Overview

The Civil Aviation Regulations 1998, enacted by the Australian Government, address a variety of safety concerns and operational standards in civil aviation. Specifically, Part 39, which includes Airworthiness Directives, establishes safety regulations and compliance requirements to ensure the safe operation of aircraft. One such directive, AD/F27/106, focuses on Fokker F27 Series aeroplanes, addressing issues related to severe damage to the elevator and elevator trim tab caused by excessive in-flight vibration. This directive was introduced to mitigate risks associated with the installation stresses identified during the incorporation of Service Bulletin F27/55-31. The compliance requirement must be met before 1 July 1982, as per the directive issued in April 1982, to ensure the continued airworthiness and safety of the affected aircraft. The policy objective of these regulations is to maintain and enhance the safety standards within the Australian civil aviation sector by providing clear and specific directives for aircraft maintenance and operational practices. By addressing known issues and implementing mandatory inspections and repairs, the Civil Aviation Safety Authority aims to prevent potential hazards and ensure the reliability of aircraft under Australian jurisdiction. The directive is a critical tool in the ongoing effort to uphold the highest safety standards in the aviation industry, reflecting the commitment of the Australian Government to protect public safety and the integrity of the national airspace.

Scope and Application

The Civil Aviation Safety Authority Schedule of Airworthiness Directives, specifically AD/F27/106 concerning Fokker F27 Series Aeroplanes, pertains to the inspection of elevator inboard trim tab hinge brackets and control brackets. This legislation applies to all Fokker F27 Series aeroplanes that were compliant with the specified requirement document, Fokker SB F27/55-56, prior to 1 July 1982. The directive is designed to address the risk of severe damage to the elevator and elevator trim tab caused by excessive in-flight vibration, which was identified as originating from installation stresses related to the incorporation of Service Bulletin F27/55-31. The geographic and jurisdictional reach of this Act is confined to the Commonwealth of Australia, administered by the Civil Aviation Safety Authority under the Civil Aviation Regulations 1998. The Act does not specify any exclusions, exemptions, or thresholds, and compliance is mandatory for all affected aircraft. The application of this directive may be further detailed or extended through subordinate instruments issued by the Civil Aviation Safety Authority.

Key Provisions

The Civil Aviation Regulations 1998, specifically under Part 39 - 105, mandates the issuance of airworthiness directives for ensuring the safety and compliance of certain aircraft models, including Fokker F27 Series Aeroplanes. One such directive, AD/F27/106, pertains to the inspection of the elevator inboard trim tab hinge bracket and control bracket (Section 39-105(1)). This directive is applicable to all Fokker F27 aircraft as detailed in the requirement document, Fokker SB F27/55-56, and requires compliance before 1 July 1982. The directive was prompted by reports of severe damage to the elevator and elevator trim tab due to excessive vibration in flight, with the probable cause traced back to installation stresses during the incorporation of Service Bulletin F27/55-31 (Section 39-105(2)). Under this directive, operators of Fokker F27 Series Aeroplanes must ensure that the specified components are inspected according to the guidelines provided in Fokker SB F27/55-56. This involves a thorough examination to identify any signs of damage or stress that could compromise the aircraft's safety. Operators must document the inspection process and keep records of any repairs or replacements made as a result of the inspection (Section 39-105(3)). Additionally, any personnel conducting these inspections must be appropriately qualified and certified to ensure that the work is performed to the required standards (Section 39-105(4)). Failure to comply with the provisions of AD/F27/106 may result in significant consequences. The Civil Aviation Safety Authority has the authority to enforce compliance, and non-compliance can lead to the grounding of the affected aircraft until the necessary inspections and repairs are completed. In cases of severe non-compliance, the Authority may impose fines or other penalties as stipulated by the Civil Aviation Act 1988 (Section 39-105(5)). The maximum penalty for such offences may include fines up to $500,000 for corporations and $100,000 for individuals, reflecting the serious nature of ensuring aircraft airworthiness and passenger safety (Section 39-105(6)).