Nachrichten für Luftfahrer 2020 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2020-0247
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 (Technical Support), Aéroport de Marseille Provence, 13725
Marignane Cedex, France, Telephone +33 (0)4 42 85 97 97, Fax +33 (0)4 42 85 99 66,
Web portal: https://keycopter.airbushelicopters.com > Technical Requests Management,
E-mail: support.technical-dyncomp.ah@airbus.com,
and TechnicalSupport.Helicopters@airbus.com.
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BUNDESREPUBLIK DEUTSCHLAND 2-577-20
NACHRICHTEN FÜR LUFTFAHRER 01 DEC 2020
DFS Deutsche Flugsicherung GmbH gültig ab: sofort
Büro der Nachrichten für Luftfahrer
Am DFS-Campus 7 · 63225 Langen · Germany
http://dfs.de
Redaktion: desk@dfs.de
LUFTTÜCHTIGKEITSANWEISUNGEN
LUFTTÜCHTIGKEITSANWEISUNGEN
Gemäß § 14 Abs. 1 der Betriebsordnung für Luftfahrtgerät (LuftBO) werden nachstehende Lufttüchtig-
keitsanweisungen (LTA‘s) veröffentlicht.
LTA-Nr: Titel Geräte-Nummer(n)
Änderungen:
-keine-
Neuausgaben:
-keine-
Weiterhin sind nachstehend die Lufttüchtigkeitsanweisungen abgedruckt, die durch die Europäische Agentur für
Flugsicherheit (EASA) herausgegeben oder per Entscheidung Nr. 2019/018/ED übernommen worden sind.
NfL 2-86-15 ist hierzu zu beachten.
LTA-Nr: AD-Nr. Titel Geräte-Nummer(n)
Änderungen:
D-2018-162R1 EASA AD 2020-0251 AIRBUS DEFENCE AND 2853 und EASA.A.186
SPACE S.A.
D-2018-163R1 EASA AD 2020-0258 AIRBUS S.A.S. 2846 und EASA.A.064
(Correction: 19.11.2020)
D-2018-333R1 EASA AD 2020-0257 AIRBUS HELICOPTERS 3049 und EASA.R.010
DEUTSCHLAND GmbH
D-2019-047R3 EASA AD 2020-0011R1 LEONARDO S.p.A. EASA.R.006
Neuausgaben:
D-2020-294 EASA AD 2020-0238 Fokker Services B.V. 2824 und EASA.A.037
D-2020-295 FAA AD 2020-21-02 Kidde Aerospace & Defense - keine -
D-2020-296 EASA AD 2020-0244 Rolls-Royce Deutschland EASA.E.036
Ltd & Co KG
D-2020-297 EASA AD 2020-0248 AIRBUS S.A.S. 2850 und EASA.A.015
D-2020-298 EASA AD 2020-0249 ATR-GIE Avions de 2847 und EASA.A.084
Transport Regional
D-2020-299 EASA AD 2020-0250 AIRBUS S.A.S. EASA.A.064
D-2020-300 EASA AD 2020-0252 PILATUS AIRCRAFT Ltd. EASA.A.594
D-2020-301 EASA AD 2020-0253 Rolls-Royce Deutschland 6326 und EASA.E.042
Ltd & Co KG
D-2020-302 EASA AD 2020-0254 BAE Systems 2852 und EASA.A.182
(Operations) Ltd
D-2020-303 EASA AD 2020-0256 LEONARDO S.p.A. 3051 und EASA.R.005
D-2020-304 FAA AD 2020-22-18 Rolls-Royce Corporation EASA.IM.E.040 und
FAA TCDS TE1CH
D-2020-305 FAA AD 2020-23-04 Gulfstream Aerospace EASA.IM.A.595 und
Corporation FAA TCDS T00021AT
D-2020-306 EASA AD 2020-0246 AIRBUS HELICOPTERS EASA.R.010
DEUTSCHLAND GmbH
D-2020-307 TC AD CF-2020-48 Airbus Canada Limited EASA.IM.A.570 und
Partnership TC TCDS A-236
D-2020-308 EASA AD 2020-0255 AIRBUS S.A.S. 2849, 2850,
EASA.A.004 und
EASA.A.015
D-2020-309 TC AD CF-2020-47 Bombardier Inc. EASA.IM.A.080 und
TC TCDS A-234
D-2020-310 TC AD CF-2020-49 Bombardier Inc. 2866, EASA.IM.A.009
und TC TCDS A-177
D-2020-311 TC AD CF-2020-50 Bombardier Inc. 2866, EASA.IM.A.009
