N247JB
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
70 reports on file, 2006-08-23 – 2025-11-13.
Part: SKIN — DAMAGED (ZONE 100) · airframe 46,958 hrs · 30,476 cycles
DURING STRUCTURAL INSPECTION, A DENT WITH OIL CANNING AND SEVERAL NICKS LOCATED BETWEEN FR17 AND FR19 WERE FOUND, AND BETWEEN STRINGERS 26R AND 26L. MOST NICKS WERE REMOVED BY BLENDING AND CLASSIFIED AS NON-SIGNIFICANT DAMAGES PER SRM 51-75-16. HOWEVER, THREE DAMAGE LOCATIONS EXCEED THE LIMITS FOR NON-SIGNIFICANT DAMAGE AND THE ALLOWABLE DAMAGE PER SRM 53-10-01 AD51, DUE TO THEIR LOCATION WITHIN A NON-ALLOWED AREA. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930779, AND DOCUMENTED PER COOPESA COO-EO-2025-23380, UNDER JOB A1Q219 NRI 21-80.
Part: SKIN — DENTED (ZONE 200) · airframe 46,958 hrs · 30,476 cycles
DURING A STRUCTURAL INSPECTION, A CRACK WAS FOUND IN FWD FUSELAGE SKIN DENTED, BTWN FR18/19, BTWN STR-18R/19R. THE AFFECTED AREA WAS REPAIRED IAW ETD2014-190-051915 AND DOCUMENTED PER COOPESA EO COO-EO-2025-23345. UNDER JOB A1Q219 NRI 21-81.
Part: REPAIR — MISINSTALLED (ZONE 100) · airframe 46,022 hrs · 30,219 cycles
DURING STRUCTURAL INSPECTION, AN EXISTING REPAIR WAS FOUND ON THE FUSELAGE SKIN AT FR19 BETWEEN STR-27R. ACCORDING TO PREVIOUS OPERATOR DOCUMENTATION, THE REPAIR WAS PERFORMED UNDER ETD2025-190-000892 GUIDELINES. DUE TO ITS CONDITION (TOOL MARKS AND POORLY DRIVEN RIVET HEADS) THE REPAIR DOUBLER WAS REMOVED FOR REPLACEMENT. THIS CONDITION WAS REPORTED AND REPAIRED IAW ETD2025-190-927001 DTD AUG 22 2025 AND DOCUMENTED COOPESA COO-EO-2025-22844-R00 , UNDER JOB A1Q176 NRI 21-32
Part: SKIN — DAMAGED (ZONE 600) · airframe 46,022 hrs · 30,219 cycles
DURING THE ACCOMPLISHMENT OF SB 190-57-0056 AT RH WING AFT REINFORCEMENT AREA, WAS FOUND FIVE OVERSIZED FASTENER HOLES LOCATED AT THE AREA AFFECTED BY THE REINFORCEMENT DOUBLERS AND FITTING. THIS CONDITION WAS REPORTEDAND REPAIRED IAW ETD2025-190-927169 DTD AUG 26 2025 AND DOCUMENTED COOPESA COO-EO-2025-22947. UNDER JOBA1Q176 NRI 6-56.
Part: SKIN — DELAMINATED (LT FLAP) · airframe 46,022 hrs · 30,219 cycles
CUSTOMER REPORTS DELAMINATION DAMAGE AFFECTING THE LH INBOARD AFT FLAP LOWER SKIN. THE DAMAGE IS LOCATED AT SPAR 2 AND RIB 5A +50MM. THE DAMAGE AREA WAS EVALUATED AS PER SRM 57-52-00 AD51, HOWEVER, THE DELAMINATION IS LOCATED AT THE ZONE 1 AREA AND TABLE 101. DAMAGE IS LOCATED CLOSE TO THE SPAR 2 FASTENER ROW AND CUSTOMER CANNOT ASSURE THE DAMAGE REMOVAL WAY TO AVOID FASTENER REMOVAL DUE TO THERE IS NO ACCESS TO INSTALL THE NEW HI-LITE FASTENER AFTER REPAIR ACCOMPLISHMENT. THIS CONDITION WAS REPORTED AND REPAIRED IAW ETD2025-190-926369 DTD AUG 09 2025 AND DOCUMENTED COOPESA COO-EO-2025-22883-R00. UNDER JOB A1Q176 NRI 5-3
Part: SKIN — DAMAGED (ZONE 500) · airframe 46,022 hrs · 30,219 cycles
DURING THE ACCOMPLISHMENT OF SB 190-57-0056 AT THE LH WING FORWARD REINFORCEMENT AREA, ALLIANCE AIRLINES FOUND TWO OVERSIZED FASTENER HOLES LOCATED IN THE AREA AFFECTED BY THE REINFORCEMENT DOUBLERS. THE FIRST ONE FASTENER HOLE (HOLE A) IS COMMON TO THE SRGT22, AND THE SECOND ONE FASTENER HOLE (HOLE B) IS COMMON TO THE SPAR I AND PYLON LOWER FORWARD FITTING INBOARD (IT HAS SMALL BURR MARKS). THIS CONDITION WAS REPORTEDAND REPAIRED IAW ETD2025-190-926697 DTD AUG 18 2025 AND DOCUMENTED COOPESA COO-EO-2025-22890. UNDER JOB A1Q176 NRI 5-48.
