N622CZ
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| Compass Airlines, LLC | Operator | on 2014-10-22 | Operator named in NTSB report |
Accident & incident history
Operated by Compass Airlines (per NTSB report)
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
130 reports on file, 2010-03-28 – 2020-01-23.
Part: SHEAR TIE — CORRODED (ZONE 100) · airframe 31,550 hrs · 19,537 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 OF THE FOLLOWING AFT CARGO SHEAR CLIPS: P/N 170-66350-002 FR77 SHEAR CLIP BY BLEND OUT AND P/N 170-66531-001 FR 88 SHEAR CLIP BY PART REPLACEMENT. REFERENCE ETD2020-170-000366 AND FIGURE 1 FOR DAMAGE LOCATIONS AND DETAILS RESPECTIVELY. 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. WORK ORDER 2817029
Part: DOUBLER — CORRODED (FRAMES 86-87) · airframe 31,550 hrs · 19,537 cycles
CORROSION ON INTERNAL SIDE OF CUTOUT AFT HOT WATER DRAIN MAST BETWEEN FR 86-87 AND STGR-28R-27R X= 923.34-939.5 Y=8 Z=61.3 WORK ORDER 2773581452
Part: SHEAR TIE — CORRODED (ZONE 100) · airframe 31,550 hrs · 19,537 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 OF THE FOLLOWING AFT CARGO SHEAR CLIPS: P/N 170-66350-002 FR77 SHEAR CLIP BY BLEND OUT AND P/N 170-66531-001 FR 88 SHEAR CLIP BY PART REPLACEMENT. REFERENCE ETD2020-170-000366 AND FIGURE 1 FOR DAMAGE LOCATIONS AND DETAILS RESPECTIVELY. 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. WORK ORDER 2817029
Part: SKIN — GOUGED (LT WING) · airframe 31,561 hrs · 19,537 cycles
DURING BASIC CHECK IN BNA, GOUGE DAMAGE WAS DISCOVERED ON THE LH WING LEADING EDGE SKIN OUTBOARD OF RIB 40. REFERENCE ETD2020-170-000683-A FIGURE 1 FOR DAMAGE LOCATION AND DETAILS. EAMS REQUESTED AND RECEIVED PERMANENT REPAIR DISPOSITION IN THE FORM OF ETD2020-170-000683-A. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF THE GOUGE DAMAGE LOCATED ON THE P/N 170-31037-021 LEADING EDGE SKIN OUTBOARD OF RIB 40 ON THE LH WING. THE DAMAGE WILL BE REPAIRED BY CUT-OUT AND INTERNAL DOUBLER INSTALLATION PER ETD2020-170-000683-A. BECAUSE THE LH WING LE SKIN IS A PSE AND THIS REPAIR IS RESTORING STRENGTH, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. EO E175-57MR-019
Part: SKIN — FRACTURED (RT WING TE FLAP) · airframe 31,561 hrs · 19,537 cycles
DURING BASIC CHECK IN BNA, DAMAGE WAS SUSTAINED ON THE RH WING IB AFT FLAP DURING A MAINTENANCE CHECK. SOME FIBER LAYERS OF THE SKIN AT THE OUTBOARD TRAILING EDGE WERE FRACTURED ON BOTH SIDES AT A LENGTH OF APPROXIMATELY 5 INCHES, AND AN EDGE OF THE SKIN WAS FRACTURED AT A LENGTH OF APPROXIMATELY 1 INCH. REFERENCE ETD2020-170-001701A FIGURE 1 FOR DAMAGE LOCATION AND DETAILS. ADDITIONALLY, THE COMPOSITE SKIN STIFFENER IN THE AREA (P/N 170-39180-002) WAS DAMAGED AND WILL BE REPLACED. EAMS REQUESTED AND RECEIVED PERMANENT REPAIR APPROVAL IN THE FORM OF ETD2020-170-001701A AND ITS CORRESPONDING ANAC DER FORM. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF THE UPPER SKIN (P/N 170-39148-408) ON THE RH WING IB AFT FLAP BY REMOVING THE DAMAGED MATERIAL AND ACCOMPLISHING A COMPOSITE REPAIR OF THE SOLID LAMINATE PER ETD2020-170-001701A. BECAUSE THE RH WING IB AFT FLAP UPPER SKIN IS A PSE AND THIS REPAIR IS RESTORING STRENGTH, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. PER ETD2020-170-001701A, FOLLOW-ON INSPECTIONS OF THIS REPAIR ARE NOT REQUIRED. EO E175-57MR-020
Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 31,550 hrs · 19,537 cycles
THIS EO PROVIDES INSTRUCTIONS TO COMPLY WITH THE INSTRUCTIONS THAT ARE SPECIFIC TO THE RH HORIZONTAL STABILIZER FROM SB 170-55-0014, WHICH ACCOMPLISHES A STRUCTURAL MODIFICATION THAT CONSISTS OF REPLACING HORIZONTAL STABILIZER RIBS 10A, 11A, AND 12A WITH NEW, REINFORCED RIBS. THIS MODIFICATION IS DESIGNED TO HELP PREVENT POSSIBLE CRACKS ON THE HORIZONTAL STABILIZER CENTER BOX RIBS AND TO REACH THE AIRCRAFT ECONOMICAL FATIGUE LIFE. COMPASS ENGINEERING HAS CLASSIFIED THIS MODIFICATION AS A MAJOR ALTERATION. ONE OR MORE OF THE RIBS THAT ARE BEING REPLACED AS PART OF THE SERVICE BULLETIN WERE FOUND CRACKED DURING AN INSPECTION WHILE AT BASIC CHECK. BY ACCOMPLISHING SB 170-55-0014, THIS EO ALSO PROVIDES A REPAIR BY REPLACEMENT OF THE AFFECTED RIB(S). COMPASS ENGINEERING HAS CLASSIFIED THIS REPAIR AS A MAJOR REPAIR. THIS EO IS BEING MADE EFFECTIVE TO ALL DELTA AIRCRAFT FOR WHICH SB 170-55-0014 IS APPLICABLE, BUT A MAXIMO EVENT WILL ONLY BE GENERATED FOR AN AIRCRAFT WHEN ONE OR MORE RIBS ARE FOUND CRACKED. THE ACCOMPLISHMENT INSTRUCTIONS OF THIS EO WERE DERIVED FROM EMBRAER SERVICE BULLETIN 170-55-0014; THEREFORE, A COPY OF THIS SB IS NOT NEEDED TO ACCOMPLISH THIS EO. WORK ORDER 2813915
Part: DOUBLER — CORRODED (COCKPIT FLOOR) · airframe 31,561 hrs · 19,537 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 ETD2020-170-000798-A 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 ETD2020-170-000798-A. 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. EO E175-53MR-482 IS BEING ACCOMPLISHED BY WO 2817686
Part: STRINGER — CORRODED (FRAMES 89-90) · airframe 31,561 hrs · 19,537 cycles
DURING BASIC CHECK AT EAMS, CORROSION WAS DISCOVERED ON THE CENTER FUSELAGE III STRINGER 21R BETWEEN FR89/FR90 (P/N 170-65257-001) DURING INSPECTION IN THE AREA. REFERENCE ETD2020-170-000573-B FIGURE 1 FOR DETAILS AND LOCATIONS. EAMS REQUESTED REPAIR DISPOSITION FROM RTS, WHO PROVIDED ETD2020-170-000573-B TO ALLOW THE INSTRUCTIONS FROM SRM II 53-22-03/ REPAIR 02P, WHICH IS APPLICABLE TO THE CENTER FUSELAGE II, TO BE USED FOR THIS STRINGER IN A DIFFERENT FUSELAGE SECTION. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A PERMANENT REPAIR OF DAMAGE TO THE STRINGER 21R BY SPLICING IN A NEW SECTION OF STRINGER PER SRM PART II 53-22-03/REPAIR 02. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR BECAUSE THE STRINGER 21R IS PSE AND THIS EO RESTORES STRENGTH. EO E175-53MR-481 IS BEING ACCOMPLISHED BY WO 2817685
