N209NN
Registered owner: AMERICAN AIRLINES INC, TX (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
FA CAN'T GET 2L DOOR TO OPEN AND DISARM. VISUALLY INSP L2 DOOR EVACUATING SLIDE/GIRT BAR FLAP AND FITTING AS PER AMM 53-23-21 AND AMM 52-12-41. CLEANED AND LUBE STICKY FITTINGS. OPENED AND CLOSED L2 DOOR. ARMED AND DISARMED DOOR OPS CHECK GOOD. REF SDS 52-12-00.
SSI 53-23-003 CENTER FUSELAGE III UNDERFLOOR, THERE IS A CORRODED SHEAR CLIP AT FR 87 BETWEEN STGR 27R-28R. (LVL 2 CORROSION) RAR SHEAR CLIP AT FR87, STGR 27R-28R IAW ERJ 175 SRM 51-40-08
CENTER FUSELAGE III UNDERFLOOR, THERE IS A CORRODED SHEAR TIE AT FR 82 BETWEEN STGR 27R-28R. (LVL 2 CORROSION) RAR SHEAR TIE AT FR 82 BETWEEN STGR 27R-28R IAW SRM 51-40-08
CENTER FUSELAGE III UNDERFLOOR, THERE IS A CORRODED SHEAR CLIP AT FR 86 BETWEEN STGR 27R-28R. (LVL 2 CORROSION) RAR SHEAR CLIP AT FR86 BETWEEN STGR 27R-28R IAW ERJ 175 SRM 51-40-08
CENTER FUSELAGE III UNDERFLOOR, THERE IS A CORRODED SHEAR TIE AT FR 88 BETWEEN STGR 27R-28R (LVL 2 CORROSION) MAJOR REPAIR) R & R SHEAR TIE AT FR88, STGR 27R-28R IAW SRM 51-40-08
FWD GALLEY RT CENTER FLOOR BEAM CORRODED BETWEEN FR 13-15. (LVL1 CORROSION)(MAJOR REPAIR) ACCOMPLISHED A PERMANENT REPAIR ON FWD GALLEY RH CENTER FLOORBEAM BETWEEN FR 14-15 IAW ERS-EJ-53MR-5456. FR 13-14 WAS FOUND TO BE WITHIN LIMITS IAW SRM 53-10-10AD01.
SSI 53-23-005 AFT GALLEY RIGHT CENTER FLOOR BEAM AT FR 86 IS CORRODED. (LVL 2 CORROSION) (MAJOR REPAIR) ACCOMPLISHED A PERMANENT REINFORCING REPAIR ON AFT GALLEY RIGHT CENTER FLOOR BEAM AT FR 86 IAW ERS-EJ-53MR-5459
FORWARD GALLEY RIGHT FORWARD FLOOR SUPPORT IS CORRODED. R & R THE FWD GALLEY RIGHT FORWARD FLOOR SUPPORT IAW SRM 51-40-08.
FORWARD GALLEY LEFT CENTER FLOOR SEAT TRACK IS CORRODED BETWEEN FR 19-20. (MAJOR REPAIR). (LVL 1 CORROSION) ACCOMPLISHED A PERMANENT REPAIR ON FORWARD GALLEY LEFT CENTER FLOOR SEAT TRACK IS CORRODED BETWEEN FR 19 AND 20 IAW ERS-EJ-53MR-5451 RO 01.
SSI 53-10-027 FORWARD GALLEY LEFT CENTER FLOOR BEAM IS CORRODED BETWEEN FR 16-17. (LVL 2 CORROSION) (MAJOR REPAIR) ACCOMPLISHED A PERMANENT REPAIR ON FORWARD GALLEY LEFT CENTER FLOOR BEAM BETWEEN FRS 16-17 IAW ERJ-175 SRM 53-10-10 RE03
CAPTAIN EMERGENCY FLASHLIGHT INOP RAR CAPTAINS EMERGENCY FLASHLIGHT IAW AMM 33-51-01 NO FURTHER DISCREPANCY NOTED
FOUND FORWARD LH PASSAGEWAY EMERGENCY "EXIT" LIGHT INOP EVALUATED AND FOUND LH EMERGENCY LIGHT POWER UNIT INOP. RAR EMERGENCY LIGHT POWER UNIT IAW AMM 33-50-01. OPS CHECK GOOD.
