Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines, 77570-77572 [2010-31172]

Download as PDF 77570 Federal Register / Vol. 75, No. 238 / Monday, December 13, 2010 / Proposed Rules the flight control surfaces for both normal and failure states, and it generates the actual surface commands that provide for stability augmentation and control about all three airplane axes. Because electronic flight control system technology has outpaced existing regulations (primarily §§ 25.671 and 25.672), a special condition is proposed to ensure appropriate mode recognition by the flight crew for events which significantly change the operating mode of the electronic flight control system. Discussion of Proposed Special Conditions Some failures of this system may lead to a degraded operating mode that does not merit a classic ‘‘failure warning’’ but in which flight envelope protection is lost and the flight crew must fly the airplane differently to avoid a stall or to avoid exceeding structural speed limitations. In that case, mode awareness by the flight crew is necessary to avoid confusion and protect safe flight. Therefore, these special conditions for flight control system mode annunciation propose suitable mode annunciation be provided to the flight crew for such events. Applicability As discussed above, these proposed special conditions are 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, these proposed special conditions 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: wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 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. If the design of the flight control system has multiple modes of operation, a means must be provided to indicate to the flight crew any mode that significantly changes or degrades the normal handling or operational characteristics of the airplane. VerDate Mar<15>2010 15:05 Dec 10, 2010 Jkt 223001 Issued in Renton, Washington. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–31177 Filed 12–10–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1151; Directorate Identifier 95–ANE–10–AD] RIN 2120–AA64 Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. FOR FURTHER INFORMATION CONTACT: Tomasz Rakowski, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7735; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede an existing airworthiness directive (AD) for General Electric (GE) CF6–45/–50 series and CF6–80A series turbofan engines with certain part number (P/N) side links of the five-link forward mount assembly installed. That AD currently requires an initial and repetitive visual inspection of the side links for cracks, and stripping and reapplying the Sermetel W coating on the side link at every exposure of the side link. That AD also requires replacing the side links and pylon attachment bolts, and inspecting the fail-safe bolt and platform lug if the side links are cracked. This proposed AD would continue to require those same inspections and stripping and reapplying the Sermetel W coating, and would add two part numbers to the applicability. This proposed AD results from a review of the inspection program, which revealed that GE had omitted two affected part numbers from the applicability. We are proposing this AD to prevent failure of the side links and possible engine separation from the airplane. DATES: We must receive any comments on this proposed AD by February 11, 2011. SUMMARY: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building ADDRESSES: PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 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– 2010–1151; Directorate Identifier 95– ANE–10–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:// www.regulations.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 Web site, anyone can find and read the comments in any of our dockets, including, if provided, 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). Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. E:\FR\FM\13DEP1.SGM 13DEP1 Federal Register / Vol. 75, No. 238 / Monday, December 13, 2010 / Proposed Rules Discussion The FAA proposes to amend 14 CFR part 39 by superseding AD 2006–12–24, Amendment 39–14650 (71 FR 34807, June 16, 2006). That AD requires inspecting and stripping and reapplying the Sermetel W coating on the side links every time one or more of the bolts attaching the side link to the fan frame—front high-pressure compressor case or the bolt attaching the side link to the mount platform are removed. That AD resulted from a report of a cracked side link found during a routine inspection at a shop visit in 2006. That condition, if not corrected, could result in failure of the side links and possible engine separation from the airplane. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 Actions Since AD 2006–12–24 Was Issued Since that AD was issued, GE performed an evaluation of the inspection program and determined that they had omitted the P/Ns for two side links that could be installed on CF6–45/ –50 series and CF6–80A series engines. GE introduced those P/N side links in 2000. The age of those side links means that they might have experienced only two shop visits (the average time between shop visits is about four years) since they were put into service. Also, about 50 percent of the new side links are spare parts and they might not be installed on any engines in service yet. Because of those conditions, we haven’t received any reports of cracks in the new P/N links. However, due to the similarity in design between these additional parts and the parts that are listed in AD 2006–12–24, the same unsafe condition could exist or develop on the additional side links. Because there is no requirement to inspect or strip and reapply the Sermetel W coating on these additional part numbers in AD 2006–12–24, they might not have been inspected for cracks, which could lead to part failure. This proposed AD would add left-hand side link, P/N 9346M99P03, and right-hand side link, P/N 9346M99P04, to the applicability. We have also updated the applicability section to list the affected engine models in the same way they are listed on their Type Certificate Data Sheets. Relevant Service Information We have reviewed and approved the technical contents of GE Service Bulletins CF6–50 S/B 72–1255, Revision 1, dated June 17, 2009, and CF6–80A S/B 72–0797, Revision 1, dated June 17, 2009, that describe procedures for inspecting and stripping and reapplying VerDate Mar<15>2010 15:05 Dec 10, 2010 Jkt 223001 the Sermetel W coating on the side links. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. For that reason, we are proposing this AD, which would require inspecting and stripping and reapplying the Sermetel W coating on the side links at each exposure of the side link. The proposed AD would require that you do these actions using the service information described previously. Costs of Compliance We estimate that this proposed AD would affect 194 engines installed on airplanes of U.S. registry. We also estimate that it would take about 8 work-hours per engine to perform the proposed actions, and that the average labor rate is $85 per work-hour. We estimate the parts cost to be negligible because only a small percentage of parts will actually require replacement as a result of this proposed AD. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $131,920 per year. 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 00011 Fmt 4702 Sfmt 4702 77571 responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed AD: 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, Incorporation by reference, 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 removing Amendment 39–14650 (71 FR 34807, June 16, 2006), and by adding a new airworthiness directive to read as follows: General Electric Company: Docket No. FAA– 2010–1151; Directorate Identifier 95– ANE–10–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by February 11, 2011. Affected ADs (b) This AD supersedes AD 2006–12–24, Amendment 39–14650. Applicability (c) This AD applies to General Electric (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, CF6–50E2B, CF6–80A, CF6– 80A1, CF6–80A2, and CF6–80A3 turbofan engines with left-hand side links part numbers (P/Ns) 9204M94P01, 9204M94P03, 9346M99P01, and 9346M99P03, and righthand side links, P/Ns 9204M94P02, 9204M94P04, 9346M99P02, and 9346M99P04, installed on the five-link forward engine mount assembly (also known E:\FR\FM\13DEP1.SGM 13DEP1 77572 Federal Register / Vol. 75, No. 238 / Monday, December 13, 2010 / Proposed Rules as Configuration 2). These engines are installed on, but not limited to, Boeing DC– 10–30, DC–10–30F (KC–10A, KDC–10), 767, and 747 series airplanes and Airbus A300 and A310 series airplanes. DEPARTMENT OF TRANSPORTATION Comments Invited Federal Aviation Administration Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers and be submitted in triplicate to the address listed above. Commenters wishing the FAA to acknowledge receipt of their comments on this notice must submit with those comments a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to Docket No. FAA–2010–1105/Airspace Docket No. 10–AAL–20.’’ The postcard will be date/time stamped and returned to the commenter. All communications received on or before the specified closing date for comments will be considered before taking action on the proposed rule. The proposal contained in this notice may be changed in light of comments received. All comments submitted will be available for examination in the public docket both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerned with this rulemaking will be filed in the docket. 14 CFR Part 71 Unsafe Condition (d) This AD results from a review of the inspection program, which revealed that GE had omitted two affected part numbers from the applicability. We are issuing this AD to prevent failure of the side links and possible engine separation from the airplane. Compliance (e) You are responsible for having the actions required by this AD performed at every exposure of the side link. Inspecting and Stripping and Reapplying the Sermetel W Coating on the Side Links (f) Inspect and strip and reapply the Sermetel W coating on each side link at every exposure of the side links. Use the following GE service bulletins (SBs): (1) For CF6–45/–50 series engines, use paragraphs 3.A. through 3.E. of the Accomplishment Instructions of CF6–50 S/B 72–1255, Revision 1, dated June 17, 2009. (2) For CF6–80A series engines, use paragraphs 3.A. through 3.E. of the Accomplishment Instructions of CF6–80A S/B 72–0797, Revision 1, dated June 17, 2009. Definition of Exposure of Side Link (g) A side link is exposed when one or more bolts that attach the side links to the fan frame-front high-pressure compressor case are removed, or when the bolt attaching the side link to the mount platform is removed. 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. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 Related Information (i) Contact Tomasz Rakowski, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7735; fax (781) 238–7199, for more information about this AD. (j) General Electric SBs CF6–50 S/B 72– 1255, Revision 1, dated June 17, 2009, and CF6–80A S/B 72–0797, Revision 1, dated June 17, 2009, pertain to the subject of this AD. Contact General Electric Aviation Operations Center (AOC), telephone (877) 432–3272; fax (877) 432–3329; or go to: https://customer.geae.com, for a copy of this service information. Issued in Burlington, Massachusetts, on November 17, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–31172 Filed 12–10–10; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 15:05 Dec 10, 2010 Jkt 223001 [Docket No. FAA–2010–1105 Airspace Docket No. 10–AAL–20] Proposed Revision of Class E Airspace; Platinum AK Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to revise Class E airspace at Platinum AK. The creation of a new Standard Instrument Approach Procedure (SIAP) at the Platinum Airport has made this action necessary to enhance safety and management of Instrument Flight Rules (IFR) operations. DATES: Comments must be received on or before January 27, 2011. ADDRESSES: Send comments on the proposal to the Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. You must identify the docket number FAA–2010–1105/ Airspace Docket No. 10–AAL–20 at the beginning of your comments. You may also submit comments on the Internet at http://www.regulations.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647–5527) is on the plaza level of the Department of Transportation NASSIF Building at the above address. An informal docket may also be examined during normal business hours at the office of the Manager, Safety, Alaska Flight Service Operations, Federal Aviation Administration, 222 West 7th Avenue, Box 14, Anchorage, AK 99513–7587. FOR FURTHER INFORMATION CONTACT: Martha Dunn, Federal Aviation Administration, 222 West 7th Avenue, Box 14, Anchorage, AK 99513–7587; telephone number (907) 271–5898; fax: (907) 271–2850; e-mail: Martha.ctr.Dunn@faa.gov. Internet address: http://www.faa.gov/about/ office_org/headquarters_offices/ato/ service_units/systemops/fs/alaskan/ rulemaking/. SUPPLEMENTARY INFORMATION: SUMMARY: PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Availability of NPRMs An electronic copy of this document may be downloaded through the Internet at http://www.regulations.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at http:// www.faa.gov/airports_airtraffic/ air_traffic/publications/ airspace_amendments/. Additionally, any person may obtain a copy of this notice by submitting a request to the Federal Aviation Administration, Office of Air Traffic Airspace Management, ATA–400, 800 Independence Avenue, SW., Washington, DC 20591 or by calling (202) 267–8783. Communications must identify both docket numbers for this notice. Persons interested in being placed on a mailing list for future NPRM’s should contact the FAA’s Office of Rulemaking, (202) 267–9677, to request a copy of Advisory Circular No. 11–2A, Notice of Proposed E:\FR\FM\13DEP1.SGM 13DEP1

