Airworthiness Directives; General Electric Company Turbofan Engines, 3139-3142 [2014-00833]

Download as PDF 3139 Proposed Rules Federal Register Vol. 79, No. 12 Friday, January 17, 2014 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 AGRICULTURE Agricultural Marketing Service 7 CFR Part 1216 [Document Number AMS–FV–13–0089] Peanut Promotion, Research and Information Order; Continuance Referendum Agricultural Marketing Service, Agriculture. ACTION: Referendum order. AGENCY: This document directs that a referendum be conducted among eligible producers of peanuts to determine whether they favor continuance of the Peanut Promotion, Research and Information Order (Order). DATES: The referendum will be conducted from April 7 through April 18, 2014. To vote in this referendum, producers must have paid assessments on peanuts produced during the representative period from January 1 through December 31, 2013, and must currently be a peanut producer. ADDRESSES: Copies of the Order may be obtained from: Referendum Agent, Promotion and Economics Division (PED), Fruit and Vegetable Program (FVP), AMS, USDA, Stop 0244, Room 1406–S, 1400 Independence Avenue SW., Washington, DC 20250–0244; telephone: (888) 720–9917 (toll free), (202) 720–9915 (direct line); facsimile: (202) 205–2800. FOR FURTHER INFORMATION CONTACT: Jeanette Palmer, Marketing Specialist, PED, FVP, AMS, USDA, Stop 0244, Room 1406–S, 1400 Independence Avenue SW., Washington, DC 20250– 0244; telephone: (888) 720–9917 (toll free), (202) 720–9915 (direct line); facsimile: (202) 205–2800; or electronic mail: Jeanette.Palmer@ams.usda.gov. SUPPLEMENTARY INFORMATION: Pursuant to the Commodity Promotion, Research and Information Act of 1996 (7 U.S.C. 7411–7425) (Act), it is hereby directed that a referendum be conducted to ascertain whether continuance of the pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 SUMMARY: VerDate Mar<15>2010 14:04 Jan 16, 2014 Jkt 232001 Order is favored by producers of peanuts covered under the program. The Order is authorized under the Act. The representative period for establishing voter eligibility for the referendum shall be the period from January 1 through December 31, 2013. Persons who are currently producers of peanuts, and who produced peanuts and paid assessments during the representative period are eligible to vote. Persons who received an exemption from assessments for the entire representative period are ineligible to vote. The referendum shall be conducted by mail from April 7 through April 18, 2014. Section 518 of the Act authorizes continuance referenda. Under section 1216.82 of the Order, the U.S. Department of Agriculture (Department) must conduct a referendum every five years or when 10 percent or more of the eligible peanut producers petition the Secretary of Agriculture to hold a referendum to determine if persons subject to assessment favor continuance of the Order. The Department would continue the Order if continuance is approved by a simple majority of the producers voting in the referendum. In accordance with the Paperwork Reduction Act of 1995 (44 U.S.C. chapter 35), the referendum ballot has been approved by the Office of Management and Budget (OMB) and assigned OMB No. 0581–0093. It has been estimated that there are approximately 9,208 producers who will be eligible to vote in the referendum. It will take an average of 15 minutes for each voter to read the voting instructions and complete the referendum ballot. Jeanette Palmer and Sonia Jimenez, PED, FVP, AMS, USDA, Stop 0244, Room 1406–S, 1400 Independence Avenue SW., Washington, DC 20250– 0244, are designated as the referendum agents to conduct this referendum. The referendum procedures 7 CFR 1216.100 through 1216.107, which were issued pursuant to the Act, shall be used to conduct the referendum. The referendum agents will mail the ballots to be cast in the referendum and voting instructions to all known producers prior to the first day of the voting period. Persons who are producers at the time of the referendum and who produced peanuts and paid assessments during the representative PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 period are eligible to vote. Persons who received an exemption from assessments during the entire representative period are ineligible to vote. Any eligible producer who does not receive a ballot should contact the referendum agent no later than one week before the end of the voting period. Ballots must be received by the referendum agent, not later than close of business 4:30 p.m. Eastern time, April 18, 2014, in order to be counted. List of Subjects in 7 CFR Part 1216 Administrative practice and procedure, Advertising, Consumer information, Marketing agreements, Peanut promotion, Reporting and recordkeeping requirements. Authority: 7 U.S.C. 7411–7425 and 7 U.S.C. 7401. Dated: January 10, 2014. Rex A. Barnes, Associate Administrator. [FR Doc. 2014–00773 Filed 1–16–14; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28413; Directorate