Airworthiness Directives; The Boeing Company Airplanes, 21726-21729 [2016-08271]

Download as PDF 21726 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations jstallworth on DSK7TPTVN1PROD with RULES having P/N C16291AA after accomplishing the specified modification. (3) For airplanes on which Thales P/N C16291AA or P/N C16291AB AOA sensors are installed as of the effective date of this AD: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, as of the effective date of this AD. (4) For airplanes on which the replacement required by paragraph (i) of this AD has been done: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing the replacement. (5) For airplanes on which the replacement required by paragraph (g) of this AD has been done: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing the replacement, except that a UTAS AOA sensor having P/N 0861ED may be installed in the standby position of that airplane. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can VerDate Sep<11>2014 14:03 Apr 12, 2016 Jkt 238001 be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. DEPARTMENT OF TRANSPORTATION (q) Related Information 14 CFR Part 39 (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0134, dated July 8, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2015–4810. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3) and (r)(4) of this AD. [Docket No. FAA–2015–2464; Directorate Identifier 2014–NM–195–AD; Amendment 39–18476; AD 2016–07–31] (r) Material Incorporated by Reference SUMMARY: (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 this AD specifies otherwise. (i) Airbus Service Bulletin A330–34–3215, Revision 03, dated July 23, 2015. (ii) Airbus Service Bulletin A330–34–3228, dated October 7, 2009. (iii) Airbus Service Bulletin A330–34– 3315, dated March 26, 2015. (iv) Airbus Service Bulletin A340–34– 4215, Revision 03, dated July 27, 2015. (v) Airbus Service Bulletin A340–34–4234, dated October 7, 2009. (vi) Airbus Service Bulletin A340–34– 4294, dated March 26, 2015. (vii) Airbus Service Bulletin A340–34– 5062, Revision 02, dated July 24, 2015. (viii) Airbus Service Bulletin A340–34– 5070, dated October 9, 2009. (ix) Airbus Service Bulletin A340–34– 5105, dated March 26, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 26, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–08267 Filed 4–12–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2013–22– 11 for certain The Boeing Company Model 747–400 and –400D series airplanes. AD 2013–22–11 required repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. Since we issued AD 2013–22–11, we received a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013–22–11. This AD adds additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam. Such cracks could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane. DATES: This AD is effective May 18, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 18, 2016. ADDRESSES: For service information identified in this final rule, 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. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2464. E:\FR\FM\13APR1.SGM 13APR1 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2464; 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 2013–22–11, Amendment 39–17643 (78 FR 66254, November 5, 2013), (‘‘AD 2013–22–11’’). AD 2013–22–11 applied to certain The Boeing Company Model 747–400 and –400D series airplanes. The NPRM published in the Federal Register on July 23, 2015 (80 FR 43648) (‘‘the NPRM’’). The NPRM was prompted by a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013–22–11. The NPRM proposed to continue to require repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. The NPRM also proposed to require additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam. Such cracking could become large and cause the floor beams to become severed and result in 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 and the FAA’s response to each comment. United Airlines supported the NPRM. Request To Revise ‘‘Exceptions to Service Information Specifications’’ Boeing requested that paragraph (m)(4), ‘‘Exceptions to Service Information Specifications,’’ of the proposed AD be revised. Boeing stated that Boeing Alert Service Bulletin 747– 53A2688, Revision 1, dated September 19, 2012, which is included in paragraph (m)(4), has the same compliance time as table 3 in Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014; therefore, Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, should also be included in paragraph (m)(4) of the proposed AD. For the reason provided by the commenter we agree to include Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, in paragraph (m)(4) of this AD. We have also revised paragraph (m)(4) of this AD 21727 by removing the reference to Boeing Alert Service Bulletin 747–53A2688, Revision 1, dated September 19, 2012, because this AD only refers to Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, for compliance times. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. The service information describes procedures for upper deck floor beam upper chord inspection and repair at floor panel attachment fastener holes in section 41 and section 42. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 84 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Inspection (retained actions from AD 2013–22–11). jstallworth on DSK7TPTVN1PROD with RULES New inspections ..................... Labor cost Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Sep<11>2014 14:03 Apr 12, 2016 Jkt 238001 Cost on U.S. operators $0 Up to $26,265 per inspection cycle. Up to $2,206,260 per inspection cycle. 0 Up to 309 work-hours × $85 per hour = $26,265 per inspection cycle. Up to 241 work-hours × $85 per hour = $20,485. We have received no definitive data that will enable us to provide a cost estimate for the repair or modification specified in this AD. Cost per product Up to $20,485 per inspection cycle. Up to $1,720,740 per inspection cycle. Parts cost 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, PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 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 E:\FR\FM\13APR1.SGM 13APR1 21728 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 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 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) 2013–22–11, Amendment 39–17643 (78 FR 66254, November 5, 2013), and adding the following new AD: ■ 2016–07–31 The Boeing Company: Amendment 39–18476; Docket No. FAA–2015–2464; Directorate Identifier 2014–NM–195–AD. jstallworth on DSK7TPTVN1PROD with RULES (a) Effective Date This AD is effective May 18, 2016. (b) Affected ADs This AD replaces AD 2013–22–11, Amendment 39–17643 (78 FR 66254, November 5, 2013) (‘‘AD 2013–22–11’’). (c) Applicability This AD applies to The Boeing Company Model 747–400 and –400D series airplanes, VerDate Sep<11>2014 14:03 Apr 12, 2016 Jkt 238001 (g) Section 41—Repetitive Inspections, and Corrective Actions (h) Section 41—Repetitive Inspection of Repaired or Modified Holes, and Corrective Actions For airplanes on which a repair specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747– 53A2688, Revision 2, dated August 21, 2014, is done, or a modification specified in Figure 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, is done: At the applicable time specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(3) of this AD, do open hole or surface HFEC for cracking of repaired or modified floor panel attachment holes in the upper deck floor beam upper chords, in accordance with Part 1 or Part 3, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the inspections thereafter at the applicable time specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. At the applicable time specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, do open hole or surface high frequency eddy current inspections (HFEC) for cracking of the floor panel attachment holes in the upper deck floor beam upper chords, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection, before further flight, repair in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, or repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the inspections thereafter at the applicable time specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, until an action specified in paragraph (g)(1) or (g)(2) of this AD is done. (1) Doing a repair as a hole modification in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD, terminates the inspections required by paragraph (g) of this AD for the modified hole only. (2) Doing a modification in accordance with Figure 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD, terminates the inspections required by paragraph (g) of this AD for the modification only. (i) Section 44—Repetitive Inspection, and Corrective Actions For airplanes identified in Group 1 in Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014: At the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(4) of this AD, do open hole or surface HFEC inspections of the floor panel attachment holes in the upper deck floor beam upper chords, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection required by this paragraph, before further flight, repair in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD. Repeat the inspections thereafter at the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, until an action specified in paragraph (i)(1) or (i)(2) of this AD is done. (1) Doing a repair as a hole modification in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(2) of this AD, terminates the inspections required by paragraph (i) of this AD for that modified hole only. (2) Doing a modification in accordance with Figure 21 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder indicating that certain upper chords of the upper deck floor beam are subject to widespread fatigue damage. This AD was also prompted by reports that certain fastener holes in the upper deck floor beam upper chords in Section 41, may not have been inspected in accordance with AD 2013–22–11. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM 13APR1 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 2014, except as required by paragraph (m)(2) of this AD, terminates the inspections required by paragraph (i) of this AD for that modified hole only. (j) Section 44—Repetitive Inspection of Repaired or Modified Holes, and Corrective Actions For airplanes identified in Group 1 in Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, on which a repair specified in Part 5 of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, is done or the modification specified in Figure 21 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, is done: At the applicable time specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(3) of this AD, do open hole or surface HFEC inspections of repaired or modified floor panel attachment holes in the upper deck floor beam upper chords, in accordance with Part 4 or Part 6, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the inspections thereafter at the applicable time specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. jstallworth on DSK7TPTVN1PROD with RULES (k) Sections 41 and 44—Replacement and Post-Replacement Repetitive Inspections At the applicable time specified in table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014: Replace all upper deck floor beam upper chords, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. Within 20,000 flight cycles after doing the replacement, do the inspections specified in paragraphs (g) and (i) of this AD, as applicable. Thereafter, repeat the inspections required by paragraphs (g) and (i) of this AD, as applicable, at the times specified in paragraphs (g) and (i) of this AD. (l) Section 41—Repetitive Inspection of Plugged or Re-Used Holes, and Corrective Actions For airplanes identified in Group 2 in Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014: At the applicable time specified in table 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, except as required by paragraph (m)(1) of this AD, at all plugged or reused floor panel attachment holes in the affected floor beam upper chords, do a surface HFEC inspection of the upper deck floor beam upper chords and detailed inspection for cracks on the vertical flange, in accordance with Part 8 of the Accomplishment Instructions of Boeing Alert VerDate Sep<11>2014 14:03 Apr 12, 2016 Jkt 238001 Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. If any crack is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the inspections thereafter at the applicable time specified in table 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014. (m) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, specifies a compliance time ‘‘after the Revision 2 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 747–53A2688, Revision 2, dated August 21, 2014; specifies to contact Boeing for certain procedures: Do the specified actions before further flight using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (3) Where table 2 or table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, specifies to contact Boeing for inspections and compliance times: Before further flight, contact the Manager, Seattle Aircraft Certification Office (ACO), FAA, for inspections and compliance times and accomplish the inspections at the given times. (4) Where Boeing Alert Service Bulletin 747–53A2688, Revision 2, dated August 21, 2014, specifies a compliance time ‘‘after the Revision 1 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after December 10, 2013 (the effective date of AD 2013–22–11). (n) Credit for Previous Actions (1) This paragraph restates the requirements of paragraph (o) of AD 2013– 22–11, with new reference to paragraph (h) of this AD. This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before December 10, 2013 (the effective date of AD 2013–22–11), using Boeing Alert Service Bulletin 747–53A2688, dated August 21, 2008, which was incorporated by reference in AD 2009–10–16, Amendment 39–15901 (74 FR 22424, May 13, 2009). (2) This paragraph provides credit for the actions required by paragraphs (g) through (k) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2688, Revision 1, dated September 19, 2012, which was incorporated by reference in AD 2013– 22–11. (o) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 PO 00000 Frm 00031 Fmt 4700 Sfmt 9990 21729 to the manager of the ACO, send it to the attention of the person identified in paragraph (p) 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, modification, or alteration 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. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2013–22–11 are approved as AMOCs for the corresponding provisions of paragraphs (g) through (k) of this AD. (p) Related Information 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. (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. (i) Boeing Alert Service Bulletin 747– 53A2688, Revision 2, dated August 21, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; phone: 206–544– 5000, extension 1; fax: 206–766–5680; Internet https://www.myboeingfleet.com. (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: https://www.archives. gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on March 30, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–08271 Filed 4–12–16; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\13APR1.SGM 13APR1