Part: SKIN — WORN (THRUST REVERSER) · airframe 46,022 hrs · 30,219 cycles
DURING THE INSPECTION WAS FOUND ON ENGINE NR 2 OUTBD THRUST REVERSER TRANSLATING COWL, EXTERNAL SKIN WITH WORN AT 1 OâCLOCK POSITION. DUE TI THIS, WAS REPORTED AND REPAIRED TO BOWDEN (ENGINEERING SOLUTIONS PTY LDT) WITH THE ENGINEERING ORDER ESE-ERJ190-78-006 ISSUE 01. UNDER JOB A1Q176 NRI 21-44
Part: SKIN — DAMAGED (ZONE 100) · airframe 46,022 hrs · 30,219 cycles
CUSTOMER REPORTS A LIGHTNING STRIKE DAMAGE AFFECTING THE EXTERNAL SKIN OF THE FWD FUSELAGE, LOCATED AT FRAME 20+85MM, STRINGER 27RH+115MM. THE DAMAGE EXCEEDS 50% OF THE SKIN THICKNESS. A 3.97MM HOLE WAS DRILLED TO INSTALL A THROUGH DAMAGE REPAIR IN ACCORDANCE WITH SRM 53-10-01 AD 53. HOWEVER, THE DAMAGE IS LOCATED LESS THAN 75.6MM FROM THE JUNCTION FASTENERS ROW, WHICH IS OUTSIDE THE LIMITS DEFINED IN THE SRM. THIS CONDITION WAS REPORTED AND REPAIRED IAW ETD2025-190-927394 .
Part: SKIN — DAMAGED (ZONE 100) · airframe 46,022 hrs · 30,219 cycles
DURING THE STRUCTURE INSPECTION IT WAS FOUND THE FORWARD FUSELAGE, AT FR18+50MM, AND S27LH + 155MM (JUST 8.0MM FROM THESTR 28L FASTENER ROW), THE EXTERNAL SKIN WITHLIGHTNING STRIKE WITH EXISTING BLEND OUT. THE BLEND OUT WAS EVALUATED AND CLASSIFIED ASNON-SIGNIFICANT AS PER SRM 51-75-16.SINCE THE LIGHTNING STRIKE DAMAGE GOES BEYOND OF THE50% OF THE SKIN THICKNESS, IT WAS REMOVED BY DRILLING A 2.3MM HOLE DIAMETER(Ã2.3MM).PERFORMED DETAIL VISUAL INSPECTION AROUND DAMAGE AREA IAW E-190 NDT MANUAL INTRODUCTIONPARAGRAPH 5B (1)(B) AND NOADDITIONAL DAMAGE WAS FOUND. THE DAMAGE WAS EVALUATED INACCORDANCE WITH THE SRM 53-10-01 AD53, HOWEVER, THE DAMAGE IS TOO CLOSE OF THE STRINGER28L, THEREFORE THERE IS NO ROOM FOR THE THROUGH DAMAGE REPAIR FASTENER AND WASHER.CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-926754 REV. C.
Earlier reports · 2006–2024 · 61 reports
2024
Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 45,941 hrs · 30,149 cycles
FLT#2254, DCA-BOS.' WHILE PERFORMING TASK CARD E190-33-50-25-710-801 FWD RH EXT EMERG LIGHT WILL NOT ILLUMINATE. ( EXTERNAL EMERGENCY-OPS NOT CONDUCTED AT NIGHT ); REMOVED AND REPLACED ELPU OPS CHECKS OK PER AMM 30-50-01. THIS CLEARS MDDR 550483 MEL 33-50-25A CATC, MX-4 UPDATED, PLACARD REMOVED.'
2023
Part: SHEAR TIE — CORRODED (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: CORROSION ON SHEAR CLIP ON AFT COMPARTMENT STRUCTURE BTW FR83 AND STRINGER 28L/29L; "REF: TOMX W/O 2404 N/R 00090 STRINGER CLIP WAS REPLACED PER EMB-190 SRM 51-41-02 AND SRM 51-43-01".
Part: SHEAR TIE — CORRODED (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: CORROSION ON SHEAR CLPI ON AFT COMPARTMENT STRUCTURE BTW FR88 AND STRG 28R/27R; "REF: TOMX W/O 2404 N/R 00096 REPLACED SHEAR CLIP PER EMB-190 SRM 51-41-02 AND SRM 5143-03"
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: DURING AFT FUS FAIRING 199ML INSTALLATION, UPPER EMERGENCY LIGHT WAS FOUND INNOPERATIVE; REF TOMX WO #2404 NR # 00176 UPPER EMERGENCY LIGHT WAS REPLACED PER EMB-190 AMM 33-50-25--000-802-A AND PER EMB-190 AMM 33-50-25--400-802-A.
