Airworthiness Directives; General Electric Company (GE) CF6-80 Series Turbofan Engines, 30956-30959 [E7-10588]

Download as PDF 30956 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I 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: I 2007–12–09 General Electric Company: Amendment 39–15087. Docket No. FAA–2006–26585; Directorate Identifier 2006–NE–44–AD. alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (i) Contact Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: tara.chaidez@faa.gov; telephone (781) 238–7773, fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on May 30, 2007. Robert Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–10746 Filed 6–4–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Effective Date (a) This airworthiness directive (AD) becomes effective July 10, 2007. [Docket No. FAA–2006–26488; Directorate Identifier 2006–NE–43–AD; Amendment 39– 15077; AD 2007–11–20] Affected ADs (b) None. RIN 2120–AA64 Applicability (c) This AD applies to General Electric Company (GE) CF34–10E2A1, CF34–10E5, CF34–10E5A1, CF34–10E6, CF34–10E6A1, and CF34–10E7 turbofan engines. These engines are installed on, but not limited to, Embraer ERJ–190 and –195 airplanes. cprice-sewell on PROD1PC71 with RULES Unsafe Condition (d) This AD results from GE’s evaluation of the effects to the combustor case due to installing version 5.10 software in the fullauthority digital electronic control (FADEC), and revising the combustor case published life limit. We are issuing this AD to prevent uncontained combustor case failure resulting in an in-flight engine shutdown and possible damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within 30 days after the effective date of this AD, unless the actions have already been done. (f) Revise the published life limit in the Airworthiness Limitations Section of the CF34–10E Engine Manual, for combustor cases, part number (P/N) 2070M47G02 and P/N 2070M47G03, from 39,600 cycles-sincenew (CSN) to 24,600 CSN. (g) The requirements of this AD have been met when the engine manual changes are made and operators have modified their continuous airworthiness maintenance plans to reflect the Engine Maintenance Program requirements specified in the GE CF34–10E Engine Manual. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 Airworthiness Directives; General Electric Company (GE) CF6–80 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for GE CF6–80 series turbofan engines with fuel shroud retaining rings, part number (P/N) J204P0084, installed. This AD requires replacing those retaining rings with a more robust design fuel shroud retaining snap ring. This AD results from two events of external engine fuel leakage and a subsequent under-cowl engine fire. We are issuing this AD to prevent an under-cowl engine fire and damage to the airplane during an engine high vibration event. DATES: This AD becomes effective July 10, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of July 10, 2007. ADDRESSES: You can get the service information identified 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 on the Internet at http://dms.dot.gov or in Room PL–401 on the plaza level of the SUMMARY: PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone: (781) 238–7176, fax: (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF6–80 series turbofan engines with fuel shroud retaining rings, part number (P/N) J204P0084, installed. We published the proposed AD in the Federal Register on February 15, 2007 (72 FR 7355). That action proposed to require replacing those retaining rings with a more robust design fuel shroud retaining snap ring. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Comment That Table 1 Compliance Schedule Is Somewhat Difficult To Follow One commenter, GE, states that the Table 1 compliance schedule in the proposed AD is somewhat difficult to follow. The commenter states that the table needs lines or spaces added, to separate some of the items in it, for clarity. We agree that the Table 1 compliance schedule in the proposed AD is difficult to follow. We have deleted the Table 1 compliance schedule from this AD, based on comments received on the proposed AD, and which are discussed in the paragraphs that follow. Request To Reduce the AD Applicability GE requests that we reduce the AD applicability to only engines with the drainless manifold configuration, since the drained manifold configuration is E:\FR\FM\05JNR1.SGM 05JNR1 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations not subjected to high internal pressure. If a fuel supply tube leaks internally, the shroud contains the fuel, preventing an external leak. We agree and reduced the AD applicability in the AD to only engines with the drainless manifold configuration. Request To Clarify Applicability GE requests that we clarify the applicability to state that engines built at the factory during production assembly with the drainless manifold configuration, are also subject to the requirements of the AD. We agree and made that clarification in the AD. SB Compliance Credit for CF6–80C2 Series Engines GE suggests that we add a note or statement to the compliance section verifying that CF6–80C2 series engine operators that have complied with a previous revision of SB No. CF6–80C2 S/B 73–0337, are in compliance with the AD. We agree. We added the ‘‘SB Compliance Credit for CF6–80C2 Series Engines’’ paragraph to the AD. Request To Revise the Compliance Section KLM Royal Dutch Airlines requests that we revise the section of the compliance that states ‘‘Comply with this AD as soon as one or more fuel shroud retaining rings are removed from the engine’’ to, ‘‘Comply with this AD during next engine shop visit for any reason.’’ The commenter states that the AD action should be only at enginelevel and not on-wing. We agree that the AD action should be only at engine-level and not on-wing. That part of the proposed compliance section was for engines that had not incorporated GE SB No. CF6–80C2 S/B 73–0253 (which eliminates the fuel drain system manifold and introduces a new drainless fuel manifold). The result is that this AD now applies to only the drainless manifold configuration. In addition, we deleted the Table 1 compliance schedule because it is no longer needed, clarified compliance paragraph (g), and clarified applicability paragraphs (c) and (d) in this AD. cprice-sewell on PROD1PC71 with RULES Request To Change Nomenclature All Nippon Airways requests that we change the proposed AD nomenclature for the rings being removed, from ‘‘retaining snap ring’’ to ‘‘retaining ring’’. We agree. We confirmed that GE’s SBs refer to the removed rings as ‘‘retaining rings’’ and to the rings being installed as ‘‘snap rings.’’ We changed the nomenclature in the AD to reflect that which the SBs use. VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 Reference Table of Fuel Manifold Part Numbers Added For reference, we added a Table under paragraph (f) which lists fuel manifold production part numbers. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 853 CF6–80 series turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about 12.5 work-hours per engine to perform the actions, and that the average labor rate is $80 per work-hour. Required parts will cost about $72 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $914,416. 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 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 30957 (2) Is not a ‘‘significant rule’’ under 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 at the address listed under ADDRESSES. 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 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I 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: I 2007–11–20 General Electric Company: Amendment 39–15077. Docket No. FAA–2006–26488; Directorate Identifier 2006–NE–43–AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 10, 2007. Affected ADs (b) None. Applicability (c) This AD applies to the following General Electric Company (GE) CF6–80C2 series turbofan engines that have incorporated GE Service Bulletin (SB) No. CF6–80C2 S/B 73–0253, or were built with the drainless manifold configuration at the factory during production assembly, and, have one or more fuel shroud retaining rings, part number (P/N) J204P0084, installed: CF6–80C2A1, CF6–80C2A2, CF6–80C2A3, CF6–80C2A5, CF6–80C2A8, CF6–80C2A5F, CF6–80C2B1, CF6–80C2B2, CF6–80C2B4, CF6–80C2B6, CF6–80C2B1F, CF6–80C2B2F, CF6–80C2B4F, CF6–80C2B5F, E:\FR\FM\05JNR1.SGM 05JNR1 30958 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations CF6–80C2B6F, CF6–80C2B6FA, CF6–80C2B7F, CF6–80C2B8F, CF6–80C2D1F, CF6–80C2L1F. (d) This AD also applies to GE CF6– 80E1A1, CF6–80E1A2, CF6–80E1A3, CF6– 80E1A4, and CF6–80E1A4B turbofan engines that have incorporated GE SB No. CF6–80E1 S/B 73–0026, or were built with the drainless manifold configuration at the factory during production assembly, and, have one or more fuel shroud retaining rings, P/N J204P0084, installed. (e) These engines are installed on, but not limited to, Airbus A300, A310, A330, Boeing 747, 767, and McDonnell Douglas MD11 airplanes. (f) For reference, the following Table 1 lists fuel manifold production P/Ns. TABLE 1.—REFERENCE OF FUEL MANIFOLD PRODUCTION P/NS TABLE 1.—REFERENCE OF FUEL MANIFOLD PRODUCTION P/NS—Continued CF6–80 E1 Series Engines Drained Fuel Manifold P/N (left side) Drainless Fuel Manifold P/N (left side) 1700M34G01 ............ 1303M31G12. Drained Fuel Manifold P/N (right side) Drainless Fuel Manifold P/N (right side) 1700M35G02 ............ 1303M32G12. Alternative Methods of Compliance (m) 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. Unsafe Condition (g) This AD results from two events of external engine fuel leakage and a subsequent under-cowl engine fire. We are issuing this AD to prevent an under-cowl engine fire and damage to the airplane during an engine high vibration event. Compliance CF6–80C2 Series Engines Drained Fuel Manifold P/N (left side) 1303M31G04 1303M31G06 1303M31G07 1303M31G08 1303M31G10 ............ Drained Fuel Manifold (right side) 1303M32G04 1303M32G06 1303M32G07 1303M32G08 1303M32G10 ............ (h) You are responsible for having the actions required by this AD performed at the next engine shop visit for any reason after the effective date of this AD, unless the actions have already been done. Drainless Fuel Manifold P/N (left side) Replacement of Fuel Shroud Retaining Snap Rings 1303M31G12. Drainless Fuel Manifold P/N (right side) 1303M32G12. SB Compliance Credit for CF6–80C2 Series Engines (l) This AD requires no further action if the fuel shroud retaining snap rings were installed in the CF6–80C2 series engines before the effective date of this AD using GE SB No. CF6–80C2 S/B 73–0337, Revision 2, dated January 11, 2007, Revision 1, dated April 19, 2005, or the Original, dated November 30, 2004. (i) Replace any fuel shroud retaining rings, P/N J204P0084, with a fuel shroud retaining snap ring, P/N 2186M12P01. Each engine has a total of 30 rings installed. (j) For CF6–80C2 series engines, use paragraphs 3.A. through 3.C.(1)(b)2, of GE SB No. CF6–80C2 S/B 73–0337, Revision 3, dated February 5, 2007, to do the replacements. (k) For CF6–80E1 series engines, use paragraphs 3.A. through 3.C.(1)(b)2, of GE SB No. CF6–80E1 S/B 73–0075, Revision 1, dated November 27, 2006, to do the replacements. Related Information (n) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference (o) You must use the General Electric Company service information specified in Table 2 of this AD to perform the replacements required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672–8400, fax (513) 672–8422, for a copy of this service information. You may review copies 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 Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federalregister/cfr/ibr-locations.html. TABLE 2.—INCORPORATION BY REFERENCE Page CF6–80C2 S/B 73–0337 ...................................................................................................... Total Pages: 13 CF6–80E1 S/B 73–0075 ...................................................................................................... Total Pages: 13 cprice-sewell on PROD1PC71 with RULES Service Bulletin No. All ................ 3 February 5, 2007. All ................ 1 November 27, 2006. VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\05JNR1.SGM Revision 05JNR1 Date 30959 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations Issued in Burlington, Massachusetts, on May 24, 2007. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–10588 Filed 6–4–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27713; Directorate Identifier 2006–NM–240–AD; Amendment 39–15079; AD 2007–12–01] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–100, DHC–8–200, and DHC–8–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC–8–100, DHC– 8–200, and DHC–8–300 series airplanes. This AD requires, for certain airplanes, modification of the upper bearing of the main landing gear (MLG) shock strut. This AD also requires, for certain airplanes, revising the de Havilland DHC–8 Maintenance Program Manual to include the MLG shock strut servicing task. This AD results from reports of over-extension of the MLG shock strut piston, which allows the torque links to go over-center and rest on the piston. We are issuing this AD to prevent loss in shock absorption during touchdown and failure of the shock strut housing, which could result in a subsequent loss of directional control. SUMMARY: This AD becomes effective July 10, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 10, 2007. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Mazdak Hobbi, Aerospace Engineer, Airframe and Propulsion Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7330; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: March 29, 2007 (72 FR 14721). That NPRM proposed to require, for certain airplanes, modification of the upper bearing of the main landing gear (MLG) shock strut. That NPRM proposed to also require, for certain airplanes, revising the de Havilland DHC–8 Maintenance Program Manual to include the MLG shock strut servicing task. Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. DATES: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Bombardier Model DHC–8–100, DHC–8–200, and DHC–8– 300 series airplanes. That NPRM was published in the Federal Register on Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM or on the determination of the cost to the public. Clarification of Part Number We have revised paragraph (i)(2) of this final rule to correct a typographical error, which resulted in an incorrect part number. Paragraph (i)(2) should have read ‘‘* * * 10129–5 or 10129– 553.’’ Clarification of Alternative Method of Compliance (AMOC) Paragraph Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Work hours cprice-sewell on PROD1PC71 with RULES Modification ........................................................ Manual Revision ................................................ 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. VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 Average labor rate per hour 4 1 $80 80 Parts $274 0 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Number of U.S.registered airplanes Cost per airplane $594 80 Up to 135 ......... 135 ................... Fleet cost Up to $80,190. $10,800. 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. E:\FR\FM\05JNR1.SGM 05JNR1

