Airworthiness Directives; the Boeing Company Airplanes, 22802-22806 [2013-09006]

Download as PDF 22802 Federal Register / Vol. 78, No. 74 / Wednesday, April 17, 2013 / Proposed Rules commenter. All public comments in response to this RFI must be in writing (including fax or email) and will be a matter of public record. Questions tkelley on DSK3SPTVN1PROD with PROPOSALS For Lenders 1. Are small- or medium-sized manufacturers a part of your ordinary portfolio of loans? If not, why not? 2. What are the biggest impediments to a small- or medium-sized manufacturer receiving a loan from your lending institution? Are there types of manufacturers (company size, industry etc.) that you would be more hesitant to loan to than others? 3. Would a new loan guarantee program make you more likely to lend to manufacturers especially small- or medium-sized manufacturers? If so, why and what increase in loan volume to these companies would you estimate would occur? 4. If EDA established a new Federal loan guarantee program that offered loan guarantees for targeted loans for smallor medium-sized manufacturers to support the use or production of innovative technology (as defined above) how much of a guarantee would your lending institution need in order to be willing to offer loans for such purposes? Besides the level of the guarantee, are there any other requirements that you would have of the guarantee program in order to offer such loans? 5. What would your lending institution require for a borrower to demonstrate that a market exists for an innovative technology product? 6. With the support of a loan guarantee program, what size loans would you anticipate making to manufacturers who meet the definition of small- or medium-sized and would you use the loan proceeds to support the use or production of innovative technologies? 7. If such a Federal program were created, what additional requirements would you require from the manufacturers, if any, to support such a loan? 8. Have you ever participated in a loan guarantee program (for example, any guarantee program provided by SBA? If not, why not? If so, would you recommend this process to others? What was your experience with loan guarantee programs (including SBA loan guarantee programs)? For Manufacturers 16:35 Apr 16, 2013 General 15. Are there any additional comments that you would like to offer about the proposal to establish a loan guarantee program that targets the use or production of innovative technologies for manufacturing? Dated: April 10, 2013. Matt Erskine, Deputy Assistant Secretary for Economic Development and Chief Operating Officer, Economic Development Administration. [FR Doc. 2013–08999 Filed 4–16–13; 8:45 am] BILLING CODE 3510–24–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0331; Directorate Identifier 2011–NM–170–AD] RIN 2120–AA64 Airworthiness Directives; the Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–200B, 747–200F, 747–300, 747SP, 747–400, SUMMARY: 9. What is the largest sized manufacturer that you would consider calling a medium-sized manufacturer? VerDate Mar<15>2010 10. Is access to capital an impediment for your development as a small- or medium-sized manufacturer? If so, why (specifically) and what is the size of your firm? 11. If accessing capital is an impediment, is securing a loan via a new Federal loan guarantee program to support the use or production of innovative technologies a strategy that you would pursue in order to access capital? If not, why not? 12. If you would pursue a loan, what size loan would be necessary to support your development needs? 13. Given that the purpose of this program would be to support innovation by re-equipping, expanding or establishing a manufacturing facility in the U.S., what types of activities and outcomes would you use the loan to support? 14. Have you ever used a loan guarantee program (for example, any guarantee program provided by the SBA)? If not, why not? If so, would you recommend this process to others? What was your experience with loan guarantee programs (including SBA loan guarantee programs)? Jkt 229001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 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 proposed AD was prompted by multiple reports of uncommanded thrust reverser unlock events. This proposed AD would require replacing certain relays and relay sockets, and doing wiring changes. For certain airplanes, this proposed AD would also require installing new relay panels, and removing and installing certain components. Additionally, this proposed AD would 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 proposing 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: We must receive comments on this proposed AD by June 3, 2013. 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 Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; phone: 206–544–5000, extension 1; fax: 206–766–5680; Internet: https:// www.myboeingfleet.com. You may review copies of the 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 https:// www.regulations.gov; or in person at the E:\FR\FM\17APP1.SGM 17APP1 Federal Register / Vol. 78, No. 74 / Wednesday, April 17, 2013 / Proposed Rules 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: 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2013–0331; Directorate Identifier 2011– NM–170–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. tkelley on DSK3SPTVN1PROD with PROPOSALS Discussion We have received multiple reports of uncommanded thrust reverser unlock events. In three of these events, all three thrust reverser locks had disengaged. One report stated that during takeoff roll on a Rolls-Royce RB211–524-powered Model 747–400 airplane, the flightcrew received the ENG 4 REV LIMTD EICAS status message and the ENG 4 REVERSER advisory and status messages. During climb, the cabin crew saw sparks from the exhaust of the number 4 engine. The event was found to be caused by a failure of the o-rings