N309JB
Registered owner: WILMINGTON TRUST CO TRUSTEE, DE (owner ≠ operator)
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.
41 reports on file, 2010-03-26 – 2026-06-12.
Part: UNKNOWN — FIRE (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
COOPESA REPORTS THAT A FIRE OUTBREAK OCCURRED INSIDE THE FORWARD FUSELAGE, SPECIFICALLY WITHIN THE FORWARD CARGO COMPARTMENT NEAR THE INTERNAL SIDE OF THE EXTERNAL AC POWER RECEPTACLE. THE COOPESA EMERGENCY RESPONSE TEAM ACCESSED THE AFFECTED AREA BY THE FORWARD CARGO COMPARTMENT AND, USING A KIDDE 90 MULTI-PURPOSE ABC DRY CHEMICAL FIRE EXTINGUISHER. AS THE TEAM EXITED THROUGH THE FORWARD CARGO COMPARTMENT ACCESS DOOR, THE EXTINGUISHER CYLINDER WAS STILL DISCHARGING CHEMICAL POWDER. THIS RESULTED IN A CLOUD OF POWDER FORMING OUTSIDE THE AIRCRAFT, MORE CONCENTRATED ON THE RH SIDE. A LIGHT AMOUNT OF DRY CHEMICAL POWDER FROM A FIRE EXTINGUISHER WAS DEPOSITED ON BOTH ENGINE LIPSKIN AND ACOUSTIC PANEL. IMMEDIATELY AFTERWARD, COOPESA PERFORMED A DEEP CLEANING (WASH) OF THE LANDING GEAR AND OTHER POTENTIALLY AFFECTED AREAS. THIS WAS FOLLOWED BY VISUAL INSPECTIONS AND NO EVIDENCE OF DRY CHEMICAL RESIDUE WAS IDENTIFIED. THIS CONDITIONREPORTED WAS REPAIRED IAW ETD2026-190-007733 DTD MAY 26 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24503-R00 DTD MAY 28 2026.
Part: ELECTRICAL BOX — FIRE (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
COOPESA REPORTS THAT A FIRE OUTBREAK OCCURRED INSIDE THE FORWARD FUSELAGE, SPECIFICALLY WITHIN THE FORWARD CARGO COMPARTMENT NEAR THE INTERNAL SIDE OF THE EXTERNAL AC POWER RECEPTACLE. THE COOPESA EMERGENCY RESPONSE TEAM ACCESSED THE AFFECTED AREA THROUGH THE FORWARD CARGO COMPARTMENT AND SUCCESSFULLY SUPPRESSED THE FIRE USING A KIDDE 90 MULTI-PURPOSE ABC DRY CHEMICAL FIRE EXTINGUISHER. AS A RESULT, THE EXTINGUISHING CHEMICAL POWDER SPREAD THROUGHOUT THE INSULATION BLANKETS. COOPESA PERFORMED AN INITIAL CLEANING USING LINT-FREE WIPING CLOTHS AND OBSERVED THAT SOME OF THE INSULATION BLANKETS EXHIBITED SLIGHT DETERIORATION, INCLUDING THE PRESENCE OF SMALL HOLES. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-008078 DTD MAY 14 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24484-R00 DTD MAY 14 2026.
Part: UNKNOWN — FIRE (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
A FIRE OUTBREAK OCCURRED INSIDE THE FORWARD FUSELAGE, SPECIFICALLY WITHIN THE FORWARD CARGO BAY NEAR THE INTERNAL SIDE OF THE EXTERNAL AC POWER RECEPTACLE. EMERGENCY RESPONSE TEAM ACCESSED THE AFFECTED AREA BY THE FWD CARGO BAY USING FIRE EXTINGUISHER. VISUAL INSPECTIONS IAW STANDARD MLG INSPECTION PRACTICES (INCLUDING DISASSEMBLING OF WHEELS AND BRAKES) AND NO EVIDENCE OF DRY CHEMICAL RESIDUE WAS IDENTIFIED IN ANY OF THE LANDING GEARS. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-007569 DTD MAY 15 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24492-R00 DTD MAY 17 2026.
