# ASB No. EC120-52A014

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### Civil version(s): B



# ALERT SERVICE BULLETIN

SUBJECT: DOORS - Sliding door

Attachment of the sliding door star support

Revision No. Date of issue

Revision 0 2004-01-16

Revision 1 2013-01-25



### Summary:

Reinforce the sliding door star support attachment.



### Reason for last Revision:

The purpose of Revision 1 of this ALERT SERVICE BUL LETIN is to change Service Bulletin No. 52-014 into

ALERT SERVICE BULLETIN No. 52A014, to make mandator y the improvement of the sliding door star support

attachment.



### Compliance:

EUROCOPTER makes compliance with this ALERT SERVICE BULLETIN mandatory. For the a ttention of

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### 1. PLANNING INFORMATION

1.A. EFFECTIVITY

1.A.1. Helicopters/installed equipment

Helicopters whose serial number (S/N) is strictly l ower than 1368, equipped with sliding door P/N

C526A2370101, on which Revision 0 of this ALERT SER VICE BULLETIN was not complied with.

1.A.2. Non-installed equipment

Sliding doors (MP/N) C526A2370101 which did not com ply with Revision 0 of the Service Bulletin N° 52-0 14.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1.C. REASON

Revision 0:

Avoid paint chips on the sliding door outside skin on external rivets, by reinforcing the star support pin

attachment.

Revision 1:

EUROCOPTER has been informed of an incident concern ing the star support pin rupture. This part is

located on the kinematics of the sliding door locki ng system.

The star support pin rupture make makes impossible all sliding door operations.

Investigations have revealed that the helicopter af fected had not complied with Revision 0 of this Ser vice

Bulletin No 52-014.

The purpose of Revision 1 is to:

- change Service Bulletin No. 52-014 into ALERT SER VICE BULLETIN No. 52A014, to make mandatory

embodiment of improvement of the sliding door star support attachment,

- add a star pin dye penetrant inspection procedure

, - add removal and installation procedures of a part of the locking system kinematics,

- to make this revision compliant with the new ALER T SERVICE BULLETIN layout.

EUROCOPTER therefore makes mandatory the star pin c heck using dye penetrant inspection, as well as

compliance with the improvement (doubling the star support pin yoke).

Revision 1 of this ALERT SERVICE BULLETIN does not supersede compliance with Revision 0 of the

Service Bulletin No 52-014.



### 1.D. DESCRIPTION

The improvement consists in reinforcing the star su pport pin using a double yoke system, which enables the

rod stress to be more efficiently sustained, which thus avoids this pin to brake.

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### 1.E. COMPLIANCE

1.E.1. Compliance at the works

Not applicable.

1.E.2. Compliance in service

The works must be performed on helicopter by the op erator.

Helicopters/Installed equipment:

Comply with Paragraph 3. of this ALERT SERVICE BULL ETIN before reaching 165 flying hours without

exceeding 2 years, following receipt of this ALERT SERVICE BULLETIN, issued on the date mentioned in

page footer.

Non-installed equipment:

Modify stock as per paragraphs 3.A. and 3.B.4. of t his ALERT SERVICE BULLETIN, prior to installation o n

helicopter and without exceeding 2 years.



### 1.F. APPROVAL

Approval of modifications:

The information or instructions relate to Aircraft Modification Approval Form (FAM) A00565 Issue 1 whi ch

was approved on April 03, 2003 under the authority of DGAC Design Organisation Approval No.FJA01.

Approval of this document:

The technical information contained in this Service Bulletin No. 52-014 Revision 0 was approved on

January 16, 2004 under the authority of DGAC Design Organization Approval No. F.JA01.

The technical information contained in this ALERT S ERVICE BULLETIN Revision 1 was approved on

January 24, 2013 under the authority of EASA Design Organization Approval No. 21J.056 for helicopters of

civil versions subject to an Airworthiness Certific ate.

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### 1.G. MANPOWER

For compliance with this ALERT SERVICE BULLETIN, EU ROCOPTER recommends the following personnel

qualifications:

Qualifications: - 2 Mechanical Technicians,

- 1 Composite Specialist.

Times are given for reference, for a standard confi guration.

Time for the operations: - 5 hours (approximately) for the removal/installation of the sliding door,

covering and linkage for 2 mechanical technicians,

- 5 hours (approximately) for the replacement of th e star support and glass

fabric plies for 1 composite specialist.

The estimated helicopter grounding time is one day and a half approximately, excluding curing time of glass

fabric ply/plies under vacuum bag and drying of the different products.



