### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 1/14

2006.03.28 EUROCOPTER

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE C EDEX F RANCE 

### CIVIL VERSION(S): L2



# ALERT SERVICE BULLETIN

No. 05.00.65

SUBJECT : TIME LIMITS - MAINTENANCE CHECKS

Check of the Attachment of Front and Rear MGB Suspension Bar Attaching Fittings



### ATA : 53

REVISION No. DATE OF APPROVAL DATE OF ISSUE

Revision 0 On : March 24, 2006 2006.03.28

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 2/14

2006.03.28 

### 1. PLANNING INFORMATION

1.A. EFFECTIVITY

1.A.1. Helicopters / Installed equipment:

For bolts securing the attaching fittings of the front and rear MGB suspension bars.

1.A.2. Non-installed equipment:

Not applicable.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1.C. REASON

To check the tightening torque of the bolts that secure the front MGB bar attaching fitting, and the bolts that secure the rear MGB bar attaching fittings. In the event of significant tightening torque load lo ss, inspect the frames 3855 and 5295 in the area of the MGB bar attaching fittings.

This ALERT SERVICE BULLETIN will form the subject of an EASA Airworthiness Directive.



### 1.D. DESCRIPTION

Analysis of the tightening torque meas urements that were to be taken on the helicopter fleet, in compliance

with AS332 ALERT TELEX No. 53.01.49 has revealed some cases of tightening torque loss of the bolts that secure the rear MGB bar fittings. The measurement readi ngs have shown that it is necessary to introduce, for AS332 helicopters, a periodic check of the tightening torque of both the bolts that secure the rear MGB bar fittings and the bolts that secure the front fitting. Significant loss of the tightening torque of the bolts t hat secure the MGB bar fittings can lead to a change in the loading mode of frames 3855 and 5295. Consequently, in the event of significant tightening torque loss of the bolts that secure the MGB bar attaching fittings , you must check that there is no crack in frames 3855

and 5295. EUROCOPTER renders compliance with the measur es defined in this ALERT SERVICE BULLETIN mandatory.

The instructions given in AS332 ALERT TELEX No. 53.01.49 are canceled by AS332 ALERT SERVICE BULLETIN No. 53.01.49 issued on January 12, 2006 and are repl aced with the instructions given in this

ALERT SERVICE BULLETIN and in Revision 1 of AL ERT TELEX No. 05.00.63 issued on January 12, 2006.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 3/14

2006.03.28 1.E. COMPLIANCE

1.E.1. Compliance at the works

1.E.1.a. On helicopters / installed equipment: Comply with paragraph 1.E.2.

1.E.1.b. On non-installed equipment: Not applicable.

1.E.2. Compliance in operation: By the operator.

1.E.2.a. On helicopters / installed equipment:

- Comply with paragraph 2.B.1. within 150 flying hours following receipt of this ALERT SERVICE

BULLETIN, issued on the date indicated in the footer,
then,

. comply with paragraph 2.B. at the latest every 825 flying hours.

1.E.2.b. On 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 th is ALERT SERVICE BULLETIN was approved on March 24, 2006 under the authority of EASA De sign Organisation Approval No. 21J.056.



### 1.G. MANPOWER

Qualification: Mechanic. Time for the operations: Approximately 3 hours for the tightening torque check of the bolts that secure the front fitting. Approximately 2 hours for the tightening tor que check of the bolts that secure the rear fittings.



### 1.H. WEIGHT AND BALANCE

Weight: None.

Moment: None.



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT STATE

Not applicable.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 4/14

2006.03.28 1.K.

REFERENCES

Aircraft Maintenance Manual (MMA) Tasks: 53-26-00-061,
53-26-00-062,

71-00-00-051.

Standard Practices Manual (MTC ) Work Cards: 20.02.05.404,

20.02.09.601.



### 1.L. OTHER DOCUMENTS CONCERNED

Maintenance Program (PRE).



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

Not applicable.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 5/14

2006.03.28 

### 2. ACCOMPLISHMENT INSTRUCTIONS

2.A. GENERAL

To avoid affecting correct measurement of the ti ghtening torque, take care to correctly lock the head of bolt (b) or (h), from the inside of the cabin.

