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 BULLETIN is to change Service Bulletin No. 52-014 into

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

attachment. 

Compliance: 

EUROCOPTER makes compliance with this ALERT SERVICE BULLETIN mandatory. 

For the attention 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 lower than 1368, equipped with sliding door P/N 

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

1.A.2. Non-installed equipment

Sliding doors (MP/N) C526A2370101 which did not comply 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 concerning the star support pin rupture. This part is 

located on the kinematics of the sliding door locking system. 

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

Investigations have revealed that the helicopter affected had not complied with Revision 0 of this Service 

Bulletin No 52-014. 

The purpose of Revision 1 is to: 

- change Service Bulletin No. 52-014 into ALERT SERVICE 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 ALERT SERVICE BULLETIN layout. 

EUROCOPTER therefore makes mandatory the star pin check 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 support 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 operator. 

Helicopters/Installed equipment: 

Comply with Paragraph 3. of this ALERT SERVICE BULLETIN 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 this ALERT SERVICE BULLETIN, prior to installation on 

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 which 

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 SERVICE 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 Certificate. 
 

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1.G. MANPOWER

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

qualifications: 

Qualifications: - 2 Mechanical Technicians,

- 1 Composite Specialist. 

Times are given for reference, for a standard configuration. 

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 the 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 compliance 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 - Airframe 

20-10-00, 3-10 : Method for Application of Primer Paints - 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 Replacing the Rivets - Airframe 

20-10-00, 3-32 : Bonding with adhesive (HYSOL EA 9396) 

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

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

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

25-23-00, 4-1 : Removal / Installation - Upholstery 

52-50-00, 4-1 : Removal - Cabin Sliding Doors Assy 

52-50-00, 4-2 : Installation - Cabin Sliding Doors 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 components, 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 mode of 

transport, the destination and the serial numbers of 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/COMPONENT 

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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Material to be ordered separately: 

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 BULLETIN 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 INTERTURBINE 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 per 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 replacing 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 install it on a workbench. 

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

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

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

- Remove pins (d). 

- Disconnect rods (b), (c) and (j) from star (h), and 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 locking 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-ketone (13) in order to remove any trace of 

thread lock, 

- screw locknut (r) on end fitting (14) threading to 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 work zone. 

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

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

- Check for cracks on pin (k1) of support (k), on zones X and Y using a dye penetrant 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 support attachment as per Paragraph 

3.B.2.d. 

. If there is a crack: 

- remove and scrap glass fabric plies (p) (intervention 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) and the three rivets (n), 

- remove and scrap support (k), 

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

- interlay adhesive (1) (not shown in the Figure) between 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), remove 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 fabric 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 distance of at least 

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

edge. 

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

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

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

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

- 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 sliding 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 - Reinforcing 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 with 

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 angle 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, Figure 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 secure 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 cotter pin (10) (Detail G, Figure 6). 

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

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

- 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 equipment

- 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 AMM 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
 

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Figure 1: Star support and its environment 

a 

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 

k1

(See Figure 3) 

Zone U 

Zone V 

Zone W 

Zone T 

CM 6240 

CM 6240 

12 

12 
 

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Figure 3: Zones defined for the dye penetrant inspection

Zone Y 

k 

k1

Zone X 

(See Figure 2) 

CM 115 

9
 

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Figure 4: Installation of glass fabric ply chips on apparent rivet heads 

Intervention 

zones E 

4 

p 

6 

7 

8 

Work zone Z 

Intervention zone E

110 mm (4.33 in.) 

100 mm 

(3.94 in.) 

a 
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Figure 5 

PRE MOD 

h 

f 

g 
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Figure 6 

POST MOD 

15 

10