Part: STRINGER — CORRODED (FRAMES 87-90) · airframe 31,561 hrs · 19,537 cycles
DURING BASIC CHECK AT EAMS, CORROSION WAS DISCOVERED ON THE CENTER FUSELAGE III STRINGER 21L BETWEEN FR87/FR90 (P/N 170-91898-003) DURING INSPECTION IN THE AREA. REFERENCE ETD2020-170-000574-A FIGURE 1 FOR DETAILS AND LOCATIONS. EAMS REQUESTED REPAIR DISPOSITION FROM RTS, WHO PROVIDED ETD2020-170-000574-A TO ALLOW THE INSTRUCTIONS FROM SRM II 53-22-03/ REPAIR 02P, WHICH IS APPLICABLE TO THE CENTER FUSELAGE II, TO BE USED FOR THIS STRINGER IN A DIFFERENT FUSELAGE SECTION. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A PERMANENT REPAIR OF DAMAGE TO THE STRINGER 21L BY SPLICING IN A NEW SECTION OF STRINGER PER SRM PART II 53-22-03/REPAIR 02. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR BECAUSE THE STRINGER 21L IS PSE AND THIS EO RESTORES STRENGTH. EO E175-53MR-480 IS BEING ACCOMPLISHED BY WO 2817684
Part: DOOR FRAME — CORRODED (FWD CARGO) · corrosion level 2 · airframe 31,550 hrs · 19,537 cycles
THIS EO PROVIDES INSTRUCTIONS TO COMPLY WITH PART I OF SB 170-53-0118, WHICH ACCOMPLISHES A MODIFICATION ON THE FORWARD CARGO DOOR SURROUNDING STRUCTURE. THIS MODIFICATION CONSISTS OF APPLYING CIC TO FASTENERS AND SURROUNDING STRUCTURE, APPLYING POLYURETHANE PROTECTIVE TAPE ON THE DOUBLERS AND SUPPORTS OF THE FORWARD CARGO DOOR, AND APPLYING FAYING AND FILLET SEALANT AROUND THE CLOSING PLATE AND SURROUNDING STRUCTURE. THESE MODIFICATIONS ARE TO PREVENT CORROSION OF THE SURROUNDING STRUCTURE PARTS OF THE FORWARD AND AFT CARGO DOORS. COMPASS ENGINEERING HAS CLASSIFIED THIS MODIFICATION AS A MINOR ALTERATION. THE ACCOMPLISHMENT INSTRUCTIONS OF THIS EO WERE DERIVED FROM EMBRAER SERVICE BULLETIN 170-53-0118; THEREFORE, A COPY OF THIS SB IS NOT NEEDED TO ACCOMPLISH THIS EO.
Part: SHEAR PANEL — CORRODED (ZONE 100) · airframe 31,550 hrs · 19,537 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 170-60259-001 FR90 GUSSET, P/N 170-60257-001 FR90 GUSSET, P/N 170-86125-001 FR89 RH SPLICE, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-65928-001 CENTER SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-92908-001 RH 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 AS A MINOR REPAIR.
Part: GUSSET — CORRODED (FRAME 90) · airframe 31,550 hrs · 19,537 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 170-60259-001 FR90 GUSSET, P/N 170-60257-001 FR90 GUSSET, P/N 170-86125-001 FR89 RH SPLICE, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-65928-001 CENTER SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-92908-001 RH 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 AS A MINOR REPAIR.
Part: GUSSET — CORRODED (FRAME 90) · airframe 31,550 hrs · 19,537 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 170-60259-001 FR90 GUSSET, P/N 170-60257-001 FR90 GUSSET, P/N 170-86125-001 FR89 RH SPLICE, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-65928-001 CENTER SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-92908-001 RH 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 AS A MINOR REPAIR.
Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,550 hrs · 19,537 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 170-60259-001 FR90 GUSSET, P/N 170-60257-001 FR90 GUSSET, P/N 170-86125-001 FR89 RH SPLICE, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-65928-001 CENTER SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-92908-001 RH 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 AS A MINOR REPAIR.
Part: SPLICE — CORRODED (ZONE 100) · airframe 31,550 hrs · 19,537 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 170-60259-001 FR90 GUSSET, P/N 170-60257-001 FR90 GUSSET, P/N 170-86125-001 FR89 RH SPLICE, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-65928-001 CENTER SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-92908-001 RH 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 AS A MINOR REPAIR.
Part: SHEAR PANEL — CORRODED (ZONE 100) · airframe 31,550 hrs · 19,537 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 170-60259-001 FR90 GUSSET, P/N 170-60257-001 FR90 GUSSET, P/N 170-86125-001 FR89 RH SPLICE, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-65928-001 CENTER SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-92908-001 RH 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 AS A MINOR REPAIR.
Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,550 hrs · 19,537 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 170-60259-001 FR90 GUSSET, P/N 170-60257-001 FR90 GUSSET, P/N 170-86125-001 FR89 RH SPLICE, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-65928-001 CENTER SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-92908-001 RH 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 AS A MINOR REPAIR.
Part: SHEAR PANEL — CORRODED (ZONE 100) · airframe 31,550 hrs · 19,537 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 170-60259-001 FR90 GUSSET, P/N 170-60257-001 FR90 GUSSET, P/N 170-86125-001 FR89 RH SPLICE, P/N 170-65927-007 LH SHEAR PANEL, P/N 170-65928-001 CENTER SHEAR PANEL, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-92908-001 RH 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 AS A MINOR REPAIR.
Part: CROSSBEAM — CORRODED (FRAME 84) · airframe 31,550 hrs · 19,537 cycles
THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF CORROSION DAMAGE DISCOVERED DURING BASIC CHECK AT EAMS ON THE UPPER FLANGE OF THE FR84 CROSSBEAM IN THE CABIN FLOOR STRUCTURE OF THE CENTER FUSELAGE III. REFER ETD2020-170-000189, FIGURE 1 FOR DAMAGE LOCATIONS AND MEASUREMENTS. EAMS REQUESTED AND RECEIVED ETD2020-170-000189 TO PERFORM A BLENDOUT AND DOUBLER REPAIR IN ACCORDANCE WITH THE PRINCIPLES OF SRM PART II 53-00-10/REPAIR 03P. BECAUSE THE FR84 FLOOR CROSSBEAM IS PSE/FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT REQUIRED PER ETD2020-170-000189. EO E175-53MR-479 IS BEING ACCOMPLISHED UNDER WO 2814642.