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: FUSELAGE / CENTER FUSELAGE II / LOWER SKIN / AT STR 29R BETWEEN FR73 â FR74 / CORROSION - PERMANENT REPAIR (CONSIDERED A MAJOR REPAIR)
Part: NONE — NONE (NONE) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: # 2 ENGINE REMOVED TO FOM; # 2 ENGINE REINSTALLED IAW E190 AMM 71-00-01.
Part: SHEAR TIE — CORRODED (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: CORROSION ON SHEAR CLIP ON AFT COMPARTMENT STRUCTURE BTW FR87 AND STRG 28R/27R; "REF: TOMX W/O 2404 N/R 00097 REPLACED SHEAR CLIP PER EMB190 SRM 51-43-03 AND SRM 51-41-02".
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: FUSELAGE / CENTER FUSELAGE III / FLOOR STRUCTURE / RH SEAT TRACK / FR84 / CORROSION - PERMANENT REPAIR (CONSIDERED A MAJOR REPAIR)
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: CORROSION ON RH SEAT TRACK LOCATED BTW RE 17/18 AND Y:300RH AT CABIN FLOOR STRUCTURE (W1); REF: TOMX W/O 2404 N/R - 00060 SEAT TRACK WAS REPLACED PER EMB-190 SRM 51-12-01, SRM 51-10-03, SRM 51-75-16, SRM 53-10-10/AD51, SRM 51-41-01, SRM 51-41-02, SRM 51-43-03 AND SRM 51-43-04.
Part: SHEAR TIE — CORRODED (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: CORROSTION ON SHEAR CLIP IN AFT COMPARTMENT STRUCTURE BTW FR82 AND STRINGER 28R/29R; "REF: TOMX W/O 2404 N/R 00089SHEAR CLIP WAS REPLACED PER EMB-190 SRM 51-41-02 AND SRM 51-43-03".
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: CPCP FINDING CORROSION ON STRINGER ON AFT COMPARTMENT STRUCTURE BTW FR 76/78 AND STRG 29R; "REF TOMX WO # 2404 NR # 00091 CORROSION ON STRINGER ON AFT COMPARTMENT STRUCTURE BTW FR 76/78 AND STRG 29R WAS REMOVED PER EMB-190 SRM 51-12-01, SRM 51-10-03 WAS MEASURED AND EVALUATED OUT OF LIMITS PER EMB190 SRM 53-23-03/AD51, THEREFORE WAS REPLACED".
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: AFTER LATCH FITTINGS REMOVAL IN REF WITH NRC 071,CORROSION ON LOWER BEAM IN CUTOUT AT FWD CARGO DOOR; REF TOMX WO # 2404 NR # 00144 CORROSION ON LOWER BEAM IN FWD CARGO DOOR CUTOUT WAS REMOVED PER EMB-190 SRM 51-12-01 AND SRM 51-10-03 AND EVALUATE WITH THE FOLLOWING MEASURES: OT= .236 IN, RT= .170 IN THEREFORE IS OUT LIMITS PER EMB 190 SRM 53-21-11/AD53 AND NDT MANUAL PART 4 51-04-00-270-804-A - LOWER BEAM WAS REPLACED PER EMB 190 SRM 51-43-04 , SRM 51-43-03 AND SRM 51-41-01.
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: CRACK AT END OF STRG 9R IN FR 73, LOCATED AT INTERNAL STRUCTURE OF CF II; REF TOMX WO #2404 TOMX NR # 00051Y:STRG 9R IN FR 73, LOCATED AT INTERNAL STRUCTURE OF CF II WAS REPLACED PER EMB 190 SRM 51-43-03 AND SRM 51-43-04.
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 65,499 hrs · 23,522 cycles
DURING HEAVY MAINTENANCE: AFTER STRG 29R REMOVAL, FOUND CORROSION AT INNER FUSELAGE SKIN LOCATED BETWEEN FR73/74 IN AFT CARGO COMPARTMENT; REF TOMX WO # 2404 NR # 00168 CORROSION AT INNER FUSELAGE SKIN LOCATED BETWEEN FR73/74 IN AFT CARGO COMPARTMENT WAS REMOVED PER EMB 190 SRM 51--12-01 PAR. 6 AND SRM 51-10-03 AND REPAIRED PER ETI-190-23-734 REV. 3. AND ETD2023--190-030959 AND JB EC 23-1219--01.
Part: BATTERY — DAMAGED (ELT) · airframe 44,633 hrs · 29,188 cycles
FLT#2754, DCA-BOS. 'ELT BATTERY ??? AND FOUND ELT WIRES DAMAGED; REPLACED ELT BATTERY REPAIRED C/P PER 25-61-01. CHECK SYSTEM OK.PER 25-61-00.'
2022
Part: LINK — MALFUNCTIONED (MLG) · airframe 42,726 hrs · 27,798 cycles
FLT 1340, NAS-MCO. AFTER LIFT OFF LANDING GEAR UP LOCK SELOIND CYCLE REPEATEDLY. GEAR HAND WOULD NOT GO UP MOMENTARILY. OCCURRED ON BOTH LEGS. THE GEAR EXTENDED NORMALLY. SEE PREVIOUS WRITE UP(12/14); REF LP 3457854, ITEM 2. REPLACED HARDWARE OF RH MAIN GEAR SLAVE LINK AS REQUIRED PER AMM 32-11-13. OPS CHECK ALL GEARS USING AMM 32-62-03. ALL CHECK OK AT THIS TIME. FOR CORRECTIVE ACTION. A/C OK FOR SERVICE.
