Nachrichten für Luftfahrer 2013 Teil II (weicht ggf. von Druckversion ab)
EASA AD No.: 2013-0248
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2013-0248
Date: 14 October 2013
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: Type/Model designation(s):
AIRBUS A300, A300-600, A300-600ST and
A310 aeroplanes
TCDS Number: France n° 145 and EASA.A.014
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2007-0293 dated 29 November 2007.
Time limits / Maintenance checks – Safe life Airworthiness
ATA 05
Limitation Items (ALS Part 1) – Amendment
Manufacturer(s): Airbus (formerly Airbus Industrie)
Applicability: Airbus A300 aeroplanes, all certified models, all Manufacturer Serial Numbers
(MSN),
Airbus A300-600 aeroplanes, all certified models, all MSN,
Airbus A300F4-608ST aeroplanes, all MSN,
Airbus A310 aeroplanes, all certified models all MSN.
Reason: The airworthiness limitations are currently distributed in the Airbus A300
Airworthiness Limitation Section (ALS), A300-600 ALS and A310 ALS.
The instructions and airworthiness limitations applicable to the Safe Life
Airworthiness Limitation Items (SL ALI) are given in Airbus A300 ALS Part 1,
A300-600 ALS Part 1 and A310 ALS Part 1, which are approved by the
European Aviation Safety Agency (EASA).
The revision 01 of Airbus A300 ALS Part 1, A300-600 ALS Part 1 and A310
ALS Part 1 introduces more restrictive instructions and/or airworthiness
limitations. Failure to comply with the maintenance requirements contained in
these revisions could constitute an unsafe condition.
For the reasons described above, this AD retains the requirements of EASA AD
2007-0293, which is superseded, and requires the implementation of the new
or more restrictive maintenance requirements and/or airworthiness limitations
as specified in the Airbus A300 ALS Part 1 Revision 1, A300-600 ALS Part 1
Revision 1 and A310 ALS Part 1 Revision 1, except for the A300 life limits
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EASA AD No.: 2013-0248
applicable to Main Landing Gear (MLG) barrel assembly, retraction actuator
assembly linkage assembly and to flanged duct, for which applicable life limits
are defined in EASA AD 2013-0210.
Effective Date: 28 October 2013
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) From the effective date of this AD, accomplish the following actions, as
Time(s):
specified in the Airbus A300 ALS Part 1 revision 01, Airbus A300-600 ALS
Part 1 revision 01, or Airbus A310 ALS Part 1 revision 01, as applicable to
aeroplane model and depending on aeroplane configuration:
(1.1) Replace each component before or upon reaching the applicable life
limit.
(1.2) Within the thresholds and intervals, accomplish all applicable
maintenance tasks.
(2) Compliance with the requirements of paragraph (1) of this AD can be
demonstrated by:
(2.1) Revising as follows, the approved Aircraft Maintenance Program
(AMP) on the basis of which the Operator or the Owner ensures the
continuing airworthiness of each operated aeroplane:
Incorporate all maintenance tasks and applicable airworthiness
limitations specified in the Airbus A300 ALS Part 1 revision 01,
Airbus A300-600 ALS Part 1 revision 01 and Airbus A310 ALS Part
1 revision 01, as applicable to aeroplane model and relevant to the
aeroplane configuration and weight variant,
and
(2.2) Complying with the approved AMP described in paragraph (2.1) of
this AD.
Ref. Publications: Airbus A300 ALS Part 1 Revision 01 approved by EASA on 05 September
2013.
Airbus A300-600 ALS Part 1 Revision 01 approved by EASA on 05 September
2013.
Airbus A310 ALS Part 1 Revision 01 approved by EASA on 05 September
2013.
The use of later approved variations or 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 September 2013 as PAD 13-137 for consultation
until 02 October 2013. No comments were received during the consultation
period.
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 SAS – EIAW (Airworthiness Office),
Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51.
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2012-078R2 38144 Braunschweig
EASA AD 2013-0256 vom 21.10.2013 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 28.10.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus, 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 und A330-343.
A340-211, A340-212, A340-213, A340-311, A340-312, A340-313, A340-541,
A340-542, A340-642 und A340-643.
Werknummern: Alle
Gerätenummer: 2849, 2850, EASA.A.004, EASA.A.015
Revisionsstand:
Diese LTA ersetzt D-2012-078R1 vom 17.02.2012
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0256 vom 21.10.2013
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 2012-078R2 ge-
führt.
