Nachrichten für Luftfahrer 2015 Teil 2 (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2013-141R3 38144 Braunschweig
EASA AD 2013-0108R3 vom 22.06.2015 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 26.06.2015
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus
Muster: A380
Baureihen: A380-841, A380-842 und A380-861
Werknummern: Ausgenommen sind Flugzeuge, an denen die Airbus Modifikation 73685, 73686
und 73477 bei der Herstellung durchgeführt worden ist.
Gerätenummer: EASA.A.110
Revisionsstand:
Diese LTA ersetzt D-2013-141R2 vom 08.05.2015
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0108R3 vom 22.06.2015
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 2013-141R3 ge-
führt.
Betrifft:
(ATA 57) Wings - Wing Rib Feet - Modification
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 2013-0108R3 vom 22.06.2015 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-2013-141R3 Seite 1 von 1 260/2015
EASA AD No.: 2013-0108R3
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2013-0108R3
Date: 22 June 2015
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Regulation (EC) No 216/2008 on behalf of the European Community, 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 EU 748/2012, Part 21.A.3B. In accordance with 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
[EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS A380 aeroplanes
TCDS Number: EASA.A.110
Foreign AD: Not applicable
Revision: This AD revises EASA AD 2013-0108R2 dated 07 May 2015.
ATA 57 Wings – Wing Rib Feet – Modification
Manufacturer(s): Airbus
Applicability: Airbus A380-841, A380-842, and A380-861 aeroplanes, all manufacturer serial
numbers, except aeroplanes on which Airbus modification (mod) 73685 and
Airbus mod 73686 have been embodied in production and except aeroplanes
on which Airbus mod 73477 has been embodied in production.
Reason: Following an unscheduled internal inspection of an A380 wing, some rib feet
were found with cracks, originating from the rib-to-wing skin panel attachment
holes (Type 1 cracks according to Airbus All Operators Transmission (AOT)
terminology). Prompted by this finding, inspections were carried out on a
number of other aeroplanes, the results of which confirmed the existence of
these cracks. During one of those inspections, a new form of rib foot cracking,
originating from the forward and aft edges of the vertical web of the rib feet,
was identified (Type 2 cracks according to Airbus AOT terminology).
This condition, if not detected and corrected, may reduce the structural
integrity of the wing.
To address this potential unsafe condition, EASA issued AD 2012-0013 to
require a one-time detailed visual inspection (DVI) to detect cracks on the wing
rib feet and, depending on findings, repair.
After that AD was issued, it was confirmed that Type 2 cracks may develop on
other aeroplanes after a certain period of time of service. Prompted by this
finding, EASA issued AD 2012-0026, superseding EASA AD 2012-0013,
extending the applicability to all aeroplane serial numbers and requiring
accomplishment of a one-time high frequency eddy current (HFEC) inspection
of certain wing rib feet and, depending on findings, accomplishment of
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EASA AD No.: 2013-0108R3
applicable corrective actions.
Subsequently, it was determined that to maintain the safety of the A380 fleet,
repetitive inspections were necessary. Consequently, EASA issued AD
2012-0114, retaining the requirements of EASA AD 2012-0026, which was
superseded, to require, for pre mod 68705 aeroplanes only, repetitive
inspections of certain wing rib feet and, depending on findings,
accomplishment of applicable corrective actions.
Since EASA AD 2012-0114 was issued, Airbus developed a set of
modifications applicable to all aeroplanes which consists in introducing
horizontal stiffeners below the manhole on certain ribs and modifying the rib
feet booms with new re-sized rib feet booms manufactured from 7010
aluminium. Metallic 7449 ribs 48 and 49 are also to be replaced with new re-
sized ribs manufactured from 7010 aluminium.
For the reasons described above, to maintain the structural integrity of the
aeroplane wings, EASA issued AD 2013-0108 (later revised to exclude from
the Applicability aeroplanes on which Airbus mod 73477 has been embodied
in production) to require modification of the hybrid rib booms. That AD also
confirmed that for pre-mod 68705 A380 aeroplanes on which the Feed Tanks
1 and 4 bottom rib feet booms have been modified in-service in accordance
with the instructions of Airbus Service Bulletin (SB) A380-57-8062, the
repetitive inspections of EASA AD 2012-0114 were no longer required.
