Airworthiness Directives; The Boeing Company Airplanes, 18456-18460 [2016-07024]

Download as PDF jstallworth on DSK7TPTVN1PROD with RULES 18456 Federal Register / Vol. 81, No. 62 / Thursday, March 31, 2016 / Rules and Regulations participants for the 12-month period February 1, 2014 to January 31, 2015; (5) For FY 2017, 60 percent based on a State’s FY 2009 SNAP-Ed expenditures, and 40 percent based on the State’s share of national SNAP participants for the 12-month period February 1, 2015 to January 31, 2016; and, (6) For FY 2018 and subsequent years, 50 percent based on a State’s FY 2009 SNAP-Ed expenditures, and 50 percent based on the State’s share of national SNAP participants for the previous 12month period ending January 31; (F) If a participating State agency notifies FNS as required in (ix) above that it will not obligate or expend all of the funds allocated to it for a fiscal year under this section, FNS may reallocate the unobligated or unexpended funds to other participating State agencies that have approved SNAP-Ed Plans during the period for which the funding is available for new obligations by FNS. Reallocated funds received by a State will be considered part of its base FY 2009 allocation for the purpose of determining the State’s allocation for the next fiscal year; funds surrendered by a State shall not be considered part of its base FY 2009 allocation for the next fiscal year for the purpose of determining the State’s allocation for the next fiscal year. (xi) Fiscal recordkeeping and reporting requirements. Each participating State agency must meet FNS fiscal recordkeeping and reporting requirements. Total SNAP-Ed expenditures and State, private, and other contributions to SNAP-Ed activities are reported through the financial reporting means and in the timeframe designated by FNS; (xii) Additional information may be required of the State agency, on an as needed basis, regarding the type of nutrition education and obesity prevention activities offered and the characteristics of the target population served, depending on the contents of the State’s SNAP-Ed Plan, to determine whether nutrition education goals are being met; (xiii) The State agency must submit a SNAP-Ed Annual Report to FNS by January 31 of each year. The report shall describe SNAP-Ed Plan project activities, outcomes, and budget for the prior year. (e) * * * (6) The SNAP-Ed Plan shall be signed by the head of the State agency and submitted prior to funding of nutrition education and obesity prevention activities when the State agency elects to request Federal grant funds to conduct these SNAP-Ed activities. The VerDate Sep<11>2014 15:13 Mar 30, 2016 Jkt 238001 Plan shall be submitted for approval no later than August 15. Approved plans become effective the following FFY October 1 to September 30. * * * * * Dated: March 24, 2016. Audrey Rowe, Administrator, Food and Nutrition Service. [FR Doc. 2016–07179 Filed 3–30–16; 8:45 am] BILLING CODE 3410–30–P DEPARTMENT OF AGRICULTURE Rural Housing Service 7 CFR Part 3555 RIN 0575–AD00 Single Family Housing Guaranteed Loan Program Correction Rule document 2016–07049, beginning on page 17361 in the issue of Tuesday, March 29, 2016, was inadvertently published and is withdrawn from that issue. [FR Doc. C1–2016–07049 Filed 3–29–16; 4:15 pm] BILLING CODE 1505–01–D DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3983; Directorate Identifier 2015–NM–141–AD; Amendment 39–18448; AD 2016–07–03] 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 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747SR, and 747SP series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper chords of the upper deck floor beams are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracks at the floor panel attachment fastener holes; repetitive inspections for cracks in the upper and lower chords of the upper deck floor beams at permanent fastener locations; repetitive inspections for cracks in certain repaired and modified SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 areas; and related investigative and corrective actions if necessary. This AD also requires repetitive replacement of the upper chords of the upper deck floor beams, including pre-replacement inspections and corrective action if necessary; and post-replacement repetitive inspections and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. DATES: This AD is effective May 5, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 5, 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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3983. 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–2015– 3983; 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, 1601 Lind Avenue SW., Renton, WA E:\FR\FM\31MRR1.SGM 31MRR1 Federal Register / Vol. 81, No. 62 / Thursday, March 31, 2016 / Rules and Regulations 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 by adding an AD that would apply to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747SR, and 747SP series airplanes. The NPRM published in the Federal Register on October 6, 2015 (80 FR 60303) (‘‘the NPRM’’). The NPRM was prompted by an evaluation by the DAH indicating that the upper chords of the upper deck floor beams are subject to WFD. The NPRM proposed to require repetitive inspections for cracks at the floor panel attachment fastener holes; repetitive inspections for cracks in the upper and lower chords of the upper deck floor beams at permanent fastener locations; repetitive inspections for cracks in certain repaired and modified areas; and related investigative and corrective actions if necessary. The NPRM also proposed to require repetitive replacement of the upper chords of the upper deck floor beams, including prereplacement inspections and corrective action if necessary; and postreplacement repetitive inspections and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. jstallworth