Document ID: chunk:federal_register_of_legislation:F2006L01301:body:0:p1
Version: federal_register_of_legislation:F2006L01301
Segment Type: other
Provision Reference: 
Character Range: 0–3103

AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/DAUPHIN/63 and issues the following AD under subregulation 39.001(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.

Eurocopter SA 360 and SA 365 (Dauphin) Series Helicopters
AD/DAUPHIN/63 Amdt 1  Tail Rotor Blade Tuning Weights  6/2006

Applicability:  Model AS 365 N3 helicopters equipped with a quiet fenestron tail rotor, after incorporation of Modification 0764B39 (Service Bulletin No. 64.00.21) and before incorporation of Modification 0764B48; and with a tail rotor hub part number 365A33-3500-02 or -03, and blade attachment bushes part number 365A33-3530-20, installed.
Requirement:       1. Install a tuning weight on each blade of the tail rotor in accordance with Eurocopter AS 365 N Alert Service Bulletin (ASB) No. 64.00.23.

                   2. Following installation of the tuning weights, accomplish paragraph 2.C. of Eurocopter ASB No. 64.00.23 Revision 1.

                Note 1:  For AS 365 N3 helicopters, compliance with ASB No. 64.00.23 Revision 1 requires prior compliance with AS 365 N Service Bulletins No. 64.00.21 and
                No. 65.00.14.

                Before installation of blade attachment bushes and tail rotor hubs held as spares:

                   a. Replace the blade attachment bushes in accordance with paragraph 2.B.5. of ASB No. 64.00.23 Revision 1.

                   b. Modify and re-identify the tail rotor hubs in accordance with paragraphs 2.B.2. and 2.C. of ASB No. 64.00.23 Revision 1.

                Note 2:  EASA AD 2006-0078 refers.
Compliance:        1. Unless already accomplished, before 30 April 2003.

                   2. The next time the tail rotor hub is removed, and at the latest by 31 December 2006.

                The compliance time for Requirement 1 remains unchanged by this issue of the Directive.
                This Amendment becomes effective on 8 June 2006.

Background:  An increase in the level of vibration is being felt by crews in the pedal units during level flight at high speed.  Tail rotor blade tuning weights are installed at each blade position to eliminate vibration and to preclude any risk of failure at the pitch control of each blade.

             Amendment 1 is issued in response to an EASA AD, which introduces a revision of the Requirement document, clarifies the identification requirements of paragraph 2.C. and corrects part numbers in paragraph 3.E of the requirement document.

Richard Castles
Delegate of the Civil Aviation Safety Authority