N197JB
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
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.
59 reports on file, 2006-09-19 – 2024-10-08.
Part: SKIN — DAMAGED (ZONE 100) · airframe 45,663 hrs · 29,768 cycles
DURING PRESENT CHECK LIGHTNING STRIKE ON FUSELAGE SKIN WAS REPORTED. THE DAMAGE WAS REWORKED AS PER ERJ SRM PART II 51-40-02 PARAG 4 AND EVALUATED THROUGH DAMAGE AS PER ERJ SRM PART II 53-10-01 AD 53 PARAG 4B(6), HOLE FOUND OUT ALLOWABLE DAMAGE LIMITS. DUE TO THIS FACT WE ARE CONTACTING ERJ FOR TECHNICAL SUPPORT EVALUATION AND APPROVAL. PERFORMED PERMANENT THROUGH DAMAGE REPAIR AT FORWARD FUSELAGE, FR11+68MM, STR20LH+95MM AND FR11+70MM, STR21LH+81MM IAW ERJ-190 SRM PART II 53-10-01, AD53, PAR.5, FIG.102 AND FR11+80MM, STR23LH+103MM IAW COOPESAâS EO NUMBER COO-EO-2024-20481-R00, REV.00 DATED JUL-23-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-019812 DATED JUL-21-24. THIS IS A MINOR REPAIR, DOCUMENTED ON COOPESAâS ITEM: A1P145 21-12.
Part: SKIN — NO DISCREPANCY (ZONE 600) · airframe 45,663 hrs · 29,768 cycles
PER ALLIANCE TASK CARD SB190-57-0056, WILL BE PERFORMED ON THE AIRCRAFT THE SB190-57-0056, HOWEVER, DURING THE RH WING AFTER REINFORCEMENT LAYOUT PROCESS, HAS BEEN NOTICED THAT THE SB REINFORCEMENT IS INTERFERING WITH AN EXISTING REPAIR INSTALLED PER ETD2019-190-158191 REV C, DTD OCT 30, 2020, DUE TO THIS FACT WE ARE CONTACTING ERJ FOR TECHNICAL SUPPORT EVALUATION AND APPROVAL. PERFORMED TEMPORARY REPAIR AT MAIN BOX-RH WING LOWER SKIN PANEL SB 190-57-0056 RH REAR REINFORCEMENT INTERFERENCE WITH PREVIOUS DOUBLER REPAIR IAW COOPESAâS ENGINEERING ORDER # COO-EO-2024-20450-R03 REV.03, DATED SEP-13-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-019100 REV.B, DATED SEP-05-24. DOCUMENTED ON COOPESAâS ITEM A1P145 21-79 AND ANAC FORM F-101-06, DATED SEP-05-24. NO ADDITIONAL INSPECTIONS REQUIRED DURING THE 12 MONTHS VALIDITY OF TEMPORARY REPAIR. THIS REPAIR IS CONSIDERED TEMPORARY AS IT WILL REQUIRE A DETAILED STRUCTURAL ANALYSIS. THE VALIDITY OF THIS REPAIR IS 12 MONTHS AS OF AUGUST 5TH, 2024 (ORIGINAL ISSUANCE OF THIS DOCUMENT) OR TILL THE SUBSTANTIATION IS CONCLUDED, WHICHEVER OCCURS FIRST.
Part: SKIN — NO DISCREPANCY (ZONE 200) · airframe 45,663 hrs · 29,768 cycles
DURING MAPPING PROCESS, THE COSTUMER REQUEST REVIEW THE TWO INTERNAL EXISTING REPAIRS, AFTER EXISTING DOCUMENTATION REVIEW AND INSPECTION OF THE AFFECTED AREA WE HAVE THE FOLLOWING COMMENTS: 1.ONLY ONE REPAIR HAS TECHNICAL RECORD UNDER ETD2010-190/01224 BUT DUE LACK INFORMATION IN THE MATERIAL TRACEABILITY WE NEED TO REASSESSMENT THIS REPAIR. 2.ADDITIONALLY INTERNAL EXISTING REPAIR IN THE ADJACENT BAY WAS FOUND AND THE COSTUMER DOES NOT HAVE DOCUMENTATION. DUE TO THIS FACT A REPAIR PROPOSAL WAS SENT TO EMBRAER FOR TECHNICAL SUPPORT EVALUATION AND APPROVAL. PERFORMED TEMPORARY REPAIR AT FORWARD FUSELAGE FROM FR19A+145MM TO X=6232.5 JUNCTION, BETWEEN STR04L+185MM AND STR06L+150MM IAW COOPESAâS ENGINEERING ORDER N° COO-EO-2024-20628-R00, REV.00 DATED AUG-08-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-021407 REV./ DATED AUG-08-24. THIS REPAIR IS CONSIDERED TEMPORARY AS IT WILL REQUIRE A DETAILED STRUCTURAL ANALYSIS, THE VALIDITY OF THIS REPAIR IS 12 MONTHS AS OF AUG-07-2024. NO ADDITIONAL INSPECTIONS REQUIRED DURING THE 12 MONTHS VALIDITY OF TEMPORARY REPAIR. THIS REPAIR IS DOCUMENTED ON COOPESAâS ITEM A1P145 21-18.
