Commonwealth legislation

AD/CF6/26 - Stage 11 to 13 Compressor Spool Inspection

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This Airworthiness Directive requires a one‑time inspection of the stage 11–13 compressor spool on General Electric CF6‑45 and CF6‑50 engines to detect fatigue cracking and measure the stage‑12 disc web‑to‑rim transition. It directs compliance with FAA AD 93‑13‑10 and references GE Service Bulletin 72‑1006 Rev 1.

Operators and maintenance organisations must perform the inspection, bear downtime and replacement costs, and reidentify or relife parts if defects are found; compliance commenced 11 November 1993.

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AD/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

View image in the official source 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.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.