Nachrichten für Luftfahrer 2019 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2019-0055-E
Emergency Airworthiness Directive
AD No.: 2019-0055-E
[Correction: 19 March 2019]
Issued: 18 March 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):
BRP-ROTAX GmbH & Co KG Rotax 912 and 915 engines
Effective Date: 20 March 2019
TCDS Number(s): EASA.E.121
Foreign AD: Not applicable
Supersedure: None
ATA 73 – Engine fuel and Control – Fuel Pump Assembly – Inspection / Replacement
Manufacturer(s):
BRP-Rotax GmbH & Co KG, formerly BRP-Powertrain GmbH & Co. KG, Bombardier-Rotax GmbH &
Co. KG, Bombardier-Rotax GmbH
Applicability:
Rotax 912 iSc2 Sport, 912 iSc3 Sport and Rotax 915 iSc3 A engines, all serial numbers (s/n).
These engines are known to be installed on, but not limited to, various general aviation aeroplane
types and models. The installation of these engines was either done by the respective aeroplane
manufacturer, or through modification of the aeroplane by Supplemental Type Certificate (STC).
Definitions:
For the purpose of this AD, the following definitions apply:
The ASB: BRP-Rotax Alert Service Bulletin (ASB) ASB-912 i-010 / ASB-915 i A-006 (single document).
Affected part: Fuel pump assemblies, having part number (P/N) 889696 (part of assembly
P/N 889697) and s/n from 180500 to 189999 inclusive; or having P/N 889698 (part of assembly
P/N 889699) and s/n from 180500 to 189999 inclusive.
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EASA AD No.: 2019-0055-E
Serviceable part: Fuel pump assemblies which are not an affected part; or an affected part which
passes an inspection (no defects found) in accordance with the instructions of the ASB.
Groups: Group 1 engines have an affected part installed. Group 2 engines do not have an affected
part installed.
Reason:
Fuel leakage was observed on an engine still on the production line. Subsequent investigation
determined a manufacturing issue as root cause of the fuel leak, and a batch of fuel pump
assemblies was identified which could experience similar fuel leaks.
This condition, if not detected and corrected, could lead to engine fire, possibly resulting in a forced
landing with consequent damage to the aeroplane and injury to occupants.
To address this potential unsafe condition, BRP-Rotax issued the ASB, providing inspection
instructions.
For the reason described above, this AD requires a one-time inspection of the affected parts and,
depending on findings, replacement. This AD also provides additional requirements for installation
of a fuel pump assembly on an engine.
This AD is republished to correct a typographical error in the second paragraph of the Required
Action(s) and Compliance Time(s) section.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Inspection:
(1) For Group 1 engines: Before next engine operation after the effective date of this AD, inspect
the affected part in accordance with the instructions of the ASB.
Corrective action(s):
(2) If, during the inspection as required by paragraph (1) of this AD, any discrepancy is found, as
identified in the ASB, before next engine operation, replace the affect part in accordance with
the instructions of the ASB.
Part(s) Installation:
(3) For Group 1 and Group 2 engines: From the effective date of this AD, it is allowed to install on
any engine a fuel pump assembly, provided that it is a serviceable part, as defined in this AD.
Ref. Publications:
BRP-Rotax ASB-912 i-010 / ASB-915 i A-006 (single document) original issue dated 13 March 2019.
The use of later approved revisions of the above-mentioned document is acceptable for compliance
with the requirements of this AD.
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EASA AD No.: 2019-0055-E
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 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.
5. For any question concerning the technical content of the requirements in this AD, please
contact: BRP-Rotax GmbH & Co KG, Telephone: +43 7246 601 0, Fax: +43 7246 601 9130,
E-mail: airworthiness@brp.com, Website www.flyrotax.com.
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An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2019-071 38144 Braunschweig
EASA AD 2019-0052 vom 14.03.2019 Fax: +49-531-2355-5298
email: ad@LBA.de
PZL-SWIDNIK 19.03.2019
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: WSK ''PZL-SWIDNIK'' S.A.
Hersteller: WSK ''PZL-SWIDNIK'' S.A.
