Airworthiness Directives; General Electric Company Model CF6-80C2D1F Turbofan Engines, 14092-14094 [06-2648]

Download as PDF 14092 Federal Register / Vol. 71, No. 54 / Tuesday, March 21, 2006 / Rules and Regulations requirements, Security measures, Spent fuel, Whistleblowing. I For the reasons set out in the preamble and under the authority of the Atomic Energy Act of 1954, as amended; the Energy Reorganization Act of 1974, as amended; and 5 U.S.C. 552 and 553; the NRC is adopting the following amendments to 10 CFR part 72. PART 72—LICENSING REQUIREMENTS FOR THE INDEPENDENT STORAGE OF SPENT NUCLEAR FUEL, HIGH-LEVEL RADIOACTIVE WASTE, AND REACTOR-RELATED GREATER THAN CLASS C WASTE 1. The authority citation for part 72 is revised to read as follows: I Authority: Secs. 51, 53, 57, 62, 63, 65, 69, 81, 161, 182, 183, 184, 186, 187, 189, 68 Stat. 929, 930, 932, 933, 934, 935, 948, 953, 954, 955, as amended, sec. 234, 83 Stat. 444, as amended (42 U.S.C. 2071, 2073, 2077, 2092, 2093, 2095, 2099, 2111, 2201, 2232, 2233, 2234, 2236, 2237, 2238, 2282); sec. 274, Pub. L. 86–373, 73 Stat. 688, as amended (42 U.S.C. 2021); sec. 201, as amended, 202, 206, 88 Stat. 1242, as amended, 1244, 1246 (42 U.S.C. 5841, 5842, 5846); Pub. L. 95–601, sec. 10, 92 Stat. 2951 as amended by Pub. L. 102– 486, sec. 7902, 106 Stat. 3123 (42 U.S.C. 5851); sec. 102, Pub. L. 91–190, 83 Stat. 853 (42 U.S.C. 4332); secs. 131, 132, 133, 135, 137, 141, Pub. L. 97–425, 96 Stat. 2229, 2230, 2232, 2241, sec. 148, Pub. L. 100–203, 101 Stat. 1330–235 (42 U.S.C. 10151, 10152, 10153, 10155, 10157, 10161, 10168); sec. 1704, 112 Stat. 2750 (44 U.S.C. 3504 note); sec. 651(e), Pub. L. 109–58, 119 Stat. 806–10 (42 U.S.C. 2014, 2021, 2021b, 2111). Section 72.44(g) also issued under secs. 142(b) and 148(c), (d), Pub. L. 100–203, 101 Stat. 1330–232, 1330–236 (42 U.S.C. 10162(b), 10168(c), (d)). Section 72.46 also issued under sec. 189, 68 Stat. 955 (42 U.S.C. 2239); sec. 134, Pub. L. 97–425, 96 Stat. 2230 (42 U.S.C. 10154). Section 72.96(d) also issued under sec. 145(g), Pub. L. 100–203, 101 Stat. 1330–235 (42 U.S.C. 10165(g)). Subpart J also issued under secs. 2(2), 2(15), 2(19), 117(a), 141(h), Pub. L. 97–425, 96 Stat. 2202, 2203, 2204, 2222, 2224 (42 U.S.C. 10101, 10137(a), 10161(h)). Subparts K and L are also issued under sec. 133, 98 Stat. 2230 (42 U.S.C. 10153) and sec. 218(a), 96 Stat. 2252 (42 U.S.C. 10198). 2. In § 72.214, Certificate of Compliance 1007 is revised to read as follows: I § 72.214 List of approved spent fuel storage casks. cprice-sewell on PROD1PC66 with RULES * * * * * Certificate Number: 1007. Initial Certificate Effective Date: May 7, 1993. Amendment Number 1 Effective Date: May 30, 2000. Amendment Number 2 Effective Date: September 5, 2000. VerDate Aug<31>2005 15:05 Mar 20, 2006 Jkt 208001 Amendment Number 3 Effective Date: May 21, 2001. Amendment Number 4 Effective Date: February 3, 2003. Amendment Number 5 Effective Date: September 13, 2005. Amendment Number 6 Effective Date: June 5, 2006. SAR Submitted by: BNG Fuel Solutions Corporation. SAR Title: Final Safety Analysis Report for the Ventilated Storage Cask System. Docket Number: 72–1007. Certificate Expiration Date: May 7, 2013. Model Number: VSC–24. * * * * * Dated at Rockville, Maryland, this 3rd day of March 2006. For the Nuclear Regulatory Commission. Luis A. Reyes, Executive Director for Operations. [FR Doc. 06–2715 Filed 3–20–06; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22055; Directorate Identifier 2005–NE–31–AD; Amendment 39– 14517; AD 2006–06–08] RIN 2120–AA64 Airworthiness Directives; General Electric Company Model CF6–80C2D1F Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) Model CF6– 80C2D1F turbofan engines. This AD requires modifying the latching system of the fan reverser. 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. DATES: This AD becomes effective April 25, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of April 25, 2006. ADDRESSES: You can get the service information identified in this AD from Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park Plaza, SUMMARY: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Baltimore, MD, 21220–4295, telephone: (410) 682–0094; fax: (410) 682–0100. You may examine the AD docket on the Internet at http://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed airworthiness directive (AD). The proposed AD applies to GE Model CF6–80C2D1F turbofan engines. We published the proposed AD in the Federal Register on October 24, 2005 (70 FR 61398). That action proposed to require modifying the latching system of the fan reverser. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Clarify the Service Bulletin Incorporations One commenter states that the AD should clarify that if Middle River Aircraft Systems (MRAS) Service Bulletin (SB) No. CF6–80C2 S/B 78– 1077 is incorporated, incorporating MRAS SB No. CF6–80C2 S/B 78–1068 is not necessary. Likewise, if MRAS SB No. CF6–80C2 S/B 78–1068 is incorporated, incorporating MRAS SB No. CF6–80C2 S/B 78–1077 is not necessary. We agree. We changed compliance paragraph (f)(2) in this AD to state ‘‘Use the Accomplishment Instructions of either MRAS SB No. CF6–80C2 S/B 78– 1068, Revision 2, dated May 16, 2005, or SB No. CF6–80C2 S/B 78–1077, Revision 1, dated May 16, 2005, (but not both SBs) to modify the latch assembly.’’ E:\FR\FM\21MRR1.SGM 21MRR1 Federal Register / Vol. 71, No. 54 / Tuesday, March 21, 2006 / Rules and Regulations Request for Incorporating by Reference the SBs One commenter requests that we incorporate by reference the required SBs in the proposed AD, to make them available through the Office of the Federal Register. We agree that the SBs should be incorporated by reference, but only in the final rule AD. The proposed AD cannot incorporate by reference any service information, because the document is only a proposal. This AD incorporates by reference the applicable SBs. cprice-sewell on PROD1PC66 with RULES Request for Referencing the Defective Part or Assembly by Part Number One commenter requests that we reference the defective part or assembly by part number in the AD. Without specific part numbers, it is impossible to determine if part manufacturer approval (PMA) equivalent parts or assemblies exist, either for defective parts or assemblies or the new-and-improved parts or assemblies. We do not agree. The affected part numbers are identified in the appropriate Service Bulletins and do not need to be repeated in the AD. In Compliance With Older Versions of the Required SBs One commenter states they have complied with older versions of all the required Service Bulletins and believes that this should satisfy the intent of the AD. We agree. We changed applicability paragraph (c) to read ‘‘This AD applies to the following General Electric Company (GE) Model CF6–80C2D1F turbofan engines: (1) Engines that have not incorporated either Middle River Aircraft Systems (MRAS) Service Bulletin (SB) No. CF6– 80C2 S/B 78–1068, Revision 2, dated May 16, 2005, any earlier revision, or original issue, or SB No. CF6–80C2 S/ B 78–1077, Revision 1, dated May 16, 2005, or original issue; and (2) Engines that have not incorporated MRAS SB No. CF6–80C2 S/B 78–1078, Revision 1, dated May 16, 2005, or original issue; and (3) Engines that have not incorporated MRAS SB No. CF6–80C2 S/B 78–1088, Revision 5, dated May 24, 2005, any earlier revision, or original issue.’’ Also, for clarification, we changed paragraphs (f), (g), and (h) to generally read ‘‘If MRAS SB No. CF6–80C2 S/B 78–10(XX), Revision (X), dated May 16, 2005, any earlier revision, or original issue, has not been incorporated, do the following:’’ Request for Compliance Time Changes One commenter requests we change the compliance time in paragraph (f) VerDate Aug<31>2005 15:05 Mar 20, 2006 Jkt 208001 from 1,200 flight hours to 1,600 flight hours, and the compliance time in paragraphs (g) and (h) from 6,000 flight hours to ‘‘not to exceed 7,500 flight hours’’. The commenter states that these changes would make the AD coincide with their A-Checks and C-Checks. We do not agree. We worked closely with GE to establish compliance times that would help ensure the AD requirements get done within about a one-and-a-half year timeframe. The first event of released thrust reverser hardware occurred in January 1997. GE issued SBs to address the problem shortly afterward. However, several MD–11 operators have not incorporated those SBs, and as a result, three more events of released thrust reverser hardware occurred since March 2004. These events could result in runway debris and a possible hazard to other aircraft. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 138 engines installed on airplanes of U.S. registry. We also estimate that it will take approximately 19 work hours per engine to perform the proposed actions, and that the average labor rate is $65 per work hour. Required parts will cost approximately $6,644 per engine. Based on these figures, we estimate the total cost of the 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 14093 that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I 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: I 2006–06–08 General Electric Company: Amendment 39–14517. Docket No. FAA–2005–22055; Directorate Identifier. 