Airworthiness Directives; General Electric Company Model CF6-80C2D1F Turbofan Engines, 61398-61400 [05-21174]

Download as PDF 61398 Federal Register / Vol. 70, No. 204 / Monday, October 24, 2005 / Proposed Rules (c) Appearance of bias—whether the testimony and/or production of records could result in the public perception that Ex-Im Bank is favoring one party over another, or advocating the position of a party to the proceeding; (d) Furtherance of agency policy— whether the testimony and/or production of records is consistent with the policy and mission of the Ex-Im Bank; (e) Prevention of fraud or injustice— whether the disclosure of the information requested is necessary to prevent the perpetration of fraud or injustice; (f) Relevance to litigation—whether the testimony and/or production of records sought is relevant to the subject litigation; (g) Necessity—whether the testimony and/or production of records, including a release of such in camera, is appropriate or necessary as determined by either the procedural rules governing the legal proceeding, or according to the relevant laws concerning privilege; (h) Availability from another source— whether the information sought through testimony or production of records is available from another source; (i) Violations of laws or regulations— whether the testimony and/or production of records would violate a statute, regulation, executive order, or other official directive; (j) Classified information—whether the testimony and/or production of records would improperly reveal information classified pursuant to applicable statute or Executive Order; and (k) Compromise of rights and interests—whether the testimony and/or production of records would compromise any of the following: law enforcement interests, constitutional rights, national security interests,, foreign policy interests, or the confidentiality of commercial and/or financial information. § 404.31 Procedure for declining to testify and/or produce records. Ex-Im Bank personnel receiving a demand to provide testimony and/or produce records regarding information acquired in the course of their performance of official duties, or due to their official status, and who have not received written authorization from the General Counsel to provide such information, shall: (a) Respectfully decline to answer or appear for examination on the grounds that such testimony is forbidden by this subpart; (b) Request the opportunity to consult with the General Counsel; VerDate Aug<31>2005 14:14 Oct 21, 2005 Jkt 208001 (c) Explain that only upon consultation may they be granted approval to provide such testimony; (d) Explain that providing such testimony or records absent approval may subject the individual to criminal liability under 18 U.S.C. 641, as well as other applicable laws, and other disciplinary action; and (e) Request a stay of the request or demand pending a determination by the General Counsel. § 404.32 Procedure in the event a decision concerning a demand is not made prior to the time a response to the demand is required. If response to a demand is required before a determination has been rendered by the General Counsel, the U.S. Attorney or such other attorney as may be designated for the purpose will appear with the Ex-Im Bank personnel upon whom the demand has been made, and will furnish the court or other authority with a copy of the regulations contained in this subpart and inform the court or other authority that the demand has been or is being, as the case may be, referred for prompt consideration of the General Counsel. The court or other authority shall be requested respectfully to stay the demand pending determination by the General Counsel. § 404.33 Procedure in the event of an adverse ruling. If the court of other authority declines to stay the effect of the demand in response to a request made in accordance with § 404.32 pending a determination by the General Counsel, or if the court or other authority rules that the demand must be complied with irrespective of the instructions from the General Counsel not to produce the material or disclose the information sought, the Ex-Im Bank personnel upon whom the demand has been made shall respectfully decline to comply with the demand (United States ex rel. Touhy v. Ragen, 340 U.S. 462). § 404.34 Procedure for demands for testimony or production of documents regarding confidential information. In addition to compliance with the requirements of this subpart, demands to provide testimony and/or produce records that concern information protected by the Privacy Act, 5 U.S.C. 552a, or any other authority mandating confidentiality of certain classes of records or information, must also satisfy the requirements for disclosure imposed by such authority before records may be produced or testimony given. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 § 404.35 Procedures for requests for Ex-Im Bank employees to provide expert or opinion testimony. No Ex-Im Bank personnel may, unless specifically authorized by the General Counsel, testify in any legal proceeding as an expert or opinion witness as to any matter related to his or her duties or the functions of the Ex-Im Bank, including the meaning of Ex-Im Bank documents. Any demand for expert or opinion testimony shall comply with the policies and procedures outlined in this subpart. § 404.36 No private right of action. Nothing in this subpart shall be construed as creating any right, substantive or procedural, enforceable at law or equity by a party against Ex-Im Bank or the United States. Dated: October 18, 2005. Howard A. Schweitzer, General Counsel (Acting), Export Import Bank of the United States. [FR Doc. 05–21147 Filed 10–21–05; 8:45 am] BILLING CODE 6690—01—M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22055; Directorate Identifier 2005–NE–31–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company Model CF6–80C2D1F Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for General Electric Company Model CF6– 80C2D1F turbofan engines. This proposed AD would require modifying the latching system of the fan reverser. This proposed AD results from 13 reports of released thrust reverser hardware. We are proposing this AD to prevent release of the thrust reverser cascade on landing, which could result in runway debris and a possible hazard to other aircraft. DATES: We must receive any comments on this proposed AD by November 23, 2005. ADDRESSES: Use one of the following addresses to comment on this proposed AD. E:\FR\FM\24OCP1.SGM 24OCP1 Federal Register / Vol. 70, No. 204 / Monday, October 24, 2005 / Proposed Rules • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You can get the service information identified in this proposed AD from Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park Plaza, Baltimore, MD, 21220–4295, telephone: (410) 682–0094; fax: (410) 682–0100. You may examine the comments on this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803– 5299; telephone (781) 238–7176; 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– 2005–22055; Directorate Identifier 2005–NE–31–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the DOT docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete VerDate Aug<31>2005 14:14 Oct 21, 2005 Jkt 208001 Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit https://dms.dot.gov. Examining the AD Docket You may examine the docket that contains the proposal, any comments received and, any final disposition in person at the Docket Management Facility Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the Docket Management Facility receives them. Discussion The FAA has received 13 reports of thrust reverser hardware released on landing. The first event occurred in January 1997. With the existing design for the forward lower latch, an operator can inadvertently close a fan reverser half with the lower latch handle in the closed position. When this happens, the barrel nut of the lower latch assembly can ride over the clevis, mounted on the engine fan case, without engaging the clevis. When it is in this position, the lower latch assembly appears engaged when it isn’t. Because the barrel nut assembly of the lower latch might be spring-loaded against the engine fan case, the fan cowl door can close without engaging the lower latch assembly. All of the incidents occurred on CF6–80C2D1F engines installed on McDonnell Douglas MD–11 airplanes. Investigations show the design of those applications contributes to the failures of the fan reversers. The Middle Rivers Aircraft Systems (MRAS) (a subsidiary of the General Electric Company) issued four service bulletins to address the problem. However, several operators of McDonnell Douglas MD–11 airplanes haven’t incorporated the recommendations of those service bulletins. As a result, three incidents occurred from March 2004 through October 2004. This condition, if not corrected, could result in release of the thrust reverser cascade on landing, which could result in runway debris and a possible hazard to other aircraft. Relevant Service Information We have reviewed and approved the technical contents of the following MRAS service bulletins (SBs): • CF6–80C2 S/B 78–1068, Revision 2, dated May 16, 2005, and CF6–80C2 S/ B 78–1077, Revision 1, dated May 16, PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 61399 2005, that describe procedures for modifying the latching system of the fan reverser. • SB CF6–80C2 S/B 78–1078, Revision 1, dated May 16, 2005, that describe procedures for replacing the existing L-shaped brackets or the upper and lower ends of the upper latch operating cable. • SB CF6–80C2 S/B 78–1088, Revision 5, dated May 16, 2005, that describe procedures for installing the new improved fan reverser upper latch. Differences Between the Proposed AD and the Manufacturer’s Service Information Middle River Aircraft Systems SB’s CF6–80C2 S/B 78–1068, Revision 2, dated May 16, 2005; CF6–80C2 S/B 78– 1077, Revision 1, dated May 16, 2005; and CF6–80C2 S/B 78–1078, Revision 1, dated May 16, 2005; apply to CF6–80C2 series engines. This proposed AD applies to the CF6–80C2D1F engine installed on the McDonnell Douglas MD–11 airplanes only. 