In order to check that the bolt does not turn w hen measuring the tightening torque, first mark the associated position of the end of the threaded section of bolt (b) or (h) (in line with the pin hole axis) with respect to nut (a) or (g) and fitting (d) or (j) (see DETAIL A Figure 3).



### 2.B. OPERATIONAL PROCEDURE

2.B.1. Check of the tightening torque of the bolts that secure the front MGB bar attaching fitting

- Remove the engines as per Subt ask 71-00-00-021 of MMA Task 71.00.00.051

.

As per Figure 1: - Remove the trimmings and soundproofing mats from the area of frame 3855 and from the area of the

attaching points of the front MGB bar attaching fitting. - Remove the sealing compound from the nuts (a). - Remove and scrap cotter pins (c).

For the recommended tightening torque values, in accordance with the Figure in Appendix 1 and MMA

Task 53-26-00-061: - Check the tightening torque of each nut (a), in accordance with MTC Work Card 20.02.05.404. - During the initial check, record each of the meas ured tightening torque values, once, in the table in

Appendix 1. - Interpret the results of the che ck in accordance with paragraph 2.B.3.

2.B.2. Check of the tightening torque of the bolts that secure the rear RH and LH MGB bar attaching fittings

As per Figure 2: - Remove the trimmings and soundproofing mats from the area of frame 5295 and from the area of the

attaching points of the mounting plates and atta ching fittings of the rear RH and LH MGB bars. - If necessary, remove the TYRAP clamps, in order to separate the electrical harnesses. - Remove the sealing compound from the nuts (g). - Remove and scrap cotter pins (c).

For the recommended tightening torque values, in accordance with MMA Task 53-26-00-061: - Check the tightening torque of each nut (g), in accordance with MTC Work Card 20.02.05.404. - Interpret the results in accordance with paragraph 2.B.3.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 6/14

2006.03.28 2.B.3. Interpretation of the results of the c hecks in accordance with paragraph 2.B.1. and 2.B.2.

As per Figures 1, 2 and 3.



### NOTE 1

If the position of the nut slots does not allow the cotter pin to be inserted within the tightening torque range, the nut must be replaced or you can reduce the thickness of washer (k) (by 0.1 to 0.2 mm) by planishing it using No. 400-grit abrasive paper. Ensure perfect flatness of the washer (protect in accordance with MTC Work Card 20.04.04.404).

2.B.3.a. Bolts securing the front MGB bar attaching fitting

2.B.3.a.1. If the loss of the tighteni ng torque load of nuts (a) is less than or equal to 20% of the recommended minimum tightening torque: - Remove the sealing compound from the nuts or screw heads on the front mounting plate (m). - Re-adjust the tightening torque of all the front mounting plate attaching nuts (n), as per MMA

Task 53-26-00-062. - Torque tighten all the front fitting attachment nuts (a), as per MMA Task 53-26-00-061 and NOTE 1. - Safety the bolts (b) and nuts (a) with cotter pins (2). - Using a paint mark, identify the posit ion of each nut (a) with respect to the fitting (d), and the position of

the head of each bolt (b) with respect to frame 3855. - Run a bead of sealant round the nuts (a) and (n ) and round the heads of the screws on the front

mounting plate (m), as per MMA Tasks 53-26-00-061 and 53-26-00-062. - Return the helicopter to flight configuration as per paragraph 2.B.6.

2.B.3.a.2. If the loss of the tightening to rque load of at least one of the nuts (a ) on the front fitting is more than 20% of the recommended minimum tightening torque: - Comply with paragraph 2.B.4. on all the front fitti ng attachment bolts (b) before resuming flights.

