Nachrichten für Luftfahrer 2015 Teil 2 (weicht ggf. von Druckversion ab)
D-2015-149 EASA AD 2015-0124 AIRBUS 2849, 2850,
EASA.A.004 und
EASA.A.015
D-2015-150 EASA AD 2015-0123 AIRBUS EASA.A.110
D-2015-151 FAA AD 2015-12-10 Pratt & Whitney Division EASA.IM.E.020
D-2015-152 TC Emergency Bell Helicopter Textron EASA.IM.R.506 und TC
AD CF-2015-16 Canada Ltd. TCDS H-107
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen
Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen
werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
LTA´s werden auch im Internet unter http://www.lba.de publiziert
Braunschweig, den 8. Juli 2015
LBA T 234.20394/NfL/150707
Das Luftfahrt-Bundesamt
Im Auftrag
Burlage
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2002-287R8 38144 Braunschweig
EASA AD 2015-0050R1 vom 19.06.2015 Fax: +49-531-2355-5298
email: ad@LBA.de
ROLLS-ROYCE DEUTSCHLAND 23.06.2015
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: Rolls-Royce Deutschland Ltd & Co KG
Hersteller: Rolls-Royce plc
Muster: TAY
Baureihen: TAY 650-15 und 651-54
Werknummern: TAY 650-15 Triebwerke: Seriennummern (S/N) gemäß Appendix 1 der EASA
AD 2015-0050R1 vom 19.06.2015. Andere (S/N), wenn in einem Flugzeug
installiert und betrieben unter einem "Air Operator Certificate" herausgegeben
von der Islamischen Republik Iran, ausgerüstet mit einer "Low Pressure
Turbine" Modul M05300AA.
TAY 651-54 Triebwerke: Alle (S/N), wenn die Triebwerke mit einer "Low
Pressure Turbine" Modul 05300AA ausgerüstet sind.
Diese Triebwerke sind in Fokker F28 Mark 0100 und Boeing 727 Flugzeugen
installiert, aber nicht auf diese beschränkt.
Gerätenummer: 6328, EASA.E.063
Revisionsstand:
Diese LTA ersetzt D-2002-287R7 vom 02.04.2015
Airworthiness Directive der ausländischen Behörde:
EASA AD 2015-0050R1 vom 19.06.2015
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 2002-287R8 ge-
führt.
Betrifft:
(ATA 72) Engine - Stages 2 and 3 Low Pressure Turbine Discs - Inspection / Replacement
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen
Luftfahrzeuge 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 Lufttüchtigkeitsan-
weisung EASA AD 2015-0050R1 vom 19.06.2015 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-2002-287R8 Seite 1 von 1 258/2015
EASA AD No.: 2015-0050R1
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2015-0050R1
Date: 19 June 2015
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 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
[EU 1321/2014 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) :
ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG Tay 650-15 and Tay 651-54 engines
TCDS Number: EASA.E.063
Foreign AD: Not applicable
Revision: This AD revises EASA AD 2015-0050 dated 23 March 2015, which superseded
EASA AD 2013-0007 dated 09 January 2013.
Engine – Stages 2 and 3 Low Pressure Turbine Discs – Inspection
ATA 72
/ Replacement
Manufacturer(s): Rolls-Royce plc
Applicability: TAY 650-15 engines, serial numbers (S/N) as identified in Appendix 1 of this
AD, and any other S/N, when installed or previously have been installed in an
aeroplane operated under an air operator certificate (AOC) issued by the
Islamic Republic of Iran and fitted with a low pressure turbine (LPT) module
M05300AA.
TAY 651-54 engines, all S/N, if fitted with a LPT module M05300AA.
These engines are known to be installed on, but not limited to, Fokker F28
Mark 0100 and Boeing 727 series aeroplanes.
Reason: Strip-down of some Tay 650-15 engines revealed excessively corroded stage
2 and stage 3 LPT discs. Subsequent evaluation concluded that the corrosion
was caused by the environment in which these engines had been operated.
This condition, if not detected and corrected, could lead to an uncontained
LPT disc failure, potentially resulting in damage to, and/or reduced control of
the aeroplane.
To address this unsafe condition, Rolls-Royce Deutschland Ltd & Co KG
(RRD) issued Alert Non-Modification Service Bulletin (NMSB) TAY-72-A1524
to provide inspection instructions for stage 2 and stage 3 LPT discs.
Consequently, EASA issued AD 2008-0122 to require repetitive inspections of
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EASA AD No.: 2015-0050R1
stage 2 and stage 3 LPT discs on certain engines. That AD was superseded
by EASA AD 2010-0060 (later revised), which was subsequently superseded
by EASA AD 2013-0007, in both cases to expand the population of affected
engines.
