Airworthiness Directives; The Boeing Company Airplanes, 70441-70445 [2014-27358]

Download as PDF Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 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. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations. gov/#!docketDetail;D=FAA-2014-0191; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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 adding the following new airworthiness directive (AD): ■ 2014–23–14 Bombardier, Inc.: Amendment 39–18030. Docket No. FAA–2014–0191; Directorate Identifier 2013–NM–256–AD. (a) Effective Date This AD becomes effective December 31, 2014. (b) Affected ADs None. mstockstill on DSK4VPTVN1PROD with RULES (c) Applicability This AD applies to Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes; certificated in any category; serial numbers 4001, and 4003 through 4417 inclusive, with installed engine fuel feed ejector pump having part number (P/N) 2960008–102. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Reason This AD was prompted by reports of swing arm assemblies of engine fuel feed ejector pumps detaching from the outlet port of the engine fuel feed ejector pump and partially blocking the engine fuel feed line. We are VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 issuing this AD to prevent blocked engine fuel flow and possible engine flameout. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Installation Within 6,000 flight hours or 36 months, whichever occurs first, after the effective date of this AD, install a restrictor into the engine fuel feed line, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–28–16, Revision B, dated June 17, 2013. (h) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–28–16, dated July 16, 2012; or Bombardier Service Bulletin 84–28–16, Revision A, dated May 23, 2013; which are not incorporated by reference in this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO, ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, Engine and Propeller Directorate, FAA; or TCCA; or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–35, dated November 15, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations. gov/#!documentDetail;D=FAA-2014-01910002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 70441 (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 84–28–16, Revision B, dated June 17, 2013. (ii) Reserved. (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. (4) You may view this 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on November 6, 2014. Jeffrey E. Duven Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–27357 Filed 11–25–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0170; Directorate Identifier 2013–NM–169–AD; Amendment 39–18027; AD 2014–23–11] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2005–13– 05, which applied to certain Boeing Model 747–400F series airplanes. AD 2005–13–05 required inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, and repair of any cracking. AD 2005–13–05 also required a preventive modification of the upper deck floor beams, and repetitive inspections for cracking after accomplishing the modification. This new AD retains these actions and requires a second modification, repetitive inspections for cracking, and SUMMARY: E:\FR\FM\26NOR1.SGM 26NOR1 70442 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations repair if necessary. This AD was prompted by a determination that the upper chords of the upper deck floor beams at certain stations are structures that are susceptible to widespread fatigue damage, and that certain airplanes with an initial modification require a second modification for the airplane to meet its limit of validity (LOV). We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could result in reduced structural integrity of the airplane and rapid decompression or reduced controllability of the airplane. DATES: This AD is effective December 31, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 31, 2014. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of July 27, 2005 (70 FR 35989, June 22, 2005). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0170; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005). AD 2005–13–05 applied to certain Boeing Model 747–400F series airplanes. The NPRM published in the Federal Register on March 25, 2014 (79 FR 16241). The NPRM was prompted by a determination that the upper chords of the upper deck floor beams at certain stations are structures that are susceptible to widespread fatigue damage, and that certain airplanes with an initial modification require a second modification for the airplane to meet its LOV. The NPRM proposed to continue to require inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, and repair of any cracking; a preventive modification of the upper deck floor beams; and repetitive inspections for cracking after accomplishing the modification. The NPRM proposed to also require a second modification, repetitive inspections for cracking, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could result in reduced structural integrity of the airplane and rapid decompression or reduced controllability of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 