Nachrichten für Luftfahrer 2004 Teil II (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2002-070R1
ersetzt: D-2002-070
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 10.06.2004
Muster: General Electric AD der ausländischen Behörde:
CF6-80E1 FAA AD 2004-09-34 Amdt. 39-13625
Geräte-Nr.: Technische Mitteilungen des Herstellers:
6319 General Electric Service Bulletin CF6-80E1 S/B 72-0164 vom
16.03.1999
General Electric Service Bulletin CF6-80E1 S/B 72-0217 Revision
2 vom 05.01.2004
Betroffenes Luftfahrtgerät:
General Electric
CF6-80E1
- Baureihen: Alle
- Werk-Nrn.: Alle Triebwerke dieses Musters, in denen Leitschaufelkränze mit den Hersteller-Teile-
nummern (P/N's) 1647M84G09 oder 1647M84G10 eingebaut sind.
Betrifft:
Hochdruckturbine, Leitschaufelkranz Stufe 2 (high pressure turbine, stage 2 nozzle guide vane, ATA-Code
72-50-00) - Rißbildung und Oberflächenschäden an den Turbinenschaufeln der Hochdruckturbine durch
Schäden am Leitschaufelkranz der 2. Stufe der Hochdruckturbine - ggf. kann dieser Fehler zum Bruch von
Turbinenschaufeln führen. Bruchstücke von hochdrehenden Motorbauteilen können das Triebwerksge-
häuse durchschlagen und schwere Schäden am Luftfahrzeug verursachen.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten AD der
ausländischen Behörde und der oben genannten Technischen Mitteilung des Herstellers zu entnehmen.
Fristen:
Alle anzuwendenden Fristen sind der o.g. AD der ausländischen Behörde zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. AD der
ausländischen Behörde.
Hinweis:
Seit dem 28.09.2003 ist die Verordnung (EG) Nr. 1702/2003 der Europäischen Union in Kraft.
Demnach sind gemäß Artikel 2 dieser Verordnung Lufttüchtigkeitsanweisungen des Entwicklungsstaates
für ausländische Lfz-Muster unmittelbar gültig. Solange die Europäische Agentur für Flugsicherheit (EASA)
noch kein eigenes Veröffentlichungsverfahren für Luttüchtigkeitsanweisungen bekanntgegeben hat,
werden solche ausländischen Lufttüchtigkeitsanweisungen ohne inhaltliche Änderungen per "Deckblatt-
LTA" durch das Luftfahrt-Bundesamt angeordnet.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2004-09-34 Amdt. 39-13625
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
nur in Betrieb genommen 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 LTA 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.
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
(LTA-Nr.: D-2002-070 vom 21.03.2002) Aktenzeichen: (10)M121-502.1/D-2002-070R1 Seite 1 von 1
[Federal Register: May 11, 2004 (Volume 69, Number 91)]
[Rules and Regulations]
[Page 26027-26029]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11my04-19]
–––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE-45-AD; Amendment 39-13625; AD 2004-09-34]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-80E1 Model Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
–––––––––––––––––––––––––––––––––––
SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for General Electric
Company (GE) CF6-80E1 model turbofan engines with high pressure turbine (HPT) stage 2 (S2)
nozzle guide vanes (NGVs) part number (P/N) 1647M84G09 or 1647M84G10, installed. That AD
currently requires flex borescope inspections of HPT S2 NGVs installed in CF6-80E1 model turbofan
engines. This AD requires the same actions but at reduced compliance intervals. This AD results
from inspection findings of HPT S2 NGVs that show cracks from distress could occur sooner and
grow faster than originally predicted. We are issuing this AD to prevent failure of HPT rotor blades
from HPT S2 NGV distress, which could result in an uncontained engine failure.
DATES: Effective May 26, 2004. The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the regulations as of May 26, 2004.
We must receive any comments on this AD by July 12, 2004.
ADDRESSES: Use one of the following addresses to submit comments on this AD:
• By mail: The Federal Aviation Administration (FAA), New England Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2001-NE-45-AD, 12 New England Executive Park,
Burlington, MA 01803-5299.
• By fax: (781) 238-7055.
• By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information referenced in this AD from General Electric Company via
Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215,
telephone (513) 672-8400, fax (513) 672-8422.
You may examine the AD docket, at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service
information, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12
New England Executive Park, Burlington, MA; or at the National Archives and Records
1
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/code_of_federal_regulations/ibr_locations.html.
FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park,
Burlington, MA 01803-5299; telephone: (781) 238-7192; fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: On January 15, 2002, the FAA issued AD 2002-01-04,
Amendment 39-12595 (67 FR 4326, January 30, 2002). That AD requires flex borescope inspections
of HPT S2 NGVs installed in CF6-80E1 model turbofan engines. That AD was the result of an
uncontained engine failure attributed to HPT S2 NGV distress. That condition, if not corrected, could
result in failure of HPT rotor blades from HPT S2 NGV distress, which could result in an
uncontained engine failure.