on DSK7TPTVN1PROD with RULES 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. A member of the public supported the NPRM and an anonymous commenter had no objection to the NPRM. Request To Clarify Credit for Previous Actions Boeing requested that we clarify that credit for previous actions is limited to those actions that comply with the new proposed requirements of the NPRM. Boeing noted that paragraph (m) of the proposed AD should provide credit for using Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003, VerDate Sep<11>2014 15:13 Mar 30, 2016 Jkt 238001 provided the new requirements specified in Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012, are met. We agree that clarification is necessary. Paragraph (m) of this AD, ‘‘Credit for Previous Actions,’’ provides credit for actions done before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003, for the corresponding actions required by paragraphs (g), (h), and (i) of this AD. Paragraphs (g), (h), and (i) of this AD refer to Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012, as the appropriate source of service information for accomplishing the actions required by those paragraphs. Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012, added certain inspection locations. Therefore, for the added inspection locations specified in Boeing Alert Service Bulletin 747– 53A2452, Revision 1, dated July 16, 2012, paragraph (m) of this AD does not provide credit because Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003, cannot be used for those locations. We have revised paragraph (m) of this AD to clarify that although credit is given for using Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003, actions required by paragraphs (g), (h), and (i) of this AD that are not identified in Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003, must still be done. Boeing also stated that credit should be given in the NPRM for Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012; and Boeing Alert Service Bulletin 747–53A2852, dated June 22, 2012. We have not included Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012; and Boeing Alert Service Bulletin 747–53A2852, dated June 22, 2012; in paragraph (m) of this AD because that service information is already cited in paragraphs (g) through (k) of this AD as the only appropriate source of service information for accomplishing the actions required by this AD. As allowed by the phrase, ‘‘unless already done,’’ in paragraph (f) of this AD, if the requirements of this AD have already been accomplished, this AD does not require that those actions be repeated. Request To Give Credit for Previous Alternative Methods of Compliance (AMOCs) Boeing requested that previously approved AMOCs for AD 2005–20–29, Amendment 39–14326 (70 FR 59246, October 12, 2005), be approved for the PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 18457 corresponding provisions of the proposed AD, provided the previously approved AMOCs satisfy the inspection locations and compliance times specified by the proposed AD. Boeing noted that AMOCs would be needed for new inspection locations and compliance times specified in the proposed AD. We acknowledge that certain AMOCs for AD 2005–20–29, Amendment 39– 14326 (70 FR 59246, October 12, 2005), might also address the actions and compliance times required by this AD. However, each individual AMOC would need to be evaluated to ensure the identified unsafe condition is addressed. Any person may request approval of an AMOC under the provisions of paragraph (o) of this AD. We have not changed this final rule in this regard. 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 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 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 the following service information. • Boeing Alert Service Bulletin 747– 53A2452, Revision 1, dated July 16, 2012. This service information describes procedures for repetitive open hole or surface high frequency eddy current (HFEC) inspections, as applicable, for cracks at the floor panel attachment fastener holes in certain areas and stations; repetitive surface HFEC inspections for cracks in the upper and lower chords of the upper deck floor beams at permanent fastener locations in certain areas and stations; and related investigative and corrective actions. This service information also describes procedures, for airplanes on which certain repairs or modifications are done, for repetitive open hole or surface HFEC inspections, as applicable, for cracks in the repaired and modified areas; and repair. • Boeing Alert Service Bulletin 747– 53A2852, dated June 22, 2012. This E:\FR\FM\31MRR1.SGM 31MRR1 18458 Federal Register / Vol. 81, No. 62 / Thursday, March 31, 2016 / Rules and Regulations service information describes procedures for repetitive replacement of the upper chords of the upper deck floor beams, including pre-replacement inspections and corrective action, and post-replacement repetitive inspections and repair. 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 67 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspections specified in Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. Replacement specified in Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012. Post-replacement inspections specified in Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012. Up to 884 work-hours × $85 per hour = $75,140, per inspection cycle. Up to 696 work-hours × $85 per hour = $59,160, per replacement. Up to 586 work-hours × $85 per hour = $49,810, per inspection cycle. 1 We Cost per product Cost on U.S. operators $0 $5,034,380, per inspection cycle. $0 $59,160, per replacement $3,963,720, per replacement. $0 1 $75,140, per inspection cycle. $49,810, per inspection cycle. $3,337,270, per inspection cycle. currently have no specific cost estimates associated with the parts necessary for the replacement. 