Agencies

[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)]
[Rules and Regulations]
[Pages 21726-21729]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08271]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2464; Directorate Identifier 2014-NM-195-AD; 
Amendment 39-18476; AD 2016-07-31]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2013-22-11 for 
certain The Boeing Company Model 747-400 and -400D series airplanes. AD 
2013-22-11 required repetitive inspections to detect cracks in the 
floor panel attachment fastener holes of certain upper deck floor beam 
upper chords, repetitive inspections, corrective actions if necessary, 
and replacement of the upper deck floor beam upper chords. Since we 
issued AD 2013-22-11, we received a report that certain fastener holes 
in the upper deck floor beam upper chords may not have been inspected 
in accordance with AD 2013-22-11. This AD adds additional repetitive 
inspections for cracks for certain airplanes, and corrective actions if 
necessary. We are issuing this AD to detect and correct fatigue 
cracking in certain upper chords of the upper deck floor beam. Such 
cracks could become large and cause the floor beams to become severed 
and result in rapid decompression or reduced controllability of the 
airplane.

DATES: This AD is effective May 18, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 18, 
2016.

ADDRESSES: For service information identified in this final rule, 
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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2464.

[[Page 21727]]

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2464; 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 2013-22-11, Amendment 39-17643 (78 FR 66254, 
November 5, 2013), (``AD 2013-22-11''). AD 2013-22-11 applied to 
certain The Boeing Company Model 747-400 and -400D series airplanes. 
The NPRM published in the Federal Register on July 23, 2015 (80 FR 
43648) (``the NPRM''). The NPRM was prompted by a report that certain 
fastener holes in the upper deck floor beam upper chords may not have 
been inspected in accordance with AD 2013-22-11. The NPRM proposed to 
continue to require repetitive inspections to detect cracks in the 
floor panel attachment fastener holes of certain upper deck floor beam 
upper chords, repetitive inspections, corrective actions if necessary, 
and replacement of the upper deck floor beam upper chords. The NPRM 
also proposed to require additional repetitive inspections for cracks 
for certain airplanes, and corrective actions if necessary. We are 
issuing this AD to detect and correct fatigue cracking in certain upper 
chords of the upper deck floor beam. Such cracking could become large 
and cause the floor beams to become severed and result in 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 and 
the FAA's response to each comment. United Airlines supported the NPRM.

Request To Revise ``Exceptions to Service Information Specifications''

    Boeing requested that paragraph (m)(4), ``Exceptions to Service 
Information Specifications,'' of the proposed AD be revised. Boeing 
stated that Boeing Alert Service Bulletin 747-53A2688, Revision 1, 
dated September 19, 2012, which is included in paragraph (m)(4), has 
the same compliance time as table 3 in Boeing Alert Service Bulletin 
747-53A2688, Revision 2, dated August 21, 2014; therefore, Boeing Alert 
Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, should 
also be included in paragraph (m)(4) of the proposed AD.
    For the reason provided by the commenter we agree to include Boeing 
Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, 
in paragraph (m)(4) of this AD. We have also revised paragraph (m)(4) 
of this AD by removing the reference to Boeing Alert Service Bulletin 
747-53A2688, Revision 1, dated September 19, 2012, because this AD only 
refers to Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated 
August 21, 2014, for compliance times.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2688, Revision 2, 
dated August 21, 2014. The service information describes procedures for 
upper deck floor beam upper chord inspection and repair at floor panel 
attachment fastener holes in section 41 and section 42. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 84 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from  Up to 309 work-                  $0  Up to $26,265 per    Up to $2,206,260
 AD 2013-22-11).                    hours x $85 per                      inspection cycle.    per inspection
                                    hour = $26,265 per                                        cycle.
                                    inspection cycle.
New inspections..................  Up to 241 work-                   0  Up to $20,485 per    Up to $1,720,740
                                    hours x $85 per                      inspection cycle.    per inspection
                                    hour = $20,485.                                           cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
a cost estimate for the repair or modification 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

[[Page 21728]]

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) 
2013-22-11, Amendment 39-17643 (78 FR 66254, November 5, 2013), and 
adding the following new AD:

2016-07-31 The Boeing Company: Amendment 39-18476; Docket No. FAA-
2015-2464; Directorate Identifier 2014-NM-195-AD.

(a) Effective Date

    This AD is effective May 18, 2016.

(b) Affected ADs

    This AD replaces AD 2013-22-11, Amendment 39-17643 (78 FR 66254, 
November 5, 2013) (``AD 2013-22-11'').

(c) Applicability

    This AD applies to The Boeing Company Model 747-400 and -400D 
series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated August 
21, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder indicating that certain upper chords of the upper deck floor 
beam are subject to widespread fatigue damage. This AD was also 
prompted by reports that certain fastener holes in the upper deck 
floor beam upper chords in Section 41, may not have been inspected 
in accordance with AD 2013-22-11. We are issuing this AD to detect 
and correct fatigue cracking in certain upper chords of the upper 
deck floor beam, which could become large and cause the floor beams 
to become severed and result in rapid decompression or reduced 
controllability of the airplane.

