N267JB

Part: ACTUATOR — FAILED (AILERONS) · airframe 43,579 hrs · 28,460 cycles

FLT#483, BOS-RDU. (AIRCRAFT DECLARED AN EMERGENCY AND PERFORMED AN AIR TURN BACK TO BOS) 'AUTO PILOT FAIL INFLIGHT AILERONS VERY DIFFICULT TO MOVE MANUALLY; FOUND AILERON TRIM ACTUATOR SLOW TO MOVE - OCCAISONALLY UNRESPONSIVE. REMOVED AND REPLACED AILERON TRIM ACTUATOR IAW AMM 27-14-01. OPS CHECKS GOOD.

Part: PCU — FAILED (RT AILERON) · airframe 43,491 hrs · 28,393 cycles

AIRCRAFT DECLARED AN EMERGENCY AND PERFORMED AND AIR TURN BACK TO BOS. AIRCRAFT FLIGHT CONTROLS STIFF AND DIFFICULT TO TURN. AIRCRAFT WOULD NOT MAINTAIN LATERAL COURSE WITH AUTO PILOT ON. AUTO PILOT FAILED. NO ABNORMAL INDICATIONS ON ANY SYSTEMS PAGE. BOTH CAPTAIN AND FIRST OFFICER CONTROLS EFFECTED; REF ITEM #2 OF LOG PAGE 3885671 (REMOVED AND REPLACED THE AILERON INBD PCU IAW AMM 27-12-01. OPS CHECK OK. ) AND ITEM #2 OF LOG PAGE 3885672 (C/W THE RIGGING OF THE AILERON PCU PER AMM 27-12-01. C/W THE RIGGING OF THE AILERON POSITION SENSOR PER AMM 27-13-02. RIGGING AND OPS CHECK SATIFACTORY.) FOR CORRECTIVE ACTIONS.

Part: ANTI-ICE VALVE — FAILED (WING-ANTI-ICE-RH) · airframe 43,205 hrs · 28,206 cycles

FLT#2783, BOS-RDU. (AIRCRAFT PERFORMED AN AIR TURN BACK TO BOS) 'A-I WING FAIL MULTIPLE OCCASIONS. COMPLIED WITH QRH. MESSAGE PERSIST; REMOVED AND REPLACED LH WING ANTI-ICE VALVE AND WING LH A-I PRESSURE SENSOR IAW AMM 30-11-01 AND AMM 30-11-03. RESPECTEVELY. OPS CHECK OK. OK TO CONTINUE.'

Part: SHUTOFF VALVE — FAILED (720001-01-001-RH) · airframe 41,584 hrs · 26,916 cycles

FLT#2231, BOS-LGA. (AIRCRAFT PERFORMED AN AIR TURN BACK TO BOS) 'DURING CLIMBOUT IN ICING CONDITIONS BLEED 2 FAILED UNABLE TO RESET PER QRH RETURNED TO BOS TO AVOID ICING CONDITIONS; REMOVED AND REPLACED PRSOV IAW AMM 36-11-03. OPS GOOD. AT THIS TIME NO FAULTS.'

Part: LIGHT — INOPERATIVE · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: DURING INTERIOR LIGHTS CHECK, EMERGENCY LIGHTS FROM CEILING PANEL 227BLC, 233ALC, 243CLC, 243GLF, AND 243ELC ARE INOPERATIVE; REF TOMX WO # 1997 N/R# 00465. TROUBLESHOOTING WAS PERFORMED PER EMB-190 FIM 33-50-00-810--813-A AND EMB-190 FIM 33-50-00-810-802-A AND ELPUS WERE REPLACED PER EMB-190 AMM 33-50-01-000-801-A AND EMB-190 AMM33-50-01-400-801-A SATISFACTORY TEST. (SUPPLEMENTAL INFORMATION ADDED TO ATA CODE)

Part: FLOOR SPLICE — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: INITIAL INSPECTION: "CPCP FINDING": CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 76 AND STGR 28RH/29RH; SUMMARY OF NRC 00272: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 76 AND STGR 28RH/29RH WAS REMOVED AND EVALUATE ORIGINAL THICKNESS IS .040" AND THE MINIMUM REMAINING THICKNESS IS 0.010" THEREFORE ITS OUT LIMITS, SHEAR CLIP WAS REPLACED PER EMB-190 SRM 51-12-01 PAR. 6 AND SRM 51-10-03 PAR. 4 A AND SRM 51-75-16 AND SRM 51-41-01, AND THE AREA WAS IDENTIFIED PER JETBLUE GMM 8.- 18.4.1 PAR. 13, REV. 29. ACC BY 201534008, INSP BY# 200900620. (CONSIDERED A MAJOR REPAIR) (SUPPLEMENTAL INFORMATION ADDED TO ATA CODE)

Part: FLOORBEAM — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: INITIAL INSPECTION: “CPCP FINDING”: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 82 AND STGR 28LH/29LH; SUMMARY OF NRC 00291: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 82 AND STGR 28LH/29LH WAS REMOVED AND EVALUATE ORIGINAL THICKNESS IS .040" AND THE MINIMUM REMAINING THICKNESS IS 0.010" THEREFORE ITS OUT LIMITS, THE SHEAR CLIP WAS REPLACED PER EMB-190 SRM 51-12-01 PAR. 6 AND SRM 51-10-03 PAR. 4 A AND SRM 51-75-16, SRM 51-41-01 AND SRM 51-41-02 ACC BY # 201429082, INSP BY # 201532960. (CONSIDERED A MAJOR REPAIR)

Part: FLAP TRACK — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: WING / LH WING / FIXED LEADING EDGE / SKIN PANEL / RIB 19 - 20 / CRACK. PERMANENT REPAIR. (CONSIDERED A MAJOR REPAIR)

Part: SLAT TRACK — CRACKED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: CRACK ON SLAT TRACK #5 CUTOUT AT LH WING FIXED LEADING EDGE UPPER SKIN; REF TOMX WO # 1997 N/R# 00208. SLAT TRACK #5 CUTOUT AT LH WING FIXED LEADING EDGE UPPER SKIN WAS REPAIRED PER.EMB-190 ETI-190-22-600 REV ORIGINAL, EC E22-532-01 AND ETD2022-190-021091 REV. .