Identifier 2007–NE–25–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directives (ADs) 90–26– 01, 91–20–02, and 2009–05–02, which apply to all General Electric Company (GE) CF6–80C2 and CF6–80E1 series turbofan engines. Since we issued ADs 90–26–01, 91–20–02, and 2009–05–02, we received a report of an undercowl fire caused by a manifold high-pressure fuel leak, and several additional reports of fuel leaks. This proposed AD would require additional repetitive inspections, replacement of tube (block) clamp, and inspection of fuel manifolds for wear at each tube (block) clamp location. We are proposing this AD to SUMMARY: E:\FR\FM\17JAP1.SGM 17JAP1 3140 Federal Register / Vol. 79, No. 12 / Friday, January 17, 2014 / Proposed Rules prevent failure of the fuel manifold, which could lead to uncontrolled engine fire, engine damage, and damage to the airplane. DATES: We must receive comments on this proposed AD by March 3, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: geae.aoc@ge.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2007– 28413; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Kasra Sharifi, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. 01830; phone 781–238–7773; fax: 781–238– 7199; email: kasra.sharifi@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28413; Directorate Identifier VerDate Mar<15>2010 14:04 Jan 16, 2014 Jkt 232001 2007–NE–25–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On December 20, 1990, we issued AD 90–26–01 (55 FR 49611, November 30, 1990), for GE CF6–80C2 series turbofan engines. That AD requires replacing fuel manifold, part numbers (P/Ns) 1303M31G04 and 1303M32G04, within 30 calendar days after the effective date of the AD. That AD resulted from a report of an engine fire. On November 15, 1991, we issued AD 91–20–02 (56 FR 55231, October 25, 1991), for the same engines. That AD requires replacing fuel manifold, P/Ns 1303M31G06, 1303M32G06, 1303M31G07, 1303M32G07, 1303M31G08, and 1303M32G08, at the next engine removal, but no later than June 30, 1993. That AD also resulted from a report of an engine fire. On March 31, 2009, we issued AD 2009–05–02 (74 FR 8161, February 24, 2009), for GE CF6–80C2 and CF6–80E1 series turbofan engines with fuel manifolds, P/Ns 1303M31G12 and 1303M32G12, installed in drainless fuel manifold assemblies. That AD requires removing the loop clamps that hold the fuel manifold to the compressor rear frame damper brackets, inspecting the fuel manifold for wear at each clamp location, and replacing the clamps with new zero-time parts. That AD also requires revising the Airworthiness Limitations Section to require repetitive fuel manifold inspection and loop clamp replacement. That AD resulted from reports of fuel leaks during engine operation. We issued these ADs to prevent failure of the fuel manifold, which could lead to uncontrolled engine fire, engine damage, and damage to the airplane. We are superseding these ADs to eliminate potentially confusing and contradictory requirements in these ADs. This proposed AD expands the inspection mandated by AD 2009–05–02 and it expands the list of banned fuel manifolds mandated by AD 90–26–01 and AD 91–20–02. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Actions Since Previous ADs Were Issued Since we issued AD 90–26–01 (55 FR 49611, November 30, 1990); AD 91–20– 02 (56 FR 55231, October 25, 1991); and AD 2009–05–02 (74 FR 8161, February 24, 2009); we received a report of an undercowl fire caused by a fuel manifold high-pressure fuel leak in engine model CF6–80C2, and several additional reports of fuel leaks; four in the CF6–80C2 and one in the CF6–80E1 model engine. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain the requirements of AD 90–26–01 (55 FR 49611, November 30, 1990); and AD 91– 20–02 (56 FR 55231, October 25, 1991); to remove certain fuel manifold P/Ns, and the requirements of AD 2009–05–02 (74 FR 8161, February 24, 2009); to inspect certain fuel manifold P/Ns and replace certain consumable components. This proposed AD would add a requirement to inspect an additional fuel manifold configuration and replacement of certain loop clamps. This proposed AD would also require repetitive inspection and replacement of tube (block) clamp, and inspection of the fuel manifold for wear at each tube (block) clamp location. This proposed AD would also require removing certain drainless fuel manifold assembly P/Ns from service. Costs of Compliance We estimate that this proposed AD would affect 1,126 engines installed on airplanes of U.S. registry. We also estimate that required parts cost about $34,894 per engine. We also estimate that is would take about 6 hours to accomplish the actions required by this AD. The average labor rate is $85 per hour. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $39,864,904. 