Nachrichten für Luftfahrer 2016 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2016-0207
Airworthiness Directive
AD No.: 2016-0207
Issued: 19 October 2016
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Regulation (EC) 216/2008 on behalf of the European Union, 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 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 (EC) 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS A330 aeroplanes
Effective Date: 18 November 2016
TCDS Number(s): EASA.A.004
Foreign AD: Not applicable
Supersedure: None
ATA 53 – Fuselage – Structural Parts / Joints – Modification / Reinforcement
Manufacturer(s):
Airbus (formerly Airbus Industrie)
Applicability:
Airbus A330-201, A330-202, A330-203, A330-223, A330-243, A330-223F, 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).
Reason:
An analysis conducted on A330 aeroplanes identified structural areas which are susceptible to
widespread fatigue damage (WFD).
This condition, if not corrected, could lead to crack initiation and undetected propagation, leading
to reduced structural integrity of the aeroplane, possibly resulting in rapid depressurisation and
consequent injury to occupants.
To address this potential unsafe condition, Airbus developed a number of modifications (Mod) and
published associated Service Bulletins (SB) for embodiment in service, to provide instructions to
reinforce the various structural parts of the fuselage.
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For the reasons described above, this AD requires accomplishment of these modifications and
reinforcements.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Modification:
(1) Before exceeding the applicable Structural Modification Point (SMP) for each Action, as defined
in Table 3 of Appendix 1 of this AD, as applicable, modify the aeroplane in accordance with the
instructions of each Airbus SB, as applicable, as specified in Appendix 1 of this AD.
Alternative Method:
(2) Modification of an aeroplane in accordance with the instructions of Airbus SB A330-53-3273 is
an acceptable alternative method to comply with the modification requirements of Action 6
(SB A330-53-3226) for that aeroplane.
Grace Period(s):
(3) For aeroplanes that are close to, or have already exceeded the SMP threshold(s), as specified
for each Action, as applicable, accomplishment of the modification can be deferred for a period
not exceeding 12 months after the effective of this AD, except for Action 8 (SB A330-53-3237),
accomplishment of which can be deferred for a period not exceeding 15 months after the
effective date of this AD.
Additional Work:
(4) For aeroplanes that have already been modified, before the effective date of this AD, in
accordance with the instructions of the original issue of Airbus SB A330-53-3144,
SB A330-53-3222, or SB A330-53-3237, as applicable, within 12 months after the effective date
of this AD, accomplish the additional work as specified in each applicable SB at Revision 01.
Ref. Publications:
Airbus SB A330-53-3144 Revision 01 dated 25 July 2006, or Revision 02 dated 20 April 2011, or
Revision 03 dated 15 January 2015, or Revision 04 dated 23 November 2015.
Airbus SB A330-53-3222 Revision 01 dated 31 March 2016.
Airbus SB A330-53-3223 original issue dated 19 January 2015.
Airbus SB A330-53-3224 original issue dated 16 January 2015, or Revision 01 dated 14 April 2016.
Airbus SB A330-53-3225 original issue dated 16 January 2015, or Revision 01 dated 26 February
2016, or Revision 02 dated 08 June 2016.
Airbus SB A330-53-3226 original issue dated 15 January 2015, or Revision 01 dated 03 March 2016.
Airbus SB A330-53-3236 original issue dated 15 January 2015, or Revision 01 dated 24 August 2015,
or Revision 02 dated 23 March 2016.
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Airbus SB A330-53-3237 Revision 01 dated 08 February 2016.
Airbus SB A330-53-3238 original issue dated 15 January 2015, or Revision 01 dated 19 October
2015.
Airbus SB A330-53-3239 original issue dated 20 April 2015, or Revision 01 dated 04 July 2016.
Airbus SB A330-53-3244 original issue dated 07 April 2015, or Revision 01 dated 02 August 2016.
Airbus SB A330-53-3248 original issue dated 07 April 2015, or Revision 01 dated 29 February 2016,
or Revision 02 dated 27 July 2016.
Airbus SB A330-53-3251 original issue dated 13 May 2015, or Revision 01 dated 23 June 2016.
Airbus SB A330-53-3252 original issue dated 10 April 2015, or Revision 01 dated 30 June 2016.
Airbus SB A330-53-3257 original issue dated 21 July 2015, or Revision 01 dated 15 March 2016.
Airbus SB A330-53-3258 original issue dated 20 April 2015.
Airbus SB A330-53-3259 original issue dated 11 May 2015, or Revision 01 dated 26 February 2016,
or Revision 02 dated 18 July 2016.
Airbus SB A330-53-3263 original issue dated 21 July 2015, or Revision 01 dated 01 December 2015.
