T.F.S. No. 00000554 

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

2010.03.31

EUROCOPTER 

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE CEDEX FRANCE

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 
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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 crack in the areas of the inner angles and flanges of the 

9° frame, on the RH side and LH side, near 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. 
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1.D. DESCRIPTION 

Revision 0: 

EUROCOPTER was recently informed of a crack which 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 given 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 studies compel EUROCOPTER to define the time limit 

for the initial check according to the helicopter version. 

EUROCOPTER informs you that an improvement (reinforcement) is currently being studied and will be 

proposed to you by a SERVICE BULLETIN. The checks required by this ALERT SERVICE BULLETIN 

will be nullified following the embodiment of this reinforcement. 

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

this ALERT SERVICE BULLETIN mandatory. 
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1.E. COMPLIANCE 

EUROCOPTER renders compliance with this 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, issued on the date indicated at the foot of the 

page:

- Comply with paragraph 2. of this ALERT SERVICE 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 BULLETIN, issued on the date indicated at the foot 

of the page:

- Comply with paragraph 2. of this ALERT SERVICE 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 
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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, issued 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 SERVICE 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 BULLETIN, issued on the date indicated at the foot 

of the page:

- Comply with paragraph 2. of this ALERT SERVICE 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 intervals 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 crack is strictly less than 33 mm:

- Comply with paragraph 2. at intervals 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). 
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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 described in the NOTE in paragraph 1.E.2.a. 

2) In inner angle (b):

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

- Comply with paragraph 2. at intervals 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 described 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 described 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. 
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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 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 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 Airworthiness 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). 
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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 there 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 configuration 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 crack is strictly less than 33 mm:

- Return the helicopter to flight configuration 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. 
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b) In inner angle (b) in accordance with view C: 

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

- Return the helicopter to flight configuration 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 SERVICE BULLETIN in the helicopter documents. 

2.D. OPERATING AND MAINTENANCE INSTRUCTIONS 

Not applicable. 
T.F.S. No. 00000554 

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A

A DETAIL B 

DETAIL B

Figure 1 

CROSS SECTION A-A FWD 

INBOARD 

Area to be checked 200 mm 

b 

a 

FWD 

AFT 

VIEW D 

VIEW C 

c 
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9° Frame - View looking forward 

9° Frame - View looking aft 

Figure 2 

Crack

Crack 
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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 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. 

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.