N258JB
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| JETBLUE AIRWAYS CORPORATION (YENA) | Operator | 2009-09-03 – 2009-09-03 | Operator named in NTSB report |
| JETBLUE AIRWAYS CORP | Operator | 2009-09-03 – 2009-09-03 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
DURING STRUCTURAL INSPECTION, SKIN WITH NICKS WERE FOUND AT FWD FUSELAGE FROM FR18+85MM / FR19+150MM, BTWN STR26L / 27L+80MM. THE NICKS REPORTED EXCEED THE LIMITS FOR NON-SIGNIFICANT DAMAGE AND THE ALLOWABLE DAMAGE PER SRM53-10-01 AD51, DUE TO THEIR LOCATION WITHIN A NON-ALLOWED AREA. THE CONDITION REPORTED WASREPAIRED IAW ETD2025-190-930779, AND DOCUMENTED PER COOPESA COO-EO-2025-23380, UNDER JOBA1Q219 NRI 21-83.
DURING STRUCTURAL INSPECTION, SMALL NICKS AND LIGHTNING STRIKE DAMAGES WERE FOUND ONTHE FUSELAGE SKIN. MOST NICKS WERE REMOVED VIA BLEND-OUTS. 3 LSDS WERE REMOVED BY DRILLING THE SKIN. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930784 AND DOCUMENTED PER COOPESA COO-EO-2025-23365, UNDER JOB A1Q219 NRI 21-52.
DURING STRUCTURAL INSPECTION, LIGHTNING STRIKE DAMAGES (LSD) WERE FOUND ON THE FUSELAGESKIN. THE LSDS WERE REMOVED BY BLENDING THE AFFECTED AREAS IN ACCORDANCE WITH SRM 51-10-03(BLEND-OUT TYPES A AND D). THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930782, ANDDOCUMENTED PER COOPESA COO-EO-2025-23375, UNDER JOB A1Q219 NRI 21-55.
DURING THE STRUCTURE INSPECTION, WAS IDENTIFIED AN EXISTING DENTS REPAIR LOCATED ON THE ENGINE NR 1, INLET COWL, INNER BARREL. ACCORDING TO DOCUMENTATION PROVIDED BY THE PREVIOUS OPERATOR, THE REPAIR WAS PERFORMED IN ACCORDANCE WITH CV20-09114 REV B. HOWEVER, THE REPAIR IS IN POOR CONDITION. THE CONDITION REPORTED WAS REPAIRED IAW ETD202-190-024520 REV B, CV20-09114 REV. B.
DURING A STRUCTURAL INSPECTION, LIGHTNING STRIKE DAMAGE (LSD) WAS FOUND ON THE FUSELAGE SKIN AT FR 97 + 25 MM, STR-27LH, DUE TO ITS PROXIMITY TO THE STRINGER 27L FASTENER ROW, THREE FASTENERS WERE REMOVED. AFTER DAMAGE REMOVAL VIA BLEND-OUT IN ACCORDANCE WITH SRM 51-10-03, THE REWORKED AREA WAS EVALUATED AND FOUND TO BE OUT OF LIMITS DUE TO ITS LOCATION WITHIN A NON-ALLOWABLE ZONE (GREY AREA). EMBRAER EVALUATION AND APPROVAL ARE THEREFORE REQUESTED. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930887, AND DOCUMENTED PER COOPESA COO-EO-2025-23377, UNDER JOB A1Q219 NRI 21-61.
DURING THE STRUCTURE INSPECTION, WAS IDENTIFIED AN EXISTING DENTS REPAIR LOCATED ON THE ENGINE NR 2, INLET COWL, INNER BARREL. ACCORDING TO DOCUMENTATION PROVIDED BY THE PREVIOUS OPERATOR, THE REPAIR WAS PERFORMED IN ACCORDANCE WITH CV20-09120. THE CONDITION REPORTED WAS REPAIRED IAW ETD2020-190-024531, COLLINS CV20-09120, AND DOCUMENTED PER COOPESA COO-EO-2025-23361,
DURING STRUCTURAL INSPECTION, LIGHTNING STRIKE DAMAGES (LSD) WERE FOUND ON THE FUSELAGE SKIN. THE LSDS WERE REMOVED BY BLENDING THE AFFECTED AREAS IN ACCORDANCE WITH SRM 51-10-03 (BLEND-OUT TYPES A AND D). THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930782, AND DOCUMENTED PER COOPESA COO-EO-2025-23375, UNDER JOB A1Q219 NRI 21-55, 21-54.
DURING A STRUCTURAL INSPECTION, CUSTOMER IDENTIFIED AN EXISTING SKIN REPAIR LOCATED BETWEEN FR23 AND FR24, AND BETWEEN STRINGERS 16L AND 17L. ACCORDING TO DOCUMENTATION PROVIDED BY THE PREVIOUS OPERATOR, THE REPAIR WAS PERFORMED IN ACCORDANCE WITH ETD2014-190-052304. HOWEVER, THE REPAIR IS IN POOR CONDITION SPECIFICALLY, THE DENT WAS NOT RECONTOURED PRIOR TO INSTALLATION. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930228 DTD OCT 15 2025 AND DOCUMENTED UNDER COOPESA COO-EO-2025-23336, UNDER JOB A1Q219 NRI 21-28
DURING A STRUCTURAL INSPECTION, A CRACK WAS FOUND IN THE LH WING LEADING EDGE SKIN CUTOUT BETWEEN RIBS 19 AND 20. THE AFFECTED AREA WAS TRIMMED IN ACCORDANCE WITH SRM 57-49-01 REP 51. HOWEVER, THE FINAL DIMENSIONS AFTER REWORK EXCEED THE MINIMUM ALLOWABLE LIMITS. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-929723 REV. B, AND DOCUMENTED PER COOPESA COO-EO-2025-23311, UNDER JOB A1Q219 NRI 21-31.
DURING A STRUCTURAL INSPECTION, A CRACK WAS FOUND IN THE RH WING LEADING EDGE SKIN CUTOUTBETWEEN RIBS 19 AND 20. THE AFFECTED AREAWAS TRIMMED IN ACCORDANCE WITH SRM 57-49-01 REP51. THE FINAL DIMENSIONS AFTER REWORK EXCEED THE MINIMUM ALLOWABLE LIMITS. THECONDITION REPORTED WAS REPAIRED IAW ETD2025-190-929724 REV. B, AND DOCUMENTED PER COOPESA COO-EO-2025-23327, UNDER JOB A1Q219 NRI 21-32.
