AD/A109/47 - Main Rotor Head Damper

Airworthiness Directive - AD/A109/47 - Main Rotor Head Damper Airworthiness Directive - AD/A109/47 - Main Rotor Head Damper CASA Airworthiness Directive Jurisdiction:Commonwealth of Australia;CorporateName:Civil Aviation Safety Authority; Issue 11/2003,Rotorcraft,Agusta A109 Series Helicopters,Main Rotor Head Damper,47 DellaCa, Donna 2 0 2022-10-25T22:28:00Z 2022-10-25T22:28:00Z 1 286 1635 Office of Parliamentary Counsel 13 3 1918 16.0000 2006-09-21T00:00:00Z Toolkit http://www.activepdf.com 2022-10-25T00:00:00Z COMMONWEALTH OF AUSTRALIA   (Civil Aviation Safety Regulations 1998) , PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES   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 CASR 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.   Agusta A109 Series Helicopters   AD/A109/47   Main Rotor Head Damper   11/2003 DM   Applicability:   All Model a 109E helicopters with dampers part number 109-0111-06-103 fitted with Microtechnica rod-end assemblies part number 3637GR85.   Requirement:   Inspect in accordance with Agusta Technical Bulletin No. 109EP-37 Revision A.   Note: ENAC AD 2003-249 refers.   Compliance:   For Part I of the Requirement document: Within 25 flight hours after 10 September 2003, unless already accomplished.   For Part II of the Requirement document: Within 25 flight hours after accomplishment of Part I of the Requirement document.   This Airworthiness Directive becomes effective on 10 September 2003.   Background:   The manufacturer received reports of fractures of the main rotor head damper rod end. Investigation revealed fatigue failure originating from the rod-end thread under cut. David Villiers Delegate of the Civil Aviation Safety Authority 4 September 2003                         The above AD is notified in the Commonwealth of Australia Gazette on 10 September 2003.       Page 1 of 1