Nachrichten für Luftfahrer 2019 Teil 2 (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
D-2019-292 3818 braunsch eig
ИВА EASA AD 2019-0274 vom 06.11.2019 Fax: +49-531-2355-5298
email: ad@LBA.de
SOCATA 11.11.2019
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: DAHER AEROSPACE
Hersteller: Compagnie DAHER,
vormals SOCATA, EADS SOCATA, Société de Construction d'Avions de
Tourisme et d'Affaires
Muster: TB Series
Baureihen: TB 20 und TB 21
Werknummern: Alle
Gerätenummer:
1063, EASA.A.378
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2019-0274 vom 06.11.2019
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 2019/018/ED übernommen und sind somit ebenfalls Airworthin-
ess Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2019-292 geführt.
Betrifft:
(ATA 32) Landing Gear - Main Landing Gear Leg - Inspection
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
fen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2019-0274 vom 06.11.2019 herausgegeben oder per Entscheidung Nr. 2019/018/ED übernommen.
D-2019-292 Seite 1 von 1 510/2019
EASA AD No.: 2019-0274
MEASA
Airworthiness Directive
AD No.: 2019-0274
European Union Aviation Safety Agency
Issued: 06 November 2019
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EU) 2018/1139 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 129 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 (EU) 2018/1139, Article 71 exemption].
Design Approval Holder's Name: Type/Model designation:
DAHER AEROSPACE TB 20 and TB 21 aeroplanes
Effective Date: 20 November 2019
TCDS Number(s): EASA.A.378
Foreign AD: Not applicable
Supersedure: None
ATA 32 - Landing Gear - Main Landing Gear Leg - Inspection
Manufacturer:
Compagnie DAHER, formerly SOCATA, EADS SOCATA, Société de Construction d'Avions de Tourisme
et d'Affaires
Applicability:
DAHER Aerospace TB 20 and TB 21 aeroplanes, all manufacturer serial numbers.
Definitions:
For the purpose of this AD, the following definitions apply:
The SB: DAHER Aerospace Service Bulletin (SB) 10-154-32.
Affected MLG area: Left-hand and right-hand main landing gear (MLG) leg area, as defined in the
SB.
Reason:
Occurrences have been reported of finding cracks on MLG legs of TB 20 and TB 21 aeroplanes.
This condition, if not detected and corrected, could lead to structural failure of an MLG leg and
consequent MLG collapse, possibly resulting in damage to the aeroplane and injury to occupants.
TE.CAP.00110-009 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 3
An agency of the European Union
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
EASA AD No.: 2019-0274
To address this potential unsafe condition, DAHER Aerospace issued the SB to provide inspection
instructions.
For the reasons described above, this AD requires repetitive special detailed inspections (SDI) using
magnetic particle method of the affected MLG area, and, depending on findings, accomplishment of
applicable corrective action (s).
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Repetitive inspections:
(1) Before exceeding 16 000 landings (LDG) since first installation of the MLG on an aeroplane, or
within 200 LDG after the effective date of this AD, whichever occurs later, and, thereafter, at
intervals not to exceed 3 200 LDG, accomplish an SDI of each affected MLG area in accordance
with the instructions of the SB.
Corrective Action(s):
(2) If, during any SDI as required by paragraph (1) of this AD, any crack is detected in an affected
MLG area, before next flight, rework that affected MLG area and, thereafter, before next flight,
accomplish another one-time SDI of that reworked affected MLG area in accordance with the
instructions of the SB.
(3) If, during the one-time SDI of a reworked affected MLG area as required by paragraph (2) of this
AD, any crack is detected, before next flight, contact DAHER for approved repair instructions
and, within the compliance time(s) specified therein, accomplish those instructions accordingly.
(4) If, during the one-time SDI of a reworked affected MLG area as required by paragraph (2) of this
AD, no cracks are detected, within 3 200 LDG after that one-time SDI, and, thereafter, at
intervals not to exceed 3 200 LDG, accomplish an SDI of that reworked affected MLG area in
accordance with the instructions of the SB.
(5) If, during any SDI as required by paragraph (4) of this AD, any crack is detected in a reworked
affected MLG area, before next flight, contact DAHER for approved repair instructions and,
within the compliance time(s) specified therein, accomplish those instructions accordingly.
Terminating Action:
(6) None.
Ref. Publications:
DAHER Aerospace SB 10-154-32 original issue dated September 2019.
The use of later approved revisions of the above-mentioned document is acceptable for compliance
with the requirements of this AD.
TE.CAP.0O110-009 © European Union 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.: 2019-0274
Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.
2. This AD was posted on 27 September 2019 as PAD 19-183 for consultation until 25 October
2019. No comments were received during the consultation period
3. Enquiries regarding this AD should be referred to the EASA Programming and Continued
Airworthiness Information Section, Certification Directorate. E-mail: ADs@easa.europa.eu.