2005–NE–31–AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 25, 2006. Affected ADs (b) None. Applicability (c) This AD applies to the following General Electric Company (GE) Model CF6– 80C2D1F turbofan engines: (1) Engines that have not incorporated either Middle River Aircraft Systems (MRAS) E:\FR\FM\21MRR1.SGM 21MRR1 14094 Federal Register / Vol. 71, No. 54 / Tuesday, March 21, 2006 / Rules and Regulations Service Bulletin (SB) No. CF6–80C2 S/B 78– 1068, Revision 2, dated May 16, 2005, any earlier revision, or original issue, or SB No. CF6–80C2 S/B 78–1077, Revision 1, dated May 16, 2005, or original issue; and (2) Engines that have not incorporated MRAS SB No. CF6–80C2 S/B 78–1078, Revision 1, dated May 16, 2005, or original issue; and (3) Engines that have not incorporated MRAS SB No. CF6–80C2 S/B 78–1088, Revision 5, dated May 24, 2005, any earlier revision, or original issue. 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) If MRAS SB No. CF6–80C2 S/B 78– 1068, Revision 2, dated May 16, 2005, any earlier revision, or original issue, or SB No. CF6–80C2 S/B 78–1077, Revision 1, dated May 16, 2005, or original issue, has not been incorporated, do the following: (1) 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. (2) Use the Accomplishment Instructions of either MRAS SB No. CF6–80C2 S/B 78– 1068, Revision 2, dated May 16, 2005, or SB No. CF6–80C2 S/B 78–1077, Revision 1, dated May 16, 2005, (but not both SBs) to modify the latch assembly. (2) Use the Accomplishment Instructions of MRAS SB CF6–80C2 S/B 78–1088, Revision 5, dated May 24, 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. Replacing the L-Shaped Support Brackets Related Information (g) If MRAS SB No. CF6–80C2 S/B 78– 1078, Revision 1, dated May 16, 2005, or original issue, has not been incorporated, do the following: (1) 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. (2) Use the Accomplishment Instructions of MRAS SB CF6–80C2 S/B 78–1078, Revision 1, dated May 16, 2005, to replace the support brackets. (j) None. Material Incorporated by Reference (k) You must use the Middle River Aircraft Systems (MRAS) Service Bulletins specified in Table 1 of this AD to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park Plaza, Baltimore, MD 21220–4295, telephone: (410) 682–0094; fax: (410) 682–0100 for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–0001, on the Internet at http://dms.dot.gov, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federalregister/cfr/ibr-locations.html. Installing the Improved Upper Latch of the Fan Reverser (h) If MRAS SB No. CF6–80C2 S/B 78– 1088, Revision 5, dated May 24, 2005, any earlier revision, or original issue, has not been incorporated, do the following: (1) 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. TABLE 1.—INCORPORATION BY REFERENCE MRAS Service Bulletin No. CF6–80C2 S/B 78–1068 Total Pages: 16 CF6–80C2 S/B 78–1077 Total Pages: 19 CF6–80C2 S/B 78–1078 Total Pages: 29 CF6–80C2 S/B 78–1088 Total Pages: 51 Page Date ................................................................................................................ ALL ........ 2 May 16, 2005. ................................................................................................................ ALL ........ 1 May 16, 2005. ................................................................................................................ ALL ........ 1 May 16, 2005. ................................................................................................................ ALL ........ 5 May 24, 2005. Issued in Burlington, Massachusetts, on March 13, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06–2648 Filed 3–20–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2005–22509; Airspace Docket No. 03–AWA–2] RIN 2120–AA66 Airspace Docket No. 03–AWA–2, FAA Docket No. FAA–2005–22509. In that rule, inadvertent errors were made in the graphic depicting the modified St. Louis Class B airspace area. This action corrects those errors. Effective Date: 0901 UTC, March 21, 2006. DATES: AGENCY: SUMMARY: This action corrects a final rule published in the Federal Register on February 15, 2006 (71 FR 7848), FOR FURTHER INFORMATION CONTACT: Steve Rohring, Airspace and Rules, Office of System Operations Airspace and AIM, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: Modification of the St. Louis Class B Airspace Area; MO cprice-sewell on PROD1PC66 with RULES Revision Federal Aviation Administration (FAA), DOT. ACTION: Final rule; correction. VerDate Aug<31>2005 15:05 Mar 20, 2006 Jkt 208001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\21MRR1.SGM 21MRR1