Part: WEB — CORRODED (ZONE 100) · airframe 45,663 hrs · 29,768 cycles
DURING THE STRUCTURE INSPECTION, ALLIANCE AIRLINES FOUND THE RH FLOOR STRUCTURE WITH A PRODUCTION DOUBLER CORRODED (AT FR11 AND Y300 MM). THE CORROSION WAS REMOVED IN ACCORDANCE THE SRM 51-12-01 PARAGRAPH 6. SINCE THE REWORK GOES TO 50 PERCENT (50%) OF THE THICKNESS (NOMINAL THICKNESS 1.0 MM, REMAINING THICKNESS 0.5 MM), THE BLENDED AREA IS OUT OF THE ALLOWABLE DAMAGES A PROPOSAL REPAIR WAS SENT TO EMBRAER FOR EVALUATION AND FINAL APPROVAL. PERFORMED PERMANENT REPAIR AT FORWARD FUSELAGE-RH COCKPIT FLOOR DOUBLER AT FR11, Y+300MM IAW COOPESAâS ENGINEERING ORDER N° COO-EO-2024-20725-R00 DATED AUG-21-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-021898 REV./ DATED AUG-21-21-24. THIS IS A MAJOR REPAIR AND DOES NOT ADVERSELY AFFECT A FATIGUE CRITICAL STRUCTURE AND DOES NOT REPRESENT AN AIRWORTHINESS LIMITATION. NO SPECIFIC OR ADDITIONAL INSPECTIONS ARE NECESSARY. DOCUMENTED ON ANAC FORM F-101-06, DATED AUG-21-24 AND COOPESAâS ITEM A1P145 2-57.
Part: SKIN — DEFORMED (ZONE 100) · airframe 45,663 hrs · 29,768 cycles
DURING PRESENT CHECK ON CENTER FUSELAGE I, IT WAS FOUND A TOOLING MARK ON FUSELAGE SKIN LOCATED AT FR30+205MM, STRG-23LH+190MM, THE MENTIONED DAMAGE WAS EVALUATED AS PER ERJ SRM PART II 53-21-01 AD 51 PARAG 5A TABLE 102 (RIVETED AREA), FIG 104, ZONE GRAY (NO DAMAGE ALLOWABLE), DUE TO THIS FACT WE ARE CONTACTING ERJ FOR TECHNICAL SUPPORT EVALUATION AND APPROVAL. PERFORMED TOOLING MARK-BLEND OUT PERMANENT REPAIR AT CENTER FUSELAGE I, FR30+205MM, STR.23LH+190MM, EXTERNAL SKIN IAW COOPESAâS ENGINEERING ORDER NO° COO-EO-2024-20590-R00 REV.00 DATED AUG-04-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-020937 REV./ DATED AUG-03-24. THIS IS A MINOR REPAIR AND DOES NOT ADVERSELY AFFECT A FATIGUE CRITICAL STRUCTURE AND DOES NOT REPRESENT AN AIRWORTHINESS LIMITATION. NO SPECIFIC OR ADDITIONAL INSPECTIONS ARE NECESSARY. DOCUMENTED ON COOPESAâS ITEM A1P145 21-22.
Part: SKIN — CORRODED (ZONE 100) · airframe 45,663 hrs · 29,768 cycles
DURING THE STRUCTURE INSPECTION IT WAS FOUND THE FUSELAGE SKIN WITH CORROSION AT THE INTERNAL SURFACE. DUE TO THE DAMAGE AREA IS BEYOND ERJ190 SRM PART II, REPAIR PROPOSAL WAS SENT TO EMBRAER FOR TECHNICAL SUPPORT EVALUATION AND APPROVAL. PERFORMED TEMPORARY REPAIR AT CENTER FUSELAGE II, LOWER SKIN FROM FR73 AND JUNCTION, BETWEEN STR.29L AND STR.29R IAW COOPESAâS ENGINEERING ORDER N° COO-EO-2024-20586-R00 REV.00 DATED AUG-05-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-020821 REV./ DATED AUG-02-24. DOCUMENTED ON COOPESA ITEM A1P145 21-62 AND ANAC FORM F-101-06, DATED AUG-02-24. THIS REPAIR IS CONSIDERED TEMPORARY AS IT WILL REQUIRE A DETAILED STRUCTURAL ANALYSIS. THE VALIDITY OF THIS REPAIR IS 12 MONTHS AS OF AUG 2ND, 2024 (ORIGINAL ISSUANCE OF THIS DOCUMENT) OR TILL THE SUBSTANTIATION IS CONCLUDED WHICHEVER OCCURS FIRST. NO ADDITIONAL INSPECTIONS REQUIRED DURING THE 12 MONTHS VALIDITY OF TEMPORARY REPAIR.