DURING STRUCTURAL INSPECTION, SMALL NICKS AND LIGHTNING STRIKE DAMAGES (LSD) WERE FOUND ON THE FUSELAGE SKIN. MOST NICKS WERE REMOVED VIA BLEND-OUTS. SIX (6) LSDS WERE REMOVED BY DRILLING THE SKIN. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930784 AND DOCUMENTED PER COOPESA COO-EO-2025-23365, UNDER JOB A1Q219 NRI 21-51.
DURING INSPECTION, A CRACK WAS FOUND ON THE LH SKIN PANEL OF THE VERTICAL STABILIZER, LOCATED NEAR THE AFT EDGE JUST BELOW RIB 06. THE AFFECTED AREA FALLS WITHIN A NON-REPAIRABLE ZONE AS DEFINED IN SRM 55-30-01/REPAIR 58P. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930311, AERNNOVA TI-170-25-195 AND DOCUMENTED PER COOPESACOO-EO-2025-23371, UNDER JOB A1Q219 NRI 21-63.
DURING A STRUCTURAL INSPECTION, NICKS WERE IDENTIFIED ON THE FUSELAGE SKIN FROM FR 32 TO FR 32 + 175 MM, BETWEEN STRINGERS 27R AND 28R. THE DAMAGE WAS REMOVED VIA BLEND-OUT IN ACCORDANCE WITH SRM 51-10-03. WHILE MOST OF THE BLENDED AREA WAS CLASSIFIED AS NON-SIGNIFICANT, A PORTION EXCEEDS THE ALLOWABLE LIMITS DEFINED IN SRM 53-21-01 AD51. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930876 AND DOCUMENTED PER COOPESA COO-EO-2025-23378, UNDER JOB A1Q219 NRI 21-86.
DURING A STRUCTURAL INSPECTION, A DENT WAS IDENTIFIED ON THE CENTER FUSELAGE LOWER SKIN AT FRAME 27 AND BETWEEN STRINGERS 27LH-28RH. ACCORDING TO DOCUMENTATION FROM THE PREVIOUS OPERATOR, THE DENT WAS ASSESSED UNDER REFERENCE ETD2017-190-094601. THE AREA IS CURRENTLY IN POOR CONDITION: THE DENT WAS NOT PROPERLY RECONTOURED, AND A CREASE IS PRESENT. ADDITIONALLY, THE DOCUMENTATION LACKS CRITICAL INFORMATION, SUCH AS WHETHER THE SHEAR CLIPS WERE REPLACED OR NOT. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930382.
DURING A STRUCTURAL INSPECTION, NICKS WERE FOUND ON THE FUSELAGE SKIN AT FR 26 AND STRINGER 27L. THE DAMAGE WAS REMOVED VIA BLEND-OUT IN ACCORDANCE WITH SRM 51-10-03. THE RESULTING BLENDED AREA WAS EVALUATED PER SRM 53-21-01 AD51 AND DETERMINED TO BE OUT OF LIMITS DUE TO EXCEEDING 10% OF THE SKIN THICKNESS. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930875, AND DOCUMENTED PER COOPESA COO-EO-2025-23374, UNDER JOB A1Q219 NRI 21-89.
DURING HEAVY MAINTENANCE: EMERGENCY LIGHT BATTERY PACK #5 FAILED OPERATIONAL CHECK; REF EAMS WO H9782, NR00001 REPLACED LIGHT BATTERY PACK #5 PER E190 AMM 33-50-01-400-801-A. OPS TEST REF AMM 33-50-00- 710-801-A. TEST PASSED.
DURING HEAVY MAINTENANCE: WINGS / LH AND RH WING / REAR LOWER SKINS / SB 190-57-0056 / REPAIR WASHER INSTALLATION - TEMPORARY REPAIR. (CONSIDERED AS A MAJOR REPAIR)
DURING HEAVY MAINTENANCE: CORROSION ON FLOOR BEAM BTW FR12 TO FR13 AND Y = 460 LH (W1); (RESOLVED ON W/O: 1228947 TASKCARD: NR-00003 ) CORROSION ON FLOOR BEAM BTW FR12 TO FR13 AND Y=460 LH (W1) WAS REMOVED PER EMB-190 SRM 51-12-01, EMB 190 SRM 51-10-03 AND WAS EVALUATED OUT OF LIMITS PER EMB 190 SRM 51-75-16. THEREFORE WAS REPLACED PER EMB 190 SRM 51-41-01, SRM 51-41-02, SRM 51-43-03 AND SRM 51-43-04. ALL WORK ACCOMPLISHED ON TOMX WO # 2265, N/R # 00142. ACCOMPLISHED BY TOMX TECH # 10000210, RII BY TOMX QC# 10000016.
DURING HEAVY MAINTENANCE: CORROSION ON FLOOR STRUCTURE LONGITUDINAL BEAM AT FR 16 AND Y= 280 LH (W1); (RESOLVED ON W/O: 1228947 TASKCARD: NR-00004 ) CORROSION ON FLOOR STRUCTURE LONGITUDINAL BEAM AT FR 16 AND Y= 280 LH (W1) WAS REMOVED PER EMB-190 51-12-01, EMB-190 SRM 51-10-03, EVALUATED OUT OF LIMITS PER EMB 190 SRM 53-10-10/AD51. THEREFORE WAS REPAIRED PER EMB 190 SRM 53-10-10 REPAIR 51P. ALL WORK ACCOMPLISHED ON TOMX WO # 2265, ACCOMPLISHED BY TOMX TECH # 10000210, RII BY TOMX QC # 325718.
DURING HEAVY MAINTENANCE: AFTER FASTENERS REMOVAL: CORROSION ON STGR 25LH BTW FR82/83 WAS FOUND; REF TOMX WO 2265 NR# 00234 STRINGER 25LH FROM FR74 TO FR90 WAS REPLACED PER EMB 190 SRM 51-41-01, SRM 51-41-02 AND SRM 51-43-03.