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: • Modifying the latching system of the fan reverser at the next normally scheduled maintenance period, or within 1,200 flight hours time-in-service (TIS) after the effective date of the proposed AD, whichever occurs first; and • Replacing the existing L-shaped support brackets of the upper and lower ends of the upper latch operating cable at the next normally scheduled maintenance period, or within 6,000 flight hours TIS after the effective date of the proposed AD, whichever occurs first; and • Installing the new improved fan reverser upper latch at the next normally scheduled maintenance period, or within 6,000 flight hours TIS after the effective date of the proposed AD, whichever occurs first. The proposed AD would require you to use the service information described previously to perform these actions. Costs of Compliance There are about 339 General Electric Company CF6–80C2D1F2 turbofan engines of the affected design in the worldwide fleet. We estimate that this proposed AD would affect 138 engines installed on airplanes of U.S. registry. We also estimate that it would take E:\FR\FM\24OCP1.SGM 24OCP1 61400 Federal Register / Vol. 70, No. 204 / Monday, October 24, 2005 / Proposed Rules approximately 19 work hours per engine to perform the proposed actions, and that the average labor rate is $65 per work hour. Required parts would cost approximately $6,644 per engine. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $1,087,302. 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: Authority for This Rulemaking 1. The authority citation for part 39 continues to read as follows: Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. VerDate Aug<31>2005 14:14 Oct 21, 2005 Jkt 208001 PART 39—AIRWORTHINESS DIRECTIVES 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 Corporation: Docket No. FAA–2005–22055; Directorate Identifier 2005–NE–31–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by November 23, 2005. Affected ADs (b) None. Unsafe Condition (d) This AD results from 13 reports of released thrust reverser hardware. We are issuing this AD to prevent release of the thrust reverser cascade on landing, which could result in runway debris and a possible hazard to other aircraft. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Modifying the Latching System of the Fan Reverser (f) At the next normally scheduled maintenance period or within 1,200 flight hours time-in-service (TIS) after the effective date of this AD, whichever occurs first, modify the latching system of the fan reverser. Use the Accomplishment Instructions of Middle River Aircraft Systems (MRAS) service bulletins (SBs) CF6–80C2 S/ B 78–1068, Revision 2, or CF6–80C2 S/B 78– 1077, Revision 1, both dated May 16, 2005 to modify the latch assembly. Replacing the L-Shaped Support Brackets (g) At the next normally scheduled maintenance period or within 6,000 flight hours TIS after the effective date of this AD, whichever occurs first, replace the existing Lshaped support brackets of the upper and lower ends of the upper latch operating cable with improved T-shaped support brackets. Use the Accomplishment Instructions of MRAS SB CF6–80C2 S/B 78–1078, Revision Frm 00006 Installing the Improved Upper Latch of the Fan Reverser (h) At the next normally scheduled maintenance period or within 6,000 flight hours TIS after the effective date of this AD, whichever occurs first, install the improved upper latch of the fan reverser. Use the Accomplishment Instructions of MRAS SB CF6–80C2 S/B 78–1088, Revision 5, dated May 16, 2005 to install the upper latch. Alternative Methods of Compliance (i) 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 (j) None. Issued in Burlington, Massachusetts, on October 13, 2005. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–21174 Filed 10–21–05; 8:45 am] BILLING CODE 4910–13–P Applicability (c) This AD applies to General Electric Company Model CF6–80C2D1F turbofan engines. These engines are installed on, but not limited to, McDonnell Douglas Corporation MD–11 airplanes. PO 00000 1, dated May 16, 2005 to replace the support brackets. Fmt 4702 Sfmt 4702 DEPARTMENT OF LABOR Office of Labor-Management Standards 29 CFR Part 404 RIN 1215–AB49 Labor Organization Officer and Employee Reports Office of Labor-Management Standards, Employment Standards Administration, United States Department of Labor. ACTION: Proposed rule; extension of comment period. AGENCY: SUMMARY: This document extends the period for comments on the proposed rule published on August 29, 2005. The proposed rule would revise the financial reports (Form LM–30) required to be filed by union officers and employees under the Labor-Management Reporting and Disclosure Act of 1959, as amended (LMRDA). The comment period, which was to expire on October 28, 2005, is extended ninety days to January 26, 2006. DATES: Comments on the proposed rule published on August 29, 2005 (70 FR 51166) must be received on or before January 26, 2006. ADDRESSES: You may submit comments, identified by RIN 1215–AB49, by any of the following methods: E-mail: OLMS-REG-1215AB49@dol.gov E:\FR\FM\24OCP1.SGM 24OCP1

