Nachrichten für Luftfahrer 2012 Teil II (weicht ggf. von Druckversion ab)
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2011-22-03 Rolls-Royce Corporation (Formerly Allison Engine Company): Amendment 39-
16845; Docket No. FAA-2011-0273; Directorate Identifier 2011-NE-08-AD.
(a) Effective Date
This AD is effective November 17, 2011.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Rolls-Royce Corporation (RRC) AE 3007A, AE 3007A1/1, AE 3007A1, AE
3007A1/3, AE 3007A1E, AE 3007A1P, and AE 3007A3 turbofan engines, with any of the 6th-
through-13th stage compressor wheel part numbers (P/Ns) in Table 1 of this AD installed.
Table 1–6th-Through-13th Stage Compressor Wheel P/Ns Affected by This AD
Compressor Wheel P/Ns with Chrome- Wheel P/Ns with Uncoated
Wheel Stage: Carbide Coated Knife Seals: Knife Seals:
6th 23074717 23062666, 23071261,
23071396
7th 23074719, 23074217 23062667, 23071262,
23071397
8th 23074721 23061628, 23071263,
9th 23074722 23061629, 23071264
th
10 23074723 23061630, 23071265
11th 23074724 23061631, 23066231
12th 23074725 23061632, 23071267
13th 23074213, 23074726 23061633, 23071268
(d) Unsafe Condition
This AD was prompted by reports of low-cycle fatigue cracks found during shop visits, in the
6th-through-13th stage compressor wheels having chrome-carbide coated or uncoated knife edge
seals. We are issuing this AD to prevent uncontained failure of the 6th-through-13th stage
compressor wheel, leading to damage to the airplane.
5
(e) Compliance
Comply with this AD within the compliance times specified, unless already done.
(f) Initial Inspection
The initial inspection compliance times for the 6th-through-13th stage compressor wheels are
based on cycles-since-new (CSN) and cycles-in-service (CIS) of their 12th and 13th stage compressor
wheels. For engines that one or both 12th and 13th stage compressor wheels have chrome-carbide
coated knife edge seals, use the compliance times listed in Table 2 of this AD. For engines that both
12th and 13th stage compressor wheels do not have chrome-carbide coated knife edge seals, use the
compliance times listed in Table 3 of this AD.
(1) Perform a one-time comprehensive eddy current inspection (ECI) of the 6th-through-13th
stage compressor wheel knife edge seals for cracks, using paragraph 2, Accomplishment Instructions,
of RRC Alert Service Bulletin (ASB) No. AE 3007A-A-72-386, Revision 4, dated June 27, 2011
(Completion of this one-time comprehensive ECI relieves you thereafter of the repetitive inspection
requirements of this AD); or
(2) Perform an initial ECI of the 6th-through-13th stage compressor wheel outer circumferences
for cracks, using paragraph 2, Accomplishment Instructions, of RRC ASB No. AE 3007A-A-72-390,
Revision 3, dated June 27, 2011.
Table 2–Initial Inspection Compliance Times for Engines, That One or Both 12th and 13th
Stage Compressor Wheels Have Chrome-Carbide Coated Knife Edge Seals
For 12th and or 13th Stage Initially Inspect After the Effective
Compressor Wheels With the Date of this AD:
Following CSN on the Effective Date
of this AD:
(i) 18,185 or more CSN. Within 15 CIS.
(ii) 16,700 to 18,184 CSN. Before accumulating 18,200 CSN.
(iii) 16,000 to 16,699 CSN. Within 1,500 CIS.
(iv) 15,100 to 15,999 CSN. Within 2,000 CIS.
(v) 14,300 to 15,099 CSN. Within 2,800 CIS.
(vi) 13,000 to 14,299 CSN. Within 3,400 CIS.
(vii) 12,300 to 12,999 CSN. Within 4,000 CIS.
(viii) 11,200 to 12,299 CSN. Within 4,600 CIS.
(ix) 9,700 to 11,199 CSN Within 5,300 CIS.
(x) Fewer than 9,700 CSN. Before accumulating 15,000 CSN or at
the next shop visit when the engine has
more than 7,000 cycles, whichever
occurs first.
6
Table 3–Initial Inspection Compliance Times for Engines, That Both 12th and 13th Stage
Compressor Wheels Do Not Have Chrome-Carbide Coated Knife Edge Seals
For 12th and or 13th Stage Compressor Wheels Initially Inspect After the Effective
With the Following CSN on the Effective Date Date of This AD:
of this AD:
(i) 18,300 or more CSN. Within 200 CIS.
(ii) 16,000 to 18,299 CSN. Within 1,500 CIS.
(iii) 15,100 to 15,999 CSN. Within 2,000 CIS.
(iv) 14,300 to 15,099 CSN. Within 2,800 CIS.
(v) 13,000 to 14,299 CSN. Within 3,400 CIS.
(vi) 12,300 to 12,999 CSN. Within 4,000 CIS.
(vii) 11,200 to 12,299 CSN. Within 4,600 CIS.
