Nachrichten für Luftfahrer 2014 Teil 2 (weicht ggf. von Druckversion ab)
Request to Allow Terminating Action for Inspections
All Nippon Airways (ANA) stated that no further action should be necessary if the repair meets
the conditions specified in Note 10 of paragraph 3.A., ''General Information,'' of the Accomplishment
Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, and
that this should be addressed in paragraph (k)(3) of the NPRM (78 FR 22439, April 16, 2013), which
terminates paragraph (g) of the NPRM.
We agree with the commenter's request. The conditions provided in Note 10 of paragraph 3.A.,
''General Information,'' of the Accomplishment Instructions of Boeing Service Bulletin 737-53A1200,
Revision 2, dated September 12, 2012, ensure that the non-SRM repairs were developed to preclude
further cracking.
We note that there is no paragraph (k)(3) in the NPRM (78 FR 22439, April 16, 2013), and infer
that ANA meant to request that a new paragraph (k)(3) be added to this final rule. Instead, we have
added new paragraph (n) to this final rule and redesignated subsequent paragraphs accordingly. New
paragraph (n) of this final rule states that the inspections required by paragraph (j) of this final rule
may be terminated at areas with repairs installed prior to the effective date of this final rule if those
repairs meet the conditions specified in Note 10 of paragraph 3.A., ''General Information,'' of the
Accomplishment Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, dated September
12, 2012.
Request to Include AMOC Approval
Boeing requested that we modify paragraph (o)(4) of the NPRM (78 FR 22439, April 16, 2013)
(paragraph (p)(4) in this final rule) to include the additional conditions shown in Note 10 of
paragraph 3.A., ''General Information,'' of the Accomplishment Instructions of Boeing Service
Bulletin 737-53A1200, Revision 2, dated September 12, 2012. Boeing stated that the paragraph
should state that AMOCs approved previously for paragraphs (f) and (i) of AD 2008-11-04,
Amendment 39-15526 (73 FR 29421, May 21, 2008), are approved as AMOCs for the corresponding
provisions of paragraphs (g) and (i) of the NPRM, provided that the repairs meet the criteria of Note
10 of paragraph 3.A., ''General Information,'' of the Accomplishment Instructions of Boeing Service
Bulletin 737-53A1200, Revision 2, dated September 12, 2012. Boeing stated that the conditions
provided in Note 10 of paragraph 3.A., ''General Information,'' of the Accomplishment Instructions of
Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, ensure that the repairs
were developed to preclude post-modification cracking.
We do not agree with the commenter's request. The commenter's concerns are adequately
addressed in paragraph (k)(2) of this final rule, which requires additional actions when repairs do not
meet the conditions specified in Note 10 of paragraph 3.A., ''General Information,'' of the
Accomplishment Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, dated September
12, 2012, whether or not the repair was approved previously as an AMOC for AD 2008-11-04,
Amendment 39-15526 (73 FR 29421, May 21, 2008). We have not changed this final rule in this
regard.
Request to Add AMOC Approval for Paragraph (g) of the NPRM (78 FR 22439, April 16,
2013)
ANA requested that we add a new paragraph (o)(5) to the NPRM (78 FR 22439, April 16, 2013)
to clarify that AMOCs approved previously for the requirements of paragraph (f) of AD 2008-11-04,
Amendment 39-15526 (73 FR 29421, May 21, 2008), are approved as AMOCs for paragraph (g) of
the NPRM. ANA stated that if the repair meets the criteria specified in Note 10 of paragraph 3.A.,
''General Information,'' of the Accomplishment Instructions of Boeing Service Bulletin 737-53A1200,
Revision 2, dated September 12, 2012, then the inspection required by paragraph (g) of the NPRM
should be terminated even if an AMOC statement in FAA Form 8100-9 (Statement of Compliance
3
with Airworthiness Standards) is not the same as paragraph (o)(4) of the NPRM. ANA asserted that a
new AMOC to the NPRM will be necessary if the AMOC statement only refers to paragraph (f) of
AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008).
