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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2014-0114-E

Date: 08 May 2014

Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance 

with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States 

and of the European third countries that participate in the activities of EASA under Article 66 

of that Regulation.

This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Type Approval Holder’s Name :

AIRBUS HELICOPTERS

Type/Model designation(s) :

EC130 B4 helicopters

TCDS Number : EASA R.008

Foreign AD: Not applicable.

Supersedure : This AD supersedes EASA AD 2011-0116 dated 06 July 2011.

ATA 53 Fuselage – Tail Boom / Fenestron Junction Frame – Inspection /

Repair

Manufacturer(s): Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)

Applicability: EC 130 B4 helicopters, all serial numbers, except:

- those that have embodied modification (mod) 073880 (Reinforcement of the 

tail boom / Fenestron junction),

- those that have embodied mod 074609 (Reinforcement of the tail 

boom/Fenestron junction).

- all those which have been repaired in accordance with Repair Design 

Approval Sheet (RDAS) No. 350 53 522 07 or 350 53 521 10, or

350 53 524 10, or 350 53 525 10, or 350 53 526 10, or 350 53 511 11, or

350 53 512 11, or 350 53 523 11, or 350 53 504 12, or AE11-0205, or

AE11-0380.

NOTE: Tail boom assembly serial number TB 7377 is not affected by this AD.

Reason: Several reports have been received of finding cracks in the tail boom /

Fenestron junction frame. Prompted by these reports, Eurocopter published 

Information Notice No. 2167-I-53. Since publication of this document, new 

cases of cracks in the tail boom / Fenestron junction frame have been 

reported.

The examination of the parts showed that the cracks were longer than in the 

previous cases. The cracks start to develop in the plane of the rivet head 

countersink on the Right Hand (RH) side of the Fenestron and spread to the 

web of the frame.

This condition, if not detected and corrected, could lead to structural failure,

possibly resulting in Fenestron detachment and consequent loss of control of 
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the helicopter.

To address this unsafe condition, EASA issued AD 2011-0116 to require 

repetitive inspections of the affected area and, depending on findings, 

accomplishment of corrective actions.

Following further investigation, Airbus Helicopters developed mod 074609, 

the purpose of which is to limit the risk of cracks appearing on the tail boom / 

Fenestron junction frame. 

Airbus Helicopters issued Revision 1 of ASB 53A019 to extend the inspection 

to the entire circumference of the frame and provided instructions to embody 

mod 074609 in service through Service Bulletin (SB) 53-024.

For the reasons described above, this AD retains the requirements of EASA 

AD 2011-0116, which is superseded, and requires embodiment of the final fix 

solution.

Effective Date: 12 May 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 10 flight hours (FH), or within 40 FH after the last inspection in 

accordance with Airbus Helicopters EC130B4 Emergency Alert Service 

Bulletin (ASB) No. 53A019 at original issue, whichever occurs later 

after the effective date of this AD, and, thereafter, at intervals not 

exceeding 40 FH, inspect the whole circumference of the tail boom / 

Fenestron junction frame (the frame) for cracks, in accordance with the 

instructions of paragraph 3.B.1 and paragraph 3.B.2 of Airbus 

Helicopters EC130B4 Emergency ASB No. 53A019 Revision 1.

(2) If, during any inspection as required by paragraph (1) of this AD, a 

crack is detected, depending on the extent of the crack(s), accomplish 

the action as specified in Table 1 of this AD, as applicable.

Table 1 – Crack detected

Extent of crack(s) Action

(a) Crack on the inside 

crossing the web

Before next flight, contact Airbus 

Helicopters for approved instructions 

and accomplish those instructions 

accordingly

(b) Crack on the inside 

crossing part of the 

frame web

Contact Airbus Helicopters. Up to 10 FH 

are allowed to ferry the helicopter to a 

location where the corrective action can 

be accomplished in accordance with 

Airbus Helicopters instructions

(c) Outside of frame only -

no crack in the frame 

web

Before next flight, strip the outside of 

the frame in accordance with the 

instructions of paragraph 3.B.3 and 

inspect the frame in accordance with 

the instructions of paragraph 3.B.4 of 

EC130B4 ASB No. 53A019 Revision 1

(3) If, during any inspection as required by paragraph (1) of this AD, no 

crack is found, within 110 FH or 6 months, whichever occurs first after 

the effective date of this AD, strip the frame in accordance with the 

instructions of paragraph 3.B.3 and inspect the frame in accordance 

with the instructions of paragraph 3.B.4, and, thereafter, at intervals not 

exceeding 100 FH inspect the frame in accordance with the instructions

of paragraph 3.B.4 of EC130B4 ASB No. 53A019 Revision 1. After the 

initial inspection as required by paragraph (3) of this AD, the repetitive 
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inspections of paragraph (1) of this AD are no longer required.

