### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 1/19

2006.07.19 EUROCOPTER

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE C EDEX F RANCE 

### CIVIL VERSION(S): B4



# ALERT SERVICE BULLETIN

No. 53A008

SUBJECT : FUSELAGE

Containment box structure installation for cabin vibration damper weights

Corresponds to MOD 073565.

REVISION No. DATE OF APPROVAL DATE OF ISSUE

No. 0 2006.07.07 2006.07.19

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 2/19

2006.07.19 

### 1. PLANNING INFORMATION

1.A. EFFECTIVITY

1.A.1. Helicopters / Equipment installed on aircraft

Helicopters pre-MOD 073565.



### NOTE 1

Refer to Individual Inspection Log B ook (RIC) (RIC AMS), equipment Log Cards (FM) or aircraft Log Book to i dentify the actual modification status

of the aircraft.

1.A.2. Equipment not installed on aircraft

Not applicable.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1. C. REASON

To install a cabin vibration damper containment device, in case of vibration damper blade failure, preventing any contact with flying control it ems located underneath the cabin floor.

This Alert Service Bulletin will form the subject of an EASA Airworthiness Directive.

Compliance with this Alert Service Bulletin will s upersede the prescriptions in Telex Alert No. 05A002

Revision 1. This information is made official by Revi sion 0 of Alert Service Bulletin No. 05A002.



### NOTE 2

It is mandatory to install two box structures, on RH side and on LH side of aircraft, for compliance with the instructions in Telex

Alert No. 05A002.

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 3/19

2006.07.19 1.D. DESCRIPTION

Eurocopter was advised of a case of cabin vibration damper blade failure. This failure was found further to a change in the aircraft vibration level felt by the aircrew. A complementary analysis of the vibration damper bl ade failure consequences show ed that the loose broken part, which remains contained in the lower fairing, could in terfere with the flying controls, and finally result in a possible jamming.

Pending a modification, Eurocopter published Telex Alert 05A002 requiring a check for any crack on RH and LH cabin vibration damper assembly blades.

Therefore, Eurocopter developed a vibration damper c ontainment device avoiding any interference in case of vibration damper blade failure. Containment of c abin vibration damper is ensured by installing a box structure, solid with the airframe structure underneath aircraft bottom struct ure. In case of vibration damper blade failure, the loose parts will be contained, whic h will avoid any interference with the environment

underneath the cabin floor.

Therefore Eurocopter renders compliance with this Alert Service Bulletin mandatory.

This Alert Service Bulletin also indicates the main tenance (defined in § 2.D.) to be applied to these box

structures: this will be introduced in Master Serv icing Recommendations in section 05.22.00 and not in

section "Airworthiness Limitations ".



### 1.E. COMPLIANCE

Eurocopter renders compliance with th is Alert Service Bulletin mandatory.

1.E.1. Compliance at the works

1.E.1.a. On helicopter

For helicopters pre-MOD 073565, comply with paragr aph 2.B. of this Alert Service Bulletin.

1.E.1.b. On equipment not installed on aircraft

Not applicable.

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 4/19

2006.07.19 1.E.2. Compliance in operation

1.E.2.a. On helicopter / equipment installed on aircraft: By operator

For aircraft pre-MOD 073521 (SB 53-006), pre-MO D 073525 (SB 53-007) (none of the two MODs embodied), comply with paragraphs 2.B.1., 2.B.2. and 2.B.5. of this Alert Service Bulletin at the latest by

31 March 2007.

For aircraft post-MOD 073521 (SB 53-006) or MOD 073525 (SB 53-007), comply with paragraphs 2.B.1.,

2.B.3. and 2.B.5. of this Alert Service Bulletin at the latest by 31 March 2007.

1.E.2.b. On equipment not installed on aircraft:

Not applicable.



### 1.F. APPROVAL

Approval is limited to civil version helicopt ers subject to Airworthiness Certificate.

1.F.1. Approval of modifications

The information or instructions relate to MOD 073565 which was approved on 16 February 2006.

1.F.2. Approval of the Service Bulletin

The technical information contained in this Alert Service Bulletin No. 53A008 Revision 0 was approved on 7 July 2006 under the authority of EASA Desi gn Organization Approval No. 21J.056.

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 5/19

2006.07.19 1.G. MANPOWER

1.G.1. Qualification

For compliance with this Alert Service Bulleti n, Eurocopter recommends the following personnel qualifications:

Qualification: 1 Airframe Technician

1.G.2. Time

Time values are indicated for refe rence, for a standard configuration.

