Airworthiness Directives; the Boeing Company Airplanes, 74038-74042 [2014-29232]

Download as PDF 74038 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules Revision A, dated December 4, 2012, to implement a reduction in service life of the ring gear carrier assembly, part number (P/N) 269A5194, from 6,000 flight hours to 5,000 flight hours. Proposed AD Requirements This proposed AD would require reducing the life limit of the ring gear carrier assembly, P/N 269A5194, from 6,000 hours TIS to 5,000 hours TIS by revising the Airworthiness Limitations section of the applicable maintenance manual. This proposed AD would also require replacing each ring gear carrier assembly with an airworthy ring gear carrier assembly on or before reaching 5,000 hours TIS. Costs of Compliance We estimate that this proposed AD would affect 16 helicopters of U.S. Registry. We estimate a minimal cost to change the life limit of the ring gear. If required, we estimate it would take 27.5 hours to replace a ring gear carrier assembly at $85 per work hour. Required parts would cost $7,591 for a total of $9,929 per helicopter. tkelley on DSK3SPTVN1PROD with PROPOSALS 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, I certify this proposed regulation: VerDate Sep<11>2014 19:17 Dec 12, 2014 Jkt 235001 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by Reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Amend § 39.13 by adding the following new airworthiness directive (AD): ■ Sikorsky Aircraft Corporation (Type Certificate Previously Held By Schweizer Aircraft Corporation): Docket No. FAA–2014–1020; Directorate Identifier 2013–SW–078–AD. (a) Applicability This AD applies to Sikorsky Aircraft Corporation Model 269D and Model 269D Configuration A helicopters with ring gear carrier assembly, part number (P/N) 269A5194, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a fatigue crack in a ring gear carrier assembly. This condition could result in failure of the main rotor transmission, loss of engine power to the main rotor, and subsequent loss of control of the helicopter. (c) Comments Due Date We must receive comments by February 13, 2015. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Before further flight: PO 00000 Frm 00007 Fmt 4702 (1) Revise the Airworthiness Limitations Section of the applicable maintenance manual by reducing the life limit of the ring gear carrier assembly, P/N 269A5194, from 6,000 hours time-in-service (TIS) to 5,000 hours TIS. (2) Remove from service any ring gear carrier assembly, P/N 269A5194, with 5,000 or more hours TIS. (f) Alternative Methods of Compliance (AMOC) (1) The Manager, New York Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Norman Perenson, Aviation Safety Engineer, New York Aircraft Certification Office, Propulsion & Services Branch, FAA, 1600 Stewart Ave., Westbury, New York; telephone (516) 228–7337; email Norman.Perenson@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (g) Additional Information Sikorsky 269D Helicopter Alert Service Bulletin No. ASB DB–040A, Revision A, dated December 4, 2012, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800–Winged–S or 203–416– 4299; email sikorskywcs@sikorsky.com. You may review a copy of information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (h) Subject Joint Aircraft Service Component (JASC) Code: 6300 Main Rotor Drive System. Issued in Fort Worth, Texas, on December 8, 2014. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–29260 Filed 12–12–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0921; Directorate Identifier 2014–NM–073–AD] RIN 2120–AA64 Airworthiness Directives; the Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: Sfmt 4702 E:\FR\FM\15DEP1.SGM 15DEP1 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules Notice of proposed rulemaking (NPRM). ACTION: We propose to supersede Airworthiness Directive (AD) 2013–14– 05, which applies to certain The Boeing Company Model 747–400 and 747–400F series airplanes. AD 2013–14–05 currently requires repetitive inspections of the longeron extension fittings for cracking, and related investigative and corrective actions if necessary. AD 2013–14–05 also provides optional terminating action for the repetitive inspections. Since we issued AD 2013– 14–05, we determined that more work is necessary on airplanes on which a terminating action (permanent repair, longeron extension fitting replacement, or modification) was accomplished. This proposed AD would continue to require the requirements of AD 2013– 14–05, and would add new repetitive high frequency eddy current (HFEC) inspections of any modified, repaired, or replaced longeron extension fitting for cracking, and applicable related investigative and corrective actions if necessary. We are proposing this AD to detect and correct cracks in the longeron extension fittings, which can become large and adversely affect the structural integrity of the airplane. SUMMARY: We must receive comments on this proposed AD by January 29, 2015. DATES: 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 http://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; 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. tkelley on DSK3SPTVN1PROD with PROPOSALS ADDRESSES: VerDate Sep<11>2014 19:17 Dec 12, 2014 Jkt 235001 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–2014– 0921; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: 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. 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–2014–0921; Directorate Identifier 2014–NM–073–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 http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On June 25, 2013, we issued AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013), for certain the Boeing Company Model 747–400 and 747–400F series airplanes. AD 2013–14– 05 requires repetitive inspections of the longeron extension fittings for cracking, and related investigative and corrective actions if necessary. AD 2013–14–05 also provides for optional terminating action for the repetitive inspections. AD 2013–14–05 resulted from reports of cracking in the outboard flange of the longeron extension fittings, which attach to the wing-to-body fairing support frame. We issued AD 2013–14– PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 74039 05 to detect and correct cracks in the longeron extension fittings, which can become large and adversely affect the structural integrity of the airplane. Actions Since AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013) Was Issued Since we issued AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013), we determined that more work is necessary on airplanes that accomplished a permanent repair, longeron extension fitting replacement, or preventive modification (the terminating actions specified in AD 2013–14–05). Relevant Service Information We reviewed Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA–2014–0921. 