Document ID: chunk:federal_register_of_legislation:F2006L03626:body:0
Version: federal_register_of_legislation:F2006L03626
Segment Type: other
Provision Reference: 
Character Range: 0–2667

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 39.001(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 315 (Lama) Series Helicopters
AD/SA 315/7  Main Rotor Blades  12/2006

Applicability:  Model SA 315 B helicopters, fitted with main rotor blades part numbers:

                3160S11-30-000, all dash numbers,

                3160S11-40-000, all dash numbers,

                3160S11-50-000, all dash numbers.
Requirement:       1. Action in accordance with paragraph 2.1 of Eurocopter Service Bulletin
                   No. 65-38 R1.

                   If the results of the checks are satisfactory, before further flight, modify the blade part numbers in accordance with paragraph 2.3 of the Requirement document, and return the blades to service.

                   2. If the results of the checks are not satisfactory, remove the blades from service.

                Note:  DGAC AD 93-104-034(B) R2 refers.
Compliance:        1.a. Unless already accomplished, before 2,900 flight hours since new or since reconstruction for blades which have logged less than 2,800 flight hours since new or since reconstruction, as applicable, at the effective date of this Directive.

                   1.b. Unless already accomplished, within 100 flight hours after the effective date of this Directive for blades which have logged 2,800 flight hours or more since new or since reconstruction, as applicable.

                   2.a. For blades subject to Compliance 1.a.; upon logging 3,000 flight hours since new or since reconstruction, as applicable.

                   2.b. For blades subject to Compliance 1.b.; within 200 flight hours after the effective date of this Directive.
                This Airworthiness Directive becomes effective on 23 November 2006.

Background:  This Directive requires certain actions in order to prevent main rotor blade fatigue damage initiated by fretting corrosion, caused by the incorrect positioning of the blade root reinforcement band.

David Villiers
Delegate of the Civil Aviation Safety Authority

13 October 2006