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British Airways B777, Uncontained engine failure and subsequent fire.- Final Report

British Airways B777, Uncontained engine failure and subsequent fire.- Final Report

από Kiriakos Tsakiridis -
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JUNE 21, 2018

Incident: Uncontained engine failure in the No. 1 engine and subsequent fire.

A British Airways Boeing 777-236ER, powered by General Electric GE90-85BG11 turbofan engines, on a takeoff ground roll at McCarran International Airport, Las Vegas, Nevada on September 8, 2015. During the takeoff roll, the cockpit voice recorder (CVR) recorded a “bang” sound at 1612:51.5,. Immediately afterward, the airplane veered to the left. and the CVR recorded the engine indicating and crew alerting system (EICAS) aural annunciation “engine fail.”. The captain moved the thrust reverser levers to their idle positions and began the rejected takeoff maneuver.

The airplane’s airspeed at the time of the rejected takeoff maneuver was about 77 knots. The start of the rejected takeoff maneuver occurred 2 seconds after the “bang” sound, and the airplane came to a stop 13 seconds after the rejected takeoff maneuver began.

The RFO observed black smoke, an orange glow, and a cabin window glass becoming “crazed.” He told a cabin crewmember to get ready to evacuate and returned to the flight deck and requested for evacuation.

All 157 passengers and 13 crewmembers evacuated the airplane through various exits and slides. Evacuation was completed about 2 minutes 32 seconds after the captain’s initial command to evacuate (1614:23).

The airplane was substantially damaged from the fire.

Probable Cause

The failure of the left engine high-pressure compressor (HPC) stage 8-10 spool, which caused the main fuel supply line to become detached from the engine main fuel pump and release fuel, resulting in a fire on the left side of the airplane. The HPC stage 8-10 spool failed due to a sustained-peak low-cycle fatigue crack that initiated in the web of the stage 8 disk; the cause of the crack initiation could not be identified by physical inspection and stress and lifing analysis.


Factors contributing to this accident was the lack of inspection procedures for the stage 8 disk web.

Engine Information

At the time of the accident, the left GE90-85BG11 turbofan engine. had accumulated 66,801 total hours and 9,992 total cycles.
The left engine had a manufacture date of June 28, 1999, and was installed on the accident airplane on January 10, 2015. At the time of the accident, the engine had accumulated 3,645 hours and 503 cycles since its last shop visit, which occurred during June and July 2014 at GE Aviation’s facility in Wales, United Kingdom.

NTSB final report