Time: 4 hours for 1 Airframe Technician

1.G.3. Estimation of aircraft downtime

4 hours.



### 1.H. WEIGHT AND BALANCE

On completion of the work mention weights and moment s in the "Weight & Balance" sheet (Flight Manual).

1.H.1. Weight

For aircraft post-MOD 073521 or MOD 073525: Weight: 0.420 kg.

For aircraft pre-MOD 073521 and pre-MOD 073525 (none of the two MODs embodied): Weight: 0.450 kg.

1.H.2. Moment

For aircraft post-MOD 073521 or MOD 073525: Longitudinal moment: 0.55 m.kg.

For aircraft pre- MOD 073521 and pre-MOD 073525 (none of the two MODs embodied): Longitudinal moment: 0.59 m.kg.



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 6/19

2006.07.19 1.J. SOFTWARE MODIFICATION EMBODIMENT STATE

Not applicable.



### 1.K. REFERENCES

The following documents are required for compli ance with this Alert Service Bulletin: - Aircraft Maintenance Manual (AMM): Task 24-00-00, 3-1: General instructions - Electrical Task 53-51-00, 4-2: Removal / Installation - Lower cowlings

- Standard Practices Manual (MTC):

Work Cards 20-02-01-415: Installati on of electrical cable bundles Work Cards 20-02-05-404: Assembling by bolts and nuts Work Cards 20-07-03-408: General principles applic able for visual cleanliness, appearance checks on an aircraft after an inspection or repair



### 1.L. OTHER DOCUMENTS AFFECTED

This Service Bulletin will give rise to amendm ent of the following documents by Eurocopter: - Aircraft Maintenance Manual (AMM) - Illustrated Parts Catalog (IPC) - Master Servicing Recommendations (PRE)

These documents will be circulated at a later date.



### 1.M. TOOLING AFFECTED

Not applicable.



### 1.N. INTERCHANGEABILITY AND MIXABILITY BETWEEN THE PARTS

1.N.1. Interchangeability

Non interchangeable.

1.N.2. Mixability

Refer to NOTE 2 of paragraph 1.C.

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 7/19

2006.07.19 

### 2. ACCOMPLISHMENT INSTRUCTIONS

2.A. GENERAL

Depending on the Aircraft Maintenance Manual (AMM). Refer to general safety instructions on elec trical generation as per Task 24-00-00, 3-1.

As per Standard Practices Manual (MTC). Protect electrical wiring during maintenance or modi fication operations as per Work Card 20-07-03-408.



### 2.B. OPERATIONAL PROCEDURE

2.B.1. Preliminary steps

- Disconnect all electrical power supply.

- Remove front lower cowlings: central (h), LH side (l) and RH side (i) (Figure 1 and 2) as per Task 53-51- 00, 4-2 (AMM).

2.B.2. Embodiment of MOD 073565 for aircraft pre- MOD 073521, pre-MOD 073525 (none of the two MODs embodied).



### NOTE 1

Installation of vibration damper box structure assembly on RH side of aircraft is identical to that on LH side (Figure 1).

Installation of box structures on vibration dampers does not affect the adjustment process.

2.B.2.a. Installation of box structure/vibrati on damper assembly on aircraft LH side (Figure 1)

As per Figure 1-DETAIL A

- Remove rivet (k) from cross-member (j) and counte r-drill hole for rivet (k) to diameter 5.5 mm (Section B-B).

- Remove:

• 4 self-locking nuts (a),

• 4 washers (d),

• 4 bolts (m),

- Scrap nuts (a), washers (d) and bolts (m).

As per Figure 1-DETAIL B

- Offer up and install unequipped box structure (4) on vibration damper.

- Install unequipped box structure (4) with:

• 4 coils (12),

• 4 spherical washers (13),

• 4 washers (11),

• 4 bolts (10),

• 4 self-locking nuts (14).

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 8/19

2006.07.19 NOTE 2

Flats on coils and on spherical washers are positioned specifically. They must be directed outward fitting.



### NOTE 3

Do not fit washers underneath 4 self-locking nuts (14).

- Tighten to tightening torque (DETAIL B).

- Offer up blanking plate assembly (1) on unequipped box structure (4).

- Assemble blanking plate (1) by means of 2 washers (3) and 2 bolts (2).

- Tighten bolts (2) to standard torque as per Work Card 20-02-05-404 (MTC).

- Tighten box structure assembly by means of bolt (6), 2 washers (7) (1 underneath bolt head, 1 underneath nut) and nut (8).

