N3102J

Part: NONE — NONE (NONE) · airframe 9,377 hrs · 3,681 cycles

FLT#81, JFK-RNO. 'SEVERE TURBULENCE AT FLT 360 FOR 5 SECONDS A/C OVERSPEED 10 KTS;.' (SUPPLEMENTAL INFORMATION TO FOLLOW)

Part: WARNING MESSAGE — ACTIVATED · airframe 8,268 hrs · 3,202 cycles

FLT#91, BOS-TPA. (AIRCRAFT DIVERTED TO JFK) 'FLT CTL FAULT APPEARED ON FL 340 " 27 FLT CTL FAULT" INFO MESSAGE -PFCC 1 DEGRADED" -PFCC 2 DEGRADED" -PFCC 3 DEGRADED"; REF L/P # 4220297, ITEM #1 (REF L/P #4220298-2 (REF J34-44-02 CHK BOTH CABLES FROM RA 2 TO ANTENNA 2.5OHM DISCONNECTED CABLE AT ANTENNA AND CHK POINT TO POINTR TO GROUND 519OHM MEGGED BOTH CABLED CHECK GOOD ITEM REMAINS OPEN FOR FURTHER T/SHOOTING) / 4220999-1 (ISOLATED BOTH COAX CABLES AN CHECKED FOR CONTINUITY FROM A6P2-E16P1 AP61-E6P1 BOTH REAAD OK CHECKED BOTH CABLES WITH MEGOHMMETER FROM VCENTRAL CONDUCTOR TO OUTER SHELL OK CHECKED CONTINUITY FROM RA2 PIN 09-J2224 PIN 71 7OHM FROM RA2 PIN 34 TO J2224 PIN 83 .6OHM NO MESSAGES PRESENT FURTHER T/S REQ PER TECH SUPPORT REQ W/ANTENNAS CONNECTED READ CONTINUITY FROM RA2 CORE TO OUTER SHELL 0HM ON BOTH CABLES FURTHER TS REQ) / 4190604-1 (ACCOMPLISHED ELECTRICAL BONDING TEST OF RA ALT TX ANTENNA SHOWS 226 OHMS TX ANTENNA SHOWS 23.8 AND RA2 BASE PLATE SHOWING 4.9 OHMS PER AMM J20-25-01-02AA-366B-A ALL VALUES NORMAL) / 4190604-2 (REMOVED TX RX ANTENNA PER AMP J34-44-05 CLEANED AND INSOPECTED ANTENNA MATING SURFACES IAW AMP J20-25-01-01AA-030A-A WITH NO FINDINGS NOTED REINSTALLED TX AND RX ANTENNA IAW AMP J34-44-05 UP TO STEP 1.11 PERFORMED ELEC BONDING TEST OF TX ANTENNA SHOWING 16 OHMS AND RX ANTENNA SHOWING 17 OHMS IAW AMP J20-25-01-02AAA-366B-A REF LP 4190604 ITEM 1 FOR PREVIOUS VALUES ) / 4190605-1 (ACCOMPLISHED INSTALL OF TX AND RX ANTENNA IAW AMP BD500-A-J3A-44-05-01AAA-720A-A REF LP 4190605 ITEM 2 FOR POS CHECK)/ 4190605-2 (PERFORMED OPS CHECK OF RA IAW AMP BD500-A-34-44-05-01AAA-320AAA OPS CHECK GOOD)/ FOR ALL WORK ACCOMPLISHED.) FOR CORRECTIVE ACTION.'

