Nachrichten für Luftfahrer 2021 Teil 2 (weicht ggf. von Druckversion ab)
LUFTTÜCHTIGKEITSANWEISUNGEN
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(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, may approve AMOCs for this AD.
Send your proposal to: Kristi Bradley, Aviation Safety Engineer, General Aviation & Rotorcraft
Section, International Validation Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222-5110; email 9-AVS-AIR-730-AMOC@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part
91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office or certificate holding district office,
before operating any aircraft complying with this AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD 2007-0256, dated September 19, 2007. You may view the
EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2013-0752.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 2500, Cabin Equipment/Furnishings.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference of the service
information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD,
unless the AD specifies otherwise.
(i) Pacific Scientific Service Bulletin SB 25-1111432, dated May 22, 2007.
(ii) [Reserved]
(3) For service information identified in this AD, contact Meggitt Services, 1785 Voyager Ave.,
Simi Valley, CA 93063, telephone 877-666-0712 or at CustomerResponse@meggitt.com.
(4) You may view this service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. For information
on the availability of this material at the FAA, call 817-222-5110.
(5) You may view this service information that is incorporated by reference at the National
Archives and Records Administration (NARA). For information on the availability of this material at
NARA, email fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued on March 25, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification Service.
[FR Doc. 2021-06979 Filed 4-5-21; 8:45 am]
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7
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T12 -
D-2021-128 38144 Braunschweig
EASA AD 2021-0122 vom 06.05.2021 Fax: +49-531-2355-5197
email: AD@LBA.de
AIRBUS HELICOPTERS 12.05.2021
DEUTSCHLAND
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: AIRBUS HELICOPTERS DEUTSCHLAND GmbH
Hersteller: Airbus Helicopters Deutschland GmbH (vormals Eurocopter Deutschland
GmbH), Airbus Helicopters Inc. (vormals American Eurocopter LLC)
Muster: MBB-BK117
Baureihen: MBB-BK117 A-1, MBB-BK117 A-3, MBB-BK117 A-4, MBB-BK117 B-1,
MBB-BK117 B-2, MBB-BK117 C-1, MBB-BK117 C-2 und MBB-BK117 D-2
Werknummern: Alle
Gerätenummer: 3049, EASA.R.010
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2021-0122 vom 06.05.2021
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 2021-128 geführt.
Betrifft:
(ATA 05) Time Limits / Maintenance Checks - Airworthiness Limitation Section - Tension Torsion Straps - Storage
Life Limit
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 2021-0122 vom 06.05.2021 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.
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EASA AD No.: 2021-0122
Airworthiness Directive
AD No.: 2021-0122
Issued: 06 May 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 DEUTSCHLAND GmbH MBB-BK117 helicopters
Effective Date: 20 May 2021
TCDS Number(s): EASA.R.010
Foreign AD: Not applicable
Supersedure: None
ATA 05 – Time Limits / Maintenance Checks – Airworthiness Limitation Section –
Tension Torsion Straps – Storage Life Limit
Manufacturer(s):
Airbus Helicopters Deutschland GmbH (AHD), formerly Eurocopter Deutschland GmbH, Eurocopter
Hubschrauber GmbH, Messerschmitt-Bölkow-Blohm GmbH; Airbus Helicopters Inc., formerly
American Eurocopter LLC
Applicability:
MBB-BK117 A-1, MBB-BK117 A-3, MBB-BK117 A-4, MBB-BK117 B-1, MBB-BK117 B-2,
MBB-BK117 C-1, MBB-BK117 C-2 and MBB-BK117 D-2 helicopters, all serial numbers.
Definitions:
For the purpose of this AD, the following definitions apply:
Bendix TT-Strap: Tension Torsion (TT) Straps, having Part Number (P/N) 2604067 or P/N 117-14110.
Lord TT-Strap: TT-Straps, having P/N J17322-1, P/N 117-14111 or P/N B622M10T1001.
The ASB: Airbus Helicopters (AH) Alert Service Bulletin (ASB) MBB-BK117-10A-133, ASB MBB-BK117
C-2-62A-014, or ASB MBB-BK117 D-2-62A-008, as applicable.
Cure date: The cure date of a TT-Strap can be determined by using the information provided in the
ASB, or by contacting AHD for applicable instructions.
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Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
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EASA AD No.: 2021-0122
Storage life: Calendar time accumulated by a TT-Strap since cure date, including the calendar time
accumulated after first installation on a helicopter, up to the date of first flight after first installation
on a helicopter.
Time in service: Calendar time accumulated by a TT-Strap since first flight after first installation on a
helicopter.
Total life: Calendar time accumulated by a TT-Strap since cure date, which is the sum of storage life
and time in service.
The SLL: Service life limit (SLL), as applicable to the part, identified in the Airworthiness Limitation
Section of the applicable Aircraft Maintenance Manual.
