Airworthiness Directives; General Electric Company CF6-45 and CF6-50 Series Turbofan Engines, 16246-16248 [E6-4702]

Download as PDF 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 VerDate Aug<31>2005 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 http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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 http://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 http:// 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 http:// 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 31MRP1 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 Frm 00002 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 E:\FR\FM\31MRP1.SGM 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 http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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 Frm 00003 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 http:// 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 http:// 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. E:\FR\FM\31MRP1.SGM 31MRP1

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 http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
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 http://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 http://
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 http://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