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. (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. Regulatory Findings jstallworth on DSK7TPTVN1PROD with RULES Parts cost § 39.13 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, ■ VerDate Sep<11>2014 17:06 Mar 30, 2016 Jkt 238001 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2016–07–03 The Boeing Company: Amendment 39–18448 ; Docket No. FAA–2015–3983; Directorate Identifier 2015–NM–141–AD. (a) Effective Date This AD is effective May 5, 2016. (b) Affected ADs This AD affects AD 2005–20–29, Amendment 39–14326 (70 FR 59246, October 12, 2005). PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747SR, and 747SP series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 747–53A2852, dated June 22, 2012. (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 (DAH) indicating that the upper chords of the upper deck floor beams are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections of the Upper Chords of the Upper Deck Floor Beams At the applicable times specified in Tables 1 through 7 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747– 53A2452, Revision 1, dated July 16, 2012, except as required by paragraph (l)(1) of this AD: Do the inspections specified in paragraphs (g)(1) and (g)(2) of this AD, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012, except as required by paragraph (l)(2) of this AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable E:\FR\FM\31MRR1.SGM 31MRR1 Federal Register / Vol. 81, No. 62 / Thursday, March 31, 2016 / Rules and Regulations times specified in Tables 1 through 7 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012. Do all applicable related investigative and corrective actions before further flight. Doing the inspections required by paragraphs (g)(1) and (g)(2) of this AD terminates the inspections required by paragraphs (m) and (n) of AD 2005–20–29, Amendment 39– 14326 (70 FR 59246, October 12, 2005). (1) Do an open hole or surface high frequency eddy current (HFEC) inspection, as applicable, for cracks at the fastener holes of the floor panel attachment in the applicable areas and stations identified in Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012. (2) Do a surface HFEC inspection for cracks in the upper and lower chords of the upper deck floor beams at permanent fastener locations in the applicable areas and stations identified in Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012. jstallworth on DSK7TPTVN1PROD with RULES (h) Terminating Modification and Repair for the Inspection Specified in Paragraph (g)(1) of This AD A fastener hole modification or a fastener hole repair in Area 1 or Area 2 as described in Boeing Alert Service Bulletin 747– 53A2452, Revision 1, dated July 16, 2012, terminates the inspection of the fastener holes of the floor panel attachment required by paragraph (g)(1) of this AD for the repaired or modified area only, provided the modification and repair, including related investigative and corrective actions, are done in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012, except as required by paragraph (l)(2) of this AD. (i) Post Modification/Repair Repetitive Inspections (1) For airplanes on which any fastener hole modification or any fastener hole repair was done as specified in Boeing Alert Service Bulletin 747–53A2452: Except as required by paragraph (i)(2) of this AD, at the applicable times specified in Tables 8 and 9 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later, do an open hole or surface HFEC inspection, as applicable, for cracks in the repaired and modified areas, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the applicable inspections thereafter at the times specified in Tables 8 and 9 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012. Doing an inspection required by this paragraph terminates the inspections required by paragraph (p) of AD 2005–20–29, Amendment 39–14326 (70 FR 59246, October 12, 2005). VerDate Sep<11>2014 15:13 Mar 30, 2016 Jkt 238001 (2) For any repair #10 or repair #13 done as specified in Boeing Alert Service Bulletin 747–53A2452: Before further flight, do postrepair inspections using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (j) Replacement of the Upper Chords of the Upper Deck Floor Beams (Includes PreReplacement Inspections) Replace the upper chords of the upper deck floor beams by doing the actions required by paragraphs (j)(1) and (j)(2) of this AD at the times specified in those paragraphs. Accomplishing the replacement required by this paragraph terminates the inspections required by paragraphs (g) and (i) of this AD. (1) Before the accumulation of 30,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, do an open hole HFEC inspection for cracks at certain fastener locations in the floor beam webs and side of body frames, and do a detailed inspection for cracks of any removed part that will be reinstalled, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2852, dated June 22, 2012, except as required by paragraph (l)(2) of this AD. Do all applicable corrective actions before further flight. (2) Before further flight after accomplishing the inspections required by paragraph (j)(1) of this AD, install new upper chords of the upper deck floor beams and reinforcing straps or angles, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2852, dated June 22, 2012, except as required by paragraph (l)(2) of this AD. (k) Post-Replacement Repetitive Inspections For airplanes on which any replacement required by paragraph (j) or (k)(2)(ii) of this AD is done: At the applicable times specified in Tables 2 through 4 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2852, dated June 22, 2012, do HFEC inspections for cracks at the permanent fastener holes and the upper chords of the upper deck floor beams, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012. (1) If