Airworthiness Directives; General Electric Company CF6-80C2 Series Turbofan Engines, 11043-11045 [E9-5575]

Download as PDF 11043 Proposed Rules Federal Register Vol. 74, No. 49 Monday, March 16, 2009 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 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0018; Directorate Identifier 2009–NE–01–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF6–80C2 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for General Electric Company (GE) CF6– 80C2 series turbofan engines with certain thrust reverser ballscrew gearbox assembly adjustable-length end actuators installed. This proposed AD would require initial visual inspections and repetitive replacements of the 3⁄8inch rod-ends installed on the thrust reverser ballscrew gearbox assembly adjustable-length end actuators, along with optional terminating action to those repetitive replacements. This proposed AD would also require initial visual inspections and replacements, if necessary, of the other hardware connecting the thrust reverser transcowls to the engine. This proposed AD results from reports of four failures of rod-ends on certain thrust reverser ballscrew gearbox assembly adjustablelength end actuators, leading to partial or complete separation of the transcowl from the engine and airplane during thrust reversal. We are proposing this AD to prevent loss of thrust control, asymmetric thrust, increased stopping distance, and possibly hazardous debris on the runway, which could result in unsafe landings. DATES: We must receive any comments on this proposed AD by May 15, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD. SUMMARY: VerDate Nov<24>2008 14:10 Mar 13, 2009 Jkt 217001 • Federal eRulemaking Portal: Go to https://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: Christopher J. Richards, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.j.richards@faa.gov; telephone (781) 238–7133; 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– 2009–0018; Directorate Identifier 2009– NE–01–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// 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). PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 Examining the AD Docket You may examine the AD docket on the Internet at https:// 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. Discussion Since January 2007, we received reports of four GE CF6–80C2 series turbofan engine thrust reverser transcowls separating from the engine and airplane during thrust reverser deployment while landing. Investigation has revealed that the 3⁄8-inch adjustable rod-ends on the adjustable-length end actuators can fail in fatigue. When a rodend fails, additional load is put on the thrust reverser system center drive unit (CDU). This additional load can cause the CDU clevis bracket fasteners to fail or the CDU clevis pin to lose its retaining capability, both causing separation of the transcowl from the engine and airplane. This condition, if not corrected, could result in loss of thrust control, asymmetric thrust, increased stopping distance, and possibly hazardous debris on the runway, which could result in unsafe landings. Relevant Service Information We have reviewed and approved the technical contents of Middle River Aircraft Systems Alert Service Bulletin (ASB) No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009. That ASB describes procedures for inspecting ballscrew gearbox assembly adjustable-length end actuator 3⁄8-inch rod-ends and torsion arms, clevis fasteners, clevis pins, and clevis pin retaining clips. That ASB also describes procedures for replacing broken rodends, worn, damaged, or deformed torsion arms, loose clevis fasteners, clevis pins that do not meet wear limits, and loose clip retainer nuts and bolts. E:\FR\FM\16MRP1.SGM 16MRP1 11044 Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Proposed Rules FAA’s Determination and Requirements of the Proposed AD products identified in this rulemaking action. 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. We are proposing this AD, which would require initial and repetitive replacements of the 3⁄8-inch rod-ends installed on the thrust reverser ballscrew gearbox assembly adjustablelength end actuators, along with optional terminating action to those repetitive replacements. The proposed AD would also require an initial visual inspection and replacement if necessary, of the other hardware that connects the thrust reverser transcowl to the engine. The proposed AD would require you to use the service information described previously to perform these actions. Regulatory Findings Costs of Compliance We estimate that this proposed AD would affect 750 GE CF6–80C2 series turbofan engines installed on airplanes of U.S. registry. We also estimate that it would take about 1.5 work-hours per engine to perform the proposed inspection, 0.8 work-hour per engine to perform the proposed rod-end replacement, and 24 work-hours per engine to perform the proposed clevis bracket replacement. The average labor rate is $80 per work-hour. Required rodends would cost about $168 per engine. We estimate that 75 engines would require clevis bracket replacement. Required replacement clevis brackets and associated labor would cost about $826,500. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $1,090,500. 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 14:10 Mar 13, 2009 Jkt 217001 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 for This Rulemaking VerDate Nov<24>2008 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. You may get a copy of this summary at the address listed under ADDRESSES. 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– 2009–0018; Directorate Identifier 2009– NE–01–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by May 15, 2009. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF6–80C2 series turbofan engines with thrust reverser ballscrew PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 gearbox assembly adjustable-length end actuators having 3⁄8-inch rod-end, part number (P/N) KBE6–59, MS21242S06, M81935/1–6, B15946–13, or 15946000–13, installed. These engines are installed on, but not limited to, Airbus A300–600/R/F and A310–200/300, and Boeing 747–200B/300/ 400/400D/400F, 767–200/300/300F/400ER, and MD–11 airplanes. Exemption (d) GE CF6–80C2 series turbofan engines that have completed the initial compliance actions in Middle River Aircraft Systems (MRAS) Alert Service Bulletin (ASB) No. CF6–80C2 S/B 78A1162, dated December 30, 2008, or ASB No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009: (1) Are allowed to take credit for accomplishing paragraphs (g) and (h) of this AD; however (2) All 3⁄8-inch rod-ends, including those on engines which satisfy paragraph (d) of this AD, are subject to the replacement requirements in paragraph (i) of this AD. Unsafe Condition (e) This AD results from reports of four failures of rod-ends on certain thrust reverser ballscrew gearbox assembly adjustable-length end actuators, leading to partial or complete separation of the transcowl from the engine and airplane during thrust reversal. We are issuing this AD to prevent loss of thrust control, asymmetric thrust, increased stopping distance, and possibly hazardous debris on the runway, which could result in unsafe landings. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Visual Inspection and Fastening Hardware Replacements (g) Within 500 flight cycles after the effective date of this AD, do the following: (1) Inspect all translating cowl clevis pin retaining clips and associated fastening hardware, including those on the center drive unit (CDU), to ensure they are properly assembled and securely fastened in place. If a retaining clip is not completely covering the clevis pin and firmly attached to the clevis, remove and replace the fastening hardware. Use paragraphs 3.B.(2)(b) and 3.B.(2)(c) of MRAS ASB No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the inspections. (2) Remove and inspect all clevis pins for physical damage or significant corrosion. Use paragraphs 3.C.(1) through 3.C.(3) of MRAS ASB No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the removals, inspections, and part disposition as necessary. (3) Inspect the clevis brackets and four clevis fasteners at each of the clevis brackets (upper, center, and lower) for structural integrity. Use paragraphs 3.F.(1)(a) and 3.F.(1)(b) of MRAS ASB No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the inspections. (4) If loose or missing clevis fasteners are found, remove and replace the clevis E:\FR\FM\16MRP1.SGM 16MRP1 Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Proposed Rules fasteners. Use paragraphs 3.F.(2)(a) through 3.F(2)(c) of MRAS ASB No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the replacements. Initial Rod-End Replacements (h) For all 3⁄8-inch translating cowl adjustable-length actuator rod-ends, P/N KBE6–59, MS21242S06, B15946–13, 15946000–13, or M81935/1–6 having more than 600 flight cycles-since-new on the effective date of this AD, replace them with P/N M81935/1–6, zero time rod-ends within 500 flight cycles after the effective date of this AD. Use paragraphs 3.E.(2) through 3.E.(7) of MRAS ASB No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the replacements. Repetitive 3⁄8-inch Rod-End Replacements (i) Repetitively replace 3⁄8-inch translating cowl adjustable-length actuator rod-ends, P/N M81935/1–6, that were installed as specified in paragraph (h) of this AD, before they accumulate 11,000 flight cycles, with a zero time 3⁄8-inch adjustable-length rod-end, P/N M81935/1–6. Use paragraphs 3.E.(2) through 3.E.(7) of MRAS ASB No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the replacements. Optional Terminating Action (j) As an optional terminating action to the repetitive 3⁄8-inch rod-end replacements required by this AD, replace the 3⁄8-inch adjustable rod-ends with either a fixed length rod-end, P/N 3238726–1, –2, or MS9560–08, or a 7/16-inch adjustable rod-end, P/N 3238729–1. Use paragraph 3.E.