Nachrichten für Luftfahrer 2018 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2018-0233R1
Appendix 1
Table 1 - Initial Inspection
FH and FC Accumulated on 03
January 2014 [the effective
Model and
date of EASA AD 2013-0310] Compliance Time
Configuration
since first flight of the
aeroplane
Before exceeding 38 200 FC or 76 400 FH,
A320 and A319 PAX, 36 200 FC or 72 400 FH, or less whichever occurs first since first flight of
pre-mod 160001 the aeroplane
and pre-SB More than 36 200 FC or Within 2 000 FC or 4 000 FH whichever
A320-57-1193 72 400 FH, but not more than occurs first after 03 January 2014 [the
(mod 160080) 45 000 FC effective date of AD 2013-0310]
Within 1 000 FC or 2 000 FH, whichever
A321 pre-mod 160021 More than 45 000 FC occurs first after 03 January 2014 [the
effective date of AD 2013-0310]
Table 2 - Initial Inspection
FH and FC Accumulated
on 09 November 2018 [the
Model and
effective date of the original Compliance Time (see Note 1 of this AD)
Configuration
issue of this AD] since first
flight of the aeroplane
Before exceeding 35 400 FC or 70 900 FH,
33 400 FC or 66 900 FH, or less whichever occurs first since first flight of
the aeroplane (see Note 2 of this AD)
Within 2 000 FC or 4 000 FH, whichever
More than 33 400 FC or
A320 and A319 PAX, occurs first since 09 November 2018 [the
66 900 FH, but no more than
post-mod 160001 or effective date of the original issue of this
40 000 FC
post-SB A320-57-1193 AD] (see Note 2 of this AD)
(mod 160080) Within 1 000 FC or 2 000 FH, whichever
More than 40 000 FC but no occurs first since 09 November 2018 [the
A321 post-mod 160021 more than 43 000 FC effective date of the original issue of this
AD] (see Note 2 of this AD)
Within 30 days after 09 November 2018
More than 43 000 FC [the effective date of the original issue of
this AD] (see Note 2 of this AD)
A319 CJ, Before exceeding 19 800 FC or 85 300 FH,
post-mod 160001 or whichever occurs first since first flight of
Not applicable
post-SB A320-57-1193 the aeroplane
(mod 160080)
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Note 1: For A320 and A319 in post-SB A320-57-1193 configuration, refer to Airworthiness
Limitations Section (ALS) Part 2 variation 3.6 or ALS Part 2 revision 4, or later further ALS Part 2
revision, for determination of the threshold when sharklet is installed.
Note 2: For A320 and A319 PAX, post-SB A320-57-1193 (mod 160080): Without exceeding the time
at which inspection is required through the threshold or compliance time for A320 and A319 PAX
aeroplanes in pre-SB A320-57-1193 (pre mod 160080) configuration.
Table 3 – Repetitive Inspections
Model and Configuration Interval (FC or FH, whichever occurs first)
A320, A319 PAX and A321 5 000 FC or 10 000 FH
A319 CJ, post mod 160001 or
post-SB A320-57-1193 (mod 2 900 FC or 12 800 FH
160080)
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2014-177R2 38144 Braunschweig
EASA AD 2018-0249 vom 16.11.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 27.11.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS S.A.S.
Hersteller: Airbus (vormals Airbus Industrie)
Muster: A330, A340
Baureihen: 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, A330-343,
A340-211, A340-212, A340-213, A340-311, A340-312 und A340-313
Werknummern: Alle
Ausgenommen sind Flugzeuge, an denen die Airbus Repair Instruction (RI)
R57115092 beidseitig rechts und links durchgeführt worden ist.
Gerätenummer: 2849, 2850, EASA.A.004, EASA.A.015
Revisionsstand:
Diese LTA ersetzt D-2014-177R1 vom 12.05.2017
Airworthiness Directive der ausländischen Behörde:
EASA AD 2018-0249 vom 16.11.2018
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls Airworthiness
Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2014-177R2 geführt.
