1955093.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,481 hrs · 12,356 cycles

AFT FUSELAGE MAIN CABIN, LT LONGITUDINAL BEAM, PN 170-65669-003, HAS MULTIPLE AREAS OF CORROSION, BETWEEN FRAME 86 & 87, Y=260.4, ZONE 200, BL 260. R & R LT MAIN CABIN LONGITUDINAL BEAM IAW SRM 51-41-01 & 51-43-01 ON WO 19451292C4 IAW EO E175-53MR-093 REV 3 WO 1832171.

Part: FLASHLIGHT — INOPERATIVE (CABIN) · airframe 19,303 hrs · 11,060 cycles

FLASHLIGHT AT R1 DOOR INOPERATIVE. R & R FLASHLIGHT AT R1 DOOR IAW AMM.

Part: SLIDE — LOW PRESSURE (R2 DOOR) · airframe 17,905 hrs · 10,217 cycles

R2 DOOR SLIDE SHOWING LO PRESS AT 2550 PSI. REPLACED R2 DOOR SLIDE IAW TASK CARD. OK FOR SERVICE.

Part: ACCESS PANEL — WORN (ZONE 400) · airframe 15,785 hrs · 9,052 cycles

RACK, SHELF, BLOWN COUNTER SINK HOLES FOR FASTENERS AS MARKED PANEL 419ML. REAMED 3 FASTENER HOLES BACK TO ROUND AND INSTALL, NAS 1169C. REPAIR WASHER IAW STANDARD PROCEDURES IN SRM 51-40-02 ON WO 739715-441 IAW ETD 2013-170-036836 AND COMPASS EA E175-54-155, REV IR WO 804828.

Part: SEAL — TORN (THRUST REVERSER) · airframe 15,785 hrs · 9,052 cycles

LEFT ENGINE OTBD THRUST REVERSER, 12 O'CLOCK PLATFORM SEAL IS TORN. REPLACED SEAL IAW EO E17X-7800-001.1, REV 2 .

Part: SEAL — TORN (THRUST REVERSER) · airframe 15,785 hrs · 9,052 cycles

LEFT ENGINE OTBD THRUST REVERSER, DRAIN MAST SEAL IS TORN. REPLACED DRAIN MAST SEAL IAW EO E17X-7800-002.1, REV IR.

Part: FLAP TRACK — WORN (LT WING FLAP) · airframe 15,785 hrs · 9,052 cycles

LEFT WING FLAP TRACK, NR 2A OTBD, WORN OUT LIMITS. BLENDED WORN AREA IAW SRM PART II 51-10-03.

Part: BULKHEAD — DAMAGED (AFT) · airframe 15,785 hrs · 9,052 cycles

DAMAGE, LEFT SIDE OF REAR PRESSURE BULKHEAD RING BETWEEN STRINGERS 12LT AND 13LT HAS DRILL MARK. BLENDED OUT DRILL MARK IAW SRM PART II 51-10-03.

Part: POWER SUPPLY — INOPERATIVE (ZONE 200) · airframe 15,785 hrs · 9,052 cycles

4 EA EMERGENCY LIGHTS INOPERATIVE IN FWD SERVICE DOOR AND COCKPIT AREA. R & R FWD LT ELPU IAW AMM 33-50-01. OPS CHECK GOOD ON WO 747498-216, PN 3400-22-10, SN 003630.

Part: SKIN — DAMAGED (FUSELAGE)

FUSELAGE SKIN AT FUSELAGE HAS AN LIGHTNING STRIKE DAMAGE. BLENDED DAMAGE AREA SMOOTH IAW SRM II 51-10-03.

Part: FLAP TRACK — WORN (LT WING FLAP) · airframe 15,785 hrs · 9,052 cycles

LEFT WING FLAP TRACK NR 2 OTBD, WORN OUT OF LIMITS THICKNESS. BLENDED WORN AREA IAW SRM PART II 51-10-03.