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 Although this proposed AD does not explicitly restate the requirements of AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013), this proposed AD would retain all of the requirements of AD 2013–14–05. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraphs (g), (h)(1), and (j) of this proposed AD. This proposed AD would require additional repetitive HFEC inspections of the left and right longeron extension fittings for cracking, and applicable related investigative and corrective actions, for airplanes that have previously accomplished a permanent repair, longeron extension fitting replacement, or preventive modification, as identified in Boeing Alert Service Bulletin 747–53A2860, dated December 4, 2012. The phrase ‘‘related investigative actions’’ is used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or E:\FR\FM\15DEP1.SGM 15DEP1 74040 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 747– 53A2860, Revision 1, dated March 18, 2014, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. the inspections in paragraph (g) of this proposed AD. In paragraph (h)(2) of this proposed AD we specify that the terminating action if done ‘‘on or after the effective date of this AD’’ must be done in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD. Clarification of Terminating Actions for Certain Inspections Paragraph (h)(1) of this proposed AD specifies that if the terminating action is done ‘‘before the effective date of this AD’’ in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, dated December 4, 2012, it terminates Costs of Compliance We estimate that this proposed AD affects 41 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost HFEC inspection [retained action from AD 2013-14-05, Amendment 39-17510 (78 FR 43763, July 22, 2013)]. Terminating action for certain inspections [retained action from AD 2013-14-05, Amendment 39-17510 (78 FR 43763, July 22, 2013)]. HFEC inspection [new action] .................. 32 work-hours × $85 per hour = $2,720 per inspection cycle. $0 479 work-hours × $85 per hour = $40,715. 32 work-hours × $85 per hour = $2,720 per inspection cycle. We estimate the following costs to do any necessary replacements that would Parts cost be required based on the results of the proposed inspection. We have no way of Cost per product Cost on U.S. operators $2,720 per inspection cycle. $111,520 per inspection cycle. 0 $40,715 .................. $1,669,315. 0 $2,720 per inspection cycle. $111,520 per inspection cycle. determining the number of aircraft that might need this replacement: ON-CONDITION COSTS Action Labor cost Replacement .................................... 464 work-hours × $85 per hour = $39,440 ............................................... 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. Authority for This Rulemaking tkelley on DSK3SPTVN1PROD with PROPOSALS According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Regulatory Findings 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 We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, VerDate Sep<11>2014 19:17 Dec 12, 2014 Jkt 235001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Cost per product Parts cost $0 $39,440 (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: E:\FR\FM\15DEP1.SGM 15DEP1 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013), and adding the following new AD: ■ The Boeing Company: Docket No. FAA– 2014–0921; Directorate Identifier 2014– NM–073–AD. (a) Comments Due Date The FAA must receive comments on this AD action by January 29, 2015. (b) Affected ADs This AD replaces AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013). (c) Applicability This AD applies to The Boeing Company Model 747–400 and –400F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracking in the outboard flange of the longeron extension fittings, and we determined that more work is necessary on airplanes on which a permanent repair, longeron extension fitting replacement, or modification was accomplished, as required by AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013) could crack. We are issuing this AD to detect and correct cracks in the longeron extension fittings, which can become large and adversely affect the structural integrity of the airplane. tkelley on DSK3SPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the applicable time specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014: Do surface high frequency eddy current (HFEC) inspections for cracking of the left and right longeron extension fittings, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD. Do all applicable corrective actions at the applicable time specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. If no VerDate Sep<11>2014 19:17 Dec 12, 2014 Jkt 235001 cracking is found, repeat the inspection thereafter at the intervals specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, until a terminating action specified in paragraph (h) of this AD is done. (h) Terminating Actions for the Inspections Required by Paragraph (g) of This AD (1) Doing the permanent repair, longeron extension fitting replacement, or preventative modification before the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, dated December 4, 2012, terminates the repetitive inspections required by paragraph (g) of this AD. Boeing Alert Service Bulletin 747–53A2860, dated December 4, 2012, was incorporated by reference in AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013). After accomplishing the actions specified in this paragraph, the actions specified in paragraph (i) of this AD must be done at the times specified in paragraph (i) of this AD. (2) Doing the repair (PART 4 of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014), longeron extension fitting replacement, or modification on or after the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD, terminates the repetitive inspection requirements of paragraph (g) of this AD. After accomplishing the actions specified in this paragraph, the actions specified in paragraph (i) of this AD must be done at the times specified in paragraph (i) of this AD. (i) Post-Modification/Repair/Replacement