Overview

The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, are designed to regulate and ensure the safety of civil aviation in Australia. The regulations encompass various aspects of airworthiness, maintenance, and operation of aircraft. One such regulation is Part 39 - 105, which pertains specifically to Airworthiness Directives issued by the Civil Aviation Safety Authority (CASA). These directives address identified safety issues with particular aircraft models, ensuring that necessary actions are taken to mitigate risks. The 2000 Airworthiness Directive AD/B767/124 for Boeing 767 Series Aeroplanes was introduced to address concerns regarding structural fatigue in the wing front spar pitch load fittings. The directive was issued under the authority of the CASA delegate to ensure compliance with safety standards and to rectify potential unsafe conditions that could compromise the structural integrity of the aircraft. The Airworthiness Directive AD/B767/124 was enacted to mandate specific inspections and modifications for Boeing 767 series aircraft, line numbers 1 through 663, in response to a structural fatigue analysis conducted by the Federal Aviation Administration (FAA). The analysis indicated that operational loads on the nacelle were higher than initially designed, potentially leading to fatigue cracking in the wing front spar pitch load fittings. The policy objective of this directive is to ensure the continued airworthiness of the affected aircraft by requiring detailed inspections and, where necessary, modifications to the nacelle strut and wing structure. This directive was notified in the Commonwealth of Australia Gazette on 9 August 2000, with an effective date of 7 September 2000, providing operators and maintenance personnel with clear instructions to address the identified safety concerns.

Scope and Application

The Airworthiness Directive (AD) issued under the Civil Aviation Regulations 1998, specifically part 39 - 105, pertains to Boeing 767 series aeroplanes, particularly those within line numbers 1 through 663. This directive applies to all aircraft of the specified model series and mandates compliance with the requirements set out by the Federal Aviation Administration's AD 2000-12-17 Amdt 39-11795. The AD, issued by the delegate of the Civil Aviation Safety Authority, is aimed at addressing structural concerns identified in the wing front spar pitch load fittings, which have been found to experience higher operational loads than initially designed for. The directive requires inspections to be conducted in accordance with the specified technical requirements to ensure safety and compliance, with a revised effective date set for 7 September 2000. Compliance with this directive is critical, as it is designed to detect and correct fatigue cracking that could potentially compromise the structural integrity of the aircraft. Modifications and inspections must be carried out as outlined in relevant Boeing Service Bulletins, and the completion of specified inspections and modifications constitutes the terminating action for the inspection requirements of this directive.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, under the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, mandates particular safety measures for Boeing 767 series aircraft. The Airworthiness Directive AD/B767/124 issued on 14 July 2000, and effective from 7 September 2000, concerns the inspection of the wing front spar pitch load fittings for Models 767 series aircraft, line numbers 1 through 663. This directive follows a structural fatigue analysis conducted by the Federal Aviation Administration (FAA) that indicates higher operational loads on the nacelle than originally accounted for in the design of these aircraft, raising concerns about fatigue cracking in the pitch load fittings. The AD requires that inspections be performed according to the technical requirements specified in FAA AD 2000-12-17 Amdt 39-11795. Boeing Service Bulletin 767-57-0053 Revision 2 also references this directive. Modifications to the nacelle strut and wing structure must be carried out in accordance with Boeing Service Bulletins 767-54-0080, 767-54-0081, or 767-54-0082, as applicable, and the lug bore inspections and insurance cut of the pitch load fitting must be completed as per Service Bulletin 767-57-0053 Revision 2. These modifications and inspections are to be completed as specified in the requirement document for the initial and repetitive inspection requirements, with the revised effective date of 7 September 2000. Compliance with these directives is mandatory for all Boeing 767 series aircraft within the specified range. The directive also stipulates that once the modifications and inspections are completed, the inspection requirements of this Airworthiness Directive are considered satisfied. Failure to adhere to these requirements could result in significant safety risks, potentially leading to structural failure and catastrophic consequences during flight. The AD was formally notified in the Commonwealth of Australia Gazette on 9 August 2000, ensuring that all relevant parties were informed of the new safety measures. Breaching the provisions of this Airworthiness Directive can have serious consequences. The Civil Aviation Regulations 1998 enforce strict compliance with airworthiness directives to ensure the safety of all aircraft in operation. Non-compliance could result in the aircraft being deemed non-airworthy, leading to grounding and potential legal repercussions for the aircraft operator. The Civil Aviation Safety Authority has the authority to enforce compliance, including the imposition of fines, and in severe cases, criminal charges may be brought against individuals or corporations responsible for non-compliance. The maximum penalties for such offences can include substantial fines and imprisonment, depending on the severity of the breach and its impact on aviation safety.