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 39.1 (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/CF6/55 Vertical Link And Pylon Attachment Bolts 7/2004
Applicability: General Electric Company (GE) CF6-80E1A2 and -80E1A4 turbofan engines with left vertical link bolts part number (P/N) 1304M26P02 installed, and pylon attachment bolts originally torqued to 450-500 lb ft.
Note 1: These engines are installed on, but not limited to Airbus Industrie A330-200 and A330-300 aeroplanes.
Requirement: 1. Reduce the pylon attachment bolt torque on each of the five bolts to 400-450 lb ft in accordance with paragraph 3 of the Accomplishment Instructions of Alert Service Bulletin (ASB) No. CF6- 80E1 S/B 72-A0184, Revision 1, dated February 26, 2002.
2. Remove the three left vertical link bolts, P/N 1304M26P02, and replace with three left vertical link bolts, P/N 1304M26P05.
Note 2: Bolts P/N 1304M26P05 are serialized and have a calculated life limit published in the Life Limits section of Chapter 5 of the engine manual.
Note 3: FAA AD 2003-26-11 Amdt 39-13409 refers.
Compliance: For Requirement 1:
For CF6-80E1A2 engines, before exceeding 7,160 cycles-since-new (CSN) or before exceeding 5,120 cycles-since- last-installation (CSLI), whichever is later.
For CF6-80E1A4 engines before exceeding 6,520 CSN or before exceeding 4,480 CSLI, whichever is later.
For Requirement 2:
At the next shop visit.
This Airworthiness Directive becomes effective on 8 July 2004.
General Electric Turbine Engines - CF6 Series
AD/CF6/55 (continued)
Background: This AD results from revised analyses by the airframe manufacturer of loads on the forward engine mount. This actions detailed in this Directive are to prevent engine separation that could result from a reduction of engine mount structural integrity due to failure of pylon attachment bolts or vertical link bolts.
James Coyne
Delegate of the Civil Aviation Safety Authority 27 May 2004
The above AD is notified in the Commonwealth of Australia Gazette on 16 June 2004.
Overview
The Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998, pertains to General Electric Company (GE) CF6-80E1A2 and -80E1A4 turbofan engines installed on Airbus Industrie A330-200 and A330-300 aeroplanes. This AD was introduced to address potential safety issues arising from the structural integrity of the engine mounts, specifically concerning the pylon attachment bolts and vertical link bolts. The directive aims to prevent engine separation by adjusting the torque of the pylon attachment bolts and replacing the left vertical link bolts. This legislative instrument was enacted on 8 July 2004 and is intended to ensure that the specified maintenance actions are carried out in accordance with the CASA's requirements.
Scope and Application
The Airworthiness Directive (AD) applies to General Electric Company (GE) CF6-80E1A2 and -80E1A4 turbofan engines equipped with specific vertical link bolts, which are installed in Airbus Industrie A330-200 and A330-300 aeroplanes, among others. The directive mandates specific actions to rectify unsafe conditions identified in the pylon attachment bolts and vertical link bolts of these engines. These actions include reducing the pylon attachment bolt torque to a specified range and replacing the left vertical link bolts with a new part number that includes a serialized and published life limit. Compliance with the AD is required within specified engine cycle limits and at the next scheduled maintenance visit. This directive, issued under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998, is applicable within the Commonwealth of Australia and becomes effective from 8 July 2004.
Key Provisions
The Airworthiness Directive (AD) AD/CF6/55 issued under subregulation 39.1(1) of the Civil Aviation Safety Regulations 1998 (CASR 1998) applies specifically to General Electric Company (GE) CF6-80E1A2 and -80E1A4 turbofan engines with certain vertical link bolts and pylon attachment bolts installed. These engines are typically used in Airbus Industrie A330-200 and A330-300 aeroplanes. The AD mandates two key actions to ensure the safety and airworthiness of these engines. Firstly, it requires the reduction of the pylon attachment bolt torque on each of the five bolts to a specified range of 400-450 lb ft. This adjustment is to be carried out in accordance with the Accomplishment Instructions of Alert Service Bulletin (ASB) No. CF6-80E1 S/B 72-A0184, Revision 1, dated February 26, 2002. Secondly, it mandates the replacement of three specific left vertical link bolts with a new set of bolts that have a serialized calculated life limit. This replacement must be done at the next shop visit. These requirements are intended to prevent engine separation due to reduced structural integrity in the forward engine mount.
The AD imposes specific obligations on the parties involved, primarily engine operators and maintenance personnel. Operators of GE CF6-80E1A2 and -80E1A4 turbofan engines must ensure that the actions outlined in the AD are performed within the specified timelines. For Requirement 1, adjustments must be made to the pylon attachment bolt torque before exceeding specific engine cycle thresholds. For Requirement 2, the replacement of the vertical link bolts must occur at the next scheduled shop visit. Maintenance personnel are responsible for following the instructions provided in the ASB and ensuring that the torque settings and bolt replacements are carried out correctly to avoid compromising the engine's airworthiness. Additionally, operators must maintain records of compliance with the AD to demonstrate adherence to the regulatory requirements.
Failure to comply with the AD may result in significant consequences. The AD is a legal mandate under the Civil Aviation Safety Regulations 1998, and non-compliance can lead to severe penalties. While the AD does not explicitly state the maximum penalties, non-compliance with CASR 1998 can result in substantial fines and potential criminal charges. The severity of the penalties may depend on the extent of the non-compliance and its impact on aviation safety. Moreover, non-compliance could lead to the grounding of affected aircraft, which would have substantial operational and financial implications for airlines. Therefore, it is crucial for operators and maintenance personnel to adhere strictly to the requirements of the AD to avoid these potential consequences.