Agencies

[Federal Register Volume 72, Number 107 (Tuesday, June 5, 2007)]
[Rules and Regulations]
[Pages 30956-30959]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26488; Directorate Identifier 2006-NE-43-AD; 
Amendment 39-15077; AD 2007-11-20]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-80 
Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE 
CF6-80 series turbofan engines with fuel shroud retaining rings, part 
number (P/N) J204P0084, installed. This AD requires replacing those 
retaining rings with a more robust design fuel shroud retaining snap 
ring. This AD results from two events of external engine fuel leakage 
and a subsequent under-cowl engine fire. We are issuing this AD to 
prevent an under-cowl engine fire and damage to the airplane during an 
engine high vibration event.

DATES: This AD becomes effective July 10, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of July 10, 2007.

ADDRESSES: You can get the service information identified 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 on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone: (781) 238-7176, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE CF6-80 series 
turbofan engines with fuel shroud retaining rings, part number (P/N) 
J204P0084, installed. We published the proposed AD in the Federal 
Register on February 15, 2007 (72 FR 7355). That action proposed to 
require replacing those retaining rings with a more robust design fuel 
shroud retaining snap ring.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The Docket Office (telephone (800) 647-5227) is 
located on the plaza level of the Department of Transportation Nassif 
Building at the street address stated in ADDRESSES. Comments will be 
available in the AD docket shortly after the DMS receives them.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Comment That Table 1 Compliance Schedule Is Somewhat Difficult To 
Follow

    One commenter, GE, states that the Table 1 compliance schedule in 
the proposed AD is somewhat difficult to follow. The commenter states 
that the table needs lines or spaces added, to separate some of the 
items in it, for clarity.
    We agree that the Table 1 compliance schedule in the proposed AD is 
difficult to follow. We have deleted the Table 1 compliance schedule 
from this AD, based on comments received on the proposed AD, and which 
are discussed in the paragraphs that follow.

Request To Reduce the AD Applicability

    GE requests that we reduce the AD applicability to only engines 
with the drainless manifold configuration, since the drained manifold 
configuration is

[[Page 30957]]

not subjected to high internal pressure. If a fuel supply tube leaks 
internally, the shroud contains the fuel, preventing an external leak. 
We agree and reduced the AD applicability in the AD to only engines 
with the drainless manifold configuration.

Request To Clarify Applicability

    GE requests that we clarify the applicability to state that engines 
built at the factory during production assembly with the drainless 
manifold configuration, are also subject to the requirements of the AD. 
We agree and made that clarification in the AD.

