Nachrichten für Luftfahrer 2013 Teil II (weicht ggf. von Druckversion ab)
EASA AD No.: 2013-0257
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Within the compliance time defined in Table 1 of this AD, depending on
Time(s):
aeroplane utilisation, reinforce the cover plate of the torsion box of the aft
passenger/crew door, Left Hand and Right Hand, in accordance with the
instructions of Airbus SB A340-53-4072 Revision 04.
Table 1 –Threshold
Compliance time (whichever occurs later, A or B)
A Within the threshold defined in Airbus SB A340-53-4072 Revision 04,
depending on aeroplane utilisation and to be counted from aeroplane
first flight.
B Within 12 months after the effective date of this AD, but without
exceeding 8 750 flight cycles since aeroplane first flight.
(2) Reinforcement of the cover plate of the torsion box of the aft
passenger/crew door, Left Hand and Right Hand accomplished on an
aeroplane, before the effective date of this AD, in accordance with Airbus
SB A340-53-4072 at original issue or Revision 01 or Revision 02 or
Revision 03, is acceptable to comply with the requirements of paragraphs
(1) of this AD.
Ref. Publications: Airbus SB A340-53-4072 at original issue dated 29 June 1998 or Revision 01
dated 05 June 2000 or Revision 02 dated 07 October 2003 or Revision 03
dated 01 April 2010 or Revision 04 date 03 February 2012.
The use of later approved revisions of this 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. This AD was posted on 11 September 2013 as PAD 13-138 for consultation
until 09 October 2013. No comments were received during the consultation
period.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive 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 – Airworthiness Office – EIAL;
E-mail: airworthiness.A330-A340@airbus.com.
TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2003-201R7 38144 Braunschweig
EASA AD2013-0260-E vom 25.10.2013 Fax: +49-531-2355-5298
email: ad@LBA.de
MD HELICOPTER 28.10.2013
DRINGEND!
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: MD Helicopters, Inc. (MDHI)
Hersteller: MD Helicopters, Inc. (MDHI), McDonnell Douglas Helicopter Systems (MDHS)
Muster: MD900
Baureihen: MD900
Werknummern: Alle
Es sind alle Hubschrauber betroffen, an denen die "Main Rotor Blade Retention
Bolts" der Part-Nummer (P/N) 900R3100001-103 und/oder -105 installiert sind.
Einige Hubschrauber haben auf dem Hubschrauber-Typenschild die
Schreibweise MD-900. Diese Hubschrauber sind baugleich und somit
auch von dieser LTA und der AD betroffen.
Gerätenummer: 3066, FAA TCDS H19NM
Revisionsstand:
Diese LTA ersetzt D-2003-201R6 vom 17.01.2013
Airworthiness Directive der ausländischen Behörde:
EASA AD2013-0260-E vom 25.10.2013
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 2003-201R7 ge-
führt.
Betrifft:
(ATA 62) Main Rotor - Main Rotor Blade Retention Bolts - Inspection / Replacement (Life Limit)
Anmerkungen:
Gemäß M.A.304 des Anhang I (Teil M) der Verordnung (EG) Nr. 2042/2003 dürfen Luftfahrzeuge
nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in den Betrieb genommen
werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsan-
weisung EASA AD2013-0260-E vom 25.10.2013 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-2003-201R7 Seite 1 von 1 581/2013
EASA AD No. : 2013-0260-E
EASA EMERGENCY AIRWORTHINESS DIRECTIVE
AD No.: 2013-0260-E
Date: 25 October 2013
Note: This Emergency 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 EC 2042/2003 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 [EC
2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
Type Approval Holder’s Name : Type/Model designation(s) :
MD HELICOPTERS, Inc. MD900 helicopters
TCDS Number : United States (FAA) H19NM
Foreign AD : None
Supersedure: This AD supersedes EASA AD 2012-0261R1 dated 16 January 2013
Main Rotor – Main Rotor Blade Retention Bolts – Inspection /
ATA 62
Replacement (Life Limit)
Manufacturer(s): MD Helicopters, Inc. (MDHI), McDonnell Douglas Helicopter Systems (MDHS).
Applicability: MD900 helicopters, all serial numbers, if Part Number (P/N) 900R3100001-103
and/or P/N 900R3100001-105 Main Rotor (MR) blade retention bolts are
installed.
Some helicopters may have the designation MD-900 on the data plate; these
helicopters belong to the same type design and consequently, this AD applies to
those helicopters.