Betrifft:
(ATA 56) Windows - Fixed Windows / Windshield Heating Connectors - Inspection / Replacement
Anmerkungen:
Gemäß M.A.304 des Anhang I (Teil M) der Verordnung (EG) Nr. 2042/2003 dürfen Luftfahrzeuge
nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in den Betrieb genommen
werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsan-
weisung EASA AD 2013-0256 vom 21.10.2013 herausgegeben oder per Entscheidung Nr. 02/2003
übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsan-
weisungen 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 Verwaltungsverfahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2012-078R2 Seite 1 von 1 574/2013
EASA AD No.: 2013-0256
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2013-0256
Date: 21 October 2013
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: Type/Model designation(s):
AIRBUS A330 and A340 aeroplanes
TCDS Number: EASA.A.004 and EASA.A.015
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2011-0242 dated 19 December 2011 and corrected
15 February 2012.
Windows – Fixed Windows / Windshield Heating Connectors –
ATA 56
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).
Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313, A340-
541, A340-542, A340-642 and A340-643 aeroplanes, all MSN.
Reason: Several operators reported cases of burning smell and/or smoke in the cockpit
during cruise phase leading in some cases to diversion. Findings showed that
the cause of these events is the burning of the Saint-Gobain Sully (SGS)
windshield connector terminal block.
This condition, if not corrected, could significantly increase the flight crew
workload which would, under some flight phases and/or circumstances
constitute an unsafe condition.
To address this unsafe condition, Airbus published 3 different Service Bulletins
(SB) and EASA issued AD 2011-0242 (later corrected) which required the
identification of the installed windshields and replacement of the affected part.
Since issuance of that AD, a new occurrence in service led Airbus to identify a
new batch of affected parts.
For the reasons described above, this AD retains the requirements of EASA AD
2011-0242, which is superseded, and requires identification and replacement of
the additionally identified windshields.
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EASA AD No.: 2013-0256
Effective Date: 04 November 2013
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
Re-statement of requirements of EASA AD 2011-0242:
Time(s):
(1) Within 1 200 Flight Hours after 02 January 2012 [the effective date of
EASA AD 2011-0242], inspect to identify the manufacturer, Part Number
(P/N) and Serial Number (S/N) of the Left Hand (LH) and Right Hand (RH)
windshields installed on the aeroplane in accordance with the instructions
of Airbus Service Bulletin (SB) A330-56-3009 Revision 01, or SB A340-56-
4008, or SB A340-56-5002, as applicable to aeroplane type and model. A
review of aeroplane delivery or maintenance records is acceptable to
determine the Manufacturer, P/N and S/N of the installed windshields,
provided the Manufacturer, P/N and S/N of the installed windshields can be
conclusively determined from that review.
(2) If the installed LH and/or RH windshield(s) is/are manufactured by SGS
and the identified P/N and S/N is/are listed in Airbus SB A330-56-3009
Revision 01, or SB A340-56-4008, or SB A340-56-5002, as applicable to
aeroplane type and model, within 9 months after 02 January 2012 [the
effective date of EASA AD 2011-0242], replace the affected LH and/or RH
windshield(s) in accordance with the instructions of Airbus SB A330-56-
3009 Revision 01, or SB A340-56-4008, or SB A340-56- 5002, as
applicable to aeroplane type and model.
New requirements of this AD:
(3) Within 6 months after the effective date of this AD, inspect to identify the
manufacturer, P/N and S/N of the LH and RH windshields installed on the
aeroplane in accordance with the instructions of Airbus SB A330-56-3009
Revision 03, or Airbus SB A340-56-4008 Revision 02, or Airbus SB A340-
56-5002 Revision 02, as applicable to aeroplane type and model. A review
of aeroplane delivery or maintenance records is acceptable to determine
the Manufacturer, P/N and S/N of the installed windshields, provided the
Manufacturer, P/N and S/N of the installed windshields can be conclusively
determined from that review.
(4) If the installed LH and/or RH windshield(s) is/are manufactured by SGS
and the identified P/N and S/N is/are listed in Appendix 2 of Airbus SB
A330-56-3009 Revision 03, or Airbus SB A340-56-4008 Revision 02, or
Airbus SB A340-56-5002 Revision 02, as applicable to aeroplane type and
model, or if the Manufacturer, or P/N or S/N is not identifiable, within 6
months after the effective date of this AD, replace the affected LH and/or
RH windshield(s) with a serviceable part in accordance with the
instructions of Airbus SB A330-56-3009 Revision 03, or SB A340-56-4008
Revision 02, or SB A340-56- 5002 Revision 02, as applicable to aeroplane
type and model.