2021
Part: SKIN — CRACKED · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, CRACK: LOWER SKIN RH WING AT WING SPAR 2 AND RIB 9A +3.00"; REF TOMX NR 00373:ACCOMPLISHED REPAIR IAW EMBRAER SRM 57-10-01 PAR 11(P)(Q)(R)(T), FIG 202 SHEET 4 AND SRM 51-43-01 PAR 5, FIG 2. TOMAX R.S. 4TOY762C TECH 89307 QC RII 236912
Part: NONE — NONE · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN FWD SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE; ALL WORK ACCOMPLISHED REF TOMX NR 00301 FWD SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28 TOMAX R.S. 4TOY762C TECH 89307 QC RII 236912 .
Part: DOOR FRAME — CORRODED (FRM 77) · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, "FROM TOMX NR 00300, INITIAL INSPECTION: ""CPCP FINDING"" CORROSION IN FASTENER PERIPHERY LOCATED OVER MACHINED BEAM BETWEEN STRG 27R/28R AND FR 77 IN AFT CARGO DOOR CUTOUT STRUCTURE" ; "FROM TOMX NR 00300, INITIAL INSPECTION: ""CPCP FINDING"" CORROSION IN FASTENER PERIPHERY LOCATED OVER MACHINED BEAM BETWEEN STRG 27R/28R AND FR 77 IN AFT CARGO DOOR CUTOUT STRUCTURE" (CONSIDERED A MAJOR REPAIR) .
Part: SEAL REST — CORRODED (FRM 77) · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN FWD SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE; "ALL WORK ACCOMPLISHED REF TOMX NR 00301 FWD SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28 ALL WORK ACCOMPLISHED REF TOMX NR 00301 FWD SEAL REST IN" (CONSIDERED A MAJOR REPAIR) .
Part: NONE — NONE · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN AFT SEAL REST IN LOWER EDGE OF AFT CARGO; ALL WORK ACCOMPLISHED REF TOMX NR 00301 AFT SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28(CLASSIFIED AS A MAJOR REPAIR)
Part: NONE — NONE · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN FWD SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE; ALL WORK ACCOMPLISHED REF TOMX NR 00301 FWD SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28 (CLASSIFIED AS A MAJOR REPAIR)
Part: NONE — NONE · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN MIDDLE SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE; ALL WORK ACCOMPLISHED REF TOMX NR 00301 MIDDLE SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28 (CLASSIFIED AS A MAJOR REPAIR)
Part: NONE — NONE · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, CRACK: LOWER SKIN RH WING AT WING SPAR 2 AND RIB 9A +3.00"; REF TOMX NR 00373:ACCOMPLISHED REPAIR IAW EMBRAER SRM 57-10-01 PAR 11(P)(Q)(R)(T), FIG 202 SHEET 4 AND SRM 51-43-01 PAR 5, FIG 2. TOMAX R.S. 4TOY762C TECH 89307 QC RII 236912 .
Part: SEAL REST — CORRODED (AFT CARGO) · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN AFT SEAL REST IN LOWER EDGE OF AFT CARGO; "ALL WORK ACCOMPLISHED REF TOMX NR 00301 AFT SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28 ALL WORK ACCOMPLISHED REF TOMX NR 00301 AFT SEAL REST IN" (CONSIDERED A MAJOR REPAIR) .
Part: NONE — NONE · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN MIDDLE SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE; ALL WORK ACCOMPLISHED REF TOMX NR 00301 MIDDLE SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28 .
Part: DOOR FRAME — CORRODED (FRM 78) · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN MIDDLE SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE; "ALL WORK ACCOMPLISHED REF TOMX NR 00301 MIDDLE SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28 ALL WORK ACCOMPLISHED REF TOMX NR 00301 MIDDLE SEAL R" (CONSIDERED A MAJOR REPAIR). .
Part: NONE — NONE · airframe 40,451 hrs · 26,175 cycles
DURING HEAVY MAINTENANCE, INITIAL INSPECTION CPCP FINDING CORROSION IN AFT SEAL REST IN LOWER EDGE OF AFT CARGO; ALL WORK ACCOMPLISHED REF TOMX NR 00301 AFT SEAL REST IN LOWER EDGE OF AFT CARGO DOOR CUTOUT STRUCTURE WAS REPLACED PER EMB 190 SRM 51-40-08 AND SRM 51-41-01 AND JETBLUE GMM 8.19.4.1 PAR 13 REV 28 .
Part: DIAPHRAGM — BLOWN · airframe 40,325 hrs · 26,094 cycles
FLT # 628, CHS-EWR. R1 DOOR REQ. SERVICING AND DOOR DIAPHRAM BLOWN. ; REPLACED R-1 SERVICE DOOR PNEUMATIC ASSY DIAPHRAM AND SHEAR PIN IAW AMM 52-41-53/400. SERVICE R-1 DOOR PNEUMATIC ASSY IAW AMM 52-41-51. LEAK CHECK OK.
