[Federal Register: February 26, 2009 (Volume 74, Number 37)]
[Rules and Regulations]
[Page 8735-8737]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26fe09-13]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24145; Directorate Identifier 2006-NE-06-AD;
Amendment 39-15823; AD 2009-04-17]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-45 and
CF6-50 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
General Electric Company (GE) CF6-45 and CF6-50 series turbofan
engines. This AD requires replacing certain forward and aft
centerbodies of the long fixed core exhaust nozzle (LFCEN) assembly.
This AD results from the engine manufacturer issuing new service
information. We are issuing this AD to prevent the forward and aft
centerbody of the LFCEN assembly from separating due to high imbalance
engine conditions, leading to damage to the airplane.
DATES: This AD becomes effective April 2, 2009. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of April 2, 2009.
ADDRESSES: You can get the service information identified in this AD
from General Electric Company via GE-Aviation, Attn: Distributions, 111
Merchant St., Room 230, Cincinnati, Ohio 45246, telephone (513) 552-
3272; fax (513) 552-3329.
The Docket Operations office is located at the Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
robert.green@faa.gov; telephone (781) 238-7754; 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) CF6-45 and CF6-50
series turbofan engines. We published the proposed AD in the Federal
Register on January 2, 2008, (73 FR 77). That action proposed to
require replacing the centerbodies with centerbodies that were modified
using the Accomplishment Instructions, Section 3, of GE SB No. CF6-50
S/B 78-0244, dated July 30, 2007, within 42 months of the effective
date of the proposed AD.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
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 Operations office (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
[[Page 8736]]
development of this AD. We have considered the comments received.
Requests To Allow Credit for Rework Performed Using GE Service Bulletin
CF6-50 S/B 78-0242
Two commenters, Atlas Air and Evergreen International Airlines,
asked us to allow credit for rework performed using GE Service Bulletin
(SB) CF6-50 S/B 78-0242, dated September 26, 2005. The commenters state
the original issue and later revision of GE SB CF6-50 S/B 78-0244 state
in Section 1, Planning Information, that forward and aft centerbody
assemblies reworked in accordance with GE SB CF6-50 S/B 78-0242, meet
the requirement of the GE SB.
We agree. The rework defined by GE SB CF6-50 S/B 78-0242 meets the
requirements of GE SB CF6-50 S/B 78-0244, Revision 1. Also, there might
be forward and aft centerbody assemblies that have been reworked using
the original issue of GE SB CF6-50 S/B 78-0244, which is acceptable. We
have added references to GE SB CF6-50 S/B 78-0244, dated July 30, 2007,
and GE SB CF6-50 S/B 78-0242, dated September 26, 2005, to paragraph
(f) of this AD.
Request To Add GE SB CF6-50 S/B 78-0244, Revision 1, Dated March 13,
2008 to the AD Compliance Section
Two commenters, GE Aviation and Boeing Commercial Airplane
Services, ask us to reference SB CF6-50 S/B 78-0244, Revision 1, dated
March 13, 2008, in the compliance section of the proposed AD. The
commenters state that operators cannot get the rivets identified in
Section 2. Material Information, paragraph A. (1) of the original issue
of GE SB CF6-50 S/B 78-0244. Those rivets are part numbers (P/Ns)
NAS1398M3-2 and NAS 1398M3-3. GE identified alternative rivets P/Ns
NAS13984-2 and NAS13984-3 in SB CF6-50 S/B 78-0244, Revision 1, dated
March 13, 2008.
We agree. We have changed GE SB CF6-50 S/B 78-0244, dated July 30,
2007, to GE SB CF6-50 S/B 78-0244, Revision 1, dated March 13, 2008, in
the regulatory text.
Recommendation To Use Rivet P/N NAS9307 as an Alternative to P/Ns
NAS13984-2 and NAS13984-3
One commenter, Nordam Prism, recommends we allow using alternative
rivets, P/N NAS9307, for installing the forward centerbody forward
doubler. The commenter suggests the P/N NAS9307 rivet is more reliable
than the specified P/N NAS1398 rivet. The commenter states the P/N
NAS9307 rivet locking collar is designed as a positive security device
that forms the rivet sleeve into the locking stem, thereby promoting
joint integrity while in service. The commenter states the P/N NAS1398
rivet doesn't offer this feature, and the lock has a tendency to
release in service. The commenter further notes the P/N NAS9307 rivet
design provides a more consistent installation with visual confirmation
of an acceptable mechanical fit. Previous experience with P/N NAS1398
rivets would often result in inspectors not accepting rivet
installation due to misplaced locking collars. The resulting removal
increased the tendency for an oversized rivet hole. In this particular
GE SB CF6-50 S/B 78-0244 application, there exists no tolerance for
oversizing the hole and installing a larger rivet. The first article
assembly effectively used the P/N NAS9307 rivet in this application.