in the air motor switcher or shutoff solenoid valves because of overheating. This let the air motor shutoff valve open, which released the air motor brake. Releasing the air motor brake in the ground mode energized the number 2 and number 3 thrust reverser gear box unlock solenoids, thereby unlocking the VerDate Mar<15>2010 16:35 Apr 16, 2013 Jkt 229001 number 2 and number 3 gear boxes. The thrust reverser system on the RollsRoyce RB211-powered Model 767 airplane is similar to that on the Model 747–400 airplane, and the Model 767 airplane thrust reverser system is likely to be susceptible to the same failure mode. This condition, if not corrected, could result an uncommanded thrust reverser deployment during takeoff or in-flight resulting in decreased airplane control and performance, possible runway excursions, and failure to climb. Relevant Service Information We reviewed the following service information: • Boeing Service Bulletin 747–78– 2178, Revision 1, dated August 4, 2011. • Boeing Service Bulletin 747–78– 2180, Revision 2, dated November 11, 2011. • Boeing Service Bulletin 767–78– 0096, Revision 1, dated December 10, 2009. For information on the procedures and compliance times, see this service information at https:// www.regulations.gov by searching for Docket No. FAA–2013–0331. Concurrent Service Information Boeing Service Bulletin 747–78–2178, Revision 1, dated August 4, 2011, specifies concurrent or prior accomplishment of Boeing Service Bulletin 747–78–2156, Revision 1, dated August 30, 2001. Boeing Service Bulletin 747–78–2180, Revision 2, dated November 11, 2011, specifies concurrent or prior accomplishment of Boeing Service Bulletin 747–78–2158, Revision 2, dated July 29, 1999. Boeing Service Bulletin 767–78–0096, Revision 1, dated December 10, 2009, specifies concurrent or prior accomplishment of Boeing Service Bulletin 767–78–0059, Revision 3, dated January 20, 1994. For information on the procedures, see this service information at https:// www.regulations.gov by searching for Docket No. FAA–2013–0331. Other Relevant Rulemaking AD 2000–01–05, Amendment 39– 11502 (65 FR 1051, January 7, 2000), which applies to certain Boeing Model 747–100B, –200, –300, and 747SP series airplanes equipped with Rolls-Royce RB211–524B2, C2, and D4 engines, requires repetitive inspections and tests of the thrust reverser control and indication system on each engine, and corrective actions if necessary; installation of a terminating modification; and repetitive operational checks of that installation, and repair if necessary. AD 2000–01–05 refers to Boeing Service Bulletin 747–78–2156, PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 22803 dated October 31, 1996, as the appropriate source of service information for accomplishing the required terminating modification. AD 2000–02–22, Amendment 39– 11540 (65 FR 5222, February 3, 2000), for certain Boeing Model 747–400 series airplanes equipped with Rolls-Royce RB211–524G/H and RB211–524G–T/H– T engines, requires installation of a modification of the thrust reverser control and indication system and wiring on each engine; and repetitive operational checks of that installation to detect discrepancies, and repair if necessary. AD 2000–02–22 refers to Boeing Service Bulletin 747–78–2158, Revision 2, dated July 29, 1999, as the appropriate source of service information for accomplishing the required modification. AD 94–17–03, Amendment 39–8998 (59 FR 41647, August 15, 1994), for certain Boeing Model 767 series airplanes equipped with Rolls-Royce RB211–524 series engines, requires inspections, adjustments, and functional checks of the thrust reverser system; installation of a terminating modification; and repetitive operational checks of the gearbox locks and the air motor brake following accomplishment of the modification. AD 94–17–03 refers to Boeing Service Bulletin 767–78–0059, Revision 2, dated June 10, 1993; or Revision 3, dated January 20, 1994; as the appropriate source of service information for accomplishing the required terminating action. 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 require accomplishing the actions specified in the service information described previously. The phrase ‘‘related investigative actions’’ might be used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that: (1) Are related to the primary actions, and (2) are actions that further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. In addition, the phrase ‘‘corrective actions’’ might be used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. E:\FR\FM\17APP1.SGM 17APP1 22804 Federal Register / Vol. 78, No. 74 / Wednesday, April 17, 2013 / Proposed Rules Costs of Compliance We estimate the following costs to comply with this proposed AD: We estimate that this proposed AD affects 1 airplane of U.S. registry. ESTIMATED COSTS Action Labor cost Cost per product 30 work-hours × $85 per hour = $2,550. $4,289 .......................... $6,839 .......................... $6,839 Up to 90 work-hours × $85 per hour = $7,650. Up to 32 work-hours × $85 per hour = $2,720. Replacement and wiring change for Model 747– 200B, 747–200F, 747–300, and 747SP series airplanes (1 U.S. airplane). Removal, installations, and wiring changes for Model 747–400 and 747–400F series airplanes (0 U.S. airplanes). Replacements and wiring changes for Model 767–300 series airplanes (0 U.S. airplanes). We estimate the following costs to do any necessary concurrent requirements. We have no way of determining the Cost on U.S. operators Parts cost Up to $16,607 .............. Up to $24,257 .............. $0 Up to $2,245 ................ Up to $4,965 ................ $0 number of aircraft that might need to do the concurrent requirements. CONCURRENT COSTS Cost per product Action Labor cost Installation of an additional locking system ............................ Installation of an additional locking gearbox on each engine and modification of the system wiring. Installation of a second locking gearbox system ................... 