N610CZ

Part: NOT REPORTED — FAILED (NOT REPORTED) · airframe 36,364 hrs · 22,980 cycles

BEFORE DEPARTURE WE NOTICED SOME NICKS ON THE N1 BLADES FOR ENGINE 2. WE HAD MAINTENANCE COME OUT AND CORRECT IT. WHILE IN ROUTE TO BOSTON WE GOT HIGH VIBES ON ENGINE 2. RAN THE QRH PROCEDURE FOR HIGH ENGINE VIBRATION. ENGINE 2 MAX HP VIBE 4.0 (AMBER). THEN ATTEMPTED TO REDUCE VIBRATION BY REDUCING ENGINE THRUST TO 75 TO 80 % N1. HEARD A GRINDING NOISE FROM THE RIGHT ENGINE. RETURNED ENGINE THRUST TO 85% AND THE NOISE WENT AWAY FOR THE NEXT 15 MINUTES OF UNEVENTFUL FLIGHT. THEN THE ENGINE 2 MADE A SHUTTERING NOISE AND THE N1 SPOOLED DOWN TO 40% WITH AN AMBER N1 FAIL ICON. WHILE STARTING TO RUN QRH FOR ENGINE FAILURE- NOTICED THE #2 ENGINE ITT STARTING TO RISE AND ELECTED TO TURN THE ENGINE OFF TO AVOID AN ITT EXCEEDANCE (MAX ITT OBSERVED WAS 817). AT THAT POINT THE ITT STARTED TO GO DOWN. RECEIVED AND €ŒENGINE EXCEEDANCE€? CAUTION AFTER LANDING. LANDING UNEVENTFUL WITH NO INJURIES. ON POST FLIGHT OBSERVED SHRAPNEL IN THE ENGINE 2 EXHAUST TAIL PIPE. (FILED OPEN)

Part: INTERCOSTAL — CORRODED (FRMS 85-86) · airframe 33,057 hrs · 20,626 cycles

CORROSION AROUND LOWER FASTENERS ON LH INTERCOSTAL BETWEEN FRAMES 85 AND 86. (C-CHECK RO 8/18/2021) REMOVED AND REPLACED LH INTERCOSTAL BETWEEN FRAMES 85 AND 86 REF. EMB 175 SRM 51-40-08..SEE CONTINUATION CARD FOR WORK DONE

Part: SKIN — DENTED (FRM 19 S20-21L) · airframe 33,057 hrs · 20,626 cycles

FORWARD FUSELAGE SKIN DENTED FRAME 19 STRINGERS 20L/21L (C-CHECK RO 8/18/2021) / PERFORMED CUTOUT AND DOUBLER REPAIR ON FWD FUSELAGE SKIN AT FR 19 BETWEEN STGR 20L-21L. REF EMB ETD2021-170-020197. SEE CONTINUATION CARD FOR WORK ACCOMPLISHED. NO APPRECIABLE WEIGHT CHANGE.

Part: DOUBLER — CORRODED (COCKPIT) · airframe 31,546 hrs · 19,293 cycles

DURING THE B6 BASIC CHECK AT EAMS, CORROSION DAMAGE WAS DISCOVERED IN THE FORWARD FUSELAGE AT THE RH 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 ETD2019-170-095566 AND ITS CORRESPONDING ANAC DER FORM. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A PERMANENT REPAIR OF CORROSION TO THE RH COCKPIT FLOOR DOUBLER BY SPLICING IN A NEW SECTION OF THE FLOOR DOUBLER PER ETD2019-170-095566. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR BECAUSE THE RH COCKPIT FLOOR DOUBLER IS A PSE AND THIS EO IS RESTORING STRENGTH. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT REQUIRED PER ETD2019-170-095566. WORK ORDER 254023529

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 31,546 hrs · 33,534 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 EMBRAER 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: DOUBLER — CORRODED (FUSELAGE) · airframe 31,546 hrs · 19,293 cycles

DURING THE B6 BASIC CHECK AT EAMS, 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 ETD2019-170-095566 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 ETD2019-170-095566. 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. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT REQUIRED PER ETD2019-170-095566. EO E175-53MR-429 IS BEING ACCOMPLISHED BY WO 2689848.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,546 hrs · 19,293 cycles

DURING THE HEAVY CHECK OF THE AIRCRAFT, DAMAGE WAS DISCOVERED ON THE LT IB SEAT TRACK (P/N 170-03264-001) AT THE FR19 CROSSBEAM IN THE FORWARD CABIN FLOOR STRUCTURE. THE BEAM WILL BE REPAIRED BY CUTOUT AND DOUBLER INSTALLATION PER SRM PART II 53-10-10 REPAIR 01P. THE LT SEAT TRACK BEAM IS NOT CLASSIFIED AS FATIGUE CRITICAL STRUCTURE (FCS), BUT IT IS CLASSIFIED AS PRIMARY STRUCTURE. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR DUE TO STRENGTH RESTORATION OF PRIMARY STRUCTURE. SUPPLEMENTAL FOLLOW UP INSPECTIONS ARE NOT REQUIRED PER SRM PART II 53-10-10 REPAIR 01P.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,546 hrs · 19,293 cycles

DURING BASIC CHECK AT EAMS, CORROSION DAMAGE WAS FOUND TO THE FORWARD FUSELAGE FRAME 16 FLOOR DOUBLER (P/N 170-12118-001) AND RH SILL BETWEEN FRAME 12 - 14 (P/N 170-05663-003). REFERENCE ETD2019-170-092106 FIGURE 1 FOR DETAILS ON THE FRAME 16 FLOOR DOUBLER AND ETD2019-170-0092196 FIGURE 1 FOR DETAILS RH SILL BETWEEN FRAME 12 - 14. EAMS REQUESTED AND RECEIVED PERMANENT REPAIRS FOR THE DAMAGE IN THE FORM OF ETD2019-170-092106 AND ETD2019-170-092196, WHICH PROVIDE INSTRUCTIONS TO ACCOMPLISH BLEND OUT REPAIR. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR. WORK ORDER 25420203307

