AD/DHC-3/33 - Wing Strut to Fuselage Tie Bar

Overview

The Civil Aviation Regulations 1998 (Cth), specifically Part 39, encompasses the Airworthiness Directives issued by the Civil Aviation Safety Authority. This regulatory framework ensures that all civil aircraft meet the necessary safety standards and are fit for operation. One such directive, AD/DHC-3/33, pertains to DHC-3 (Otter) series aeroplanes, addressing the issue of corrosion in the wing strut to fuselage tie bar. The directive was enacted to mitigate the risks associated with tie bar lugs and the internal channel section under the cabin floor, which have been found to corrode. This legislation was introduced by the Australian Government to ensure compliance with safety standards and prevent potential structural failures. The compliance requirement mandates action in accordance with de Havilland Canada Service Bulletin 3/37 Rev B and necessitates inspections and maintenance actions not exceeding 12 months prior to the initial issue of a Certificate of Airworthiness and thereafter at regular intervals. The Civil Aviation Regulations 1998, overseen by the Civil Aviation Safety Authority, aim to maintain the highest standards of aviation safety in Australia. This legislative instrument addresses specific issues identified in aircraft maintenance and operation, ensuring that any potential safety hazards are promptly identified and rectified. AD/DHC-3/33, in particular, references the need for rigorous inspection and maintenance procedures to prevent corrosion in critical components of DHC-3 (Otter) series aeroplanes. By mandating these actions, the legislation seeks to uphold the integrity and safety of these aircraft, thereby protecting passengers and crew, and ensuring the reliability of air transport services.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39, Section 105, mandates that all DHC-3 (Otter) series aeroplanes must comply with the airworthiness directives outlined in the legislation. This requirement applies universally to all models of the DHC-3 aircraft. The directive mandates that actions must be taken in accordance with de Havilland Canada Service Bulletin 3/37 Rev B, referencing the Canadian Airworthiness Directive CF-82-26. This compliance must be observed prior to the initial issue of a Certificate of Airworthiness and subsequently at intervals not exceeding twelve months. The background provided indicates that issues with tie bar lugs corroding and internal channel sections beneath the cabin floor have been identified, necessitating the adherence to these stringent regulations to ensure safety and airworthiness of the aircraft.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, includes the Civil Aviation Safety Authority Schedule of Airworthiness Directives for DHC-3 (Otter) Series Aeroplanes. Within this schedule, AD/DHC-3/33 pertains to the "Wing Strut to Fuselage Tie Bar" (section 13/87). This directive applies to all models of the DHC-3 aircraft series. The primary requirement of this directive is to take action in accordance with de Havilland Canada Service Bulletin 3/37 Revision B (section 13/87). Additionally, it references Canadian Airworthiness Directive CF-82-26 for further guidance. Compliance with this directive necessitates addressing the issue of corroded tie bar lugs and the internal channel section under the cabin floor prior to the initial issue of a Certificate of Airworthiness and subsequently at intervals not exceeding 12 months. Under the Civil Aviation Regulations 1998, the obligations imposed by AD/DHC-3/33 are clear and specific. Aircraft operators must ensure that the wing strut to fuselage tie bar is inspected and repaired or replaced as per the requirements outlined in de Havilland Canada Service Bulletin 3/37 Revision B. This involves a detailed examination of the tie bar lugs and the internal channel section under the cabin floor, which have been identified as prone to corrosion. Such inspections must occur before the aircraft is issued a Certificate of Airworthiness and must be repeated at regular intervals, not exceeding 12 months, to maintain the aircraft's airworthiness. Failure to comply with the provisions of AD/DHC-3/33 can lead to serious consequences. The Civil Aviation Regulations 1998 outline potential offences and penalties for non-compliance with airworthiness directives. If an operator fails to adhere to the requirements of AD/DHC-3/33, they could face civil penalties, which may include fines. Additionally, continued operation of an aircraft that does not meet these airworthiness standards could result in criminal charges. Under the Civil Aviation Act 1988, the maximum penalty for operating an aircraft that is not in a condition for safe flight could include substantial fines and imprisonment. Therefore, ensuring compliance with AD/DHC-3/33 is not only a regulatory requirement but also a critical safety measure to protect passengers and crew.