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, E:\FR\FM\17JAP1.SGM 17JAP1 Federal Register / Vol. 79, No. 12 / Friday, January 17, 2014 / Proposed Rules 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 proposed 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), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing airworthiness directive (AD) 90–26–01 (55 FR 49611, November 30, 1990); AD 91–20–02 (56 FR 55231, October 25, 1991); and AD 2009–05–02 (74 FR 8161, February 24, 2009); and ■ b. Adding the following new AD: ■ ■ General Electric Company: Docket No. FAA– 2007–28413; Directorate Identifier 2007– NE–25–AD. (a) Comments Due Date The FAA must receive comments on this AD action by March 3, 2014. (b) Affected ADs This AD supersedes AD 90–26–01 (55 FR 49611, November 30, 1990); AD 91–20–02 (56 FR 55231, October 25, 1991); and AD 2009–05–02 (74 FR 8161, February 24, 2009). (c) Applicability This AD applies to all General Electric Company (GE) CF6–80C2 and CF6–80E1 turbofan engines with fuel manifold, part numbers (P/Ns) 1303M31G04,1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 1303M32G07, 1303M31G08, 1303M32G08,1308M31G12, 1308M32G12, 2420M70G01, and 2420M71G01, installed. (d) Unsafe Condition This AD was prompted by a report of an undercowl fire caused by a fuel manifold high-pressure fuel leak, and several additional reports of fuel leaks. We are issuing this AD to prevent failure of the fuel manifold, which could lead to uncontrolled engine fire, engine damage, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Fuel Manifold Removal. (i) For CF6–80C2 and CF6–80E1 series engines, before further flight after the 3141 effective date of this AD, remove fuel manifold, P/Ns 1303M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 1303M32G07, 1303M31G08, and 1303M32G08, from service. (ii) For CF6–80C2 and CF6–80E1 series engines, at the next engine shop visit after effective date of this AD, remove fuel manifold, P/Ns 1303M31G12, 1303M32G12, 2420M70G01, and 2420M71G01, from service. (2) Fuel Manifold, Loop Clamp, and Tube (Block) Clamp Inspection and Replacement— Drainless Assembly. (i) For CF6–80C2 series engines, with fuel manifold, P/N 1303M31G12 or 1303M32G12, installed, refer to Table 1 to paragraph (e) of this AD, accomplish the initial inspections of the fuel manifold and replacement of the loop clamps in accordance with paragraphs 3.A and 3.D of GE Service Bulletin (SB) CF6– 80C2 S/B 73–0326, Revision 4, dated December 23, 2009. (ii) For CF6–80C2 series engines, with fuel manifold, P/Ns 2420M70G01 or 2420M71G01, installed, refer to Table 1 to paragraph (e) of this AD, accomplish the initial inspection of the fuel manifold and replacement of the loop clamps in accordance with paragraphs 3.C and 3.D of GE SB CF6–80C2 S/B 73–0326, Revision 4, dated December 23, 2009. (iii) For CF6–80E1 series engines, with fuel manifold, P/Ns 1303M31G12 or 1303M32G12, installed, refer to Table 1 to paragraph (e) of this AD, accomplish the initial inspection of the fuel manifold and replacement of the loop clamps in accordance with paragraphs 3.A and 3.C of GE SB CF6–80E1 S/B 73–0061, Revision 4, dated December 23, 2009. (iv) For CF6–80E1 series engines, with fuel manifold P/Ns 2420M70G01 or 2420M71G01 installed, refer to Table 1 to paragraph (e) of this AD, accomplish the initial inspection of the fuel manifold and replacement of the loop clamps in accordance with paragraphs 3.B and 3.C of GE SB CF6–80E1 S/B 73–0061, Revision 4, dated December 23, 2009. (v) Thereafter, inspect fuel manifolds P/Ns 1303M31G12, 1303M32G12, 2420M70G01, and 2420M71G01 installed, within every 7,500 flight hours (FH) since the last inspection, in accordance with paragraphs (e)(2)(i) through (e)(2)(iv) of this AD. TABLE 1 TO PARAGRAPH (E)—FUEL MANIFOLD INSPECTION AND LOOP CLAMP REPLACEMENT AND INSPECTION CRITERIA If: Then: pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 1—If the engine was previously inspected using any of the following: • GE SB CF6–80C2 SB 73–0326 R04, Revision 4, dated December 23, 2009; Then inspect fuel manifold and replace clamps within 7,500 flight hours (FH) time-since-last-inspection (TSLI) or within 6 months after the effective date of this AD, whichever occurs first. • GE SB CF6–80C2 SB 73–0326, Revision 3, dated April 24, 2009; • GE SB CF6–80E1 SB 73–0061 R04, Revision 4, dated December 23, 2009 or; • GE SB CF6–80E1 SB 73–0061, Revision 3, dated April, 24, 2009. 2—If the loop clamps installed at last shop visit were previously used or of unknown heritage or the engine was previously inspected using either of the following: VerDate Mar<15>2010 14:04 Jan 16, 2014 Jkt 232001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\17JAP1.SGM 17JAP1 3142 Federal Register / Vol. 79, No. 12 / Friday, January 17, 2014 / Proposed Rules TABLE 1 TO PARAGRAPH (E)—FUEL MANIFOLD INSPECTION AND LOOP CLAMP REPLACEMENT AND INSPECTION CRITERIA— Continued If: Then: • GE CF6–80C2 SB 73–0326, Revision 2, dated August 30, 2007 or earlier; • GE CF6–80E1 SB 73–0061, Revision 2, dated August 30, 2007 or earlier. 