EASA AD No.: 2014-0214

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0214

Date: 24 September 2014

Note: This 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 EU 748/2012, Part 21.A.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].

Design Approval Holder’s Name:

AIRBUS HELICOPTERS

Type/Model designation(s):

AS 365 N3 and EC 155 helicopters

TCDS Number: EASA.R.105

Foreign AD: Not applicable

Supersedure: None

ATA 25 Equipment / Furnishing – External Life Rafts – Inspection 

Manufacturer(s): Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)

Applicability: AS 365 N3 helicopters, all manufacturer serial numbers, if equipped with 

external life rafts in the footsteps with junction units having Manufacturer Part 

Number (MP/N) 200197 or MP/N 200188 (Airbus Helicopters P/N 

704A341302.48 or P/N 704A341302.30).

EC 155 B and EC 155 B1 helicopters, all manufacturer serial numbers, if 

equipped with external life rafts in the footsteps with junction units having MP/N 

200188 (Airbus Helicopters P/N 704A341302.30).

Reason: Failure of the external life raft deployment test was reported by an AS 365 

operator. The affected external life raft, mounted in the helicopter footstep 

structure, underwent a scheduled maintenance with interval of 600 flight hours 

or 24 months, and the failure occurred during an attempt to release the life raft 

by pulling the left hand (LH) internal deployment handle. Subsequent 

investigations revealed presence of corrosion damage inside the LH junction 

unit, which blocked the deployment handle.

This condition, if not detected and corrected, could result in failure of 

deployment of the external life raft (for example after a ditching), impeding or 

preventing safe evacuation of the occupants from the helicopter.

To address this potentially unsafe condition, Airbus Helicopters issued Alert 

Service Bulletin (ASB) AS365-05.00.67 and ASB EC155-05A027, as applicable 

to helicopter model, to provide instructions to detect and correct corrosion.

For the reason described above, this AD requires a one-time inspection of the 

right hand (RH) and LH junction units of the external life raft installation and, 

depending on findings, corrective action. This AD also requires to contact 

Airbus Helicopters in case of finding any corrosion.
EASA AD No.: 2014-0214

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2

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Effective Date: 01 October 2014

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Before the next flight, after the effective date of this AD, where the 

operation requires life rafts to be carried on the helicopter, inspect the 

deployment system of the external life rafts in accordance with the 

instructions of paragraph 1.E.2 of Airbus Helicopters ASB AS365-05.00.67

Revision 1 or ASB EC155-05A027 Revision 1, as applicable to the 

helicopter model.

(2) Depending on findings detected during the inspection, as required by 

paragraph (1) of this AD, within the compliance time defined in 1.E.2 of 

Airbus Helicopters ASB AS365-05.00.67 Revision 1 or ASB EC155-

05A027 Revision 1, as applicable to the helicopter model, measure an 

operational clearance and inspect for corrosion the LH and RH junction 

units of the external life raft deployment system in accordance with the 

instructions of paragraphs 3.A and 3.B Airbus Helicopters ASB AS365-

05.00.67 Revision 1 or ASB EC155-05A027 Revision 1, as applicable to 

helicopter model.

(3) Unless accomplished as required by paragraph (2) of this AD, within 90 

days after the effective date of this AD, measure an operational clearance 

and inspect for corrosion the LH and RH junction units of the external life 

raft deployment system in accordance with the instructions of paragraphs

3.A and 3.B of Airbus Helicopters ASB AS365-05.00.67 Revision 1or ASB 

EC155-05A027 Revision 1, as applicable to the helicopter model.

(4) If, during the measurement and inspection, as required by paragraph (2) or 

(3) of this AD, as applicable, any clearance deviation or corrosion, as 

defined in paragraphs 3.A and 3.B of Airbus Helicopters ASB AS365-

05.00.67 Revision 1 or ASB EC155-05A027 Revision 1, as applicable to 

helicopter model, is detected, before next flight, accomplish the applicable 

corrective action(s) in accordance with the instructions of paragraph 3.A 

and 3.B Airbus Helicopters ASB AS365-05.00.67 Revision 1 or ASB 

EC155-05A027 Revision 1, as applicable to helicopter model.

(5) Within 30 days after accomplishment of the actions required by paragraph 

(1) and (2) of this AD, report the inspection results to Airbus Helicopters in

accordance with the instructions of paragraph 1.E.2 of Airbus Helicopters 

ASB AS365-05.00.67 Revision 1 or ASB EC155-05A027 Revision 1, as 

applicable to the helicopter model.

Ref. Publications: Airbus Helicopters ASB AS365-05.00.67 Revision 1, dated 01 September 2014.

Airbus Helicopters ASB EC155-05A027 Revision 1, dated 01 September 2014.

The use of later approved revisions of these documents 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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

3. Enquiries regarding this AD should be referred to the Safety Information 

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: Airbus Helicopters (EBSESB) – Aéroport de 

Marseille Provence 13725 Marignane Cedex, France;

Telephone +33 (4) 42 85 97 97; Fax +33 (4) 42 85 99 66;

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