Nachrichten für Luftfahrer 2016 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2016-0223
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 your designated Rolls-Royce representative, or download the publication from your
Rolls Royce Care account at https://customers.rolls-royce.com.
If you do not have a designated representative or Rolls Royce Care account, please contact
Corporate Communications at Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom
Telephone +44 (0)1332 242424,
or send an email through http://www.rolls-royce.com/contact/civil_team.jsp identifying the
correspondence as being related to Airworthiness Directives.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 4 of 4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2012-139R2 38144 Braunschweig
EASA AD 2016-0227 vom 10.11.2016 Fax: +49-531-2355-5298
email: ad@LBA.de
ROLLS-ROYCE 14.11.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: Rolls-Royce plc
Hersteller: Rolls-Royce plc
Muster: RB211 Trent 500 Series Engines
Baureihen: RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61,
RB211 Trent 556A2-61, RB211 Trent 556B-61, RB211 Trent 556B2-61,
RB211 Trent 560-61 und RB211 Trent 560A2-61
Werknummern: Alle
Die betroffenen Triebwerke sind in Airbus A340-500 und A340-600 Flugzeugen
installiert, aber nicht auf diese beschränkt.
Gerätenummer: 6343, EASA.E.060
Revisionsstand:
Diese LTA ersetzt D-2012-139R1 vom 16.11.2012
Airworthiness Directive der ausländischen Behörde:
EASA AD 2016-0227 vom 10.11.2016
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 2012-139R2 geführt.
Betrifft:
(ATA 73) Engine - Low Pressure Fuel Tubes, Clips and Fuel Oil Heat Exchanger Mounts - Inspection
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
EASA AD 2016-0227 vom 10.11.2016 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-2012-139R2 Seite 1 von 1 519/2016
EASA AD No.: 2016-0227
Airworthiness Directive
AD No.: 2016-0227
Issued: 10 November 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):
ROLLS-ROYCE plc RB211 Trent 500 engines
Effective Date: 24 November 2016
TCDS Number(s): EASA.E.060
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2012-0237R1 dated 14 November 2012.
ATA 73 – Engine – Low Pressure Fuel Tubes, Clips and Fuel Oil Heat Exchanger
Mounts – Inspection
Manufacturer(s):
Rolls-Royce plc (RR)
Applicability:
RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61 and 560A2-61
engines, all serial numbers.
These engines are known to be installed on, but not limited to, Airbus A340-500 and A340-600
series aeroplanes.
Reason:
Fuel leaks from the low pressure (LP) fuel tubes, which run between the LP fuel pumps and high
pressure (HP) fuel pumps, occurred in-service. The results of subsequent technical investigations
showed that these were caused by frettage between the securing clips and the LP fuel tube outer
surface, which reduces the fuel tube thickness, leading to fracture of the fuel tube and consequent
fuel leak.
This condition, if not detected early enough or if not correctly managed, could lead to critical fuel
unbalance or in-flight fuel starvation. Fuel leak detection and the associated aeroplane procedures
can be complex, leading to some flight crews failing to detect and/or address such situations.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 4
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An agency of the European Union
EASA AD No.: 2016-0227
To address this potential unsafe condition, RR published Alert Non-Modification Service Bulletin
(NMSB) RB.211-73-AG797 to provide inspection instructions as a precautionary measure to mitigate
the risk of in-flight fuel starvation. Consequently, EASA issued AD 2011-0243 to require a one-time
on-wing inspection of the LP fuel tubes and the associated clips and, depending on findings,
replacement of the affected parts with serviceable parts.
After that AD was issued, further engineering evaluation based on the reported inspection results
showed the need for repetitive inspections. Prompted by these findings, RR published Alert NMSB
RB.211-73-AG948 to provide inspection instructions, and EASA issued AD 2012-0237 (later revised),
retaining the requirements of EASA AD 2011-0243, which was superseded, and introduced
additional repetitive inspections of LP fuel tubes, clips and fuel-to-oil heat exchanger (FOHE) mounts
and, depending on findings, accomplishment of applicable corrective action(s).
Since EASA AD 2012-0237R1 was issued, further evaluation of the reported inspection results
showed the need to correct some technical instructions and to reduce the inspection interval.
Prompted by these findings, RR issued Alert NMSB RB.211-73-AG948 Revision 2 to provide those
amended instructions, and Revision 3 to revise the associated compliance times.
For the reasons described above, this AD retains the requirements of EASA AD 2012-0237R1, which
is superseded, but requires the use of the instructions as provided in the NMSB.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Note 1: Where, in this AD, reference is made to an RR Mod, SB or NMSB with an ‘A’ (Alert) in the
number, it should be recognised that an earlier or later revision may not have that ‘A’. This kind of
change does not effectively alter the publication references for the purpose of this AD.
Note 2: RR Alert NMSB RB.211-73-AG948 Revision 3 is hereafter referred to as ‘the NMSB’ in this
AD.