RIGHT SIDE BRAKE 425 C BRAKE OVERHEAT EICAS MESSAGE MULTIPLE TIMES FOUND CMC CODE 32400013UT1, FOLLOW THE FIM 32-47-00 EXTREME CONDITIONS OF THE BRAKE ASSEMBLY USE (AIPC 32-49-11)(AMM MPP 32-49-11/400) NO MAINTENANCE ACTION REQUIRED AT THIS TIME.
METALIC SMELL THROUGH FLIGHT DECK AND CABIN NOTICED MORE ON THE DECENT AND LOWER POWER SETTINGS PERFORMED BOTH E-1 AND E-2 ENG RUNS. NO DEFECT NOTED OR ODERS NOTICED. A/C OK FOR SERVICE. RUNS C/W PER E-175 AMM 71-00-01.
DUE TO BRAKE FAULT.UPON ROTATION RECEVIED BRK RH & LH FAULT. BRAKE TEMPS IN EXCESS OF 600 ON LANDING. BRAKE NOT EFFECTIVE ON LANDING. PAX DEPLANED ON TAXI WAS A/CSWAPPED. FLT CONT. -C/A-PREFORMED CMC DOWNLOAD FOUND FAULT CODE 32411017BCM OUTBD 28V INPUT FAULT FOLLOWED BY 32411002BCM OUTBD SHUTOFF VALVE FAULT INITIAL INSPECTION FOUND BRK OUTBD C/B F10 AND INTEGRATED STBY PWR2 C/B B9 OUT, RESET BOTH CIRCUIT BREAKERS AND PREFORMED MAIN BRAKE OPS TEST IAW AMM 32-41-00-710-801 AND CMC IBIT TEST FOR BCM1 RESISTANCE TEST, PR PULSE INIT TEST, AND SHUTOFF VLV INIT TEST IAW AMM 45-45-00 ALL TEST PASS AND BRAKE SYSTEM OPERATIONAL CHECKS GOOD. WITH NO FURTHER FAULTS.
TRANSFERED FROM ERS-EJ-53MR-4800 (STEP 21) - ACCOMPLISHMENT OF THIS MAJOR REPAIR REQUIRES AIRWORTHINESS RELEASE IAW GPM 12-05.(MAJOR REPAIR)-C/A-C/W AIRWORTHINESS RELEASE ON AML PAGE 4752605 DUE TO MAJOR REPAIR ERS-EJ-53MR-4800.
MAIN DOOR SLIDE DETACHED. COFIRMED REMOVAL OF MAIN DOOR SLIDE IAW AMM 25-65-01.
FIRE LH INBD BRAKE. PAX DEPLANED VIA JB NO INJURIES REPORTED. OPEN
IN FLIGHT CLIMBING THROUGH APPROX FL 260 PAX DOOR AFT OPEN L2 RAN QRH PROCEDURE, HAD 2 GREEN INDICATORS AND NORMAL PRESSURIZATION. MEL 52-22, AUTH 090257M-C, LGPG 4673956, ITEM 1. C/A: INTERROGATED DOOR PAX AFT OPEN WARNING, CODE NR 52122111PSS REF E175 FIM 52-72-00. FOUND FRAME SIDE SENSOR TARGET INDICATOR BINDING, NO SPRING ACTION. R&R SPRING AND LUBED TARGET. E175 AMM 53-23-21 SUBTASK 020-013-A AND AMM 53-23-21-640-801-A. TARGET STILL BINDING. UPDATED KVA. MEL REMAINS OPEN. PLACARD STILL INSTALLED.
DDOR PAX AFT OPEN AT CRUISE FAS REPORT ALL LOCKED INDICATORS NORMAL. PRESSURIZATION ALSO NORMAL. INDICATION CLEARED ON DESCENT-C/A-DEFERRED AFT PAX DOOR INDICATION PER MEL 52-22
FA REPORTS LEFT FORWARD ENTRY DOOR VERY HARD TO OPEN AND CLOSE. CLEANED AND LUBED THE LEFT FORWARD MAIN DOOR HANDLE, IAW MTX PRACTICE 175 AMM 52-11-00 OP CK GOOD AT THIS TIME
CRESENT MOON GOUGE ON LT SIDE OF TAIL JACK POINT EXTERIOR SKIN. REPAIRED THE SKIN IAW ERS-EJ-53-MR-4147.
THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE IN THE CENTER FUSELAGE III AFT CABIN FLOOR STRUCTURE BY REPLACEMENT OF THE FOLLOWING PARTS: P/N 170-91919-001 RH SHEAR PANEL P/N 170-86125-001 FR89 RH FLOOR SPLICE. REPLACEMENT OF PARTS WILL BE ACCOMPLISHED IN ACCORDANCE WITH EMBRAER PRODUCTION DRAWINGS LISTED IN TABLE 2 AND SRM PART II CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT BE REQUIRED FOR DIRECT REPLACEMENT OF PARTS. BECAUSE THE CABIN FLOOR STRUCTURE IS PSE PER THE EMBRAER SRM AND ITS REPLACEMENT IS COMPLEX, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY COMPASS ENGINEERING AS A MAJOR REPAIR. WO# 2822891-343
CORROSION 192CR ATTACH FLANGE. REPLACED 192CR ATTACH FLANGE REF SRM 51-40-08 PAINTED REF SRM 51-23-06. WO# 2822891-489
CORROSION 192DL ATTACH FLANGE. REPLACED 192DL FLANGE REF SRM 51-40-08 PAINTED TOP COAT SRN 51-23-06. WO# 2822891-490
THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE IN THE CENTER FUSELAGE III AFT CABIN FLOOR STRUCTURE BY REPLACEMENT OF THE FOLLOWING PARTS: P/N 170-91919-001 RH SHEAR PANEL P/N 170-86125-001 FR89 RH FLOOR SPLICE. REPLACEMENT OF PARTS WILL BE ACCOMPLISHED IN ACCORDANCE WITH EMBRAER PRODUCTION DRAWINGS LISTED IN TABLE 2 AND SRM PART II CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT BE REQUIRED FOR DIRECT REPLACEMENT OF PARTS. BECAUSE THE CABIN FLOOR STRUCTURE IS PSE PER THE EMBRAER SRM AND ITS REPLACEMENT IS COMPLEX, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY COMPASS ENGINEERING AS A MAJOR REPAIR. WO# 2822891-348
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.
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.
THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE IN THE CENTER FUSELAGE III AFT CABIN FLOOR STRUCTURE BY REPLACEMENT OF THE FOLLOWING PART: P/N 1170-86125-001 FR89 RH FLOOR SPLICE REPLACEMENT OF PARTS WILL BE ACCOMPLISHED IN ACCORDANCE WITH EMBRAER PRODUCTION DRAWINGS LISTED IN TABLE 2 AND SRM PART II CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT BE REQUIRED FOR DIRECT REPLACEMENT OF PARTS. BECAUSE THE CABIN FLOOR STRUCTURE IS PSE PER THE EMBRAER SRM AND ITS REPLACEMENT IS COMPLEX, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY COMPASS ENGINEERING AS A MAJOR REPAIR. EO E175-53MR-488 IS BEING ACCOMPLISHED BY WO 2837261
THIS EO IS BEING ISSUED TO PROVIDE INSTRUCTIONS TO ACCOMPLISH THE PERMANENT REPAIRS OF CORROSION DAMAGE IN THE CENTER FUSELAGE III AFT CABIN FLOOR STRUCTURE BY REPLACEMENT OF THE FOLLOWING PART: P/N 170-91919-001 RH SHEAR PANEL REPLACEMENT OF PARTS WILL BE ACCOMPLISHED IN ACCORDANCE WITH EMBRAER PRODUCTION DRAWINGS LISTED IN TABLE 2 AND SRM PART II CHAPTER 51 PRINCIPLES. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT BE REQUIRED FOR DIRECT REPLACEMENT OF PARTS. BECAUSE THE CABIN FLOOR STRUCTURE IS PSE PER THE EMBRAER SRM AND ITS REPLACEMENT IS COMPLEX, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY COMPASS ENGINEERING AS A MAJOR REPAIR. EO E175-53MR-488 IS BEING ACCOMPLISHED BY WO 2837261