(f) Compliance

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

(g) Section 41--Repetitive Inspections, and Corrective Actions

    At the applicable time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, 
Revision 2, dated August 21, 2014, do open hole or surface high 
frequency eddy current inspections (HFEC) for cracking of the floor 
panel attachment holes in the upper deck floor beam upper chords, in 
accordance with Part 1 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 
2014. If any crack is found during any inspection, before further 
flight, repair in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 
2, dated August 21, 2014, or repair using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD. Repeat the inspections thereafter at the applicable time 
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 
2014, until an action specified in paragraph (g)(1) or (g)(2) of 
this AD is done.
    (1) Doing a repair as a hole modification in accordance with 
Part 2 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as 
required by paragraph (m)(2) of this AD, terminates the inspections 
required by paragraph (g) of this AD for the modified hole only.
    (2) Doing a modification in accordance with Figure 5 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014, except as required by 
paragraph (m)(2) of this AD, terminates the inspections required by 
paragraph (g) of this AD for the modification only.

(h) Section 41--Repetitive Inspection of Repaired or Modified Holes, 
and Corrective Actions

    For airplanes on which a repair specified in Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014, is done, or a 
modification specified in Figure 5 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 
2, dated August 21, 2014, is done: At the applicable time specified 
in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, 
except as required by paragraph (m)(3) of this AD, do open hole or 
surface HFEC for cracking of repaired or modified floor panel 
attachment holes in the upper deck floor beam upper chords, in 
accordance with Part 1 or Part 3, as applicable, of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014. If any crack is found 
during any inspection required by this paragraph, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (o) of this AD. Repeat the 
inspections thereafter at the applicable time specified in table 2 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2688, Revision 2, dated August 21, 2014.

(i) Section 44--Repetitive Inspection, and Corrective Actions

    For airplanes identified in Group 1 in Boeing Alert Service 
Bulletin 747-53A2688, Revision 2, dated August 21, 2014: At the 
applicable time specified in table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, 
Revision 2, dated August 21, 2014, except as required by paragraph 
(m)(4) of this AD, do open hole or surface HFEC inspections of the 
floor panel attachment holes in the upper deck floor beam upper 
chords, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated 
August 21, 2014. If any crack is found during any inspection 
required by this paragraph, before further flight, repair in 
accordance with Part 5 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2688, Revision 2, dated August 21, 
2014, except as required by paragraph (m)(2) of this AD. Repeat the 
inspections thereafter at the applicable time specified in table 3 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2688, Revision 2, dated August 21, 2014, until an action 
specified in paragraph (i)(1) or (i)(2) of this AD is done.
    (1) Doing a repair as a hole modification in accordance with 
Part 5 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2688, Revision 2, dated August 21, 2014, except as 
required by paragraph (m)(2) of this AD, terminates the inspections 
required by paragraph (i) of this AD for that modified hole only.
    (2) Doing a modification in accordance with Figure 21 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21,

[[Page 21729]]

2014, except as required by paragraph (m)(2) of this AD, terminates 
the inspections required by paragraph (i) of this AD for that 
modified hole only.

(j) Section 44--Repetitive Inspection of Repaired or Modified Holes, 
and Corrective Actions

    For airplanes identified in Group 1 in Boeing Alert Service 
Bulletin 747-53A2688, Revision 2, dated August 21, 2014, on which a 
repair specified in Part 5 of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014, is done or the 
modification specified in Figure 21 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 
2, dated August 21, 2014, is done: At the applicable time specified 
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2688, Revision 2, dated August 21, 2014, 
except as required by paragraph (m)(3) of this AD, do open hole or 
surface HFEC inspections of repaired or modified floor panel 
attachment holes in the upper deck floor beam upper chords, in 
accordance with Part 4 or Part 6, as applicable, of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2688, Revision 2, dated August 21, 2014. If any crack is found 
during any inspection by this paragraph, before further flight, 
repair using a method approved in accordance with the procedures 
specified in paragraph (o) of this AD. Repeat the inspections 
thereafter at the applicable time specified in table 4 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, 
Revision 2, dated August 21, 2014.