On-wing Inspections:
(1) Within the compliance time specified in Table 1 of this AD, as applicable, and, thereafter, at
intervals not to exceed 5 000 engine flight hours (EFH), accomplish an on-wing inspection of the
LP fuel tubes, clips and FOHE mounts (hereafter referred to as ‘the affected parts’ in this AD) in
accordance with the instructions of Section 3 of the NMSB.
Table 1 – Initial On-Wing Inspection (see Note 3 of this AD)
EFH Accumulated Compliance Time
Within 800 EFH after the effective date of this AD, or before
Less than 5 000 EFH
exceeding 5 000 EFH, whichever occurs later
Within 800 EFH after the effective date of this AD, or before
5 000 EFH or more
exceeding 6 000 EFH, whichever occurs first
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 4
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An agency of the European Union
EASA AD No.: 2016-0227
Note 3: Unless stated otherwise, the EFH specified in Table 1 are those accumulated by the engine,
on the effective date of this AD, since the accomplishment of one of the following, whichever
occurred latest:
(i) Embodiment of RR SB RB.211-73-F737 (any revision) or RB.211-73-F738 (any revision).
(ii) Last inspection in accordance with NMSB RB.211-73-AG797 (any revision).
(iii) Last inspection in accordance with NMSB RB.211-73-G723 (any revision).
(iv) Last inspection in accordance with NMSB RB.211-73-AG948 (any revision).
Corrective Action(s):
(2) If, during any inspection as required by paragraph (1) of this AD, any discrepancy is identified,
before next flight, replace the defective or damaged parts with serviceable parts in accordance
with the instructions of Section 3 of the NMSB.
In-shop Inspection(s) / Corrective Action(s):
(3) From the effective date of this AD, during each qualified shop visit (see Note 4 of this AD) and
during each engine overhaul, inspect the affected parts in accordance with the instructions of
Section 3 of the NMSB and, depending on findings, accomplish all applicable corrective actions
before release to service of the engine.
Note 4: For the purpose of this AD, a qualified shop visit is defined as any shop visit for an engine
subject to a Level 1 to Level 4 workscope, as defined by the Trent 500 Generic Engine Management
Programme (RM1870 Issue 28), and includes ‘hospital’ shop visits.
Note 5: A shop visit inspection as required by paragraph (3) of this AD may be accomplished as a
substitute to an on-wing inspection as required by paragraph (1) of this AD.
(4) If, on the effective date of this AD, an engine is in a qualified shop visit (see Note 4 of this AD),
before release to service of that engine, inspect the affected parts and, depending on findings,
accomplish all applicable corrective actions in accordance with the instructions of Section 3 of
the NMSB.
Ref. Publications:
Rolls-Royce NMSB RB.211-73-AG948 original issue dated 28 September 2012, or Revision 1
dated 10 June 2013, or Revision 2 dated 01 August 2016, or Revision 3 dated 09 September 2016.
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. This AD was posted on 20 September 2016 as PAD 16-135 for consultation until 18 October
2016. The Comment Response Document can be found at http://ad.easa.europa.eu.
3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2016-0227
4. For any question concerning the technical content of the requirements in this AD, please
contact your designated Rolls-Royce representative, or download the publication from your
Rolls Royce Care account at https://customers.rolls-royce.com.
If you do not have a designated representative or Rolls-Royce Care account, please contact
Corporate Communications at Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom
Telephone +44 (0)1332 242424, or
send an email through http://www.rolls-royce.com/contact/civil_team.jsp identifying the
correspondence as being related to Airworthiness Directives.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 4 of 4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2013-039R1 38144 Braunschweig
FAA AD 2016-22-11 - Amdt. 39-18700 Fax: +49-531-2355-5298
email: ad@LBA.de
ENGINE ALLIANCE 07.11.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: Engine Alliance LLC
Hersteller: GE Aviation, Pratt & Whitney Division
Muster: GP7200
Baureihen: GP7270 und GP7277
Werknummern: Betroffen sind Triebwerke, die mit "High Pressure Turbine (HPT) Stage 2
Nozzle Segment" mit den Hersteller-Teilenummern (P/N) 2101M24G01,
2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05 oder 2101M24G06
ausgerüstet sind.
Gerätenummer: EASA.IM.E.026, FAA TCDS E00072EN
Revisionsstand:
Diese LTA ersetzt D-2013-039 vom 08.02.2013
Airworthiness Directive der ausländischen Behörde:
FAA AD 2016-22-11 - Amdt. 39-18700
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 2013-039R1 geführt.