(viii) 9,700 to 11,199 CSN. Within 5,300 CIS.
(ix) Fewer than 9,700 CSN. Before accumulating 15,000 CSN or
at the next shop visit when the
engine has more than 7,000 cycles,
whichever occurs first.
(g) Repetitive Inspections
(1) After passing the initial inspection, perform repetitive ECIs of the compressor wheel outer
circumference, for cracks, within every 5,000 cycles-since-last-inspection (CSLI), using paragraph 2,
Accomplishment Instructions, of RRC ASB No. AE 3007A-A-72-390, Revision 3, dated June 27,
2011; or
(2) Perform a one-time comprehensive ECI of the 6th-through-13th stage compressor wheel
knife edge seals for cracks, within 5,000 CSLI using paragraph 2, Accomplishment Instructions, of
RRC ASB No. AE 3007A-A-72-386, Revision 4, dated June 27, 2011. Completion of this one-time
ECI comprehensive inspection relieves you thereafter of the repetitive inspection requirements of this
AD.
(h) 6th-Through-13th Stage Compressor Wheels Found Cracked
Remove from service before further flight 6th-through-13th stage compressor wheels that are
found cracked.
(i) Special Flight Permits
Special Flight Permits are limited to essential flight crew only.
(j) Reporting Requirements
Report all inspection results within 10 days, to AE Service Data, Rolls-Royce Corporation, Attn:
AE Service Data Manager, P.O. Box 420, Speed Code U17, Indianapolis, IN 46206-0420, email:
royce.com">cra.rel.data@rolls-royce.com. Use the reporting instructions in:
(1) Paragraph 2.D. of ASB No. AE 3007A-A-72-386, Revision 4, dated June 27, 2011.
7
(2) Service Bulletin Compliance Form of RRC ASB No. AE 3007A-A-72-390, Revision 3, dated
June 27, 2011.
(k) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor
shall a person be subject to a penalty for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that collection of information displays a
current valid OMB Control Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection
Clearance Officer, AES-200.
(l) Previous Inspection Credit
(1) If you previously performed an ECI of the 6th-through-13th stage compressor wheels using
RRC ASB No. AE 3007A-A-390, Revision 1, dated February 14, 2011 or Revision 2, dated June 10,
2011, or Revision 3, dated June 27, 2011, you met the initial inspection requirements of this AD.
(2) If you previously performed a one-time comprehensive ECI of the 6th-through-13th stage
compressor wheel knife edge seals, using RRC ASB No. AE 3007A-A-72-386, dated October 20,
2010, or Revision 1, dated December 17, 2010, or Revision 2 dated January 10, 2011, or Revision 3,
dated June 10, 2011, you met the initial inspection requirements of paragraph (f) of this AD.
Completion of this one-time comprehensive inspection relieves you of the repetitive inspection
requirements of this AD.
(3) If you previously performed an ultrasonic inspection of the compressor wheel knife edge
seals, using RRC Service Bulletin No. AE 3007A-72-382, dated April 6, 2010, prior to publication of
RRC ASB No. AE 3007A-A-72-386, dated October 20, 2010, you met the initial inspection
requirements of this AD. Completion of this one-time ultrasonic inspection relieves you of the
repetitive inspection requirements of this AD.
(m) Alternative Methods of Compliance (AMOCs)
The Manager, Chicago Aircraft Certification Office, may approve AMOCs for this AD. Use the
procedures found in 14 CFR 39.19 to make your request.
(n) Related Information
For more information about this AD, contact Kyri Zaroyiannis, Aerospace Engineer, Chicago
Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 E. Devon Ave., Des Plaines, IL
60018; phone: (847) 294-7836; fax: (847) 294-7834; email: kyri.zaroyiannis@faa.gov.
(o) Material Incorporated by Reference
You must use the following service information to do the actions required by this AD, unless the
AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following service information on the date
specified:
(1) Rolls-Royce Corporation Alert Service Bulletin No. AE 3007A-A-72-386, Revision 4, dated
June 27, 2011, approved for IBR November 17, 2011.
8
(2) Rolls-Royce Corporation Alert Service Bulletin No. AE 3007A-A-72-390, Revision 3, dated
June 27, 2011, approved for IBR November 17, 2011.
(3) For service information identified in this AD, contact Rolls-Royce Corporation, P.O. Box
420, Indianapolis, IN 46206; phone: (317) 230-3774; fax: (317) 230-6084; email:
royce.com">indy.pubs.services@rolls-royce.com.
(4) You may review copies of the service information at the FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of
this material at the FAA, call (781) 238-7125.
(5) You may also review copies of the service information that is incorporated by reference at the
National Archives and Records Administration (NARA). For information on the availability of this
material at an NARA facility, call (202) 741-6030, or go to
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Burlington, Massachusetts, on October 25, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
9
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-064 Fax: +49-531-2355-725
email: ad@lba.de
AIRBUS Datum der Bekanntgabe: 24.01.2012
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 Airbus Modifikation 71738 bei der
Flugzeugherstellung durchgeführt worden ist.
