Document ID: chunk:federal_register_of_legislation:F2006L03585:body:0:p2
Version: federal_register_of_legislation:F2006L03585
Segment Type: other
Provision Reference: 
Character Range: 2845–4506

53-006) or MOD 073525 (SB No. 53-007), install a vibration damper / casing assembly on the RH and LH side of the helicopter, in compliance with the instructions specified in paragraphs 2.B.1, 2.B.3. and 2.B.5. of Eurocopter ASB No. 53A008 or any subsequent EASA approved revisions, as is applicable.

                Terminating Action.

             Compliance with Requirements 3 or 4 or 5 as is applicable provides terminating action to the repetitive inspections detailed in Requirement 1 of this AD.

             Note:  EASA AD 2006-0273 dated 4 September 2006 and AD 2006-0278 dated
             7 September 2006 refers.
Compliance:     1. Repetitively before the first flight of the day after the effective date of this AD.

                2. Before further flight.

                3. No later than 30 June 2007.

                4. No later than 31 May 2007.

                5. No later than 31 May 2007.
             This Amendment becomes effective on 23 November 2006.
Background:  In the event of a failure of the blade of the RH cabin vibration damper assembly, for helicopters fitted with an automatic flight control system, the failed part that remains trapped in the bottom structure lower fairing can interfere with the trim actuator rod which is installed nearby.  Such interference could jam the flight controls.

             This amendment introduces a mandatory modification to the vibration damper assembly which terminate the repetitive inspection called up in this AD.

             The original issue of this AD became effective 20 June 2005.

James Coyne
Delegate of the Civil Aviation Safety Authority

13 October 2006