COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Grumman G21 (Goose) Series Aeroplanes
AD/G21/1 Below Floor Control System Components - Inspection
10/77
Applicability: All models.
Requirement: 1. Remove and disassemble:
(i) Elevator Torque Tube Assembly P/N 12755,
(ii) Rudder Torque Tube Assembly P/N 12756,
(iii) Rudder Pedal Torque Tube Assembly LH and RH P/N 12757 and 12758,
(iv) Hinge Support Assembly P/N 12725.
2. Inspect all parts for corrosion and/or cracks using visual and dye penetrant or magnetic particle techniques.
Note: FAA AD 73-12-6 Amendment 39-1657 refers.
Compliance: Initially before issue of Certificate of Airworthiness and there- after at intervals not exceeding 2000 hours time in service or two years whichever occurs first.
Overview
The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, form a comprehensive regulatory framework governing various aspects of civil aviation operations within Australia. Specifically, Part 39 - 105 addresses the authority's schedule of airworthiness directives, which are critical for ensuring the safety and reliability of aircraft. This regulatory approach was introduced to address safety concerns and fill gaps in existing aviation safety standards, aiming to maintain high safety benchmarks in the Australian aviation sector. The Civil Aviation Safety Authority (CASA) issues these directives, with a clear policy objective to prevent air accidents and enhance the overall safety of civil aviation. This legislative instrument aims to ensure that all aircraft, including the Grumman G21 (Goose) Series Aeroplanes, meet stringent safety requirements through regular inspections and maintenance checks.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105 concerning the Civil Aviation Safety Authority Schedule of Airworthiness Directives, applies to all Grumman G21 (Goose) series aeroplanes, mandating stringent inspection requirements for specific components. This legislation is pertinent to the aviation industry, affecting aircraft operators, maintenance personnel, and regulatory authorities within the Commonwealth of Australia. The directive stipulates the need to remove and disassemble the Elevator Torque Tube Assembly, Rudder Torque Tube Assembly, Rudder Pedal Torque Tube Assembly (LH and RH), and Hinge Support Assembly to inspect these parts for corrosion or cracks using visual and dye penetrant or magnetic particle techniques. Compliance with this directive is mandatory, with inspections required initially before the issue of a Certificate of Airworthiness and subsequently at intervals not exceeding 2000 hours of time in service or two years, whichever comes first. This regulation ensures the safety and airworthiness of Grumman G21 aeroplanes by enforcing thorough maintenance checks on critical control system components.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, address the safety directives for various aircraft, including the Grumman G21 (Goose) Series Aeroplanes. The relevant directive, AD/G21/1, focuses on the inspection of the below floor control system components. According to section 10/77, this directive applies to all models of the Grumman G21 series. The primary requirement outlined in section 1 mandates the removal and disassembly of several specific components: (i) the Elevator Torque Tube Assembly P/N 12755, (ii) the Rudder Torque Tube Assembly P/N 12756, (iii) the Rudder Pedal Torque Tube Assembly for both left and right sides (P/N 12757 and 12758), and (iv) the Hinge Support Assembly P/N 12725. Following the disassembly, the regulation requires an inspection of all these parts for corrosion and/or cracks using either visual inspection methods or more advanced techniques such as dye penetrant or magnetic particle inspection.
Under these regulations, the operators and owners of Grumman G21 series aeroplanes have clear obligations to ensure that the specified components are thoroughly inspected and maintained. Compliance with this directive is mandatory and must occur initially before the issue of a Certificate of Airworthiness. After this initial inspection, the components must be re-inspected at intervals not exceeding 2000 hours of time in service or two years, whichever comes first. This periodic inspection requirement underscores the importance of ongoing maintenance and vigilance in ensuring the safety and airworthiness of these aircraft.
In addition to the inspection and maintenance requirements, the Civil Aviation Regulations impose significant obligations on the parties governed by this directive. Operators and owners must ensure that the specified components are not only inspected but also repaired or replaced as necessary to maintain their integrity and functionality. Failure to comply with these regulations can result in severe consequences, including the potential grounding of the aircraft until the required inspections and repairs are completed. This underscores the critical nature of adhering to the specified timelines and methods of inspection as mandated by the regulations.
Failure to comply with the provisions of AD/G21/1 can lead to serious consequences. The regulations impose penalties for non-compliance, which may include fines and other legal sanctions. In cases of severe non-compliance, there may also be criminal penalties, particularly if the non-compliance results in a safety incident or endangers the safety of passengers or crew. The maximum penalties for such breaches are determined by the relevant aviation safety laws and can vary depending on the severity and impact of the non-compliance. Therefore, it is crucial for operators and owners of Grumman G21 series aeroplanes to take these regulations seriously and ensure full compliance to avoid any adverse legal or safety consequences.