Airworthiness Directives; General Electric Company CF6-45 and CF6-50 Series Turbofan Engines, 292-294 [2010-33167]

Download as PDF wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 292 Federal Register / Vol. 76, No. 2 / Tuesday, January 4, 2011 / Proposed Rules Although § 25.562 was written with forward- and aft-facing seats in mind, the orientation of the seat does not change the relevant test conditions, and the rule applies to all seats regardless of orientation. The dynamic test conditions included in § 25.562 are directly applicable to side-facing seats. However, for injury pass/fail criteria, the orientation of the seat may be significant. For forward-, aft-, and side-facing seats the injury criteria are currently limited to head, spine, and femur loads. The head and lumbar loads are critical but the femur load is not critical. For a side-facing seat, additional injury parameters may be identified and evaluation of those parameters would be necessary to provide an acceptable level of safety. When evaluating side-facing seats the following should be taken into consideration: 1. The isolation of one occupant from another. Occupants should not rely on impact with other occupants to provide energy absorption; body-to-body impacts are unacceptable. 2. The restraint system and the retention of occupants in the seat. Addressing this concern may necessitate providing a means of restraint for the lower limbs as well as the torso. Failure to limit the forward (in the airplane’s coordinate system) travel of the lower limbs may cause the occupant to come out of the restraint system or produce severe injuries due to the resulting position of the restraint system and/or twisting (torsional load) of the lower lumbar spinal column. 3. The load limit in the torso in the lateral direction. Human tolerance for side-facing seats differs from that for forward- or aft-facing seats. The automotive industry has developed test procedures and occupant injury criteria appropriate for side impact conditions. The criteria include limiting lateral pelvic accelerations and using the ‘‘Thoracic Trauma Index,’’ which is defined in 49 CFR 571.214. Use of the side impact dummy (SID) identified in 49 CFR part 572, subpart F, rather than the Hybrid II dummy identified in 49 CFR part 572, subpart B, is required to evaluate these parameters. The Hybrid II dummy is used in the current § 25.562 test. Testing with a SID is the best means available to assess the injury potential of a sideward impact condition. Such an evaluation is considered necessary to provide an acceptable level of safety for side-facing seats. The side-facing seat proposed special conditions have been determined to result in a level of safety equivalent to that provided by the injury pass/fail VerDate Mar<15>2010 14:05 Jan 03, 2011 Jkt 223001 criteria in § 25.562 for forward- or aftfacing seats. Applicability As discussed above, this proposed special condition is applicable to the GVI. Should Gulfstream apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design features, this proposed special condition would apply to that model as well. Conclusion This action affects only certain novel or unusual design features of the GVI. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for the GVI airplanes. In addition to the airworthiness standards in §§ 25.562 and 25.785, the following proposed special conditions provide injury criteria and installation/ testing guidelines that represent the minimum acceptable airworthiness standard for single-place side-facing seats: A. The Proposed Injury Criteria 1. Existing Criteria: All injury protection criteria of § 25.562(c)(1) through (c)(6) apply to the occupant of a side-facing seat. Head injury criterion (HIC) assessments are only required for head contact with the seat and/or adjacent structures. 2. Body-to-Wall/Furnishing Contact: The seat must be installed aft of a structure such as an interior wall or furnishing that will support the pelvis, upper arm, chest, and head of an occupant seated next to the structure. A conservative representation of the structure and its stiffness must be included in the tests. It is recommended, but not required, that the contact surface of this structure be covered with at least two inches of energy absorbing protective padding (foam or equivalent), such as Ensolite. 3. Thoracic Trauma: Thoracic trauma index (TTI) injury criterion must be substantiated by dynamic test or by rational analysis based on previous test(s) of a similar seat installation. Testing must be conducted with a side PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 impact dummy (SID), as defined by Title 49, Code of Federal Regulations (49 CFR) part 572, Subpart F, or its equivalent. TTI must be less than 85, as defined in 49 CFR part 572, subpart F. SID TTI data must be processed as defined in Federal Motor Vehicle Safety Standard (FMVSS) part 571.214, section S6.13.5. 