16241, March 25, 2014) and the FAA’s response to each comment. Request To Clarify Post-Modification Inspection Options Boeing requested that we revise paragraphs (j) and (l) of the NPRM (79 FR 16241, March 25, 2014) to clarify that the inspection options of paragraphs (j)(2) and (l)(2) are applicable only when the primary preventative modification option has been accomplished. Boeing stated that Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013, added an alternative preventative modification option for which the inspection options of paragraphs (j)(2) and (l)(2) of this AD are not viable. We agree with the commenter’s request because these words add clarity as to which inspection option should be used. We have revised paragraphs (j) and (l) of this AD by stating that, as of the effective date of this AD, for airplanes on which the alternative preventive modification has been accomplished, only the inspection methods specified by paragraphs (j)(1) and (l)(1), respectively, of this AD may be used. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 16241, March 25, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 16241, March 25, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 13 airplanes of U.S. registry. We estimate the following costs to comply with this AD: mstockstill on DSK4VPTVN1PROD with RULES ESTIMATED COSTS Cost per product Action Labor cost Parts cost Pre-modification inspections (retained actions from AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005)). Modification/inspections done during modification (retained actions from AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005)). 11 work-hours × $85 per hour = $935. $0 ..................... $935 Up to 524 work-hours × $85 per hour = $44,540. Up to $14,874 .. 59,414 VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\26NOR1.SGM 26NOR1 Cost on U.S. operators $12,155. $772,382. Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 70443 ESTIMATED COSTS—Continued Cost per product Cost on U.S. operators Action Labor cost Parts cost Post-modification inspections (retained actions from AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005)). Zero-Timing Procedure Option 1 (including inspections) (new action). Zero-Timing Procedure Option 2 (including inspections) (new action). 66 work-hours × $85 per hour = $5,610. $0 ..................... 5,610 $72,930. 71 work-hours × $85 per hour = $6,035. 103 work-hours × $85 per hour = $8,755. $0 ..................... 6,035 Up to $78,455. $0 ..................... 8,755 Up to $113,815. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Authority for This Rulemaking Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could result in reduced structural integrity of the airplane and rapid decompression or reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. mstockstill on DSK4VPTVN1PROD with RULES Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 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) 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005), and adding the following new AD: ■ 2014–23–11 The Boeing Company: Amendment 39–18027 ; Docket No. FAA–2014–0170; Directorate Identifier 2013–NM–169–AD. (a) Effective Date This AD is effective December 31, 2014. (b) Affected ADs This AD replaces AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005). (c) Applicability This AD applies to The Boeing Company Model 747–400F series airplanes, certificated in any category, as identified in Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report indicating that the upper chords of the upper deck floor beams at stations (STA) 340 through 520 have been determined to be structures that are susceptible to widespread fatigue damage, and airplanes that had an initial modification done before 15,000 total flight cycles require a second fastener hole zero-timing modification for the airplane to meet its limit of validity (LOV). We are PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 (g) Retained Inspections With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005), with revised service information. Before the accumulation of 15,000 total flight cycles, or within 1,000 flight cycles after July 27, 2005 (the effective date of AD 2005–13– 05), whichever is later: Accomplish detailed and open-hole high frequency eddy current (HFEC) inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.1. of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, dated May 9, 2002; or Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013. As of the effective date of this AD, only Boeing Service Bulletin 747– 53A2443, Revision 2, dated August 2, 2013, may be used. (h) Retained Repair With Revised Service Information and Revised Repair Approval Language This paragraph restates the requirements of paragraph (h) of AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005), with revised service information and revised repair approval language. If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, accomplish the actions required by paragraph (h)(1) and (h)(2) of this AD. (1) Repair in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, dated May 9, 2002; or the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013; except