[Federal Register: June 5, 2007 (Volume 72, Number 107)]
[Rules and Regulations]
[Page 30956-30959]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05jn07-2]
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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.
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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
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Service Bulletin No. Page Revision Date
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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
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[[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]
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