Nachrichten für Luftfahrer 2017 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2017-0057
Recording AD compliance:
(5) When the AMP of a helicopter has been revised as required by paragraph (3) or (4) of this AD,
as applicable, that action ensures (see Note of this AD) continued accomplishment of the tasks
as required by paragraphs (1) and (2) of this AD for that helicopter. Consequently, after revising
the AMP, as required by paragraph (3) or (4) of this AD, as applicable, it is not necessary that
accomplishment of individual action is recorded for demonstration of AD compliance on a
continued basis.
Note: For affected PZL W-3A helicopters registered in Europe, complying with the approved AMP, as
specified in paragraph (3) or (4) of this AD, as applicable, is required by Commission Regulation (EU)
No 1321/2014, Part M.A.301, paragraph 3.
Ref. Publications:
PZL W-3A AE 30.04.20.1 MM (English) Chapter 4, Revision 13, dated January 2017.
PZL W-3A AE 30.04.20.1 IOT (Polish), Chapter 4, Revision 12, dated July 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 07 March 2017 as PAD 17-024 for consultation until 04 April 2017. No
comments were received during the consultation period.
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: WSK "PZL- Świdnik" S.A., Al. Lotników Polskich 1, 21-045 Świdnik, Poland
Facsimile +48 81722 5710, Telephone +48 81722 6112
E-mail: jerzy.klimkowski@leonardocompany.com.
TE.CAP.00110-005 © 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-2017-029R2 38144 Braunschweig
EASA Emergency AD 2017-0064-E vom Fax: +49-531-2355-5298
12.04.2017 email: ad@LBA.de
SAFRAN HELICOPTER ENGINES 12.04.2017
DRINGEND!
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: SAFRAN HELICOPTER ENGINES
Hersteller: SAFRAN Helicopter Engines (vormals Turbomeca S.A.)
Muster: ARRIEL 1
Baureihen: ARRIEL 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K, 1K1, 1S und 1S1
Werknummern: Alle
Die betroffenen Triebwerke sind in folgenden Hubschraubern installiert, aber
nicht auf diese beschränkt: Airbus Helicopters (vormals Eurocopter, Eurocopter
France, Aerospatiale) AS 350 B, BA, BB, B1 und B2, AS 365 und SA 365 (alle
Baureihen, außer AS 365 N3), Airbus Helicopters Deutschland (vormals
Eurocopter Deutschland, Messerschmitt-Bölkow-Blohm) MBB-BK-117-C1 und -
C2, Leonardo (vormals AgustaWestland, Agusta) A109K2 und Sikorsky S-76A.
Gerätenummer: 7010, EASA.E.073
Revisionsstand:
Diese LTA ersetzt D-2017-029R1 vom 23.02.2017
Airworthiness Directive der ausländischen Behörde:
EASA Emergency AD 2017-0064-E vom 12.04.2017
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 2017-029R2 geführt.
Betrifft:
(ATA 73) - Engine Fuel & Control - Drain Valve Assembly - 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
EASA Emergency AD 2017-0064-E vom 12.04.2017 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-2017-029R2 Seite 1 von 1 146/2017
EASA AD No.: 2017-0064-E
Emergency Airworthiness Directive
AD No.: 2017-0064-E
Issued: 12 April 2017
Note: This Emergency 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):
SAFRAN HELICOPTER ENGINES ARRIEL 1 engines
Effective Date: 14 April 2017
TCDS Number(s): EASA.E.073
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2017-0019R1 dated 22 February 2017.
ATA 73 – Engine Fuel & Control – Drain Valve Assembly – Inspection / Replacement
Manufacturer(s):
SAFRAN Helicopter Engines, S.A. (formerly Turbomeca, S.A.)
Applicability:
ARRIEL 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K, 1K1, 1S and 1S1 engines, all serial numbers.
These engines are known to be installed on, but not limited to, Airbus Helicopters (formerly
Eurocopter, Eurocopter France, Aerospatiale) AS 350 B, BA, BB, B1 and B2, AS 365 and SA 365 (all
models, except AS 365 N3), Airbus Helicopters Deutschland (formerly Eurocopter Deutschland,
Messerschmitt-Bölkow-Blohm) MBB-BK117-C1 and -C2, Leonardo (formerly AgustaWestland,
Agusta) A 109 K2, and Sikorsky S-76A helicopters.
Reason:
Some fuel leaks were reported originating from the drain valve (DV) assembly on certain ARRIEL 1
engines. Investigation results revealed that these fuel leaks had been caused by a non-compliant
diaphragm holes position.
This condition, if not detected and corrected, could lead to fuel spraying on engine hot section and
fire, possibly resulting in a commanded in-flight shut-down with consequent emergency
autorotation landing on single engine helicopter.
TE.CAP.00111-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 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.: 2017-0064-E
To address this potential unsafe condition, SAFRAN Helicopter Engines published Mandatory Service
Bulletin (MSB) 292 73 0851, providing instructions to identify the affected DV, temporary measures
(wrapping) and repetitive inspections, and removal from service of the affected DV.
