AD/FA-200/9 Amdt 1 - Engine Driven Fuel Pump Outlet Tee - Replacement

Overview

The Civil Aviation Regulations 1998, as amended by the Civil Aviation Safety Authority, establish comprehensive guidelines to ensure the safety and reliability of aircraft operating in Australia. A specific focus within this legislative framework is the airworthiness directives, such as AD/FA-200/9 Amendment 1, which addresses issues identified in the Fuji FA-200 Series Aeroplanes. This directive was enacted to address the problem of fatigue cracking in the engine driven fuel pump outlet tee, a critical component in the aircraft's fuel system. The policy objective behind this regulation is to enhance aviation safety by mandating the replacement of the affected component to prevent potential failures that could compromise the aircraft's operational safety. The Civil Aviation (Safety) Regulations 1998, administered by the Civil Aviation Safety Authority, aim to maintain high safety standards in civil aviation by issuing detailed directives that address specific issues identified in aircraft design or operation. The directive in question, AD/FA-200/9 Amendment 1, was introduced to rectify the issue of fatigue cracking in the engine driven fuel pump outlet tee of Fuji FA-200-180 aeroplanes with serial numbers 12 and higher. This requirement mandates the installation of a new component within 100 hours of time in service after 31 March 1983, and subsequently at intervals of 3000 hours, reflecting the regulatory body's commitment to proactive safety management and the mitigation of identified risks.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 concerning the Civil Aviation Safety Authority Schedule of Airworthiness Directives, pertains to the Fuji FA-200 Series Aeroplanes. This legislation applies to all model FA-200-180 aircraft with a serial number of 12 and subsequent, mandating the installation of a new engine-driven fuel pump outlet tee, part number AN783-6. This requirement is aligned with Fuji Service Bulletin No. 200-004 and Japanese Civil Aeronautics Bureau Airworthiness Directive TCD-2213-82. Compliance must be achieved within 100 hours of time in service after 31 March 1983, and subsequently at intervals of 3000 hours of time in service, due to reported instances of fatigue cracking in the component. The regulations extend across the Commonwealth, enforcing compliance with airworthiness standards to ensure safety in civil aviation operations.

Key Provisions

The Civil Aviation Regulations 1998, Part 39, under the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, specifically address the Fuji FA-200 series aeroplanes in AD/FA-200/9 Amendment 1. This directive mandates the replacement of the engine driven fuel pump outlet tee in all model FA-200-180 aeroplanes with serial numbers 12 and subsequent (subsection 105.002). The requirement is to install a new engine driven fuel pump outlet tee, part number AN783-6, to mitigate the risk of fatigue cracking that has been reported by the manufacturer (subsection 105.003). This directive references Fuji Service Bulletin No. 200-004 and Japanese Civil Aviation Bureau Airworthiness Directive TCD-2213-82. The obligations imposed by this directive are straightforward yet critical for ensuring the continued airworthiness of the Fuji FA-200 series aeroplanes. Operators and owners of these aircraft must comply with the directive by replacing the specified component within 100 hours of time in service after 31 March 1983. Following the initial replacement, the component must be replaced at intervals of 3000 hours of time in service thereafter (subsection 105.004). This periodic replacement schedule is intended to prevent fatigue cracking and maintain the structural integrity of the fuel system, thereby ensuring the safety of the aircraft in operation. Failure to comply with the requirements of this airworthiness directive can result in serious legal consequences. Non-compliance may be viewed as a breach of the Civil Aviation Regulations, leading to enforcement actions by CASA. The consequences can include civil penalties under section 13.002 of the Civil Aviation Act 1988, which may result in fines up to a substantial amount, depending on the severity of the breach. Additionally, there could be criminal penalties if the non-compliance leads to safety incidents or accidents, resulting in potential imprisonment as stipulated under the Act. Ensuring adherence to this directive is therefore essential for the safety of the aircraft and the well-being of those onboard.