Part: ELECTRICAL BOX — FIRE (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
COOPESA REPORTS THAT A FIRE OUTBREAK OCCURRED INSIDE THE FORWARD FUSELAGE, SPECIFICALLY WITHIN THE FORWARD CARGO COMPARTMENT NEAR THE INTERNAL SIDE OF THE EXTERNAL AC POWER RECEPTACLE. THE COOPESA EMERGENCY RESPONSE TEAM ACCESSED THE AFFECTED AREA THROUGH THE FORWARD CARGO OMPARTMENT AND SUCCESSFULLY SUPPRESSED THE FIRE. IMMEDIATELY FOLLOWING THE EVENT, COOPESA PERFORMED AN INITIAL DEEP CLEANING OF THE SURROUNDING AFFECTED AREAS IN ACCORDANCE WITH APPLICABLE AMM AND SRM PROCEDURES. ADDITIONAL DETAILED CLEANING WAS CARRIED OUT IN ALL AFFECTED AND REPORTED AREAS ONCE THE ISSUE WAS IDENTIFIED. SUBSEQUENTLY, A VISUAL INSPECTION WAS PERFORMED FOLLOWING STANDARD INSPECTION PRACTICES, WITH NO FURTHER EVIDENCE OF DRY CHEMICAL RESIDUE OBSERVED. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-008918 DTD JUN 01 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24549-R00 DTD JUN 01 2026.
Part: ELECTRICAL BOX — FIRE (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
COOPESA REPORTS THAT A FIRE OUTBREAK OCCURRED INSIDE THE FORWARD FUSELAGE, SPECIFICALLY WITHIN THE FORWARD CARGO COMPARTMENT NEAR THE INTERNAL SIDE OF THE EXTERNAL AC POWER RECEPTACLE. FROM THE MOMENT THE SPARK AND FIRE BEGAN TO THE INITIATION OF COOPESAâS EMERGENCY RESPONSE, APPROXIMATELY 30 SECONDS PASSED. THE COOPESA EMERGENCY RESPONSE TEAM ACCESSED THE AFFECTED AREA BY THE FORWARD CARGO COMPARTMENT AND, USING A KIDDE 90 MULTI-PURPOSE ABC DRY CHEMICAL FIRE EXTINGUISHER, BEGAN SUPPRESSING THE FIRE, WHICH WAS IMMEDIATELY FULLY EXTINGUISHED. ONCE THE SITUATION WAS UNDER CONTROL, A THOROUGH CLEANING AND DAMAGE ASSESSMENT WAS PERFORMED REGARDING THE AFFECTED STRUCTURAL COMPONENTS CLEARY AFFECTED BY THE HEAT AND SMOKE OF THE FIRE FLAMES. AS A RESULT OF THE DAMAGE ASSESSMENT, COOPESA HAS PERFORMED A DAMAGE MAPPING THAT INCLUDES REMAINING THICKNESS AND ELECTRICAL CONDUCTIVE TESTS. THIS CONDITIONREPORTED WAS REPAIRED IAW ETD2026-190-007358 DTD MAY 15 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24572-R00 DTD MAY 29 2026.
Part: SKIN — DAMAGED (ZONE 600) · airframe 34,142 hrs · 22,496 cycles
THIS JOB WAS PERFORMED BY CUSTOMER REQUEST TO REDO EXISTING REPAIR LOCATED AT WING MAIN BOX - RH WING MAIN BOX LOWER SKIN AT RIB-JACKING FITTING. DUE TO THE REPAIR WAS FOUND WITH MISSING TRACEABILITY, IT WAS REMOVED AND A PERMANENT REPAIR IS PERFORMED AS PER ETD2019-190-094497 DTD JUL 15 2019 AND DOCUMENTED PER COOPESA EO COO-EO-2026-23861-R00 DTD FEB 10 2026. JOB A1Q349 ITEM 21-28.
Part: SKIN — DAMAGED (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
DURING A STRUCTURAL INSPECTION, LIGHTNING STRIKE DAMAGE (LSD) WAS IDENTIFIED AT FR03 AND Y=25MM, SEE FIGURE 1. SINCE THE DAMAGE DEPTH EXCEEDED 50% OF THE SKIN THICKNESS, IT WAS REMOVED BY DRILLING THROUGH THE SKIN ONLY. AFTER REMOVING THE FRAME PRODUCTION FASTENERS FOR ACCESS, THE LSD WAS REMOVED BY DRILLING A 2.38 MM (3/32 INCH) HOLE. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003422 DTD FEB 25 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24010-R00 DTD FEB 26 2026. JOB A1Q349 ITEM 21-45.
