COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Hiller UH-12 Series Helicopters
AD/HILLER 12/36
Amdt 1
Main Drive Torsion Coupling
P/N 21047-15 - Inspection of Lower Plate
10/82
Applicability: All Hiller UH-12E series, UH-12L series, OH-23G, OH-23F helicopters, fitted with a torsion coupling P/N 21047-15.
Requirement: Conduct a fluorescent penetrant inspection of the lower half of the coupling, around the entire perimeter of the base where the eight cut out windows are located between the wear sleeve and the lower flange to which the rubber is bonded.
FAA AD 82-16-07 refers.
Compliance: Within 10 hours’ time in service after 4 August 1982, and thereafter at periods not exceeding 50 hours’ time in service.
Background: Due to a possible manufacturing defect, all P/N 21047-15 couplings are to be inspected for cracks in the area of the lower plate windows. There have been two cracked couplings reported on local helicopters.
Overview
The Civil Aviation Regulations 1998, as amended by F2006B10361, were enacted to address specific safety concerns related to the Hiller UH-12 series helicopters, particularly those involving the main drive torsion coupling part number 21047-15. This legislation was introduced to ensure the safety of these aircraft by mandating rigorous inspections for manufacturing defects, which had previously been identified in two local helicopters. The objective of this Airworthiness Directive is to prevent the occurrence of cracks in the lower plate windows of the coupling, thereby maintaining the structural integrity and safety of the aircraft. This directive applies to all Hiller UH-12E and UH-12L series, as well as OH-23G and OH-23F helicopters equipped with the specified torsion coupling. Compliance with the inspection requirements is mandatory and must be conducted within 10 hours’ time in service following the directive's issuance on 4 August 1982, and subsequently at intervals not exceeding 50 hours’ time in service.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertain to the Airworthiness Directives issued by the Civil Aviation Safety Authority (CASA) and govern the safety standards for civil aviation in Australia. The regulation under discussion, AD/HILLER 12/36 Amendment 1, applies to all Hiller UH-12E series, UH-12L series, OH-23G, and OH-23F helicopters equipped with a specific torsion coupling part number 21047-15. The regulation mandates that these helicopters must undergo a fluorescent penetrant inspection of the lower half of the coupling, focusing on the base area around the eight cut-out windows where the wear sleeve meets the lower flange to which the rubber is bonded. This requirement is aimed at detecting any cracks that may have developed in this critical area due to a potential manufacturing defect. The directive references the Federal Aviation Administration's AD 82-16-07 and necessitates compliance within 10 hours of time in service after 4 August 1982, and subsequently at intervals not exceeding 50 hours of time in service. This regulation underscores the importance of stringent safety checks to mitigate risks associated with identified defects in aircraft components.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, mandate that all operators of Hiller UH-12E series, UH-12L series, OH-23G, and OH-23F helicopters fitted with a torsion coupling P/N 21047-15 must conduct a fluorescent penetrant inspection of the lower half of the coupling (Section 10/82). This inspection must be carried out around the entire perimeter of the base, focusing on the area where the eight cut out windows are located between the wear sleeve and the lower flange to which the rubber is bonded. This requirement is outlined in AD/HILLER 12/36 and references FAA AD 82-16-07. Operators are to perform this inspection within 10 hours’ time in service after 4 August 1982 and must repeat the inspection at intervals not exceeding 50 hours’ time in service thereafter.
Compliance with these provisions is crucial for ensuring the safety and airworthiness of the affected helicopters. Operators must ensure that the specified inspections are performed by qualified personnel and documented appropriately to demonstrate compliance with the regulations. Failure to conduct these inspections within the stipulated timeframes could result in the aircraft being deemed unairworthy, potentially leading to grounding of the helicopter until the required inspections are completed and any necessary repairs are made.
Breach of these regulatory requirements can result in significant consequences. Civil penalties can be imposed, including fines, and in more severe cases, criminal charges may be brought against the operators or responsible individuals. The maximum penalties for non-compliance with these safety directives can include fines up to $275,000 for corporations and $55,000 for individuals, reflecting the serious nature of these safety obligations. Additionally, non-compliance may also lead to the suspension or revocation of the operator's licence, further impacting their ability to conduct operations.