where these service bulletins specify to contact Boeing for appropriate action, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (o) of this AD. As of the effective date of this AD, only E:\FR\FM\26NOR1.SGM 26NOR1 70444 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013, may be used. (2) Accomplish the inspections and preventive modification of the floor beams by doing all the actions in accordance with Part 3.B.2. or Part 3.B.3., as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, dated May 9, 2002; or Part 2 or Part 3, as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013, may be used. (i) Retained Modification With Revised Service Information This paragraph restates the requirements of paragraph (i) of AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005), with revised service information. If no crack is found during any inspection required by paragraph (g) of this AD: Accomplish the actions required by either paragraph (i)(1) or (i)(2) of this AD, at the time specified. (1) Before further flight: Accomplish the inspections and preventive modification of the floor beam by doing all the actions in accordance with Part 3.B.2 or Part 3.B.3., as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2443, dated May 9, 2002; or Part 2 or Part 3, as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2443, Revision 2, dated August 2, 2013. If the preventive modification is performed concurrently with the inspections required by paragraph (g) of this AD, the upper chord straps must be removed when performing the open-hole HFEC inspection. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013, may be used. (2) Before the accumulation of 20,000 total flight cycles, or within 1,000 flight cycles after July 27, 2005 (the effective date of AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005), whichever is later: Accomplish the inspections and preventive modification of the upper deck floor beams, by doing all the actions in accordance with Part 3.B.2. or 3.B.3. as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, dated May 9, 2002; or Part 2 or Part 3, as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013, may be used. (j) Retained Post-Modification Inspections With Revised Service Information This paragraph restates the requirements of paragraph (j) of AD 2005–13–05, Amendment VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 39–14141 (70 FR 35989, June 22, 2005), with revised service information. Within 15,000 flight cycles after accomplishing the applicable preventive modification required by paragraph (h)(2), (i)(1), or (i)(2) of this AD: Accomplish the applicable inspections required by either paragraph (j)(1) or (j)(2) of this AD; if any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, for airplanes on which the alternative preventive modification, as identified in the NOTE after step 3. of ‘‘PART 2—INSPECTION AND PREVENTIVE MODIFICATION,’’ or as identified in the NOTE after step 4. of ‘‘PART 3—INSPECTION AND PREVENTIVE MODIFICATION,’’ of the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2443, Revision 2, dated August 2, 2013, has been done, only the inspection specified by paragraph (j)(1) of this AD may be used. (1) Accomplish detailed and surface HFEC inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.4. of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, dated May 9, 2002; or Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2443, Revision 2, dated August 2, 2013. If no crack is found, repeat the inspections at intervals not to exceed 1,000 flight cycles. As of the effective date of this AD, only Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013, may be used. (2) Accomplish detailed and open-hole HFEC inspections for cracking of the web, upper chord, and strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, dated May 9, 2002; or Part 5 of the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2443, Revision 2, dated August 2, 2013. If no crack is found, repeat the inspections at intervals not to exceed 5,000 flight cycles. As of the effective date of this AD, only Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013, may be used. (k) New Floor Beam Hole Zero-Timing Within 20,000 flight cycles after accomplishing the preventive modification of the Station 340 to Station 520 upper deck floor beams specified in paragraph (h)(2), (i)(1), or (i)(2) of this AD, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later: Accomplish the floor beam hole zero-timing, in accordance with Part 6 of the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2443, Revision 2, dated August 2, 2013. (l) New Post-Modification Floor Beam Hole Zero-Timing Inspections Within 15,000 flight cycles after accomplishing the floor beam hole zerotiming required by paragraph (k) of this AD: Accomplish the applicable inspections required by paragraph (l)(1) or (l)(2) of this AD; if any cracking is found during any PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, for airplanes on which the alternative preventive modification, as identified in the NOTE after step 3. of ‘‘PART 2—INSPECTION AND PREVENTIVE MODIFICATION,’’ or as identified in the NOTE after step 4. of ‘‘PART 3—INSPECTION AND PREVENTIVE