We don't agree. GE states the P/N NAS9307 rivet doesn't offer a
0.094-inch diameter option that is consistent with the existing repair.
The proposed P/N NAS9307M-4-0X rivet size (0.125-inch diameter) would
work in this configuration, but the repair area might not accommodate
the next higher, P/N NAS9307M-5-0X rivet size (0.165-inch diameter),
precluding oversized rivet holes or future repairs. GE further notes
the spindle material of the P/N NAS9307 rivet might be made of PH15-7
corrosion resistant steel. The P/N PH15-7 material doesn't offer the
same corrosion resistance in an exhaust environment as the A386 spindle
material used in the P/N NAS1398 rivets. We didn't change the
Regulatory text.
Request To Remove the KC-10A Airplane From the ``Used on'' Section of
Paragraph (c) of the Proposed AD
One commenter, Boeing Commercial Airplane Services, asks us to
remove the reference to the KC-10A airplane from the ``used on but not
limited to'' sentence in paragraph (c) of the proposed AD. Boeing
states the KC-10A doesn't use the LFCEN configuration.
We agree. We supply the ``used on, but not limited to'' list of
airplanes in paragraph (c) of the proposed AD to aid operators and
users in identifying if their airplane might use the affected engines.
Since the list is for information only, we are not expanding the scope
of the proposed AD by adding or removing any airframe. We removed the
KC-10A from the ``installed on but not limited to'' sentence in
paragraph (c) of this AD.
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 379 GE CF6-45 and CF6-50
series turbofan engines installed on airplanes of U.S. registry. We
also estimate that it will take about 44 work hours per engine to
perform the actions, and that the average labor rate is $80 per work
hour. Required parts would cost about $11,000 per engine. Based on
these figures, we estimate the total cost of this AD to U.S. operators
to be $2,802,360.
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
[[Page 8737]]
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, 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:
2009-04-17 General Electric Company: Amendment 39-15823. Docket No.
FAA-2006-24145; Directorate Identifier 2006-NE-06-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April 2,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-45A,
CF6-45A2, CF6-50A, CF6-50C, CF6-50CA, CF6-50C1, CF6-50C2, CF6-50C2B,
CF6-50C2D, CF6-50E, CF6-50E1, CF6-50E2, and CF6-50E2B series
turbofan engines with a long fixed core exhaust nozzle (LFCEN)
assembly forward centerbody, part number (P/N) 1313M55G01 or G02, P/
N 9076M28G09 or G10, and aft centerbody P/N 1313M56G01 or
9076M46G05, installed. These engines are installed on, but not
limited to, Airbus A300 series, Boeing 747 series, McDonnell Douglas
DC-10 series, and DC-10-30F (KDC-10) airplanes.
Unsafe Condition
(d) This AD results from reports of separation of LFCEN assembly
forward and aft centerbodies due to high imbalance engine
conditions. This AD results from the GE issuing new service
information. We are issuing this AD to prevent the forward and aft
centerbody of the LFCEN assembly from separating due to high
imbalance engine conditions, leading to damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within 42 months after the effective date of this AD,
unless the actions have already been done.
(f) Replace the forward centerbody, P/N 1313M55G01 or G02, P/N
9076M28G09 or G10, and aft centerbody, P/N 1313M56G01 or 9076M46G05
with a forward and aft centerbody that have been modified using with
the Accomplishment Instructions, Section 3, of GE Service Bulletin
No. CF6-50 S/B 78-0244, Revision 1, dated March 13, 2008, CF6-50 S/B
78-0244, dated July 30, 2007, or CF6-50 S/B 78-0242, dated September
26, 2005.
Alternative Methods of Compliance
(g) 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
(h) Contact Robert Green, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199,
for more information about this AD.
Material Incorporated by Reference
(i) None.
Issued in Burlington, Massachusetts, on February 12, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E9-3615 Filed 2-25-09; 8:45 am]
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