ASB No. EC130-52A009 

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Civil version(s): B4 

ALERT SERVICE BULLETIN 

SUBJECT: DOORS - Sliding door

 Attachment of the sliding door star support

 Corresponds to MOD 07 3796 

Revision No. Date of issue 

Revision 0 2010-03-30 

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. 52-009 into

ALERT SERVICE BULLETIN No. 52A009, 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 equipped with a sliding door P/N C526S1101051, and: 

- pre MOD 07 3796 (reinforcement of the sliding door star support attachment), 

or 

- pre MOD 07 2921 (industrialized sliding door). 

NOTE 1 

Refer to the aircraft individual inspection record 

(or RIC AMS) to identify the actual modification status of the 

aircraft. 

NOTE 2 

Helicopters on which Service Bulletin No. 52-009 Revision 0 

was complied with, are not affected by this ALERT 

SERVICE BULLETIN Revision 1. 

1.A.2. Non-installed equipment

Sliding doors (P/N) C526S1101051 and: 

- pre MOD 07 3796 (reinforcement of the sliding door star support attachment), 

or 

- pre MOD 07 2921 (industrialized sliding door). 

NOTE 1 

Refer to the aircraft individual inspection record 

(or RIC AMS) to identify the actual modification status of the 

aircraft. 

NOTE 2 

Helicopters on which Service Bulletin No. 52-009 Revision 0 

was complied with, are not affected by this ALERT 

SERVICE BULLETIN Revision 1. 

1.B. ASSOCIATED REQUIREMENTS 

Not applicable. 
 

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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 52-009. 

The purpose of Revision 1 is to: 

- change Service Bulletin No. 52-009 into ALERT SERVICE BULLETIN No. 52A009, to make mandatory 

embodiment of modification 07 3796 for 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 52-009. 

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. 

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. 
 

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1.F. APPROVAL

Approval of modifications: 

The information or instructions relate to modification 073796 which was approved on May 16, 2003 under the 

authority of EASA Design Organization Approval No. 21J.056 for helicopters of civil versions subject to an 

Airworthiness Certificate. 

Approval of this document: 

The technical information contained in this Service Bulletin No. 52-009 Revision 0 was approved on 

March 23, 2010 under the authority of EASA Design Organization Approval No. 21J.056 for helicopters of

civil versions subject to an Airworthiness Certificate. 

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. 

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: 0.143 m.kg 

Lateral moment: -0.0555 m.kg 

Vertical moment: -0.134 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: 

Standard Practices Manual (MTC): 

MTC: 20.01.01.301 : Miscellaneous products used on helicopters - Use of greases

MTC: 20.02.04.401 : Riveting - pitch and edge distance

MTC: 20.02.04.402 : Installation of rivets for retrofitting and repair

MTC: 20.02.04.601 : General riveting acceptance requirements

MTC: 20.02.05.401 : Joining - Joining by riveting

MTC: 20.02.06.401 : Safetying and locking of assemblies - Safetying plain pins

MTC: 20.02.06.404 : Safetying and locking of assemblies - Safetying with cotter pins

MTC: 20.02.09.101 : Check for cracks - General principles applicable to dye penetrant inspection 

procedure 

MTC: 20.02.09.601 : Check for cracks - Check of structural components and parts by dye penetrant 

inspection

MTC: 20.03.02.406 : General rivet replacement principles - CHERRY-MAX rivets A.S.N.A. 0077 and 0078

MTC: 20.03.02.409 : General rivet replacement principles - Installation of blind rivets ASN-NSA 1919 

and 1921

MTC: 20.03.06.406 : Structural repairs - Vacuum bag techniques

MTC: 20.04.01.102 : Cleaning of parts - Use of standard cleaning products on individual parts and on 

aircraft

MTC: 20.04.01.402 : Cleaning of parts - Cleaning removed detail parts with liquid solvents

MTC: 20.04.04.401 : Surface treatment before painting - Surface preparation before painting

MTC: 20.04.05.101 : General information concerning painting means and touch-up works