Muster: PZL SW-4
Baureihen: PZL SW-4
Werknummern: Alle
Gerätenummer: EASA.R.100
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2019-0052 vom 14.03.2019
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls Airworthiness
Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2019-071 geführt.
Betrifft:
(ATA 78) Exhaust - Exhaust Ducts and Clamps - Inspection / Modification
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 2019-0052 vom 14.03.2019 herausgegeben oder per Entscheidung Nr. 02/2003 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-2019-071 Seite 1 von 1 126/2019
EASA AD No.: 2019-0052
Airworthiness Directive
AD No.: 2019-0052
Issued: 14 March 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(s):
WSK “PZL – ŚWIDNIK” S.A. PZL SW-4 helicopters
Effective Date: 21 March 2019
TCDS Number(s): EASA.R.100
Foreign AD: Not applicable
Supersedure: None
ATA 78 – Exhaust – Exhaust Ducts and Clamps – Inspection / Modification
Manufacturer(s):
WSK “PZL – Świdnik” S.A.
Applicability:
PZL SW-4 helicopters, all serial numbers (s/n).
Definitions:
For the purpose of this AD, the following definitions apply:
Affected duct: Exhaust ducts, Part Number (P/N) 60.04.102.00.01 (any revision) and P/N
60.04.102.00.02 revision A (right-hand (RH) ducts); and P/N 60.04.103.00.00 revision K or earlier
(left-hand (LH) ducts).
Clamp: Exhaust duct clamps, P/N 60.04.105.00.00.
Improved duct: Exhaust Ducts, P/N 60.04.102.00.02 revision B or later (RH ducts); and
P/N 60.04.103.00.00 revision L or later (LH ducts). Each part is identified by a permanent mark
stating the P/N, revision level and year of manufacture.
The MB: WSK “PZL-ŚWIDNIK” S.A. PZL SW-4 Mandatory Bulletin (MB) No. BO-60-18-94.
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EASA AD No.: 2019-0052
Groups: Group 1 helicopters are those with s/n 60.02.02, 60.03.23, 60.03.24, 60.04.02, 60.04.03,
60.04.05 and 60.04.06.
Group 2 helicopters are those with s/n 60.01.04, 60.02.02, 60.03.22, 60.03.23, 60.03.24, 60.04.02,
60.04.03, 60.04.04, 60.04.05, 60.04.06 and 60.04.07.
Group 3 helicopters are those with s/n 60.04.08, 60.04.09 and 60.04.10, and later s/n.
Reason:
Occurrences were reported of finding cracked clamps and damaged affected ducts. Subsequent
investigation determined that the reason of the clamp cracking could be attributed to imperfect
maintenance installation instructions, application of which might introduce stress induced cracks.
Investigation of cracked exhaust ducts determined that a manufacturing deficiency (missing specific
heat treatment) may have led to crack initiation.
This condition, if not detected and corrected, could lead to detachment of a clamp or affected duct,
possibly resulting in impact or thermal damage on rotors and consequent reduced control of the
helicopter.
Prompted by these events, WSK “PZL – Świdnik” S.A. improved the applicable clamp installation
maintenance instructions and identified helicopters on which clamps could be installed not in
accordance with those improved maintenance instructions. Additionally, WSK “PZL – Świdnik” S.A.
developed improved manufacturing procedures (specific heat treatment) of exhaust ducts and
some ducts manufactured in accordance with those improved procedures have been installed
(Group 3 helicopters). WSK “PZL – Świdnik” S.A. also issued the MB to provide inspection and
modification instructions for Group 1 and Group 2 helicopters.
For the reasons described above, this AD requires a one-time inspection of clamps on certain
helicopters, repetitive inspections of affected ducts and, depending on findings, repair or
replacement. This AD also requires a modification by installing improved exhaust ducts, which
constitutes terminating action for repetitive inspections. This AD also introduces part installation
restrictions to prevent installation of affected ducts.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Inspection(s):
(1) Group 1 helicopters: Within 25 flight hours (FH) after the effective date of this AD, inspect each
clamp in accordance with the instructions of Chapter II section 1 of the MB.
(2) Group 2 helicopters: Within 25 FH after the effective date of this AD and, thereafter, at
intervals not to exceed 25 FH, inspect each affected duct in accordance with the instructions of
Chapter II section 2 of the MB.