Part: STRUCTURE — CRACKED (LT WING LET) · airframe 31,550 hrs · 19,537 cycles
THIS EO PROVIDES INSTRUCTIONS TO COMPLY WITH SB 170-57-0072 PART I, WHICH ACCOMPLISHES A STRUCTURAL MODIFICATION THAT CONSISTS OF REPLACING THE CURRENT LH WING TIP SPAR 1 (P/N 171-16231-001 OR 171-16231-003) WITH A NEW, REDESIGNED SPAR 1 (P/N 171-22480-401), WHICH HAS IMPROVED THICKNESS AND RADIUS. THIS MODIFICATION IS TO IMPROVE THE FATIGUE LIFE OF THE ATTACHMENT BETWEEN SPARS 1 OF WING TIP AND WING STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS MODIFICATION AS A MAJOR ALTERATION. A PORTION OF THE MODIFICATION WILL TAKE PLACE OFF-WING ON THE REMOVED WING TIP (P/N 171-16240-4XX). THIS WILL BE DOCUMENTED BY COMPASS SHOP BUILD SPECIFICATION SBS-17X-5730-02. THE RETURNED WING TIP MAY BE REIDENTIFIED BY THE TIME IT RETURNS TO THE AIRFRAME (P/N 171-16240-6XX). PER 14 CFR § 121.703 AND THE COMPASS GMM, IT IS REQUIRED TO REPORT THE OCCURRENCE OR DETECTION OF FOLLOWING TO THE FAA: CRACKS, PERMANENT DEFORMATION, OR CORROSION OF AIRCRAFT STRUCTURES IF MORE THAN THE MAXIMUM ACCEPTABLE TO THE MANUFACTURER OR THE FAA. IF THE SPAR 1 THAT BEING REPLACED AS PART OF THE SERVICE BULLETIN WAS FOUND CRACKED DURING THE MODIFICATION, AN SDR IS REQUIRED TO BE SUBMITTED. THE ACCOMPLISHMENT INSTRUCTIONS OF THIS EO WERE DERIVED FROM EMBRAER SERVICE BULLETIN 170-57-0072; THEREFORE, A COPY OF THIS SB IS NOT NEEDED TO ACCOMPLISH THIS EO.
Earlier reports · 2010–2019 · 110 reports
2019
Part: RIB — GOUGED (HORIZONTAL STAB) · airframe 31,550 hrs · 19,537 cycles
DURING BASIC CHECK AT EAMS, TWO SMALL GOUGE DAMAGES O/B OF RIB 3 ON THE LH HORIZONTAL STABILIZER UPPER SKIN (P/N 170-62726-015). REFERENCE ETD2020-170-000754, FIGURE 1 FOR DETAILS, FOR THE DAMAGE LOCATION AND DIMENSION. EAMS REQUESTED & RECEIVED PERMANENT REPAIR DISPOSITION IN THE FORM OF ETD2020-170-000754, WHICH ALLOW THE AREAS TO BE BLENDED AND LEAVE AS-IS, PROVIDED NDT INSPECTION VERIFIES DAMAGE REMOVAL AND SURFACE PROTECTION IS RESTORED. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR. WORK ORDER 273581628
Part: FLASHLIGHT — INOPERATIVE (FWD CABIN) · airframe 31,087 hrs · 19,149 cycles
L1 FLASHLIGHT INOPERATIVE. REMOVED AND REPLACED IAW AMM 33-51-01. OK FOR SERVICE.
Part: LIFE VEST — TORN (CABIN) · airframe 30,850 hrs · 18,919 cycles
R1 FA LIFE VEST TORN. REMOVED AND REPLACED R1 FA LIFE VEST IAW SMPE 175-25-016. OK FOR SVC.
Part: SPAR — CRACKED (LT WING) · airframe 29,212 hrs · 17,559 cycles
FOUND CRACK IN LT WING SPAR II LOWER FLANGE AT HOLE A3. CRACK EXTENDED FROM HOLE A3 FORWARD TO EDGE OF LOWER FLANGE AND FROM HOLE A3 AFT TO AFT EDGE OF FLANGE AND APPROXIMATELY .25" UP THE WEB. SB 170-53-0053 PART III PREVENTIVE MODIFICATION HAD BEEN ACCOMPLISHED ON AIRCRAFT 12.953.59 FH AND 8,317 FC PRIOR TO THE DETECTION OF THE CRACK. CRACKED SECTION WAS CUTOUT AND A MAJOR REPAIR OF SPAR II WAS ACCOMPLISHED PER ENGINEERING ORDER E17X-57AD-004 AND ETD2018-170-132148.
2018
Part: FLAP TRACK — CORRODED (LT WING TE FLAP) · airframe 27,224 hrs · 15,923 cycles
CORROSION DAMAGE WAS DISCOVERED ON THE OUTBOARD FLAP TRACK FITTING ON THE LT INBD MAIN FLAP, AROUND A FASTENER HOLE FOR THE AFT FLAP TRACK RAILS. REPAIRED IAW ETD2018-170-016936A. MAJOR REPAIR.
Part: CROSSBEAM — CORRODED (FRAME 14) · airframe 27,224 hrs · 15,923 cycles
INSPECTION DISCOVERED THE FORWARD FRAME 14 CROSSBEAM, CORRODED. REPAIRED THE CROSSBEAM IAW DRAWING AND SRM.
2016
Part: FLASHLIGHT — INOPERATIVE (ZONE 200) · airframe 22,280 hrs · 12,716 cycles
LEFT AFT EMER FLASHLIGHT INOPERATIVE. R & R AFT LT FLASHLIGHT IAW 33-51-0. OK FOR SERVICE.
Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
FORWARD MAIN CABIN RT AFT FLOOR SILL, PN 170-05661-003, BETWEEN FRAME 17 - 20 & Y=+1060 - +1257, HAS CORROSION IN SEVERAL AREAS, X=5064 - 607. R & R FWD CABIN RT AFT FLOOR SILL IAW SRM 51-41-01 & 51-43-01 ON WO 19665301E3 IAW EO E175-5300-144 REV IR WO 2020529.
Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT MAIN CABIN FLOOR RT SHEAR PANEL, PN 170-91919-001, AT FRAME 87 - 88 & Y= +304 - +1041 HAS CORROSION, X=23865 - 24048. R & R AFT CABIN RT SHEAR PANEL IAW SRM 51-41-01 & 51-43-01 ON WO 19665312G8 IAW EO E175-5300-145 REV IR WO 2020539.
Part: RETAINER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
CENTER FUSELAGE III WASTE ACCESS DOOR CUT OUT IN INTERNAL RETAINERS, PN 170-86654-003 & 170-86655-003, HAS CORROSION BETWEEN STATIONS 24048 - 24458 & STRINGER 24R - 26R. PERMANENTLY REMOVED THE WASTE PAN RETAINERS ON WO 19665351F9 IAW EO E17X-5300-004.2 REV 1 WO 2016603.
Part: GUSSET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT MAIN CABIN FLOOR RT OTBD GUSSET, PN 170-60259-001, AT FRAME 90, Y=+457 - +698 HAS CORROSION, X=24868. R & R RT OTBD GUSSET IAW SRM 51-41-01 & 51-43-01 ON WO 19665312F5 IAW EO E175-5300-145 REV IR WO 2020539.
Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT MAIN CABIN FLOOR CTR SHEAR PANEL, PN 170-65928-001, AT FRAME 87 - 88 & Y= +222 TO -222 HAS CORROSION, X=23865 - 24048. R & R AFT CABIN CTR SHEAR PANEL IAW SRM 51-41-01 & 51-43-01 ON WO 19665312G6 IAW EO E175-5300-145 REV IR WO 2020539.
Part: GUSSET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT CABIN FLOOR RT INBD GUSSET, PN 170-60257-001, AT FRAME 90, Y=+260 HAS CORROSION X=24868. R & R RT INBD GUSSET IAW SRM 51-41-01 & 51-43-01 ON WO 19665312F2 IAW EO E175-5300-145 REV IR WO 2020539.