Note: A serviceable windshield is a windshield not listed in Appendix 1 of Airbus
SB A330-56-3009 Revision 03, or SB A340-56-4008 Revision 02, or SB A340-
56-5002 Revision 02, or included in the list but having a suffix “U” added to the
S/N on the identification plate.
(5) An aeroplane which, before the effective date of this AD, has been
inspected and, depending on findings, corrected as required by paragraphs
(1) and (2) of this AD, is not affected by the requirement of paragraphs (3)
and (4) of this AD, provided that, since those actions were accomplished
on that aeroplane, no replacement windshield has been installed with a
P/N and S/N as listed in Appendix 2 of Airbus SB A330-56-3009 Revision
03, or Airbus SB A340-56-4008 Revision 02, or Airbus SB A340-56-5002
Revision 02, as applicable to aeroplane type and model.
(6) From the effective date of this AD, do not install on an aeroplane any
affected windshield from SGS having a P/N and S/N as listed in Appendix
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EASA AD No.: 2013-0256
1 of Airbus SB A330-56-3009 Revision 03, or Airbus SB A340-56-4008
Revision 02, or Airbus SB A340-56-5002 Revision 02, as applicable to
aeroplane type and model, unless a suffix “U” has been added on the S/N
identification plate.
Ref. Publications: Airbus SB A330-56-3009 original issue dated 04 May 2010 or revision 01 dated
27 January 2011, or revision 02 dated 08 February 2012, or Revision 03 dated
01 August 2013.
Airbus SB A340-56-4008 original issue dated 04 May 2010, or revision 01 dated
08 February 2012, or Revision 02 dated 01 August 2013.
Airbus SB A340-56-5002 original issue dated 04 May 2010, or revision 01 dated
08 February 2012, or Revision 02 dated 01 August 2013.
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 18 September 2013 as PAD 13-142 for consultation
until 15 October 2013. No comments were received during the consultation
period.
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.
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2012-081R1 38144 Braunschweig
EASA AD 2013-0254 vom 18.10.2013 Fax: +49-531-2355-5298
email: ad@LBA.de
SAAB 23.10.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: SAAB AB - Aeronautics
Hersteller: SAAB AB - Aeronautics, SAAB Aerosystems
Muster: SAAB 340
Baureihen: SAAB SF340A und SAAB 340B
Werknummern: Baureihe SAAB SF340A: (S/N) 004 bis 159
Baureihe SAAB 340B: (S/N) 160 bis 459
Ausgenommen sind Flugzeuge, an denen die SAAB Modifikation (Mod.) Nr.
2650 und/ oder 2859 durchgeführt wurde.
Diese Lufttüchtigkeitsanweisung gilt nicht für Flugzeuge mit den (S/N) 170, 342,
362, 363, 367, 372, 379, 385, 395, 405, 409, 431 und 455.
Gerätenummer: 2524, EASA.A.068
Revisionsstand:
Diese LTA ersetzt D-2012-081 vom 30.01.2012
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0254 vom 18.10.2013
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 2012-081R1 ge-
führt.
Betrifft:
(ATA 27) Flight Controls - Stall Warning / Identification System / Ice Speed Curves - Deactivation
Anmerkungen:
Gemäß M.A.304 des Anhang I (Teil M) der Verordnung (EG) Nr. 2042/2003 dürfen Luftfahrzeuge
nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in den Betrieb genommen
werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsan-
weisung EASA AD 2013-0254 vom 18.10.2013 herausgegeben oder per Entscheidung Nr. 02/2003
übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsan-
weisungen 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 Verwaltungsverfahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2012-081R1 Seite 1 von 1 567/2013
EASA AD No.: 2013-0254
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2013-0254
Date: 18 October 2013
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: Type/Model designation(s):
SAAB AB, Aeronautics SF340A and 340B aeroplanes
TCDS Number: A.068
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2011-0219 dated 11 November 2011.
Flight Controls – Stall Warning / Identification System / Ice Speed
ATA 27
Curves – Deactivation
Manufacturer(s): SAAB AB, Aeronautics (formerly SAAB Aerosystems).
