Airworthiness Directives; The Boeing Company Airplanes, 15667-15671 [2014-06155]

Download as PDF Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 18, 2013; or Section 3.B. or 3.C. of RR Alert NMSB No. RB.211–72–AG971, Revision 1, dated September 27, 2013, to do the inspection. Thereafter, inspect every 1,000 FC. (iv) Perform an inspection of the top core vanes, before exceeding 3,800 FCSN. Use Section 3.C. of RR Alert NMSB No. RB.211– 72–AG971, Revision 1, dated September 27, 2013, to do the inspection. Thereafter, inspect every 3,800 FC. (2) If any inspection required by paragraph (e)(1) of this AD fails, remove the TBH from service. (3) Remove any TBH from service before the TBH exceeds 17,200 FCSN. (f) Credit for Previous Actions (1) If, before the effective date of this AD, you performed inspections and corrective actions using RR Alert NMSB No. RB.211– 72–AG971, dated September 20, 2012 or RR Alert NMSB No. RB.211–72–AH154, dated June 13, 2013; you met the requirements of paragraph (e)(1) of this AD. (2) If, before the effective date of this AD, the last in-shop inspection of the mount lug run-outs was accomplished using Section 3.C. of RR Alert NMSB No. RB.211–72– AG971, dated September 20, 2012, the compliance time interval for the next onwing or in-shop inspection of the fail safe catcher, as required by paragraphs (e)(1)(ii) and (e)(1)(iii) of this AD, may be counted from that last in-shop inspection of the mount lug run-outs. (3) If, before the effective date of this AD, you performed inspections and corrective actions using RR Technical Variance (TV) No. 124801, Issue 2, dated July 4, 2012 or earlier versions; or TV No. 124851, Issue 2, dated July 4, 2012 or earlier versions; you met the requirements of paragraph (e)(1)(i) of this AD. (4) If, before the effective date of this AD, you performed inspections and corrective actions using RR TV No. 132043, Issue 1, dated March 25, 2013 or earlier versions; or TV No. 132217, Issue 5, dated May 23, 2013 or earlier versions; you met the requirements of paragraphs (e)(1)(ii) and (e)(1)(iii) of this AD. (5) Any inspections and corrective actions performed are not terminating action for the repetitive inspections required by paragraph (e)(1) of this AD. mstockstill on DSK4VPTVN1PROD with RULES (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. (h) Related Information (1) For more information about this AD, contact Anthony W. Cerra, Jr., Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7128; fax: 781–238– 7199; email: anthony.cerra@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2013–0240 (correction), dated October 4, 2013, for more information. You may examine the MCAI in the AD docket on the Internet at http:// VerDate Mar<15>2010 15:59 Mar 20, 2014 Jkt 232001 www.regulations.gov by searching for and locating it in Docket No. FAA–2013–1015. (3) RR Repeater TV No. 132043, Repeater TV No. 132217, TV No. 124801, and TV No. 124851, which are not incorporated by reference in this AD, can be obtained from RR, using the contact information in paragraph (i)(3) of this AD. (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. (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) Rolls-Royce plc Alert Non-Modification Service Bulletin (NMSB) No. RB.211–72– AG971, Revision 1, dated September 27, 2013. (ii) Rolls-Royce plc Alert NMSB No. RB.211–72–AH154, Revision 1, dated June 18, 2013. (3) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332– 242424; fax: 011–44–1332–245418, or email: http://www.rolls-royce.com/contact/civil_ team.jsp. (4) You may view this service information at 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/ibrlocations.html. Issued in Burlington, Massachusetts, on February 27, 2014. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2014–04952 Filed 3–20–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0331; Directorate Identifier 2011–NM–170–AD; Amendment 39–17792; AD 2014–05–19] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 ACTION: 15667 Final rule. We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–200B, 747–200F, 747–300, 747SP, 747–400, and 747–400F series airplanes equipped with Rolls-Royce RB211–524 engines; and certain Model 767–300 series airplanes equipped with Rolls-Royce RB211–524 engines. This AD was prompted by multiple reports of uncommanded thrust reverser unlock events. This AD requires replacing certain relays and relay sockets, and doing wiring changes. For certain airplanes, this AD also requires installing new relay panels, and removing and installing certain components. Additionally, this AD requires, for certain airplanes, accomplishing concurrent actions, which include installing an additional locking system on the thrust reversers and modifying system wiring for inflight fault indications of the thrust reverser system. We are issuing this AD to prevent an uncommanded thrust reverser deployment during takeoff or in flight, resulting in decreased airplane control and performance, possible runway excursions, and failure to climb. DATES: This AD is effective April 25, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of April 25, 2014. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of February 18, 2000 (65 FR 5222, February 3, 2000). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of September 14, 1994 (59 FR 41647, August 15, 1994). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; by searching for and locating Docket No. FAA–2013– 0331; or in person at the Docket E:\FR\FM\21MRR1.SGM 21MRR1 15668 Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Tung Tran, Aerospace Engineer, Propulsion Branch, ANM–140S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6505; fax: 425–917–6590; email: Tung.Tran@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747–200B, 747–200F, 747–300, 747SP, 747–400, and 747–400F series airplanes equipped with Rolls-Royce RB211–524 engines; and certain Model 767–300 series airplanes equipped with Rolls-Royce RB211–524 engines. The NPRM published in the Federal Register on April 17, 2013 (78 FR 22802). The NPRM was prompted by multiple reports of uncommanded thrust reverser unlock events. The NPRM proposed to require replacing certain relays and relay sockets, and doing wiring changes. For certain airplanes, the NPRM proposed to require installing new relay panels, and removing and installing certain components. Additionally, the NPRM proposed to require, for certain airplanes, accomplishing concurrent actions, which include installing an additional locking system on the thrust reversers, installing an additional locking gearbox on each engine and modifying system wiring for in-flight fault indications of the thrust reverser system, and installing a second locking gearbox system on the thrust reversers. We are issuing this AD to prevent an uncommanded thrust reverser deployment during takeoff or in flight, resulting in decreased airplane control and performance, possible runway excursions, and failure to climb. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (78 FR 22802, April 17, 2013) and the FAA’s response to each comment. Support for the NPRM (78 FR 22802, April 17, 2013) Boeing stated that it concurred with the contents of the NPRM (78 FR 22802, April 17, 2013). The Air Line Pilots Association International stated that it agrees with the intent of the NPRM (78 FR 22802, April 17, 2013). Request To Specify Thrust Reverser Unit (TRU) Part Numbers Rolls-Royce plc requested that instead of specifying the engine models, we specify the part numbers of the affected TRUs for tracking purposes. Rolls-Royce plc stated that the TRUs are swapped from engine to engine, and AD compliance would be difficult to track unless it is tracked based on the TRUs. We do not agree with the commenter’s request. This final rule only requires changes to the control logic of the thrust reverser by modifying the associated electrical panels on the airplane. There is no requirement for TRU hardware replacement. Therefore, it is unnecessary to specify the part numbers of the affected TRUs in this final rule. We have not changed this final rule in this regard. Statement of Financial Impact Rolls-Royce plc stated that it is likely the actions required by the NPRM (78 FR 22802, April 17, 2013) will have a significant financial affect upon Middle Eastern and Far East operations. RollsRoyce plc did not request any change to the NPRM in this regard. The commenter did not provide specific information to substantiate why Middle Eastern and Far East operations would be uniquely affected. The Costs of Compliance paragraph in this final rule is based on estimates provided in the service information and is an estimate of costs incurred by United States operators. We have not changed this final rule in this regard. Changes to This Final Rule We clarified the required actions specified in the SUMMARY section of this final rule by removing the wording ‘‘installing an additional locking system on the thrust reversers’’ and ‘‘installing a second locking gearbox system on the thrust reversers.’’ These actions are included in the phrase ‘‘installing an additional locking system on the thrust reversers.’’ No change has been made to the actions required by this final rule. We revised paragraph (b) of this final rule to indicate that this final rule affects the requirements of AD 2000–01– 05, Amendment 39–11502 (65 FR 1051, January 7, 2000). We revised paragraph (h)(2) of this final rule to clarify that the installation of an additional gearbox is on the thrust reverser of each engine, rather than on each engine. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 22802, April 17, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 22802, April 17, 2013). Costs of Compliance We estimate that this AD affects 1 airplane of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS mstockstill on DSK4VPTVN1PROD with RULES Action Labor cost Parts cost Cost per product Replacement and wiring change for Model 747–200B, 747–200F, 747– 300, and 747SP series airplanes (1 U.S.