2014-21-01: Fuel manifold

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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: 0 a. Removing airworthiness directive (AD) 90-26-01, Amendment 39-6810 (55 FR 49611, November 30, 1990); AD 91-20-02, Amendment 39-8036 (56 FR 55231, October 25, 1991); and AD 2009-05-02, Amendment 39-15826 (74 FR 8161, February 24, 2009); and 0 b. Adding the following new AD: 2014-21-01 General Electric Company: Amendment 39-17993; Docket No. FAA-2007-28413; Directorate Identifier 2007-NE-25-AD. (a) Effective Date This AD is effective November 28, 2014. (b) Affected ADs This AD supersedes AD 90-26-01, Amendment 39-6810 (55 FR 49611, November 30, 1990); AD 91-20-02, Amendment 39-8036 (56FR 55231, October 25, 1991); and AD 2009-05-02, Amendment 39-15826, (74 FR 8161, February 24, 2009). (c) Applicability This AD applies to all General Electric Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines with fuel manifold, part number (P/N) 1303M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 1303M32G07, 1303M31G08, 1303M32G08, 1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01, installed. (d) Unsafe Condition This AD was prompted by a report of an under-cowl 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) After the effective date of this AD, do not return to service any CF6-80C2 or CF6-80E1 series engine with fuel manifold P/ N 1303M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 1303M32G07, 1303M31G08, or 1303M32G08, installed. (ii) At the next engine shop visit after the effective date of this AD, remove from service fuel manifold P/Ns 1303M31G12, 1303M32G12, 2420M70G01, and 2420M71G01. (2) Fuel Manifold, Loop Clamp, and Tube (Block) Clamp Initial and Repetitive Inspection and Replacement. (i) For CF6-80C2 and CF680E1 series engines, with fuel manifold, P/N 1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01 installed, inspect the fuel manifold and replace if required by inspection results, and replace the loop clamps as follows: (A) For CF6-80C2 series engines, use paragraphs 3.A, 3.C, and 3.D of GE CF6-80C2 Service Bulletin (SB) No. S/B 73-0326 R04, Revision 4, dated December 23, 2009, to do the inspection and replacements. (B) For CF6-80E1 series engines, use paragraphs 3.A, 3.B, and 3.C of GE CF6-80E1 SB No. S/B 73-0061 R04, Revision 4, dated December 23, 2009, to do the inspection and replacements. (C) Compliance time for fuel manifold inspection and loop clamp replacement: (1) If the engine is a first-run engine, inspect the fuel manifold and replace the loop clamps within 7,500 flight hours (FH) time-since-new (TSN). (2) If the engine's fuel manifold was ever inspected and new loop clamps were previously installed, inspect the fuel manifold and replace the loop clamps within 7,500 FH time-since-last-inspection (TSLI). (3) If the engine's fuel manifold was not inspected, new loop clamps were not installed, or it is unknown when the loop clamps were installed, inspect the fuel manifold and replace the loop clamps within 1,750 FH time-since-last-shop-visit or within 4 months after the effective date of this AD, whichever occurs later. (ii) For CF6-80C2 and CF6-80E1 series engines, with fuel manifold, P/N 1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01, with tube (block) clamp, P/N 1153M26G15, installed, inspect fuel manifold and tube (block) clamps, and replace if required by inspection results, as follows: (A) For CF6-80C2 series engines, use paragraphs 3.A.(1) through 3.A.(8) and 3.C.(1) through 3.C.(2) of GE CF6-80C2 SB No. S/B 73- 0414, Revision 1, dated May 29, 2014, to do the inspection. (B) For CF6-80E1 series engines, use paragraphs 3.A.(1) through 3.A.(6) and 3.C.(1) [[Page 63311]] through 3.C.(2) of GE CF6-80E1 SB No. S/B 73-0121, Revision 1, dated May 29, 2014, to do the inspection. (C) Compliance time for fuel manifold and tube (block) clamp inspection: (1) If the engine is a first-run engine, inspect the fuel manifold and tube (block) clamps within 7,500 FH TSN or within 3 months after the effective date of this AD, whichever occurs later. (2) If the engine was previously inspected using either of GE CF6-80C2 SB No. S/B 73-0414, Revision 1, dated May 29, 2014, or GE CF6-80E1 SB No. S/B 73-0121, Revision 1, dated May 29, 2014, or earlier versions, then inspect thefuel manifold and tube (block) clamps within 7,500 FH TSLI or within 3 months after the effective date of this AD, whichever occurs later. (3) If the engine is not a first-run engine and was not previously inspected using GE CF6-80C2 SB No. S/B 73-0414, Revision 1, dated May 29, 2014, or GE CF6-80E1 SB No. S/B 73-0121, Revision 1, dated May 29, 2014, or earlier versions, then inspect the fuel manifold and tube (block) clamps within 7,500 FH TSN or within 3 months after the effective date of this AD, whichever occurs later. (iii) Thereafter, inspect fuel manifold, P/Ns 1303M31G12, 1303M32G12, 2420M70G01, and 2420M71G01, and tube (block) clamps, replace if required by inspection results, and replace the loop clamps within every 7,500 FH TSLI, using paragraphs (e)(2)(i)(A), (e)(2)(i)(B), (e)(2)(ii)(A), and (e)(2)(ii)(B) of this AD, as applicable. (f) Definition (1) For the purposes of this AD, an engine shop visit is the induction of an engine into the shop where the separation of a major engine flange occurs, except that induction into the shop for any of the reasons in paragraphs (f)(i) through (f)(iv) of this AD is not an engine shop visit: (i) Induction of an engine into a shop solely for removal of the compressor top or bottom case for airfoil maintenance, or for variable stator vane bushing replacement; (ii) Induction of an engine into a shop solely for replacement of the turbine rear frame; (iii) Induction of an engine into a shop solely for replacement of the accessory gearbox or transfer gearbox, or both; or (iv) Induction of an engine into a shop solely for core vibration trim balance procedure that requires separation of a major engine flange. (2) For the purposes of this AD, a first-run engine is an engine that has not had a shop visit since entering service. (g) Alternative Methods of Compliance (AMOCs) (1) 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. (2) Previously approved AMOCs for AD 2009-05-02 (74 FR 8161, February 24, 2009) remain approved for the corresponding requirements of paragraphs (e)(1) and (e)(2) of this AD. (h) 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. 01803; phone (781) 238-7773; fax: (781) 238-7199; email: kasra.sharifi@faa.gov. (2) For additional details of the under cowl fire that prompted this AD, refer to National Transportation Safety Board (NTSB) safety recommendation (SR) A-13-028. The NTSB SR is available on the Internet at http://www.ntsb.gov/doclib/recletters/2013/A-13-028.pdf. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a)and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) General Electric Company (GE) CF6-80C2 Service Bulletin (SB) No. 73-0326 R04, Revision 4, dated December 23, 2009. (ii) GE CF6-80C2 SB No. S/B 73-0414, Revision 1, dated May 29, 2014. (iii) GE CF6-80E1 SB No. 73-0061 R04, Revision 4, dated December 23, 2009. (iv) GE CF6-80E1 SB No. S/B 73-0121, Revision 1, dated May 29, 2014. (3) For GE 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. (5) You may view this service information 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.