ASN Wikibase Occurrence # 247551
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| Date: | Thursday 1 December 2005 |
| Time: | |
| Type: |  Boeing 767-3Q8ER |
| Owner/operator: | Skymark Airlines |
| Registration: | JA767B |
| MSN: | 27617/722 |
| Year of manufacture: | 1998 |
| Fatalities: | Fatalities: 0 / Occupants: 90 |
| Aircraft damage: | Minor |
| Category: | Serious incident |
| Location: | Kagoshima Airport -
 Japan
|
| Phase: | Take off |
| Nature: | Passenger - Scheduled |
| Departure airport: | Kagoshima Airport (KOJ/RJFK) |
| Tokyo International Airport | |
| Investigating agency: | JTSB |
| Confidence Rating: |  Information verified through data from accident investigation authorities |
The Boeing 767-300 JA767B, operated as Skymark Airlines scheduled Flight 306, took off from Kagoshima Airport at 16:45 (Japan Standard Time, UTC+9h) on December 1, 2005. Immediately after takeoff, vibration started on the right engine , and at about 16:48 the fire warning on the right engine was activated. The flight crew shut down the right engine and returned to the Kagoshima Airport at 17: 04 for a successful single engine landing.
Of the total of 90 persons on board, consisting of a pilot in command (PIC), a co-pilot, nine flight attendants, and 79 passengers, no one was injured. The aircraft suffered minor damage. After takeoff, the grass area alongside the runway caught fire.
PROBABLE CAUSE
It is estimated that this serious incident was caused as follows: When the Aircraft became airborne, one of the 2nd stage high-pressure turbine blades of the right engine was fractured which had had considerable fatigue crack, leading other blades to be fractured which caused vibration to the right engine from unbalanced rotation, and the vibration further caused fracture of the fuel supply tube #6 inside the shroud can, moreover, the retaining ring at the end of the shroud can was dislodged by the pressure of fuel injected in the shroud can as well as by the engine vibration causing the fuel to leak, then the fuel was ignited when it contacted the hot section, and resulted in a flame in the engine designated fire zone.
Although the exact cause of the fatigue crack found in the turbine blade could not be determined precisely, it is considered possible that the following factors were combined and contributed:
-because the TA (turnaround) radius of the cooling air passage inside the blades was smaller, the stress was prone to concentrate on that area and thereby it became prone to cause cracks, and later, the cracks progressed due to low-cycle fatigue,
-because sulfur was detected from the rupture surface, the blade was in the condition that crack came by hot corrosion.
-thinner LE passage wall of the shank created the high stresses on the entire blades.
The most probable cause for the fracture of the fuel supply tube was the excessive loads placed on the tube due to vibrations from the engine imbalance.
As for the fire warning which did not activate immediately until a significant area of the core cowl had been melted, it is estimated that it was because the flame was directed to the area where no fire detector element was routed.
Accident investigation:
 |
|
Sources:
JTSB
Images:
Photo: JTSB
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 06-Feb-2021 16:49 | harro | Added |
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