AD/CF6/60 High Pressure Compressor Case (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

General Electric Turbine Engines - CF6 Series

AD/CF6/60 High Pressure Compressor Case 1/2006

Applicability:

General Electric Company (GE) CF6-80E1A1, -80E1A2, -80E1A3, -80E1A4, and
-80E1A4/B turbofan engines.

Note 1:  These engines are installed on, but not limited to, Airbus Industrie A330 series aeroplanes.

Requirement:

For HPC cases, P/N 1509M97G07 and P/N 2083M69G03, perform fluorescent-penetrant inspection (FPI) of the circumferential flange spotfaces at the first hole in the aft flange above and below each horizontal split line flange.  See Figure 1 of this AD for reference.

Information on inspecting these areas can be found in the ALS of GE Engine Manual GEK 99376, Revision 19, dated 15 August 2005.

Note 2:  FAA AD 2005-23-09 Amdt 39-14367 refers.
Compliance:	The initial inspection, unless previously accomplished must be performed at or before reaching 7,300 cycles-since-new, thereafter repeat the inspection at intervals within 3,700 cycles-since-last-inspection.
This Airworthiness Directive becomes effective on 19 January 2006.
Background:	This AD results from the discovery that high pressure compressor (HPC) cases, part number (P/N) 1509M97G07 and P/N 2083M69G03, were inadvertently left out of the Airworthiness Limitations Section (ALS), Chapter 05-21-02, of GE Engine Manual GEK 99376, Revision 17.  This AD is intended to prevent failure of the HPC case aft flange, due to cracking.

James Coyne
Delegate of the Civil Aviation Safety Authority

30 November 2005