Part: SKIN — CORRODED (ZONE 100) · airframe 45,663 hrs · 29,768 cycles
DURING THE STRUCTURE INSPECTION IT WAS FOUND THE FUSELAGE SKIN WITH CORROSION AT THE INTERNAL SURFACE. DUE TO THE DAMAGE AREA IS BEYOND ERJ190 SRM PART II, A REPAIR PROPOSAL WAS SENT TO EMBRAER FOR TECHNICAL SUPPORT EVALUATION AND APPROVAL. PERFORMED PERMANENT BLEND OUT REPAIR AT SKIN PANEL, LOWER CENTER FUSELAGE III, AFT CARGO COMPARTMENT, BETWEEN FR73-200MM AND FR74+90MM UNDER STRINGER 29RH IAW COOPESAâS ENGINEERING ORDER N° COO-EO-2024-20606-R00 DATED AUG-06-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-021088 REV./ DATED AUG-05-24. THIS IS A MINOR REPAIR AND DOES NOT ADVERSELY AFFECT A FATIGUE CRITICAL STRUCTURE AND DOES NOT REPRESENT AN AIRWORTHINESS LIMITATION. NO SPECIFIC OR ADDITIONAL INSPECTIONS ARE NECESSARY. DOCUMENTED ON COOPESAâS ITEM A1P145 1-101.
Part: SILENCER — NO DISCREPANCY · airframe 45,663 hrs · 29,768 cycles
DURING THE CHECK AT AEM, A DENT WAS FOUND IN THE SILENCER RH SKIN P/N 170-50118-003 AT 26INCH FRON AFT EDGE. THE DENT IS OUT OF NEAR TO THE INTERNAL STRUCTURE AT P/N 170-50143-401 BAFFLE #5 LEVEL AND DIMENSIONS ARE: L= 2,059", W= 1,848" AND DEPTH= 0,099". AEM PROPOSED TO PERFORM AN EXTERNAL SKIN REPAIR. PERFORMED PERMANENT REPAIR AT TAIL CONE, SILENCER SKIN SECTION, RH SIDE, BETWEEN X=37917 AND X=38057 IAW COOPESAâS ENGINEERING ORDER N° COO-EO-2024-20638-R00 REV.00 DATED AUG-09-24 AND EMBRAER TECHNICAL DISPOSITION ETD2017-190-075160 REV.A DATED SEP-05-17. THIS IS A MAJOR REPAIR. INSPECTION INSTRUCTIONS: THERE IS NO CHANGE IN THE MAINTENANCE PLAN DUE TO THIS REPAIR INSTALLATION. AFTER THAT, THE INSPECTIONS MUST BE PERFORMED ACCORDING TO THE MRB-APENDIX A (ALI SECTION). DOCUMENTED ON COOPESAâS ITEM A1P145 21-77 AND ANAC FORM F200-06G (05.06) DATED SEP-05-17.
Part: SILENCER — NO DISCREPANCY · airframe 45,663 hrs · 29,768 cycles
DURING INSPECTION CUSTOMER REPORTS ONE (1) UNDOCUMENTED EXISTING REPAIR TO THE TAIL CONE SILENCER OUTER SKIN. THE EXISTING REPAIR HAS BEEN REMOVED AND SKIN CUT OUT MEASURES: 30MM IN LENGTH, 30MM IN WIDTH, MINIMUM EDGE DISTANCE OF EXISTING FASTENER HOLE FROM CUT OUT IS 8MM, MINIMUM EXISTING PITCH DISTANCE IS 12MM, MINIMUM DISTANCE FROM EXISTING FASTENER HOLE TO NEARBY UNDERLYING STRUCTURE FASTENER LINE IS 19MM AND ALL REPAIR HOLES ARE 4.05MM.PROPOSAL REPAIR WAS SENT TO EMBRAER FOR EVALUATION AND FINAL APPROVAL. PERFORMED PERMANENT REPAIR AT TAIL CONE, SILENCER FWD SKIN PANEL, RH UPPER SIDE JUST FWD OF THE BAFLE 1 FRAME IAW COOPESAâS ENGINEERING ORDER N° COO-EO-2024-20735-R00 REV.00, DATED AUG-22-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-021523 REV./, DATED AUG-22-24. COLLINS AEROSPACE INSTRUCTION REF:CV24-10089-REPAIR. THIS REPAIR DOES NOT ADVERSELY AFFECT A FATIGUE CRITICAL STRUCTURE AND DOES NOT REPRESENT AIRWORTHINESS LIMITATIONS. NO SPECIFIC OR ADDITIONAL INSPECTIONS ARE NECESSARY. THIS REPAIR IS CONSIDERED MAJOR AND IS DOCUMENTED ON COOPESAâS ITEM A1P145 21-78 AN ANAC FORM F-101-06, DATED AUG-22-24.
Part: SKIN — DEFORMED (ZONE 100) · airframe 45,663 hrs · 29,768 cycles
DURING PRESENT CHECK ON CENTER FUSELAGE, IT WAS FOUND TOOLING MARK ON FUSELAGE SKIN LOCATED AT FR32+120MM, STRG-25LH, THE MENTIONED DAMAGE WAS EVALUATED AS PER ERJ SRM PART II 53-21-01 AD 51 PARAG 5A TABLE 102 (RIVETED AREA), FIG 104, ZONE GRAY (NO DAMAGE ALLOWABLE), DUE TO THIS FACT WE ARE CONTACTING ERJ FOR TECHNICAL SUPPORT EVALUATION AND APPROVAL. PERFORMED TOOLING MARK- BLEND OUT PERMANENT REPAIR AT CENTER FUSELAGE I, FR32+120MM, STRG-25LH, EXTERNAL SKIN IAW COOPESAâS ENGINEERING ORDER N° COO-EO-2024-20590-R00 REV.00 DATED AUG-06-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-020939 REV./, AUG-03-24. THIS IS A MINOR REPAIR AND DOES NOT ADVERSELY AFFECT A FATIGUE CRITICAL STRUCTURE AND DOES NOT REPRESENT AN AIRWORTHINESS LIMITATION. NO SPECIFIC OR ADDITIONAL INSPECTIONS ARE NECESSARY. DOCUMENTED ON COOPESAâS ITEM A1P145 21-23.
