N206NN

Part: POWER SUPPLY — INOPERATIVE (ZONE 200) · airframe 28,022 hrs · 18,626 cycles

EMERGENCY LIGHT BATTERY FAULT EICAS MESSAGE. TWO EMERGRENCY LIGHTS IN THE CENTER OF THE CABIN DO NOT ILLUMINATE. R & R AFT RT OTBD EMERGENCY LIGHT POWER UNIT IAW AMM 33-50-01. ALL LIGHTS CAME ON, NO BATT FAULT EICAS MSG

Part: CONTROL COLUMN — OBSTRUCTED (ZONE 100) · airframe 25,412 hrs · 16,704 cycles

YOKE IS LOCKED WILL NOT ROTATE LEFT ON FLIGHT CONTROL CHECK ONLY ROTATE RIGHT. FOUND FLASH LIGHT STUCK BETWEEN AILERON CONTROL QUADRANT ASSY AND ICC ON THE FWD AVIONICS COMPARTMENT. REMOVED FLASH LIGHT. PERF. RETURN TO SERVICE FLIGHT CONTROLS IAW AMM 27-00-00. AND PERF. TEST AILERON IAW AMM 27-12-01. NO DEFECTS NOTED.

Part: WINDSHIELD — CRACKED (ZONE 200) · airframe 25,382 hrs · 16,676 cycles

CRACK/ BUBBLE IN FO WINDSHIELD EXPANDING IN FLIGHT. EMERGENCY DECLARED. DIVERT TO ATL. OVERWEIGHT LANDING. NORMAL SINK RATE. NO INJURIES. FOUND CRACKS TO BE URETHANE INTERLAYERS EXPOSED TO MOISTURE PER AMM 56-11-00-210-801-A STEP 2.A.(6). FOUND DELAMINATION MEASURING 1.5" ALONG TOP LH EDGE, CURRENTLY ON TDMI 006T56104, WITHIN DEFERRABLE LIMITS PER SRM 56-11-00/AD01 TABLE 102 AND AMM 56-11-00 STEP 2.G.(2).(A) AND (B). PERFORMED PRESSURIZATION OF AIRCRAFT IAW AMM 21-31-00, NO LEAKS NOTED.

Part: SEAT TRACK — CORRODED (LH) · corrosion level 2 · airframe 20,874 hrs · 13,453 cycles

LH INBD SEAT TRACK BEAM IS CORRODED BY FR 18 CROSSMEMBER (LEVEL 2 CORROSION)-C/A-COMPLETE:COMPLETED REPAIR TO SEAT TRACK BEAM AT FR 18 IAW SRM 53-10-10

Part: LIGHT — CRACKED (LH) · airframe 20,874 hrs · 13,453 cycles

LH EMERGENCY LIGHT STRIPS #2,3,4,AND 7 REQUIRE REPLACEMENT DUE TO CRACKED PLASTICS.-C/A-COMPLETE:INSTALLED NEW PHOTOLUMINESCENT LIGHT STIRPS IAW EMB 175 AMM 33-50-21

Part: LIGHT — CRACKED (RH) · airframe 20,874 hrs · 13,453 cycles

RH EMERGENCY LIGHT STRIPS #1,4,9 AND 11 HAVE CRACKED PLASTICS REQUIRING REPLACEMENT.-C/A-COMPLETE:INSTALLED NEW PHOTOLUMINESCENT LIGHT STRIPS IAW EMB 175 AMM 33-50-21

Part: SENSOR — FAILED (RH) · airframe 20,735 hrs · 13,350 cycles

SLAT FAIL INFLIGHT. EMRGENCY DECLARED. TAXI NORMAL TO GATE. -C/A-T/S IAW FIM 27-83-00-810-810. RAR TRACK 3 INBD RH SKEW SENSOR IAW AMM 27-83-02. TAT SF-ACE 2 IAW AMM 27-53-02. OPS CHECK FAILED

Part: EICAS — ACTIVATED (PASS DOOR) · airframe 15,201 hrs · 9,750 cycles

DOOR PAX FWD OPEN WARNING EICAS MSG DURING CLIMB FOLLOWED BY CABIN PRESSURIZATION ISSUES DECLARED EMERGENCY-C/A-CYCLED MAIN CABIN DOOR IAW SDSMM 52-11-00 ALL IND NORMAL PRESSURIZEDA/C IAW EMB AMM 21-31-00 ALL INDICATION NORMAL. NO FAULTS FOUND AT THIS TIME.