We do not agree. Paragraph (p)(4) of this final rule (which was designated as paragraph (o)(4) of
the NPRM (78 FR 22439, April 16, 2013)), as currently worded, addresses ANA's concern. A repair
which has an AMOC for only paragraph (f) of AD 2008-11-04, Amendment 39-15526 (73 FR 29421,
May 21, 2008), would be approved as an AMOC for the corresponding provisions of paragraph (g) of
this final rule.
Further, we understand ANA to mean that this particular repair satisfies the conditions specified
in Note 10 of paragraph 3.A., ''General Information,'' of the Accomplishment Instructions of Boeing
Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012. If this is the case, then new
paragraph (n) of this final rule, discussed previously, means that this repair satisfies the requirements
of paragraph (j) of this final rule, which would terminate the inspection requirements of paragraph (f)
of AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008) in the repaired area. We
have not changed this final rule in this regard.
Request to Change Optional Terminating Action Paragraph (i) of the NPRM (78 FR 22439,
April 16, 2013)
SWA requested that we delete Note 1 to paragraph (i) of the NPRM (78 FR 22439, April 16,
2013), which states that ''Guidance on repairs can be found in Boeing 737-100/-200 SRM 53-30-1,
Figure 20, 21, 31, or 32; or Boeing 737-300/-400/-500 SRM 53-10-01, Repair 5, 6, or 8; as
applicable.'' SWA noted that Boeing 737-300/-500 SRM 53-10-01, Repairs 5, 6, and 8 have been
removed as they are no longer applicable. SWA stated that the NPRM (78 FR 22439, April 16, 2013)
is in error when it states that guidance on repairs can be found in these locations.
We agree with SWA's request. Subsequent to the issuance of AD 2008-11-04, Amendment 39-
15526 (73 FR 29421, May 21, 2008), Boeing removed the noted SRM repairs from the 737-300/-
400/-500 SRMs. For the Boeing 737-100/200 SRM, the noted repairs were not removed, but each
page was watermarked OBSOLETE. For clarity, we have deleted Note 1 to paragraph (i) of this final
rule.
Boeing requested that we not retain paragraph (i) from AD 2008-11-04, Amendment 39-15526
(73 FR 29421, May 21, 2008). Boeing asserted that paragraph (i) of AD 2008-11-04 provides
terminating actions for airplanes on which areas were repaired in accordance with ''Boeing 737-100/ -
200 SRM 53-30-1, Figures 20, 21, 31, or 32; or Boeing 737-300/-400/-500 SRM 53-10-01, Repair 5,
6, or 8.'' Boeing stated that allowing the repairs listed in paragraph (i) of the NPRM (78 FR 22439,
April 16, 2013) as terminating action would conflict with Boeing Service Bulletin 737-53A1200,
Revision 2, dated September 12, 2012, and paragraph (k) of the NPRM. Boeing added that Boeing
Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, requires follow-on inspections
for SRM repairs, which are required based on fleet reports showing crack susceptibility after the
repair has been installed. Boeing stated that new repairs are now provided in the SRM.
We disagree with the commenter's request. Paragraph (i) of AD 2008-11-04, Amendment 39-
15526 (73 FR 29421, May 21, 2008), is not retained as written in AD 2008-11-04, but rather it is
retained ''. . . with revised method of compliance language. . . .'' Paragraph (i) states, ''The inspections
specified in paragraph (g) of this AD may be terminated at areas repaired using a method approved in
accordance with the procedures specified in paragraph (p) [AMOC] of this AD.'' Thus, operators
cannot continue to install the noted obsolete/removed repairs specified previously in AD 2008-11-04.
Boeing has addressed repairs installed previously by providing inspections for them in Boeing
Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012. These inspections are
mandated by paragraph (k) of this final rule. We have not changed this final rule in this regard.