DURING HEAVY MAINTENANCE: INITIAL INSPECTION [CPCP FINDING]: CORROSION ON FLOOR STRUCTURE LONGITUDINAL BEAM, LOCATED BTW FR12 TO FR19 AND Y= 280 RH (W1); EF TOMX WO 2265 NR # 00141 BTW FR13 TO FR14 AND Y= 280 RH (W1) OUT LIMITS PER EMB190 SRM 53-10-10/AD51 THEREFORE WAS REPAIRED PER EMB 190 ETI-190--23-569 REV2, ETD2023-190-014750 REV.:/, ECE23-509-01.
DURING HEAVY MAINTENANCE: JETBLUE CUSTOMER N/R: LAV SERVICE PANEL CUTOUT, FUSELAGE SKIN HAS CORROSION; (RESOLVED ON W/O: 1206076 TASKCARD: NR-00013 ) SKIN AND DOUBLER OF LAV SERVICE PANEL AREA WERE REPAIRED PER EMB-190 SRM 53-23-60 REPAIR 51. ALL WORK ACCOMPLISHED ON TOMX WO # 2265. N/R # 00300. ACCOMPLISHED BY TOMX TECH # 10000267. RII BY TOMX QC # 10000016. REPAIR PARTS REQUIRE RE-INSPECTION AT 4009 FC BY LFEC (NDT PART 6 TASK 53-23-00-250-804-) PER EMB SRM 53-23 -60 PART 6.
DURING HEAVY MAINTENANCE: WINGS / RH WING / WING MAIN BOX / LOWER SKIN PANEL SB APPLICATION / DISCREPANT FASTENER - TEMPORARY REPAIR. (CONSIDERED AS A MAJOR REPAIR)
DURING HEAVY MAINTENANCE: AFTER RH ELEVATOR BEARING REMOVAL FROM HINGE, FITTING #2 WAS FOUND CORROSION IN HOUSING; REPLACED HOUSING AT RH ELEVATOR HINGE FITTING #2 PER EMB-190 SRM 51-43-03. REF TOMX NR 0323.
DURING HEAVY MAINTENANCE: REPLACE THE INBOARD AND OUTBOARD SPAR AT THE RH PYLON DUE TO AFT LUG CORROSION; REF TOMX W/O 2265 NR00306: INBD AND OUTBD SPARS AT RH PYLON WERE REPLACED PER EMB-190 SRM 51-43-03, 51-43-04, EMBRAER ANNEX A SPAR REPLACEMENT PROCEDURE REV D IN REFERENCE TO ETI-190-23-570 REV 3, ETD2023-190-015500, AND JB EC E23-631-01.
DURING HEAVY MAINTENANCE: REPLACE THE INBOARD AND OUTBOARD SPAR AT THE LH PYLON DUE TO AFT LUG CORROSION; REF TOMX W/O 2265 NR00305: INBD AND OUTBD SPARS AT LH PYLON WERE REPLACED PER EMB-190 SRM 51-43-03, 51-43-04, EMBRAER ANNEX A SPAR REPLACEMENT PROCEDURE REV D IN REFERENCE TO ETI-190-23-571 REV 3, ETD2023-190-015504, AND JB EC E23-630-01.
DURING HEAVY MAINTENANCE: MAJOR REPAIR: REPLACE THE EXISTING REPAIR DOUBLER IN LH WING THAT INTERFERES WITH THE INSTALLATION OF SB190-57-0056, LH WING REAR LOWER SKIN PANEL REINFORCEMENTS; REF TOMX W/O NR-00318: REPAIRED INTERFERENCE BETWEEN EXISTING REPAIR DOUBLER AND SB57-0056 REINFORCEMENT DOUBLER ON LH WING LOWER SKIN PANEL RIB9-10 IAW ETI-190-23-580 REV. 7, ETD2023-190-015894 REV 0, AND JB EC E23-778-01.
DURING HEAVY MAINTENANCE: INITIAL INSPECTION [CPCP FINDING]: CORROSION ON FLOOR STRUCTURE LONGITUDINAL BEAM, LOCATED BTW FR12 TO FR19 AND Y= 280 RH (W1); REF TOMX WO 2265 NR # 00141 BTW FR13 TO FR14 AND Y= 280 RH (W1) OUT LIMITS PER EMB190 SRM 53-10-10/AD51 THEREFORE WAS REPAIRED PER EMB 190 ETI-190-23-569 REV2, ETD2023-190-014750 REV.:/, ECE23-509-01 EF TOMX WO 2265 NR # 00141 BTW FR13 TO FR14 AND Y= 280 RH (W1) OUT LIMITS PER EMB190 SRM 53-10-10/AD51 THEREFORE WAS REPAIRED PER EMB 190 ETI-190--23-569 REV2, ETD2023-190-014750 REV.:/, ECE23-509-01(CONSIDERED AS A MAJOR REPAIR)
DURING HEAVY MAINTENANCE: WINGS / RH & LH WING / FWD LWR SKINS / SB IMPLEMENTATION / FWD FITTINGS / BOLT INSTALLATION / WASHER DEVIATION - PERMANENT REPAIR. (CONSIDERED AS A MAJOR REPAIR)
DURING HEAVY MAINTENANCE: WINGS / RH WING / WING MAIN BOX / LOWER SKIN PANEL SB APPLICATION / DISCREPANT FASTENER - TEMPORARY REPAIR. (CONSIDERED AS A MAJOR REPAIR)
DURING HEAVY MAINTENANCE: WINGS / LH WING / LOWER SKIN PANEL BETWEEN RIB 9-10 / EXISTING REPAIR & SB 57-0056 DOUBLER INTERFERENCE - TEMPORARY REPAIR. (CONSIDERED AS A MAJOR REPAIR)
DURING HEAVY MAINTENANCE: FUSELAGE / FWD FUSELAGE / FLOOR STRUCTURE AT FR 13-14 AND Y= 280 RH / CORROSION - PERMANENT REPAIR. (CONSIDERED AS A MAJOR REPAIR)
DURING HEAVY MAINTENANCE: FUSELAGE / CENTER FUSELAGE III / FRAME 88 / BETWEEN STRINGER 27R AND 28R / EXISTING MISDRILLED HOLE - PERMANENT REPAIR. (CONSIDERED AS A MAJOR REPAIR)
DURING HEAVY MAINTENANCE: INITIAL INSPECTION [CPCP FINDING]: CORROSION ON FLOOR STRUCTURE LONGITUDINAL BEAM BTW FR 86 TO FR 89 AND Y=250 LH (W2); (RESOLVED ON W/O: 1228947 TASKCARD: NR-00001 ) CORROSION ON FLOOR STRUCTURE LONGITUDINAL BEAM BTW FR 86 TO FR 89 AND Y=250 LH (W2) WAS REMOVED PER EMB-190 SRM 51-10-03, SRM 51-12-01, EVALUATED OUT OF LIMITS PER EMB 190 SRM 53-23-10 AD/52. THEREFORE WAS REPLACED PER EMB 190 SRM 51-41-01, EMB 190 SRM 51-43-03, AND EMB 190 SRM 51-42-01. ALL WORK ACCOMPLISHED ON T0MX WO: N258JB/2265/E190/B8 CHECK, N/R # 00152. TECHOPS MX #10000210, TECHOPS MX RII# 10000266.