-registered airplane). 30 work-hours × $85 per hour = $2,550 $4,289 .................... $6,839 .................... VerDate Mar<15>2010 15:59 Mar 20, 2014 Jkt 232001 PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 E:\FR\FM\21MRR1.SGM 21MRR1 Cost on U.S. operators $6,839 15669 Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations ESTIMATED COSTS—Continued Cost on U.S. operators Action Labor cost Parts cost Cost per product Removal, installations, and wiring changes for Model 747–400 and 747– 400F series airplanes (0 U.S.-registered airplanes). Replacements and wiring changes for Model 767–300 series airplanes (0 U.S.-registered airplanes). Up to 90 work-hours × $85 per hour = $7,650. Up to $16,607 ........ Up to $24,257 ........ 0 Up to 32 work-hours × $85 per hour = $2,720. Up to $2,245 .......... Up to $4,965 .......... 0 We estimate the following costs to do any necessary concurrent requirements. We have no way of determining the number of aircraft that might need accomplishment of the concurrent requirements. CONCURRENT COSTS Cost per product Action Labor cost Installation of an additional locking system for Model 747–200B, 747–200F, 747–300, and 747SP series airplanes. Installation of an additional locking gearbox on each engine and modification of the system wiring for Model 747–400 and 747–400F series airplanes. Installation of a second locking gearbox system for Model 767–300 series airplanes. 336 work-hours × $85 per hour = $28,560 .................. $62,674 $91,234 185 work-hours × $85 per hour = $15,725 .................. 72,860 88,585 754 work-hours × $85 per hour = $64,090 .................. 0 64,090 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. mstockstill on DSK4VPTVN1PROD with RULES Regulatory Findings 15:59 Mar 20, 2014 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 FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES Jkt 232001 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 (AD): ■ 2014–05–19 The Boeing Company: Amendment 39–17792; Docket No. FAA–2013–0331; Directorate Identifier 2011–NM–170–AD. PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 (a) Effective Date This AD is effective April 25, 2014. (b) Affected ADs This AD affects the requirements of AD 2000–01–05, Amendment 39–11502 (65 FR 1051, January 7, 2000). (c) Applicability This AD applies to The Boeing Company airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, and equipped with RollsRoyce RB211–524 engines. (1) Model 747–200B, 747–200F, 747–300, and 747SP series airplanes, as identified in Boeing Service Bulletin 747–78–2178, Revision 1, dated August 4, 2011. (2) Model 747–400 and 747–400F series airplanes, as identified in Boeing Service Bulletin 747–78–2180, Revision 2, dated November 11, 2011. (3) Model 767–300 series airplanes, as identified in Boeing Service Bulletin 767–78– 0096, Revision 1, dated December 10, 2009. (d) Subject 1. The authority citation for part 39 continues to read as follows: ■ 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: VerDate Mar<15>2010 (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), (3) Will not affect intrastate aviation in Alaska, 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. Parts cost Joint Aircraft System/Component (JASC) Code 7830, Engine Thrust Reverser. (e) Unsafe Condition This AD was prompted by multiple reports of uncommanded thrust reverser unlock events, three of which had all three locks disengaged. We are issuing this AD to prevent an uncommanded thrust reverser deployment during takeoff or in flight resulting in decreased airplane control and performance, possible runway excursions, and failure to climb. E:\FR\FM\21MRR1.SGM 21MRR1 15670 Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations (f) Compliance Comply with this AD within the compliance times specified, unless already done. mstockstill on DSK4VPTVN1PROD with RULES (g) Replacement Within 60 months after the effective date of this AD: Do the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, as applicable. (1) For Model 747–200B, 747–200F, 747– 300, and 747SP series airplanes: Replace relays and relay sockets in the P252 and P253 panels with new relays and relay sockets, and do wiring changes, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–78–2178, Revision 1, dated August 4, 2011. (2) For Model 747–400 and 747–400F series airplanes: Install the components removed from the existing P252 and P253 panels, install new relays and relay sockets, and do wiring changes on the new P252 and P253 relay panels, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–78–2180, Revision 2, dated November 11, 2011. (3) For Model 767–300 series airplanes: Replace relays and relay sockets in the P36 and P37 panels with new relays and relay sockets, and do wiring changes