Atlas Air on fire

[///AMG]

Close enough. Even has a hat, sorta.

Night Captain

 

[thepotato232]

...Enemy of the Day Captain?

 

[Boris Badenov]

Night Captain

Well, yeah. I mean *obviously* the Captain was asleep, that's when this sort of thing happens! Sleep tight, @derg @Stone Cold, et al.

 

[///AMG]

Well, yeah. I mean *obviously* the Captain was asleep, that's when this sort of thing happens! Sleep tight, @derg @Stone Cold, et al.

Sleep well sweet princes

 

[Minuteman]

“A post-incident inspection of the General Electric (GE) GEnx-2B67 engine revealed burnthrough of the thrust reverser fan duct fixed inner wall (see figure 1). The engine cases wereintact and there was no evidence of an uncontained engine failure. The combustor diffusernozzle (CDN) case port M borescope plug was not secured in the case and was found loose inthe engine cowling. The burn through observed on the thrust reverser wall was directly abovethe open CDN port M. The engine low pressure spool (N1) and high pressure spool (N2)manually rotated smoothly. A borescope inspection through CDN port M was performed andno combustor damage was visible. A preliminary review of quick access recorder (QAR), flightdata recorder (FDR), and continuous engine operating data (CEOD) showed no evidence ofengine failure or surge/stall.

A review of the aircraft’s maintenance records revealed that on January 14, 2024, the aircraft underwent an “ENG 2 COMBUSTION SECTION- BORESCOPE NOZZLE- INSPECT” performed by a third-party vendor that required the removal of the port M borescope plug (see figure 2 for location of port M). The maintenance work card provided instructions on how to properly reinstall the borescope plugs to ensure the locking feature was properly engaged. The work card was initialed by the technician performing the work and an inspector, indicating this task had been completed in accordance with the maintenance manual procedure.”

NubTuhSuB Prelim Report

 

[mightynimbus]

View attachment 76639

“A post-incident inspection of the General Electric (GE) GEnx-2B67 engine revealed burnthrough of the thrust reverser fan duct fixed inner wall (see figure 1). The engine cases wereintact and there was no evidence of an uncontained engine failure. The combustor diffusernozzle (CDN) case port M borescope plug was not secured in the case and was found loose inthe engine cowling. The burn through observed on the thrust reverser wall was directly abovethe open CDN port M. The engine low pressure spool (N1) and high pressure spool (N2)manually rotated smoothly. A borescope inspection through CDN port M was performed andno combustor damage was visible. A preliminary review of quick access recorder (QAR), flightdata recorder (FDR), and continuous engine operating data (CEOD) showed no evidence ofengine failure or surge/stall.

A review of the aircraft’s maintenance records revealed that on January 14, 2024, the aircraft underwent an “ENG 2 COMBUSTION SECTION- BORESCOPE NOZZLE- INSPECT” performed by a third-party vendor that required the removal of the port M borescope plug (see figure 2 for location of port M). The maintenance work card provided instructions on how to properly reinstall the borescope plugs to ensure the locking feature was properly engaged. The work card was initialed by the technician performing the work and an inspector, indicating this task had been completed in accordance with the maintenance manual procedure.”

NubTuhSuB Prelim Report

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