Airworthiness Directives; General Electric Company CF6-45 and CF6-50 Series Turbofan Engines, 16246-16248 [E6-4702]
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16246
Proposed Rules
Federal Register
Vol. 71, No. 62
Friday, March 31, 2006
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
OFFICE OF PERSONNEL
MANAGEMENT
RIN 2120–AA64
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24145; Directorate
Identifier 2006–NE–06–AD]
5 CFR Part 724
Airworthiness Directives; General
Electric Company CF6–45 and CF6–50
Series Turbofan Engines
RIN 3206–AK55
AGENCY:
Implementation of Title II of the
Notification and Federal Employee
Antidiscrimination and Retaliation Act
of 2002—Reporting and Best Practices
Office of Personnel
Management.
AGENCY:
Proposed rule; reopening of
comment period.
ACTION:
SUMMARY: On January 25, 2006, the
Office of Personnel Management (OPM)
issued proposed rules regarding the
reporting and best practices
requirements of Title II of the No FEAR
Act (71 FR 4053). The proposed rule
contained a 60-day comment period. In
response to requests by the No Fear
Coalition and Members of Congress to
extend the comment period, OPM has
reopened the initial comment period
until May 1, 2006.
Comments must be received on
or before May 1, 2006.
DATES:
Send or deliver written
comments to Ana A. Mazzi, Deputy
Associate Director for Workforce
Relations and Accountability Policy,
Office of Personnel Management, Room
7H28, 1900 E Street, NW., Washington,
DC 20415; by FAX at (202) 606–2613; or
by e-mail at NoFEAR@opm.gov.
ADDRESSES:
Gary
D. Wahlert by telephone at (202) 606–
2930; by FAX at (202) 606–2613; or by
e-mail at NoFEAR@opm.gov.
hsrobinson on PROD1PC61 with PROPOSALS
FOR FURTHER INFORMATION CONTACT:
Office of Personnel Management.
Linda M. Springer,
Director.
[FR Doc. 06–3166 Filed 3–29–06; 1:13 pm]
BILLING CODE 6325–39–P
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14:53 Mar 30, 2006
Jkt 208001
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain General Electric Company (GE)
CF6–45 and CF6–50 series turbofan
engines. This proposed AD would
require inspecting and reworking
certain forward and aft center bodies of
the long fixed core exhaust nozzle
(LFCEN) assembly. This proposed AD
results from reports of separation of
LFCEN assembly forward and aft center
bodies, due to high imbalance engine
conditions during flight. We are
proposing this AD to prevent the
forward and aft center body of the
LFCEN assembly from separating,
leading to additional damage to the
engine and airplane, possible damage to
other airplanes, and to objects on the
ground.
We must receive any comments
on this proposed AD by May 30, 2006.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DATES:
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
You can get the service information
identified in this proposed 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.
You may examine the comments on
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT:
Karen Curtis, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7192; fax
(781) 238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2006–24145; Directorate Identifier
2006–NE–06–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the DOT
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78) or you may visit https://
dms.dot.gov.
Examining the AD Docket
You may examine the docket that
contains the proposal, any comments
received and, any final disposition in
person at the DOT Docket Office
E:\FR\FM\31MRP1.SGM
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Federal Register / Vol. 71, No. 62 / Friday, March 31, 2006 / Proposed Rules
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
Docket Management Facility receives
them.
Discussion
Since 1975, 45 events of forward and
aft center bodies separating from the
engine have been reported. GE’s
investigation of the earlier events
identified nut plate corrosion, and loose
and missing fasteners as causes for the
center body separations. In 1987, GE
issued Service Bulletin (SB) No. CF6–50
S/B 78–216 to inspect for these
conditions and add improved fasteners.
In 2001, GE issued a Fleet Highlight and
an All Operators Wire to remind
operators of the availability of SB No.
CF6–50 S/B 78–216. In 2003, GE issued
SB No. CF6–50 S/B 78–241 for
improved fastener torque.
In 2000, two separation events
occurred. Investigation by GE and the
FAA determined that bird strikes or
other similar events can result in high
engine imbalance conditions. These
conditions can result in high stress and
movement at the joint between the
forward and aft center bodies, degrading
the structural integrity of the joint, and
separating the center bodies from the
engine.
