AD/CF6/20 - High Pressure Compressor Rotor Stages 11 to 14 Vane to Spool Rubs

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Legislation au F2006B08464 In force Legislative Instrument

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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/CF6/20 High Pressure Compressor Rotor Stages

11 to 14 Vane to Spool Rubs

Applicability: CF6-80A and CF6-80C2.

 

Requirement: Action in accordance with the Technical Requirements of FAA AD 91-15-25 Amendment 39-7090.

 

Note: GE Service Bulletins 72-459 Revision 2 and 72-130 Revision 2 refer.


11/91

 

Compliance: As specified in the Requirement Document with an effective date of 28 November 1991.

 

Background: The FAA AD is prompted by reports of HPCR stages 11-14 spool-shafts found in service with spool rub. This condition, if not corrected could result in uncontained engine failure.

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.