Consequently, EASA issued Emergency AD 2017-0019-E (later revised) to require replacement of the
affected DV, or wrapping and repetitive inspections, pending replacement of the affected DV. After
that AD was issued, SAFRAN Helicopter Engines developed a new alternative solution to the DV
replacement and published MSB 292 73 0851 version B for in-service introduction of that
alternative. Consequently, EASA issued AD 2017-0019R1 to introduce the wrap of the affected DV
with heat-shrinkable tubing, as a new alternative method, pending DV replacement.
After that AD was issued, additional fuel leak events were reported on DV assemblies which were
equipped with compliant diaphragm hole positions. Subsequent investigation results revealed that
these fuel leaks were actually caused by the fact that the diaphragm of the affected DV is more
sensitive to operation stress than the previous design diaphragm.
To address this potential unsafe condition, SAFRAN Helicopter Engines published MSB 292 73 0853,
providing instructions to identify, inspect and correct the affected DV.
For the reasons described above, this AD supersedes EASA AD 2017-0019R1, to require a one-time
visual inspection of the affected DV, followed by repetitive inspections and, depending on findings,
accomplishment of applicable corrective action(s).
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Note 1: SAFRAN Helicopter Engines MSB 292 73 0853 (any version) is hereafter referred to as ‘the
MSB’ in this AD.
Note 2: For the purpose of this AD, an affected DV, subject to inspections and wrapping, is a DV
manufactured, repaired or overhauled on or after 01 January 2016.
Note 3: For the purpose of this AD, a serviceable DV is an unaffected DV (see Note 2 of this AD) or
an affected DV that is wrapped and leak-free in accordance with the instructions of the MSB.
Note 4: The MSB introduces an extended service limit for certain DV that are not subject to the
inspections and wrapping. This AD does not impose that limit.
Inspection:
(1) Within 10 flight hours (FH) or 7 days, whichever occurs first after the effective date of this AD,
visually inspect the affected DV in accordance with the instructions of the MSB.
Corrective Action(s):
(2) If, during the inspection as required by paragraph (1) of this AD, a fuel leak is detected, before
next flight, replace the affected DV with a serviceable DV (see Note 3 of this AD) in accordance
with the instructions of the MSB.
TE.CAP.00111-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 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.: 2017-0064-E
(3) If, during the inspection as required by paragraph (1) of this AD, no fuel leak is detected,
before next flight, wrap the affected DV with a self-amalgamate tape or with a heat shrinkable
tubing in accordance with the instructions of the MSB.
Repetitive Inspections:
(4) Before next flight after wrapping of an affected DV, as required by paragraph (3) of this AD,
and, thereafter, before each first flight of the day, inspect the affected DV in accordance with
the instructions of the MSB.
Corrective Action(s):
(5) If, during any inspection as required by paragraph (4) of this AD, a fuel leak is detected, before
next flight, replace the affected DV with a serviceable DV (see Note 3 of this AD) in accordance
with the instructions of the MSB.
(6) If, during any inspection as required by paragraph (4) of this AD, the wrapping is found
defective, before next flight, remove the wrap and re-wrap the affected DV in accordance
with the instructions of the MSB.
Credit:
(7) Inspections and corrective actions (including any wrapping of a DV) on an engine,
accomplished before the effective date of this AD in accordance with the instructions of
SAFRAN Helicopter Engines MSB 292 73 0851, is acceptable to comply with the initial
requirements of this AD for that engine.
Part(s) Installation:
(8) From the effective date of this AD, it is allowed to install a DV on an engine, provided it is a
serviceable DV (see Note 3 of this AD).
Terminating Action:
(9) Replacement on an engine of an affected DV, as required by paragraph (5) of this AD, does not
constitute terminating action for the repetitive inspections as required by paragraph (4) of
this AD for that engine.
Ref. Publications:
SAFRAN Helicopter Engines MSB 292 73 0853 version A dated 07 April 2017.
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 results of the safety assessment have indicated the need for immediate publication and
notification, without the full consultation process.
TE.CAP.00111-005 © 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.: 2017-0064-E
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 nearest SAFRAN Helicopter Engines technical representative or connect to
www.tools.safran-helicopter-engines.com.
TE.CAP.00111-005 © 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-2017-070R1 38144 Braunschweig
ANAC BAD 2017-03-01 "Adoption Suspended" und Fax: +49-531-2355-5298
EASA Decision zur ANAC BAD 2017-03-01 vom email: ad@LBA.de
07.04.2017
EMBRAER 11.04.2017
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Embraer S.A.
Hersteller: EMBRAER
Muster: ERJ 170
ERJ 190
Baureihen: ERJ 170-100 LR, ERJ 170-100 SE, ERJ 170-100 STD, ERJ 170-100 SU,
ERJ 170-200 LR, ERJ 170-200 STD und ERJ 170-200 SU.
ERJ 190-100 STD, ERJ 190-100 LR, ERJ 190-100 IGW, ERJ 190-100 SR,
ERJ 190-200 STD, ERJ 190-200 LR und ERJ 190-200 IGW.