in the P33, P36, and P37 panels, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767–78–0096, Revision 1, dated December 10, 2009. (h) Concurrent Requirements (1) For Model 747–200B, 747–200F, 747– 300, and 747SP series airplanes: Prior to or concurrently with accomplishing the actions required by paragraph (g)(1) of this AD, install an additional locking system on the thrust reversers, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–78–2156, Revision 1, dated August 30, 2001. Accomplishing this installation is a method of compliance with the installation required by paragraph (c) of AD 2000–01–05, Amendment 39–11502 (65 FR 1051, January 7, 2000). (2) For Model 747–400 and 747–400F series airplanes identified as Group 1, 2, 3, 4, 7, 8, or 9 airplanes in Boeing Service Bulletin 747–78–2180, Revision 2, dated November 11, 2011: Prior to or concurrently with accomplishing the actions required by paragraph (g)(2) of this AD, install an additional locking gearbox on the thrust reversers of each engine and modify system wiring for in-flight fault indications of the thrust reverser system, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–78–2158, Revision 2, dated July 29, 1999. Note 1 to paragraph (h)(2) of this AD: Paragraph (a)(1) of AD 2000–02–22, Amendment 39–11540 (65 FR 5222, February 3, 2000), refers to Boeing Service Bulletin 747–78–2158, Revision 2, dated July 29, 1999, as the appropriate source of service information for accomplishing the installation required by that paragraph. (3) For Model 767–300 series airplanes identified as Group 2 airplanes in Boeing Service Bulletin 767–78–0096, Revision 1, dated December 10, 2009: Prior to or VerDate Mar<15>2010 15:59 Mar 20, 2014 Jkt 232001 concurrently with accomplishing the actions required by paragraph (g)(3) of this AD, install a second locking gearbox system on the thrust reversers, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767–78–0059, Revision 3, dated January 20, 1994. Note 2 to paragraph (h)(3) of this AD: Paragraph (c) of AD 94–17–03, Amendment 39–8998 (59 FR 41647, August 15, 1994), refers to Boeing Service Bulletin 767–78– 0059, Revision 3, dated January 20, 1994, as an appropriate source of service information for accomplishing the installation required by that paragraph. (i) Credit for Previous Actions (1) This paragraph provides credit for the requirements of paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 747–78–2178, dated January 22, 2009, which is not incorporated by reference in this AD. (2) This paragraph provides credit for the requirements of paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 747–78–2180, dated April 10, 2008, which is not incorporated by reference in this AD. (3) This paragraph provides credit for the requirements of paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 747–78–2180, Revision 1, dated November 11, 2010, which is not incorporated by reference in this AD. (4) This paragraph provides credit for the requirements of paragraph (g)(3) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 767–78–0096, dated August 7, 2008, which is not incorporated by reference in this AD. (5) This paragraph provides credit for the requirements of paragraph (h)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 747–78–2156, dated October 31, 1996, which was incorporated by reference in AD 99–18–03, Amendment 39–11269 (64 FR 47365, August 31, 1999). Note 3 to paragraph (i)(5) of this AD: Paragraph (c) of AD 2000–01–05, Amendment 39–11502 (65 FR 1051, January 7, 2000), refers to Boeing Service Bulletin 747–78–2156, dated October 31, 1996, as the appropriate source of service information for accomplishing the installation required by that paragraph. (6) This paragraph provides credit for the requirements of paragraph (h)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 747–78–2158, Revision 1, dated January 22, 1998, which is not incorporated by reference in this AD. Note 4 to paragraph (i)(6) of this AD: In AD 2000–02–22, Amendment 39–11540 (65 FR 5222, February 3, 2000), Note 2 to paragraph (a)(1) of AD 2000–02–22 refers to Boeing Service Bulletin 747–78–2158, Revision 1, dated January 22, 1998, as a method of compliance for accomplishing the PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 installation required by paragraph (a)(1) of AD 2000–02–22. (7) This paragraph provides credit for the requirements of paragraph (h)(3) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 767–78–0059, Revision 2, dated June 10, 1993, which is not incorporated by reference in this AD, which was incorporated by reference in AD 94–17–03, Amendment 39–8998 (59 FR 41647, August 15, 1994). Note 5 to paragraph (i)(7) of this AD: Paragraph (c) of AD 94–17–03, Amendment 39–8998 (59 FR 41647, August 15, 1994), refers to Boeing Service Bulletin 767–78– 0059, Revision 2, dated June 10, 1993, as an appropriate source of service information for accomplishing the installation required by that paragraph. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information (1) For more information about this AD, contact Tung Tran, Aerospace Engineer, Propulsion Branch, ANM–140S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6505; fax: 425–917– 6590; email: Tung.Tran@faa.gov. (2) Service information identified in this AD that is not incorporated by reference may be obtained at the addresses specified in paragraphs (l)(6) and (l)(7) of this AD. (l) 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. (3) The following service information was approved for IBR on April 25, 2014. (i) Boeing Service Bulletin 747–78–2156, Revision 1, dated August 30, 2001. E:\FR\FM\21MRR1.SGM 21MRR1 Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations (ii) Boeing Service Bulletin 747–78–2178, Revision 1, dated August 4, 2011. (iii) Boeing Service Bulletin 747–78–2180, Revision 2, dated November 11, 2011. (iv) Boeing Service Bulletin 767–78–0096, Revision 1, dated December 10, 2009. (4) The following service information was approved for IBR on February 18, 2000 (65 FR 5222, February 3, 2000). (i) Boeing Service Bulletin 747–78–2158, Revision 2, dated July 29, 1999. (ii) Reserved. (5) The following service information was approved for IBR on September 14, 1994 (59 FR 41647, August 15, 1994). (i) Boeing Service Bulletin 767–78–0059, Revision 3, dated January 20, 1994. (ii) Reserved. (6) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com. (7) You may view this service information at FAA, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (8) You may view this service information that is incorporated by reference 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/ibrlocations.html. Issued in Renton, Washington, on February 19, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–06155 Filed 3–20–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–1023; Directorate Identifier 2013–NM–042–AD; Amendment 39–17797; AD 2014–05–24] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. mstockstill on DSK4VPTVN1PROD with RULES AGENCY: We are superseding Airworthiness Directive (AD) 84–19–01 for certain The Boeing Company Model 747–100, 747–200B, and 747–200F series airplanes. AD 84–19–01 required repetitive inspections for cracking of certain tension ties, and repair and SUMMARY: VerDate Mar<15>2010 15:59 Mar 20, 2014 Jkt 232001 certain modifications if necessary. This new AD requires, for certain airplanes, additional inspections for cracking of the tension tie at body station (BS) 760 or 780, corrective action if necessary, and eventual modification of the tension ties. For all airplanes, this new AD requires repetitive post-modification inspections for cracking of the tension tie at BS 760 or 780, and corrective action if necessary. This AD was prompted by reports of cracking in the BS 760 tension tie as a result of bending due to cabin pressurization. We are issuing this AD to detect and correct tension tie cracking, which could eventually result in in-flight depressurization of the airplane and the inability to withstand current regulatory failsafe loads. DATES: This AD is effective April 25, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 25, 2014. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 1023; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov. PO 00000 Frm 00039 Fmt 4700 Sfmt 4700 15671 SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 84–19–01, Amendment 39–4913 (Docket No. 84– NM–10–AD; 49 FR 36365, September 17, 1984). AD 84–19–01 applied to certain Boeing Model 747–100, 747– 200B, and 747–200F series airplanes. The NPRM published in the Federal Register on December 6, 2013 (78 FR 73457). The NPRM was prompted by reports of cracking in the BS 760 tension tie as a result of bending due to cabin pressurization. The NPRM proposed to continue to require repetitive inspections for cracking of certain tension ties, and repair and certain modifications if necessary. The NPRM also proposed to require, for certain airplanes, additional inspections for cracking of the tension tie at BS 760 or 780, corrective action if necessary, and eventual modification of the tension ties. For all airplanes, the NPRM also proposed to require repetitive postmodification inspections for cracking of the tension tie at BS 760 or 780, and corrective action if necessary. We are issuing this AD to detect and correct tension tie cracking, which could eventually result in in-flight depressurization of the airplane and the inability to withstand current regulatory failsafe loads. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Boeing supported the NPRM (78 FR 73457, December 6, 2013). Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 73457, December 6, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 73457, December 6, 2013). Costs of Compliance We estimate that this AD affects 24 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\21MRR1.SGM 21MRR1

