AD/G1159/36 - Corrosion and Cracking Fuselage Station 452

Overview

The Civil Aviation Regulations 1998, amended in 2006, were enacted by the Australian Parliament to ensure the safety and efficiency of civil aviation within the country. The Civil Aviation (Airworthiness) Regulations 1998, which include Part 39, aim to establish standards for the airworthiness of aircraft, with a particular focus on addressing safety concerns that could compromise the structural integrity of aeroplanes. The legislation fills the gap by providing specific directives for the inspection, maintenance, and repair of aircraft to prevent potential hazards, such as corrosion and cracking, which can lead to catastrophic failures. The policy objective is to safeguard public safety and to maintain the highest possible standards of airworthiness for all aircraft operating in Australian airspace. One specific legislative instrument under the Civil Aviation Regulations 1998, known as AD/G1159/36, addresses the problem of corrosion and cracking in the Grumman Gulfstream G1159 and G-IV Series aeroplanes. This directive targets a particular area of the aircraft, Fuselage Station 452, where significant corrosion and cracking issues have been reported. The requirement includes detailed inspections and, if necessary, the replacement of parts to prevent structural failure. This targeted approach ensures that the identified safety issues are promptly and effectively managed, thereby enhancing the overall safety of these aircraft in service.

Scope and Application

The Civil Aviation Regulations 1998, under Part 39 - 105 and the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, specifically addresses the maintenance and inspection requirements for Gulfstream (Grumman) G1159 and G-IV Series Aeroplanes. This directive applies to all aircraft within the specified serial numbers, necessitating a stringent visual and borescopic inspection to detect corrosion or cracks in critical fuselage components. These inspections are crucial to ensure the safety and airworthiness of the aircraft, with any identified defects requiring prompt replacement according to a scheme approved by the Authority. The directive mandates compliance prior to 30 September 1990, reflecting the urgency to mitigate identified risks of corrosion and cracking that could compromise the structural integrity of the aircraft.

Key Provisions

The Civil Aviation Regulations 1998, Part 39, under the 105 Civil Aviation Safety Authority Schedule of Airworthiness Directives for the Gulfstream (Grumman) G1159 and G-IV Series Aeroplanes, includes specific provisions to address corrosion and cracking at Fuselage Station 452 (section 1). The directive, identified as AD/G1159/36, applies to specific serial numbers of the aircraft (section 2). The main requirements outlined in this directive include conducting a visual inspection for corrosion or cracks in critical parts at Fuselage Station 452 (section 3(1)), inspecting the lower cavity of the "clothespin" attach fitting with a borescope (section 3(2)), inspecting the upper cavity of the fitting using a borescope or an approved scheme (section 3(3)), inspecting the wing upper aft plank for corrosion or defects using ultrasonic equipment (section 3(4)), and replacing any cracked or corroded parts according to an approved scheme (section 3(5)). Additionally, the directive refers to FAA Emergency AD 90-13-02 (section 5). The Act imposes specific obligations on the parties involved, such as the aircraft operators and maintenance personnel, to ensure that the required inspections and repairs are carried out meticulously and in accordance with the approved schemes. The inspections must be performed by qualified personnel using the specified equipment and methods to ensure the integrity of the aircraft (section 3). Operators and maintenance personnel must ensure that any identified defects are rectified promptly and in compliance with the Civil Aviation Safety Authority's guidelines. The directive also requires that any modifications, such as the installation of a drain hole in the "clothespin" attach fitting, are carried out as per the referenced Gulfstream G-II Customer Bulletin No 42, Section V, dated December 15, 1969 (section 3(2)). Failure to comply with the requirements set out in this directive may result in serious safety risks, including the potential for substantial reduction in wing integrity. The Civil Aviation Regulations 1998 do not explicitly state the penalties for non-compliance in this directive; however, general provisions of the Civil Aviation Act 1988 apply, which may include fines, imprisonment, or both. The severity of the penalties would depend on the nature and extent of the non-compliance and the impact on aviation safety. Operators and maintenance personnel must therefore ensure strict adherence to the directive to avoid any potential legal consequences.