Werknummern: Gemäß Embraer Service Bulletin (SB) 170-53-0051 Revision 3 vom 21.08.2013
und Embraer Service Bulletin (SB) 190-53-0019 Revision 3 vom 21.08.2013
Gerätenummer: EASA.IM.A.001, EASA.IM.A.071
Revisionsstand:
Diese LTA ersetzt D-2017-070 vom 21.03.2017
Airworthiness Directive der ausländischen Behörde:
ANAC BAD 2017-03-01 "Adoption Suspended" und
EASA Decision zur ANAC BAD 2017-03-01 vom 07.04.2017
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 2017-070R1 geführt.
Betrifft:
BR-2017-03-01 : EASA ADOPTION SUSPENDED - DECISION ATTACHED
Hinweis: Mit der "EASA Decision to Suspend Adoption of ANAC AD 2017-03-01" vom 07.04.2017 wurde die
vorläufige Rücknahme der brasilianischen ANAC AD 2017-03-01 durch die EASA bekanntgegeben. Bis zu einer
endgültigen Entscheidung der EASA, ist eine Durchführung der ANAC AD 2017-03-01 nicht vorgeschrieben.
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
ANAC BAD 2017-03-01 "Adoption Suspended" und
EASA Decision zur ANAC BAD 2017-03-01 vom 07.04.2017 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.
D-2017-070R1 Seite 1 von 2 143/2017
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-2017-070R1 Seite 2 von 2 143/2017
EASA Decision to Suspend
Adoption of ANAC AD 2017-03-01
EASA considerations, leading to the decision to suspend adoption of ANAC AD 2017-03-01
On 10 March 2017, the Agência Nacional de Aviação Civil (ANAC) of Brazil disseminated
AD 2017-03-01, applicable to Embraer S.A. ERJ 170 and ERJ 190 aeroplanes.
That AD, which requires repetitive inspections of the forward pressure bulkhead, and a
reinforcement modification to prevent fatigue cracking, was adopted by the Agency under the
provisions of ED Decision 02/2003.
Since that AD was issued, operator comments have indicated that this AD includes references to a
Maintenance Review Board (MRB) task which is not valid for aeroplanes operated under EASA
jurisdiction. This means that the AD, as published, cannot be complied with on those aeroplanes.
It would appear that, for aeroplanes operated under EASA jurisdiction, another MRB task exists,
but the inspection intervals for that task are different from those specified in the AD.
Consequently, EASA have decided to contact Embraer and ANAC Brazil for further information.
Pending the outcome of this consultation, the adoption of ANAC AD 2017-03-01 is temporarily
suspended and, pending a final decision, compliance with the AD is not required for aeroplanes
operated under EASA jurisdiction.
In case you need further information, please contact the Safety Information Section, Certification
Directorate, EASA; E-mail ADs@easa.europa.eu.
Original Signed
Cologne, 07 April 2017
AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL BRAZIL
BRAZILIAN AIRWORTHINESS DIRECTIVE
ED
D
AD No.: 20170301 Effective Date: 24 Mar. 2017
EN
The following Brazilian Airworthiness Directive (AD), issued by the Agência Nacional de Aviação Civil (ANAC) in accordance with
provisions of Chapter IV, Title III of Código Brasileiro de Aeronáutica Law No. 7,565 dated 19 December 1986 and Regulamento Brasileiro
da Aviação Civil (RBAC) 39, applies to all aircraft registered in the Registro Aeronáutico Brasileiro. No person may operate an aircraft to which
this AD applies, unless it has previously complied with the requirements established herein.
AD No. 20170301 EMBRAER / 391411.
APPLICABILITY:
SP
SU
(a) This Airworthiness Directive (AD) applies to Embraer S.A. airplanes, as specified in
paragraphs (a)(1) and (a)(2) of this AD.
(1) Model ERJ 170100 LR, ERJ 170100 SE, ERJ 170100 STD, ERJ 170100 SU, ERJ
170200 LR, ERJ 170200 STD, and ERJ 170200 SU airplanes, as identified in Embraer Service Bulletin
170530051, Revision 3, dated August 21, 2013.
N
(2) Model ERJ 190100STD, ERJ 190100 LR, ERJ 190100 IGW, ERJ 190100 SR, ERJ
190200STD, ERJ 190200 LR, and ERJ 190200 IGW airplanes, as identified in Embraer Service
O
Bulletin 190530019, Revision 3, dated August 21, 2013.
AFFECTED ADs:
I
None.
PT
REASON:
This AD was prompted by an evaluation by the design approval holder indicating that the
forward pressure bulkhead is subject to widespread fatigue damage. The modification required by this AD
is intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support
O
the established structural maintenance program. We are issuing this AD to prevent fatigue cracking of the
forward pressure bulkhead, which could result in reduced structural integrity of the airplane.
AD
REQUIRED ACTION:
This AD requires inspections for cracking and the installation of additional doublers and
reinforcements on the forward pressure bulkhead.
COMPLIANCE:
Do the actions required by this AD within the compliance times specified, unless the
actions have already been done.
(b) Repetitive inspections and repairs
(1) For airplanes identified in paragraph (a)(1) of this AD: Before the accumulation of
25,954 total flight cycles, or within 3,600 flight cycles after the effective date of this AD, whichever