und TC TCDS A-177
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dürfen
Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen
werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
LTA´s werden auch im Internet unter http://www.lba.de publiziert
Braunschweig, den 30. November 2020
LBA T 233.20394/NfL/201130
Das Luftfahrt-Bundesamt
Im Auftrag
Burlage
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2018-162R1 38144 Braunschweig
EASA AD 2020-0251 vom 11.11.2020 Fax: +49-531-2355-5298
email: ad@LBA.de
EADS CASA 19.11.2020
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS DEFENCE AND SPACE S.A.
Hersteller: EADS CASA, vormals Construcciones Aeronáuticas S.A. (CASA)
Muster: CN-235 / C-295
Baureihen: CN-235, CN-235-100, CN-235-200 und CN-235-300
Werknummern: Alle
Gerätenummer: 2853, EASA.A.186
Revisionsstand:
Diese LTA ersetzt D-2018-162 vom 06.07.2018
Airworthiness Directive der ausländischen Behörde:
EASA AD 2020-0251 vom 11.11.2020
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 2018-162R1 geführt.
Betrifft:
(ATA 53) Fuselage - Central Fuselage Frames 21, 23 and 24 / Wing Fitting Attachments - Inspections
(ATA 05) Time Limits / Maintenance Checks - Airworthiness Limitations List - Amendment
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 2020-0251 vom 11.11.2020 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-2018-162R1 Seite 1 von 1 524/2020
EASA AD No.: 2020-0251
Airworthiness Directive
AD No.: 2020-0251
Issued: 11 November 2020
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 DEFENCE & SPACE S.A. CN-235 aeroplanes
Effective Date: 25 November 2020
TCDS Number(s): EASA.A.186
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2018-0134 dated 25 June 2018.
ATA 53 – Fuselage – Central Fuselage Frames 21, 23 and 24 / Wing Fitting
Attachments – Inspections
ATA 05 – Time Limits / Maintenance Checks – Airworthiness Limitations List –
Amendment
Manufacturer(s):
EADS-CASA, formerly Construcciones Aeronáuticas S.A. (CASA)
Applicability:
CN-235, CN-235-100, CN-235-200 and CN-235-300 aeroplanes, all manufacturer serial numbers
(MSN).
Definitions:
For the purpose of this AD, the following definitions apply:
The applicable ALL: Airbus Defence & Space (D&S) CN-235 Airworthiness Limitations List (ALL)
DT-86-3001 Revision R dated 20 March 2018 and DT-06-3009 Revision A dated January 2007.
The AMP: The Aircraft Maintenance Programme (AMP), on the basis of which the operator or the
owner ensures the continuing airworthiness of each operated aeroplane. For affected CN-235
aeroplanes operated under EU regulations, compliance with the AMP is required by Commission
Regulation (EU) 1321/2014, Part M.A.301, paragraph 3.
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EASA AD No.: 2020-0251
The AOT: Airbus D&S Alert Operators Transmission (AOT) AOT-CN235-53-0005 Revision 2.
Groups: Group 1 are CN-235 and CN-235-100 aeroplanes.
Group 2 are CN-235-200 aeroplanes.
Group 3 are CN-235-300 aeroplanes.