Since EASA AD 2013-0108R1 was issued, accomplishment of Wing Rib Feet
modifications in service prompted the need for issuance of several additional
Airbus adaptations and repair solutions. Consequently, EASA issued AD
2013-0108R2 to introduce Airbus Repair Design Approval Sheet (RDAS) or
Technical Disposition (TD) as an acceptable alternative method when
accomplishment of the modification instructions is not possible due to
aeroplane configuration.
This AD is revised to recognise Airbus Technical Adaptations (TA) which
address system installation deviations when accomplishment of the
modification instructions is not possible due to aeroplane configuration.
Effective Date: Revision 3: 22 June 2015
Revision 2: 07 May 2015
Revision 1: 13 September 2013
Original issue: 04 June 2013
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) For aeroplanes on which Airbus mod 68705 has not been embodied in
Time(s):
production, within the compliance times as indicated in Table 1 of this AD,
accomplish all actions specified in Table 1 of this AD on the left-hand (LH)
and right-hand (RH) wings.
(2) Modification of a pre mod 68705 aeroplane in accordance with the
instructions of Airbus SB A380-57-8062, as required by paragraph (1) of
this AD, constitutes terminating action for the repetitive inspection
requirements of EASA AD 2012-0114 for that aeroplane.
(3) For aeroplanes on which Airbus mod 68705 has been embodied in
production, within the compliance times as indicated in Table 2 of this AD,
accomplish all actions specified in Table 2 of this AD on the LH and RH
wings.
(4) If, during modification of an aeroplane as required by paragraph (1) or (3)
of this AD, any discrepancy (see Note) is detected, which makes the
accomplishment of any part of the modification instructions impossible,
before next flight, contact Airbus to obtain an approved RDAS, or TA, or
TD, and accomplish that repair accordingly, including post-repair follow-on
action(s), as applicable.
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EASA AD No.: 2013-0108R3
Note: For the purpose of this AD, a discrepancy is a necessary design
deviation due to production related concessions that directly affect the
sensitive area of the modification such as rib boom attachment to the wing
skin or rib web, or items related to post mod fuel system tests, access or
removal of hydraulic systems or simply typographical corrections.
Ref. Publications: Airbus SB A380-57-8062 original issue, dated 18 December 2012.
Airbus SB A380-57-8063 original issue, dated 19 December 2012.
Airbus SB A380-57-8064 original issue, dated 18 December 2012.
Airbus SB A380-57-8065 original issue, dated 18 December 2012.
Airbus SB A380-57-8066 original issue, dated 20 December 2012, or
Revision 01 dated 19 April 2013.
Airbus SB A380-57-8067 original issue, dated 18 December 2012.
Airbus SB A380-57-8068 original issue, dated 18 December 2012, or
Revision 01 dated 17 May 2013.
Airbus SB A380-57-8069 original issue, dated 18 December 2012, or
Revision 01 dated 17 May 2013.
Airbus SB A380-57-8070 original issue, dated 18 December 2012, or Revision
01 dated 24 April 2013.
Airbus SB A380-57-8077 original issue dated 24 April 2013.
Airbus SB A380-57-8078 original issue dated 24 April 2013.
Airbus SB A380-57-8079 original issue dated 12 April 2013.
Airbus SB A380-57-8082 original issue dated 12 April 2013.
Airbus SB A380-57-8084 original issue dated 24 April 2013.
The use of later approved revisions of these 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. The original issue of this AD was posted on 15 April 2013 as PAD 13-054
for consultation until 13 May 2013. No comments were received during the
consultation period.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in
this AD, please contact: AIRBUS SAS - EIANA (Airworthiness Office),
E-mail: account.airworth-A380@airbus.com.
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EASA AD No.: 2013-0108R3
Table 1 – Hybrid Rib Boom Modification applicable to aeroplanes on which Airbus mod 68705 has not
been embodied in production
Required Actions Compliance times
Modify the Feed Tanks 1 and 4 bottom rib feet
booms on hybrid Rib 24, Rib 25, Rib 26, Rib 27,
Rib 29 and Rib 30 in accordance with the
instructions of Airbus SB A380-57-8062.
