EASA AD No.: 2014-0076-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 1/2

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

EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2014-0076-E

Date: 25 March 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].

Design Approval Holder’s Name:

AIRBUS HELICOPTERS

Type/Model designation(s):

AS 350 and AS 355 helicopters

TCDS Number: EASA.R.008 and EASA.R.146

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Rear Structure Junction Frame Reinforcement Angles –

Inspection

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

Applicability: AS 350 B, BA, BB, B1, B2, B3 and D helicopters, and AS 355 E, F, F1, F2, N

and NP helicopters, all serial numbers,

- if incorporating modification (MOD) 07 3215, or 

- if equipped with at least one reinforcement angle, Part Number (P/N)

350A08.2493.21 or P/N 350A08.2493.23, following the repair carried out in 

accordance with MRM Work Card 53.10.22.772 or AMM Task 53-31-00, 8-5.

Reason: During the inspection of several AS 355 helicopters, cracks were found in the 

reinforcement angles of the rear structure / tail boom junction frame.

Subsequent investigation revealed that cracks were initiated on the non-visible 

surface of the angle (surface in contact with the frame).

This condition, if not detected and corrected, could lead to further crack 

propagation and subsequent loss of the tail boom, resulting in loss of the 

helicopter.

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

affected area and, depending on findings, replacement of affected parts.

Terminating corrective action is currently under investigation by Airbus 

Helicopters. This AD is considered as a temporary measure and further AD 

action may follow.

Effective Date: 27 March 2014
EASA AD No.: 2014-0076-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 2/2

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

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time as defined in Table 1 of this AD, and, 

thereafter, at intervals not to exceed 10 flight hours (FH), inspect the 

reinforcement angles in accordance with the instructions of paragraph 

3.B.1 of Airbus Helicopters Emergency Alert Service Bulletin (ASB) AS350 

05.00.70 or ASB AS355 05.00.62, as applicable to helicopter type.

Table 1 – Inspection Threshold

FH accumulated (on the effective 

date of this AD) since installation of 

MOD 07 3215, or since installation

of a reinforcement angle

Compliance Time

Less than 640 FH

Before exceeding 650 FH, but 

not before accumulating 640 

FH

640 FH or more

Within 10 FH after the 

effective date of this AD

(2) Within 165 FH after the initial inspection as required by paragraph (1) of 

this AD, and, thereafter, at intervals not to exceed 165 FH, inspect the 

reinforcement angles in accordance with the instructions of paragraph 

3.B.2 of Airbus Helicopters ASB AS350 05.00.70 or ASB AS355 05.00.62, 

as applicable to helicopter type.

(3) Accomplishment of the first inspection as required by paragraph (2) of this 

AD constitutes terminating action for the repetitive inspections required by 

paragraph (1) of this AD.

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

cracks are detected, before next flight, contact Airbus Helicopters for 

approved instructions for corrective action(s) and accomplish those 

instructions accordingly.

Ref. Publications: Airbus Helicopters Emergency ASB AS350 05.00.70 dated 24 March 2014.

Airbus Helicopters Emergency ASB AS355 05.00.62 dated 24 March 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 – 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@eurocopter.com.