Airworthiness Directives; the Boeing Company Airplanes, 67048-67052 [2014-26536]

Download as PDF 67048 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0289; Directorate Identifier 2013–NM–146–AD; Amendment 39–18016; AD 2014–22–11] RIN 2120–AA64 Airworthiness Directives; the Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2012–13– 08 for certain the Boeing Company Model 747–100, 747–100B, 747–200B, 747–200C, 747–200F, 747–400F, 747SR, and 747SP series airplanes, without a stretched upper deck or stretched upper deck modification. AD 2012–13–08 required inspections of tension ties and surrounding structure for cracking, and related investigative and corrective actions if necessary; modification of tension tie structure or tension tie and frame structure at specified stations; and post-modification inspections of some modified and unmodified areas, and repair if necessary. This new AD adds inspections in unmodified center section tension ties, and repair if necessary; post-modification inspections of modified and unmodified areas, and repair if necessary; a new modification of tension tie and frame structures; and inspections of tension ties and surrounding structure, and related investigative and corrective actions if necessary. This new AD reduces an inspection interval. This AD was prompted by widespread fatigue damage analysis that resulted in a determination that more inspections are necessary. We are issuing this AD to prevent tension ties from becoming severed or disconnected from the frames, which could lead to reduced structural integrity and sudden decompression of the airplane in flight. DATES: This AD is effective December 17, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 17, 2014. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of August 14, 2012 (77 FR 40481, July 10, 2012). The Director of the Federal Register approved the incorporation by reference wreier-aviles on DSK5TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:57 Nov 10, 2014 Jkt 235001 of a certain other publication listed in this AD as of February 16, 2006 (71 FR 1947, January 12, 2006). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.govby searching for and locating Docket No. FAA–2014– 0289; 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, Seattle Aircraft Certification Office (ACO), FAA, 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 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012). AD 2012–13–08 applied to certain The Boeing Company Model 747–100, 747–100B, 747–200B, 747– 200C, 747–200F, 747–400F, 747SR, and 747SP series airplanes, without a stretched upper deck or stretched upper deck modification. The NPRM published in the Federal Register on May 29, 2014 (79 FR 30756). The NPRM was prompted by a widespread fatigue damage analysis conducted by Boeing that resulted in a determination that additional inspections are needed. The NPRM proposed to continue to require PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 repetitive inspections of tension ties and surrounding structure for cracking, additional inspections for certain airplanes, and related investigative and corrective actions if necessary. The NPRM also proposed to continue to require modification of tension tie structure or tension tie and frame structure at specified stations, a postmodification inspection of any modified area for cracking, repetitive inspections for cracking in the unmodified areas of the tension tie structure and frame structure at certain stations, and repair if necessary. The NPRM proposed to add, for certain airplanes, surface HFEC inspections for cracking in unmodified center section tension ties, and repair if necessary; repetitive post-modification eddy current inspections for cracking of modified and unmodified areas, and repair if necessary; a new modification (replacement) of tension tie and frame structures; and repetitive inspections of tension ties and surrounding structure for cracking, and related investigative and corrective actions if necessary. The NPRM also proposed to reduce an inspection interval. We are issuing this AD to prevent tension ties from becoming severed or disconnected from the frames, which could lead to reduced structural integrity and sudden decompression of the airplane in flight. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Boeing stated that it concurred with the contents of the NPRM (79 FR 30756, May 29, 2014). Conclusion We reviewed the relevant data, considered the comments received, 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 (79 FR 30756, May 29, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 30756, May 29, 2014). Costs of Compliance We estimate that this AD affects 86 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\12NOR1.SGM 12NOR1 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 67049 ESTIMATED COSTS Action Inspection (retained from AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012)). One-time inspection for Group 2 airplanes, (retained from AD 2012– 13–08, Amendment 39– 17110 (77 FR 40481, July 10, 2012)). Modification (retained from AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012)). Inspection for unmodified area (retained from AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012)). Labor cost Parts cost 8 work-hours per tension tie location, between 8 and 12 tension tie locations per airplane, depending on airplane configuration × $85 per hour = between $5,440 and $8,160. 