(1) of MRAS ASB No. CF6–80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the replacements. Installation Prohibition (k) Rod-ends removed to comply with this AD are not eligible for installation on any aircraft. Previous Credit (l) Inspections and replacements and optional terminating action performed before the effective date of this AD using MRAS ASB No. CF6–80C2 S/B 78A1162, dated December 30, 2008, satisfy the required initial actions and optional terminating action of this AD. Alternative Methods of Compliance (m) 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 (n) Contact Christopher J. Richards, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.j.richards@faa.gov; telephone (781) 238–7133; fax (781) 238–7199, for more information about this AD. (o) Contact Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park Plaza, Baltimore, MD 21220, attn: Warranty Support; telephone (410) 682–0094; fax (410) VerDate Nov<24>2008 14:10 Mar 13, 2009 Jkt 217001 682–0100, for a copy of the service information identified in this AD. Issued in Burlington, Massachusetts, on March 9, 2009. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–5575 Filed 3–13–09; 8:45 am] BILLING CODE 4910–13–P FEDERAL TRADE COMMISSION 16 CFR Part 305 [RIN 3084–AB03] Rule Concerning Disclosures Regarding Energy Consumption and Water Use of Certain Home Appliances and Other Products Required Under the Energy Policy and Conservation Act (‘‘Appliance Labeling Rule’’) AGENCY: Federal Trade Commission (FTC or Commission). ACTION: Advance notice of proposed rulemaking. SUMMARY: Section 325 of the Energy Independence and Security Act of 2007 provides the Commission with authority to promulgate energy labeling rules for consumer electronics, including televisions. The Commission is seeking comment on whether it should require labels for televisions and other consumer electronic products. DATES: Comments must be received by May 14, 2009. ADDRESSES: Interested parties are invited to submit written comments electronically or in paper form. Comments should refer to ‘‘Consumer Electronics Labeling, Project No. P094201’’ to facilitate the organization of comments. Please note that comments will be placed on the public record of this proceeding—including on the publicly accessible FTC website, at (https://www.ftc.gov/os/ publiccomments.shtm)—and therefore should not include any sensitive or confidential information. In particular, comments should not include any sensitive personal information, such as an individual’s Social Security Number; date of birth; driver’s license number or other state identification number, or foreign country equivalent; passport number; financial account number; or credit or debit card number. Comments also should not include any sensitive health information, such as medical records or other individually identifiable health information. In addition, comments should not include any ‘‘[t]rade secrets and commercial or financial information obtained from a PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 11045 person and privileged or confidential . . . .,’’ as provided in Section 6(f) of the FTC Act, 15 U.S.C. 46(f), and Commission Rule 4.10(a)(2), 16 CFR 4.10(a)(2). Comments containing material for which confidential treatment is requested must be filed in paper form, must be clearly labeled ‘‘Confidential,’’ and must comply with FTC Rule 4.9(c).1 Because paper mail addressed to the FTC is subject to delay due to heightened security screening, please consider submitting your comments in electronic form. Comments filed in electronic form should be submitted by using the following weblink: (https:// secure.commentworks.com/ftcelectronicslabeling) (and following the instructions on the web-based form). To ensure that the Commission considers an electronic comment, you must file it on the web-based form at the weblink (https://secure.commentworks.com/ftcelectronicslabeling). If this Notice appears at (https://www.regulations.gov/ search/index.jsp,) you may also file an electronic comment through that website. The Commission will consider all comments that regulations.gov forwards to it. You may also visit the FTC website at https://www.ftc.gov to read the Notice and the news release describing it. A comment filed in paper form should include the ‘‘Consumer Electronics Labeling, Project No. P094201’’ reference both in the text and on the envelope, and should be mailed or delivered to the following address: Federal Trade Commission, Office of the Secretary, Room H-135 (Annex T), 600 Pennsylvania Avenue, NW, Washington, DC 20580. The FTC requests that any comment filed in paper form be sent by courier or overnight service, if possible, because U.S. postal mail in the Washington area and at the Commission is subject to delay due to heightened security precautions. The FTC Act and other laws the Commission administers permit the collection of public comments to consider and use in this proceeding as appropriate. The Commission will consider all timely and responsive public comments that it receives, whether filed in paper or electronic form. Comments received will be available to the public on the FTC 1 FTC Rule 4.2(d), 16 CFR 4.2(d). The comment must be accompanied by an explicit request for confidential treatment, including the factual and legal basis for the request, and must identify the specific portions of the comment to be withheld from the public record. The request will be granted or denied by the Commission’s General Counsel, consistent with applicable law and the public interest. See FTC Rule 4.9(c), 16 CFR 4.9(c). E:\FR\FM\16MRP1.SGM 16MRP1