FLT#23, DCA-MCO. 'COCKPIT DOOR HINGE PIN POPPED OUT OF POSITION; REPLACED COCKPIT DOOR LOWER HINGE AND ADJUSTED COCKPIT DOOR IAW AMM 52-51-01. A/C OK FOR SERVICE.'
FLT 726, BWI - BOS. AIRCRAFT PERFORMED AN AIR TURN BACK TO BWI, BLEED 1 OVERPRESSURE MSG APPEARED ON CLIMB AFTER TAKEOFF. RAN QRH PROCD, MSG RETURNED. DISPATCH ADVISED RETURN TO BWI; ACCOMPLISHED FIM TASK 36 14 00 810 867A. REMOVED AND REPLACED LH BLEED OVERPRESSURE SWITCH AS NEEDED. IAW AMM 36 14 02. OPS CHECK GOOD LH ENG NEEDS A IDLE CHECK RUN PER MCC. ACCOMPLISHED SATISFACTORY GRND RUN IDLE CHECK ENG1 BLEED ON APU BLEED OFF. NO FURTHER FAULTS WERE NOTED AND ACFT IS OK FOR CONT SERVICE.
FLT 1182, RIC-BOS. ODOR OF EXHAUST IN FLIGHT DECK ONLY. DURING THE LAST PART OF THE CLIMB, CRUISE, AND DESCENT. MILD, EXHAUST SMELL THROUGH FLIGHT DECK VENTS WOULD COME AND GO DURING WAVES. OVERALL LASTING ABOUT 30 MINUTES. WHEN PACK 1 WAS TURNED OFF THE ODOR ALMOST IMMEDIATELY WENT AWAY. COMPLIED WITH INFO NOTICE TSM 21-20-00-810-801A & NOTICE SECTION B1 ACCOMPLISHED DECONTAMINATION B AND, R & R BOTH RECIRRUILATION FILTERS IAW AMM 21-24-02. NO ODOR WAS NOTED. PACK BURNS SUCCESSFULLY. A/C OK FOR CONTINUED SERVICE. PACK NR 1 IS OPERABLE.
FLT#2028, MCO-EWR. 'ODOR DIRTY SOCKS DETECTED ON TAKE-OFF ROLL LEVEL 1 DURATION OF 5 MINUTES MODERATE INTENSITY DETECTED IN COCKPIT ONLY NO REPORT OF ODOR FROM FLIGHT ATTENDANTS SUSPECTED SUSPECTED SOURCE IS AIR SUPPLY VENTS APU WAS OFF; PERFORMED PACK BURN PER FIM 21-21-00 NO DIRTY SOCK SMELL NOTICE OK TO CONTINUE SERVICE.'
FLT#2454, DCA-BOS. 'R1 DOOR ASSIST BOTTLE SHOWS 500PSI REQUIRED SERVICE; R1 DOOR ASSIST BOTTLE SERVICED IAW AMM 52-41-51.'
FLT # 733, MCO-SJU (AIRTURN BACK TO MCO). CLIMBING THROUGH FL230 ENG 2 LP VIBRATION WAS 4.1 FOLLOWED QRH PROCEDURE; PER FIM 77-31-00-810-816A R/R EVM MODULE PER AMM 77-31-01. BITE CK GOOD.
FLT 932, IAH-BOS. EMERGENCY LIGHT AT CEILING PANEL 11 INOPERABLE. R & R EMERGENCY LIGHT POWER UNIT NR 6, IAW AMM 33-50-01. OPERATIONS CHECK GOOD. A/C OK FOR SERVICE.
DURING HEAVY MAINTENANCE, PERFORMED PERMANENT REPAIR ON EXTERNAL SKIN BETWEEN FR 96 TO FR 97 AT STGR 23R LOWER FUSELAGE. PERFORMED PERMANENT REPAIR ON EXTERNAL SKIN BETWEEN FR96 TO FR97 AT LEVEL STGR 23R LOWER FUSELAGE, IAW E190 SRM 53-30-01, REPAIR 63, ITEM 5.
DURING HEAVY MAINTENANCE, CORROSION INTERNAL SKIN ON ACCESS PANEL 351GL IN TAIL COMPARTMENT. ACCOMPLISHED REPAIR OF CORROSION DAMAGE FOUND ON THE TAIL CONE ( S/N: 0200001, P/N 170-50005-421) APU BAY FWD ACCESS PANEL 351GL IN ACCORDANCE WITH EA 53-0571-20 COVER REV 0, PART 1 AND 2, EC NO E20-600-01 AND ETD 2020-190-024949 REV B.
DURING HEAVY MAINTENANCE DENT EXTERNAL SKIN FR 96 TO FR 97 AT LEVEL STR23L LOWER FUSELAGE. PERFORMED PERMANENT REPAIR ON EXTERNAL SKIN BETWEEN FR96 TO FR97 AT LEVEL STGR 23L LOWER FUSELAGE, IAW E190 SRM 53-30-01, REPAIR 63, ITEM 5. DETAILED VISUAL INSPECTION IS REQUIRED IAW E190 SRM 53-30-01, REPAIR 63, ITEM 6. INSPECTION THRESHOLD INTERNAL SIDE (20,000 FC/ 26,600FH) WHICHEVER OCCURS FIRST, INTERVAL (10,000 FC/ 26,600 FH) WHICHEVER OCCURS FIRST INTERVAL ( 5,000 FC/ 6,650 FH) WHICHEVER OCCUS FIRST.
