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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2006 - 0152 

Date: 30 May 2006

No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 

requirements of that Airworthiness Directive unless otherwise 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-2005-100, EASA approval No. 2005-5889 

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

Supply 

Manufacturer(s): EUROCOPTER (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 (AD) is issued following the discovery of 

electro-valve power supply disruptions which caused the landing gear to 

retract, the helicopter to drop, and damage 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 Alert 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. 
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Effective Date: 12 June 2006 

Compliance: 1. Reminder of the measures those are 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 with 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 Revision 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 with 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 Alert Service Bulletin No.32.00.18 R1. 

or later approved revisions. 

Remarks : 1. If requested and appropriately substantiated 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 Airworthiness Directive should be referred to 

Mr. M. Capaccio, Airworthiness Directive 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 13725 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