### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 1/12

2010.03.31 EUROCOPTER

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE C EDEX F RANCE



# EMERGENCY 

# ALERT SERVICE BULLETIN

DAUPHIN NUMBER VERSIONS

Civil: N, N1, N2, N3 

# AS365 05.00.57 Military: F, Fs, Fi, K 

# AS565 05.00.25 Military: AA, MA, MB, SA, SB, UB

Civil: G1 

# SA366 05.39 Military: GA



### SUBJECT: TIME LIMITS / MAINTENANCE CHECKS

Check of the 9° frame

ATA : 53

REVISION No. DATE OF APPROVAL DATE OF ISSUE

Revision 0 On: June 12, 2009 2009.06.12 Revision 1 On: March 30, 2010 2010.03.31

This document is available on the internet: www.eurocopter.com/techpub

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 2/12

2010.03.31 

### 1. PLANNING INFORMATION

1.A. EFFECTIVITY

1.A.1. Helicopters/installed equipment

On 9° frames, all part numbers.

1.A.2. Non-installed equipment

Not applicable.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1.C. REASON

To check at regular intervals that there is no crac k in the areas of the inner angles and flanges of the
9° frame, on the RH side and LH side, n ear the splice (See Figure 1, DETAIL B).

This ALERT SERVICE BULLETIN formed the subject of EASA Airworthiness Directive

No. 2009-0125-E.

The purpose of Revision 1 of this ALERT SERVICE BULLETIN is to modify the time limit for first compliance with paragraph 1.E.2.a. according to the aircraft versions.

Revision 1 of this ALERT SERVICE BULLETIN will form the subject of an EASA Airworthiness

Directive.

Revision 1 of this ALERT SERVICE BULLETIN affects compliance with Revision 0.

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 3/12

2010.03.31 

### 1.D. DESCRIPTION

Revision 0 :

EUROCOPTER was recently informed of a crack wh ich was discovered in the 9° frame of an AS365 N2 helicopter which had logged a total of 10,786 flying hours.

The crack which was located 230 mm above the cabin floor and which had grown over a large section
of the 9° frame, on the RH side, was discovered during the Major Inspection of the helicopter. If it had not been discovered early, this crack, over time , could have led to the failure of the 9° frame.

Pending the results of the analyses that are currently being conducted to establish the cause of this crack, EUROCOPTER renders the instructions gi ven in this ALERT SERVICE BULLETIN mandatory.

Revision 1 :

The examinations and analyses performed since Revision 0 was issued have shown that the time required for initiation of a crack in this area varies a lot according to the weight and balance data of the different aircraft versions. Consequently, these studi es compel EUROCOPTER to define the time limit for the initial check according to the helicopter version.

EUROCOPTER informs you that an improvement (rei nforcement) is currently being studied and will be proposed to you by a SERVICE BULLETIN. The c hecks required by this ALERT SERVICE BULLETIN will be nullified following the embodiment of this reinforcement.

Pending the availability of this improvement, EURO COPTER renders compliance with Revision 1 of

this ALERT SERVICE BU LLETIN mandatory.

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 4/12

2010.03.31 

### 1.E. COMPLIANCE

EUROCOPTER renders compliance with th is ALERT SERVICE BULLETIN mandatory.

1.E.1. Compliance at the works

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

Not applicable.

1.E.1.b. On non-installed equipment

Not applicable.

1.E.2. Compliance in service: By the operator:

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

For AS565 helicopter versions MA, MB, SA, SB and UB, and AS365 helicopter versions N2 and N3, and SA366 GA helicopters:

For helicopters which have not reached the threshold defined in the table below, on receipt of
Revision 1 of this ALERT SERVICE BULLETIN, issu ed on the date indicated at the foot of the

page:

- Comply with paragraph 2. of this ALERT SERVI CE BULLETIN at the latest when the helicopter

reaches the time limit for first compliance , specified in the table below,
Then, - Comply with paragraph 1.E.2.a.1. (Interpretation of the results).

For helicopters which have reached or exceeded the threshold , defined in the table below, on receipt of Revision 1 of this ALERT SERVICE BU LLETIN, issued on the date indicated at the foot of the page:

- Comply with paragraph 2. of this ALERT SER VICE BULLETIN within 10 flying hours following

receipt of Revision 1 of this ALERT SERVICE BULLETIN, issued on the date indicated at the foot of the page, unless compliance was ensured in accordance with Revision 0.
Then, - Comply with paragraph 1.E.2.a.1. (Interpretation of the results).

