Document ID: chunk:federal_register_of_legislation:F2006L03622:body:0
Version: federal_register_of_legislation:F2006L03622
Segment Type: other
Provision Reference: 
Character Range: 0–2430

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 315/3  Main Rotor Blade Root Skin and  12/2006
             Reinforcement Strip Bonding

Applicability:  Model SA 315 B helicopters, equipped with main rotor blade part number:

                3160S11-10000 all dash numbers, 3160S11-30000 all dash numbers, 3160S11-35000 all dash numbers, 3160S11-40000 all dash numbers, 3160S11-45000 all dash numbers, 3160S11-50000 all dash numbers, and 3160S11-55000 all dash numbers.
Requirement:    Inspect the main rotor blade spar skin and the blade root reinforcement strip area for bonding separation, cracks, and corrosion in accordance with paragraph 2 of Eurocopter Service Bulletin No. 05.34 R1.

                If bonding separation, cracking, or corrosion is detected during any inspection, and is within the criteria defined in paragraph 2 of the Requirement document, before further flight, remove the blade from service.

                Inspect blades held as spares before entry into service.

                Note:  DGAC AD 98-277-040(A) R1 refers.
Compliance:     Unless the initial inspection is already accomplished, within 25 flight hours or 30 days after 23 November 2006, whichever occurs first.

                Inspect thereafter at intervals not to exceed 100 flight hours or 6 months, whichever occurs first; except when bonding separation is detected in the non-hatched area of the reinforcement strip, in which case the inspection interval is reduced to 25 flight hours.
                This Airworthiness Directive becomes effective on 23 November 2006.
Background:     The DGAC received a report of main rotor blade failure on a SE 3130 helicopter.

David Villiers
Delegate of the Civil Aviation Safety Authority

12 October 2006