Betrifft:
(ATA 57) Wings - Centre Wing Box Fastener Holes at Frame 40 Vertical Web - Inspection / Modification
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
fen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2018-0249 vom 16.11.2018 herausgegeben oder per Entscheidung Nr. 02/2003 übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsanweisun-
gen direkt in der Bundesrepublik Deutschland gültig und bedürfen keiner Umsetzung durch das Luftfahrt-
Bundesamt.
Mit Hilfe dieser Übersichtsseite veröffentlicht das Luftfahrt-Bundesamt ebenfalls die über § 14 Abs. 2 direkt
gültigen Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und im Internet unter
www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt keinem Verwaltungsver-
fahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2014-177R2 Seite 1 von 1 538/2018
EASA AD No.: 2018-0249
Airworthiness Directive
AD No.: 2018-0249
Issued: 16 November 2018
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EU) 2018/1139 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 129 of that Regulation.
This AD is issued in accordance with Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (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 [Regulation (EU) 1321/2014 Annex I,
Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EU) 2018/1139, Article 71 exemption].
Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS A330 and A340 aeroplanes
Effective Date: 30 November 2018
TCDS Numbers: EASA.A.004, EASA.A.015
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2017-0069 dated 25 April 2017.
ATA 57 – Wings – Centre Wing Box Fastener Holes at Frame 40 Vertical Web –
Inspection / Modification
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,
except those on which Airbus Repair Instruction (RI) R57115092 has been embodied in service on
both Right Hand (RH) and Left Hand (LH) sides.
Definitions:
For the purpose of this AD, the following definition applies:
The applicable Inspection SB: Airbus Service Bulletin (SB) A330-57-3114 Revision 01 (centre wing
box (CWB) area to be inspected: below – see references in Table 1 of this AD), SB A330-57-3115
Revision 02 (above) and SB A330-57-3116 Revision 02 (below); or SB A340-57-4123 original issue
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(below), SB A340-57-4124 Revision 03 (above) and SB A340-57-4125 Revision 02 (below), as
applicable.
The applicable Modification SB: Airbus SB A330-57-3129 Revision 01 and SB A340-57-4136
Revision 01, as applicable.
The applicable Optional Modification SB: Airbus SB A330-57-3130 (at any revision), SB A330-57-
3131 (at any revision) and SB A330-57-3132 (at any revision), as applicable; or SB A340-57-4137 (at
any revision), SB A340-57-4138 and SB A340-57-4139 (at any revision), as applicable.
Reason:
During accomplishment of A330 Airworthiness Limitation Item (ALI) task 57-11-04 on the rear fitting
of the Frame (FR) 40 between stringers (STR) 38 and STR39 on both left-hand (LH) and right-hand
(RH) sides of the fuselage, cracks were found on an adjacent hole. After reaming at second oversize
of the subject hole, the crack was still present. As a result of a sampling inspection program,
additional crack findings were reported on this adjacent hole on other A330 and A340 aeroplanes.
This condition, if not detected and corrected, could affect the structural integrity of the centre
fuselage of the aeroplane.
Prompted by these findings, Airbus issued the applicable Inspection SB (at the time, all at original
issue) to provide inspection instructions and, consequently, EASA issued AD 2014-0149 to require
removal of the fasteners and repetitive special detailed inspections (SDI), including rototests, of
fastener holes at FR40 vertical web above or below CWB lower panel reference on both LH and RH
sides of the fuselage, and, depending on findings, accomplishment of the applicable corrective
actions. That AD did not apply to aeroplanes on which Airbus modification (mod) 55792 or mod
55306 had been embodied in production.
After that AD was issued, Airbus published SB A330-57-3115 Revision 01 and SB A340-57-4124
Revision 02, which introduced revised thresholds and intervals for the repetitive inspections of the
inside CWB (above bottom skin). In addition, for certain aeroplanes, Airbus developed mod 206051,
introducing reinforcement of the structural integrity of the inside CWB (above bottom skin) area,
and published the applicable Modification SB (both original issue), which avoided the need for
repetitive inspections for the inside of the CWB for those aeroplane. Airbus also published SB A330-
57-3116 Revision 01 and SB A340-57-4125 Revision 01, to include aeroplanes in post-mod 44360
and post-mod 49202 configuration for inspections of the outside CWB (below bottom skin), and
introduced revised thresholds and intervals for the repetitive inspections of the outside CWB, and
to provide an alleviation of the number of holes to be inspected. The repetitive inspection program
for aeroplanes in pre-mod 44360 configuration remained unchanged.