Part: SLIDE — DEPLOYED (R1-SLIDE) · airframe 40,325 hrs · 26,094 cycles
FLT # 628, CHS-EWR. A/C OOS DUE TO R1 DOOR SLIDE BLOWN ; R/R OF R1 DOOR SLIDE IAW AMM 52-11-40. OPS CHECK GOOD A/C OK FOR SVC.
Part: CONTROL MODULE — FAILED (BRAKE SYSTEM) · airframe 39,833 hrs · 25,772 cycles
FLT 2155, JFK-FLL. IN CRUISE, GOT "BRK FH FAULT" AND "BRK LH FAULT". AFTER LANDING, GOT "LG NO DISPATCH" WITH BRK FAULT MESSAGES. NOTICED HYDRAULIC SYSTEM 1 QUANTITY SHOWED DASHES MOMENTARILY; R & R #2 BCM SLOT 16 MAU#2 IAW AMM32-41-07 SOFTWARE LOAD GOOD .OPS CK GOOD FUNCTIONAL CK GOOD.
Part: WARNING MESSAGE — FALSE ACTIVATION (RT AILERON) · airframe 38,957 hrs · 25,257 cycles
FLIGHT 663, EWR-JAX. AILERON RT HAND FAIL MSG APPEARED AT CRUISE; TROUBLESHOT IAW FIM REFERENCE 27-03-00-810-926-A . PERFORMED RETURN TO SERVICE TEST IAW AMM 27-00-00 AND AILERON RT HAND FAIL MESSAGE CLEARED. NO FURTHER DEFECTS NOTED.
2019
Part: POWER UNIT — FAILED (CABIN) · airframe 37,161 hrs · 24,013 cycles
FLT 1979, DCA-FLL. WHILE PERFORMING T/C E190-33-50-01-720-801-AFT. FOUND AFT ELPU 5+6 FAILS FUNCTIONAL TEST; R & R ELPU 5 + 6 IAW AMM 33-50-01. OPS CK OK. A/C OK TO CONT SVC.
Part: UNKNOWN — ODOR (COCKPIT) · airframe 35,449 hrs · 22,832 cycles
FT # 2133, DESCENDING THRU 12K, GOT STRONG JET EXHAUST SMELLING FUMES IN COCKPIT. GOT VERY STRONG SMELLING BOTH PILOTS WENT ON O2. TURNING RECIRCS OFF BRIEFLY HELPED, BUT STRONG FUMES CONTINUED. NO SMELL DETECTED IN CABIN; PER FIM 21-20-00-810-801A & 803A PERFORMED INSPECTION OF THE AREAS THROUGHOUT CABIN / FLT DECK / AVIONICS AREAS W/ NO DEFECTS NOTED. OPERATED APU BLEED, ENGINE BLEEDS WITH EACH PACK 1 & 2 SEPARATELY. NO DEFECTS NOTED. ALSO FIM 25-30-00-810-801A ABNORMAL GALLEY SMELL PLUS 25-40-00-810-801 LAVATORY CHECKS NORMAL. ACFT OK FOR CONT SVC AT THIS TIME.
2018
Part: BATTERY — DISCHARGED (CABIN) · airframe 34,266 hrs · 21,998 cycles
FLT 2680, EWR-BOS. 2 EACH EMERGENCY LIGHT POWER UNITS FAILED OPERATIONAL TEST. REPLACED 2 EACH EMERGENCY POWER UNITS IAW AMM 33-50-01.
Part: BATTERY — DISCHARGED (CABIN) · airframe 34,266 hrs · 21,998 cycles
FLT 2680, EWR-BOS. 2 EACH EMERGENCY LIGHT POWER UNITS FAILED OPERATIONAL TEST. REPLACED 2 EACH EMERGENCY POWER UNITS IAW AMM 33-50-01.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,833 hrs · 21,667 cycles
DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON REF NR 2018-222179 SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR74 AND S-29L ON AFT CARGO COMPARTMENT; REPLACED SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR74 AND STR29L ON AFT CARGO COMPARTMENT IAW SRM 51-40-08 AND DWG 170-65180-433.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,833 hrs · 21,667 cycles
DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON REF NR 2018-222183 SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR80 BETWEEN S29L-S29R (2EA) ON AFT CARGO COMPARTMENT; REPLACED SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR80 BETWEEN S29L & 29R (2EA) ON AFT CARGO COMPARTMENT IAW SRM 51-40-08 & DWG 170-651180-433.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,833 hrs · 21,667 cycles
DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON REF NR 2018-222183 SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR80 BETWEEN S29L TO S29R (2EA) ON AFT CARGO COMPARTMENT; REPLACED SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR80 BETWEEN S 29L TO S29R (2EA) ON AFT CARGO COMPARTMENT IAW SRM 51-40-08 & DWG 170-65180-433.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,833 hrs · 21,667 cycles
DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON REF NR 2018-222180 SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR76 AND BETWEEN S29R TO S-29L (2EA) ON AFT CARGO COMPARTMENT; REPLACED SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR76 AND BETWEEN S29R TO S29L ON AFT CARGO COMPARTMENT IAW SRM 51-40-08 AND DWG 170-65180-433.
