Nachrichten für Luftfahrer 2018 Teil 2 (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2018-085 38144 Braunschweig
EASA AD 2018-0071 vom 26.03.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
CFM INTERNATIONAL 29.03.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: CFM International S.A.
Hersteller: SAFRAN Aircraft Engines, vormals SNECMA (Frankreich) und
General Electric Aircraft Engines (U.S.A.)
Muster: CFM56-7B
Baureihen: CFM56-7B20, CFM56-7B22, CFM56-7B22/B1, CFM56-7B24, CFM56-7B24/B1,
CFM56-7B26, CFM56-7B26/B1, CFM56-7B26/B2, CFM56-7B27, CFM56-
7B27/B1, CFM56-7B27/B3, CFM56-7B20/2, CFM56-7B22/2, CFM56-7B24/2,
CFM56-7B26/2, CFM56-7B27/2, CFM56-7B20/3, CFM56-7B22/3, CFM56-
7B22/3B1, CFM56-7B24/3, CFM56-7B24/3B1, CFM56-7B26/3, CFM56-
7B26/3B1, CFM56-7B26/3B2, CFM56-7B27/3, CFM56-7B27/3B1, CFM56-
7B27/3B1F, CFM56-7B27/3B3, CFM56-7B26/3F, CFM56-7B26/3B2F, CFM56-
7B27/3F, CFM56-7B20E, CFM56-7B22E, CFM56-7B22E/B1, CFM56-7B24E,
CFM56-7B24E/B1, CFM56-7B26E, CFM56-7B26E/B1, CFM56-7B26E/B2,
CFM56-7B27E, CFM56-7B27E/B1, CFM56-7B27E/B3, CFM56-7B26E/F,
CFM56-7B26E/B2F, CFM56-7B27E/F und CFM56-7B27E/B1F
Werknummern: Alle
Die betroffenen Triebwerke sind in Boeing 737-600, 737-700, 737-800 und
737-900 Flugzeugen installiert, aber nicht auf diese beschränkt.
Gerätenummer: 6337, EASA.E.004
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2018-0071 vom 26.03.2018
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 2018-085 geführt.
Betrifft:
(ATA 72) Engine - Fan Blades - 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 2018-0071 vom 26.03.2018 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-2018-085 Seite 1 von 1 162/2018
EASA AD No.: 2018-0071
Airworthiness Directive
AD No.: 2018-0071
Issued: 26 March 2018
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):
CFM INTERNATIONAL S.A. CFM56-7B engines
Effective Date: 02 April 2018
TCDS Number(s): EASA.E.004
Foreign AD: Not applicable
Supersedure: None
ATA 72 – Engine – Fan Blades – Inspection
Manufacturer(s):
SAFRAN Aircraft Engines, formerly SNECMA (France); General Electric Aircraft Engines (United
States)
Applicability:
CFM56-7B20, CFM56-7B22, CFM56-7B22/B1, CFM56-7B24, CFM56-7B24/B1, CFM56-7B26,
CFM56-7B26/B1, CFM56-7B26/B2, CFM56-7B27, CFM56-7B27/B1, CFM56-7B27/B3, CFM56-7B20/2,
CFM56-7B22/2, CFM56-7B24/2, CFM56-7B26/2, CFM56-7B27/2, CFM56-7B20/3, CFM56-7B22/3,
CFM56-7B22/3B1, CFM56-7B24/3, CFM56-7B24/3B1, CFM56-7B26/3, CFM56-7B26/3B1,
CFM56-7B26/3B2, CFM56-7B27/3, CFM56-7B27/3B1, CFM56-7B27/3B1F, CFM56-7B27/3B3,
CFM56-7B26/3F, CFM56-7B26/3B2F, CFM56-7B27/3F, CFM56-7B20E, CFM56-7B22E,
CFM56-7B22E/B1, CFM56-7B24E, CFM56-7B24E/B1, CFM56-7B26E, CFM56-7B26E/B1,
CFM56-7B26E/B2, CFM56-7B27E, CFM56-7B27E/B1, CFM56-7B27E/B3, CFM56-7B26E/F,
CFM56-7B26E/B2F, CFM56-7B27E/F and CFM56-7B27E/B1F engines, all serial numbers.
These engines are known to be installed on, but not limited to, Boeing 737-600, 737-700, 737-800
and 737-900 aeroplanes.
