EASB

Revision 0 2014-06-06 Page 1/10

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 05A017 B4, T2

Revision No. Date of issue

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
EASB

Revision 0 2014-06-06 Page 2/10

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

1. PLANNING INFORMATION

1.A. EFFECTIVITY

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 (Detail 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 conditions 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.
EASB

Revision 0 2014-06-06 Page 3/10

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

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:

Comply 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 intervals 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 BULLETIN Revision 0 was 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. 
EASB

Revision 0 2014-06-06 Page 4/10

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

1.G. MANPOWER

For compliance with this ALERT SERVICE BULLETIN, Airbus Helicopters 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 MIXABILITY OF PARTS

Not applicable.
EASB

Revision 0 2014-06-06 Page 5/10

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

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

Products 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.interturbine.com

Telephone: +49.41.91.809.300

AOG: +49.41.91.809.444

2.D. MATERIAL TO BE RETURNED

Not applicable.
EASB

Revision 0 2014-06-06 Page 6/10

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

3. ACCOMPLISHMENT INSTRUCTIONS

3.A. GENERAL

NOTE 1 

Contact details of the Airbus Helicopters Customer Service Technical Support 

Department:

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 boom, of the tail boom / Fenestron junction frame (with removal of 

the stabilizer)

As per Figures 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 Figures 2 and 3:

NOTE 3

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

- Using a borescope through 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, 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.
EASB

Revision 0 2014-06-06 Page 7/10

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

3.B.3. Interpretation of the results

a) If there are no cracks: 

. Leave as is.

. If previously removed, install the horizontal 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 this document:

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

3.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Not applicable.
EASB

Revision 0 2014-06-06 Page 8/10

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

Figure 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
EASB

Revision 0 2014-06-06 Page 9/10

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

Fenestron

DETAIL A – View looking aft 

a

b

b

b

C

DETAIL C

Tail boom

B

B

b
EASB

Revision 0 2014-06-06 Page 10/10

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

Figure 3

Examples of cracks

Example of a 

crack

Example of a 

crack