Part: SKIN — DAMAGED (FUSELAGE) · airframe 33,833 hrs · 21,667 cycles
DURING HEAVY MAINTENANCE ( BASIC 6 CHECK AT SAL) FOR A/C N247JB, WHILE ACCOMPLISHING JACKING PROCEDURES, CREASE DAMAGE WAS A RESULT OF IMPROPERLY FOLLOWING PROCEDURES. THE DAMAGE IS COMMON TO THE REAR FUSELAGE SKIN (P/N 190-61701-003) AT FR 92/FR93 & STR 29L-29R. THE DAMAGE IS REPORTED AS 2.498âL X 0.045âW X 0.045âDEPTH AND IS SHOWN IN FIGURE 1 & 2 OF THE REF /1/ EA & REF /2/ ETD. DAMAGE FOUND TO BE OUT OF SRM PART II 53-30-01 /REPAIR 63P SCOPE DUE TO THE DAMAGE LOCATION, THEREFORE AEROMAN CONTACTED EMBRAER FOR REPAIR INSTRUCTIONS, PROPOSING A PERMANENT REPAIR WITH THE GUIDELINES OF REF/3/. EMBRAER PROVIDED REF /2/ ETD WHICH PROVIDES PERMANENT REPAIR, ALLOWING THE INSTALLATION OF A REPAIR DOUBLER PER REF /3/ GUIDELINES, WITH ADDITIONAL POST REPAIIR INSPECTIONS REQUIRED (METHOD: INTERNAL & EXTERNAL DET, .THRESHOLD: 20,000FC FROM REPAIR EMBODIMENT, INTERVAL; 5000FC). THE REPAIR WAS PERFORMED AS DETAILED IN THE REF /2/ ETD AND THE REF /1/ AEROMAN EA PROVIDED THE INSTRUCTIONS FOR THIS REPAIR. THIS EC ACCOMPLISHES THE PERMANENT REPAIR AND COMPLIES WITH REF /2/ ETD WITHOUT DEVIATION. THIS EC E18-583-01 PROVIDES THE PERMANENT REPAIR INSTRUCTIONS PER THE REF /2/ ETD. EC E18-583-02 PROVIDES THE POST REPAIR INSPECTION INSTRUCTIONS (METHOD: INTERNAL & EXTERNAL DET, .THRESHOLD: 20,000FC FROM REPAIR EMBODIMENT, INTERVAL; 5000FC) PER THE REF /2/ ETD; THIS PERMANENT REPAIR HAS BEEN APPROVED VIA REF /2/ ETD AND IS CLASSIFIED AS âMAJORâ ACCORDING TO THE GUIDELINES SPECIFIED IN THE REF /4/ MX-244.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,833 hrs · 21,667 cycles
DURING HEAVY MAINTENANCE, CORROSION WAS DISCOVERED ON REF NR 2018-222184 SUPPORT BRACKET FLOOR STRUCTURE AT FR81 ANFD SR-29R ON AFT CARGO COMPARTMENT; REPLACED SUPPORT BRACKET FLOOR STRUCTURE LOCATED AT FR81 AND S-29R ON AFT CARGO COMPARTMENT IAW SRM 51-40-08.
2017
Part: BATTERY PACK — FAILED (EMERGENCY LIGHT) · airframe 32,214 hrs · 20,518 cycles
FT # 1282, RIC-BOS. EMERGENCY LIGHT OVER L1 DOOR INOP; R & R #1 EMERGENCY POWER UNIT PER AMM 33-50-01. OPS CHECK GOOD.
2015
Part: SHEAR TIE — CORRODED (FRAME 76) · corrosion level 2 · airframe 26,575 hrs · 16,488 cycles
CORROSION ON SHEAR TIE, FRAME 76 + 1.0 BETWEEN STRINGERS 28 AND 29R. R & R CORRODED THE SHEAR TIE IAW SRM 51-41-01 AND 51-41-02.
2014
Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 23,187 hrs · 14,197 cycles
COCKPIT EMERGENCY LIGHTS DID NOT ILLUMINATE. R & R COCKPIT EMERGENCY LIGHT POWER UNIT IAW AMM 33-50-01. OPS CHECKED OK.
Part: TRANSMITTER — FAILED (OIL PRESSURE) · airframe 22,923 hrs · 14,017 cycles
CREW PERFORMED QRH DUE TO NR 1 ENGINE OIL LOW PRESSURE. ENGINE SHUTDOWN, MESSAGE WAS TRANSIENT THROUGHOUT FLIGHT. SENT DVDR INFO TO MFG PERFORMED FIM TASK 79-33-00-810-805-A. ALL WIRING CHECKED GOOD. NR 1ENGINE OIL PRESSURE TRANSMITTER R & R IAW AMM 79-33-03. OPS & LEAK CHECKED GOOD.