Part: TRANSCEIVER — FAULTED (NR 2 RA) · airframe 8,222 hrs · 3,184 cycles

FLT#1185, JFK- RDU. (AIRCRAFT PERFORMED AN AIR TURN BACK TO JFK) ' AFTER TAKEOFF, THE #2 RA WAS GIVING BAD INFO UP TP FL 300. SPEED MODE WENT TO RETARD AND ENGINES ROLLED TO IDLE AT FL 180. ALSO RECEIVED ' GEAR ' WARNING AT ALTITUDE (BOTH ENGINES WENT TO IDLE); REF LOG PAGES 4220271-1 (REMOVED AND REPLACED RA #2 TRANSCEIVER IAW AMP 34-44-01. OPS CHECK GOOD ) AND 4220271-2 (APPLIED SEALANT TAPE AND SEALANT PER AMM J34-44-05. OPS CHECK TRANSFERRED TO L/P 4220275-2 FOR RA #1 SYSTEM) AND 4220272-1 (REMOVED AND REPLACED RA #2 TRANCEIVING ANTENNA PER AMM J34-44-05. OPS CHECK TRANSFERRED TO L/P 4220275-2) AND 4220275-1 (REMOVED AND REPLACED FWD RA #2 ANTENNA PER AMM J34-44-05.) AND 4220275-2 (PERFORMED OPS CHECK OF RA 1+2 ANTENNA PER AMP J34-44-05 . OPS CHK GOOD NO FAULTS AT THIS TIME) FOR ALL COMPLETED WORK REGARDING THIS DEFECT.'

Part: DOUBLER — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: LH AIR DATA SYSTEM PROBE (ADSP) DOUBLER CORROSION + LIGHTNING STRIKE FOUND ON MULTIPLE SCREW ATTACH POINTS; REF AVIANOR WO 102-J3 NR 3102 REPAIRED IAW EC AC24-1429-01 AND REO 500-53-11-271 TIME LIMITED REPAIR ANALYSIS TO DETERMINE ADDITIONAL REQUIREMENTS WILL BE COMPLETED WITHIN 12 MONTHS OT THE ISSUE DATE OF THIS REPAIR.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON AFT SERVICE DOOR SURROUND STRUCTURE SKIN AROUND SCUFF PLATE HOLES, 9 PLACES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00015) REF AVIANOR WO 102-J3 NR 3016 CORROSION REPAIRED IAW EC AC24-1408-01 AND REO 500-53-61-1540 TEMP REPAIR DVI PER ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH. TEMP REPAIR VALID FOR 10,000 FH FROM REO INCORPORATION.

Part: SKIN — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON LWR SKIN OF AFT PASSENGER DOOR SURROUND STRUCTURE AROUND SCUFF PLATE HOLES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00014) REF AVIANOR WO 102-J3 NR 3023 CORROSION REPAIRED IAW EC AC24-1399-01 AND REO 500-53-61-1544 TEMP REPAIR DVI IAW ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH TEMP REPAIR VALID FOR 10,000 FH FROM INCORPORATION OF REO.

Part: SKIN — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON UPPER SKIN OF AFT CARGO COMPARTMENT DOOR SURROUND STRUCTURE AROUND SCUFF PLATE HOLES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00013) REF AVIANOR WO 102-J3 NR 3021 CORROSION REPAIRED IAW EC AC24-1428-01 AND REO 500-53-61-1551 TEMP REPAIR DVI PER ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH TEMP REPAIR IS VALID FOR 10,000FH FROM INCORPORATION OF REO.

Part: SKIN — CORRODED (ZONE 800) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON FWD PASSENGER DOOR SKIN AREA AROUND SCUFF PLATE FASTENER HOLES 8 PLACES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00011) REF AVIANOR WO 102-J3 NR 3012 CORROSION ON FWD PASSENGER DOOR SKIN AROUND SCUFF PLATE HOLES REPAIRED IAW JB EC AC24-1391-01 AND REO 500-53-21-1007 TEMPORARY DISPOSITION DVI OF DISCREPANT AREAS PER ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FLIGHT HOURS TEMPORARY REPAIR IS VALID FOR 10000 FLIGHT HOURS FROM INCORPORATION OF THIS REO.

