ALERT SERVICE BULLETIN AS332 

Approved under EASA DOA No. 21J.056. 32.00.18 Page 1/18

This document is available on the Internet: www.eurocopter.com/techpub 2010.07.12

 EUROCOPTER

HNIQUE SUPPORT

E CEDEX FRANCE CIVIL VERSION(S): C, C1, L, L1 

MILITARY VERSION(S): B, B1, M, M1, F1 

 DIRECTION TEC

13725 MARIGNAN

ALERT SERVICE BULLETIN 

No. 32.00.18 

 

 

SUBJECT: LANDING GEAR

 Solenoid valve power supply modification 

Corresponds to MODs 0725670, 332A088381 and 332P083218 

REVISION No. DATE OF APPROVAL DATE OF ISSUE

 

No. 0 2005.05.11 2005.05.24 

No. 1 2006.03.15 2006.03.27 

No. 2 2010.07.05 2010.07.12 

 
 ALERT SERVICE BULLETIN AS332 

1. PLANNING INFORMATION 

1.A. EFFECTIVITY 

1.A.1. Aircraft / installed equipment 

Helicopters pre-MOD 0723817: 

- not affected by MOD 0725670 (aircraft wiring) or on which Service Bulletin 32.00.12 was not complied with, 

- equipped with control panel 33G stated in paragraph 1.A.2. pre-MOD 0725670 or 332P083218 or 

332A088381 or on with Service Bulletin 32.00.12 was not complied with. 

Are not concerned: aircraft post-MOD ETAT S204 (Government Modification) forming the subject of KITS 

No. 332A07-2567-071 or 332A07-2567-072. 

Are not concerned : aircraft No. 2330, 2376, 2399, 2401 and 2403, version F1; they form the subject of Alert 

Service Bulletin No. 32.00.20 Revision 0. 

NOTE

Refer to the aircraft Individual Inspection Log Book (RIC 

AMS) or the aircraft Log Book to identify the actual 

modification status of the aircraft. 

1.A.2. Equipment not installed on aircraft 

- Control panel "33G", kneeling-type main L/G, no-NVG compatible, P/N 332A67-1623-00. 

- Control panel "33G", standard-type main L/G, no-NVG compatible, P/N 332A67-1623-06. 

- Control panel "33G", standard-type main L/G, no-NVG compatible, P/N 332A67-1623-0610. 

- Control panel "33G", standard-type, NVG-compatible main L/G, P/N 332A67-1623-0651. 

- Control panel "33G", NVG-compatible main L/G P/N 332P67-1601-00/01/02 and 03 of versions M1 and B1. 

1.B. ASSOCIATED REQUIREMENTS 

Not applicable. 

1.C. REASON 

- To prevent "main L/G retraction" solenoid valve actuation when aircraft is on ground. 

- Revision 0 of this Alert Service Bulletin formed the subject of an Airworthiness Directive published by 

DGAC on behalf of EASA. 

- Revision 0 of this Alert Service Bulletin superseded Service Bulletin No. 32.00.12 Revision 1, without 

however affecting its previous compliance. 

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 ALERT SERVICE BULLETIN AS332 

- Revision 1 of this Alert Service Bulletin is intended to: 

 modify paragraph 2.B.3.b. (Tests) in order to correct the checks to be carried out depending on 

position of "101G" switch and render the tests conform to those in Service Bulletin 32.00.12: 

- switch "101G" "emergency extension" on "normal", circuit closed between 33GA-c and 33GA-b 

(was open in Revision 0), 

- switch "101G" on "Emergency", circuit open between 33GA-d and 33GA-e, (was closed in Revision 

0). 

 extend compliance to control panels P/N 332A67-1623-0610. 

- Revision 1 of this Alert Service Bulletin formed the subject of a new Airworthiness Directive published by 

DGAC on behalf of EASA. 

- Revision 1 supersedes compliance with Revision 0 of this Alert Service Bulletin. 

- Revision 2 of this Alert Service Bulletin consists in specifying that this Alert Service Bulletin does not 

applies to aircraft version F1 No. 2330, 2376, 2399, 2401 and 2403 equipped with SLING/ASSIST optional 

equipment, but which will be modified by Alert Service Bulletin 32.00.20 Revision 0. 

- Revision 2 supersedes compliance with the previous revisions of this Alert Service Bulletin for versions F1 

(Flipper). 

1.D. DESCRIPTION 

Electrical interferences on the solenoid valve power supply line have caused untimely retraction of the main 

L/G, causing aircraft to sink, with resulting damage to the front section of the bottom structure. 

Therefore, EUROCOPTER renders compliance with this Alert Service Bulletin mandatory. 

Revision 0 of this Alert Service Bulletin consisted in: 

- shutting down +28V power supply to the "main L/G retraction" solenoid valve by a modification to the main 

L/G control tab on the "33G" control panel, 

- replacing the fixed connector on the "33G" main L/G control panel, 

- replacing the removable connector on the corresponding wiring. 

This is intended to prevent untimely power supply to the solenoid valve when the main L/G control tab is on 

"extended" and to avoid main L/G retraction. 

Revision 1 consists in making the tests compliant with Service Bulletin 32.00.12. 

Revision 2 consists in explaining that aircraft version F1, No. 2330, 2376, 2399, 2401 and 2403 equipped 

with SLING/ASSIST optional equipment will be modified by compliance with Alert Service 

Bulletin No. 32.00.20 Revision 0. 

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1.E. COMPLIANCE 

Eurocopter renders compliance with this Alert Service Bulletin mandatory 

1.E.1.Compliance at the works 

1.E.1.a. On aircraft 

Before delivery, comply with paragraph 2.B. of this Alert Service Bulletin. 

1.E.1.b. On equipment not installed on aircraft 

Before delivery, modify stock as per paragraph 2.B.5. 

1.E.2. Compliance in operation 

1.E.2.a. On aircraft / installed equipment: By operator 

Compliance with Revision 0 of this Alert Service Bulletin: 

Comply with paragraph 2.B. of this Alert Service Bulletin, by December 31, 2005, as from receipt of this 

Alert Service Bulletin, published at the date mentioned in the page footer. 

Compliance with Revision 1 of this Alert Service Bulletin: 

- for aircraft on which with this Alert Service Bulletin, Revision 0, had already been complied with, only 

comply with paragraph 2.B.3. (Tests) within 3 months as from receipt of this Alert Service Bulletin 

published at the date mentioned in the page footer, 

- for aircraft equipped with "33G" control panel, standard-type main L/G, non-NVG compatible, P/N 

332A67-1623-0610, comply with paragraph 2.B. within 3 months as from receipt of this Alert Service 

Bulletin published at the date mentioned in the page footer. 

1.E.2.b. On equipment not installed on aircraft: By operator 

Before installation on helicopter, modify stock of control panel as per paragraph 2.B.5. within 3 months as 

from receipt of this Alert Service Bulletin published at the date mentioned in the page footer. 

1.F. APPROVAL 

Approval is limited to civil version helicopters subject to an Airworthiness Certificate. 

1.F.1. Approval of modifications 

The information or instructions relate to Aircraft Modification Approval Form (FAM) No. 0725670 Issue 2 

which was approved on December 7, 1999 under the authority of DGAC Design Organization Approval 

No. F.JA01. 
 ALERT SERVICE BULLETIN AS332 

1.F.2. Approval of Alert Service Bulletin 

The technical information contained in this Alert Service Bulletin No. 32.00.18 Revision 0 was approved on 

May 11, 2005 under the authority of EASA Design Organization Approval No. 21J.056. 

The technical information contained in this Alert Service Bulletin No. 32.00.18 Revision 1 was approved on 

March 15, 2006 under the authority of EASA Design Organization Approval No. 21J.056. 

The technical information contained in this Alert Service Bulletin No. 32.00.18 Revision 2 was approved on 

July 05, 2010 under the authority of EASA Design Organization Approval No. 21J.056. 

1.G. MANPOWER 

Qualification 

For compliance with this Alert Service Bulletin, Eurocopter recommends the following personnel 

qualifications: 

Qualification: 1 Electrician. 

Time for the operations 

Time values are indicated for reference, for a standard configuration. 

Time for customers not having complied with Revision 0: 15 hours for Electrician. 

Time for customers having complied with Revision 0: 1 hour for Electrician (tests). 

1.H. WEIGHT AND BALANCE 

1.H.1. Weight 

Weight: Negligible. 

1.H.2. Moment 

Longitudinal moment: Negligible.

1.I. EFFECT ON ELECTRICAL LOADS 

Aircraft's electrical load analysis is not affected. 

1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD 

Not applicable. 

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1.K. REFERENCES 

The following documents are required for compliance with this Alert Service Bulletin: 

Maintenance Manual (MET): 

- Work Cards 24.00.00.301, 32.30.00.501, 32.30.00.502, 32.30.00.503 and 32.30.00.601. 

Standard Practices Manual (MTC): 

- Work Cards 20.07.03.406 and 20.07.03.408. 

1.L. OTHER DOCUMENTS AFFECTED 

This Alert Service Bulletin will give rise to amendment of the following documents by Eurocopter: IPC. 

This document will be circulated at a later date. 

1.M. TOOLING AFFECTED 

Not applicable. 

1.N. INTERCHANGEABILITY OR MIXABILITY OF PARTS 

1.N.1. Interchangeability 

New and former design control panels are not interchangeable. 

1.N.2. Mixability 

Not applicable. 
 ALERT SERVICE BULLETIN AS332 

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2. ACCOMPLISHMENT INSTRUCTIONS 

2.A. GENERAL 

- Instructions for intervention on aircraft electrical network and use of ground power networks as per MTC 

Work Card 20.07.03.406 or MET Work Card 24.00.00.301. 

- Guidelines for cleanliness check as per MTC Work Card 20.07.03.408. 

2.B. OPERATIONAL PROCEDURE. 

2.B.1. Preliminary steps 

- Implement suitable access means. 

- Comply with electrical safety instructions as per MTC Work Card 20.07.03.406 or MET Work Card 

24.00.00.301. 

2.B.2. Procedure 

2.B.2.a. Modification of "33G" main L/G control panel (Figures 1 and 2) 

- In "33G" control panel, disconnect all wires from fixed connector (a) after noting their connection 

markings and terminals. 

- Remove fixed connector (a) "2041PN" and scrap. 

- Install new connector (1) "2041PW"; connector's main fool-proofing device must face up control panel. 

- Suppress caps (b) from wire (c), in reserve allowance in "33G" control panel. 

- Swage contact (2) on connector (1) side of "33G" control panel, with adaptor (bb) 2.02, force 5. 

- Swage contact (10) on toggle switch "44G" side, with adaptor (bb) 7.02, force 4. 

- Connect wire (c) between terminal "W" of connector (1) and terminal "3A" of toggle switch "44G". 

- Reconnect wiring assembly to match previously noted markers. 

- Disconnect all wires from removable connector (d) after noting their connection markings and terminals. 

- Remove removable connector (d) "2041SN" and scrap. 

- Install new connector (5) "2041SW". 

- Reconnect wire "1GA9E" to terminal "W" of connector (5). 

- Reconnect wire "1GA10E", on connector side, to its initial position "R". 

- Reconnect wiring assembly to match previously noted markers. 

2.B.2.b. Modification of connector "100G" (Figures 1 and 2) 

- Remove backplane and unscrew connector (e). 

- Insulate wire "1GA25E" between removable connector (f) of "35G" L/G control unit and connector (e) with 

caps (7). 

- Use extractor (ee) to remove contacts. 

- Disconnect wire "1GA10E" from terminal "W". 

- Swage contact (11) with swaging pliers (dd), wire gauge 26/22, at terminal "W". 

- Reconnect wire "1GA10E" to terminal "19" of connector (e). 
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2.B.2.c. "1GA5103E" wiring routing (Figures 1 and 2) 

- Place wire (3) in "NOMEX" sheath (8). 

- Route wire (3) between removable connector (f) of "35G" L/G control unit and connector (5) of "33G" 

control panel as per electrical routing diagram (Figure 1). 

- Cut wire (3) to required length. 

- At each end of wire swage female contacts (6), adaptor (bb) 2.02, force 6. 

- Connect wire (3) between terminal "A" of removable connector (f) of "35G" L/G control unit and terminal 

"s" of connector (5) on "33G" control panel. 

- Bond label (12) on "33G" control panel in order to indicate new identification (332A67-1623-10) for 

aircraft equipped with non-kneeling main L/G or label (332A08-8381-01) for aircraft equipped with 

kneeling-type main L/G. 

- Identify NVG-compatible main L/G control panels as per paragraph 2.C. 

2.B.3. Functional tests 

2.B.3.a. Checking "33G" connector wiring electrical continuity 

Terminal Wire Terminal

33GA-G 1GX1NE 3Na (Ground) 

33GA-i 2GX2E 31L2-a23 

33GA-H 1GX2E 31L2-c22 

33GA-S 1GW13E 31L2-a37 

33GA-k 1GW14E 31L2-d27 

33GA-V 2GW13E 31L2-e23 

33GA-T 2GW14E 31L2-a36 

33GA-p 1GA7E 100GA-U 

33GA-r 1GA8E 100GA-V 

33GA-W 1GA9E 100GA-X 

33GA-R 1GA10E 100GA-19 

33GA-s 1GA5103E 35GB-A 

33GA-t 1GA13E 100GA-S 

33GA-n 1GA56F 103G4-B 

33GA-m 1GA15E 100GA-T 

33GA-g 1GA45NE 50P-U 

33GA-L 1GA16E 100GA-M 

33GA-U 1GA17E 100GA-N 

33GA-Z 1GW17E 31L2-d18 

33GA-a 1GW18E 31L2-d17 

33GA-K 1GA18E 100GA-A 

33GA-d 1GA27E 100GA-17 

33GA-h 1GA41E 100GA-18 

33GA-J 2GA3E 1G1 (2alpha) 

33GA-e 1GA40E 57 delta 2-H 

33GA-f 1GA42E 57 delta 2-J 

33GA-c 1GA38E 100GA-14 

33GA-b 1GA43E 35GB-C 

33GA-j 1GA44E 3 alpha-C (1G2) 
 ALERT SERVICE BULLETIN AS332 

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2.B.3.b. Checking "33GA" main L/G control panel wiring electrical continuity 

Switch "44G" on main L/G down: 

- circuit closed between 33GA-p and 33GA-r, 

- circuit open between 33GA-p and 33GA-W, 

- circuit open between 33GA-R and 33GA-s. 

Switch "44G" on main L/G up: 

- circuit open between 33GA-p and 33GA-r, 

- circuit closed between 33GA-p and 33GA-W, 

- circuit closed between 33GA-R and 33GA-s. 

Switch "46G": 

- circuit closed between 33GA-a and 33GA-Z, 

- circuit open between 33GA-U and 33GA-L. 

"REARM" button depressed: 

Circuit closed between 33GA-U and 33GA-L. 

Switch "sortie secours électrique" (electrical emergency extension) "101G" on "normal": 

- circuit closed between 33GA-d and 33GA-e, 

- circuit closed between 33GA-h and 33GA-f, 

- circuit closed between 33GA-c and 33GA-b, 

- circuit open between 33GA-j and 33GA-e, 

- circuit open between 33GA-g and 33GA-f. 

Switch "101G" on "SECOURS" (EMERGENCY): 

- circuit closed between 33GA-j and 33GA-e, 

- circuit closed between 33GA-g and 33GA-f, 

- circuit open between 33GA-d and 33GA-e, 

- circuit open between 33GA-h and 33GA-f, 

- circuit open between 33GA-c and 33GA-b. 

Light "EMERG" "48G1": 

Circuit closed between 33GA-k and 33GA-S. 

Light "EMERG" "48G2": 

Circuit closed between 33GA-T and 33GA-V. 

2.B.3.c. Checking electrical continuity of lighting system inside "33G" control panel (Figure 1 – Detail A) 

Check with ohmmeter: 

- contact between fixed connector (1) and internal lighting connector, 

- continuity between: 

- 33GA-G and connector mid-point (wire item 25), 

- 33GA-i and connector LH point (wire item 26), 

- 33GA-H and connector RH point (wire item 24). 
 ALERT SERVICE BULLETIN AS332 

2.B.3.d. L/G functional check 

- Set aircraft into test condition. 

- Carry out tests of main L/G (retraction, extension, W-o-W safety) as per MET Work Cards 32.30.00.501, 

502, 503 and 601. 

- Aircraft on jacks in “VOL” (FLIGHT) position, check that "REARM" light comes on after system power-up. 

- Rearm main L/G. 

2.B.4. Final steps 

- Disengage access means. 

- Carry out visual check of work zone as per MTC Work Card 20.07.03.408. 

- Restore aircraft to flight condition. 

2.B.5. Operational procedure on equipment not installed on aircraft 

2.B.5.a. Retrofitting of spare part stocks (Figures 1 and 2) 

Retrofit stock of main L/G control panels listed in paragraph 1.A.2. as follows: 

- in "33G" control panel, disconnect all wires from fixed connector (a) after noting their connection 

markings and terminals, 

- remove fixed connector (a) "2041PN" and scrap, 

- install new connector (1) "2041PW", connector's main fool-proofing device must face up control panel, 

- suppress caps (b) of wire (c), in reserve allowance in "33G" control panel 

- swage contact (2) on connector (1) side of "33G" control panel with adaptor (bb) 2.02, force 5, 

- swage contact (10) on toggle switch "44G" side, with adaptor (bb) 7.02, force 4, 

- connect wire (c) between terminal "W" of connector (1) and terminal "3A" of toggle switch "44G", 

- reconnect wiring assembly to match previously noted markers, 

- carry out electrical continuity tests as per paragraphs 2.B.3.b. and 2.B.3.c.., 

- re-identify post-MOD control panel as per table in paragraph 2.C. 

2.B.5.b. Replacement of spare part stocks 

Not applicable. 

2.C. IDENTIFICATION 

2.C.1. Identification of modifications in the documentation 

- Record compliance with this Alert Service Bulletin No. 32.00.18 Revision 2, and embodiment of MOD 

0725670 (3) in the aircraft documents. 

- Record embodiment of MOD 332A088381 (1) and 332P083218 (2) in the aircraft documents, according to 

aircraft configuration. 

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2.C.2. Identification of modifications on equipment 

Re-identify "33G" no-NVG compatible main L/G control panels as per table below. 

Key Word Former P/N New P/N Remark 

"33G" control panel, standard-type main 

L/G, no-NVG compatible 

332A67-1623-06 332A67-1623-10 (3) 

"33G" control panel, standard-type main 

L/G, no-NVG compatible 

332A67-1623-0610 332A67-1623-10 (3) 

"33G" control panel, kneeling-type main 

L/G, no-NVG compatible 

332A67-1623-00 332A08-8381-01 (1) 

Re-identify "33G" NVG compatible main L/G control panels, with ink, next to existing marking, and as per 

table below. 

Key Word Former P/N New P/N Remark 

"33G" main L/G control panel, NVG 

compatible 

332P67-1601-00 332P67-1601-08 (2) 

"33G" main L/G control panel, NVG 

compatible 

332P67-1601-01 332P67-1601-09 (2) 

"33G" main L/G control panel, NVG 

compatible 

332P67-1601-02 332P67-1601-10 (2) 

"33G" main L/G control panel, NVG 

compatible 

332P67-1601-03 332P67-1601-11 (2) 

"33G" main L/G control panel, NVG 

compatible 

332A67-1623-0651 332A67-1623-1051 (3) 

2.D. OPERATING AND MAINTENANCE INSTRUCTIONS 

2.D.1. Operating instruction(s) 

As per Flight Manual (PMV). 

2.D.2. Maintenance instruction(s) 

Not applicable. 
 ALERT SERVICE BULLETIN AS332 

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Figure 1

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 ALERT SERVICE BULLETIN AS332 

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3. MATERIAL INFORMATION 

3.A. MATERIAL: COST – AVAILABILITY 

3.A.1. Cost 

The kit will be delivered free of charge upon operator's order until June 30, 2006. 

3.A.2. Availability 

Kits or components will be delivered upon operator’s order. 

3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT 

Not applicable. 

3.C. MATERIAL REQUIRED FOR EACH AIRCRAFT, ENGINE/COMPONENTS 

3.C.1. Kit or component(s) to be ordered for 1 aircraft 

New P/N (in MPN) Qty Item Key Word Former P/N Instructions 

Disposition 

332A07-2567-072 Improvement of main L/G

locking on ground (W-o-W) 

E0053R20B41PWF 1 1 Connector 6100GAA20B41PN scrap 

EN3155-018M2020 1 2 Contact, to be swaged 

EN2266-005A004P 10 m 3 Wire, single core, UV laser 

E0052R20B41SWF 1 5 Connector 6114RAA20B41SN scrap 

EN3155-019F2020 2 6 Contact, to be swaged 

E0737R1332 2 7 Cap 

EN6049-003-04-5 10 m 8 Sheath, "NOMEX", braided 

EN3155-016M2018 1 10 Contact, to be swaged 

DHS715-121.20 1 11 Contact 

332A07-2567-099 1 12 Set of labels 

3.C.2. Material to be ordered separately 

Not applicable. 
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3.C.3. Ingredients to be ordered separately 

As per Work Cards mentioned in this Alert Service Bulletin. 

The ingredients can be ordered separately, from INTERTURBINE. 

Website: http://www.itlogistics.de

Telephone: +49.41.91.809.300 

AOG: +49.41.91.809.444 

3.C.4. Tooling(s) 

As per Work Cards mentioned in this Alert Service Bulletin and list below. 

P/N Material 

or equivalent Qty Item Key Word Instruction 

M22520/2.01 aa Swaging pliers 

M22520/2.02 and 

7.02 

bb Swaging pliers 

M81969-14-11 cc Fitting/extraction tool 

90028-3 dd Swaging pliers Gauge 26/22 

465195-1 ee Contact extractor 

AD1377 ff Swaging pliers 

GS-4H gg Tyrap clamp pliers 

AMP47386 hh Swaging pliers 

ii Multimeter 

3.C.5. Material required for item not installed 

For control panel modification, order kit 332A07-2567-072. 

3.D. PROCUREMENT CONDITIONS 

Order the required quantity from the EUROCOPTER network's Customer Support Sales Department 

From 

EUROCOPTER 

Etablissement de Marignane 

Direction VENTES Service Client 

S.V. 

13725 MARIGNANE CEDEX 

FRANCE 

NOTE 1

On the purchase order, please specify the mode of 

transport, the destination and the serial numbers of the 

aircraft to be modified. 
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NOTE 2

For ALERT SERVICE BULLETINS, order by: 

Telex: HELICOP 410 969F 

Fax: +33 (0)4.42.85.99.96 

4. APPENDIX 

Not applicable. 

 ALERT SERVICE BULLETIN AS332 

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NOTE 2

For ALERT SERVICE BULLETINS, order by: 

Telex: HELICOP 410 969F 

Fax: +33 (0)4.42.85.99.96 

4. APPENDIX 

Not applicable.