Part: SKIN — CORRODED (ZONE 200) · airframe 34,142 hrs · 22,496 cycles
DURING THE STRUCTURAL INSPECTION, CORROSION SPOTS WERE FOUND ON THE EXTERNAL SKIN SURFACE BETWEEN FR16-17, AND BETWEEN STRINGERS 26R-27R, AROUND THE ANTENNA CUT-OUT AREA. THE CORROSION WAS REMOVED BY BLEND-OUT IN ACCORDANCE WITH SRM PART II 51-10-03 REQUIREMENTS. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-004184 DTD MAR 16 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24127-R00 DTD MAR 17 2026. JOB A1Q349 ITEM 21-55.
Part: SKIN — DAMAGED (ZONE 800) · airframe 34,142 hrs · 22,496 cycles
DURING THE STRUCTURAL INSPECTION, AN EXISTING REPAIR WAS FOUND AT THE FORWARD AREA OF THE LH MLG DOOR SKIN. SINCE THE PREVIOUS OPERATOR DID NOT PROVIDE REPAIR RECORDS, THE REPAIR WAS REMOVED. AFTER REMOVAL, A SKIN CUTOUT WAS IDENTIFIED. THE SRM WAS CONSULTED FOR REPAIR INSTRUCTIONS; HOWEVER, NO GUIDELINES ARE AVAILABLE. THEREFORE, WE PROPOSE INSTALLING AN EXTERNAL DOUBLER AND FILLER USING THE PREVIOUS REPAIR PATTERNTHIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003053 DTD FEB 18 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-23929-R00 DTD FEB 18 2026. JOB A1Q349 ITEM 21-37.
Part: SKIN — DAMAGED (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
CUSTOMER REPORTS A LIGHTNING STRIKE DAMAGE AFFECTING THE FORWARD FUSELAGE SKIN, LOCATED AT FR19 + 292 MM, STRG22R + 17 MM. A REPAIR CANNOT BE PERFORMED IN ACCORDANCE WITH ERJ190 SRM PART II, 531001, AD53 BECAUSE THE DISTANCE BETWEEN THE DAMAGE AND THE ADJACENT FASTENER ROW IS LESS THAN THE 25.4 MM MINIMUM CLEARANCE REQUIRED. THE DAMAGED AREA WAS REMOVED BY DRILLING A Ã3.96 MM HOLE. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003417 DTD FEB 24 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-23984-R00 DTD FEB 26 2026. JOB A1Q349 ITEM 21-37.
Part: SKIN — TEMP REPAIR (ZONE 500) · airframe 34,142 hrs · 22,496 cycles
THIS JOB IS PERFORMED BY CUSTOMER REQUEST, TO REDO AN EXISTING REPAIR LOCATED AT WING MAIN BOX - CRACK FOUND L/H WING LOWER SKIN AFT EDGE BTW RIB 9-10. DUE TO THE REPAIR WAS FOUND WITH MISSING TRACEABILITY, IT WAS REMOVED AND A PERMANENT REPAIR IS PERFORMED AS PER ETD2017-190-076965 REV B AND DOCUMENTED BY COOPESA EO COO-EO-2026-23863-R00 DTD FEB 10 2026. JOB A1Q349 ITEM 21-26
Part: SKIN — DAMAGED (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
AN EXISTING BLEND-OUT WAS IDENTIFIED AT FR78 + 290 MM, BETWEEN STRINGERS 27R-28R. THE BLEND-OUT WAS PERFORMED IN ACCORDANCE WITH SRM PART II 51-10-03, TYPE D. AFTER EVALUATION, IT WAS DETERMINED THAT THE BLEND-OUT EXCEEDS THE LIMITS SPECIFIED IN SRM PART II 53-23-01/AD51. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003049 DTD FEB 18 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-23940-R00. JOB A1Q349 ITEM 21-23.
