Document ID: chunk:federal_register_of_legislation:F2006B08478:body:0
Version: federal_register_of_legislation:F2006B08478
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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/CF6/35 Compressor Rear Frame Midflange 13/95

 Applicability: General Electric CF6-80A engines.

            Requirement: Action in accordance with the technical requirements of FAA AD 95-17-16 Amendment 39-9347.

            Note: GE CF6-80A SB No. 72-593 Revision 2 also refers.

 Compliance: Effective 7 December 1995:

            Unless previously accomplished, as specified in the Requirement Document, except for paragraph (b) which has a revised compliance date of 30 June 1997.

            Note: Paragraph (b) requires replacement or rework of the CRF midflange which is considered terminating action for the inspections.

            Background: General Electric has advised that axial cracks have been found in the CRF midflanges and in one event a CRF midflange crack resulted in flange separation and a subsequent rejected take-off.

            This Directive mandates a repetitive on-wing eddy current inspection or optional on- wing fluorescent particle inspection (FPI), repetitive shop level FPI of the CRF midflange area and replacement or rework of the CRF midflange.