ALERT SERVICE BULLETIN AS365 

Approved under EASA DOA No. 21J.056. 67.00.10 Page 1/12

 2009.02.25 This document is available on the internet: www.eurocopter.com/techpub 

 EUROCOPTER

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE CEDEX FRANCE CIVIL VERSION(S): N, N1, N2, N3 

 MILITARY VERSION(S): F, Fi, Fs, K 

 ALERT SERVICE BULLETIN 

No. 67.00.10 

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 AS365 

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CAUTION 

THE INFORMATION AND INSTRUCTIONS CONTAINED IN 

THIS ALERT SERVICE BULLETIN 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 "low pitch" locking system and not modified per MOD 0767B65. 

NOTE

MOD 0767B65 is introduced by Service Bulletin No. 67.00.12. 

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 collective pitch lever is moved to the "low-pitch" position, 

. untimely collective pitch lever 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 superseded Revision 1 of ALERT TELEX No. 67.00.10, dated July 6, 2005, 

. modified paragraphs 2.B.2., 2.B.3. and 3.C.3. and Detail 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 informs the users that helicopters modified per 

MOD 0767B65 (introduced by Service Bulletin No. 67.00.12) are not concerned by the instructions of this 

ALERT SERVICE BULLETIN. 

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

Directive. 
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1.D. DESCRIPTION 

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

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

collective pitch lever to the "low pitch" position: The reason for this occurrence is attributed to an anomaly 

concerning the shape of the restraining tab. 

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

When the collective pitch lever is in the locked configuration, it should apply a minimum upward load to 

ensure that the restraining tab remains locked to the collective pitch lever. If this load is too low (in the 

event of incorrect adjustment), there is a risk of unwanted collective pitch lever unlocking. 

In view of the elements outlined above, EUROCOPTER 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. 67.00.10, issued 

on July 6, 2005. 

1.E.1. Compliance at the works 

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

BULLETIN. 

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

1.E.2. Compliance in service: 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. 67.00.10, issued on June 30, 2005 

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 Revision 0 of this ALERT SERVICE BULLETIN No. 67.00.10 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. 67.00.10 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. 
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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. 
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2. ACCOMPLISHMENT INSTRUCTIONS 

2.A. GENERAL 

- Comply with the electrical power general instructions as per MET Work Card 24.00.00.301. 

- Comply with the hydraulic power general instructions as per MET Work Card 29.00.00.301. 

- Comply with the flight control general instructions 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 system 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 tolerance 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. 
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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 loosen 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 that the collective pitch lever (C) unlocks 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 loosen the locknuts of the rod (M). 

- Apply the previously calculated difference 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 opposite the lever index (P), remove the label (Figure 2 - 

Detail Q). 

- Affix a new pitch indicator label (5) opposite 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 the 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 configuration 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 tab (F) in compliance with paragraph 2.B.6. 
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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 restraining 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) (Detail K), until it is lightly distorted, 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 restraining 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 helicopter, and disconnect the hydraulic ground power unit (1). 

2.C. IDENTIFICATION 

Record compliance with this ALERT SERVICE 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 the current maintenance will be incorporated in the 

Maintenance Manual (MET) and Maintenance Program (PRE) through a Revision. 
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Figure 1: Collective pitch lever and restraining tab 
 ALERT SERVICE BULLETIN AS365 

Approved under EASA DOA No. 21J.056. 67.00.10 Page 9/12

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Figure 2: Adjustment of the collective link rods 
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3. MATERIAL INFORMATION

3.A. MATERIAL: COST - AVAILABILITY 

For any information concerning kits and/or components, 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 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 
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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. 
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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.