AD/BO 105/14 - Dual Hydraulic System Switch Over

Overview

The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, address the need for stringent aviation safety standards to ensure the integrity and reliability of aircraft operations. Part 39 - 105, pertaining to the Civil Aviation Safety Authority Schedule of Airworthiness Directives, specifically targets the maintenance and operational safety of aircraft, such as the Eurocopter BO 105 Series Helicopters. This regulation was introduced to address critical safety concerns, particularly the potential for excessive wear in the servo connecting components of the hydraulic systems, which could compromise the functionality of the hydraulic system switch over. The policy objective is to mandate compliance with specific maintenance protocols to prevent operational failures and ensure the safety of all personnel and passengers involved in aviation activities. The regulation under discussion, AD/BO 105/14, requires all BO 105 helicopters equipped with certain tandem hydraulic units to undergo a functional test of the hydraulic system switch over. This requirement is to be executed in accordance with MBB Alert Service Bulletin No ASB-BO 105-40-102, with compliance mandated within 50 hours of time in service after 25 August 1989 or by 30 September 1989, whichever comes first. This directive ensures that identified safety risks are mitigated promptly, aligning with the overarching goal of maintaining high safety standards within the civil aviation sector.

Scope and Application

The Civil Aviation Regulations 1998, specifically PART 39 - 105 under the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, applies to all model BO 105 helicopters with tandem hydraulic units P/N 105-45028 that have specific valve body manifolds installed in either No. 1 or 2 hydraulic systems. This regulation is applicable across the Commonwealth of Australia and mandates compliance with the action outlined in MBB Alert Service Bulletin No ASB-BO 105-40-102. The requirement is for a functional test of the hydraulic system switch over to address potential excessive wear in the servo connecting components. Compliance must be achieved within 50 hours of time in service after 25 August 1989, or by 30 September 1989, whichever is sooner. This directive ensures that all affected helicopters meet the specified safety standards to maintain airworthiness. The regulation does not specify any exclusions or exemptions, and its application is direct without the need for subordinate instruments to extend or restrict its scope.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, details various airworthiness directives applicable to different aircraft, including the Eurocopter BO 105 series helicopters. This legislative instrument (F2006B04803) mandates that all model BO 105 helicopters equipped with tandem hydraulic units P/N 105-45028 and specific valve body manifolds (D133-756E, D133-756, ZE1-126-1, ZE2-126-1, or ZE2-126) must adhere to certain safety directives. The directive in question is AD/BO 105/14, which pertains to the "Dual Hydraulic System Switch Over" and was issued on 10 August 1989. This directive mandates that operators must comply with MBB Alert Service Bulletin No ASB-BO 105-40-102 to address potential issues with excessive wear in the servo connecting components. Operators of the affected helicopters are required to conduct a functional test of the hydraulic system switch over as outlined in the aforementioned service bulletin. This action must be completed within a specified timeframe: within 50 hours of time in service after 25 August 1989 or by 30 September 1989, whichever comes first. Compliance with this directive is critical to maintaining the airworthiness of the aircraft, as referenced in LBA AD 89-123. Failure to comply with these provisions could result in significant safety risks, including potential hydraulic system failures during flight, which could compromise the safety of the aircraft and its occupants. The obligations imposed by this directive are clear and specific. Operators must ensure that the functional test of the hydraulic system switch over is performed by qualified personnel following the procedures detailed in MBB Alert Service Bulletin No ASB-BO 105-40-102. This involves detailed checks and potentially making repairs or adjustments to the servo connecting components to mitigate the risk of excessive wear. The directive also mandates that these actions are completed within the prescribed timeframe to ensure that the aircraft remains airworthy and compliant with regulatory standards. Additionally, operators are responsible for documenting the completion of the required tests and any actions taken, as this documentation may be required for audits or inspections by the Civil Aviation Safety Authority (CASA). Failure to comply with the provisions of this directive can have serious legal and safety implications. Under the Civil Aviation Act 1988 and the Civil Aviation Regulations 1998, non-compliance with an airworthiness directive can result in enforcement actions, including fines and potential criminal charges. The severity of the penalties depends on the nature and extent of the non-compliance, but the maximum penalties can be substantial. For example, individuals or corporations found guilty of non-compliance with airworthiness directives can face fines of up to $210,000 and imprisonment for up to two years. Furthermore, CASA can take additional actions such as grounding the aircraft, imposing operational restrictions, or revoking the aircraft's certificate of airworthiness, all of which can have significant financial and operational consequences for the operator.