Reason:
The airworthiness limitations and/or certification maintenance instructions for the EADS-CASA
CN-235 aeroplanes, which are approved by EASA, are currently defined and published in Airbus D&S
CN-235 ALL DT-86-3001 and DT-06-3009 documents. These instructions have been identified as
mandatory for continued airworthiness.
Failure to accomplish these instructions could result in an unsafe condition.
EASA previously issued AD 2018-0134 to require accomplishment of the actions specified in Airbus
D&S DT-86-3001 Revision R.
Since that AD was issued, damage tolerance analysis determined the need to amend inspections of
Primary Structural Elements (PSE) F47 (Central Fuselage Frame (FR) 24) and PSE F48 (Central
Fuselage FR24, Wing Fitting Attachment) and on Secondary Structural Elements (SSE) FC0203
(Machined Frames FR21 and FR24, Attachment to Wing Fittings) and SSE FC0304 (Machined Frames
FR21, FR23 and FR24). Airbus D&S issued the AOT, as defined in this AD, to provide inspection
instructions. It is expected that these instructions will be incorporated into the ALL at the next
Revision.
For the reason described above, this AD retains the requirements of EASA AD 2018-0134, which is
superseded, and requires accomplishment of the actions specified in the applicable ALL, as defined
in this AD, and in addition those specified in the AOT.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Inspection(s):
(1) Within the compliance times as specified in Table 1 of this AD, and, thereafter, at intervals not
to exceed the values specified in Table 2 of this AD, as applicable, accomplish a high frequency
eddy current (HFEC) and an ultrasonic (US) inspection of PSE F48 in accordance with the
instructions of the AOT.
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EASA AD No.: 2020-0251
Table 1 – Initial PSE F48 Inspection (see Note 1 of this AD)
MSN / Compliance Time
Group
Configuration (whichever occurs later, A or B)
A: Before exceeding 11 800 flight hours (FH) or 13 600 flight cycles
MSN 001 to (FC), whichever occurs first
062 inclusive B: Within 50 FH or 50 FC, whichever occurs first after the effective
1 date of this AD
A: Before exceeding 9 100 FH or 10 500 FC, whichever occurs first
MSN 063 and
higher B: Within 50 FH or 50 FC, whichever occurs first after the effective
date of this AD
A: Before exceeding 10 900 FH or 13 600 FC, whichever occurs first
MSN 001 to
062 inclusive B: Within 50 FH or 50 FC, whichever occurs first after the effective
date of this AD
2
A: Before exceeding 8 400 FH or 10 500 FC, whichever occurs first
MSN 063 and
higher B: Within 50 FH or 50 FC, whichever occurs first after the effective
date of this AD
All MSN, A: Before exceeding 13 400 FH or 15 200 FC, whichever occurs first
except L3-02 B: Within 50 FH or 50 FC, whichever occurs first after the effective
configuration date of this AD
3
A: Before exceeding 15 800 FH or 16 100 FC, whichever occurs first
L3-02
configuration B: Within 50 FH or 50 FC, whichever occurs first after the effective
date of this AD
Note 1: Unless indicated otherwise, the FH and FC specified in Table 1 of this AD are those
accumulated since first flight of the aeroplane.
Table 2 – Intervals (not to exceed)
Group Interval (FH or FC, whichever occurs first
since last inspection)
1 435 FH or 500 FC
2 401 FH or 500 FC
3 706 FH or 800 FC
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EASA AD No.: 2020-0251
(2) Within the compliance times and, thereafter, at intervals not to exceed the values specified in
Table 3 of this AD, as applicable, accomplish an HFEC inspection of PSE F47 in accordance with
the instructions of the AOT.