Part: FLAP TRACK — WORN (LT WING FLAP) · airframe 15,785 hrs · 9,052 cycles

RT WING FLAP TRACK NR 2A INBD, WORN OUT OF LIMITS IAW SRM 57-52-03, TABLE 101. BLENDED WORN AREA IAW SRM PART II 51-10-03.

Part: FLAP TRACK — WORN (LT WING FLAP) · airframe 15,785 hrs · 9,052 cycles

RIGHT WING FLAP TRACK 1A, WORN OUT OF LIMITS IAW SRM 57-52-03, TABLE 101. R & R RT AFT FLAP TRACK IAW AMM 57-54-25.

Part: FLAP TRACK — GOUGED (LT WING) · airframe 15,785 hrs · 9,052 cycles

LEFT WING INBD FLAP TRACK 1A, WORN OUT OF LIMITS. R & R LT AFT FLAP TRACK 1A IAW AMM 57-54-25.

Part: FLAP TRACK — WORN (RT WING FLAP) · airframe 15,785 hrs · 9,052 cycles

RT WING FLAP TRACK NR 2A INBD, WORN OUT OF LIMITS IAW SRM 57-52-03, TABLE 101. BLENDED WORN AREA IAW SRM PART II 51-10-03.

Part: SPAR — DAMAGED (LT WING) · airframe 15,787 hrs · 9,053 cycles

DURING ACCOMPLISHMENT OF EO E17X-57AD-001.1, A BUSHING FROM PRODUCTION WAS DISCOVERED IN A SB 170-57-0053, REWORKED FASTENER HOLE. SINCE THE DAMAGE IS NOT COVERED IN THE SB, A REPAIR WAS REQUESTED FROM MFG AND PROVIDED BY ETD2013-170-037735A AND APPROVED BY FORM 8110-3. BECAUSE THIS STRUCTURE IS PSE, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR ALTERATION FOR THE ACCOMPLISHMENT OF SB 170-57-0053 AND A MAJOR REPAIR FOR THE ELIMINATION OF THE COLD WORKING PROCESS ON 1EA SUBJECT FASTENER HOLE THAT HAD A BUSHING INSTALLED AT PRODUCTION. THE ACCOMPLISHEMENT OF THIS REPAIR WAS ON EO E17X-57AD-001.6.

Part: SEAL DEPRESSOR — CORRODED (ZONE 100) · airframe 15,785 hrs · 9,052 cycles

FWD CARGO DOOR CUTOUT STRUCTURE, CENTER SEAL DEPRESSOR, HAS CORROSION. R & R CENTER SEAL DEPRESSOR IAW SRM 51-41-01 AND 51-43-01.

Part: SEAL DEPRESSOR — CORRODED (ZONE 100) · airframe 15,785 hrs · 9,052 cycles

FWD CARGO DOOR CUTOUT STRUCTURE FWD SEAL DEPRESSOR, PN 170-66803-401, HAS CORROSION AT X=7120, STR 24R-26R. R & R FWD SEAL DEPRESSOR IAW SRM 51-41-01 AND 51-43-01 ON WO 739715-122, IAW COMPASS EO E175-53MR-108, REV 2, WO 802092.

Part: SEAL DEPRESSOR — CORRODED (ZONE 100) · airframe 15,785 hrs · 9,052 cycles

FWD CARGO DOOR CUTOUT STRUCTURE AFT SEAL DEPRESSOR, HAS CORROSION AT X=8558, STR 24-26R. R & R FWD SEAL DEPRESSOR IAW SRM 51-41-01 AND 51-43-01.

Part: SEAL DEPRESSOR — CORRODED (CARGO DOOR) · airframe 15,785 hrs · 9,052 cycles

AFT CARGO DOOR CENTER DEPRESSOR HAS CORROSION. REPLACED AFT CARGO DOOR SEAL DEPRESSOR IAW EO E175-53MR-107.