Inspections For airplanes on which any action identified in paragraph (h) of this AD has been accomplished (including if done as a corrective action required by paragraph (g) or (j) of this AD): At the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(1) of this AD, do a HFEC inspection of the left and right longeron extension fittings for cracking, as applicable, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. Do all applicable corrective actions at the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD. If no cracking is found, repeat the inspection thereafter at the interval specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. (j) Inspection of Temporary Repair and Corrective Actions For airplanes on which a temporary repair as specified in Boeing Alert Service Bulletin PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 74041 747–53A2860 has been done: At the times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, do a surface HFEC inspection of the temporary repair of the longeron extension fittings for cracking, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD. Do all applicable corrective actions before further flight. (k) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, specifies a compliance time ‘‘after the Revision 1 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, specifies to contact Boeing for repair information: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (g) and (j) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2860, dated December 4, 2012, which was incorporated by reference in AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013). (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 (m)(1) 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 (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. (4) AMOCs approved previously for AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013), are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), and (j) of this AD. E:\FR\FM\15DEP1.SGM 15DEP1 74042 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules (n) Related Information (1) For more information about this AD, 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. (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; 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. Issued in Renton, Washington, on December 5, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–29232 Filed 12–12–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2014–0869; Airspace Docket No. 14–AWP–6] Proposed Establishment of Class E Airspace; Hazen, NV Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to establish Class E airspace at the Hazen VHF Omni-Directional Radio Range Tactical Air Navigation Aid (VORTAC), Hazen, NV, to facilitate vectoring of Instrument Flight Rules (IFR) aircraft under control of Oakland Air Route Traffic Control Center (ARTCC). The FAA is proposing this action to enhance the safety and management of aircraft operations within the National Airspace System. DATES: Comments must be received on or before January 29, 2015. ADDRESSES: Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590; telephone (202) 366–9826. You must identify FAA Docket No. FAA–2014–0869; Airspace Docket No. 14–AWP–6, at the beginning of your comments. You may also submit tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 19:17 Dec 12, 2014 Jkt 235001 comments through the Internet at http://www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Steve Haga, Federal Aviation Administration, Operations Support Group, Western Service Center, 1601 Lind Avenue SW., Renton, WA 98057; telephone (425) 203–4563. SUPPLEMENTARY INFORMATION: Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers (FAA Docket No. FAA– 2014–0869 and Airspace Docket No. 14– AWP–6) and be submitted in triplicate to the Docket Management System (see ADDRESSES section for address and phone number). You may also submit comments through the Internet at http://www.regulations.gov. Commenters wishing the FAA to acknowledge receipt of their comments on this action must submit with those comments a self-addressed stamped postcard on which the following statement is made: ‘‘Comments to FAA Docket No. FAA–2014–0869 and Airspace Docket No. 14–AWP–6’’. The postcard will be date/time stamped and returned to the commenter. All communications received on or before the specified closing date for comments will be considered before taking action on the proposed rule. The proposal contained in this action may be changed in light of comments received. All comments submitted will be available for examination in the public docket both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerned with this rulemaking will be filed in the docket. Availability of NPRM’s An electronic copy of this document may be downloaded through the Internet at http://www.regulations.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at http:// www.faa.gov/airports_airtraffic/air_ traffic/publications/airspace_ amendments/. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office (see the ADDRESSES section for the address and phone number) between 9:00 a.m. and 5:00 p.m., Monday through Friday, except federal holidays. An informal docket may also be examined during normal business hours at the Northwest Mountain Regional Office of the Federal Aviation Administration, Air Traffic Organization, Western Service Center, Operations Support Group, 1601 Lind Avenue SW., Renton, WA 98057. Persons interested in being placed on a mailing list for future NPRM’s should contact the FAA’s Office of Rulemaking, (202) 267–9677, for a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. The Proposal The FAA is proposing an amendment to Title 14 Code of Federal Regulations (14 CFR) Part 71 by establishing Class E en route domestic airspace extending upward from 1,200 feet above the surface at the Hazen VORTAC navigation aid, Hazen, NV. This action would contain aircraft while in IFR conditions under control of Oakland ARTCC by vectoring aircraft from en route airspace to terminal areas. Class E airspace designations are published in paragraph 6006, of FAA Order 7400.9Y, dated August 6, 2014, and effective September 15, 2014, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designation listed in this document will be published subsequently in this Order. The FAA has determined this proposed regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified this proposed rule, when promulgated, would not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the U.S. Code. Subtitle 1, E:\FR\FM\15DEP1.SGM 15DEP1