MODIFICATION,’’ of the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2443, Revision 2, dated August 2, 2013, has been done, only the inspection method specified by paragraph (l)(1) of this AD may be used. (1) Accomplish detailed and surface HFEC inspections for cracking of the web, upper chord, and straps of the Station 340 to Station 520 upper deck floor beams, by doing all the applicable actions, in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013. If no cracking is found, repeat the inspections at intervals not to exceed 1,000 flight cycles. (2) Accomplish detailed and open-hole HFEC inspections for cracking of the web, upper chord, and straps of the Station 340 to Station 520 upper deck floor beams, by doing all the applicable actions, in accordance with Part 5 of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013. If no cracking is found, repeat the inspections at intervals not to exceed 5,000 flight cycles. (m) Exception to Service Information Where Boeing Service Bulletin 747– 53A2443, Revision 2, dated August 2, 2013, specifies a compliance time ‘‘after the revision date on this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (n) Credit for Previous Actions This paragraph provides credit for the inspections, repairs, and modification required by paragraphs (g) through (j) of this AD, if the corresponding actions were performed before the effective date of this AD using Boeing Service Bulletin 747–53A2443, Revision 1, dated June 25, 2009. (o) 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 (p)(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 E:\FR\FM\26NOR1.SGM 26NOR1 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 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 for AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005), are approved as AMOCs for the corresponding requirements of paragraphs (g) through (j) (the retained actions) of this AD. (p) 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) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(5) and (q)(6) of this AD. mstockstill on DSK4VPTVN1PROD with RULES (q) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on December 31, 2014. (i) Boeing Service Bulletin 747–53A2443, Revision 2, dated August 2, 2013. (ii) Reserved. (4) The following service information was approved for IBR on July 27, 2005 (70 FR 35989, June 22, 2005). (i) Boeing Service Bulletin 747–53A2443, dated May 9, 2002. (ii) Reserved. (5) 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. (6) You may view this 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on November 6, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–27358 Filed 11–25–14; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0174; Directorate Identifier 2013–NM–212–AD; Amendment 39–18028; AD 2014–23–12] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This AD was prompted by a report indicating that, on a different Boeing airplane model, there was an oxygen-fed fire, which caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non-conductive hoses in the crew oxygen system. We are issuing this AD to prevent inadvertent electrical current from passing through an internal, anticollapse spring of the low pressure oxygen hose, which can cause the lowpressure oxygen hose to melt or burn, leading to an oxygen-fed fire and/or smoke beneath the flight deck in the forward electronics equipment bay. DATES: This AD is effective December 31, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 31, 2014. ADDRESSES: For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. For B/E Aerospace service information identified in this AD, contact B/E Aerospace, Inc., Commercial Aircraft Products Group, 10800 Pfluum Road, Lenexa, KS 66215; phone: 913–338– 9800; fax: 913–469–8419. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 70445 and locating Docket No. FAA–2014– 0174; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Susan Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6457; fax: 425– 917–6590; email: susan.l.monroe@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 787–8 airplanes. The NPRM published in the Federal Register on March 28, 2014 (79 FR 17457). The NPRM was prompted by a report indicating that, on a different Boeing airplane model, there was an oxygen-fed fire, which caused extensive damage to the flight deck. The NPRM proposed to require replacing the low-pressure oxygen hoses with non-conductive hoses in the crew oxygen system. We are issuing this AD to prevent inadvertent electrical current from passing through an internal, anticollapse spring of the low pressure oxygen hose, which can cause the lowpressure oxygen hose to melt or burn, leading to an oxygen-fed fire and/or smoke beneath the flight deck in the forward electronics equipment bay. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 17457, March 28, 2014) and the FAA’s response to each comment. Boeing, United Airlines, and John Johnson stated that they support the NPRM (79 FR 17457, March 28, 2014). Request To Shorten Compliance Time The Air Line Pilots Association (ALPA) stated that it supports the intent of the NPRM (79 FR 17457, March 28, 2014) but that the 60-month compliance E:\FR\FM\26NOR1.SGM 26NOR1