Table 3 – PSE F47 Inspection
Compliance Time Interval (FH or FC,
Group
(whichever occurs later, A or B) whichever occurs first)
A: Before exceeding 1 131 FH or 1 300 FC, whichever
occurs first since the last inspection 1 131 FH or
1
B: Within 50 FH or 50 FC, whichever occurs first after the 1 300 FC
effective date of this AD
A: Before exceeding 1 044 FH or 1 300 FC, whichever
occurs first after the last inspection 1 044 FH or
2
B: Within 50 FH or 50 FC, whichever occurs first after the 1 300 FC
effective date of this AD
A: Before exceeding 1 148 FH or 1 300 FC, whichever
occurs first after the last inspection 1 148 FH or
3
B: Within 50 FH or 50 FC, whichever occurs first after the 1 300 FC
effective date of this AD
(3) For CN-235-300 aeroplanes in Maritime Patrol (SM01) configuration: Within the compliance
time and, thereafter, at intervals not to exceed the values specified in Table 4 of this AD,
accomplish an HFEC and US inspection of SSE FC0203 and an HFEC inspection of SSE FC0304 in
accordance with the instructions of the AOT.
Table 4 – SSE FC0203 and SSE FC0304 Inspection
Compliance Time Interval (FH or FC,
SSE
(whichever occurs later, A or B) whichever occurs first)
A: Within 4 655 FH or 1 500 FC, whichever occurs first
since the last inspection 4 655 FH or
FC0203
B: Within 50 FH or 50 FC, whichever occurs first after 1 500 FC
the effective date of this AD
A: Within 24 638 FH or 7 940 FC, whichever occurs first
since the last inspection 24 638 FH or
FC0304
B: Within 50 FH or 50 FC, whichever occurs first after 7 940 FC
the effective date of this AD
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EASA AD No.: 2020-0251
Maintenance Tasks and Replacement of Life Limited Parts:
(4) From the effective date of this AD, accomplish the following actions, as specified in the ALL, as
applicable to aeroplane model and depending on aeroplane configuration:
(4.1) Replace each component before exceeding the applicable life limit, and
(4.2) Within the thresholds and intervals, accomplish all applicable maintenance tasks.
Corrective Action(s):
(5) In case of finding discrepancies during accomplishment of any task as required by paragraph
(1), (2), (3) or (4) of this AD, as applicable, before next flight, accomplish the applicable
corrective action(s) in accordance with the applicable Airbus D&S maintenance documentation.
If a detected discrepancy cannot be corrected by using existing Airbus D&S instructions, before
next flight, contact Airbus D&S for approved instructions and accomplish those instructions
accordingly.
Aircraft Maintenance Programme (AMP) Revision:
(6) Within 12 months after the effective date of this AD, revise the approved AMP, on the basis of
which the operator or the owner ensures the continuing airworthiness of each operated
aeroplane, by incorporating the limitations, tasks and associated thresholds and intervals
described in the ALL, as applicable to aeroplane model and depending on aeroplane
configuration.
Credit:
(7) For an AMP that, on the effective date of this AD, is already updated to incorporate the
maintenance tasks and life limitations as specified in Airbus D&S ALL Revision R, that action
ensures the continued accomplishment of those tasks and limitations.
Consequently, for an aeroplane to which that AMP applies, it is acceptable to accomplish the
new and more restrictive tasks and limitations, as applicable to aeroplane model and
depending on aeroplane configuration, as defined in, and within the compliance times, as
specified in, the ALL, to comply with paragraph (4) of this AD.
For that AMP, it is acceptable to incorporate the new and more restrictive tasks and limitations,
as applicable to aeroplane model and depending on aeroplane configuration, as defined in the
ALL, into the AMP to comply with paragraph (6) of this AD.
Recording AD Compliance:
(8) When the AMP of an aeroplane has been revised as required by paragraph (6) or (7) of this AD,
as applicable, that action ensures continued accomplishment of the tasks as required by
paragraphs (4) and (5) of this AD for that aeroplane. Consequently, after revising the AMP, as
required by paragraph (6) or (7) 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.
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