### 1.H. WEIGHT AND BALANCE

Weight: 0.06 kg.

Longitudinal moment: 0.132 m.kg

Lateral moment: -0.042 m.kg

Vertical moment: -0.139 m.kg



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD

Not applicable.

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### 1.K. REFERENCES

The following documents are necessary for complianc e with this ALERT SERVICE BULLETIN:

Aircraft Maintenance Manual (AMM):

20-10-00, 3-1 : Locking - Airframe

20-10-00, 3-8 : Cleaning of Mechanical Parts - Ai rframe

20-10-00, 3-10 : Method for Application of Primer P aints - Airframe

20-10-00, 3-14 : Method for application of Sealants - Airframe

20-10-00, 3-15 : Bonding with Adhesives - Airframe

20-10-00, 3-19 : Dye Check - Airframe

20-10-00, 3-27 : Method for Installing and Replacin g the Rivets - Airframe

20-10-00, 3-32 : Bonding with adhesive (HYSOL EA 93 96)

20-10-00, 3-33 : General riveting acceptance requir ements - Airframe

20-10-00, 3-35 : Resin Application Procedure HYSOL EA 9395 - Airframe

20-10-00, 3-43 : Monitoring of Equipment in Service , Marking and Specific version Identification - Air frame

20-10-00, 3-45 : Method for Installation of Blind R ivets ASN-NSA 1919 et 1921 - Airframe

20-20-00, 3-1 : Standard Practices - Structure

25-23-00, 4-1 : Removal / Installation - Upholste ry

52-50-00, 4-1 : Removal - Cabin Sliding Doors Ass y 52-50-00, 4-2 : Installation - Cabin Sliding Door s Assy

52-50-00, 6-1 : Inspection - Cabin Sliding Door



### 1.L. DOCUMENTS AFFECTED

Not applicable.



### 1.M. INTERCHANGEABILITY OR MIXABILITY OF PARTS

Not applicable.

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### 2. MATERIAL INFORMATION

2.A. MATERIAL: PRICE - AVAILABILITY - PROCUREMENT

For all information concerning the kits and/or comp onents, contact the EUROCOPTER Network Sales and

Customer Relations Department.

Order the required quantity from:

EUROCOPTER

Etablissement de Marignane

Direction Ventes et Relations Client (ECR)

13725 MARIGNANE CEDEX

FRANCE



### NOTE 1

On the purchase order, please always specify the mo de of

transport, the destination and the serial numbers o f the

aircraft to be modified.



### NOTE 2

For ALERT SERVICE BULLETINS, order by:

Telex: HELICOP 410 969F

Fax: +33 (0)4.42.85.99.96.



### 2.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.



### 2.C. MATERIAL REQUIRED FOR EACH HELICOPTER/COMPONEN T

Kits or components to be ordered for one helicopter or one assembly:

Key Word Qty New

P/N Item Former

P/N Instruction

Kit including: 1 C008A005650071 / / /

Cotter pin 1 EN2367-18020 10 EN2367-18020 Scrap

Cotter pin 3 23310CA010015 11 23310CA010015 Scrap

Plate 1 C526A2370201 15 / /

Angle bracket 1 C526A2369201 16 / /

Rivet 2 21215TB3205 18 / /

Blind rivet 4 ASNA0077E406 19 / /

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Key Word Qty New

P/N Item Former

P/N Instruction

Support AR 677-1-20-511 2 677-1-20-511 /

Rivet 1 NAS1919C04S03U 3 NAS1919C04S03U Scrap

Rivet 3 ASNA0077E403 4 ASNA0077E403 Scrap

Glass fabric AR ECS0030-27 6 ECS0030-27 Scrap

Dry carbon fabric AR ECS0031-12 13 / /

End fitting AR 677-1-10-514 14 677-1-10-514 /

Products to be ordered separately:

As per Tasks mentioned in this ALERT SERVICE BULLET IN and list below:

Key Word Qty Product P/N CM Item

Adhesive AR ECS6054-1031 6041 1

Adhesive tape AR Scotch 3M 471 or equivalent 783 5

Adhesive compound AR ECS0010.10 / 7

Primer paint AR ECS2067.20 / 8

Grease AR DCSEA354 115 9

Grease AR DCSEA395 101 12

Sealant AR ECS2068.10 6240 17

The products can be ordered separately, from INTER TURBINE AVIATION LOGISTICS company.

Website: http://www.interturbine.com

Phone: +49.41.91.809.300

AOG: +49.41.91.809.444



### 2.D. MATERIAL TO BE RETURNED

Not applicable.