GE and the FAA determined that
additional improvements are necessary
to ensure structural integrity of the
center body joints during high
imbalance events. GE completed
certification in 2004 of improved
forward and aft center bodies. GE’s
improvement adds doublers, larger nuts
and bolts, and higher strength corrosion
resistant nut plates.
This condition, if not corrected, could
result in the forward and aft center body
of the LFCEN assembly separating,
leading to additional damage to the
engine and airplane, possible damage to
other airplanes, and to objects on the
ground.
hsrobinson on PROD1PC61 with PROPOSALS
Relevant Service Information
We have reviewed and approved the
technical contents of GE SB No. CF6–50
S/B 78–0242, dated September 26, 2005,
that identifies disassembly, inspection,
rework, and reassembly procedures for
the forward and aft center body, to add
doublers, larger nuts and bolts, and
higher strength corrosion resistant nut
plates.
VerDate Aug<31>2005
14:53 Mar 30, 2006
Jkt 208001
FAA’s Determination and Requirements
of the Proposed AD
We evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which will require reworking the
forward and aft center bodies to add
doublers, larger nuts and bolts, and
higher strength corrosion resistant nut
plates. This rework is required the next
time the forward center body and aft
center body are removed from the
engine after the effective date of this
proposed AD. The proposed AD would
require you to use the service
information described previously to
perform these actions.
Costs of Compliance
We estimate that this proposed AD
would affect 238 CF6–45 and CF6–50
series turbofan engines installed on
airplanes of U.S. registry. We also
estimate that it would take about 22
work hours per engine to perform the
proposed actions, and that the average
labor rate is $80 per work hour.
Required parts would cost about $6,000
per engine. Based on these figures, we
estimate the total cost of the proposed
AD to U.S. operators to be $1,846,880.
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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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
PO 00000
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Fmt 4702
Sfmt 4702
16247
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed 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. Would 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 regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration proposes to
amend 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:
General Electric Company: Docket No. FAA–
2006–24145; Directorate Identifier 2006–
NE–06–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by May
30, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric
Company (GE) CF6–45A, CF6–45A2, CF6–
50C, CF6–50C1, CF6–50C2, CF6–50C2B,
CF6–50C2D, CF6–50E, CF6–50E1, CF6–50E2,
and CF6–50E2B series turbofan engines with
long fixed core exhaust nozzle (LFCEN)
assembly forward center body, part number
(P/N) 1313M55G01 or G02, P/N 9076M28G09
or G10, and aft center body 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 (KC–10A,
KDC–10) airplanes.
Unsafe Condition
(d) This AD results from reports of
separation of LFCEN assembly forward and
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31MRP1
16248
Federal Register / Vol. 71, No. 62 / Friday, March 31, 2006 / Proposed Rules
aft center bodies, due to high imbalance
engine conditions during flight. We are
issuing this AD to prevent the forward and
aft center body of the LFCEN assembly from
separating, leading to additional damage to
the engine and airplane, possible damage to
other airplanes, and to objects on the ground.
AGENCY:
cooling plates installed. That AD
currently requires a onetime eddy
current inspection (ECI) of boltholes in
certain P/N stage 2 turbine aft cooling
plates. This proposed AD would expand
the population of affected CT7
turboprop engine models, but would
reduce the number of cooling plates
affected. It would also require a onetime
ECI of boltholes in certain P/N stage 2
turbine aft cooling plates. This proposed
AD results from the manufacturer
identifying the affected stage 2 turbine
aft cooling plates by serial number. We
are proposing this AD to prevent
separation of the stage 2 turbine aft
cooling plate, resulting in uncontained
engine failure and damage to the
airplane.