- Carry out visual checks of aircraft as per Work Card 20-07-03-408 (MTC).

2.B.3. Embodiment of MOD 073565 for aircraft post-MOD 073521 or MOD 073525

Installation of box structures on vibration damper s installation does not affect adjustment process.

2.B.3.a. Installation of box structure/vibrati on damper assembly on aircraft RH side (Figure 2)

- Remove rivet (k) from cross-member (j) and counte r-drill hole for rivet (k) to diameter 5.5 mm (Section D-D).

- Remove chronologically, recording the removed items (DETAIL B):

• 4 self-locking nuts (t),

• 4 washers (b),

• 4 bolts (c),

• 8 washers (d),

• 4 spherical washers (e),

• 4 coils (f).

- Scrap nuts (t) and washers (d).

- Keep folding shims (p), (q), (r), (s) in place (DETAIL C).

- Offer up and install unequipped box structur e (4) on vibration damper (DETAIL B).

- Install unequipped box structure (4) in previously recorded order, with:

• 4 coils (f),

• 4 spherical washers (e),

• 4 washers (5),

• 4 bolts (c),

• 4 washers (b),

• 4 self-locking nuts (15).



### NOTE 4

Flats on coils and spherical was hers are positioned specifically. They must be directed outward fitting.

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 9/19

2006.07.19 - As per DETAIL C, adjust profiles of folding shims (p ), (q), (r) and (s), only at blending radii identified as (R) on fittings. The other shim radii may be out of contact with other radii on fittings.

- Tighten to torque (DETAIL B).

- Offer up blanking plate assembly (1) on unequipped box structure (4).

- Assemble blanking plate (1) by means of 2 washers (3) and 2 bolts (2).

- Tighten bolts (2) to standard torque as per Work Card 20-02-05-404 (MTC).

- Tighten box structure assembly by means of bolt (6), 2 washers (7) (1 underneath bolt head, 1 underneath nut) and nut (8).

- Carry out visual checks of aircraft as per Work Card 20-07-03-408 (MTC).

2.B.3.b. Installation of box structure/vibrati on damper assembly on aircraft LH side (Figure 3)

- Remove rivet (n) from cross-member (j) and counte r-drill hole for rivet (n) to diameter 5.5 mm (Section C-C).

- Remove chronologically, recording the removed items (DETAIL E):

• 4 self-locking nuts (t),

• 4 bolts (m),

• 4 washers (d),

• 4 spherical washers (e),

• 4 coils (f).

- Scrap nuts (t) and washers (d).

- Offer up and install unequipped box structur e (4) on vibration damper (DETAIL E).

- Install unequipped box structure (4) in previously recorded order, with:

• 4 bolts (m),

• 4 washers (5),

• 4 coils (f),

• 4 spherical washers (e),

• 4 self-locking nuts (15).



### NOTE 5

Flats on coils and of spherical washers are positioned specifically. They must be directed outward fitting.



### NOTE 6

Do not fit washers underneath 4 self-locking nuts (15).

- Tighten to torque as per DETAIL E.

- Offer up blanking plate assembly (1) on unequipped box structure (4).

- Assemble blanking plate (1) by means of 2 washers (3) and 2 bolts (2).

- Tighten bolts (2) to standard torque as per Work Card 20-02-05-404 (MTC).

- Tighten box structure assembly by means of bolt (6), 2 washers (7) (1 underneath bolt head, 1 underneath nut) and nut (8).

- Carry out visual checks of aircraft as per Work Card 20-07-03-408 (MTC).

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 10/19

2006.07.19 2.B.4. Tests

Not applicable.

2.B.5. Final steps

- Re-install front lower cowlings: central (h), RH side (i), LH side (l) (Figures 1 and 2). - Reconnect all electrical power supplie s as per Work Card 20-07-03-406 (MTC). - Restore aircraft to flight condition.

2.B.6. Retrofitting of spare part stocks

Not applicable.



### 2.C. IDENTIFICATION

2.C.1. Identification of modi fications in the documents

Record embodiment of Modification 073565 and compliance with this Alert Service Bulletin No. 53A008

Revision 0 in the aircraft documents.

2.C.2. Identification of modifications on material

Not applicable.



### 2.D. OPERATING AND MAINTENANCE INSTRUCTIONS

2.D.1. Operating instruction(s)

Not applicable.

2.D.2. Maintenance instruction(s)

Check condition of vibration damper box structures every 500 hours or 2 year s (whichever occurs first), with respect to the following criteria: - Check for cracks, deformations, wear or corrosion. - Check presence of all nuts & bolts and check bolt tightening. In case of cracks, deformations, wear or corrosion, replace box structure.