DURING HEAVY MAINTENANCE, CRACK RIB 10 WING MAIN BOX LOWER SKIN SPAR 2 TRAILING EDGE RT WING. PERFORMED PERMANENT REPAIR ON RIB 10 WING MAIN BOX LOWER SKIN SPAR 2 TRAILING EDGE RT WING IAW E190 SRM 57-10-01, REPAIR 54 ITEM 9 FIGURE 201 SHEET 6. NO FURTHER ACTION REQUIRED, REF AEROMAN WO# 2020-288/1 WCC 2020-243009.
DURING HEAVY MAINTENANCE, INOPERABLE EMERGENCY LIGHT POWER UNIT AT MID CABIN P/N 3400-22-10 S/N 001995 IN PASSENGER CABIN. RESOLVED ON W/O: 1050580 TASKCARD: NR-00009. REMOVED AND REPLACED EMERGENCY LIGHT POWER UNIT AT MID CABIN, IAW 3190 AMM 33-50-01-000-801-A AND AMM 33-50-01-400-801-A. PERFORMED FULL CHARGE OF THE EMERENCY LIGHTS POWER UNITS IAW E190 AMM 33-50-01-800-8.
DURING HEAVY MAINTENANCE, INOPERABLE EXTERNAL SKIN LT FWD EMERGENCY LIGHT ON UPPER FUSELAGE (1EA). R & R FWD EXTERNAL EMERGENCY LIGHT ASSEMBLY LT SIDE, IAW E190 AMM 33-50-25-000-802-A AND E190 AMM 33-50-25-400-802-A. PERFORMED OPERATIONAL TEST EXTERNAL EMERGENCY LIGHT, IAW E190 AMM 33-55-25-710-801-A ,TEST IS OK PER AEROMAN WORK ORDER.
DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON SHEAR TIE FLOOR STRUCTURE AT FR 76 BTWN STR 28R TO STR 29R ON AFT CARGO COMPARTMENT; REPLACED SHEAR TIE FLOOR STRUCTURE LOCATED AT LEVEL FR 76 BTWN STR 28R TO STR 29R ON AFT CARGO COMPARTMENT. IAW E190 SRM-51-40-08 & DWG 170-65180-4445 REF AEROMAN N/R 20180-287278.
DURING HEAVY MAINTENANCE, B6 CHECK AT (SAL), A CRACK (LENGTH: 2.627 INCHES) WAS FOUND ON LT WING REAR LOWER SKIN (P/N 190-33065-013) AT RIB 10+1". SEE THE REF /1/ EA FOR MORE DETAILS. THE DAMAGE IS FOUND TO BE OUTSIDE OF REF /3/ SRM LIMITS. THEREFORE, CONTACTED FOR REPAIR DISPOSITION. PROVIDED THE REF /2/ ETD WHICH PROVIDES INSTRUCTIONS TO CUT OUT THE CRACKS, PERFORM NDT INSPECTIONS AND INSTALL 1 REPAIR DOUBLER. THE REF /2/ ETD IS A TIME LIMITED REPAIR REQUIRING A DETAILED STRUCTURAL ANALYSIS WITH 12 MONTHS. THIS EC E18-733-01 PROVIDES THE TIME LIMITED REPAIR INSTRUCTIONS PER THE REF /2/ ETD & REF /1/ EA WITHOUT DEVIATIONS. EC E18-733-02 PROVIDES A PLACEHOLDER TO TRACK THE FOLLOW UP ANALYSIS REQUIRED WITHIN 12 MONTHS; THIS TIME LIMITED REPAIR, REQUIRING FURTHER ANALYSIS WITHIN 12 MONTHS, HAS BEEN APPROVED VIA REF /2/ ETD WITH ANAC FORM AND IS CLASSIFIED AS MAJOR.
FLT 1479, DCA-FLL. FOUND AFT ESCAPE DOOR SLIDE BUSTLE BRACKET DAMAGED(AFT). REMOVE SLIDE FOR REPAIR, REPLACED SHOCK MOUNT ON SLIDE AND REINSTALLED SLIDE ASSY IAW 25-65-01. ALL CHECKS NORMAL.
DURING MAINTENANCE, CORROSION WAS FOUND ON CENTER SEAL REST 2" AFT OF FRAME 26. R & R FWD CARGO DOOR CENTER SEAL REST IAW SRM 51-41-01.
DURING MAINTENANCE, CORROSION WAS REPORTED ON FLOOR SUPPORT BRACKET FWD OF FRAME 16, RBL 26, R & R SUPPORT IAW E190 SRM 51-41-01. APPLIED TOP COAT REF E190 SRM 51-23-06.
DURING MAINTENANCE, CORROSION WAS FOUND ON FWD LAV AREA FLOOR DOUBLER PANEL. PREVIOUSLY BLENDED AREA 1" FWD OF FRAME 16, LBL 121. R & R FWD LAV FLOOR DOUBLER 1" FWD OF FRAME 16, LBL 12, REF E190, SRM 51-41-02.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA RT SEAT TRACK BEAM 12" AFT OF FRAME 86, RBL 10". R & R AFT WET AREA RT SEAT TRACK BEAM REF SRM 51-41-01, 51-43-03, AND 51-42-01.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA RT SEAT TRACK BEAM, 12" AFT OF FRAME 85, RBL10. R & R RT SEAT TRACK BEAM IAW SRM 51-41-01 AND 51-43-03.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA RT SHEAR PANEL 4" AFT OF FRAME 87, RBL 23". R & R RT SHEAR PANEL FRAME 87, 88 IAW SRM 51-42-03, SRM 51-42-04, SRM 51-21-00.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT CARGO DOOR SEAL REST NEAR THE 2ND LATCH SPOOL FROM THE FWD END. R & R AFT CARGO CENTER SEAL REST IAW SRM 51-41-01.
DURING MAINTENANCE, CORROSION WAS FOUND ON RT SEAT TRACK, GALLEY ATTACH AREA 8" FWD OF FRAME 20, RBL 13. R & R RT SEAT TRACK FWD FRAME 20, RBL13 IAW SRM 51-41-02 AND SRM 51-40-02.
DURING MAINTENANCE, CORROSION WAS FOUND ON FWD LAV AFT OTBD ATTACH POINT SUPPORT FR16, LBL34, AROUND BOLT HOLE. R & R FWD LAV AFT OTBD ATTACH POINT SUPPORT AT FRAME 16, LBL 34 IAW SRM 51-43-03.
DURING MAINTENANCE, CORROSION WAS FOUND ON RT FLOOR SILL 1" FWD OF FRAME 19, RBL 40. REMOVED CORROSION ON RT FLOOR SILL 1" FWD OF FRAME 19, RBL 40 IAW SRM 51-10-03.
