AD/PA-23/45 - Engine Control Support Bracket Assembly - Inspection

Overview

The Civil Aviation Regulations 1998, specifically Part 39 - 105, which pertains to the Civil Aviation Safety Authority Schedule of Airworthiness Directives, was enacted to ensure the continued safety and airworthiness of aircraft within Australia's airspace. One of the directives under this legislation is AD/PA-23/45, which addresses the inspection requirements for the engine control support bracket assembly of Piper PA-23 (Apache and Aztec) series aeroplanes. This directive was introduced to address specific safety concerns associated with the engine control support bracket assembly, ensuring that the aircraft meet stringent safety standards. The objective of this directive, as with other measures under the Civil Aviation Regulations, is to mitigate the risks associated with the identified problem, thereby enhancing the overall safety of civil aviation operations in Australia. The Civil Aviation Regulations 1998 were enacted by the Parliament of Australia and are administered by the Civil Aviation Safety Authority (CASA). The policy objective of AD/PA-23/45 is to ensure that the engine control support bracket assembly on the specified Piper PA-23 models is regularly inspected and maintained, thus preventing potential mechanical failures that could compromise the safety of the aircraft and its occupants. This directive mandates specific inspection intervals based on the total time in service of the aircraft, ensuring that all affected aircraft are inspected within a certain timeframe and at regular intervals thereafter.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 under the Civil Aviation Safety Authority, governs the airworthiness directives for Piper PA-23 (Apache and Aztec) series aeroplanes. This legislation applies to specific models of these aircraft, namely the PA-23 and PA-23-160 with serial numbers ranging from 23-1 to 23-1870, and the PA-23-250 with serial numbers from 27-1 to 27-140. The regulation mandates inspections of the engine control support bracket assembly, as outlined in Piper Service Bulletin No. 335. The compliance requirements are structured based on the total time in service of the aircraft; for those with more than 2000 hours of service as of 21 June 1971, inspections must occur within 25 hours of service and then at intervals not exceeding 100 hours. Conversely, for aircraft with less than 200 hours of service, inspections must take place within 50 hours of service following 21 June 1971, with subsequent inspections at intervals not exceeding 100 hours. The regulation’s scope and application ensure that all affected aircraft maintain their airworthiness through regular and systematic inspections.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, provides detailed requirements for the airworthiness of certain aircraft models under the Civil Aviation Safety Authority (CASA) schedule. In this case, the legislation focuses on the Piper PA-23 (Apache and Aztec) series aeroplanes, as outlined in AD/PA-23/45. This particular airworthiness directive (AD) mandates inspections of the engine control support bracket assembly, which is detailed in Piper Service Bulletin No. 335. The directive applies to specific serial number ranges of the Piper PA-23 and PA-23-250 models, ensuring that these aircraft maintain their airworthiness standards through regular and specified inspections. The main provisions of this AD (AD/PA-23/45) require that aircraft meeting the specified serial numbers undergo inspections of the engine control support bracket assembly. For aircraft that have accumulated more than 2000 hours of total time in service as of 21 June 1971, the inspection must be carried out within 25 hours of time in service following this date, and then at intervals not exceeding 100 hours thereafter (section 1). For aircraft with less than 200 hours of total time in service as of 21 June 1971, the inspection must occur within 50 hours of time in service following this date, and then at intervals not exceeding 100 hours thereafter (section 2). These timeframes and intervals are critical to ensuring that the engine control support bracket assembly remains in a safe and operational condition. Operators and owners of the affected Piper PA-23 and PA-23-250 series aircraft are obligated to comply with these inspection requirements. This includes conducting the initial inspection within the stipulated timeframe, and subsequent inspections at the specified intervals. Non-compliance with these requirements can result in the aircraft being deemed unairworthy, which could lead to grounding and potential legal consequences. Additionally, the AD mandates that all findings from inspections are properly documented and retained for regulatory review, ensuring transparency and accountability in maintaining the aircraft's airworthiness. Failure to comply with the inspection requirements set out in AD/PA-23/45 can result in serious consequences. While the specific penalties for non-compliance are not detailed in the text, general provisions within the Civil Aviation Regulations 1998 could include fines, enforcement actions, and potential grounding of the aircraft. In severe cases, non-compliance might lead to criminal charges if it is determined that the failure to inspect or rectify issues has resulted in a breach of safety regulations, leading to potential harm or accidents. Therefore, adherence to these inspection requirements is not only a regulatory obligation but also a critical safety measure to protect passengers and crew.