Airbus SB A330-53-3273 original issue dated 28 September 2016
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 11 May 2016 as PAD 16-067 for consultation until 22 June 2016 and
republished on 22 September 2016 as PAD 16-067R1 for additional consultation until
06 October 2016. 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. 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.
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Appendix 1 – SMP / Modifications
[Each applicable SB defines the aeroplanes and configuration(s) for which the actions are required]
Notes referenced in the Tables below:
Note 1: LR = flight hours (FH) optimized set for aeroplane in Long Range (LR) operations; SR = flight
cycles (FC) optimized set for aeroplane in Short Range (SR) operations.
Note 2: Weight Variant (WV) Group definitions:
Table 1
Aeroplanes WV Group Weight variants
Group 32A 020, 021, 022, 023, 024, 025, 026 and 027
A330-200 050, 051, 052, 053, 054, 055, 056, 057, 058, 059, 060, 061,
Group 32E
062, 063, 064, 080, 081, 082 and 083
A330-200F - 000, 001 and 002
Group 33A 000, 001, 002, 003 and 004
Group 33B 010, 011, 012, 013 and 014
A330-300 Group 33C 020, 024, 025, 026 and 027
Group 33D 022
030, 031, 032, 033, 034, 035, 039, 050, 051, 052, 053, 054,
Group 33E
055, 056, 057, 058, 059, 060, 080, 081, 082 and 083
Note 3: Window of Embodiment: For some modifications, it was deemed necessary to establish a
“lower threshold” (as defined in FC and FH, as specified in Table 2 of this AD – if two limits are
indicated, both are required to be exceeded), before which it is not advisable to accomplish the
modification. For aeroplanes already modified before that threshold was reached, it is anticipated
that accomplishment of additional maintenance tasks (modification/inspection), to be developed by
Airbus, will be required.
Table 2 - Lower Threshold for Modification
SB (Mod) Applicability (Note 2) Modification Not Before:
Groups 32A, 32E, 33A, 33C, 33D and
10 000 FC
33E
A330-53-3222 R01
Group 33B 12 000 FC
A330-200F 8 900 FC and 26 600 FH
A330-53-3224 Group 33A 10 000 FC and 6 600 FH
A330-53-3225 Group 33A 3 900 FC and 10 200 FH
A330-53-3237 R01 Groups 32A, 33A, 33B, 33C and 33D 3 900 FC
A330-53-3238 R01 Groups 32A, 33A, 33B, 33C and 33D 9 000 FC
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Note 4: SMP limits in FH have also been determined but are not shown in Table 3 because they
exceed the currently applicable certified limit (DSG or ISG) of the aeroplane. For the purpose of this
AD, SMP limits in FH, as defined in the applicable SB, are currently not applicable, as they depend on
the outcome of an Extended Service Goal (ESG) certification by EASA.
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An aeroplane complies with the requirements of this AD when all applicable actions from 1 to 18 defined in Table 3 of this AD are accomplished.
Table 3
Applicable SB SMP SR (Note 1) SMP LR (Note 1)
Applicability
Action Description of action (Equivalent Airbus (FC or FH, whichever occurs first)
(Note 2)
production Mod) (*) = Note 4
Group 32A 32 500 FC (*) 26 600 FC (*)
Group 33A 23 700 FC / 71 300 FH 20 400 FC (*)
Improve circumferential joints at Frame (FR)
1 Group 33B A330-53-3144 R01 27 600 FC / 83 000FH 23 700 FC (*)
45 and 54 of the fuselage
Group 33C 23 300 FC / 70 000 FH 20 000 FC (*)
Group 33D 22 700 FC / 68 300 FH 19 500 FC (*)
Groups 32A
23 100 FC / 80 900 FH 20 900 FC (*)
and 32E
Improve splicing area from FR48 to FR53-2 Group 33A 24 200 FC / 79 100 FH 21 800 FC (*)
A330-53-3222 R01
2 between Stringer (STGR) 23 and 26 Left Group 33B 19 700 FC / 64 300 FH 17 700 FC (*)
(Mod 204315)
Hand (LH)/Right Hand (RH) of the fuselage Groups 33C,
21 600 FC / 70 600 FH 19 400 FC (*)
33D and 33E
A330-200F 27 400 FC / 82 200 FH
Groups 32A,
Reinforce couplings in area FR20 – FR25 /
32E, 33B,
3 STGR20 RH – STRG22 RH of the forward A330-53-3223 30 900 FC
33C, 33D and
fuselage
33E
Reinforce circumferential joint at FR72 of
4 Group 33A A330-53-3224 29 700 FC / 89 600 FH 25 500 FC (*)
the fuselage