(4) If, during any inspection as required by paragraph (2) – Table 1 or by 

paragraph (3) of this AD, or during any other maintenance action, a 

crack is detected that reaches the radius of the frame, inspect the 

inside of the frame in accordance with the instructions of paragraph

3.B.1 of EC130B4 ASB No. 53A019 Revision 1. Thereafter, repeat the 

same inspection at intervals not exceeding 40 FH.

(5) Depending on findings during any inspection as required by paragraph 

(4) of this AD, accomplish the corrective action as specified in Table 2

of this AD, as applicable.

Table 2 – Crack detected

Extent of crack(s) Action

(a) Entirely crossing the frame 

web 

Before next flight, contact Airbus 

Helicopters for approved instructions 

and accomplish those instructions 

accordingly

(b) Crossing part of the frame 

web

Up to 10 FH are allowed to ferry the 

helicopter to a location where the 

corrective action can be 

accomplished; then contact Airbus 

Helicopters for approved instructions 

and accomplish those instructions 

accordingly

(c) Outside of frame only - no 

crack in the frame web

Up to 85 FH are allowed after the 

previous maintenance action when 

the frame was inspected (i.e. the one 

preceding the maintenance action 

during which a crack reaching the 

radius of the frame was detected).

Then, up to 10 FH are allowed to 

ferry the helicopter to a location 

where the corrective action can be 

accomplished; then contact Airbus 

Helicopters for approved instructions 

and accomplish those instructions 

accordingly.

If the crack that reaches the radius of 

the frame was detected during the 

initial inspection as required by

paragraph (1) of this AD, accomplish 

the actions required by line (b) of this 

Table 2

(6) If, during any inspection as required by paragraph (2) – Table 1 or by 

paragraph (3) of this AD, or during any other maintenance action, a 

crack is detected that does not reach the radius of the frame, inspect 

the frame in accordance with the instructions of paragraph 3.B.1 and 

3.B.4 of EC130B4 ASB No. 53A019 Revision 1. Thereafter, repeat the 

same inspection at intervals not exceeding 40 FH.

(7) Depending on findings during any inspection as required by paragraph 

(6) of this AD, accomplish the corrective action as specified in Table 3

of this AD, as applicable.
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Table 3 – Crack detected

Extent of crack(s) Action

(a) Entirely crossing the frame 

web 

.Before next flight, contact Airbus 

Helicopters for approved instructions 

and accomplish those instructions 

accordingly

(b) Crossing part of the frame 

web

Up to 10 FH are allowed to ferry the 

helicopter to a location where the 

corrective action can be 

accomplished; then contact Airbus 

Helicopters for approved instructions 

and accomplish those instructions 

accordingly

(c) Outside of frame only - no 

crack in the frame web

Flights are allowed within 12 months 

after detecting a crack that does not 

reach the radius of the frame.

Then, up to 10 FH are allowed to 

ferry the helicopter to a location 

where the corrective action can be 

accomplished; then contact Airbus 

Helicopters for approved instructions 

and accomplish those instructions 

accordingly

(8) From the effective date of this AD, do not install a tail boom assembly 

on a helicopter unless it incorporates modification 073880 or 074609.

(9) Not later than 31 December 2017, modify the helicopter in accordance 

with the instructions of Airbus Helicopters EC130B4 SB No. 53-024.

(10) Modification of a helicopter as required by paragraph (9) of this AD 

constitutes terminating action for all repetitive inspections required by 

this AD for that helicopter.

Ref. Publications: Eurocopter EC130B4 SB 53-024 dated 08 January 2013, or Revision 1 dated 

09 December 2013, or Airbus Helicopters EC130B4 SB 53-024 Revision 2 

dated 15 April 2014.

Airbus Helicopters EC130B4 Emergency ASB 53A019 Revision 1 dated 15 

April 2014.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. The results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in 

this AD, please contact: Airbus Helicopters Technical Support 

Department of the Customer Service,

Telephone +33 (0)4.42.85.97.16, Fax + 33 (0)4.42.85.99.66,

E-mail: airframe.technical-support@eurocopter.com.