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,546 hrs · 19,293 cycles

DURING BASIC CHECK AT EAMS, CORROSION DAMAGE WAS FOUND TO THE FORWARD FUSELAGE FRAME 16 FLOOR DOUBLER (P/N 170-12118-001) AND RH SILL BETWEEN FRAME 12 - 14 (P/N 170-05663-003). REFERENCE ETD2019-170-092106 FIGURE 1 FOR DETAILS ON THE FRAME 16 FLOOR DOUBLER AND ETD2019-170-0092196 FIGURE 1 FOR DETAILS RH SILL BETWEEN FRAME 12 - 14. EAMS REQUESTED AND RECEIVED PERMANENT REPAIRS FOR THE DAMAGE IN THE FORM OF ETD2019-170-092106 AND ETD2019-170-092196, WHICH PROVIDE INSTRUCTIONS TO ACCOMPLISH BLEND OUT REPAIR. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR. WORK ORDER 2542023315

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 31,546 hrs · 19,293 cycles

DURING BASIC CHECK AT EAMS, CORROSION DAMAGE WAS FOUND TO THE CENTER FUSELAGE III FLOOR STRUCTURE FRAME 86RH (P/N 170-86101-001) AND FLOOR SPLICE AT FRAME 90 (P/N 170-86119-005). REFERENCE ETD2019-170-092046 FIGURE 1 FOR DETAILS ON THE FRAME 86RH AND ETD2019-170-0092063 FIGURE 1 FOR DETAILS ON THE FLOOR SPLICE AT FRAME 90. EAMS REQUESTED AND RECEIVED PERMANENT REPAIRS FOR THE DAMAGE IN THE FORM OF ETD2019-170-092046 AND ETD2019-170-092063, WHICH PROVIDE INSTRUCTIONS TO ACCOMPLISH BLEND OUT REPAIR. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR. WORK ORDER 2542023312

Part: GUSSET — CORRODED (FRAME 90) · airframe 31,546 hrs · 19,293 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 170-86181-005 RH PANEL SUPPORT, P/N 170-86139-005 LH SILL PANEL FR 88-90, P/N 170-66796-001 LH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 LH IB GUSSET, P/N 170-60261-001 GUSSET FR 90 LH OTBD, P/N 170-92907-001 LH PANEL 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 A MINOR REPAIR. WORK ORDER 2542023321

Part: GUSSET — CORRODED (FRAME 90) · airframe 31,546 hrs · 19,293 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 170-86181-005 RH PANEL SUPPORT, P/N 170-86139-005 LH SILL PANEL FR 88-90, P/N 170-66796-001 LH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 LH IB GUSSET, P/N 170-60261-001 GUSSET FR 90 LH OTBD, P/N 170-92907-001 LH PANEL 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 A MINOR REPAIR. WORK ORDER 2542023325

Part: SUPPORT — CORRODED (ZONE 100) · airframe 31,546 hrs · 19,293 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 170-86181-005 RH PANEL SUPPORT, P/N 170-86139-005 LH SILL PANEL FR 88-90, P/N 170-66796-001 LH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 LH IB GUSSET, P/N 170-60261-001 GUSSET FR 90 LH OTBD, P/N 170-92907-001 LH PANEL 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 A MINOR REPAIR. WORK ORDER 2542023309

Part: FLOOR SUPPORT — CORRODED (FRAME 16) · airframe 31,546 hrs · 19,293 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 170-07311-001 (-003) FLOOR DOUBLER, P/N 170-05661-003 (-005) RH SILL, P/N 170-04071-001 FR16 RH FLOOR 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 A MINOR REPAIR. WORK ORDER 2542023322

Part: FLOOR SPLICE — CORRODED (ZONE 100) · airframe 31,546 hrs · 19,293 cycles

DURING BASIC CHECK AT EAMS, CORROSION DAMAGE WAS FOUND TO THE CENTER FUSELAGE III FLOOR STRUCTURE FRAME 86RH (P/N 170-86101-001) AND FLOOR SPLICE AT FRAME 90 (P/N 170-86119-005). REFERENCE ETD2019-170-092046 FIGURE 1 FOR DETAILS ON THE FRAME 86RH AND ETD2019-170-0092063 FIGURE 1 FOR DETAILS ON THE FLOOR SPLICE AT FRAME 90. EAMS REQUESTED AND RECEIVED PERMANENT REPAIRS FOR THE DAMAGE IN THE FORM OF ETD2019-170-092046 AND ETD2019-170-092063, WHICH PROVIDE INSTRUCTIONS TO ACCOMPLISH BLEND OUT REPAIR. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR. WORK ORDER 2542023323

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,546 hrs · 19,293 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 170-86181-005 RH PANEL SUPPORT, P/N 170-86139-005 LH SILL PANEL FR 88-90, P/N 170-66796-001 LH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 LH IB GUSSET, P/N 170-60261-001 GUSSET FR 90 LH OTBD, P/N 170-92907-001 LH PANEL 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 A MINOR REPAIR. WORK ORDER 2542023327

Part: PANEL — CORRODED (ZONE 100) · airframe 31,546 hrs · 19,293 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 170-86181-005 RH PANEL SUPPORT, P/N 170-86139-005 LH SILL PANEL FR 88-90, P/N 170-66796-001 LH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 LH IB GUSSET, P/N 170-60261-001 GUSSET FR 90 LH OTBD, P/N 170-92907-001 LH PANEL 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 A MINOR REPAIR. WORK ORDER 254203316

Part: GUSSET — CORRODED (FRAME 90) · airframe 31,546 hrs · 19,293 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 170-86181-005 RH PANEL SUPPORT, P/N 170-86139-005 LH SILL PANEL FR 88-90, P/N 170-66796-001 LH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 LH IB GUSSET, P/N 170-60261-001 GUSSET FR 90 LH OTBD, P/N 170-92907-001 LH PANEL 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 A MINOR REPAIR. WORK ORDER 2542023320

Part: SHEAR PANEL — CORRODED (ZONE 100) · airframe 31,546 hrs · 19,293 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 170-86181-005 RH PANEL SUPPORT, P/N 170-86139-005 LH SILL PANEL FR 88-90, P/N 170-66796-001 LH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60259-001 FR90 RH OB GUSSET, P/N 170-60257-001 FR90 LH IB GUSSET, P/N 170-60261-001 GUSSET FR 90 LH OTBD, P/N 170-92907-001 LH PANEL 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 A MINOR REPAIR. WORK ORDER 2542023314

