AD/CF6/66 Uncontained Fan Blade Failure (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/CF6/66 Uncontained Fan Blade Failure 8/2007

Applicability:

General Electric Company (GE) CF6-50C, CF6-50C1, CF6-50C2, CF6-50C2B,
CF6-50C2F, and CF6-50C2R turbofan engines, with a forward fan stator case, part number (P/N) 9064M53G04, GO5, G06, G07, G08, G09, G10, G12, or G13, or
P/N 9173M37G01, G02, G03, G04, G05, or G06 installed.

Note 1:  These engines are installed on, but not limited to, Airbus A300, McDonnell Douglas DC-10 series, and DC-10-30F (KC-10A, KDC-10) aeroplanes.

Requirement:

Rework the forward fan stator case and install the fan module secondary containment shield.

-      For engines on Airbus 300 series aeroplanes, use paragraph 3, Accomplishment Instructions, of GE Service Bulletin (SB) No. CF6-50 S/B 72-0985, Revision 2, dated 21 March 2007, to do the rework and installation.

-      For engines on McDonnell Douglas aeroplanes, use paragraph 3, Accomplishment Instructions, of GE SB No. CF6-50 S/B 72-0986, Revision 2, dated 21 March 2007, to do the rework and installation.

The rework and installation specified above can also be done on-wing.

Previous credit is allowed for fan stator cases reworked and containment shields installed using GE SB No. CF6-50 S/B 72-0985, dated 2 December 1991 or Revision 1, dated 15 September 1998, or GE SB No. CF6-50 S/B 72-0986, dated 2 December 1991 or Revision 1, dated 15 September 1998, before the effective date of this AD.

Note 2:  FAA AD 2007-11-18 Amdt 39-15075 dated 22 May 2007 refers.

Compliance:

At the next engine shop visit after the effective date of this AD, but no later than
30 June 2010, unless previously accomplished.

This Airworthiness Directive becomes effective on 2 August 2007.

Background: This AD results from reports of uncontained fan blade failures causing damage and separation of aeroplane hydraulic lines.  The issuing of this AD is intended to prevent uncontained fan blade failures, which can result in separation of aeroplane hydraulic lines, damage to critical aeroplane systems, and possible loss of aeroplane control.

David Punshon
Delegate of the Civil Aviation Safety Authority

21 June 2007