Part: SKIN — CORRODED (ZONE 800) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON LWR SKIN SURROUND FWD CARGO DOOR AROUND SCUFF PLATES HOLES 9; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00010) REF AVIANOR WO 102J-3 NR 3014 CORROSION ON LWR SKIN SURROUND FWD CARGO DOOR AROUND SCUFF PLATES HOLES REPAIRED IAW EC NO AC24-1405 AND REO 500-53-21-1013 TEMPORARY REPAIR DVI OF DISCREPANT AREAS PER ANDTP BD500-A-J51-00-90-01QQQ-018A-A AT INTERVALS NOT TO EXCEED 1000 FLIGHT HOURS THIS TEMPORARY REPAIR IS VALID FOR 1000 FLIGHT HOURS FROM TIME OF INCORPORATION OF THIS REO. 11 PLACES OF CORROSION IN TOTAL.

Part: STRUCTURE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: MULTIPLE CORROSION SPOTS AT FR49 BETWEEN RBL 4.0-RBL 9.0; REF AVIANOR PROJ 102J-3, NR 3230, FR49 PN C02382115-001 OUT OF LIMITS AND REPLACED IAW BD500-A-J51-77-00-00AAA-078A-A AND BD500-A-J51-77-00-00AAA-028A-A.

Part: SCUFF PLATE — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#11 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00037) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#4 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00029) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#6 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00032) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: DOOR FRAME — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FOUND CORROSION ON AFT STRIKER OF AFT SERVICE DOOR SURROUND STRUCTURE; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00021) REF AVIANOR WO 102-J3 NR 3018 REMOVED CORROSION IAW EC AC24-1474-01 AND REO 500-53-61-1571.

Part: FRAME — CORRODED (WNG-BDY FAIRING) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: MULTIPLE SPOTS OF CORROSION ON WTBF FRAME 36 LBL SIDE; REF AVIANOR WO 102-J3 NR 3240 CORROSION REPAIRED IAW EC AC24-1423-01 AND REO 500-53-82-675 TEMP REPAIR DVI IAW ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH TEMP REPAIR VALID FOR 10,000 FH FROM INCORPORATION OF THIS REO.

Part: SKIN — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: LOWER FUSELAGE SKIN FOUND WITH CORROSION AROUND FASTENER AT FR78 AND STRG 35L; REF AVIANOR WO 102J-3 NR 3046 CORROSION REPAIRED IAW EC AC24-1500-01 AND REO 500-53-61-1553.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#7 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00033) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SCUFF PLATE — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#10 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00036) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: STRIKER — CORRODED (ZONE 800) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND AT AFT LOWER STRIKER ON AFT PASSENGER DOOR SURROUND STRUCTURE AROUND SCUFF PLATE HOLES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00022) REMOVED CORROSION ON AFT LOWER STRIKER OF AFT PASSENGER DOOR SURROUND STRUCTURE AROUND SCUFF PLATE HOLES IAW EC AC24-1468-01 AND REO 500-61-1573 REF AVIANOR WO 102-J3 NR 3029.

Part: SKIN — DENTED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FUSELAGE / NOSE FUSELAGE / SKIN PANEL / LOWER LH INTERCOSTAL FR 13-15 / DENT DAMAGE - PERMANENT REPAIR; REF AVIANOR PROJ 102J-3, NR 3065, AC24-929-03 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-11-272. INTELL-IFORM UPDATED.

Part: FRAME — CORRODED (WNG-BDY FAIRING) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: MULTIPLE CORROSION SPOTS AT FRAME 48 BTW LBL 4.0 TO LBL 51.0; REF AVIANOR WO 102-J3 NR 3231 REPAIRED IAW EC AC24-1424-01 AND GREO 500-53-82-675 TEMP REPAIR DVI IAW ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH TEMP REPAIR VALID FOR 10,000 FH FROM INCORPORATION OF REO.