Part: SPAR — CRACKED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: A 0.343” LENGTH CRACK WAS FOUND AT RH PYLON INBOARD SPAR AFT BUSHING BORE; REF TOMX WO# 1997 N/R# 00403. RH PYLON INBOARD SPAR WAS REPLACED PER EMB-190 S.R.M. 51-43-03 AND S.R.M. 51-43-04. .

Part: FLOORBEAM — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: CORROSIÓN ON FLOOR STRUCTURE RH WEB BTW FR 87-88, W2; REF TOMX NR 00241 WO 1997 WEB FLOOR STRUCTURE RH BTW FR 87-88, W2 WAS REPLACED PER EMB-190 SRM 51-42-01. .

Part: FLOOR SUPPORT — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: INITIAL INSPECTION: “CPCP FINDING”: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 73 AND STGR 27LH/28LH; SUMMARY OF NRC 00287: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 73 AND STGR 27LH/28LH WAS REMOVED AND EVALUATE ORIGINAL THICKNESS IS .040" AND THE MINIMUM REMAINING THICKNESS IS 0.011" THEREFORE ITS OUT LIMITS, SHEAR CLIP WAS REPLACED PER EMB-190 SRM 51-12-01 PAR. 6 AND SRM 51-10-03 PAR. 4 A, SRM 51-75-16, SRM 51-41-01 AND IDENTIFIED AREA PER JETBLUE GMM 8.18.4.1 PAR.13 REV- REF NR #287 ACC BY # 200702030, INSP BY # 200002656. (CONSIDERED A MAJOR REPAIR)

Part: FLOOR SKIN — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: FUSELAGE / CENTER FUSELAGE III / FR82-83 & STGR 22L / CORROSION. PERMANENT REPAIR. (CONSIDERED A MAJOR REPAIR)

Part: FLOORBEAM — CORRODED (FS87-88) · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: CORROSIÓN ON FLOOR STRUCTURE CENTRAL WEB BTW FR 87-88; W2; REF. TOMX WO.1997 NR-00240 - FLOOR STRUCTURE CENTRAL WEB BTW FR 87-88; W2 WAS REPLACED PER.EMB-190 SRM 51-42-01.

Part: BUSHING — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: CORROSION ON BUSHING HOUSING AT RH FITTING ASSY FRAME 100 INBD/OUTBD LUG; REF TOMX WO# 1997 N/R# 00424. BUSHING HOUSING AT RH FITTING ASSY FRAME 100 INBD/OUTBD LUG WERE REPAIRED PER ETI-190-22-612 REV. 7, ETD2022-190-021932 REV. ORIG & EC: E22-593-01. .

Part: SPAR — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: CORROSION ON SHARE CLIP BTW FR 16 AT STGR 28R AND STGR 28L ON FWD CARGO COMPARTMENT; REF TOMX WO# 1997 N/R# 00314. SHARE CLIP BTW FR 16 AT STGR 28R AND STGR 28L ON FWD CARGO COMPARTMENT WAS REPLACED PER EMB 190 SRM 51-43-01 AND SRM 51-41-02, NO ADDITIONAL ACTION OR INSPECTION IS REQUIRED. .

Part: FLOOR SUPPORT — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: INITIAL INSPECTION: “CPCP FINDING”: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 83 AND STGR 21LH/22LH; SUMMARY OF NRC 00298:CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 83 AND STGR 21LH/22LH WERE REMOVED AND EVALUATE THE ORIGINAL THICKNESS IS .040" AND THE MINIMUM REMAINING THICKNESS IS 0.011" THEREFORE ITS OUT LIMITS, SHEAR CLIP WAS REPLACED PER EMB-190 SRM 51-10-03 PAR 4.D, SRM 51-75-16 PAR 4., SRM 51-75-16, SRM 51-41-01 SRM 51-41-02 AND IDENTIFIED AREA PER JETBLUE GMM 8.18.4.1 PAR. 13, REV. 29. REF NR #298 ACC BY # 200702030, INSP BY 200002656. (CONSIDERED A MAJOR REPAIR)

Part: HINGE — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: FUSELAGE / REAR FUSELAGE / H. STABILIZER HINGE / FR 100 / RH FITTING/ MISALIGNMENT - TEMPORARY REPAIR. (CONSIDERED A MAJOR REPAIR)

Part: SHEAR TIE — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: INITIAL INSPECTION: “CPCP FINDING”: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 78 AND STGR 24LH/25LH; SUMMARY OF NRC 00264: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 78 AND STGR 24LH/25LH WAS REMOVED AND EVALUATE ORIGINAL THICKNESS IS .050" AND MINIMUM REMAINING THICKNESS IS 0.005" THEREFORE ITS OUT LIMITS, THE SHEAR CLIP WAS REPLACED PER EMB-190 SRM 51-12-01 PAR. 6 AND SRM 51-10-03 PAR. 4 A AND SRM 51-75-16 PAR 4 AND SRM 51-41-01 AND SRM 51-41-02 AND AREA WERE IDENTIFIED PER JETBLUE GMM 8.18.4.1 PAR.13 REV.29. REF NR 264 ACC BY #200702030, INSP BY #200002656. (CONSIDERED A MAJOR REPAIR)

Part: FLOOR SKIN — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: INITIAL INSPECTION: “CPCP FINDING”: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 78 AND STGR 23LH/24LH; SUMMARY OF NRC 00265: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 78 AND STGR 23LH/24LH WAS REMOVED AND EVALUATE ORIGINAL THICKNESS IS .050" AND MINIMUM REMAINING THICKNESS IS 0.015" THEREFORE ITS OUT LIMITS SHEAR CLIP WAS REPLACED PER EMB-190 SRM 51-12-01 PAR. 6 AND SRM 51-10-03 PAR. 4 A AND SRM 51-75-16 PAR 4 AND SRM 51-41--01 AND AREA WERE IDENTIFIED PER JETBLUE GMM 8.18.4.1 PAR. 13, REV. 29. REF NR# 265 ACC BY # 200702030, INSP BY# 200900620. (CONSIDERED A MAJOR REPAIR)

