Nachrichten für Luftfahrer 2015 Teil 2 (weicht ggf. von Druckversion ab)
(ii) Reserved.
(3) For service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-
227-1221.
(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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate,
Aircraft Certification Service.
10
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2015-294 38144 Braunschweig
EASA Emergency AD 2015-0239-E vom Fax: +49-531-2355-5298
18.12.2015 email: ad@LBA.de
AIRBUS HELICOPTERS 21.12.2015
DRINGEND!
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: AIRBUS HELICOPTERS
Hersteller: Airbus Helicopters (vormals Eurocopter, Eurocopter France, Aerospatiale)
Muster: AS 332
EC 225
Baureihen: AS 332 C, AS 332 C1, AS 332 L, AS 332 L1, AS 332 L2 und EC 225 LP
Werknummern: Alle
Betroffen sind Hubschrauber, die mit einem Notschwimmerwerk (Emergency
Flotation Gear) ausgerüstet sind.
Gerätenummer: 3043, EASA.R.002
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA Emergency AD 2015-0239-E vom 18.12.2015
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 2015-294 geführt.
Betrifft:
(ATA 32) Landing Gear - Emergency Flotation Gear Upper Fitting Attaching Screws - Inspection /
Replacement
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen
Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb
genommen werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden
sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsan-
weisung EASA Emergency AD 2015-0239-E vom 18.12.2015 herausgegeben oder per Entschei-
dung Nr. 02/2003 übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsan-
weisungen 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 gültige Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und
im Internet unter www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt
keinem Verwaltungsverfahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2015-294 Seite 1 von 1 513/2015
EASA AD No.: 2015-0239-E
Emergency Airworthiness Directive
AD No.: 2015-0239-E
Issued: 18 December 2015
Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Regulation (EC) 216/2008 on behalf of the European Union, its Member States and of the
European third countries that participate in the activities of EASA under Article 66 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 (EC) 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS HELICOPTERS AS 332 and EC 225 helicopters
Effective Date: 22 December 2015
TCDS Number(s): EASA.R.002
Foreign AD: Not applicable
Supersedure: None
ATA 32 – Landing Gear – Emergency Flotation Gear Upper Fitting Attaching Screws –
Inspection / Replacement
Manufacturer(s):
Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)
Applicability:
AS 332 C, AS 332 C1, AS 332 L, AS 332 L1, AS 332 L2 and EC 225 LP helicopters, all manufacturer
serial numbers, if equipped with emergency flotation gear.
Reason:
An occurence was reported of rupture of a screw on the rear upper fitting on the left hand (LH)
emergency flotation gear on an AS 332 helicopter. Investigations have not yet identified the root
cause of this failure.
This condition, if not detected and corrected, could result, in case of ditching, in failure of an
emergency flotation system and, consequently, unstable floating of the helicopter, possibly
resulting in injuy to the occupants.
To address this potential unsafe condition, Airbus Helicopters (AH) issued AS332 Emergency Alert
Service Bulletin (ASB) 05.01.06 and EC225 ASB 05A047 (hereafter referred to as ‘the applicable ASB’
in this AD), providing inspection instructions.
TE.CAP.00111-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 2
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An agency of the European Union
EASA AD No.: 2015-0239-E
For the reason described above, this AD requires repetitive inspections of the lower screws of the
rear upper fitting on the rear LH and right hand (RH) emergency flotation gears and, depending on
findings, accomplishment of applicable corrective action(s).
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
(1) Within 15 flight hours (FH) after the effective date of this AD, and, thereafter, at intervals not to
exceed 15 FH, inspect the heads of the three (3) screws on the rear upper fitting of each
emergency flotation gear, both LH and RH sides, in accordance with the instructions of
paragraph 3.B.1 of the applicable ASB.
(2) If, during any inspection as required by paragraph (1) of this AD, at least one screw head moves
or is found missing on one fitting, before the next flight when the emergency flotation system
must be armed, replace the two lower screws and the upper screw on that fitting in accordance
with the instructions of paragraph 3.B.2 of the applicable ASB.
(3) Replacement of screws on a helicopter, as required by paragraph (2) of this AD, does not
constitute terminating action for the repetitive inspections as required by paragraph (1) of this
AD for that helicopter.
Ref. Publications:
Airbus Helicopters AS332 Emergency ASB 05.01.06, original issue, dated 18 December 2015.
Airbus Helicopters EC225 Emergency ASB 05A047, original issue, dated 18 December 2015.