Agencies

[Federal Register Volume 74, Number 49 (Monday, March 16, 2009)]
[Proposed Rules]
[Pages 11043-11045]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-5575]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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.

========================================================================


Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / 
Proposed Rules

[[Page 11043]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0018; Directorate Identifier 2009-NE-01-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-80C2 
Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for General Electric Company (GE) CF6-80C2 series turbofan engines with 
certain thrust reverser ballscrew gearbox assembly adjustable-length 
end actuators installed. This proposed AD would require initial visual 
inspections and repetitive replacements of the \3/8\-inch rod-ends 
installed on the thrust reverser ballscrew gearbox assembly adjustable-
length end actuators, along with optional terminating action to those 
repetitive replacements. This proposed AD would also require initial 
visual inspections and replacements, if necessary, of the other 
hardware connecting the thrust reverser transcowls to the engine. This 
proposed AD results from reports of four failures of rod-ends on 
certain thrust reverser ballscrew gearbox assembly adjustable-length 
end actuators, leading to partial or complete separation of the 
transcowl from the engine and airplane during thrust reversal. We are 
proposing this AD to prevent loss of thrust control, asymmetric thrust, 
increased stopping distance, and possibly hazardous debris on the 
runway, which could result in unsafe landings.

DATES: We must receive any comments on this proposed AD by May 15, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to https://
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: Christopher J. Richards, Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.j.richards@faa.gov; telephone (781) 238-7133; 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-2009-0018; Directorate 
Identifier 2009-NE-01-AD'' in the subject line of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the proposed AD. We will consider 
all comments received by the closing date and may amend the proposed AD 
in light of those comments.
    We will post all comments we receive, without change, to https://
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 https://
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.

Discussion

    Since January 2007, we received reports of four GE CF6-80C2 series 
turbofan engine thrust reverser transcowls separating from the engine 
and airplane during thrust reverser deployment while landing. 
Investigation has revealed that the \3/8\-inch adjustable rod-ends on 
the adjustable-length end actuators can fail in fatigue. When a rod-end 
fails, additional load is put on the thrust reverser system center 
drive unit (CDU). This additional load can cause the CDU clevis bracket 
fasteners to fail or the CDU clevis pin to lose its retaining 
capability, both causing separation of the transcowl from the engine 
and airplane. This condition, if not corrected, could result in loss of 
thrust control, asymmetric thrust, increased stopping distance, and 
possibly hazardous debris on the runway, which could result in unsafe 
landings.

Relevant Service Information

    We have reviewed and approved the technical contents of Middle 
River Aircraft Systems Alert Service Bulletin (ASB) No. CF6-80C2 S/B 
78A1162, Revision 1, dated February 13, 2009. That ASB describes 
procedures for inspecting ballscrew gearbox assembly adjustable-length 
end actuator \3/8\-inch rod-ends and torsion arms, clevis fasteners, 
clevis pins, and clevis pin retaining clips. That ASB also describes 
procedures for replacing broken rod-ends, worn, damaged, or deformed 
torsion arms, loose clevis fasteners, clevis pins that do not meet wear 
limits, and loose clip retainer nuts and bolts.

[[Page 11044]]

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. We are proposing this AD, which would require 
initial and repetitive replacements of the \3/8\-inch rod-ends 
installed on the thrust reverser ballscrew gearbox assembly adjustable-
length end actuators, along with optional terminating action to those 
repetitive replacements. The proposed AD would also require an initial 
visual inspection and replacement if necessary, of the other hardware 
that connects the thrust reverser transcowl to the engine. 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 750 GE CF6-80C2 
series turbofan engines installed on airplanes of U.S. registry. We 
also estimate that it would take about 1.5 work-hours per engine to 
perform the proposed inspection, 0.8 work-hour per engine to perform 
the proposed rod-end replacement, and 24 work-hours per engine to 
perform the proposed clevis bracket replacement. The average labor rate 
is $80 per work-hour. Required rod-ends would cost about $168 per 
engine. We estimate that 75 engines would require clevis bracket 
replacement. Required replacement clevis brackets and associated labor 
would cost about $826,500. Based on these figures, we estimate the 
total cost of the proposed AD to U.S. operators to be $1,090,500.

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. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 adding the following new 
airworthiness directive:

General Electric Company: Docket No. FAA-2009-0018; Directorate 
Identifier 2009-NE-01-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by May 15, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80C2 
series turbofan engines with thrust reverser ballscrew gearbox 
assembly adjustable-length end actuators having \3/8\-inch rod-end, 
part number (P/N) KBE6-59, MS21242S06, M81935/1-6, B15946-13, or 
15946000-13, installed. These engines are installed on, but not 
limited to, Airbus A300-600/R/F and A310-200/300, and Boeing 747-
200B/300/400/400D/400F, 767-200/300/300F/400ER, and MD-11 airplanes.

Exemption

    (d) GE CF6-80C2 series turbofan engines that have completed the 
initial compliance actions in Middle River Aircraft Systems (MRAS) 
Alert Service Bulletin (ASB) No. CF6-80C2 S/B 78A1162, dated 
December 30, 2008, or ASB No. CF6-80C2 S/B 78A1162, Revision 1, 
dated February 13, 2009:
    (1) Are allowed to take credit for accomplishing paragraphs (g) 
and (h) of this AD; however
    (2) All \3/8\-inch rod-ends, including those on engines which 
satisfy paragraph (d) of this AD, are subject to the replacement 
requirements in paragraph (i) of this AD.

