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 146/58 Landing Gear Brake Unit 1/97
Applicability: All BAe 146 and Avro 146-RJ aircraft fitted with Dunlop Carbon Brake Units which have a spacer installed.
Requirement: Inspect the brake unit and set the wear remaining length of the wear indicator pin in accordance with Dunlop Mandatory Service Bulletin No. 32-1105.
Note: British Aerospace Service Bulletin S.B. 32-142 refers.
Compliance: Prior to 4 March 1996.
Background: The manufacturer received reports that some brakes have worn excessively causing a number of failures of the pressure stator or the adjacent rotor on brakes which have a spacer installed. To prevent such failures, this service bulletin incorporates a new procedure to find and set the wear remaining length of the wear indicator pin.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, were enacted to regulate civil aviation safety in Australia. This legislative instrument, F2006B03508, was introduced to address the issue of excessive brake wear in British Aerospace BAe 146 Series Aeroplanes fitted with Dunlop Carbon Brake Units that had a spacer installed. The problem arose from reports of failures in the pressure stator or the adjacent rotor due to excessive brake wear, prompting the need for a revised procedure to inspect and set the wear remaining length of the wear indicator pin in accordance with Dunlop Mandatory Service Bulletin No. 32-1105. The policy objective is to ensure the airworthiness of these aircraft by preventing brake-related failures, thereby maintaining high safety standards in civil aviation.
Scope and Application
The Civil Aviation Regulations 1998, specifically under Part 39 - 105 and the Civil Aviation Safety Authority Schedule of Airworthiness Directives, mandate that all BAe 146 and Avro 146-RJ aircraft fitted with Dunlop Carbon Brake Units having a spacer installed must adhere to the requirements outlined in AD/BAe 146/58. This legislation applies to the aircraft's landing gear brake unit, mandating an inspection and the setting of the wear remaining length of the wear indicator pin according to Dunlop Mandatory Service Bulletin No. 32-1105. This directive is in response to reports of excessive brake wear that led to failures in the pressure stator or adjacent rotor. The compliance deadline for these requirements is set before 4 March 1996, ensuring that all affected aircraft meet the specified safety standards to prevent future failures. The regulation's scope is confined to Commonwealth aviation regulations, applying nationally across Australia, and it extends its reach to ensure the safety and reliability of the specified aircraft models.
Key Provisions
The Civil Aviation Regulations 1998, particularly Part 39, contains the Schedule of Airworthiness Directives (ADs), which are regulatory requirements for maintaining the airworthiness of specific aircraft. The AD in question (AD/BAe 146/58) pertains to the British Aerospace BAe 146 series aeroplanes and addresses the inspection and setting of the wear indicator pin in the landing gear brake unit for those fitted with Dunlop Carbon Brake Units and a spacer (section 1). This directive is applicable to all BAe 146 and Avro 146-RJ aircraft that meet the specified criteria (section 2). The requirement is to inspect the brake unit and set the wear remaining length of the wear indicator pin in accordance with Dunlop Mandatory Service Bulletin No. 32-1105 (section 3). The compliance date for this directive was set as prior to 4 March 1996 (section 4).
The obligations under this directive are specific and mandatory for aircraft operators. They must ensure that the inspection and setting of the wear indicator pin are carried out as per the guidelines in Dunlop Mandatory Service Bulletin No. 32-1105. This involves a thorough inspection of the brake units to determine the remaining length of the wear indicator pin and adjusting it to the specified parameters to prevent excessive wear and potential failures of the pressure stator or the adjacent rotor. Additionally, operators should refer to British Aerospace Service Bulletin S.B. 32-142 for further details or clarifications (section 5). Compliance with this directive is critical to maintaining the safety and airworthiness of the aircraft.
Failure to comply with the requirements outlined in this AD could result in serious safety risks, including potential in-flight failures of the brake system. While the Civil Aviation Regulations do not explicitly state offences or penalties for non-compliance with specific ADs, non-compliance can lead to enforcement actions by the Civil Aviation Safety Authority (CASA). The penalties for non-compliance can include fines, enforcement notices, and in severe cases, suspension or revocation of the aircraft’s certificate of airworthiness. These regulatory actions are designed to ensure that aircraft remain in a safe and airworthy condition, thereby protecting the safety of passengers, crew, and the general public.