EASA AD No.: 2014-0068

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0068

Date: 18 March 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

Type/Model designation(s):

A330 and A340-200/-300 aeroplanes

TCDS Number: EASA.A.004 and EASA.A.015

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2013-0219 dated 17 September 2013.

ATA 53 Fuselage – Trimmable Horizontal Stabilizer Support Struts –

Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243,

A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323,

A330-341, A330-342 and A330-343 aeroplanes, all manufacturer serial

Numbers (MSN), and

Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313

aeroplanes, all MSN.

Reason: During scheduled maintenance on A330 aeroplanes, several Trimmable 

Horizontal Stabilizer (THS) support struts at frame (FR) 91 were found cracked 

at strut body ends.

The THS is supported and articulated at FR 91 by four struts to fix the hinges 

(Y-bolts) and keep the structural integrity in lateral direction. 

Analysis revealed that cracks can reduce ability of the support struts to carry 

specified tension loads. 

This condition, if not detected and corrected, could lead to the loss of all four 

THS support struts at FR91, which would make the remaining structure unable 

to carry limit loads, resulting in the loss of Horizontal Tail Plane.

A340-500/600 aeroplanes are not affected by this AD as different material is 

used on THS support struts.

To address this potentially unsafe condition, EASA issued AD 2013-0076 to 

require repetitive special detailed inspections of all 8 strut ends of the THS 

support located at FR91 in the tail cone and, depending on findings, 
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replacement of THS support struts. That AD also required, for aeroplanes on 

which Airbus Modification 203493 had not been embodied in production, or

Airbus Service Bulletin (SB) A330-53-3204 or SB A340-53-4199, as applicable, 

has not been embodied in service, the installation of a clamping device on each 

support strut end to stop growth of possible cracks (crack stopper function) in 

order to secure integrity of the struts.

Since issuance of EASA AD 2013-0076, it has been discovered that several 

aeroplanes are fitted with another strut configuration (SARMA Strut) than the 

TAC (Technical Airborne Components Industries) strut, which caused the other 

strut not to be considered. Consequently, Airbus revised Airbus SB 

A330-53-3206 and SB A340-53-4208, accordingly in order to add a one-time

inspection for SARMA struts and in case of finding to replace it with a TAC strut 

and thereafter to accomplish repetitive inspections and EASA issued AD

2013-0219, which is superseded, and required accomplishment of the 

instructions as specified in the latest revision of each SB, as applicable. 

Since issuance of EASA AD 2013-0219, based on the reporting received from 

operators, it has been determined that repetitive inspections are also to be 

accomplished for aeroplanes equipped with SARMA strut. Airbus introduced 

that inspection in the applicable SB at revision 3.

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

2013-0219, which is superseded, and requires accomplishment of repetitive 

inspective inspection for aeroplanes equipped with SARMA strut.

This AD is considered as an interim action, pending the development of a 

terminating action.

Effective Date: 01 April 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

For the purpose of this AD, SARMA strut is a strut on which the diameter 

of the strut end is lower than 43 mm. All other struts are TAC strut.

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

and, thereafter, at intervals not to exceed 42 months or 20 000 flight hours 

(FH), whichever occurs first, accomplish a High Frequency Eddy Current 

(HFEC) inspection of all TAC strut ends of the THS support located at 

FR91 in the tail cone in accordance with the instructions of Airbus SB 

A330-53-3206 Revision 03, or SB A340-53-4208 Revision 03, as 

applicable to aeroplane type.