Part: UNKNOWN — ODOR (CABIN) · airframe 13,991 hrs · 8,941 cycles

CABIN ZONE 3 HAS CIGARETTE ODOR COMING OUT. INTERROGATED CABIN ZONE E FOR CIGARETTE ODOR IAW FIM 25-30-00-810-801-A. NO DEFECTS FOUND.

Part: LIGHT — FADED (CABIN) · airframe 13,928 hrs · 8,869 cycles

PCR EMERGENCY FLOOR STRIP INBD FWD CLOSET FADED (FOUND DURING CONFORMITY). REMOVED AND REPLACED EMERGENCY FLOOR STRIP INBD FWD CLOSET IAW AMM 33-50-21.

Part: ACCUMULATOR — LOW (EVAC SLIDE) · airframe 13,928 hrs · 8,869 cycles

AFT PAX DOOR SLIDE ACCUMULATOR IS LOW. REMOVED AND REPLACED AFT PAX DOOR SLIDE IAW AMM 25-65-01 TORQUMETER EASI 8238, AND TQW EASI 4327.

Part: SEAT TRACK — CORRODED (FRAMES 84-85) · corrosion level 2 · airframe 13,479 hrs · 8,596 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A PERMANENT REPAIR OF CORROSION DAMAGE TO THE CENTER FUSELAGE III RH IB SEAT TRACK P/N 170-86082-005. ACCOMPLISHMENT OF THIS TRACK SPLICE REPAIR WILL BE PER ETD2020-170-001434B AND SRM 1583 PART II 53-00-10/REPAIR 01P. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR BECAUSE THE SEAT TRACK IS A PSE AND THIS EO IS RESTORING STRENGTH. RH INBD SEAT TRACK FR 84/85 AS MARKED.W.O.#2800746208

Part: FIRE BOTTLE — DISCHARGED (ZONE 100) · airframe 13,479 hrs · 8,596 cycles

APU FIRE BOTTLE DISCHARGE MESSAGE DURING SYSTEM TEST. WO# 2800746437

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 13,479 hrs · 8,596 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH A PERMANENT REPAIR OF CORROSION DAMAGE TO THE CENTER FUSELAGE III RH IB SEAT TRACK P/N 170-86082-005. ACCOMPLISHMENT OF THIS TRACK SPLICE REPAIR WILL BE PER ETD2020-170-001434B AND SRM 1583 PART II 53-00-10/REPAIR 01P. ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR BECAUSE THE SEAT TRACK IS A PSE AND THIS EO IS RESTORING STRENGTH. EO E175-53MR-485 IS BEING ACCOMPLISHED BY WO 2821457.

Part: CROSSBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 13,479 hrs · 8,596 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. THE DAMAGE IS LOCATED OUTBOARD OF THE RH INBOARD SEAT TRACK BEAM, AND THERE ARE NO SRM REPAIRS FOR THIS AMOUNT OF DAMAGE. REFERENCE ETD2020-170-001460-B FIGURES 1-2 FOR DETAILS. EAMS REQUESTED AND RECEIVED ETD2020-170-001460-B TO PERFORM A CUTOUT AND DOUBLER REPAIR IN ACCORDANCE WITH THE PRINCIPLES OF SRM PART II 53-00-10/REPAIR 03P FIGURE 203. BECAUSE THE FR84 FLOOR CROSSBEAM IS PSE/FCS, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR.