DATES: We must receive any comments
on this proposed AD by May 30, 2006.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact General Electric Aircraft
Engines CT7 Series Turboprop Engines,
1000 Western Ave, Lynn, MA 01910;
telephone (781) 594–3140, fax (781)
594–4805, for the service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT:
Mark Bouyer, Engine Certification
Office, FAA, Engine and Propeller
Directorate, 12 New England Executive
Park, Burlington, MA 01803; telephone
(781) 238–7755; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for General Electric
Company (GE) CT7–5A2, –5A3, –7A,
–7A1, –9B, –9B1, and –9B2 turboprop
engines, with certain part number (P/N)
and serial number stage 2 turbine aft
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20944; Directorate Identifier
2003–NE–64–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
Compliance
(e) You are responsible for having the
actions required by this AD performed the
next time the forward and aft center bodies
are removed from the engine after the
effective date of this AD, unless the actions
have already been done.
(f) Rework the forward and aft center
bodies to add doublers, larger nuts and bolts,
and higher strength corrosion resistant nut
plates. Use paragraph 3, Accomplishment
Instructions, of GE Service Bulletin No. CF6–
50 S/B 78–0242, dated September 26, 2005,
to identify the procedures required to do
these actions.
Definition
(g) For the purposes of this AD, ‘‘next time
the forward and aft center bodies are
removed from the engine’’ includes when the
center bodies are removed from the engine to
take the engine off-wing.
Alternative Methods of Compliance
(h) 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.
Issued in Burlington, Massachusetts, on
March 27, 2006.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E6–4702 Filed 3–30–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20944; Directorate
Identifier 2003–NE–64–AD]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company CT7–5, –7, and –9
Series Turboprop Engines
hsrobinson on PROD1PC61 with PROPOSALS
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
VerDate Aug<31>2005
14:53 Mar 30, 2006
Jkt 208001
PO 00000
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Fmt 4702
Sfmt 4702
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the DMS
web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78) or you may visit https://
dms.dot.gov.
Examining the AD Docket
You may examine the docket that
contains the proposal, any comments
received and any final disposition in
person at the DMS Docket Offices
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.
Discussion
On April 19, 2005, the FAA issued
AD 2005–18–01, Amendment 39–14247
(70 FR 54835, September 19, 2005). That
AD requires a onetime ECI of boltholes
in certain P/N stage 2 turbine aft cooling
plates. That AD resulted from reports of
six stage 2 turbine aft cooling plate
boltholes found cracked during
inspection. That condition, if not
corrected, could result in stage 2 turbine
aft cooling plate separation, resulting in
uncontained engine failure and damage
to the airplane.
Actions Since AD 2005–18–01 Was
Issued
Since that AD was issued, GE
determined that it is necessary to
expand the population of affected CT7
turboprop engine models to include
CT7–9C/–9C3/–9D/–9D2 turboprop
engines with stage 2 turbine aft cooling
plate P/N 6064T07P01, 6064T07P02,
6064T07P05, or 6068T36P01 installed.
GE also defined the affected population
of cooling plates by serial number. This
proposed AD includes these model
engines.
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]]>Agencies
[Federal Register Volume 71, Number 62 (Friday, March 31, 2006)]
[Proposed Rules]
[Pages 16246-16248]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-4702]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24145; Directorate Identifier 2006-NE-06-AD]
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: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain General Electric Company (GE) CF6-45 and CF6-50 series
turbofan engines. This proposed AD would require inspecting and
reworking certain forward and aft center bodies of the long fixed core
exhaust nozzle (LFCEN) assembly. This proposed AD results from reports
of separation of LFCEN assembly forward and aft center bodies, due to
high imbalance engine conditions during flight. We are proposing this
AD to prevent the forward and aft center body of the LFCEN assembly
from separating, leading to additional damage to the engine and
airplane, possible damage to other airplanes, and to objects on the
ground.
DATES: We must receive any comments on this proposed AD by May 30,
2006.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You can get the service information identified in this proposed 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.
You may examine the comments on this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7192; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2006-24145;
Directorate Identifier 2006-NE-06-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of the
DOT Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit https://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the proposal, any comments
received and, any final disposition in person at the DOT Docket Office
[[Page 16247]]
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 Docket Management Facility receives
them.