4
Conclusion
We reviewed the relevant data, considered the comments received, and determined that air safety
and the public interest require adopting this AD with the changes described previously and minor
editorial changes. We have determined that these minor changes:
• Are consistent with the intent that was proposed in the NPRM (78 FR 22439, April 16, 2013)
for correcting the unsafe condition; and
• Do not add any additional burden upon the public than was already proposed in the NPRM
(78 FR 22439, April 16, 2013).
We also determined that these changes will not increase the economic burden on any operator or
increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 547 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
Action Labor cost Parts Cost per Cost on U.S.
cost product operators
Inspections [actions retained from Up to 73 work-hours × $0 Up to $6,205 Up to
AD 2008-11-04, Amendment 39- $85 per hour = $6,205 per inspection $3,394,135 per
15526 (73 FR 29421, May 21, per inspection cycle cycle inspection cycle.
2008)]
Inspection [new action] Up to 34 work-hours × 0 Up to $2,890 Up to
$85 per hour = $2,890 per inspection $1,580,830 per
per inspection cycle cycle inspection cycle.
We have received no definitive data that would enable us to provide cost estimates for the on-
condition actions specified in this AD.
Authority for this Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States, on the relationship between the
national government and the States, or on the distribution of power and responsibilities among the
various levels of government.
5
For the reasons discussed above, I certify that this AD:
(1) Is not a ''significant regulatory action'' under Executive Order 12866,
(2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or negative, on a substantial number of
small entities under the criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR
part 39 as follows:
PART 39–AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2008-11-04, Amendment
39-15526 (73 FR 29421, May 21, 2008), and adding the following new AD:
6
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2014-05-21 The Boeing Company: Amendment 39-17794; Docket No. FAA-2013-0327;
Directorate Identifier 2011-NM-161-AD.
(a) Effective Date
This AD is effective April 22, 2014.
(b) Affected ADs
This AD supersedes AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008).
(c) Applicability
This AD applies to The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes, certificated in any category, as identified in Boeing Service Bulletin 737-53A1200,
Revision 2, dated September 12, 2012.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by multiple reports of cracks in the skin and/or bear strap at the forward
galley service doorway hinge cutouts, and multiple reports of cracking under the repairs installed at
the hinge cutouts. We are issuing this AD to detect and correct such cracking, which could result in
rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (f) of AD 2008-11-04, Amendment 39-
15526 (73 FR 29421, May 21, 2008). Except as provided by paragraph (h)(1) of this AD, at the
applicable times specified in paragraph 1.E. ''Compliance,'' of Boeing Alert Service Bulletin 737-
53A1200, dated April 13, 2006, do external detailed, low frequency eddy current (LFEC), high
frequency eddy current (HFEC), and HFEC rotary probe inspections, as applicable, for cracks in and
around the upper and lower hinge cutouts of the forward entry and forward galley service doorways,
in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1200,
dated April 13, 2006, except as provided by paragraphs (h)(2) and (i) of this AD. Do not exceed the
applicable repetitive interval for the previous inspection, as specified in Boeing Alert Service Bulletin
737-53A1200, dated April 13, 2006, as Option A or Option B. Repair any crack before further flight
using a method approved in accordance with the procedures specified in paragraph (p) of this AD.
7
Accomplishment of the actions required by paragraph (j) of this AD terminates the requirements of
this paragraph.
(h) Retained Exceptions to Service Bulletin Specifications
This paragraph restates the requirements of paragraphs (g) and (h) of AD 2008-11-04,
Amendment 39-15526 (73 FR 29421, May 21, 2008).
(1) Where Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006, specifies a
compliance time after the release date of that service bulletin, this AD requires compliance within the
specified compliance time after June 25, 2008 (the effective date of AD 2008-11-04, Amendment 39-
15526 (73 FR 29421, May 21, 2008)).
(2) Although Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006, specifies
contacting Boeing for information about installing an optional preventive modification that would
terminate the repetitive inspections specified in paragraph (g) of this AD, this AD requires that any
terminating action be done by using a method approved in accordance with the procedures specified
in paragraph (p) of this AD.
