| 摘要 |
With an aircraft engine in a horizontal position, its low pressure shaft (5, fig. 1) is fixed axially so it cannot rotate by means of a tool 8, comprising a central disc (8b, figs. 4a,4b) secured to an end disc of the shaft, and a cross piece (8a) connecting the disc to segments (8c) at its ends which are secured to the engine outlet guide vane housing. The front end bearing housing (or low pressure compressor component) 7a is then fastened to a lifting tool 10, after which it is removed from or pressed onto the shaft (5) by means of an hydraulic power tool 12.
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