AD/EC 225/6 Main Rotor Hub Coning Stop Supports (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 EC 225 Series Helicopters

AD/EC 225/6 Main Rotor Hub Coning Stop Supports 11/2008

Applicability:

EC 225 LP helicopters, all serial numbers.

Requirement:

1.    Carry out a visual check (or if in doubt a dye penetrant check) for cracks in the area of the attachment points on the main rotor hub reinforcement ring of the lugs securing the coning stop support and also of the lugs securing the dome fairing support, in accordance with the instructions given in paragraph 2.B.1 of EUROCOPTER EC 225 Alert Service Bulletin No. 05A003 Revision 1 or later approved revision.

If a crack is found in one of the five lugs of the coning stop support and/or in one of the five lugs of the dome fairing support then;

(i)    Remove and replace the coning stop support assembly and/or remove and replace the dome fairing support.

2.    For helicopters that have been modified in accordance with EUROCOPTER
EC 225 SB No. 62-005 (Modification 332A08.0929.00), in addition to the inspection in requirement (1), readjust the tightening torque of the screws securing the dome fairing support to the reinforcement ring, in accordance with EUROCOPTER EC 225 Alert Service Bulletin No. 05A003 Revision 1 or later approved revision.

3.    Modification of any helicopters in accordance with Eurocopter EC 225 SB No. 62-005 (mod 332A08.0929.00) is no longer allowed.

4.    All components installed and/or modified in accordance EUROCOPTER EC 225 SB No. 62-005 (Modification 332A08.0929.00), are to be removed from service.

To be able to reach the place where the coning stop support assembly or the dome fairing support will be replaced, flight without the dome fairing itself is permitted on the condition that:

• the dome fairing and its attachment screws are removed in accordance with the instructions given in the Note in paragraph 2.B.1.b of the referenced ASB; and

• the flight crews are informed that when flying without the dome fairing, the lateral vibration of the helicopter significantly deteriorates at speeds of 70 to 120 KIAS but that this phenomenon only affects the comfort of the helicopter and in no way jeopardizes flight safety.

Note:  EASA AD 2007-0197-E, dated 24 July 2007 refers.

Compliance:

1.    Every 15 flight hours or 7 days, whichever occurs first.

(i)    Before further flight (only of cracks are found in lugs after inspection per requirement 1).

2.    Initially within 15 flight hours or 7 days (whichever first) and thereafter at 25 hourly intervals.

3.    From the effective date of this directive.

4.    Before further flight.

This Airworthiness Directive becomes effective on 23 October 2008.

Background:

This Airworthiness Directive is issued following reports of cracks and failure of the main rotor hub coning stop support lugs at their attachment points on the reinforcement ring where the dome fairing is secured.  Some further cracks have been reported affecting the dome fairing support assemblies, in particular, but not confined to, those modified to Eurocopter EC 225 Service bulletin No. 62-005.

This AD requires inspections of the dome fairing support lugs and the removal from service of parts installed during modification per Eurocopter EC 225 Service bulletin No. 62-005.

David Villiers
Delegate of the Civil Aviation Safety Authority

27 August 2008