Nachrichten für Luftfahrer 2012 Teil II (weicht ggf. von Druckversion ab)
[Federal Register Volume 77, Number 139 (Thursday, July 19, 2012)]
[Rules and Regulations]
[Pages 42419-42421]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-17592]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0758; Directorate Identifier 2012-CE-027-AD; Amendment 39-17129;
AD 2012-14-15]
RIN 2120-AA64
Airworthiness Directives; Honeywell International, Inc. Global Navigation Satellite Sensor
Units
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for certain aircraft equipped with
Honeywell International, Inc. Model KGS200 Mercury2 wide area augmentation system (WAAS)
global navigation satellite sensor units (GNSSU). This AD requires you cease all localizer
performance (LP), localizer performance with vertical guidance (LPV), and satellite based
augmentation system (SBAS) lateral navigation/vertical navigation (LNAV/VNAV) approaches until
a software problem is corrected. This AD was prompted by a report and follow-up investigation of a
software problem that occurred during flight test trials of SBAS-capable aircraft using a similar
Honeywell global positioning system (GPS) sensor and the same software as the Model KGS200
Mercury2 GNSSU. A software problem occurred that could result in misleading information during
LP, LPV, or SBAS LNAV/VNAV approaches. We are issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective July 19, 2012.
We must receive comments on this AD by September 4, 2012.
ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by
any of the following methods:
• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for
submitting comments.
• Fax: 202-493-2251.
• Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
1
• Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between
9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at
the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (phone: 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
• Non-Pilatus aircraft-related: Albert Ma, Aerospace Engineer, Wichita Aircraft Certification
Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946-4151;
fax: (316) 946-4107; email: albert.ma@faa.gov.
• Pilatus aircraft-related: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-
4090; email: doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We received a report that during flight test trials of SBAS-capable aircraft using a similar
Honeywell GPS sensor with the same software as the Honeywell International, Inc. Model KGS200
Mercury2 WAAS GNSSU, a software problem occurred that could result in misleading information
during LP, LPV, or SBAS LNAV/VNAV approaches.
Investigation found the GPS receiver could compute an incorrect ionospheric correction and
error estimate such that the error estimate no longer bounds the error and the downstream monitor
cannot detect it. This can potentially lead to hazardously misleading information.
The software problem is due to a mathematical rounding error, which results in misleading
information.
At this time, the only type-certificated airplanes that the product is installed in is Pilatus PC-
12/47E airplanes.
This condition, if not corrected, could result in misleading information during instrument
meteorological conditions, which could prevent the aircraft from performing safe instrument
approach procedures, causing controlled flight into terrain.
FAA's Determination
We are issuing this AD because we evaluated all the relevant information and determined the
unsafe condition described previously is likely to exist or develop in other products of the same type
design.
AD Requirements
This AD requires incorporating airworthiness limitations and placards that prohibit LP, LPV, and
SBAS LNAV/VNAV approaches until the software problem is corrected.
2
Interim Action
We consider this AD interim action. If and when new software is developed, the FAA will
evaluate this software and may take further rulemaking action.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found
that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule
because this condition, if not corrected, could result in misleading information during instrument
meteorological conditions, which could prevent the aircraft from performing safe instrument
approach procedures, causing controlled flight into terrain. Therefore, we find that notice and
opportunity for prior public comment are impracticable and that good cause exists for making this
amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight safety and was not preceded by
notice and an opportunity for public comment. However, we invite you to send any written data,
views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES
section. Include the docket number FAA-2012-17129 and Directorate Identifier 2012-CE-027-AD at
the beginning of your comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will consider all comments received by
the closing date and may amend this AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including
any personal information you provide. We will also post a report summarizing each substantive
verbal contact we receive about this AD.
Costs of Compliance
We estimate that this AD affects 195 GNSSU installed on, but not limited to, PILATUS
AIRCRAFT LTD. Model PILATUS PC-12/47E 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
cost product U.S.
operators
Incorporate language into the limitations 0.5 work-hour × $85 $5 $47.50 $9,263
section of the flight manual and per hour = $42.50.
manufacture and install a placard.
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,
3
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.
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):
4
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2012-14-15 Honeywell International, Inc.: Amendment 39-17129; Docket No. FAA-2012-0758;
Directorate Identifier 2012-CE-027-AD.
(a) Effective Date
This AD is effective July 19, 2012.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all Honeywell International, Inc. Model KGS200 Mercury2 wide area
augmentation system (WAAS) global navigation satellite sensor units (GNSSU), Honeywell part
numbers (P/N) 066-01201-0102 and 066-01201-0104.
(2) This product is installed on, but not limited to, PILATUS AIRCRAFT LTD. Model
PILATUS PC-12/47E airplanes, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code
3457, Navigation.
