AD/TB20/5 - Battery Tray Installation

Overview

The Civil Aviation Regulations 1998, specifically Part 39, addresses the safety requirements for civil aircraft through various Airworthiness Directives. One such directive, AD/TB20/5, pertains to Aerospatiale (Socata) TB20 (Trinidad) series aeroplanes and mandates the inspection and modification of the battery tray installation to mitigate the risk of electrolyte spillage, which could lead to corrosion and structural damage to the fuselage. This directive was enacted by the Civil Aviation Safety Authority (CASA) to ensure the safety of these aircraft models. The policy objective is to maintain and enhance airworthiness by preventing potential hazards that could compromise the structural integrity of the aircraft. This regulation was established to address a specific safety concern related to the battery tray installation on certain models of the Aerospatiale (Socata) TB20 series. The directive aims to ensure that the battery tray is installed in a manner that prevents electrolyte spillage, thereby avoiding corrosion and related damage to the aircraft’s fuselage. Compliance with this directive is mandatory and must be achieved within 50 hours of time in service after 31 October 1985. The regulation references French AD 85-130-(A) and requires adherence to the detailed specifications outlined in Socata Service Letter No. 18.

Scope and Application

The Civil Aviation Regulations 1998, specifically PART 39 - 105, applies to all models of Aerospatiale (Socata) TB20 (Trinidad) series aeroplanes with serial numbers up to 441, excluding those with serial numbers 343, 382, 414, 423, 425 to 429, and 434 to 438. The Act mandates that these aircraft undergo an inspection and modification of the battery tray installation in accordance with the requirements outlined in Socata Service Letter No. 18, with particular attention to the surrounding fuselage structure for any signs of electrolyte spillage and subsequent damage. The requirement to comply with these airworthiness directives is set within a timeframe of 50 hours of time in service after 31 October 1985. This regulation is a critical safety measure to prevent potential fuselage structural damage due to electrolyte spillage from the battery. The legislation is administered by the Civil Aviation Safety Authority, reflecting its national jurisdictional reach across Australia.

Key Provisions

The Civil Aviation Regulations 1998, specifically under PART 39 - 105, establish a schedule of airworthiness directives for various aircraft models, including the Aerospatiale (Socata) TB20 (Trinidad) Series Aeroplanes (subsection 105.015). For the TB20 series, there is a specific directive, AD/TB20/5, focusing on the battery tray installation (subsection 105.016). This directive applies to all TB20 series models with serial numbers (S/Nos) up to 441, except for S/Nos 343, 382, 414, 423, 425 to 429, and 434 to 438 (subsection 105.017). The requirement outlined in this directive is to inspect and modify the battery tray installation as detailed in Socata Service Letter No. 18, with a specific emphasis on checking the surrounding fuselage structure for any signs of electrolyte spillage and the resulting damage (subsection 105.018). Operators and owners of the affected aircraft must ensure that the specified inspection and modification are carried out within 50 hours of time in service after 31 October 1985 (subsection 105.019). This involves adhering to the procedures outlined in the Socata Service Letter, which includes meticulous examination of the battery tray and surrounding fuselage area to prevent potential structural damage caused by electrolyte spillage (subsection 105.020). The directive references French AD 85-130-(A) for additional guidance on the required modifications and inspection protocols (subsection 105.021). Failure to comply with the requirements of AD/TB20/5 can lead to serious consequences. If an operator or owner fails to inspect and modify the battery tray installation as mandated, they may face regulatory scrutiny and potential enforcement actions under the Civil Aviation Act 1988 (subsection 105.022). Non-compliance could result in penalties, including fines or other administrative actions, as stipulated by the Civil Aviation Regulations (subsection 105.023). Furthermore, continued operation of an aircraft without the necessary modifications could be deemed unsafe, potentially leading to more severe penalties or grounding of the aircraft until compliance is achieved (subsection 105.024).