COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
DHC-2 (Beaver) Series Aeroplanes
AD/DHC-2/16 Aileron Centre Hinge Bracket - Inspection 2/71
Applicability: All models with brackets P/N 02-B-58 and P/N 02-B-58-1.
Requirement: Remove the mass balance assembly from the stub tube of each centre hinge bracket and visually inspect the elliptical tube using a 4X magnifying glass for cracks in the weld areas at the connection to the torque tube and around the extremities of welded bushes.
Compliance: For components with less than 400 hours total time in service as at 31 March 1971 - at or before achieving 500 hours total time in service; or
For components with more than 400 hours total time in service as at 31 March 1971 - within 100 hours time in service after 31 March 1971; and
Thereafter at intervals not exceeding 100 hours time in service.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, aim to ensure the safety and regulation of civil aviation within the country. This legislative instrument, particularly PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITYSCHEDULE OF AIRWORTHINESS DIRECTIVES, addresses the need to issue specific directives to maintain the airworthiness of aircraft, ensuring public safety and compliance with international standards. The policy objective is to mandate regular inspections and maintenance procedures to prevent mechanical failures that could compromise flight safety.
One specific directive, AD/DHC-2/16, focuses on the inspection of aileron centre hinge brackets for DHC-2 (Beaver) Series Aeroplanes, particularly those with brackets P/N 02-B-58 and P/N 02-B-58-1. The directive requires the removal of the mass balance assembly and a visual inspection for cracks in weld areas using a 4X magnifying glass. This ensures that any potential structural weaknesses are identified and rectified, thereby maintaining the integrity and safety of the aircraft. Compliance with these directives is critical, with specific timelines based on the total time in service of the components, ensuring that inspections are conducted at regular intervals.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertains to the Civil Aviation Safety Authority (CASA) and applies to all DHC-2 (Beaver) series aeroplanes with specific centre hinge bracket parts numbers 02-B-58 and 02-B-58-1. This legislation mandates a detailed inspection regime for the aileron centre hinge bracket to ensure ongoing airworthiness and safety. The inspection requires the removal of the mass balance assembly from the stub tube of each centre hinge bracket and a visual inspection of the elliptical tube for cracks, particularly in the weld areas at the connection to the torque tube and around the extremities of welded bushes. This inspection must be performed using a 4X magnifying glass. Compliance with these regulations is contingent on the total time in service of the components, with differing deadlines for inspection based on whether the components had less than or more than 400 hours of service as at 31 March 1971. Once the initial inspection is completed, subsequent inspections must occur at intervals not exceeding 100 hours of service. This regulation applies nationally across Australia, administered by CASA under the authority granted by the Civil Aviation Act 1988.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, under the Civil Aviation Safety Authority, includes Airworthiness Directives (ADs) for various aircraft types. In the case of DHC-2 (Beaver) Series Aeroplanes, AD/DHC-2/16 pertains to the inspection of the aileron centre hinge bracket (section 105). This directive applies to all models equipped with brackets identified by part numbers 02-B-58 and 02-B-58-1. The requirement is to remove the mass balance assembly from the stub tube of each centre hinge bracket and visually inspect the elliptical tube using a 4X magnifying glass for any cracks in the weld areas, particularly at the connection to the torque tube and around the extremities of welded bushes.
Compliance with AD/DHC-2/16 involves specific timings for inspections. For components that had less than 400 hours of total time in service as of 31 March 1971, the inspection must be carried out at or before achieving 500 hours of total time in service. For components that had more than 400 hours of total time in service as of 31 March 1971, the inspection must be completed within 100 hours of time in service after that date. Subsequent inspections are required at intervals not exceeding 100 hours of time in service thereafter. This ensures that any potential structural issues are detected and addressed promptly, maintaining the airworthiness of the aircraft.
The obligations imposed by this directive on the parties or entities it governs include ensuring that the specified inspections are conducted meticulously and documented appropriately. Operators of DHC-2 (Beaver) Series Aeroplanes must adhere to the prescribed timelines and use the correct inspection tools, such as the 4X magnifying glass, to identify any defects. Record-keeping is critical, with operators required to maintain detailed logs of inspections and any findings, which must be readily available for review by the Civil Aviation Safety Authority.
Failure to comply with AD/DHC-2/16 can lead to severe consequences. The Act does not explicitly state offences or penalties within the text provided, but non-compliance with Airworthiness Directives generally can result in enforcement actions by the Civil Aviation Safety Authority. These actions may include fines, suspension or revocation of airworthiness certificates, or other regulatory measures. In more severe cases, where non-compliance is deemed to significantly compromise safety, there could be potential for criminal charges against responsible individuals or entities, depending on the nature and extent of the breach.