Part: SKIN — DEFORMED (ZONE 100) · airframe 45,663 hrs · 29,768 cycles
OUR CUSTOMER REPORT US, THE FUSELAGE SKIN WITH EXISTING TOOL MARKS AT FR 15, STR-22LH +115MM, EVALUATED AFFECTED AREA, FOUND IT OUT OF LIMITS IAW ERJ190 PART II SRM 53-10-01 AD51, PARAG 4B, TABLE 102, FIG 101. DUE TO THIS FACT WE ARE CONTACTING ERJ FOR TECHNICAL SUPPORT EVALUATION AND APPROVAL. PERFORMED PERMANENT REPAIR AT FORWARD FUSELAGE, EXTERNAL SKIN AT FR14+140MM TO FR15-90MM, BETWEEN STR22LH+30MM AND STR23LH+90MM IAW COOPESAâS ENGINEERING ORDER N° COO-EO-2024-20670-R00 REV.00 DATED AUG-14-24 AND EMBRAER TECHNICAL DISPOSITION ETD2024-190-020586 REV./ DATED AUG-13-24. DOCUMENTED ON COOPESAâS ITEM A1P145 21-44 AND ANAC FORM F-101-06 DATED AUG-13-24, INSPECTION INSTRUCTIONS: EXTERNAL LOW FREQUENCY EDDY CURRENT (SDI) NDT PART 6, TASK 51-06-00-250-805A, THRESHOLD OF 20,000FC OR 26,600FH WHICHEVER OCCURS FIRST, INTERVAL OF 20,000FC OR 26,600FH WHICHEVER OCCURS FIRST. THIS IS AN ADDITIONAL AND SPECIFIC INSPECTION REQUIREMENT. IT REPRESENTS THE REPAIR AIRWORTHINESS LIMITATION; HOWEVER, IT DOES NOT DISMISS ANY OTHER EXISTING MAINTENANCE TASK. THRESHOLD IS COUNTED SINCE THE REPAIR ACCOMPLISHMENT.
Earlier reports · 2006–2023 · 48 reports
2023
Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 45,575 hrs · 29,720 cycles
FLT#24, MCO-DCA. 'EMER LT BATT FAULT; REMOVED & REPLACED AFT RH EMERGENCY LIGHT POWER UNIT. OPS CHECK GOOD REF AMM 33-50-01.'
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 45,196 hrs · 29,443 cycles
DURING HEAVY MAINTENANCE: AFT GALLEY CEILING PANEL 254 CRC EMERGENCY EXIT LIGHT INOP; CHARGED EMERGENCY LIGHT POWER UNIT PER EMB 190 AMM 33-50-01-800-801-A AFT CEILING PANEL 254 EMERGENCY LIGHTS OPS CHECK GOOD PER EMB 190 AMM 33-50-00-710-801-A .
Part: ISIS — FAILED (UNKNOWN) · airframe 44,317 hrs · 28,777 cycles
FLT#1109, BOS-NAS. (AIRCRAFT DIVERTED TO JFK) ' IESS DISPLAYS "OUT OF ORDER"; REMOVED AND REPLACED IES DISPLAY DUE TO INTERMIT "OUT OF ORDER" MSG PER AMM 34-11-01. OPS TEST PER 34-11-00-710-801. NO FURTHER DEFECTS WERE NOTED. A/C OK FOR SERVICE.'
Part: HEAT EXCHANGER — FAILED · airframe 43,565 hrs · 28,258 cycles
FLT#1745, BOS-CLT. (AIRCRAFT PERFORMED AN AIR TURN BACK T BOS) ' CABIN PRESSURIZATION CYCLING UP AND DOWN AS MUCH AS 2500 FPM DURING CRUISE. MANUAL CONTROL OF THE OUTFLOW VALVE IS NO HELP. BLEED PRESSURES CYCLING FROM 10 PSI TO 48 PSI. BOTH BLEED CYCLING PRESSURE BUT MORE SO ON THE RIGHT; REF DEFECT 3582714-1 (REMOVED AND REPLACED ACM IAW AMM 21-51-05 UP TO ITEM, SUBTASK 420-002-A STEP # 9), 3582714-2, 3582713-1 (REMOVED AND REPLACED DUAL HEAT EXCHANGER IAW AMM 21-51-04. OPS CHECK AND LEAK CHECK REQUIRED.), 3582713-2 (OPS CHECK AND LEAK CHECK PER AMM 21-51-00) FOR CORRECTIVE ACTION.'