Serviceable part: Lord TT-Straps, as defined in this AD, eligible for installation, and having a storage
life not exceeding 5 years.
Reason:
It has been determined that ageing of the elastomeric material of certain TT-Straps, during the
period since manufacturing date up to first flight on a helicopter, may affect its structural
characteristics.
This condition, if not corrected, could lead to premature failure of a TT-Strap, possibly resulting in
loss of control of the helicopter.
To address this potential unsafe condition, AHD issued the ASB, providing instructions to implement
limits for storage life, as defined in this AD, of certain TT-Straps.
For the reason described above, this AD requires implementation of those storage life limits, and
provides conditions for installation of parts. This AD also requires removal from service of Bendix
TT-Straps, as defined in this AD, and prohibits (re)installation of those straps.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Replacement:
(1) Within the compliance time as specified in Table 1 of this AD, as applicable, replace each
Lord TT-Strap and Bendix TT-Strap with a serviceable part in accordance with the instructions of
the ASB.
27.05.2021
TE.CAP.00110-010 © European Union 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
LUFTTÜCHTIGKEITSANWEISUNGEN
2021-2-615
EASA AD No.: 2021-0122
Table 1 – TT-Strap Replacement (see Note 1 of this AD)
Storage Life Total Life Compliance Time
Before exceeding the SLL, or before the storage
5 years or less Not relevant
life exceeds 5 years, whichever occurs first
Before the total life exceeds 17 years, or within
2 months after the effective date of this AD,
17 years or less
whichever occurs later, but not exceeding the
SLL
More than 5 During the next helicopter periodical inspection
More than 17
years or within 2 months, whichever occurs later after
years, but less
the effective date of this AD, but not exceeding
than 20 years
the SLL
Within 2 months after the effective date of this
20 years or more
AD, but not exceeding the SLL
Note 1: Unless specified otherwise, the storage life and total life calendar time periods indicated in
Table 1 of this AD are those accumulated, on the effective date of this AD, by the affected TT-Strap.
Parts Installation:
(2) From the effective date of this AD, do not install on any helicopter a Bendix TT-Strap.
(3) From the effective date of this AD, it is allowed to install on any helicopter a Lord TT-Strap,
provided the first flight of that helicopter after that installation is accomplished before the
storage life of that TT-Strap exceeds 5 years and that, following installation, the TT-strap is
replaced before exceeding the SLL.
Ref. Publications:
AH ASB MBB-BK117-10A-133 original issue dated 20 March 2021, and revision 1 dated 06 May
2021.
AH ASB MBB-BK117 C-2-62A-014 original issue dated 20 March 2021, and revision 1 dated 06 May
2021.
AH ASB MBB-BK117 D-2-62A-008 original issue dated 20 March 2021, and revision 1 dated 06 May
2021.
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 31 March 2021 as PAD 21-051 for consultation until 28 April 2021. No
comments were received during the consultation period.
27.05.2021
TE.CAP.00110-010 © European Union 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
LUFTTÜCHTIGKEITSANWEISUNGEN
2021-2-615
EASA AD No.: 2021-0122
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 Deutschland GmbH, Industriestrasse 4, 86609 Donauwörth,
Federal Republic of Germany, Telephone: + 33 (0)4 42 85 97 97;
Web portal: https://keycopter.airbushelicopters.com > Technical Request Management
E-mail: customersupport.helicopters@airbus.com.
27.05.2021
TE.CAP.00110-010 © European Union 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
LUFTTÜCHTIGKEITSANWEISUNGEN
2021-2-615
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T12 -
D-2021-129 38144 Braunschweig
TC AD CF-2021-18 vom 06.05.2021 Fax: +49-531-2355-5197
email: AD@LBA.de
AIRBUS CANADA LP 12.05.2021
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Airbus Canada Limited Partnership
Hersteller: Airbus Canada Limited Partnership,
vormals C Series Aircraft Limited Partnership (CSALP), Bombardier Inc.
Muster: BD-500
Baureihen: BD-500-1A10 und BD-500-1A11
Werknummern: Alle
Gerätenummer: EASA.IM.A.570, TC TCDS A-236
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
TC AD CF-2021-18 vom 06.05.2021
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 2021-129 geführt.
Betrifft:
(ATA 32) Landing Gear - Main Landing Gear Lower Spindle Pin Corrosion
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
TC AD CF-2021-18 vom 06.05.2021 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.
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LUFTTÜCHTIGKEITSANWEISUNGEN
TP 7245E
2021-2-615
1 of 2
AD Number: CF-2021-18
AIRWORTHINESS DIRECTIVE
This Airworthiness Directive (AD) is issued pursuant to Canadian Aviation Regulation (CAR) 521.427.