Gerätenummer: EASA.A.110
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2012-0010 vom 18.01.2012
Betrifft:
(ATA 31) Indicating & Recording Systems - Flight Data Recording System (FDRS) - Software Installation
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 2012-0010 vom 18.01.2012.
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 A380-31-8050 vom 20.10.2011
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-2012-064 Seite 1 von 1 042/2012
EASA AD No.: 2012-0010
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2012-0010
Date: 18 January 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].
Type Approval Holder’s Name : Type/Model designation(s) :
AIRBUS A380 aeroplanes
TCDS Number: EASA.A.110
Foreign AD: Not applicable
Supersedure: None
Indicating & Recording Systems – Flight Data Recording System
ATA 31
(FDRS) – Software Installation
Manufacturer(s): Airbus
Applicability: Airbus A380-841, A380-842, and A380-861 aeroplanes, all manufacturer
serial numbers (MSN), except aeroplanes on which Airbus modification
71738 has been embodied in production.
Reason: Reboots of the Acquisition and Flight Data Interface Application (AFDIA)
software of the Centralized Data Acquisition Module (CDAM) have been
reported.
Investigations have revealed that the content of the non-volatile memory had
been corrupted, which causes the unit to reboot continuously.
This condition, if not corrected, could result in a deficiency in systems used
to assist in the enquiry following an accident or serious incident, preventing
them to perform their intended function.
For the reasons described above, this AD requires the installation of the
updated AFDIA software, which ensures correct operation of the CDAM.
Effective Date: 01 February 2012
Required Action(s) Required as indicated, unless already accomplished:
and Compliance
(1) Within 3 months after the effective date of this AD, install on CDAM the
Time(s):
AFDIA software, having Part Number (P/N) SFI53S0002S0386, in
accordance with the instructions of Airbus Service Bulletin
(SB) A380-31-8050.
EASA Form 110 Page 1/2
EASA AD No.: 2012-0010
(2) After the effective date of this AD, do not install on any aeroplane the
AFDIA software having P/N SFI50S0002S0385.
Ref. Publications: Airbus Service Bulletin A380-31-8050 original issue dated 20 October 2011.
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 required actions and the risk allowance have granted the issuance
of a Final AD with Request for Comments, postponing the public
consultation process after publication.
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 SAS - EANA (Airworthiness Office),
Phone: +33 562110253 ; Fax:+33 562 110 307
E-mail: account.airworth-A380@airbus.com and
Nicolas.Cordeau@airbus.com.
EASA Form 110 Page 2/2
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-065 Fax: +49-531-2355-725
email: ad@lba.de
AIRBUS Datum der Bekanntgabe: 24.01.2012
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: 0003, 0005 bis 0017, 0019 bis 0023, 0025 bis 0030, 0033, 0034, 0038, 0040,
0041, 0043, 0045 und 0051
Gerätenummer: EASA.A.110
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2012-0011 vom 20.01.2012
Betrifft:
(ATA 49) Airborne Auxiliary Power - Auxiliary Power Unit (APU) Air Intake Duct Access Cover Cut-Out - 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 2012-0011 vom 20.01.2012.
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 A380-49-8005 vom 10.08.2011
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-2012-065 Seite 1 von 1 043/2012
EASA AD No : 2012-0011
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2012-0011
Date: 20 January 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].
Type Approval Holder’s Name : Type/Model designation(s) :
AIRBUS A380 Aeroplanes
TCDS Number : EASA.A.110
Foreign AD : Not applicable
Supersedure : None
Airborne Auxiliary Power – Auxiliary Power Unit (APU) Air Intake
ATA 49
Duct Access Cover Cut-Out – Inspection / Repair
Manufacturer(s): Airbus
Applicability: Airbus A380-841, A380-842, and A380-861 Aeroplanes, manufacturer serial
numbers (MSN): 0003, 0005 through 0017 inclusive, 0019 through 0023
inclusive, 0025 through 0030 inclusive, 0033, 0034, 0038, 0040, 0041, 0043,
0045 and 0051.
Reason: During an inspection on an in-production aeroplane, the following non
conformities have been discovered on an APU air intake duct access cover
cut-out:
- Missing epoxy resin around the inserts and at the edge of the air
intake duct wall cut-out, and
- Missing epoxy adhesive at the edges of the air intake duct wall cut-
out.
It was found that these materials have not been applied on a specific group of
aeroplanes due to an incorrect quality process during production. However,
the fire sealant ensures continuing proper fire protection.
In addition, it has been identified that task 49-16-00-210-801-A of the Airbus
A380 Aircraft Maintenance Manual (AMM), titled “General Visual Inspection of
inner surfaces of Air Intake Duct and P-Seal at Housing/Duct Interface”, did
not contain instructions to apply fire sealant compound for the in-service
installation procedure of the APU air intake duct inspection access cover.
The investigation has shown that the in-service accomplishment of this
incorrect AMM task in combination with the absence of epoxy resin and
EASA Form 110 Page 1/2