336 work-hours × $85 per hour = $28,560 ........ 185 work-hours × $85 per hour = $15,725 ........ $62,674 $72,860 $91,234 $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. tkelley on DSK3SPTVN1PROD with PROPOSALS Regulatory Findings We 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 VerDate Mar<15>2010 16:35 Apr 16, 2013 Jkt 229001 responsibilities among the various levels of government. For the reasons discussed above, I certify this 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, 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Parts cost § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2013–0331; Directorate Identifier 2011– NM–170–AD. (a) Comments Due Date We must receive comments by June 3, 2013. (b) Affected ADs None. (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, 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 airplanes, identified in Boeing Service Bulletin 747–78–2180, Revision 2, dated November 11, 2011. (3) Model 767–300 airplanes, as identified in Boeing Service Bulletin 767–78–0096, Revision 1, dated December 10, 2009. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 7830, Engine Thrust Reverser. E:\FR\FM\17APP1.SGM 17APP1 Federal Register / Vol. 78, No. 74 / Wednesday, April 17, 2013 / Proposed Rules (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. (f) Compliance Comply with this AD within the compliance times specified, unless already done. tkelley on DSK3SPTVN1PROD with PROPOSALS (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 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, VerDate Mar<15>2010 16:35 Apr 16, 2013 Jkt 229001 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. (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. (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. (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. (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. 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. 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 22805 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. 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-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 ODA 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) 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; phone: 206–544– 5000, extension 1; fax: 206–766–5680; Internet: https://www.myboeingfleet.com.You may review copies of the referenced service information at the 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. E:\FR\FM\17APP1.SGM 17APP1 22806 Federal Register / Vol. 78, No. 74 / Wednesday, April 17, 2013 / Proposed Rules Issued in Renton, Washington, on April 10, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–09006 Filed 4–16–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0332; Directorate Identifier 2013–NM–009–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes. This proposed AD was prompted by reports of airspeed mismatch between the pilot and copilot’s airspeed indicators, which occurred during or after heavy rain. This proposed AD would require, for certain airplanes, inspecting for drain bottles having certain part numbers, and replacing affected drain bottles. This proposed AD would require, for certain other airplanes, replacing drain bottles. We are proposing this AD to prevent pitot static tubing from becoming blocked by water, which if not corrected, could lead to erroneous airspeed and altitude indications, and consequent loss of control of the airplane. SUMMARY: We must receive comments on this proposed AD by June 3, 2013. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. tkelley on DSK3SPTVN1PROD with PROPOSALS DATES: VerDate Mar<15>2010 16:35 Apr 16, 2013 Jkt 229001 For service information identified in this proposed AD, contact Bombardier, ˆ Inc., 400 Cote-Vertu Road West, Dorval, ´ Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You may review copies of the 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 https:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7318; fax (516) 794–5531. 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–2013–0332; Directorate Identifier 2013–NM–009–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 based on 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 Transport Canada Civil Aviation, which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2012–30, dated December 7, 2012 (referred to after this as the Mandatory Continuing PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: A number of reports were received from the operators indicating airspeed mismatch between the pilot and co-pilot’s airspeed indicators. The erroneous indication occurred during or after heavy rain. Further investigation revealed that during heavy precipitation, the pitot static tubing may become partially or completely blocked by the water which didn’t enter the drain bottle(s). This condition, if not corrected, may result in erroneous airspeed and altitude indications [and consequent loss of control of the airplane]. This [Canadian] AD mandates [for certain airplanes] the replacement of the drain bottles to improve drainage of the pitot-static tubing [and, for certain other airplanes, an inspection for, and replacement of, certain drain bottles]. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Bombardier, Inc. has issued the following service bulletins. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. • Bombardier Service Bulletin 601– 0617, Revision 03, dated December 20, 2012. • Bombardier Service Bulletin 604– 34–065, Revision 02, dated December 20, 2012. • Bombardier Service Bulletin 605– 34–027, Revision 02, dated December 20, 2012. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 77 products of U.S. registry. We also estimate that it would take about 5 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost up to $2,939 per E:\FR\FM\17APP1.SGM 17APP1