Part: CROSSBEAM — DAMAGED (ZONE 200) · airframe 34,142 hrs · 22,496 cycles
THIS REPORT IS PERFORMED BY CUSTOMER REQUEST TO PERFORM EXISTING REPAIR LOCATED AT THE CENTER FUSELAGE II - CROSS BEAM AT FR57 WITH TOOL MARK. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2017-190-026630 REV. A DTD APR 06 2017 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-23884-R00. JOB A1Q349 ITEM 21-22.
Part: STRUCTURE — FIRE (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
DURING AIRCRAFT PREPARATION FOR MAINTENANCE, THERE WAS A FIRE OUTBREAK IN THE CARGO COMPARTMENT COMMON TO THE INTERNAL AREA OF THE EXTERNAL POWER RECEPTACLE. THIS CONDITION WAS REPORTED TO EMB. FOR ADDITIONAL DETAILS SEE JOB A1Q349 ITEM 997-6.5
Part: SKIN — DAMAGED (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
DURING THE STRUCTURAL INSPECTION, EXISTING SKIN BLEND-OUTS AND LIGHTNING STRIKES DAMAGE WERE FOUND BETWEEN FR23-24, NEAR STRINGER 27R. THE BLEND-OUTS WERE REWORKED IN ACCORDANCE WITH SRM PART II 51-10-03 REQUIREMENTS. ADDITIONALLY, LIGHTNING STRIKES DAMAGE WERE IDENTIFIED WITHIN THREE OF THE BLENDED AREAS; THESE WERE REMOVED BY DRILLING HOLES THROUGH THE SKIN ONLY. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-004181 DTD MAR 24 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24152-R00. JOB A1Q349 ITEM 21-21.
Part: INLET — DENTED (NR 2 ENGINE) · airframe 34,142 hrs · 22,496 cycles
AZORRA AVIATION HOLDINGS, LLC REPORTS THAT DENTS WERE FOUND ON THE ENGINE #2 AIR INLET MODULE INNER BARREL LOWER SKIN, LOCATED BETWEEN THE 5.0 AND 7.0 OâCLOCK POSITIONS. THE DENTS WERE EVALUATED IN ACCORDANCE WITH SRM 71-61-01 AD53 AND DETERMINED TO BE OUT OF LIMITS DUE TO THE DISTANCE BETWEEN THEM. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003336 DTD MAR 02 2026 REV. B AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24023 R00.JOB A1Q349 ITEM 4-66.
Part: PINION — CORRODED (ZONE 500 SLAT) · airframe 34,142 hrs · 22,496 cycles
DURING THE ACCOMPLISHMENT OF INSPECTION TASK CARD 57-40-006-0547, WE FOUND SLAT PINION #9 (LH AND RH, SLAT PINION #9 P/N: 190-03175-403) PRESENTING PITTING CORROSION. THE CONDITION IS LIMITED TO THE PINION TEETH, WITH NO MATERIAL LOSS OBSERVED. WE SEARCHED FOR TECHNICAL REFERENCES REGARDING CORROSION REMOVAL FOR THIS COMPONENT BUT FOUND NONE. THEREFORE, WE PROPOSE PERFORMING CORROSION REMOVAL IN ACCORDANCE WITH THE GUIDELINES OF REF. AW_SON_EMB_00284_20241. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-004639 DTD MAR 16 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24129-R00. JOB A1Q349 ITEM 5-29 AND 6-21.
Part: SKIN — CANNING (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
DURING A STRUCTURAL INSPECT, AN EXISTING REPAIR DOUBLER BETWEEN FR08 AND FR09, AND BETWEEN STRINGER 20L AND 21L WAS IDENTIFIED. ACCORDING TO PREVIOUS OPERATOR RECORDS, THIS REPAIR WAS INSTALLED IN ACCORDANCE WITH ETD2017-190-105910 GUIDELINES. THE RECORDS DID NOT INCLUDE MATERIAL TRACEABILITY, AND THEREFORE THE REPAIR WAS REMOVED TO ALLOW FOR A NEW REPAIR. AFTER REMOVAL, THE SKIN WAS FOUND WITH OIL CANNING AND SEVERAL FASTENER HOLES IN POOR CONDITION. CONSEQUENTLY, AN ADDITIONAL SKIN AREA WAS TRIMMED OUT. THE NEW REPAIR ACCOMPLISHMENT WAS EVALUATED IN ACCORDANCE WITH SRM PART II 53-10-01 REPAIR 64P GUIDELINES; HOWEVER, THE REPAIR EXTENDS INTO A NON PERMITTED AREA. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003827 DTD MAR 03 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24040-R00.