any cracking is found during any inspection required by the introductory text of paragraph (k) or paragraph (k)(2)(i) of this AD, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (2) If no cracking is found during any inspection required by the introductory text of paragraph (k) or paragraph (k)(2)(i) of this AD, do the actions required by paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. (i) Repeat the inspections specified in paragraph (k) of this AD thereafter at the applicable times specified in Tables 8 and 9 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012. (ii) Within 10,000 flight cycles after accomplishing the initial HFEC inspections PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 18459 required by the introductory text of paragraph (k) of this AD, replace the upper chords of the upper deck floor beams by doing the actions specified in paragraphs (j)(1) and (j)(2) of this AD. (l) Exceptions to Service Information (1) Where Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012, specifies a compliance time ‘‘after the Revision 1 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747–53A2452, Revision 1, dated July 16, 2012; or Boeing Alert Service Bulletin 747– 53A2852, dated June 22, 2012; specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (m) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g), (h), and (i) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003. For the actions required by paragraphs (g), (h), and (i) of this AD that are not identified in Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003, those actions must still be done. Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003, is incorporated by reference in AD 2005–20–29, Amendment 39–14326 (70 FR 59246, October 12, 2005). (n) Special Flight Permit Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (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) 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. E:\FR\FM\31MRR1.SGM 31MRR1 18460 Federal Register / Vol. 81, No. 62 / Thursday, March 31, 2016 / Rules and Regulations (p) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 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)(3) and (q)(4) 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. (i) Boeing Alert Service Bulletin 747– 53A2452, Revision 1, dated July 16, 2012. (ii) Boeing Alert Service Bulletin 747– 53A2852, dated June 22, 2012. (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; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at 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. ACTION: Discussion Final rule. We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. (Honeywell) TFE731–4, –4R, –5AR, –5BR, and –5R turbofan engines. This AD was prompted by a report of certain interstage turbine transition (ITT) ducts failing to meet containment capability requirements. This AD requires replacing certain ITT ducts. We are issuing this AD to prevent failure of the ITT duct, which could lead to an uncontained part release, damage to the engine, and damage to the airplane. SUMMARY: This AD is effective May 5, 2016 The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 5, 2016. DATES: For service information identified in this final rule, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034–2802; phone: 800–601–3099; Internet: https:// myaerospace.honeywell.com/wps/ portal/!ut/. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015– 2208. ADDRESSES: Examining the AD Docket [Docket No. FAA–2015–2208; Directorate Identifier 2015–NE–19–AD; Amendment 39– 18447; AD 2016–07–02] You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2208; 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 Document 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. RIN 2120–AA64 FOR FURTHER INFORMATION CONTACT: Issued in Renton, Washington, on March 20, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–07024 Filed 3–30–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration jstallworth on DSK7TPTVN1PROD with RULES 14 CFR Part 39 Airworthiness Directives; Honeywell International Inc. (Type Certificate Previously Held by AlliedSignal Inc., Garrett Turbine Engine Company) Turbofan Engines Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Sep<11>2014 15:13 Mar 30, 2016 Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; phone: 562–627–5246; fax: 562–627–5210; email: joseph.costa@ faa.gov. SUPPLEMENTARY INFORMATION: Jkt 238001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to Honeywell TFE731–4, –4R, –5AR, –5BR, and –5R turbofan engines with ITT duct, part number (P/N) 3075292–4, installed, with a serial number (S/N) listed in Table 2 of Honeywell Service Bulletin (SB) TFE731–72–3789, Revision 0, dated March 23, 2015. The NPRM published in the Federal Register on October 29, 2015 (80 FR 66481). The NPRM was prompted by report of certain ITT ducts that were not properly heat treated and failed to meet containment capability requirements. The NPRM proposed to require replacing certain ITT ducts. We are issuing this AD to correct the unsafe condition on these products. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 66481, October 29, 2015) or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR 66481, October 29, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 66481, October 29, 2015). Related Service Information Under 1 CFR Part 51 We reviewed Honeywell SB TFE731– 72–3789, Revision 0, dated March 23, 2015. The SB describes procedures for removing affected ITT ducts. 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 47 engines installed on airplanes of U.S. registry. We also estimate that it will take about 2 hours per engine to comply with this AD. The average labor rate is $85 per hour. We estimate that replacement parts will cost $15,000 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $712,990. E:\FR\FM\31MRR1.SGM 31MRR1