Unsafe Condition

    (e) This AD results from reports of four failures of rod-ends on 
certain thrust reverser ballscrew gearbox assembly adjustable-length 
end actuators, leading to partial or complete separation of the 
transcowl from the engine and airplane during thrust reversal. We 
are issuing this AD to prevent loss of thrust control, asymmetric 
thrust, increased stopping distance, and possibly hazardous debris 
on the runway, which could result in unsafe landings.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Visual Inspection and Fastening Hardware Replacements

    (g) Within 500 flight cycles after the effective date of this 
AD, do the following:
    (1) Inspect all translating cowl clevis pin retaining clips and 
associated fastening hardware, including those on the center drive 
unit (CDU), to ensure they are properly assembled and securely 
fastened in place. If a retaining clip is not completely covering 
the clevis pin and firmly attached to the clevis, remove and replace 
the fastening hardware. Use paragraphs 3.B.(2)(b) and 3.B.(2)(c) of 
MRAS ASB No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13, 
2009, to do the inspections.
    (2) Remove and inspect all clevis pins for physical damage or 
significant corrosion. Use paragraphs 3.C.(1) through 3.C.(3) of 
MRAS ASB No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13, 
2009, to do the removals, inspections, and part disposition as 
necessary.
    (3) Inspect the clevis brackets and four clevis fasteners at 
each of the clevis brackets (upper, center, and lower) for 
structural integrity. Use paragraphs 3.F.(1)(a) and 3.F.(1)(b) of 
MRAS ASB No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13, 
2009, to do the inspections.
    (4) If loose or missing clevis fasteners are found, remove and 
replace the clevis

[[Page 11045]]

fasteners. Use paragraphs 3.F.(2)(a) through 3.F(2)(c) of MRAS ASB 
No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do 
the replacements.

Initial Rod-End Replacements

    (h) For all \3/8\-inch translating cowl adjustable-length 
actuator rod-ends, P/N KBE6-59, MS21242S06, B15946-13, 15946000-13, 
or M81935/1-6 having more than 600 flight cycles-since-new on the 
effective date of this AD, replace them with P/N M81935/1-6, zero 
time rod-ends within 500 flight cycles after the effective date of 
this AD. Use paragraphs 3.E.(2) through 3.E.(7) of MRAS ASB No. CF6-
80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the 
replacements.

Repetitive \3/8\-inch Rod-End Replacements

    (i) Repetitively replace \3/8\-inch translating cowl adjustable-
length actuator rod-ends, P/N M81935/1-6, that were installed as 
specified in paragraph (h) of this AD, before they accumulate 11,000 
flight cycles, with a zero time \3/8\-inch adjustable-length rod-
end, P/N M81935/1-6. Use paragraphs 3.E.(2) through 3.E.(7) of MRAS 
ASB No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13, 2009, 
to do the replacements.

Optional Terminating Action

    (j) As an optional terminating action to the repetitive \3/8\-
inch rod-end replacements required by this AD, replace the \3/8\-
inch adjustable rod-ends with either a fixed length rod-end, P/N 
3238726-1, -2, or MS9560-08, or a 7/16-inch adjustable rod-end, P/N 
3238729-1. Use paragraph 3.E.(1) of MRAS ASB No. CF6-80C2 S/B 
78A1162, Revision 1, dated February 13, 2009, to do the 
replacements.

Installation Prohibition

    (k) Rod-ends removed to comply with this AD are not eligible for 
installation on any aircraft.

Previous Credit

    (l) Inspections and replacements and optional terminating action 
performed before the effective date of this AD using MRAS ASB No. 
CF6-80C2 S/B 78A1162, dated December 30, 2008, satisfy the required 
initial actions and optional terminating action of this AD.

Alternative Methods of Compliance

    (m) 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

    (n) Contact Christopher J. Richards, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
christopher.j.richards@faa.gov; telephone (781) 238-7133; fax (781) 
238-7199, for more information about this AD.
    (o) Contact Middle River Aircraft Systems, Mail Point 46, 103 
Chesapeake Park Plaza, Baltimore, MD 21220, attn: Warranty Support; 
telephone (410) 682-0094; fax (410) 682-0100, for a copy of the 
service information identified in this AD.

    Issued in Burlington, Massachusetts, on March 9, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. E9-5575 Filed 3-13-09; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.