Nachrichten für Luftfahrer 2022 Teil 2 (weicht ggf. von Druckversion ab)
LUFTTÜCHTIGKEITSANWEISUNGEN
2022-2-672
EASA AD No.: 2022-0053
Inspection:
(1) For Group 1 helicopters: Within the compliance time specified in Table 1 of this AD, as
applicable, inspect the external and internal tubes of the affected part in accordance with the
instructions of the ASB.
Table 1 – Inspection
Helicopter Operation Date of First Installation on a Compliance Time
Helicopter [After the effective date of this
(see Note 1 of this AD) AD, unless specified otherwise]
Only Standard 15 February 2016, or before Within 27 months
Non-standard From 16 February 2016 until 15 Within 27 months or 7 years
February 2022 inclusive since first installation of an
affected part on an helicopter,
whichever occurs first
Non-standard 15 February 2016, or before
Unknown Any Within 13 months
Any Unknown
Note 1: When the affected part sub-assemblies have different dates of first installation on a
helicopter, the oldest date of first installation must be used.
Corrective Action(s):
(2) If, during the inspection as required by paragraph (1) of this AD, any crack or leafing/exfoliant
corrosion, as defined in the ASB, is found on an affected part, before next flight, contact AH for
approved repair instructions, and within the compliance time(s) specified therein, accomplish
those instructions accordingly.
(3) If, during the inspection as required by paragraph (1) of this AD, corrosion, except
leafing/exfoliant corrosion, is found on an affected part, before next flight, remove the
corrosion from the affected area and measure the residual thickness of the affected part sub-
assemblies in accordance with the instructions of the ASB.
(4) If, during the measurement as required by paragraph (3) of this AD, the residual thickness of an
affected part sub-assembly does not meet the acceptability criteria as specified in Table 3 of
the ASB, before next flight, contact AH for approved repair instructions, and within the
compliance time(s) specified therein, accomplish those instructions accordingly.
(5) Replacing an affected part sub-assembly of a helicopter which does not meet the acceptability
criteria specified in Table 3 of the ASB, or on which crack(s) or leafing/exfoliant corrosion have
been found, with a serviceable part, is an acceptable method to comply with the requirements
of paragraphs (2) or (4) of this AD, as applicable, for that helicopter. This can be accomplished
in accordance with the instructions of the applicable Aircraft Maintenance Manual.
11.04.2022
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EASA AD No.: 2022-0053
Credit:
(6) Inspection and corrective action(s), accomplished on EC 130 B4 or EC 130 T2 helicopters before
the effective date of this AD in accordance with the instructions of AH ASB EC130-05A035
Revision 01, are acceptable to comply with the requirements of paragraphs (1), (2), (3) and (4)
of this AD, as applicable, for that helicopter.
Reporting:
(7) Within 30 days after the inspection as required by paragraph (1) of this AD, or within 30 days
after the effective date of this AD, whichever occurs later, report the inspection results to AH.
This can be accomplished using the Appendix of the ASB.
Part(s) Installation:
(8) For Group 1 and Group 2 helicopters: From the effective date of this AD, it is allowed to install
an affected part, or an affected part sub-assembly, on any helicopter, provided it is a
serviceable part, as defined in this AD.
Ref. Publications:
AH ASB EC130-32A013 original issue dated 15 February 2022.
AH ASB EC120-32A014 original issue dated 15 February 2022.
AH ASB EC130-05A035 Revision 01 dated 10 December 2020.
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 21 February 2022 as PAD 22-016 for consultation until 21 March 2022.
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
11.04.2022
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LUFTTÜCHTIGKEITSANWEISUNGEN
2022-2-672
EASA AD No.: 2022-0053
contact: Airbus Helicopters Customer Support, Telephone +33 (0)4.42.85.97.89,
Fax + 33 (0)4.42.85.99.66,
E-mail: Airframe.Technical-Support@airbus.com, Keycopter Technical Request
Management: TechnicalSupport.Helicopters@airbus.com.
11.04.2022
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LUFTTÜCHTIGKEITSANWEISUNGEN
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T12 -
D-2022-095 38144 Braunschweig
EASA AD 2022-0049 vom 21.03.2022 Fax: +49-531-2355-5199
email: AD@LBA.de
AIRBUS 29.03.2022
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS S.A.S.