Agencies

[Federal Register Volume 81, Number 62 (Thursday, March 31, 2016)]
[Rules and Regulations]
[Pages 18456-18460]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07024]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3983; Directorate Identifier 2015-NM-141-AD; 
Amendment 39-18448; AD 2016-07-03]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-300, 747SR, and 747SP series airplanes. This AD was prompted by an 
evaluation by the design approval holder (DAH) indicating that the 
upper chords of the upper deck floor beams are subject to widespread 
fatigue damage (WFD). This AD requires repetitive inspections for 
cracks at the floor panel attachment fastener holes; repetitive 
inspections for cracks in the upper and lower chords of the upper deck 
floor beams at permanent fastener locations; repetitive inspections for 
cracks in certain repaired and modified areas; and related 
investigative and corrective actions if necessary. This AD also 
requires repetitive replacement of the upper chords of the upper deck 
floor beams, including pre-replacement inspections and corrective 
action if necessary; and post-replacement repetitive inspections and 
repair if necessary. We are issuing this AD to detect and correct 
fatigue cracking of the upper chords of the upper deck floor beams. 
Undetected cracking could result in large deflection or deformation of 
the upper deck floor beams, resulting in damage to wire bundles and 
control cables for the flight control system, and reduced 
controllability of the airplane. Multiple adjacent severed floor beams 
could result in rapid decompression of the airplane.

DATES: This AD is effective May 5, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 5, 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3983.

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-2015-
3983; 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, 
1601 Lind Avenue SW., Renton, WA

[[Page 18457]]

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 by adding an AD that would apply to certain The Boeing Company 
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and 
747SP series airplanes. The NPRM published in the Federal Register on 
October 6, 2015 (80 FR 60303) (``the NPRM''). The NPRM was prompted by 
an evaluation by the DAH indicating that the upper chords of the upper 
deck floor beams are subject to WFD. The NPRM proposed to require 
repetitive inspections for cracks at the floor panel attachment 
fastener holes; repetitive inspections for cracks in the upper and 
lower chords of the upper deck floor beams at permanent fastener 
locations; repetitive inspections for cracks in certain repaired and 
modified areas; and related investigative and corrective actions if 
necessary. The NPRM also proposed to require repetitive replacement of 
the upper chords of the upper deck floor beams, including pre-
replacement inspections and corrective action if necessary; and post-
replacement repetitive inspections and repair if necessary. We are 
issuing this AD to detect and correct fatigue cracking of the upper 
chords of the upper deck floor beams. Undetected cracking could result 
in large deflection or deformation of the upper deck floor beams, 
resulting in damage to wire bundles and control cables for the flight 
control system, and reduced controllability of the airplane. Multiple 
adjacent severed floor beams could result in rapid decompression 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. A member of the public supported 
the NPRM and an anonymous commenter had no objection to the NPRM.

