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

# EMERGENCY



# ALERT SERVICE BULLETIN

SUBJECT : FUSELAGE

Check of the tail boom / Fenestron junction frame

ATA : 53

AIRCRAFT

CONCERNED NUMBER Version(s)

Civil Military

EC130 05A0 17 B4, T2



### Revision No. Date of is sue

Revision 0 2014

- 06

- 06



### Summary :

Visual check, through the inside of the tail boom, for cracks on the tail boom / Fenestron junction frame.



### Compliance :

Compliance with this ALERT SERVICE BULLETIN is mandatory. For the attention of

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### 1. PLANNING INFORMATION

1.A. EFFE CTIVITY

1.A.1. Helicopters/installed equipment

On all EC130 B4 and T2 helicopters.

1.A.2. Non

- installed equipment

Not applicable.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1.C. REASON

Revision 0 : On the EC130 B4 tail boom / Fenestron junction frame, two cases of cracks were found in a new area of the

frame during non

- scheduled inspections.

Examination revealed that the crack had initiated in the radius between the web and the flange on the tail

cone side, in the lower RH part of the frame (De tail A, Figure 1).

It spreads rapidly by following the radius along the web of the frame.

The cracks are of considerable length and no deterioration is visible from the outside of the helicopter.

The inspection of this area which can reveal these cracks is scheduled at the " 600 hours // 2 years "

inspection.

Information Notice (IN) No. 2167

- I

- 53 was issued on June 15, 2010 to specify the applicable maintenance.

Considering the cases encountered in service, this periodicity is unsuitable.

In these conditi ons and under high tail rotor thrust load, the resistance margins of this junction may be

insufficient.

Consequently, Airbus Helicopters makes compliance with this ALERT SERVICE BULLETIN mandatory. Its

purpose is to enable a detailed visual check through the inside of the tail boom.



### 1.D. DESCRIPTION

Compliance with this ALERT SERVICE BULLETIN consists in checking that there are no cracks on the tail

boom / Fenestron junction frame.

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### 1.E. COMPLIANCE

1.E.1. Compliance at the works

Not applicable.

1. E.2. Compliance in service

Helicopters/installed equipment :

For helicopters which have logged less than 690 flying hours :

C omply with paragraph 3.B.1. at the latest when reaching 700 flying hours

. Then comply with paragraph 3.B.1. or 3.B.2. at intervals not exceeding 25 flying hours.

For helicopters which have logged 690 or more flying hours : Comply with paragraph 3.B.1. within 10 flying hours following receipt of Revision 0 of this ALERT SERVICE

BULLETIN.

Then comply with paragraph 3.B.1. or 3.B.2. at i ntervals not exceeding 25 flying hours.

Non

- installed equipment : Not applicable.



### 1.F. APPROVAL

Approval of modifications:

Not applicable.

Approval of this document :

The technical information contained in this ALERT SERVICE BULLET IN Revision 0 wa s approved

on June 06, 2014 under the authority of EASA Design Organization Approval No. 21J.056 for helicopters of

civil versions subject to an Airworthiness Certificate.

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### 1.G. MANPOWER

For compliance with this ALERT SERVICE BULLETIN, Airbus Helicop ters recommends the following

personnel qualifications:

Qualification: 1 Technician

The time for the operations is given for information purposes, for a standard configuration.

Time for the operations: approximately 1 hour to comply with paragraph 3 .B.1. (with removal of the

stabilizer)

approximately 30 minutes to comply with paragraph 3.B.2. (without removal of the

stabilizer)



### 1.H. WEIGHT AND BALANCE

Not applicable.



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD

Not applicable.



### 1.K. REFERENCES

Aircraft Maintenance Manual (AMM) :

AMM: 55

- 11

- 00,4

- 1: Removal/Installation

- Horizontal stabilizer

Standard Practices Manual (MTC) :

- MTC: 20.04.01.102: Use of cleaning products on individual parts and on aircraft

- MTC: 20.02.09.101: Crack detection through dye

- penetrant inspection: General

- MTC: 20.02.09.601: Checking structural parts/components using the dye

- penetrant procedure



### 1.L. DOCUMENTS AFFECTED

Not applicable.



