### 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 C EDEX F RANCE 

### 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 AL ERT 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 suppor t 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 ALER T 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, i ssued on February 01, 2005, EUROCOPTER introduced periodic monitoring to make sure that there is no cra ck 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-c onformity 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 measur es defined in this ALERT SERVICE BULLETIN, mandatory.



### 1.E. COMPLIANCE

The following measures are mandatory from receip t 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 hav ing 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 havi ng 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 with in 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 helicopter s 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 De sign 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 r ear 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 par ticularly in the radius in area Z. If in doubt, perform a

dye penetrant inspection in accordanc e 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 c onfiguration 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 slid ing 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 us ing 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 c onfiguration 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 SERVI CE 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 fo r 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.