2012
Part: ACQUISITION UNIT — MALFUNCTIONED (NR 3) · airframe 17,122 hrs · 10,365 cycles
FLT 572 PBI-HPN, CREW DECLARED EMERGENCY DUE TO AVNX MAU 3A FAIL EN ROUTE. ACCOMPLISHED FIM TASK 31-42-00-810-812A. MESSAGE CLEARED. A/C OK TO CONTINUE. ON 8/5/12 FLT 585 MAU 3 FAILED TWICE IN CLIMBOUT AND CRUISE. REMOVED AND REPLACED MAU 3 NIC 1 AND MAU 3 PWR SUPPLY 1. ON 8/6/12 FLT 1791 MAU 3 FAIL EICAS MSG -REPEATED.
Part: BRACKET — OUT OF ADJUST (GIRT BAR) · airframe 17,079 hrs · 10,342 cycles
FLT 1213 BOS-BUF, ON GROUND UNABLE TO OPEN L1 DOOR AT THE GATE. REMOVED DEBRIS FROM GIRT BAR FLOOR FITTINGS. OPS CHECK GOOD. THIS ITEM REPEATED ON FLIGHT 1018 ON 8/2/12. THE GIRT BAR BRACKET WAS ADJUSTED. ADJUSTED FWD PAX DOOR EMERGENCY EVACUATION SLIDE MECHANISM REFERENCE E190 AMM 52-11-40 AND 52-11-00. OPS CHECK GOOD.
2011
Part: PRECOOLER — LEAKING (BLEED AIR SYS) · airframe 13,031 hrs · 7,812 cycles
FLT 620 HOU-BOS, AIR RETURN TO HOU DUE TO ENG 1 BLEED LEAK AT FL190 IN CLIMB. LEVELED RAN QRH AT 250 RESET DID NOT WORK. STARTED APU, APU NORMAL BUT NO BLEED AIR FROM ANY SYSTEM. CAB ALT REACHED 11600 PRIOR TO EMERGENCY DESCENT. T/S BLEED 1 LEAK FOUND BAD PRECOOLER. REMOVED AND REPLACED ENGINE 1 PRECOOLER IAW 36-11-08-04. OPS AND LEAK CHECK GOOD. NOTE: ENGINE 2 BLEED ALREADY ON MEL.
2010
Part: SLIDE — UNSERVICEABLE (R1 DOOR) · airframe 12,402 hrs · 7,434 cycles
FLT 1005 BOS-JFK, ON GROUND CREW REPORTED R-1 DOOR HANDLE NOT WORKING FREELY. INSPECTED AND FOUND LANYARD PIN AFT/RIGHT ON THE R1 DOOR BROKEN OF THE STRING AND STUCK ON THE FLOOR FITTING FLAP. REMOVED AND REPLACED R1 EVACUATION EMERGENCY SLIDE IAW 25-65-01. ALL OPS NORMAL.
2009
Part: WIRE — DAMAGED (BLEED AIR SYS) · airframe 8,643 hrs · 5,183 cycles
FLT 1148, MCO-BTV, DIVERTED TO RDU, EICAS DISPLAY BLEED RT LEAK. PERFORMED QRH PROCEDURES SEVERAL TIMES. BLEED 2 LEAK ILLUMINATED. PROBLEM ISOLATED TO WIRING. AWAITING FINAL FIX.
Part: WASHER — BROKEN (NLG DOOR) · airframe 8,450 hrs · 5,068 cycles
FLT 1289 - BOS-RIC - ON CLIMBOUT NOSE DOOR OPEN ECAM, VIBRATION NOTICED ON CLIMBOUT AND CRUISE. ECAM INDICATION CAME ON AND DISAPPEARED 4 OR 5 TIMES IN FLIGHT. THE VIBRATION DID INCREASE WITH AND INCREASE IN SPEED. DIVERTED TO JFK. UPON INSPECTION OF NLG AND AND NLG DOOR LINKAGES FOUND 3 OF 4 LINKAGE RODS LOCK WASHERS BROKEN. REPLACED ALL 4 LOCK WASHERS PER AMM 32-22-00. PERFORMED OPERATIONAL TEST OF L/G PER AMM 32-33-00. OPS CHECKS GOOD. NO OTHER DEFECTS NOTED.
Part: FADEC — FAILED (NR 1 ENGINE) · airframe 8,412 hrs · 5,046 cycles
FLT 1012, JFK-BOS, NR 1 ENGINE CYCLED BACK ABOUT 30 PERCENT N1 AT 10,000 FT. A/C YAWED LEFT. AUTO THROTTLES DISENGAGED. N1 WAS NORMAL IN CRUISE. ENG 1 NO DISPATCH EICAS MESSAGE ON LANDING. REMOVED AND REPLACED NR 1 ENGINE FADEC IAW AMM 73-21-01. OPS CHECK GOOD. REMOVED AND REPLACED THROTTLE QUADRANT ASSY IAW AMM 76-11-01 PRECAUTIONARY. OPS CHECK GOOD. PERFORMED GROUND POWER ASSURANCE RUN IAW GE EMM 72-00-00-760-118. ALL SYSTEMS CHECK NORMAL. A/C OK FOR SERVICE.
