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