COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-24 (Comanche) Series Aeroplanes
AD/PA-24/41
Amdt 2
Wing Inspection for Fatigue Cracking 12/91
Applicability: All model PA-24 Model PA-24-250 S/N 24-1 and subsequent Model PA-24-260 S/N 24-3642, 24-4000 and subsequent Model PA-24-400 S/N 26-1 and subsequent.
Requirement: Modify the wing skin and visually inspect the left and right wing lower main spar caps and upper main spar attachment plate, in accordance with the Technical Requirements of FAA Emergency Airworthiness Directive 82-19-01 Piper dated 3 September 1982.
Note: The FAA rescinded AD 82-19-01 on 27 April 1988 and no longer supplies copies . A copy of this document is available, free of charge from Manager, Airworthiness and Operations Branch, Civil Aviation Authority, GPO Box 367,CANBERRA ACT 2601.
Compliance: At intervals not exceeding 100 hours time in service. This Directive was originally issued in June 1984. This amendment, which is issued for clarification only and does not affect compliance times, is effective from 12 December 1991.
Background: This requirement is based upon a FAA Directive issued to prevent the possibility of catastrophic wing failure associated with fatigue damage. Amendment 1 to this Directive clarified that the inspection is repetitive. Amendment 2 clarifies that the inspections must be continued for Australian registered aircraft (even though AD 82- 19-01 has been withdrawn by the FAA), because the possibility of fatigue cracking still exists.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, address the regulation of airworthiness directives to ensure the safety of aircraft operating within Australia. Enacted by the Commonwealth of Australia, these regulations were introduced to fill the gap in ensuring that aircraft meet the necessary safety standards, particularly in light of the risks associated with fatigue cracking in specific aircraft models. The policy objective of these regulations is to mandate regular inspections and modifications to prevent catastrophic failures, as demonstrated by the Airworthiness Directive AD/PA-24/41 Amendment 2 concerning Piper PA-24 (Comanche) series aeroplanes. This amendment, issued to clarify the ongoing necessity of wing inspections despite the withdrawal of the corresponding Federal Aviation Administration directive, underscores a commitment to maintaining stringent safety protocols to protect both crew and passengers.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the Airworthiness Directives for various aircraft types, including the Piper PA-24 (Comanche) Series Aeroplanes, as detailed in AD/PA-24/41 Amendment 2. This regulation applies to all model PA-24 aircraft, including the PA-24-250 series with serial numbers starting from 24-1, the PA-24-260 series with serial numbers 24-3642 and subsequent, and the PA-24-400 series with serial numbers 26-1 and subsequent. The requirement mandates modifications to the wing skin and visual inspections of the left and right wing lower main spar caps and upper main spar attachment plates, following the technical requirements outlined in the FAA Emergency Airworthiness Directive 82-19-01 Piper dated 3 September 1982. Compliance with these inspections must occur at intervals not exceeding 100 hours of time in service, ensuring the safety and airworthiness of these aircraft. Despite the FAA rescinding AD 82-19-01 on 27 April 1988, Australian regulations continue to enforce these inspections, reflecting ongoing concerns about the potential for fatigue cracking.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39 - 105, specifically address the airworthiness directives for Piper PA-24 (Comanche) series aeroplanes. One key provision is AD/PA-24/41 Amendment 2, which pertains to the wing inspection for fatigue cracking (Section 12/91). This directive applies to all model PA-24 aircraft with specific serial numbers: PA-24-250 starting from serial number 24-1, PA-24-260 starting from serial number 24-3642 and 24-4000 onwards, and PA-24-400 starting from serial number 26-1 and onwards (Section 12/91). The requirement is to modify the wing skin and visually inspect the left and right wing lower main spar caps and upper main spar attachment plate, following the technical requirements outlined in the FAA Emergency Airworthiness Directive 82-19-01 Piper dated 3 September 1982. Although the FAA rescinded AD 82-19-01 on 27 April 1988, a copy of this directive can be obtained from the Manager, Airworthiness and Operations Branch, Civil Aviation Authority, GPO Box 367, Canberra ACT 2601.
The Act imposes several obligations on the parties or entities governed by these regulations. Aircraft owners, operators, and maintenance personnel must ensure that the specified modifications and inspections are carried out at intervals not exceeding 100 hours of time in service. This ongoing requirement is essential to maintain the airworthiness of the aircraft and prevent potential catastrophic wing failure due to fatigue damage. Compliance with these airworthiness directives is mandatory, and failure to adhere to these provisions can result in severe safety implications.
In terms of potential breaches and consequences, the Civil Aviation Regulations 1998 outline that non-compliance with airworthiness directives can lead to various civil and criminal penalties. While the specific maximum penalties are not detailed in the provided text, it is clear that such violations can have serious repercussions. Civil penalties may include fines and other administrative actions, while criminal penalties could involve imprisonment, depending on the severity and impact of the non-compliance. These measures underscore the importance of adhering to the regulations to ensure the safety and integrity of civil aviation operations.