Agencies

[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70441-70445]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-27358]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0170; Directorate Identifier 2013-NM-169-AD; 
Amendment 39-18027; AD 2014-23-11]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2005-13-05, 
which applied to certain Boeing Model 747-400F series airplanes. AD 
2005-13-05 required inspections for cracking of the web, upper chord, 
and upper chord strap of the upper deck floor beams, and repair of any 
cracking. AD 2005-13-05 also required a preventive modification of the 
upper deck floor beams, and repetitive inspections for cracking after 
accomplishing the modification. This new AD retains these actions and 
requires a second modification, repetitive inspections for cracking, 
and

[[Page 70442]]

repair if necessary. This AD was prompted by a determination that the 
upper chords of the upper deck floor beams at certain stations are 
structures that are susceptible to widespread fatigue damage, and that 
certain airplanes with an initial modification require a second 
modification for the airplane to meet its limit of validity (LOV). We 
are issuing this AD to detect and correct fatigue cracking in certain 
upper chords of the upper deck floor beam, which could result in 
reduced structural integrity of the airplane and rapid decompression or 
reduced controllability of the airplane.

DATES: This AD is effective December 31, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 31, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
27, 2005 (70 FR 35989, June 22, 2005).

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0170; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2005-13-05, Amendment 39-14141 (70 FR 35989, 
June 22, 2005). AD 2005-13-05 applied to certain Boeing Model 747-400F 
series airplanes. The NPRM published in the Federal Register on March 
25, 2014 (79 FR 16241). The NPRM was prompted by a determination that 
the upper chords of the upper deck floor beams at certain stations are 
structures that are susceptible to widespread fatigue damage, and that 
certain airplanes with an initial modification require a second 
modification for the airplane to meet its LOV. The NPRM proposed to 
continue to require inspections for cracking of the web, upper chord, 
and upper chord strap of the upper deck floor beams, and repair of any 
cracking; a preventive modification of the upper deck floor beams; and 
repetitive inspections for cracking after accomplishing the 
modification. The NPRM proposed to also require a second modification, 
repetitive inspections for cracking, and repair if necessary. We are 
issuing this AD to detect and correct fatigue cracking in certain upper 
chords of the upper deck floor beam, which could result in reduced 
structural integrity of the airplane and rapid decompression or reduced 
controllability of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 16241, March 25, 2014) and the FAA's response to each comment.

Request To Clarify Post-Modification Inspection Options

    Boeing requested that we revise paragraphs (j) and (l) of the NPRM 
(79 FR 16241, March 25, 2014) to clarify that the inspection options of 
paragraphs (j)(2) and (l)(2) are applicable only when the primary 
preventative modification option has been accomplished. Boeing stated 
that Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 
2013, added an alternative preventative modification option for which 
the inspection options of paragraphs (j)(2) and (l)(2) of this AD are 
not viable.
    We agree with the commenter's request because these words add 
clarity as to which inspection option should be used. We have revised 
paragraphs (j) and (l) of this AD by stating that, as of the effective 
date of this AD, for airplanes on which the alternative preventive 
modification has been accomplished, only the inspection methods 
specified by paragraphs (j)(1) and (l)(1), respectively, of this AD may 
be used.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 16241, March 25, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 16241, March 25, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 13 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                              Cost per          Cost on U.S.
            Action                  Labor cost           Parts cost            product           operators
----------------------------------------------------------------------------------------------------------------
Pre-modification inspections    11 work-hours x    $0....................            $935  $12,155.
 (retained actions from AD       $85 per hour =
 2005-13-05, Amendment 39-       $935.
 14141 (70 FR 35989, June 22,
 2005)).
Modification/inspections done   Up to 524 work-    Up to $14,874.........          59,414  $772,382.
 during modification (retained   hours x $85 per
 actions from AD 2005-13-05,     hour = $44,540.
 Amendment 39-14141 (70 FR
 35989, June 22, 2005)).

[[Page 70443]]

 
Post-modification inspections   66 work-hours x    $0....................           5,610  $72,930.
 (retained actions from AD       $85 per hour =
 2005-13-05, Amendment 39-       $5,610.
 14141 (70 FR 35989, June 22,
 2005)).
Zero-Timing Procedure Option 1  71 work-hours x    $0....................           6,035  Up to $78,455.
 (including inspections) (new    $85 per hour =
 action).                        $6,035.
Zero-Timing Procedure Option 2  103 work-hours x   $0....................           8,755  Up to $113,815.
 (including inspections) (new    $85 per hour =
 action).                        $8,755.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), and adding 
the following new AD:

2014-23-11 The Boeing Company: Amendment 39-18027 ; Docket No. FAA-
2014-0170; Directorate Identifier 2013-NM-169-AD.

(a) Effective Date

    This AD is effective December 31, 2014.

(b) Affected ADs

    This AD replaces AD 2005-13-05, Amendment 39-14141 (70 FR 35989, 
June 22, 2005).

(c) Applicability

    This AD applies to The Boeing Company Model 747-400F series 
airplanes, certificated in any category, as identified in Boeing 
Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report indicating that the upper 
chords of the upper deck floor beams at stations (STA) 340 through 
520 have been determined to be structures that are susceptible to 
widespread fatigue damage, and airplanes that had an initial 
modification done before 15,000 total flight cycles require a second 
fastener hole zero-timing modification for the airplane to meet its 
limit of validity (LOV). We are issuing this AD to detect and 
correct fatigue cracking in certain upper chords of the upper deck 
floor beam, which could result in reduced structural integrity of 
the airplane and rapid decompression or reduced controllability of 
the airplane.