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### 3. ACCOMPLISHMENT INSTRUCTIONS

3.A. GENERAL

Read and comply with instructions for safetying as per AMM Task 20-10-00, 3-1.

Read and comply with instructions for cleaning as p er AMM Task 20-10-00, 3-8.

Read and comply with instructions for bonding with adhesives as per AMM Task 20-10-00, 3-15.

Read and comply the method for installing and repla cing the rivets as per AMM Task 20-10-00, 3-27.

Read and comply standard practices as per AMM Task 20-20-00, 3-1.



### 3.B. OPERATIONAL PROCEDURE

3.B.1. Preliminary steps (Figure 1)

- Park the helicopter in a hangar.

- Clear access to work zones.

- Install suitable access means.

- Remove sliding door

(a) (Figure 1) as per AMM Task 52-50-00, 4-1 and install it on a workbench.

- Remove the sliding door skin as per AMM Task 25-23-00, 4-1.

- Protect the covering of sliding door (a) and inst all it on a workbench.

3.B.2. Reinforcing the sliding door star support at tachment (Figures 1 to 6)

3.B.2.a. Disconnecting rods and removing the star ( Figure 1)

- Remove and discard cotter pins (e) (Detail A, Fig ure 1).

- Remove pins (d).

- Disconnect rods (b), (c) and (j) from star (h), a nd lock them in order to disengage the work zone.

- Remove and scrap cotter pin (f) and washer (g)

. - Remove star (h).

3.B.2.b. Visual inspection of upper and lower locki ng pin control rod end fittings (Figure 1)

- Examine both end fittings (s) (Detail A, Figure 1 ) and make sure that they are neither twisted nor

broken:

. if both end fittings (s) are neither twisted nor broken:

- leave as is,

- comply with Paragraph 3.B.2.c.

. if at least one of the two end fittings is twisted or broken : - using a rule, measure and record length (L),

- loosen locknut (r),

- loosen and remove end fitting (s) concerned,

- remove locknut (r),

- scrap end fitting (s),

- clean locknut (r) threading with Methyl-ethyl-ket one (13) in order to remove any trace of

thread lock,

- screw locknut (r) on end fitting (14) threading t o length (L),

- screw end fitting (14) until locknut (r) touches the related rod,

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### NOTE 1

End fitting (14) can be screwed in or out a quarter turn

maximum to enable free pin (d) fitting into star (h).

- lock the related rod in order to disengage the wo rk zone.

3.B.2.c. Checking the star support pin using dye pe netrant inspection (Figures 1 to 4)

- Clean zones X and Y (Detail C, Figure 3).

- Check for cracks on pin (k 1 ) of support (k), on zones X and Y using a dye pene trant inspection as per

AMM Task 20-10-00, 3-19:

. If no cracks are found:

- put star (h) in position (Detail A, Figure1),

- embody the improvement of the sliding door star s upport attachment as per Paragraph

3.B.2.d.

. If there is a crack:

- remove and scrap glass fabric plies (p) (interven tion zone E, Figure 4),

- clean contact surfaces between glass fabric plies (p) and sliding door (a) skin,

- remove and scrap rivet (m) (Detail B, Figure 2) a nd the three rivets (n),

- remove and scrap support (k),

- clean contact surfaces between sliding door (a) s kin and support (k),

- interlay adhesive (1) (not shown in the Figure) b etween sliding door (a) skin and support (2)

as per AMM Task 20-10-00, 3-35,

- put support (2) in position using a rivet (3) and three rivets (4) as per AMM Task

20-10-00, 3-33 and 20-10-00, 3-45,

- delimit work zone Z (intervention zone E, Figure 4) using adhesive tape (5) (not shown in the

Figure),



### CAUTION

WHILE GRINDING, DO NOT DAMAGE THE FIRST

PLIES OF SLIDING DOOR (a) SKIN IN CARBON

FABRIC (DETAIL D, FIGURE 4).

- using abrasive paper (grit size 80 to 240), remov e the finish paint and primer paint on

work zone Z, up to the carbon fiber,

- cut out three square-shaped glass fabric plies (6 ) as per intervention zone E (Figure 4),



### NOTE 2

If the surface of a glass fabric ply (6) enables it , it is possible

to cover several rivet heads with only one glass fa bric ply (6).

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### NOTE 3

When installing to the center a glass fabric ply (6 ) on several

rivet heads (4), it is necessary to leave a distanc e of at least

20 mm (.79 in.) between rivet head (4) and the squa re outer

edge.

