EASA AD No.: 201 4

- 0214

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 201 4

- 0214

Date: 24 September 201 4

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 E U 748/2012 , Part 21

. A.3B. In accordan ce 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 ope rate 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

F oreign AD: Not applicable

Supersedure: N one



### ATA 2 5 Equipment / Furnishing

– External L ife R afts

– Inspection

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

Applicability: AS 365 N 3 helicopters

, all manufacturer serial numbers , if equipped with

exter nal 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 exter nal life rafts in the footsteps with junction units having MP/N 200188 ( Airbus Helicopters P/N 704A34130 2.30).

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 t he failure occurred during an attempt to release the life raft by pulling the left hand (LH) internal deployment handle. Subsequent
i nvestigations revealed presence of corrosion damage inside the LH junction
unit

, which block ed t he 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 a ny corrosion

.EASA AD No.: 201 4

- 0214

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: 01 October 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously:

(1) B efore 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 requir ed 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 an d inspect for corrosion the LH an d RH junction
unit s of the external life raft deployment system in accordance with the instructions of paragraph s 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 an d RH junction unit s of the external life
raft deployment system in accordance with the instructions of paragraph s 3.A and 3.B of Airbus Helicopters ASB AS365

- 05.00.67 Revision 1 or 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
de fi n ed in paragraph s 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 ) W ithin 30 days after accomplishment of the actions required by paragraph (1) and (2) of this AD

, report the inspection result s 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 th e s e document s 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 pu blication.

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 re quirements in this AD, please contact: Airbus Helicopters ( EBSESB )

– Aéroport de Marseille Provence 13725 Marignane Cedex, France; Telephone +33 (4) 42 85 97 97; F ax +33 (4) 42 85 99 66;
E

- mail: Directive.technical

- support@ airbus.com

.