3—If the engine is a first-run engine, an engine with zero-time, or has new loop clamps previously installed on-wing or at shop visit. 4—If the engine has already exceeded the 1,750 FH initial inspection threshold on the effective date of this AD but has fewer than 4,500 flight hours TSLI. 5—If the engine has already exceeded the 4,500 FH initial inspection threshold on the effective date of this AD. (3) For CF6–80C2 series engines, with fuel manifold, P/Ns 1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01, with tube (block) clamp, P/N 1153M26G15, refer to Table 2 to paragraph (e) of this AD, accomplish the initial inspection of the fuel manifold and tube (block) clamp, and replacement of the fuel manifold and tube (block) clamp, if required based on inspection results, in accordance with Then inspect fuel manifold and replace clamps within 1,750 FH timesince-last-shop-visit or within 4 months after the effective date of this AD, whichever occurs first. Then inspect fuel manifold and replace clamps within 7,500 FH timesince-new or since zero-time that new loop clamps were installed. Then inspect fuel manifold and replace clamps within 4,500 FH TSLI or 4 months after the effective date of this AD, whichever occurs first. Then inspect fuel manifold and replace clamps within 4 months after the effective date of this AD. paragraph 3.A of GE SB CF6–80C2 S/B 73– 0414, dated July 2, 2013. (4) For CF6–80E1 series engines, with fuel manifold, P/Ns 1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01, with tube (block) clamp, P/N 1153M26G15, refer to Table 2 to paragraph (e) of this AD, accomplish the initial inspections of the fuel manifold and tube (block) clamp, and replacement of the fuel manifold and tube (block) clamp, if required based on inspection results, in accordance with paragraph 3.A of GE SB CF6–80E1 S/B 73– 0121, dated July 2, 2013. (5) Thereafter, inspect fuel manifold, P/Ns 1303M31G12, 1303M32G12, 2420M70G01, and 2420M71G01, within every 7,500 flight hours (FH) since the last inspection, in accordance with paragraphs (e)(3) and (e)(4) of this AD. TABLE 2 TO PARAGRAPH (E)—FUEL MANIFOLD AND TUBE (BLOCK) CLAMP INSPECTION AND REPLACEMENT CRITERIA If: Then: 1—If the engine is a first run engine or the engine was previously inspected using either of the following: • GE SB CF6–80C2 S/B 73–0414, dated July 2, 2013; • GE SB CF6–80E1 S/B 73–0121 dated July 02, 2013. 2—If the engine has already exceeded the 7,500 FH initial inspection threshold on the effective date of this AD. Then inspect clamps and replace within 7,500 FH TSLI. Then inspect clamps and replace within 3 months after the effective date of this AD. (f) Prohibition Statement (i) Related Information After the effective date of this AD, do not install fuel manifold, P/Ns 1308M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 1303M32G07, 1303M31G08, 1303M32G08, 1308M31G12, 1308M32G12, 2420M70G01, or 2420M71G01, on any engine. (1) For more information about this AD, contact Kasra Sharifi, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01830; phone 781–238–7773; fax: 781–238–7199; email: kasra.sharifi@faa.gov. (2) General Electric Service Bulletin (SB) CF6–80C2 S/B 73–0326, Revision 4, dated December 23, 2009, SB CF6–80E1 S/B 73– 0061, Revision 4, dated December 23, 2009, SB CF6–80C2 S/B 73–0414, dated July 2, 2013, and SB CF6–80E1 S/B 73–0121, dated July 2, 2013, pertain to the subject of this AD and can be obtained from GE using the contact information in paragraph (i)(3) of this AD. (3) For service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: geae.aoc@ge.com. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (g) Definition pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 For the purpose of this AD, an engine shop visit is the induction of an engine into the shop for maintenance involving separation of pairs of major mating engine flanges (lettered flanges), except that the separation of engine flanges solely for the purposes of transporting the engine without subsequent engine maintenance does not constitute an engine shop visit. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. Previously approved AMOCs for AD 2009–05–02 (74 FR 8161, February 24, 2009) remain approved for the corresponding requirements of paragraphs (e)(1) through (e)(5) of this AD. VerDate Mar<15>2010 14:04 Jan 16, 2014 Jkt 232001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Issued in Burlington, Massachusetts, on December, 24, 2013. Frank P. Paskiewicz, Acting Director, Aircraft Certification Service. [FR Doc. 2014–00833 Filed 1–16–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Part 1 [REG–154890–03] RIN 1545–BJ42 Basis in Interests in Tax-Exempt Trusts Internal Revenue Service (IRS), Treasury. ACTION: Notice of proposed rulemaking. AGENCY: This document contains proposed regulations that provide rules for determining a taxable beneficiary’s basis in a term interest in a charitable remainder trust upon a sale or other disposition of all interests in the trust to SUMMARY: E:\FR\FM\17JAP1.SGM 17JAP1

