COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 200 (Super King Air) Series Aeroplanes
AD/BEECH 200/61 Main Landing Gear Clevis Assembly 1/99
Applicability: Models and serial numbers listed in Raytheon Aircraft Mandatory Service Bulletin (MSB) 2728.
Requirement: Replace the left and right main landing gear actuator clevis assembly with a clevis assembly of improved design in accordance with the Accomplishment Instructions section in Raytheon Aircraft MSB 2728 or MSB 2728 Revision 1.
Note: FAA AD 98-21-35 Amdt 39-10843 refers.
Compliance: Unless already accomplished, within 200 hours time in service after 28 January 1999.
This Airworthiness Directive becomes effective on 28 January 1999.
Background: The FAA received reports of main landing gear failure on two of the affected aircraft. The actions specified by this Directive are intended to prevent failure of the actuator clevis assembly in the main landing gear caused by fatigue cracking of the original design part, which could lead to loss of control of the aircraft during landing operations.
Overview
The Civil Aviation Regulations 1998, amended by the legislative instrument F2006B03714, address a specific safety concern related to the Beechcraft 200 (Super King Air) Series aeroplanes. This regulation was introduced to address the risk of main landing gear failure due to fatigue cracking of the original clevis assembly design. The problem identified was the potential for loss of control during landing operations, which prompted the Civil Aviation Safety Authority to issue Airworthiness Directive AD/BEECH 200/61. The policy objective is to enhance the safety of the aircraft by mandating the replacement of the left and right main landing gear actuator clevis assembly with a design that has improved durability and resistance to fatigue cracking. Compliance with this directive is required within 200 hours of the aircraft being in service after 28 January 1999, ensuring that all affected aircraft are brought up to the required safety standards.
Scope and Application
The Civil Aviation Safety Authority (CASA) Regulations 1998, specifically Part 39 - 105, addresses the airworthiness of Beechcraft 200 (Super King Air) series aeroplanes through Airworthiness Directive AD/BEECH 200/61. This legislation mandates the replacement of the left and right main landing gear actuator clevis assembly for certain models and serial numbers identified in Raytheon Aircraft Mandatory Service Bulletin 2728. The directive applies to those aeroplanes specifically listed in the mentioned bulletin, requiring compliance within 200 hours of service after 28 January 1999, the effective date of the directive. This regulatory action stems from reports of main landing gear failure attributed to fatigue cracking in the original design, thereby necessitating preventive measures to ensure the safety of aircraft during landing operations. The directive references FAA AD 98-21-35 Amendment 39-10843, indicating an alignment with international safety standards.
Key Provisions
The Civil Aviation Regulations 1998, specifically in Part 39 - 105, address airworthiness directives pertaining to certain aircraft models. One such directive, AD/BEECH 200/61, concerns the Beechcraft 200 (Super King Air) Series Aeroplanes and mandates modifications to the main landing gear clevis assembly (Section 1/99). This directive applies to the specific models and serial numbers detailed in Raytheon Aircraft Mandatory Service Bulletin (MSB) 2728. The directive requires the replacement of the left and right main landing gear actuator clevis assembly with an improved design, as outlined in the Accomplishment Instructions section of MSB 2728 or MSB 2728 Revision 1. The directive references FAA AD 98-21-35 Amdt 39-10843 for additional context and guidance.
Operators and owners of affected Beechcraft 200 (Super King Air) Series Aeroplanes are obligated to comply with this directive. They must ensure that the specified modifications are carried out unless they have already been completed. The compliance timeframe requires the replacement to be accomplished within 200 hours of time in service after 28 January 1999, the effective date of the directive. The directive aims to prevent potential failures of the main landing gear actuator clevis assembly due to fatigue cracking in the original design, which could result in loss of control during landing operations.
Failure to comply with this airworthiness directive may result in serious safety hazards. The directive stems from reports received by the FAA regarding main landing gear failures in two affected aircraft. These failures were attributed to the fatigue cracking of the original clevis assembly design. Operators and owners who fail to adhere to the directive's requirements risk compromising the safety of their aircraft and potentially facing severe consequences during flight operations. The directive underscores the importance of timely compliance to mitigate risks associated with the identified safety issue.