### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 1/12

2009.02.25

This document is available on t he internet: www.eur ocopter.com/techpub EUROCOPTER

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE C EDEX F RANCE 

### CIVIL VERSION(S): G1 MILITARY VERSION(S): GA 

# ALERT SERVICE BULLETIN

No. 67.05

SUBJECT : ROTOR FLIGHT CONTROLS

Check of the Collective Pitch Lever Restraining Tab

REVISION No. DATE OF APPROVAL DATE OF ISSUE

Revision 0 On: January 20, 2006 2006.01.20 Revision 1 On: February 23, 2009 2009.02.25

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 2/12

2009.02.25 CAUTION

THE INFORMATION AND INSTRUCTIONS CONTAINED IN

THIS ALERT SERVICE BU LLETIN ARE INTENDED FOR

MAINTENANCE PERSONNEL AND FLIGHT CREWS



### 1. PLANNING INFORMATION

1.A. EFFECTIVITY

1.A.1. Helicopters/Installed equipment

-Helicopters fitted with the collective pitch lever "l ow pitch" locking system and not modified per MOD 0767B65.



### NOTE

MOD 0767B65 is introduced by Service Bulletin No. 67.07. Refer to the aircraft individual inspection record (MOD record), or the aircraft log book to identify the actual configuration of the helicopter.

1.A.2. Non-installed equipment: Not applicable.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1.C. REASON

- To prevent the risk of:

. untimely collective pitch lever locking, when the collectiv e pitch lever is moved to the "low-pitch" position, . untimely collective pitch leve r unlocking during engine starting.

- Revision 0 of this ALERT SERVICE BULLETIN formed the subject of Revision 1 of Airworthiness Directive

No. F-2005-127 issued by the DGAC on behalf of the EASA.

- Revision 0 of this ALERT SERVICE BULLETIN:

. superseded Revision 1 of ALERT TELEX No. 67.05, dated July 6, 2005, . modified paragraphs 2.B.2., 2.B.3. and 3.C.3. and De tail B on Figure 1, with no change to the technical

content: - specifying the various types of spring scales to be used: “pull type” spring scale (1) or “push type"

spring scale (3), - providing additional information concerning the use of the “pull type” spring scale (NOTE in

paragraph 2.B.2.).

- Revision 1 of this ALERT SERVICE BULLETIN in forms the users that helicopters modified per

MOD 0767B65 (introduced by Service Bulletin No. 67.07) are not concerned by the instructions of this

ALERT SERVICE BULLETIN.

- Revision 1 of this ALERT SERVICE BULLETIN w ill form the subject of a new EASA Airworthiness

Directive.

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 3/12

2009.02.25 1.D. DESCRIPTION

One of our operators has discovered two problem s on the collective pitch lever locking system:

- One case of untimely locking of the collective pitc h lever, which occurred in flight, when moving the

collective pitch lever to the "low pitch" position: T he reason for this occurrence is attributed to an anomaly concerning the shape of the restraining tab.

- One case of untimely unlocking of the co llective pitch lever during engine starting.

When the collective pitch lever is in the locked conf iguration, it should apply a minimum upward load to ensure that the restraining tab remains locked to the co llective pitch lever. If this load is too low (in the event of incorrect adjustment), there is a ri sk of unwanted collective pitch lever unlocking.

In view of the elements outlined above, EUROCOPT ER renders compliance with this ALERT SERVICE BULLETIN mandatory.



### 1.E. COMPLIANCE

The following measures are mandatory since receipt of Revision 1 of ALERT TELEX No. 67.05, issued on July 6, 2005.

1.E.1. Compliance at the works

1.E.1.a. On helicopters/installed equipment: Before deliv ery, comply with paragraph 2. of this ALERT SERVICE

BULLETIN.

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

1.E.2. Compliance in se rvice: By the operator

1.E.2.a. On helicopters/installed equipment: Comply with paragraph 2. within the 50 flying hours following receipt of Revision 0 of ALERT TELEX No. 67.05, issued on June 30, 2005.

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



### 1.F. APPROVAL

Approval is limited to civil version helicopter s subject to an Airworthiness Certificate.

The technical information contained in Revision 0 of this ALERT SERVICE BULLETIN No. 67.05 was approved on January 20, 2006 under the authority of EASA Design Organisation Approval No. 21J.056.

The technical information contained in Revision 1 of this ALERT SERVICE BULLETIN No. 67.05 was approved on February 23, 2009 under the authority of EASA Design Organisation Approval No. 21J.056.