Part: SKIN — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON LOWER SKIN OF AFT CARGO COMPARTMENT SURROUND STRUCTURE AROUND SCUFF PLATE HOLES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00016) REF AVIANOR WO 102-J3 NR 3019 CORROSION REPAIRED IAW EC AC24-1401-01 AND REO 500-53-61-122 TEMP REPAIR DVI PER BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH. TEMP REPAIR VALID FOR 10,000 FH FROM INCORPORATION OF REO.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#8 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00034) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON FWD LWR STRIKER ON AFT PASSENGER DOOR SURROUND STRUCTURE AROUND SCUFF PLATE HOLES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00019) REF AVIANOR WO 102-J3 NR 3028 REMOVED CORROSION ON LWR STRIKER OF AFT PASSENGER DOOR SURROUND STRUCTURE AROUND SCUFF PLATE HOLES IAW EC AC24-1473-01 AND REO 500-53-61-1578.

Part: SCUFF PLATE — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON SILL OF AFT CARGO COMPARTMENT DOOR LOWER STRUCTURE AROUND SCUFF PLATE HOLES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00018) REF AVIANOR WO 102-J3 NR 3020 CORROSION REPAIRED IAW EC AC24-1448-01 AND REO 500-53-61-1548 INSPECTION REQUIRED AT 1000 FH INTERVALS TEMP REPAIR IS VALID FOR 10,000 FH FROM REO INCORPORATION.

Part: SCUFF PLATE — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#12 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00038) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: LONGERON — CORRODED (WNG-BDY FAIRING) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: 2 SPOTS OF CORROSION AT WTBF LONGERON LBL 4.0 NEAR FRAME 52; REF AVIANOR WO 102J-3 NR 3228 WTBF LONGERON AT LBL 4.0 FR 52 REPLACED IAW ASRP BD500-A-J51-42-21-00AAA-098A-A.

Part: LONGERON — CORRODED (WNG-BDY FAIRING) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: MULTIPLE SPOTS OF CORROSION AT WTBF LONGERON LBL9.0 BTW FR49 AND 51; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00009) REF AVIANOR WO 102J-3 NR 3232 WTBF LONGERON PN C02382110-001 BTWN FR49-51 AT LBL9 REPAIRED IAW JETBLUE AC24-1425-01 AND REO 500-53-82-676 TEMPORARY REPAIR DVI OF DISCREPANT AREAS PER AIVDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FLIGHT HOURS. THIS TEMPORARY REPAIR IS VALID FOR 1000 FLIGHT HOURS FROM TIME OF INCORPERATION OF THIS REO.

Part: FRAME — CORRODED (WNG-BDY FAIRING) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: MULTIPLE SPOTS OF CORROSION ON WTBF FRAME 36 RBL SIDE; REF AVIANOR WO 102-J3 NR 3241 CORROSION REPAIRED IAW EC AC24-1422-01 AND REO 500-53-82-675 TEMP REPAIR DVI PER ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH TEMP REPAIR VALID FOR 10,000 FH FROM REO INCORPORATION.

Part: FRAME — CORRODED (WNG-BDY FAIRING) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: MULTIPLE SPOTS OR CORROSION AT WTBF FRAME 52.5 LBL 8.8; REF AVIANOR WO 102-J3 NR 3227 CORROSION REPAIRED IAW EC AC24-1419-01 AND REO 500-53-82-675 TEMP REPAIR DVI IAW ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH TEMP REPAIR VALID FOR 10,000 FH FROM REO INCORPORATION.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20); REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#2 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00027) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: PANEL — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON WASTE DOOR SERVICE PANEL AND HINGES; REF AVIANOR PROJ 102J-3, NR 3231, NEW WASTE SERVICE DOOR INSTALLED IAW BD500-A-J52-47-06-050AAA-720A-A AND BD500-A-J51-77-00-00AAA-028A-A.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 7,926 hrs · 3,063 cycles