(i) Retained Optional Terminating Action
This paragraph restates the optional terminating action specified paragraph (i) of AD 2008-11-
04, Amendment 39-15526 (73 FR 29421, May 21, 2008), with revised method of compliance
language and removal of note 1 to paragraph (i) of this AD. The inspections specified in paragraph
(g) of this AD may be terminated at areas repaired using a method approved in accordance with the
procedures specified in paragraph (p) of this AD.
(j) New Repetitive Inspections and Repair
Except as required by paragraph (l)(1) of this AD, at the applicable times specified in Paragraph
1.E., ''Compliance,'' of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012:
Do an external and internal detailed inspection, HFEC inspection, and HFEC hole probe inspection,
at the forward entry and galley service doorway upper and lower hinge cutouts for cracking in the
skin, bonded doubler, bearstrap, and frame outer chord, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, except
as required by paragraph (m) of this AD. Options provided in Boeing Service Bulletin 737-53A1200,
Revision 2, dated September 12, 2012, for accomplishing the inspections are acceptable for
compliance with the corresponding requirements of this paragraph. Repeat the applicable inspections
thereafter at the applicable times specified in paragraph 1.E., ''Compliance,'' of Boeing Service
Bulletin 737-53A1200, Revision 2, dated September 12, 2012. If any crack is found, before further
flight, repair using a method approved in accordance with the procedures specified in paragraph (p)
of this AD. Accomplishment of the initial inspections terminates the requirements of paragraph (g) of
this AD.
(k) New Actions for Airplanes With Certain Repairs Installed
(1) For airplanes with any structural repair manual (SRM) repair specified in paragraphs (k)(1)(i)
through (k)(1)(vii) of this AD installed, at the applicable times specified in paragraph 1.E.,
''Compliance,'' of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012: Do
an external and internal detailed inspection, HFEC inspection, and LFEC inspection, at the forward
entry and galley service doorway upper and lower hinge cutouts for cracking in the skin, bearstrap,
and frame outer chord, in accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-53A1200, Revision 2, dated September 12, 2012, except as required by paragraph (l)(2)
of this AD. Repeat the inspection thereafter at the applicable times specified in paragraph 1.E.,
8
''Compliance,'' of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012. If
any crack is found, before further flight, repair using a method approved in accordance with the
procedures specified in paragraph (p) of this AD.
(i) Repair specified in Boeing 737-100/ -200 SRM 53-30-03, Figure 21.
(ii) Repair specified in Boeing 737-100/200 SRM 53-30-03, Figure 31.
(iii) Repair 5 specified in Boeing 737-300 SRM 53-10-01; Repair 5 specified in Boeing 737-400
SRM 53-10-01; or Repair 5 specified in Boeing 737-500 SRM 53-10-01; installed at the upper or
lower hinge cutout.
(iv) Repair specified in Boeing 737-100/200 SRM 53-30-03, Figure 20.
(v) Repair 6 specified in Boeing 737-300 SRM 53-10-01; Repair 6 specified in Boeing 737-400
SRM 53-10-01; or Repair 6 specified in Boeing 737-500 SRM 53-10-01.
(vi) Repair 8 specified in Boeing 737-300 SRM 53-10-01; Repair 8 specified in Boeing 737-400
SRM 53-10-01; or Repair 8 specified in Boeing 737-500 SRM 53-10-01.
(vii) Repair specified in Boeing 737-100/200 SRM 53-30-03, Figure 32.
(2) For airplanes with any repair installed at the forward entry doorway or forward galley
doorway, upper or lower hinge cutout, that does not meet the conditions specified in Note 10 of
paragraph 3.A., ''General Information,'' of the Accomplishment Instructions of Boeing Service
Bulletin 737-53A1200, Revision 2, dated September 12, 2012: Except as required by paragraph (l) of
this AD, at the applicable times specified in paragraph 1.E., ''Compliance,'' of Boeing Service
Bulletin 737-53A1200, Revision 2, dated September 12, 2012, contact the Manager, Seattle ACO,
FAA, for instructions, using the procedures specified in paragraph (p) of this AD, and do the actions
required by the FAA.