Part: SEAL DEPRESSOR — CORRODED (CARGO DOOR)

AFT CARGO CENTER DEPRESSOR HAS CORROSION AS MARKED X=20757, Y=430. REPLACED AFT CARGO CENTER SEAL DEPRESSOR IAW EO E175-53MR-107.

Part: FINGER DOUBLER — CORRODED (CARGO DOOR) · airframe 15,785 hrs · 9,052 cycles

FWD CARGO DOOR CUTOUT FWD FINGER DOUBLER HAS CORROSION. R & R FWD FINGER DOUBLER.

Part: FINGER DOUBLER — CORRODED (FWD CARGO DOOR) · airframe 15,785 hrs · 9,052 cycles

FWD CARGO DOOR CUTOUT AFT FINGER DOUBLER HAS CORROSION. R & R AFT FINGER DOUBLER.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 7,603 hrs · 4,493 cycles

EMERGENCY LIGHTS ILLUMINATE WHEN POWER IS SHUTOFF. R & R R2 EMERGENCY LIGHT PACK IAW E175 AMM 33-50-01, 0PS CHECKS GOOD, ACFT OK FOR SERVICE.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHT) · airframe 7,564 hrs · 4,471 cycles

R2 EXIT SIGNS INOP. CHARGED EMERGENCY LIGHTING SYS IAW AMM 33-50-01 AND PERFOMED OPS TEST IAW EAMM 33-50-00-710-801-A. OPS CK GOOD. ACFT, OK FOR SERVICE.

Part: SLIDE — NO TEST (R2 DOOR) · airframe 6,753 hrs · 3,976 cycles

DURING ROUTINE OVERNIGHT MX, THE EMERGENCY EVACTUATION SLIDE TEST DEPLOYMENT LOCATED AT THE R2 POSITION ON ACFTT WAS UNSUCCESSFUL. THE SLIDE DEPLOYED IN A FWD MOTION, CONTACTED THE R2 DOOR, AND PUNCTURED THE SLIDE. THE SLIDE DEFLATED AS A RESULT OF THE CONTACT WITH THE DOOR. IT WAS DETERMINED THAT THE SLIDE ITSELF WAS AT FAULT. THE R2 DOOR ASSIST BOTTLE WAS VERIFIED CHARGED TO THE PROPER LEVEL BEFORE THE DEPLOYMENT TEST WAS CARRIED OUT, AND THE DOOR WAS FULLY OPEN BEFORE THE SLIDE DEPLOYED.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHTS) · airframe 5,578 hrs · 3,282 cycles

AIRCRAFT HAD AN "MER LT BATT FAULT" EICAS MESSAGE ON POWER-UP. PERFORMED ELPU CHARGE IAW AMM 35-50-01-800-802A. OPS CK NORMAL IAW AMM 33-50-00-710-801A. NO OTHER DEFECTS NOTED. NO PARTS WERE REQUIRED.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 5,272 hrs · 3,102 cycles

DURING BASIC CHECK INSP, MX VISIT CORROSION WAS FOUND ON LT FLOOR TRACK, PN 170-03264-001 PERMANENT REPAIR WAS MADE IAW ETD 2010-170/00030 AND COMPASS EO E175-53MR-020. MUST BE REPLACED AT NEXT BASIC CHECK.

Part: SENSOR — DAMAGED (SLAT SYSTEM) · airframe 3,693 hrs · 2,190 cycles

ON APPROACH AMBER SLAT FAIL, SHAKER ANTICIPATED, AOA LIMIT FAIL, AND SPOILER FAULT WHEN SELECTING SLAT FLAP POSITION 2. TROUBLESHOT SYS DOWN TO BAD SKEW SENSOR NR2-3 LT SIDE. REMOVED AND REPLACED THE 2/3 SKEW SENSOR IAW AMM 27-83-01. SLAT SYS OPS CHECK GOOD. ACFT IS OK FOR SERVICE.