ALERT SERVICE BULLETIN AS332 

Approved under EASA DOA No. 21J.056. 05.00.76 Page 1/16

 2008.02.20

 

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

 EUROCOPTER

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE CEDEX FRANCE CIVIL VERSION(S): C,C1,L,L1 

 MILITARY VERSION(S): B,B1,M,M1,F1 

 ALERT SERVICE BULLETIN 

No. 05.00.76 

SUBJECT: TIME LIMITS - MAINTENANCE CHECKS

Check of the outer skin and the butt strap at Frame 5295

ATA : 53 

REVISION No. DATE OF APPROVAL DATE OF ISSUE 

 

Revision 0 On: February 20, 2008 2008.02.20 

 

 
 ALERT SERVICE BULLETIN AS332 

Approved under EASA DOA No. 21J.056. 05.00.76 Page 2/16

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1. PLANNING INFORMATION 

1.A. EFFECTIVITY 

1.A.1. Helicopters/Installed equipment 

Helicopters pre-MOD 0722907, except for serial numbers 2078 and 2102. 

NOTE

Helicopters modified per MOD 0722907 and helicopters 

S/N 2078 and 2102 are not concerned by the instructions in this 

ALERT SERVICE BULLETIN (refer to the aircraft Individual 

Inspection Log Book to identify the actual modification status of 

the aircraft). 

Frame 5295 on helicopters S/N 2078 and 2102 has been 

replaced through compliance with repair sheets 332.53.509.07 

and 332.53.502.06 respectively. 

1.A.2. Non-installed equipment 

Not applicable. 

1.B. ASSOCIATED REQUIREMENTS 

Not applicable. 

1.C. REASON 

To periodically check that there are no cracks in the outer skin or the butt strap in the sliding cowling LH and 

RH rail attachment areas on Frame 5295. 

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

EUROCOPTER has been informed of a crack detected in Frame 5295 in the attachment area of an MGB 

rear suspension bar on an AS332L helicopter.

This helicopter had logged a total of 28,338 flying hours. Frame 5295 equipping this helicopter was of the 

"first generation" definition (Pre-MOD 0722907), i.e., comprising plates and angles assembled by riveting. 

The crack in Frame 5295 was detected due to the presence of a crack in the outer skin and in the butt strap 

near the sliding cowling rail, during an ALF check (check after the last flight of the day). 

After removing the coverings and certain structural components, such as gussets and angles, damage was 

noted from inside the helicopter: cracks in the flange and the outer angles and in part of the web, near the 

sliding cowling rail attachment (refer to Figure 4). 

Considering the examinations and analyses of these cracks, EUROCOPTER is introducing additional 

monitoring requirements for Frame 5295, on the outside of the helicopter, on the skin and on the butt strap 

near the sliding cowling rail attachment. 

This check is made easier by embodying MOD 0726478, which consists in cutting out the sliding cowling 

rails locally. 

This cut-out exposes the splice near the rail attachment holes, making it easier to detect a crack and thus 

reducing the risks of cracks occurring in Frame 5295. 

EUROCOPTER renders compliance with the measures defined in this ALERT SERVICE BULLETIN, 

mandatory. 
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1.E. COMPLIANCE 

1.E.1. Compliance at the works 

1.E.1.a. On helicopters/installed equipment: Not applicable. 

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

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

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

1) On helicopters which have logged less than 8,800 flying hours on receipt of this ALERT SERVICE 

BULLETIN, issued on the date indicated at the foot of the page: 

- Comply with paragraph 2.B. at the latest within 10 flying hours after reaching 8,800 flying hours, then, 

a) If there is no crack in the outer skin or in the butt strap in area 1:

- comply with paragraph 2.B. at intervals not exceeding 10 flying hours. 

b) If there is a crack in the outer skin and/or in the butt strap in area 1, and if there is no crack in area 

1 of Frame 5295:

- Contact the Customer Service Technical Support Operations Department (ESTVA) to ask for the 

appropriate repair sheet according to how the crack is situated, by: 

Tel.: +33 (0)4.42.85.99.29 

Fax: +33 (0)4.42.85.99.66. 

. Pending compliance with the appropriate repair sheet, comply with paragraph 2.B.2. at intervals 

not exceeding 50 flying hours. 

and 

. After compliance with the appropriate repair sheet, comply with paragraph 2.B. at intervals not 

exceeding 10 flying hours. 

c) If there is a crack in the outer skin and/or in the butt strap in area 1, and if there is a crack in area 1 

of Frame 5295:

- Stop flights. 