Definitions:
For the purpose of this AD, the following definitions apply:
The SB: CFM International CFM56-7B Service Bulletin (SB) No. 72-1024.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2018-0071
Affected fan blade: a fan blade having Part Number (P/N) 340-001-022-0, P/N 340-001-027-0,
P/N 340-001-029-0, P/N 340-001-037-0 or P/N 340-001-039-0.
Serviceable fan blade: a not affected fan blade; or an affected fan blade which is new, or which
passed an inspection in accordance with the instructions of the SB, or of CFM56-7B SB No. 72-1019,
or an eddy current inspection (ECI) in accordance with CFM International Engine Shop Manual
(ESM) task 72-21-01-200-001 Revision 55 or later.
Reason:
An occurrence was reported of fan blade failure on a CFM56-7B engine. The released fan blade was
initially contained by the engine case, but there was subsequent uncontained forward release of
debris and separation of the inlet cowl. Preliminary investigation determined that the fracture in
the blade initiated from the fan blade dovetail.
This condition, if not detected and corrected, could lead to fan blade failure, possibly resulting in
uncontained forward release of debris, with consequent damage to the engine and the aeroplane.
To address this potential unsafe condition, CFM International issued CFM56-7B SB No. 72-1019,
later revised, and CFM56-7B SB No. 72-1024, providing inspection instructions.
For the reason described above, this AD requires a one-time inspection of certain fan blades, and,
depending on findings, accomplishment of applicable corrective action(s).
This AD is considered an interim action and further AD action may follow.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Inspection:
(1) Within 9 months after the effective date of this AD, accomplish an ultrasonic inspection of each
affected fan blade in accordance with the instructions of the SB.
Corrective Action(s):
(2) If, during the inspection as required by paragraph (1) of this AD, any discrepancy is detected on
a fan blade, before next flight, or before release to service of the engine, as applicable, replace
that fan blade with a serviceable part in accordance with the instructions of the SB.
Credit:
(3) Accomplishment of ECI of a fan blade of an engine in accordance with CFM International ESM
task 72-21-01-200-001 Revision 55 or later is acceptable to comply with the requirements of
paragraph (1) of this AD, as applicable, for that fan blade.
(4) Inspections and corrective actions accomplished on an engine in accordance with the
instructions of CFM56-7B SB No. 72-1019 are acceptable to comply with the requirements of
paragraphs (1) and (2) of this AD for that engine.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2018-0071
Part installation:
(5) From the effective date of this AD, it is allowed to install a fan blade on an engine, provided it is
serviceable.
Ref. Publications:
CFM International S.A. CFM56-7B SB No. 72-1019 original issue dated 24 March 2017, or Revision 01
dated 13 June 2017.
CFM International S.A. CFM56-7B SB No. 72-1024 original issue dated 26 July 2017.
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 29 September 2017 as PAD 17-132 for consultation until 27 October
2017, and republished on 05 March 2018 for additional consultation until 19 March 2018. The
Comment Response Document 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:
CFM SA Customer Support Centre, Telephone: +33 1 64 14 88 66, Fax: +33 1 64 79 85 55
E-mail: cfm.csc@safrangroup.com.
or
CFM Inc. Aviation Operations Centre, Telephone: +1 513-552-3272, or +1 877-432-3272,
Fax: +1 877-432-3329, E-mail: geae.aoc@ge.com, or aviation.fleetsupport@ge.com.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 3
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-2018-086 38144 Braunschweig
EASA AD 2018-0065 vom 23.03.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS HELICOPTERS 03.04.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: AIRBUS HELICOPTERS
Hersteller: Airbus Helicopters (vormals Eurocopter, Eurocopter France, Aerospatiale)
Muster: SA 330
Baureihen: SA 330 J
Werknummern: Alle
Gerätenummer: 3043, EASA.R.002
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2018-0065 vom 23.03.2018
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 2018-086 geführt.
Betrifft:
(ATA 05) Time Limits / Maintenance Checks - Main Gearbox / Particle Detectors - 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 2018-0065 vom 23.03.2018 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-2018-086 Seite 1 von 1 169/2018
EASA AD No.: 2018-0065
Airworthiness Directive
AD No.: 2018-0065
Issued: 23 March 2018
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 HELICOPTERS SA 330 helicopters
Effective Date: 30 March 2018
TCDS Number(s): EASA.R.002
Foreign AD: Not applicable
Supersedure: None
ATA 05 – Time Limits / Maintenance Checks – Main Gearbox / Particle Detectors –
Inspection
Manufacturer(s):
Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aérospatiale)
Applicability:
SA 330 J helicoptes, all serial numbers.