Discussion
Since 1975, 45 events of forward and aft center bodies separating
from the engine have been reported. GE's investigation of the earlier
events identified nut plate corrosion, and loose and missing fasteners
as causes for the center body separations. In 1987, GE issued Service
Bulletin (SB) No. CF6-50 S/B 78-216 to inspect for these conditions and
add improved fasteners. In 2001, GE issued a Fleet Highlight and an All
Operators Wire to remind operators of the availability of SB No. CF6-50
S/B 78-216. In 2003, GE issued SB No. CF6-50 S/B 78-241 for improved
fastener torque.
In 2000, two separation events occurred. Investigation by GE and
the FAA determined that bird strikes or other similar events can result
in high engine imbalance conditions. These conditions can result in
high stress and movement at the joint between the forward and aft
center bodies, degrading the structural integrity of the joint, and
separating the center bodies from the engine.
GE and the FAA determined that additional improvements are
necessary to ensure structural integrity of the center body joints
during high imbalance events. GE completed certification in 2004 of
improved forward and aft center bodies. GE's improvement adds doublers,
larger nuts and bolts, and higher strength corrosion resistant nut
plates.
This condition, if not corrected, could result in the forward and
aft center body of the LFCEN assembly separating, leading to additional
damage to the engine and airplane, possible damage to other airplanes,
and to objects on the ground.
Relevant Service Information
We have reviewed and approved the technical contents of GE SB No.
CF6-50 S/B 78-0242, dated September 26, 2005, that identifies
disassembly, inspection, rework, and reassembly procedures for the
forward and aft center body, to add doublers, larger nuts and bolts,
and higher strength corrosion resistant nut plates.
FAA's Determination and Requirements of the Proposed AD
We evaluated all pertinent information and identified an unsafe
condition that is likely to exist or develop on other products of this
same type design. We are proposing this AD, which will require
reworking the forward and aft center bodies to add doublers, larger
nuts and bolts, and higher strength corrosion resistant nut plates.
This rework is required the next time the forward center body and aft
center body are removed from the engine after the effective date of
this proposed AD. The proposed AD would require you to use the service
information described previously to perform these actions.
Costs of Compliance
We estimate that this proposed AD would affect 238 CF6-45 and CF6-
50 series turbofan engines installed on airplanes of U.S. registry. We
also estimate that it would take about 22 work hours per engine to
perform the proposed actions, and that the average labor rate is $80
per work hour. Required parts would cost about $6,000 per engine. Based
on these figures, we estimate the total cost of the proposed AD to U.S.
operators to be $1,846,880.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
General Electric Company: Docket No. FAA-2006-24145; Directorate
Identifier 2006-NE-06-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by May 30,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-45A,
CF6-45A2, CF6-50C, CF6-50C1, CF6-50C2, CF6-50C2B, CF6-50C2D, CF6-
50E, CF6-50E1, CF6-50E2, and CF6-50E2B series turbofan engines with
long fixed core exhaust nozzle (LFCEN) assembly forward center body,
part number (P/N) 1313M55G01 or G02, P/N 9076M28G09 or G10, and aft
center body 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 (KC-10A, KDC-
10) airplanes.
Unsafe Condition
(d) This AD results from reports of separation of LFCEN assembly
forward and
[[Page 16248]]
aft center bodies, due to high imbalance engine conditions during
flight. We are issuing this AD to prevent the forward and aft center
body of the LFCEN assembly from separating, leading to additional
damage to the engine and airplane, possible damage to other
airplanes, and to objects on the ground.
Compliance
(e) You are responsible for having the actions required by this
AD performed the next time the forward and aft center bodies are
removed from the engine after the effective date of this AD, unless
the actions have already been done.
(f) Rework the forward and aft center bodies to add doublers,
larger nuts and bolts, and higher strength corrosion resistant nut
plates. Use paragraph 3, Accomplishment Instructions, of GE Service
Bulletin No. CF6-50 S/B 78-0242, dated September 26, 2005, to
identify the procedures required to do these actions.
Definition
(g) For the purposes of this AD, ``next time the forward and aft
center bodies are removed from the engine'' includes when the center
bodies are removed from the engine to take the engine off-wing.
Alternative Methods of Compliance
(h) 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.
Issued in Burlington, Massachusetts, on March 27, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-4702 Filed 3-30-06; 8:45 am]
BILLING CODE 4910-13-P