- Inform the Customer Service Technical Support Operations Department (ESTVA) by: 

Tel.: +33 (0)4.42.85.99.29 

Fax: +33 (0)4.42.85.99.66. 

- EUROCOPTER recommends compliance with paragraph 2.B.3. within 300 flying hours/6 months after 

reaching 8,800 flying hours (the first limit reached is applicable). 
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2) On helicopters which have logged 8,800 flying hours or more on receipt of this ALERT SERVICE 

BULLETIN, issued on the date indicated at the foot of the page:

- Comply with paragraph 2.B. at the latest within 10 flying hours, 

then, 

a) If there is no crack in the outer skin or in the butt strap in area 1:

- comply with paragraph 2.B. at intervals not exceeding 10 flying hours. 

b) If there is a crack in the outer skin and/or in the butt strap in area 1, and if there is no crack in area 

1 of Frame 5295:

- Contact the Customer Service Technical Support Operations Department (ESTVA) to ask for the 

appropriate repair sheet according to how the crack is situated, by: 

Tel.: +33 (0)4.42.85.99.29 

Fax: +33 (0)4.42.85.99.66. 

. Pending compliance with the appropriate repair sheet, comply with paragraph 2.B.2. at intervals 

not exceeding 50 flying hours. 

and 

. After compliance with the appropriate repair sheet, comply with paragraph 2.B. at intervals not 

exceeding 10 flying hours. 

c) If there is a crack in the outer skin and/or in the butt strap in area 1, and if there is a crack in area 1 

of Frame 5295:

- Stop flights. 

- Inform the Customer Service Technical Support Operations Department (ESTVA) by: 

Tel.: +33 (0)4.42.85.99.29 

Fax: +33 (0)4.42.85.99.66. 

- EUROCOPTER recommends compliance with paragraph 2.B.3. within 300 flying hours/6 months 

following receipt of this ALERT SERVICE BULLETIN, issued on the date indicated at the foot of the 

page (the first limit reached is applicable). 

1.E.2.b. On spares: Not applicable. 

1.F. APPROVAL 

Approval is limited to civil version helicopters subject to an Airworthiness Certificate. 

The technical information given in this ALERT SERVICE BULLETIN was approved 

on February 20, 2008 under the authority of EASA Design Organisation Approval No. 21J.056. 

1.G. MANPOWER 

Qualification: Mechanic or structure technician. 

Time: 15 minutes (approximately, for compliance with paragraph 2.B.1.). 

1 hour (approximately, for compliance with paragraph 2.B.2.). 

3 hours (approximately, for compliance with paragraph 2.B.3.). 
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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: 53.50.00.403, 

53.50.00.601. 

Standard Practices Manual (MTC) Work Cards: 20.02.09.601, 

20.04.04.403, 

20.04.05.402, 

20.04.05.403. 

1.L. OTHER DOCUMENTS CONCERNED 

Maintenance Program (PRE). 

Maintenance Manual (MET). 

1.M. INTERCHANGEABILITY AND MIXABILITY OF PARTS 

Not applicable. 
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2. ACCOMPLISHMENT INSTRUCTIONS 

2.A. GENERAL 

The operational procedure in paragraph 2.B. describes the operations for one side and for the front and rear 

section of Frame 5295, and must be applied to both the LH and RH sides of Frame 5295 (refer to Figure 1). 

2.B. OPERATIONAL PROCEDURE 

2.B.1. Visual check of the outer skin and the butt strap in the sliding cowling LH and RH rail attachment areas on 

Frame 5295 

As per Figure 2

- Open the sliding cowling. 

- Visually check that there is no crack in the outer skin or in the butt strap in area 1: 

NOTE

Area 1 includes the screws attaching the sliding cowling rail to 

the front and rear section of Frame 5295 and to the skin. 

Interpretation of the results:

a) If there is no crack in the outer skin and in the butt strap in area 1: 

- Leave as is. 

- Close the sliding cowling. 

- Resume flights. 

b) If there is a crack in the outer skin and/or in the butt strap in area 1: 

- Visually check that there are no cracks in Frame 5295 in accordance with paragraph 2.B.2. 

2.B.2. Visual check to make sure there are no cracks in Frame 5295 

2.B.2.a. Preliminary steps 

As per Figures 3 and 4

- Gain access to area 1 of Frame 5295. 

. Remove stringer gusset (c) and fitting (d). 