SB Compliance Credit for CF6-80C2 Series Engines

    GE suggests that we add a note or statement to the compliance 
section verifying that CF6-80C2 series engine operators that have 
complied with a previous revision of SB No. CF6-80C2 S/B 73-0337, are 
in compliance with the AD. We agree. We added the ``SB Compliance 
Credit for CF6-80C2 Series Engines'' paragraph to the AD.

Request To Revise the Compliance Section

    KLM Royal Dutch Airlines requests that we revise the section of the 
compliance that states ``Comply with this AD as soon as one or more 
fuel shroud retaining rings are removed from the engine'' to, ``Comply 
with this AD during next engine shop visit for any reason.'' The 
commenter states that the AD action should be only at engine-level and 
not on-wing.
    We agree that the AD action should be only at engine-level and not 
on-wing. That part of the proposed compliance section was for engines 
that had not incorporated GE SB No. CF6-80C2 S/B 73-0253 (which 
eliminates the fuel drain system manifold and introduces a new 
drainless fuel manifold). The result is that this AD now applies to 
only the drainless manifold configuration. In addition, we deleted the 
Table 1 compliance schedule because it is no longer needed, clarified 
compliance paragraph (g), and clarified applicability paragraphs (c) 
and (d) in this AD.

Request To Change Nomenclature

    All Nippon Airways requests that we change the proposed AD 
nomenclature for the rings being removed, from ``retaining snap ring'' 
to ``retaining ring''. We agree. We confirmed that GE's SBs refer to 
the removed rings as ``retaining rings'' and to the rings being 
installed as ``snap rings.'' We changed the nomenclature in the AD to 
reflect that which the SBs use.

Reference Table of Fuel Manifold Part Numbers Added

    For reference, we added a Table under paragraph (f) which lists 
fuel manifold production part numbers.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 853 CF6-80 series turbofan 
engines installed on airplanes of U.S. registry. We also estimate that 
it will take about 12.5 work-hours per engine to perform the actions, 
and that the average labor rate is $80 per work-hour. Required parts 
will cost about $72 per engine. Based on these figures, we estimate the 
total cost of the AD to U.S. operators to be $914,416.

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

    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 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); 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 at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2007-11-20 General Electric Company: Amendment 39-15077. Docket No. 
FAA-2006-26488; Directorate Identifier 2006-NE-43-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 10, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following General Electric Company 
(GE) CF6-80C2 series turbofan engines that have incorporated GE 
Service Bulletin (SB) No. CF6-80C2 S/B 73-0253, or were built with 
the drainless manifold configuration at the factory during 
production assembly, and, have one or more fuel shroud retaining 
rings, part number (P/N) J204P0084, installed:

CF6-80C2A1,
CF6-80C2A2,
CF6-80C2A3,
CF6-80C2A5,
CF6-80C2A8,
CF6-80C2A5F,
CF6-80C2B1,
CF6-80C2B2,
CF6-80C2B4,
CF6-80C2B6,
CF6-80C2B1F,
CF6-80C2B2F,
CF6-80C2B4F,
CF6-80C2B5F,

[[Page 30958]]

CF6-80C2B6F,
CF6-80C2B6FA,
CF6-80C2B7F,
CF6-80C2B8F,
CF6-80C2D1F,
CF6-80C2L1F.

    (d) This AD also applies to GE CF6-80E1A1, CF6-80E1A2, CF6-
80E1A3, CF6-80E1A4, and CF6-80E1A4B turbofan engines that have 
incorporated GE SB No. CF6-80E1 S/B 73-0026, or were built with the 
drainless manifold configuration at the factory during production 
assembly, and, have one or more fuel shroud retaining rings, P/N 
J204P0084, installed.
    (e) These engines are installed on, but not limited to, Airbus 
A300, A310, A330, Boeing 747, 767, and McDonnell Douglas MD11 
airplanes.
    (f) For reference, the following Table 1 lists fuel manifold 
production P/Ns.

