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Commonwealth legislation
This amendment requires operators of GE CF6-series engines to reinspect or remove from service certain high-pressure turbine stage two nozzle guide vanes (NGVs), using the inspection procedures in GE Service Bulletin CF6-80E1 S/B 72-0217 Rev 2. It ties compliance timing to cycles‑since‑overhaul and cycles‑in‑service thresholds. The amendment shortens inspection intervals because cracks were found to grow faster than initially expected. That requires more frequent inspection, increasing operator inspection and scheduling costs; the AD and the referenced service bulletin set the standards and deadlines.
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Direct links to the current provisions in AD/CF6/48 Amdt 1 - Nozzle Guide Vanes.
Reinspect or remove from service the NGVs.
Remove from service, or re-inspect using the Accomplishment Instructions of GE SB No. CF6-80E1 S/B 72-0217, Revision 2, dated 5 January 5 2004.
Note 3: FAA AD 2004-09-34 Amdt 39-13625 refers.
Compliance: For Requirement 1: Unless previously accomplished in accordance with the Conditions and Reinspection intervals listed in the "Inspection Table for Cracking in the Airfoil Outer Fillet," Figure 5, of GE Service Bulletin (SB) No. CF6-80E1 S/B 72-0217, Revision 2, or within 200 cycles-in-service-since-last inspection (CSLI), whichever is earlier.
For Requirement 2: For NGVs with more than 800 cycles-since-overhaul (CSO) on the effective date of this AD, within 50 cycles-in-service (CIS) after the effective date of this AD; thereafter in accordance with the Conditions and Reinspection intervals listed in the "Inspection Table for Cracking in the Airfoil Outer Fillet," Figure 5, of GE SB No. CF6-80E1 S/B 72-0217, Revision 2.
AD/CF6/48 Amdt 1 (continued)
For NGVs with 800 or fewer CSO on the effective date of this AD, at the first regular HPT blade inspection after 800 CSO, but before reaching 900 CSO; thereafter in accordance with the Conditions and Reinspection intervals listed in the "Inspection Table for Cracking in the Airfoil Outer Fillet," Figure 5, of GE SB No. CF6-80E1 S/B 72-0217, Revision 2.
For the purposes of this AD, cycles-since-overhaul (CSO) is defined as cycles since repair as described in GE SB No. CF6-80E1 S/B 72-0164 dated 16 March 1999.
The original issue of this Directive became effective on 20 February 2003. This Amendment becomes effective on 30 September 2004.
Background: An uncontained failure has been attributed to high-pressure turbine stage two nozzle guide vane distress. This directive introduced an inspection program to identify early signs of distress.
This amendment reduces the inspection interval, because it has been determined that the cracks that develop could grow at a faster rate than originally expected.
The original issue of this Directive became effective on 20 February 2003.
Signature of Gary J Carr Delegate of the Civil Aviation Safety Authority
Gary J Carr
Delegate of the Civil Aviation Safety Authority 13 August 2004
View image in the official source
The above AD is notified in the Commonwealth of Australia Gazette on 8 September 2004.
Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.
Reinspect or remove from service the NGVs.
Remove from service, or re-inspect using the Accomplishment Instructions of GE SB No. CF6-80E1 S/B 72-0217, Revision 2, dated 5 January 5 2004.
Note 3: FAA AD 2004-09-34 Amdt 39-13625 refers.
Compliance: For Requirement 1: Unless previously accomplished in accordance with the Conditions and Reinspection intervals listed in the "Inspection Table for Cracking in the Airfoil Outer Fillet," Figure 5, of GE Service Bulletin (SB) No. CF6-80E1 S/B 72-0217, Revision 2, or within 200 cycles-in-service-since-last inspection (CSLI), whichever is earlier.
For Requirement 2: For NGVs with more than 800 cycles-since-overhaul (CSO) on the effective date of this AD, within 50 cycles-in-service (CIS) after the effective date of this AD; thereafter in accordance with the Conditions and Reinspection intervals listed in the "Inspection Table for Cracking in the Airfoil Outer Fillet," Figure 5, of GE SB No. CF6-80E1 S/B 72-0217, Revision 2.
AD/CF6/48 Amdt 1 (continued)
For NGVs with 800 or fewer CSO on the effective date of this AD, at the first regular HPT blade inspection after 800 CSO, but before reaching 900 CSO; thereafter in accordance with the Conditions and Reinspection intervals listed in the "Inspection Table for Cracking in the Airfoil Outer Fillet," Figure 5, of GE SB No. CF6-80E1 S/B 72-0217, Revision 2.
For the purposes of this AD, cycles-since-overhaul (CSO) is defined as cycles since repair as described in GE SB No. CF6-80E1 S/B 72-0164 dated 16 March 1999.
The original issue of this Directive became effective on 20 February 2003. This Amendment becomes effective on 30 September 2004.
Background: An uncontained failure has been attributed to high-pressure turbine stage two nozzle guide vane distress. This directive introduced an inspection program to identify early signs of distress.
This amendment reduces the inspection interval, because it has been determined that the cracks that develop could grow at a faster rate than originally expected.
The original issue of this Directive became effective on 20 February 2003.
Gary J Carr
Delegate of the Civil Aviation Safety Authority 13 August 2004
The above AD is notified in the Commonwealth of Australia Gazette on 8 September 2004.