Part: SHEAR RESTRAINT — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: INITIAL INSPECTION: “CPCP FINDING”: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 78 AND STGR 22LH/23LH; SUMMARY OF NRC 00266: CORROSION ON AFT CARGO INTERNAL STRUCTURE SHEARCLIP BTW FR 78 AND STGR 22LH/23LH WAS REMOVED AND EVALUATE ORIGINAL THICKNESS IS .050" AND MINIMUM REMAINING THICKNESS REF N^ #266 ACC BY # 201534008, INSP BY # 200801852 IS 0.010" THEREFORE ITS OUT LIMITS SHEAR CLIP WAS REPLACED PER EMB-190 SRM 51-12-01 PAR. 6 AND SRM 51-10-03 PAR 4 A AND SRM 51-75-16 PAR 4 AND SRM 51-41-01 AND AREA WAS IDENTIFIED PER JETBLUE GMM 8.18.4.1 PAR. 13, REV. 29. (CONSIDERED A MAJOR REPAIR)

Part: STRINGER — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: CORROSION ON STGR21L BTW FR83/FR82 AFT CARGO COMPARTMENT; REF TOMX N/R 00381 WO 1997 STGR22L BTW FR83/FR82 AFT CARGO COMPARTMENT WAS REPLACED PER EMB-190 SRM 53-23-00 REPAIR 51, THERE IS NO CHANGE TO THE MAINTENANCE PLAN DUE TO THIS REPAIR INSTALLATION.

Part: STRINGER — CORRODED · airframe 40,206 hrs · 25,852 cycles

DURING HEAVY MAINTENANCE: INITIAL INSPECTION “CPCP FINDING”: CORROSION LOCATED ON SPLICE STRG 21L AND BETWEEN FR 88/89 INTERNAL STRUCTURE CF III; IN COMPLEMENT WIP # 14. A NEW SPLICE WAS INSTALLED ON STRG 21LH AND BETWEEN FR 88/89 INTERNAL STRUCTURE CF III PER EMB 190 SRM 53-23-03, REP 51, PAR 5(O) TO 5(- S).ACC BY # 200802267, INSP BY # 200002656. (CONSIDERED A MAJOR REPAIR)

Part: EXHAUST DUCT — LEAKING · airframe 39,704 hrs · 25,483 cycles

FLT#1527, EWR-FLL. "BLEED 2 LEAK AT FL 150 ON ARRIVAL; ACCOMPLISHED ENG#2 PRECOOLER EXHAUST DUCT RE-SEAL AS PER M.M 54-50-25 & EMBRAER ETD2010/190-10969. ACCOMPLISHED ENG 2 IDLE RUN AND ENG 2 BLEED SYS LEAK/OPS CHECK AS REQUIRED PER M.M. 36-00-00. ALL OPS/IND. NORMAL AT THIS TIME. NO LEAKS DETECTED. OK TO CONTINUE.'

Part: ENGINE — FAULTED (NR 2) · airframe 38,677 hrs · 24,771 cycles

FLT# 1355, BOS-DCA (RETURNED BACK BOS). ENG 1 CONTROL FAULT ITT INDICATION WENT AMBER AND FUEL FLOW WAS 500PPHABOVE #2 DURING CLIMB. ENGINE WOULD NOT MAKE CLIMB 1 THRUST WITHIN ITT LIMITS ; R & R # 1 ENGINE IAW AMM 71-00-01

Part: RIB — CRACKED (RT WING) · airframe 37,007 hrs · 23,745 cycles

DURING HEAVY MAINTENANCE, REF NDT 57-40-00-211-802 CRACK RIB 17 WING MAIN BOX LEADING EDGE AREA RT WING, REF AEROMAN WO 2020-388/1, NR 2020-360939. REMOVED AND REPLACED RIB 17 LOCATED LEADING EDGE ON RT WING, IAW E190-SRM 51-40-08 AND DWG 190-31005-409.

Part: RIB — CRACKED (LT WING) · airframe 37,007 hrs · 23,745 cycles

DURING HEAVY MAINTENANCE, REF NDT 57-40-00-211-802, CRACK RIB 17 WING MAIN BOX LEADING EDGE AREA LT WING, REF AEROMAN WO 2020-388/1, NR 2020-360940. REMOVED AND REPLACED RIB 17 LOCATED LEADING EDGE ON LT WING, IAW E190 SRM 51-40-08 DWG 190-31005-409.

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 37,007 hrs · 23,745 cycles

DURING HEAVY MAINTENANCE, INOPERABLE EMERGENCY LIGHT POWER UNIT AFT RT INBOARD, REF AEROMAN N/R 2020-360932. REMOVED AND REPLACED ELPU, IAW E190 AMM 33-50-01-400-801-A. OPERATIONS CHECK GOOD, IAW E190- 33-50-00-710-801-A.

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 37,007 hrs · 23,745 cycles

DURING HEAVY MAINTENANCE, INOPERABLE EMERGENCY LIGHT BATTERY AFT RT, REF AEROMAN N/R 2020-360931. REMOVED AND REPLACED ELPU, IAW E190-AMM 33-50-01-400-801-A. OPERATIONS CHECK GOOD, IAW E190 AMM 33-50-01-710-801-A.

Part: RIB — CRACKED (LT WING) · airframe 37,007 hrs · 23,745 cycles

DURING HEAVY MAINTENANCE, REF NDT 57-40-00-211-802, CRACK RIB 22 WING MAIN BOX LEADING EDGE AREA LT WING, REF AEROMAN WO 2020-388/1, NR 2020-360941. REMOVED AND REPLACED RIB 22 AND FASTENERS LOCATED LEADING EDGE AREA LT WING, IAW SRM 51-40-08 AND DRAWING 190-31005-409.

