# eurocopter an EADS Company 

### ALERT SERVICE BULLETIN EC130 EUROCOPTER DIRECTION TEC HNIQUE SU PPORT 13725 MARIGNA NE CE DEX F RANCE 

### 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

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# 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) , -b elow 67 , on the copilot's side (P/N 350A27521201 ) . To be able to read the serial number, disengage boot (c) (Figure 1). Ifnecessary , disengage protecting sleeve (d). 1.A.2. Non -i nstalled equ ipment: Twist grip assemblies with serial numbers:

- be low 64 , on the pilot's side (P/N 350A27520900 , 350A27520901 , 350A27520902 or 350A27520903), -b elow 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 th at during an autorotation training procedure , the engine rem ained 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. 

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### 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 Qual ification : 1 mechanic. Time : Approximately 1 5 minutes for the check, and approximately 2 hours for replacement (as necessary).



### Approved under EASA DOA No. 21J.056. 

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### 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 .



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### ALERT SERVICE BULLETIN EC130 

### 2. ACCOMPLISHMENT INSTRUCTIONS 2.A. GENERAL The che ck 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 pi lot collecti ve 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 of35 N to the gage along arc A in order to prevent the unfolding ofclamp (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-compl iant collective levermust 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 . 

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### 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 of35 N to the gage along arc A in order to prevent the unfolding ofclamp (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 comp lia nce with this ALE RT SERVICE BUL LETIN in the ai rcraft docu me nts. 

### 2.D. OPERATING AND MAINTENANCE INSTRUCTIONS Not applicable . 

### Approved under EASA DOA No . 21J.056 . 

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### EADS Company



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### Approved under EASA DOA No . 21J .056. 

# 76A001 ALERT SERVICE BULLETIN EC130



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### Approved under EASA DOA No . 21J .056. 

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### ALERT SERVICE BULLETIN EC 1 30



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### Approved under EASA DOA No . 21J .056 . 

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# 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 Sca le 

### 3.D. MATERIA L REQUI RE D FOR EACH SPARE PART Not applicable . 

### 3.E. RE-IDENTIFIED PARTS Not applicable. 

### Approved under EASA DOA No . 21J .056 . 

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### EADS Company 

### ALERT SERVICE BULLETIN EC130 3.F. TOOLING: COST- AVAILABILITY Fo r 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 ForALERT 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 ofthe aircraft to be modified.



### Approved under EASA DOA No . 21J.056 . 

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