4. Pelvis: Pelvic lateral acceleration must be shown by dynamic test or by rational analysis based on previous test(s) of a similar seat installation not to exceed 130g. Pelvic acceleration data must be processed as defined in FMVSS part 571.214, section S6.13.5. 5. Shoulder Strap Loads: Where upper torso straps (shoulder straps) are used for occupants, tension loads in individual straps must not exceed 1,750 pounds. If dual straps are used for restraining the upper torso, the total strap tension loads must not exceed 2,000 pounds. B. General Test Guidelines 1. One longitudinal test with the SID or its equivalent, undeformed floor, no yaw, and with all lateral structural supports (armrests/walls). Pass/fail injury assessments: TTI and pelvic acceleration. 2. One longitudinal test with the Hybrid II anthropomorphic test dummy (ATD), deformed floor, with 10 degrees yaw, and with all lateral structural support (armrests/walls). Pass/fail injury assessments: HIC; and upper torso restrain load, restraint system retention and pelvic acceleration. 3. Vertical (14g) test is to be conducted with modified Hybrid II ATDs with existing pass/fail criteria. Issued in Renton, Washington, on December 22, 2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–33221 Filed 1–3–11; 8:45 am] BILLING CODE 4910–13–P 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 Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\04JAP1.SGM 04JAP1 Federal Register / Vol. 76, No. 2 / Tuesday, January 4, 2011 / Proposed Rules Notice of proposed rulemaking (NPRM). ACTION: We propose to supersede an existing airworthiness directive (AD) that applies to General Electric Company (GE) CF6–45 and CF6–50 series turbofan engines. The existing AD requires replacing certain forward and aft centerbodies of the long fixed core exhaust nozzle (LFCEN) assembly. Since we issued that AD, we became aware that other forward and aft centerbodies are also affected. This proposed AD would add certain new centerbodies requiring replacement. This proposed AD is prompted by the discovery of more part numbers (P/Ns) of centerbodies requiring replacement. We are proposing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating from the engine, damage to the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by February 18, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact General Electric Company, GE–Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, telephone 513–552–3272; fax 513–552– 3329; e-mail: geae.aoc@ge.com. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. VerDate Mar<15>2010 14:05 Jan 03, 2011 Jkt 223001 FOR FURTHER INFORMATION CONTACT: Tomasz Rakowski, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate; phone: 781– 238–7735; fax: 781–238–7199; e-mail: tomasz.rakowski@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2006–24145; Directorate Identifier 2006–NE–06–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion 293 the applicability of this proposed AD to remove them from service. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would add forward centerbody P/Ns 9076M28G05, G06, and G08, P/Ns 9076M82G01, G03, and aft centerbody P/Ns 9076M46G02, G04, to those P/Ns in AD 2009–04–17 to be removed from service. Costs of Compliance We estimate that this proposed AD would affect 383 GE CF6–45 and CF6– 50 series turbofan engines installed on airplanes of U.S. registry. We also estimate that it would take about 44 work hours per engine to perform the actions required by this AD, and that the average labor rate is $85 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 $5,645,420. Actions Since Existing AD Was Issued 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. Since we issued AD 2009–04–17, we identified seven additional centerbody P/Ns that should have been included in the AD. These centerbodies are of the same design and construction as those identified in the original AD and therefore, are subject to the same unsafe condition. We added forward centerbodies P/N 9076M28G05, G06, G08, P/N 9076M82G01, G03, and aft centerbodies P/N 9076M46G02, G04 to 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. On February 12, 2009, we issued AD 2009–04–17, Amendment 39–15823 (74 FR 8735, February 26, 2009), for GE CF6–45 and CF6–50 series turbofan engines. That AD requires replacing LFCEN assembly forward centerbodies P/N 1313M55G01 or G02, P/N 9076M28G09 or G10, and aft centerbodies P/N 1313M56G01 or 9076M46G05 with modified centerbodies. That AD resulted from reports of separation of centerbodies from the engine due to high imbalance engine conditions caused by events including bird strikes. Separation of the centerbodies from the engine would cause engine damage and airplane damage. We issued that AD to prevent the forward and aft centerbody of the LFCEN assembly from separating from the engine, damage to the engine, and damage to the airplane. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\04JAP1.SGM 04JAP1 294 Federal Register / Vol. 76, No. 2 / Tuesday, January 4, 2011 / Proposed Rules 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), (3) Will not affect intrastate aviation in Alaska, and (4) 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2009–04–17, Amendment 39–15823 (74 FR 8735; February 26, 2009), and adding the following new AD: General Electric Company: Docket No. FAA– 2006–24145; Directorate Identifier 2006– NE–06–AD. Comments Due Date (a) The FAA must receive comments on this AD action by February 18, 2011. Affected ADs (b) This AD supersedes AD 2009–04–17, Amendment 39–15823. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 DEPARTMENT OF COMMERCE Compliance 15 CFR Part 922 (e) Comply with this AD within the compliance times specified, unless already done. (1) Within 18 months after the effective date of this AD, replace forward centerbody, P/N 1313M55G01 and G02, P/N 9076M28G05, G06, G08, G09, and G10, P/N 9076M82G01 and G03, and aft centerbody P/N 1313M56G01, P/N 9076M46G02, G04, and G05 with a forward and aft centerbody that has been modified using the Accomplishment Instructions, Section 3, of GE Service Bulletin (SB) 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. [0908041219–0073–02] Centerbody Installation Prohibition PART 39—AIRWORTHINESS DIRECTIVES § 39.13 affected, requiring replacement. We are issuing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating from the engine, damage to the engine, and damage to the airplane. Applicability (c) This AD applies to the following engines with a long fixed core exhaust nozzle (LFCEN) assembly forward centerbody, part number (P/N) 1313M55G01 or G02, P/N 9076M28G05, G06, G08, G09, or G10, P/N 9076M82G01 or G03, and aft centerbody P/N 1313M56G01, or P/N 9076M46G02, G04, or G05, installed in: (1) 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 turbofan engines; including engines marked on the engine data plate as CF6–50C2–F and CF6–50C2–R. (2) 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. (2) After 18 months from the effective date of this AD, do not install any engine with forward centerbody, P/N 1313M55G01 or G02, P/N 9076M28G05, G06, G08, G09, or G10, P/N 9076M82G01 or G03, or aft centerbody P/N 1313M56G01, P/N 9076M46G02, G04, or G05 on any airplane. Alternative Methods of Compliance (AMOCs) (f) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) For more information about this AD, contact Tomasz Rakowski, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate; phone: 781– 238–7735; fax: 781–238–7199; e-mail: tomasz.rakowski@faa.gov. (h) For service information identified in this AD, contact General Electric Company, GE–Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, telephone 513–552– 3272; fax 513–552–3329; e-mail: geae.aoc@ge.com. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on December 28, 2010. Peter A. White, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–33167 Filed 1–3–11; 8:45 am] BILLING CODE 4910–13–P Unsafe Condition (d) This AD was prompted by the discovery of more P/Ns of centerbodies VerDate Mar<15>2010 14:05 Jan 03, 2011 Jkt 223001 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 National Oceanic and Atmospheric Administration RIN 0648–AX79 Amendments to National Marine Sanctuary Regulations Regarding Low Overflights in Designated Zones Office of National Marine Sanctuaries (ONMS), National Oceanic and Atmospheric Administration (NOAA), Department of Commerce (DOC). ACTION: Extension of public comment period. AGENCY: On December 8, 2010, NOAA published a proposed rule in the Federal Register to amend the low overflight regulations of the Channel Islands, Monterey Bay, Gulf of the Farallones, and Olympic Coast national marine sanctuaries. Specifically, NOAA proposes to amend the regulations requiring that motorized aircraft maintain certain minimum altitudes above specified locations within the boundaries of the listed sanctuaries; and state that failure to comply with these altitude limits is presumed to disturb marine mammals or seabirds and is a violation of the sanctuary regulations. DATES: The public comment period on the proposed rule published at 75 FR 76319, December 8, 2010, will be extended an additional 30 days from the original due date of January 7, 2011. Comments will be accepted through February 7, 2011. ADDRESSES: You may submit comments, identified by RIN 0648–AX79 by any one of the following methods: • Electronic Submissions: Submit all electronic public comments via the Federal eRulemaking Portal https:// www.regulations.gov. • Mail: Debra Malek, Office of National Marine Sanctuaries, 1305 EastWest Highway, 11th floor, Silver Spring, MD 20910. Instructions: No comments will be posted for public viewing until after the comment period has closed. All comments received are a part of the public record and will be posted to https://www.regulations.gov without change. All Personal Identifying Information (for example, name, address, etc.) voluntarily submitted by the commenter may be publicly accessible. Do not submit confidential business information or otherwise sensitive or protected information. SUMMARY: E:\FR\FM\04JAP1.SGM 04JAP1