- apply adhesive compound (7) on the glass fabric p ly/-ies (6) as per

AMM Task 20-10-00, 3-32,

- center a glass fabric ply (6) on apparent rivet h eads (4),

- cure the glass fabric ply/-ies (6) in a vacuum ba g,

- carry out a surface treatment before painting,

- apply a primer paint layer (8) on work zone Z as per AMM Task 20-10-00, 3-10,

- apply a finish paint layer as per the color of sl iding door (a) outer skin (Detail D, Figure 4),

- apply grease (9) (Detail C, Figure 3) on Zone X,

- put star (h) in position (Detail A, Figure 1),

- carry out the improvement of the star attachment as per paragraph 3.B.2.d.

3.B.2.d. Embodiment of modification A00565 - Reinfo rcing the sliding door star support (Figures 5 and 6)

- Reinforce stringer (q) (Section H-H, Figure 6) by means of three carbon fabric plies (13) soaked wit h

adhesive (7).



### NOTE 4

The orientation of carbon fabric plies (13) has no importance

whatsoever.

- Put in position plate (15) on support (k) or (2) pin and center it.

- Put in position angle bracket (16) under stringer (q) and put it against plate (15).

- Secure angle bracket (16) and plate (15) assembly

. - Counter-drill two holes dia 3.3 mm (.13 in.) in a ngle bracket (16), to match plate (15) holes.

- Pin angle bracket (16) and plate (15).

- Counter-drill four holes dia 3.3 mm (.13 in.) in stringer (q), to match angle bracket (16) holes.

- Interlay sealant (17) between angle bracket (16) and plate (15), as per AMM Task 20-10-00, 3-14.

- Put in position angle bracket (16) on plate (15) by means of two rivets (18) (Detail G, Figure 6).

- By means of four rivets (19) (Section J-J, Figure 6), put in position plate (15) (Section H-H, Figur e 6) and

angle bracket (16) assembly on stringer (q).

- Put in position cotter pin (10) (Detail A, Figure 1) without locking it.

- Connect rods (b), (c) and (j) to star (h), and se cure them by means of pins (d).

- Lock each pin (d) by means of a cotter pin (11).

- Apply grease (12) (Detail B, Figure 2) to zones T , U, V and W.

- Lock star (h) (Detail F, Figure 5) by means of co tter pin (10) (Detail G, Figure 6).

- Mark as per Paragraph 3.C. of this ALERT SERVICE BULLETIN.

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- Put in position sliding door (a) skin as per AMM Task 25-23-00, 4-1.

- Put in position sliding door (a) as per AMM Task 52-50-00, 4-2.

- Perform operating test of the sliding door as per AMM Task 52-50-00, 6-1.

- Perform aircraft appearance checks.

- Remove the access means.

3.B.4. Operational procedure on non-installed equip ment

- Retrofit stock of sliding doors as per Paragraph 3.B.2. of this ALERT SERVICE BULLETIN.



### 3.C. IDENTIFICATION

Identification of this document:

Record compliance with this ALERT SERVICE BULLETIN Revision 1 on the helicopter documents.

Identification of modifications on the equipment:

Identify the assembly as per the table below and AM M Task 20-10-00, 3-43.

Key Word Former P / N New P/N MOD Marking type

Sliding door

assembly C526A2370101 C526A2370101

+ ASB No. 52A014 R1 ASB No. 52A014 R1 Indelible ink



### 3.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Not applicable.

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## PAGE LEFT BLANK INTENTIONALLY

# ASB No. EC120-52A014

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e

11 h c

j

d

e

11

e

11

d d

f

g

10 b s

14

r

s

14 L

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Figure 2: Star support, star pin and definition of the zones to be greased

a

h k

2

m

3 n

4 n

4

k 1 (See Figure 3)

Zone U

Zone V Zone W Zone T

CM 6240 CM 6240

12 12

# ASB No. EC120-52A014

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Zone X (See Figure 2)

CM 115

9

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zones E

4

p

6

7

8

Work zone Z 

## Intervention zone E

110 mm (4.33 in.) 100 mm

(3.94 in.) aASBNo. EC120-52A014Revision 0 2004-01-16Page 17/19Revision 1 2013-01-25This document is available on the Internet:www.eurocopter.com/techpubFigure 5PRE MODhfgASBNo. EC120-52A014Revision 0 2004-01-16Page 18/19Revision 1 2013-01-25This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC120-52A014Revision 0 2004-01-16Page 19/19Revision 1 2013-01-25This document is available on the Internet:www.eurocopter.com/techpubFigure 6SectionJ-JSectionH-H18POST MOD151716713q191510k ou/or 2