Part: SEAL DEPRESSOR — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT CARGO DOOR CUT OUT LOWER FWD CORNER REST, PN 170-85492-403, HAS CORROSION, X=20007 - 20242 & Y= STRINGER 26R - 27R. R & R AFT CARGO LOWER FWD SEAL DEPRESSOR IAW SRM 51-41-01 & 51-43-01 ON WO 14752411I9 IAW EO E175-53MR-108 REV 2 WO 527915.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
FORWARD MAIN CABIN CROSS FRAME 16 RT FLOOR PANEL SUPPORT, PN 170-04071-001 AT Y=+717 IS CORRODED, X=4711. R & R FWD CABIN CROSS FRAME 16 RT FLOOR PANEL SUPPORT IAW SRM 51-41-01 & 51-43-01 ON WO 19665301D5 IAW EO E175-5300-144 REV IR WO 2020529.
Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
FORWARD CABIN RT FWD FLOOR SILL, PN 170-05663-003, BETWEEN FRAME 12 - 14 & Y=+920 - +1244, HAS CORROSION IN SEVERAL AREAS, X=3679 - 4270. R & R FWD CABIN RT FWD FLOOR SILL IAW SRM 51-41-01 & 51-43-01 ON WO 19665301E1 IAW EO E175-5300-144 REV IR WO 2020529.
Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
FORWARD MAIN CABIN LT FWD FLOOR DOUBLER, PN 170-12118-001, AT FRAME 16 BETWEEN Y=-304 - -914 HAS CORROSION, X=4711. R & R LT FWD DOUBLER IAW SRM 51-41-01 & 51-43-01 ON WO 19665301D8 IAW EO E175-5300-144 REV IR WO 2020529.
Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
FORWARD MAIN CABIN LT AFT FLOOR DOUBLER, PN 170-07311-001, AT FRAME 19 Y=-635 HAS CORROSION, X=5645. R & R LT FWD DOUBLER IAW SRM 51-41-01 & 51-43-01 ON WO 19665301E5 IAW EO E175-5300-144 REV IR WO 2020529.
Part: PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT MAIN CABIN FLOOR LT SHEAR PANEL, PN 170-65927-007, AT FRAME 87 - 88 & Y= -304 - -1041 HAS CORROSION, X=23865 - 24048. R & R AFT CABIN LT SHEAR PANEL IAW SRM 51-41-01 & 51-43-01 ON WO 19665312G2 IAW EO E175-5300-145 REV IR WO 2020539.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
FORWARD MAIN CABIN CROSS FRAME 16 LT FLOOR SUPPORT, PN 170-13633-001, AT Y=-1140 HAS CORROSION, X=4711. R & R FWD CABIN CROSS FRAME 16 LT FLOOR PANEL SUPPORT IAW SRM 51-41-01 & 51-43-01 ON WO 19665301D7 IAW EO E175-5300-144 REV IR WO 2020529.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,853 hrs · 12,467 cycles
THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF CORROSION DAMAGE TO THE AFT CABIN FLOOR STRUCTURE RT AFT SEAT TRACK PN 170-86082-003 AT FRAME 84 & Y=+260. THE APPROX DAMAGE DIMENSIONS ARE AS FOLLOWS, 2.0 INCHES X 1.0 INCH TO A MAX DEPTH OF .020 INCH DEEP. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR DUE TO STRENGTH RESTORATION, WILL REQUIRE FOLLOW UP INSPECTIONS. EO E175-53MR-238.1 WILL BE ISSUED TO ACCOMPLISH THE FOLLOW UP INSPECTIONS IAW ANAC DER FORM ATTACHED. REF TASK 53-23-005-0001 INTERNAL GVI, THRESHOLD OF 20,483FC OR 27,242FH, INTERVAL OF 10,133 FC OR 11,124FH, IS SUFFICIENT & IS MET USING THE INSPECTION REQUIREMENTS, MPG & MRBR REVISION 11, THRESHOLD IS COUNTED SINCE NEW.
Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 21,853 hrs · 12,467 cycles
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, REF ETD2016-170-010421A FOR DAMAGE DIMENSIONS & LOCATIONS. REQUESTED & RECEIVED A REPAIR IN THE FORM OF ETD2016-170-010421A FOR THE ACCOMPLISHMENT OF THE CROSSBEAM FRAME 17 REPAIR ANGLE INSTALLATION. BECAUSE 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-239.1 IAW ANAC DER FORM ATTACHED. REF 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 11. EO E175-53MR-029 REV IR WAS ISSUED TO REPAIR DAMAGE FOUND ON THE CROSSBEAM BACK IN 2010. DURING THE CURRENT CHECK CORROSION DAMAGE WAS FOUND ON THE PRECIOUS REPAIR STRAP. THE DAMAGE WAS BLEND & ETD2016-170-010421A ALLOWS THE DAMAGE TO REMAIN AS IS. ACCOMPLISHMENT OF THIS REPAIR IS ON EO E175-53MR-239 UNDER WO -2022008.
Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 21,853 hrs · 12,467 cycles
THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A TEMPORARY REPAIR OF CORROSION DAMAGE TO THE CROSSBEAM FRAME 14 PN 170-21766-413 UPPER FLANGE, REF ETD2016-170-010422, & FIGURES FOR DAMAGE DIMENSIONS & LOCATIONS. REQUESTED & RECEIVED A TEMPORARY REPAIR IN THE FORM OF ETD2016-170-010422 FOR THE ACCOMPLISHMENT OF THE CROSSBEAM FRAME 14 REPAIR ANGLE INSTALLATION TO BE CARRIED TO NEXT BASIC CHECK. BECAUSE THE FLOOR CROSSBEAM FRAME 14 IS PSE & FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. ACCOMPLISHMENT OF THE PERMANENT REPAIR BY BEAM DIRECT REPLACEMENT WILL BE ACCOMPLISHED ON EO E175-53MR-240.1 DURING THE NEXT BASIC CHECK. ACCOMPLISHMENT OF THIS MAJOR REPAIR WAS ON EO E175-53MR-240 UNDER WO 2022042.
Part: DOUBLER — DENTED (FUSELAGE) · airframe 21,853 hrs · 12,467 cycles
DURING THE ACCOMPLISHMENT OF THE B4 BASIC CHECK, INSPECTION DISCOVERED DENT DAMAGE TO A PREVIOUSLY INSTALLED REPAIR DOUBLER LOCATED, BETWEEN FRAME 21 & 22, STRINGER 13L & 16L. THE DENT DAMAGE MEASURES 10.50 INCHES X 4.0 INCHES TO A MAX DEPTH OF .090 INCH DEEP. ALSO REPORTED TWO EACH DENTS ADJACENT TO THE REPAIR DOUBLER MEASURING 2.60 INCHES X 1.20 INCHES TO A MAX DEPTH OF .012 INCH DEEP & 2.20 INCHES X 1.40 INCHES TO A MAX DEPTH OF .016 INCH DEEP. THE REPAIR DOUBLER WAS INSTALLED ON EO E175-53MR-051 UNDER DISPOSITION ETD2010-170-08975. VT-SAA REMOVED THE DAMAGED REPAIR DOUBLER FOR DAMAGE MAPPING & EVALUATION. REQUESTED & RECEIVED A PERMANENT REPAIR IN THE FORM OF ETD2016-170-011418A. ENGINEERING HAS CLASSIFIED THIS REPAIR AS A MAJOR REPAIR. EO E175-53MR-051.1 REMAINS THE SAME FOR THE ACCOMPLISHMENT OF THE SUPPLEMENTAL FOLLOW UP INSPECTIONS REQUIRED BY ETD2016-170-011418A & ETD2010-170-08975. REF TASK 53-10-015-0002, EXTERNAL DET, THRESHOLD OF 26,129FC INTERVAL OF 9,750FC OR THRESHOLD OF 34,751FH INTERVAL OF 12,967FH, WHICHEVER OCCURS FIRST, IS SUFFICIENT & IS MET USING THE INSPECTION REQUIREMENTS, MPG & MRBR REVISION 11. THRESHOLD IS COUNTED SINCE NEW. ACCOMPLISHMENT OF THIS MAJOR REPAIR WAS ON EO E175-53MR-051.2 UNDER WO 2021319.