(k) Sections 41 and 44--Replacement and Post-Replacement Repetitive 
Inspections

    At the applicable time specified in table 5 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, 
Revision 2, dated August 21, 2014: Replace all upper deck floor beam 
upper chords, in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2688, Revision 
2, dated August 21, 2014. Within 20,000 flight cycles after doing 
the replacement, do the inspections specified in paragraphs (g) and 
(i) of this AD, as applicable. Thereafter, repeat the inspections 
required by paragraphs (g) and (i) of this AD, as applicable, at the 
times specified in paragraphs (g) and (i) of this AD.

(l) Section 41--Repetitive Inspection of Plugged or Re-Used Holes, and 
Corrective Actions

    For airplanes identified in Group 2 in Boeing Alert Service 
Bulletin 747-53A2688, Revision 2, dated August 21, 2014: At the 
applicable time specified in table 6 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2688, 
Revision 2, dated August 21, 2014, except as required by paragraph 
(m)(1) of this AD, at all plugged or reused floor panel attachment 
holes in the affected floor beam upper chords, do a surface HFEC 
inspection of the upper deck floor beam upper chords and detailed 
inspection for cracks on the vertical flange, in accordance with 
Part 8 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2688, Revision 2, dated August 21, 2014. If any 
crack is found during any inspection required by this paragraph, 
before further flight, repair using a method approved in accordance 
with the procedures specified in paragraph (o) of this AD. Repeat 
the inspections thereafter at the applicable time specified in table 
6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2688, Revision 2, dated August 21, 2014.

(m) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 747-53A2688, Revision 2, 
dated August 21, 2014, specifies a compliance time ``after the 
Revision 2 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 747-53A2688, Revision 2, 
dated August 21, 2014; specifies to contact Boeing for certain 
procedures: Do the specified actions before further flight using a 
method approved in accordance with the procedures specified in 
paragraph (o) of this AD.
    (3) Where table 2 or table 4 of paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated 
August 21, 2014, specifies to contact Boeing for inspections and 
compliance times: Before further flight, contact the Manager, 
Seattle Aircraft Certification Office (ACO), FAA, for inspections 
and compliance times and accomplish the inspections at the given 
times.
    (4) Where Boeing Alert Service Bulletin 747-53A2688, Revision 2, 
dated August 21, 2014, specifies a compliance time ``after the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after December 10, 
2013 (the effective date of AD 2013-22-11).

(n) Credit for Previous Actions

    (1) This paragraph restates the requirements of paragraph (o) of 
AD 2013-22-11, with new reference to paragraph (h) of this AD. This 
paragraph provides credit for the actions required by paragraphs (g) 
and (h) of this AD, if those actions were performed before December 
10, 2013 (the effective date of AD 2013-22-11), using Boeing Alert 
Service Bulletin 747-53A2688, dated August 21, 2008, which was 
incorporated by reference in AD 2009-10-16, Amendment 39-15901 (74 
FR 22424, May 13, 2009).
    (2) This paragraph provides credit for the actions required by 
paragraphs (g) through (k) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Alert 
Service Bulletin 747-53A2688, Revision 1, dated September 19, 2012, 
which was incorporated by reference in AD 2013-22-11.

(o) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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) 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, modification, or alteration 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. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane and the approval must 
specifically refer to this AD.
    (4) AMOCs approved for AD 2013-22-11 are approved as AMOCs for 
the corresponding provisions of paragraphs (g) through (k) of this 
AD.

(p) Related Information

    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.

(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.
    (i) Boeing Alert Service Bulletin 747-53A2688, Revision 2, dated 
August 21, 2014.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; phone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 30, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08271 Filed 4-12-16; 8:45 am]
 BILLING CODE 4910-13-P
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