eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

EUROCOPTER 

DIRECTION TECHNIQUE SUPPORT 

13725 MARIGNA NE CEDEX FRANCE CIVIL VERSION(S): 84 

ALERT SERVICE BULLETIN 

No. 76A001 

SUBJECT: ENGINE CONTROLS 

Check of the Twist Grip Drive Tube and Control Pinion Attachment 

REVISION No. 

Revision 0 

Approved under EASA DOA No. 21J .056. 

DATE OF APPROVAL 

Date: February 9, 2006 

76A001 

DATE OF ISSUE 

2006.02.10 

Page 1/11 

2006.02.10 
eurocopter 

an EAOS Company 

ALERT SERVICE BULLETIN EC130 

1. PLANNING INFORMATION 

1.A. EFFECTIVITY 

1.A.1 . Helicopters I Installed equipment: 

Helicopters equipped with twist grip assemblies with serial numbers: 

- below 64, on the pilot's side (P/N 350A27520900, 350A27520901 , 350A27520902 or 350A27520903), 

-below 67, on the copilot's side (P/N 350A27521201 ). 

To be able to read the serial number, disengage boot (c) 

(Figure 1). If necessary, disengage protecting sleeve (d). 

1.A.2. Non-installed equipment: 

Twist grip assemblies with serial numbers: 

- below 64, on the pilot's side (P/N 350A27520900, 350A27520901 , 350A27520902 or 350A27520903), 

-below 67, on the copilot's side (P/N 350A27521201 ). 

1.8. ASSOCIATED REQUIREMENTS 

Not applicable. 

1.C. REASON 

The purpose of this ALERT SERVICE BULLETIN which will form the subject of an Airworthiness Directive 

issued by the DGAC on be half of the EASA, is to ensure correct bonding strength of the control pinion on the 

pilot and copilot collective lever drive tubes. 

1.D. DESCRIPTION 

A customer has informed EUROCOPTER that during an autorotation training procedure, the engine 

remained at idle rating although the twist grip had been turned back to the flight position. The autorotation 

procedure was continued without damage and the helicopter was landed. 

Analysis has revealed failure of the twist grip drive tube and control pinion bonded attachment due to noncompliant surface preparation. 

Compliance with this ALERT SERVICE BULLETIN consists in applying a load to the twist grips in order to 

check the bonding strength . 

This check is included in the manufacturing process for twist grips with serial numbers above those specified 

in "EFFECTIVITY" paragraph 1.A.. 

Approved under EASA DOA No. 21J.056. 76A001 Page 2/11 

2006.02.10 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

1.E. COMPLIANCE 

EUROCOPTER renders compliance with this ALERT SERVICE BULLETIN mandatory. 

1.E.1 . At the works 

1.E.1.a. On helicopters I installed equipment: Before delivery, check the bonding between the pilot and copilot 

collective lever drive tubes and the control pinions, in compliance 

with paragraphs 2.B.1 . and 2.B.2. 

1.E.1.b. On spares: Before installation on a helicopter, check the bonding between the drive tube and the control 

pinion in compliance with paragraph 2.B.3. 

1.E.2. Retrofit action: By the operator, 

1.E.2.a. On helicopters I installed equipment: Check the bonding between the pilot and copilot collective lever 

drive tubes and the control pinions, in compliance with 

paragraphs 2.B.1. and 2.B.2., within 110 flying hours or 4 

months (the first limit reached is applicable) following receipt of 

this ALERT SERVICE BULLETIN, issued on the date indicated 

in the footer. 

1.E.2.b. On spares: Before installation on a helicopter, check the bonding between the drive tube and the control 

pinion in compliance with paragraph 2.B.3 . 

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 

February 9, 2006 under the authority of EASA Design Organisation Approval No. 21 J.056. 

1.G. MANPOWER 

Qualification : 1 mechanic. 

Time: Approximately 15 minutes for the check, and approximately 2 hours for replacement (as necessary). 

Approved under EASA DOA No. 21J.056. 76A001 Page 3/11 

2006.02.10 
eurocopter 

an EAOS Company 

1.H. WEIGHT AND BALANCE 

Not applicable. 

1.1. EFFECT ON ELECTRICAL LOADS 

Not applicable. 

1.J. SOFTWARE MODIFICATION EMBODIMENT STATE 

Not applicable. 

1.K. REFERENCES 

Aircraft Maintenance Manual (AMM): Task 67-12-00, 4-1 . 

1.L. OTHER DOCUMENTS CONCERNED 

Not applicable. 

1.M. INTERCHANGEABILITY AND MIXABILITY OF PARTS 

Not applicable. 

Approved under EASA DOA No. 21J.056. 76A001 

ALERT SERVICE BULLETIN EC130 

Page 4/11 

2006.02.1 0 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

2. ACCOMPLISHMENT INSTRUCTIONS 

2.A. GENERAL 

The check of the bonding between the twist grip drive tube and the control pinion, described paragraph 

2.8.2 . applies to the copilot collective lever (a). This same check must be applied to the pilot collective 

lever (b). 