FLT#8581, YMX-BOS. DURING TAXI OUT, PERFORMED LEFT (1) ENG. ICE SHEDDING PROCEDURE. AIRCRAFT BEGAN SKIDDING RIGHT OF TAXIWAY CENTERLINE. IMMEDIATELY REDUCED THRUST AND APPLIED BRAKES. AIRCRAFT STOPPED ON PAVEMENT APPROXIMATELY AT 60° ANGLE TO TAXIWAY. UNABLE TO TURN BACK ONTO TAXIWAY DUE TO LIMITED SURFACE AVAILABLE; PER AVIANOR PROJECT JB – 3102 – SPV01, THE FOLLOWING AMP TASKS: OPERATIONAL TEST OF LIGHTS IAW BD 500–A– J33–41–00–01AAA–320A–A, OPERATIONAL TEST OF NO WHEEL STEERING IN ACCORDANCE WITH AMP BD 500 – A – J32–51–00–01AAA, NLG INSP IAW AMP BD 500 – A – J20–91 – 07–0 1AAA–310D –A, MLG INSP IAW AMP BD 500–A – J20–91–07–02AAA-310D – A, WERE COMPLETED WITH NO FINDINGS .'

Part: SKIN — DENTED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FUSELAGE / LHS FWD FUSELAGE / SKIN AT FR24-26 BETWEEN STR 23L-24L / DENT DAMAGE - PERMANENT REPAIR; REFERENCES: /1/ DAMAGE REPORT 102L-3 – 3065 /2/ REO 500-53-21-911 /3/ REO 500-53-21-1011. AT THE CURRENT C CHECK FOR N3102J AT YMX, MAINTENANCE PERSONNEL REPORTED DENT DAMAGE COMMON TO THE SKIN PANEL (PN C02312220-005) LOCATED AT FR 24-26 BETWEEN STGR 23L AND 24L WITH DIMENSIONS MEASURING 1.6” IN LENGTH BY 1.6” IN WIDTH WITH A .015” DEPTH AS REPORTED ON THE REF/1/ DAMAGE REPORT. A SEARCH OF THE AIRCRAFT MAINTENANCE RECORDS SHOWED THAT THE DENT WAS PREVIOUSLY DISPOSITIONED WITH A TEMPORARY REPAIR FOR 1500 FH UNDER THE REF/2/ REO. YMX SUBMITTED THE PREVIOUSLY REPORTED DENT DAMAGE TO AIRBUS CANADA REQUESTING PERMANENT REPAIR PLAN DISPOSITION. AIRBUS CANADA PROVIDED A REPAIR PLAN VIA THE REF/3/ REO CONSISTING OF TRIMMING OUT THE DENT DAMAGE, ACCOMPLISHING REQUISITE INSPECTIONS AND FABRICATING AND INSTALLING A REINFORCING REPAIR. THE SKIN PANEL IS PRIMARY STRUCTURE AND FATIGUE CRITICAL BASELINE STRUCTURE (FCBS). A DAMAGE TOLERANCE ANALYSIS MUST BE INCORPORATED WITH 12 MONTHS OF THE REPAIR EMBODIMENT. THIS EC AC24-1479-01 ACCOMPLISHES THE PERMANENT REPAIR PER THE REF /3/ REO WITHOUT DEVIATIONS. EC AC24-1479-02 TRACKS THE INCORPORATION OF THE DTA WITHIN 12 MONTHS OF THE EMBODIMENT OF THIS REPAIR. SUBSTANTIATION: THIS PERMANENT REPAIR HAS BEEN APPROVED VIA THE REF /3/ REO AND CLASSIFIED AS MAJOR. (E/C: AC24-1479-01)