Agencies

[Federal Register Volume 79, Number 55 (Friday, March 21, 2014)]
[Rules and Regulations]
[Pages 15667-15671]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06155]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0331; Directorate Identifier 2011-NM-170-AD; 
Amendment 39-17792; AD 2014-05-19]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-200B, 747-200F, 747-300, 747SP, 747-400, 
and 747-400F series airplanes equipped with Rolls-Royce RB211-524 
engines; and certain Model 767-300 series airplanes equipped with 
Rolls-Royce RB211-524 engines. This AD was prompted by multiple reports 
of uncommanded thrust reverser unlock events. This AD requires 
replacing certain relays and relay sockets, and doing wiring changes. 
For certain airplanes, this AD also requires installing new relay 
panels, and removing and installing certain components. Additionally, 
this AD requires, for certain airplanes, accomplishing concurrent 
actions, which include installing an additional locking system on the 
thrust reversers and modifying system wiring for in-flight fault 
indications of the thrust reverser system. We are issuing this AD to 
prevent an uncommanded thrust reverser deployment during takeoff or in 
flight, resulting in decreased airplane control and performance, 
possible runway excursions, and failure to climb.

DATES: This AD is effective April 25, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of April 25, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
February 18, 2000 (65 FR 5222, February 3, 2000).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
September 14, 1994 (59 FR 41647, August 15, 1994).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; by searching for and locating Docket No. FAA-2013-
0331; or in person at the Docket

[[Page 15668]]

Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this AD, the regulatory 
evaluation, any comments received, and other information. The address 
for the Docket Office (phone: 800-647-5527) is Docket Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Tung Tran, Aerospace Engineer, 
Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office 
(ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6505; fax: 425-917-6590; email: Tung.Tran@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 747-200B, 747-200F, 747-300, 747SP, 747-400, and 747-400F series 
airplanes equipped with Rolls-Royce RB211-524 engines; and certain 
Model 767-300 series airplanes equipped with Rolls-Royce RB211-524 
engines. The NPRM published in the Federal Register on April 17, 2013 
(78 FR 22802). The NPRM was prompted by multiple reports of uncommanded 
thrust reverser unlock events. The NPRM proposed to require replacing 
certain relays and relay sockets, and doing wiring changes. For certain 
airplanes, the NPRM proposed to require installing new relay panels, 
and removing and installing certain components. Additionally, the NPRM 
proposed to require, for certain airplanes, accomplishing concurrent 
actions, which include installing an additional locking system on the 
thrust reversers, installing an additional locking gearbox on each 
engine and modifying system wiring for in-flight fault indications of 
the thrust reverser system, and installing a second locking gearbox 
system on the thrust reversers. We are issuing this AD to prevent an 
uncommanded thrust reverser deployment during takeoff or in flight, 
resulting in decreased airplane control and performance, possible 
runway excursions, and failure to climb.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 22802, April 17, 2013) and the FAA's response to each comment.

Support for the NPRM (78 FR 22802, April 17, 2013)

    Boeing stated that it concurred with the contents of the NPRM (78 
FR 22802, April 17, 2013).
    The Air Line Pilots Association International stated that it agrees 
with the intent of the NPRM (78 FR 22802, April 17, 2013).

Request To Specify Thrust Reverser Unit (TRU) Part Numbers

    Rolls-Royce plc requested that instead of specifying the engine 
models, we specify the part numbers of the affected TRUs for tracking 
purposes. Rolls-Royce plc stated that the TRUs are swapped from engine 
to engine, and AD compliance would be difficult to track unless it is 
tracked based on the TRUs.
    We do not agree with the commenter's request. This final rule only 
requires changes to the control logic of the thrust reverser by 
modifying the associated electrical panels on the airplane. There is no 
requirement for TRU hardware replacement. Therefore, it is unnecessary 
to specify the part numbers of the affected TRUs in this final rule. We 
have not changed this final rule in this regard.

Statement of Financial Impact

    Rolls-Royce plc stated that it is likely the actions required by 
the NPRM (78 FR 22802, April 17, 2013) will have a significant 
financial affect upon Middle Eastern and Far East operations. Rolls-
Royce plc did not request any change to the NPRM in this regard.
    The commenter did not provide specific information to substantiate 
why Middle Eastern and Far East operations would be uniquely affected. 
The Costs of Compliance paragraph in this final rule is based on 
estimates provided in the service information and is an estimate of 
costs incurred by United States operators. We have not changed this 
final rule in this regard.

Changes to This Final Rule

    We clarified the required actions specified in the SUMMARY section 
of this final rule by removing the wording ``installing an additional 
locking system on the thrust reversers'' and ``installing a second 
locking gearbox system on the thrust reversers.'' These actions are 
included in the phrase ``installing an additional locking system on the 
thrust reversers.'' No change has been made to the actions required by 
this final rule.
    We revised paragraph (b) of this final rule to indicate that this 
final rule affects the requirements of AD 2000-01-05, Amendment 39-
11502 (65 FR 1051, January 7, 2000).
    We revised paragraph (h)(2) of this final rule to clarify that the 
installation of an additional gearbox is on the thrust reverser of each 
engine, rather than on each engine.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 22802, April 17, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 22802, April 17, 2013).

Costs of Compliance

    We estimate that this AD affects 1 airplane of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost on U.S.
             Action                     Labor cost            Parts cost       Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Replacement and wiring change    30 work-hours x $85 per  $4,289............  $6,839............          $6,839
 for Model 747-200B, 747-200F,    hour = $2,550.
 747-300, and 747SP series
 airplanes (1 U.S.-registered
 airplane).

[[Page 15669]]

 
Removal, installations, and      Up to 90 work-hours x    Up to $16,607.....  Up to $24,257.....               0
 wiring changes for Model 747-    $85 per hour = $7,650.
 400 and 747-400F series
 airplanes (0 U.S.-registered
 airplanes).
Replacements and wiring changes  Up to 32 work-hours x    Up to $2,245......  Up to $4,965......               0
 for Model 767-300 series         $85 per hour = $2,720.
 airplanes (0 U.S.-registered
 airplanes).
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary concurrent 
requirements. We have no way of determining the number of aircraft that 
might need accomplishment of the concurrent requirements.

