COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Extra EA-300 Series Aeroplanes
AD/EXTRA/2 Wing Root Rib and Auxiliary Spar Attachment 5/95
Applicability: All Models.
Requirement: Visually inspect, using a borescope, the wing root rib and auxiliary spar for cracking. Inspect for delamination between the upper and lower skins and the wing root rib and auxiliary spar using the sonic or "coin tap" method. Inspect in accordance with Extra Service Bulletin (SB) 300-2-93, Issue B, Part I. Remove the auxiliary spar to fuselage attachment bolt. Visually inspect the fuselage auxiliary spar attachment fitting for cracks. Inspect in accordance with Extra SB 300-2-93, Issue B, Part II.
Note 1: German LBA AD 93-145 refers.
Compliance: Inspect before 250 hours time in service or before 25 hours time in service after 27 April 1995, whichever occurs last. Re-inspect thereafter at intervals not exceeding 100 hours time in service.
Background: Delamination and cracking has been experienced during the fatigue test.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, is an integral part of Australia's regulatory framework governing civil aviation safety. Enacted by the Commonwealth of Australia, these regulations were established to ensure that all civil aircraft meet stringent safety standards. The particular focus of the legislation in question is to address issues of structural integrity in Extra EA-300 Series aeroplanes, particularly concerning the wing root rib and auxiliary spar. This legislation was introduced to tackle the problem of delamination and cracking in these components, which have been observed during fatigue tests. The policy objective is to mandate regular and thorough inspections to prevent catastrophic failures, thereby enhancing overall aviation safety.
Compliance with these regulations is mandatory, requiring inspections to occur before the aircraft reaches 250 hours of service or 25 hours after a specified date, with subsequent inspections at intervals not exceeding 100 hours of service. This proactive approach aims to ensure that any delamination or cracking is identified and rectified promptly, thereby maintaining the structural integrity of the aircraft.
Scope and Application
The Civil Aviation Regulations 1998, under Part 39 - 105, specifically addresses the airworthiness of Extra EA-300 Series Aeroplanes with Airworthiness Directive AD/EXTRA/2, which pertains to the inspection of the wing root rib and auxiliary spar attachment. This regulation applies to all models of Extra EA-300 Series aeroplanes and mandates a thorough visual inspection of the wing root rib and auxiliary spar for cracking, as well as checking for delamination between the upper and lower skins and the wing root rib and auxiliary spar using sonic or "coin tap" methods. The directive requires compliance with Extra Service Bulletin (SB) 300-2-93, Issue B, Part I, and the removal of the auxiliary spar to fuselage attachment bolt to inspect the fitting for cracks, adhering to Extra SB 300-2-93, Issue B, Part II. This inspection must be completed before 250 hours of time in service or before 25 hours of time in service after 27 April 1995, whichever occurs last, and should be repeated at intervals not exceeding 100 hours of time in service. This regulation is part of the national framework overseen by the Civil Aviation Safety Authority, ensuring that all Extra EA-300 Series aeroplanes meet specific safety standards to prevent structural failures such as delamination and cracking.
Key Provisions
The main operative sections of the Civil Aviation Regulations 1998, specifically PART 39 - 105, mandate specific safety directives for the Extra EA-300 series aeroplanes. Section AD/EXTRA/2 outlines the requirement for detailed visual inspections of the wing root rib and auxiliary spar, as well as the fuselage auxiliary spar attachment. It requires the use of a borescope for a visual inspection to detect any cracking, and a sonic or "coin tap" method to check for delamination between the upper and lower skins and the wing root rib and auxiliary spar. The regulations mandate that these inspections be carried out in accordance with the Extra Service Bulletin (SB) 300-2-93, Issue B, Part I and Part II. Additionally, the auxiliary spar to fuselage attachment bolt must be removed to visually inspect the fuselage auxiliary spar attachment fitting for cracks.
The obligations and requirements imposed by this legislation are stringent and precise. Operators of Extra EA-300 series aeroplanes must adhere to a strict inspection schedule. The initial inspection must be performed before the aeroplane accumulates 250 hours of time in service or 25 hours of time in service after 27 April 1995, whichever occurs last. Following this initial inspection, subsequent inspections must be conducted at intervals not exceeding 100 hours of time in service. These inspections are crucial to ensuring the safety of the aircraft and its passengers, as they are designed to detect and prevent potential structural issues such as delamination and cracking.
Failure to comply with the stipulated inspection requirements can result in significant legal consequences. The Civil Aviation Regulations 1998 enforce strict penalties for non-compliance with the specified directives. While the exact penalties are not explicitly stated in the text, it is implied that breaches of these safety regulations could lead to enforcement actions by the Civil Aviation Safety Authority (CASA). Such actions might include fines, the grounding of the aircraft, or other regulatory measures to ensure that the aircraft meets the necessary safety standards. The overarching intent of these provisions is to maintain the highest safety standards in civil aviation, ensuring the integrity and reliability of Extra EA-300 series aeroplanes.