Request To Clarify Credit for Previous Actions

    Boeing requested that we clarify that credit for previous actions 
is limited to those actions that comply with the new proposed 
requirements of the NPRM. Boeing noted that paragraph (m) of the 
proposed AD should provide credit for using Boeing Alert Service 
Bulletin 747-53A2452, dated April 3, 2003, provided the new 
requirements specified in Boeing Alert Service Bulletin 747-53A2452, 
Revision 1, dated July 16, 2012, are met.
    We agree that clarification is necessary. Paragraph (m) of this AD, 
``Credit for Previous Actions,'' provides credit for actions done 
before the effective date of this AD using Boeing Alert Service 
Bulletin 747-53A2452, dated April 3, 2003, for the corresponding 
actions required by paragraphs (g), (h), and (i) of this AD. Paragraphs 
(g), (h), and (i) of this AD refer to Boeing Alert Service Bulletin 
747-53A2452, Revision 1, dated July 16, 2012, as the appropriate source 
of service information for accomplishing the actions required by those 
paragraphs. Boeing Alert Service Bulletin 747-53A2452, Revision 1, 
dated July 16, 2012, added certain inspection locations. Therefore, for 
the added inspection locations specified in Boeing Alert Service 
Bulletin 747-53A2452, Revision 1, dated July 16, 2012, paragraph (m) of 
this AD does not provide credit because Boeing Alert Service Bulletin 
747-53A2452, dated April 3, 2003, cannot be used for those locations. 
We have revised paragraph (m) of this AD to clarify that although 
credit is given for using Boeing Alert Service Bulletin 747-53A2452, 
dated April 3, 2003, actions required by paragraphs (g), (h), and (i) 
of this AD that are not identified in Boeing Alert Service Bulletin 
747-53A2452, dated April 3, 2003, must still be done.
    Boeing also stated that credit should be given in the NPRM for 
Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 
2012; and Boeing Alert Service Bulletin 747-53A2852, dated June 22, 
2012.
    We have not included Boeing Alert Service Bulletin 747-53A2452, 
Revision 1, dated July 16, 2012; and Boeing Alert Service Bulletin 747-
53A2852, dated June 22, 2012; in paragraph (m) of this AD because that 
service information is already cited in paragraphs (g) through (k) of 
this AD as the only appropriate source of service information for 
accomplishing the actions required by this AD. As allowed by the 
phrase, ``unless already done,'' in paragraph (f) of this AD, if the 
requirements of this AD have already been accomplished, this AD does 
not require that those actions be repeated.

Request To Give Credit for Previous Alternative Methods of Compliance 
(AMOCs)

    Boeing requested that previously approved AMOCs for AD 2005-20-29, 
Amendment 39-14326 (70 FR 59246, October 12, 2005), be approved for the 
corresponding provisions of the proposed AD, provided the previously 
approved AMOCs satisfy the inspection locations and compliance times 
specified by the proposed AD. Boeing noted that AMOCs would be needed 
for new inspection locations and compliance times specified in the 
proposed AD.
    We acknowledge that certain AMOCs for AD 2005-20-29, Amendment 39-
14326 (70 FR 59246, October 12, 2005), might also address the actions 
and compliance times required by this AD. However, each individual AMOC 
would need to be evaluated to ensure the identified unsafe condition is 
addressed. Any person may request approval of an AMOC under the 
provisions of paragraph (o) of this AD. We have not changed this final 
rule in this regard.

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 changes described previously--and minor editorial 
changes. We have determined that these minor changes:
     [Agr]re 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 the following service information.
     Boeing Alert Service Bulletin 747-53A2452, Revision 1, 
dated July 16, 2012. This service information describes procedures for 
repetitive open hole or surface high frequency eddy current (HFEC) 
inspections, as applicable, for cracks at the floor panel attachment 
fastener holes in certain areas and stations; repetitive surface HFEC 
inspections for cracks in the upper and lower chords of the upper deck 
floor beams at permanent fastener locations in certain areas and 
stations; and related investigative and corrective actions. This 
service information also describes procedures, for airplanes on which 
certain repairs or modifications are done, for repetitive open hole or 
surface HFEC inspections, as applicable, for cracks in the repaired and 
modified areas; and repair.
     Boeing Alert Service Bulletin 747-53A2852, dated June 22, 
2012. This

