Nachrichten für Luftfahrer 2012 Teil II (weicht ggf. von Druckversion ab)
(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):
6
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2011-21-03 The Boeing Company: Amendment 39-16826; Docket No. FAA-2010-1312;
Directorate Identifier 2010-NM-220-AD.
Effective Date
(a) This AD is effective November 16, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 777-200, -200LR, -300, and -300ER series
airplanes; certificated in any category; as identified in Boeing Service Bulletin 777-24-0102,
Revision 1, dated June 17, 2010; and Boeing Special Attention Service Bulletin 777-29-0032, dated
August 9, 2007.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America
Codes 29: Hydraulic power; and 24: Electrical power.
Unsafe Condition
(e) This AD was prompted by a report of a fire in the main equipment center due to failure of an
external power connector, which caused high-temperature arcing and subsequent splatter of molten
copper on an adjacent hydraulic tube, creating a hole in the tube and spraying hydraulic fluid into the
power connector, resulting in a fire. In addition there were several reports of overheating or arcing of
external power connectors, and one report of a fire due to arcing caused by foreign object debris
(FOD). We are issuing this AD to prevent FOD from entering the primary and secondary external
power connectors, which could result in overheating or arcing and consequent fire in the main
equipment center.
Compliance
(f) Comply with this AD within the compliance times specified, unless already done.
Modification
(g) Within 36 months after the effective date of this AD, do the actions required by paragraphs
(g)(1) and (g)(2) of this AD.
(1) For airplanes identified in Boeing Service Bulletin 777-24-0102, Revision 1, dated June 17,
2010: Install FOD rubber shields over the primary and secondary external power connectors, in
7
accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-24-0102, Revision
1, dated June 17, 2010.
(2) For airplanes identified in Boeing Special Attention Service Bulletin 777-29-0032, dated
August 9, 2007: Wrap silicone tape around the hydraulic tube, in accordance with the
Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-29-0032, dated
August 9, 2007.
Exception to Service Information
(h) Figure 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin
777-29-0032, dated August 9, 2007, does not identify the units of the dimensions of the silicone tape
installed on the hydraulic tube; those dimensions are identified in inches.
Credit for Actions Accomplished in Accordance With Previous Service Information
(i) Actions done before the effective date of this AD in accordance with Boeing Service Bulletin
777-24-0102, dated July 12, 2007, are acceptable for compliance with the corresponding
requirements of paragraph (g)(1) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(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 e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your Principal Maintenance Inspector or Principal
Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards
District Office.
Related Information
(k) For more information about this AD, contact Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; phone: (425) 917-6482; fax: (425) 917-6590; e-
mail: georgios.roussos@faa.gov.
(l) For service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-
2207; telephone 206-544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the 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.
Material Incorporated by Reference
(m) You must use Boeing Service Bulletin 777-24-0102, Revision 1, dated June 17, 2010; or
Boeing Special Attention Service Bulletin 777-29-0032, dated August 9, 2007; as applicable; to do
the actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of the service
information contained under 5 U.S.C. 552(a) and 1 CFR part 51.
8
(2) 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;
telephone 206-544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
(3) You may review copies of the service information at the 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.
(4) 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 Renton, Washington, on September 27, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
9
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-063 Fax: +49-531-2355-725
email: ad@lba.de
ROLLS-ROYCE Datum der Bekanntgabe: 23.01.2012
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: Rolls-Royce Corporation
Hersteller: Rolls-Royce Corporation, Allison Engine Company
Muster: AE 3007
Baureihen: AE 3007A, AE 3007A1/1, AE 3007A1, AE 3007A1/3, AE 3007A1E,
AE 3007A1P und AE 3007A3
Werknummern: Alle
Betroffen sind nur Triebwerke mit einem Compressor Wheel der 6. bis 13. Stufe
mit folgenden Teilenummern (P/N):
Stufe Wheel P/N mit Wheel P/Ns mit
Chrome-Carbide Uncoated Knife Seals
Coated Knife Seals
6. 23074717 23062666, 23071261 oder 23071396
7. 23074719 oder 23062667, 23071262 oder 23071397
23074217
8. 23074721 23061628 oder 23071263
9. 23074722 23061629 oder 23071264
10. 23074723 23061630 oder 23071265
11. 23074724 23061631 oder 23066231
12. 23074725 23061632 oder 23071267
13. 23074213 oder 23061633 oder 23071268
23074726
Gerätenummer: 6317, EASA.IM.E.044
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2011-22-03 - Amdt. 39-16845
Betrifft:
(ATA 72) Engine Turbine - Compressor Wheel Knife Edge Seals and Outer Circumference - Inspection
Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten FAA Airworthiness Directive
und den genannten technischen Mitteilungen 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 FAA Airworthiness Directive zu entnehmen. Die Laufzeit aller
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten FAA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2011-22-03 - Amdt. 39-16845.