Agencies

[Federal Register Volume 75, Number 238 (Monday, December 13, 2010)]
[Proposed Rules]
[Pages 77570-77572]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-31172]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1151; Directorate Identifier 95-ANE-10-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for General Electric (GE) CF6-45/-50 series and CF6-80A 
series turbofan engines with certain part number (P/N) side links of 
the five-link forward mount assembly installed. That AD currently 
requires an initial and repetitive visual inspection of the side links 
for cracks, and stripping and reapplying the Sermetel W coating on the 
side link at every exposure of the side link. That AD also requires 
replacing the side links and pylon attachment bolts, and inspecting the 
fail-safe bolt and platform lug if the side links are cracked. This 
proposed AD would continue to require those same inspections and 
stripping and reapplying the Sermetel W coating, and would add two part 
numbers to the applicability. This proposed AD results from a review of 
the inspection program, which revealed that GE had omitted two affected 
part numbers from the applicability. We are proposing this AD to 
prevent failure of the side links and possible engine separation from 
the airplane.

DATES: We must receive any comments on this proposed AD by February 11, 
2011.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

FOR FURTHER INFORMATION CONTACT: Tomasz Rakowski, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7735; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

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-2010-1151; Directorate 
Identifier 95-ANE-10-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://www.regulations.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 Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, 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).

Examining the AD Docket

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

[[Page 77571]]

Discussion

    The FAA proposes to amend 14 CFR part 39 by superseding AD 2006-12-
24, Amendment 39-14650 (71 FR 34807, June 16, 2006). That AD requires 
inspecting and stripping and reapplying the Sermetel W coating on the 
side links every time one or more of the bolts attaching the side link 
to the fan frame--front high-pressure compressor case or the bolt 
attaching the side link to the mount platform are removed. That AD 
resulted from a report of a cracked side link found during a routine 
inspection at a shop visit in 2006. That condition, if not corrected, 
could result in failure of the side links and possible engine 
separation from the airplane.