[[Page 18458]]

service information describes procedures for repetitive replacement of 
the upper chords of the upper deck floor beams, including pre-
replacement inspections and corrective action, and post-replacement 
repetitive inspections and repair.
    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 67 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
----------------------------------------------------------------------------------------------------------------
Inspections specified in Boeing    Up to 884 work-                  $0  $75,140, per         $5,034,380, per
 Alert Service Bulletin             hours x $85 per                      inspection cycle.    inspection cycle.
 747[dash]53A2452, Revision 1,      hour = $75,140,
 dated July 16, 2012.               per inspection
                                    cycle.
Replacement specified in Boeing    Up to 696 work-              \1\ $0  $59,160, per         $3,963,720, per
 Alert Service Bulletin             hours x $85 per                      replacement.         replacement.
 747[dash]53A2852, dated June 22,   hour = $59,160,
 2012.                              per replacement.
Post-replacement inspections       Up to 586 work-                  $0  $49,810, per         $3,337,270, per
 specified in Boeing Alert          hours x $85 per                      inspection cycle.    inspection cycle.
 Service Bulletin                   hour = $49,810,
 747[dash]53A2852, dated June 22,   per inspection
 2012.                              cycle.
----------------------------------------------------------------------------------------------------------------
\1\ We currently have no specific cost estimates associated with the parts necessary for the replacement.

    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

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-07-03 The Boeing Company: Amendment 39-18448 ; Docket No. FAA-
2015-3983; Directorate Identifier 2015-NM-141-AD.

(a) Effective Date

    This AD is effective May 5, 2016.

(b) Affected ADs

    This AD affects AD 2005-20-29, Amendment 39-14326 (70 FR 59246, 
October 12, 2005).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes; 
certificated in any category; as identified in Boeing Alert Service 
Bulletin 747-53A2852, dated June 22, 2012.

(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 (DAH) indicating that the upper chords of the upper deck 
floor beams are subject to widespread fatigue damage (WFD). We are 
issuing this AD to detect and correct fatigue cracking of the upper 
chords of the upper deck floor beams. Undetected cracking could 
result in large deflection or deformation of the upper deck floor 
beams, resulting in damage to wire bundles and control cables for 
the flight control system, and reduced controllability of the 
airplane. Multiple adjacent severed floor beams could result in 
rapid decompression of the airplane.

(f) Compliance

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

(g) Repetitive Inspections of the Upper Chords of the Upper Deck Floor 
Beams

    At the applicable times specified in Tables 1 through 7 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2452, Revision 1, dated July 16, 2012, except as required by 
paragraph (l)(1) of this AD: Do the inspections specified in 
paragraphs (g)(1) and (g)(2) of this AD, and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2452, Revision 1, dated July 16, 2012, except as required by 
paragraph (l)(2) of this AD. Repeat the inspections specified in 
paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable

[[Page 18459]]

times specified in Tables 1 through 7 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452, 
Revision 1, dated July 16, 2012. Do all applicable related 
investigative and corrective actions before further flight. Doing 
the inspections required by paragraphs (g)(1) and (g)(2) of this AD 
terminates the inspections required by paragraphs (m) and (n) of AD 
2005-20-29, Amendment 39-14326 (70 FR 59246, October 12, 2005).
    (1) Do an open hole or surface high frequency eddy current 
(HFEC) inspection, as applicable, for cracks at the fastener holes 
of the floor panel attachment in the applicable areas and stations 
identified in Boeing Alert Service Bulletin 747-53A2452, Revision 1, 
dated July 16, 2012.
    (2) Do a surface HFEC inspection for cracks in the upper and 
lower chords of the upper deck floor beams at permanent fastener 
locations in the applicable areas and stations identified in Boeing 
Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012.

(h) Terminating Modification and Repair for the Inspection Specified in 
Paragraph (g)(1) of This AD

    A fastener hole modification or a fastener hole repair in Area 1 
or Area 2 as described in Boeing Alert Service Bulletin 747-53A2452, 
Revision 1, dated July 16, 2012, terminates the inspection of the 
fastener holes of the floor panel attachment required by paragraph 
(g)(1) of this AD for the repaired or modified area only, provided 
the modification and repair, including related investigative and 
corrective actions, are done in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2452, Revision 
1, dated July 16, 2012, except as required by paragraph (l)(2) of 
this AD.

