AD/ROBIN/28 Amdt 1 - Wing Attachment Hardware

Overview

The Civil Aviation Regulations 1998, under the authority of the Commonwealth of Australia and administered by the Civil Aviation Safety Authority, were enacted to ensure the safety of civil aviation within Australia. A specific legislative instrument within this framework, F2006B06626, was introduced to address a safety issue identified in Avions Pierre Robin model R2160 aircraft, specifically concerning the wing attachment hardware. This legislative instrument was prompted by a report from the French airworthiness authority, the DGAC, which detailed an in-flight failure of the wing attachments in a Robin R2160 aircraft. The policy objective of this legislative instrument is to mandate inspections and replacements of wing attachment hardware to ensure the continuing airworthiness of these aircraft, thereby mitigating the risk of similar incidents. The directive became effective on 2 January 1997, imposing specific requirements for inspections, flight restrictions, and hardware replacement to enhance the safety standards of the affected aircraft.

Scope and Application

The Civil Aviation Regulations 1998, under PART 39 - 105, specifically targets the Avions Pierre Robin model R2160 aircraft with less than 3400 hours of time in service, imposing several critical airworthiness directives. These directives are mandated to ensure the safety and continued airworthiness of the aircraft by addressing issues with the wing attachment hardware. The regulations apply to all serial numbers of the specified aircraft model and require compliance with specific inspections and modifications to the wing attachment hardware. This includes checking the presence and torque of wing attachment bolts, restricting certain flight conditions until further modifications are made, and replacing wing attachment hardware in accordance with detailed sections of specific manufacturer notes. Compliance deadlines are set for specific actions to ensure that the safety measures are implemented in a timely manner. The application of these directives is national, covering all relevant aircraft within the Commonwealth of Australia, and is enforced by the Civil Aviation Safety Authority. The directives also allow for extensions and modifications through subordinate instruments, enabling the Civil Aviation Safety Authority to adapt the regulations in response to new information or changing conditions. However, this specific legislative instrument does not outline any exclusions, exemptions, or thresholds beyond the specified aircraft model and its operational hours. The directives are designed to maintain the safety standards of the aircraft, with the ultimate goal of preventing incidents similar to the in-flight failure reported by the French airworthiness authority, the DGAC. The regulations are continuously monitored and updated to reflect the latest safety requirements and industry practices.

Key Provisions

The Civil Aviation Safety Authority's Airworthiness Directive (AD) for Robin Aviation Series Aeroplanes, specifically AD/ROBIN/28 Amendment 1, sets forth several key requirements and compliance deadlines for the maintenance and inspection of Avions Pierre Robin model R2160 aircraft. The directive applies to all serial numbers of this aircraft model with less than 3400 hours of time in service. The main requirements under this directive (sections 1-5) include inspecting the wing attachment hardware for the presence of six bolts per wing and ensuring that all bolts are torqued to 50Nm (section 1). It mandates restricting flight operations to +3.8g and -1.52g, with spinning prohibited, and requires the installation of a temporary placard over the currently installed limitations placard (section 2). The wing attachment hardware must be replaced according to sections 2 and 3 of Avions Pierre Robin NOTE NAV 96-3, dated 2 May 1996 (section 3). The torque of the front and rear wing attachment bolts must also be checked in accordance with section 3.3 of the same note, with further inspection required if the torque is incorrect (section 4). Finally, the wing attachment hardware must be inspected according to sections 2 and 3 of NOTE NAV 96-3 (section 5). The AD imposes specific obligations on the operators and owners of the affected aircraft to ensure compliance with the outlined requirements. Before further flight after 13 March 1996, operators must ensure that the initial inspection of the wing attachment hardware and bolt torque is conducted (section 1). Until the wing attachment hardware is replaced, they must adhere to the flight restrictions specified in section 2. The replacement of the wing attachment hardware must be completed before 100 hours of time in service after 2 January 1997 (section 3). Subsequently, the torque of the front and rear wing attachment bolts must be checked before 100 hours of time in service after compliance with requirement 3 and at intervals not exceeding 100 hours thereafter (section 4). Lastly, the wing attachment hardware must be inspected before 1000 hours of time in service after compliance with requirement 3 and at intervals not exceeding 1000 hours thereafter (section 5). Failure to comply with the requirements of the AD may result in serious safety concerns and potential legal consequences. The AD does not explicitly state penalties for non-compliance, but non-compliance with airworthiness directives can lead to enforcement actions under the Civil Aviation Act 1988 and the Civil Aviation Regulations 1988. Possible consequences include fines, imprisonment, or both, depending on the severity of the breach. Additionally, non-compliance may result in the grounding of the aircraft, which can have significant operational and financial impacts on the operator.