AD/ROCK-114/13 Amdt 1 - Vertical Stabiliser Forward Spar Attachment Structure

Overview

The Civil Aviation Regulations 1998, specifically PART 39 - 105, which is a legislative instrument under the Civil Aviation Act 1988, addresses the safety and airworthiness of aircraft in Australia. One such legislative instrument, F2006B06646, pertains to Gulfstream (Rockwell) 114 Series Aeroplanes, where it introduces Airworthiness Directives to ensure the safety of these aircraft models. Enacted by the Australian Government, this regulation aims to mitigate risks associated with specific structural components by mandating inspections and modifications. The policy objective is to enhance safety and prevent potential structural failures by requiring regular checks and necessary repairs to critical parts of the aircraft, as illustrated by the directive related to the vertical stabiliser forward spar attachment structure. The directive AD/ROCK-114/13 Amendment 1, dated 3/88, applies to Gulfstream 114 and 114A models with serial numbers ranging from 14001 to 14540. It specifies that an inspection for cracks in the fuselage frame and vertical fin attachment fitting must be conducted within 10 hours of the aircraft being in service after 7 May 1987, and any modifications must be made before further flight if cracks are detected, or by 24 March 1989 at the latest. This directive responds to reports of cracking in the vertical stabiliser forward spar attachment structure, highlighting the importance of timely intervention to maintain airworthiness and safety standards.

Scope and Application

The Civil Aviation Regulations 1998, as part of the broader legislative framework governing aviation safety in Australia, specifically addresses the maintenance and operational standards of aircraft through the Civil Aviation Safety Authority (CASA). Part 39 of these regulations includes Airworthiness Directives (ADs) that mandate specific safety measures for certain aircraft models. AD/ROCK-114/13 Amendment 1 pertains to the Gulfstream (Rockwell) 114 Series aeroplanes, focusing on the vertical stabiliser forward spar attachment structure for models 114 and 114A with serial numbers ranging from 14001 to 14540. This directive is binding and applies directly to the operators and maintainers of these specific aircraft, ensuring that they comply with the stipulated safety requirements to prevent structural failure. The directive requires operators to inspect the vertical stabiliser forward spar attachment structure for any signs of cracks within 10 hours of service following 7 May 1987 and to modify the attachment according to Gulfstream Aerospace Service Bulletin 114-23A if such cracks are detected, with modifications required before further flight. If no cracks are found, the modifications must be completed by 24 March 1989. The directive is clear that simple AC 43.13 type repairs are not considered sufficient for compliance. This regulatory measure underscores the importance of stringent oversight and proactive maintenance to ensure the safety of all aircraft operating under the Australian Civil Aviation Regulations.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, detail the Airworthiness Directives for Gulfstream (Rockwell) 114 Series Aeroplanes, with AD/ROCK-114/13 Amendment 1 addressing the vertical stabiliser forward spar attachment structure (Sections 1-2). This directive applies to models 114 and 114A with serial numbers ranging from 14001 to 14540. The directive outlines two key requirements: first, an inspection for cracks in the fuselage frame and the vertical fin attachment fitting, as specified in Part I of Gulfstream Aerospace SB 114-23A (Section 3). Secondly, it mandates modifications to the vertical fin attachment in accordance with Part II of the same Service Bulletin, explicitly stating that simple AC 43.13 type repairs are not acceptable (Section 4). The obligations imposed by this directive are clear and specific. Operators of the affected aircraft must ensure that the inspection for cracks is conducted within 10 hours of time in service after 7 May 1987 (Section 5). If cracks are detected, the required modifications must be completed before further flight. If no cracks are found, the modifications must be completed by no later than 24 March 1989 (Section 6). These obligations underscore the importance of timely and thorough inspections and repairs to maintain airworthiness and safety standards. Failure to comply with the requirements of this directive can result in severe consequences. The Civil Aviation Safety Authority may take enforcement action against operators who do not adhere to the stipulated inspection and repair timelines. While the specific penalties are not detailed in the directive, non-compliance with airworthiness directives typically results in significant civil penalties, and in severe cases, could lead to criminal charges. These potential penalties underscore the critical nature of adhering to the directive to ensure the safety and airworthiness of the aircraft in question.