Modify the Mid Tank bottom rib feet booms on Whichever occurs first between a) or b) :
hybrid Rib 14 Forward (FWD), Rib 14 Aft (AFT),
a) Before the accumulation of 28 500 flight hours
Rib 15 FWD, Rib 15 AFT, Rib 17 AFT, Rib 18,
(FH) since the aeroplane first flight, or
Rib 19, Rib 20 and Rib 21 in accordance with the
instructions of Airbus SB A380-57-8063. b) within 6 years since the date of issuance of
the original certificate of airworthiness or date
Modify the Inner Tank top and bottom rib feet of issuance of the original export certificate of
booms on hybrid Rib 11 FWD, Rib 12 FWD and airworthiness, as applicable, whichever occurs
Rib 12 AFT in accordance with the instructions of first.
Airbus SB A380-57-8064.
Modify the full Ribs at Vent Tank Rib 48 and Rib
49 in accordance with the instructions of Airbus
SB A380-57-8066.
Modify the Feed Tanks 2 and 3 top and bottom
rib feet booms on hybrid Rib 3 FWD in
accordance with the instructions of Airbus SB
A380-57-8065.
Modify the Outer Tank bottom rib feet booms on
hybrid Rib 36, Rib 37, Rib 38 and Rib 39 in
accordance with the instructions of Airbus SB
A380-57-8067.
Modify the Mid Tank top rib feet booms on hybrid Within 6 years since the date of issuance of the
Rib 14 FWD, Rib 14 AFT, Rib 15 FWD, Rib 15 original certificate of airworthiness or date of
AFT, Rib 17 AFT, Rib 18, Rib 19, Rib 20 and Rib issuance of the original export certificate of
21 in accordance with the instructions of Airbus airworthiness, as applicable, whichever occurs
SB A380-57-8068. first.
Modify the Feed Tanks 1 and 4 top rib feet
booms on hybrid Rib 24, Rib 25, Rib 26, Rib 27,
Rib 29 and Rib 30 in accordance with the
instructions of Airbus SB A380-57-8069.
Modify the Outer Tank top rib feet booms on
hybrid Rib 36, Rib 37, Rib 38 and Rib 39 in
accordance with the instructions of Airbus SB
A380-57-8070.
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EASA AD No.: 2013-0108R3
Table 2 – Hybrid Rib Boom Modification applicable to aeroplanes on which Airbus mod 68705 has been
embodied in production
Required Actions Compliance times
Modify the Feed Tanks 1 and 4 bottom rib feet a) or b), as applicable:
booms on hybrid Rib 24, Rib 25, Rib 26, Rib 27,
a) For aeroplanes on which Airbus Interim
Rib 29 and Rib 30 in accordance with the
Adaptation mod 73022 has not been
instructions of Airbus SB A380-57-8082.
embodied in production: before the
accumulation of 700 flight cycles (FC) since
Modify the Mid Tank bottom rib feet booms on the aeroplane first flight.
hybrid Rib 14 FWD, Rib 14 AFT, Rib 15 FWD,
Rib 15 AFT, Rib 17 AFT, Rib 18, Rib 19, Rib 20 b) For aeroplanes on which Airbus Interim
and Rib 21 in accordance with the instructions of Adaptation mod 73022 has been embodied in
Airbus SB A380-57-8079. production: before the accumulation of 1 300
FC since the aeroplane first flight.
Modify the Inner Tank top and bottom rib feet Whichever occurs first, a) or b) :
booms on hybrid Rib 11 FWD, Rib 12 FWD and
a) Before the accumulation of 18 500 FH since
Rib 12 AFT in accordance with the instructions of
aeroplane first flight, or
Airbus SB A380-57-8078.
b) within 6 years since the date of issuance of
Modify the full Ribs at Vent Tank Rib 48 and Rib the original certificate of airworthiness or date
49 in accordance with the instructions of Airbus of issuance of the original export certificate of
SB A380-57-8066. airworthiness, as applicable, whichever
occurs first.