DURING MAINTENANCE, CORROSION WAS FOUND ON RT FLOOR SILL BETWEEN FRAME 16 AND FRAME 19 AT RBL 40. R & R RT FLOOR SILL BETWEEN FRAME 16 AND FRAME 19 AT RBL 40, REF SRM 51-41-02 AND 51-43-04.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA RT PANEL SUPPORT AT FRAME 84, RBL 18". R & R AFT WET AREA PANEL SUPPORT AT FRAME 84, RBL 18 IAW SRM 51-41-02, 51-43-04.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA AFT PAX DOOR LOWER BEAM 6" AFT OF FRAME 85, LBL 45". R & R AFT SERVICE DOOR LOWER BEAM.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA AFT PAX DOOR LOWER BEAM 6" AFT OF FRAME 85, LBL47. R & R AFT SERVICE DOOR LOWER BEAM.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA AFT PAX DOOR LOWER BEAM 8" AFT OF FRAME 85, LBL 47. R & R AFT SERVICE DOOR LOWER BEAM.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA, AFT PAX AREA DOOR LOWER BEAM AT FRAME 86, LBL 46; R & R AFT PAX DOOR LOWER BEAM IAW SRM 51-41-01, 51-41-02, 51-41-03, 51-43-04.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA RT PANEL SUPPORT AT FRAME 89, RBL 43". REMOVED CORROSION FROM AFT WET AREA RT PANEL SUPPORT AT FRAME 89, RBL 43.
DURING MAINTENANCE, CORROSION WAS FOUND ON AFT WET AREA RT PANEL SUPPORT AT FRAME 90, RBL 42". R & R RT PANEL SUPPORT IAW SRM 51-42-01 & 51-43-03.
IMMEDIATELY AFTER TAKEOFF, GEAR HINGE HARD TO MOVE. USED LANDING GEAR LEVEL, ON LOCK REL, OVERRIDE TO GET GEAR TO COME UP AND DIVERTED IAW FRH/FIM 26-61-00-810-807-A00. R & R SPDA1, SLOT 13 DC POWER MODULE IAW 24-61-00. ACFT PLACED ON JACKS PERFORMED, OPS TEST IAW MM 32-33-01. OPS CHECKED GOOD.
AIR RETURN DUE TO BLEED 1 OVER PRESSURE. COULD NOT RESET VIA QRH. CMC FAULT CODE 36146225AM1. PERFORMED FIM TASK 36-14-00-810-817-A. FAILURE OF THE OVER PRESSURE SWITCH. R & R 1 BLEED OVER PRESSURE SWITCH IAW AMM 36-14-01-000-801-A & 36-14-01-400-801-A. OPS CHECK GOOD.
DURING MAINTENANCE CHECK, FOUND CORROSION ON FLOORBEAM AT FRAME 17. REMOVED CORROSION BY BLENDING, CUT OUT DAMAGE, PERFORMED HFEC INSPECTION, FABRICATED REPAIR ANGLE AND FILLER. TREATED AND PRIMED REPAIR PARTS, INSTALLED REPAIR, PRIMED AND TOPCOATED REPAIR. WORK ACCOMPLISHED IAW EC E14-306-01.
ON MAINTENANCE CHECK, FOUND CORROSION ON FWD CABIN CROSSBEAM AT FRAME 14 OTBD OF RT SEAT TRACK ON REAR. REMOVED STRAP, FABRICATED REPAIR STRAP, ACCOMPLISHED DVI OF BEAM, PRIMED AND TOPCOAT REPAIR. WORK COMPLIED WITH TC EC E14-307-01.
CREW DECLARED AN EMERGENCY AND ACFT RETURN TO DEPARTURE, LANDING GEAR LEVER WOULD NOT COME UP ON TAKEOFF. ACCOMPLISHED QRH 12-8 WHICH LED US TO QRH 12-10 LG WOW FAIL. NO OTHER INDICATIONS. NON NORMAL LANDING ACFT WT APPROX 89K LBS. ACCOMPLISHED FIM TASK 32-33-01. R & R LANDING CONTROL LEVER AS PRECAUTION. IAW MM 32-33-00-710-803-A/500-OPS TEST OF LANDING EXT/RET SYS IAW TASK 32-33-00-8710-801-A/500. OPS CHECK NORMAL.
ACFT DIVERTED DUE TO AVNX MAU 3A FAILURE. AFTER LANDING CIRCUIT BREAKER B34 MAU 3 POWER TRIPPED. R & R POWER SUPPLY MAU 3, POWER 1. OPS CHECKED OK IAW FIM TASK 45-45-21-47. THE FAULT REPEATED AND THE MAU3 NIC 1 PROC MODULE WAS R & R IAW AMM 31-41-04. OPS CHECKED NORMAL.
FLT 874 MCO-SJU, AIR RETURN TO SJU DUE TO LOSS OF BOTH BLEEDS NR 1 WAS ON MEL, NR 2 FAILED PASSING 23,500 FEET. AIRCRAFT BEGAN TO DEPRESSURIZE, CABIN ALTITUDE NEVER EXCEEDED 7500 FEET DURING DESCENT HIGH POWER. REMOVED AND REPLACED ENGINE NR 2 NAPRSOV IAW AMM 36-11-03. RUN FOR CHECKS OF BOTH ENGINE BLEED SYSTEM ALL CHECKS NORMAL.
FLT 874 MCO-SJU, AIR RETURN TO MCO DUE TO LOSS OF BOTH BLEEDS NR 1 WAS ON MEL, NR 2 FAILED PASSING 23,500 FEET. AIRCRAFT BEGAN TO DEPRESSURIZE, CABIN ALTITUDE NEVER EXCEEDED 7500 FEET DURING DESCENT HIGH POWER. REMOVED AND REPLACED ENGINE NR 2 FAN AIR VALVE IAW AMM 36-11-09. RUN FOR CHECKS OF BOTH ENGINE BLEED SYS ALL CHECKS NORMAL.
FLT 6308 ORD-BOS, AIRCRAFT DIVERTED - 45 MINUTES INTO FLIGHT MFD 1 (DU2) FAILED AND THE CB POPPED, NO ASSOCIATED ODOR NOTED. REMOVED AND REPLACED MFD 1 (DU2) IAW AMM 31-61-01, OPS CHECK NORMAL. NOTE: THE PFD NR 2 DISPLAY UNIT ALSO FAILED ON THIS FLIGHT.