                                                Concurrent Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Installation of an additional locking        336 work-hours x $85 per hour =             $62,674         $91,234
 system for Model 747-200B, 747-200F, 747-    $28,560.
 300, and 747SP series airplanes.
Installation of an additional locking        185 work-hours x $85 per hour =              72,860          88,585
 gearbox on each engine and modification of   $15,725.
 the system wiring for Model 747-400 and
 747-400F series airplanes.
Installation of a second locking gearbox     754 work-hours x $85 per hour =                   0          64,090
 system for Model 767-300 series airplanes.   $64,090.
----------------------------------------------------------------------------------------------------------------

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

    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),
    (3) Will not affect intrastate aviation in Alaska, 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.

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 adding the following new airworthiness 
directive (AD):

2014-05-19 The Boeing Company: Amendment 39-17792; Docket No. FAA-
2013-0331; Directorate Identifier 2011-NM-170-AD.

(a) Effective Date

    This AD is effective April 25, 2014.

(b) Affected ADs

    This AD affects the requirements of AD 2000-01-05, Amendment 39-
11502 (65 FR 1051, January 7, 2000).

(c) Applicability

    This AD applies to The Boeing Company airplanes, certificated in 
any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, and equipped with Rolls-Royce RB211-524 engines.
    (1) Model 747-200B, 747-200F, 747-300, and 747SP series 
airplanes, as identified in Boeing Service Bulletin 747-78-2178, 
Revision 1, dated August 4, 2011.
    (2) Model 747-400 and 747-400F series airplanes, as identified 
in Boeing Service Bulletin 747-78-2180, Revision 2, dated November 
11, 2011.
    (3) Model 767-300 series airplanes, as identified in Boeing 
Service Bulletin 767-78-0096, Revision 1, dated December 10, 2009.

(d) Subject

    Joint Aircraft System/Component (JASC) Code 7830, Engine Thrust 
Reverser.

(e) Unsafe Condition

    This AD was prompted by multiple reports of uncommanded thrust 
reverser unlock events, three of which had all three locks 
disengaged. We are issuing this AD to prevent an uncommanded thrust 
reverser deployment during takeoff or in flight resulting in 
decreased airplane control and performance, possible runway 
excursions, and failure to climb.

[[Page 15670]]

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Replacement

    Within 60 months after the effective date of this AD: Do the 
actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD, as applicable.
    (1) For Model 747-200B, 747-200F, 747-300, and 747SP series 
airplanes: Replace relays and relay sockets in the P252 and P253 
panels with new relays and relay sockets, and do wiring changes, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-78-2178, Revision 1, dated August 4, 2011.
    (2) For Model 747-400 and 747-400F series airplanes: Install the 
components removed from the existing P252 and P253 panels, install 
new relays and relay sockets, and do wiring changes on the new P252 
and P253 relay panels, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-78-2180, Revision 2, 
dated November 11, 2011.
    (3) For Model 767-300 series airplanes: Replace relays and relay 
sockets in the P36 and P37 panels with new relays and relay sockets, 
and do wiring changes in the P33, P36, and P37 panels, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 767-
78-0096, Revision 1, dated December 10, 2009.

(h) Concurrent Requirements

    (1) For Model 747-200B, 747-200F, 747-300, and 747SP series 
airplanes: Prior to or concurrently with accomplishing the actions 
required by paragraph (g)(1) of this AD, install an additional 
locking system on the thrust reversers, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-78-2156, 
Revision 1, dated August 30, 2001. Accomplishing this installation 
is a method of compliance with the installation required by 
paragraph (c) of AD 2000-01-05, Amendment 39-11502 (65 FR 1051, 
January 7, 2000).
    (2) For Model 747-400 and 747-400F series airplanes identified 
as Group 1, 2, 3, 4, 7, 8, or 9 airplanes in Boeing Service Bulletin 
747-78-2180, Revision 2, dated November 11, 2011: Prior to or 
concurrently with accomplishing the actions required by paragraph 
(g)(2) of this AD, install an additional locking gearbox on the 
thrust reversers of each engine and modify system wiring for in-
flight fault indications of the thrust reverser system, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-78-2158, Revision 2, dated July 29, 1999.

    Note 1 to paragraph (h)(2) of this AD:  Paragraph (a)(1) of AD 
2000-02-22, Amendment 39-11540 (65 FR 5222, February 3, 2000), 
refers to Boeing Service Bulletin 747-78-2158, Revision 2, dated 
July 29, 1999, as the appropriate source of service information for 
accomplishing the installation required by that paragraph.

    (3) For Model 767-300 series airplanes identified as Group 2 
airplanes in Boeing Service Bulletin 767-78-0096, Revision 1, dated 
December 10, 2009: Prior to or concurrently with accomplishing the 
actions required by paragraph (g)(3) of this AD, install a second 
locking gearbox system on the thrust reversers, in accordance with 
the Accomplishment Instructions of Boeing Service Bulletin 767-78-
0059, Revision 3, dated January 20, 1994.