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT MAIN CABIN LT AFT FLOORBEAM, PN 170-65669-003, HAS CORROSION, X=23041 - 23453, Y= -260. R & R AFT CABIN LT FLOORBEAM IAW SRM 51-41-01 & 51-43-01 ON WO 19665312G4 IAW EO E175-53MR-093 REV 3 WO 2017644.
Part: SEAT TRACK — GOUGED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
RIGHT SIDE LATERAL SEAT TRACK 170-02056-008 GOUGED, BETWEEN FRAME 49 & 50, Y= +1066. R & R RT LATERAL SEAT TRACK FROM FRAME 34.5 - 59.5 IAW SRM 51-41-01 & 51-43-01 ON WO 14889502U3 IAW EO E175-53MR-196 REV IR WO 2018667.
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT MAIN CABIN FLOOR RT AFT FLOORBEAM, PN 170-65669-004, HAS CORROSION. X=23041 - 23453, Y= -260. R & R AFT CABIN RT FLOORBEAM IAW SRM 51-41-01 & 51-43-01 ON WO 119665312H4 IAW EO E175-53MR-094 REV 4 WO 2017467.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
FORWARD MAIN CABIN FLOOR RT SEAT TRACK, PN 170-03263-001, BETWEEN FRAMES 14 - 17, AT Y=+273 IS CORRODED IN SEVERAL AREAS. X=4270 - 5064 R & R FWD CABIN RT SEAT TRACK IAW SRM 51-41-01 & 51-43-01 ON WO 19665301E2 IAW EO E175-53MR-062 REV 5 WO 2017067.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
FORWARD MAIN CABIN FLOOR LT SEAT TRACK, PN 170-03264-001, BETWEEN FRAMES 19 - 20, AT Y=-273 HAS CORROSION. X=5645 - 6070 R & R FWD CABIN LT SEAT TRACK IAW SRM 51-41-01 & 51-43-01 ON WO 19665301E4 IAW EO E175-53MR-061 REV 5 WO 2017556.
Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 21,853 hrs · 12,467 cycles
THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIR OF CORROSION DAMAGE TO THE CROSSBEAM FRAME 16, PN 170-21768-407, UPPER FLANGE, REF ETD2016-170-009658 & FIG 1 FOR DAMAGE DIMENSIONS & LOCATIONS. VT-SAA REQUESTED & RECEIVED A REPAIR IN THE FORM OF ETD 2016-170-009658 FOR THE ACCOMPLISHMENT OF THE CROSSBEAM FRAME 16 REPAIR ANGLE INSTALLATION. BECAUSE THE FLOOR CROSSBEAM FRAME 16 IS PSE & FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. FOLLOW UP INSPECTIONS WILL BE ACCOMPLISHED ON EO E175-53MR-231.1 IAW ANAC DER FORM ATTACHED. REF TASK 53-10-027-0001, INTERNAL GVI, THRESHOLD OF 25,202 FC, INTERVAL OF 25,202 FC IS SUFFICIENT & IS MET USING THE INSPECTION REQUIREMENTS. MPG & MRBR REVISION 11. THRESHOLD IS COUNTED SINCE NEW. ACCOMPLISHMENT OF THIS MAJOR REPAIR WAS ON EO E175-53MR-231 UNDER WO 2020778.
Part: SEAL REST — CORRODED (FUSELAGE) · corrosion level 2 · airframe 21,853 hrs · 12,467 cycles
AFT CARGO DOOR CUT OUT LOWER CTR SEAL REST, PN 170-85251-401, HAS CORROSION. X= 20242 - 20951, Y= STRINGER 27R. R&R AFT CARGO LOWER CTR SEAL DEPRESSOR IAW SRM 51-41-01 & 51-43-01 ON WO 14752671J9 IAW EO E175-53MR-108 REV 2 WO 527915.
2015
Part: FLASHLIGHT — INOPERATIVE (CABIN) · airframe 20,692 hrs · 11,792 cycles
R1 DOOR FLASHLIGHT LED NOT BLINKING. R & R R1 DOOR FLASHLIGHT IAW AMM 33-51-01. OPERATIONS CHECKED GOOD. THIS CLEARS DM1952994 & PLACARD REMOVED. OK FOR SERVICE.
Part: TRANSMITTER — FAILED (ELT) · airframe 18,990 hrs · 10,799 cycles
ELT FAILED OPERATIONAL CHECK TASK CARD CPS-25-003 STEP 2, D, 1 B. DEFERRED IAW MEL 25-61-00-2. TRANSFERRED TO SDI AS DM 1547443. PLACARD INSTALLED, M ACTION COMPLIED WITH. OK FOR SERVICE.
2014
Part: SENSOR — FAILED (LE SLAT) · airframe 17,146 hrs · 9,748 cycles
DUE TO AN EICAS SLAT FAIL MSG & AS A PRECAUTIONARY MEASURE ONLY, THE CREW OF FLIGHT 5769 DTW TO DFW DECLARED AN EMERGENCY WITH ZFW UPON CROSSING INTO THEIR AIRSPACE. THE CREW ASKED FOR & WAS APPROVED FOR A LONG ROLL OUT UPON LANDING DFW, COMBINED WITH USING MORE THAN NORMAL REVERSE THRUST THE CREW KEPT BRAKE TEMPS NORMAL. THE ACFT SAFELY CLEARED THE RUNWAY & TAXIED TO THE GATE UNDER ITS OWN POWER. MX COMPLIED WITH FIM, R & R RT INBD T1 SLAT SKEW SENSOR IAW AMM, OPERATIONS CHECKED GOOD. MSG CLEARED & OK FOR SERVICE.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
RIGHT WING FLAP TRACK NR 1 INBD, PN 170-39310-003, WORN OUT OF LIMITS WIDTH REDUCTION W .003 INCHES IAW SRM 57-52-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-620 IAW ETD 2011-170 01072E & EA E175-57-184 2 REV IR WORK ORDER 906310.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
LEFT WING FLAP TRACK NR 2 OTBD, PN 170-39312-003, WORN OUT OF LIMITS WIDTH REDUCTION W .012 INCHES IAW SRM 57-52-03 TABLES 102 & THICKNESS REDUCTION D .020 INCHES IAW SRM 57-52-03 TABLES 101. BLENDED WORN AREAS IAW SRM PART II 51-10-03 ON WORK ORDER 737209-524 IAW ETD 2011-170 01072E & EA E175-57-184 1 REV IR WORK ORDER 906309.
Part: GUSSET — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR RT OTBD GUSSET, PN 170-60259-001 CORRODED X 24868.0, Y +482 TO +711. R & R RT OTBD GUSSET IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-240 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: PANEL — WORN (RT PYLON) · airframe 16,259 hrs · 9,242 cycles
FASTENER HOLE ON RT ENG PANEL 429LR IS WORN OVERSIZE. REAMED FASTENER HOLE BACK TO ROUND & INSTALLED NAS 1169C REPAIR WASHER IAW STANDARD PROCEDURES IN SRM 51-40-02 ON WORK ORDER 737209-474 IAW ETD 2014-170-004813 & EA E175-54-161 REV 1 WORK ORDER 915246.
