COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
British Aerospace BAe 146 Series Aeroplanes
AD/BAe 146/14 Electric Flap Control Unit 8/89
Applicability: All series 100 and 100A aircraft constructors number E1002 and subsequent. All series 200 and 200A aircraft constructors number E2012 and subsequent. All series 300 and 300A aircraft constructors number E3118 and subsequent.
Requirement: 1. Action in accordance with BAe Mandatory Service Bulletin 11-36-01104A and B.
2. Action in accordance with BAe Mandatory Service Bulletin 27-95-70420A. Compliance: Requirement 1 prior to 10 October 1989. Requirement 2 prior to 10 May 1990. Background: These modifications are intended to:
deter flight crew from removing or re-racking the flap system E.C.U. or pulling associated circuit breakers in light and thus endangering the aircraft during a legitimate flap system fault condition.
overcome spurious warnings caused by slow start-ups after prolonged cold soak conditions.
overcome the need to provide additional warning against re-racking in flight.
overcome the need to reduce the computer lightning susceptibility to an approved level.
Overview
The Civil Aviation Regulations 1998, amended by the legislative instrument F2006B03468, address the critical issue of ensuring the airworthiness of British Aerospace BAe 146 Series aeroplanes, particularly concerning their electric flap control units. Enacted by the Australian Parliament, the policy objective behind this legislation is to enhance safety and reliability in aviation, thereby protecting the lives of passengers and crew. This legislative instrument introduces specific airworthiness directives that require certain modifications to the electric flap control units of BAe 146 aircraft series, aimed at preventing dangerous actions by flight crews and mitigating issues such as spurious warnings, cold soak conditions, and lightning susceptibility. These measures are designed to ensure that the aircraft remain safe and operationally reliable, thereby maintaining high standards of civil aviation safety.
Scope and Application
The Civil Aviation Regulations 1998, as outlined in Part 39 - 105 of the Commonwealth of Australia's Civil Aviation Safety Authority Schedule of Airworthiness Directives, specifically addresses British Aerospace BAe 146 Series Aeroplanes through AD/BAe 146/14 Electric Flap Control Unit. This regulation applies to all series 100 and 100A aircraft with constructors number E1002 and subsequent, as well as series 200 and 200A aircraft with constructors number E2012 and subsequent, and series 300 and 300A aircraft with constructors number E3118 and subsequent. The Act mandates that modifications be carried out in accordance with BAe Mandatory Service Bulletins 11-36-01104A and B, and 27-95-70420A, with compliance required by specific dates: Requirement 1 must be completed prior to 10 October 1989, and Requirement 2 prior to 10 May 1990. The purpose of these modifications is to deter flight crew from interfering with the flap system E.C.U. or pulling associated circuit breakers during a legitimate flap system fault condition, to overcome spurious warnings caused by slow start-ups after prolonged cold soak conditions, and to reduce computer lightning susceptibility to an approved level. This regulation extends across the Commonwealth, applying nationally and ensuring that all specified aircraft meet the outlined safety standards.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105 (subsection 39-105), details the Airworthiness Directives (AD) for the British Aerospace BAe 146 Series Aeroplanes. This section mandates actions for ensuring the safety of certain aircraft models, namely series 100 and 100A with constructors numbers E1002 and subsequent, series 200 and 200A with constructors numbers E2012 and subsequent, and series 300 and 300A with constructors numbers E3118 and subsequent. The primary requirements (section 39-105(1)) are that these aircraft must undergo modifications as specified in British Aerospace's Mandatory Service Bulletins 11-36-01104A and B, and 27-95-70420A. These modifications must be completed by specific deadlines: Requirement 1 must be addressed before 10 October 1989, while Requirement 2 must be completed prior to 10 May 1990.
The obligations imposed by this legislation on the parties governed by it are substantial. Aircraft owners and operators must ensure that their BAe 146 Series Aeroplanes adhere to the specified modifications. This involves not only the physical modifications of the aircraft but also the compliance with the timelines provided. Failure to adhere to these requirements could result in the aircraft being deemed non-airworthy, thus preventing it from operating legally. The directive's intent is to mitigate risks associated with potential flight crew actions and to address technical issues such as spurious warnings, the risk of in-flight re-racking, and lightning susceptibility.
The consequences for non-compliance with these provisions are outlined within the regulations. While specific civil or criminal penalties are not detailed within the excerpt, non-compliance can lead to significant repercussions. These may include fines, the grounding of non-compliant aircraft, and potential criminal charges if the non-compliance results in safety breaches or accidents. The severity of penalties could escalate depending on the extent of non-compliance and its impact on aviation safety. The overarching aim is to ensure that all BAe 146 Series Aeroplanes are maintained to a standard that ensures the safety of flight operations and protects both the crew and passengers.