Aircraft versions Threshold Time limit for 1st compliance

AS565 (MB, SB and UB) 790 hours 800 hours

AS565 (MA and SA) 1,390 hours 1,400 hours

AS365 N3

SA366 GA 2,090 hours 2,100 hours

AS365 N2 3,190 hours 3,200 hours

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 5/12

2010.03.31 For AS365 helicopter versions N, N1, F, FS, Fi and K, and SA366 G1 helicopters:

For helicopters which have not reached the threshold defined in the table below, on receipt of
Revision 1 of this ALERT SERVICE BULLETIN, issu ed on the date indicated at the foot of the

page:

- Cancel the checks performed in accordance with Revision 0 of this ALERT SERVICE

BULLETIN, - Comply with paragraph 2 of this ALERT SERVI CE BULLETIN at the latest when the helicopter

reaches the time limit for first compliance specified in the table below,
Then, - Comply with paragraph 1.E.2.a.1. (Interpretation of the results).

For helicopters which have reached or exceeded the threshold , defined in the table below, on receipt of Revision 1 of this ALERT SERVICE BU LLETIN, issued on the date indicated at the foot of the page:

- Comply with paragraph 2. of this ALERT SER VICE BULLETIN within 10 flying hours following

receipt of Revision 1 of this ALERT SERVICE BULLETIN, issued on the date indicated at the foot of the page, unless compliance was ensured in accordance with Revision 0.
Then, - Comply with paragraph 1.E.2.a.1. (Interpretation of the results).

Aircraft versions Threshold Time limit for 1st compliance

AS365 (Fs and K) 7,990 hours 8,000 hours

AS365 N 8,990 hours 9,000 hours

AS365 (F, N1 and Fi)

SA366 G1 9,990 hours 10,000 hours

365 FS 10,990 hours 11,000 hours

1.E.2.a.1. Interpretation of the results :

a) If there is no crack in the 9° frame :

- Comply with paragraph 2. at inte rvals not exceeding 110 flying hours.

b) If a crack is found:

1) In inner flange (a) of the 9° frame :

a) if the length of the cra ck is strictly less than 33 mm:

- Comply with paragraph 2. at in tervals not exceeding 10 flying hours.

- Contact the EUROCOPTER Customer Service Technical Support Department to request

a “Repair Design Approval Sheet” (RDAS), in accordance with the conditions described in the NOTE in paragraph 1.E.2.a. - Comply with this “Repair Design Approval Sheet” (RDAS) no later than within 660 flying

hours or 1 year (the first limit reached is applicable).

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 6/12

2010.03.31 b) if the length of the crack is equal to or more than 33 mm :

- Contact the EUROCOPTER Customer Service Technical Support Department to request

a “Repair Design Approval Sheet” (RDAS), to be complied with before resuming flights, in

accordance with the conditions describ ed in the NOTE in paragraph 1.E.2.a.

2) In inner angle (b):

a) if the length of the cra ck is strictly less than 33 mm :

- Comply with paragraph 2. at in tervals not exceeding 10 flying hours.

- Contact the EUROCOPTER Customer Service Technical Support Department to request

a “Repair Design Approval Sheet” (RDAS), in accordance with the conditions described in the NOTE in paragraph 1.E.2.a. - Comply with this “Repair Design Approval Sheet” (RDAS) no later than within 660 flying

hours or 1 year (the first limit reached is applicable).

b) if the length of the crack is equal to or more than 33 mm :

- Contact the EUROCOPTER Customer Service Technical Support Department to request

a “Repair Design Approval Sheet” (RDAS), to be complied with before resuming flights, in

accordance with the conditions describ ed in the NOTE in paragraph 1.E.2.a.

3) In inner angle (b) and in inner flange (a) of the 9° frame :

- Contact the EUROCOPTER Customer Service Technical Support Department to request

a “Repair Design Approval Sheet” (RDAS), to be complied with before resuming flights, in

accordance with the conditions describ ed in the NOTE in paragraph 1.E.2.a.



### NOTE

EUROCOPTER remains at your disposal for any further information or support you may require to comply with the instructions given in this ALERT SERVICE BULLETIN:

Contact the EUROCOPTER Customer Service Technical Support Department By: Phone: +33 (0)4.42.85.97.10 Fax: +33 (0)4.42.85.99.66

Email: Airframe.technical-support@eurocopter.com

1.E.2.b. On non-installed equipment

Not applicable.



### 1.F. APPROVAL

1.F.1. Approval of modifications

Not applicable.

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 7/12

2010.03.31 1.F.2. Approval of the Service Bulletin

The technical information given in this ALERT SERVICE BULLETIN Revision 0 was approved
on June 12, 2009 under th e authority of EASA Design Organisation Approval No. 21J.056 for civil version helicopters subject to an Airworthiness Certificate.