Corrective Action(s):
(3) If, during the inspection as required by paragraph (1) of this AD, any damaged clamp is
detected, before next flight, replace the damaged clamp with a new part in accordance with
the instructions of Chapter II section 1 of the MB.
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EASA AD No.: 2019-0052
(4) If, during any inspection as required by paragraph (2) of this AD, any cracked duct is detected,
before next flight, accomplish a repair of the affected duct in accordance with the instructions
of Chapter II section 2 of the MB, or replace the affected duct with an improved duct in
accordance with the instructions of Chapter II section 3 of the MB.
Modification:
(5) Group 2 helicopters: Unless accomplished as required by paragraph (4) of this AD, for both RH
and LH ducts, within 12 months after the effective date of this AD, modify the helicopter by
replacing each affected duct with an improved duct in accordance with the instructions of
Chapter II section 3 of the MB.
Terminating Action:
(6) Modification of a helicopter as required by paragraph (5) of this AD, or replacement of both RH
and LH ducts as required by paragraph (4) of this AD, as applicable, constitutes terminating
action for repetitive inspections as required by paragraph (2) of this AD for that helicopter.
Parts Installation:
(7) Do not install on any helicopter an affected duct, as required by paragraph (7.1) and (7.2) of
this AD, as applicable.
(7.1) Group 2 helicopters: After modification of the helicopter as required by paragraph (5) of
this AD, or after replacement of both RH and LH ducts as required by paragraph (4) of this
AD, as applicable.
(7.2) Group 3 helicopters: From the effective date of this AD.
Ref. Publications:
WSK “PZL-ŚWIDNIK” S.A. PZL SW-4 MB No. BO-60-18-94 original issue dated 06 March 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. Based on the required actions and the compliance time, EASA have decided to issue a Final AD
with Request for Comments, postponing the public consultation process until after publication.
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.
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EASA AD No.: 2019-0052
5. For any question concerning the technical content of the requirements in this AD, please
contact: WSK "PZL- Świdnik" S.A., Al. Lotników Polskich 1, 21-045 Świdnik, Poland,
Telephone: (+48) 81 722 6140; E-mail: PL-CustomerSupport.AW@leonardocompany.com.
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2019-072 38144 Braunschweig
FAA AD 2019-01-08 - Amdt. 39-19547 Fax: +49-531-2355-5298
email: ad@LBA.de
BOEING 19.03.2019
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: The Boeing Company
Hersteller: The Boeing Company
Muster: BOEING 777
Baureihen: 777-200, 777-200LR, 777-300 und 777-300ER
Werknummern: Gemäß Boeing Special Attention Service Bulletin (SB) 777- 25-0649 Revision 1
vom 06.10.2017
Gerätenummer: 2863, EASA.IM.A.003, FAA TCDS T00001SE
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2019-01-08 - Amdt. 39-19547
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls Airworthiness
Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2019-072 geführt.
Betrifft:
(ATA 25) Equipment - Galley Mounted Seat Fittings - Modification
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
FAA AD 2019-01-08 - Amdt. 39-19547 herausgegeben oder per Entscheidung Nr. 02/2003 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-2019-072 Seite 1 von 1 104/2019
[Federal Register Volume 84, Number 32 (Friday, February 15, 2019)]
[Rules and Regulations]
[Pages 4318-4320]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-02159]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0581; Product Identifier 2018-NM-029-AD; Amendment 39-19547; AD
2019-01-08]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company
Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by a report that
showed a non-compliance exists on some in-service galley attendant seat fitting installations. The
non-compliance could result in flight attendant seats failing in a high-G crash. This AD requires
modifications for galley mounted seat fittings. We are issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective March 22, 2019.
The Director of the Federal Register approved the incorporation by reference of a certain
publication listed in this AD as of March 22, 2019.
ADDRESSES: For service information identified in this final rule, contact Boeing Commercial
Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57,
Seal Beach, CA 90740-5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You
may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St.,
Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195.
It is also available on the internet at http://www.regulations.gov by searching for and locating Docket
No. FAA-2018-0581.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2018-0581; or in person at Docket Operations between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the
regulatory evaluation, any comments received, and other information. The address for Docket
1
