Document ID: chunk:federal_register_of_legislation:F2006B08469:body:0
Version: federal_register_of_legislation:F2006B08469
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 General Electric Turbine Engines - CF6 Series

AD/CF6/26 Stage 11 to 13 Compressor Spool Inspection 12/93

 Applicability: CF6-45/-50 series.

 Requirement: Action in accordance with the technical requirements of FAA AD 93-13-10.

            Note: GE Service Bulletin No 72-1006 Revision 1 dated 14 November 1991 refers.
 Compliance: As specified in the FAA AD with effectivity commencing 11 November 1993. Background:               There have been reports of fatigue cracking in the 12th stage compressor disc.
            Consequently, there is need for a one time inspection for cracking and measurement
            of the stage 12 compressor disc web-to-rim transition area of the stage 11-13 compressor spool. Depending on the results, the items are then to be replaced, reidentified and relifed.