Hersteller: Airbus, vormals Airbus Industrie
Muster: A330
A340
Baureihen: A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-243F,
A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, A330-341,
A330-342, A330-343, A330-743L, A330-841 und A330-941.
A340-211, A340-212, A340-213, A340-311, A340-312 und A340-313.
Werknummern: Alle
Gerätenummer: 2849, 2850, EASA.A.004, EASA.A.015
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2022-0049 vom 21.03.2022
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 2022-095 geführt.
Betrifft:
(ATA 32) Landing Gear - Nose and Main Landing Gear Main Fittings and Main Landing Gear Sliding Pistons -
Replacement
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 2022-0049 vom 21.03.2022 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.
11.04.2022
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LUFTTÜCHTIGKEITSANWEISUNGEN
2022-2-672
EASA AD No.: 2022-0049
Airworthiness Directive
AD No.: 2022-0049
Issued: 21 March 2022
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 or
Annex Vb Part ML.A.301, as applicable, 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 Annex Vb Part ML.A.303, as applicable] 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 A330 and A340 aeroplanes
Effective Date: 04 April 2022
TCDS Number(s): EASA.A.004, EASA.A.015
Foreign AD: Not applicable
Supersedure: None
ATA 32 – Landing Gear – Nose and Main Landing Gear Main Fittings and Main
Landing Gear Sliding Pistons – Replacement
Manufacturer(s):
Airbus, formerly Airbus Industrie
Applicability:
Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-243F, A330-301,
A330-302, A330-303, A330-321, A330-322, A330-323, A330-341, A330-342, A330-343, A330-743L,
A330-841 and A330-941 aeroplanes, all manufacturer serial numbers (MSN); and
Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313 aeroplanes, all MSN.
Definitions:
For the purpose of this AD, the following definitions apply:
The SB: Airbus Service Bulletin (SB) A330-32-3302 or SB A340-32-4321, as applicable.
Affected part: Nose landing gear (NLG) and main landing gear (MLG) main fittings, and MLG sliding
pistons, having a Part Number and a serial number listed in the SB.
11.04.2022
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EASA AD No.: 2022-0049
Serviceable part: Affected parts, which have not exceeded the applicable revised life limit, as
published in the SB; and NLG and MLG main fittings, and MLG sliding pistons, eligible for
installation, which are not affected parts.
Repaired MLG sliding piston: Affected part MLG sliding piston, repaired in accordance with the
instructions of the applicable Component Maintenance Manual.
Groups: Group 1 aeroplanes are those that have an affected part installed. Group 2 aeroplanes are
those that do not have an affected part installed.
Reason:
Airbus quality control identified that certain landing gear parts have been manufactured with
improper material and/or using a deviating manufacturing processes. Further analysis determined
that those parts cannot be operated until the applicable life limit, as published in the applicable
Airworthiness Limitations Section.
This condition, if not corrected, could lead to NLG or MLG structural fatigue failure and subsequent
collapse of a landing gear, possibly resulting in damage to the aeroplane and injury to occupants.
To address this potential unsafe condition, Airbus published the SB, providing lists of affected parts
and revised life limits.
For the reasons described above, this AD requires implementing revised life limits for affected parts,
and re-assessment of repairs previously accomplished on affected MLG sliding pistons.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Replacement:
(1) For Group 1 aeroplanes: Before exceeding the applicable revised life limit, as published in the
SB, or within 3 months after the effective date of this AD, whichever occurs later, replace each
affected part with a serviceable part. This can be accomplished in accordance with the
instructions of the applicable Aircraft Maintenance Manual.
Re-assessment of Repair(s):
(2) For Group 1 aeroplanes that, on the effective date of this AD, have a repaired MLG sliding
piston installed, within 3 months after the effective date of this AD, contact Airbus for approved
instructions and, within the compliance time specified therein, accomplish those instructions
accordingly.
Part(s) Installation:
(3) For Group 1 and Group 2 aeroplanes: From the effective date of this AD, it is allowed to install
on any aeroplane an affected part, provided it is a serviceable part, as defined in this AD, and
that, following installation, that part is replaced with a serviceable part before exceeding the
applicable revised life limit, as published in the SB.
