EASA AD No.: 2014-0145-E

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2014-0145-E

Date: 06 June 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 21A.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].

Design Approval Holder’s Name:

AIRBUS HELICOPTERS

Type/Model designation(s):

EC130 helicopters

TCDS Number: EASA.R.008

Foreign AD: Not applicable

Supersedure: None

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

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

Applicability: EC130 B4 and EC 130 T2 helicopters, all serial numbers.

Reason: Two events of crack propagation through the junction frame of the tail boom / 

Fenestron were reported following non-scheduled inspections of EC130 B4 

helicopters. The investigation revealed that the cracks initiated in the lower right 

hand (RH) part of the frame between the web and the flange where the lower 

spar of the tail boom is joined. Although the cracks were of significant length, no 

deterioration was visible from the outside of the helicopter. 

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

possibly resulting in Fenestron detachment and consequent loss of control of 

the helicopter.

To address this unsafe condition, Airbus Helicopters issued Emergency Alert 

Service Bulletin (ASB) No. 05A017 to provide instructions for detailed visual 

checks on the inside of the tail boom.

For the reasons described above, this AD requires repetitive inspections of the 

affected area and, depending on findings, accomplishment of applicable 

corrective actions.

Effective Date: 09 June 2014
EASA AD No.: 2014-0145-E

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the threshold as specified in Table 1 of this AD, as applicable, 

accomplish a detailed visual inspection of the frame web in the radius 

between the web and the flange on the tail cone side in accordance with 

the instructions of paragraph 3.B.1 of Airbus Helicopters EC130 

Emergency ASB No. 05A017.

(2) Within 25 flight hours (FH) after the inspection as required by paragraph 

(1) of this AD, and, thereafter, at intervals not to exceed 25 FH, accomplish

the inspection, in accordance with the instructions of paragraph 3.B.2 of 

Airbus Helicopters EC130 Emergency ASB No. 05A017. 

Table 1 – Inspection Threshold

FH accumulated, on the effective 

date of this AD, since first flight

Compliance Time

Less than 690 FH Before exceeding 700 FH.

690 FH or more Within 10 FH or 7 days, 

whichever occurs first after the 

effective date of this AD

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

crack is detected, before next flight, contact Airbus Helicopters for 

approved repair instructions and accomplish those instructions accordingly.

(4) Repair of a helicopter as required by paragraph (3) of this AD does not 

constitute terminating action for the repetitive inspections as required by 

this AD.

Ref. Publications: Airbus Helicopter EC130 Emergency ASB 05A017 Rev. 0 dated 06 June 2014.

The use of later approved revisions of this document 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, Customer Services, Technical Support Department,

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

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