Part: SEAT TRACK — CORRODED (FRAMES 13-14) · corrosion level 2 · airframe 13,479 hrs · 8,596 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 FORWARD FUSELAGE RH IB SEAT TRACK (P/N 170-03263-001) BETWEEN FR13 AND FR14 IN THE FORWARD CABIN FLOOR STRUCTURE. EAMS REQUESTED AND RECEIVED ETD2020-170-001436 TO PERFORM A CUTOUT AND DOUBLER REPAIR. THE RH 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 ETD2020-170-001436.FWD WET AREA. RH SEAT TRACK FWD AND AFT OF FR13 AS MARKED Y= 273.0, X= 273.0, Z= -490.0;W.O.#2800746251

Part: GUSSET — CORRODED (FRAME 90) · corrosion level 2 · airframe 13,479 hrs · 8,596 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE IN THE FORWARD AND AFT CABIN FLOOR STRUCTURE BY REPLACEMENT OF THE FOLLOWING: P/N 170-05663-005 RH FLOOR SILL, P/N 170-92908-001 RH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60257-001 FR90 RH IB GUSSET. 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. WO # 2800746207.

Part: FLOOR SUPPORT — CORRODED (FRAME 84) · corrosion level 2 · airframe 13,479 hrs · 8,596 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE IN THE FORWARD AND AFT CABIN FLOOR STRUCTURE BY REPLACEMENT OF THE FOLLOWING: P/N 170-05663-005 RH FLOOR SILL, P/N 170-92908-001 RH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60257-001 FR90 RH IB GUSSET. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS A MINOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (FRAMES 12-13) · corrosion level 2 · airframe 13,479 hrs · 8,596 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE IN THE FORWARD AND AFT CABIN FLOOR STRUCTURE BY REPLACEMENT OF THE FOLLOWING: P/N 170-05663-005 RH FLOOR SILL, P/N 170-92908-001 RH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60257-001 FR90 RH IB GUSSET. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS A MINOR REPAIR.

Part: SHEAR PANEL — CORRODED (FRAME 87) · corrosion level 2 · airframe 13,479 hrs · 8,596 cycles

THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE IN THE FORWARD AND AFT CABIN FLOOR STRUCTURE BY REPLACEMENT OF THE FOLLOWING: P/N 170-05663-005 RH FLOOR SILL, P/N 170-92908-001 RH PANEL SUPPORT, P/N 170-91919-001 RH SHEAR PANEL, P/N 170-60257-001 FR90 RH IB GUSSET. REPLACEMENT OF PARTS IS ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN TABLE 2 AND SRM CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW UP INSPECTIONS WILL NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE FLOOR STRUCTURE. COMPASS ENGINEERING HAS CLASSIFIED THIS A MINOR REPAIR.

Part: SKIN — DAMAGED (FRAME 23) · airframe 13,479 hrs · 8,596 cycles

DAMAGE AREA 1, AFFECTING THE CENTER FUSELAGE I LOWER RIGHT SKIN PANEL (P/N 170-92574-005) JUST FORWARD OF FR23 AND ABOVE STGR-13R COULD NOT BE REPAIRED THROUGH A MINOR REPAIR IN ACCORDANCE WITH SRM 53-00-00/REPAIR 03P BECAUSE THE AFFECTED HOLE SIZE EXCEEDED THE ALLOWABLE LIMITS. EAMS REQUESTED AND RECEIVED A REPAIR FOR THE AFFECTED HOLE IN THE FORM OF ETD2020-170-002280, WHICH PROVIDES TWO OPTIONS TO ACCOMPLISH A PERMANENT REPAIR. OPTION 1 IS TO REAM THE HOLE TO REMOVE THE DAMAGE AND INSTALL REPAIR BUSHING PER SRM PART II 51-10-07, CASE 1. OPTION 2 IS TO CUT OUT THE DAMAGE AND INSTALL A REPAIR DOUBLER. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH OPTION 1, WHICH IS THE PERMANENT REPAIR OF DAMAGE AROUND A FASTENER HOLE BY REAMING THE HOLE AND INSTALLING A REPAIR BUSHING. BECAUSE THE CENTER FUSELAGE I LOWER RIGHT SKIN IS A PSE AND THE EO IS RESTORING STRENGTH, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. OPTION 1 DOES NOT REQUIRE SUPPLEMENTAL FOLLOW-ON INSPECTIONS PER ETD2020-170-002280. EO E175-53MR-486 IS BEING ACCOMPLISHED BY WO 2821166

