EASA AD No.: 2015-0094

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0094

Date: 29 May 2015

Note: This 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):

AS 350, AS 355 and EC 130 helicopters

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

Foreign AD: Not applicable

Supersedure: None

ATA 63 Main Rotor Drive – Cross-Bar – 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, and 

EC130 B4 and T2 helicopters, 

all serial numbers.

Reason: Two occurrences were reported of finding cracks in the bi-directional suspension 

cross-bar (i.e. crossbeam) on AS350 B3 helicopters. The cracks were detected, 

during a maintenance check, at the attachment holes of the transmission deck 

attachment fittings. In both cases, the helicopters were equipped with a cargo 

hook and had completed missions with a significant number of torque cycles (TC), 

(see Note). Because of common design features, such cracks may potentially also 

occur on other AS350, AS355 and EC 130 helicopter models. Crack growth may 

lead to failure of one of the four yokes and significantly increased stress load on 

the remaining yokes.

This condition, if not detected and corrected, could lead to cracks developing in 

the remaining yokes and increased loading of the cross-bar, possibly resulting in 

cross-bar failure and consequent loss of the helicopter.

To address this potential unsafe condition, Airbus Helicopters (AH) issued four

Alert Service Bulletins (ASB) AS350-05.00.84, ASB AS355-05.00.73, ASB EC130-

05A021 and ASB EC130-05A022 to provide instructions for periodic inspections of 

the cross-bar on affected helicopters.

For the reason described above, this AD requires repetitive inspections of the bidirectional suspension cross-bar and, depending on findings, replacement of the 

cross-bar with a serviceable one.
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The instructions contained in these ASBs will be incorporated in the Airworthiness 

Limitation Section (ALS) of the respective rotorcraft as part of the next revision.

Effective Date: 12 June 2015

Required 

Action(s) and 

Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) During the next scheduled main gearbox removal after the effective date of 

this AD, and, thereafter, at intervals not to exceed the values specified in 

Table 1 of this AD, as applicable to helicopter model, inspect each

bi-directional suspension cross-bar Part Number (P/N) 350A38-1040-20 or 

P/N 350A38-1040-00, as applicable, in accordance with the instructions of

paragraph 3.B of AH ASB AS350-05.00.84, or ASB AS355-05.00.73, or ASB 

EC130-05A021, or ASB EC130-05A022, as applicable.

Table 1 – Inspection of Bi-Directional Suspension Cross-Bar

Helicopter Model(s)

Interval

(flight hours (FH) or TC, 

whichever occurs first)

AS 350 B, BA, BB, B1, B2, D 4 500 FH or 60 000 TC

AS 350 B3

AS 355 (all models) 3 300 FH or 60 000 TC

EC130 B4

EC130 T2 3 300 FH or 40 000 TC

Note: The definition of TC can be found in paragraph 1.E.2 of the applicable 

AH ASB.

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

detected, before next flight, replace the bi-directional suspension cross-bar 

with a serviceable one in accordance with paragraph 3.B of AH ASB 

AS350-05.00.84, or ASB AS355-05.00.73, or ASB EC130-05A021, or

ASB EC130-05A022, as applicable.

(3) Replacement of the bi-directional suspension cross-bar on a helicopter as 

required by paragraph (2) of this AD does not constitute terminating action for 

the repetitive inspections as required by paragraph (1) of this AD for that 

helicopter.

Ref. Publications: AH ASB AS350-05.00.84 original issue dated 21 May 2015.

AH ASB AS355-05.00.73 original issue dated 21 May 2015.

AH ASB EC130-05A021 original issue dated 21 May 2015.

AH ASB EC130-05A022 original issue dated 21 May 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 result 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.
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4. For any question concerning the technical content of the requirements in this 

AD, please contact:

Airbus Helicopters (ESBESB) – Aeroport de Marseille Provence, 

1375 Marignane Cedex, France

Telephone: +33 (4) 12 85 97 97; Fax: +33 (4) 85 99 66

E-mail: directive.technical-support@airbus.com