          Table 1.--Reference of Fuel Manifold Production P/Ns
------------------------------------------------------------------------
 
------------------------------------------------------------------------
                         CF6-80C2 Series Engines
------------------------------------------------------------------------
   Drained Fuel Manifold P/N (left      Drainless Fuel Manifold P/N
                side)                 (left side)
------------------------------------------------------------------------
1303M31G04
1303M31G06
1303M31G07
1303M31G08
1303M31G10..........................  1303M31G12.
------------------------------------------------------------------------
 Drained Fuel Manifold (right side)     Drainless Fuel Manifold P/N
                                      (right side)
------------------------------------------------------------------------
1303M32G04
1303M32G06
1303M32G07
1303M32G08
1303M32G10..........................  1303M32G12.
------------------------------------------------------------------------
                        CF6-80 E1 Series Engines
------------------------------------------------------------------------
   Drained Fuel Manifold P/N (left      Drainless Fuel Manifold P/N
                side)                 (left side)
------------------------------------------------------------------------
1700M34G01..........................  1303M31G12.
------------------------------------------------------------------------
  Drained Fuel Manifold P/N (right      Drainless Fuel Manifold P/N
                side)                 (right side)
------------------------------------------------------------------------
1700M35G02..........................  1303M32G12.
------------------------------------------------------------------------

Unsafe Condition

    (g) This AD results from two events of external engine fuel 
leakage and a subsequent under-cowl engine fire. We are issuing this 
AD to prevent an under-cowl engine fire and damage to the airplane 
during an engine high vibration event.

Compliance

    (h) You are responsible for having the actions required by this 
AD performed at the next engine shop visit for any reason after the 
effective date of this AD, unless the actions have already been 
done.

Replacement of Fuel Shroud Retaining Snap Rings

    (i) Replace any fuel shroud retaining rings, P/N J204P0084, with 
a fuel shroud retaining snap ring, P/N 2186M12P01. Each engine has a 
total of 30 rings installed.
    (j) For CF6-80C2 series engines, use paragraphs 3.A. through 
3.C.(1)(b)2, of GE SB No. CF6-80C2 S/B 73-0337, Revision 3, dated 
February 5, 2007, to do the replacements.
    (k) For CF6-80E1 series engines, use paragraphs 3.A. through 
3.C.(1)(b)2, of GE SB No. CF6-80E1 S/B 73-0075, Revision 1, dated 
November 27, 2006, to do the replacements.

SB Compliance Credit for CF6-80C2 Series Engines

    (l) This AD requires no further action if the fuel shroud 
retaining snap rings were installed in the CF6-80C2 series engines 
before the effective date of this AD using GE SB No. CF6-80C2 S/B 
73-0337, Revision 2, dated January 11, 2007, Revision 1, dated April 
19, 2005, or the Original, dated November 30, 2004.

Alternative Methods of Compliance

    (m) 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.

Related Information

    (n) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (o) You must use the General Electric Company service 
information specified in Table 2 of this AD to perform the 
replacements required by this AD. The Director of the Federal 
Register approved the incorporation by reference of the documents 
listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. Contact General Electric Company via Lockheed Martin 
Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 
45215, telephone (513) 672-8400, fax (513) 672-8422, for a copy of 
this service information. You may review copies 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 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.

                                      Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
        Service Bulletin No.                    Page              Revision                   Date
----------------------------------------------------------------------------------------------------------------
CF6-80C2 S/B 73-0337................  All.....................            3  February 5, 2007.
    Total Pages: 13
CF6-80E1 S/B 73-0075................  All.....................            1  November 27, 2006.
    Total Pages: 13
----------------------------------------------------------------------------------------------------------------



[[Page 30959]]

    Issued in Burlington, Massachusetts, on May 24, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-10588 Filed 6-4-07; 8:45 am]
BILLING CODE 4910-13-P