Consequently, EASA issued AD 2017-0069, partially retaining the requirements of EASA AD
2014-0149, which was superseded, to require new repetitive SDI (which include rototests) of the
fastener holes at FR40 of the inside and the outside CWB (above and below bottom skin), and the
implementation of the modification of the inside CWB.
Since that AD was issued, Airbus finalised an inspection program for A330-200F aeroplanes and
published SB A330-57-3116 Revision 02, SB A330-57-3132 Revision 01 and SB A330-57-3129
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Revision 01 accordingly. Airbus also published the applicable Modification SB, introducing a lower
threshold for the modification, which allows operation to the Extended Service Goal (ESG) objective
without any additional inspections. For the same reason, Airbus issued SB A330-57-3115
Revision 02, SB A330-57-4124 Revision 03, SB A330-57-3130 Revision 01 and SB A340-57-4137
Revision 01, for aeroplanes in post-mod 206050 configuration. Finally, it was determined that the
lower threshold for embodiment of the applicable Modification SB must be counted from aeroplane
first flight, not since Airbus mod 206049 implementation, as previously indicated.
For the reasons described above, this AD retains the requirements of EASA AD 2017-0069, which is
superseded, extends the compliance time for A330-200F aeroplanes as no accomplishment
instructions existed before, adds references to the latest Airbus SB revisions, introduces a window
of embodiment for modification of the inside CWB, as well as a correction of the window of
embodiment for the applicable Optional Modification SB.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Repetitive Inspections:
(1) Before exceeding the thresholds as specified in the applicable Inspection SB, except as
specified in paragraph (2) of this AD, depending on aeroplane configuration and utilisation, or
within the compliance time specified in Table 1 of this AD, whichever occurs later, and,
thereafter, at intervals not to exceed the values defined in the applicable Inspection SB,
except as specified in paragraph (3) of this AD, depending on aeroplane configuration, remove
the fasteners and accomplish an SDI (including rototests) of the fastener holes at FR40 vertical
web, on both LH and RH sides, of the affected CWB lower panel area in accordance with the
instructions of the applicable Inspection SB.
Table 1 – Inspection Threshold
CWB
Aeroplane (configuration) Compliance Time
Area
Within 2 400 flight cycles (FC) or 24 months,
A330 (pre-mod 44360),
whichever occurs first after 27 June 2014 [the
except A330-200F
effective date of EASA AD 2014-0149]
Below
Within 1 300 FC or 24 months, whichever occurs
A340 (pre-mod 44360) first after 27 June 2014 [the effective date of EASA
AD 2014-0149]
A330 and A340 (post-mod
Below
44360), except A330-200F
Within 18 months after 23 May 2017 [the effective
A330 and A340 (post-mod date of EASA AD 2017-0069]
44360 and pre-mod Above
55306), except A330-200F
A330-200F Below Within 24 months after the effective date of this
AD
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(2) When it is determined that no Repair Design Approval Sheet (RDAS) is found to exist for the
FR40 area on an aeroplane, it is acceptable to accomplish the first SDI on that aeroplane
before exceeding the applicable threshold, instead of ‘before next flight’, as specified in the
applicable Inspection SB.
(3) For post-mod 44360 aeroplanes and pre-mod 55306 aeroplanes that have previously been
inspected (see paragraph (8) of this AD) as previously required by EASA AD 2014-0149, it is
allowed to defer the next due inspection to 18 months after 23 May 2017 [the effective date
of this EASA AD 2017-0069], provided the previous inspection interval, as applicable,
depending on aeroplane configuration and utilisation, as defined in the previous revision of
the applicable Inspection SB, is not exceeded.
Corrective Action(s):
(4) If, during any SDI (including rototests) as required by paragraph (1) of this AD, no crack is
detected, before next flight, install new fasteners in transition fit, in accordance with the
instructions of the applicable Inspection SB.