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 31,546 hrs · 19,293 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE ON CONDITION REPLACEMENT OF A DAMAGED OR PREVIOUSLY REPAIRED RT FLOOR TRACK P/N 170-03263-001 BETWEEN FRAMES 12 AND 20 WITH A NEW P/N 170-03263-001 FLOOR TRACK. THE FLOOR TRACK WILL BE REPLACED USING PRODUCTION DRAWINGS. BECAUSE THE TRACK IS A PSE, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,546 hrs · 19,293 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE ON CONDITION REPAIR OF CORROSION OR OTHER DAMAGE TO THE CENTER FUSELAGE I LT LATERAL SEAT TRACK P/N 170-92570-005 (-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 NEW PARTS PER THE PRODUCTION DRAWINGS, THE AIRCRAFT STRUCTURE REMAINS IN ITS ORIGINAL CONFIGURATION. THEREFORE, SUPPLEMENTAL FOLLOW UP INSPECTIONS ARE NOT REQUIRED. UPON COMPLETION OF THIS EO, AN SDR IS REQUIRED TO BE SUBMITTED.

Part: DOUBLER — CORRODED (ZONE 100) · airframe 31,545 hrs · 19,239 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 170-07311-001 (-003) FLOOR DOUBLER, P/N 170-05661-003 (-005) RH SILL, P/N 170-04071-001 FR16 RH FLOOR 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 A MINOR REPAIR. WORK ORDER 2542023310

Part: SEAT TRACK — CORRODED (FRAME 19) · airframe 31,546 hrs · 19,293 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A PERMANENT REPAIR OF CORROSION DAMAGE DISCOVERED DURING BASIC CHECK AT EAMS ON THE LH IB SEAT TRACK (P/N 170-03264-001) AT THE FR19 CROSSBEAM IN THE FORWARD CABIN FLOOR STRUCTURE. THE BEAM WILL BE REPAIRED BY CUTOUT AND DOUBLER INSTALLATION PER SRM PART II 53-10-10 REPAIR 01P. THE LH SEAT TRACK BEAM IS NOT CLASSIFIED AS FATIGUE CRITICAL STRUCTURE (FCS), BUT IT IS CLASSIFIED AS PRIMARY STRUCTURE. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR DUE TO STRENGTH RESTORATION OF PRIMARY STRUCTURE. SUPPLEMENTAL FOLLOW UP INSPECTIONS ARE NOT REQUIRED PER SRM PART II 53-10-10 REPAIR 01P. WORK ORDER 254202308

Part: STRINGER — CORRODED (FUSELAGE) · airframe 26,674 hrs · 15,510 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF CENTER FUSELAGE III STRINGER 29R, BY PART REPLACEMENT DUE TO CORROSION DAMAGE BEING DISCOVERED BETWEEN FR75-FR80 DURING THE AIRCRAFT’S BASIC CHECK. THERE ARE SEVERAL AREAS OF CORROSION AND PITTING DAMAGE ON STGR-29R WITH THE DEEPEST AREA MEASURING 0.30 INCH (REF EO E175-53MR-356, FIGURES 1-5, FOR DAMAGE LOCATIONS AND DIMENSIONS). PART REPLACEMENT WILL BE ACCOMPLISHED IN ACCORDANCE WITH DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF STGR-29R. BECAUSE STGR-29R IS PSE AND FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY ENGINEERING AS A MAJOR REPAIR DUE TO STRENGTH RESTORATION. PERMANENT REPAIR WILL BE ACCOMPLISHED ON WORK ORDER 2310275

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 26,674 hrs · 15,510 cycles

RIGHT HORIZONTAL STABILIZER HAS A CRACKED RIB 12A. REPAIRED IAW DRAWINGS, SRM 51.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 26,674 hrs · 15,510 cycles

RIB 11A ON THE RT HORIZONTAL STABILIZER CRACKED. REPAIRED IAW DRAWING 170-62400-453,

Part: SLIDE — UNSERVICEABLE (L2 DOOR) · airframe 26,168 hrs · 15,189 cycles

FOUND SAFETY STRING ON L2 EVACUATION SLIDE BROKEN. R&R L2 EMERGENCY SLIDE IAW AMM-25-65-01. OK FOR SVC.

Part: DIAPHRAGM — DAMAGED (ASSIST BOTTLE) · airframe 25,320 hrs · 14,661 cycles

DURING REPAIR FOR A L2 DOOR ESCAPE SLIDE INDICATION, THE L2 DOOR ASSIST BOTTLE WAS DEPLETED. R & R THE DIAPHRAM AND SHEAR PIN IAW AMM 52-12-53 SVC'D DOOR ASSIT BOTTLE TO 2000 PSI IAW AMM 52-12-51 AND OPENED RT2210398 TO RECHECK ASSIST BOTTLE PSI IN 24 TO 48 HRS. A/C OK FOR SVC.

Part: FLASHLIGHT — INOPERATIVE (FWD CABIN) · airframe 24,814 hrs · 14,342 cycles

FWD LEFT FA FLASHLIGHT INOPERATIVE. REMOVED AND REPLACED FLASHLIGHT IAW AMM 33-51-01. OK FOR SERVICE.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 23,948 hrs · 13,805 cycles

AFT EMERGENCY EXIT LOCATOR INOPERATIVE ON TEST. R & R AFT EMERGENCY EXIT BATTERY IAW AMM 33-50-01. NO FIX. SLAVED LIGHT TO FWD BATTERY. LAMP OPS GOOD. R & R NR 3 EMERGENCY LIGHT POWER UNIT IAW AMM 33-50-01, OPS CHECKED GOOD IAW AMM 33-50-00 OPS CHECKED GOOD. OK FOR SERVICE.

Part: DIAPHRAGM — DEFECTIVE (L2 DOOR) · airframe 23,825 hrs · 13,729 cycles

THE L2 DOOR WAS FOUND DIFFICULT TO ARM AND DISARM, THE EVACUATION ESCAPE SLIDE BUSTLE PIN WAS FOUND DETACHED AND PNEUMATIC ASSIST BOTTLE PRESSURE WAS DEPLETED. THE L2 DOOR DIAPHRAGM ASSY WAS REPLACED IAW AMM AND WAS CHARGED. THE EVACUATION SLIDE MECHANISM WAS ADJUSTED IAW AMM. OPS CHECK GOOD, NO DEFECTS NOTED, ACFT OK FOR SERVICE.

