Statuts:	Enquête Officielle
Date:	13 JUN 1996
Heure:	12:08
Type/Sous-type:	McDonnell Douglas DC-10-30
Compagnie:	Garuda Indonesia Airways
Immatriculation:	PK-GIE
Numéro de série:	46685/284
Année de Fabrication:	1979
Heures de vol:	46325
Moteurs:	3 General Electric CF6-50C
Equipage:	victimes: 0 / à bord: 15
Passagers:	victimes: 3 / à bord: 260
Total:	victimes: 3 / à bord: 275
Dégats de l'appareil:	Perte Totale
Conséquences:	Written off (damaged beyond repair)
Lieu de l'accident:	Fukuoka Airport (FUK) (Japon)
Phase de vol:	Au décollage (TOF)
Nature:	Transport de Passagers Intern.
Aéroport de départ:	Fukuoka Airport (FUK/RJFF), Japon
Aéroport de destination:	Denpasar-Ngurah Rai Bali International Airport (DPS/WADD), Indonésie
Numéro de vol:	865

Détails:
Flight GA865 was a regular flight from Fukuoka Airport (FUK) to Jakarta with an en-route stop in Denpasar (DPS), Bali. At 11:55 the DC-10 was pushed back from gate 5. The crew reported "Ready for taxi." In reply, Fukuoka Ground instructed the aircraft: "Taxi via E2, contact Tower." The crew taxied to runway 16 and were instructed by the Tower controller to hold short. After waiting for another plane to land, Flight 865 was cleared to taxi into position and hold. At 12:06:53 takeoff clearance was given. The DC-10 accelerated for takeoff. The nose was raised and at a speed of 158 kts the first officer called "Rotate". It was 12:07:40. Three seconds later, at a radio altitude of 9 feet, a fan blade of the 1st stage HP turbine from the no. 3 engine separated. The N1 dropped to 23,7% within a few seconds. At 12:07:45 the flight engineer called ""Engine failure number one." Takeoff was aborted at about the V2 speed and the airplane contacted the runway one second later at a vertical acceleration force of 2.1 Gs.
The thrust reversers were deployed and ground spoilers were extended. The DC-10 skidded off the runway through a ditch, fence and a road, before coming to a halt 620 m past the runway threshold.
Investigation revealed that the turbine blade that failed, had operated for 30913 and 6182 cycles. General Electric had advised customers to discard blades after about 6000 cycles.

The causes of the accident were as follows: "Although the CAS was well in excess of V1 and the aircraft had already lifted off from the runway, the takeoff was aborted. Consequently the aircraft departed the end of the runway, came to rest and caught fire. It is estimated that contributing to the rejection of the takeoff under this circumstance was the fact that the CAP's judgement in the event of the engine failure was inadequate."

Sources:
» ICAO Adrep Summary 4/96 (#35)