Agencies

[Federal Register Volume 79, Number 240 (Monday, December 15, 2014)]
[Proposed Rules]
[Pages 74038-74042]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-29232]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0921; Directorate Identifier 2014-NM-073-AD]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 74039]]


ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-14-
05, which applies to certain The Boeing Company Model 747-400 and 747-
400F series airplanes. AD 2013-14-05 currently requires repetitive 
inspections of the longeron extension fittings for cracking, and 
related investigative and corrective actions if necessary. AD 2013-14-
05 also provides optional terminating action for the repetitive 
inspections. Since we issued AD 2013-14-05, we determined that more 
work is necessary on airplanes on which a terminating action (permanent 
repair, longeron extension fitting replacement, or modification) was 
accomplished. This proposed AD would continue to require the 
requirements of AD 2013-14-05, and would add new repetitive high 
frequency eddy current (HFEC) inspections of any modified, repaired, or 
replaced longeron extension fitting for cracking, and applicable 
related investigative and corrective actions if necessary. We are 
proposing this AD to detect and correct cracks in the longeron 
extension fittings, which can become large and adversely affect the 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by January 29, 
2015.

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 http://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; 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-2014-
0921; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: 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.

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-2014-0921; 
Directorate Identifier 2014-NM-073-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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On June 25, 2013, we issued AD 2013-14-05, Amendment 39-17510 (78 
FR 43763, July 22, 2013), for certain the Boeing Company Model 747-400 
and 747-400F series airplanes. AD 2013-14-05 requires repetitive 
inspections of the longeron extension fittings for cracking, and 
related investigative and corrective actions if necessary. AD 2013-14-
05 also provides for optional terminating action for the repetitive 
inspections. AD 2013-14-05 resulted from reports of cracking in the 
outboard flange of the longeron extension fittings, which attach to the 
wing-to-body fairing support frame. We issued AD 2013-14-05 to detect 
and correct cracks in the longeron extension fittings, which can become 
large and adversely affect the structural integrity of the airplane.

