EASA AD No.: 2014-0216

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0216

Date: 24 September 2014

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 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):

SA 341 G and SA 342 J helicopters

TCDS Number: EASA.R.125

Foreign AD: Not applicable

Supersedure: None

ATA 65 Main Rotor – Main Rotor Hub Torsion Bars – Inspection 

Manufacturer(s): Aerospatiale

Applicability: SA 341 G and SA 342 J helicopters, all manufacturer serial numbers.

Reason: Several cases of cracks were found on the polyurethane (PU) coating of the 

main rotor hub (MRH) torsion bars P/N 704A33633274 installed on military

SA 341 helicopters. These parts can also be installed on civilian SA 341 and 

SA 342 helicopters. In addition, analysis of the cracked torsion bars has shown 

that small areas of superficial corrosion on the strands inside the bars can also 

develop during the manufacturing process. The cracking of the PU coating near 

these areas and the associated penetration of water can lead to further and 

deeper development of the corrosion.

This condition, if not detected and corrected, allows water to penetrate into the 

torsion bar, causing corrosion and failure of the metal strands inside the bar, 

which could lead to torsion bar failure, resulting in in-flight loss of a main rotor 

blade and consequent loss of control of the helicopter.

To address this unsafe condition, Airbus Helicopters issued Alert Service 

Bulletin (ASB) SA341/SA342-05.40, providing instructions for reducing the 

intervals of the existing repetitive inspection of the torsion bars, which are 

described in the applicable maintenance manual (document identified as MDE) 

and currently required through the existing instructions for continued 

airworthiness (document identified as PRE).

For the reasons described above, this AD requires reduced intervals for the 

repetitive inspection of the torsion bars compared to the existing intervals

indicated in the current PRE document.

Effective Date: 08 October 2014
EASA AD No.: 2014-0216

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Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Initially, within the compliance time specified in Table 1 or Table 2 of this 

AD, as applicable, and, thereafter, at intervals not to exceed the values as 

specified in Table 3 of this AD, as applicable, inspect the MRH torsion bars 

P/N 704A33633274 in accordance with the instructions of Airbus 

Helicopters MDE Work Card n° 65.12.607.

Table 1 – Initial Inspection of Torsion Bars installed less than 5 years

Flight Hours (FH) accumulated by 

the helicopter (on the effective date 

of this AD) since last inspection of 

the torsion bar

Compliance Time 

less than 320 FH Before exceeding 420 FH or 

24 months, whichever occurs 

first since last inspection

320 FH or more Within 100 FH, or within the 

scheduled inspection time limit 

for the torsion bars as 

indicated in the current PRE, 

whichever occurs first after the 

effective date of this AD.

Table 2 – Initial Inspection of Torsion Bars installed 5 years or more

Service life (FH or calendar time) 

accumulated by the helicopter on 

the effective date of this AD since 

last inspection of the torsion bar

Compliance Time 

less than 320 FH, and last inspection 

performed less than 6 months before 

the effective date of this AD

Before exceeding 420 FH or 

12 months, whichever occurs 

first since last inspection

320 FH or more, or last inspection 

performed 6 months or more before 

the effective date of this AD

Within 100 FH, or within 6 

months, or within the 

scheduled inspection time limit 

for the torsion bars as 

indicated in the current PRE, 

whichever occurs first after the 

effective date of this AD.

Table 3 – Repetitive Inspections of Torsion Bars

Duration of installation of the 

torsion bar on a helicopter

Inspection Intervals

(not to exceed)

less than 6 years 420 FH or 24 months, whichever 

occurs first, until reaching the limit of 

6 years after first installation on a 

helicopter

6 years or more 420 FH or 12 months, whichever 

occurs first, without exceeding the 

existing service life limits indicated in 

the airworthiness limit section of the 

current PRE.

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

the PU coating of a torsion bar is found which matches or exceeds the 

criteria defined in MDE Work Card n° 65.12.607, before next flight, replace 
EASA AD No.: 2014-0216

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the affected torsion bar with a serviceable one in accordance with the 

instructions of Airbus Helicopters ASB SA341/SA342-05.40.

(3) Replacement of a torsion 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.

(4) From the effective date of this AD, installation on a helicopter of MRH 

torsion bars P/N 704A33633274 is allowed, provided that, following

installation, the helicopter is inspected and, depending on findings,

corrected, as required by this AD.

Ref. Publications: Airbus Helicopters ASB SA341/SA342-05.40 original issue dated 28 April 2014.

Airbus Helicopters MDE Work Card n° 65.12.607.

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. This AD was posted on 20 August 2014 as PAD 14-132 for consultation 

until 17 September 2014. No comments were received during the 

consultation period.

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 (STDI) – Aéroport de Marseille 

Provence 13725 Marignane Cedex, France,

Telephone +33 (4) 42 85 97 97; Fax +33 (4) 42 85 99 66,

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