AD/CF6/17 - Stage 1 Fan Rotor Disc
1AD/CF6/17 - Stage 1 Fan Rotor Disc
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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/CF6/17 Stage 1 Fan Rotor Disc 3/91
Applicability: CF6 - 6, -45, -50, -80A.
Requirement: Inspect the stage 1 fan disc dovetail post for cracks in accordance with the technical requirements of the FAA AD 91-01-04 Amdt 39-6847.
Note: The GE SB 72-999, 965 and 575 covering the -50/-45, -6 and -80A series respectively refer.
Compliance: As specified in the Requirement Document.
Background: Five stage 1 fan discs have been discovered with cracks in the dovetail post area. The defect has the potential for multiple blade release, engine power loss and uncontained engine failure.