Agencies

[Federal Register Volume 79, Number 12 (Friday, January 17, 2014)]
[Proposed Rules]
[Pages 3139-3142]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-00833]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28413; Directorate Identifier 2007-NE-25-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede airworthiness directives (ADs) 90-26-
01, 91-20-02, and 2009-05-02, which apply to all General Electric 
Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines. Since we 
issued ADs 90-26-01, 91-20-02, and 2009-05-02, we received a report of 
an undercowl fire caused by a manifold high-pressure fuel leak, and 
several additional reports of fuel leaks. This proposed AD would 
require additional repetitive inspections, replacement of tube (block) 
clamp, and inspection of fuel manifolds for wear at each tube (block) 
clamp location. We are proposing this AD to

[[Page 3140]]

prevent failure of the fuel manifold, which could lead to uncontrolled 
engine fire, engine damage, and damage to the airplane.

DATES: We must receive comments on this proposed AD by March 3, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: geae.aoc@ge.com. You 
may view this service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2007-
28413; or in person at the Docket Management Facility between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Office (phone: 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Kasra Sharifi, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA. 01830; phone 781-238-7773; 
fax: 781-238-7199; email: kasra.sharifi@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28413; Directorate Identifier 2007-NE-25-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 20, 1990, we issued AD 90-26-01 (55 FR 49611, November 
30, 1990), for GE CF6-80C2 series turbofan engines. That AD requires 
replacing fuel manifold, part numbers (P/Ns) 1303M31G04 and 1303M32G04, 
within 30 calendar days after the effective date of the AD. That AD 
resulted from a report of an engine fire.
    On November 15, 1991, we issued AD 91-20-02 (56 FR 55231, October 
25, 1991), for the same engines. That AD requires replacing fuel 
manifold, P/Ns 1303M31G06, 1303M32G06, 1303M31G07, 1303M32G07, 
1303M31G08, and 1303M32G08, at the next engine removal, but no later 
than June 30, 1993. That AD also resulted from a report of an engine 
fire.
    On March 31, 2009, we issued AD 2009-05-02 (74 FR 8161, February 
24, 2009), for GE CF6-80C2 and CF6-80E1 series turbofan engines with 
fuel manifolds, P/Ns 1303M31G12 and 1303M32G12, installed in drainless 
fuel manifold assemblies. That AD requires removing the loop clamps 
that hold the fuel manifold to the compressor rear frame damper 
brackets, inspecting the fuel manifold for wear at each clamp location, 
and replacing the clamps with new zero-time parts. That AD also 
requires revising the Airworthiness Limitations Section to require 
repetitive fuel manifold inspection and loop clamp replacement. That AD 
resulted from reports of fuel leaks during engine operation.
    We issued these ADs to prevent failure of the fuel manifold, which 
could lead to uncontrolled engine fire, engine damage, and damage to 
the airplane. We are superseding these ADs to eliminate potentially 
confusing and contradictory requirements in these ADs. This proposed AD 
expands the inspection mandated by AD 2009-05-02 and it expands the 
list of banned fuel manifolds mandated by AD 90-26-01 and AD 91-20-02.