D-2012-063 Seite 1 von 2 036/2012
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. 1. Rolls-Royce Corporation Alert Service Bulletin AE 3007A-A-72-386 Revision 4 vom 27.06.2011 2. Rolls-Royce Corporation Alert Service Bulletin AE 3007A-A-72-390 Revision 3 vom 27.06.2011 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-2012-063 Seite 2 von 2 036/2012
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0273; Directorate Identifier 2011-NE-08-AD; Amendment 39-16845;
AD 2011-22-03]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for Rolls-Royce Corporation
(RRC) AE 3007A, AE 3007A1/1, AE 3007A1, AE 3007A1/3, AE 3007A1E, AE 3007A1P, and AE
3007A3 turbofan engines. This AD requires initial and repetitive eddy current inspections (ECI) of
certain 6th-through-13th stage compressor wheel knife edge seals, and initial and repetitive ECIs of
the compressor wheel outer circumference, for cracks. 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.
DATES: This AD is effective November 17, 2011.
The Director of the Federal Register approved the incorporation by reference of certain
publications listed in the AD as of November 17, 2011.
We must receive comments on this AD by December 19, 2011.
ADDRESSES: You may send comments 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.
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.
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. You may review copies of the referenced 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.
1
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: 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.
SUPPLEMENTARY INFORMATION:
Discussion
We received 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, on RRC AE
3007A, AE 3007A1/1, AE 3007A1, AE 3007A1/3, AE 3007A1E, AE 3007A1P, and AE 3007A3
turbofan engines. These cracks can deteriorate the integrity of the compressor wheel by lengthening
into the outer circumference of the wheel. This condition, if not corrected, could result in uncontained
failure of the 6th-through-13th stage compressor wheel, leading to damage to the airplane.
Relevant Service Information
We reviewed RRC Alert Service Bulletin (ASB) No. AE 3007A-A-72-386, Revision 4, dated
June 27, 2011, which describes procedures for performing a one-time comprehensive ECI of the
compressor wheel outer circumference, for cracks. We also reviewed RRC ASB No. AE 3007A-A-
72-390, Revision 3, dated June 27, 2011, which describes procedures for initial and repetitive
inspections of affected 6th-through-13th stage compressor wheel knife edge seals and the compressor
wheel outer circumference, for cracks.
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 accomplishing the actions specified in the service information described
previously. The AD also requires sending the inspection results 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.
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 our risk assessment indicates these parts, uninspected, pose an unacceptable level of risk to
the traveling public. 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.
2
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-2011-0273 and Directorate Identifier 2011-NE-08-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 will affect 1,402 RRC AE 3007A, AE 3007A1/1, AE 3007A1, AE
3007A1/3, AE 3007A1E, AE 3007A1P, and AE 3007A3 turbofan engines installed on 616 airplanes
of U.S. registry. We also estimate that it will take about 6 hours to perform one inspection of the
affected 6th-through-13th stage compressor wheel knife edge seals and the compressor wheel outer
circumference, for each engine. The average labor rate is $85 per work-hour. We anticipate required
parts costs to be $35,546,000. Based on these figures, we estimate the total cost of the AD to U.S.
operators to be $36,259,926.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
3
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