### 1.G. MANPOWER

Qualification: 2 mechanics. Time: Approximately 3 hours.

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 4/12

2009.02.25 1.H. WEIGHT AND BALANCE

Weight: Not applicable. Moment: Not applicable.



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT STATE

Not applicable.



### 1.K. REFERENCES

- Maintenance Manual (MET):

Work Cards: 24.00.00.301,
29.00.00.301,

67.00.00.301.



### 1.L. OTHER DOCUMENTS CONCERNED

Maintenance Manual (MET). Maintenance Program (PRE).



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

Not applicable.

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 5/12

2009.02.25 

### 2. ACCOMPLISHMENT INSTRUCTIONS

2.A. GENERAL

- Comply with the electrical power general in structions as per MET Work Card 24.00.00.301. - Comply with the hydraulic power general inst ructions as per MET Work Card 29.00.00.301. - Comply with the flight control general inst ructions as per MET Work Card 67.00.00.301.



### 2.B. OPERATIONAL PROCEDURE

2.B.1. Preliminary steps

- Pressurize the LH or RH hydraulic power sy stem using the hydraulic ground power unit (1). - Energize the aircraft electrical power system.

2.B.2. Check focused on the risk of collective pitch lever (C) unlocking (Figure 1 - Detail B)

- Completely loosen the friction. - Lock the collective pitch lever (C). - Using a “pull type” spring scale (2) or a “push type” spring scale (6), measure the load "G" required to

unlock the pilot's collective pitch lever (C).

NOTE

If you use a “pull type” spring scale (2), it shall be kept slightly away from the console to be able to measure the load “G”.

- If the collective pitch lever (C) unlocks at:

. a load "G" = 9 daN (with a tolerance of minus 4 daN and plus 5 daN), the adjustment is correct:

- comply with paragraph 2.B.5., . a load "G" outside the tolerance limits, the adjustment is incorrect:

- comply with paragraph 2.B.3.

2.B.3. Adjustment of collective pitch lever (C) unlocking (Figure 1 - Detail B)

- Adjust the restraining tab (F) using the oblong holes, in such a way that the collective pitch lever (C)

unlocks at a load "G" = 9 daN (-4 / +5), measured using a “pull type” spring scale (2) or a “push type” spring scale (6).

. If the load "G" read is within the toler ance limits, comply with paragraph 2.B.5. . When the restraining tab (F) is in the adjustment stop position, and the load "G" read is not within the

tolerance limits, you must re-adjust the rods (L) and (M), in compliance with paragraph 2.B.4.

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 6/12

2009.02.25 2.B.4. Adjustment of the collective link rods (L) and (M), Figures 1 and 2

- Open the bottom structure lateral and lower fairings. - Remove the rod (L): bolts, washers, nuts, cotter pins. - Measure the length of the rod (L ) and record the measurement "L1".

- Remove the heat shrinkable sheath from both ends of the rod (L). - Disengage the nut retainers and loos en the locknuts of the rod (L). - Install the rod (L) on the helicopter. - Immobilize the restraining tab (F) in the mid-position with respect to the oblong holes. - Lock the collective pitch lever (C), (Figure 1 - Detail B). - Set the length of the rod (L) so t hat the collective pitch lever (C) unlo cks at a load "G" = 9 daN (-4 / +5),

measured with a spring scale (2). (Figure 1 - Detail B). - Check that the collective pitch lever (C) does not touch the collective lever base housing (N) when the

lever is in the "high-pitch" position. - Remove the rod (L): - Measure the new length of the rod (L) and record the measurement "L2". - Calculate the difference in length of the rod (L ), i.e. the “L2 - L1” measurement, and record it. - Torque tighten and lock the locknuts, seal the rod (L), as per MET Work Card 67.00.00.301. - Install the rod (L) on the helicopter, and secure the rod as per MET Work Card 67.00.00.301. - Remove the rod (M): bolts, washers, nuts, cotter pins. - Measure the length of the rod (M ) and record the measurement "M1".

- Remove the heat shrinkable sheath from both ends of the rod (M). - Disengage the nut retainers and loos en the locknuts of the rod (M). - Apply the previously calculated diffe rence in length "L2 - L1" to the rod (M), with a tolerance of plus or

minus 0.5 mm. - Torque tighten and lock the locknuts, seal the rod (M), as per MET Work Card 67.00.00.301. - Install the rod (M) on the helicopter, and secure the rod, as per MET Work Card 67.00.00.301. - Install the collective mixing unit shim tool (4) on the left mixing unit (Figure 2 - Detail R). - If the 3°15' pitch indicator label (O) is no longer opposit e the lever index (P), remove the label (Figure 2 -

Detail Q). - Affix a new pitch indicator label (5) opposit e the lever index (P) (Figure 2 - Detail R). - Remove the collective mixing unit shim tool (4). - Comply with paragraph 2.B.5.