The use of later approved revisions of these documents (that may be published as standard SB
and/or separately revised) 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 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. For any question concerning the technical content of the requirements in this AD, please
contact: Airbus Helicopters (EBSESB) – Aéroport de Marseille Provence 13725 Marignane
Cedex, France; Telephone +33 (4) 42 85 97 97; Fax +33 (4) 42 85 99 66;
E-mail: Directive.technical-support@airbus.com.
TE.CAP.00111-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 2
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An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2015-295 38144 Braunschweig
EASA AD 2015-0235 vom 18.12.2015 Fax: +49-531-2355-5298
email: ad@LBA.de
ENSTROM 21.12.2015
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: Enstrom Helicopter Corporation
Hersteller: Enstrom Helicopter Corporation
Muster: F-28, 280
Baureihen: F-28A, F-28C, F-28C-2, 280 und 280C
Werknummern: Alle
Gerätenummer: 3041, EASA.IM.R.122, FAA TCDS H1CE
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2015-0235 vom 18.12.2015
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 2015-295 geführt.
Betrifft:
(ATA 04) Life limited items - Airworthiness limitation Section Amendment / Implementation
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen
Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb
genommen werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden
sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsan-
weisung EASA AD 2015-0235 vom 18.12.2015 herausgegeben oder per Entscheidung Nr. 02/2003
übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsan-
weisungen 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 gültige Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und
im Internet unter www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt
keinem Verwaltungsverfahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2015-295 Seite 1 von 1 514/2015
EASA AD No.: 2015-0235
Airworthiness Directive
AD No.: 2015-0235
Issued: 18 December 2015
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) 216/2008 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 66 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 (EC) 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name: Type/Model designation(s):
ENSTROM HELICOPTERS CORPORATION F-28 and 280 helicopters
Effective Date: 28 December 2015
TCDS Number(s): EASA.IM.R.122
Foreign AD: Not applicable
Supersedure: None
ATA 04 – Life limited items - Airworthiness limitation Section Amendment /
Implementation
Manufacturer(s):
Enstrom Helicopter Corporation
Applicability:
Enstrom F-28A, F-28C, F-28C-2, 280 and 280C helicopters, all variants, all serial numbers.
Reason:
The airworthiness limitations applicable to the Enstrom F-28 and 280 helicopters are listed in the
Federal Aviation Administration Type Certificate Data Sheet H1CE. This document is not legally
binding for helicopters operated under EASA rules.
Failure to comply with these life limits could affect the safety of the helicopter and constitutes a
potential unsafe condition.
For the reason described above, this AD provides a list of applicable airworthiness limitation and
mandates compliance with these requirements.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
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EASA AD No.: 2015-0235
(1) From the effective date of this AD, replace each component before exceeding the applicable
life limit as specified in the Appendix 1 of this AD.
(2) Within 12 months after the effective date of this AD, revise the approved aircraft
maintenance programme (AMP), on the basis of which the operator or the owner ensures the
continuing airworthiness of each operated helicopter, by incorporating the limitations
described in the Appendix 1 of this AD.
(3) When an AMP of an helicopter has been revised as required by paragraph (2) of this AD, as
applicable, that action ensures (see Note 1 of this AD) continued accomplishment of the tasks
as required by paragraph (1) of this AD for that helicopter. Consequently, after revising the
AMP, as required by paragraph (2) of this AD, as applicable, it is not necessary that
accomplishment of individual tasks is recorded for demonstration of AD compliance on a
continued basis.
Note 1: For affected helicopters registered in Europe, complying with the approved AMP as
specified in paragraph (2) of this AD is required by Commission Regulation (EU) No 1321/2014, Part
M.A.301, paragraph 3.
Ref. Publications:
FAA TCDS No. H1CE.
Enstrom Service Information Letter (SIL) No. 0116.
