AD/PC-12/17 - Windshield Heat Wiring

Overview

The Civil Aviation Regulations 1998, specifically the legislative instrument F2006B06080, addresses issues related to the airworthiness of Pilatus PC-12 series aeroplanes. Enacted by the Australian Government, this legislation aims to ensure the safety and reliability of aircraft by implementing specific directives. One such directive, AD/PC-12/17, focuses on the modification of electrical wiring in Pilatus PC-12 and PC-12/45 aeroplanes to prevent overheating of the windshield de-ice system. This directive was introduced to address the risk of total electrical power loss in the aircraft, as identified by reports of overheating in the electrical components of the windshields. The directive mandates compliance before further flight and became effective on 28 June 1999, aligning with international standards set by the Federal Office of Civil Aviation (FOCA) in Switzerland. The policy objective behind this legislative instrument is to maintain the highest safety standards in civil aviation by ensuring all aircraft comply with necessary airworthiness directives. By enacting these regulations, the Australian Government reinforces its commitment to protecting the safety of passengers and crew, as well as maintaining the integrity of the national airspace. This approach is crucial for the continued operation and reliability of commercial and private aviation within Australia.

Scope and Application

The Civil Aviation Regulations 1998, specifically PART 39 - 105 pertaining to the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, includes a directive concerning the Pilatus PC-12 series aeroplanes. AD/PC-12/17 focuses on the windshield heat wiring of all Model PC-12 and PC-12/45 aeroplanes with Manufacture’s Serial Numbers ranging from 101 to 320, which are equipped with specific windshields identified by Pilatus Part Numbers 959.81.10.107 LH and 959.81.10.108 RH. The affected windshields are characterised by the presence of three embedded temperature sensors on the outboard edge. This directive mandates a modification to the electrical wiring in line with Pilatus PC-12 Service Bulletin 30-005 and references FOCA Switzerland AD HB 99-347. Compliance with this directive requires the modification to be completed before further flight, and it became effective on 28 June 1999. The directive aims to address reported incidents of overheating in the windshield de-ice system's electrical power supply and temperature sensor wires, which could otherwise lead to a complete loss of electrical power in the aircraft. The directive applies nationally across Australia and is enforced by the Civil Aviation Safety Authority.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, establish the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives. Within this framework, AD/PC-12/17 pertains to Pilatus PC-12 series aeroplanes, focusing on the windshield heat wiring. The directive (sections 1-4) applies to all Model PC-12 and PC-12/45 aeroplanes with Manufacture’s Serial Numbers ranging from 101 to 320, provided they are equipped with windshields identified by Pilatus Part Numbers (P/N) 959.81.10.107 LH and 959.81.10.108 RH, or PPG P/N NP 172121-5 LH and NP172121-6 RH. These windshields can be distinguished by the presence of three embedded temperature sensors on the outboard edge. The directive mandates that the electrical wiring be modified in accordance with Pilatus PC-12 Service Bulletin 30-005. Compliance with this directive is essential before any further flight, and the directive became effective on 28 June 1999. The obligations imposed by AD/PC-12/17 require operators and owners of affected Pilatus PC-12 series aeroplanes to ensure that the electrical wiring modification is performed as specified in the Pilatus Service Bulletin 30-005. This involves a thorough inspection and, if necessary, the replacement or repair of the wiring to prevent overheating of the de-ice system electrical power supply and temperature sensor wires. This modification is critical to avert potential total loss of electrical power, which could compromise flight safety. Operators must document the compliance with this directive in the aircraft's maintenance records and ensure that all modifications are completed by certified personnel. Failure to comply with AD/PC-12/17 can result in serious consequences. Under the Civil Aviation Regulations 1998, non-compliance can lead to civil penalties. The specific penalties for violating this directive can include substantial fines and, in severe cases, the grounding of the affected aircraft until compliance is achieved. Additionally, operators may face scrutiny and potential legal action from CASA if they fail to adhere to the requirements, which could further result in reputational damage and financial losses. The severity of the penalty often depends on the degree of non-compliance and the impact on aviation safety.