Agencies

[Federal Register Volume 70, Number 204 (Monday, October 24, 2005)]
[Proposed Rules]
[Pages 61398-61400]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-21174]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22055; Directorate Identifier 2005-NE-31-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Model CF6-
80C2D1F Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for General Electric Company Model CF6-80C2D1F turbofan engines. This 
proposed AD would require modifying the latching system of the fan 
reverser. This proposed AD results from 13 reports of released thrust 
reverser hardware. We are proposing this AD to prevent release of the 
thrust reverser cascade on landing, which could result in runway debris 
and a possible hazard to other aircraft.

DATES: We must receive any comments on this proposed AD by November 23, 
2005.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.

[[Page 61399]]

     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You can get the service information identified in this proposed AD 
from Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park 
Plaza, Baltimore, MD, 21220-4295, telephone: (410) 682-0094; fax: (410) 
682-0100.
    You may examine the comments on this proposed AD in the AD docket 
on the Internet at https://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7176; 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-2005-22055; 
Directorate Identifier 2005-NE-31-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of the 
DOT docket Web site, anyone can find and read the comments in any of 
our dockets, including the name of the individual who sent the comment 
(or signed the comment on behalf of an association, business, labor 
union, etc.). You may review the DOT's complete Privacy Act Statement 
in the Federal Register published on April 11, 2000 (65 FR 19477-78) or 
you may visit https://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, any comments 
received and, any final disposition in person at the Docket Management 
Facility Docket Offices between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the Docket Management Facility receives them.

Discussion

    The FAA has received 13 reports of thrust reverser hardware 
released on landing. The first event occurred in January 1997. With the 
existing design for the forward lower latch, an operator can 
inadvertently close a fan reverser half with the lower latch handle in 
the closed position. When this happens, the barrel nut of the lower 
latch assembly can ride over the clevis, mounted on the engine fan 
case, without engaging the clevis. When it is in this position, the 
lower latch assembly appears engaged when it isn't. Because the barrel 
nut assembly of the lower latch might be spring-loaded against the 
engine fan case, the fan cowl door can close without engaging the lower 
latch assembly. All of the incidents occurred on CF6-80C2D1F engines 
installed on McDonnell Douglas MD-11 airplanes. Investigations show the 
design of those applications contributes to the failures of the fan 
reversers. The Middle Rivers Aircraft Systems (MRAS) (a subsidiary of 
the General Electric Company) issued four service bulletins to address 
the problem. However, several operators of McDonnell Douglas MD-11 
airplanes haven't incorporated the recommendations of those service 
bulletins. As a result, three incidents occurred from March 2004 
through October 2004. This condition, if not corrected, could result in 
release of the thrust reverser cascade on landing, which could result 
in runway debris and a possible hazard to other aircraft.

Relevant Service Information

    We have reviewed and approved the technical contents of the 
following MRAS service bulletins (SBs):
     CF6-80C2 S/B 78-1068, Revision 2, dated May 16, 2005, and 
CF6-80C2 S/B 78-1077, Revision 1, dated May 16, 2005, that describe 
procedures for modifying the latching system of the fan reverser.
     SB CF6-80C2 S/B 78-1078, Revision 1, dated May 16, 2005, 
that describe procedures for replacing the existing L-shaped brackets 
or the upper and lower ends of the upper latch operating cable.
     SB CF6-80C2 S/B 78-1088, Revision 5, dated May 16, 2005, 
that describe procedures for installing the new improved fan reverser 
upper latch.

