AD/CF6/38 - Stage 1 Fan Disk Inspection (Cth)

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/CF6/38 Stage 1 Fan Disk Inspection 1/99 DM

Applicability: General Electric Company CF6-6, -45, -50, -80A and 80C2 series turbofan engines with Stage 1 fan disks installed, identified by serial numbers (S/N) in the following GE Alert Service Bulletins (ASBs):

1. CF6-6 ASB 72-A996 Revision 4 dated 9 June 1998.

2. CF6-50 ASB 72-A988 Revision 6 dated 25 August 1998.

3. CF6-80A ASB 72-A565 Revision 5 dated 9 June 1998.

4. CF6-80C2 ASB 72-A478 Revision 4 dated 9 June 1998.

These engines are installed on, but not limited to, Boeing 747 and 767, Airbus 300 and 310, McDonnell Douglas DC-10 and MD-11 Series aircraft.

Requirement: On fan disks affected by this Directive, perform an ultrasonic immersion inspection for cracks in accordance with the applicable alert service bulletin (as identified in the applicability section above), remove from service any disks found to be cracked and replace with serviceable components.

Compliance: Before next flight after the effective date of this Directive.

This Airworthiness Directive becomes effective on 25 November 1998.

Note: US FAA AD 98-22-06 Amendment 39-10853 refers.

Background: Stage 1 fan disks manufactured between late 1984 and early 1985 have been found to be cracked during routine shop inspections. The actions in this Directive are intended to prevent fan disk failures, due to cracks, which could result in an uncontained engine failure and damage to the aircraft. This Directive reflects a country of origin AD.