Reason: There have been 11 reported failures of P/N 900R3100001-103 MR blade
retention bolts between June 2003 and May 2009. For what appear to be a
variety of reasons, these failures did not result in accidents. However, based on
data gathered from the known failures, and after careful consideration of all other
available information, EASA determined that an unsafe condition exists or is
likely to develop on MD900 helicopters with these P/N bolts installed.
This condition, if not detected and corrected, could result in in-flight loss of blade
retention capability and consequent loss of the helicopter.
Based on these findings, EASA issued AD 2010-0050 (later revised) to require
repetitive detailed visual and tactile inspections of the P/N 900R3100001-103 MR
blade retention bolts and to impose reduced life limits on the affected bolts.
Since EASA AD 2010-0050R1 was issued, 4 more failures of P/N
900R3100001-105 MR blade retention bolts have been reported in service, the
latest in December 2012. Analysis results of the reported failures to date indicate
that a similar failure mode exists for the -105 bolt as determined previously for
the -103 bolts.
TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 1/4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
EASA AD No. : 2013-0260-E
Thereafter, EASA issued AD 2012-0261 applying those requirements to all
helicopters with P/N 900R3100001-103 and/or -105 MR blade retention bolts
installed, and requiring replacement of any bolts that have already reached or
exceeded the life limits.
Subsequently, EASA AD 2012-0261R1 was issued to amend paragraph (8),
removing the need to obtain explicit authorisation from MDHI to install a mix of
different P/N bolts on a single helicopter.
After the issue of EASA AD 2012-0261R, two more failures of P/N
900R3100001-105 MR blade retention bolts were reported in October 2013 on
helicopters registered in a European Member State. Neither MDHI, FAA nor
EASA have so far been able to ascertain the root cause of these failures. The
failures, however, are continuing to occur, thus increasing the risk that the
mitigations currently in place may no longer grant the required level of safety.
For the reasons described above this AD, which supersedes EASA AD
2012-0261R1, as a containment measure reduces the life limit of the affected MR
blade retention bolts installed on all MD900 helicopters.
This AD is still considered to be an interim measure, until a cause is established
to explain the reported bolt failures and consequent corrective measures are
introduced by the approval holder of the type design.
Effective Date: 28 October 2013
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Within 30 days after 21 December 2012 [the effective date of the original
Time(s):
issue of AD 2012-0261R1], amend the applicable Rotorcraft Flight Manual
(RFM) Section 4-2 PILOT’S DAILY PREFLIGHT CHECK and Section 4-3
PILOT’S PREFLIGHT CHECK to incorporate the repetitive pre-flight
retention bolt visual and ‘touch’ check instructions as detailed in Appendix I
and Appendix II of this AD, respectively. This may be accomplished by
inserting a copy of Appendix I and Appendix II of this AD into the applicable
sections of the RFM.
(2) If, during any of the repetitive RFM checks as required by paragraph (1) of
this AD, a failed bolt is detected, before next flight, replace the bolt with a
serviceable part in accordance with the instructions of the MD900 Rotorcraft
Maintenance Manual, CSP-900RMM-2, Section 62-10-00, Page 401 through
405 inclusive.
(3) Within 10 days after replacement of a failed bolt as required by paragraph
(2) of this AD, send a full report, including the failed bolt, to MD Helicopters,
address indicated in the Remarks section of this AD.
(4) Within 30 days after 21 December 2012 [the effective date of the original
issue of AD 2012-0261R1], for each P/N 900R3100001-103 and -105 MR
blade retention bolt installed on a helicopter, establish the total hours time-
in-service (TIS) accumulated since installation on any MD900 helicopter.
(5) From the effective date of this AD, the life limit for the affected MR blade
retention bolts is 400 hours TIS for all helicopters. After establishing the total
hours TIS accumulated for each bolt as required by paragraph (4) of this AD,
each bolt must be replaced, before exceeding the new life limit, with a
serviceable part in accordance with the instructions of the MD900 Rotorcraft
Maintenance Manual, CSP-900RMM-2, Section 62-10-00, Page 401 through
405 inclusive.
