Nachrichten für Luftfahrer 2013 Teil II (weicht ggf. von Druckversion ab)
We also determined that these changes will not increase the economic burden on any operator or
increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 161 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
Inspection Between 4 and 16 work-hours × $85 $0 Between $340 Between $54,740
per hour = Between $340 and $1,360. and $1,360. and $218,960.
We estimate the following costs to do any necessary replacements that would be required based
on the results of the inspection. We have no way of determining the number of aircraft that might
need these replacements:
On-condition Costs
Action Labor cost Parts cost Cost per product
Replacement 1 work-hour × $85 per hour = $85 $137 $222
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
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.
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.
4
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 adding the following new airworthiness directive (AD):
5
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2013-05-10 The Boeing Company: Amendment 39-17382; Docket No. FAA-2011-1417;
Directorate Identifier 2011-NM-159-AD.
(a) Effective Date
This AD is effective May 3, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F
series airplanes, certificated in any category, as identified in Boeing Special Attention Service
Bulletin 777-25-0507, dated June 30, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code
25, Equipment/Furnishings.
(e) Unsafe Condition
This AD was prompted by reports that escape slides/rafts did not deploy due to galvanic
corrosion of the door-mounted slide/raft packboard release mechanisms. We are issuing this AD to
detect and correct corrosion in the packboard release mechanisms, which could interfere with escape
slide/raft deployment, prohibit doors from opening in the armed mode, and cause consequent delay
and injury during evacuation of passengers and crew from the cabin in the event of an emergency.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Inspection and Replacement
Within 42 months after the effective date of this AD, at the applicable passenger/crew entry
doors identified in Boeing Special Attention Service Bulletin 777-25-0507, dated June 30, 2011, that
have not been modified as specified in Air Cruisers Service Bulletin 777 107-25-30, dated September
30, 2010 (which is not incorporated by reference in this AD): Do a general visual inspection of the
housing assembly of the packboard release mechanism to determine if its surface treatment has been
sealed; and if unsealed, before further flight, replace the housing assembly with a new or serviceable
housing assembly; in accordance with the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 777-25-0507, dated June 30, 2011.
6
Note 1 to paragraph (g) of this AD: Boeing Special Attention Service Bulletin 777-25-0507,
dated June 30, 2011, refers to Air Cruisers Service Bulletin 777 107-25-30, dated September 30, 2010
(which is not incorporated by reference in this AD), as an additional source of guidance for
inspecting and installing a new housing assembly of the door-mounted slide/raft packboard release
mechanism.
(h) Optional Terminating Action
Verifying the housing assembly has been replaced with a new or serviceable housing assembly
by inspecting for a stencil to verify that there is a stencil marked ''Inspected and/or Mod per S.B. 777
107-25-30'' on the girt assembly and upper lacing cover on the housing assembly of the packboard
release mechanism; or by reviewing technical or maintenance records, if it can be conclusively
determined that the modification specified in Air Cruisers Service Bulletin 777 107-25-30, dated
September 30, 2010, (which is not incorporated by reference in this AD), as specified in Boeing
Special Attention Service Bulletin 777-25-0507, dated June 30, 2011, has been accomplished;
terminates the requirements of paragraph (g) of this AD.
(i) Definition of a General Visual Inspection
For the purposes of this AD, a general visual inspection is: A visual examination of an interior or
exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of
inspection is made from within touching distance unless otherwise specified. A mirror may be
necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is
made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms
may be required to gain proximity to the area being checked.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (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 the Related Information section 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.
(k) Related Information
(1) For more information about this AD, contact Ana Martinez Hueto, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6592; fax: 425-
917-6591; email: ana.m.hueto@faa.gov.
(2) For Air Cruisers service information identified in this AD, contact Air Cruisers Company,
1747 State Route 34, Wall, NJ 07727-3935; telephone: 732 681-3527; fax: 732 681-9163; email:
Aircruisers@zodiacaerospace.com. You may review copies of the referenced 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
(l) 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.
