ANA B772 near Tokyo on Dec 13th 2013, engine shut down in flight

Last Update: November 3, 2015 / 15:33:00 GMT/Zulu time

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Photo of ANA All Nippon Airways JA701A, Boeing 777-200 — ANA All Nippon Airways JA701A, Boeing 777-200 (Photo credit: Alec@B92 / Flickr / License: CC by-sa)

Incident Facts

Date of incident
Dec 13, 2013

Classification
Incident

Cause
Engine shut down in flight

Airline
ANA All Nippon Airways

Flight number
NH-243

Departure
Tokyo Haneda, Japan

Destination
Fukuoka, Japan

Aircraft Registration
JA701A

Aircraft Type
Boeing 777-200

ICAO Type Designator
B772

An ANA All Nippon Airways Boeing 777-200, registration JA701A performing flight NH-243 from Tokyo Haneda to Fukuoka (Japan) with 353 passengers and 11 crew, was climbing through FL330 out of Tokyo when the right hand engine's (PW4074) exhaust gas temperature rose significantly beyond operational limits and thrust was lost from the right hand engine. The crew shut the engine down and returned to Tokyo's Haneda Airport for a safe landing.

A replacement Boeing 777-200 registration JA712A reached Fukuoka with a delay of 3:20 hours.

The airline reported a blade in the 5th stage of the high pressure compressor had failed causing damage downstream.

Japan's Transportation Safety Board (JTSB) rated the occurrense a serious incident and opened an investigation.

On Oct 29th 2015 the JTSB released their final report concluding the probable cause of the serious incident was:

It is highly probable that the serious incident occurred because the engine interior was damaged due to the damage of the blades around the entire periphery of the first stage disc of HPC (stage 5) of the No.2 Engine (the right engine) during the flight.

With regard to the damage of the blades around the entire periphery of the first stage disc of HPC, it is somewhat likely that one of the blades was damaged at the dovetail part and fell off from the slot.

The JTSB wrote that the blades of the 6th and last stage low pressure compressor showed nicks and dents at their leading edges, the blades of first stage of the high pressure compressor were severly damaged with all blades either fractured at the airfoil root or missing from their slots, the same applies for the 2nd stage of the high pressure compressor. The damage in the first high pressure compressor stages caused abnormal combustion.

The JTSB analysed that the slots of all but one blades of the 1st stage high pressure compressor showed scratch marks in the direction of rotation. This and other characteristics were not found in that one slot, which thus is believed to have been the origin of the engine failure with all other blade damage being secondary.