Part: SHUTOFF VALVE — INTERMITTENT (BLEED AIR SYS) · airframe 22,129 hrs · 12,731 cycles

BLEED 1 FAIL MSG AT FL314. QRH 2.5 COMPLETE, CONDITION PERSISTS. DEFERRED IAW MEL 36-00-00-1, TRANSFERRED TO SDI & PLACARD INSTALLED. ACFT OK FOR SERVICE. REPLACED NR 1 NAPRSOV IAW AMM 36-11-03. OPERATIONS CHECK REQUIRED. DM REMAINS OPEN. PERFORMED A CREW ASSISTED ENG RUN OPERATIONS CHECK FOR THE NAPRSOV IAW AMM 36-11-03. OPERATIONS CHECKED GOOD. BLEED 1 FAIL IS CLEARED, THIS DM REMAINS OPEN. PERFORMED OPERATIONS CHECK OF AIRCRAFTS BLEED TEST IAW AMM 36-00-00 500. OPERATIONS CHECKED GOOD. ACFT OK FOR SERVICE THIS CLEARS DM1984152. SDI UPDATED & PLACARD REMOVED.

Part: FLASHLIGHT — INOPERATIVE (CABIN) · airframe 21,872 hrs · 12,591 cycles

FLIGHT ATTENDANT FLASHLIGHT BY R1 DOOR INOPERATIVE. DEFERRED FLIGHT ATTENDANT FLASHLIGHT BY R1 DOOR IAW MEL 25-62-07-1. TRANSFERRED TO SDI, NO MX ACTION REQUIRED. PLACARD INSTALLED. ACFT OK FOR SERVICE, MEL 25-62-07-1 CAT C. R & R FLIGHT ATTENDANT FLASHLIGHT ASSEMBLY BY R1 DOOR IAW AMM33-51-01. OPERATIONS CHECKED GOOD. THIS CLEARS DM 1965666. SDI SIGNED, PLACARD REMOVED, MX NOTIFIED & OK FOR SERVICE.

Part: CROSSBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

MAIN CABIN FLOOR STRUCTURE HAS CORROSION AT FRAME 17 & RBL 13 - 42. FOUND DURING OK TO CLOSE. ACCOMPLISHED PERMANENT REPAIR IAW EO E175-53MR-205 REV IR WO 1944007. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF CORROSION DAMAGE TO THE CROSSBEAM FRAME 17 PN 170-21769-405, UPPER FLANGE LOCATED BETWEEN Y=15 & Y=42.7, OTBD OF TRACK Y=11, REF ETD 2015-170-073605B, FIGURES 1 & 2. THE APPROX DAMAGE DIMENSIONS ARE AS FOLLOWS, 27.50 INCHES X .90 INCH WITH 100% EXFOLIATION. REQUESTED & RECEIVED A REPAIR IN THE FORM OF ETD 2015-170-073605B FOR THE ACCOMPLISHMENT OF THE CROSSBEAM FRAME 17 REPAIR ANGLE APPROVAL. BECAUSE THE FLOOR CROSSBEAM FRAME 17 IS PSE & FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

AFT MAIN CABIN FLOOR STRUCTURE, LT GALLEY SUPPORT PN 170-86132-003, HAS CORROSION AT FRAME 90, Y=42. REPLACED LT GALLEY SUPPORT IAW SRM 51-41-02 & EO E175-5300-119 REV IR WO 1941393.

Part: MOUNT BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

AFT PAX DOOR, AFT SLIDE FITTING LOWER MOUNT BRACKET HAS CORROSION AROUND NUTPLATE. DURING BASIC CHECK, INSPECTION FOUND THE AFT PAX DOOR SURROUNDING STRUCTURE ANGLE, NUT HOLDER PN 170-85282-401 WITH CORROSION DAMAGE. THE CORROSION DAMAGE MEASURES THE FOLLOWING APPROX DIMENSIONS, 1.5 INCHES X 1.0 INCH WITH 100% EXFOLIATION. REQUESTED & RECEIVED A PERMANENT REPAIR IN THE FORM OF ETD 2015-170-072131, TO FABRICATE THE CRACKED ANGLE BRACKET FROM 7475-T761 .040 INCH THICK SHEET & REPLACE IT. ENGINEERING HAS CLASSIFIED THIS REPAIR AS A MINOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN LT FLOOR SUPPORT PN 170-13633-001 AT FRAME 16, Y= -45, Z=19.29 HAS CORROSION. R & R LT FLOOR SUPPORT IAW SRM 51-41-02 & EO E175-5300-118 REV IR WO 1941779.

Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN, LT FLOOR SILL PN 170-03275-005 AT FRAME 16, FROM Y= -46 - Y= -49 HAS CORROSION. R & R LT FLOOR SILL IAW SRM 51-41-02 & EO E175-5300-118 REV IR WO 1941779.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

PASSENGER CABIN FLOOR SEAT TRACK BETWEEN FRAME 19 - 20, RBL10 IS CORRODED AT UPPER SURFACE. R & R SEAT TRACK 170-03263-001 IAW SRM 51-41-02 & EO E175-53MR-062 REV 5 WO 1939698. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE ON CONDITION REPLACEMENT OF A DAMAGED OR PREVIOUSLY REPAIRED RT FLOOR TRACK PN 170-03263-001 BETWEEN FRAMES 12 & 20 WITH A NEW PN 170-03263-001 FLOOR TRACK. THE FLOOR TRACK WILL BE REPLACED USING PRODUCTION DWGS. BECAUSE THE TRACK IS A PSE, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR.

Part: RETAINER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

AFT INTERIOR FUSELAGE WASTE CUT OUT DOOR STRUCTURE RETAINERS HAS CORROSION, BETWEEN STATION 22270.0 & 22680.0 & STRINGER 26R. REMOVED & DISCARDED WASTE PAN RETAINERS 170-86654-003 & 170-86655-003 IAW EO-E175X-5300-004.2 WO 1938853.