(i) Boeing Special Attention Service Bulletin 777-25-0507, dated June 30, 2011.
(ii) Reserved.
(3) For Boeing 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, Washington. 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 March 5, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
8
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
38144 Braunschweig
D-2013-129 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS Datum der Bekanntgabe: 29.04.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus, Airbus Industrie
Muster: A330,
A340
Baureihen: A330-301, A330-321, A330-322, A330-342, A340-211, A340-212, A340-213,
A340-311, A340-312 und A340-313
Werknummern: Alle
Betroffen sind Flugzeuge, bei denen die Airbus Modifikation 42547 während der
Herstellung eingerüstet wurde.
Ebenfalls betroffen sind Flugzeuge der genannten Baureihen des Musters
A340, bei denen die Airbus Modifikation 41300 während der Herstellung
eingerüstet wurde.
Gerätenummer: 2849, 2850, EASA.A.004, EASA.A.015
Revisionsstand:
Diese LTA ersetzt D-2002-088 vom 04.04.2002 / D-2002-089 vom 04.04.2002
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0092 vom 15.04.2013
Betrifft:
(ATA 57) Wings - Inner Rear Spar Upper Build Slot - Inspection / Modification
Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten EASA Airworthiness
Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen. Alle erforderlichen Maßnahmen
zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und innerhalb der vorgesehenen
Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von den Maßnahmen
und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Alle anzuwendenden Fristen sind der genannten EASA Airworthiness Directive zu entnehmen. Die Laufzeit aller
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten EASA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2013-0092 vom 15.04.2013.
Zugehörige technische Dokumente:
Hinweis: Die Anwendung von nachfolgenden Ausgaben bzw. Revisionsständen der genannten zugehörigen technischen Dokumente ist zulässig, wenn dies nach
der Airworthiness Directive der ausländischen Behörde ausdrücklich gestattet ist oder wenn diese von der ausländischen Behörde in Bezug auf die referenzierte
Airworthiness Directive genehmigt worden sind.
Airbus Service Bulletin A330-57-3058 vom 29.08.2001
Airbus Service Bulletin A330-57-3059 Revision 1 vom 13.09.2001
Airbus Service Bulletin A330-57-3059 Revision 2 vom 20.09.2012
Airbus Service Bulletin A330-57-3059 vom 16.03.2011
Airbus Service Bulletin A340-57-4065 vom 29.08.2001
Airbus Service Bulletin A340-57-4066 Revision 1 vom 13.09.2001
Airbus Service Bulletin A340-57-4066 Revision 2 vom 20.09.2012
Airbus Service Bulletin A340-57-4066 vom 16.03.2001
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der Sicherheit des Luftverkehrs, das in diesem Fall
das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es erforderlich, die sofortige Vollziehung dieser Lufttüchtigkeitsanweisung
anzuordnen.
D-2013-129 Seite 1 von 2 250/2013
Rechtsbehelfsbelehrung: Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge- richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie- derherstellen bzw. anordnen. D-2013-129 Seite 2 von 2 250/2013
EASA AD No.: 2013-0092
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2013-0092
Date: 15 April 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):
AIRBUS A330 and A340-200/300 aeroplanes
TCDS Number: EASA.A.004, EASA.A.015
Foreign AD: Not applicable
Supersedure: This AD supersedes DGAC France AD 2001-269(B) dated 27 June 2001 and
DGAC France AD 2001-268 (B)R1 dated 25 July 2001.
Wings – Inner Rear Spar Upper Build Slot – Inspection /
ATA 57
Modification
Manufacturer(s): Airbus (formerly Airbus Industries)
Applicability: Airbus A330-301, A330-321, A330-322, A330-342 aeroplanes, all Manufacturer
Serial Numbers (MSN), except those on which Airbus modification 42547 has
been embodied in production
and
Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313
aeroplanes, all MSN, except those on which Airbus modification 42547 or
modification 41300 has been embodied in production.
Reason: During wing fatigue test, a crack was detected which propagated from the tip of
the build slot in the vertical web of the wing inner rear spar between rib 1 and 2.
