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Printed page label not indexed. PDF page 5.
significantly reduced the life of the oil feed stub pipe on the No. 2 engine so that a fatigue crack developed, ultimately releasing oil during the flight that resulted in an internal oil fire. That fire led to the separationOpen official document at PDF page 5ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 61. PDF page 81.
an arc of about 90° of the oil feed stub pipe and was identified to be a pre-existing fatigue crack. The origin of this crack could not be precisely determined, however, the general shape of the crack indicated its originOpen official document at PDF page 81ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 62. PDF page 82.
stub pipe wall measurements Image modified from a Rolls-Royce plc supplied mode The fatigue crack coincided with the thinnest wall section and it was apparent that the counter bore 62 used during manufacture to enlarge the inner diameter of theOpen official document at PDF page 82ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 70. PDF page 90.
pipe (Figure 50). The location of the peak stress corresponded with the location of the fatigue crack in the oil feed stub pipe in the occurrence engine. Figure 50: Oil feed stub pipe stress distribution Image source: Rolls Royce plc.Open official document at PDF page 90ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 79. PDF page 99.
1: Oil feed stub pipe failure and oil fire As described in Part 2 of this report, a fatigue crack initiated and grew in the HP/IP oil feed stub pipe below the shoulder where it fits into the HP/IP bearingOpen official document at PDF page 99ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 131. PDF page 151.
heated the intermediate pressure (IP) turbine drive arm until the material failed. A fatigue crack had formed in the wall of the oil feed stub pipe over a period of time, and on the occurrence flight the crack reached aOpen official document at PDF page 151ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010