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.
Boeing 767 Series Aeroplanes
AD/B767/200 Primary Nacelle Strut Structure 11/2004
Applicability: Model 767-200, -300, and -300F series aircraft, line numbers 1 through 663; powered by Pratt & Whitney or General Electric engines.
Requirement: Action in accordance with the technical requirements of FAA AD 2004-16-12 Amdt 39-13768.
Compliance: For the requirements of FAA AD 2001-02-07 (previously reflected in CASA AD/B767/134) the revised effective date of 19 April 2001 applies.
For the requirements of FAA AD 2001-06-12 (previously reflected in CASA AD/B767/137) the revised effective date of 12 July 2001 applies.
For the requirements of FAA AD 2001-08-23 (previously reflected in CASA AD/B767/135 Amdt 1) the revised effective date of 10 April 2001 applies.
For the new requirements of FAA AD 2004-16-12, as specified in the Requirement document, with a revised effective date of 28 October 2004.
This Airworthiness Directive becomes effective on 28 October 2004.
Background: This Directive requires, for aircraft subject to FAA AD 2001-02-07 and AD 2001-06- 12 on which certain modifications have been accomplished previously, reworking the aft pitch load fitting, and installing a new diagonal brace fuse pin. This Directive also requires, for aircraft subject to FAA AD 2001-08-23, replacing the outboard pitch load fitting of the wing front spar with a new, improved fitting.
The actions specified by this Directive are intended to prevent fatigue cracking in primary strut structure, which could result in separation of the strut and engine from the aircraft.
Boeing 767 Series Aeroplanes
AD/B767/200 (continued)
Compliance times for requirements contained in previous ADs are unchanged.
David Villiers
Delegate of the Civil Aviation Safety Authority 15 September 2004
The above AD is notified in the Commonwealth of Australia Gazette on 6 October 2004.
Overview
The Airworthiness Directive AD/B767/200 was issued by a delegate of the Civil Aviation Safety Authority (CASA) on 15 September 2004 to address safety concerns regarding the primary nacelle strut structure of Boeing 767 series aircraft. The directive applies to Model 767-200, -300, and -300F series aircraft, specifically line numbers 1 through 663, that are powered by Pratt & Whitney or General Electric engines. The aim of the directive is to prevent fatigue cracking in the primary strut structure, which could lead to the separation of the strut and engine from the aircraft. The CASA delegate has aligned the requirements of this directive with the technical requirements of FAA AD 2004-16-12 Amdt 39-13768, and has set revised effective dates for compliance with previous directives. This Airworthiness Directive became effective on 28 October 2004, and was subsequently notified in the Commonwealth of Australia Gazette on 6 October 2004.
Scope and Application
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 specifically to Boeing 767-200, -300, and -300F series aircraft with line numbers ranging from 1 through 663, and powered by Pratt & Whitney or General Electric engines. This legislation mandates that corrective actions must be implemented on the primary nacelle strut structure of the specified aircraft models, aligning with the technical requirements outlined in FAA AD 2004-16-12 Amendment 39-13768. These actions are necessary to address an unsafe condition that could lead to fatigue cracking in the primary strut structure, potentially resulting in the separation of the strut and engine from the aircraft. The directive sets forth a revised effective date of 28 October 2004, superseding previous ADs and ensuring the continued airworthiness of the affected aircraft by enforcing the specified modifications.
Key Provisions
The Airworthiness Directive (AD) issued under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998 (CASR 1998) targets specific Boeing 767 Series Aeroplanes, namely the 767-200, -300, and -300F series aircraft with line numbers 1 through 663 powered by either Pratt & Whitney or General Electric engines. The directive, labelled AD/B767/200, mandates specific actions to address unsafe conditions identified in the primary nacelle strut structure of these aircraft. These actions include reworking the aft pitch load fitting and installing a new diagonal brace fuse pin, as outlined in FAA AD 2004-16-12 Amdt 39-13768, and replacing the outboard pitch load fitting of the wing front spar with an improved fitting, as specified in FAA AD 2001-08-23. The directive emphasises the necessity of these actions to prevent fatigue cracking in the primary strut structure, which could potentially lead to the separation of the strut and engine from the aircraft.
Operators and owners of the specified Boeing 767 series aircraft are obligated to comply with the AD by taking the necessary actions as per the technical requirements of FAA AD 2004-16-12 Amdt 39-13768. This includes the reworking of the aft pitch load fitting and the installation of a new diagonal brace fuse pin. Furthermore, operators must ensure that the outboard pitch load fitting of the wing front spar is replaced with a new, improved fitting. These requirements must be implemented in accordance with the instructions provided and by the specified compliance dates, which are detailed in the directive. Operators must also ensure that previous ADs, such as FAA AD 2001-02-07, FAA AD 2001-06-12, and FAA AD 2001-08-23, are adhered to with their respective revised effective dates.
Failure to comply with the AD may result in serious safety implications, including the risk of fatigue cracking leading to potential separation of the strut and engine from the aircraft. While the AD itself does not specify penalties, non-compliance with CASR 1998 could lead to enforcement actions by the Civil Aviation Safety Authority (CASA). Penalties for non-compliance with CASR 1998 can include substantial fines and, in severe cases, criminal charges. The exact penalties depend on the nature and severity of the non-compliance, but they can include significant financial penalties and imprisonment for individuals found guilty of serious violations.