Part: SHUTOFF VALVE — FAILED (RIGHT) · airframe 43,565 hrs · 28,258 cycles
FLT 1745, AIRCRAFT PERFORMED AN AIR TURN BACK T BOS, CABIN PRESSURIZATION CYCLING UP AND DOWN AS MUCH AS 2500 FPM DURING CRUISE. MANUAL CONTROL OF THE OUTFLOW VALVE, NO HELP. BLEED PRESSURES CYCLING FROM 10 PSI TO 48 PSI. BOTH BLEED CYCLING PRESSURE BUT MORE SO ON RIGHT. REMOVED AND REPLACED ACM IAW AMM 21-51-05 UP TO ITEM, SUBTASK 420-002-A STEP 9, 3582714-2, 3582713-1. REMOVED AND REPLACED DUAL HEAT EXCHANGER IAW AMM 21-51-04. OPS CHECK AND LEAK CHECK REQUIRED, 3582713-2, OPS CHECK AND LEAK CHECK IAW AMM 21-51-00.
2022
Part: NONE — NONE · airframe 41,585 hrs · 26,804 cycles
FLT 360, PHL-BOS. AFTER TAKEOFF FROM RWY 27L PHL.WE RECEIVED EGPWS ALERT TOO LOW TERRAIN.WE WERE CLIMBING THROUGH 700'. FO NOTICED APPR2 NOT AVAIL MESSAGE. A320 AHEAD OF US DID NOT REPORT ANY INTERFERENCE.SUSPECT 5G INTERFERENCE.; COMPLIED WITH INFO NOTICE 2022-T001.NO DEFECT NOTED.OK FOR SERVICE.5G NOT SUSPECTED.MCC JORGE ADVISED.AMM REF 34-31-00-710-801-A
2021
Part: WARNING MESSAGE — FALSE INDICATION (L1 DOOR) · airframe 39,705 hrs · 25,623 cycles
FLT 215, BOS-DFW. RETURNED TO FIELD. IN FLIGHT L1 DOOR OPEN INDICATION ON MFD & EICAS. ALL VISUAL INDICATORS SHOWED GREEN. WARNING MESSAGE DISSAPEARED UPON LANDING; OPERATIONAL CHECK OF DOOR NML PER AMM 52-11-00. MCC CHRIS NOTIFIED.
2020
Part: CONTROL MODULE — FAILED (NLG STEERING) · airframe 39,452 hrs · 25,443 cycles
FLT # 640, CLE-BOS. EMERGENCY DECLARED. AFTER LOWERING THE LANDING GEAR ON APPROACH, WE GOT A STEER FAIL EICAS MESSAGE NO STEERING ON THE GROUND,; R/R STEERING CONTROL MODULE IAW AMM 35-53-01 & ACCOMPLISHED STEERING FEEDBACK SENSOR ADJUSTMENT (ON GROUND) IAW AMM 32-53-09.OK FOR SERVICE.
2019
Part: STRINGER — CORRODED (FRAMES 88-89) · airframe 38,820 hrs · 25,046 cycles
DURING HEAVY MAINTENANCE, CORROSION STRINGER 28R AT LEVEL FR88 TO FR89 LOWER FUSELAGE; PERFORMED PERMANENT REPAIR ON STRINGER 29R AT LEVEL FR88 TO FR89 LOWER FUSELAGE IAW E190 SRM 53-23-03 REPAIR 51P TYPICAL SPLICE REPAIR OF STRINGERS ITEM 5 FIGURE 210.
Part: STRUT — CORRODED (RT MLG) · airframe 38,820 hrs · 25,046 cycles
DURING HEAVY MAINTENANCE, CORROSION SHOCK STRUT FWD PINTLE PIN ON RH MLG (1 EA), CORROSION SHOCK STRUT FWD PINTLE PIN ON LH MLG (1 EA); REF WO# 2019-240/1 AEROMAN WCC 2019-370284 & WCC 2019-370283 FOR WORK PERFORMED. REMOVED AND REPLACED SHOCK STRUT FWD PINTLE PINS ON LH AND RH MLG (1 EA SIDE) AMM 32-11-01.
Part: SKIN — CRACKED (RT WING) · airframe 38,820 hrs · 25,046 cycles
DURING HEAVY MAINTENANCE, CRACK TRAILING EDGE LOCATED ON LOWER SKIN RIB 19 ON RH WING; REF AEROMAN WO# 2019-240/1 WCC# 2019-370001 FOR WORK PERFORMED, PERFORMED REPAIR TO RH WING /LWRSKIN/ REAR SPAR AREA/ BETWEEN RIBS 10 AND 11 CRACK & OVERSIZED HOLES PER AEROMAN EA 57-0364-19 COVER REV O AND PART 1 TO 4, ETD 2019-190-38191 REV B AND EC E19-1023-01 TEMP REPAIR WITH NO REINSPECTS.
Part: SKIN — CORRODED (FRAMES 88-89) · airframe 38,820 hrs · 25,046 cycles
DURING HEAVY MAINTENANCE, CORROSION EXTERNAL SKIN, FRAMES 88 TO 89, STRINGERS 25R TO 27R. PERFORMED A PERMANENT REPAIR ON THE EXTERNAL SKIN IAW SRM 53-23-30 REPAIR 51.