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Applicable SB SMP SR (Note 1) SMP LR (Note 1)
Applicability
Action Description of action (Equivalent Airbus (FC or FH, whichever occurs first)
(Note 2)
production Mod) (*) = Note 4
Reinforce circumferential joint at FR58 of
5 Group 33A A330-53-3225 16 300 FC / 49 300 FH 13 300 FC / 90 700 FH
the fuselage
Group 32A 26 100 FC / 91 600 FH 21 000 FC (*)
Groups 33C,
Reinforce circumferential joint between 15 600 FC / 46 800 FH 12 600 FC / 84 800 FH
33D and 33E
6 FR53.6 – FR53.7 for emergency door TYPE 1 A330-53-3226
Group 33A 34 400 FC (*) 27 800 FC (*)
area of the centre fuselage
Group 33B 19 900 FC / 59 800 FH 16 100 FC (*)
Group 32E 19 900 FC / 69 900 FH 16 200 FC (*)
Reinforce circumferential joint between
7 FR53.6 – FR53.7 LH/RH of option emergency Group 33A A330-53-3236 30 900 FC / 93 200 FH 25 400 FC (*)
door TYPE A area of the centre fuselage
Group 33A
Improve fatigue life of internal centre
Group 33B
8 fuselage structure on longitudinal beams A330-53-3237 R01 27 300 FC
above the centre wing box Groups 32A,
33C and 33D
Group 32A 38 400 FC
Update lower / lateral frame splicing with Group 33A 28 800 FC
9 corner fitting between FR53.3 and FR54 of Group 33B A330-53-3238 36 200 FC
the centre fuselage
Groups 33C
34 700 FC
and 33D
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Applicable SB SMP SR (Note 1) SMP LR (Note 1)
Applicability
Action Description of action (Equivalent Airbus (FC or FH, whichever occurs first)
(Note 2)
production Mod) (*) = Note 4
Reinforce longitudinal butt joints in
10 A330-200F A330-53-3239 15 100 FC
section 13
Reinforce circumferential joint at FR31
11 between STRG 7LH and STRG 8RH of A330-200F A330-53-3244 15 500 FC / 46 500 FH
forward fuselage
Reinforce frame couplings in section 13, 14
12 Group 33A A330-53-3248 32 000 FC
and 14A of the forward fuselage
Group 33C
Pre-Mod 38 200 FC (*) 32 000 FC (*)
46636
Reinforce circumferential joint/stringer
Groups 33C
13 coupling in area of FR37.1 of the forward A330-53-3251
and 33D
fuselage 30 600 FC / 99 500 FH 27 600 FC (*)
Post-Mod
46636
Group 33E 32 200 FC (*) 29 100 FC (*)
Groups 33C
Reinforce circumferential joint/stringer and 33D,
30 600 FC / 99 500 FH 27 600 FC (*)
14 coupling in area of FR37.1 of the forward Post-Mod A330-53-3252
fuselage 46636
Group 33E 32 200 FC (*) 29 100 FC (*)
Reinforce frame couplings in rear area of Group 33A
15 A330-53-3257 24 000 FC
the fuselage and 33B
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Applicable SB SMP SR (Note 1) SMP LR (Note 1)
Applicability
Action Description of action (Equivalent Airbus (FC or FH, whichever occurs first)
(Note 2)
production Mod) (*) = Note 4
Reinforce corner fittings in section 13 of the
16 Group 32A A330-53-3258 31 800 FC
forward fuselage
Reinforce circumferential joint at FR58 Group 32E 18 500 FC / 65 400 FH 14 600 FC / 95 700 FH
17 (aeroplane Post-Mod 40556/D18255) of the Group 33A A330-53-3259 34 800 FC (*) 28 400 FC (*)
rear fuselage Group 33B 33 500 FC (*) 27 400 FC (*)
Groups 32A,
32E, 33B,
18 Reinforce frames in rear area of the fuselage A330-53-3263 23 300 FC / 69 700 FH 20 800 FC (*)
33C, 33D and
33E
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-290 38144 Braunschweig
FAA AD 2016-21-02 - Amdt. 39-18683 Fax: +49-531-2355-5298
email: ad@LBA.de
SIKORSKY 07.11.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: Sikorsky Aircraft Corporation
Hersteller: Sikorsky Aircraft Corporation
Muster: Sikorsky S-92A
Baureihen: S-92A
Werknummern: 920006 bis 920250
Gerätenummer: EASA.IM.R.001
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2016-21-02 - Amdt. 39-18683
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 2016-290 geführt.
Betrifft:
(ATA 26) Fire Protection - Fire Bottle Inertia Switch Wiring / Fire Extinguishing System - Modification / Test
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
FAA AD 2016-21-02 - Amdt. 39-18683 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
gültige 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-2016-290 Seite 1 von 1 488/2016