Part: SKIN — CRACKED (NR 1 PYLON) · airframe 36,424 hrs · 23,367 cycles

FT # 526, TPA-JFK. #1 ENGINE INBOARD PYLON CRACK (REF ORIGINAL INSP LP 2766591-1); AEROMAN WO# 2019-414/1 WCC# 2019-414201 PERFORMED PROCEDURE TO LH PYLON IB UPPER SPAR LINK SPAR REPLACEMENT ALTERNATE TOOLING PER AEROMAN EA 54-50-76-19 REV 0(COVER 1 PART 1) AND ETD 2019-190-163192

Part: DOUBLER — CORRODED (FRAMES 88-89) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON CNTR FUSE BELOW FLR PNL WASTE PAN DOUBLER; REF NRC FOR ALL WORK ACP. RPL FWD PAN DOUBLER IAW SRM 51-43-04

Part: SKIN — DAMAGED (RUDDER) · airframe 33,384 hrs · 21,195 cycles

DURING BASIC 6 CHECK AT YRQ DATED 11/18, OBJECT IMPACT AND PERFORATION DAMAGE WAS FOUND ON THE RUDDER P/N 190-09910-431 S/N 0000261387 RT SKIN PANEL P/N 190-63064-409. SEE REF. (1) FOR DETAILS. ULTRASONIC INSPECTION WAS ACCOMPLISHED ON THE AREAS SURROUNDING THE DAMAGE AND ON THE PANEL INNER AND OUTER SURFACES, WITH NO ADDITIONAL DAMAGE FOUND. YRQ CONTACTED FOR AN APPROVED DOUBLER REPAIR SINCE YRQ DOES NOT HAVE ACCESS TO AN AUTOCLAVE TO ACCOMPLISH THE SRM REPAIR. PROVIDED THE REF.(1) ETD PROVDING REPAIR DISPOSITION CONSISTING OF INSTALLING A REPAIR DOUBLER PER SRM 55-40-00 REPAIR 51P BUT USING A 1.6MM THICK TI6AL4V REPAIR DOUBLER, JOINING EXISTING COPPER MESH TO THE REPAIR DOUBLER, FILLING EXISTING COUNTERSINKS WITH ADHESIVE, ATTACHING REPAIR DOUBLER WITH SPECIFIED FASTENERS, AND PERFORMING RUDDER BALANCING. THIS EC INCORPORATES THE REF.(1) ETD WITHOUT DEVIATION. THIS REPAIR IS SUBJECT TOFOLLOW-UP EXTERNAL DET INSPECTIONS AT A 15,000 FH THRESHOLD AND 15,000 FH INTERVAL. EC E18-915-02 ACCOMPLISHES THE FOLLOW-UP INSPECTIONS; THIS REPAIR HAS BEEN APPROVED BY THE REF.(2) ANAC FORM. THIS REPAIR IS CLASSIFIED AS A MAJOR PERMANENT REPAIR REQUIRING FOLLOW-UP INSPECTIONS. PROVIDED REF/4 ALLOWING A MINOR DEVIATION TO STEP 9 OF REF/3/ TO PREVENT INTERFERENCE WTIH THE EDGE OF RUDDER AND ADJACENT SPAR.

Part: DIVERTER — BROKEN (APU) · airframe 33,383 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE AT YRQ FOUND WITH A SECTION OF APU OIL COOLER AIR INLET DIVERTER (P/N: 170-50258-005) FOUND BROKEN AND MISSING. ALSO, WHILE INVESTIGATION OF AFFECTED AREA, YRQ FOUND APU COMPARTMENT RT UPPER PANEL CRACKED AT 6 PLACES. DVI AND HFEC INSPECTIONS CARRIED OUT TO DETERMINE FULL EXTEND OF THE CRACKS. SEE REF/2/ DEFINITION SHEET, FIGURE 1 FOR MORE DETAILS. THE DAMAGE AREA WAS EVALUATED PER THE REF/3/ SRM REPAIR AND IT WAS DETERMINED THAT IT IS NOT ALLOWED IN THIS AREA. CONTACTED AND PROVIDED THE REF/1/ ETD REQUIRING THE REF/2/ REPAIR INSTRUCTIONS TO BE ACCOMPLISHED. THE REPAIR CONSIST OF ACCOMPLISH A DOUBLER REPAIR PER THE RED/3/ SRM WITH DEVIATION OF DOUBLER CROSSING FASTENER ROW AND ALLOWS FOR THE INSTALLATION OF (1) ROW OF FASTENERS AS SHOWN IN FIGURE 2 OF THE REF/2/ REPAIR. IT ALSO REQUIRES THE INSTALLATION OF FLOW DIVERTER (P/N 170-50400-001) USING THE INSTRUCTIONS WITHIN THE REF/4/ SB190-49-0005. REF/4/ SB HAS BEEN PARTIALLY COMPLETED. NOTE: THIS IS THE ONLY AIRCRAFT IN THE FLEET THAT HAS THE REF/4/ SB MOD DIVERTER (P/N 170-50400-001) INSTALLED. THIS WAS REQUIRED ON THIS REPAIR FOR 2 REASONS (1. THE PRE-MOD PN 170-50258-005 WAS NOT PROCURABLE AND 2. DUE TO THE SHAPE OF THE PRE-MOD DIVERTER IT WOULD INTERFERE WITH THE REPAIR DOUBLER). FOR THESE REASONS THE POST MOD DIVERTER WAS INSTALLED. THE REF/1/ ETD REPAIR HAS A 5000FH LIFE LIMITATION AND A 600 FH RE-INSPECTION REQUIREMENT. EC E18-1003-01 ACCOMPLISHES THE REF/1/ ETD REPAIR WITHOUT DEVIATION. EC E18-1003-02 ACCOMPLISHES THE POST REPAIR INSPECTIONS (EXTERNAL DVI) EVERY 600 FH PER THE REF/1/ ETD REPAIR WITHOUT DEVIATION. EC E18-1003-03 TRACKS THE REPAIR LIMITATION OF 5000FH PER THE REF/1/ ETD WITHOUT DEVIATION; THIS REPAIR IS APPROVED PER REF /1/ ETD AND IS CLASSIFIED AS TEMPORARY WITH POST REPAIR INSPECTIONS AND MAJOR.