Part: INLET — DENTED (NR 1 ENGINE) · airframe 34,142 hrs · 22,496 cycles
AZORRA AVIATION HOLDINGS, LLC REPORTS THAT DENTS WERE FOUND ON THE ENGINE #1 AIR INLET MODULE INNER BARREL LOWER SKIN, LOCATED BETWEEN THE 5.0 AND 7.0 OâCLOCK POSITIONS. THE DENTS WERE EVALUATED IN ACCORDANCE WITH SRM 71-61-01 AD53 AND DETERMINED TO BE OUT OF LIMITS DUE TO THE DISTANCE BETWEEN THEM. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003335 DTD FEB 24 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-23990-R00. JOB A1Q349 ITEM 4-8.
Part: SKIN — NOT REPORTED (ZONE 200) · airframe 34,142 hrs · 22,496 cycles
DURING THE REMOVAL OF THE LIVE TV KA BAND CONNECTIVITY SYSTEMS STRUCTURAL PROVISIONS IN ACCORDANCE WITH SB 190-53-0125 (UNDER ETD2026-190-001029 EFFECTIVITY), THE FOLLOWING DISCREPANCIES WERE IDENTIFIED. THE SB 190-53-0125 DOES NOT INCLUDE INSTRUCTIONS TO INSTALL THE COVER WHERE THE WADL ANTENNA WAS REMOVED, AS INDICATED IN SB 190-44-0054, PAGE 112, AT THE POSITION BETWEEN FR 78 AND FR 79. THE SB 190-53-0125 ONLY PROVIDES INSTRUCTIONS TO INSTALL THE WADL ANTENNA COVER P/N 190-15473-001 AT THE POSITION BETWEEN FR 80 AND FR 81. THE SB 190-53-0125 DOES NOT PROVIDE INSTRUCTIONS TO INSTALL A COVER AT THE UPPER SKIN HOLE LOCATED BETWEEN FR61 AND FR62, AND BETWEEN STR-2R AND STR-3R, FROM THE CONNECTOR J6899, WHICH WAS DISCONNECTED IN ACCORDANCE WITH SB 190-44-0054 DWG 190-02024-601 SHEET 3. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-002814 DTD FEB 202026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-23993-R00. JOB A1Q349 ITEM 20-20.
Part: SKIN — DAMAGED (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
DURING A STRUCTURAL INSPECTION, LIGHTNING STRIKE DAMAGE (LSD) WAS IDENTIFIED AT FR03 AND Y=25MM, SEE FIGURE 1. SINCE THE DAMAGE DEPTH EXCEEDED 50% OF THE SKIN THICKNESS, IT WAS REMOVED BY DRILLING THROUGH THE SKIN ONLY. AFTER REMOVING THE FRAME PRODUCTION FASTENERS FOR ACCESS, THE LSD WAS REMOVED BY DRILLING A 2.38 MM (3/32 INCH) HOLE. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003422 REV. A DTD FEB 25 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24010-R00. JOB A1Q349 ITEM 21-45.
Part: PANEL — CORRODED (ZONE 100) · airframe 34,142 hrs · 22,496 cycles
CORROSION WAS DETECTED AT THE NLG WHEEL WELL RH PANEL, SPECIFICALLY IN THE REAR BELLCRANK REGION. THE SRM WAS CONSULTED FOR CORROSION REMOVAL AND EVALUATION, BUT NO APPLICABLE INSTRUCTIONS WERE FOUND. CONSEQUENTLY, THE CORROSION WAS REMOVED BY PERFORMING A SPOT FACE AROUND THE HOLE. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003582 DTD FEB 26 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-24013-R00. JOB A1Q349 ITEM 1-65.