(e) Unsafe Condition
This AD was prompted by a report and follow-up investigation of a software problem that
occurred during flight test trials of satellite based augmentation system (SBAS)-capable aircraft using
a similar Honeywell global positioning system (GPS) sensor and the same software as the Model
KGS200 Mercury2 GNSSU. A software problem occurred that could result in misleading information
during localizer performance (LP), localizer performance with vertical guidance (LPV), or SBAS
lateral navigation/vertical navigation (LNAV/VNAV) approaches. We are issuing this AD to correct
the unsafe condition on these products.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Incorporate Language Into the Limitations Section of the Aircraft Flight Manual
(1) Before further flight after July 19, 2012 (the effective date of this AD), incorporate language
into the limitations section of the aircraft flight manual (AFM) that states, ''localizer performance
(LP), localizer performance with vertical guidance (LPV), and satellite based augmentation system
(SBAS) lateral navigation/vertical navigation (LNAV/VNAV) approach operations are prohibited.'' If
it can be determined by a review of the AFM that the aircraft does not have LP capability and uses
5
barometric vertical navigation (VNAV), then it is permissible to incorporate language into the
limitation section of the AFM that states, ''local performance with vertical guidance (LPV)
approaches are prohibited.''
(2) The AFM action required by this AD may be done by an owner/operator (pilot) holding at
least a private pilot certificate and must be entered into the aircraft records showing compliance with
this AD in accordance with 14 CFR 43.9 (a)(1)(4) and 14 CFR 91.417(a)(2)(v). The record must be
maintained as required by 14 CFR §§ 91.173, 121.380, or 135.439.
(h) Fabricate and Install a Placard
(1) Within 3 days after July 19, 2012 (the effective date of this AD), fabricate and install a
placard that states, ''LP, LPV, and SBAS LNAV/VNAV approaches are prohibited.'' If it can be
determined by a review of the AFM that the aircraft does not have LP capability and uses VNAV,
then it is permissible to use a placard that states, ''LPV approaches are prohibited.''
(2) The placard shall be manufactured so that the font size is at least an 1/8'' with black lettering
on a white background. The placard must be fabricated and installed by a certificated aircraft
mechanic on the instrument panel in clear view of the pilot.
(i) Special Flight Permit
Special flight permits are prohibited for this AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Wichita 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.
(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
For more information about this AD, contact:
(1) Non-Pilatus aircraft-related: Albert Ma, Aerospace Engineer, Wichita Aircraft Certification
Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946-4151; fax:
(316) 946-4107; email: albert.ma@faa.gov; or
(2) Pilatus aircraft-related: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane
Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax:
(816) 329-4090; email: doug.rudolph@faa.gov.
(l) Material Incorporated by Reference
None.
Issued in Kansas City, Missouri, on July 13, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate,
Aircraft Certification Service.
6
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-291 Fax: +49-531-2355-725
email: ad@lba.de
AIRBUS Datum der Bekanntgabe: 20.07.2012
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus, Airbus Industrie
Muster: A320
Baureihen: A318-112, A319-111, A319-112, A319-115, A319-132 und A319-133
Werknummern: 3983, 3985, 3998, 4000, 4004, 4007, 4018, 4020, 4029, 4036, 4038, 4039,
4040, 4048, 4052, 4056, 4069, 4071, 4076, 4080, 4087, 4089, 4121, 4125,
4127, 4129, 4132, 4141, 4151, 4163, 4164, 4166, 4169, 4171, 4182, 4192,
4200, 4204, 4211, 4215, 4222, 4227, 4228, 4254, 4256, 4258, 4259, 4262,
4268, 4275, 4282, 4285, 4287, 4301, 4313, 4319, 4327, 4332 und 4336
Gerätenummer: 2846, EASA.A.064
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2012-0132 vom 19.07.2012
Betrifft:
(ATA 53) Fuselage - Forward Fuselage Frame (FR) 24 Circumferential Junction - Inspection / Repair
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 2012-0132 vom 19.07.2012.
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 A320-00-1219 (Originalausgabe) vom 09.11.2010
Airbus Service Bulletin A320-00-1219 Revision 01 vom 08.12.2010
Airbus Service Bulletin A320-00-1219 Revision 02 vom 06.09.2011
Airbus Service Bulletin A320-00-1219 Revision 03 vom 28.03.2012
Airbus Service Bulletin A320-53-1242 (Originalausgabe) vom 22.05.2012
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.
