Commonwealth legislation

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

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Commonwealth

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legislative instrument

Plain English Summary

3/10 complexity

Requires lubrication of the main landing gear actuator rod ends on specified Beechcraft 1900 serial numbers, or alternatively installation of Teflon-lined rod ends (P/N M81935/1-8K) as a terminating action. Operators must meet set flight‑hour deadlines for lubrication or part replacement.

The directive responds to reports of rod‑end separations caused by excessive bearing friction that can stop gear extension or cause collapse; operators bear maintenance and parts costs and must track compliance (Requirement 1–2; Compliance; Background).

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

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Beechcraft 1900 Series Aeroplanes

AD/BEECH 1900/22 Main Landing Gear Actuator Rod Ends 4/98

Applicability: Model Serial Numbers

1900 UA-2 and UA-3

1900C UB-1 through UB-74, and UC-1 through UC-174 1900D UE-1 through UE-249 and UE-252

Requirement: 1. Lubricate the main landing gear actuator rod ends in accordance with Raytheon Safety Communique 1900-28.

Note: Installation of part number (P/N) M81935/1-8K (or FAA - approved equivalent part number) main landing gear actuator rod ends constitutes terminating action to the lubricating requirements of Requirement 1 of this Directive.

Install Teflon-lined main landing gear actuator rod ends, P/N M81935/1-8K (or FAA - approved equivalent part number), in accordance with the Accomplishment Instructions section of Raytheon Mandatory Service Bulletin 2730.

Note 1: Installing these Teflon-lined rod ends re-identifies the main landing gear actuator as P/N 114-380041-13.

Note 2: FAA AD 97-26-15 Amdt 39-10258 refers.

Compliance: 1. Upon accumulating 1,200 hours time in service on each P/N 114-380041-11 main landing gear actuator, or within 100 hours time in service after 26 March 1998, whichever occurs later.

Unless already accomplished, within 600 hours time in service after 26 March 1998.

This airworthiness directive becomes effective on 26 March 1998.

Background: The FAA received reports of in-flight separations of the rod end that attaches the actuator to the arm of the main landing gear drag brace assembly. The separations were caused by excessive friction in the rod end bearing, and could result in the inability to lower the main landing gear or result in landing gear collapse during landing.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

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