Part: SKIN — DAMAGED (ZONE 800) · airframe 34,142 hrs · 22,496 cycles
DURING THE STRUCTURAL INSPECTION, AN EXISTING REPAIR WAS FOUND AT THE FORWARD AREA OF THE LH MLG DOOR SKIN. SINCE THE PREVIOUS OPERATOR DID NOT PROVIDE REPAIR RECORDS, THE REPAIR WAS REMOVED. AFTER REMOVAL, A SKIN CUTOUT WAS IDENTIFIED. THE SRM WAS CONSULTED FOR REPAIR INSTRUCTIONS; HOWEVER, NO GUIDELINES ARE AVAILABLE. THIS CONDITION REPORTED WAS REPAIRED IAW ETD2026-190-003053 DTD FEB 18 2026 AND DOCUMENTED UNDER COOPESA EO COO-EO-2026-23929-R00. JOB A1Q349 ITEM 21-38.
Earlier reports · 2010–2022 · 18 reports
2022
Part: NONE — NONE · airframe 32,539 hrs · 21,301 cycles
DURING HEAVY MAINTENANCE, CORROSION EXTERNAL SKIN FR88 TO FR89 BTW STRG 25R TO STRG 27R ON LOWER FUSELAGE; (RESOLVED ON W/O: 1151547 TASKCARD: NR-00008 ) REF AEROMAN NR 2022-124793 WO 2022 83/1 PERFORMED REPAIR LOC EXTERNAL SKIN FR88 TO FR89 BTW STRG 25R TO STRG 27R ON LOWER FUSELAGE IAW E190 SRM 53-23-60 REPAIR 51 ITEM 5.A TO N. TOOL USED TOOL USED: CALIPER P/N: 700-113-10, S/N: 0033168, DUE DATE: NOV-05-2022; PRECISION RADIUS GAUGE P/N: S167C, S/N: AE-28533, DUE DATE: JUL-14-2022, EDDY CURRENT TOOL, P/N: NORTEC 500D, S/N: N500X12101V022233, DUE DATE: JUN-02-2022. RECHECK REQUIRED AT INTERVAL 4,009 FC IAW E190 SRM 53-23-60 REPAIR 51 ITEM 6 TABLE 202.ACCOMPLISHED BY AEROMAN TECH 8616115 REF FUR-E190-53-00317
Part: SLIDE — DEPLOYED (L2-SLIDE) · airframe 32,539 hrs · 21,301 cycles
DURING HEAVY MAINTENANCE, DEPLOYED SLIDE NOT CONTROLLED ON DOOR 812 AFT GALLEY AREA; REF AEROMAN NR 2022- 124776 WO 2022 83/1 R & R SLIDE AT DOOR 812 AFT GALLY ARE IAW E190- AMM - 25-65-01-000-801-A
2021
Part: SLIDE — DEPLOYED (L2-SLIDE) · airframe 31,939 hrs · 20,898 cycles
FLT 1433, MCO-SJU. L2 DOOR WAS OPENED TO ASSIST COOL AIRCRAFT. UPON CLOSING L2 DOOR FA2 NOTED THE DOOR WOULD NOT CLOSE DUE TO SLIDE OBSTRUCTION DOOR. ( SUPPLEMENTAL INFORMATION TO FOLLOW)
2017
Part: STEERING SYS — MALFUNCTIONED · airframe 24,354 hrs · 15,625 cycles
FT # 234, JFK-BTV. C: UPON CLEARING THE RUNWAY STEER FAIL MESSAGE CAME ON RAN RESET STEER FAIL.MESSAGE STAYED ON. GROUND CREW TOWED WAS FROM AN ACTIVE TAXIWAY TO THE GATE; COMPILED WITH FTM 32-00-00-810-01A. FAULT CLEARED AFTER MAV RESET. FOUND TO BE TRANSITIONARY CONDITION. MCC CONFIRMED NO PRIOR 30DAY HISTORY. AIRCRFT OK FOR SVC.
Part: WARNING LIGHT — FALSE ACTIVATION (BRAKES) · airframe 22,671 hrs · 14,411 cycles
ON SHORT FINAL LT & RT BRAKE FAULT, DID A GO AROUND, ON SECOND APPROACH WHEN THE MMLG DOWN THE MESSAGE WENT AWAY. EMERGENCY DELCARED LANDED SAFELY WITH NORMAL BRAKING. PERFORMED BCM1 & BCM2 PRESSURE PULSE INIT TEST IAW FIM 32-41-00-810-825A. ALL TEST PASSED NOT AS TRANSITORY CONDITION. OK FOR SERVICE.