    Note 2 to paragraph (h)(3) of this AD:  Paragraph (c) of AD 94-
17-03, Amendment 39-8998 (59 FR 41647, August 15, 1994), refers to 
Boeing Service Bulletin 767-78-0059, Revision 3, dated January 20, 
1994, as an appropriate source of service information for 
accomplishing the installation required by that paragraph.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the requirements of 
paragraph (g)(1) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2178, dated January 22, 2009, which is not incorporated by reference 
in this AD.
    (2) This paragraph provides credit for the requirements of 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2180, dated April 10, 2008, which is not incorporated by reference 
in this AD.
    (3) This paragraph provides credit for the requirements of 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2180, Revision 1, dated November 11, 2010, which is not incorporated 
by reference in this AD.
    (4) This paragraph provides credit for the requirements of 
paragraph (g)(3) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 767-78-
0096, dated August 7, 2008, which is not incorporated by reference 
in this AD.
    (5) This paragraph provides credit for the requirements of 
paragraph (h)(1) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2156, dated October 31, 1996, which was incorporated by reference in 
AD 99-18-03, Amendment 39-11269 (64 FR 47365, August 31, 1999).

    Note 3 to paragraph (i)(5) of this AD:  Paragraph (c) of AD 
2000-01-05, Amendment 39-11502 (65 FR 1051, January 7, 2000), refers 
to Boeing Service Bulletin 747-78-2156, dated October 31, 1996, as 
the appropriate source of service information for accomplishing the 
installation required by that paragraph.

    (6) This paragraph provides credit for the requirements of 
paragraph (h)(2) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2158, Revision 1, dated January 22, 1998, which is not incorporated 
by reference in this AD.

    Note 4 to paragraph (i)(6) of this AD:  In AD 2000-02-22, 
Amendment 39-11540 (65 FR 5222, February 3, 2000), Note 2 to 
paragraph (a)(1) of AD 2000-02-22 refers to Boeing Service Bulletin 
747-78-2158, Revision 1, dated January 22, 1998, as a method of 
compliance for accomplishing the installation required by paragraph 
(a)(1) of AD 2000-02-22.

    (7) This paragraph provides credit for the requirements of 
paragraph (h)(3) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 767-78-
0059, Revision 2, dated June 10, 1993, which is not incorporated by 
reference in this AD, which was incorporated by reference in AD 94-
17-03, Amendment 39-8998 (59 FR 41647, August 15, 1994).

    Note 5 to paragraph (i)(7) of this AD:  Paragraph (c) of AD 94-
17-03, Amendment 39-8998 (59 FR 41647, August 15, 1994), refers to 
Boeing Service Bulletin 767-78-0059, Revision 2, dated June 10, 
1993, as an appropriate source of service information for 
accomplishing the installation required by that paragraph.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the ACO, send it to the attention of the 
person identified in paragraph (k) of this AD. Information may be 
emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
that has been authorized by the Manager, Seattle ACO, to make those 
findings. For a repair method to be approved, the repair must meet 
the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(k) Related Information

    (1) For more information about this AD, contact Tung Tran, 
Aerospace Engineer, Propulsion Branch, ANM-140S, Seattle Aircraft 
Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6505; fax: 425-917-6590; email: 
Tung.Tran@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (l)(6) and (l)(7) of this AD.

(l) 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.
    (3) The following service information was approved for IBR on 
April 25, 2014.
    (i) Boeing Service Bulletin 747-78-2156, Revision 1, dated 
August 30, 2001.

[[Page 15671]]

    (ii) Boeing Service Bulletin 747-78-2178, Revision 1, dated 
August 4, 2011.
    (iii) Boeing Service Bulletin 747-78-2180, Revision 2, dated 
November 11, 2011.
    (iv) Boeing Service Bulletin 767-78-0096, Revision 1, dated 
December 10, 2009.
    (4) The following service information was approved for IBR on 
February 18, 2000 (65 FR 5222, February 3, 2000).
    (i) Boeing Service Bulletin 747-78-2158, Revision 2, dated July 
29, 1999.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
September 14, 1994 (59 FR 41647, August 15, 1994).
    (i) Boeing Service Bulletin 767-78-0059, Revision 3, dated 
January 20, 1994.
    (ii) Reserved.
    (6) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
https://www.myboeingfleet.com.
    (7) You may view this service information at FAA, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (8) You may view this service information that is incorporated 
by reference 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.

    Issued in Renton, Washington, on February 19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-06155 Filed 3-20-14; 8:45 am]
BILLING CODE 4910-13-P