AD/SA 315/4 Main Rotor Blade Cuff to Spar Assembly (Cth)

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 315/4 Main Rotor Blade Cuff to Spar Assembly 12/2006

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 areas for cracks in accordance with paragraph 2.B. of Eurocopter Service Bulletin No. 05.39.

Note:  DGAC AD 1998-171-039(A) R2 refers.

Compliance:

1.    For blades which have accumulated less than 400 flight hours:

Upon accumulating 400 flight hours.

2.    For blades which have accumulated more than 400 flight hours:

And which have been previously checked in accordance with Eurocopter Service Telex No. 01-20 or 01-30, within 25 flight hours after the last check, unless already accomplished.

3.    For blades which have accumulated more than 400 flight hours:

And which have not been previously checked in accordance with Eurocopter Service Telex No. 01-20 or 01-30, before further flight.

4.    Repeat inspection at intervals not to exceed 100 flight hours or 600 flight cycles, whichever occurs first.

5.    Accomplish inspection before further flight after a sudden occurrence of vibrations at 1 omega.

6.    Accomplish inspection on blades held as spares before installation on the helicopter.

This Airworthiness Directive becomes effective on 23 November 2006.

Background: The DGAC received a report of the failure of a main rotor blade on a SA 315 B helicopter.

David Villiers
Delegate of the Civil Aviation Safety Authority

12 October 2006