Part: PANEL SUPPORT — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR RT PANEL SUPPORT, PN 170-86181-005 CORRODED X 24048.0 - 24868.0, Y +838. R & R RT PANEL SUPPORT IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-242 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: GUSSET — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR LT OTBD GUSSET, PN 170-60261-001 CORRODED X 24868.0 , Y 457 TO 508. R & R LT OTBD GUSSET IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-244 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
RIGHT WING FLAP TRACK NR 1 OTBD, PN 170-39310-004, WORN OUT OF LIMITS WIDTH REDUCTION W .005 INCHES IAW SRM 57-52-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-621 IAW ETD 2011-170 01072E & EA E175-57-184 2 REV IR WORK ORDER 906310.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
RIGHT WING FLAP TRACK NR 2 OTBD, PN 170-39312-004, WORN OUT OF LIMITS WIDTH REDUCTION W .010 INCHES IAW SRM 57-52-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-623 IAW ETD 2011-170 01072E & EA E175-57-184 2 REV IR WORK ORDER 906310.
Part: FLAP TRACK — WORN (ZONE 500) · airframe 16,259 hrs · 9,242 cycles
LEFT WING FLAP TRACK NR 1 INBD, WORN OUT OF LIMITS WIDTH REDUCTION W .003 INCHES IAW SRM 57-52-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
RIGHT WING FLAP TRACK NR 2 OTBD, PN 170-39312-004, WORN OUT OF LIMITS THICKNESS REDUCTION D .015 INCHES IAW SRM 57-52-03 TABLE 101. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-623 IAW ETD 2011-170 01072E & COMPASS EA E175-57-184 2 REV IR WORK ORDER 906310.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
LEFT WING FLAP TRACK NR 2 INBD, PN 170-39313-003, WORN OUT OF LIMITS WIDTH REDUCTION W .006 INCHES IAW SRM 57-52-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-523 IAW ETD 2011-170 01072E & EA E175-57-184 1 REV IR WORK ORDER 906309.
Part: UPPER SHEET — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR RT UPPER SHEET, PN 170-86101-001, HAS CORROSION AT X 23341 Y 273. R & R RT UPPER SHEET IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-217 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: GUSSET — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR LT INBD GUSSET, PN 170-60257-001 CORRODED X 24868.0, Y 254 TO 305. R & R LT INBD GUSSET IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-243 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
LEFT WING FLAP TRACK NR 3 OTBD, PN 170-39314-001 WORN OUT OF LIMITS WIDTH REDUCTION W .003 INCHES IAW SRM 57-55-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-528 IAW ETD 2011-170 01072E & EA E175-57-184 1 REV IR WORK ORDER 906309.
Part: PANEL — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR LT SHEAR PANEL, PN 170-65927-007, CORRODED X 23865.0, Y 330. R & R RT SHEAR PANEL IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-239 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: PANEL — WORN (LT PYLON) · airframe 16,259 hrs · 9,242 cycles
FASTENER HOLE ON LT ENG PYLON PANEL 419ML IS WORN OVERSIZE. REAMED FASTENER HOLE BACK TO ROUND & INSTALLED NAS 1169C REPAIR WASHER IAW STANDARD PROCEDURES IN SRM 51-40-02 ON WORK ORDER 737209-475 IAW ETD 2014-170-004813 & EA E175-54-161 REV 1 WORK ORDER 915246.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
LT WING FLAP TRACK NR 1 OTBD, PN 170-39310-003, WORN OUT OF LIMITS WIDTH REDUCTION W .003 INCHES IAW SRM 57-52-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-521 IAW ETD 2011-170 01072E & EA E175-57-184 1 REV IR WORK ORDER 906309.
Part: RETAINER — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
LAVATORY WASTE PAN INBD FWD RETAINER, PN 170-86654-003 IS CORRODED. R & R INBD FWD RETAINER IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-130 IAW EO E175-5300-060 REV 1 WORK ORDER 904996.
Part: PANEL SUPPORT — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR RT PANEL SUPPORT, PN 170-66797-001 FWD PANEL SUPPORT HAS CORROSION AT X 4000 Y 718. R & R RT PANEL SUPPORT IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-216 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
RIGHT WING FLAP TRACK NR 3 OTBD, PN 170-39314-002, WORN OUT OF LIMITS WIDTH REDUCTION W .005 INCHES IAW SRM 57-55-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-626 IAW ETD 2011-170 01072E & EA E175-57-184 2 REV IR WORK ORDER 906310.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
RIGHT WING FLAP TRACK NR 2A INBD, PN 170-39320-004, WORN OUT OF LIMITS THICKNESS REDUCTION D .010 INCHES IAW SRM 57-52-03 TABLE 101. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-624 IAW ETD 2011-170 01072E & EA E175-57-184 2 REV IR WORK ORDER 906310.
Part: PANEL — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR RT SHEAR PANEL, PN 170-91919-001, HAS CORROSION FROM X 24048, Y 285 - 1143. R & R RT SHEAR PANEL IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-215 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: WASHER — LOOSE (ZONE 400) · airframe 16,259 hrs · 9,242 cycles
LEFT PYLON OTBD LOWER WING TO PYLON ATTACHMENT BOLT HAS A LOOSE WASHER.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
RIGHT WING FLAP TRACK NR 2 INBD, PN 170-39313-004, WORN OUT OF LIMITS THICKNESS REDUCTION D .014 INCHES IAW SRM 57-52-03 TABLE 101. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-622 IAW ETD 2011-170 01072E & EA E175-57-184 2 REV IR WORK ORDER 906310.
Part: PANEL — WORN (CARGO BAY) · airframe 16,259 hrs · 9,242 cycles
PUNCTURE ON FWD CARGO AFT BULKHEAD PANEL 132AZ. CUT OUT DAMAGED AREA, FABRICATED & INSTALLED A REPAIR DOUBLER ON WORK ORDER 787256-206 IAW SRM 51-31-00 & 51-75-00 PRINCIPLES IAW ETD 2014-170-003201 & EA E175-50-011 REV IR WORK ORDER 910494.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR RT BEAM, PN 170-65669-004, HAS CORROSION AT Y 273 X 23865. R & R RT FLOOR BEAM IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-218 IAW EO E175-53MR-094 REV 4 WORK ORDER 903422.
Part: PANEL — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR CTR SHEAR PANEL, PN 170-65928-001, HAS CORROSION FROM X 24048 Y 222.3 TO 222.3. R & R CTR SHEAR PANEL IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-219 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
RIGHT WING FLAP TRACK NR 2A OTBD, PN 170-39321-004 WORN OUT OF LIMITS THICKNESS REDUCTION D .020 INCHES IAW SRM 57-52-03 TABLE 101. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-625 IAW ETD 2011-170 01072E & EA E175-57-184 2 REV IR WORK ORDER 906310.
Part: PANEL — WORN (RT PYLON) · airframe 16,259 hrs · 9,242 cycles
PYLON PANEL 419YL HAS ELONGATED FASTENER HOLE. REAMED FASTENER HOLE BACK TO ROUND & INSTALLED NAS 1169C REPAIR WASHER IAW STANDARD PROCEDURES IN SRM 51-40-02 ON WORK ORDER 737209-412 IAW ETD 2014-170-004813 & EA E175-54-161 REV 1 WORK ORDER 915246.
Part: GUSSET — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR RT INBD GUSSET, PN 170-60257-001 CORRODED X 24868.0, Y +254 TO +305. R & R RT INBD GUSSET IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-241 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
LEFT WING FLAP TRACK NR 3 INBD, PN 170-39315-001, WORN OUT OF LIMITS WIDTH REDUCTION W .002 INCHES IAW SRM 57-55-03 TABLE 102. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-527 IAW ETD 2011-170 01072E & EA E175-57-184 1 REV IR WORK ORDER 906309.