(5) If, during any SDI (including rototests) as required by paragraph (1) of this AD, a crack is
detected, accomplish the applicable actions (additional inspection followed by repetitive
inspections) within the times specified in, and in accordance with the instructions of, the
applicable Inspection SB, or, depending on findings, before next flight, contact Airbus to
obtain an RDAS and accomplish that repair accordingly, including post-repair follow-on
action(s), if any are specified in that RDAS.
(6) If, during any SDI (including rototests) on a post-mod 44360 aeroplane, as required by
paragraph (1) of this AD, a crack is detected only on the LH or RH side, as previously repaired
by an Airbus RDAS, it is acceptable to partially apply the applicable Optional Modification SB
(optional terminating action – see section ‘Definitions’ and paragraph (13) and (14) of this
AD), on the opposite side of that aeroplane, provided no RDAS, as specified in the applicable
Inspection SB, was found to exist on that side.
Modification:
(7) For aeroplanes in post-mod 55306 and pre-mod 55792 configuration and for aeroplanes in
post-mod 55792 and pre-mod 205225 configuration, within the applicable window of
embodiment as specified in Table 2 of this AD, depending on short range (SR) or long range
(LR) operation (see Note 1 of this AD), or within the applicable compliance time specified in
Table 3 of this AD, whichever occurs later, modify the inside CWB (above bottom skin) in
accordance with the instructions of the applicable Modification SB.
For an A330-300 or A340-300 aeroplane on which Airbus SB A330-57-3129 (original issue or
Revision 01) or SB A340-57-4136 (original issue or Revision 01), as applicable, was embodied
before reaching the applicable lower threshold as defined in Table 2 of this AD, within 12
months after the effective date of this AD, contact Airbus for additional instructions and,
within the compliance time specified by Airbus, accomplish those instructions accordingly.
Note 1: The instructions provided by Airbus Operators Information Telex (OIT) 999.0086/11 can be
used to determine whether an aeroplane is operated SR or LR.
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Table 2 – Window of embodiment for CWB Modification (see Notes 1 and 2 of this AD)
Lower Threshold, not before Upper Threshold, before exceeding
Aeroplanes
(FH or FC, whichever occurs first) (FH or FC, whichever occurs first )
A330-200, SR: 36 908 FH or 10 545 FC
none
except -200F LR: 51 198 FH or 7 877 FC
SR: 32 475 FH or 9 941 FC
A330-300 2 016 FC
LR: 52 115 FH or 7 702 FC
A330-200F 20 902 FH or 3 634 FC 25 833 FH or 8 611 FC
SR: 27 627 FH or 6 907 FC
A340-300 25 399 FH or 5 036 FC
LR: 35 065 FH or 5 195 FC
Note 2: The flight hours (FH) and FC specified in Table 2 of this AD are those accumulated by the
aeroplane since first flight.
Table 3 – Grace Period
Aeroplanes Compliance Time
A330 and A340, Within 18 months after 23 May 2017 [the effective date of
except A330-200F EASA AD 2017-0069]
A330-200F Within 18 months after the effective date of this AD
Credit:
(8) Inspection(s) and corrective action(s) on an aeroplane, accomplished before the effective date
of this AD in accordance with the instructions Airbus SB A330-57-3114 original issue, or SB
A330-57-3115 original issue or Revision 01, or SB A330-57-3116 original issue or Revision 01,
or SB A340-57-4123 original issue, or SB A340-57-4124 original issue, or Revision 01, or
Revision 02, or SB A340-57-4125 original issue, or Revision 01, as applicable, are acceptable to
comply with the initial requirements of paragraphs (1), (4) and (5) of this AD, as applicable, for
that aeroplane.
(9) Inspection(s) and corrective action(s) and installation of fasteners on an aeroplane,
accomplished before 23 May 2017 [the effective date of EASA AD 2017-0069] in accordance
with the instructions of Airbus Technical Disposition Reference LR57D11023270,
LR57D11023714, or LR57D11029170, or LR57D11029171, or LR57D11029172, or
LR57D11029173, or LR57D11030740, or LR57D11030741, as applicable, are acceptable to
comply with the initial requirements of paragraphs (1), (4) and (5) of this AD, as applicable, for
that aeroplane.