Part: SEAT TRACK — CORRODED (FRAME 17) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON RH INBD TRACK FR17; REF NRC FOR ALL WORK ACP. SEAT TRACK RPL PER SRM 51-41-01/02, 51-43-03

Part: SHEAR TIE — CORRODED (FRAME 72) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON AFT CARGO COMPARTMENT, SHEAR CLIP AT FR 72 AND BTW STR 27L-28L. NOTE: NO ALLOWABLE OR DEFINED LIMITS IN THE SRM, THEREFORE THE PART IS TO BE REPLACED; NOTED SHEAR CLIP (P/N: 190-28351-001) REMOVED AND REPLACED PER SRM 51-41-01 AND 51-41-02. REF. AAR NRC # 4000060-1000-0069. PROJECT NO. N267JB-1

Part: SEAL REST — CORRODED (CARGO DOORWAY) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON AFT CARGO DOOR CUT OUT LWR CRNR SEAL REST; REF NRC FOR ALL WORK ACP: RPL SEAL REST IAW SRM 53-23-29 FIG20

Part: SHEAR TIE — CORRODED (FRAME 88) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON CNTR FUSE 111 BELOW CABIN FLR SHEAR CLIP FR88; REF NRC FOR ALL WORK ACP. SHEAR CLIP RPL SRM 51-41-01, 51-41-02

Part: SEAL REST — CORRODED (CARGO DOORWAY) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON AFT CARGO DR CUT OUT MID LWR SEAL REST; REF NRC FOR ALL WORK ACP: MIDDLE LWR SEAL REST RPL PER SRM 51-41-01

Part: DOUBLER — CORRODED (FRAMES 18-19) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON PASS CABIN FR18-19 FLR SUPP DOUBLER; REF NRC FOR ALL WORK ACP. FLR SUPP DOUBLER CORR RPL IAW SRM 51-41-02, 51-43-04

Part: SHEAR TIE — CORRODED (FRAME 88) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON SHEAR CLIP FR87; REF NRC FOR ALL WORK ACP. SHEAR CLIP RPL AT FR 87 STGR 29L-29R IAW SRM 51-41-01,02,03.

Part: GUSSET — CORRODED (FRAME 90) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON PAX CABIN FR90 RBL11 GUSSET PLATE; REF NRC FOR ALL WORK ACP. RPL GUSSET PLATE IAW SRM 51-41-02

Part: SEAT TRACK — CORRODED (FRAME 17) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON PASS CABIN RH INBD SEAT TRACK CORR FR17; REF NRC FOR ALL WORK ACP. SEAT TRACK RPL IAW SRM 51-41-01/02, 51-43-03

Part: SHEAR TIE — CORRODED (FRAME 89) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON CNTR FUSE III BELOW CABIN FLOOR CORR SHEAR CLIP FR89; REF NRC FOR ALL WORK ACP. SHEAR CLIPS RPL IAW SRM 51-41-01, -02, & 51-43-03.

Part: DOUBLER — CORRODED (FRAME 16) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON PAX CABIN FLR DOUBLER FR16; REF NRC FOR ALL WORK ACP. RPL FLR DOUBLER IAW SRM 51-41-02.

Part: THRESHOLD — CORRODED (FRAMES 77-80) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON AFT CARGO DR CUTOUT CORR THRESHOLD FINGER PLATE; REF NRC FOR ALL WORK ACP. THRESHOLD FWD FINGER PLATE RPL IAW SRM 51-43-03, 51-43-04

Part: CROSSBEAM — CORRODED (FRAME 17) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON PASS CABIN UPR FLANGE CR BEAM FR17; REF NRC FOR ALL WORK ACP: RPL SUPP ANGLE PER SRM 51-43-03.

Part: DOUBLER — CORRODED (FRAMES 19-20) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON RH TRANSPONDER ANTENNA DOUBLER CORRBET FR19 -FR20; REF NRC FOR ALL WORK ACP. RH TRANSPONDER ANT DOUBLER RPL IAW SRM 51-41-02

Part: SHEAR PANEL — CORRODED (FRAMES 87-88) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON PAX CABIN RH SHEAR PNL FR87-88; REF NRC FOR ALL WORK ACP. RH SHEAR PNL RPL IAW SRM 51-42-01, 51-42-03

Part: GUSSET — CORRODED (FRAME 90) · corrosion level 2 · airframe 33,384 hrs · 21,195 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON PAX CABIN GUSSET PLATE FR90 RBL23; REF NRC FOR ALL WORK ACP. RPL GUSSET PLATE IAW SRM 51-41-02

Part: PLATE — LACK OF LUBE (GIRT BAR) · airframe 28,494 hrs · 17,615 cycles

R1 DOOR WOULD NOT DISARM. IT WAS FOUND THAT THE R1 DOOR GIRT BAR WAS CATCHING ON AFT GIRT BAR CLEAT SPRING PLATE. LUBRICATED SPRING PLATE WITH DRY RELEASE LUBRICANT. CYCLED, ARMED R1 DOOR 5 CYCLES. OP CHECKED NORMAL PER AMM 52-41-40.

Part: POWER SUPPLY — FAULTY (MAU) · airframe 28,238 hrs · 17,434 cycles

FLT 2224, MCO-DCA, DIVERTED TO IAD. FLIGHT CREW RECEIVED A STEER FAIL MESSAGE ON EICAS. THEY FOLLOWED THE QRH RESET WITH NO POSITIVE RESULTS. CREW ELECTED TO DIVERT INTO IAD, SINCE THERE WAS HIGH FLIGHT VOLUME INTO DCA. AIRCRAFT LANDED WITHOUT INCIDENT. ; PERFORMED T/S IAW FIM 45-45-00-810-941-A TRANSITORY CONDITION OF MAU 2 POWER SUPPLY 1. PERFORMED RESET IAW 45-45-00. MESSAGE REMOVED. PERFORMED GENERAL VISUAL INSPECTION OF NOSE LANDING GEAR IAW AMM 32-50-00. AIRCRAFT OK FOR SERVICE.