Part: FLOORBEAM — CORRODED (FRAME 84) · airframe 13,479 hrs · 8,596 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. THE DAMAGE IS LOCATED OUTBOARD OF THE RH INBOARD SEAT TRACK BEAM, AND THERE ARE NO SRM REPAIRS FOR THIS AMOUNT OF DAMAGE. REFERENCE ETD2020-170-001460-B FIGURES 1-2 FOR DETAILS. EAMS REQUESTED AND RECEIVED ETD2020-170-001460-B TO PERFORM A CUTOUT AND DOUBLER REPAIR IN ACCORDANCE WITH THE PRINCIPLES OF SRM PART II 53-00-10/REPAIR 03P FIGURE 203. 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 ETD2020-170-001460-B. EO E175-53MR-486 IS BEING ACCOMPLISHED BY WO 2821166

Part: SERVICE PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 13,479 hrs · 8,596 cycles

WASTE SERVICING PANEL 152AR HAS CORROSION ON THE FORWARD LEFT CORNER OF THE INTERNAL SURFACE. REMOVED AND REPLACED WASTE SERVICING PANEL 152AR REF EMB AMM 20-10-02.

Part: SKIN — BURNED (FRAME 23) · airframe 13,479 hrs · 8,596 cycles

DAMAGE AREA 1, AFFECTING THE CENTER FUSELAGE I LOWER RIGHT SKIN PANEL (P/N 170-92574-005) JUST FORWARD OF FR23 AND ABOVE STGR-13R COULD NOT BE REPAIRED THROUGH A MINOR REPAIR IN ACCORDANCE WITH SRM 53-00-00/REPAIR 03P BECAUSE THE AFFECTED HOLE SIZE EXCEEDED THE ALLOWABLE LIMITS. EAMS REQUESTED AND RECEIVED A REPAIR FOR THE AFFECTED HOLE IN THE FORM OF ETD2020-170-002280, WHICH PROVIDES TWO OPTIONS TO ACCOMPLISH A PERMANENT REPAIR. OPTION 1 IS TO REAM THE HOLE TO REMOVE THE DAMAGE AND INSTALL REPAIR BUSHING PER SRM PART II 51-10-07, CASE 1. OPTION 2 IS TO CUT OUT THE DAMAGE AND INSTALL A REPAIR DOUBLER. THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH OPTION 1, WHICH IS THE PERMANENT REPAIR OF DAMAGE AROUND A FASTENER HOLE BY REAMING THE HOLE AND INSTALLING A REPAIR BUSHING. BECAUSE THE CENTER FUSELAGE I LOWER RIGHT SKIN IS A PSE AND THE EO IS RESTORING STRENGTH, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED AS A MAJOR REPAIR. OPTION 1 DOES NOT REQUIRE SUPPLEMENTAL FOLLOW-ON INSPECTIONS PER ETD2020-170-002280. EO E175-53MR-486 IS BEING ACCOMPLISHED BY WO 2821166

Part: SEAT TRACK — CORRODED (ZONE 100) · airframe 13,479 hrs · 8,596 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 FORWARD FUSELAGE RH IB SEAT TRACK (P/N 170-03263-001) BETWEEN FR13 AND FR14 IN THE FORWARD CABIN FLOOR STRUCTURE. EAMS REQUESTED AND RECEIVED ETD2020-170-001436 TO PERFORM A CUTOUT AND DOUBLER REPAIR. THE RH 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 ETD2020-170-001436. EO E175-53MR-483 IS BEING ACCOMPLISHED BY WO 2821165

Part: SLIDE — UNLACED (PAX DOOR) · airframe 13,479 hrs · 8,596 cycles

FORWARD PAX DOOR EMERGENCY EVAC SLIDE UNLACED DURING INSTALL. WO#2800746431

Part: SEAT TRACK — CORRODED (ZONE 100) · airframe 13,479 hrs · 8,596 cycles

DURING BASIC CHECK AT EAMS, EAMS REPORTED CENTER FUSELAGE III LH INBOARD SEAT TRACK WITH CORROSION AT THE END OF THE PART. REFER TO FIGURE 1 FOR DETAILS. COMPASS ENGINEERING HAS CLASSIFIED THIS AS A MINOR REPAIR. WORK ORDER 2817744