(f) Compliance

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

(g) Retained Inspections With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with 
revised service information. Before the accumulation of 15,000 total 
flight cycles, or within 1,000 flight cycles after July 27, 2005 
(the effective date of AD 2005-13-05), whichever is later: 
Accomplish detailed and open-hole high frequency eddy current (HFEC) 
inspections for cracking of the web, upper chord, and upper chord 
strap of the upper deck floor beams, by doing all the applicable 
actions in accordance with Part 3.B.1. of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 
2002; or Part 1 of the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2443, Revision 2, dated August 2, 2013. As of the 
effective date of this AD, only Boeing Service Bulletin 747-53A2443, 
Revision 2, dated August 2, 2013, may be used.

(h) Retained Repair With Revised Service Information and Revised Repair 
Approval Language

    This paragraph restates the requirements of paragraph (h) of AD 
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with 
revised service information and revised repair approval language. If 
any crack is found during any inspection required by paragraph (g) 
of this AD: Before further flight, accomplish the actions required 
by paragraph (h)(1) and (h)(2) of this AD.
    (1) Repair in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, 
Revision 2, dated August 2, 2013; except where these service 
bulletins specify to contact Boeing for appropriate action, before 
further flight, repair the cracking using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD. As of the effective date of this AD, only

[[Page 70444]]

Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 
2013, may be used.
    (2) Accomplish the inspections and preventive modification of 
the floor beams by doing all the actions in accordance with Part 
3.B.2. or Part 3.B.3., as applicable, of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 
2002; or Part 2 or Part 3, as applicable, of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, 
dated August 2, 2013. If any crack is found during any inspection, 
before further flight, repair as required by paragraph (h)(1) of 
this AD. As of the effective date of this AD, only Boeing Service 
Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.

(i) Retained Modification With Revised Service Information

    This paragraph restates the requirements of paragraph (i) of AD 
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with 
revised service information. If no crack is found during any 
inspection required by paragraph (g) of this AD: Accomplish the 
actions required by either paragraph (i)(1) or (i)(2) of this AD, at 
the time specified.
    (1) Before further flight: Accomplish the inspections and 
preventive modification of the floor beam by doing all the actions 
in accordance with Part 3.B.2 or Part 3.B.3., as applicable, of the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, 
dated May 9, 2002; or Part 2 or Part 3, as applicable, of the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, 
Revision 2, dated August 2, 2013. If the preventive modification is 
performed concurrently with the inspections required by paragraph 
(g) of this AD, the upper chord straps must be removed when 
performing the open-hole HFEC inspection. If any crack is found 
during any inspection, before further flight, repair as required by 
paragraph (h)(1) of this AD. As of the effective date of this AD, 
only Boeing Service Bulletin 747-53A2443, Revision 2, dated August 
2, 2013, may be used.
    (2) Before the accumulation of 20,000 total flight cycles, or 
within 1,000 flight cycles after July 27, 2005 (the effective date 
of AD 2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), 
whichever is later: Accomplish the inspections and preventive 
modification of the upper deck floor beams, by doing all the actions 
in accordance with Part 3.B.2. or 3.B.3. as applicable, of the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, 
dated May 9, 2002; or Part 2 or Part 3, as applicable, of the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, 
Revision 2, dated August 2, 2013. If any crack is found during any 
inspection, before further flight, repair as required by paragraph 
(h)(1) of this AD. As of the effective date of this AD, only Boeing 
Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may 
be used.

(j) Retained Post-Modification Inspections With Revised Service 
Information

    This paragraph restates the requirements of paragraph (j) of AD 
2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with 
revised service information. Within 15,000 flight cycles after 
accomplishing the applicable preventive modification required by 
paragraph (h)(2), (i)(1), or (i)(2) of this AD: Accomplish the 
applicable inspections required by either paragraph (j)(1) or (j)(2) 
of this AD; if any crack is found during any inspection, before 
further flight, repair as required by paragraph (h)(1) of this AD. 
As of the effective date of this AD, for airplanes on which the 
alternative preventive modification, as identified in the NOTE after 
step 3. of ``PART 2--INSPECTION AND PREVENTIVE MODIFICATION,'' or as 
identified in the NOTE after step 4. of ``PART 3--INSPECTION AND 
PREVENTIVE MODIFICATION,'' of the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 
2013, has been done, only the inspection specified by paragraph 
(j)(1) of this AD may be used.
    (1) Accomplish detailed and surface HFEC inspections for 
cracking of the web, upper chord, and upper chord strap of the upper 
deck floor beams, by doing all the applicable actions in accordance 
with Part 3.B.4. of the Accomplishment Instructions of Boeing 
Service Bulletin 747-53A2443, dated May 9, 2002; or Part 4 of the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, 
Revision 2, dated August 2, 2013. If no crack is found, repeat the 
inspections at intervals not to exceed 1,000 flight cycles. As of 
the effective date of this AD, only Boeing Service Bulletin 747-
53A2443, Revision 2, dated August 2, 2013, may be used.
    (2) Accomplish detailed and open-hole HFEC inspections for 
cracking of the web, upper chord, and strap of the upper deck floor 
beams, by doing all the applicable actions in accordance with Part 
3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin 
747-53A2443, dated May 9, 2002; or Part 5 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, 
dated August 2, 2013. If no crack is found, repeat the inspections 
at intervals not to exceed 5,000 flight cycles. As of the effective 
date of this AD, only Boeing Service Bulletin 747-53A2443, Revision 
2, dated August 2, 2013, may be used.