FLT 6308 ORD-BOS, AIRCRAFT DIVERTED TO SYR - APPROXIMATELY 30 MINUTES AFTER DU2 FAILED (F/O PFD) FAILED AND THE CB POPPED. REMOVED AND REPLACED PFD NR 2 (DU5) IAW AMM 31-61-01, OPS CHECKED GOOD.
FLT 917 JFK-ORD, WHILE AT CRUISE MFD 1 SCREEN WENT BLANK MFD 1 CB POPPED AND THE SCREEN FELT WARM TO THE TOUCH. ALSO THE F/O AND F1 BOTH REPORTED, SMELLED AN ODOR SIMILAR TO BURNING ELECTRICAL WIRING. REMOVED AND REPLACED MFD NR 1 REFERENCE AMM 31-61-01. OPS CHECK GOOD. CAT CHECK ACCOMPLISHED NO MESSAGES PRESENT CAT OK.
FLT 14 FLL-JFK, WHILE ACCOMPLISHING CABIN CONDITION CHECK TASK CARD, FOUND L2 DOOR EXIT IDENTIFIER SIGN INOP. REMOVED AND REPLACED ELPU NR 5 IAW AMM REF 33-50-01. OPS CHECK GOOD.
FLT NR 1118 RDU-JFK, AFT GALLEY EMERGENCY CENTER CEILING LIGHT AND LAST ROW EMERGENCY CEILING LIGHT INOP FOUND DURING WEEKLY CHECK. REMOVED AND REPLACED POWER SUPPLY UNIT NR 4 IAW 33-50-01. OPS CHECK GOOD.
FLT 1717 MCO-SDQ, AIR RETURN TO MCO DUE TO FLIGHT DECK DOOR OPENED AND WILL/WOULD NOT CLOSE ON TAKEOFF. ACCOMPLISHED E/C E12-515-01. ADDITION OF SPACER BEHIND LOWER HINGE SOCKET. REMOVED & REPLACED UPPER DOOR HINGE AND PIN & LOWER DOOR HINGE AND PIN ASSEMBLIES IAW AMM 52-51-01. CHECK OK.
FLT 1082 CLT-JFK, CREW DECLARED EMERGENCY DUE TO CAPTAINS WINDSHIELD CRACKED AT CRUISE (FL310). REMOVED AND REPLACED CAPTAINS WINDSHIELD PER AMM 56-11-00, CHECK GOOD.
FLT 1179 BOS-EWR, STRAIGHT AND LEVEL FLIGHT AT 180 KNOTS FLAPS WERE ALREADY AT 1 WHEN WE RECEIVED A SLAT FAIL EICAS MESSAGE. FLAP HANDLE WAS NOT MOVED WHEN WE GOT THE FAILURE. PERFORMED FIM PROCEDURES 27-81-00-810-805A SUBTASK 810-028-A FOUND TO BE IN A TRANSITORY CONDITION. CYCLED SLAT/FLAPS SEVERAL TIMES AND POWER DOWN AIRCRAFT. REF TSI 7925 IF NO FAULTS FOUND REPLACED LEFT WING OUTBD SKEW SENSOR DUE TO PREVIOUS HIT ON SAME ITEM. REMOVED AND REPLACED LEFT OUTBD SKEW SENSOR. OPS CHECK OK.
FLT 338 MCO-IAD, ON GROUND MAINTENANCE CHECK FOUND FWD LT FAIRING EMERGENCY LIGHT INOP (EXTERNAL EMERGENCY LIGHTS). REMOVED AND REPLACED LT FWD EXTERNAL EMERGENCY LIGHT ASSY REF AMM 33-50-00. NOTE: PART IS NON SERIALIZED.
FLT 1795 FLL-CUN - SPORADIC AFT LAV OPERATION WITH NO PERSON IN THE LAVATORY COMBINING WITH ODOR OF MELTING PLASTIC AND STRONG ELECTRICAL. ACCOMPLISHED TSM 25-30-00-801A.IDENTIFIED THE AFT LAVATORY VACUUM GENERATOR RUNNING CONTINUOUSLY, DEACTIVATED AFT VACUUM GENERATOR PER MEL 38-32-09 CONDITION 3. COULD NOT DUPLICATE WRITE UP, WASTE SYS VAC GENERATOR + LAV/WASTE SYS OPS NORMAL OPERATED SYS MULTIPLE TIMES OK FOR SERVICE REF MM 38-32-09 NOTED CLOSED C/B ON LICC FOR VAC BLOWER.
FLT 1790 NAS-FLL - STRONG ELECTRICAL ODOR BETWEEN ROWS 23-25. TURNED OFF IFE RACK IN DESCENT. AS PER FIM TASK 21-20-00-810-801A, DETECTED ABNORMAL NOISE FROM IFE COOLING FAN. SUSPECT IFE COOLING FAN AT FAULT. DE-ACTIVATED IFE SYS AND IFE RACK P/B AND LTV SYS/WADL/XM RADIO. NO OTHER DEFECTS NOTED. OK TO CONTINUE.
FLT 1796 CUN-FLL - ARCHING ELECTRICAL ODOR STILL REOCCURRING AFT GALLEY CART AREA. FOUND HEAVY BURNED SMELL IN AFT AVIONICS EQUIPMENT AND DETECTED BURNED ODOR AND EVIDENCE OF COMPONENT OVERHEATING ON QAR UNIT. FOUND QAR WITH HEAVY BURNED SMELL. REMOVED AND REPLACED QAR IAW 31-32-01-04.
FLT 6452 JFK-BNA, DURING 12K CHECK AT BNA - CORROSION AT FRAME 14 RT RBL 18 TO RBL 30. REMOVED CORROSION FRAME 14RT OUT OF LIMITS. REPAIRED IAW JETBLUE EC E10-586-01. EAMS N/R H1708-1514.
FLT 6452 JFK-BNA, DURING 12K CHECK AT BNA - CORROSION AT FRAME 87 TOP OF BEAM. REMOVED CORROSION IAW SRM 51-12-01 DUE OUT OF LIMITS. REMOVED AND REPLACED CENTER WEB IAW SRM II 51-42-01 AND 51-43-01, EAMS NR H1708-2537.
