EASA AD No.: 2015-0033-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 1/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2015-0033-E

Date: 24 February 2015

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 EU 1321/2014 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

[EU 1321/2014 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):

EC 130 helicopters

TCDS Number: EASA.R.008

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2014-0145R1 dated 13 June 2014.

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

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

Applicability: EC 130 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 EC 130 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 (AH) issued EC130 

Emergency Alert Service Bulletin (ASB) No. 05A017 to provide instructions for 

detailed visual checks on the inside of the tail boom.

Prompted by these findings, EASA issued Emergency AD 2014-0145-E (later 

revised) to require repetitive inspections of the affected area and, depending on 

findings, accomplishment of applicable corrective actions.

Since EASA AD 2014-0145R1 was published, it was determined that, apart from 

the existing flight hours (FH) inspection interval, an inspection interval defined in 

sling cycles is necessary. In addition, AH issued Service Bulletin (SB)

EC130-53-029 which provides a modification that will allow the inspections to be 

accomplished from outside the tailboom. AH have revised EC130 ASB No. 

05A017 (Revision 2) accordingly, to define this alternative method.
EASA AD No.: 2015-0033-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 2/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

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

2014-0145R1, which is superseded, and allows, for post-MOD 350A087421 and 

post-SB EC130-53-029 helicopters, an alternative visual (external) inspection

method, although with reduced inspection intervals, in combination with the 

internal inspections at extended intervals. This AD also introduces an additional 

sling cycle interval, the definition of which is to be found in AH EC130 ASB 

05A017 Revision 2. This AD also specifies that certain tasks can be accomplished 

by the pilot.

Effective Date: 26 February 2015

Required Action(s) 

Compliance

Time(s) and 

required personnel 

qualifications:

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 AH EC130 Emergency ASB 05A017.

Table 1 – Inspection Threshold

FH accumulated by the junction 

frame, on 09 June 2014 [the 

effective date of EASA AD 2014-

0145-E], since installation

Compliance Time

Less than 690 FH Before exceeding 700 FH

690 FH or more Within 10 FH after 09 June 2014 

[the effective date of EASA AD

2014-0145-E]

(2) Within 25 FH or 390 sling cycles (see Note 1), whichever occurs first after the 

inspection as required by paragraph (1) of this AD, and, thereafter, at 

intervals not to exceed 25 FH or 390 sling cycles, whichever occurs first, 

accomplish an inspection in accordance with the instructions of paragraph 

3.B.1 or 3.B.2 of AH EC130 Emergency ASB 05A017.

Note 1: The definition of sling cycles can be found in paragraph 1.E.2 (b) of AH 

EC130 ASB No. 05A017 Revision 2.

(3) For helicopters modified in production by AH MOD. 350A087421, or in 

service in accordance with the instructions of AH SB EC130-53-029, as an 

alternative to the inspections as required by paragraphs (1) and (2) of this 

AD, it is acceptable to accomplish the inspections as specified in paragraphs 

(3.1) and (3.2) of this AD.

(3.1) Within 10 FH or 250 sling cycles, whichever occurs first after 

modification of the helicopter, and, thereafter, at intervals not 

exceeding 10 FH or 250 sling cycles, whichever occurs first, 

accomplish a visual inspection (see Note 2) of the tailboom from 

outside in accordance with the instructions of paragraph 3.B.3 of AH 

Emergency ASB EC130 05A017 Revision 2.

(3.2) Within 660 FH after modification of the helicopter, and, thereafter, at 

intervals not to exceed 660 FH, 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 or 

3.B.2 of AH EC130 Emergency ASB 05A017 Revision 2.

Note 2: The visual inspection specified in paragraph 3.B.3 (a) of AH Emergency 

ASB EC130 No. 05A017 Revision 2 may be carried out by the pilot. All other 

instructions as specified in paragraph 3.B of AH Emergency ASB EC130 No. 

05A017 Revision 2 must be accomplished by a person appropriately trained and 

certified for those actions.
EASA AD No.: 2015-0033-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 3/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

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

crack is detected, before next flight, contact AH for approved repair 

instructions and accomplish those instructions accordingly.

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

constitute terminating action for the repetitive inspections as required by this 

AD.

(6) Replacement of a junction frame on a helicopter is allowed, provided that,

before exceeding 700 FH after installation of the replacement junction frame, 

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

and the flange on the tail cone side is accomplished in accordance with the 

instructions of paragraph 3.B.1 of Airbus Helicopters EC130 Emergency ASB 

No. 05A017 and, thereafter, the helicopter is inspected as required by 

paragraph (2) or paragraph (3) of this AD.

Ref. Publications: Airbus Helicopters EC130 Emergency ASB No. 05A017 original issue,

dated 06 June 2014, or Revision 1 dated 13 June 2014, or Revision 2

dated 20 February 2015.

Airbus Helicopters SB EC130-53-029 dated 20 February 2015.

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, Certification 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 (EBSESB) – Aéroport de Marseille Provence, 13725 

Marignane Cedex, France; telephone +33 (4) 12 85 97 97; facsimile +33 (4) 

85 99 66; E-mail: Directive.technical-support@airbus.com.