Applicability: Model SF340A aeroplanes serial numbers (s/n) 004 through 159 inclusive, and
Model 340B aeroplanes s/n 160 through 459 inclusive, except aeroplanes
modified in accordance with SAAB AB modification (mod.) No. 2650 and/or
mod. No.2859.
Note: This AD does not apply to aeroplanes with s/n 170, 342, 362, 363, 367,
372, 379, 385, 395, 405, 409, 431 and 455.
Reason: A few natural stall events, specifically when operating in icing conditions, have
been experienced on SAAB 340 series aeroplanes, without receiving a prior
stall warning.
This condition, if not corrected, could result in loss of control of the aeroplane.
To address this potential unsafe condition, SAAB developed a modified stall
warning system, incorporating improved stall warning logic, and issued Service
Bulletin (SB) 340-27-098 and SB 340-27-099, which include instructions to
replace the present Stall Warning Computer (SWC) with a new SWC, and
instructions to activate the new SWC. The new system includes stall warning
curves optimized for operation in icing conditions, which are activated by
selection of Engine Anti-Ice.
Consequently, EASA issued AD 2011-0219 to require installation of the
improved SWC on Saab 340 aeroplanes.
Since that AD was issued, in-service experience with the improved stall
warning system revealed cases of premature stall warning activation during the
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EASA AD No.: 2013-0254
take-off phase. In numerous recorded cases, the onset of stall warning
occurred without the 6 minute delay after weight off wheels.
This condition, if not corrected, could lead to premature stick shaker activation
and consequent increase in pilot workload during the take-off phase, possibly
resulting in reduced control of the aeroplane.
To address this potential unsafe condition, SAAB AB issued SB 340-27-116 to
provide instructions for temporary deactivation of the stall warning system ice
speed curves for aeroplanes modified in accordance with SAAB SB 340-27-098
or SB 340-27-099. The ice speed curves are intended to activate stall warning
shaker only. The trigger level for stall identification (pusher) remains
unchanged.
For the reasons described above, this AD partially retains the requirements of
EASA AD 2011-0219, which is superseded, and requires, for aeroplanes that
have already installed the new SWC, deactivation of the ice speed curves. For
aeroplanes that do not yet have the new SWC installed, only the provisions for
this installation must be installed.
Pending the investigation to determine the reason for the too early activation,
no permanent action regarding SWC replacement is defined. This AD is
considered to be an interim measure and further AD action may follow.
Effective Date: 25 October 2013
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
Requirement retained from EASA AD 2011-0219:
Time(s):
(1) Within 3 months after the effective date of this AD, modify the aeroplane in
accordance with the instructions of SAAB SB 340-27-097 (SAAB mod
3311).
New requirements of this AD:
(2) Within 30 days after the effective date of this AD, accomplish the following
actions, as applicable to aeroplane configuration, in accordance with the
instructions of SAAB SB 340-27-116:
(2.1) For aeroplanes with basic wing tip that have been modified in
accordance with SAAB SB 340-27-098, deactivate the stall speed
curves in the SWC part number (P/N) 0020AK6.
(2.2) For aeroplanes with extended wing tip that have been modified in
accordance with SAAB SB 340-27-099, deactivate the stall speed
curves in the SWC P/N 0020AK7.
(3) After modification of an aeroplane as required by paragraph (2.1) or (2.2)
of this AD, as applicable, do not install any SWC P/N 0020AK, or P/N
0020AK1, or P/N 0020AK2, or P/N 0020AK4, or P/N 0020AK3 MOD 1 on
that aeroplane.
(4) Aeroplanes modified in accordance with SAAB AB SB 340-27-097 (SAAB
mod 3311) and not modified in accordance with SAAB AB SB 340-27-098
or SB 340-27-099, as applicable, are not affected by requirements of
paragraph (2) of this AD.
Ref. Publications: SAAB SB 340-27-097 original issue dated 01 September 2011, or Revision 01
dated 26 September 2011, or Revision 02 dated 07 October 2011,
SAAB SB 340-27-098 original issue dated 01 September 2011,
SAAB SB 340-27-099 original issue dated 01 September 2011,
SAAB SB 340-27-116 original issue dated 18 October 2013.
The use of later approved revisions of these documents is acceptable for
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EASA AD No.: 2013-0254
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:
Saab AB, Support and Services
SE-581 88 Linköping, Sweden
Fax: +46 13 184874
E-mail: saab340.techsupport@saabgroup.com.
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