4. Information about any failures, malfunctions, defects or other occurrences, which may be
similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on
a product, part or appliance not affected by this AD, can be reported to the EU aviation safety
reporting system.
5. For any question concerning the technical content of the requirements in this AD, please
contact: DAHER AEROSPACE, Direction des services, 65921 Tarbes Cedex 9, France,
Telephone +33 (0) 5 62 41 73 00, Fax + 33 (0) 5 62 41 76 54,
E-mail: TBMCare@daher.com.
TE. CAP.00110-009 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified Page 3 of 3
An agency of the European Union
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2019-293
ИВА EASA Emergency AD 2019-0277-E vom
12.11.2019
-3x. 49-631-2358-3298
email: ad@LBA.de
SAFRAN HELICOPTER ENGINES 13.11.2019
Betroffenes Luftfahrtgerät:
DRINGEND!
Art des Luftfahrtgerätes: Propeller
Inhaber der Musterzulassung: SAFRAN HELICOPTER ENGINES
Hersteller: Safran Helicopter Engines,
vormals Turbomeca S.A., Rolls-Royce Turbomeca Ltd
Muster: RTM 322
Baureihen: RTM 322-01/9 und RTM 322-01/9A
Werknummern: Alle
Die betroffenen Triebwerke sind in NH Industries NH90 (Militär) Hubschraubern
installiert, jedoch nicht auf diese beschränkt.
Gerätenummer: EASA.E.009
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA Emergency AD 2019-0277-E vom 12.11.2019
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 2019/018/ED übernommen und sind somit ebenfalls Airworthin-
ess Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2019-293 geführt.
Betrifft:
(ATA 75) Air - Anti-icing Valve Assembly Gaskets - Replacement
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
ten Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA Emergency AD 2019-0277-E vom 12.11.2019 herausgegeben oder per Entscheidung Nr. 2019/018/ED
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-2019-293 Seite 1 von 1 516/2019
EASA AD No.: 2019-0277-E
Emergency Airworthiness Directive
MEASA
European Union Aviation Safety Agency
AD No.: 2019-0277-E
Issued: 12 November 2019
Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Regulation (EU) 2018/1139 on behalf of the European Union, its Member States and of the
European third countries that participate in the activities of EASA under Article 129 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 (EU) 2018/1139, Article 71 exemption).
Design Approval Holder's Name: Type/Model designation(s):
SAFRAN HELICOPTER ENGINES RTM322 engines
Effective Date: 14 November 2019
TCDS Number(s): EASA.E.009
Foreign AD: Not applicable
Supersedure: None
ATA 75 - Air - Anti-icing Valve Assembly Gaskets - Replacement
Manufacturer(s):
SAFRAN Helicopter Engines, S.A. (SAFRAN), formerly Turboméca, S.A.
Applicability:
RTM 322-01/9 and RTM 322-01/9A engines, all serial numbers.
These engines are known to be installed on, but not limited to, NH Industries NH90 (military)
helicopters.
Definitions:
For the purpose of this AD, the following definitions apply:
The MSB: SAFRAN Mandatory Service Bulletin (MSB) MSBP-M3-A-75-09-00-04A-A-A.
Affected part: Anti-icing valve assembly gaskets, having Part Number (P/N) 0322710040, or
P/N 0322710050.
Serviceable part: Anti-icing valve assembly gaskets, having P/N 0000231350, or P/N 0000231360.
Groups: Group 1 engines are those that have an affected part installed. Group 2 engines are those
that do not have an affected part installed.
TE.CAP.00111-009 © European Union 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.: 2019-0277-E
Icing conditions: Whenever the ambient temperature is +5°C or less and visible humidity conditions
are present.
Reason:
Occurrences have been reported that SAFRAN Modification C3062 may cause stress to the outlet
pipe of the anti-icing valve which connects the anti-icing valve to the air intake casing. This may lead
to a reduction in, or even to a loss of, the anti-icing function of inlet guide vanes and air intake
casing (P3 air leak).
This condition, if not corrected, may lead to an uncommanded engine in-flight shut-down, possibly
resulting in an emergency landing, with consequent damage to the helicopter and injury to
occupants.
To address this potential unsafe condition, SAFRAN issued the MSB, providing instructions for
replacement of the affected parts.
For the reason described above, this AD requires removal from service of the affected parts. This AD
also prohibits (re)installation of an affected part.
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:
Replacement:
(1) For a helicopter having two Group 1 engines installed: Before next flight into known or
expected icing conditions after the effective date of this AD, replace on at least one engine the
affected part with a serviceable part, as defined in this AD, in accordance with the instructions
of the MSB.
(2) For Group 1 engines: During the next scheduled 50 flight hour maintenance visit, replace each
affected part with a serviceable part, as defined in this AD, in accordance with the instructions
of the MSB.
