AD/PC-6/43 - Aileron Attachment Bracket

Overview

The Civil Aviation Regulations 1998, enacted by the Australian Parliament, provide a comprehensive framework for regulating civil aviation activities within Australia. This legislation, under Part 39, specifically addresses airworthiness directives to ensure that aircraft meet necessary safety standards. One such directive, AD/PC-6/43, was introduced to address the identified issue of cracks in the aileron attachment brackets of the Pilatus Porter PC-6 Series Aeroplanes. This problem was found to stem from fatigue due to overspeeding and harsh manoeuvring at high speeds, posing a safety risk. The directive mandates that modifications to the aileron/flap mountings must be made in accordance with Pilatus Service Bulletin No. 138, Rev. 2, and compliance is required within 100 hours of time in service from the directive's effective date of 27 March 1997. This legislative measure aims to enhance the overall safety and reliability of these aircraft in Australian airspace. The policy objective behind this specific airworthiness directive is to mitigate the risk of in-flight structural failure by ensuring that the identified design flaw is rectified promptly. By aligning with international safety standards, as referenced by the Swiss Federal Office of Civil Aviation's AD HB 84-023, the directive underscores a commitment to maintaining high safety benchmarks in civil aviation. The requirement for timely compliance ensures that aircraft operators are aware of and address the critical safety issue, thereby protecting both passengers and crew from potential hazards associated with the identified defect.

Scope and Application

The Civil Aviation Regulations 1998, as amended, govern various aspects of civil aviation within Australia and its territories, ensuring compliance with international standards and maintaining airworthiness. Specifically, Part 39 - 105 of the Regulations pertains to Airworthiness Directives, which mandate certain modifications and inspections to ensure the safe operation of aircraft. This legislative instrument applies to Pilatus Porter PC-6 Series aeroplanes, specifically those up to Serial No. 815. The regulation requires the modification of aileron/flap mountings in accordance with Pilatus Service Bulletin No. 138, Revision 2, due to the identified issue of cracks in the angle brackets that form the attachment of the aileron flap mountings. These cracks, attributed to fatigue resulting from overspeeding and harsh manoeuvring at high speeds, necessitate prompt compliance. The directive becomes effective from 27 March 1997, and compliance must be achieved within 100 hours of time in service from this date. The directive aligns with Swiss FOA AD HB 84-023, indicating a coordinated international approach to addressing this safety concern. The regulation applies nationally across Australia, overseen by the Civil Aviation Safety Authority, and is not limited to specific regions or entities but rather to the specified model and serial numbers of the aircraft in question.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, under the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, include a directive for Pilatus Porter PC-6 Series Aeroplanes, designated AD/PC-6/43. This directive, dated 4/97, pertains to the modification of aileron/flap mountings as per Pilatus Service Bulletin (SB) No. 138, Rev. 2, and references Swiss FOA AD HB 84-023. This directive applies to Pilatus PC-6 Porter / Turbo Porter aircraft up to serial number 815. It requires the modification of aileron/flap mountings to address cracks found in the angle brackets, which have been attributed to fatigue due to overspeeding and harsh manoeuvring of the aircraft at high speeds. Under this directive, the applicable aircraft must undergo the specified modifications to their aileron/flap mountings within 100 hours of time in service from the effective date of the directive, which is 27 March 1997. This requirement ensures that the modifications are implemented in a timely manner to mitigate the risk of structural failure due to the identified fatigue cracks. The directive mandates adherence to the procedures outlined in Pilatus Service Bulletin No. 138, Revision 2, to ensure that the modifications are carried out correctly and safely. Failure to comply with this directive may result in the aircraft being deemed unairworthy, thereby preventing its operation until the required modifications are completed. The obligations imposed by this Airworthiness Directive are significant for aircraft operators and maintenance personnel. Operators must ensure that the specified modifications are completed within the stipulated timeframe, and maintenance personnel must be trained and competent to carry out the modifications as per the service bulletin. Documentation of the modifications must be maintained in the aircraft's logbook to demonstrate compliance with the directive. Additionally, the directive mandates that the aircraft cannot be returned to service until the required modifications have been completed and verified by an authorised inspector. Failure to comply with this Airworthiness Directive may result in severe consequences. Under the Civil Aviation Act 1988, non-compliance can lead to civil penalties, including fines and potential prosecution. The maximum penalty for each offence can be significant, reflecting the serious nature of airworthiness issues. Additionally, the aircraft may be grounded and cannot be operated until the required modifications are completed and verified, which can have substantial operational and financial implications for the operator. In cases of severe non-compliance, criminal charges may be brought against the operator or responsible individuals, leading to further penalties and legal repercussions.