Modify the Feed Tanks 2 and 3 top and bottom
rib feet booms on hybrid Rib 3 FWD in
accordance with the instructions of Airbus SB
A380-57-8077.
Modify the Outer Tank bottom rib feet booms on
hybrid Rib 36, Rib 37, Rib 38 and Rib 39 in
accordance with the instructions of Airbus SB
A380-57-8084.
Modify the Mid Tank top rib feet booms on hybrid Within 6 years since the date of issuance of the
Rib 14 FWD, Rib 14 AFT, Rib 15 FWD, Rib 15 original certificate of airworthiness or date of
AFT, Rib 17 AFT, Rib 18, Rib 19, Rib 20 and Rib issuance of the original export certificate of
21 in accordance with the instructions of Airbus airworthiness, as applicable, whichever occurs
SB A380-57-8068. first.
Modify the Feed Tanks 1 and 4 top rib feet
booms on hybrid Rib 24, Rib 25, Rib 26, Rib 27,
Rib 29 and Rib 30 in accordance with the
instructions of Airbus SB A380-57-8069.
Modify the Outer Tank top rib feet booms on
hybrid Rib 36, Rib 37, Rib 38 and Rib 39 in
accordance with the instructions of Airbus SB
A380-57-8070.
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2013-214R1 38144 Braunschweig
EASA AD 2015-0112 vom 16.06.2015 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS HELICOPTERS 22.06.2015
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: AIRBUS HELICOPTERS
Hersteller: Airbus Helicopters, Eurocopter, Eurocopter France
Muster: PUMA, SUPER PUMA
Baureihen: AS 332 L1 und EC 225 LP
Werknummern: AS 332 L1: Seriennummer (S/N) 2774
EC 225 LP: (S/N) 2600, 2623, 2645, 2656, 2659, 2663, 2666, 2670, 2673,
2685, 2691 bis 2693, 2702, 2715, 2716, 2721, 2725, 2739, 2744, 2747, 2753,
2756, 2759 und 2767
Gerätenummer: 3043, EASA.R.002
Revisionsstand:
Diese LTA ersetzt D-2013-214 vom 08.08.2013
Airworthiness Directive der ausländischen Behörde:
EASA AD 2015-0112 vom 16.06.2015
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 2013-214R1 ge-
führt.
Betrifft:
(ATA 30) Ice and Rain Protection - Electrical Multi-Purpose Air Intakes – Modification
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 2015-0112 vom 16.06.2015 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-2013-214R1 Seite 1 von 1 254/2015
EASA AD No.: 2015-0112
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2015-0112
Date: 16 June 2015
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) No 216/2008 on behalf of the European Community, 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 EU 748/2012, Part 21.A.3B. In accordance with 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
[EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS HELICOPTERS AS 332 L1 and EC 225 LP helicopters
TCDS Number: EASA.R.002
Foreign AD: Not applicable
Supersedure: This AD supersedes EASA AD 2013-0173 dated 01 August 2013.
Ice and Rain Protection – Electrical Multi-Purpose Air Intakes –
ATA 30
Modification
Manufacturer(s): Airbus Helicopters (formerly Eurocopter, Eurocopter France)
Applicability: AS 332 L1 helicopter, manufacturer serial number (S/N) 2774, and EC 225 LP
helicopters, manufacturer S/N 2600, 2623, 2645, 2656, 2659, 2663, 2666,
2670, 2673, 2685, 2691, 2692, 2693, 2702, 2715, 2716, 2721, 2725, 2739,
2744, 2747, 2753, 2756, 2759 and 2767.
Reason: For some helicopters equipped with electrical Multi-Purpose Air Intakes (MPAI),
power generation failure conditions were identified that would cause power
supply loss of the engine electro-valves controlling inflation of the MPAI seals to
close the engine air intakes. The power supply loss on these electro-valves
results in deflation of, or failure to inflate, MPAI seals on both engine air
intakes.
This condition, if not corrected, could lead to ice ingestion by the engines during
flight in icing conditions, possibly resulting in dual engine flame-out.