Actions After AD 2002-01-04 Was Issued
After AD 2002-01-04 was issued, GE received inspection findings of HPT S2 NGVs that show
cracks from distress. GE and the FAA have determined that cracks from this distress could occur
sooner and propagate faster than originally predicted, and have also determined that the inspection
compliance intervals of AD 2002-01-04 are too long.
Relevant Service Information
We have reviewed and approved the technical contents of GE Service Bulletin (SB) No. CF6-
80E1 S/B 72-0217, Revision 2, dated January 5, 2004, that describes procedures for initial and
repetitive flex borescope inspection of HPT S2 NGV P/Ns 1647M84G09 and 1647M84G10.
FAA's Determination and Requirements of This AD
Although no airplanes that are registered in the United States use these GE CF6-80E1 model
turbofan engines, the possibility exists that the engine model could be used on airplanes that are
registered in the United States in the future. The unsafe condition described previously is likely to
exist or develop on other GE CF6-80E1 model turbofan engines of the same type design. We are
issuing this AD to prevent blade failure from HPT S2 NGV distress, which could result in an
uncontained engine failure. This AD requires flex borescope inspections of HPT S2 NGVs installed
in GE CF6-80E1 model turbofan engines. These actions are required at initial and repetitive
compliance intervals that are reduced from the intervals in AD 2002-01-04. You must use the service
information described previously to perform the actions required by this AD.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this engine model, notice and opportunity for
public comment before issuing this AD are unnecessary. Therefore, a situation exists that allows the
immediate adoption of this regulation.
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 submit any written relevant
data, views, or arguments regarding this AD. Send your comments to an address listed under
2
ADDRESSES. Include ''AD Docket No. 2001-NE-45-AD'' in the subject line of your comments. If
you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped
postcard with the docket number written on it; we will date-stamp your postcard and mail it back to
you. We specifically invite comments on the overall regulatory, economic, environmental, and
energy aspects of the rule that might suggest a need to modify it. If a person contacts us verbally, and
that contact relates to a substantive part of this AD, we will summarize the contact and place the
summary in the docket. We will consider all comments received by the closing date and may amend
the AD in light of those comments.
We are reviewing the writing style we currently use in regulatory documents. We are interested
in your comments on whether the style of this document is clear, and your suggestions to improve the
clarity of our communications with you. You may get more information about plain language at
http://www.faa.gov/language and http://www/plainlanguage.gov.
Examining the AD Docket
You may examine the AD Docket (including any comments and service information), by
appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See
ADDRESSES for the location.
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.
For the reasons discussed above, I certify that the regulation:
1. Is not a ''significant regulatory action'' under Executive Order 12866;
2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979); and
3. 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.
We prepared a summary of the costs to comply with this AD and placed it in the AD Docket.
You may get a copy of this summary by sending a request to us at the address listed under
ADDRESSES. Include ''AD Docket No. 2001-NE-45-AD'' in your request.
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 Federal Aviation
Administration amends part 39 of the Federal Aviation Regulations (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.
3
§ 39.13 [Amended]
2. The FAA amends § 39.13 by removing Amendment 39-12595 (67 FR 4326, January 30, 2002) and
by adding a new airworthiness directive, Amendment 39-13625, to read as follows:
4
AIRWORTHINESS DIRECTIVE
Aircraft Certification Service U.S. Department
Washington, DC of Transportation
Federal Aviation
Administration
We post ADs on the internet at "www.faa.gov"
The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39,
applies to an aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect aviation safety and are regulations which require immediate
attention. You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of the Airworthiness
Directive (reference 14 CFR part 39, subpart 39.3).
2004-09-34 General Electric Company: Amendment 39-13625. Docket No. 2001-NE-45-AD.
Supersedes AD 2002-01-04, Amendment 39-12595.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 26, 2004.
Affected ADs
(b) This AD supersedes AD 2002-01-04.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-80E1 engine models with high
pressure turbine (HPT) stage 2 (S2) nozzle guide vanes (NGVs), part number (P/N) 1647M84G09 or
1647M84G10, installed. These engines are installed on, but not limited to, Airbus A330 airplanes.
Unsafe Condition
(d) This AD results from inspection findings of HPT S2 NGVs that show cracks from distress
could occur sooner and propagate faster than originally predicted. We are issuing this AD to prevent
failure of HPT rotor blades from HPT S2 NGV distress, which could result in an uncontained engine
failure.
Compliance
(e) You are responsible for having the actions required by this AD performed within the
compliance times specified unless the actions have already been done.
