EASA AD No.: 2013

- 0173

TE. CAP.00110

- 00 3 © 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

. : 2013

- 0173

Date: 01 August 2013

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 :

EUROCOPTER Type/Model designation(s) :

AS 332 L1 and EC 225 LP helicopters

TCDS Number: EASA.R.002

F oreign AD: Not applicable

Supersedure: None



### ATA 3 0 Ice and Rain Protection

– Electrical M ulti

- Purpose Air Intakes

– Modification

Manufacturer(s): Eurocopter (formerly EUROCOPTER France)

Applicability: AS 332 L1 helicopter manufacturer serial number ( S/N ) 2774, and EC 225 LP helicopter manufacturer S/N 2600, S/N 2623, S/N 2645, S/N 2656, S/N 2659, S/N 2663, S/N 2666, S/N 2670, S/N 2673, S/N 2685, S/N 2691, S/N 2692, S/N 2693, S/N 2702, S/N 2715, S/N 2716, S/N 2721, S/N 2725, S/N 2739, S/N 2744, S/N 2747, S/N 2753, S/N 2756, S/N 2759, S/N 2767, S/N 2779 and S/N
2794.

Reason: For some helic opters equipped with electrical Multi

- Purpose Air Intakes (MPAI), power generation failure conditions were identified that would caus e power supply loss of the engine electro

- valves controlling inflat ion of the MPAI seals to close the engine air intakes

. Th e power supply loss on these electro

- valves result s in deflation or not inflation of MPAI seals on both engine air intakes.

This condition, if not corrected, could lead to ice ingestion by the engines during flight in icing conditions possibly resulting in dual engine flame

- out.

To address this unsafe condition , E urocopter issued Aler t Service Bulletin (ASB) No.AS332

- 30.00.74 and ASB No.EC225

- 30A032 to provide modification of some electrical bus bars and circuit breakers (MOD 332P083736.01, MOD 332P083736.02 and MOD 332P083736.05) for affected helicopters.

For the reasons described abov e, this AD r equir es accomplishment of modification MOD 332P083736.01 or MOD 332P083736.02 or MOD 332P083736.05, as applicable to helicopter model and serial number, and update the Rotorcraft Flight Manual ( RFM )

.EASA AD No.: 2013

- 0173

TE. CAP.00110

- 00 3 © 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: 08 August 2013

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:
(1) Within 110 flight hours after the effective date of this AD, accomplish modification specified in Table 1 below, as applicable to helicopter model and serial number

, in accordance with the instructions of paragraph 3. of Eurocopter ASB No.AS332

- 30.00.74 or ASB No EC225

- 30A032, as applicable to helicopter models. Table 1

Helicopter models and serial numbers

(S/N) Required modification

AS 332 L1 with S/N 2774 MOD 332P083736.05

EC 225 LP with S/N 2600, S/N 2623, S/N 2645, S/N 2656, S/N 2659, S/N 2663, S/N 2666, S/N 2670, S/N 2673, S/N 2693 MOD 332P083736.01

EC 225 LP with S/N 2685, S/N 2691, S/N 2692, S/N 2702, S/N 2715, S/N 2716, S/N 2721, S/N 2725, S/N 2739, S/N 2744, S/N 2747, S/N 2753, S/N 2756, S/N 2759, S/N 2767, S/N 2779, S/N 2794 MOD 332P083736.02

(2) Concurrently with the modification as required by paragraph (1) of this AD amend the RFM by inserting a copy of the pages of the Appendix of Eurocopter AS B No.AS332

- 30.00.74 or ASB No EC225

- 30A032, as applicable to helicopter model, and operate the helicopter accordingly.

Th e RFM amendment can also be accomplished by incorporating later applicable RFM revision s

.

Ref. Publications: Eurocopter ASB No. AS33 2

- 30.00.74, revision 0, dated 31 July 2013

. Eurocopter ASB No. EC225

- 30A032

, revision 0 dated 31 J uly 2013.
The use of later approved revisions of th i s 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. 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 A D should be referred to the Safety Information Section, Executive 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) 42 85 97 97, Facsimile +33 (4) 42 85 99 66 E

- mail: Directive.technical

- support@eurocopter.com

.