MTC: 20.04.05.420 : Paint and primer application procedure - Use of CA 8620 primer

MTC: 20.05.01.101 : General sealing procedures - General sealing methods

MTC: 20.05.01.102 : General sealing procedures - Sealing compound application methods

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

MTC: 20.06.01.102 : Bonding with adhesives - Bonding methods

MTC: 20.06.01.411 : Bonding with adhesives - Use of HYSOL EA 9396 adhesive

MTC: 20.06.01.418 : Bonding with adhesives - Use of EA 9395 adhesive

MTC: 20.07.02.201 : Safety instructions - Helicopter parked inside a hangar

MTC: 20.07.03.408 : Technical instructions - General principles applicable for visual cleanliness 

appearance checks on an aircraft after an inspection or a repair

MTC: 20.08.05.103 : General rules applicable in aeronautics - Monitoring of parts in operation, marking 

and service life customization

Aircraft Maintenance Manual (AMM): 

AMM: 25-27-00, 4-2 : Covering - Removal / Installation - Door covering

AMM: 52-12-00, 4-1 : Removal - Sliding door

AMM: 52-12-00, 4-2 : Installation - 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 350A0737960071 / / / 

 

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 use of greases as per MTC Work Card 20.01.01.301. 

Read and comply with instructions for riveting as per MTC Work Cards 20.02.04.401 and 20.02.04.402. 

Read and comply with general riveting acceptance instructions as per MTC Work Card 20.02.04.601. 

Read and comply with general instructions for joining by riveting as per MTC Work Card 20.04.05.401. 

Read and comply with instructions for safetying and locking plain pins as per MTC Work Card 20.02.06.401. 

Read and comply with instructions for safetying with cotter pins as per MTC Work Card 20.02.06.404. 

Read and comply with instructions for cleaning parts as per MTC Work Cards 20.04.01.102 and 

20.04.01.402. 

Read and comply with general information on painting means and touch-up works as per 

MTC Work Card 20.04.05.101. 

Read and comply with instructions for bonding with adhesives as per MTC Work Cards 20.06.01.101 and 

20.06.01.102. 

Read and comply with safety instructions for parking an aircraft in a hangar as per 

MTC Work Card 20.07.02.201. 

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 52-12-00, 4-1 and install it on a workbench.

- Remove the sliding door (a) skin as per AMM Task 25-27-00, 4-2.

- 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, 
 

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

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

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 

MTC Work Cards 20.02.09.101 and 20.02.09.601. 

. If no cracks are found: 

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

- embody modification 07 3796 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 MTC Work Card 20.06.01.418, 

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

MTC Work Cards 20.03.02.406 and 20.03.02.409, 

- 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 

MTC Work Card 20.06.01.411, 

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

- cure the glass fabric ply/-ies (6) in a vacuum bag as per MTC Work Card 20.03.06.406, 

- carry out a surface treatment before painting as per MTC Work Card 20.04.04.401, 

- apply a primer paint layer (8) on work zone Z as per MTC Work Card 20.04.05.420, 

- 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, 

- embody modification 07 3796 as per Paragraph 3.B.2.d. 

3.B.2.d. Embodiment of modification 07 3796 - 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 MTC Work Cards 20.05.01.101

and 20.05.01.102. 

- 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), as per MTC Work Card 20.03.02.406. 

- 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 25-27-00, 4-2.

- Put in position sliding door (a) as per AMM Task 52-12-00, 4-2.

- Perform operating test of the sliding door as per AMM Task 52-12-00, 6-1.

- Perform aircraft appearance checks as per MTC Work Card 20.07.03.408. 

- 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 MTC Work Card 20.08.05.103. 

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

 

Sliding door 

assembly C526S1101051 C526S1101051 + ASB No. 52A009 R1 07 3796 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 

a 

4 

p 

6 

7 

8 

Work zone Z 

Intervention zone E

110 mm (4.33 in.) 

100 mm 

(3.94 in.) 
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Figure 5 

PRE MOD 

h 

f 

g 
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Figure 6 

POST MOD 

15 

10