Actions Since Previous ADs Were Issued

    Since we issued AD 90-26-01 (55 FR 49611, November 30, 1990); AD 
91-20-02 (56 FR 55231, October 25, 1991); and AD 2009-05-02 (74 FR 
8161, February 24, 2009); we received a report of an undercowl fire 
caused by a fuel manifold high-pressure fuel leak in engine model CF6-
80C2, and several additional reports of fuel leaks; four in the CF6-
80C2 and one in the CF6-80E1 model engine.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 90-26-01 (55 
FR 49611, November 30, 1990); and AD 91-20-02 (56 FR 55231, October 25, 
1991); to remove certain fuel manifold P/Ns, and the requirements of AD 
2009-05-02 (74 FR 8161, February 24, 2009); to inspect certain fuel 
manifold P/Ns and replace certain consumable components. This proposed 
AD would add a requirement to inspect an additional fuel manifold 
configuration and replacement of certain loop clamps. This proposed AD 
would also require repetitive inspection and replacement of tube 
(block) clamp, and inspection of the fuel manifold for wear at each 
tube (block) clamp location. This proposed AD would also require 
removing certain drainless fuel manifold assembly P/Ns from service.

Costs of Compliance

    We estimate that this proposed AD would affect 1,126 engines 
installed on airplanes of U.S. registry. We also estimate that required 
parts cost about $34,894 per engine. We also estimate that is would 
take about 6 hours to accomplish the actions required by this AD. The 
average labor rate is $85 per hour. Based on these figures, we estimate 
the total cost of the proposed AD to U.S. operators to be $39,864,904.

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,

[[Page 3141]]

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 proposed 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),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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:
0
a. Removing airworthiness directive (AD) 90-26-01 (55 FR 49611, 
November 30, 1990); AD 91-20-02 (56 FR 55231, October 25, 1991); and AD 
2009-05-02 (74 FR 8161, February 24, 2009); and
0
b. Adding the following new AD:

General Electric Company: Docket No. FAA-2007-28413; Directorate 
Identifier 2007-NE-25-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by March 3, 
2014.

(b) Affected ADs

    This AD supersedes AD 90-26-01 (55 FR 49611, November 30, 1990); 
AD 91-20-02 (56 FR 55231, October 25, 1991); and AD 2009-05-02 (74 
FR 8161, February 24, 2009).

(c) Applicability

    This AD applies to all General Electric Company (GE) CF6-80C2 
and CF6-80E1 turbofan engines with fuel manifold, part numbers (P/
Ns) 1303M31G04,1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 
1303M32G07, 1303M31G08, 1303M32G08,1308M31G12, 1308M32G12, 
2420M70G01, and 2420M71G01, installed.