Part: SEAL REST — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON FORWARD CARGO DOOR CUTOUT, CENTER SEAL REST. R & R SEAL REST, PN 170-66804-401.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON RT SEAT TRACK FROM FRAME 12-20, RBL12. R & R SEAT TRACK, PN 170-03263-001.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON PANEL SUPPORT SILL AT FRAME 90, LBL43. R & R PANEL SUPPORT, PN 170-86139-005.

Part: FINGER DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON FORWARD CARGO LOWER BEAM AFT FINGER DOUBLER AT FRAME 25, RBL14. R & R FINGER DOUBLER, PN 170-67115-002.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON SHEAR CLIP AT FRAME 67 BETWEEN STR 27-STR 28. R & R SHEAR CLIP.

Part: FINGER DOUBLER — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON AFT CARGO DOOR FINGER DOUBLER. R & R FINGER DOUBLER, PN 170-85070-001.

Part: BEAM — CORRODED (L1 DOOR) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON L1 DOOR LOWER BEAM UNDER AFT FLOOR FITTING. REPAIRED BEAM IAW ENGINEERING ISSUED EC E16-673-01.

Part: FINGER DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON FWD CARGO LOWER BEAM FWD FINGER DOUBLER AT FRAME 24; RBL16. R & R FINGER DOUBLER, PN 170-67115-001.

Part: BEAM — CORRODED (L1 DOOR) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON L1 DOOR LOWER BEAM 9.5 " AFT OF FRAME 18, LBL49. REPAIRED BEAM IAW ENGINEERING ISSUED EC E16-658-01 AND ETD 2016-190-072982.

Part: BEAM — CORRODED (R1 DOOR) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON R1 DOOR LOWER BEAM 10.75" AFT OF FRAME 16, RBL49. REPAIRED BEAM IAW ENGINEERING ISSUED EC16-660-01.

Part: SEAL REST — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED AFT CARGO DOOR LOWER CENTER SEAL REST. R & R SEAL REST, PN 170-85251-401.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON FORWARD CARGO O2 BOX CUTOUT AT FRAME 23+6, STR 20R. R & R REPLACED STRINGER, PN 170-67342-001.

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,113 hrs · 16,665 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON FWD CARGO DOOR LOWER CUTOUT BEAM AT FRAME 26+9, RBL 17. R & R BEAM, PN 170-67118-003.

Part: BATTERY — FAILED (EMERGENCY LIGHTS) · airframe 26,278 hrs · 16,088 cycles

EMERGENCY LIGHTS IN AISLE STAY ON EVEN WITH ACFT POWDERED DOWN AND WITH THE EMERGENCY LIGHT SWITCH IN THE OFF POSITION; FOUND EMERGENCY BATTERY FAULTED LOCATED ABOVE R1 DOOR. R & R IAW AMM 33-50-01.

Part: CIRCUIT CARD — FAILED (MAU 1) · airframe 22,668 hrs · 13,756 cycles

CREW DECLARED AN EMERGENCY FAILED IN FLIGHT. R & R MAU1 NIC1 CARD IAW AMM 31-41-04. NO FAULTS NOTED.

Part: STRINGER — CORRODED (FRAMES 76-91) · airframe 21,387 hrs · 12,902 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED AT STRINGER 23L BETWEEN FRAMES 76-91. REPAIRED IAW E14-466-01. AND SRM 53-23-03 FIG 25, ITEM 80.

Part: STRINGER — CORRODED (FRAMES 88-89) · airframe 21,387 hrs · 12,902 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON AFT CABIN STRINGER 21L BETWEEN FRAMES 88 - 89. CUTOUT THE STRINGER. PERFORMED HFEC IAW NDT PART 1, 51-00-00-916-803. INSTALLED NEW STRINGER BETWEEN FRAMES 88 - 91. FABRICATED REPAIR PARTS AND INSTALLED NEW STRINGER 21L. C/W IAW E14-466-01 AND SRM 53-23-03, FIG 25, ITEM 100A. RETURN TO NORMAL CONFIGURATION.

Part: STRINGER — CORRODED (FRAME 91) · airframe 21,387 hrs · 21,902 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS FOUND ON STRINGER 21L, FRAME 91. REPAIRED IAW E14-466-01 AND SRM 53-23-03, FIG 25, ITEM 80.

Part: TRACK — CORRODED (GALLEY) · airframe 21,387 hrs · 12,902 cycles

DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED AT FORWARD GALLEY TRACK AT FRAME 16, LBL 11.75". ACCOMPLISH DVI TO ENSURE ALL CORROSION IS REMOVED. FABRICATED REPAIR STRAP, APPLIED A COAT OF INTERFACE SEALANT. TREAT THE REPAIR PARTS WITH A PROTECTIVE FINISH. FILLED ANY REWORKED AREAS AS REQUIRED. TREATED, TOP COATED NEW DOUBLER, IAW E14-455-01 AND SRM 53-10-10, FIGURE 56A, ITEM 260.

Part: WARNING MESSAGE — ILLUMINATED (NR 1 BLEED) · airframe 21,096 hrs · 12,695 cycles

BLEED 1 FAIL AT FL280. PERFORMED EMERGENCY DESCENT TO 10000 CABIN ALT REACHED 9300. ACFT DIVERTED IAW FIM 36-10-00-810-804-AA, NO CORRELATED OR ACTIVE MESSAGES, INSPECTED BLEED 1 PRESSURE SENSOR TUBE, NO DEFECTS NOTED. R & R NR 1 BLEED PRESSURE SENSOR IAW E190MM 36-14-02, GROUND RAN ACFT, OPS CHECK GOOD AT THIS TIME. THE NR 2 ENGINE NPRSOV WAS R & R IAW E190MM 36-11-03.