Differences Between the Proposed AD and the Manufacturer's Service 
Information

    Middle River Aircraft Systems SB's CF6-80C2 S/B 78-1068, Revision 
2, dated May 16, 2005; CF6-80C2 S/B 78-1077, Revision 1, dated May 16, 
2005; and CF6-80C2 S/B 78-1078, Revision 1, dated May 16, 2005; apply 
to CF6-80C2 series engines. This proposed AD applies to the CF6-80C2D1F 
engine installed on the McDonnell Douglas MD-11 airplanes only.

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:
     Modifying the latching system of the fan reverser at the 
next normally scheduled maintenance period, or within 1,200 flight 
hours time-in-service (TIS) after the effective date of the proposed 
AD, whichever occurs first; and
     Replacing the existing L-shaped support brackets of the 
upper and lower ends of the upper latch operating cable at the next 
normally scheduled maintenance period, or within 6,000 flight hours TIS 
after the effective date of the proposed AD, whichever occurs first; 
and
     Installing the new improved fan reverser upper latch at 
the next normally scheduled maintenance period, or within 6,000 flight 
hours TIS after the effective date of the proposed AD, whichever occurs 
first.
    The proposed AD would require you to use the service information 
described previously to perform these actions.

Costs of Compliance

    There are about 339 General Electric Company CF6-80C2D1F2 turbofan 
engines of the affected design in the worldwide fleet. We estimate that 
this proposed AD would affect 138 engines installed on airplanes of 
U.S. registry. We also estimate that it would take

[[Page 61400]]

approximately 19 work hours per engine to perform the proposed actions, 
and that the average labor rate is $65 per work hour. Required parts 
would cost approximately $6,644 per engine. Based on these figures, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$1,087,302.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 14 CFR part 39 as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:

General Electric Corporation: Docket No. FAA-2005-22055; Directorate 
Identifier 2005-NE-31-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by November 23, 
2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company Model CF6-
80C2D1F turbofan engines. These engines are installed on, but not 
limited to, McDonnell Douglas Corporation MD-11 airplanes.

Unsafe Condition

    (d) This AD results from 13 reports of released thrust reverser 
hardware. We are issuing this AD to prevent release of the thrust 
reverser cascade on landing, which could result in runway debris and 
a possible hazard to other aircraft.

Compliance

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

Modifying the Latching System of the Fan Reverser

    (f) At the next normally scheduled maintenance period or within 
1,200 flight hours time-in-service (TIS) after the effective date of 
this AD, whichever occurs first, modify the latching system of the 
fan reverser. Use the Accomplishment Instructions of Middle River 
Aircraft Systems (MRAS) service bulletins (SBs) CF6-80C2 S/B 78-
1068, Revision 2, or CF6-80C2 S/B 78-1077, Revision 1, both dated 
May 16, 2005 to modify the latch assembly.

Replacing the L-Shaped Support Brackets

    (g) At the next normally scheduled maintenance period or within 
6,000 flight hours TIS after the effective date of this AD, 
whichever occurs first, replace the existing L-shaped support 
brackets of the upper and lower ends of the upper latch operating 
cable with improved T-shaped support brackets. Use the 
Accomplishment Instructions of MRAS SB CF6-80C2 S/B 78-1078, 
Revision 1, dated May 16, 2005 to replace the support brackets.

Installing the Improved Upper Latch of the Fan Reverser

    (h) At the next normally scheduled maintenance period or within 
6,000 flight hours TIS after the effective date of this AD, 
whichever occurs first, install the improved upper latch of the fan 
reverser. Use the Accomplishment Instructions of MRAS SB CF6-80C2 S/
B 78-1088, Revision 5, dated May 16, 2005 to install the upper 
latch.

Alternative Methods of Compliance

    (i) 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

    (j) None.

    Issued in Burlington, Massachusetts, on October 13, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-21174 Filed 10-21-05; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.