Part: PANEL SUPPORT — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR LT PANEL SUPPORT, PN 170-86139-005, IS CORRODED X 24868.0, Y -838. R & R LT PANEL SUPPORT IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-245 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: PANEL SUPPORT — BROKEN (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
AFT CABIN FLOOR LT PANEL SUPPORT, PN 170-66796-001, BROKEN X 23453.0, Y 736. R & R LT PANEL SUPPORT IAW SRM 51-41-01 & 51-43-01 ON WORK ORDER 737209-238 IAW EO E175-5300-097 REV IR WORK ORDER 906482.
Part: PANEL — WORN (ZONE 400) · airframe 16,259 hrs · 9,242 cycles
FASTENER HOLE ON RH ENGINE PANEL 429LR IS WORN OVERSIZE. REAMED FASTENER HOLE BACK TO ROUND AND INSTALL NAS 1169C REPAIR WASHER IAW STANDARD PROCEDURES IN SRM 51-40-02.
Part: FLAP TRACK — WORN (TE FLAP) · airframe 16,259 hrs · 9,242 cycles
LEFT WING FLAP TRACK NR 2A OTBD, PN 170-39321-003 WORN OUT OF LIMITS THICKNESS REDUCTION D .016 INCHES IAW SRM 57-52-03 TABLE 101. BLENDED WORN AREA IAW SRM PART II 51-10-03 ON WORK ORDER 737209-526 IAW ETD 2011-170 01072E & EA E175-57-184 1 REV IR WORK ORDER 906309.
Part: SEAL DEPRESSOR — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
FORWARD CARGO DOOR CUTOUT STRUCTURE, CTR CORNER SEAL DEPRESSOR HAS CORROSION. R & R CTR CORNER SEAL DEPRESSOR PN 170-66804-401 IAW EO E175-53MR-108.
Part: FINGER DOUBLER — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
FORWARD CARGO DOOR CUTOUT STRUCTURE, FWD FINGER DOUBLER PN 170-67115-001 GOUGED. R & R FWD FINGER DOUBLER PN 170-67115-001 IAW EO E175-53MR-125 REV 1.
Part: SEAL DEPRESSOR — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
FORWARD CARGO DOOR CUTOUT STRUCTURE, FWD CORNER SEAL DEPRESSOR HAS CORROSION. R & R FWD CORNER SEAL DEPRESSOR PN 170-66803-401 IAW EO E175-53MR-108. CORRECT CONTROL NUMBER.
Part: SEAL DEPRESSOR — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
FWD CARGO DOOR CUTOUT STRUCTURE, FWD CORNER SEAL DEPRESSOR HAS CORROSION AS MARKED X 7658.2 & Y 450. R & R FWD CORNER SEAL DEPRESSOR PN 170-66803-401 IAW WITH EO E175-53MR-108.
Part: FINGER DOUBLER — CORRODED (FUSELAGE) · airframe 16,259 hrs · 9,242 cycles
FORWARD CARGO DOOR CUTOUT STRUCTURE, AFT FINGER DOUBLER PN 170-67115-002 GOUGED. R & R AFT FINGER DOUBLER PN 170-67115-002 IAW EO E175-53MR-125 REV 1.
Part: SPAR — CRACKED (WING) · airframe 16,259 hrs · 9,242 cycles
WHILE ACCOMPLISHING SB170-57-0038 ON EO E17X-57MA-004, CRACK DAMAGE WAS DISCOVERED SPAR III LT SIDE, TWO EACH CRACKS APPROXIMATELY 045 INCHES, CRACK INDICATIONS AT THE 4:00 AND 8:00 OâCLOCK POSITIONS. RACKS START AT THE SURFACE OF THE BULKHEAD & EXTEND INTO THE BORE THAT WERE FOUND IN THE CRITICAL FASTENER HOLE ON THE LT SIDE AFTER IT HAD BEEN ENLARGED TO 8MM, .314 INCHES IN DIAMETER IAW THE SB. RT SIDE, TWO EACH CRACKS APPROXIMATELY .045 INCHES CRACK INDICATIONS AT THE 5:00 & 10:00 OâCLOCK POSITIONS. CRACKS START AT THE SURFACE OF THE BULKHEAD & EXTEND INTO THE BORE THAT WERE FOUND IN THE CRITICAL FASTENER HOLE ON THE RT SIDE AFTER IT HAD BEEN ENLARGED TO 8MM, .314 INCHES IN DIAMETER IAW THE SB. THE CRACK DAMAGE WAS REMOVED BY SPOT FACING TO .50 INCHES ON THE LT & RT SIDES IAW ETD2014-170-001927. REPAIR WILL BE ACCOMPLISHED EO E17X-57MA-004.14 UNDER WORK ORDER 908512.
2012
Part: DOUBLER — CORRODED (ZONE 100) · airframe 10,845 hrs · 6,220 cycles
WASTE VALVE PAN DOUBLER IS CORRODED AT FRAME 88 AND STRINGER 27R. REMOVED AND REPLACED LAVATORY WASTE PAN DOUBLER IAW EMB SRM 51-40-02 PER EA E175-53-245 ON WO# 468233-109.
Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
LEFT FLOORBEAM DOUBLER AT FRAME 16 HAS CORROSION. REMOVED AND REPLACED FLOORBEAM DOUBLER IAW SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-051 R0 ON WO 468233-257.
Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
FLOORBEAM HAS CORROSION AT FRAME 16. REMOVED AND REPLACED FLOORBEAM IAW SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-061 R3 ON WO468233-252.
Part: FINGER DOUBLER — CORRODED (ZONE 100) · airframe 10,845 hrs · 6,220 cycles
FWD CARGO DOOR CUTOUT FWD FINGER DOUBLER HAS SEVERAL SPOTS OF CORROSION. REMOVED AND REPLACED FINGER DOUBLER IAW SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-106 R0 ON WO 468233-130.
Part: SEAL DEPRESSOR — CORRODED (CARGO DOOR) · airframe 10,845 hrs · 6,220 cycles
FWD CARGO DOOR FWD SEAL DEPRESSOR HAS CORROSION. REMOVED AND REPLACED FWD SEAL DEPRESSOR IAW SRM 51-41-01 & 53-21-29 PER EO E175-53MR-108 ON WO 468233-127.
Part: DOUBLER — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
WASTE VALVE PAN DOUBLER IS CORRODED AT FRAME 88 AND STRINGER 27R. REMOVED AND REPLACED LAV WASTE PAN DOUBLER IAW SRM 51-40-02 PER EA E175-53-245 ON WO 468233-109.
Part: GUSSET — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
LEFT GUSSET PLATE AT FRAME 90 CORRODED. REMOVED AND REPLACED GUSSET PLATE IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-050 R0 ON WO 468233-270.
Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
CENTER SHEAR PANEL CORRODED ON RIVET HEAD ONLY. REMOVED AND REPLACED CENTER SHEAR PANEL IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-050 R0 ON WO 468233-266
Part: GUSSET — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
RIGHT GUSSET PLATE AT FRAME 90 AND AROUND RACK CORRODED. REMOVED AND REPLACED GUSSET PLATE IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-050 R0 ON WO 468233-268.
Part: GUSSET — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
GUSSET PLATE AT FRAME 90. REMOVED AND REPLACED GUSSET PLATE IAW EMB SRM 51-41-01 & 51-43-01 PER EO E175-53MR-050 R0 ON WO# 468233-269.
Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
RIGHT FLOOR SUPPORT BETWEEN FRAMES 86/87 CORRODED. REMOVED AND REPLACED FLOOR SUPPORT IAW SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-094 R2 ON WO# 468233-262.