Agencies

[Federal Register Volume 71, Number 54 (Tuesday, March 21, 2006)]
[Rules and Regulations]
[Pages 14092-14094]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2648]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22055; Directorate Identifier 2005-NE-31-AD; 
Amendment 39-14517; AD 2006-06-08]
RIN 2120-AA64


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

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
General Electric Company (GE) Model CF6-80C2D1F turbofan engines. This 
AD requires modifying the latching system of the fan reverser. 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.

DATES: This AD becomes effective April 25, 2006. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of April 25, 2006.

ADDRESSES: You can get the service information identified in this 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 AD docket on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to GE Model CF6-80C2D1F turbofan engines. We published the proposed AD 
in the Federal Register on October 24, 2005 (70 FR 61398). That action 
proposed to require modifying the latching system of the fan reverser.

Examining the AD Docket

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

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Clarify the Service Bulletin Incorporations

    One commenter states that the AD should clarify that if Middle 
River Aircraft Systems (MRAS) Service Bulletin (SB) No. CF6-80C2 S/B 
78-1077 is incorporated, incorporating MRAS SB No. CF6-80C2 S/B 78-1068 
is not necessary. Likewise, if MRAS SB No. CF6-80C2 S/B 78-1068 is 
incorporated, incorporating MRAS SB No. CF6-80C2 S/B 78-1077 is not 
necessary.
    We agree. We changed compliance paragraph (f)(2) in this AD to 
state ``Use the Accomplishment Instructions of either MRAS SB No. CF6-
80C2 S/B 78-1068, Revision 2, dated May 16, 2005, or SB No. CF6-80C2 S/
B 78-1077, Revision 1, dated May 16, 2005, (but not both SBs) to modify 
the latch assembly.''

[[Page 14093]]

Request for Incorporating by Reference the SBs

    One commenter requests that we incorporate by reference the 
required SBs in the proposed AD, to make them available through the 
Office of the Federal Register. We agree that the SBs should be 
incorporated by reference, but only in the final rule AD. The proposed 
AD cannot incorporate by reference any service information, because the 
document is only a proposal. This AD incorporates by reference the 
applicable SBs.

Request for Referencing the Defective Part or Assembly by Part Number

    One commenter requests that we reference the defective part or 
assembly by part number in the AD. Without specific part numbers, it is 
impossible to determine if part manufacturer approval (PMA) equivalent 
parts or assemblies exist, either for defective parts or assemblies or 
the new-and-improved parts or assemblies.
    We do not agree. The affected part numbers are identified in the 
appropriate Service Bulletins and do not need to be repeated in the AD.

In Compliance With Older Versions of the Required SBs

    One commenter states they have complied with older versions of all 
the required Service Bulletins and believes that this should satisfy 
the intent of the AD. We agree. We changed applicability paragraph (c) 
to read ``This AD applies to the following General Electric Company 
(GE) Model CF6-80C2D1F turbofan engines:
    (1) Engines that have not incorporated either Middle River Aircraft 
Systems (MRAS) Service Bulletin (SB) No. CF6-80C2 S/B 78-1068, Revision 
2, dated May 16, 2005, any earlier revision, or original issue, or SB 
No. CF6-80C2 S/B 78-1077, Revision 1, dated May 16, 2005, or original 
issue; and
    (2) Engines that have not incorporated MRAS SB No. CF6-80C2 S/B 78-
1078, Revision 1, dated May 16, 2005, or original issue; and
    (3) Engines that have not incorporated MRAS SB No. CF6-80C2 S/B 78-
1088, Revision 5, dated May 24, 2005, any earlier revision, or original 
issue.''
    Also, for clarification, we changed paragraphs (f), (g), and (h) to 
generally read ``If MRAS SB No. CF6-80C2 S/B 78-10(XX), Revision (X), 
dated May 16, 2005, any earlier revision, or original issue, has not 
been incorporated, do the following:''