6 work-hours × $85 per hour = $510. $0 ...................................... Between $5,440 and $8,160 per inspection cycle. Between $467,840 and $701,760, per inspection cycle. None .................................. $510 .................................. $43,860. Between $18,657 and $658,423. Between $20,697 and $669,473. Between $1,779,942 and $57,574,678. None .................................. Between $1,360 and $2,040, per inspection cycle. Between $116,960 and $175,440. None .................................. Between $1,360 and $2,040. Between $116,960 and $175,440. Up to $658,423 ................. Up to $691,318 ................. Up to $691,318. None .................................. $1,530 for each tension tie, per inspection cycle. $131,580 for each tension tie, per inspection cycle. None .................................. Up to $10,200 ................... Up to $877,200. Between 24 and 130 workhours, depending on station location × $85 per hour = between $2,040 and 11,050. 2 work-hours per tension tie location, between 8 and 12 tension tie locations per airplane, depending on airplane configuration × $85 per hour = between $1,360 and $2,040. Inspection for modified 2 work-hours per tension area (retained from AD tie location, between 8 2012–13–08, Amendand 12 tension tie locament 39–17110 (77 FR tions per airplane, de40481, July 10, 2012)). pending on airplane configuration × $85 per hour = between $1,360 and $2,040. Modification (new action; 1 Up to 387 work-hours, deU.S. -registered airplane). pending on station location × $85 per hour = up to $32,895. Post-modification eddy cur- 18 work-hours × $85 per rent inspection of all hour = $1,530 for each areas (new action). tension tie. Surface high frequency Up to 120 work-hours, deeddy current inspection pending on airplane conof unmodified tension tie figuration × $85 per hour center sections (new ac= Up to $10,200. tion). wreier-aviles on DSK5TPTVN1PROD with RULES 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 VerDate Sep<11>2014 14:57 Nov 10, 2014 Jkt 235001 Cost per product air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 Cost on U.S. operators 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. E:\FR\FM\12NOR1.SGM 12NOR1 67050 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 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) 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012), and adding the following new AD: ■ 2014–22–11 The Boeing Company: Amendment 39–18016; Docket No. FAA–2014–0289; Directorate Identifier 2013–NM–146–AD. (a) Effective Date This AD is effective December 17, 2014. (b) Affected ADs This AD replaces AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012). (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–200B, 747– 200C, 747–200F, 747–400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an analysis by the manufacturer indicating that tension ties are susceptible to widespread fatigue damage. The actions were developed to support the airplane’s limit of validity of the engineering data that support the established structural maintenance program. We are issuing this AD to prevent tension ties from becoming severed or disconnected from the frames, which could lead to reduced structural integrity and sudden decompression of the airplane in flight. wreier-aviles on DSK5TPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Actions for Group 1 and Groups 3 Through 6 Airplanes This paragraph restates the requirements of paragraph (g) of AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012). For Group 1, and Groups 3 through 6 airplanes identified in Boeing Special Attention Service Bulletin 747–53–2502, dated April 21, 2005: At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do VerDate Sep<11>2014 14:57 Nov 10, 2014 Jkt 235001 detailed and high frequency eddy current (HFEC) inspections for cracking of each affected tension tie and of the surrounding structure. If any cracking is found: Before further flight, do all applicable corrective and related investigative actions. Do all actions in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2502, dated April 21, 2005; or Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010. Where Boeing Special Attention Service Bulletin 747–53–2502, dated April 21, 2005; or Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010; specifies to contact Boeing for repair instructions: Before further flight, repair the area using a method approved in accordance with the procedures specified in paragraph (n) of this AD. As of August 14, 2012 (the effective date of AD 2012–13–08), only Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010, may be used to accomplish the actions required in this paragraph. (1) For airplanes identified in Boeing Special Attention Service Bulletin 747–53– 2502, dated April 21, 2005, as Groups 1, 3, and 6 airplanes: Do the first inspections before the accumulation of 20,000 total flight cycles, or within 1,000 flight cycles after February 16, 2006 (the effective date of AD 2006–01–07, Amendment 39–14446 (71 FR 1947, January 12, 2006)), whichever occurs later; and repeat the inspections thereafter at intervals not to exceed 4,000 flight cycles until the modification required by paragraph (j) of this AD is accomplished. (2) For airplanes identified in Boeing Special Attention Service Bulletin 747–53– 2502, dated April 21, 2005, as Groups 4 and 5 airplanes: Do the first inspections before the accumulation of 17,000 total flight cycles, or within 1,000 flight cycles after February 16, 2006 (the effective date of AD 2006–01– 07, Amendment 39–14446 (71 FR 1947, January 12, 2006)), whichever occurs later; and repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles until the modification required by paragraph (j) of this AD is