Part: SKIN — DENTED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FUSELAGE / FWD FUSELAGE / FR 24-26 / STGR 23-24 LH / DENT - PERMANENT REPAIR; REFERENCES /1/ AIRBUS CANADA REO-500-53-21-911 /2/ AIRBUS CANADA REO-500-53-11-243 /3/ DAMAGE PICTURES /4/ MX 244. DESCRIPTION: ON 7/17/2024, A/C N3102J MSN 55144 @ BOS, BOS MX REPORTED THREE (QTY 3) DENTS ON LH SIDE OF FWD FUSELAGE. TWO (QTY 2) DENTS ARE BETWEEN FR 13-15 , ONE (QTY 1) DENT IS BETWEEN FR 24-26 AND STGR 23-24 LH. SEE THE REF/3/ FOR DETAILS. NOTE- THIS EC ONLY COVERS THE DENT (QTY 1) BETWEEN FR 24-26 AND HAS BEEN DISPOSITIONED PER REF /1/ REO. THE OTHER TWO (QTY 2) DENTS BETWEEN FR 13-15 HAVE BEEN DISPOSITIONED AS PER REF /2/ REO. DENT DIMENSIONS ARE: L= 1.6”, W=1.6”, DEPTH= 0.015” AND 0.375" FAR FROM FR26 FASTENER ROW. THE ASRP WAS CONSULTED AND NO ALLOWABLE AND REPAIR WERE FOUND FOR THIS DAMAGE DUE TO PROXIMITY CONDITIONS. AIRBUS CANADA WAS CONTACTED FOR DISPOSITION AND PROVIDED REF /1/ REO AS A TEMPORARY REPAIR TO LEAVE THE DENT AS IS AFTER PERFORMING LPI AND SURFACE PROTECTION. THIS REPAIR IS VALID FOR 1500 FH WITH DET INSPECTION EVERY 1000FH AS PER REF/1/ REO. EC AC24-925-01 IS ISSUED TO ACCOMPLISH TIME LIMITED REPAIR IAW REF /1/ REO. EC AC24-925-02 IS ISSUED TO TRACK DET INSPECTION OF THE AREA (INTERVAL 1000FH) APPROVED VIA REF /1/ REO. EC AC24-925-03 IS ISSUED TO TRACK PERMANENT REPAIR WITHIN 1500 FH - PENDING OEM INSTRUCTIONS. SUBSTANTIATION: THIS EC IS ISSUED TO TRACK PERMANENT REPAIR WHICH IS REQUIRED WITHIN 1500FH, AND CLASSIFIED AS OTHER. REVISION 01 THIS EC IS REVISED TO NOTE THE ISSUANCE OF REO 500-53-21-911 REV A, WHICH CORRECTS THE POST REPAIR INSPECTION INTERVALS TO BE 100FH (WAS 1000FH). ADDITIONALLY, THIS EC WAS ERRONEOUSLY TERMINATED IN BOS AT THE TIME OF THE TEMPORARY REPAIR, SO IT HAS BEEN RE-OPENED. ***REVISION 02*** /5/ AIRBUS CANADA REO 500-53-21-1011. THIS EC IS REVISED TO INCORPORATE REO 500-53-21-1011 WHICH PROVIDES THE PERMANENT REPAIR INSTRUCTIONS. SUBSTANTIATION: THIS PERMANENT REPAIR HAS BEEN APPROVED VIA THE REF /5/ REO AND CLASSIFIED AS “MAJOR” (E/C: AC24-925-03)

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#3 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00028) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#1 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00026) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SKIN — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: CORROSION FOUND ON UPPER SKIN OF FWD CARGO DOOR SURROUND STRUCTURE ANROUND SCUFF PLATE HOLES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00012) REF AVIANOR WO 102-J3 NR 3083 CORROSION REPAIRED ON UPPER SKIN OF FWD CARGO COMPARTMENT DOOR SURROUND STRUCTURE AROUND SCUFF PLATE HOLES IAW EC AC24-1398-01 AND REO 500-53-21-1009 TEMPORARY REPAIR DVI OF DISCREPANT AREA PER ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH THIS TEMP REPAIR IS VALID FOR 10,000 FH FROM INCORPORATION OF THIS REO.

Part: DOUBLER — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FUSELAGE WASTE ACCESS SURROUNDING CUTOUT FOUND WITH CORROSION AT AFT EDGE INTERNAL DOUBLER; REF AVIANOR PROJ 102J-3, NR 3032, AC24-1431-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-61-1557 INTELLIFORM UPDATED.