. If necessary, 

- remove the TYRAP clamps to separate the electrical harnesses when performing the visual or 

borescope check, 

- remove the soundproofing mats. 

- Visually check that there are no cracks in area 1 of Frame 5295. 

If in doubt, carry out a dye penetrant inspection as per MTC Work Card 20.02.09.601. 
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2.B.2.b. Interpretation of the results

1) If there is no crack in area 1 of Frame 5295: 

- Reinstall stringer gusset (c) and fitting (d). 

- Fit TYRAP clamps if they were removed. 

- If necessary, reinstall the LH and RH coverings and the ceiling coverings between two inspections. 

- Resume flights. 

2) If there is a crack in area 1 of Frame 5295: 

- Stop flights. 

- Inform the Customer Service Technical Support Operations Department (ESTVA) by: 

Tel.: +33 (0)4.42.85.99.29 

Fax: +33 (0)4.42.85.99.66. 

2.B.3. Embodiment of MOD 0726478R2 on the sliding cowling rails and shims in the attachment areas on 

Frame 5295 

- Remove the sliding cowling as per MET Work Card 53.50.00.403. 

As per Figure 5

- On the LH and RH rail, identify particularly the two attachment holes (b) and the two attachment screws (a) 

at Frame 5295. 

- Before removal, identify the position of the screws and the shims. 

- Remove the rail, if necessary. 

- Retain all the removed hardware. 

- Mark and cut the rail as per Detail B. 

- Cut the corresponding shims to match the cut-out in the rails. 

- Deburr the shims and the rails and remove sharp edges. 

- Touch up the reworked areas with ALODINE as per MTC Work Card 20.04.04.403. 

- Touch up the EPOXY P05 primer paint and the top coat paint as per MTC Work Cards 20.04.05.402 and 

403. 

- Install the shims and the rails. 

- Fit one or two washers, both items (1) and (2), on the two LH side and two RH side screws (a), in order to 

compensate for the thickness of the rail and the shims, as per Detail C (Pre-MOD 0722828) or Detail D 

(Post-MOD 0722828). 

- Apply a layer of MASTINOX sealant to the shank of screws (a). 

- Install the two screws (a) on the RH side and the two screws (a) on the LH side of the helicopter, equipped 

with washers (1) and (2). 

- Apply a bead of sealant (3) around the heads of the screws and the rails as per Detail C or Detail D. 

- Remove excess sealant (3). 

- Install the sliding cowling as per MET Work Card 53.50.00.403 and check the sliding cowling as per MET 

Work Card 53.50.00.601. 
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2.C. IDENTIFICATION 

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

Following compliance with paragraph 2.B.3., record embodiment of MOD 0726478R2 in the aircraft 

documents. 

2.D. OPERATING AND MAINTENANCE INSTRUCTIONS 

Not applicable. 
 ALERT SERVICE BULLETIN AS332 

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Figure 1 

Frame X5295 

Frame X5295 
 ALERT SERVICE BULLETIN AS332 

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Crack in the outer 

skin and in the butt strap

Figure 2 

Area 1 

Frame X5295 

Cowling rail 
 ALERT SERVICE BULLETIN AS332 

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AREA 1 at the attachment screws of the sliding cowling upper rail

Figure 3 

Area 1: With black marks 

indicating movements in the 

area.

Frame X 5295 - View looking forward

Area 1 
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Figure 4 

Cracks 

Crack in outer skin 

Frame 5295 

Frame X 5295 - View looking aft

INACCESSIBLE AREA 

ACCESSIBLE AREA 

Fitting (d) 

Stringer gusset (c) 
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Figure 5 

View Post-MOD 0726478R2 

View Pre-MOD 0726478R2 

Post-MOD 0722828 

Pre-MOD 0722828 
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3. MATERIAL INFORMATION

3.A. MATERIAL: COST - AVAILABILITY 

Not applicable. 

3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT 

Not applicable. 

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

3.C.1. Kit or component(s) to be ordered 

New Part Number Qty Item Key Word Former Part Number Instructions 

Disposition 

23111AG050LE 8 1 Washer 

23119AG050LE 8 2 Washer 

3.C.2. Product(s) to be ordered separately 

New Part Number Qty Item Key Word Former Part Number Instructions 

Disposition 

 

* PR1771B2SEMK654 AR 3 Sealing compound 

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.D. MATERIAL REQUIRED FOR EACH SPARE PART 

Not applicable. 

3.E. RE-IDENTIFIED PARTS 

Not applicable. 

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 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.