Nachrichten für Luftfahrer 2021 Teil 2 (weicht ggf. von Druckversion ab)
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EASA AD No.: 2020-0033R1
Airworthiness Directive
AD No.: 2020-0033R1
Issued: 10 December 2021
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(s):
SAFRAN HELICOPTER ENGINES ARRIUS 2 engines
Effective Date: Revision 1: 17 December 2021
Original issue: 10 March 2020
TCDS Number(s): EASA.E.029
Foreign AD: Not applicable
Revision: This AD revises EASA AD 2020-0033 dated 25 February 2020, which superseded
EASA AD 2013-0082 dated 02 April 2013.
ATA 73 – Engine Fuel & Control – Hydro-mechanical Metering Unit / Drive Link
Splines – Inspection
Manufacturer(s):
SAFRAN Helicopter Engines (SAFRAN), formerly Turboméca
Applicability:
ARRIUS 2B1, ARRIUS 2B1A, ARRIUS 2B2, ARRIUS 2G1, ARRIUS 2K1 and ARRIUS 2K2 engines, all serial
numbers.
These engines are known to be installed on, but not limited to, Airbus Helicopters Deutschland
EC135, Leonardo A109 and KAMOV 226T twin-engine helicopters.
Definitions:
For the purpose of this AD, the following definitions apply:
Groups:
Group 1 are hydro-mechanical metering Units (HMU) that were first installed on a helicopter on or
before 31 January 2013, and which have never been inspected in accordance with Turboméca MSB
319 73 2825 version G or later (including HMU that have previously been inspected in accordance
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EASA AD No.: 2020-0033R1
with Turboméca MSB 319 73 2825 version F or earlier), and which do not have SAFRAN modification
(mod) TU139 embodied.
Group 2 are HMU that were first installed on a helicopter after 31 January 2013, or HMU that have
previously been inspected in accordance with Turboméca MSB 319 73 2825 version G or later, and
which do not have SAFRAN mod TU139 embodied.
Group 3 are HMU which have SAFRAN mod TU139 embodied.
The MSB: SAFRAN Mandatory Service Bulletin (MSB) 319 73 2825 version K.
Serviceable part: An HMU that is new (not previously installed); or an HMU that, before installation,
has passed an inspection (no discrepancies found, as identified in the MSB), or has been corrected,
in accordance with the instructions of the MSB; or an HMU which has SAFRAN mod TU139
embodied.
Reason:
A number of in-flight shut-down (IFSD) occurrences have been reported for ARRIUS 2 engines. The
results of the technical investigations concluded that these events were caused by deterioration of
the splines on the high pressure (HP) / low pressure (LP) pump assembly drive shaft of the HMU,
which eventually interrupted the fuel supply to the engine.
This condition, if not detected and corrected, could lead to further cases of engine IFSD, possibly
resulting in forced landing with consequent damage to the helicopter and injury to occupants.
To address these occurrences, Turboméca published MSB 319 73 2825 (up to version G) to provide
instructions for inspection of the HMU and sleeve assembly. Consequently, EASA issued AD 2013-
0082 to require repetitive inspections of the drive gear shaft splines of the HP pump, and,
depending on findings, accomplishment of applicable corrective action(s).
Since that AD was issued, SAFRAN published MSB 319 73 2825 version J to provide specific
inspection instructions for HMU installed on a helicopter after 31 January 2013, to reduce the
compliance time for the initial inspection of Group 1 engines that were not previously inspected in
accordance with version G or later of the MSB, and to provide some operational margin before the
first inspection in all possible scenarios.
For the reason described above, this AD retains the requirements of AD 2013-0082, which is
superseded. The original issue of this AD required accomplishment of the actions in accordance with
the instructions of SAFRAN MSB 319 73 2825 version J.
This AD is revised, further to the publication of the MSB, as defined in this AD, to remove the
inspection and cleaning requirements for HMU with an improved design (corresponding to SAFRAN
mod TU 139 introduced in 2015). This AD also introduces installation of an improved HMU as an
optional terminating action.
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EASA AD No.: 2020-0033R1
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Inspection(s) / Cleaning:
(1) For Group 1 and Group 2 HMU: Within the compliance time specified in Table 1 of this AD, as
applicable, and, thereafter, at intervals not to exceed 500 HMU operating hours (see Note 1 of
this AD), and before re-installation of the HMU after each removal, visually inspect the drive
gear shaft splines of the HP pump and clean and inspect the sleeve assembly splines in
accordance with the instructions of the MSB.
Note 1: A non-cumulative tolerance of 10% may be applied to the repetitive inspection interval
defined in paragraph (1) of this AD. No tolerance may be applied to the compliance time for initial
inspection defined in Table 1 of this AD.