After EASA AD 2013-0007 was issued, it was identified that stage 2 and stage
3 LPT discs corrosion may also affect engines, which were operated in such
an environment in the past.
For the reasons described above, EASA issued AD 2015-0050, retaining the
requirements of EASA AD 2013-0007, which was superseded, and expanded
the AD applicability to include engines, which were previously operated under
these specific environmental conditions.
After that AD was issued, RRD issued Revision 6 of NMSB TAY-72-A1524
introducing a clarification about the counting of the service life accumulated by
the stage 2 and stage 3 LPT discs relevant for accomplishment of inspection
required by that NMSB.
This AD is revised to introduce the new compliance time relevant for
accomplishment of the inspection required by this AD.
Effective Date: Revision 1: 19 June 2015
Original issue: 06 April 2015
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) After 12 April 2010 [the effective date of EASA AD 2010-0060], before
Time(s):
exceeding the threshold as defined in Table 1 of this AD, as applicable ,
and, thereafter, at intervals not to exceed 11 700 FC, inspect the stage 2
and stage 3 LPT discs for corrosion in accordance with the instructions of
RRD NMSB TAY-72-A1524 at Revision 5 (or later approved revisions).
Table 1 Inspection threshold
(Flight cycles (FC) accumulated by the stage 2 and stage 3 LPT discs)
Engine model Compliance time
TAY 651-54 11 700 FC accumulated since new
11 700 FC accumulated since the first installation
TAY 650-15 of the engine on an aeroplane operated under an
AOC issued by the Islamic Republic of Iran
(2) If, during any inspection as required by paragraph (1) of this AD, corrosion
is detected on a stage 2 or stage 3 LPT disc, before release to service of
the engine, replace the affected stage 2 or stage 3 LPT disc, as
applicable, with a serviceable part in accordance with approved
maintenance instructions.
(3) Inspections and corrective actions, accomplished before 06 April 2015
[the effective date of this AD at original issue] in accordance with RRD
NMSB TAY-72-A1524 at Revision 4 (or earlier revisions) are acceptable
to comply with the requirements of paragraphs (1) and (2) of this AD.
For engines which are no longer installed on an aeroplane operated
under an AOC issued by the Islamic Republic of Iran:
(4) Replacement of the affected stage 2 and stage 3 LPT discs as required by
paragraph (2) of this AD constitutes terminating action for repetitive
inspections as required by paragraph (1) of this AD.
Ref. Publications: RRD NMSB TAY-72-A1524, Revision 4, dated 16 November 2012, or
Revision 5, dated 13 February 2015, or Revision 6, dated 16 June 2015.
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EASA AD No.: 2015-0050R1
The use of later approved revisions of this document 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. The original issue of this AD was posted on 19 February 2015 as PAD
15-014 for consultation until 19 March 2015. 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:
Rolls-Royce Deutschland Ltd & Co KG
Eschenweg 11 - 15827 Dahlewitz – Germany
Telephone: +49 (0) 33 7086 1768 ; Fax: +49 (0) 33 7086 3356.
Email: rrd.techhelp@rolls-royce.com.
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EASA AD No.: 2015-0050R1
Appendix 1
List of TAY 650-15 engine S/N’s affected by this AD
17249 17251 17255 17256 17273 17275 17280 17281 17282
17300 17301 17303 17327 17332 17344 17358 17360 17365
17370 17376 17393 17413 17425 17426 17433 17437 17438
17443 17445 17446 17460 17470 17474 17478 17490 17491
17517 17518 17520 17521 17522 17523 17534 17535 17536
17537 17538 17539 17540 17541 17542 17552 17553 17556
17561 17562 17563 17580 17581 17585 17612 17613 17618
17635 17637 17645 17661 17686 17694 17698 17699 17701
17702 17707 17716 17718 17719 17723 17724 17731 17736
17737 17738 17739 17740 17741 17742 17756 17757 17759
17760 17807 17808
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2009-223R3 38144 Braunschweig
EASA AD 2014-0124R1 vom 23.06.2015 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 30.06.2015
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus, Airbus Industrie
Muster: A310, A300-600
Baureihen: Alle A310 und A300-600 Baureihen
Werknummern: Alle
Gerätenummer: 2830, EASA.A.172
Revisionsstand:
Diese LTA ersetzt D-2009-223R2 vom 22.05.2014
Airworthiness Directive der ausländischen Behörde:
EASA AD 2014-0124R1 vom 23.06.2015
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 2009-223R3 ge-
führt.
Betrifft:
(ATA 05) Time Limits and Maintenance Checks - Damage Tolerant Airworthiness Limitation Items - ALS
Part 2 - Amendment
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen
Luftfahrzeuge 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 Lufttüchtigkeitsan-
weisung EASA AD 2014-0124R1 vom 23.06.2015 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-2009-223R3 Seite 1 von 1 266/2015
EASA AD No.: 2014-0124R1
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2014-0124R1
Date: 23 June 2015
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 A300-600 and A310 aeroplanes
TCDS Number: EASA.A.172
Foreign AD: Not applicable
Revision: This AD revises EASA AD 2014-0124 dated 16 May 2014 which superseded
EASA AD 2011-0198 dated 19 October 2011.