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. For any question concerning the technical content of the requirements in this AD, please
contact: Enstrom Helicopter Corporation,
2209 22nd Street, Menominee, Michigan 49858,
United States of America
E-mail: engineering@enstromhelicopter.com.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 6
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EASA AD No.: 2015-0235
Appendix 1 – Life Limits – Replacement Compliance Times
Component Part Number Old Part Number F-28A 280
Name (P/N)
Bearing, Belt Idler ECD018-11 202SZZ 600 FH 600 FH
Pulley
Bearing, Upper Jack ECD014-11, Z99606X3B 600 FH** 600 FH**
Strut ECD014-13 6308-2RS
Clutch 28-13401-1 CL40526-1 thru -7 1 200 FH 1 200 FH
(Formsprag)
Bearing, Lower ECD009-11, 5201SBKZZ 1 200 FH** 1 200 FH**
Swashplate ECD009-13
Bearing Upper ECD013-11, Z993L13X3B 1 200 FH** 1 200 FH**
Swashplate ECD013-13 6013-RS
Tail Rotor Blade, 28-15120-1 4 500 FH++ 4 500 FH++
3.3 in. cord
Tail Rotor Spindle 28-15202-13 7 500 FH 7 500 FH
(3.3 in. cord T/R Assy)
Coupling, Tail Rotor 28-13609-1 1 200 FH 1 200 FH
Driveshaft
Coupling, Flex Pack 28-01041-3 A005-1992 (Dana) 1 200 FH 1 200 FH
Assembly
Tail Rotor Gear set ECD074-1, XR-137-2YL, 1 200 FH 1 200 FH
ECD074-2 XR-137-2R
Tail Rotor Gear set ECD100-1, 1 200 FH 1 200 FH
ECD100-2,
ECD100-1A,
ECD100-2A,
ECD100-1B,
ECD100-2B
Tail Rotor Gear set ECD101 –1, -2 1 200 FH 1 200 FH
Main Rotor Spindle 28-14282-11 19 000 FH 19 000 FH
Thrust Bearing 28-14320-12, ΔΔ ΔΔ
(Lamiflex) 28-14320-15
Tachometer Drive NAS1611-333 Δ Δ
Belt (O-Ring)
** On Condition when used with grease fitting
++ Right hand installations only (28-16300); left hand installations are on
condition.
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EASA AD No.: 2015-0235
Component Part Number Old Part Number F-28A 280
Name (P/N)
ΔΔ Retire from service 5 calendar years from date of manufacture all
Lamiflex bearings serial number 5997 and prior.
Retire from service 5 calendar years from date of installation* or 8
calendar years from date of manufacture, whichever occurs first, all
Lamiflex bearings serial numbers 5998 and subsequent.
*Note: Date of installation is defined as the date the Lamiflex bearing
packaging is opened.
Δ Retire from service 5 calendar years from date of installation or
package opening, or 8 years from date of manufacture, whichever
occurs first.
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EASA AD No.: 2015-0235
Component Part Number Old Part F-28C/F-28C-2/280C
Name (P/N) Number
MTOW = MTOW = MTOW =
2200 lbs 2350 lbs 2600 lbs
Bearing, Belt Idler ECD018-11 202SZZ 600 FH 600 FH 600 FH
Pulley
Bearing, Upper Jack ECD014-11, Z99606X3B 600 FH** 600 FH** 600 FH**
Strut ECD014-13 6308-2RS
Clutch 28-13401-1 CL40526-1 1 200 FH 1 200 FH 1 200 FH
CL40526-2
CL40526-3
CL40526-4
CL40526-5
CL40526-6
CL40526-7
(Formsprag)
Turbo Charger RJ0328 1 000 FH 1 000 FH 1 000 FH
Model 301E10-2
Turbo Charger RJ0332 2 000 FH 2 000 FH 2 000 FH
Model 325E10-2
Turbo Charger 103574-00 2 000 FH 2 000 FH 2 000 FH
Model 3BT2EE10J2
Turbo Charger 600700-00 103574-00 2 000 FH 2 000 FH 2 000 FH
Model 3BT5EE10J2
Bearing, Lower ECD009-11, 5201SBKZZ 1 200 FH** 1 200 FH** 1 200 FH**
Swashplate ECD009-13
Bearing Upper ECD013-11, Z993L13X3B 1 200 FH** 1 200 FH** 1 200 FH**
Swashplate ECD013-13 6013-RS
Universal Housing, 28-16119-1, 20 560 FH 17 700 FH 17 700 FH
Lower Swashplate 28-16119-3
Tail Rotor Blade, 28-150002-1 3 100 FH 3 100 FH 3 100 FH
4.4 in. cord
Tail Rotor Spindle 28-15202-13 7 500 FH N/A N/A
(3.3 in. cord T/R
Assy)
Tail Rotor Spindle 28-150064-11, 1 200 FH 1 200 FH 1 200 FH
(4.4 in. cord T/R 28-150064-13
Assy)
Tail Rotor Spindle 28-150074-11, 1 200 FH 1 200 FH 1 200 FH
(4.4 in. cord T/R 28-150074-13
Assy)
Tail Rotor Blade Grip 28-150044-1, 6 200 FH 6 200 FH 6 200 FH
28-150044-3
Tail Rotor Blade Grip 28-150013-1 3 100 FH 3 100 FH 3 100 FH
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