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-2012-291 Seite 1 von 1 395/2012
EASA AD No : 2012-0132
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2012-0132
Date: 19 July 2012
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 EC 1702/2003, 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 A318 and A319 aeroplanes
TCDS Number : EASA.A.064
Foreign AD : Not applicable
Supersedure : None
Fuselage – Forward Fuselage Frame (FR) 24 Circumferential
ATA 53
Junction – Inspection / Repair
Manufacturer(s): Airbus (formerly Airbus Industrie)
Applicability: Airbus A318-112, A319-111, A319-112, A319-115, A319-132 and A319-133
aeroplane models, manufacturer serial numbers (MSN) 3983, 3985, 3998,
4000, 4004, 4007, 4018, 4020, 4029, 4036, 4038, 4039, 4040, 4048, 4052,
4056, 4069, 4071, 4076, 4080, 4087, 4089, 4121, 4125, 4127, 4129, 4132,
4141, 4151, 4163, 4164, 4166, 4169, 4171, 4182, 4192, 4200, 4204, 4211,
4215, 4222, 4227, 4228, 4254, 4256, 4258, 4259, 4262, 4268, 4275, 4282,
4285, 4287, 4301, 4313, 4319, 4327, 4332 and 4336.
Reason: During a ground inspection of an A319 aeroplane in production, it was
discovered that one fastener was missing at stringer (STGR) 39 on the right-
hand (RH) side of FR24 (Section 13-14 side). The hole of the missing fastener
was not drilled. The missing fastener, a 4.8 mm diameter titanium bolt, Part
Number (P/N) EN 6114 V3-7, should connect the cargo door keel beam foot to
the circumferential butt-strap and the section 13-14 lower shell panel. Further
investigations have revealed that the affected fastener has not been installed
on a limited number of aeroplanes in production, due to incorrect production
instructions.
This condition, if not corrected, could impair the structural integrity of the
affected aeroplanes.
For the reasons described above, this AD requires a special detailed
inspection (SDI) of the affected area and, depending on findings, the
accomplishment of applicable corrective actions.
Effective Date: 02 August 2012
CAP.00110-001 © 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 : 2012-0132
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Within the threshold indicated in Table 1 of this AD as applicable to the
Time(s):
aeroplane configuration, accomplish a visual inspection of the fastener at
FR24 STGR 39 RH, in accordance with the instructions of Airbus Service
Bulletin (SB) A320-53-1242.
Table 1 – Compliance time
Aeroplane Configuration Inspection Threshold
A319 aeroplanes except MSN Before the accumulation of 5 000
4151, 4228 and 4319, flight cycles (FC) since first flight of
and the aeroplane, or within 4 300 FC
after the effective date of this AD,
A318 aeroplanes, pre-mod
whichever occurs later.
39195, and on which Airbus SB
A320-00-1219 has not been
embodied in service.
A318 aeroplanes, post-mod Before the accumulation of 3 000 FC
39195, and on which Airbus SB since first flight of the aeroplane.
A320-00-1219 has been
embodied in service.
A319 aeroplanes, MSN 4151, Before the accumulation of 2 500 FC
4228 and 4319 (post-mod since first flight of the aeroplane.
28238, 28162 and 28342)
(2) If, during the visual inspection as required by paragraph (1) of this AD, the
fastener is found missing, within the compliance time indicated in Table 1
of this AD, as applicable, accomplish a SDI of the five holes surrounding
the missing fastener at FR24 STGR 39 RH side to detect any crack, in
accordance with the instructions of Airbus SB A320-53-1242.
(3) If, during the SDI as required by paragraph (2) of this AD, no crack is
found, within the compliance time indicated in Table 1 of this AD, apply
the corrective actions (repair) in accordance with the instructions of Airbus
SB A320-53-1242.
(4) If, during the SDI as required by paragraph (2) of this AD, any crack is
found, before next flight, contact Airbus for approved repair instructions
and accomplish those instructions accordingly.
Ref. Publications: Airbus SB A320-53-1242 original issue, dated 22 May 2012.
Airbus SB A320-00-1219 original issue dated 09 November 2010, Revision 01
dated 08 December 2010, Revision 02 dated 06 September 2011 or Revision
03 dated 28 March 2012.
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. This AD was posted on 05 June 2012 as PAD 12-059 for consultation until
03 July 2012. 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 – EIAS,
Fax +33 5 61 93 44 51; E-mail: account.airworth-eas@airbus.com.
CAP.00110-001 © 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
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-292 Fax: +49-531-2355-725
email: ad@lba.de
AIRBUS Datum der Bekanntgabe: 20.07.2012
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus, Airbus Industrie
Muster: A380
Baureihen: A380-841, A380-842 und A380-861
Werknummern: Alle
Ausgenommen sind Flugzeuge, an denen die beiden Airbus Modifikationen
70498 und 71229 oder die beiden Modifikationen 71089 und 71230 bei der
Flugzeugherstellung durchgeführt worden sind.
Gerätenummer: EASA.A.110
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2012-0135 vom 20.07.2012
Betrifft:
(ATA 35) Oxygen - Crew Oxygen / Rod Fitting and Cylinder Brackets of Oxygen Box and Reverse Z Stop Fitting
Screws - 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 2012-0135 vom 20.07.2012.
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 A380-35-8007 (Originalausgabe) vom 06.12.2011
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.
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-2012-292 Seite 1 von 1 396/2012