Request for Compliance Time Changes

    One commenter requests we change the compliance time in paragraph 
(f) from 1,200 flight hours to 1,600 flight hours, and the compliance 
time in paragraphs (g) and (h) from 6,000 flight hours to ``not to 
exceed 7,500 flight hours''. The commenter states that these changes 
would make the AD coincide with their A-Checks and C-Checks.
    We do not agree. We worked closely with GE to establish compliance 
times that would help ensure the AD requirements get done within about 
a one-and-a-half year timeframe. The first event of released thrust 
reverser hardware occurred in January 1997. GE issued SBs to address 
the problem shortly afterward. However, several MD-11 operators have 
not incorporated those SBs, and as a result, three more events of 
released thrust reverser hardware occurred since March 2004. These 
events could result in runway debris and a possible hazard to other 
aircraft.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 138 engines installed on 
airplanes of U.S. registry. We also estimate that it will take 
approximately 19 work hours per engine to perform the proposed actions, 
and that the average labor rate is $65 per work hour. Required parts 
will cost approximately $6,644 per engine. Based on these figures, we 
estimate the total cost of the 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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. 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.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2006-06-08 General Electric Company: Amendment 39-14517. Docket No. 
FAA-2005-22055; Directorate Identifier. 2005-NE-31-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
25, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following General Electric Company 
(GE) Model CF6-80C2D1F turbofan engines:
    (1) Engines that have not incorporated either Middle River 
Aircraft Systems (MRAS)

[[Page 14094]]

Service Bulletin (SB) No. CF6-80C2 S/B 78-1068, Revision 2, dated 
May 16, 2005, any earlier revision, or original issue, or SB No. 
CF6-80C2 S/B 78-1077, Revision 1, dated May 16, 2005, or original 
issue; and
    (2) Engines that have not incorporated MRAS SB No. CF6-80C2 S/B 
78-1078, Revision 1, dated May 16, 2005, or original issue; and
    (3) Engines that have not incorporated MRAS SB No. CF6-80C2 S/B 
78-1088, Revision 5, dated May 24, 2005, any earlier revision, or 
original issue. 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) If MRAS SB No. CF6-80C2 S/B 78-1068, Revision 2, dated May 
16, 2005, any earlier revision, or original issue, or SB No. CF6-
80C2 S/B 78-1077, Revision 1, dated May 16, 2005, or original issue, 
has not been incorporated, do the following:
    (1) 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.
    (2) Use the Accomplishment Instructions of either MRAS SB No. 
CF6-80C2 S/B 78-1068, Revision 2, dated May 16, 2005, or SB No. CF6-
80C2 S/B 78-1077, Revision 1, dated May 16, 2005, (but not both SBs) 
to modify the latch assembly.

Replacing the L-Shaped Support Brackets

    (g) If MRAS SB No. CF6-80C2 S/B 78-1078, Revision 1, dated May 
16, 2005, or original issue, has not been incorporated, do the 
following:
    (1) 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.
    (2) 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) If MRAS SB No. CF6-80C2 S/B 78-1088, Revision 5, dated May 
24, 2005, any earlier revision, or original issue, has not been 
incorporated, do the following:
    (1) 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.
    (2) Use the Accomplishment Instructions of MRAS SB CF6-80C2 S/B 
78-1088, Revision 5, dated May 24, 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.

Material Incorporated by Reference

    (k) You must use the Middle River Aircraft Systems (MRAS) 
Service Bulletins specified in Table 1 of this AD to perform the 
actions required by this AD. The Director of the Federal Register 
approved the incorporation by reference of the documents listed in 
Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Contact Middle River Aircraft Systems, Mail Point 46, 103 
Chesapeake Park Plaza, Baltimore, MD 21220-4295, telephone: (410) 
682-0094; fax: (410) 682-0100 for a copy of this service 
information. You may review copies at the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC 20590-0001, on the 
Internet at http://dms.dot.gov, or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr-locations.html.

                                      Table 1.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
       MRAS Service Bulletin No.                  Page           Revision                   Date
----------------------------------------------------------------------------------------------------------------
CF6-80C2 S/B 78-1068...................  ALL..................           2  May 16, 2005.
  Total Pages: 16
CF6-80C2 S/B 78-1077...................  ALL..................           1  May 16, 2005.
  Total Pages: 19
CF6-80C2 S/B 78-1078...................  ALL..................           1  May 16, 2005.
  Total Pages: 29
CF6-80C2 S/B 78-1088...................  ALL..................           5  May 24, 2005.
  Total Pages: 51
----------------------------------------------------------------------------------------------------------------


    Issued in Burlington, Massachusetts, on March 13, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 06-2648 Filed 3-20-06; 8:45 am]
BILLING CODE 4910-13-P