2.B.5. Check focused on the risk of unwanted locking (Figure 1 - Detail A)

- Set the collective pitch lever to the "low pitch" position and hold it in this position, without forcing

downwards. - Tighten the friction lock. - Check the clearance "J1" between the locking pin of t he collective pitch lever (C) and the L-section of the

restraining tab (F).

. If J1 > 3 mm, the adjustment is correct:

- loosen the friction lock, - return the helicopter to its original conf iguration in compliance with paragraph 2.B.7. . If J1 < 3 mm, the adjustment is incorrect:

- loosen the friction lock, - modify the shape of the restraining t ab (F) in compliance with paragraph 2.B.6.

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 7/12

2009.02.25 2.B.6. Modifying the shape of the restraining tab (F) (Figure 1)

CAUTION

DO NOT UNBEND THE RESTRAINING TAB (F) AFTER

HAVING BENT IT.

- Identify the position of the restrain ing tab (F) on the console so that it can be re-installed at the same

location after removal.

- Remove the restraining tab (F): screws (D), washers (E), Detail A.

- On a workbench:

. Clamp the restraining tab (F) in a vice (3) fitted with soft jaws, as shown on Detail K. . Gradually apply a load "H" to the restraining tab (F) (Deta il K), until it is lightly dist orted, in order to ensure

a clearance J1 > 3 mm, on the helicopter.

- Install the restraining tab (F) at the position previously identified: screws (D), washers (E), Detail A.

. If J1 > 3 mm, the adjustment is correct:

- comply with paragraph 2.B.2., in order to make sure that the load "G" is correct.
. If J1 < 3 mm, further distort the re straining tab (F) in the vice (3).

2.B.7. Final steps

- De-energize the aircraft electrical power system. - Cut the hydraulic power supply of the helic opter, and disconnect the hydraulic ground power

unit (1).



### 2.C. IDENTIFICATION

Record compliance with this ALERT SERVI CE BULLETIN in the aircraft documents.



### 2.D. OPERATING AND MAINTENANCE INSTRUCTIONS

2.D.1. Operating instructions: Not applicable.

2.D.2. Maintenance instructions

A routine check to be carried out in addition to t he current maintenance will be incorporated in the Maintenance Manual (MET) and Maintenance Program (PRE) through a Revision.

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 8/12

2009.02.25 Figure 1: Collective pitch lever and restraining tab

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 9/12

2009.02.25 Figure 2: Adjustment of the collective link rods

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 10/12

2009.02.25 

### 3. MATERIAL INFORMATION

3.A. MATERIAL: COST - AVAILABILITY

For any information concerning kits and/or com ponents, contact the Sales and Customer Relations Department of the EUROCOPTER Network.



### 3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.



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

3.C.1. Component(s)

New Part Number Qty Item Key Word Former Part Number Instructions Disposition

365A00033722 A/R 5 Label 365A00033722

3.C.2. Items to be ordered separately

Not applicable.

The materials identified by an asterisk "*" or required fo r 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

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 11/12

2009.02.25 3.C.3. Tooling

Part Number Qty Item Key Word

703A94.7503.01 (ICO 90.42.00.01.030)

or 703A94.7501.01 (ICO 90.42.00.01.040) A/R 1 Hydraulic ground power unit

/

/ A/R

A/R 2

6 “Pull type” spring scale

or “Push type” spring scale

365A94.2740.08 (ICO 92.40.00.04.020)

or 365A94.2740.09 (ICO 92.40.00.05.020)

or 366A94.2700

/ A/R /

4 Flight control rigging tool kit Including:

Collective mixing unit shim



### 3.D. MATERIAL REQUIRED FOR EACH SPARE PART

Not applicable.



### 3.E. RE-IDENTIFIED PARTS

Not applicable.



### 3.F. TOOLING: COST - AVAILABILITY

Not applicable.

### ALERT SERVICE BULLETIN SA366

Approved under EASA DOA No. 21J.056. 

# 67.05 Page 12/12

2009.02.25 3.G. 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 aircraft to be

modified.



### 4. APPENDIX

Not applicable.