NGVs Previously Inspected by Flex Borescope
(f) For NGVs inspected by flex borescope before the effective date of this AD, reinspect or
remove from service the NGVs using the Conditions and Reinspection intervals listed in the
''Inspection Table for Cracking in the Airfoil Outer Fillet,'' Figure 5, of GE Service Bulletin (SB) No.
CF6-80E1 S/B 72-0217, Revision 2, dated January 5, 2004, or within 200 cycles-in-service-since-last
inspection (CSLI), whichever is earlier.
5
NGVs Not Previously Inspected by Flex Borescope
(g) For NGVs not previously inspected by flex borescope, remove from service, or inspect using
the Accomplishment Instructions of GE SB No. CF6-80E1 S/B 72-0217, Revision 2, dated January 5,
2004, at the following:
(1) For NGVs with more than 800 cycles-since-overhaul (CSO) on the effective date of this AD,
within 50 cycles-in-service (CIS) after the effective date of this AD.
(2) For NGVs with 800 or fewer CSO on the effective date of this AD, at the first regular HPT
blade inspection after 800 CSO, but before reaching 900 CSO.
(3) Reinspect or remove from service NGVs using the Conditions and Reinspection intervals
listed in the ''Inspection Table for Cracking in the Airfoil Outer Fillet,'' Figure 5, of GE SB No. CF6-
80E1 S/B 72-0217, Revision 2, dated January 5, 2004.
Cycles-Since-Overhaul Defined
(h) For the purposes of this AD, cycles-since-overhaul (CSO) is defined as cycles since repair as
described in GE SB No. CF6-80E1 S/B 72-0164, dated March 16, 1999.
Engines Not Affected by this AD
(i) Engines configured with HPT S2 NGV P/Ns 1647M84G05, 1647M84G06, 2080M47G01,
2080M47G02, 2086M62G03, or 2086M62G04 are not affected by this AD.
Alternative Methods of Compliance
(j) The Manager, Engine Certification Office, has the authority to approve alternative methods of
compliance for this AD if requested using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(k) You must use General Electric Company Service Bulletin No. CF6-80E1 S/B 72-0217,
Revision 2, dated January 5, 2004, to perform the inspections required by this AD. The Director of
the Federal Register approved the incorporation by reference of this service bulletin in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from General Electric Company via
Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215,
telephone (513) 672-8400, fax (513) 672-8422. You may review copies at the Federal Aviation
Administration (FAA), New England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA 01803-5299; or 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/code_of_federal_regulations/ibr_locations.html.
Related Information
(l) None.
Issued in Burlington, Massachusetts, on April 29, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 04-10371 Filed 5-10-04; 8:45 am]
BILLING CODE 4910-13-P
6
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2003-100R1
ersetzt: D-2003-100
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 10.06.2004
Muster: Eurocopter AD der ausländischen Behörde:
AS 350 DGAC AD F-2003-002 R1 vom 18.02.2004
Geräte-Nr.: Technische Mitteilungen des Herstellers:
3048 Eurocopter AS 350 Alert Service Bulletin No. 67.00.24
Betroffenes Luftfahrtgerät:
Eurocopter
AS 350
- Baureihen: AS 350 B, BA, B1, B2, B3, BB und D mit durchgeführter MOD 070682 (Bestandteil des AS
350 Service Bulletin No. 67.09) und vor der Durchführung der MOD 073179
- Werk-Nrn.: alle, ausgestattet mit Steuerknüppel-Abdeckkappen P/N 350A27-1612-20
Betrifft:
Flugsteuerung, Steuerknüppel (''rotor flight controls - cyclic stick'')
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten AD der
ausländischen Behörde und der oben genannten Technischen Mitteilung des Herstellers zu entnehmen.
Fristen:
Alle anzuwendenden Fristen sind der o.g. AD der ausländischen Behörde zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. AD der
ausländischen Behörde.
Hinweis:
Seit dem 28.09.2003 ist die Verordnung (EG) Nr. 1702/2003 der Europäischen Union in Kraft.
Demnach sind gemäß Artikel 2 dieser Verordnung Lufttüchtigkeitsanweisungen des Entwicklungsstaates für
ausländische Lfz-Muster unmittelbar gültig. Solange die Europäische Agentur für Flugsicherheit (EASA) noch
kein eigenes Veröffentlichungsverfahren für Luttüchtigkeitsanweisungen bekanntgegeben hat, werden solche
ausländischen Lufttüchtigkeitsanweisungen ohne inhaltliche Änderungen per "Deckblatt-LTA" durch das
Luftfahrt-Bundesamt angeordnet.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
DGAC AD F-2003-002 R1 vom 18.02.2004
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
nur in Betrieb genommen 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 LTA 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.
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
(LTA-Nr.: D-2003-100 vom 03.04.2003) Aktenzeichen: (02)M123-502.1/D-2003-100R1 Seite 1 von 1