Part: SEAL DEPRESSOR — CORRODED (ZONE 100) · airframe 10,845 hrs · 6,220 cycles
FWD CARGO DOOR CENTER SEAL DEPRESSOR HAS CORROSION. REMOVED AND REPLACED FWD CARGO DOOR CENTER SEAL DEPRESSOR IAW SRM 51-41-01 & 53-21-29 PER EO E175-53MR-108 ON WO# 468233-128.
Part: SEAL DEPRESSOR — CORRODED (ZONE 100) · airframe 10,845 hrs · 6,220 cycles
FWD CARGO DOOR AFT SEAL DEPRESSOR HAS CORROSION. REMOVED AND REPLACED SEAL DEPRESSOR IAW EMB SRM SRM 51-41-01 & 53-21-29 PER EO E175-53MR-108 ON WO 468233-129.
Part: FINGER DOUBLER — CORRODED (ZONE 100) · airframe 10,845 hrs · 6,220 cycles
FWD CARGO DOOR CUTOUT AFT FINGER DOUBLER HAS SEVERAL SPOTS OF CORROSION. REMOVED CORROSION BY BLENDING AND PERFORMED NDT IAW ETD 2012-170-003476 PER EO E175-53MR-106 R0 ON WO 468233-131.
Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
RIGHT SHEAR PANEL HAS CORROSION. REMOVED AND REPLACED SHEAR PANEL IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-050 R0 ON WO 468233-265
Part: FIREWALL — CRACKED (APU BAY) · airframe 10,845 hrs · 6,220 cycles
APU FIREWALL PANEL 351BZ HAS 0.5" CRACK AT UPPER AND LOWER I/B ANGLES. CRACK ROUTED OUT AND NDT PERFORMED VERIFYING NO MORE CRACKING EXISTS ON WO 468233-319 IAW ETD 2012-170-003356 AND EA E175-53-246 IR WO 531362.
Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
LEFT SHEAR PLATE CORRODED ON AND AROUND RIVET HEADS. REMOVED AND REPLACED SHEAR PLATE IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-050 R0 ON WO 468233-267.
Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 10,845 hrs · 6,220 cycles
FWD CARGO FLOORBEAM HAS SEVERAL SPOTS OF CORROSION AT CARGO ENTRY. REMOVED AND REPLACED FWD FLOORBEAM IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-109 ON WO 468233-132.
Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
FLOORBEAM DOUBLER AT FRAME 14 HAS CORROSION. REMOVED AND REPLACED FLOORBEAM DOUBLER IAW SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-051 R0 ON WO 468233-254.
Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
FLOORBEAM AT FRAME 87 CORRODED. REMOVED AND REPLACED FLOORBEAM IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-093 R1 ON WO 468233-263.
Part: SILL — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
LEFT SILL AT FRAME 19 HAS CORROSION. REMOVED AND REPLACED SILL IAW SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-051 R0 ON WO 468233-259
Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
FLOORBEAM HAS CORROSION BETWEEN FRAMES 13 AND 14.REMOVED AND REPLACED FLOORBEAM IAW SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-062 R3 ON WO 468233-249.
Part: WEB — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
LEFT WEB BETWEEN FRAMES 85/86 HAS A SMALL SPOT OF CORROSION. REMOVED AND REPLACED WEB IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-050 R0 ON WO 468233-260.
Part: WEB — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
WEB BETWEEN FRAMES 85/86 CORRODED. REMOVED AND REPLACED WEB IAW SRM 51-41-01 & 51-43-01 PER EO E175-53MR-050 R0 ON WO 468233-261
Part: SILL — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
LEFT SILL HAS CORROSION AT FRAME 16. REMOVED AND REPLACED SILL IAW SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-051 R0 ON WO 468233-256.
Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 10,845 hrs · 6,220 cycles
LEFT FLOORBEAM DOUBLER AT FRAME 19 HAS CORROSION. REMOVED AND REPLACED FLOORBEAM DOUBLER IAW EMB SRM SRM 51-41-01 & 51-43-01 PER EO E175-53MR-051 R0 ON WO 468233-258.
2010
Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 7,087 hrs · 4,143 cycles
EMERGENCY BATTERY FAULT ON IECAS AFTER ELPU TEST. INTERROGATED CMC, ACTIVE FAULT SHOWED RT FWD ELPU FAULT CODE 33500001UTI. REPLACED RT FWD ELPU IAW E175 AMM 33-50-01 MESSAGE CLEARED AND OPS CHECK GOOD. OK FOR SERVICE.
Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHTS) · airframe 6,832 hrs · 4,003 cycles
FWD EMERGENCY LIGHTS STAYED ON WITH POWER SHUTDOWN.
Part: BATTERY PACK — FAULTY (EMERGENCY LIGHTS) · airframe 6,658 hrs · 3,898 cycles
EMER LIGHT BATT FAULT EMERGENCY LIGHTS AT ROW 14, AFT LAV, AND DOOR L2 INOP. R & R EMERGENCY LIGHT POWER UNIT IAW AMM 33-50-01-04. OPS CHECK NORMAL.
Part: BRAKE ASSY — FAILED (LT MLG) · airframe 6,341 hrs · 3,704 cycles
BRAKE LT FAULT MSG ON EICAS ON TAXI OUT THEN EMER BRAKE FAULT MSG ON TAXI OUT. FOUND NR1 BRAKE FAILED. REPLACED NR1 MLG BRAKE IAW AMM 32-49-11, OPS CHECK GOOD.
Part: CIRCUIT BREAKER — TRIPPED (NR 1 MAU) · airframe 6,283 hrs · 3,667 cycles
AVNX MAU 1 A FAIL CAUTION MESSAGE IN FLIGHT. FOUND MAU 1 POWER 1 CB ON LHCBP OUT. RESET CIRCUIT BREAKER AND PERFORMED FIM TASK 31-42-00-810-808-A. CHECKS OK.RESET MAU 1 NIC 1 AMM 45-45-00. PERFORMED RETURN TO SERIVE IAW AMM 27-00-00-070-801-A.
Part: CIRCUIT BREAKER — FAILED · airframe 6,283 hrs · 3,667 cycles
AVNX MAU 1 A FAIL CAUTION MESSAGE IN FLIGHT. FOUND MAU 1 POWER 1 CIRCUIT BREAKER ON LHCBP OUT. RESET CIRCUIT BREAKER AND PERFORMED FIM TASK 31-42-00-810-808-A. CHECKS OK.RESET MAU 1 NIC 1 AMM 45-45-00. PERFORMED RETURN TO SERIVE IAW AMM 27-00-00-070-801-A.
Part: CIRCUIT BREAKER — TRIPPED (NR 1 MAU) · airframe 6,283 hrs · 3,667 cycles
AVIONICS MAU 1 A FAIL CAUTION MESSAGE IN FLIGHT. FOUND MAU 1, POWER 1 CIRCUIT BREAKER ON LT CIRCUIT BREAKER PANEL OUT. RESET CIRCUIT BREAKER AND PERFORMED FIM TASK 31-42-00-810-808-A. CHECKS OK. RESET MAU 1, NIC 1, AMM 45-45-00. PERFORMED RETURN TO SERVICE IAW AMM 27-00-00-070-801-A.
Part: SENSOR — DEFECTIVE (SLAT SKEW) · airframe 5,790 hrs · 3,377 cycles
SLAT FAIL MESSAGE ON TAKEOFF. SLATS WOULD NOT RETRACT. RETURNED TO DEPARTURE.
Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 5,242 hrs · 3,042 cycles
DURING BASIC CHECK INSP, CORROSION WAS FOUND ON LT FLOOR TRACK PN 170-03264-001 BETWEEN FR17 AND FR19 (BL265L). PERMANENT REPAIR WAS ACCOMPLISHED REF ETD 2010-170/02106 AND COMPASS EO E175-53MR-029.