ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 1/10

 2006.07.19

 EUROCOPTER

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE CEDEX FRANCE CIVIL VERSION(S): E,F,F1,F2,N 

 

 ALERT SERVICE BULLETIN 

No. 05.00.45 

SUBJECT: TIME LIMITS - MAINTENANCE CHECKS

Check of the Sliding Door Rear Roller Support Shaft and Rear Fitting

ATA: 52

REVISION No. DATE OF APPROVAL DATE OF ISSUE 

 

Revision 0 On: April 19, 2006 2006.07.19 

 

 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 2/10

 2006.07.19

1. PLANNING INFORMATION 

1.A. EFFECTIVITY 

1.A.1. Helicopters / Installed equipment: 

Rear roller support shafts and rear fittings fitted to sliding doors. 

NOTE

Helicopters post-MOD 073298 and/or 073308 (introduced by 

ALERT SERVICE BULLETIN No. 52.00.23) are not 

concerned by this ALERT SERVICE BULLETIN.

1.A.2. Non-installed equipment: 

Sliding doors that have logged flying hours. 

1.B. ASSOCIATED REQUIREMENTS 

Not applicable. 

1.C. REASON 

- To make sure that there is no crack in the roller support shaft of the rear fitting in order to prevent the loss 

of the sliding door when operating the door in flight or on the ground or when performing flights with the 

door open. 

- This ALERT SERVICE BULLETIN: 

. supersedes Revision 1 of ALERT TELEX No. 05.00.45, issued on June 08, 2005, with no change to the 

technical content. 

. informs operators that compliance with ALERT SERVICE BULLETIN No. 52.00.23 (MOD 073298 and/or 

073308) cancels the instructions in this ALERT SERVICE BULLETIN. 

- This ALERT SERVICE BULLETIN will form the subject of an EASA Airworthiness Directive. 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 3/10

 2006.07.19

1.D. DESCRIPTION 

In Revision 0 of ALERT TELEX No. 05.00.45, issued on February 01, 2005, EUROCOPTER introduced 

periodic monitoring to make sure that there is no crack in the rear roller support shaft of the sliding door. 

This monitoring requirement was subsequent to a case of total failure and a case of a crack discovered on 

the support shaft. 

Examination of these shafts showed that the cracks started from one of the holes provided for one of the two 

spring pins that secure the support shaft inside the fitting. The cracks then developed due to fatigue. 

Metallurgical analysis revealed a non-conformity concerning the heat treatment of the material of these two 

shafts, which, at this stage of the investigation, seems to be the main cause of this problem. 

It has not been possible to establish the cause of this non-conformity and to isolate a specific batch of parts. 

Consequently, all helicopters are potentially affected by this non-conformity. 

Since Revision 0 of ALERT TELEX No. 05.00.45 was issued, EUROCOPTER has been informed of a case 

of a crack and a case of failure affecting a roller support shaft rear attachment fitting. 

EUROCOPTER renders compliance with the measures defined in this ALERT SERVICE BULLETIN, 

mandatory. 

1.E. COMPLIANCE 

The following measures are mandatory from receipt of Revision 0 of ALERT TELEX No. 05.00.45, 

issued on February 01, 2005. 

1.E.1. Compliance at the works 

1.E.1.a. On helicopters / installed equipment: 

Before delivery, comply with paragraph 1.E.2. 

1.E.1.b. Non-installed equipment: Not applicable. 

1.E.2. Compliance in operation: By the operator, 

1.E.2.a. On helicopters / installed equipment: 

1.E.2.a.1. On sliding doors having logged less than 90 flying hours: 

- Comply with paragraph 2.B. at 110 flying hours, 

then, 

- comply with paragraph 2.B. every 110 flying hours. 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 4/10

 2006.07.19

1.E.2.a.2. On sliding doors having logged more than 90 flying hours: 

- Compliance with paragraph 2.B. was required within 20 flying hours following receipt of Revision 0 of 

ALERT TELEX No. 05.00.45, issued on February 01, 2005. 

- From receipt of Revision 1 of ALERT TELEX No. 05.00.45, issued on June 08, 2005, 

. comply with paragraph 2.B. at the latest within 110 flying hours following last compliance with 

Revision 0 of ALERT TELEX No. 05.00.45, 

then, 

. comply with paragraph 2.B. every 110 flying hours. 

1.E.2.b. Non-installed equipment: 

Comply with paragraph 2.B. on sliding doors having logged flying hours, before installation on an aircraft. 

1.F. APPROVAL 

1.F.1. Approval of the modifications 

Not applicable. 

1.F.2. Approval of the Service Bulletin 

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

The technical information contained in this ALERT SERVICE BULLETIN was approved 

on April 19, 2006 under the authority of EASA Design Organisation Approval No. 21J.056. 

1.G. MANPOWER 

Qualification: Not applicable. 

Time: Not applicable. 

1.H. WEIGHT AND BALANCE 

Weight: Not applicable. 

Moment: Not applicable. 

1.I. EFFECT ON ELECTRICAL LOADS 

Not applicable. 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 5/10

 2006.07.19

1.J. SOFTWARE MODIFICATION EMBODIMENT STATE 

Not applicable. 

1.K. REFERENCES 

Maintenance Manual (MET): Work Cards: 52.91.10.401, 

52.91.10.501. 

Standard Practices Manual (MTC): Work Card: 20.02.09.601. 