Actions Since AD 2006-12-24 Was Issued

    Since that AD was issued, GE performed an evaluation of the 
inspection program and determined that they had omitted the P/Ns for 
two side links that could be installed on CF6-45/-50 series and CF6-80A 
series engines. GE introduced those P/N side links in 2000. The age of 
those side links means that they might have experienced only two shop 
visits (the average time between shop visits is about four years) since 
they were put into service. Also, about 50 percent of the new side 
links are spare parts and they might not be installed on any engines in 
service yet. Because of those conditions, we haven't received any 
reports of cracks in the new P/N links. However, due to the similarity 
in design between these additional parts and the parts that are listed 
in AD 2006-12-24, the same unsafe condition could exist or develop on 
the additional side links. Because there is no requirement to inspect 
or strip and reapply the Sermetel W coating on these additional part 
numbers in AD 2006-12-24, they might not have been inspected for 
cracks, which could lead to part failure. This proposed AD would add 
left-hand side link, P/N 9346M99P03, and right-hand side link, P/N 
9346M99P04, to the applicability. We have also updated the 
applicability section to list the affected engine models in the same 
way they are listed on their Type Certificate Data Sheets.

Relevant Service Information

    We have reviewed and approved the technical contents of GE Service 
Bulletins CF6-50 S/B 72-1255, Revision 1, dated June 17, 2009, and CF6-
80A S/B 72-0797, Revision 1, dated June 17, 2009, that describe 
procedures for inspecting and stripping and reapplying the Sermetel W 
coating on the side links.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. For that reason, we are proposing this AD, 
which would require inspecting and stripping and reapplying the 
Sermetel W coating on the side links at each exposure of the side link. 
The proposed AD would require that you do these actions using the 
service information described previously.

Costs of Compliance

    We estimate that this proposed AD would affect 194 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 8 work-hours per engine to perform the proposed actions, and 
that the average labor rate is $85 per work-hour. We estimate the parts 
cost to be negligible because only a small percentage of parts will 
actually require replacement as a result of this proposed AD. Based on 
these figures, we estimate the total cost of the proposed AD to U.S. 
operators to be $131,920 per year.

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 AD:
    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, Incorporation by 
reference, 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 removing Amendment 39-14650 (71 FR 
34807, June 16, 2006), and by adding a new airworthiness directive to 
read as follows:

General Electric Company: Docket No. FAA-2010-1151; Directorate 
Identifier 95-ANE-10-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by February 11, 
2011.

Affected ADs

    (b) This AD supersedes AD 2006-12-24, Amendment 39-14650.

Applicability

    (c) This AD applies to General Electric (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, CF6-50E2B, CF6-80A, CF6-80A1, 
CF6-80A2, and CF6-80A3 turbofan engines with left-hand side links 
part numbers (P/Ns) 9204M94P01, 9204M94P03, 9346M99P01, and 
9346M99P03, and right-hand side links, P/Ns 9204M94P02, 9204M94P04, 
9346M99P02, and 9346M99P04, installed on the five-link forward 
engine mount assembly (also known

[[Page 77572]]

as Configuration 2). These engines are installed on, but not limited 
to, Boeing DC-10-30, DC-10-30F (KC-10A, KDC-10), 767, and 747 series 
airplanes and Airbus A300 and A310 series airplanes.

Unsafe Condition

    (d) This AD results from a review of the inspection program, 
which revealed that GE had omitted two affected part numbers from 
the applicability. We are issuing this AD to prevent failure of the 
side links and possible engine separation from the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed at every exposure of the side link.

Inspecting and Stripping and Reapplying the Sermetel W Coating on the 
Side Links

    (f) Inspect and strip and reapply the Sermetel W coating on each 
side link at every exposure of the side links. Use the following GE 
service bulletins (SBs):
    (1) For CF6-45/-50 series engines, use paragraphs 3.A. through 
3.E. of the Accomplishment Instructions of CF6-50 S/B 72-1255, 
Revision 1, dated June 17, 2009.
    (2) For CF6-80A series engines, use paragraphs 3.A. through 3.E. 
of the Accomplishment Instructions of CF6-80A S/B 72-0797, Revision 
1, dated June 17, 2009.

Definition of Exposure of Side Link

    (g) A side link is exposed when one or more bolts that attach 
the side links to the fan frame-front high-pressure compressor case 
are removed, or when the bolt attaching the side link to the mount 
platform is removed.

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.

Related Information

    (i) Contact Tomasz Rakowski, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; telephone (781) 238-
7735; fax (781) 238-7199, for more information about this AD.
    (j) General Electric SBs CF6-50 S/B 72-1255, Revision 1, dated 
June 17, 2009, and CF6-80A S/B 72-0797, Revision 1, dated June 17, 
2009, pertain to the subject of this AD. Contact General Electric 
Aviation Operations Center (AOC), telephone (877) 432-3272; fax 
(877) 432-3329; or go to: https://customer.geae.com, for a copy of 
this service information.

    Issued in Burlington, Massachusetts, on November 17, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-31172 Filed 12-10-10; 8:45 am]
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