Table 1 - Initial inspection for TAC strut ends

A340 MSN A330 MSN Compliance Time

002 through 

210 inclusive

012 through 209 

inclusive 

within 6 months after 03 April 

2013 [the effective date of AD 

2013-0076]

212 through 

447 inclusive

211 through 422 

inclusive

within 24 months after 03 April 

2013 [the effective date of AD 

2013-0076]

450 through 

955 inclusive

423 and 

subsequent

within 36 months after 03 April 

2013 [the effective date of AD 

2013-0076], or since aeroplane 

first flight, whichever occurs later 

For aeroplanes on which Airbus modification 203493 has been embodied 

in production, or Airbus SB A330-53-3204 or SB A340-53-4199, as 

applicable, has been embodied in service, remove the clamp from each 

strut end before accomplishing this inspection.
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(2) Before next flight after any inspection as required by paragraph (1) of this 

AD, accomplish the corrective action(s), depending on the inspection 

results, as specified in Table 2 of this AD in accordance with the 

instructions of Airbus SB A330-53-3206 Revision 02 or SB A340-53-4208 

Revision 02, as applicable to aeroplane type.

Table 2 – Actions after a TAC strut end inspection

Inspection results Actions

No crack, or cracks within 

acceptable limits

Install or re-install clamps

Cracks outside acceptable 

limits

Replace strut(s) with TAC 

strut(s) and install clamps

(3) Within the compliance time specified in Table 3 of this AD, as applicable,

accomplish a one-time HFEC inspection of all SARMA strut ends of the 

THS support located at FR91 in the tail cone in accordance with the 

instructions of Airbus SB A330-53-3206 Revision 03, or SB A340-53-4208 

Revision 03, as applicable to aeroplane type.

Table 3 - Inspection for SARMA strut ends

A340 MSN A330 MSN Compliance Time

002 through 

210 inclusive

012 through 209 

inclusive 

within 6 months after 03 April 

2013

212 through 

447 inclusive

211 through 422 

inclusive

within 24 months after 03 April 

2013

450 through 

955 inclusive

423 and 

subsequent

within 36 months after 03 April 

2013 or since aeroplane first 

flight, whichever occurs later 

(4) Within 12 months after the initial inspection, as required by paragraph (3) 

of this AD, or within 3 months after the effective date of this AD, whichever 

occurs later, and thereafter, at intervals not to exceed 12 months, 

accomplish a HFEC inspection of all SARMA strut ends of the THS 

support located at FR91 in the tail cone in accordance with the instructions 

of Airbus SB A330-53-3206 Revision 03, or SB A340-53-4208 Revision 03, 

as applicable to aeroplane type.

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

crack on at least one strut end is detected, before next flight, replace each 

cracked strut with a TAC strut and install clamps in accordance with the 

instructions of Airbus SB A330-53-3206 Revision 03, or SB A340-53-4208 

Revision 03, as applicable to aeroplane type.

(6) Replacement of THS struts on an aeroplane, as required by paragraph (2)

or (5) of this AD, as applicable, does not constitute terminating action for 

the repetitive inspections as required by paragraph (1) or (4) of this AD for 

that aeroplane.

(7) Inspections and corrective actions, accomplished before the effective date 

of this AD, in accordance with the instructions of Airbus SB A330-53-3206 

at original issue or Revision 01 or Revision 02, or SB A340-53-4208 at 

original issue or Revision 01 or Revision 02, as applicable to aeroplane 

type, are acceptable to comply with the initial requirements of this AD. After 

the effective date of this AD, the repetitive inspections and applicable 

corrective actions must be accomplished in accordance with the 

instructions of Airbus SB A330-53-3206 Revision 03 or SB A340-53-4208 

Revision 03, as applicable to aeroplane type.
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Ref. Publications: Airbus SB A330-53-3204 original issue dated 07 February 2013, or Revision 01 

dated 13 June 2013.

Airbus SB A330-53-3206 original issue dated 07 February 2013, or Revision 01

dated 10 June 2013, or Revision 02 dated 08 August 2013, or Revision 03 

dated 28 February 2014.

Airbus SB A340-53-4199 original issue dated 07 February 2013, or Revision 01 

dated 13 June 2013.

Airbus SB A340-53-4208 original issue dated 07 February 2013, or Revision 01

dated 10 June 2013, or Revision 02 dated 08 August 2013, or Revision 03 

dated 28 February 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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

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 – Airworthiness Office – EIAL;

E-mail: airworthiness.A330-A340@airbus.com.