2017
Part: ENGINE — MULTIPLE FAIL (NR 1) · airframe 31,215 hrs · 19,715 cycles
AIRCRAFT DEPARTED AND DURING CLIMBOUT ENCOUNTERED A NR 1 ENGINE ROLLBACK WITH SEVERAL FAULT MESSAGES. RETURN TO FIELD, R & R THENR 1 ENGINE.
2016
Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 30,022 hrs · 18,921 cycles
DURING ROUTINE MAINTENANCE, THE EMERGENCY LIGHT BATTERY FAILED CAPACITY CHECK. R & R EMERGENCY POWER SUPPLY IAW AMM 33-50-01. OPS CHECK PASSED.
2015
Part: DOWNLOCK SENSOR — MALFUNCTIONED (MLG) · airframe 26,842 hrs · 16,726 cycles
AIR RETURNED, AFTER TAKEOFF, GEAR LEVER COULD NOT BE RAISED. COMPLIED WITH QRH AND LANDED AT DEPARTURE. AFTER ENGINE SHUTDOWN EICAS MSG "LG NO DISPATCH" DISPLAYED AND THEN EXTINGUISHED. R & R RT MLG DOWNLOCK 2 PROX SENSOR IAW AMM 32-61-07. PERFORMED LANDING GEAR SYSTEM OPS CHECK OF LANDING GEAR EXTENSION AND RETRACTION IAW AMM 32-33-00-710-801-A500. ALL CHECKS NORMAL AND SATISFACTORY.
Part: BEAM — CORRODED (FRAME 16-19) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION FWD CABIN, FWD PAX DOOR LOWER BEAM FRAMES 16 - 19, STR 18L, CORRODED. R & R BEAM IAW SRM 51-43-03, 51-43-04. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: DOUBLER — CORRODED (FRAMES 19-20) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION FWD CABIN LT AFT DOUBLER FRAMES 19 - 20, LBL 12.5 - 36. R & R DOUBLER IAW SRM 51-41-02. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: BEAM — CORRODED (FRAMES 14-17) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION FWD CABIN, FWD SERVICE DOOR LOWER BEAM FR14-FR17, STR 18R CORRODED. R & R BEAM IAW SRM 51-23-06 THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: SHEAR TIE — CORRODED (FRAME 87) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION SHEAR TIE AT FR 87, STR 27R AND 28R. R & R SHEAR TIE IAW SRM 51-41-02. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: SHEAR TIE — CORRODED (FRAME 17) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION SHEAR CLIP AT FRAME 17 AT STR 25R AND 26R. R & R SHEAR CLIP IAW SRM 51-41-02 THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: FLOOR SUPPORT — CORRODED (FRAME 75) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION CARGO FLOOR SUPPPORT FRAME 75, STR 29R. R & R SUPPORT IAW SRM 51-41-02. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: BEAM — CORRODED (FRAMES 77-80) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION AFT CARGO DOOR LOWER BEAM. R & R BEAM IAW SRM 51-41-01 51-41-02. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: SHEAR TIE — CORRODED (FRAME 86) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION SHEAR TIE AT FRAME 86, STR 29L AND 29R. R & R SHEAR TIE IAW SRM 51-41-01, 51-41-02. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: SEAT TRACK — CORRODED (FRAMES 12-21) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION FWD CABIN. LT SEAT TRACK, FR12 - 21, LBL 9.5 - LBL 12.5. FABRICATED FILLERS AND DOUBLERS AND INSTALLED IAW SRM 53-10-10. REPAIR 51, THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: FLOORBEAM — CORRODED (FRAME 75) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION CARGO FLOOR SUPPORT AT FRAME 75, STR 29L. R & R SUPPORT IAW SRM 51-41-02. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: FLOOR SUPPORT — CORRODED (FRAME 76) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION CARGO FLOOR SUPPORT AT FRAME 76, STR 29R. R & R SUPPORT IAW SRM 51-41-02. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: FINGER DOUBLER — CORRODED (FRAME 77) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION AFT CARGO DOOR FINGER DOUBLER. R & R DOUBLER IAW SRM 51-43-03, 51-43-04. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: SHEAR TIE — CORRODED (FRAME 88) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE, FOUND CORROSION SHEAR TIE AT FR 88 STR 27R AND 28R. R & R SHEAR CLIP IAW SRM 51-41-02. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: SEAT TRACK — CORRODED (FRAMES 12-21) · corrosion level 2 · airframe 26,177 hrs · 16,249 cycles
DURING HEAVY MAINTENANCE FOUND CORROSION FWD CABIN RT SEAT TRACK, FR12 - 21, RBL 9.5-RBL 12.5. FABRICATED FILLERS AND DOUBLERS AND INSTALLED IAW SRM 53-10-10, REPAIR 51. THIS ITEM HAS BEEN CLASSIFIED AS A LEVEL 2 CORROSION.