Agencies

[Federal Register Volume 78, Number 74 (Wednesday, April 17, 2013)]
[Proposed Rules]
[Pages 22802-22806]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-09006]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0331; Directorate Identifier 2011-NM-170-AD]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt 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 proposed AD was prompted by 
multiple reports of uncommanded thrust reverser unlock events. This 
proposed AD would require replacing certain relays and relay sockets, 
and doing wiring changes. For certain airplanes, this proposed AD would 
also require installing new relay panels, and removing and installing 
certain components. Additionally, this proposed AD would 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 proposing 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: We must receive comments on this proposed AD by June 3, 2013.

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 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; phone: 206-544-5000, 
extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may review copies of the 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 https://www.regulations.gov; or in person at the

[[Page 22803]]

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: 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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2013-0331; 
Directorate Identifier 2011-NM-170-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

    We have received multiple reports of uncommanded thrust reverser 
unlock events. In three of these events, all three thrust reverser 
locks had disengaged. One report stated that during takeoff roll on a 
Rolls-Royce RB211-524-powered Model 747-400 airplane, the flightcrew 
received the ENG 4 REV LIMTD EICAS status message and the ENG 4 
REVERSER advisory and status messages. During climb, the cabin crew saw 
sparks from the exhaust of the number 4 engine. The event was found to 
be caused by a failure of the o-rings in the air motor switcher or 
shutoff solenoid valves because of overheating. This let the air motor 
shutoff valve open, which released the air motor brake. Releasing the 
air motor brake in the ground mode energized the number 2 and number 3 
thrust reverser gear box unlock solenoids, thereby unlocking the number 
2 and number 3 gear boxes. The thrust reverser system on the Rolls-
Royce RB211-powered Model 767 airplane is similar to that on the Model 
747-400 airplane, and the Model 767 airplane thrust reverser system is 
likely to be susceptible to the same failure mode. This condition, if 
not corrected, could result an uncommanded thrust reverser deployment 
during takeoff or in-flight resulting in decreased airplane control and 
performance, possible runway excursions, and failure to climb.

Relevant Service Information

    We reviewed the following service information:
     Boeing Service Bulletin 747-78-2178, Revision 1, dated 
August 4, 2011.
     Boeing Service Bulletin 747-78-2180, Revision 2, dated 
November 11, 2011.
     Boeing Service Bulletin 767-78-0096, Revision 1, dated 
December 10, 2009.
    For information on the procedures and compliance times, see this 
service information at https://www.regulations.gov by searching for 
Docket No. FAA-2013-0331.

Concurrent Service Information

    Boeing Service Bulletin 747-78-2178, Revision 1, dated August 4, 
2011, specifies concurrent or prior accomplishment of Boeing Service 
Bulletin 747-78-2156, Revision 1, dated August 30, 2001. Boeing Service 
Bulletin 747-78-2180, Revision 2, dated November 11, 2011, specifies 
concurrent or prior accomplishment of Boeing Service Bulletin 747-78-
2158, Revision 2, dated July 29, 1999. Boeing Service Bulletin 767-78-
0096, Revision 1, dated December 10, 2009, specifies concurrent or 
prior accomplishment of Boeing Service Bulletin 767-78-0059, Revision 
3, dated January 20, 1994. For information on the procedures, see this 
service information at https://www.regulations.gov by searching for 
Docket No. FAA-2013-0331.

