AD/BEECH 1900/22 - Main Landing Gear Actuator Rod Ends

Overview

The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the safety of civil aviation through the Civil Aviation Safety Authority (CASA) by issuing Airworthiness Directives (AD). Enacted by the Australian Parliament, these regulations are intended to ensure the safe operation of aircraft by imposing standards on aircraft maintenance, operation, and design. This particular legislative instrument, F2006B03639, pertains to the Beechcraft 1900 Series aeroplanes and was introduced to mitigate the risk of in-flight separation of the main landing gear actuator rod ends, which could lead to severe operational hazards such as the inability to lower the landing gear or landing gear collapse during landing. The objective is to maintain the safety and reliability of the aircraft by mandating specific maintenance actions, such as lubricating and replacing certain components, to prevent mechanical failures.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 and the Civil Aviation Safety Authority Schedule of Airworthiness Directives, apply to the Beechcraft 1900 Series Aeroplanes as outlined in AD/BEECH 1900/22. This regulation pertains to the main landing gear actuator rod ends for specific model serial numbers: 1900 UA-2 and UA-3, 1900C UB-1 through UB-74, and UC-1 through UC-174, as well as 1900D UE-1 through UE-249 and UE-252. The directive mandates the lubrication of these components in accordance with Raytheon Safety Communique 1900-28 and requires the installation of Teflon-lined main landing gear actuator rod ends, P/N M81935/1-8K or an FAA-approved equivalent, as per Raytheon Mandatory Service Bulletin 2730. Compliance must be achieved upon reaching 1,200 hours of time in service on each P/N 114-380041-11 main landing gear actuator, or within 100 hours of time in service after 26 March 1998, whichever is later. Additionally, compliance must be achieved within 600 hours of time in service after 26 March 1998 if not already completed. This airworthiness directive took effect on 26 March 1998, following reports of in-flight separations of the rod ends due to excessive friction, which could potentially result in the inability to lower the main landing gear or landing gear collapse during landing.

Key Provisions

The Civil Aviation Regulations 1998, particularly Part 39 - 105, address the specific airworthiness requirements for Beechcraft 1900 Series aeroplanes, as outlined in AD/BEECH 1900/22. This directive mandates that certain models and serial numbers of the aircraft must adhere to specific maintenance procedures to ensure the safety of the main landing gear actuator rod ends. The primary requirement is to lubricate the main landing gear actuator rod ends in accordance with Raytheon Safety Communique 1900-28 (section 1). Additionally, the directive requires the installation of Teflon-lined main landing gear actuator rod ends, specified as part number M81935/1-8K or its FAA-approved equivalent, as detailed in Raytheon Mandatory Service Bulletin 2730 (section 1(2)). These installations must be completed under the conditions specified, such as the re-identification of the main landing gear actuator as P/N 114-380041-13 upon installation (section 1(2), Note 1). Compliance with these requirements is essential for the safe operation of the Beechcraft 1900 Series aeroplanes. Specifically, the main landing gear actuator rod ends must be lubricated or replaced upon accumulating 1,200 hours of time in service on each P/N 114-380041-11 main landing gear actuator, or within 100 hours after 26 March 1998, whichever occurs later (section Compliance 1). Additionally, the Teflon-lined rod ends must be installed within 600 hours of time in service after 26 March 1998, unless they have already been installed (section Compliance 2). This directive became effective on 26 March 1998, and it is crucial that operators of the affected aircraft adhere to these provisions to maintain airworthiness. Failure to comply with the provisions outlined in AD/BEECH 1900/22 can result in significant safety risks. The directive was issued in response to reports of in-flight separations of the rod end that attaches the actuator to the arm of the main landing gear drag brace assembly, which were caused by excessive friction in the rod end bearing. Such separations could lead to the inability to lower the main landing gear or result in landing gear collapse during landing, posing a severe threat to aircraft safety (Background). Consequently, non-compliance with these airworthiness directives can lead to severe consequences, including potential accidents and grounding of the aircraft until compliance is achieved. The regulatory framework imposes strict obligations on aircraft operators and maintenance personnel to ensure that the specified maintenance actions are carried out to mitigate these risks.