Table 1 – Initial HMU Inspection
HMU Group / Condition Compliance Time
Group 1 / 150 HMU operating hours or Within 50 HMU operating hours after 10 March 2020
more accumulated (see Note 2) [the effective date of the original issue of this AD]
Group 1 / less than 150 HMU operating Before exceeding 200 HMU operating hours
hours accumulated (see Note 2)
Group 2 Within 500 HMU operating hours after the last
inspection, or after first installation of the HMU
on a helicopter, as applicable
Note 2: Unless indicated otherwise, the operating hours specified in Table 1 of this AD are those
accumulated, on 10 March 2020 [the effective date of the original issue of this AD], by the HMU
since new (first installation on a helicopter) or since last overhaul.
Corrective Action(s):
(2) If, during any inspection as required by paragraph (1) of this AD, a discrepancy is detected, as
defined in the MSB, before next flight, replace the sleeve assembly on the affected HP pump
drive gear shaft, or replace the affected HMU with a serviceable part in accordance with the
instructions of the MSB.
Credit:
(3) Inspection(s) and corrective action(s) on an engine, accomplished before the effective date of
this AD in accordance with the instructions of Turboméca MSB 319 73 2825 version G or later,
are acceptable to comply with the initial requirements of paragraphs (1) and (2) of this AD for
that engine.
Optional Terminating Action:
(4) Installation on a helicopter of a Group 3 HMU, or of an engine with a Group 3 HMU installed,
constitutes terminating action for the repetitive inspection and cleaning requirements of this
AD for that helicopter.
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Parts / Engine Installation:
(5) From the effective date of this AD, it is allowed to install an HMU on an engine, or an engine on
a helicopter, provided that the HMU is a serviceable part, as defined in this AD, and that,
following installation, each pre-mod TU 139 HMU is inspected as required by this AD.
Ref. Publications:
Turboméca MSB 319 73 2825 version G dated 24 January 2013, or version H dated 01 September
2014, or version I dated 26 April 2016; and SAFRAN MSB 319 73 2825 version J dated 15 March
2019 or version K dated 16 November 2021.
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 original issue of this AD was posted on 22 January 2020 as PAD 20-104 for consultation
until 19 February 2020. 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. 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. This may include reporting on the same or similar components, other than
those covered by the design to which this AD applies, if the same unsafe condition can exist or
may develop on an aircraft with those components installed. Such components may be
installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate
(STC) or other modification.
5. For any question concerning the technical content of the requirements in this AD, please
contact please contact your nearest SAFRAN Helicopter Engines technical representative, or
connect to www.tools.safran-helicopter-engines.com. 21.12.2021
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T12 -
D-2014-159R8 38144 Braunschweig
EASA AD 2018-0104R1 vom 08.12.2021 Fax: +49-531-2355-5197
email: AD@LBA.de
AIRBUS HELICOPTERS 09.12.2021
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: AIRBUS HELICOPTERS
Hersteller: Airbus Helicopters,
vormals Eurocopter, Eurocopter France
Muster: EC 130
Baureihen: EC 130 B4 und EC 130 T2
Werknummern: Alle
Ausgenommen sind Hubschrauber, an denen die Airbus Modifikation
(MOD) 074775 oder MOD 074581 durchgeführt worden ist.
Gerätenummer: 3048, EASA.R.008
Revisionsstand:
Diese LTA ersetzt D-2014-159R7 vom 09.05.2018
Airworthiness Directive der ausländischen Behörde:
EASA AD 2018-0104R1 vom 08.12.2021
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 2014-159R8 geführt.
Betrifft:
(ATA 53) Fuselage - Tail Boom / Fenestron Junction Frame - Inspection
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301(f)(1), ML.A.301(d)(1),
M.A.303 und ML.A.303 dürfen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen
Termin nur in Betrieb genommen werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchge-
führt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2018-0104R1 vom 08.12.2021 herausgegeben oder per Entscheidung Nr. 2019/018/ED übernom-
men.
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.
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EASA AD No.: 2018-0104R1
Airworthiness Directive
AD No.: 2018-0104R1
Issued: 08 December 2021
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(s):
AIRBUS HELICOPTERS EC 130 helicopters
Effective Date: Revision 1: 15 December 2021
Original issue: 11 May 2018
TCDS Number(s): EASA.R.008
Foreign AD: Not applicable
Revision: This AD revises EASA AD 2018-0104 dated 04 May 2018, which superseded EASA
AD 2017-0080 dated 05 May 2017.
ATA 53 – Fuselage – Tail Boom / Fenestron Junction Frame – Inspection
Manufacturer(s):
Airbus Helicopters (AH), formerly Eurocopter, Eurocopter France
Applicability:
EC 130 B4 and EC 130 T2 helicopters, all serial numbers, except those on which Airbus modification
(mod) 074775 or mod 074581 has been embodied.