Part: UNKNOWN — ODOR (COCKPIT) · airframe 7,909 hrs · 4,786 cycles
FLT 80, JFK-SYR, FUMES SMELLED IN COCKPIT (ELECTRICAL). PERFORMED FIM 21-20-00-810 AND FOUND SLIGHT ENGINE CONTAMINATION. PERFORMED ENGINE RUNS AND FOUND NO DISCREPANCIES. COMPLETED LIVE TV E190 ELECTRICAL ODOR SYSTEM INTEGRITY CHECK. NO FAULT FOUND LTV SYSTEM. OPS CHECK GOOD IAW LTV MM 44-20-10. A/C OK FOR SERVICE.
Part: DEFLECTOR — VIBRATION (L1 DOOR) · airframe 7,537 hrs · 4,572 cycles
PRONOUNCED L1 DOOR VIBRATION ON DESCENT THRU 8500 FT. AFTER DEBRIEFING THE CABIN & FLIGHT CREW IT WAS DETERMINED THE VIBRATION WAS AT L1 DOOR DEFLECTOR. CREW DECLARED EMERGENCY. PART OF THE DOOR SEAL WAS REMOVED PREVIOUSLY. THE REMAINING DOOR SEAL WAS TRIMMED AS REQUIRED PER CDL C-52-10-01. PERFORMED FAULT ISOLATION MANUAL 05-50-00-810-801-A. A/C OK FOR SERVICE.
2008
Part: PUMP — LEAKING (NR 2 ENGINE) · airframe 6,677 hrs · 4,114 cycles
FLT 1419, BOS-JAX - AIR TURNBACK, HYD 2 LO QTY. REMOVED AND REPLACED NR 2 ENG DRIVEN PUMP IAW AMM 29-11-01. REMOVED AND REPLACED HYD FILTERS, LEAK CHECK OK.
Part: ACTUATOR — MALFUNCTIONED (LE SLAT) · airframe 6,656 hrs · 4,103 cycles
FLT 1150, MCO-PWM, DIVERTED TO BOS, SLAT FAIL IN FLIGHT. T/S PER FIM 27-81-00-810-802A, FOUND SLAT ACT NR 6 TORQUE LIMITER TRIPPED. REMOVED AND REPLACED PER AMM 27-81-01, OPS CHECK NORMAL.
Part: PDU — FAILED (LE SLAT) · airframe 6,623 hrs · 4,085 cycles
ORD-JFK, SLAT FAIL ON APPROACH TO LANDING, QRH ITEMS COMPLETED. AFTER EMBRAER ANALYZED THE FHDB FOR SLAT FAIL EVENT (REPEAT ITEM) IT WAS DETERMINED THAT THE SLAT SURFACES JAMMED IN FLIGHT DURING APPROACH. FIM TASK 27-81-00-810-802-A. PERFORMED FIM TASK 27-83-00-810-804-A. REPLACED NR 1 SLAT LT ELECTRIC PDU MOTOR. REF AMM 27-83-04. ALSO C/W FIM TASK 27-81-00-810-802-A. OPS CHECK OK.
2007
Part: SENSOR — MALFUNCTIONED (SLAT SKEW) · airframe 3,437 hrs · 2,274 cycles
SLAT FAIL INFLIGHT, NO SLATS AT ALL, APPROACH SLAT 0/FLAP 2, FLAPS OPERATED NORMALLY. UPON TROUBLESHOOTING THROUGH CMC, FOUND FAULT CODE 27811013ACE, L WING OUTBD SLAT PANEL SKEW, REMOVED & REPLACED LEFT OUTBOARD SLAT SKEW SENSOR 3/4 IAW EMB 190 AMM 27-83-01 AND PERFORMED OPERATIONAL TEST PER EMB 190 AMM 27-83-01-710-801-A/500. OPS CHECK GOOD AND MESSAGE CLEARED AT THIS TIME. A/C IS OK FOR RETURN TO SERVICE.
2006
Part: SHAFT — SHEARED (FUEL PUMP) · airframe 75 hrs · 50 cycles
ENGINE NR 2 FAIL FL310 DID QRH AND LANDED. ACCOMPLISHED EA E06-446, ENGINE TROUBLESHOOT PROCEDURE FOR N247JB. NR 2 ENGINE S/N 994202 MAIN FUEL PUMP SHAFT SHEARED. REPLACED NR 2 ENGINE FUEL PUMP IAW AMM 73-11-01 AND GE 73-00-00. REPLACED FMU IAW AMM 73-21-03 & GE 73-00-00. REPLACED THE MAIN FUEL TO OIL HEAT EXCHANGER. PERFORMED ENGINE TRANSIT CHECK, OIL CONSUMPTION CHECK AND ENGINE FUEL AND OIL SYSTEM LEAK CHECK.
Part: MODULATOR — FAILED (SPDA NR 2) · airframe 9 hrs · 5 cycles
SPDA FAIL MESSAGE. REMOVED AND REPLACED SPDA MICRO/COMM MODULE IN THE SPDA 2 POSITION IAW AMM 24-61-07-000-801-AND 24-61-07-400-801-A.