Part: GUSSET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

AFT MAIN CABIN, RT UPPER GUSSET PLATE PN 170-60259-001 AT FRAME 90, Y=23, Z= -19.29. REPLACED RT UPPER GUSSET IAW SRM 51-41-02 & EO E175-5300-119 REV IR WO 1941393.

Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

AFT MAIN CABIN, LT SHEAR PANEL PN 170-65927-007, BETWEEN FRAME 87 & 88, Y= -11 - Y=41, Z=19.29. REPLACED LT SHEAR PANEL IAW SRM 51-41-02 & EO E175-5300-119 REV IR WO 1941393.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN FLOOR SUPPORT AT FRAME 19, Y=-43, Z=-19.29 HAS CORROSION. R & R MAIN CABIN FLOOR SUPPORT PN 170-29704-001 IAW SRM 51-41-02 & EO E175-5300-118 REV IR WO 1941779.

Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN RT FLOOR SILL PN 170-05663-003 BETWEEN FRAME 12 & 14, FROM Y=37 - Y=49, Z=19.29. R & R RT FLOOR SILL IAW SRM 51-41-02 & EO E175-5300-118 REV IR WO 1941779.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN FLOOR PANEL SUPPORT PN 170-13939-001 AT FRAME 17, Y= 29:Z=-19.29 HAS CORROSION. R & R MAIN CABIN FLOOR PANEL SUPPORT IAW SRM 51-41-02 & EO E175-5300-118 REV IR WO 1941779.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN, FLOOR DOUBLER PN 170-12118-001 AT FRAME 16, FROM Y= -13 - Y=36, Z=19.29. R & R DOUBLER SRM 51-41-02 & EO E175-5300-118 REV IR.

Part: CROSSBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN, FRAME 17, CROSSBEAM 170-21769-405, Y= 4, Z= -19.29 HAS CORROSION. REPAIRED IAW EO E175-53 MR-203 REV IR. THIS EO IS ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH PERMANENT REPAIR OF CORROSION DAMAGE IAW ETD 2015-170-071373. BECAUSE THIS IS PSE & FCS, THIS HAS BEEN CLASSIFIED AS A MAJOR REPAIR.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN, RT FLOOR TRACK PN 170-03263-001, BETWEEN FRAME 17 & 13, Z= -19.29 HAS CORROSION IN SEVERAL AREAS. R & R RT SEAT TRACK IAW SRM 51-41-02 & EO E175-53MR-062 REV 5 WO 1939698.

Part: RETAINER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

AFT INTERIOR FUSELAGE WASTE CUT OUT DOOR STRUCTURE RETAINERS HAS CORROSION, BETWEEN STATION 22270.0 & 22680.0 & STRINGER 26R. REMOVED & DISCARDED WASTE PAN RETAINERS 170-86654-003 & 170-86655-003 IAW EO-E175X-5300-004.2 WO 1938853.

Part: CROSSBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN FRAME 14, CROSSBEAM PN 170-21766-409, BETWEEN Y=13 - Y=36 HAS CORROSION. REPAIRED IAW EO-E175-53 MR-202 REV 1 WO 1941725. THIS EO IS ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH PERMANENT REPAIR OF CORROSION DAMAGE TO THE CROSSBEAM UPPER FLANGE, IAW ETD 2015-170-071303A. BECAUSE THIS IS PSE & FCS, ACCOMPLISHMENT HAS BEEN CLASSIFIED A MAJOR REPAIR.

Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

AFT MAIN CABIN, CTR SHEAR PANEL PN 170-65928-001, BETWEEN FRAME 87 & 88 FROM Y=-11 - Y=11, Z=-19.29. REPLACED CTR SHEAR PANEL IAW SRM 51-41-02 & EO E175-5300-119 REV IR WO 1941393.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN, LT FLOOR TRACK PN 170-03264-001, BETWEEN FRAME 16 & 19, Y= -11, Z= -19.29 HAS CORROSION IN SEVERAL AREAS. R & R LT SEAT TRACK IAW SRM 51-41-02 & EO E175-53MR-061 REV 5 WO 1939696.

Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

AFT MAIN CABIN, RT SHEAR PANEL PN 170-91919-001, BETWEEN FRAME 87 & 88 FROM Y=11 - Y=41, Z=19.29 HAS CORROSION. REPLACED RT SHEAR PANEL IAW SRM 51-42-01, 51-43-01 & EO E175-5300-119 REV IR WO 1941393.

Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,472 hrs · 12,350 cycles

FORWARD MAIN CABIN, RT FLOOR SILL PN 170-05661-003, BETWEEN FRAME 17 & 20 FROM Y=31 - Y=38, Z=19.29. R & R RT FLOOR SILL IAW SRM 51-41-02 & EO E175-5300-118 REV IR WO 1941779.

Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 21,472 hrs · 12,350 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF CORROSION DAMAGE TO THE CROSSBEAM FRAME 17, UPPER FLANGE LOCATED BETWEEN Y=15 & Y=42.7, OTBD OF TRACK Y=11. REFERENCE ETD2015-170-073605B & FIGURES 1 & 2. THE APPROX DAMAGE DIMENSIONS ARE AS FOLLOWS, 27.50 INCHES X .90 INCH WITH 100% EXFOLIATION. VT-SAA REQUESTED & RECEIVED A REPAIR IN THE FORM OF ETD2015-170-073605B FOR THE ACCOMPLISHMENT OF THE REPAIR ANGLE APPROVAL. BECAUSE THE FLOOR CROSSBEAM FRAME 17 IS PSE & FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR.L FOLLOW UP INSPECTIONS WILL BE ACCOMPLISHED ON EO E175-53MR-205.1 IAW ANAC DER FORM ATTACHED. REF TASK 53-10-027-0001, INTERNAL GVI THRESHOLD OF 25,202 FC, INTERVAL OF 25,202FC IS SUFFICIENT & IS MET USING THE INSPECTION REQUIREMENTS, MPG & MRBR REVISION 10. THRESHOLD IS COUNTED SINCE NEW. ACCOMPLISHMENT OF THIS MAJOR REPAIR WAS ON EO E175-53MR-205 UNDER WO 1943967.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,472 hrs · 12,350 cycles

