COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-23 (Apache and Aztec) Series Aeroplanes
AD/PA-23/82 Flap Spar Hinge Attachment Areas - Inspection 4/81
Applicability: All models PA-23/PA23-160, PA23-235, PA-23-250 and PA-23-250 (6 place) with S/Nos. prior to 27-7405301.
Document: Piper SL No. 853.
Note: FAA AD 81-04-05 amendment 39-4040 also refers.
Compliance: Unless already accomplished, initially inspect within 100 hours time in service after achieving 2000 hours time in service since manufacture and thereafter at intervals not exceeding 100 hours time in service until modified in accordance with Piper SL 853.
Background: Reports have been received by the manufacturer of cracks forming in the flap spar and radiating from the hinge attachment areas.
Overview
The Civil Aviation Regulations 1998 (CAR 1998) were enacted to ensure the safety and regulation of civil aviation in Australia. Part 39, in particular, addresses various aspects of airworthiness, including the issuance of airworthiness directives to address safety concerns. The 1998 regulations were introduced to provide a comprehensive framework for the operation of civil aviation in Australia, ensuring that all aircraft meet the necessary safety standards. One such airworthiness directive, AD/PA-23/82, was issued to address the problem of cracks forming in the flap spar hinge attachment areas of Piper PA-23 (Apache and Aztec) series aeroplanes, which could potentially compromise the structural integrity of these aircraft. The policy objective of the CAR 1998 and associated directives is to enhance aviation safety by mandating regular inspections and necessary modifications to prevent such issues.
The AD/PA-23/82 directive was issued by the Civil Aviation Safety Authority (CASA) under the authority of the CAR 1998. It applies to all Piper PA-23 series aeroplanes with specific serial numbers and mandates inspections at specified intervals to detect and address any cracks in the flap spar hinge attachment areas. This directive is intended to mitigate the risk of in-flight failure due to structural weaknesses, thereby ensuring the continued safety of these aircraft. The directive references relevant documentation, such as Piper Service Letter 853 and FAA AD 81-04-05, to provide comprehensive guidance on the required inspections and modifications.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, applies to all Piper PA-23 series aeroplanes, including models PA23-160, PA23-235, PA-23-250, and PA-23-250 (6 place) with serial numbers prior to 27-7405301. The scope of this legislation is to mandate regular inspections of the flap spar hinge attachment areas to ensure the airworthiness of these aircraft. The directive stems from reports of cracks forming in the flap spar and radiating from the hinge attachment areas, posing a safety concern. Compliance with this regulation requires an initial inspection within 100 hours of time in service after the aircraft has accumulated 2000 hours since manufacture, followed by subsequent inspections at intervals not exceeding 100 hours until modifications as per Piper Service Letter 853 are implemented. This legislation is enforced by the Civil Aviation Safety Authority (CASA) under the Commonwealth of Australia and its reach is national, affecting all operators of the specified aircraft within Australia. The regulation does not specify any exclusions, exemptions, or thresholds beyond the aircraft models and serial numbers mentioned. The regulation’s application may also be extended or restricted through subordinate instruments issued by CASA.
Key Provisions
The Civil Aviation Regulations 1998, specifically in Part 39 - 105 under the Civil Aviation Safety Authority Schedule of Airworthiness Directives, contains detailed instructions concerning the maintenance and inspection of certain Piper PA-23 (Apache and Aztec) series aeroplanes. For instance, AD/PA-23/82 (Section 4/81) mandates a thorough inspection of the flap spar hinge attachment areas to detect any cracks that may form in these critical components. This directive applies to all models PA-23/PA23-160, PA23-235, PA-23-250 and PA-23-250 (6 place) with serial numbers (S/Nos.) prior to 27-7405301. The inspection protocol outlined in the document must be adhered to in accordance with Piper Service Letter (SL) No. 853, with additional reference to FAA AD 81-04-05 Amendment 39-4040.
Entities and operators governed by this legislation must comply with the outlined inspection requirements. Specifically, they must conduct an initial inspection within 100 hours of the aeroplane reaching 2000 hours of service since manufacture. Following this initial inspection, subsequent inspections must occur at intervals not exceeding 100 hours of time in service until the aeroplane is modified as per Piper SL 853. This ongoing inspection protocol is crucial for maintaining the structural integrity of the aeroplanes, particularly given the reported incidents of cracks in the flap spar and radiating from the hinge attachment areas.
Failure to comply with the inspection requirements stipulated in the Civil Aviation Regulations can lead to serious consequences. While the regulations do not explicitly state the exact penalties for non-compliance, breaches of airworthiness directives typically result in severe civil or criminal penalties under the Civil Aviation Act 1988. In the case of a violation, the Civil Aviation Safety Authority (CASA) may impose fines or other sanctions, and in more severe instances, the operator could face prosecution. The severity of the penalty would depend on the nature and extent of the breach, but the overarching goal is to ensure compliance to maintain the highest safety standards in civil aviation.