Part: CONTROLLER — FAILED (BLEED SYS) · airframe 25,952 hrs · 16,106 cycles
DURING FLIGHT BLEED NR 1 EICAS MESSAGE, AFTER QRH WAS RUN THE MSG DID NOT EXTINGUISH. AN EMERGENCY WAS DECLARED. REPLACED AMS CONTROLLER 1 AND 2 AND PERFORMED APPLICABLE CK IAW 21-00-01-000-801A. ENG 1 AND 2 RUN AND NO DEFECT NOTED.
Part: CONTROLLER — FAILED (BLEED AIR) · airframe 25,952 hrs · 16,106 cycles
DURING FLIGHT, BLEED NR 1 EICAS MESSAGE, AFTER QRH WAS RUN THE MSG DID NOT EXTINGUISH. AN EMERGENCY WAS DECLARED. REPLACED AMS CONTROLLER 1 AND 2 AND PERFORMED APPLICABLE CK IAW 21-00-01-000-801A. ENGINE 1 AND 2 RUN AND NO DEFECT NOTED.
2014
Part: POWER SUPPLY — FAILED (EMERGENCY LIGHT) · airframe 22,305 hrs · 13,683 cycles
DURING MAINTENANCE CHECK, FOUND FWD CABIN CEILING EMERGENCY LIGHT AT PANEL 227BLC INOPERATIVE. R & R EMERGENCY LIGHT POWER UNIT NR 2 IAW AMM 33-50-01. OPS CHECKED GOOD, OK FOR SERVICE.
2013
Part: COFFEEMAKER — OVERHEATED (GALLEY) · airframe 20,405 hrs · 12,490 cycles
FLT 1004 JFK-BOS, CREW REPORTED HOT ELECTRICAL SMELL IN FWD GALLEY. FOUND NR 1 COFFEEMAKER OVERHEATING REMOVED AND REPLACED BOTH COFFEEMAKERS IAW MM 25-30-00. NO DEFECTS NOTED AT THIS TIME.
2012
Part: SENSOR — FAILED (LE SLAT) · airframe 16,444 hrs · 10,085 cycles
FLT NR 1718, SLAT FAILED. REPLACED & REPLACED RT SLAT 3/4 HARNESS W612 & SLAT 3/4 SKEW SENSOR IN REF TO AMM 27-83-01. OPS CHECK NORMAL.
2011
Part: FAN — FAILED (NR 1) · airframe 15,415 hrs · 9,437 cycles
FLT 1243 BOS-CLT, DURING FLIGHT FAINT ELECTRICAL SMELL MORE PRONOUNCE AT GATE, UP AROUND F/O SIDE OF FLIGHT DECK AND BETWEEN FLIGHT DECK AND CABIN. REMOVED AND REPLACED NR 1 RECIRCULATING FAN IAW AMM 21-24-01, OPS CHECKS OK.
Part: COUPLER — FAILED (HF COMM) · airframe 14,636 hrs · 8,946 cycles
FLT 1871 BOS-BDA, AIR RETURN TO BOS DUE TO HF WOULD NOT TRANSMIT ASSOCIATED WITH A LOUD TONE IN HEADSET. SCRATCH PAD MESSAGE HF 1 TUNE FAIL. REPLACED HF COUPLER AND PERFORMED APPLICABLE CHECK IAW 23-11-00, TEST OK.
2009
Part: CONTROL MODULE — MALFUNCTIONED (STEERING SYS) · airframe 10,721 hrs · 6,609 cycles
FLT JB571 HPN-PBI STEER FAIL ON LANDING GEAR EXTENSION, EMERGENCY DECLARED. AFTER POWERING UP, INTERROGATED CMC FOR ACTIVE MAINT MESSAGES AND CORRELATED MESSAGES. NO MESSAGES NOTED. REMOVED AND REPLACED STEERING CONTROL MODULE AS PRECAUTIONARY IAW AMM 32-53-01. SYS OPS CHECK NORMAL.
Part: POWER UNIT — FAILED (CABIN) · airframe 9,599 hrs · 5,948 cycles
R2 DOOR LOWER EMERGENCY LIGHT INOP. REMOVED AND REPLACED THE NR 6 EMERGENCY LIGHT POWER UNIT IAW AMM 33-50-01. OPS CHECK NORMAL.
Part: UNKNOWN — FUMES (CABIN) · airframe 8,138 hrs · 5,067 cycles
FLT NR 582, FLL-HPN, CLIMBING THROUGH 2500' FEET F1 REPORTED HEAVY FUMES IN CABIN, QRH PROCEDURES WERE FOLLOWED, IFE/CSS POWER WAS TURNED OFF AS A PRECAUTION. RETURNED TO FLL. PERFORMED FIM TASK 21-20-00-810-801-A. FOUND NO C/B'S TRIPPED. NO FAULTS. ALL CABIN & COCKPIT LIGHTING OPERATIONAL. RAN PACKS ON APU & ENGINES. NO FAULTS OR SMELLS NOTED. C/W WITH ELECTRICAL ODOR SYSTEM INTEGRITY CHECK LTV MM 44-20-10. NO EVIDEBNCE OF SMOKE OR ELECTRICAL BURNING SMELL. OPS CHECK GOOD. ACFT OK FOR SERVICE.