Definitions:
For the purpose of this AD, the following definitions apply:
The ASB: AH EC 130 Emergency Alert Service Bulletin (ASB) 05A017 Revision 6, or later approved
revisions.
The modification SB: AH Service Bulletin (SB) EC130-53-036.
Sling cycles: Counting/Cycles as defined in AH ASB 05A017 Revision 2, or later approved revisions.
Groups: Group 1 helicopters are those in pre-mod AH 350A087421 or pre-SB EC130-53-029
configuration. Group 2 helicopters are those in post-mod AH 350A087421 or post-SB EC130-53-029
configuration. Group 3 helicopters are Group 1 or Group 2 helicopters which are post-mod 074609,
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or on which the skin in the fenestron/tail boom junction area was repaired in accordance with the
instructions of SB EC130-53-024.
Reason:
Following inspection of EC 130 helicopters, two events were reported of finding crack propagation
through the junction frame of the tail boom/fenestron. The investigation revealed that the cracks
initiated in the lower right-hand part of the frame between the web and the flange, where the
lower spar of the tail boom is joined. Although the cracks were of significant length, no
deterioration was visible from the outside of the helicopter.
This condition, if not detected and corrected, could lead to structural failure, possibly resulting in
fenestron detachment and consequent loss of control of the helicopter.
To initially address this potential unsafe condition, AH issued ASB 05A017 at original issue (later
revised) to provide instructions for detailed visual inspections (DVI) on the inside of the tail boom.
Prompted by these findings, EASA issued Emergency AD 2014-0145-E (later revised) to require
repetitive inspections of the affected area and, depending on findings, accomplishment of
applicable corrective action(s).
Following further developments involving multiple revisions of AH ASB 05A017, EASA AD
2014-0145R1 was superseded by EASA Emergency AD 2015-0033-E (later revised), EASA AD
2015-0033R1 was superseded by EASA AD 2016-0240, subsequently superseded by EASA
Emergency AD 2017-0066-E, each time retaining the previous AD requirements. EASA then issued
AD 2017-0080, retaining the requirements of EASA Emergency AD 2017-0066-E, which was
superseded, and additionally requiring removal of the stabilizer before the cleaning and visual
inspection of the frame during each 660 flight hour (FH) inspection of Group 2 helicopters.
After EASA AD 2017-0080 was issued, in parallel to the protective measures developed over time,
AH designed a new modification, mod 074775, consisting of 4 carbon patches on the EC 130
fenestron/tail cone junction, and published the modification SB, as defined in this AD, accordingly.
After implementation of this design change, either in production or in service through a retrofit (the
modification SB), the inspections were no longer necessary. Based on the available information,
EASA determined that continued inspections may not be sufficient to adequately address the risk
and this modification is necessary to ensure long-term fleet safety, and consequently issued AD
2018-0104, which superseded EASA AD 2017-0080, retaining its requirements and mandating
modification of the affected helicopters as terminating action for the repetitive inspections required
by that AD.
Since AD 2018-0104 was issued, AH developed mod 074581 and issued ASB 05A017 Revision 8, to
exclude the post-mod 074581 helicopters from the Applicability. This AD is therefore revised
accordingly. This AD also includes editorial changes, introducing the latest AD writing standards,
without affecting the requirements.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
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Inspection(s)/Cleaning:
(1) For Group 1 helicopters: Within the compliance time as specified in Table 1 of this AD, as
applicable, accomplish the cleaning and a DVI of the frame web in the radius between the
web and the flange on the tail cone side in accordance with the instructions of paragraphs
3.B.5 and 3.B.1 of the ASB.
Table 1 – Inspection Threshold
FH accumulated (see Note 1) Compliance Time
Less than 325 FH Before exceeding 350 FH
Within 25 FH after 25 April 2017 [the effective
325 FH or more, but less than 675 FH
date of EASA AD 2017-0066-E]
675 FH or more, but less than 690 FH Before exceeding 700 FH
Within 10 FH after 25 April 2017 [the effective
690 FH or more
date of EASA AD 2017-0066-E]
Note 1: Unless specified otherwise, the FH referenced in Table 1 of this AD are those accumulated
by the junction frame since first installation on a helicopter.
(2) Within 25 FH or 390 sling cycles (see Note 2 of this AD), whichever occurs first after the
inspection as required by paragraph (1) of this AD, and, thereafter, at intervals not to exceed
25 FH or 390 sling cycles, whichever occurs first, inspect the frame web in the radius between
the web and the flange on the tail cone side in accordance with the instructions of paragraph
3.B.1 or 3.B.2 of the ASB.