DURING BASIC CHECK, INSPECTION DISCOVERED CORROSION DAMAGE ON THE CABIN SEAT TRACKS PN 170-27305-003 & 170-67861-005. PERMANENT REPAIRS BY REPLACEMENT IS ACCOMPLISHED IAW DWG LISTED IN TABLE 2 & SRM CHAPTER 51 PRINCIPLES, REF ATTACHED FIGURES IDENTIFYING THE GOUGE DAMAGE LOCATIONS & DIMENSIONS 2.9 INCHES X .80 INCH X .011 INCH, .9 INCH X .40 INCH X .013 INCH, 1.4 INCHES X .35 INCH X .011 INCH & 1.4 INCHES X .35 X .002 INCH. SINCE THE TRACK IS BEING REPLACED WITH LIKE PARTS, NO CHANGES TO THE INSPECTIONS IN THE EXISTING MX PROGRAM ARE REQUIRED. ENGINEERING HAS CLASSIFIED THIS REPAIR AS A MAJOR REPAIR. ALSO SUBMITTED SDR C77A20150806002 FOR PN 170-27305-003. ACCOMPLISHMENT OF THIS MAJOR REPAIR IS ON EO E175-53MR-204 UNDER WO 1942406.

Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 21,472 hrs · 12,350 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF CORROSION DAMAGE TO THE CROSSBEAM FRAME 17 UPPER FLANGE, REF ETD2015-170-071373, & FIGURES FOR DAMAGE DIMENSIONS & LOCATIONS, 3.0 INCHES X .50 INCH X .095 INCH. REQUESTED & RECEIVED A REPAIR IN THE FORM OF ETD2015-170-071373 FOR THE ACCOMPLISHMENT OF THE REPAIR ANGLE APPROVAL. THE FLOOR CROSSBEAM FRAME 17 IS PSE & FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. FOLLOW UP INSPECTIONS WILL BE ACCOMPLISHED ON EO E175-53MR-203.1 IAW ANAC DER FORM ATTACHED. REF TASK 53-10-027-0001, INTERNAL GVI THRESHOLD OF 25,202 FC, INTERVAL OF 25,202FC, IS SUFFICIENT & IS MET USING THE INSPECTION REQUIREMENTS, MPG & MRBR REVISION 10. THRESHOLD IS COUNTED SINCE NEW. ACCOMPLISHMENT OF THIS MAJOR REPAIR WAS ON EO E175-53MR-203 UNDER WO 1942236.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,472 hrs · 12,350 cycles

DURING BASIC CHECK, INSPECTION DISCOVERED CORROSION DAMAGE ON THE CABIN SEAT TRACKS PN 170-27305-003 & 170-67861-005. PERMANENT REPAIRS BY REPLACEMENT IS ACCOMPLISHED IAW DWG LISTED IN TABLE 2 & SRM CHAPTER 51 PRINCIPLES, REF ATTACHED FIGURES IDENTIFYING THE GOUGE DAMAGE LOCATIONS & DIMENSIONS 2.9 INCHES X .80 INCH X .011 INCH, .9 INCH X .40 INCH X .013 INCH, 1.4 INCHES X .35 INCH X .011 INCH & 1.4 INCHES X .35 X .002 INCH. SINCE THE TRACK IS BEING REPLACED WITH LIKE PARTS, NO CHANGES TO THE INSPECTIONS IN THE EXISTING MX PROGRAM ARE REQUIRED. ENGINEERING HAS CLASSIFIED THIS REPAIR AS A MAJOR REPAIR. ALSO SUBMITTED SDR C77A20150806002 FOR PN 170-27305-003. ACCOMPLISHMENT OF THIS MAJOR REPAIR IS ON EO E175-53MR-204 UNDER WO 1942406.

Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 21,472 hrs · 12,350 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF CORROSION DAMAGE TO THE CROSSBEAM FRAME 14 UPPER FLANGE, REF ETD2015-170-071303A, & FIGURES FOR DAMAGE DIMENSIONS & LOCATIONS, 35 INCHES X .70 INCH TO A MAXIMUM DEPTH OF .047 INCH DEEP, 6.30 INCHES X .90 INCH TO A MAXIMUM DEPTH OF .047 INCH DEEP & 1.35 INCHES X .80 WITH 100% MATERIAL LOSS CUT-OUT. REQUESTED & RECEIVED A REPAIR IN THE FORM OF ETD2015-170-071303A FOR THE ACCOMPLISHMENT OF THE CROSSBEAM FRAME 14 REPAIR ANGLE APPROVAL. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. FOLLOW UP INSPECTIONS WILL BE ACCOMPLISHED ON EO E175-53MR-202.1 IAW ANAC DER FORM ATTACHED. REFERENCE TASK 53-10-027-0001, INTERNAL GVI THRESHOLD OF 25,202FC, INTERVAL OF 25,202FC IS SUFFICIENT & IS MET USING THE INSPECTION REQUIREMENTS, MPG & MRBR REVISION 10. THRESHOLD IS COUNTED SINCE NEW. ACCOMPLISHMENT OF THIS MAJOR REPAIR IS ON EO E175-53MR-202 UNDER WO 1941725.

Part: FLOOR SUPPORT — CORRODED (FRAME 87) · corrosion level 2 · airframe 21,421 hrs · 12,244 cycles

AFT CABIN FLOOR SUPPORT HAS CORROSION AT FRAME 87 Y 29, X 23865 Y 737. R & R THE FLOOR SUPPORT IAW SRM 51-41-01 & 51-43-01.

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 20,451 hrs · 11,731 cycles

L2 FLIGHT ATTENDANT FLASHLIGHT INOPERATIVE. DEFERRED IAW MEL 25-62-07-1. TRANSFERRED TO SDI. PLACARD INSTALLED. OK FOR SERVICE. MEL APPLIED, MEL 25-62-07-1 CAT C. L2 FLIGHT ATTENDANT FLASHLIGHT INOPERATIVE. R & R L2 FLASHLIGHT BATTERY IAW AMM 33-51-01. OPERATIONS CHECKED GOOD. THIS CLEARS DM1880536. PLACARD SDI SIGNED, MXC NOTIFIED. ACFT OK FOR SERVICE.