(d) Unsafe Condition

    This AD was prompted by a report of an undercowl fire caused by 
a fuel manifold high-pressure fuel leak, and several additional 
reports of fuel leaks. We are issuing this AD to prevent failure of 
the fuel manifold, which could lead to uncontrolled engine fire, 
engine damage, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Fuel Manifold Removal.
    (i) For CF6-80C2 and CF6-80E1 series engines, before further 
flight after the effective date of this AD, remove fuel manifold, P/
Ns 1303M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 
1303M32G07, 1303M31G08, and 1303M32G08, from service.
    (ii) For CF6-80C2 and CF6-80E1 series engines, at the next 
engine shop visit after effective date of this AD, remove fuel 
manifold, P/Ns 1303M31G12, 1303M32G12, 2420M70G01, and 2420M71G01, 
from service.
    (2) Fuel Manifold, Loop Clamp, and Tube (Block) Clamp Inspection 
and Replacement--Drainless Assembly.
    (i) For CF6-80C2 series engines, with fuel manifold, P/N 
1303M31G12 or 1303M32G12, installed, refer to Table 1 to paragraph 
(e) of this AD, accomplish the initial inspections of the fuel 
manifold and replacement of the loop clamps in accordance with 
paragraphs 3.A and 3.D of GE Service Bulletin (SB) CF6-80C2 S/B 73-
0326, Revision 4, dated December 23, 2009.
    (ii) For CF6-80C2 series engines, with fuel manifold, P/Ns 
2420M70G01 or 2420M71G01, installed, refer to Table 1 to paragraph 
(e) of this AD, accomplish the initial inspection of the fuel 
manifold and replacement of the loop clamps in accordance with 
paragraphs 3.C and 3.D of GE SB CF6-80C2 S/B 73-0326, Revision 4, 
dated December 23, 2009.
    (iii) For CF6-80E1 series engines, with fuel manifold, P/Ns 
1303M31G12 or 1303M32G12, installed, refer to Table 1 to paragraph 
(e) of this AD, accomplish the initial inspection of the fuel 
manifold and replacement of the loop clamps in accordance with 
paragraphs 3.A and 3.C of GE SB CF6-80E1 S/B 73-0061, Revision 4, 
dated December 23, 2009.
    (iv) For CF6-80E1 series engines, with fuel manifold P/Ns 
2420M70G01 or 2420M71G01 installed, refer to Table 1 to paragraph 
(e) of this AD, accomplish the initial inspection of the fuel 
manifold and replacement of the loop clamps in accordance with 
paragraphs 3.B and 3.C of GE SB CF6-80E1 S/B 73-0061, Revision 4, 
dated December 23, 2009.
    (v) Thereafter, inspect fuel manifolds P/Ns 1303M31G12, 
1303M32G12, 2420M70G01, and 2420M71G01 installed, within every 7,500 
flight hours (FH) since the last inspection, in accordance with 
paragraphs (e)(2)(i) through (e)(2)(iv) of this AD.

    Table 1 to Paragraph (e)--Fuel Manifold Inspection and Loop Clamp
                   Replacement and Inspection Criteria
------------------------------------------------------------------------
                  If:                                 Then:
------------------------------------------------------------------------
1--If the engine was previously
 inspected using any of the following:
     GE SB CF6-80C2 SB 73-0326   Then inspect fuel manifold and
     R04, Revision 4, dated December      replace clamps within 7,500
     23, 2009;                            flight hours (FH) time-since-
                                          last-inspection (TSLI) or
                                          within 6 months after the
                                          effective date of this AD,
                                          whichever occurs first.
     GE SB CF6-80C2 SB 73-0326,
     Revision 3, dated April 24, 2009;
     GE SB CF6-80E1 SB 73-0061
     R04, Revision 4, dated December
     23, 2009 or;
     GE SB CF6-80E1 SB 73-0061,
     Revision 3, dated April, 24, 2009.
2--If the loop clamps installed at last
 shop visit were previously used or of
 unknown heritage or the engine was
 previously inspected using either of
 the following:

[[Page 3142]]

 
     GE CF6-80C2 SB 73-0326,     Then inspect fuel manifold and
     Revision 2, dated August 30, 2007    replace clamps within 1,750 FH
     or earlier;                          time-since-last-shop-visit or
                                          within 4 months after the
                                          effective date of this AD,
                                          whichever occurs first.
     GE CF6-80E1 SB 73-0061,
     Revision 2, dated August 30, 2007
     or earlier.
3--If the engine is a first-run engine,  Then inspect fuel manifold and
 an engine with zero-time, or has new     replace clamps within 7,500 FH
 loop clamps previously installed on-     time-since-new or since zero-
 wing or at shop visit.                   time that new loop clamps were
                                          installed.
4--If the engine has already exceeded    Then inspect fuel manifold and
 the 1,750 FH initial inspection          replace clamps within 4,500 FH
 threshold on the effective date of       TSLI or 4 months after the
 this AD but has fewer than 4,500         effective date of this AD,
 flight hours TSLI.                       whichever occurs first.
5--If the engine has already exceeded    Then inspect fuel manifold and
 the 4,500 FH initial inspection          replace clamps within 4 months
 threshold on the effective date of       after the effective date of
 this AD.                                 this AD.
------------------------------------------------------------------------

