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Printed page xii. PDF page 14.
between the lower centre fuselage and body fairing. That loom included wires that provided redundancy (back -up) for some of the systems already affected by the severing of wires in the wing leading edge. This additional damage rendered some ofOpen official document at PDF page 14ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 11. PDF page 31.
result of: - the loss of function to the aircraft's green hydraulic system - reduced redundancy within the aircraft's other (yellow) hydraulic system. Electrical power, resulting from: - a loss of electrical power generation at engines No. 1 andOpen official document at PDF page 31ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 31. PDF page 51.
uncontained engine failure, the simulation identified that the aircraft had sufficient redundancy to continue safe operation. 1.13.2 Engineering analysis of the occurrence An engineering analysis by the airframe manufacturer applied the conditions from the event flight usOpen official document at PDF page 51ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 224. PDF page 244.
inboard aileron. Each aileron had two independent actuators per control surface for redundancy (see the previous discussion at section B.3.3.3 titled Primary flight controls actuation systems). The loss of the Green hydraulic system and impact damage to the aircraft'sOpen official document at PDF page 244ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010