Part: SEAL — WORN (THRUST REVERSER) · airframe 15,808 hrs · 9,019 cycles

LEFT ENGINE INBD THRUST REVERSER LOWER DRAIN MAST SEAL IS TORN. REPLACED LOWER SEALS BY INCORPORATION OF SB 78-0050 R01 IAW EO E17X-7800-002.2, REV IR.

Part: UPPER SHEET — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION ON LT UPPER SHEET, BETWEEN FR 85 & FR 86. R & R LT UPPER SHEET IAW SRM 51-41-01 AND 51-43-01.

Part: WIRE — DAMAGED (ZONE 100) · airframe 15,808 hrs · 9,019 cycles

EVIDENCE OF ARCING ON AFT RT CENTER OF LICC, FROM CONTACT WITH WIRE W120-01391-20. REPAIRED DAMAGED WIRES W120-01391-20, W120-00975-24W, W120-00975-24BL, W120-00975-240R, W120-01456-24, W120-01392-20 IAW STANDARD WIRING PRACTICES MANUAL 20-41-20.

Part: SEAL DEPRESSOR — CORRODED (CARGO DOORWAY) · airframe 15,808 hrs · 9,019 cycles

FORWARD CARGO DOOR CUTOUT STRUCTURE CENTER SEAL DEPRESSOR, PN 170-66804-401, HAS CORROSION AT X=7120-7675 Y=450. R & R CENTER SEAL DEPRESSOR IAW SRM 51-41-01 AND 51-43-01.

Part: FLAP TRACK — WORN (LT WING TE FLAPS) · airframe 15,808 hrs · 9,019 cycles

LEFT WING INBD FLAP, NR 2 OTBD TRACK, WORN OUT OF LIMITS THICKNESS REDUCTION D=.015" IAW SRM 57-52-03. BLENDED WORN AREA IAW SRM PART II 51-10-03.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION WAS FOUND ON LT FLOORBEAM SPLICE PLATE AT FR 87 X=23850 Y= -273. R & R LT FLOORBEAM SPLICE IAW SRM 51-41-01 AND 51-43-01.

Part: FINGER DOUBLER — CORRODED (ZONE 100) · airframe 15,808 hrs · 9,019 cycles

FWD CARGO DOOR CUTOUT STRUCTURE FWD FINGER DOUBLER HAS CORROSION AT X= 6820-7150, Y=290-300. R & R FWD FINGER DOUBLER IAW SRM 51-41-01 AND 51-43-01.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION ON RT FLOORBEAM, AT FR 87 X= 23850 Y=273. R & R FLOORBEAM IAW SRM 51-41-01 AND 51-43-01.

Part: NUT — LOOSE (PYLON ATTACH) · airframe 15,808 hrs · 9,019 cycles

LOW TORQUE INDICATED ON LT PYLON OTBD AFT ATTACH BOLT. REMOVED CASTELLATED NUT, RETORQUED AND SAFETIED IAW EO E17X-5400-001, REV IR.

Part: UPPER SHEET — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

RT UPPER SHEET , IS CORRODED ALONG THE TOP SURFACE. R & R RT UPPER SHEET IAW SRM 51-41-01 AND 51-43-01.

Part: LUG — GOUGED (NLG ACTUATOR) · airframe 15,808 hrs · 9,019 cycles

NLG HAS GOUGE ON INBD RETRACT ACTUATOR LUG ON INSIDE BUSHING FLANGE BLENDED DAMAGE SMOOTH IAW SRM 51-10-03 & 51-12-01.

Part: BUSHING — MIGRATED (NLG ACTUATOR) · airframe 15,808 hrs · 9,019 cycles

NLG RETRACT ACTUATOR LWR INBD BUSHING IS MIGRATED. REPLACED NLG RETRACT ACTUATOR FITTING BUSHINGS IAW ED-LLI-10-0008 AND EO E17X-3200-007, REV IR.

Part: NUT — LOOSE (PYLON ATTACH) · airframe 15,808 hrs · 9,019 cycles

LOW TORQUE INDICATED ON LT PYLON INBD-AFT PYLON ATTACH BOLT BY LOOSE WASHER AT PYLON LOWER LINK FITTING. REMOVED CASTELLATED NUT, RETORQUED AND SAFETIED IAW EO E17X-5400-001, REV IR.

Part: SEAL — WORN (THRUST REVERSER) · airframe 15,808 hrs · 9,019 cycles

LT ENGINE INBD THRUST REVERSER FRONT 12 O'CLOCK PLATFORM SEAL IS TORN. REPLACED UPPER SEALS ON WO 736585-411 BY INCORPORATION OF SB 78-0055 R01 IAW EO E17X-7800-001.2, REV 3.

Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

LEFT SHEAR PANEL IS CORRODED ALONG THE FWD RIVET LINE. X=23865.0, Y= -304.8 - 1041.4. R & R LT SHEAR PANEL IAW SRM 51-41-01 AND 51-43-01.

Part: FINGER DOUBLER — CORRODED (ZONE 100) · airframe 15,808 hrs · 9,019 cycles

FORWARD CARGO DOOR CUTOUT STRUCTURE AFT FINGER DOUBLER HAS CORROSION AT X= 7505-7685 Y= 280-390. R & R AFT FINGER DOUBLER IAW SRM 51-41-01 AND 51-43-01.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION ON LT FLOOR SUPPORT, AT OF FR 88 TO FR 90 X=24028 - 24866 , Y= -635. R & R LT FLOOR SUPPORT IAW SRM 51-41-01 AND 51-43-01.

Part: SEAL — WORN (THRUST REVERSER) · airframe 15,808 hrs · 9,019 cycles

LEFT ENGINE INBD THRUST REVERSER FRONT 12 O'CLOCK CORE COWL SEAL IS TORN. REPLACED UPPER SEALS BY INCORPORATION OF SB 78-0055 R01 IAW EO E17X-7800-001.2, REV 3.

Part: FLAP TRACK — WORN (RT WING TE FLAP) · airframe 15,808 hrs · 9,019 cycles

RT WING INBD FLAP, NR 2A OTBD TRACK, WORN OUT OF LIMITS THICKNESS REDUCTION D=.014" IAW SRM 57-52-03. BLENDED WORN AREA IAW SRM PART II 51-10-03.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION ON FLOORBEAM AT FR 87 X=23850, Y=273. R & R FLOORBEAM IAW SRM 51-41-01 AND 51-43-01.