    (3) For CF6-80C2 series engines, with fuel manifold, P/Ns 
1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01, with tube (block) 
clamp, P/N 1153M26G15, refer to Table 2 to paragraph (e) of this AD, 
accomplish the initial inspection of the fuel manifold and tube 
(block) clamp, and replacement of the fuel manifold and tube (block) 
clamp, if required based on inspection results, in accordance with 
paragraph 3.A of GE SB CF6-80C2 S/B 73-0414, dated July 2, 2013.
    (4) For CF6-80E1 series engines, with fuel manifold, P/Ns 
1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01, with tube (block) 
clamp, P/N 1153M26G15, refer to Table 2 to paragraph (e) of this AD, 
accomplish the initial inspections of the fuel manifold and tube 
(block) clamp, and replacement of the fuel manifold and tube (block) 
clamp, if required based on inspection results, in accordance with 
paragraph 3.A of GE SB CF6-80E1 S/B 73-0121, dated July 2, 2013.
    (5) Thereafter, inspect fuel manifold, P/Ns 1303M31G12, 
1303M32G12, 2420M70G01, and 2420M71G01, within every 7,500 flight 
hours (FH) since the last inspection, in accordance with paragraphs 
(e)(3) and (e)(4) of this AD.

     Table 2 to Paragraph (e)--Fuel Manifold and Tube (Block) Clamp
                   Inspection and Replacement Criteria
------------------------------------------------------------------------
                  If:                                 Then:
------------------------------------------------------------------------
1--If the engine is a first run engine
 or the engine was previously inspected
 using either of the following:
     GE SB CF6-80C2 S/B 73-      Then inspect clamps and replace
     0414, dated July 2, 2013;            within 7,500 FH TSLI.
     GE SB CF6-80E1 S/B 73-0121
     dated July 02, 2013.
2--If the engine has already exceeded    Then inspect clamps and replace
 the 7,500 FH initial inspection          within 3 months after the
 threshold on the effective date of       effective date of this AD.
 this AD.
------------------------------------------------------------------------

(f) Prohibition Statement

    After the effective date of this AD, do not install fuel 
manifold, P/Ns 1308M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 
1303M31G07, 1303M32G07, 1303M31G08, 1303M32G08, 1308M31G12, 
1308M32G12, 2420M70G01, or 2420M71G01, on any engine.

(g) Definition

    For the purpose of this AD, an engine shop visit is the 
induction of an engine into the shop for maintenance involving 
separation of pairs of major mating engine flanges (lettered 
flanges), except that the separation of engine flanges solely for 
the purposes of transporting the engine without subsequent engine 
maintenance does not constitute an engine shop visit.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. Previously approved AMOCs for AD 2009-05-02 (74 FR 8161, 
February 24, 2009) remain approved for the corresponding 
requirements of paragraphs (e)(1) through (e)(5) of this AD.

(i) Related Information

    (1) For more information about this AD, contact Kasra Sharifi, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01830; phone 781-238-7773; fax: 781-238-7199; email: 
kasra.sharifi@faa.gov.
    (2) General Electric Service Bulletin (SB) CF6-80C2 S/B 73-0326, 
Revision 4, dated December 23, 2009, SB CF6-80E1 S/B 73-0061, 
Revision 4, dated December 23, 2009, SB CF6-80C2 S/B 73-0414, dated 
July 2, 2013, and SB CF6-80E1 S/B 73-0121, dated July 2, 2013, 
pertain to the subject of this AD and can be obtained from GE using 
the contact information in paragraph (i)(3) of this AD.
    (3) For service information identified in this AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: geae.aoc@ge.com.
    (4) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.

    Issued in Burlington, Massachusetts, on December, 24, 2013.
Frank P. Paskiewicz,
Acting Director, Aircraft Certification Service.
[FR Doc. 2014-00833 Filed 1-16-14; 8:45 am]
BILLING CODE 4910-13-P

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