Part: LONGERON — CORRODED · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: 8 SPOTS OF CORROSION ON WTBF LONGERON RBL 4.0 BETWEEN FR50-52; REF AVIANOR PROJ 102J-3, NR 3229, REPLACED WTBF LONGERON RBL 4.0 BETWEEN FR50-52 IAW ASRP BD500-A-J51-42-21-00AAA-078A-A.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#5 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00030) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SKIN — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FUSELAGE SKIN AT WASTE ACCESS DOOR CUTOUT FOUND WITH CORROSION ON FWD EDGE; REF AVIANOR WO 102-J3 NR 3033 CORROSION REPAIRED IAW EC AC24-1450-01 AND REO 500-53-61-1545 TEMP REPAIR. DVI IAW ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH. TEMP REPAIR IS VALID FOR 10,000 FH FROM REO INCORPORATION.

Part: SCUFF PLATE — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FOUND CORROSION ON SILL OF FWD CARGO COMPARTMENT DOOR LOWER SURROUND STRUCTURE AROUND SCUFF PLATE HOLES; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00020) REF AVIANOR WO 102-J3 NR 3082 REMOVED CORROSION IAW EC AC24-1474-01 AND REO 500-53-21-1021 TEMP REPAIR DVI IAW ANDTP BD500-A-J51-00-90-01AAA-018A-A AT INTERVALS NOT TO EXCEED 1000 FH. TEMP REPAIR VALID FOR 10,000 FH FROM REO INCORPORATION.

Part: SCUFF PLATE — CORRODED (ZONE 200) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#9 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00035) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: SCUFF PLATE — CORRODED (ZONE 100) · airframe 7,925 hrs · 3,062 cycles

DURING HEAVY MAINTENANCE: FWD SERVICE DOOR CORROSION FOUND ON FASTENER HOLES UNDERNEATH SCUFF PLATE- (FR17-20) (DETAIL#13 ) TC AC24-1441-01; (RESOLVED ON W/O: 1335461 TASKCARD: NR-00039) REF AVIANOR PROJ 102J-3, NR 3039, AC24-1441-01 ASSIGNED TO ACCOMPLISH REPAIR PER AIB REO500-53-21-1015.

Part: BUSTLE — DAMAGED (ZONE 800) · airframe 6,798 hrs · 2,509 cycles

FLT#1138, AUS-BOS. 'WO 1339017 AND SVC CHECK AND SLIDE ASSIGNED; ACCOMPLISHED W/O 1339017 SVC CHECK AND SLIDE. SLIDE BUSTLE ASSY DAMAGED DURING SLIDE DEPLOYMENT L2 DOOR; INSTALLED L2 DOOR BUSTLE IAW AMP TASK 25-63-00-01-R1. CHAPTER 5 INSP DUE AS A RESULT OF A BOTCHED L2 SLIDE DEPLOYMENT; SPECIAL REGULAR INSP OF L2 DOOR & AREA C/W IAW AMP 05-51-13. NO ADVERSE FINDINGS. ACFT OK FOR SVC.'

Part: SLIDE — NONE (NONE) · airframe 6,783 hrs · 2,505 cycles

FLT#1152, MCO-BOS. 'W/O #1339611 CONTROLLED SLIDE DEPLOYMENT ASSIGNED; W/O #1339611 CONTROLLED SLIDE DEPLOYMENT COMPLETED. DUE TO CONTROLLED SLIDE DEPLOYMENT ON R1 DOOR, DOOR ASSIST REQUIRES NEW DIAPHRAGM; REMOVED AND REPLACED R1 DOOR ASSIST DIAPHRAGM IAW AMP 52-00-00.'

Part: BOTTLE — LOW PRESSURE (SLIDE) · airframe 6,646 hrs · 2,456 cycles

FLT#265, BOS-RSW. 'AFTER PARKING WING SLIDE AMBER EICAS. R WING SLIDE AMBER INDICATION ON DOORS SYN PAGE; INSP'D R OWEED SLIDE CYLINDER PRESS GAUGE PER AMP 25-63-02 & FOUND PRESSURE BELOW LIMIT. REMOVED AND REPLACED R OWEED SLIDE ASSY PER AMP 25-63-02. EICAS CAUTION MSG NO LONGER SHOWING. ITEM OK FOR SVC.'

