AD/CF6/36 Amdt 1 Forward Engine Mount Assembly (Cth)
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CF6/36 and issues the following 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/CF6/36 Amdt 1 | Forward Engine Mount Assembly | 9/2006 |
Applicability: | CF6-45/-50 and CF6-80A turbofan engines with left-hand side links part numbers 9204M94P01, 9204M94P03, and 9346M99P01, and right-hand side links part numbers 9204M94P02, 9204M94P04, and 9346M99P02, installed on the five-link forward engine mount assembly (also known as Configuration 2). These engines are installed on, but not limited to Boeing Models DC10-15, DC10-30, B767, and B747 series aircraft and Airbus Models A300 and A310 series aircraft. |
Requirement: | Action in accordance with the technical requirements of FAA AD 2006-12-24 Note 1: Shop level refurbishment of the side links is terminating action to the on-wing inspection program. Note 2: General Electric Aircraft Engines Service Bulletins CF6-50 S/B 72-1255, dated 26 January 2005, and CF6-80A S/B 72-0797, dated 26 January 2005, or later FAA approved revisions, refer. |
Compliance: | As specified in the Requirement document, with a revised effective date of |
| This Amendment becomes effective on 31 August 2006. | |
Background: | The manufacturer has advised that side links experience stress corrosion cracking when the protective coating becomes damaged. This Directive intends to prevent a side link fracture by mandating an initial and repetitive on-wing visual inspection of the side links of the five-link forward mount assembly for cracks. If the side links are found cracked replacement of the side links and pylon attachment bolts and inspection of the fail-safe bolt and platform lug is required. |
| Amendment 1 is issued in response to a new FAA AD, which additionally requires inspecting and refurbishing the side link at every exposure of the side link, and also requires the same actions on certain part number side links installed on CF6-80A turbofan engines. |
David Villiers
Delegate of the Civil Aviation Safety Authority
21 July 2006
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