Agencies

[Federal Register Volume 76, Number 2 (Tuesday, January 4, 2011)]
[Proposed Rules]
[Pages 292-294]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-33167]


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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]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-45 and 
CF6-50 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 293]]


ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to General Electric Company (GE) CF6-45 and CF6-50 
series turbofan engines. The existing AD requires replacing certain 
forward and aft centerbodies of the long fixed core exhaust nozzle 
(LFCEN) assembly. Since we issued that AD, we became aware that other 
forward and aft centerbodies are also affected. This proposed AD would 
add certain new centerbodies requiring replacement. This proposed AD is 
prompted by the discovery of more part numbers (P/Ns) of centerbodies 
requiring replacement. We are proposing this AD to prevent the forward 
and aft centerbody of the LFCEN assembly from separating from the 
engine, damage to the engine, and damage to the airplane.

DATES: We must receive comments on this proposed AD by February 18, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact General 
Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 
45215, telephone 513-552-3272; fax 513-552-3329; e-mail: 
geae.aoc@ge.com. You may review copies of the referenced service 
information at the FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA. For information on the availability of 
this material at the FAA, call 781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Tomasz Rakowski, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate; 
phone: 781-238-7735; fax: 781-238-7199; e-mail: 
tomasz.rakowski@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2006-
24145; Directorate Identifier 2006-NE-06-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On February 12, 2009, we issued AD 2009-04-17, Amendment 39-15823 
(74 FR 8735, February 26, 2009), for GE CF6-45 and CF6-50 series 
turbofan engines. That AD requires replacing LFCEN assembly forward 
centerbodies P/N 1313M55G01 or G02, P/N 9076M28G09 or G10, and aft 
centerbodies P/N 1313M56G01 or 9076M46G05 with modified centerbodies. 
That AD resulted from reports of separation of centerbodies from the 
engine due to high imbalance engine conditions caused by events 
including bird strikes. Separation of the centerbodies from the engine 
would cause engine damage and airplane damage. We issued that AD to 
prevent the forward and aft centerbody of the LFCEN assembly from 
separating from the engine, damage to the engine, and damage to the 
airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2009-04-17, we identified seven additional 
centerbody P/Ns that should have been included in the AD. These 
centerbodies are of the same design and construction as those 
identified in the original AD and therefore, are subject to the same 
unsafe condition. We added forward centerbodies P/N 9076M28G05, G06, 
G08, P/N 9076M82G01, G03, and aft centerbodies P/N 9076M46G02, G04 to 
the applicability of this proposed AD to remove them from service.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would add forward centerbody P/Ns 9076M28G05, G06, 
and G08, P/Ns 9076M82G01, G03, and aft centerbody P/Ns 9076M46G02, G04, 
to those P/Ns in AD 2009-04-17 to be removed from service.

Costs of Compliance

    We estimate that this proposed AD would affect 383 GE CF6-45 and 
CF6-50 series turbofan engines installed on airplanes of U.S. registry. 
We also estimate that it would take about 44 work hours per engine to 
perform the actions required by this AD, and that the average labor 
rate is $85 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 $5,645,420.

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.

[[Page 294]]

    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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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 removing airworthiness directive 
(AD) 2009-04-17, Amendment 39-15823 (74 FR 8735; February 26, 2009), 
and adding the following new AD:

General Electric Company: Docket No. FAA-2006-24145; Directorate 
Identifier 2006-NE-06-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
18, 2011.

Affected ADs

    (b) This AD supersedes AD 2009-04-17, Amendment 39-15823.

Applicability

    (c) This AD applies to the following engines with a long fixed 
core exhaust nozzle (LFCEN) assembly forward centerbody, part number 
(P/N) 1313M55G01 or G02, P/N 9076M28G05, G06, G08, G09, or G10, P/N 
9076M82G01 or G03, and aft centerbody P/N 1313M56G01, or P/N 
9076M46G02, G04, or G05, installed in:
    (1) 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 turbofan engines; including 
engines marked on the engine data plate as CF6-50C2-F and CF6-50C2-
R.
    (2) 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 was prompted by the discovery of more P/Ns of 
centerbodies affected, requiring replacement. We are issuing this AD 
to prevent the forward and aft centerbody of the LFCEN assembly from 
separating from the engine, damage to the engine, and damage to the 
airplane.

Compliance

    (e) Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 18 months after the effective date of this AD, 
replace forward centerbody, P/N 1313M55G01 and G02, P/N 9076M28G05, 
G06, G08, G09, and G10, P/N 9076M82G01 and G03, and aft centerbody 
P/N 1313M56G01, P/N 9076M46G02, G04, and G05 with a forward and aft 
centerbody that has been modified using the Accomplishment 
Instructions, Section 3, of GE Service Bulletin (SB) 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.

Centerbody Installation Prohibition

    (2) After 18 months from the effective date of this AD, do not 
install any engine with forward centerbody, P/N 1313M55G01 or G02, 
P/N 9076M28G05, G06, G08, G09, or G10, P/N 9076M82G01 or G03, or aft 
centerbody P/N 1313M56G01, P/N 9076M46G02, G04, or G05 on any 
airplane.

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Engine Certification Office, FAA, may approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19.

Related Information

    (g) For more information about this AD, contact Tomasz Rakowski, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate; phone: 781-238-7735; fax: 781-238-7199; e-
mail: tomasz.rakowski@faa.gov.
    (h) For service information identified in this AD, contact 
General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215, telephone 513-552-3272; fax 513-552-3329; e-
mail: geae.aoc@ge.com. You may review copies of the referenced 
service information at the FAA, Engine & Propeller Directorate. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on December 28, 2010.
Peter A. White,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-33167 Filed 1-3-11; 8:45 am]
BILLING CODE 4910-13-P
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