Concurrent Inspection:
(3) Concurrent with replacement of an affected part on an engine, as required by paragraph (1) or
(2) of this AD, as applicable, inspect the P/N 0322767180 outlet pipe in accordance with the
instructions of the MSB.
Corrective Action(s):
(4) If, during the inspection as required by paragraph (3) of this AD, the outlet pipe is found
cracked, before next flight, replace the outlet pipe with a new P/N 0322767180 outlet pipe, or a
P/N 0322767180 outlet pipe that has passed an inspection (no crack detected) in accordance
with the instructions of the MSB.
Page 2 of 3
TE. CAP.00111-009 © European Union Aviation Safety Agency. All rights reserved. IS09001 Certified.
An agency of the European Union
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
EASA AD No.: 2019-0277-E
Parts Installation:
(5) For Group 1 and Group 2 engines: From the effective date of this AD, do not install an affected
part on any engine.
Engine Installation:
(6) From the effective date of this AD, do not install a Group 1 engine on any helicopter.
Ref. Publications:
SAFRAN Helicopter Engines MSBP-M3-A-75-09-00-04A-A-A original issue dated 08 November 2019.
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. The results of the safety assessment have indicated the need for immediate publication and
notification, without the full consultation process.
3. Enquiries regarding this AD should be referred to the EASA Programming and Continued
Airworthiness Information Section, Certification Directorate. E-mail: ADs@easa.europa.eu.
4. Information about any failures, malfunctions, defects or other occurrences, which may be
similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on
a product, part or appliance not affected by this AD, can be reported to the EU aviation safety
reporting system.
5. 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.
Page 3 of 3
*.,. TE.CAP.00111-009 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified.
An agency of the European Union
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
ИВА
D-2019-294 38144 Braunschweig
ANAC BAD 2019-11-06 - Amdt. 39-1450 Fax: +49-531-2355-5298
email: ad@LBA.de
EMBRAER 13.11.2019
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung:
Hersteller:
EMBRAER
Embraer S.A., Embraer Executive Aircraft Inc.
Muster: EMB-505
Baureihen: EMB-505
Werknummern: Gemäß Embraer Service Bulletin Nr. 505-55-A004 Revision 2 vom 06.11.2019.
Gerätenummer: EASA.IM.A. 158, ANAC TCDS EA-2009T12
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
ANAC BAD 2019-11-06 - Amdt. 39-1450
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 2019/018/ED übernommen und sind somit ebenfalls Airworthin-
ess Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2019-294 geführt.
Betrifft:
(ATA 55) Stabilizers - Mass-balance Weights of the Control Surfaces and their Attachments - Inspection /
Replacement
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
fen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
ANAC BAD 2019-11-06 - Amdt. 39-1450 herausgegeben oder per Entscheidung Nr. 2019/018/ED übernom-
Gemaß § 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
Mit Hilfe dieser Übersichtsseite veröffentlicht das Luftfahrt-Bundesamt ebenfalls die über § 14 Abs. 2 direkt
Kite LA tel TAg Dieser Senice dient reinen Informatonswecken une liegt keinem wattngsver
fahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2019-294 Seite 1 von 1
514/2019
08/11/2019
SEI/ANAC - 3707023 - Formulário F-900-04F
ANAC
AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL - BRAZIL
BRAZILIAN AIRWORTHINESS DIRECTIVE
AD No.: 2019-11-06 Effective Date: 08 Nov. 2019
The following Brazilian Airworthiness Directive (AD), issued by the Agência Nacional de Aviação Civil (ANAC) in acordance with
provisions of Chapter IV, Title Ill 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. 2019-11-06 - EMBRAER / 39-1450.
APPLICABILITY:
This Airworthiness Directive is applicable to Embraer model EMB-505 airplanes, as
identified in Embraer Service Bulletin No 505-55-A004, revision 2, dated November 06, 2019.
CANCELLATION / REVISION:
Not applicable.
REASON:
It has been found the occurrence of corrosion in the mass-balance weights of the control
surfaces. The corrosion may lead to loss of mass or the detachment of the mass-balance weights, resulting
in an unbalanced control surface, which, in conjunction with certain flight conditions, could lead to flutter
and possible loss of airplane control.
Since this condition may occur in other aircraft of the same type and affects flight safety, a
corrective action is required. Thus, suficient reason exists to request compliance with this AD in the
indicated time limit.
REQUIRED ACTION:
Inspection of the mass-balance weights of the elevators, ailerons and rudder, and their
attachment parts, and replacement as necessary.
COMPLIANCE:
Required as indicated below, unless already accomplished.
Within 60 calendar days or 100 FH, whichever occurs first, after the effective date of this
AD, carry out the actions in paragraphs (a) to (f) of this AD.
(a) Elevator adjustable mass-balance and attachments inspection and replacement
(1) Inspect the elevator adjustable mass-balance weight and attachment parts for integrity
and corrosion.
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