FLT 6452 JFK-BNA, DURING 12K CHECK AT BNA - LT FLOORBEAM FROM FR 14 TO 17 CORRODED. LT SEAT TRACK CORRODED OUT OF LIMITS IN MULTIPLE LOCATIONS. REPAIRED IAW JETBLUE E10-586-01, EAMS NR H1708-1519.
FLT 6452 JFK-BNA, DURING 12K CHECK AT BNA - RT FLOORBEAM FRAME 13 TO 17 CORRODED. RT FLOORBEAM CORRODED OUT OF LIMITS. REMOVED AND REPLACED FLOORBEAM IAW SRM II 51-23-04 AND 05.
FLT 25 BTV-JFK, CREW DECLARED EMERGENCY DUE TO DURING APPROACH UPON GEAR EXTENSION EICAS MSG BRAKE FAULT AND BRAKE LT FAULT. A GO AROUND WAS CONDUCTED FOR MANEUVERING IN THE AREA TO WORK THROUGH QRH PROCEDURE. REMOVED AND REPLACED NR 2 MAIN BRAKE SHUT OFF VALVE PER AMM 32-41-03. NO FURTHER FAULTS NOTED.
FLT 1793 FLL-CUN - ON PUSHBACK AFTER NR 1 ENG START, F/A 2 REPORTED SMELLING SMOKE IN AFT GALLEY AREA. REMOVED AND REPLACED MID NR 1 AVIONICS VENTILATION FAN. GROUND OPS CHECK OK IAW 21-26-04.
FLT 1715 MCO-CUN - ON DECENT INTO CUN IDG NR 1 OIL HIGH TEMP MESSAGE. MX CHECKED IDG OIL LEVEL FOUND LOW, SERVICED IDG OIL, OPS AND LEAK CHECKED OK PER AMM 12-13-09.
FLT 1781 MCO-NAS UPON LANDING IN NAS AN ENGINE FIRE 1 INDICATION APPEARED. AFTER TAXIING CLEAR, STOPPED AIRCRAFT, PERFORMED QRH FOR ENGINE FIRE ON GROUND. MESSAGE CLEARED AFTER THE FIRE WENT AWAY AND THE ENGINE SHUTDOWN. FOUND HPTACC (HIGH PRESS TURB ACTIVE CONTROL CLEARANCE VALVE) FUEL LINE LEAKING. REPLACED ENGINE ASSY IAW AMM 71-00-01.
FLT 922, ORD-BOS, DIVERTED TO BUF, COCKPIT SMOKE SMELL AT FL LEVEL 380. EICAS WENT BLANK. FIRST GOT MFD 1 & 2 FAULT FOLLOWED QRH. SMOKE SMELL WAS NOT PRESENT IN CABIN. EMERGENCY LANDING AT BUF. PULLED OUT MFD 2. FOUND BURNED CIRCUIT BOARD SMELL AT REAR CONNECTORS. REMOVED AND REPLACED MFD 2 (DU4) PER AMM 31-61-01-04. OPS CHECK GOOD PER 31-61-00-710-801-A. OK FOR SERVICE.
FLT 447, BOS-TPA, DIVERTED TO JFK, BLEED 1 FAIL EICAS AT FL300, BLEED 1 PSI ABOUT 7 PSI, UNABLE TO MAINTAIN CABIN ALTITUDE. CLIMBING 800 FPM WITH CRUISE THRUST. FAULT CODE 36111200AM1 FOUND ON CMC. REMOVED AND REPLACED NACELLE PRSOV IAW AMM 36-11-03. OPERATIONAL CHECK OK. NO FAULT NOTED ON NR 1 BLEED SYSTEM. (S)
FLT 1205, HPN-RSW, FLAPS FAIL ON FINAL APPROACH, UNABLE TO RESET PER QRH, FLAP "0" LANDING, LANDING SPEED APPROX 180 KTS. T/S PER FIM TASK 27-51-00-810-802-A, REMOVED AND REPLACED L4 FLAP ACTUATOR DUE TO BEING POPPED IAW AMM 27-51-01, ALL OPS CHECKS NORMAL AMM 27-50-00-710-801-A1500.
FLT 1062, AUS-JFK, FLAPS FAIL UPON FLAP EXTENSION, FLAPS FAILED AT ZERO DEGREES, SLATS WERE OPERATIONAL. REMOVED AND REPLACED NR 2L FLAP ACTUATOR PER MM 27-51-01, OPS CHECK OK, REF EA-E08-189.
FLT 1295, BOS-PIT, HAD FLAP FAIL EICAS MESSAGE WHEN SELECTION FLAPS 1 DURING APPROACH INTO KPIT, RAN QRH WOULD NOT RESET HAD TO LAND FLAPS/SLATS 0, SLATS WORKED NORMALLY. RESET SYSTEM PER FIM 27-51-00-810-802-A00 FAULT CODES 275312014ACE, 27534007ACE, 27532018ACE CLEARED AT THIS TIME PER FIM, IS A TRANSITORY CONDITION, RAN SYSTEM TEST PER MM 27-53-02, OPS CHECK NORMAL AT THIS TIME.
FLIGHT MANAGEMENT DISABLED, ADS 3 FAIL AND OVERSPEED ANNUNCIATION IN DESCENT AT 17000FT, UNRELIABLE AIRSPEED INDICATIONS AND MULTIPLE EICAS MESSAGES AT 17,000 FT. UNABLE TO RE-ENGAGE AP/AT, APPR 2 NOT AVAIL DISPLAYED ON EICAS AT FL180 WITH 30.20 SET ON ALL 3 ALTIMETERS AND ILS 22L (JFK) CRS TUNED CORRECTLY ON BOTH CA AND FO SIDES. AP/AT UNCOMMANDED DISENGAGE AT 17,000 FT. PMA CLEARED ON BOTH CA/FO SIDE. MULTIPLE EICAS MESSAGES ILLUMINATED. CA AIRSPEED UNRELIABLE BEFORE AND AFTER MANUAL REVERSION TO ADS3. AP/AT WOULD NOT RE-ENGAGE ONLY LOC/GS WOULD ARM ON THE FMA. NOTHING ELSE WOULD ARM. OVERSPEED ANNUNCIATED AND DISPLAYED ON BOTH CA/FO AIRSPEED TAPES BEFORE AND AFTER MANUAL REVERSION TO ADS 3. STICK SH