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## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2006 - 0152

Date: 30 May 2006

No person may operate an aircraft to which an Airworthi ness Directive applies, except in accordance with the requirements of that Airworthiness Directive unless otherwi se agreed with the Authority of the State of Registry.


### Type Approval Holder’s Name:

EUROCOPTER Type/Model designation(s) :

AS 332 C, C1, L and L1 helicopters

TCDS Number: France 127

Foreign AD: None

Supersedure: DGAC AD F-2005-1 00, EASA approval No. 2005-5889



### ATA: 32 Landing Gear – Modification to the Electro-Valve Power Supply

Manufacturer(s): EUROCOPT ER (Formerly EUROCOPTER FRANCE, AEROSPATIALE)

Applicability: AS 332 C, C1, L and L1 helicopters not modified per MOD 0723817 and: - not modified per MOD 0725670 (helicopter wiring) or per EUROCOPTER AS 332 Service Bulletin (SB) No. 32.00.12, - equipped with a control unit “33 G”, part number (PN) 332A67- 1623-00, 332A67-1623-06, 332A67-1623-0610 or 332A67-1623- 0651, not modified per MOD 0725670 or 332P083218 or 332A088381 or per AS 332 SB No. 32.00.12.

Reason: This Airworthiness Directive (A D) is issued following the discovery of electro-valve power supply disruptions which caused the landing gear to retract, the helicopter to drop, and dam age to the forward section of the bottom structure. This latest AD supersedes AD F-2005-100 and covers Revision 1 of referenced EUROCOPTER AS 332 Aler t Service Bulletin (ASB)

No. 32.00.18 in order to:

- extend applicability to a new control unit “33 G” (PN 332A67-1623- 0610),

- correct the definition of the functional tests to be carried out.

### 2/2 Effective Date: 12 June 2006

Compliance: 1. Reminder of the measures those ar e mandatory as from July 2, 2005, the effective date of AD F-2005-100.

At the latest by December 31, 2005, modify landing gear control unit “33G” and its wiring, and check these modifications by carrying out functional tests, in compliance wi th the instructions specified in paragraph 2.B. of Revision 0 of EUROCOPTER AS 332 ASB No. 32.00.18.

2. The following measures are mandatory as from the effective date of this AD:

2.1. Helicopters having already been modified in compliance with DGAC AD F-2005-100 and Revi sion 0 of the referenced ASB:

No later than within 3 months, repeat the functional tests to check the modifications, in compliance with the instructions specified in paragraph 2.B.3. of the referenced ASB.

2.2. Helicopters fitted with control unit “33G” PN 332A67-1623-0610.

No later than within 3 months, modify this control unit and its wiring and then check these modifications by carrying out functional tests, in compliance wi th the instructions specified in paragraph 2.B. of the referenced ASB.

2.3. No later than within 3 months: before installation on a helicopter, of control units defined in this AD and held as spares, comply with the instructions specified in paragraph 2.B.5. of the referenced ASB.

Ref. Publications: EUROCOPTER AS 332 Al ert Service Bulletin No.32.00.18 R1.
or later approved revisions.

Remarks : 1. If requested and appropriately su bstantiated the responsible EASA manager for the related product has the authority to accept Alternative Method of Compliance (AMOCs) for this AD.
2. This AD was posted as PAD 06-073 for consultation on 22 March 2006 with a comment period until 5 April 2006. No comment was raised during the consultation period. 3. Enquiries regarding this Airworthin ess Directive should be referred to Mr. M. Capaccio, Airworthiness Dire ctive Focal Point - Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any questions concerning the technical content of the requirements in this AD, please contact: EUROCOPTER (STXI) - Aéroport de Marseille Provence 1 3725 Marignane Cedex - France. Ph.: 33 (0) 4 42 85 97 97 - Fax: 33 (0) 4 42 85 99 66. E-mail: Directive.technical-support@eurocopter.com