1.L. OTHER DOCUMENTS CONCERNED 

Not applicable. 

1.M. INTERCHANGEABILITY AND MIXABILITY OF PARTS 

Not applicable. 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 6/10

 2006.07.19

2. ACCOMPLISHMENT INSTRUCTIONS 

2.A. GENERAL 

Not applicable. 

2.B. OPERATIONAL PROCEDURE 

2.B.1. Preliminary steps 

- Remove the sliding door as per MET Work Card 52.91.10.401. 

2.B.2. Check of the sliding door rear roller support shaft and rear fitting 

As per Figure 1: 

- Before removing shaft (c), identify the locating hole of pin (b) on fitting (g) in order to retain the same 

longitudinal setting if shaft (c) needs replacing. 

- Remove both pins (a) and (b) and shaft (c) from fitting (g). 

- Scrap the two pins (a) and (b). 

- Perform a dye penetrant inspection on shaft (c) in accordance with MTC Work Card 20.02.09.601 in order 

to make sure that there is no crack at pin holes (a) and (b). 

- Visually check that there is no crack in fitting (g) and particularly in the radius in area Z. If in doubt, perform a 

dye penetrant inspection in accordance with MTC Work Card 20.02.09.601. 

- If no crack is found in shaft (c) and fitting (g): 

. re-install shaft (c) on fitting (g), 

. fit spring pins (2) and (3) with MASTINOX 6856 K sealing compound, 

. plug the pin holes in fitting (g) with PR1771B2SEMK654 sealing compound, 

. return the aircraft to flight configuration as per paragraph 2.B.4. 

- If a crack is detected in fitting (g): 

. remove and discard fitting (g), 

. install a new fitting (5) on the rear support, 

. adjust the position of fitting (5) when the sliding door is installed on the helicopter, in accordance with 

MET Work Card MET 52.91.10.501. 

- If a crack is found in shaft (c): 

. replace shaft (c) with a shaft (1) in compliance with paragraph 2.B.3. 

. inform the EUROCOPTER Customer Service Technical Support Operations Department at: 

. Tel.: 33 (0)4.42.85.97.03 

. Fax: 33 (0)4.42.85.99.66 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 7/10

 2006.07.19

2.B.3. Replacement of the sliding door rear roller support shaft 

As per Figure 1: 

- Remove pin (d), washer (e) and roller (f) from shaft (c). 

- Scrap shaft (c) and pin (d), retain washer (e) and roller (f). 

- Fit a shaft (1) with: roller (f), washer (e) and a spring pin (4). 

- Insert shaft (1) thus equipped into fitting (g), and using a 2.5 mm drill bit, position shaft (1) in the hole 

identified beforehand on fitting (g). 

- Drill the hole for spring pin (2) in shaft (1) to 2.5 mm diameter. 

- Remove shaft (1) from fitting (g) and deburr the 2.5 mm diameter hole. 

- Insert and position shaft (1) in fitting (g). 

- Install spring pins (2) and (3) with MASTINOX 6856 K sealing compound. 

- Plug the pin holes in fitting (g) with PR1771B2SEMK654 sealing compound. 

- Return the aircraft to flight configuration as per paragraph 2.B.4. 

2.B.4. Final steps 

- Reinstall the sliding door as per MET Work Card 52.91.10.401. 

- Resume flights. 

2.C. IDENTIFICATION 

Record compliance with this ALERT SERVICE BULLETIN in the aircraft documents. 

2.D. OPERATING AND MAINTENANCE INSTRUCTIONS 

Not applicable. 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 8/10

 2006.07.19

Figure 1 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 9/10

 2006.07.19

3. MATERIAL INFORMATION

3.A. MATERIAL: COST - AVAILABILITY 

For any information, contact the Customer Service Sales Department. 

3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT 

Not applicable. 

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

3.C.1. Component(s) to be ordered for one sliding door: 

New Part Number Qty Item Key Word Former Part 

Number 

Instructions 

Disposition 

350A25-1275-20 1 1 Shaft 

NSA5319-04-015 2 2 and 3 Spring pin 

NSA5319-04-012 1 4 Spring pin 

350A25-1270-20 1 5 Roller support fitting 

3.C.2. Products to be ordered separately: 

 Part Number Qty Item Key Word 

"*" PR1771B2SEMK654 AR Sealing compound 

"*" MASTINOX 6856 K AR Sealing compound 

The materials identified by an asterisk "*" or required for compliance with the tasks and/or work cards listed in 

paragraph 1.K., can be ordered from the INTERTURBINE company, 

Website: http://www.itlogistics.de

Phone: +49.41.91.809.300 

AOG: +49.41.91.809.444 
 ALERT SERVICE BULLETIN AS355 

Approved under EASA DOA No. 21J.056. 05.00.45 Page 10/10

 2006.07.19

3.D. PROCUREMENT CONDITIONS 

Order the required quantity (unless otherwise specified) 

from 

EUROCOPTER 

Etablissement de Marignane 

Direction VENTES Service Client 

S.V. 

13725 MARIGNANE CEDEX 

FRANCE 

NOTE 1

For ALERT SERVICE BULLETINS, order by: 

Telex: HELICOP 410 969F 

Fax: +33 (0)4.42.85.99.96. 

NOTE 2

On the purchase order, please specify the mode of 

transport, the destination and the serial numbers of the 

aircraft to be modified. 

4. APPENDIX 

Not applicable.