No person shall conduct a take-off or permit a take-off to be conducted in an aircraft that is in their legal
custody and control, unless the requirements of CAR 605.84 pertaining to ADs are met. Standard 625 -
Aircraft Equipment and Maintenance Standards Appendix H provides information concerning alternative
means of compliance (AMOC) with ADs.
Number: Effective Date:
CF-2021-18 20 May 2021
ATA: Type Certificate:
32 A-236
Subject:
Landing Gear – Main Landing Gear (MLG) Lower Spindle Pin Corrosion
Applicability:
Airbus Canada Limited Partnership (formerly C Series Aircraft Limited Partnership, Bombardier Inc.)
model BD-500-1A10 and BD-500-1A11 aeroplanes, all serial numbers.
Compliance:
As indicated below, unless already accomplished.
Background:
There have been several in-service findings of corrosion on the flange of the MLG lower spindle pin. An
investigation revealed that micro-fretting of the anti-rotation washer at the spindle pin flange surface
causes abrasion of the protective coating and leaves the flange area susceptible to corrosion.
The MLG lower spindle pin is a principal structural element (PSE). If the corrosion progresses from the
flange to the adjacent radius area, it can lead to low cycle fatigue (LCF) cracking, failure of the MLG lower
spindle pin, and collapse of the MLG.
In order to mitigate this unsafe condition, this AD mandates initial and repetitive inspections of the MLG
lower spindle pin to detect damage, and to repair or replace the MLG lower spindle pin if damage is
found. This AD is considered interim action and further AD action may follow.
For the purposes of airworthiness monitoring and development of further corrective actions, operators are
strongly encouraged to complete and return the Service Bulletin Findings Record as detailed in Airbus
Canada Service Bulletin (SB) BD500-321003 after completing each inspection.
Corrective Actions:
Part I – Initial Inspection
Inspect and repair or replace, as applicable, the left and right MLG lower spindle pin in accordance with
the Accomplishment Instructions of Airbus Canada SB BD500-321003 Issue 001, dated 13 April 2021, or
later revisions approved by the Chief, Continuing Airworthiness, Transport Canada, within the following
compliance time:
A. MLG having accumulated, as of the effective date of this AD, 5500 total flight cycles (FC) or more:
within 6 months from the effective date of this AD.
B. MLG having accumulated, as of the effective date of this AD, less than 5500 total FC, whichever
occurs last:
1. Whichever occurs first: before accumulating 5500 total FC on the MLG or within 36 months from
the effective date of this AD; or
27.05.2021
2. Within 12 months from the effective date of this AD.
LUFTTÜCHTIGKEITSANWEISUNGEN
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Part II – Repeat Inspection
Thereafter, at intervals of 3000 FC or 24 months, whichever occurs first, carry out repetitive inspections
and repair or replacement, as applicable, of the left and right MLG lower spindle pin in accordance with
the Accomplishment Instructions of Airbus Canada SB BD500-321003 Issue 001, dated 13 April 2021, or
later revisions approved by the Chief, Continuing Airworthiness, Transport Canada.
Authorization:
For the Minister of Transport,
ORIGINAL SIGNED BY
Matthew Weeks
Acting Chief, Continuing Airworthiness
Issued on 6 May 2021
Contact:
Barry Devereux, Continuing Airworthiness, Ottawa, telephone 888-663-3639, facsimile 613-996-9178 or
e-mail TC.AirworthinessDirectives-Consignesdenavigabilite.TC@tc.gc.ca or any Transport Canada
Centre.
27.05.2021
LUFTTÜCHTIGKEITSANWEISUNGEN
2021-2-615
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T12 -
D-2021-130 38144 Braunschweig
ANAC BAD 2021-05-01 - Amdt. 39-1480 Fax: +49-531-2355-5197
email: AD@LBA.de
EMBRAER 14.05.2021
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Yaborã Indústria Aeronáutica S.A.
Hersteller: Yaborã Indústria Aeronáutica S.A., vormals Embraer S.A., Empresa Brasileira
de Aeronáutica S.A. (EMBRAER)
Muster: ERJ 190
Baureihen: ERJ 190-300 und ERJ 190-400
Werknummern: Alle
Betroffen sind Flugzeuge mit installierter Hydrauliksystem Nr. 3
Wechselstrom-Hydraulikpumpe (Alternating Current Motor Pump)
ACMP 3A mit der Part-Nummer (P/N) 3033041-101.
Gerätenummer: EASA.IM.A.071, ANAC TCDS EA-2005T13
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
ANAC BAD 2021-05-01 - Amdt. 39-1480
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 2021-130 geführt.
Betrifft:
(ATA 29) Hydraulic Power - Alternating Current Motor Pump - 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 2021-05-01 - Amdt. 39-1480 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.
27.05.2021
D-2021-130 Seite 1 von 1 215/2021