(i) Post Modification/Repair Repetitive Inspections

    (1) For airplanes on which any fastener hole modification or any 
fastener hole repair was done as specified in Boeing Alert Service 
Bulletin 747-53A2452: Except as required by paragraph (i)(2) of this 
AD, at the applicable times specified in Tables 8 and 9 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452, 
Revision 1, dated July 16, 2012, or within 1,000 flight cycles after 
the effective date of this AD, whichever occurs later, do an open 
hole or surface HFEC inspection, as applicable, for cracks in the 
repaired and modified areas, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2452, Revision 
1, dated July 16, 2012. If any cracking is found, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (o) of this AD. Repeat the 
applicable inspections thereafter at the times specified in Tables 8 
and 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2452, Revision 1, dated July 16, 2012. Doing an 
inspection required by this paragraph terminates the inspections 
required by paragraph (p) of AD 2005-20-29, Amendment 39-14326 (70 
FR 59246, October 12, 2005).
    (2) For any repair #10 or repair #13 done as specified in Boeing 
Alert Service Bulletin 747-53A2452: Before further flight, do post-
repair inspections using a method approved in accordance with the 
procedures specified in paragraph (o) of this AD.

(j) Replacement of the Upper Chords of the Upper Deck Floor Beams 
(Includes Pre-Replacement Inspections)

    Replace the upper chords of the upper deck floor beams by doing 
the actions required by paragraphs (j)(1) and (j)(2) of this AD at 
the times specified in those paragraphs. Accomplishing the 
replacement required by this paragraph terminates the inspections 
required by paragraphs (g) and (i) of this AD.
    (1) Before the accumulation of 30,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later, do an open hole HFEC inspection for cracks 
at certain fastener locations in the floor beam webs and side of 
body frames, and do a detailed inspection for cracks of any removed 
part that will be re-installed, and do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012, 
except as required by paragraph (l)(2) of this AD. Do all applicable 
corrective actions before further flight.
    (2) Before further flight after accomplishing the inspections 
required by paragraph (j)(1) of this AD, install new upper chords of 
the upper deck floor beams and reinforcing straps or angles, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2852, dated June 22, 2012, except as 
required by paragraph (l)(2) of this AD.

(k) Post-Replacement Repetitive Inspections

    For airplanes on which any replacement required by paragraph (j) 
or (k)(2)(ii) of this AD is done: At the applicable times specified 
in Tables 2 through 4 in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2852, dated June 22, 2012, do HFEC 
inspections for cracks at the permanent fastener holes and the upper 
chords of the upper deck floor beams, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2452, Revision 1, dated July 16, 2012.
    (1) If any cracking is found during any inspection required by 
the introductory text of paragraph (k) or paragraph (k)(2)(i) of 
this AD, before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.
    (2) If no cracking is found during any inspection required by 
the introductory text of paragraph (k) or paragraph (k)(2)(i) of 
this AD, do the actions required by paragraphs (k)(2)(i) and 
(k)(2)(ii) of this AD.
    (i) Repeat the inspections specified in paragraph (k) of this AD 
thereafter at the applicable times specified in Tables 8 and 9 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2452, Revision 1, dated July 16, 2012.
    (ii) Within 10,000 flight cycles after accomplishing the initial 
HFEC inspections required by the introductory text of paragraph (k) 
of this AD, replace the upper chords of the upper deck floor beams 
by doing the actions specified in paragraphs (j)(1) and (j)(2) of 
this AD.

(l) Exceptions to Service Information

    (1) Where Boeing Alert Service Bulletin 747-53A2452, Revision 1, 
dated July 16, 2012, specifies a compliance time ``after the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where Boeing Alert Service Bulletin 747-53A2452, Revision 1, 
dated July 16, 2012; or Boeing Alert Service Bulletin 747-53A2852, 
dated June 22, 2012; specifies to contact Boeing for appropriate 
action: Before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Alert 
Service Bulletin 747-53A2452, dated April 3, 2003. For the actions 
required by paragraphs (g), (h), and (i) of this AD that are not 
identified in Boeing Alert Service Bulletin 747-53A2452, dated April 
3, 2003, those actions must still be done. Boeing Alert Service 
Bulletin 747-53A2452, dated April 3, 2003, is incorporated by 
reference in AD 2005-20-29, Amendment 39-14326 (70 FR 59246, October 
12, 2005).

(n) Special Flight Permit

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(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) 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.

[[Page 18460]]

(p) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 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)(3) and (q)(4) 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.
    (i) Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated 
July 16, 2012.
    (ii) Boeing Alert Service Bulletin 747-53A2852, dated June 22, 
2012.
    (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; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at 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/ibr-locations.html.

    Issued in Renton, Washington, on March 20, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07024 Filed 3-30-16; 8:45 am]
 BILLING CODE 4910-13-P