Actions Since AD 2013-14-05, Amendment 39-17510 (78 FR 43763, July 22, 
2013) Was Issued

    Since we issued AD 2013-14-05, Amendment 39-17510 (78 FR 43763, 
July 22, 2013), we determined that more work is necessary on airplanes 
that accomplished a permanent repair, longeron extension fitting 
replacement, or preventive modification (the terminating actions 
specified in AD 2013-14-05).

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-53A2860, Revision 1, 
dated March 18, 2014. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2014-0921.

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

    Although this proposed AD does not explicitly restate the 
requirements of AD 2013-14-05, Amendment 39-17510 (78 FR 43763, July 
22, 2013), this proposed AD would retain all of the requirements of AD 
2013-14-05. Those requirements are referenced in the service 
information identified previously, which, in turn, is referenced in 
paragraphs (g), (h)(1), and (j) of this proposed AD. This proposed AD 
would require additional repetitive HFEC inspections of the left and 
right longeron extension fittings for cracking, and applicable related 
investigative and corrective actions, for airplanes that have 
previously accomplished a permanent repair, longeron extension fitting 
replacement, or preventive modification, as identified in Boeing Alert 
Service Bulletin 747-53A2860, dated December 4, 2012.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary actions, and (2) further 
investigate the nature of any condition found. Related investigative 
actions in an AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or

[[Page 74040]]

address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 747-53A2860, Revision 1, dated March 
18, 2014, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this proposed AD would require 
repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Clarification of Terminating Actions for Certain Inspections

    Paragraph (h)(1) of this proposed AD specifies that if the 
terminating action is done ``before the effective date of this AD'' in 
accordance with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2860, dated December 4, 2012, it terminates the 
inspections in paragraph (g) of this proposed AD. In paragraph (h)(2) 
of this proposed AD we specify that the terminating action if done ``on 
or after the effective date of this AD'' must be done in accordance 
with the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2860, Revision 1, dated March 18, 2014, except as required by 
paragraph (k)(2) of this AD.

Costs of Compliance

    We estimate that this proposed AD affects 41 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                                 Cost on U.S.
             Action                      Labor cost          Parts cost    Cost per product        operators
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HFEC inspection [retained action  32 work-hours x $85 per            $0  $2,720 per           $111,520 per
 from AD 2013[dash]14[dash]05,     hour = $2,720 per                      inspection cycle.    inspection cycle.
 Amendment 39[dash]17510 (78 FR    inspection cycle.
 43763, July 22, 2013)].
Terminating action for certain    479 work-hours x $85 per            0  $40,715............  $1,669,315.
 inspections [retained action      hour = $40,715.
 from AD 2013[dash]14[dash]05,
 Amendment 39[dash]17510 (78 FR
 43763, July 22, 2013)].
HFEC inspection [new action]....  32 work-hours x $85 per             0  $2,720 per           $111,520 per
                                   hour = $2,720 per                      inspection cycle.    inspection cycle.
                                   inspection cycle.
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    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
this replacement:

                                               On-Condition Costs
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                                                                                                     Cost per
                Action                                 Labor cost                   Parts cost        product
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Replacement...........................  464 work-hours x $85 per hour = $39,440.              $0         $39,440
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    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, 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:

[[Page 74041]]

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 removing Airworthiness Directive (AD) 
2013-14-05, Amendment 39-17510 (78 FR 43763, July 22, 2013), and adding 
the following new AD:

The Boeing Company: Docket No. FAA-2014-0921; Directorate Identifier 
2014-NM-073-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by January 29, 
2015.

(b) Affected ADs

    This AD replaces AD 2013-14-05, Amendment 39-17510 (78 FR 43763, 
July 22, 2013).