2.B.3.b. Bolts securing the rear RH and LH MGB bar attaching fittings

2.B.3.b.1. If the loss of the tighteni ng torque load of nuts (g) is less than or equal to 20% of the recommended minimum tightening torque: - Remove the sealing compound from the nuts or screw heads on the rear RH and LH mounting plate. - Re-adjust the tightening torque of the nuts (f) on t he rear RH and LH mounting plate (e), as per MMA

Task 53-26-00-062. - Torque tighten all the attachment nuts (g) of t he fittings, as per MMA Task 53-26-00-061 and NOTE 1. - Safety the bolts (h) and nuts (g) with cotter pins (2). - Using a paint mark, identify the posit ion of each nut (g) with respect to the fitting (j), and the position of

the head of each bolt (h) with respect to frame 5295. - Run a bead of sealant round the nuts (g) and (f ) and round the heads of the screws on the rear

mounting plates (e), as per MMA Tasks 53-26-00-061 and 53-26-00-062. - Return the helicopter to flight configur ation, in compliance with paragraph 2.B.6.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 7/14

2006.03.28 2.B.3.b.2. If the loss of the tightening to rque load of at least one of the nuts (g) on the rear fittings is more than 20% of the recommended minimum tightening torque: - Comply with paragraph 2.B.5. on all the attachment bolts (h) of the rear fitting concerned, before

resuming flights.

2.B.4. Readjustment of the tightening torque of the screws that secure t he front mounting plate and check for absence of cracks in the bolts (b) that secure the front MGB bar attaching fitting

As per Figure 1: - Remove the sealing compound from the nuts or screw heads on the front mounting plate (m). - Re-adjust the tightening torque of all the nuts (n) on the front mounting plate, as per MMA

Task 53-26-00-062. - Run a bead of sealant round the nuts (n) and round t he heads of the screws that secure the front

mounting plate (m), as per MMA Task 53-26-00-062.

As per Figures 1 and 3: - If a tightening torque loss is detected on at least one of t he four nuts (a) on attaching fitting (d), as specified

in paragraph 2.B.3.a.2.: . Visually check that there is no crack in frame 3855, in the attachment area of attaching fitting (d) (see the

photos shown on Figure 1). If in doubt, carry out a dye penetrant inspection as per MTC Work Card

20.02.09.601. - If there is a crack in frame 3855,

. suspend flights and contact the Customer Service Technical Support Operations Department (STXS), by Tel.: +33 (0)4.42.85.99.29 Fax: +33 (0)4.42.85.99.66, in order to define the steps to be taken.

. Remove the four bolts (b), one by one, in order to carry out a dye penetrant inspection. . Carry out a dye penetrant inspection on the threaded bolt section as well as in the bolt head-to-plain

section blending radius of the four bolts (b), as per MTC Work Card 20.02.09.601. - If no crack is found in the four bolts (b), you can re-install the four bolts (b), as per MMA Task 53-26-00-

061 - and NOTE 2. Torque tighten the nuts (a) to the tightening torque specified in MMA Task 53-26-00-061

and see NOTE 1. - If a crack is found in one of the four bolts (b), scrap and replace all four bolts (b) that secure the front

fitting (d), with bolts (b), checked by dye penetrant in spection if the bolts are not new, or with new bolts (1), before resuming flights. In stall the four bolts (1) or (b) as per MMA Task 53-26-00-061 and NOTE 2, and torque tighten the nuts (a) or (3) to the torque value specified in MMA Task 53-26-00-061

and see NOTE 1.



### NOTE 2

Refer to Service Letter No. 1617-63-03. It defines the precautions that are to be taken when you re-install the bolts (b) or (h) and nuts (a) or (g) with MASTINOX.

. Safety the bolts (b) or (1) and the nuts (a) or (3) with cotter pins (2). . Using a paint mark, identify the position of each nut (a) or (3) with respect to the fitting (d), and the position

of the head of each bolt (b) or (1) with respect to frame 3855. . Run a bead of sealant round the nuts (a) or (3), as per MMA Task 53-26-00-061. . Return the helicopter to flight configur ation, in accordance with paragraph 2.B.6.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 8/14

2006.03.28 2.B.5. Readjustment of the tightening tor que of the nuts of the screw s that secure the rear mounting plates (e), and check for absence of cracks in the bolts (h) that se cure the rear RH and LH MGB bar attaching fitting(s)

As per Figure 2: - Remove the sealing compound from the nuts or scr ew heads on the rear RH and LH mounting plate (e). - Re-adjust the tightening torque of nuts (f) on the rear RH and LH mounting plate (e), as per MMA

Task 53-26-00-062.
- Run a bead of sealant round the nuts and round the heads of the screws that secure the rear RH and

LH mounting plate (e), as per MMA Task 53-26-00-062.

