AD/CF6/26 - Stage 11 to 13 Compressor Spool Inspection
1AD/CF6/26 - Stage 11 to 13 Compressor Spool Inspection
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Image unavailable in extracted text 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.