11.04.2022
TE.CAP.00110-010 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
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2022-2-672
EASA AD No.: 2022-0049
(4) For Group 1 and Group 2 aeroplanes: From the effective date of this AD, it is allowed to install a
repaired MLG sliding piston on any aeroplane, provided that, before that installation, Airbus
has been contacted for approved instructions and that, following installation, those instructions
are accomplished accordingly and within the compliance time(s) specified therein.
Ref. Publications:
Airbus SB A330-32-3302 original issue dated 18 January 2022.
Airbus SB A340-32-4321 original issue dated 18 January 2022.
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 26 January 2022 as PAD 22-007 for consultation until 23 February 2022.
The Comment Response Documents 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 – IIAL (Airworthiness Office), E-mail: airworthiness.A330-A340@airbus.com. 11.04.2022
TE.CAP.00110-010 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 3
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An agency of the European Union
LUFTTÜCHTIGKEITSANWEISUNGEN
2022-2-672
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T12 -
D-2022-096 38144 Braunschweig
FAA AD 2022-04-08 - Amdt. 39-21950 Fax: +49-531-2355-5199
email: AD@LBA.de
AIRBUS 30.03.2022
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS S.A.S.
Hersteller: Airbus, vormals Airbus Industrie
Muster: A318, A319, A320, A321
Baureihen: A318-111, A318-112, A318-121, A318-122,
A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132,
A319-133, A319-151N, A319-153N, A319-171N,
A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-232,
A320-233, A320-251N, A320-252N, A320-253N, A320-271N, A320-272N,
A320-273N,
A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231,
A321-232, A321-251N, A321-251NX, A321-252N, A321-252NX, A321-253N,
A321-253NX, A321-271N, A321-271NX, A321-272N und A321-272NX
Werknummern: Alle
Betroffen sind Flugzeuge, die mit einer gemäß "Parts Manufacturer Approval"
(PMA) von der FAA für das "Type Design" zugelassenen "Forward and Aft
Cargo Compartment Door Seal" Baugruppe mit der Teilenummer (P/N)
D5237106020400, einschließlich aber nicht beschränkt auf PMA P/N
D5237106020400S, ausgerüstet sind.
Gerätenummer: 2846, EASA.A.064
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2022-04-08 - Amdt. 39-21950
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 2022-096 geführt.
Betrifft:
(ATA 26, 52) Fire Protection / Doors - Cargo Door Seals - Replacement / Operational Limitation / Placard
Installation
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
FAA AD 2022-04-08 - Amdt. 39-21950 herausgegeben oder per Entscheidung Nr. 2019/018/ED übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsanweisun-
11.04.2022
gen direkt in der Bundesrepublik Deutschland gültig und bedürfen keiner Umsetzung durch das Luftfahrt-
Bundesamt.
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LUFTTÜCHTIGKEITSANWEISUNGEN
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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.
11.04.2022
D-2022-096 Seite 2 von 2 165/2022
LUFTTÜCHTIGKEITSANWEISUNGEN
2022-2-672
[Federal Register Volume 87, Number 44 (Monday, March 7, 2022)]
[Rules and Regulations]
[Pages 12565-12569]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-04665]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0883; Project Identifier AD-2021-00307-T; Amendment 39-21950; AD
2022-04-08]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-16-01, which applied to
all Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2020-16-01 required
repetitive cleaning and greasing of affected cargo door seals (both original equipment manufacturer
(OEM) and parts manufacturer approval (PMA) parts). This AD was prompted by reports of low
halon concentration in the forward and aft cargo compartments due to air leakage through cargo
compartment door seals, and the FAA's determination that improved cargo door seals must be
installed and that certain flight operations must be limited until the improved cargo door seals are
installed. This AD retains certain actions required by AD 2020-16-01 and requires replacing certain
forward and aft cargo compartment door seals with new seals and installing a placard on the cargo
compartment doors; and for certain airplanes, revising the existing airplane flight manual (AFM) to
implement an operational limitation for certain routes. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective April 11, 2022.
The Director of the Federal Register approved the incorporation by reference of certain
publications listed in this AD as of April 11, 2022.
The Director of the Federal Register approved the incorporation by reference of a certain other
publication listed in this AD as of October 20, 2021 (86 FR 51265, September 15, 2021).
ADDRESSES: For Airbus service information identified in this final rule, contact Airbus SAS,
Airworthiness Office–EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
11.04.2022
internet http://www.airbus.com. For European Union Aviation Safety Agency (EASA) material
identified in this final rule, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may
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