Other Relevant Rulemaking

    AD 2000-01-05, Amendment 39-11502 (65 FR 1051, January 7, 2000), 
which applies to certain Boeing Model 747-100B, -200, -300, and 747SP 
series airplanes equipped with Rolls-Royce RB211-524B2, C2, and D4 
engines, requires repetitive inspections and tests of the thrust 
reverser control and indication system on each engine, and corrective 
actions if necessary; installation of a terminating modification; and 
repetitive operational checks of that installation, and repair if 
necessary. AD 2000-01-05 refers to Boeing Service Bulletin 747-78-2156, 
dated October 31, 1996, as the appropriate source of service 
information for accomplishing the required terminating modification.
    AD 2000-02-22, Amendment 39-11540 (65 FR 5222, February 3, 2000), 
for certain Boeing Model 747-400 series airplanes equipped with Rolls-
Royce RB211-524G/H and RB211-524G-T/H-T engines, requires installation 
of a modification of the thrust reverser control and indication system 
and wiring on each engine; and repetitive operational checks of that 
installation to detect discrepancies, and repair if necessary. AD 2000-
02-22 refers to Boeing Service Bulletin 747-78-2158, Revision 2, dated 
July 29, 1999, as the appropriate source of service information for 
accomplishing the required modification.
    AD 94-17-03, Amendment 39-8998 (59 FR 41647, August 15, 1994), for 
certain Boeing Model 767 series airplanes equipped with Rolls-Royce 
RB211-524 series engines, requires inspections, adjustments, and 
functional checks of the thrust reverser system; installation of a 
terminating modification; and repetitive operational checks of the 
gearbox locks and the air motor brake following accomplishment of the 
modification. AD 94-17-03 refers to Boeing Service Bulletin 767-78-
0059, Revision 2, dated June 10, 1993; or Revision 3, dated January 20, 
1994; as the appropriate source of service information for 
accomplishing the required terminating action.

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 require accomplishing the actions specified 
in the service information described previously.
    The phrase ``related investigative actions'' might be used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that: (1) Are related to the primary actions, and (2) are actions that 
further investigate the nature of any condition found. Related 
investigative actions in an AD could include, for example, inspections.
    In addition, the phrase ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

[[Page 22804]]

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost on U.S.
              Action                    Labor cost           Parts cost        Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Replacement and wiring change for  30 work-hours x $85  $4,289.............  $6,839.............          $6,839
 Model 747-200B, 747-200F, 747-     per hour = $2,550.
 300, and 747SP series airplanes
 (1 U.S. airplane).
Removal, installations, and        Up to 90 work-hours  Up to $16,607......  Up to $24,257......              $0
 wiring changes for Model 747-400   x $85 per hour =
 and 747-400F series airplanes (0   $7,650.
 U.S. airplanes).
Replacements and wiring changes    Up to 32 work-hours  Up to $2,245.......  Up to $4,965.......              $0
 for Model 767-300 series           x $85 per hour =
 airplanes (0 U.S. airplanes).      $2,720.
----------------------------------------------------------------------------------------------------------------

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

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

    We 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 this 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, 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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2013-0331; Directorate Identifier 
2011-NM-170-AD.

(a) Comments Due Date

    We must receive comments by June 3, 2013.

(b) Affected ADs

    None.

(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, 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 airplanes, identified in Boeing 
Service Bulletin 747-78-2180, Revision 2, dated November 11, 2011.
    (3) Model 767-300 airplanes, as identified in Boeing Service 
Bulletin 767-78-0096, Revision 1, dated December 10, 2009.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 7830, Engine Thrust Reverser.

[[Page 22805]]

(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.

(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 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.
    (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.
    (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.
    (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.
    (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.


    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.


    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.


    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 the Related Information section 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 ODA 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) 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; phone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com.You may review copies of the referenced 
service information at the 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.


[[Page 22806]]


    Issued in Renton, Washington, on April 10, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2013-09006 Filed 4-16-13; 8:45 am]
BILLING CODE 4910-13-P
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