Part: STRAP — CORRODED (ZONE 100) · airframe 13,479 hrs · 8,596 cycles

DURING BASIC CHECK AT EAMS, EAMS REPORTED CORROSION ON THE AFT STRAP FOR THE AFT BELLY FAIRING. REFER TO FIGURE 1 FOR DETAILS. COMPASS HAS DESIGNATED THIS AS A MINOR REPAIR. WORK ORDER 2818803

Part: STRUCTURE — CRACKED (RT WINGLET) · airframe 13,479 hrs · 8,596 cycles

THIS EO PROVIDES INSTRUCTIONS TO COMPLY WITH SB 170-57-0072 PART II, WHICH ACCOMPLISHES A STRUCTURAL MODIFICATION THAT CONSISTS OF REPLACING THE CURRENT RH WING TIP SPAR 1 (P/N 171-16231-002 OR 171-16231-004) WITH A NEW, REDESIGNED SPAR 1 (P/N 171-171-22480-402), 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. WORK ORDER 2803004

Part: STRUCTURE — CRACKED (LT WINGLET) · airframe 13,479 hrs · 8,596 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. WORK ORDER 2803005

Part: ENGINE — FAILED (NR 1) · airframe 12,921 hrs · 8,249 cycles

ENG 1 FAIL ON CLIMBOUT. LOUD BANG NOISE FOLLOWED BY LOSS OF THRUST AND ENG 1 FAIL MSG.UPON LANDING MZ PERFORMED A BORESCOPE OF AND CONFIRMED HPT BLADES MISSING. ENGINE CHANGE IN PROGRESS AS SDR SUBMITTED. SUPPLIMENTAL SDR TO FOLLOW

Part: BRAKE ASSY — FAILED · airframe 8,732 hrs · 5,617 cycles

CREW RECEIVED AN INTERMITTENT PARKING BRAKE EICAS MESSAGES DURING FLIGHT. DECLARED AN EMERGENCY. LANDED SAFELY, PARK BRAKE NOT RELEASED, QRH CLEARED ONCE, THEN MESSAGE INTERMITTENT REMAINDER OF FLIGHT, WITH BRAKE FAULT AFTER LANDING. FURTHER INSPECTION FOUND A LOOSE CONNECTOR ON THE BRAKE CONTROL VALVE. SECURED THE CONNECTOR IAW AMM 32-41-09. FOUND EXCESS DUST ON PARK BRAKE HANDLE, CLEANED PARK BRAKE HANDLE. R & R THE PARK BRAKE PRESSURE SWITCH ON THE INBD SYS 2 HYD IAW AMM 32-44-09. PERFORMED WIRING CHECKS IAW WM 27-43-51. ALL PASSED. R & R HS-ACE IAW AMM 27-43-01. R & R TRIM CONTROL PANEL IAW AMM 27-03-04. OK FOR SERVICE. NO ACTIVE FAULT PRESENT. PERFORMED FIM 32-41-00-810-852-A, BLOCKS 1 - 5. NO ACTIVE FAULT THROUGHOUT TESTS, ALL TESTS PASSED. RESET BCM 1 & 2. PARK FAULT NOW ACTIVE. SAME FAULT CODE 32400001UT1. OK FOR SERVICE. R & R THE NR 4 BRAKE IAW AMM 32-49-11. BLEED THE BRAKE, OPS CHECKED NORMAL, OK FOR SERVICE. PERFORMED TROUBLESHOOTING STEPS ON THE PRESSURE SWITCH SYS 1 PINS 6 & 2/6 & 1, NO LB OK INDICATION NOTED PERFORMED MEGAOHMS TEST ON GROUNDING BLOCKS GS0051 & GS0052, OHMS READING 0.01 IAW WM 32-11-50. PERFORMED OPS TEST OF THE PARK BRAKE SYSTEM IAW AMM 32-44-00-710-801-A, OPS CHECKED GOOD. ACFT OK FOR SERVICE.