This condition, if not detected and corrected, could lead to reduced structural
integrity of the wing.
To address this potentially unsafe situation, DGAC France issued AD 2001-
268(B)R1 and AD 2001-269(B) to require repetitive High Frequency Eddy
Current (HFEC) inspections of the aft face of the inner rear spar web in the area
adjacent to the outboard end of the build slot and, depending on findings, repair
of the inner rear spar web.
Since these ADs were issued, in the frame of a new fatigue and damage
tolerance evaluation, taking into account aeroplane utilization and Widespread
Fatigue Damage (WFD) analysis, the thresholds and intervals of the affected
inspections have been reassessed. The conclusion of this reassessment was
that several thresholds and intervals must be reduced to allow timely detection
TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3
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EASA AD No.: 2013-0092
of cracks and the accomplishment of an applicable corrective action.
For the reason described above, this AD retains the requirements of DGAC
France AD 2001-268(B)R1 and AD 2001-269(B), which are superseded, but
requires those actions within the new thresholds and intervals.
Effective Date: 29 April 2013
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Initially, within the compliance time defined in Table 1 of this AD, as
Time(s):
applicable, and thereafter at intervals not to exceed the values defined in
Airbus Service Bulletin (SB) A330-57-3059 Revision 02, or SB A340-57-
4066 Revision 02, as applicable to aeroplane type and depending on
aeroplane utilization, accomplish a HFEC inspection of the aft face of the
rear spar at the area adjacent to the bolt holes and the end of the build slot
in accordance with the instructions of Airbus SB A330-57-3059 Revision
02, or SB A340-57-4066 Revision 02, as applicable to aeroplane type.
Table 1 – Initial Inspection
Compliance time (whichever occurs later, A or B)
A Within the threshold or interval, as applicable, as defined in
Airbus SB A330-57-3059 Revision 02, or SB A340-57-4066
Revision 02, as applicable to aeroplane type and depending on
aeroplane utilization
B Within 18 months after the effective date of this AD
(2) Inspections and corrective actions, accomplished before the effective date
of this AD in accordance with the instructions of Airbus SB A330-57-3059
at original issue or Revision 01, or SB A340-57-4066 at original issue or
Revision 01, as applicable to aeroplane type, are acceptable for
compliance with the initial requirements of paragraph (1) of this AD.
After the effective date of this AD, inspections and applicable corrective
actions as required by this AD must be accomplished in accordance with
the instructions of Airbus SB A330-57-3059 Revision 02 or A340-57-4066
Revision 02, as applicable to aeroplane type.
(3) If, during any inspection as required by paragraph (1) of this AD,
discrepancies are detected, before next flight, accomplish the applicable
corrective actions in accordance with the instructions of Airbus SB A330-
57-3059 Revision 02, or SB A340-57-4066 Revision 02, as applicable to
aeroplane type.
(4) Modification of an aeroplane in accordance with the instructions of Airbus
SB A330-57-3058, or SB A340-57-4065, as applicable to aeroplane type,
constitutes terminating action for the repetitive inspections as required by
paragraph (1) of this AD for that aeroplane.
Ref. Publications: Airbus SB A330-57-3058 original issue dated 29 August 2001.
Airbus SB A330-57-3059 original issue dated 16 March 2001, or Revision 1
dated 13 September 2001, or Revision 2 dated 20 September 2012.
Airbus SB A340-57-4065 original issue dated 29 August 2001.
Airbus SB A340-57-4066 original issue dated 16 March 2001, or Revision 1
dated 13 September 2001, or Revision 2 dated 20 September 2012.
The use of later approved revisions of these documents is acceptable for
compliance with the requirements of this AD.
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EASA AD No.: 2013-0092
Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative
Methods of Compliance for this AD.
2. This AD was posted on 12 March 2013 as PAD 13-047 for consultation until
09 April 2013. The Comment Response Document can be found at
http://ad.easa.europa.eu.
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. 3/3
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