DURING THE B2 BASIC CHECK AT EAMS, CRACK DAMAGE WAS DISCOVERED ON THE LH HORIZONTAL STABILIZER RIB 12A FLANGE. THIS EO IS BEING ISSUED TO ACCOMPLISH THE PERMANENT REPAIR OF THE LH HORIZONTAL STABILIZER RIB 12A BY REMOVING AND REPLACING IT WITH A NEW PART. PART REPLACEMENT WILL BE ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN THE REFERENCES AND SRM CHAPTER 51 STANDARD PRACTICES. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE PART. BECAUSE THE LH HORIZONTAL STABILIZER RIB 12A IS PSE AND ACCESS FOR REPLACEMENT IS COMPLEX, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY COMPASS ENGINEERING AS A MAJOR REPAIR. EO E175-55MR-037 IS BEING ACCOMPLISHED BY WO 2836858
DURING THE B2 BASIC CHECK AT EAMS, CRACK DAMAGE WAS DISCOVERED ON THE RH HORIZONTAL STABILIZER RIB 12A FLANGE. THIS EO IS BEING ISSUED TO ACCOMPLISH THE PERMANENT REPAIR OF THE RH HORIZONTAL STABILIZER RIB 12A BY REMOVING AND REPLACING IT WITH A NEW PART. PART REPLACEMENT WILL BE ACCOMPLISHED IN ACCORDANCE WITH EMBRAER DRAWINGS LISTED IN THE REFERENCES AND SRM CHAPTER 51 STANDARD PRACTICES. SUPPLEMENTAL FOLLOW-ON INSPECTIONS ARE NOT BE REQUIRED FOR DIRECT REPLACEMENT OF THE PART. BECAUSE THE RH HORIZONTAL STABILIZER RIB 12A IS PSE AND ACCESS FOR REPLACEMENT IS COMPLEX, ACCOMPLISHMENT OF THIS EO HAS BEEN CLASSIFIED BY COMPASS ENGINEERING AS A MAJOR REPAIR. EO E175-55MR-036 IS BEING ACCOMPLISHED BY WO 2836857
FWD R/H EMERGENCY EXIT LIGHT INOP. R&R FWD RH EMERGENCY LIGHT POWER UNIT (ELPU) OPS CHECK GOOD IAW AMM 33-50-01. OK FOR SVC.
FWD AND AFT FA FLASHLIGHT BULB INOP. REMOVE AND REPLACE FWD AND AFT FLASHLIGHT BULB IAW CMM 25-60-02 OK FOR SERVICE.
FLIGHT AIR RETURNED SHORTLY AFTER TAKEOFF, DUE TO A SMOKE ODOR IN THE COCKPIT. AN EMERGENCY WAS DECLARED AND LANDED SAFELY. STRONG ELECTRICAL ODOR THOUGHOUT ACFT, WORSE IN CABIN. PERFORMED FIM TASK 21-20-00-810-801-A. NO DEFECTS NOTED. PERFORMED ENG RUN AND OPS CHECKED BLEED SYS IAW AMM 36-11-00. NO DEFECTS OR ODORS NOTED. OK FOR SVC.
CREW REPORTED, LANDING GEAR NOT RETRACTING. FLIGHT HAS DECLARED AN EMERGENCY AND HAS ELECTED TO DIVERT TO OAK. AT 6000' QRH 13.5 FOLLOWED SELECTING GEAR UP. GEAR RETRACTED NORMAL WITH ALL INDICATIONS NORMAL. NO OVERWEIGHT SITUATION IN OAK. AIRCRAFT WILL REQUIRE TO BE FERRIED TO A FACILITY WHERE GEAR SWINGS CAN BE CONDUCTED. UNABLE TO RAISE GEAR LEVER ON T/O. FOLLOWED QRH 13.5 - NO LG WOW SYS FAIL EICAS MSG. PRESS AND HELD DN LOCK REL GEAR LEVER UP AND ALL IND NORMAL. WAS NOT AN OVER-WEIGHT LANDING. PERFORMED FIM TASK 32-33-00-810-801. FOUND TO BE FAILURE OF THE SPDA1 SLOT 13 REMOVED & REPLACED SPDA1 SLOT 13 IAW AMM 24-61-13. PERFORMED LANDING GEAR EXTENSION AND RETRACTION ON JACKS OPS TEST IAW AMM 32-33-00-710-801. OPS CHECK GOOD. NO FURTHER DEFECTS NOTED AT THIS TIME. A/C OK FOR SVC.
R2 DOOR EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED A BLOWN FUSE IN POWER SUPPLY IAW SMPE 17X-33-002 REV 1. OPS CHECKED GOOD. ACFT OK FOR SERVICE.
CEILING LIGHT AT ROW 16 INOPERATIVE. REMOVED AND REPLACED EMERGENCY LIGHT POWER UNIT IAW AMM 33-50-01. OPS CHECKED GOOD. ACFT OK FOR SERVICE.
L1 DOOR EXIT IDENTIFIER INOPERATIVE. R & R L1 DOOR EXIT IDENTIFIER IAW AMM 33-50-15. OK FOR SERVICE.