Part: SKIN — CHAFED (LT NACELLE) · airframe 15,808 hrs · 9,019 cycles

LT PYLON INBD FACE HAS A CHAFE AT THE LOWER FWD CORNER OF THE AFT CUT OUT. BLENDED DAMAGE SMOOTH IAW SRM II 51-10-03.

Part: FIREWALL — CRACKED (APU BAY) · airframe 15,808 hrs · 9,019 cycles

APU FIREWALL 351BZ, HAS TWO CRACKS IN THE RADIUS AT BOTH ENDS. UPPER CRACK IS 0.400" AND LWR CRACK IS 0.500" X=28868.0. BOTH CRACKS ROUTED OUT AND NDT PERFORMED VERIFYING NO MORE CRACKING EXISTS IAW ETD 2013-170-027936 AND EA E175-53-372, REV IR.

Part: GUSSET — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION ON RT INBD GUSSET AT FR 90 X=24867, Y= 273 . R & R GUSSET IAW SRM 51-41-01 AND 51-43-01.

Part: GUSSET — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION ON RT OTBD GUSSET, AT FR 90 X=24740 Y=508. R & R RT OTBD GUSSET IAW SRM 51-41-01 AND 51-43-01.

Part: PANEL — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

RT SHEAR PANEL IS CORRODED ALONG THE FWD RIVET LINE. R & R RT SHEAR PANEL IAW SRM 51-41-01 AND 51-43-01.

Part: SPLICE PLATE — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION ON RT SPLICE PLATE AT FR 89 X=24435, Y=273. R & R SPLICE PLATE IAW SRM 51-41-01 AND 51-43-01.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CORROSION ON RT FLOOR SUPPORT AT FR 88 TO FR 90 X=24028 TO X=24866, Y=635. R & R FLOOR SUPPORT IAW SRM 51-41-01 AND 51-43-01.

Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

CENTER SHEAR PANEL, IS CORRODED ALONG THE FWD RIVET LINE. X=23865.0, Y= -222.3 - 222.3. R & R CENTER SHEAR PANEL IAW SRM 51-41-01 AND 51-43-01.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 15,808 hrs · 9,019 cycles

FLOOR SUPPORT FROM FRAME 89 TO 90 HAS CORROSION AT X=24434 TO 24867, Y=-273. REMOVED CORROSION IAW SRM 51-10-03 & 51-12-01 IAW ETD 2013-170-028346 AND EO E175-53MR-144, REV 1.

Part: THRESHOLD — CORRODED (ZONE 100) · airframe 15,808 hrs · 9,019 cycles

FWD CARGO DOOR CUTOUT STRUCTURE HORIZONTAL BEAM HAS CORROSION AT X=7200- 7625 Y= 390. R & R THRESHOLD BEAM IAW SRM 51-41-01 AND 51-43-01.

Part: SEAT TRACK — CORRODED (ZONE 100) · airframe 15,808 hrs · 9,019 cycles

CORROSION DAMAGE TO THE AFT CABIN FLOOR STRUCTURE RT AFT SEAT TRACK, AT FR84. THE NOMINAL THICKNESS OF THE FLANGE IS 0.080". THE CORROSION DAMAGE WAS BLENDED OUT.

Part: SKIN — CRACKED (ZONE 600) · airframe 15,808 hrs · 9,019 cycles

ONE CRACK WAS FOUND IN THE CRITICAL FASTENER HOLE ON THE RT SIDE AFTER IT HAD BEEN ENLARGED TO 8MM (.314") DIAMETER IAW THE SB. ACCOMPLISHED MAJOR REPAIR IAW EO E17X-57MA-004.7

Part: FLOORBEAM — DAMAGED (ZONE 100) · airframe 15,808 hrs · 9,019 cycles

FASTENER HOLE ELONGATED ON CROSSBEAM AT FRAME 89.

Part: BATTERY PACK — DISCHARGED (ZONE 200) · airframe 8,294 hrs · 4,813 cycles

COCKPIT EMERGENCY LIGHT INOP. R & R BATTERY ELPU FOR COCKPIT LIGHT, OPS CH OK IAW AMM 33-50-01.

Part: COFFEEMAKER — FAILED (AFT GALLEY) · airframe 7,140 hrs · 4,139 cycles

DURING CRUISE, DECLARED AN EMERGENCY AND DIVERTED DUE TO A REPORT OF SMOKE IN THE AFT CABIN AREA. WHILE STILL IN FLIGHT, THE F/A DETERMINED THE SMOKE WAS COMING FROM THE AFT INBD COFFEEMAKER AND TURNED THE COFFEEMAKER TO OFF. THE SMOKE DISSIPATED. THE ACFT LANDED SAFELY. MX WAS DISPATCHED TO THE ACFT AND THEY PROCEEDED TO REMOVE BOTH INBD AND OTBD COFFEEMAKERS TO INSPECT POWER RECEPTACLES AND LINES. FOUND NO DAMAGE OR DEFECTS. THE COFFEEMAKERS WERE REINSTALLED AND THE FAULTY INBD COFFEEMAKER'S CIRCUIT BREAKER WAS PULLED AND COLLARD TO ISOLATE ELECTRICAL POWER. THE COFFEEMAKER WAS PLACED ON MEL 25-20-07-1-N WITH EA TO PULL AND COLLAR ASSOCIATED CIRCUIT BREAKER. THE ACFT WAS RETURNED TO SERVICE. REF W/O 292168.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 5,773 hrs · 3,345 cycles

EMERGENCY LIGHT BATTERY FAULTY.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 5,339 hrs · 3,094 cycles

DURING BASIC CHECK INSPECTION MX VISIT, CORROSION WAS FOUND ON RT FLOOR TRACK PN 170-03263-001 FROM FR14 TO FR 17 AT BL 273R. TEMPORARY REPAIR WAS MADE REF ETD 2009-170/09173A AND COMPASS EO E175-53MR-018. PERMANENT REPAIR TO BE MADE AT NEXT BASIC CHECK WITH REPLACEMENT OF FLOOR TRACK PN 170-03263-001.