(6) Based on the determination as required by paragraph (4) of this AD, for each
bolt that has already reached or exceeded the new life limit as established in
paragraph (5),
- within 15 days after the effective date of this AD for MR blade retention
bolts that, on the effective date of this AD, have accumulated less than
1 000 hours TIS, or
TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 2/4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
EASA AD No. : 2013-0260-E
- within 5 days after the effective date of this AD for MR blade retention
bolts that, on the effective date of this AD, have accumulated 1 000 hours
TIS or more,
replace the bolt with a serviceable bolt in accordance with the instructions
of the MD900 Rotorcraft Maintenance Manual, CSP-900RMM-2, Section
62-10-00, Page 401 through 405 inclusive.
(7) Within 30 days after removal of a bolt as a result of the replacement action
as required by paragraph (5) or (6) of this AD, as applicable, return the bolt
to MD Helicopters, address indicated in the Remarks section of this AD.
(8) Replacement of MR blade retention bolts does not constitute terminating
action for the requirements of this AD. Replacement of all the bolts on a
helicopter with P/N 900R3100001-101 bolts is an acceptable terminating
action, as this AD does not apply to those bolts. Installation of a mix of
different P/N bolts on a single helicopter is only allowed within the criteria as
specified in the MD900 RMM, CSP-900RMM-2, Section 62-10-00.
Ref. Publication(s): MD900 Rotorcraft Maintenance Manual, CSP-900RMM-2.
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 public consultation process.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in this
AD, please contact:
MD Helicopters Inc., Attn: Customer Support Division, 4555 East McDowell
Road, Mail Stop M615, Mesa, Arizona 85215-9734, The United States of
America. Telephone +1-800-388-3378, fax +1-480-346-6813, or
on the Web at http://www.mdhelicopters.com.
TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 3/4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
EASA AD No. : 2013-0260-E
Appendix I
4–2. PILOT’S DAILY PREFLIGHT CHECK
Note: This check is in addition to the checks as specified in
section 4-2 of the basic RFM.
Blade attach pins (bolts):
Carry out a ‘touch check’ (e.g. light hand pressure) of each
blade bolt cam handle/spring clip to detect easy sideways
movement, i.e. lack of bolt tension.
If any movement (shift) is detected, before further flight,
contact maintenance for corrective action.
Appendix II
4–3. PILOT’S PREFLIGHT CHECK
Note: This check is in addition to the checks as specified in
section 4-3 of the basic RFM.
Rotor Blades:
Accomplish a visual check of each MR blade retention bolt
vertical position relative to its neighbour, and the lower and
upper surface of the pitch case. This check must include a
‘touch check’ (e.g. light hand pressure) of each blade bolt cam
handle/spring clip to detect easy sideways movement, i.e. lack
of bolt tension.
If any movement (shift) is detected, before further flight,
contact maintenance for corrective action.
TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 4/4
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2004-395R3 38144 Braunschweig
EASA AD 2013-0104R1 (Correction: 24.10.2013) Fax: +49-531-2355-5298
vom 24.05.2013 email: ad@LBA.de
SOCATA 25.10.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: SOCATA
Hersteller: SOCATA, EADS SOCATA
Muster: TBM 700
Baureihen: Alle TBM 700 Baureihen
Werknummern: Alle
Gerätenummer: 2070, EASA.A.010
Revisionsstand:
Diese LTA ersetzt D-2004-395R2 vom 27.05.2013
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0104R1 (Correction: 24.10.2013) vom 24.05.2013
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 2004-395R3 ge-
führt.
Betrifft:
(ATA 27) Flight Control - Flap Actuator - Inspection / Replacement
Anmerkungen:
Gemäß M.A.304 des Anhang I (Teil M) der Verordnung (EG) Nr. 2042/2003 dürfen Luftfahrzeuge
nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in den 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 2013-0104R1 (Correction: 24.10.2013) vom 24.05.2013 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-2004-395R3 Seite 1 von 1 577/2013
EASA AD No.: 2013-0104R1
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2013-0104R1
[Correction: 24 October 2013]
Date: 24 May 2013
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 21A.3B. In accordance with EC 2042/2003 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
[EC 2042/2003 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):
SOCATA TBM 700 aeroplanes
TCDS Number: EASA A.010
Foreign AD: Not applicable
Revision: This AD revises EASA AD 2013-0104 dated 13 May 2013.
ATA 27 Flight Control – Flap Actuator – Inspection / Replacement
Manufacturer(s): SOCATA (formerly EADS SOCATA)
Applicability: SOCATA TBM 700 aeroplanes, all manufacturer serial numbers.