To address this unsafe condition, Eurocopter issued Alert Service Bulletin
(ASB) No. AS332-30.00.74 and ASB No. EC225-30A032 to provide instructions
to modify some electrical bus bars and circuit breakers (modification (MOD)
332P083736.01, MOD 332P083736.02 and MOD 332P083736.05) for the
affected helicopters.
Consequently, EASA issued AD 2013-0173 to require accomplishment of
Eurocopter MOD 332P083736.01, or MOD 332P083736.02, or MOD
332P083736.05, as applicable to helicopter model and serial number, and to
update the applicable Rotorcraft Flight Manual (RFM).Since that AD was
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EASA AD No.: 2015-0112
issued, the instructions of Eurocopter ASB No. EC225-30A032 for aircraft
functional check after accomplishment of MOD 332P083736.01 or MOD
332P083736.02 revealed to be incorrect for certain affected EC 225 LP
helicopters (when in post-MOD 07-26566 and
pre-MOD 07-26688 configuration). Additionally, it was determined that some
EC 225 LP helicopters (S/N 2779 and 2794) were not affected by the unsafe
condition addressed by the AD.
For the reasons described above, this AD retains the requirements of EASA AD
2013-0173, which is superseded, and requires an additional post-MOD
functional check of the MPAI for EC 225 LP helicopters in post-MOD 07-26566
and pre-MOD 07-26688 configuration. This AD also removes two S/N from the
Applicability.
Effective Date: 30 June 2015
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Within 110 flight hours after 08 August 2013 [the effective date of EASA
Time(s):
AD 2013-0173], accomplish the modification specified in Table 1 below, as
applicable to helicopter model and S/N, in accordance with the instructions
of paragraph 3 of Eurocopter ASB No. AS332-30.00.74 or Airbus
Helicopters (formerly Eurocopter) ASB No. EC225-30A032 Revision 1, as
applicable to helicopter model.
Table 1 – Modification
Helicopter models and S/N Required modification
AS 332 L1: S/N 2774 MOD 332P083736.05
EC 225 LP: S/N 2600, 2623, 2645, 2656,
MOD 332P083736.01
2659, 2663, 2666, 2670, 2673 and 2693
EC 225 LP: S/N 2685, 2691, 2692, 2702,
2715, 2716, 2721, 2725, 2739, 2744, 2747, MOD 332P083736.02
2753, 2756, 2759 and 2767
(2) Concurrently with the modification as required by paragraph (1) of this AD,
amend the RFM by inserting a copy of the pages of the Appendix of
Eurocopter ASB No. AS332-30.00.74 or ASB No. EC225-30A032, as
applicable to helicopter model, notify all flight crews and, thereafter,
operate the helicopter accordingly.
The RFM amendment can also be accomplished by incorporating a later
applicable RFM revision that contains the affected instructions.
(3) Modification of an EC 225 LP helicopter, accomplished before the effective
date of this AD in accordance with the instructions of Eurocopter ASB No.
EC225-30A032 original issue, is acceptable to comply with paragraph (1)
of this AD for that helicopter, except for EC 225 LP helicopters in post-
MOD 26566 and pre-MOD 07-26688 configuration – see paragraph (4) of
this AD.
(4) For EC 225 LP helicopters in post-MOD 26566 and pre-MOD 07-26688
configuration:
Within 30 days after the effective date of this AD, accomplish an additional
functional check of the MPAI in accordance with the instructions of
paragraph 3.B.4 of Airbus Helicopters ASB No. EC225-30A032 Revision 1.
(5) If, during the additional functional check as required by paragraph (4) of
this AD, any discrepancy is detected, before next flight, contact Airbus
Helicopters for applicable corrective action instructions and accomplish
those instructions accordingly.
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EASA AD No.: 2015-0112
Ref. Publications: Eurocopter ASB No. AS332-30.00.74, original issue dated 31 July 2013.
Eurocopter ASB No. EC225-30A032, original issue dated 31 July 2013, or
Airbus Helicopters ASB No. EC225-30A032, Revision 1 dated 07 April 2015.
The use of later approved revisions of these 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. 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 Safety Information
Section, Certification Directorate, EASA. 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, Facsimile +33 (4) 42 85 99 66
E-mail: contact.msm.ah@airbus.com.
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