eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

EUROCOPTER 

DIRECTION TECHNIQUE SUPPORT 

13725 MARIGNANE C EDEX FRANCE CIVIL VERSION(S): 84 

ALERT SERVICE BULLETIN 

No. 65A002 

SUBJECT: TAIL ROTOR DRIVE 

Check of the perpendicularity of bearing No. 1, and check for absence of 

cracks and loosening of the rivets in the tube-to-flange attachment of the 

tail rotor drive center section shaft 

REVISION No. 

Revision 0 

Approved under EASA DOA No. 21J .056. 

DATE OF APPROVAL 

Date: November 15, 2005 

65A002 

DATE OF ISSUE 

2005.11 .16 " 

Page 1/9 

2005.11 .16 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

1. PLANNING INFORMATION 

1.A. EFFECTIVITY 

1.A.1. Helicopters/Installed equipment: 

On helicopters delivered before January 1, 2005 (refer to the aircraft log book). 

1.A.2. Non-installed equipment: 

Not applicable. 

1.8. ASSOCIATED REQUIREMENTS 

Not applicable. 

1.C. REASON 

To prevent loosening of the rivets in the center section shaft tube-to-flange attachment, by checking the 

perpendicularity of bearing No. 1 relative to the tail rotor drive center section shaft. 

1.D. DESCRIPTION 

EUROCOPTER has been informed of several cases of loosened rivets in the tube-to-flange attachment of 

the tail rotor drive center section shaft (on the center section I rear section coupling side). In one case, this 

loosening of rivets was associated with a crack in the tube which started from a loosened-rivet hole. These 

problems were detected during the periodic monitoring of the flanges, as defined in the Maintenance 

Program (MSM). 

Examinations of some of these center section shafts have revealed that bearing No. 1 was not 

perpendicular relative to the tail rotor drive center section shaft. This can cause abnormal loads in the flange 

and explain the loosening of rivets and the crack that was found . 

To prevent these occurrences, which could lead to failure of the tail rotor drive center section shaft, 

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

mandatory. 

Approved under EASA DOA No. 21 J.056. 65A002 Page 2/9 

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eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

1.E. COMPLIANCE 

1.E.1 . Compliance at the works 

1.E.1.a. On helicopters/installed equipment: Compliance with paragraph 2.B. is ensured before delivery, since 

January 1, 2005. 

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: Comply once with paragraph 2.B., no later than within the 50 flying 

hours or 3 months following receipt of this ALERT SERVICE 

BULLETIN , issued on the date indicated in the footer {the first limit 

reached is applicable). 

1.E.2.b. Non-installed equipment: Not applicable. 

1.F. APPROVAL 

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

The technical information contained in this ALERT SERVICE BULLETIN was approved 

on November 15, 2005 under the authority of EASA Design Organisation Approval No. 21 J.056. 

1.G. MANPOWER 

Qualification : Mechanic. 

Time: approximately 1 hour. 

1.H. WEIGHT AND BALANCE 

Weight: Not applicable. 

Moment: Not applicable. 

1.1. EFFECT ON ELECTRICAL LOADS 

No effect. 

Approved under EASA DOA No. 21J .056. 65A002 Page 3/9 

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eurocopter 

an EADS Company 

1.J. SOFTWARE MODIFICATION EMBODIMENT STATE 

Not applicable. 

1.K. REFERENCES 

Aircraft Maintenance Manual (AMM) Task 65-11-00, 4-8. 

1.L. OTHER DOCUMENTS CONCERNED 

Aircraft Maintenance Manual (AMM). 

Maintenance Program (MSM). 

1.M. INTERCHANGEABILITY OR MIXABILITY OF PARTS 

Not applicable. 

Approved under EASA DOA No. 21J.056. 65A002 

ALERT SERVICE BULLETIN EC130 

Page 4/9 

2005.11 .1 6 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

2. ACCOMPLISHMENT INSTRUCTIONS 

2.A. GENERAL 

Not applicable. 