Reason: In 2003, an excessive wear of the inner flap actuator drive nut was detected,
which was increased by grease pollution.
This condition, if not detected and corrected, may lead to an improper play
between the actuator threaded rod and the drive nut which could result in loss
of flap control, ultimately reducing control of the aeroplane.
To address this unsafe condition, DGAC France issued AD 2004-134,
requiring repetitive inspections and cleaning of the flap actuators.
After that AD was issued, further analyses were performed in the frame of an
improvement of the TBM 700 Aircraft Maintenance Program. The results of
these analyses revealed that the inspection threshold and interval allowing a
timely detection of wears and the accomplishment of an applicable corrective
action can be extended. Prompted by these results, SOCATA issued Revision
01 of Service Bulletin (SB) 70-118-27.
For the reasons described above, this AD retains the requirements of DGAC
France AD 2004-134, which is superseded, but extends the inspection
thresholds and intervals.
This AD has been revised to introduce, for the initial inspection as required by
this AD, a grace period of 300 FC since the last actuator play check
performed in accordance with SOCATA SB 70-118-27.
TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
EASA AD No.: 2013-0104R1
This AD has been re-published to correct a paragraph reference in the
required actions, paragraph (4).
Effective Date: 27 May 2013
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Before the accumulation of 200 flight hours (FH) or 12 months, whichever
Time(s):
occurs first, since the first installation of left hand (LH) or right hand (RH)
inner flap actuators on an aeroplane and thereafter, at intervals not to
exceed 200 FH or 12 months, whichever occurs first, clean and lubricate
LH or RH inner actuator rods in accordance with the instructions of
SOCATA SB 70-118-27.
(2) Within 1 200 FH since first installation of LH or RH inner flap actuators on
an aeroplane or within 300 FH since the last actuator play check
accomplished in accordance with SOCATA SB 70-118-27, as applicable,
and thereafter, at intervals not to exceed 200 FH or 12 months,
whichever occurs first, for each inner flap actuator check play between
the drive nut and the internal actuator rod in accordance with the
instructions of SOCATA SB 70-118-27.
Note: The non-cumulative tolerance as defined in SOCATA TBM 700
Maintenance Manual may be applied to the actions specified in paragraphs
(1) and (2) of this AD.
(3) If, during any check as required by paragraph (2) of this AD, a
discrepancy is detected, before next flight, accomplish the applicable
corrective actions in accordance with the instructions of SOCATA SB 70-
118-27.
(4) Accomplishment of corrective actions as required by paragraph (3) of this
AD does not constitute terminating action for the check as required by
paragraph (2) of this AD.
Ref. Publications: SOCATA SB 70-118-27 Original issue dated May 2004, or Revision 1 dated
August 2012.
The use of later approved revisions of this 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. The original issue of this AD was posted on 09 April 2013 as PAD 13-052
for consultation until 07 May 2013. No comments were received during
the consultation period.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in
this AD, please contact:
SOCATA, Direction des services, 65921 Tarbes Cedex 9, France.
Tel.: +33 (0) 5 62 41 73 00, Fax: + 33 (0) 5 62 41 76 54,
or for the U.S.A,
SOCATA NORTH AMERICA, North Perry Airport, 7501 South Airport
Road, Pembroke Pines, Florida 33023, The United States of America.
Tel.: +1 (954) 893 1400, Fax: +1 (954) 964 4141.
TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2004-395R4 38144 Braunschweig
EASA AD 2013-0104R1 (Correction: 25.10.2013) Fax: +49-531-2355-5298
vom 24.05.2013 email: ad@LBA.de
SOCATA 30.10.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: SOCATA
Hersteller: SOCATA, EADS SOCATA
Muster: TBM 700
Baureihen: Alle
Werknummern: Alle
Gerätenummer: 2070, EASA.A.010
Revisionsstand:
Diese LTA ersetzt D-2004-395R3 vom 25.10.2013
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0104R1 (Correction: 25.10.2013) vom 24.05.2013
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 2004-395R4 ge-
führt.
Betrifft:
(ATA 27) Flight Control - Flap Actuator - Inspection / Replacement
Anmerkungen:
Gemäß M.A.304 des Anhang I (Teil M) der Verordnung (EG) Nr. 2042/2003 dürfen Luftfahrzeuge
nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in den 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 2013-0104R1 (Correction: 25.10.2013) vom 24.05.2013 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-2004-395R4 Seite 1 von 1 591/2013