Definitions:
For the purpose of this AD, the following definitions apply:
The ASB: Airbus Helicopters (AH) Alert Service Bulletin (ASB) SA330-05.103.
ALF: After last flight of the day (ALF) inspection.
Reason:
Investigation prompted by an EC 225 helicopter accident revealed involvement of a failure of a
second stage planet gear of the Main Gearbox (MGB).
AH is reviewing its entire range of helicopters in regard to this particular issue.
As a precautionary measure, AH issued the ASB, applicable to SA 330 J helicopters, providing
updated inspection intervals and particle assessment criteria, aligning the SA 330 J particle
inspection to the standards set for EC 225 LP/AS 332 L2 helicopters.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2018-0065
For the reason described above, this AD requires repetitive inspections of the MGB particle detector
and, depending on findings, analysis of particles found and accomplishment of applicable corrective
action(s).
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Inspections / Analyses:
(1) From the effective date of this AD, during each ALF inspection, or at intervals not to exceed 10
flight hours, whichever occurs first, inspect the MGB particle detector in accordance with the
instructions of Section 3 of the ASB.
(2) If, during any inspection as required by paragraph (1) of this AD, particles are detected, before
next flight, analyse the particles in accordance with the instructions of Appendix 4.A. of the
ASB.
Corrective Action(s):
(3) If, during any analysis as required by paragraph (2) of this AD, particles are detected which
exceed the limits specified in Appendix 4.A. of the ASB, before next flight, accomplish the
applicable corrective action(s) in accordance with the instructions of Appendix 4.A. of the ASB.
Terminating Action:
(4) None.
Parts Installation:
(5) From the effective date of this AD, it is allowed to install an MGB assembly on any helicopter,
provided that, following installation, it is inspected as required by this AD.
Ref. Publications:
AH ASB SA330-05.103 original issue dated 20 March 2018.
The use of later approved revisions of the above-mentioned 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. 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 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 Helicopters (EBSESB) – Aéroport de Marseille Provence, 13725 Marignane
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2018-0065
Cedex, France; Telephone +33 (4) 42 85 97 97; Fax +33 (4) 42 85 99 66;
E-mail: Directive.technical-support@airbus.com.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 3
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-2018-087 38144 Braunschweig
EASA AD 2018-0066 vom 23.03.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS HELICOPTERS 03.04.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: AIRBUS HELICOPTERS
Hersteller: Airbus Helicopters (vormals Eurocopter, Eurocopter France, Aerospatiale)
Muster: AS 332
Baureihen: AS 332 L, AS 332 L1, AS 332 C und AS 332 C1
Werknummern: Alle
Gerätenummer: 3043, EASA.R.002
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2018-0066 vom 23.03.2018
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 2018-087 geführt.
Betrifft:
(ATA 05) Time Limits / Maintenance Checks - Main Gearbox / Particle Detectors - Inspection
(ATA 63) Main Rotor Drive - Planet Gear Assemblies - 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
EASA AD 2018-0066 vom 23.03.2018 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-2018-087 Seite 1 von 1 171/2018
EASA AD No.: 2018-0066
Airworthiness Directive
AD No.: 2018-0066
Issued: 23 March 2018
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 HELICOPTERS AS 332 helicopters
Effective Date: 30 March 2018
TCDS Number(s): EASA.R.002
Foreign AD: Not applicable
Supersedure: None
ATA 05 – Time Limits / Maintenance Checks – Main Gearbox / Particle Detectors –
Inspection
ATA 63 – Main Rotor Drive – Planet Gear Assemblies – Replacement
Manufacturer(s):
Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aérospatiale)
Applicability:
AS 332 L, AS 332 L1, AS 332 C and AS 332 C1 helicopters, all serial numbers.
Definitions:
For the purpose of this AD, the following definitions apply:
The ASB: Airbus Helicopters (AH) Alert Service Bulletin (ASB) AS332-05.01.08
Affected MGB: A Main Gearbox (MGB) equipped with at least one Type A second stage planet gear,
identified by part number (P/N) in Appendix 4.B of the ASB.
Serviceable MGB: An MGB equipped with Type B second stage planet gears only, identified by P/N
in Appendix 4.B of the ASB.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
