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Printed page 1. PDF page 13.
(including 1 infant) on board. As the aircraft was climbing through 28,300 feet the outer panel of one blade in the fan of the No 1 (left) engine detached. This gave rise to a series of compressor stalls in theOpen official document at PDF page 13Aircraft Accident Report 4/90
Printed page 40. PDF page 52.
Two larger pieces were identified, by thickness mapping, as having come from a blade outer panel. At this time, the complete outer panels of four blades (Nos 9, 17,31 and 34) had not been identified and there were only sufficientOpen official document at PDF page 52Aircraft Accident Report 4/90
Printed page 83. PDF page 95.
Examination of the No 2 engine fan after shut down (Appendix 1, fig 4a) revealed that the outer panel of one fan blade had detached outboard of the mid-span shroud and become lodged in the space between the fan andOpen official document at PDF page 95Aircraft Accident Report 4/90
Printed page 112. PDF page 124.
levels were consistent with those produced by an engine with a fan which had one blade outer panel missing when compared with the data derived from engine testing (see paragraph 1.16.1) and that later available from the FDR record fromOpen official document at PDF page 124Aircraft Accident Report 4/90
Printed page 144. PDF page 156.
engine suffered fatigue of one of its fan blades which caused detachment of the blade outer panel. This led to a series of compressor stalls, over a period of 22 seconds, until the engine autothrottle was disengaged. The severe mechanicalOpen official document at PDF page 156Aircraft Accident Report 4/90