2.8. OPERATIONAL PROCEDURE 

2.B.1 . Preliminary steps 

- Remove the tail rotor drive shaft fairings . 

2.B.2. Procedure 

As per Figure 1: 

-Visually check that there are no cracks and no loosened rivets at the center section shaft tube-to-flange 

attachment. If there are cracks or loosened rivets, replace the center section shaft. 

-Check the perpendicularity of bearing No. 1: 

. Procure a dial gage (1) equipped with a long feeler pin . 

. Protect the tube of the center section shaft with adhesive paper in the area where the dial gage is to be 

secured (DETAIL A) . 

. Install and secure the dial gage on the tube of the center section shaft with the locally-manufactured 

supports (5) and "TYRAP" (or other) type clamps . 

. Bring the feeler of the dial gage into contact with the face of the ball ring (2) (DETAIL B) . 

. Turn the center section shaft one full turn by hand and check the perpendicularity of the bearing (3). 

Interpretation of the results: 

- If the out-of-perpendicularity of the bearing (3) is equal to or less than 0.1 mm, 

. leave as is, 

. remove the dial gage ( 1) and the protective adhesive paper from the tube of the center section shaft. 

- If the out-of-perpendicularity of the bearing (3) is more than 0.1 mm, 

. loosen the screws (4) by one quarter of a turn until the ball ring (2) is released, 

. make sure that the bearing (3) and the ball ring (2) are free to move, 

. turn the center section shaft by hand and make sure that the out-of-perpendicularity of the bearing as 

read on the dial gage (1) is "equal to or less than 0.1 mm", 

. tighten the 4 screws (4) in accordance with the procedure and the tightening torque indicated in AMM 

Task 65-11-00, 4-8, 

. once again, using the dial gage (1 ), make sure that the out-of-perpendicularity of the bearing is effectively 

"equal to or less than 0.1 mm", 

. remove the dial gage ( 1) and the protective adhesive paper from the tube of the center section shaft. 

2.B.3. Final steps 

- Install the tail rotor drive shaft fairings. 

Approved under EASA DOA No. 21J .056. 65A002 Page 5/9 

2005.11.16 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

2.C. IDENTIFICATION 

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

2.D. OPERATING AND MAINTENANCE INSTRUCTIONS 

Not applicable. 

Approved under EASA DOA No. 21J .056. 65A002 Page 6/9 

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eurocopter 

an EAOS Company 

2 

Figure 1 

Approved under EASA DOA No. 21 J.056. 65A002 

ALERT SERVICE BULLETIN EC130 

A 

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I 1----i 

! 

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2005.11.1 6 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

3. MATERIAL INFORMATION 

3.A. MATERIAL: COST- AVAILABILITY 

Not applicable. 

3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT 

Not applicable. . 

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

3.C.1. Components(s): 

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: +49.4 1.91.809.300 

AOG: +49.4 1.91 .809.444 

3.D. MATERIAL REQUIRED FOR EACH SPARE PART 

Not applicable. 

3.E. RE-IDENTIFIED PARTS 

Not applicable. 

3.F. TOOLING: COST- AVAILABILITY 

For any information, contact the Customer Service Sales Department. 

Approved under EASA DOA No. 21J .056. 65A002 Page 8/9 

2005.11.16 
eurocopt,er 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

3.G. PROCUREMENT CONDITIONS 

Order the required quantity (unless otherwise specified) 

from 

EUROCOPTER 

Etablissement de Marignane 

Direction VENTES Service Client 

s.v. 

13725 MARIGNANE CEDEX 

FRANCE 

4. APPENDIX 

Not applicable. 

NOTE1 

For ALERT SERVICE BULLETINS, order by: 

Telex: HELICOP 410 969F 

Fax: +33 (0)4 42 85 99 96 

NOTE2 

On the purchase order, please specify the mode of 

transport, 

the destination and the serial numbers of the aircraft to be 

modified. 

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2005.11.16