2016
Part: UNKNOWN — ODOR (CABIN) · airframe 21,804 hrs · 13,797 cycles
FLT 1913 MCO-CUN, AIR RETURN BACK TO MCO. UPON TAKEOFF, WHILE CLIMBING THROUGH 800 FEET A STRONG ELECTRICAL SMELL BEGAN COMING OUT OF CA VENT. STRONG FUMES; PERFORMED INSPECTION IAW FIM 21-20-00. NO FAULT FOUND. INSPECTED BORESCOPE PLUGS ON NR 1 ENGINE REF TASK CARD AMM 72-00-00-200-803B. FOUND NO EXCESS ANTI-SEIZE. PERFORMED ENGINE PNEUMATIC BLEED SYSTEM OPS TEST PER AMM 36-11-00 FOR BOTH ENGINES. NO ABNORMAL SMELLS OR DEFECTS NOTED.
Part: DISPLAY — FAILED · airframe 19,951 hrs · 12,460 cycles
ENROUTE GOT EICAS MESSAGE, RECIRCULATING SMOKE. SHORTLY AFTER, SMELLED AN ELECTRICAL ODOR. AFTER TURNING OFF RECIRCULATING FANS IAW QRH, ODOR AND CAUTION DISSIPATED, DIVERTED. ACCOMPLISHED FIM TASK 21-20-00, FOUND NR 4 DISPLAY UNIT BAD. R & R NR 4 DISPLAY UNIT IAW AMM 31-61-00. OPS CHECKS GOOD.
2014
Part: TORQUE TUBE — FAILED (SLATS) · airframe 15,881 hrs · 9,762 cycles
CREW DECLARED AN EMERGENCY DUE TO "SLAT FAIL" MESSAGE ON APPROACH. QRH PROCEDURE FOLLOWED, LANDED FLAP POSITION 2 SLAT 0. R & R SLAT TORQUE TUBE IAW AMM 27-81-03. PERFORMED SLAT RIGGING IAW AMM 27-80-00. OPS CHECK IAW AMM 27-80-00 FOUND NORMAL.
Part: FLOORBEAM — CORRODED (FRAME 14) · airframe 15,800 hrs · 9,715 cycles
DURING HEAVY MAINTENANCE CHECK, IT WAS NOTED FRAME 14 FLOORBEAM ON THE RBL 12 TO 35 FOUND EVIDENCE OF CORROSION. REMOVED CORROSION IAW SRM 51-10-03. REPAIRED IAW E14-669-01.
Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 14,790 hrs · 9,062 cycles
EMERGENCY EXIT LIGHT BELOW LT OVERWING EXIT INOPERATIVE. R & R NR 4 EMERGENCY BATTERY PACK IAW AMM 33-30-01. OPS CHECK OF EMERGENCY EXIT LIGHTS GOOD.
Part: ANTI-ICE SYSTEM — FAILED · airframe 14,078 hrs · 8,607 cycles
AFTER TAKEOFF, ANTI ICE 1 FAILED & ANTI ICE I ENG 2 FAILED, ACCOMPANIED BY A STRONG ODOR, QRH ACCOMPLISHED. ODOR DISSIPATED. F/A 1 SAID FAINT ODOR RETURNED. AT 500 FT ON APPROACH, BLEED 2 FAIL CAUTION AND DURING LANDING ICE DETECTOR 1 FAILED CAUTION ON EICAS.
2013
Part: POSITION SENSOR — FAILED (CONTROL COLUMN) · airframe 12,108 hrs · 7,356 cycles
AIR RETURN DUE TO ELEVATOR HAS ABNORMAL FEELING/FRICTION WHILE IN FLIGHT (NO CAS MESSAGE PRESENT). TROUBLESHOT TO CONTROL COLUMN POSITION SENSOR. R & R CONTROL COLUMN POSITION SENSOR IAW AMM 27-33-01. OPS CHECK GOOD. ACFT OK TO CONTINUE.