(3) Within 150 FH after the inspection as required by paragraph (1) of this AD and, thereafter, at
intervals not to exceed 150 FH, accomplish the cleaning and a DVI of the frame web in the
radius between the web and the flange on the tail cone side in accordance with the
instructions of paragraphs 3.B.5 and 3.B.1 of the ASB.
Note 2: See Definitions in this AD.
(4) For Group 2 helicopters: Before exceeding 350 FH accumulated by the junction frame since
first installation on a helicopter, or within 10 FH after modification (SB EC130-53-029
installation in-service), whichever occurs later, accomplish a visual inspection of the tail boom
from outside in accordance with the instructions of paragraph 3.B.3 of the ASB.
(5) Within 10 FH or 250 sling cycles, whichever occurs first after the inspection as required by
paragraph (4) of this AD, and, thereafter, at intervals not to exceed 10 FH or 250 sling cycles,
whichever occurs first, accomplish a visual inspection (see Note 3 of this AD) of the tail boom
from outside in accordance with the instructions of paragraph 3.B.3 of the ASB.
Note 3: The visual inspection as specified in paragraph 3.B.3 (a) of the ASB may be carried out by
the pilot.
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(6) Within 660 FH after the inspection as required by paragraph (4) of this AD, and, thereafter, at
intervals not to exceed 660 FH, remove the stabilizer and accomplish the cleaning and a DVI of
the frame web in the radius between the web and the flange on the tail cone side in
accordance with the instructions of paragraphs 3.B.5 and 3.B.1 of the ASB.
Credit:
(7) Accomplishment of a cleaning and a DVI on a helicopter, as required by paragraph (3) of this
AD, is acceptable for compliance with an inspection as required by paragraph (2) of this AD for
that helicopter.
(8) Accomplishment of a cleaning and a DVI on a helicopter, as required by paragraph (6) of this
AD, is acceptable for compliance with an inspection as required by paragraph (5) of this AD for
that helicopter.
Corrective Action(s):
(9) If, during any inspection as required by this AD, any crack is detected, before next flight,
contact AH for approved repair instructions and accomplish those instructions accordingly.
Modification:
(10) For Group 1 and Group 2 helicopters, except Group 3 helicopters: Within 56 months after 11
May 2018 [the effective date of the original issue of this AD], modify the tail boom/fenestron
junction (mod 074775) in accordance with the instructions of the modification SB.
(11) For Group 3 helicopters: Contact Airbus Helicopters to define the conditions for embodiment
of modification 074775 and, within 56 months after 11 May 2018 [the effective date of the
original issue of this AD], modify the helicopter accordingly.
Terminating Action(s):
(12) Repair of a helicopter, as required by paragraph (9) of this AD, does not constitute terminating
action for the repetitive inspections as required by this AD for that helicopter, unless explicitly
indicated in those repair instructions.
(13) Modification of a helicopter as required by paragraph (10) or (11) of this AD, as applicable,
constitutes terminating action for the repetitive inspections as required by this AD for that
helicopter, except as specified in paragraph (14) of this AD.
Part(s) Installation:
(14) Installation of a replacement (new/previously not installed) junction frame on a helicopter is
allowed, provided that, before exceeding 350 FH after installation, cleaning and a DVI of the
frame web in the radius between the web and the flange on the tail cone side is
accomplished, in accordance with the instructions of paragraph 3.B.5 and 3.B.1 of the ASB,
and, following installation, the helicopter is inspected as required by paragraph (2) and (3), or
(5) and (6) of this AD, as applicable.
Ref. Publications:
AH EC130 Emergency ASB No. 05A017 Revision 2 dated 20 February 2015, or Revision 3 dated 07
March 2016, or Revision 4 dated 30 November 2016, or Revision 5 dated 21 April 2017, or
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Revision 6 dated 03 May 2017, or Revision 7 dated 21 March 2018, or Revision 8 dated 06
December 2021.
AH SB EC130-53-029 original issue dated 20 February 2015, or Revision 1 dated 27 January 2016.
AH SB EC130-53-036 Revision 01 dated 21 March 2018.
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. The original issue of this AD was posted on 27 March 2018 as PAD 18-045 for consultation until
10 April 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. 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. This may include reporting on the same or similar components, other than
those covered by the design to which this AD applies, if the same unsafe condition can exist or
may develop on an aircraft with those components installed. Such components may be
installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate
(STC) or other modification.
5. For any question concerning the technical content of the requirements in this AD, please
contact: Airbus Helicopters Customer Support, Telephone +33 (0)4.42.85.97.89, Fax + 33
(0)4.42.85.99.66, E-mail: support.technical-airframe.ah@airbus.com, Airbus World: Technical
Request Management: https://airbusworld.helicopters.airbus.com.
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