AD/RB211/32 Amdt 2 Stage 5 Compressor Disc Inspection (Cth)
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/RB211/32 Amdt 1 and issues the following AD under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Rolls Royce Turbine Engines - RB211 Series
| AD/RB211/32 Amdt 2 | Stage 5 Compressor Disc - Inspection | 7/2005 |
Applicability: | Model RB211-524 series engines, all marks, which do not incorporate Service Bulletin (SB) RB211-72-E182 and which are installed in Lockheed L-1011, Boeing 747 and 767 aircraft. |
Requirement: | 1. Remove IP Compressor Stage 5 discs from service. 2. Remove from service any disc, which exceeds the cyclic life defined in Table 2. The provisions of Requirement 1 of this Directive cannot be applied post 1 December 2008. Note: UK CAA AD G-2005-0008 EASA Approval No.2005-2139 dated 4 March 2005 refers. This Directive supersedes UK CAA AD 006-04-2002. |
Compliance: | 1. Before the cyclic life limits defined in Table 1 unless either of the following qualifying Magnetic Particle Inspection (MPI) or Eddy Current Inspection (ECI) are satisfied. (a) Discs that have completed the workshop MPI or ECI in accordance with RB211-72-AD428 may remain in service post these workshop inspections for the cyclic lives given in Table 3 or until 1 December 2008 or until the cyclic life limit given in Table 4 is reached, whichever is sooner. Or (b) Discs that have completed satisfactory in-situ ECI in accordance with the appropriate instructions (given below) may remain in service post the in-situ inspection for the cyclic lives given in Table 3 or until I December 2008 or until the cyclic life limit given in Table 4 is reached whichever is sooner. The in-situ ECI can be used only once between workshop inspections. |
| 2. With effect of the 1 December 2008. Table 1: Cyclic life limits without qualifying NDT inspection.
Table 2 Cyclic life limits effective on 1 December 2008.
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| Table 3 Cyclic life alleviation post qualifying NDT inspection.
Table 4 Cyclic life limits
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| This Amendment becomes effective on 7 July 2005. | |||||||||||||||||||||||||||
Background: | Cracking at the cooling air holes in the front spacer arm has been found in IP Compressor stage 5 discs at overhaul. The discs are predominantly high life, from RB211-524C2 and 524D4 engines but are common to all marks of 524 engines. It was concluded from the examination of these discs, that the cracking has the potential to affect disc integrity within the declared safe cyclic lives. This directive supersedes an existing directive to limit its applicability to engines, which do not feature RB211-72-E182. It also adds a reference to the Service Bulletin RB211-72-E171 introducing an on-wing inspection technique for the RB211-524G/H engine types. |
| The original issue of this Directive became effective on 2 October 2003. |
James Coyne
Delegate of the Civil Aviation Safety Authority
27 May 2005
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