Part: SLIDE — UNWANTED DEPLOY (L1 DOOR) · airframe 5,916 hrs · 2,178 cycles

FLT#8361, MCO-JFK. ' L1 DOOR EMERGENCY ESCAPE SLIDE INADVERTENTLY DEPLOYED BY INFLIGHT CREW; REMOVED AND REPLACED L1 DOOR EMERGENCY ESCAPE SLIDE REF BD500-A-J25-63-01-01AAA-720A-A., BD500-A-J25-63-01-01AAA-520A-A.'

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 2,857 hrs · 1,102 cycles

FLT#2895, BOS- PUJ. (AIRCRAFT PERFORMED AN AIR TURN BACK TO BOS) ' SLAT SLOW EICAS. HAS HISTORY.' (SUPPLEMENTAL INFORMATION TO FOLLOW)

Part: SENSOR — FAILED (NR 1 ENGINE) · airframe 2,782 hrs · 1,075 cycles

FLT#592, TPA-BOS. ' LEFT ENGINE OIL PRESSURE WARNING IN CRUISE AT FL 350. MSG STAYED ON TEMPORARILY THEN WENT OUT TWO TIMES 3RD WARNING MESSAGE STAYED ON AND FCL REQUIRED ENGINE SHUTDOWN. DID NOT QUALIFY TO RESTART; ACCOMPLISHED ENGINE CHANGE UNDER W/O 1243879 DEFECT TRANSFERRED TO SWO 1243882. REF DEFECT 3609518, ITEM 2

Part: BRAKE DISC — WARPED (MLG)

THE AIR CREW REPORTED THE ACFT BRAKES WERE SPONGY DURING BRAKING APPLICATION. THERE HAVE BEEN MANY REPORTS BY USAF PILOTS IN THE T-3A PROGRAM PERTAINING TO SPONGY OR DEFECTIVE BRAKES. A DETAILED INSPECTION OF THIS AIRCRAFT'S BRAKING SYSTEM REVEALED A WARPED BRAKE DISC. AFTER 2 YEARS AND 30,000 FLYING HOURS AT THE USAFA, ONLY 5 CLEVELAND BRAKE DISCS (P/N 164-02000) HAVE WARPED ON 54 AIRCRAFT. THERE HAVE BEEN PROLBLEMS WITH THE T-3A BRAKING SYSTEM AND THE SLINGSBY MANUFACTURED MASTER CYLINDERS (P/N T67G73231 NOW REVISED TO P/N T67G73213 LATEST REVISION). THIS OCCURRENCE DID NOT APPEAR TO INVOLVE THE MASTER CYLINDERS AS THE DEFECTIVE COMPONENT IN THE BRAKING SYSTEM.

Part: MASTER CYLINDERS — FAILED (BRAKE)

AIR CREWS HAVE REPORTED AIRCRAFT BRAKE PEDALS WERE SPONGY OR HAVE FADED/FAILED DURING BRAKING APPLICATIONS. AFTER 20,000 HOURS OF OPERATION AT THE USAFA, BRAKE SYSTEMS STARTED TO DEVELOP PROBLEMS. REVISED BRAKE BLEEDING PROCEDURES WERE DEVELOPED, OPERATOR BRAKING APPLICATION TECHNIQUE IMPROVED AND AIRCRAFT KEPT FLYING WHILE MORE EMERGENCIES WERE DELCARED FOR BRAKE FAILURES. FINALLY, THE MASTER BRAKE CYLINDER WAS MODIFIED UNDER SAL MOD 726 (P/N T67G73213). THE ENTIRE FLEET IS BEING UPGRADED TO THE MODIFIED MASTER CYLINDER WHILE ACCUMULATING 50,000 FLYING HOURS. SAL AND PARKER/CLEVELAND HAVE BEEN TASKED TO IMPROVE THE CURRENT BRAKING SYSTEM.