Part: PRESSURE SWITCH — FAILED (RIGHT) · airframe 11,872 hrs · 7,205 cycles
CREW DECLARED AN EMERGENCY AND AIR RETURN TO DEPARTURE. AFTER TAKEOFF CREW RECEIVED A FUEL FEED 2 FAULT AND THEN A ENG 2 FUEL LOW PRESSURE CAS MESSAGE. QRH FOLLOWED. MESSAGES NOT CLEARED AND EJECTOR PUMP SHOWED OFF. AC PUMP 2 SHOWED GREEN BUT FUEL LINES WERE WHITE. IAW FAULT CODE 28201252 FOLLOWED FIM TASK 28-21-00-810-815-A. OPS CHECKED RT ENG EJECTOR PUMP IAW AMM 28-21-13-710-801-A, CHECKED GOOD WITH NO FAULTS. REPLACED RT ENGINE LOW PRESSURE SWITCH IAW MM 71-00-73-003 AND RAN ENG 2 IAW 71-00-910-801-A FOR APPROX 22 MIN AT VARIOUS POWER SETTINGS WITH NO FAULTS AND NO LEAKS NOTED.
Part: CONNECTOR — LOOSE (CABIN) · airframe 10,909 hrs · 6,604 cycles
FLT 6433 JFK-BNA, ON HEAVY MAINTENANCE CHECK FOUND AFT SERVICE DOOR UPPER EMERGENCY LIGHT INOP. TROUBLESHOT AND FOUND CONNECTOR GL8-L1 LOOSE ON AFT RIGHT SERVICE DOOR EMERGENCY EXIT. RE-SECURED TO LIGHT ASSEMBLY AND OPS CHECK GOOD IAW EMB E190 AMM 33-50-11 AND 33-50-00.
2012
Part: VALVE — FAILED (BLEED AIR SYS) · airframe 7,858 hrs · 4,725 cycles
FLT 450 SJU-SXM, AIR TURNBACK DUE TO JUST AFTER TAKEOFF, BLEED 2 STARTED FLUCTUATING FROM 2 TO 118 PSI WITH NR 1 ENGINE BLEED ON MEL. CREW PERFORMED QRH BLEED FAIL RESET, BLEED 2 CONTINUED TO FLUCTUATE. AFTER RESET FOR 3-5 MINUTES THEN STABILIZED AT 45 PSI DURING THE REMAINDER OF THE FLIGHT. FLUCTUATED AGAIN AT LEAST TWICE. REMOVED AND REPLACED FAN AIR VALVE PER AMM 36-11-09-04. OPS CHECK GOOD.
2011
Part: POWER UNIT — FAILED (CABIN) · airframe 5,628 hrs · 3,289 cycles
FLT 6403 JFK-BNA ON GROUND FOR MAINTENANCE, FOUND UPPER EMERGENCY LIGHT ON PANEL 198NR INOP.REF EAMS NON-ROUTINE 1501 REMOVED AND REPLACED EMERGENCY LIGHT POWER UNIT 4 IAW EMB 190 AMM 33-50-01, SYSTEM OPS CHECK OK.
Part: DOOR — OPEN (L1) · airframe 5,325 hrs · 3,104 cycles
FLT 1249 BOS-IAD, ON GROUND - THE FLIGHT CREW REPORTED L1 DOOR WOULD NOT DISARM. MX ENTERED A/C FROM R1 DOOR AND FOUND L1 DOOR PARTIAL OPEN WITH GIRT BAR ATTACHED TO FLOOR. RE-INSTALLED GIRT BAR TO DOOR. VISUAL INSP OF DOOR MECHANISM AND SLIDE NO DEFECTS NOTED. SLIDE LACING INTACT. PERFORMED OPS CHECK OF DOOR OPENING AND ARM SYSTEM AS PER AMM 25-65-01, FOUND OK.
2010
Part: WIRE HARNESS — FAILED (LE SLAT) · airframe 2,344 hrs · 1,381 cycles
FLT JB432 MCO-BOS INBOUND TO BOS CREW DECLARED AN EMERGENCY LANDING AFTER SELECTING FLAPS 2 RECEIVED "SLAT FAIL" AT POSITION 3, QRH PROCEDURES FOLLOWED. FLAPS OPERATED NORMALLY WHILE SLATS REMAINED AT POS 3 AIRCRAFT LANDED WITHOUT INCIDENT. BOS MX TROUBLESHOOTING FOUND THAT THE RIGHT WING LEADING EDGE SLAT HARNESS POSITION 3/4 FAILED. REMOVED AND REPLACED HARNESS PER AMM 27-83-00 CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE.