EUROCOPTER

CIVIL VERSION: B4

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE CEDEX FRANCE

SERVICE BULLETIN

No. 56-003

SUBJECT: WINDOWS

Center windscreen improvement

Corresponds to MOD 073590

REVISION No. DATE OF APPROVAL DATE OF ISSUE

Revision 0 On: November 16, 2010 2010.11.16

Approved under EASA DOA No. 21J.056. 56-003 Page 1/20

This document is available on the Internet: www.eurocopter.com/techpub 2010.11.16

SERVICE BULLETIN EC130
1. PLANNING INFORMATION

WARNING

THE INFORMATION AND INSTRUCTIONS IN THIS

SERVICE BULLETIN ARE INTENDED FOR

MAINTENANCE TEAMS AND FLIGHT CREWS.

1.A. EFFECTIVITY

1.A.1. Helicopters/installed equipment

Helicopters pre-MOD 073590.

NOTE

Refer to the aircraft Certificate of Conformity (or RIC AMSIndividual Inspection Log Book), the Equipment Log Cards

(FM) or the aircraft Log Book to identify the actual

modification status of the aircraft.

1.A.2. Non-installed equipment

Center windscreens P/N 350A25-9004-00, 350A25-9025-00 and 350A25-9041-20.

1.B. ASSOCIATED REQUIREMENTS

Not applicable.

1.C. REASON

To replace the center windscreen by a new windscreen with a changed curvature, thickness and material, offering

a higher strength.

Compliance with this service bulletin relieves from the obligation of compliance and is an alternative to the EASB

No. 05A005.

1.D. DESCRIPTION

Eurocopter was advised of a case a failure of the center windscreen in flight, resulting in a flight interruption but

without any incident for the passengers.

Besides, cases of center windscreen deformation in service were also reported.

The analyses conducted by Eurocopter showed that the center windscreen cracking phenomenon could be

worsened in case of local deformation of the windscreen. This phenomenon occurs at high airspeed, with a

deformation of the windscreen inwards the cabin together with an altered optical quality in some cases.

Eurocopter published EASB No. 05A005 in order to define an instruction for visual inspection before each flight

and for a maximum flight speed limitation in case of deformation in flight, until the panel is replaced.

Consequently, Eurocopter issued modification 073590 which consists of improving the center windscreen design

in order to lift the instructions dictated by EASB No. 05A005.

Approved under EASA DOA No. 21J.056. 56-003 Page 2/20

2010.11.16

SERVICE BULLETIN EC130
Therefore, EUROCOPTER recommends compliance with this Service Bulletin.

1.E. COMPLIANCE

1.E.1. Compliance at the works

1.E.1.a. On helicopters

Not applicable.

1.E.1.b. On non-installed equipment

Not applicable.

1.E.2. Compliance in service

1.E.2.a. On Helicopters/installed equipment

EUROCOPTER recommends compliance with this Service Bulletin.

The works must be performed on helicopter by Operator.

1.E.2.b. On non-installed equipment

Not applicable.

1.F. APPROVAL

1.F.1. Approval of modifications

The information or instructions relating to modification 073590 which was approved on April 14, 2009 by EASA

for helicopters of civil versions subject to an Airworthiness Certificate.

1.F.2. Approval of the Service Bulletin

The technical information contained in this Service Bulletin No. 56-003 Revision 0 was approved on November

16, 2010 under the authority of EASA Design Organization Approval No. 21J.056 for helicopters of civil versions

subject to an Airworthiness Certificate.

1.G. MANPOWER

1.G.1. Qualification

For compliance with this Service Bulletin Eurocopter recommends the following personnel qualifications:

Qualification:

- 1 Airframe Technician,

- 1 Mechanical Technician.

Specialist:

- 1 Painter.

Approved under EASA DOA No. 21J.056. 56-003 Page 3/20

2010.11.16

SERVICE BULLETIN EC130
1.G.2. Time for the operations

Time for the operations is indicated for reference, for a standard configuration.

Time for the operations:

- 10 hours approximately for Airframe Technician,

- 8 hours approximately for Mechanical Technician,

- 2 hours approximately for Painter.

1.G.3. Estimated helicopter grounding time

72 hours minimum inclusive of curing time.

1.H. WEIGHT AND BALANCE

1.H.1. Weight

Weight: + 1.458 kg.

1.H.2. Moment

Longitudinal moment: + 1.233 m.kg.

1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.

1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD

Not applicable.

1.K. REFERENCES

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

AMM : 12-30-00, 3-1 : Cleaning - Helicopter,

AMM : 24-00-00, 3-1 : General instructions – Electrical system,

AMM : 56-00-00, 3-1 : General instructions - Plexiglas,

AMM : 56-00-00, 3-2a : General instructions – Window panel bonding procedure (BETASEAL HV3),

General instructions – Window panel bonding procedure (SIKAFLEX 265 HF and

BETAMATE 7120),

AMM : 56-00-00, 3-2b :

AMM : 56-11-00, 4-1a : Removal / Installation - Windscreen (Pre-MOD 073544),

AMM : 56-11-00, 4-1b : Removal / Installation - Windscreen (Post-MOD 073544),

AMM : 56-11-00, 4-1c : Removal / Installation - Windscreen (Pre-MOD 073567 and 073568),

AMM : 60-00-00, 3-1 : General instructions - Mechanical,

MTC : 20.02.01.418 : Protection of electrical wiring during system maintenance, repair or modification operations,

MTC : 20.02.05.404 : Joining - Assembling by bolts and nuts,

MTC : 20.02.06.101 : Safetying and locking assemblies - General,

MTC : 20.02.06.409 : Safetying and locking assemblies – Safetying with LOCTITE compound,

Cleaning of parts - Description and use of standard cleaning products for individual parts

and on aircraft,

MTC : 20.04.01.102 :

Approved under EASA DOA No. 21J.056. 56-003 Page 4/20

2010.11.16

SERVICE BULLETIN EC130
Cleaning of parts - Cleaning removed detail parts with liquid solvents (bare, treated or

painted metal surfaces),

MTC : 20.04.01.402 :

Corrosion inhibiting and prevention procedures – Surface protective treatment against

corrosion,

MTC : 20.04.03.102 :

Paint and primer application procedure - General information concerning painting means

and paint touch-ups,

MTC : 20.04.05.101 :

MTC : 20.04.05.601 : Paint and primer application procedure – Checks after paint application,

MTC : 20.05.01.101 : General sealing procedures - General sealing methods,

MTC : 20.05.01.102 : General sealing procedures – Sealing compound application methods,

Sealing compounds used in structural repairs or on transmission assemblies – Sealing

compounds MASTINOX 6856 K and 6856 H,

MTC : 20.05.01.211 :

Sealing compounds used in structural repairs or on transmission assemblies – Sealing

compound PR 1829 B2,

MTC : 20.05.01.212 :

MTC : 20.06.01.101 : Bonding with adhesives - General rules for bonding with adhesive,

MTC : 20.07.02.201 : Safety instructions - Aircraft parked inside a hangar,

Technical instructions - Instructions applicable when working on an aircraft electrical circuit

or when energizing aircraft power generating systems on ground,

MTC : 20.07.03.406 :

Technical instructions - General principles applicable for visual cleanliness, appearance

checks on an aircraft after an inspection or repair.

MTC : 20.07.03.408 :

1.L. OTHER DOCUMENTS AFFECTED

1.L.1. Documents already updated

Not applicable.

1.L.2. Documents to be updated

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

These documents will be circulated at a later date.

The modification will be integrated in Illustrated Parts Catalog (IPC) for new aircraft. The IPC for retrofitted

aircraft will not be updated.

1.M. TOOLING AFFECTED

Not applicable.

1.N. INTERCHANGEABILITY OR MIXABILITY OF PARTS

1.N.1. Interchangeability

Interchanging parts is prohibited.

1.N.2. Mixability

Not applicable.

Approved under EASA DOA No. 21J.056. 56-003 Page 5/20

2010.11.16

SERVICE BULLETIN EC130
2. ACCOMPLISHMENT INSTRUCTIONS

2.A. GENERAL

- Comply with general safety instructions on electrical power generation as per Work Card 20.07.03.406 (MTC)

and as per Task 24-00-00, 3-1 (AMM).

- Comply with instructions for electrical earthing of aircraft as per Work Card 20.07.02.201 (MTC).

- Comply with general mechanical instructions as per Task 60-00-00, 3-1 (AMM).

- For system maintenance, repair or modification operations, protect electrical wiring as per Work Card

20.02.01.418 (MTC).

- Comply with general instructions concerning Plexiglas as per Task 56-00-00, 3-1 (AMM).

- For bonding window panels, comply with general instructions as per Task 56-00-00, 3-2a (AMM) and/or Task

56-00-00.3-2b (AMM).

- For windscreen installation comply with general sealing and sealant application methods as per Work Cards

20.05.01.101 and 20.05.01.102 (MTC).

- Clean parts by means of solvent as per Work Cards 20.04.01.102 and 20.04.01.402 (MTC).

- Carry out sealing and joining by means of MASTINOX sealant (24) (for protection against galvanic couple

corrosion on heterogeneous metal assemblies; this compound maintains some plasticity in the course of time

and allows easier removal during equipment overhaul) as per Work Card 20.05.01.211 (MTC).

- Comply with sealing and sealant application methods as per Work Cards 20.05.01.101 and 20.05.01.102 (MTC).

- Assemble by bolts and nuts and apply tightening torques as per Work Card 20.02.05.404 (MTC).

2.B. OPERATIONAL PROCEDURE

2.B.1. Preliminary steps

- Install access means.

- Remove panels and equipment as required for access to work zone.

- Disconnect all electrical power supplies, inclusive of the battery.

2.B.2. Procedure

CAUTION

THE WINDSCREEN ELEMENT IS FLEXIBLE BREAKS

VERY EASILY. HANDLE WITH THE UTMOST CARE AND

ONLY REMOVE PROTECTIVE FILMS ON COMPLETION

OF INSTALLATION.

2.B.2.a. Removing center windscreen

CAUTION

DURING REMOVAL OF CENTER WINDSCREEN, TAKE

ALL STEPS NOT TO DAMAGE CANOPY POSTS OR RH

AND LH WINDSCREENS.

Remove center windscreen as per Task 56-11-00, 4-1a or 56-11-00, 4-1b or 56-11-00, 4-1c (AMM).

Approved under EASA DOA No. 21J.056. 56-003 Page 6/20

2010.11.16

SERVICE BULLETIN EC130
2.B.2.b. Installing center windscreen (Figure 1, Figure 2, Figure 3)

CAUTION

DURING WINDSCREEN AND COVER STRIP

INSTALLATION, COMPLY WITH THE

COVERING/OVERLAPPING DIMENSIONS MENTIONED

IN THE VARIOUS ILLUSTRATIONS IN THIS SERVICE

BULLETIN.

2.B.2.b.1. Preparing canopy posts (Figure 1)

CAUTION

WHEN SANDING AND DEGREASING CANOPY POSTS,

PAY SPECIAL ATTENTION NOT TO DAMAGE LATERAL

WINDSCREENS.

- Apply adhesive tape (11) at edge of area to be sanded.

- Check that the adhesive compound was fully eliminated and sand the canopy posts and blending radii

with abrasive paper (10) as required.

- Clean by means of a lint-free cloth and thinner (Methyl-Ethyl-Ketone) (26) in order to eliminate any residue.

- Prepare surfaces before bonding as per Work Card 20.06.01.101 (MTC).

- Bond adhesive stops (2) on canopy posts to match the detailed location zone on Figure 1.

NOTE 1

Stops (2) will allow the adhesive product thickness to be

calibrated.

2.B.2.b.2. Preparing windscreen element for installation (Figure 1, Figure 2, Figure 3)

- Position windscreen element (1) on center canopy posts.

- Maintain windscreen (1) at center canopy posts by means of attachment bolts (a) and attachment washers

(min. outer diameter 20 mm (0.787 in.) and inner diameter 5 mm (0.197 in.)) on upper and lower attachment

points of cover strips (b).

- Check overlapping between window panel and canopy post (Details ZONES 1, 2, 3 and 4 of Figures 1

and 2):

. at zone 1: 17 mm +10/-2 (0.669 in. +0.394/-0.0787),

. at zone 2: 19 mm +10/-2 (0.748 in. +0.394/-0.0787). Maximum acceptable variation of play J is 1mm

(0.0394 in.) over a length of 100 mm (3.94 in.),

. at zone 3: 19 mm +/-4 (0.748 in. +/- 0.157),

. at zone 4: 11 mm +10/-3 (0.433 in. +0.394/-0.118).

CAUTION

IT MAY BE NECESSARY TO ADJUST WINDSCREEN

ELEMENT BY EDGE-TRIMMING.

- Adjusting center windscreen element (1) :

Mark area to be trimmed by means of adhesive tape (11) taking into account the overlapping dimensions

and plays to be met,

.

. remove windscreen element (1) from canopy post and trim marked area as per Task 56-00-00, 3-1 (AMM).

Approved under EASA DOA No. 21J.056. 56-003 Page 7/20

2010.11.16

SERVICE BULLETIN EC130
- Carry out finishing of windscreen element and check after trimming (on whole circumference of window

panel) as per Task 56-00-00, 3-1 (AMM).

- Reinstall trimmed windscreen (1) and check overlapping plays between window panel and canopy post.

NOTE 2

It may be necessary to relocate stops (2).

- On internal face of windscreen:

. remove protective film over a width of 50 mm approximately (1.97 in.),

. outline by means erasable felt tip pen (not aggressive for windscreen surface) zone (V) to be bonded,

corresponding to the thickness of canopy posts (Detail F),

. remove windscreen (1),

. bond adhesive tape (11) on whole internal periphery of windscreen (1) at a distance of 8 mm +2/0 (0.315

in. +0.0787/-0) from edge of zone (V) (Detail J),

. dry clean the felt tip pen mark and degrease windscreen's internal face by means of towelettes impregnated

with gasoline (20) and a lint-free cloth,

. sand the area (V) to be bonded by means of abrasive paper (12) in order to obtain a surface roughness

Ra 1.6 and to make the area entirely opaque,

. clean and degrease the whole sanded area by means of towelettes impregnated with gasoline (20).

2.B.2.b.3. Bonding center windscreen element (Figure 2, Figure 3)

NOTE 3

Bonding of windscreen (1) is ensured by docking and

centering the element on both center posts and on front

shield.

- Carry out bonding of center windscreen (1) by means of primer (21) and of adhesive (22) as per Task

56-00-00, 3-2b (AMM) and as per Paragraph 4.A.:

. press on whole bonded area of windscreen (1) to make the adhesive flow until windscreen is resting on

stops (2),

. secure windscreen (1) :

.. at center posts by means of 4 bolts (a) and 4 attachment washers previously used (min. outer diameter

20 mm (0.787 in.) and inner diameter 5 mm (0.197 in.)) (at uppermost and lowermost points),

.. by means of a strap in order to ensure correct docking at lower part of windscreen (do not tension the

strap: it is only used for security),

- Remove adhesive tapes (11).

- Comply with drying time for adhesive as per Task 56-00-00, 3-2b (AMM).

2.B.2.b.4. Installing finishing elements (Figure 2, Figure 3)

NOTE 4

The aircraft sideslip indicator (c) is installed on LH side for

the aircraft configuration with Pilot on LH side.

- After drying, remove attachment points of center posts and cross strap.

- On workbench, drill cover strips (3) to diameter 8.1 mm to match former cover strips (b) and attachment

holes (G) and (H). Deburr and apply protection against corrosion as per Work Card 20.04.03.102 (MTC).

- Installing cover strips (3) :

install cover strip (3), sideslip indicator support (c) and washers (d), apply Loctite (25) and bring bolts (5)

into contact. Tighten 1/6 of a turn,

.

Approved under EASA DOA No. 21J.056. 56-003 Page 8/20

2010.11.16

SERVICE BULLETIN EC130
. apply Loctite (25) and bring bolts (4) into contact. Tighten 1/6 of a turn,

. install second cover strip (3), apply Loctite (25) and bring bolts (4) into contact. Tighten 1/6 of a turn.

- Produce internal and external sealing bead by means of sealant (23) in order to eliminate any local adhesive

unevenness as per Work Card 20.05.01.212 (MTC).

- Remove protective films affixed on both faces of windscreen element (1).

- Post-MOD 073706, carry out UV protection of bonding zones on windscreen element (1) as per Task

56-00-00, 3-1 (AMM) (For aircraft pre-MOD 073706, it is possible to apply the UV protection on all window

panels via Service Bulletin No. 56-002).

- Carry out paint touch-up works with aircraft paint shade as per Work Cards 20.04.05.101 and

20.04.05.601 (MTC).

NOTE 5

Finishing paint touch-up works are incumbent on Operator.

2.B.3. Tests

Not applicable.

2.B.4. Final steps

- Clean windscreen elements as per Task 12-30-00, 3-1 (AMM).

- Check aspect and cleanliness as per Work Card 20.07.03.408 (MTC).

- Install panels and equipment which were removed during preliminary steps (Paragraph 2.B.1.).

- Reconnect all electrical power supplies, inclusive of the battery.

- Remove the access means.

- Set helicopter into flight condition.

2.B.5. Ground run/flight test

Not applicable.

2.C. OPERATIONAL PROCEDURE ON NON-INSTALLED EQUIPMENT

2.C.1. Stock retrofitting

Not applicable.

2.C.2. Stock replacement, stock scrapping and stock building-up

At the Operator's initiative, replace stocks of center windscreens P/N 350A25-9004-00, 350A25-9025-00 and

350A25-9041-20 by center windscreen P/N 350A25-9045-20.

2.D. IDENTIFICATION

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

Record embodiment of Modification 073590 and compliance with this Service Bulletin Revision 0 in the aircraft

documents.

Approved under EASA DOA No. 21J.056. 56-003 Page 9/20

2010.11.16

SERVICE BULLETIN EC130
2.D.2. Identification of modifications on equipment

Not applicable.

2.D.3. Identification of the new version

Not applicable.

2.E. OPERATING AND MAINTENANCE INSTRUCTIONS

2.E.1. Operating instructions

Not applicable.

2.E.2. Scheduled maintenance instructions

Not applicable.

2.E.3. Unscheduled maintenance instructions

Not applicable.

Approved under EASA DOA No. 21J.056. 56-003 Page 10/20

2010.11.16

SERVICE BULLETIN EC130
Figure 1

Approved under EASA DOA No. 21J.056. 56-003 Page 11/20

2010.11.16

SERVICE BULLETIN EC130
PAGE LEFT BLANK INTENTIONALLY

Approved under EASA DOA No. 21J.056. 56-003 Page 12/20

2010.11.16

SERVICE BULLETIN EC130
Figure 2

Approved under EASA DOA No. 21J.056. 56-003 Page 13/20

2010.11.16

SERVICE BULLETIN EC130
PAGE LEFT BLANK INTENTIONALLY

Approved under EASA DOA No. 21J.056. 56-003 Page 14/20

2010.11.16

SERVICE BULLETIN EC130
Figure 3

Approved under EASA DOA No. 21J.056. 56-003 Page 15/20

2010.11.16

SERVICE BULLETIN EC130
PAGE LEFT BLANK INTENTIONALLY

Approved under EASA DOA No. 21J.056. 56-003 Page 16/20

2010.11.16

SERVICE BULLETIN EC130
3. MATERIAL INFORMATION

3.A. MATERIAL: PRICE AND AVAILABILITY

3.A.1. Cost

3.A.1.a. Components

For any information concerning cost of modification kits and/or components or for assistance consult the

EUROCOPTER network's Customer Support Sales Department.

3.A.1.b. Tools

Not applicable.

3.A.2. Availability

3.A.2.a. Components

The kits or components will be delivered upon Operator's order.

3.A.2.b. Tools

Not applicable.

3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.

3.C. MATERIAL REQUIRED FOR EACH HELICOPTER/ENGINE /COMPONENT

3.C.1. Kits or components to be ordered for one helicopter or one assembly

Material P/N Qty Item Key Word Former P/N Instructions

350A07-3590-0071 1 Replacement center windscreen including:

350A25-9004-00 or Scrap

350A25-9025-00 or

350A25-9041-20

350A25-9045-20 1 (1) Center windscreen

350A25-9033-21 or Scrap

350A25-9033-23

SJ-5378 28 (2) Stop (adhesive)

PF-V-25/5.5 2 (3) Cover strip C561A1101101 Scrap

A0164TK050S020X 8 (4) Bolt A0164TK050S020X Scrap

A0164TK050S022X 2 (5) Bolt A0164TK050S022X Scrap

Approved under EASA DOA No. 21J.056. 56-003 Page 17/20

2010.11.16

SERVICE BULLETIN EC130
3.C.2. Material to be ordered separately

As per Work Cards and Tasks mentioned in this Service Bulletin.

Material P/N Qty Item Key Word

1 m (10) Abrasive paper 80

471L19BLANC 1 (11) Adhesive tape

1 m (12) Abrasive paper 400

NOTE 1

The quantities mentioned in the table above are estimates

and do not systematically correspond to the packaging of

all ingredients.

3.C.3. Material to be modified at the Manufacturer's or to be returned

Not applicable.

3.C.4. Products to be ordered separately

As per Work Cards and Tasks mentioned in this Service Bulletin and list below:

The ingredients may be ordered separately, from the INTERTURBINE AVIATION LOGISTICS Company,

Website: http://www.interturbine.com

Telephone: +49.41.91.809.300

AOG: +49.41.91.809.444

Material P/N Qty Item Key Word

ESSENCEGLT 5 liters (20) Gasoline G, 5-liter can

ECS2030.30 1 liter (21) Primer

ECS2028.30 1 liter (22) Adhesive (SIKAFLEX 265 HF)

ECS6046-1091 1 kg (23) Sealant (PR1829B2)

MASTINOX sealant, 160 ml

tube

MASTINOX 6856 K 160 ml (24)

LOCTITE 50cc – Medium

strength threadlocker

ASNA4018 50 cc (25)

MEK thinner

(Methyl-Ethyl-Ketone)

MEK 1 liter (26)

NOTE 2

The quantities mentioned in the table above are estimates

and do not systematically correspond to the packaging of

all ingredients.

Approved under EASA DOA No. 21J.056. 56-003 Page 18/20

2010.11.16

SERVICE BULLETIN EC130
3.C.5. Tools

As per Work Cards and Tasks mentioned in this Service Bulletin.

3.C.6. Material supplied by the User

Not applicable.

3.C.7. Material required for not-installed components

As required, place orders for material listed in Paragraph 3.C.1.

3.D. PROCUREMENT CONDITIONS

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

or from

EUROCOPTER

Etablissement de Marignane

Direction VENTES Service Client (C.R.)

13725 MARIGNANE CEDEX

FRANCE

NOTE 3

On the purchase order, please specify the mode of

transport, the destination and the serial numbers of the

aircraft to be modified.

Approved under EASA DOA No. 21J.056. 56-003 Page 19/20

2010.11.16

SERVICE BULLETIN EC130
4. APPENDIX

4.A. DETAILED INSTRUCTIONS FOR ADHESIVE APPLICATION

Approved under EASA DOA No. 21J.056. 56-003 Page 20/20

2010.11.16

SERVICE BULLETIN EC130

4. APPENDIX

4.A. DETAILED INSTRUCTIONS FOR ADHESIVE APPLICATION

Approved under EASA DOA No. 21J.056. 56-003 Page 20/20

2010.11.16

SERVICE BULLETIN EC130