As per Figures 2 and 3: - If a tightening torque loss is detected on the nut(s) (g ) of attaching fitting (j), as specified in

paragraph 2.B.3.b.2.: . Visually check that there is no crack in frame 5295, in the attachment area of attaching fitting (j) (see

the photos shown on Figure 2). If in doubt, carry out a dye penetrant inspection as per MTC Work
Card 20.02.09.601. - If there is a crack in frame 5295,

. suspend flights and contact the Customer Service Technical Support Operations Department (STXS), by Tel.: +33 (0)4.42.85.99.29 Fax: +33 (0)4.42.85.99.66 in order to define the steps to be taken.

. Remove the 4 bolts (h), one by one, in order to carry out a dye penetrant inspection. . Carry out a dye penetrant inspection on the threaded bolt section as well as in the bolt head-to-plain

section blending radius of the four bolts (h), as per MTC Work Card 20.02.09.601. - If no crack is found in the four bolts (h), you can re -install the four bolts (h), as per MMA Task 53-26-00-061

and NOTE 2. Torque tighten the nuts (g) to the ti ghtening torque specified in MMA Task 53-26-00-061 and
see NOTE 1. - If a crack is found in one of the four bolts (h), scrap and replace all four bolts (h) that secure the fitting

concerned, with bolts (h), checked by dye penetrant inspection if the bolts are not new, or with new bolts (5), before resuming flights. Install the f our bolts (5) or (h) as per MMA Task 53-26-00-061 and NOTE 2. Torque tighten the nuts (g) or (4) to t he tightening torque specified in MMA Task 53-26-00-061
and see NOTE 1.

- Safety the bolts (h) or (5) and the nuts (g) or (4) with cotter pins (2). - Using a paint mark (DETAIL A Figure 3), identify the position of each nut (g) or (4) with respect to the

fitting (j), and the position of the head of each bolt (h) or (5) with respect to frame 5295. - Run a bead of sealant round the nuts (g) or (4), as per MMA Task 53-26-00-061. - Return the helicopter to flight configur ation, in accordance with paragraph 2.B.6.

2.B.6. Final steps

- Re-install the TYRAP clamps if they were removed. - Install the trimmings and soundproofing mats in the area of frame 3855 and / or frame 5295. - Install the engines, as per Subta sk 71-00-00-421 of MMA Task 71.00.00.051.



### 2.C. IDENTIFICATION

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



### 2.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Not applicable.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 9/14

2006.03.28 Inspection zones on frame 3855, in the area of th e bolts that secure the front attaching fitting

Figure 1

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 10/14

2006.03.28 Inspection zone on frame 5295, in the area of th e bolts that secure the rear attaching fitting

Figure 2

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 11/14

2006.03.28 Figure 3

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 12/14

2006.03.28 

### 3. MATERIAL INFORMATION

3.A. MATERIAL: COST – AVAILABILITY

For any information, contact the Customer Service Sales Department.



### 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

332A22161320 or 21 A/R 1 Bolt, attachment, front 23310CA020025 12 2 Cotter pin

ASNA0045-120BCL A/R 3 Nut

ASNA0045-100BCL A/R 4 Nut 332A22161420 A/R 5 Bolt, attachment, rear

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

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



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

Not applicable.



### 3.E. RE-IDENTIFIED PARTS

Not applicable.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 13/14

2006.03.28 3.F. TOOLING: COST – AVAILABILITY

Not applicable.



### 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



### 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.

### ALERT SERVICE BULLETIN AS332

Approved under EASA DOA No. 21J.056. 

# 05.00.65 Page 14/14

2006.03.28 

### 4. APPENDIX

Send the tightening torque measurement readings to the Technical Support Operations – Customer Service Department (STXS) at the EUROCOPT ER / Marignane works, for analysis. Fax: 33 (0)4.42.85.99.66.



### Helicopter S/N: Flying hours logged:

Tightening torque loads measured on the front fitting

Nut 1 2 3 4

daNm

Lbf.in

Appendix 1 FERRURE AVANT

FRONT FITTING