EASA AD No.: 2008-0204-E 

EASA Form 111 Page 1/2 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2008-0204-E 

Date: 04 December 2008 

Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the 

European third countries that participate in the activities of EASA under Article 66 of that Regulation 

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an 

aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Agency [EC 

2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

Eurocopter 

Type/Model designation(s) : 

365 N series helicopters 

TCDS Number : France No.159 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA Emergency AD 2008-0110-E dated 06 June 2008. 

ATA 55 Stabilizers – Never-Exceed Speed (VNE) and Rate-of-Descent (R/D) – 

Limitations 

Manufacturer(s): Eurocopter, Eurocopter France, Société Nationale Industrielle Aerospatiale 

(SNIAS) 

Applicability: SA 365 N, SA 365 N1, AS 365 N2 and AS 365 N3 helicopters, all serial numbers. 

Reason: 

Eurocopter has received some reports of failed horizontal stabilizers on recently 

delivered AS 365 N3 helicopters. The failures occurred during acceptance test 

and training flights as part of the demonstration of the never-exceed speed (VNE) 

and resulted into in-flight separation and loss of the failed sections. In each case, 

the helicopters succeeded in returning to base with no further problems. 

To ensure the safety of flight and people on the ground, EASA issued Emergency 

AD 2008-0110-E to require the introduction of a never-exceed speed (VNE) 

limitation for helicopters with certain Part Number (P/N) horizontal stabilizers. 

Tests conducted on the helicopter and in the laboratory have revealed that the 

reported incidents were due to a vibration phenomenon that may arise in the 

descent flight phases at high speed, regardless of the stabilizer definition. 

Eurocopter is developing an improvement that is expected to solve this problem. 

Pending the availability of a final solution as a result of further studies and to 

ensure continued flight safety and the safety of people on the ground, this new 

EASA AD retains the requirements of AD 2008-0110-E, which is superseded, 

expands the applicability of the VNE limitation to all 365N helicopters, regardless 

of P/N horizontal stabilizers installed and in addition requires the implementation 

of a -1500 ft/min Rate of Descent (R/D) limitation beyond 140 knots Indicated Air 

Speed (IAS). 
EASA AD No.: 2008-0204-E 

EASA Form 111 Page 2/2 

Considering that the stabilizer assembly procedure on SA 366 G1 helicopters 

modifies the dynamic behaviour of the stabilizer, it has been concluded that the 

unsafe condition addressed by this AD does not exist on that helicopter and 

consequently, the SA 366 G1 has been deleted from the applicability of this AD. 

As a result, the VNE limitation as required by EASA AD 2008-0110-E can be 

removed from those helicopters.

Effective Date: 08 December 2008 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Before next flight after 07 June 2008 [the effective date of AD 2008-0110-E], 

in accordance with the instructions of Eurocopter Alert Service Bulletin (ASB) 

01.00.60, accomplish the following: 

 - Amend the Rotorcraft Flight Manual (RFM) to include a VNE of 150 Knots 

IAS. This may be accomplished by inserting a copy of this AD into the RFM. 

 - Install one or more labels (placards) on the cockpit instrument panel, in full 

view of the pilot and co-pilot, as specified in Eurocopter ASB 01.00.60, 

paragraph 2B, Figure 1, Item 1. 

(2) Before next flight after the effective date of this AD, in accordance with the 

instructions of Eurocopter ASB 01.00.60 Revision 1, accomplish the 

following: 

 - Amend the Rotorcraft Flight Manual (RFM) to include a -1500 feet/minute 

rate of descent (R/D) limitation beyond 140 knots. 

This may be accomplished by inserting a copy of this AD into the RFM. 

 - Install one or more labels (placards) on the cockpit instrument panel, in full 

view of the pilot and co-pilot, as specified in Eurocopter ASB 01.00.60 

Revision 1, paragraph 2B, Figure 1, Item 2. 

Ref. Publications: 

Eurocopter ASB 01.00.60 dated 06 June 2008 and ASB 01.00.60 Revision 1 dated 

02 December 2008. 

The use of later approved revisions of this document is acceptable for compliance 

with the requirements of this AD. 

Remarks :

1. If requested and appropriately substantiated, EASA can approve Alternative 

Methods of Compliance for this AD. 

2. The safety assessment has requested not to implement the full consultation 

process and an immediate publication and notification. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification Directorate, 

EASA. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements in this 

AD, please contact: 

EUROCOPTER (STDI) – Aéroport de Marseille Provence 13725 Marignane 

Cedex, France; telephone +33 (4) 12 85 97 97; facsimile +33 (4) 85 99 66; 

E-mail: Directive.technical-support@eurocopter.com