2008
Part: ACM — FAILED (NR 2) · airframe 7,886 hrs · 4,929 cycles
FLT NR 434, MCO-BOS, AIR RETURN TO MCO, FUMES OF UNKNOWN ORIGIN REPORTED IN CABIN AFTER TAKE OFF. COMPLETED QRH FUMES DISSIPATED. COMPLETED SMOKE REMOVAL. QRH AND FUMES RETURNED WHEN PACKS RESELECTED ON RETURN TO PACKS OFF CONFIG AND FUMES DISSIPATED AGAIN. (AIR CONDITIONING PACKS-SINGLE) R&R NR 2 AIR CYCLE MACHINE IAW 21-51-05. OPS CHECK NORMAL, NO ODOR PRESENT.
Part: ACTUATOR — FAILED (T/E FLAP) · airframe 5,142 hrs · 3,434 cycles
FLT 903, JFK-ORD, FLAP FAIL EICAS WHEN SELECTING FLAPS 1. RETURNED TO MCO, REMOVED AND REPLACED RIGHT OUTBOARD FLAP NR 4 ACTUATOR ASSY IAW AMM 27-51-01. OPS CHECK OK IAW AMM 27-51-01.
2007
Part: WIRE HARNESS — FAULTY (WING) · airframe 4,707 hrs · 3,209 cycles
FLT 1604, JFK-PWM, DIVERTED TO BOS DUE A-I WING 2 LEAK EICAS WARNING MSG DISPLAYED DURING CLIMBOUT 11,000 FT OCCURED DURING A-I WING TEST. HARD FAULT WARNING ON EICAS, RT TEMP SENSOR SLAT 4 INBOARD (FAULT CODE 301142021 AM1). REMOVED AND REPLACED SLAT HARNESS W612 AND TEMP SENSOR PER AMM 27-83-07, AMM 30-11-02 AI OPERATION CHECKS NORMALLY. OK FOR SERVICE.
Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 4,300 hrs · 2,949 cycles
LEFT FWD OVERWING EMERGENCY LIGHT INOP. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY PACK NR 4, OPS CHECK OF EMERGENCY LIGHTS GOOD REF AMM 33-50-01-04.
Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 4,295 hrs · 2,945 cycles
COCKPIT EMERGENCY LIGHT DOES NOT ILLUMINATE WITH SWITCH IN THE ON POSITION. REMOVED AND REPLACED NR 1 BATTERY PACK IAW AMM 33-50-00, OPS CHECK OK.
Part: WIRE HARNESS — DEFECTIVE (L/E SLAT) · airframe 3,565 hrs · 2,455 cycles
SLAT FAIL AFTER TAKEOFF. FLT 1094, CMH-JFK RETURNED FOR LANDING AT CMH. REPLACED RIGHT SLAT 2/3 & 3/4 SKEW SENSOR HARNESSES PER AMM 27-83-07-400-801. CLEARED SF-ACE INHIBITS. NO EICAS MSG PRESENT. OPS CHECK OF SLATS IS NORMAL PER AMM 27-710-801. OK FOR RETURN TO SERVICE.
Part: WIRE HARNESS — DEFECTIVE (L/E SLAT) · airframe 3,565 hrs · 2,455 cycles
SLAT FAIL AFTER TAKEOFF. FLT 1094, CMH-JFK RETURNED FOR LANDING AT CMH. REPLACED RIGHT SLAT 2/3 & 3/4 SKEW SENSOR HARNESSES PER AMM 27-83-07-400-801. CLEARED SF-ACE INHIBITS. NO EICAS MSG PRESENT. OPS CHECK OF SLATS IS NORMAL PER AMM 27-80-710-801. OK FOR RETURN TO SERVICE.
Part: BATTERY — OVERTEMP (NR 2) · airframe 2,197 hrs · 1,545 cycles
BATTERY 2 OVERTEMP MESSAGE APPEARED ON TAXI. TROUBLESHOT PER E190 FIM TASK 24-36-00-810-804-A. REMOVED AND REPLACED BATTERY NR 2 PER AMM PART II 24-36-01. OPS CHECKED NORMAL.
2006
Part: ACM — FAILED (NR 2) · airframe 1,481 hrs · 1,025 cycles
PASSING THRU 24,OOO FEET ON DESCENT INTO TPA, FLIGHT ATTENDANT CALLED WITH "SMOKE IN THE CABIN" AT THE SAME TIME, F/O REPORTED SMELLING SMOKE (NOT ELECTRICAL TYPE) CONTINUED DESCENT AND INITIATED QRM FOR SMOKE IN CABIN. PUSHING PACK 1 OUT DID NOT STOP SMOKE. PUSHING OUT BOTH BLEEDS STOPPED SMOKE GENERATION. LANDED IN MCO. REMOVED AND REPLACED THE NR 2 ACM PER MM 21-51-00 AND HEAT EXCHANGER PER MM 21-51-04 AND OPS CHECK AND LEAK CHECK OK AS PER AMM TASK 21-51-00-710-801-A. ACCOMPLISHED TSI N197T00837 VISUAL INSPECTION OF PACK. ALSO TSI N197T00839 PACK OPERATIONAL TEST. NO SMOKE NOTED IN CABIN AFTER THESE PROCEDURES WERE ACCOMPLISHED.