The technical information given in this ALERT SERVICE BULLETIN Revision 0 was approved on June 12, 2009 by the EUROCOPTER Airworthiness department for military version helicopters.

The technical information given in this ALERT SERVICE BULLETIN Revision 1 was approved on March 30, 2010 under the authority of EASA Design Organisation Approval No. 21J.056 for civil version helicopters subject to an Airworthiness Certificate.

The technical information given in this ALERT SERVICE BULLETIN Revision 1 was approved on March 30, 2010 by the EUROCOPTER Airworthines s department for military version helicopters.



### 1.G. MANPOWER

1.G.1. Qualification

Mechanic or Structural Technician.

1.G.2. Time for the operations

Approximately 3 hours for compliance with paragraph 2. (excluding customization).



### 1.H. WEIGHT AND BALANCE

Not applicable.



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD

Not applicable.



### 1.K. REFERENCES

Not applicable.



### 1.L. OTHER DOCUMENTS AFFECTED

Maintenance Manual (MET) Work Card: 53.00.00.602. Maintenance Program (PRE).

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 8/12

2010.03.31 

### 1.M. TOOLING AFFECTED

Not applicable.



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

Not applicable.



### 2. ACCOMPLISHMENT INSTRUCTIONS

2.A. GENERAL

The procedure given in paragraph 2. B. describes the operations for one side only of the 9° frame, it

must be carried out on both the LH and RH sides.



### 2.B. OPERATIONAL PROCEDURE

2.B.1. Preliminary steps

- Remove the coverings from the 9° frame.

2.B.2. Visual check to ensure that there are no cracks in the 9° frame

As per Figure 1:

Using a magnifying glass, visually check that t here are no cracks (See photos in Figure 2) in the 9° frame in the areas of inner angles (b) and flanges (a) near splice (c) (See DETAIL B and CROSS SECTION A-A).

Interpretation of the results:

- If there is no crack in the 9° frame in accordance with views C and D:

. Leave as is and return the helicopter to flight c onfiguration in accordance with paragraph 2.B.3.,
then, . Comply with the instructions in paragraph 1.E.2.a.1.a.

- If a crack is found:

a) In inner flange (a) of the 9° frame in accordance with view D :

1) if the length of the cra ck is strictly less than 33 mm:

- Return the helicopter to flight configurat ion in accordance with paragraph 2.B.3. - Comply with the instructions in paragraph 1.E.2.a.1.b.1.a.

2) if the length of the crack is equal to or more than 33 mm:

- Comply with the instructions in paragraph 1.E.2.a.1.b.1.b.

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 9/12

2010.03.31 b) In inner angle (b) in accordance with view C :

1) if the length of the cra ck is strictly less than 33 mm:

- Return the helicopter to flight configurat ion in accordance with paragraph 2.B.3. - Comply with the instructions in paragraph 1.E.2.a.1.b.2.a.

2) if the length of the crack is equal to or more than 33 mm :

- Comply with the instructions in paragraph 1.E.2.a.1.b.2.b.

c) In inner angle (b) and in inner flange (a) of the 9° frame :

- Comply with the instructions in paragraph 1.E.2.a.1.b.3.

2.B.3. Final steps

- Reinstall the coverings on the 9° frame. - Resume flights.



### 2.C. IDENTIFICATION

Record first compliance with this ALERT SER VICE BULLETIN in the helicopter documents.



### 2.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Not applicable.

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 10/12

2010.03.31



# A

A DETAIL B

DETAIL B

Figure 1 FWD 

# CROSS SECTION A-A

INBOARD



### Area to be checked 200 mm b

a FWD AFT



### VIEW D VIEW C

c

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 11/12

2010.03.31 9° Frame - View looking forward

9° Frame - View looking aft

Figure 2 Crack

Crack

### T.F.S. No. 00000554

Approved under EASA DOA No. 21J.056 Page 12/12

2010.03.31 

### 3. MATERIAL INFORMATION

3.A. MATERIAL: PRICE AND AVAILABILITY

Not applicable.



### 3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.



### 3.C. MATERIAL REQUIRED FOR EACH HELICOPTER/ENGINE/COMPONENT

The materials identified by an asterisk "*" or re quired for compliance with the Tasks and/or Work Cards listed in paragraph 1.K., can be or dered from the INTERTURBINE company:

Website: http://www.itlogistics.de

Phone: +49.41.91.809.300

AOG: +49.41.91.809.444.



### 3.D. PROCUREMENT CONDITIONS

Order the required quantity (unless otherwise specified)

from

EUROCOPTER Etablissement de Marignane

Direction Ventes et Relations Client

ECR

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 helicopters to be modified.



### 4. APPENDIX

Not applicable.