AD/PC-6/31 - Wing Strut Internal Corrosion - Inspection

Overview

The Civil Aviation Regulations 1998, specifically within Part 39, includes Airworthiness Directives to ensure the safety of aircraft operations in Australia. The regulation in question, AD/PC-6/31, addresses the issue of internal corrosion in the wing struts of Pilatus Porter PC-6 Series aeroplanes. This directive was enacted to mitigate risks associated with structural integrity due to corrosion, which could potentially compromise the safety of these aircraft. The regulation applies to all models of the Pilatus Porter PC-6 Series except those produced by Fairchild Hiller. Compliance with this directive requires inspections to be conducted within 100 hours of time in service after 31 August 1971 and at intervals not exceeding 100 hours thereafter, as outlined in Pilatus Service Bulletin No. 105. This legislative instrument is designed to uphold safety standards and ensure that aircraft maintain their airworthiness as mandated by the Civil Aviation Safety Authority.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105, apply to all Pilatus Porter PC-6 Series Aeroplanes, with the exception of those produced by Fairchild Hiller, requiring an inspection for wing strut internal corrosion. This legislation mandates that all applicable aircraft models must undergo a thorough inspection within 100 hours of time in service following 31 August 1971, and subsequently at intervals not exceeding 100 hours of time in service. This requirement is intended to ensure the continued airworthiness of these aircraft by addressing potential structural integrity issues. The compliance with these directives is to be evidenced by referencing Pilatus Service Bulletin No. 105, ensuring adherence to the specified maintenance schedule. While this regulation is comprehensive in its scope for the designated aircraft models, it does not extend to the Fairchild Hiller-produced variants, thereby excluding them from the mandatory inspection requirements.

Key Provisions

The main operative sections of the Civil Aviation Regulations 1998, specifically Part 39 - 105, establish detailed requirements for ensuring the airworthiness of Pilatus Porter PC-6 Series aeroplanes, particularly regarding the inspection of wing strut internal corrosion. Section 39-105.7/71 specifies that these provisions apply to all models of the Pilatus Porter PC-6 Series, except those produced by Fairchild Hiller. Compliance with these directives is crucial to maintaining the safety and operational integrity of these aircraft. The regulations mandate that inspections for internal corrosion of the wing struts be conducted within 100 hours of time in service after 31 August 1971, and then at intervals not exceeding 100 hours of time in service thereafter. This is to be done in accordance with Pilatus SB No. 105, which provides the necessary guidance and procedures for these inspections. The obligations imposed on the operators and owners of the Pilatus Porter PC-6 Series aeroplanes are stringent and clear. They must ensure that the aircraft undergo the specified inspections for wing strut internal corrosion as outlined in the regulation. This means that every 100 hours of flight time, operators must conduct a thorough inspection of the wing struts to detect any signs of internal corrosion. The inspection must be performed by qualified personnel and documented in accordance with the procedures set forth in Pilatus SB No. 105. Failure to comply with these inspection intervals and procedures could compromise the airworthiness of the aircraft, potentially leading to safety risks. Failure to adhere to the requirements of the Civil Aviation Regulations 1998 can result in significant consequences. Under Section 97 of the Civil Aviation Act 1988, non-compliance with airworthiness directives can be considered an offence. The penalties for such breaches can be severe, with maximum fines of up to $21,000 for individuals and $105,000 for corporations. Furthermore, continued non-compliance may result in the suspension or revocation of the aircraft's certificate of airworthiness, which could ground the aircraft and prevent it from being flown until the required inspections are completed and any identified issues are rectified. This not only poses a risk to the safety of passengers and crew but also carries potential legal ramifications for the operators and owners of the aircraft.