Part: WIRE — MISINSTALLED (NR 1 A/C PACK) · airframe 20,266 hrs · 12,180 cycles

AIR RETURN AND EMERGENCY EVACUATION DUE TO SMOKE IN COCKPIT AND CABIN. INSPECTION ACCOMPLISHED AND FOUND NR 1 ACM AT FAULT. REMOVED AND REPLACED ACM IAW AMM 21-51-05. ACCOMPLISHED EC E14-150-01. FURTHER INSPECTION FOUND LT PACK CONDENSER INLET TEMP SENSOR AND PACK OUTLET TEMP SENSOR WIRING CROSSED. RESTORED WIRING TO NORMAL CONFIGURATION. PERFORMED OPS CHECK OF BOTH LT & RT PACKS IAW AMM 21-51-00-710-801-A. WITH NO DEFECTS NOTED.

Part: ACM — FAILED (RIGHT) · airframe 20,035 hrs · 12,039 cycles

CREW DECLARED AN EMERGENCY DUE TO SMOKE IN CABIN AND SMOKE STOPPED WHEN "CABIN IFE" WAS TURNED OFF. EXECUTED SMOKE CABIN SMOKE QRH TO IDENTIFY IFE, THEN EXECUTED SMOKE/FUME REMOVAL QRH TO DISIPATE SMOKE. SUSPECT SMOKE WAS FROM IFE BECAUSE IT STOPPED WHEN REMOVED POWER FROM IFE IAW QRH PROCEDURE. ACCOMPLISHED FIM TASK 21-20-00-810-801-A NO ABNORMALITIES NOTED. ACCOMPLISHED ELECTRICAL ODOR INTEGRITY CHECK IAW MM 44-20-10, PAGES 5034-5036 VISUAL AND SENSORY INSPECTION SHOW NO EVIDENCE LTV SYSTEM IS COMPROMISED. ALL OPS NORMAL. FOUND DEBRIS ON HEAT EXCHANGER. RT AIR CYCLE MACHINE AND DUAL HEAT EXCHANGER WAS R & R IAW AMM 21-51-04 AND 21-51-05. OPS AND LEAK CHECKED GOOD.

Part: ACM — FAILED (AC BAY) · airframe 16,624 hrs · 9,893 cycles

FLT 1736 SJU-FLL, CREW DECLARED EMERGENCY AND AIRCRAFT RETURN TO SJU DUE TO VISIBLE SMOKE IN COCKPIT AND CABIN DURING CLIMBOUT. SMOKE OF SOURCE COULD NOT BE IDENTIFIED. PERFORMED SMOKE AND ABNORMAL SMELL IN CABIN AND COCKPIT CHECK IAW FIM 21-20-00-810-801A FOUND ACM AT FAULT. WHEN PACK NR 1 IS SWITCHED ON, BURN SMELL FILLS THE COCKPIT. REMOVED AND REPLACED PACK NR 1 ACM AS PER AMM 21-51-05. OPS CHECK PER AMM 21-51-00-710-801-A500 ALL PARAMETERS OK.

Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 16,576 hrs · 9,858 cycles

FLT 6410 JFK-BNA, ON HEAVY MAINTENANCE CHECK FOUND FWD CABIN FR 17 CROSSBEAM CORRODED LBL 9 TO RBL 40. FABRICATED L SHAPED REPAIR ANGLES, BLENDED OUT GOUGE DAMAGE, HFEC INSPECTION PERFORMED AS PER EC E12-758-01.

Part: CONTROLLER — FAILED (COCKPIT) · airframe 15,239 hrs · 8,965 cycles

FLT 254 DFW-BOS, WHILE DESCENDING THROUGH FLT 17000 FEET THE F/O'S WINDSHIELD OUTER LAYER SHATTERED. REMOVED AND REPLACED WINDOW HEAT CONTROLLER IAW E190 AMM 30-42-01. OPS CHECK GOOD.

Part: CONTROLLER — FAILED (COCKPIT) · airframe 15,239 hrs · 8,965 cycles

FLT 245 DFW-BOS, WHILE DESCENDING THROUGH FL 17000 FEET, THE F/O'S WINDSHIELD OUTER LAYER SHATTERED. REMOVED AND REPLACED WINDOW HEAT CONTROLLER IAW E190 AMM 30-42-01. OPS CHECK GOOD.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 15,239 hrs · 8,965 cycles

FLT 254 DFW-BOS, WHILE DESCENDING THROUGH FLT 17,000 FEET THE F/O'S WINDSHIELD OUTER LAYER SHATTERED. REMOVED AND REPLACED F/O WINDSHIELD IAW AMM 56-11-00. OPS CHECK NORMAL.

Part: PRESSURE SWITCH — FAILED (NR 1 ENGINE) · airframe 15,184 hrs · 8,936 cycles

FLT 1321 BOS-BWI, CREW DECLARED EMERGENCY DUE TO ENGINE 1 FUEL LO PRESSURE. PERFORMED FIM 73-31-00-810-801A. REMOVED AND REPLACED NR 1 ENGINE FUEL PRESSURE SWITCH IAW AMM 73-31-01. OPS AND LEAK CHECK OK.

Part: AMPLIFIER — FAILED (HF SYSTEM) · airframe 14,757 hrs · 8,641 cycles

FLT 1731, AIR TURNBACK DUE TO HF TUNING FAILED, UNABLE TO TRANSMIT USING LOW, MED, HIGH TRANSMIT POWER. PERFORMED TROUBLESHOOTING, REMOVED AND REPLACED HF TRANSCEIVER AND HF ANTENNA COUPLER IAW AMM 23-11-03 AND AMM 23-11-01. OPS CHECKED NO HELP. IHF AMPLIFIER WAS REMOVED AND REPLACED IAW AMM 23-11-04-04. OPS CHECK OK.