### 1.M. INTERCHANGEABILITY OR MIXAB ILITY OF PARTS

Not applicable.

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### 2. MATERIAL INFORMATION

2.A. MATERIAL: PRICE

- AVAILABILITY

- PROCUREMENT

Not applicable.



### 2.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.



### 2.C. MATERIAL REQUIRED FOR EACH HELICOPTER/COMPONENT

Produc ts to be ordered separately :

As per the Tasks specified in this ALERT SERVICE BULLETIN:

The products can be ordered separately from the INTERTURBINE AVIATION LOGISTICS company.

Website: http://www.interturbi ne.com

Telephone: +49.41.91.809.300

AOG: +49.41.91.809.444



### 2.D. MATERIAL TO BE RETURNED

Not applicable.

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### 3. ACCOMPLISHMENT INSTRUCTIONS

3.A. GENERAL

NOTE 1

Contact details of the Airbus Helicopters Customer Service Technical Support

Departmen t:

Tel.: +33 (0)4.42.85.97.16.

Fax: +33 (0)4.42.85.99.66.

E

- mail: airframe.technical

- support@eurocopter.com



### 3.B. OPERATIONAL PROCEDURE

3.B.1. Inspection, through the inside of the tail b oom, of the tail boom / Fenestron junction frame (with removal of

the stabilizer)

As per Figure s 1 and 3 :

- Remove the horizontal stabilizer as per AMM Task 55

- 11

- 00,4

- 1.

- If necessary, clean the area to be checked defined in figure 1 of the junction frame (a)

(see detail A and cross

- section B

- B) as per MTC Work Card 20.04.01.102.



### NOTE 2

For this inspection, the surface of the frame must be clean.

- Check that there are no cracks on the web of the frame (a) and in the radius between the web and the

flange on the tail cone side. Pay particular attention to the area around the 4 spars (b). (See Detail C)

. If in doubt, perform a dye

- penetrant inspection as per MTC Work Cards 20.02.09.101 and 20.02.09.601.

Then interpret the results as per paragraph 3.B.3.

3.B.2. Inspection, through the inside of the tail boom, of the tail boom / Fenestron junction frame (without removal

of the stabilizer)

As per Figure s 2 and 3 :



### NOTE 3

For this inspection, the surface of the frame must be clean.

- Using a borescope thro ugh the stabilizer opening , check that there are no cracks on the web of the frame

(a) and in the radius between the web and the flange on the tail cone side. Pay particular attention to the

area around the 4 spars (b). (See Detail C)

. If in doubt, perfor m a dye

- penetrant inspection as per MTC Work Cards 20.02.09.101 and 20.02.09.601.

Then interpret the results as per paragraph 3.B.3.

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a) If there are no cracks :

. Leave as is.

. If previously removed, install the hori zontal stabilizer as per AMM Task 55

- 11

- 00,4

- 1.

. Resume flights.

b) If any cracks are found :

. Contact Airbus Helicopters to define the conditions for returning the helicopter to conformity

(refer to NOTE 1).



### 3.C. IDENTIFICATION

Identification of thi s document :

Record first compliance with this ALERT SERVICE BULLETIN in the helicopter documents.



### 3.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Not applicable.

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This document is available on the internet: www.airbushelicopters.com/techpub F igure 1

Check of the frame with removal of the stabilizer 

# A

a Cross

- section

B

- B

Fenestron



### DETAIL A

– View looking aft

a b

b b 

# C

DETAIL C Tail boom

B B

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This document is available on the internet: www.airbushelicopters.com/techpub Figure 2

Check of the frame without removal of the stabilizer

Borescope insertion 

## A

a Cross

- section

B

- B

F enestron



### DETAIL A

– View looking aft

a b

b b



# C DETAIL C Tail boom

B

B



### b

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This document is available on the internet: www.airbushelicopters.com/techpub Figure 3

Examples of cracks

Example of a

crack Example of a

crack