2.8. OPERATIONAL PROCEDURE 

2.8.1 . Preliminary steps 

-Make sure that the pilot and copilot twist grips are set to "OFF". 

- De-energize the aircraft electrical power system. 

2.8.2. Check of the bonding between the twist grip drive tube and the control pinion 

- Apply a load to the twist grip: 

. On the twist grip of the copilot collective lever, as indicated on Figure 1, install twist grip adjusting 

gage (g) or an adjusting gage made locally, consisting of one clamp (3), one bolt (4), one nut (5) and one 

metal piece to be used as a lever arm, as shown on Figure 3. 

NOTE1 

The twist grip adjusting gage (g) is available from 

EUROCOPTER or can be made as shown on Figure 2 . 

. Using spring scale (h), apply a load of 35 N, tangentially to the twist grip of collective lever (a), in the 

"reduction" direction. 

NOTE2 

Apply a load of 35 N to the gage along arc A in order to 

prevent the unfolding of clamp (3). 

- If the twist grip does not turn, leave as is. 

- If the grip turns : 

. Replace the collective lever as per AMM Task 67-12-00, 4-1, before resuming flights . 

NOTE3 

The non-compliant collective lever must be returned for 

repair . 

. Inform EUROCOPT ER, by fax: 

Departement Operations Support Technique 

Service STXM 

Fax: +33(0)4-42-85-99-66 

-Remove twist grip adjusting gage (g) or the adjusting gage made locally. 

Approved under EASA DOA No. 21J .056. 76A001 Page 5/11 

2006.02.10 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

2.8.3. Check of the bonding between the twist grip drive tube and the control pinion on non-installed equipment 

- Clamp area E of the collective lever, as shown on Figure 1, in a vice with soft jaws. 

-Apply load to the twist grip: 

. On the twist grip of the collective lever, as indicated on Figure 1, install twist grip adjusting gage (g) or an 

adjusting gage made locally, consisting of one clamp (3), one bolt (4), one nut (5) and one metal piece to 

be used as a lever arm, as shown on Figure 3. 

NOTE4 

The twist grip adjusting gage (g) is available from 

EUROCOPTER or can be made as shown on Figure 2 . 

. Using spring scale (h), apply a load of 35 N, tangentially to the twist grip of the collective lever, in the 

"reduction" direction. 

NOTES 

Apply a load of 35 N to the gage along arc A in order to 

prevent the unfolding of clamp (3). 

-If the twist grip does not turn , leave as is. 

- If the grip turns : 

. Replace the collective lever. 

NOTE6 

The non-compliant collective lever must be returned for 

repair . 

. Inform EUROCOPTER, by fax: 

Departement Operation Support Technique 

Service STXM 

Fax: +33(0)4-42-85-99-66 

- Remove twist grip adjusting gage (g) or the adjusting gage made locally. 

- Remove the collective lever from the vice. 

2.C. IDENTIFICATION 

Record 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. 76A001 Page 6/11 

2006.02.10 
eurocopter 

an EADS Company 

c 

C-C 

f 

E 

Figure 1: Collective levers 

Approved under EASA DOA No. 21J .056. 76A001 

ALERT SERVICE BULLETIN EC130 

d 

Page 7/11 

2006.02. 10 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

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Figure 2: Twist grip adjusting gage 

Approved under EASA DOA No. 21J .056. 76A001 

C") 

i R 12,5 

Page 8/11 

2006.02.10 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

165 

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5 

200 

Figure 3: Gage made locally 

Approved under EASA DOA No. 21J .056. 76A001 Page 9/11 

2006.02.10 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

3. MATERIAL INFORMATION 

3.A. MATERIAL: COST- AVAILABILITY 

For any information, contact the Customer Support Sales Department. 

3.8. INFORMATION CONCERNING INDUSTRIAL SUPPORT 

Not applicable. 

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

3.C.1. Component(s): 

New Part Number 

350A27521201 

350A27520903 

Qty Item Key Word 

1 Copilot twist grip assembly 

2 Pilot twist grip assembly 

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

New Part Number 

ASNA0021-25G49 

22125BC050014L 

22431BC050L 

Qty Item Key Word 

3 

4 

5 

Clamp 

Bolt 

Nut 

Former Part 

Number 

Instructions 

Disposition 

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.C.3. Tool(s): 

Part Number Qty 

350A942720.00 

Item Key Word 

g 

h 

Twist grip adjusting gage 

Spring Scale 

3.D. MATERIAL REQUIRED FOR EACH SPARE PART 

Not applicable. 

3.E. RE-IDENTIFIED PARTS 

Not applicable. 

Approved under EASA DOA No. 21J .056. 76A001 Page 10/11 

2006.02.10 
eurocopter 

an EADS Company 

ALERT SERVICE BULLETIN EC130 

3.F. TOOLING: COST- AVAILABILITY 

For any information, contact the Customer Support Sales Department. 

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: HEL/COP 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. 

Approved under EASA DOA No. 21J.056. 76A001 Page 11/11 

2006.02.10