Part: ROD — BROKEN (TE FLAP) · airframe 11,090 hrs · 6,387 cycles

FLT 1056 PIT-JFK, ON TAKE OFF NOTICED MODERATE TRIM/ROLL WITH FLAPS EXTENDED. OPPOSITE TRIM REQUIRED WHEN FLAPS RETRACTED. UPON LANDING SIGNIFICANT ROLL/TRIM REQUIRED WHEN FLAPS EXTENDED. REMOVED AND REPLACED NR 1 AND NR 2 LT AND RT MAIN FLAP CARRIAGE LOWER ROD ASSY ON INBD FLAP. OPS CHECK GOOD.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 10,992 hrs · 6,331 cycles

FLT 6403 JFK-BNA, ON SCHEDULE MAINT CHECK FOUND LT FLOORBEAM AT Y=273.0L CORRODED BETWEEN FRAMES 16,17 & 18. REMOVED CORROSION REF SRM 51-12-00. REPAIRED DAMAGE AS PER JETBLUE EA E10-735-01 REVISION 12-9-10 REF EAMS H1908-2605. REPAIR WAS CLASSIFIED AS MAJOR REPAIR.

Part: ACM — FAILED (AC BAY) · airframe 8,780 hrs · 5,103 cycles

FLT JB1762 SJU-FLL AIR TURN BACK TO SJU, CREW REPORTED AT CLIMBOUT THROUGH 10000 FT SMELL AND VISIBLE INDICATION OF SMOKE IN COCKPIT AND CABIN. AIRCRAFT RETURNED TO SJU AND ACCOMPLISHED EVACUATION L1, L2 R1 AND R2 DOOR SLIDES DEPLOYED. MX PERFORMED AMM FIM 21-20-810-801-A FOR SMOKE/SMELL IN PAX CABIN AND COCKPIT DETECTED METAL SMELL IN CABIN PRESENT WHEN NR 1 PACK RUNNING. STATIC TORQUE CHECK OF LT PACK ACM FAILED. REMOVED AND REPLACED NR 1 PACK ACM PER AMM 21-51-05-04, LEAK CHECK AND OPS CHECK NORMAL.

Part: CONTROL LEVER — FAULTY (COCKPIT) · airframe 7,932 hrs · 4,599 cycles

FLT 1244 CLT-BOS - DECLARED AN EMERGENCY FOR "FLAP FAIL" EICAS MESSAGE WITH FLAPS ZERO ON LANDING. MX TROUBLESHOT FLAPS PER AMM 27-51-00-810-802-A FOUND FLAP SLAT CONTROL LEVER AT FAULT. REMOVED AND REPLACED SLAT FLAP CONTROL LEVER AND FUNCTIONAL CHECKED OK IAW AMM 27-53-01. CHECKED FLAP TORQUE LIMITER TRIP INDICATORS ALL NORMAL, GREASED LEFT FLAP JACK SCREWS AND RE-RIGGED FLAP CONTROL SYSTEM PER AMM 27-50-00, ALL CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: ELECTRICAL SYS — FAILED (SLAT/FLAP SYS) · airframe 7,846 hrs · 4,548 cycles

FLT JB624 - HOU-JFK "FLAP FAIL" EICAS MESSAGE ON APPROACH TO JFK FLAPS/SLATS 0 APPROACH. FL4000 AT 210 KTS SELECTED FLAPS 1 AND SLATS EXTENDED BUT FLAPS DID NOT, DID NOT RECEIVE "LO RATE" MESSAGE. CREW DECLARED EMERGENCY AIRCRAFT LANDED SAFELY. MX PERFORMED TROUBLESHOOTING PER FAULT CODE 27532018ACE, REMOVED AND REPLACED S-FACE NR 1 OPS CHECK GOOD. CYCLED FLAPS SEVERAL TIMES IAW AMM 27-53-02, NO FAULTS FOUND. AIRCRAFT RETURNED TO SERVICE.

Part: ACM — ODOR (NR 1)

PACK 1 INOPERATIVE EICAS DISPLAYED IN FLIGHT. QRH RESET SUCCESSFUL. ON SHORT FINAL NOTICED BURNING ODOR, TURNED OFF PACK 1 AND ODOR WENT AWAY. REMOVED AND REPLACED NR 1 ACM IAW AMM 21-51-00. NO LEAKS NOTED OK TO CONTINUE SERVICE. (K)

Part: POWER UNIT — FAILED (CABIN) · airframe 4,139 hrs · 2,471 cycles

ON MX INSP, ROW 11, RT LOWER EMERGENCY LIGHT INOP. REMOVED AND REPLACED RT CENTER EMERGENCY LIGHT POWER UNIT IAW AMM 33-50-01. OPS CHECK GOOD. (S)

Part: STRUT — UNDERSERVICED (NLG) · airframe 612 hrs · 403 cycles

FLT 5102, AIR TURNBACK DUE LDG VOW SYS FAIL CAS, LANDING GEAR FAILED TO RETRACT. SERVICED NOSE LANDING GEAR SHOCK STRUT IAW AMM 32-21-04. PERFORMED OPS CHECK OF LANDING GEAR RETRACTION SYSTEM IAW 32-33-00-05. OPS TEST GOOD.

Part: ACM — SEIZED (NR 1) · airframe 338 hrs · 222 cycles

FLT 1251, 1029Z, AIR RETURN, SMOKE IN COCKPIT, PACK NR 1 FAIL. PERFORMED TROUBLESHOOTING IAW FIM 21-51-00-810-833A, FOUND PACK NR 1 ACM SEIZED. REMOVED AND REPLACED NR 1 ACM IAW AMM 21-51-05, OPS CK GOOD.

Part: RUDDER — OUT OF RIG · airframe 217 hrs · 130 cycles

AFTER APPLICATION OF 40 PERCENT N1 ON TAKEOFF, AIRCRAFT RESPONDED OPPOSITE TO RUDDER INPUT. PRE-TAKEOFF FLIGHT CONTROL CHECK WAS GOOD. WITH ADDITIONAL INFORMATION FROM EMBRAER ENGINEERING REGARDING RUDT ALIGNMENT MARKINGS (INDEXES) ACCOMPLISHED RIGGING OF CAPTS & F/O'S RUDDER PEDALS PER MM 32-53-03, OPS CHECK OKAY. ALSO PERFORMED TAXI CHECK. TAXI CHECK WAS OK.