Master Servicing Recommendations (PRE) will integrat e this instruction in section 05.22.00 "Inspection periodicities" at the time of the next Revision. After integration of this instruction in Master Servicing Recommendations (PRE), refer to the PRE.ALERT SERVICE BULLETIN EC130Approved under EASA DOA No. 21J.056.53A008Page 11/192006.07.19Figure 1ALERT SERVICE BULLETIN EC130Approved under EASA DOA No. 21J.056.53A008Page 12/192006.07.19PAGE LEFT BLANK INTENTIONALLYALERT SERVICE BULLETIN EC130Approved under EASA DOA No. 21J.056.53A008Page 13/192006.07.19Figure 2ALERT SERVICE BULLETIN EC130Approved under EASA DOA No. 21J.056.53A008Page 14/192006.07.19PAGE LEFT BLANK INTENTIONALLYALERT SERVICE BULLETIN EC130Approved under EASA DOA No. 21J.056.53A008Page 15/192006.07.19Figure 3ALERT SERVICE BULLETIN EC130Approved under EASA DOA No. 21J.056.53A008Page 16/192006.07.19PAGE LEFT BLANK INTENTIONALLY

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 17/19

2006.07.19 

### 3. MATERIAL INFORMATION

3.A. MATERIAL: COST – AVAILABILITY

3.A.1. COST

The kits and/or components will be delivered free of charge on operator's order until 31 March 2007.

3.A.2. Availability

The kits or components will be delivered upon operator's order.



### 3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.



### 3.C. MATERIAL REQUIRED FOR EACH HELICOPTER/ENGINE/COMPONENT

3.C.1. Kit to be ordered for one helicopter

Material P/N Qty It. Key Word It. Former P/N Instruction

Helicopters pre-MOD 073521, pre-MOD 073525 (none of the 2 embodied)

350A07-3565-0072 Kit including

350A21-4922-01 2 1 Plate assy, blanking

22125BC050012L 4 2 Bolt

23116AG050LE 4 3 Washer 350A21-4922-20 2 4 Structure, box, unequipped

22125BE050016L 2 6 Bolt

23111AG050LE 4 7 Washer

ASN52320BH050N 2 8 Nut

22201BE060052L 8 10 Bolt

23116AG060LE 8 11 Washer

350A08-7029-21 8 12 Coil 332A22-1948-20 8 13 Washer, spherical ASN52320BH060N 8 14 Nut a ASN52320BH060N Scrap

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 18/19

2006.07.19 Material P/N Qty It. Key Word It. Former P/N Instruction

Helicopters post-MOD 073521 or MOD 073525

350A07-3565-0071 Kit including

350A21-4922-01 2 1 Plate assy, blanking

22125BC050012L 4 2 Bolt

23116AG050LE 4 3 Washer 350A21-4922-20 2 4 Structure, box, unequipped 23116AG080LE 8 5 Washer d 23112AG080LE Scrap

22125BE050016L 2 6 Bolt

23111AG050LE 4 7 Washer

ASN52320BH050N 2 8 Nut

9 Not in use ASN52320BH080N 8 15 Nut t ASN52320BH080N Scrap

3.C.2. Material to be ordered separately

Not applicable.

3.C.3. Ingredient (s) to be ordered separately

The ingredients required for compliance with Tasks and Work Cards mentioned can be ordered from

INTERTURBINE.

Website: http://www.itlogistics.de Telephone: +49.41.91.809.300

AOG: +49.41.91.809.444

As per Work Cards and Tasks mentioned in this Alert Service Bulletin.

3.C.4. Tooling(s)

As per Work Cards and Tasks mentioned in this Alert Service Bulletin.

3.C.5. Material required for item not installed on aircraft

Not applicable.

### ALERT SERVICE BULLETIN EC130

Approved under EASA DOA No. 21J.056. 

# 53A008 Page 19/19

2006.07.19 3.D. PROCUREMENT CONDITIONS

Order the required quantity from the EUROCOPTER network's Customer Support Sales Department,

or from

EUROCOPTER Etablissement de Marignane Direction VENTES Service Client (S.V.)

13725 MARIGNANE CEDEX

FRANCE



### NOTE

For ALERT SERVICE BULLETINS, order by:

Telex: HELICOP 410 969F Fax: +33 (0)4.42.85.99.96.



### 4. APPENDIX

Not applicable.