Time Limits and Maintenance Checks – Damage Tolerant
ATA 05
Airworthiness Limitation Items – ALS Part 2 – Amendment
Manufacturer(s): Airbus (formerly Airbus Industrie)
Applicability: Airbus A310 and A300-600 aeroplanes, all certified models, all Manufacturer
Serial Numbers.
Reason: The airworthiness limitations applicable to the Damage Tolerant Airworthiness
Limitation Items (DT ALIs) are currently listed in Airbus ALI Documents, which
are referred to in the A300, A310 and A300-600 Airworthiness Limitations
Sections.
Airbus revised the A300 ALI Document, and this issue was approved by EASA.
Airbus A300 ALS Part 2 Revision 01 introduced more restrictive maintenance
requirements and airworthiness limitations, which were identified as mandatory
actions for continued airworthiness.
EASA AD 2011-0198 required compliance with the maintenance requirements
and associated airworthiness limitations defined in the following documents:
- AIRBUS A300 ALI Document issue 04,
- AIRBUS A310 ALI Document issue 08, and
- AIRBUS A300-600 ALI Document issue 13 and Temporary Revision 13.1.
EASA issued AD 2014-0124, retaining the requirements of EASA AD 2011-
0198, which was superseded, and required, for A300 aeroplanes,
implementation of new or more restrictive maintenance instructions and/or
airworthiness limitations as specified in Airbus A300 ALS Part 2 Revision 01.
The requirements for A310 and A300-600 aeroplanes remained unchanged.
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EASA AD No.: 2014-0124R1
Since that AD was issued, Airbus issued A300 ALS Part 2 Revision 02. At the
opportunity of a change in the Airbus ALS procedure, separate ALS ADs will be
published for A300, A310 and A300-600.
This AD is therefore revised to remove A300 aeroplanes from the applicability
(A300 ALS Part 2 covered by AD 2015-0115). This AD will be split with the next
ALS update for A310 or A300-600.
Revision 1: 07 July 2015
Effective Date:
Original issue: 30 May 2014
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance (1) From the effective date of this AD, within the compliance times defined in
Time(s): the Record of Revisions (ROR) pages of the following document, as
applicable to aeroplane model:
- Airbus A300-600 ALI Document issue 13 and Temporary Revision 13.1,
or
- Airbus A310 ALI document Revision 08,
accomplish all applicable maintenance tasks as specified in these
documents.
(2) In case of finding discrepancies (as defined in applicable Airbus
documentation) during accomplishment of any task as required by
paragraph (1) of this AD, within the applicable compliance time specified in
the applicable Airbus documentation, accomplish the applicable
maintenance procedures for corrective actions in accordance with the
approved maintenance documentation. If no compliance time is identified
in the applicable Airbus documentation, accomplish the applicable
corrective actions before next flight. If a detected discrepancy is not
identified in the applicable Airbus documentation, before next flight, contact
Airbus for approved instructions and accomplish those instructions
accordingly.
(3) Compliance with the requirements of paragraphs (1) and (2) of this AD can
be demonstrated by:
(3.1) Revising as follows, the approved Aircraft Maintenance Programme
(AMP) on the basis of which the operator or the owner ensures the
continuing airworthiness of each operated aeroplane:
Incorporate all maintenance requirements and associated
airworthiness limitations specified in
- Airbus A300-600 ALI Document issue 13 and Temporary
Revision 13.1, or
- Airbus A310 ALI Document Revision 08
as applicable to aeroplane model
and
(3.2) Complying with the approved AMP described in paragraph (3.1) of
this AD.
Ref. Publications: Airbus A310 ALI Document issue 08, reference AI/SE-M2/95A.1309/07
approved by EASA on 05 October 2011.
Airbus A300-600 ALI Document issue 13, reference AI/SE-M2/95A.1310/07
approved by EASA on 24 May 2011.
Airbus A300-600 ALI Document TR 13.1, reference AI/SE-M2/95A.1310/07
approved by EASA on 24 May 2011.
The use of later approved variations or revisions of these documents is
acceptable for compliance with the requirements of this AD.
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EASA AD No.: 2014-0124R1
Remarks: 1. If requested and appropriately substantiated, EASA can approve
Alternative Methods of Compliance for this AD.
2. The original issue of this AD was posted on 11 April 2014 as PAD 14-069
for consultation until 09 May 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 SAS – EIAW (Airworthiness Office)
E-mail: continued.airworthiness-wb.external@airbus.com.
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