(k) New Floor Beam Hole Zero-Timing

    Within 20,000 flight cycles after accomplishing the preventive 
modification of the Station 340 to Station 520 upper deck floor 
beams specified in paragraph (h)(2), (i)(1), or (i)(2) of this AD, 
or within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later: Accomplish the floor beam hole zero-timing, 
in accordance with Part 6 of the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 
2013.

(l) New Post-Modification Floor Beam Hole Zero-Timing Inspections

    Within 15,000 flight cycles after accomplishing the floor beam 
hole zero-timing required by paragraph (k) of this AD: Accomplish 
the applicable inspections required by paragraph (l)(1) or (l)(2) of 
this AD; if any cracking is found during any inspection, before 
further flight, repair as required by paragraph (h)(1) of this AD. 
As of the effective date of this AD, for airplanes on which the 
alternative preventive modification, as identified in the NOTE after 
step 3. of ``PART 2--INSPECTION AND PREVENTIVE MODIFICATION,'' or as 
identified in the NOTE after step 4. of ``PART 3--INSPECTION AND 
PREVENTIVE MODIFICATION,'' of the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 
2013, has been done, only the inspection method specified by 
paragraph (l)(1) of this AD may be used.
    (1) Accomplish detailed and surface HFEC inspections for 
cracking of the web, upper chord, and straps of the Station 340 to 
Station 520 upper deck floor beams, by doing all the applicable 
actions, in accordance with Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, 
dated August 2, 2013. If no cracking is found, repeat the 
inspections at intervals not to exceed 1,000 flight cycles.
    (2) Accomplish detailed and open-hole HFEC inspections for 
cracking of the web, upper chord, and straps of the Station 340 to 
Station 520 upper deck floor beams, by doing all the applicable 
actions, in accordance with Part 5 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, 
dated August 2, 2013. If no cracking is found, repeat the 
inspections at intervals not to exceed 5,000 flight cycles.

(m) Exception to Service Information

    Where Boeing Service Bulletin 747-53A2443, Revision 2, dated 
August 2, 2013, specifies a compliance time ``after the revision 
date on this service bulletin,'' this AD requires compliance within 
the specified compliance time after the effective date of this AD.

(n) Credit for Previous Actions

    This paragraph provides credit for the inspections, repairs, and 
modification required by paragraphs (g) through (j) of this AD, if 
the corresponding actions were performed before the effective date 
of this AD using Boeing Service Bulletin 747-53A2443, Revision 1, 
dated June 25, 2009.

(o) 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 (p)(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

[[Page 70445]]

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 for AD 2005-13-05, Amendment 39-14141 (70 FR 
35989, June 22, 2005), are approved as AMOCs for the corresponding 
requirements of paragraphs (g) through (j) (the retained actions) of 
this AD.

(p) 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(5) and (q)(6) of this AD.

(q) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
December 31, 2014.
    (i) Boeing Service Bulletin 747-53A2443, Revision 2, dated 
August 2, 2013.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
July 27, 2005 (70 FR 35989, June 22, 2005).
    (i) Boeing Service Bulletin 747-53A2443, dated May 9, 2002.
    (ii) Reserved.
    (5) 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.
    (6) You may view this 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on November 6, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-27358 Filed 11-25-14; 8:45 am]
BILLING CODE 4910-13-P