(10) Modification of an aeroplane, before the effective date of this AD in accordance with the
instructions of Airbus SB A330-57-3129 at original issue, or SB A340-57-4136 at original issue,
as applicable, is acceptable to comply with the modification requirements of paragraph (7) of
this AD, provided the modification was accomplished within the applicable window of
embodiment as specified in Table 2 of this AD.
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Related Actions:
(11) Accomplishment on an aeroplane of the initial and repetitive inspections as required by this
AD, cancels the need to accomplish Airworthiness Limitation Items (ALI) task 57-11-02 and
task 57-11-04 for that aeroplane.
(12) Modification of an aeroplane as required by paragraph (7) of this AD cancels the need to
accomplish ALI task 57-11-02 for that aeroplane.
Terminating Action:
(13) Modification of a post-mod 44360 aeroplane by multiple cold working in accordance with the
instructions of the applicable Optional Modification SB, constitutes terminating action for the
repetitive SDI (including rototests) as required by this AD for that aeroplane, provided this is
accomplished within the compliance times specified in the applicable Inspection SB,
depending on aeroplane configuration and on accumulated FH/FC at the time of applicable
Optional Modification SB embodiment.
(14) Partial application (LH or RH side) of the applicable Optional Modification SB on an aeroplane,
as specified in paragraph (6) of this AD, constitutes terminating action for the repetitive SDI
(including rototests) as required by this AD for the modified LH or RH side of that aeroplane.
Ref. Publications:
Airbus SB A330-57-3114 original issue dated 12 March 2013, or Revision 01 dated 13 January 2017.
Airbus SB A330-57-3115 original issue dated 04 April 2013, or Revision 01 dated 23 November 2016,
or Revision 02 dated 29 May 2018.
Airbus SB A330-57-3116 original issue dated 12 March 2013, or Revision 01 dated 23 November
2016, or Revision 02 dated 05 February 2018.
Airbus SB A330-57-3129 original issue dated 05 October 2016, or Revision 01 dated 21 September
2017.
Airbus SB A330-57-3130 original issue dated 23 November 2016, or Revision 01 dated 18 February
2018.
Airbus SB A330-57-3131 original issue dated 23 November 2016, or Revision 01 dated 13 February
2018.
Airbus SB A330-57-3132 original issue dated 23 November 2016, or Revision 01 dated 05 February
2018.
Airbus SB A340-57-4123 original issue dated 12 March 2013, or Revision 01 dated 13 January 2017.
Airbus SB A340-57-4124 original issue dated 04 April 2013, or Revision 01 dated 22 August 2013, or
Revision 02 dated 23 November 2016, or Revision 03 dated 28 May 2018.
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Airbus SB A340-57-4125 original issue dated 12 March 2013, or Revision 01 dated 23 November
2016, or Revision 02 dated 25 April 2018.
Airbus SB A340-57-4136 original issue dated 05 October 2016, or Revision 01 dated 27 September
2017.
Airbus SB A340-57-4137 original issue dated 23 November 2016, or Revision 01 dated 27 September
2017.
Airbus SB A340-57-4138 original issue dated 23 November 2016, or Revision 01 dated 13 February
2018.
Airbus SB A340-57-4139 original issue dated 23 November 2016.
Airbus OIT 999.0086/11 dated 9 November 2011.
The use of later approved revisions of the above-mentioned 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 13 September 2018 as PAD 18-127 and republished on 26 September
2018 as PAD 18-127R1 for consultation until 11 October 2018. The Comment Response
Documents can be found in the EASA Safety Publications Tool, in the compressed (zipped) file
attached to the record for this AD.
3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.
4. Information about any failures, malfunctions, defects or other occurrences, which may be
similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on
a product, part or appliance not affected by this AD, can be reported to the EU aviation safety
reporting system.
5. For any question concerning the technical content of the requirements in this AD, please
contact: AIRBUS – EIAL (Airworthiness Office), E-mail: airworthiness.A330-A340@airbus.com.
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