COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Fokker F100 (F28 Mk 100) Series Aeroplanes AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section. AD/F100/41 Main Landing Gear Torque Link Dampers 6/2000 Applicability: Model F 28 Mk 0070 and 0100 aircraft. Requirement: Remove main landing gear torque link dampers P/N 23700-1 or 23700-3 from the aircraft and install modified main landing gear damper P/N 23700-5 IAW Fokker SB SBF-100-32-114. Note: RLD AD 1999-138 Dated 29 October1999 refers. Compliance: Unless previously carried out, any Fokker 100 aircraft fitted with Messier Dowty dampers not modified to CSB-32-50, within 15 months time in service from the effective date of this Directive. Unless previously carried out, any Fokker 100 aircraft fitted with Messier Dowty dampers modified to CSB-32-50, within 21 months time in service from the effective date of this Directive. Unless previously carried out, any Fokker 100 aircraft fitted with Menasco dampers, within 24 months time in service from the effective date of this Directive. Unless previously carried out, any Fokker 70 aircraft fitted with Menasco dampers, within 24 months time in service from the effective date of this Directive. This Airworthiness Directive becomes effective on 15 June 2000. Background: The aircraft manufacturer has advised that following a main landing gear separation, after landing, investigation confirmed that separation of the landing gear had been caused by performance degradation of the damper and the resulting loss of damping capability. Eugene Paul Holzapfel Delegate of the Civil Aviation Safety Authority 2 May 2000 The above AD is notified in the Commonwealth of Australia Gazette on 17 May 2000.