(c) Applicability

    This AD applies to The Boeing Company Model 747-400 and -400F 
series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 747-53A2860, Revision 1, dated March 
18, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in the outboard 
flange of the longeron extension fittings, and we determined that 
more work is necessary on airplanes on which a permanent repair, 
longeron extension fitting replacement, or modification was 
accomplished, as required by AD 2013-14-05, Amendment 39-17510 (78 
FR 43763, July 22, 2013) could crack. We are issuing this AD to 
detect and correct cracks in the longeron extension fittings, which 
can become large and adversely affect the structural integrity of 
the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    At the applicable time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2860, 
Revision 1, dated March 18, 2014: Do surface high frequency eddy 
current (HFEC) inspections for cracking of the left and right 
longeron extension fittings, and all applicable corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2860, Revision 1, dated March 18, 2014, 
except as required by paragraph (k)(2) of this AD. Do all applicable 
corrective actions at the applicable time specified in table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2860, Revision 1, dated March 18, 2014. If no cracking is 
found, repeat the inspection thereafter at the intervals specified 
in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2860, Revision 1, dated March 18, 2014, 
until a terminating action specified in paragraph (h) of this AD is 
done.

(h) Terminating Actions for the Inspections Required by Paragraph (g) 
of This AD

    (1) Doing the permanent repair, longeron extension fitting 
replacement, or preventative modification before the effective date 
of this AD, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2860, dated December 4, 2012, 
terminates the repetitive inspections required by paragraph (g) of 
this AD. Boeing Alert Service Bulletin 747-53A2860, dated December 
4, 2012, was incorporated by reference in AD 2013-14-05, Amendment 
39-17510 (78 FR 43763, July 22, 2013). After accomplishing the 
actions specified in this paragraph, the actions specified in 
paragraph (i) of this AD must be done at the times specified in 
paragraph (i) of this AD.
    (2) Doing the repair (PART 4 of Boeing Alert Service Bulletin 
747-53A2860, Revision 1, dated March 18, 2014), longeron extension 
fitting replacement, or modification on or after the effective date 
of this AD, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2860, Revision 1, dated March 
18, 2014, except as required by paragraph (k)(2) of this AD, 
terminates the repetitive inspection requirements of paragraph (g) 
of this AD. After accomplishing the actions specified in this 
paragraph, the actions specified in paragraph (i) of this AD must be 
done at the times specified in paragraph (i) of this AD.

(i) Post-Modification/Repair/Replacement Inspections

    For airplanes on which any action identified in paragraph (h) of 
this AD has been accomplished (including if done as a corrective 
action required by paragraph (g) or (j) of this AD): At the 
applicable time specified in table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2860, 
Revision 1, dated March 18, 2014, except as required by paragraph 
(k)(1) of this AD, do a HFEC inspection of the left and right 
longeron extension fittings for cracking, as applicable, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2860, Revision 
1, dated March 18, 2014. Do all applicable corrective actions at the 
applicable time specified in table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2860, 
Revision 1, dated March 18, 2014, except as required by paragraph 
(k)(2) of this AD. If no cracking is found, repeat the inspection 
thereafter at the interval specified in table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2860, 
Revision 1, dated March 18, 2014.

(j) Inspection of Temporary Repair and Corrective Actions

    For airplanes on which a temporary repair as specified in Boeing 
Alert Service Bulletin 747-53A2860 has been done: At the times 
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2860, Revision 1, dated March 18, 
2014, do a surface HFEC inspection of the temporary repair of the 
longeron extension fittings for cracking, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2860, Revision 
1, dated March 18, 2014, except as required by paragraph (k)(2) of 
this AD. Do all applicable corrective actions before further flight.

(k) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 747-53A2860, Revision 1, 
dated March 18, 2014, specifies a compliance time ``after the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where Boeing Alert Service Bulletin 747-53A2860, Revision 1, 
dated March 18, 2014, specifies to contact Boeing for repair 
information: Before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (m) of this 
AD.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (g) and (j) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 747-53A2860, dated December 4, 2012, which was incorporated 
by reference in AD 2013-14-05, Amendment 39-17510 (78 FR 43763, July 
22, 2013).

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
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 (m)(1) 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 
(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.
    (4) AMOCs approved previously for AD 2013-14-05, Amendment 39-
17510 (78 FR 43763, July 22, 2013), are approved as AMOCs for the 
corresponding provisions of paragraphs (g), (h), and (j) of this AD.

[[Page 74042]]

(n) Related Information

    (1) For more information about this AD, 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.
    (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; 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.

    Issued in Renton, Washington, on December 5, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-29232 Filed 12-12-14; 8:45 am]
BILLING CODE 4910-13-P