Betrifft:
(ATA 72) High Pressure Turbine Stage 2 Nozzles - 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 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 2016-22-11 - Amdt. 39-18700 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-2013-039R1 Seite 1 von 1 504/2016
[Federal Register Volume 81, Number 211 (Tuesday, November 1, 2016)]
[Rules and Regulations]
[Pages 75684-75686]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-26280]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1293; Directorate Identifier 2012-NE-45-AD; Amendment 39-18700;
AD 2016-22-11]
RIN 2120-AA64
Airworthiness Directives; Engine Alliance Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
––––––––––––––––––––––––––––––––––
SUMMARY: We are superseding airworthiness directive (AD) 2013-02-06 for all Engine Alliance
(EA) GP7270 and GP7277 turbofan engines with certain part number (P/N) high-pressure turbine
(HPT) stage 2 nozzle segments installed. AD 2013-02-06 required initial and repetitive borescope
inspections (BSI) and removal from service of these nozzles before further flight if one or more burn
holes were detected in any HPT stage 2 nozzle segment. AD 2013-02-06 also required removal from
service of these HPT stage 2 nozzle segments at the next engine shop visit. This AD requires the
same inspections as AD-2013-02-06, requires removal of affected HPT stage 2 nozzles at next piece-
part exposure, and adds certain P/Ns to the applicability. This AD was prompted by another report of
inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage
2 nozzle, burn-through of the turbine case, and in-flight shutdown. We are issuing this AD to prevent
HPT stage 2 nozzle failure, uncontrolled fire, in-flight shutdown, and damage to the airplane.
DATES: This AD is effective November 16, 2016.
We must receive any comments on this AD by December 16, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by
any of the following methods:
• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for
submitting comments.
• Fax: 202-493-2251.
• Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
1
• Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2012-1293; or in person at the Docket Management Facility between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD,
the regulatory evaluation, any comments received, and other information. The street address for the
Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Martin Adler, Aerospace Engineer, Engine &
Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7157;
fax: 781-238-7199; email: martin.adler@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On January 15, 2013, we issued AD 2013-02-06, Amendment 39-17327 (78 FR 5710, January
28, 2013), (''AD 2013-02-06''), for all Engine Alliance GP7270 and GP7277 turbofan engines with an
HPT stage 2 nozzle, P/N 2101M24G01, 2101M24G02, or 2101M24G03, installed. AD 2013-02-06
required initial and repetitive BSIs and removal from service of these nozzles before further flight if
any burn holes were detected in the affected nozzles. AD 2013-02-06 also required removal from
service of the affected nozzles at the next engine shop visit. AD 2013-02-06 resulted from a report of
inadequate cooling of the HPT stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-
through of the turbine case, and in-flight shutdown. We issued AD 2013-02-06 to prevent HPT stage
2 nozzle failure, uncontrolled fire, in-flight shutdown, and damage to the airplane.
Actions Since AD 2013-02-06 Was Issued
Since we issued AD 2013-02-06, we received another report of inadequate cooling of the HPT
stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the
turbine case, and in-flight shutdown. This event occurred with HPT stage 2 nozzle, P/N
2101M24G04, 2101M24G05, or 2101M24G06 installed. Investigation revealed that the event was
caused by damage to the HPT stage 2 nozzle due to inadequate part cooling. We are issuing this AD
to prevent HPT stage 2 nozzle failure, uncontrolled fire, in-flight shutdown, and damage to the
airplane.
Related Service Information
We reviewed EA Service Bulletins EAGP7-72-190, dated December 6, 2012 and EAGP7-72-
262, Revision No. 5, dated December 18, 2015. This service information describes procedures for
inspecting the HPT stage 2 nozzle segments.
FAA's Determination
We are issuing this AD because we evaluated all the relevant information and determined the
unsafe condition described previously is likely to exist or develop in other products of the same type
design.
2
AD Requirements
This AD requires initial and repetitive BSIs of the HPT stage 1 shroud and HPT stage 2 nozzle
segments and removal from service of these nozzle segments before further flight if one or more burn
holes are detected on the HPT stage 2 nozzle or if the HPT stage 1 shroud is found distorted. This AD
also requires removal from service of any HPT stage 2 nozzle segment, P/N 2101M24G01,
2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, or 2101M24G06, at next piece-part
exposure.
FAA's Justification and Determination of the Effective Date
No domestic operators use this product. Therefore, we find that notice and opportunity for prior
public comment are unnecessary and that good cause exists for making this amendment effective in
less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight safety, and we did not provide
you with notice and an opportunity to provide your comments before it becomes effective. However,
we invite you to send any written data, views, or arguments about this AD. Send your comments to
an address listed under the ADDRESSES section. Include the docket number FAA-2012-1293 and
Directorate Identifier 2012-NE-45-AD at the beginning of your comments. We specifically invite
comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We
will consider all comments received by the closing date and may amend this AD because of those
comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including
any personal information you provide. We will also post a report summarizing each substantive
verbal contact we receive about this AD.
Costs of Compliance
We estimate that this AD will affect no engines installed on airplanes of U.S. registry. We also
estimate that it will take about two hours per engine to perform a BSI of the HPT stage 2 nozzle. The
average labor rate is $85 per hour. Required parts cost about $504,486 per engine. Based on these
figures, we estimate the cost of this AD to U.S. operators to be $0.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order 13132. This AD will not
have a substantial direct effect on the States, on the relationship between the national government and
3