(l) New Exception to Service Bulletin Specifications
(1) Where Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012,
specifies a compliance time after the issue date of Boeing Service Bulletin 737-53A1200, Revision 1,
dated July 7, 2011, this AD requires compliance within the specified compliance time after the
effective date of this AD.
(2) Where Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012,
specifies to contact Boeing for further instructions, this AD requires contacting the Manager, Seattle
Aircraft Certification Office (ACO), FAA, for instructions and doing the actions required by the
FAA, using the procedures specified in paragraph (p) of this AD.
(m) Exception for Group 5 Airplanes
For Group 5 airplanes identified in Boeing Service Bulletin 737-53A1200, Revision 2, dated
September 12, 2012: Before further flight, contact the Manager, Seattle ACO, FAA, for instructions,
using the procedures specified in paragraph (p) of this AD, and do the actions required by the FAA.
(n) Terminating Actions
The inspections required by paragraph (j) of this AD may be terminated at areas with repairs
installed prior to the effective date of this AD, provided the repairs meet the conditions specified in
Note 10 of paragraph 3.A., ''General Information,'' of the Accomplishment Instructions of Boeing
Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012.
(o) Credit for Previous Actions
This paragraph provides credit for the actions required by paragraphs (j) and (k) of this AD, if
those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin
737-53A1200, Revision 1, dated July 7, 2011, which is not incorporated by reference in this AD.
9
(p) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the attention of the person identified in
paragraph (q)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the local flight standards district office/certificate holding district
office.
(3) An AMOC that provides an acceptable level of safety may be used for any repair required by
this AD if it is approved by the Boeing Commercial Airplanes Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings.
For a repair method to be approved, the repair must meet the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) AMOCs approved previously for paragraphs (f) and (i) of AD 2008-11-04, Amendment 39-
15526 (73 FR 29421, May 21, 2008), are approved as AMOCs for the corresponding provisions of
paragraphs (g) and (i) of this AD.
(q) Related Information
(1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe
Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: Alan.Pohl@faa.gov.
(2) Service information identified in this AD that is not incorporated by reference may be
obtained at the addresses specified in paragraphs (r)(5) and (r)(6) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference (IBR) 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.
(3) The following service information was approved for IBR on April 22, 2014.
(i) Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012.
(ii) Reserved.
(4) The following service information was approved for IBR on June 25, 2008 (73 FR 29421,
May 21, 2008).
(i) Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006.
(ii) Reserved.
(5) 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;
phone: 206-544-5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com.
(6) You may view this service information at the 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.
(7) 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.
10
Issued in Renton, Washington, on February 19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
11
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2010-244R1 38144 Braunschweig
EASA AD 2010-0156R1 vom 03.04.2014 Fax: +49-531-2355-5298
email: ad@LBA.de
FOKKER 07.04.2014
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Fokker Services B.V.
Hersteller: Fokker Aircraft B.V.
Muster: F28
Baureihen: F28 Mark 1000, F28 Mark 2000, F28 Mark 3000 und F28 Mark 4000
Werknummern: Ausgenommen sind alle Flugzeuge, die gemäß dem Fokker Services Service
Bulletin SBF28-57-098 oder SBF28-28-054 Revision 1 modifiziert wurden.
Gerätenummer: 2824, EASA.A.037
Revisionsstand:
Diese LTA ersetzt D-2010-244 vom 20.09.2010
Airworthiness Directive der ausländischen Behörde:
EASA AD 2010-0156R1 vom 03.04.2014
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 2010-244R1 ge-
führt.
Betrifft:
(ATA 28) Fuel - Outer Wing Upper Skin Panel Reinforcement Structure - Inspection / Rework [Fuel Tank
Safety]
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 2010-0156R1 vom 03.04.2014 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-2010-244R1 Seite 1 von 1 178/2014
