COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 76 (Duchess) Series Aeroplanes
AD/BEECH 76/18
Amdt 1
MLG “A” Frame Assembly 8/97
Applicability: Model 76 aircraft with serial numbers ME-1 through ME-437, that do not have both a part number (P/N) 105-810023-75 (left) and P/N 105-810023-76 (right) main landing gear (MLG) “A” frame assembly installed.
Requirement: Inspect, using both visual and dye penetrant methods, both the left and right MLG “A” frame assemblies for cracks in accordance with the Accomplishment Instructions section of Raytheon Mandatory Service Bulletin 2361 Revision III. Pay particular attention to the tips of the gussets and the small corrosion treatment hole adjacent to the gusset.
If any MLG “A” frame assembly is found cracked, replace the assembly with one of the following in accordance with Chapter 32 of the Raytheon Model 76 Maintenance Manual:
(a) A new MLG “A” frame assembly with the same P/N as that found cracked. The 100 hours’ time in service repetitive inspection requirement still applies when this design “A” frame is installed.
(b) A P/N 105-810023-75 (left) or P/N 105-810023-76 (right) MLG “A” frame assembly, as applicable. Repetitive inspections are no longer required on an MLG “A” frame assembly incorporating this design configuration.
Installing both P/N 105-810023-75 (left) and P/N 105-810023-76 (right) MLG “A” frame assemblies eliminates the repetitive inspection requirement of this directive.
Note: FAA AD 97-06-10 Amdt 39-9967 refers.
Compliance: Within 100 hours’ time in service after 17 July 1997, and thereafter at intervals not to exceed 100 hours’ time in service, until both P/N 105-810023-75 and P/N 105- 810023-76 MLG “A” frame assemblies are installed.
This airworthiness directive becomes effective on 17 July 1997.
Background: The FAA received reports of fatigue cracks developing on the main landing gear “A” frame assembly of Beech Model 76 aircraft. These cracks, if not detected and corrected, would cause the main landing gear to collapse.
Amendment 1 is issued in response to a new FAA AD which introduces terminating action for the repetitive inspection requirement of this directive if certain improved design “A” frame assemblies are installed.
Overview
The Civil Aviation Regulations 1998, specifically within Part 39 - 105, addresses the safety of aircraft operations through the issuance of airworthiness directives. These regulations were enacted by the Parliament of Australia to ensure that civil aviation activities are conducted with the utmost regard for safety and public protection. This particular directive, AD/BEECH 76/18 Amendment 1, targets a safety issue identified with the main landing gear “A” frame assemblies of Beechcraft 76 (Duchess) Series aeroplanes. The problem it addresses involves the development of fatigue cracks in the “A” frame assemblies, which could lead to catastrophic failure of the landing gear. The policy objective is to mandate regular inspections and, if necessary, the replacement of these components to prevent any such failure, thereby enhancing overall aircraft safety.
This airworthiness directive was introduced in response to reports of cracks in the main landing gear “A” frame assemblies of Beech Model 76 aircraft, which were reported to the Federal Aviation Administration (FAA). The directive requires inspections and potential replacements of the assemblies to mitigate the risk of landing gear collapse. Compliance must be achieved within 100 hours of time in service following the directive's effective date of 17 July 1997, and subsequently at intervals not exceeding 100 hours. The directive also references FAA AD 97-06-10 Amendment 39-9967, indicating alignment with international safety standards.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertains to the oversight of airworthiness directives for aircraft within Australia, applying to all aircraft registered in Australia, including those of the Beechcraft 76 (Duchess) Series. This legislative instrument addresses the maintenance and safety requirements for the main landing gear (MLG) “A” frame assembly of the Beechcraft 76 aircraft, particularly focusing on those models with specific serial numbers that do not have certain improved design assemblies installed. The directive mandates that inspections be conducted using both visual and dye penetrant methods to detect cracks in the MLG “A” frame assemblies, with special attention to the tips of the gussets and the small corrosion treatment hole adjacent to the gusset. If any cracks are detected, the assembly must be replaced according to specified guidelines, which may involve using an improved design assembly to eliminate the need for repetitive inspections. The directive applies to all relevant aircraft within the Commonwealth of Australia and becomes effective from 17 July 1997, with compliance required within 100 hours’ time in service after this date and subsequently at intervals not exceeding 100 hours’ time in service until the specified MLG “A” frame assemblies are installed.
Key Provisions
The Civil Aviation Regulations 1998, Part 39 – 105, specifically AD/BEECH 76/18 Amendment 1, pertains to the main landing gear (MLG) “A” frame assembly of the Beechcraft 76 (Duchess) series aeroplanes. This Airworthiness Directive (AD) applies to aircraft with serial numbers ME-1 through ME-437, excluding those that have already been equipped with specific main landing gear “A” frame assemblies (P/N 105-810023-75 for the left and P/N 105-810023-76 for the right). The directive mandates a thorough inspection of both left and right MLG “A” frame assemblies for any cracks using both visual and dye penetrant methods, with particular attention to the tips of the gussets and the small corrosion treatment hole adjacent to the gusset, as per the instructions in Raytheon Mandatory Service Bulletin 2361 Revision III.
The AD imposes specific obligations on the operators of affected aircraft to ensure compliance. Operators must inspect the specified MLG “A” frame assemblies within 100 hours of time in service after the effective date of the AD, 17 July 1997, and subsequently at intervals not exceeding 100 hours until the specified design assemblies are installed. If any cracks are detected during inspection, the cracked assembly must be replaced with either a new assembly of the same part number or the specified improved design assembly (P/N 105-810023-75 or P/N 105-810023-76). The installation of both improved design assemblies will terminate the repetitive inspection requirement under this directive.
Failure to comply with this AD may have significant consequences. Although the specific civil or criminal penalties are not detailed in the legislative instrument, non-compliance with ADs issued by the Civil Aviation Safety Authority (CASA) under the Civil Aviation Act 1988 and the Civil Aviation Regulations 1988 typically results in enforcement actions which could include fines, suspension, or revocation of airworthiness certificates, as well as potential criminal charges for serious breaches. The exact penalties would depend on the severity and frequency of non-compliance and would be determined under the relevant sections of the Civil Aviation Act 1988.