COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Boeing 747 Series Aeroplanes
AD/B747/95 Wing Leading Edge Duct 6/91
Applicability: Model 747 series, line positions 2 through 707; except model 747-400 series. Requirement: Action in accordance with the Technical Requirements of FAA AD 91-06-08 Amdt
39-6928.
Compliance: As specified in the Requirement document with a revised effective date of 13 June 1991 for Australian registered aircraft.
Background: This Directive is raised to reflect the above FAA AD amendment which is prompted, in part, by the discovery that the existing AD (88-17-07), incorrectly states that the stress relieving procedure constitutes terminating action for titanium T-ducts.
Additionally, the FAA has determined that, in the interest of continuing airworthiness, the terminating action must be mandatory and that a proof pressure test must be required. Cracked or ruptured ducts, if not corrected, could lead to damage to wing leading edge panels and associated problems. Effective date required by the FAA is extended by two months.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the need for adherence to Airworthiness Directives (ADs) for aircraft operating in Australian airspace. This legislative instrument, enacted by the Commonwealth of Australia, aims to ensure the safety and airworthiness of aircraft through regulatory compliance. The AD in question pertains to Boeing 747 Series aeroplanes, excluding the 747-400 series, and concerns the wing leading edge duct. The requirement outlined in AD/B747/95 is to comply with the Technical Requirements of FAA AD 91-06-08 Amendment 39-6928, with an effective date of 13 June 1991 for Australian registered aircraft. This directive was introduced to rectify inaccuracies in previous ADs and to mandate a proof pressure test for the wing leading edge ducts, addressing the potential safety risks posed by cracked or ruptured ducts. The policy objective is to maintain the highest safety standards in civil aviation through stringent regulatory oversight and compliance with international standards.
Scope and Application
The Civil Aviation Regulations 1998, under Part 39 - 105, pertain specifically to the Civil Aviation Safety Authority's schedule of airworthiness directives concerning Boeing 747 series aeroplanes. The legislation applies to all Boeing 747 models, except for the 747-400 series, within line positions 2 through 707. The primary focus of this particular directive is the wing leading edge duct, as outlined in AD/B747/95, which mandates actions in accordance with the Technical Requirements of FAA AD 91-06-08 Amdt39-6928. The directive necessitates compliance with the specified requirements, with a revised effective date of 13 June 1991 for aircraft registered in Australia. The directive addresses the correction of an error in a previous airworthiness directive (AD 88-17-07) and establishes that the terminating action must be mandatory, including a proof pressure test, to prevent potential damage to wing leading edge panels and associated issues. The directive is a reflection of FAA requirements, adapted to ensure the airworthiness of Australian registered aircraft within this category.
Key Provisions
The Civil Aviation Regulations 1998, particularly Part 39, which pertains to airworthiness directives, includes provisions for maintaining the safety of Boeing 747 series aeroplanes, specifically in the context of wing leading edge duct maintenance. Section AD/B747/95 outlines the requirements and compliance details for these aircraft, with a particular focus on models 747 series, excluding the 747-400 series. This directive applies to line positions 2 through 707 and mandates compliance with the Technical Requirements outlined in FAA AD 91-06-08 Amendment 39-6928, with a revised effective date of 13 June 1991 for Australian registered aircraft.
The obligations imposed by this directive require operators and owners of the specified Boeing 747 series aircraft to adhere strictly to the Technical Requirements specified in the FAA AD 91-06-08 Amendment 39-6928. This involves conducting mandatory actions to address potential issues with the wing leading edge ducts, particularly focusing on the stress relieving procedures. Operators must ensure that the ducts are inspected and tested for cracks or ruptures and that corrective actions are taken as necessary to prevent damage to the wing leading edge panels and associated problems. The directive underscores the necessity of rigorous maintenance protocols to ensure the ongoing airworthiness of these aircraft.
Failure to comply with the provisions set forth in the Civil Aviation Regulations 1998 can result in significant consequences. While the specific legal text does not explicitly detail penalties for non-compliance, it is understood that any breach of airworthiness directives can lead to enforcement actions by the Civil Aviation Safety Authority (CASA). These actions may include fines, grounding of the aircraft, or even revocation of the aircraft’s certificate of airworthiness. Such stringent measures underscore the importance of adhering to the mandated safety standards and procedures.
The directive is a response to the discovery that a previous airworthiness directive (AD 88-17-07) contained inaccuracies regarding the stress-relieving procedure for titanium T-ducts. The Federal Aviation Administration (FAA) determined that a mandatory terminating action, including a proof pressure test, was necessary to ensure the safety of these aircraft. This directive aims to correct the previous oversight and provide clear, enforceable requirements to mitigate potential safety risks associated with wing leading edge duct failures. The FAA extended the effective date by two months to allow operators sufficient time to implement the necessary changes and comply with the new standards.