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Printed page 5. PDF page 25.
application (LPA) 7 (section 1.14). The inoperative wing leading edge lift devices, reduced braking function, reduced number of operational spoilers and inactive left engine thrust reverser8 resulted in an abnormal landing configuration, which in turn affected the landOpen official document at PDF page 25ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010
Printed page 12. PDF page 32.
aircraft's auxiliary power unit (APU) generators on the ground. Flight controls, through: - reduced aileron and spoiler function - the loss of wing leading edge slats and droop nose function.10 Engine control, as a result of: - lossOpen official document at PDF page 32ATSB 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.
within the confines of the runway, the risks associated with maximum effort braking were reduced. 21 Based upon the Cooper-Harper rating scale. The Cooper-Harper rating scale is a standardised aircraft handling quality rating scale that was developed by the 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 226. PDF page 246.
wing landing gear. 120 During the landing, the initially heavy braking by the crew was reduced as the landing roll progressed. Asymmetric braking during the landing resulted from the unavailability of the left wing landing gear brakes and caused theOpen official document at PDF page 246ATSB AO-2010-089: In-flight uncontained engine failure, Airbus A380-842 VH-OQA, overhead Batam Island, 4 November 2010