Part: SUPPORT FITTING — DISLODGED (FLAP FAIRING) · airframe 154 hrs · 69 cycles

FLAP & SLAT FAIL ON RETRACTION. REMOVED RT NR 3 FLAP TRACK FAIRING IAW 57-58-25 AMM. FOUND UPPER & LOWER TRUNNION MOUNT BEARINGS DISLODGED WITH THE UPPER MIGRATED COMPLETELY OUT. LEFT NR 3 TRUNNION MOUNT, LOWER, IS ALSO DISPLACED. THIS WORK ORDER REMAINS OPEN. R & R NR 3 RT & LT GIMBAL ASSEMBLIES IAW AMM 57-57-37 & TRUNNION ATTACHMENTS IAW AMM 27-51-01. OVER TRAVEL STOP TO BALL NUT MEASUREMENT OUT OF LIMITS. MECHANICAL RIG REQUIRED, THIS ITEM REMAINS OPEN. PERFORMED MECHANICAL RIGGING ON RT NR 3 FLAP TRACK IAW AMM 27-50-00. ACFT OK FOR SERVICE.

Part: CONTROL LEVER — DEFECTIVE (COCKPIT) · airframe 154 hrs · 69 cycles

FLAP & SLAP FAIL AFTER TAKEOFF. PERFORMED QRH 7.10 SLAT INDICATED GREEN WITH FLAPS INDICATING AMBER & ZERO POSITION. PERFORMED FLAP PDU MOTOR BRAKE RELEASE IAW AMM 45-45-00-970-805-A/200, CONDUCTED VISUAL INSPECTION OF THE FLAP & SLAT ACTUATORS & SKEW SENSORS. ALL VISUAL CHECKS GOOD. PERFORMED FLAP CONTROL SYS OPERATIONS TEST, NO DISCREPANCIES NOTED & COULD NOT REPLICATE FAULT IAW AMM 27-50-00. PERFORMED RETURN TO SERVICE TEST IAW AMM 27-00-00 & FLAP LO RATE MSG APPEARED. PERFORMED FIM 27-53-00-810-820-A TO SUBTASK 813-836-A & CLEARED MSG. FURTHER TROUBLESHOOTING REQUIRED TO FIND ROOT CAUSE IAW MXC, WO 1940360 REMAINS OPEN. R & R FLAP SLAT LEVER IAW AMM 27-53-01/400, OPERATIONS CHECKED GOOD. WO 940360 REMAINS OPEN. PERFORMED SLAT CONTROL ELEC RIGGING IAW AMM 27-80-00-820-802-A 200. CLEARED SLAT INHIBITS IAW AMM 45-45-00-970-805-A 200. PERFORMED GVI OF FLAP SKEW SENSORS, CONNECTORS, & WIRING HARNESSES, NO DEFECTS NOTED. WO 1940360 REMAINS OPEN. AFTER NUMEROUS GVI & DETAILED INSPECTIONS OF FLAP SYS THE REMOVAL & REPLACEMENT OF SFCL, NUMEROUS OPERATIONS CHECK OF FLAP SYS VERIFICATION OF ALL PARAMETERS BEING IN ACCEPTABLE RANGES & NO MSGS PRESENT ON EICAS NOR DEFECTS INDUCED FROM REPEAT OPERATIONS CHECK. FAULT PREVIOUSLY REPORTED COULD NOT BE DUPLICATED, NO FURTHER DEFECTS NOTED AT THIS TIME. OPERATIONS CHECKED GOOD IAW AMM 27-50-00 IAW WO 1940360 FOR PREVIOUS ACCOMPLISHED TASK. THIS ACTION CLOSES WORK ORDER 1940360.

Part: SENSOR — FAILED (LE SLAT) · airframe 152 hrs · 67 cycles

FLAP FAIL MESSAGE ON CLIMB OUT, 30 SECONDS AFTER FLAPS INDICATED 0. COMPLETED QRH. R & R T3 & T4 SKEW SENSORS IAW AMM 27-83-01 & 27-83-02. OPERATIONS CHECKED GOOD.