AD/CESSNA 206/44 - Electrical Power Distribution and Control

Overview

The Civil Aviation Regulations 1998, specifically under Part 39 - 105 of the Civil Aviation Safety Authority Schedule of Airworthiness Directives, includes AD/CESSNA 206/44 pertaining to the electrical power distribution and control of certain Cessna 206 Series aeroplanes. This legislation was enacted to address issues of electrical interference and system redundancy in specified Cessna 206G models, particularly those modified under U.S. Turbine Conversion. The Civil Aviation Safety Authority, through the Australian Government, introduced this directive to ensure the safety and reliability of the electrical systems in these aircraft, thereby reducing the risk of erroneous bearing information and system failures during critical operations. The policy objective behind AD/CESSNA 206/44 is to mitigate the risks associated with the existing voltage regulator interfering with the Automatic Direction Finder (ADF) system and to enhance system redundancy by separating the engine start and auto feather circuits. The directive requires compliance with specific modifications within a defined timeframe post the issuance date of 31 August 1986, ensuring that these safety improvements are implemented to maintain the airworthiness of the affected aircraft.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 concerning Airworthiness Directives, applies to all Cessna Model U206G aeroplanes and those modified in accordance with U.S. Turbine Conversion under FAA STC SA2353NM. This regulation mandates specific serial numbers, listed in the schedule, to comply with the directives regarding the electrical power distribution and control systems. The regulation is issued by the Civil Aviation Safety Authority and applies on a national level throughout Australia. The primary requirement is the replacement of the voltage regulator in accordance with Soloy Service Bulletin 04-763, which must be completed within 100 hours of the aeroplane being in service after 31 August 1986. For certain specified serial numbers, an additional requirement to modify the electrical system circuit breaker installation in accordance with Soloy Service Bulletin 02-763 must be completed within 200 hours of the aeroplane being in service after the same date. This directive is instrumental in ensuring the safe operation of these specific aircraft models by addressing known issues with the electrical systems.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, contains an Airworthiness Directive (AD) AD/CESSNA 206/44 which pertains to the Cessna 206 Series aeroplanes, particularly those identified by their serial numbers and Soloy data plate numbers. This directive addresses the electrical power distribution and control issues within these aeroplanes (AD/CESSNA 206/44, 8/86). The directive applies to all Cessna Model U206G and FAA STC SA2353NM (Soloy numbers: TU206G) aeroplanes that have been modified in accordance with the U.S. Turbine Conversion. The affected serial numbers are listed in the directive, with specific Soloy data plate numbers also noted. The primary requirements of this directive are twofold. Firstly, the voltage regulator must be replaced in accordance with Soloy Service Bulletin 04-763. Secondly, for a subset of aeroplanes with specific serial numbers, the electrical system circuit breaker installation must be modified in accordance with Soloy Service Bulletin 02-763. It is also noted that FAA AD 86-11-07 Amendment 39-5324 is relevant to this directive. Compliance with these requirements is to be achieved within certain timeframes. For the replacement of the voltage regulator, compliance is required within 100 hours of time in service after 31 August 1986. For the modification of the electrical system circuit breaker installation, compliance is required within 200 hours of time in service after 31 August 1986. Entities governed by this directive, including owners and operators of the specified Cessna 206 Series aeroplanes, have specific obligations. These obligations include ensuring that the voltage regulator is replaced and, for the specified serial numbers, that the electrical system circuit breaker installation is modified as per the referenced service bulletins. These obligations are critical to maintaining the airworthiness and safety of the aircraft. Failure to comply with these requirements can result in serious safety issues, including the potential for erroneous bearing information to be displayed and the simultaneous inoperativeness of both the engine start and auto feather circuits in the event of an electrical fault or pilot action. Failure to comply with the directives outlined in AD/CESSNA 206/44 may result in both civil and criminal consequences. While the specific civil penalties are not detailed in the text, non-compliance with airworthiness directives can generally lead to penalties under the Civil Aviation Act 1988. Criminal penalties may also apply, depending on the severity of the breach and the impact on aviation safety. The maximum penalties for breaches of civil aviation regulations can include substantial fines and, in severe cases, imprisonment. The specific penalties would be determined based on the circumstances of the breach and any resulting harm or endangerment.