accomplished. (h) Retained Inspections for Group 2 Airplanes This paragraph restates the requirements of paragraph (h) of AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012). For Group 2 airplanes identified in Boeing Alert Service Bulletin 747 53A2502, Revision 1, dated June 17, 2010: At the applicable times specified in paragraphs (h)(1) and (h)(2) of this AD, do detailed and HFEC inspections for cracking of each affected tension tie and of the surrounding structure, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2502, dated April 21, 2005; or Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010. If any cracking is found: Before further flight, do all applicable corrective and related investigative actions. Do all actions in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2502, dated April 21, 2005; or Boeing Alert PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010. Where Boeing Special Attention Service Bulletin 747–53–2502, dated April 21, 2005; or Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010; specify to contact Boeing for repair instructions: Before further flight, repair the area using a method approved in accordance with the procedures specified in paragraph (n) of this AD. As of August 14, 2012 (the effective date of AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012)), only Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010, may be used to accomplish the actions required by this paragraph. Repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles until the modification required by paragraph (j) of this AD is accomplished. (1) For stations (STA) 780 through 940: Before the accumulation of 17,000 total flight cycles, or within 1,000 flight cycles after February 16, 2006 (the effective date of AD 2006–01–07, Amendment 39–14446 (71 FR 1947, January 12, 2006)), whichever occurs later. (2) For STA 720, 740, and 760: At the earlier of the times specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD. (i) Before the accumulation of 17,000 total flight cycles, or within 1,000 flight cycles after February 16, 2006 (the effective date of AD 2006–01–07, Amendment 39–14446 (71 FR 1947, January 12, 2006)), whichever occurs later. (ii) Before the accumulation of 8,000 total flight cycles, or within 1,000 flight cycles after August 14, 2012 (the effective date of AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012)), whichever occurs later. (i) Retained One-Time Inspection for Group 2 Airplanes This paragraph restates the requirements of paragraph (i) of AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012). For airplanes identified in Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010, as Group 2 airplanes: Before the accumulation of 8,000 total flight cycles, or within 1,000 flight cycles after August 14, 2012 (the effective date of AD 2012–13–08), whichever occurs later, do a general visual inspection for correct configuration, as identified in Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010, of each affected tension tie and of the surrounding structure, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010. (1) If all tension ties match the correct configurations specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010, no further work is required by this paragraph. (2) If any incorrect configuration is found, before further flight, do detailed and open fastener-hole HFEC inspections for cracking in the tension tie and frame, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010. E:\FR\FM\12NOR1.SGM 12NOR1 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations wreier-aviles on DSK5TPTVN1PROD with RULES (i) If no crack is found during the inspections required by paragraph (i)(2) of this AD: Before further flight, install the correct configuration for the tension ties at locations where the incorrect configuration was found, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010; except where Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010, specifies to contact Boeing for installation instructions, use a method approved in accordance with the procedures specified in paragraph (n) of this AD. (ii) If any crack is found during the inspections required by paragraph (i)(2) of this AD, before further flight, do the actions specified in paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD. (A) Repair the crack in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010; except where Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010, specifies to contact Boeing for appropriate action, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (B) Install the correct configuration for the tension ties at locations where the incorrect configuration was found, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010; except where Boeing Alert Service Bulletin 747– 53A2502, Revision 1, dated June 17, 2010, specifies to contact Boeing for installation instructions, use a method approved in accordance with the procedures specified in paragraph (n) of this AD. (j) New Tension Tie and Frame Modification and Inspections (1) For Groups 1 through 16, Configuration 1, airplanes identified in Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013: At the applicable compliance time specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, except as required by paragraph (l)(1) of this AD, do tension tie and frame modifications, in accordance with Part 1, and surface HFEC inspections for cracks, in accordance with Part 4, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013. Accomplishment of these modifications terminates the repetitive inspections required by paragraphs (g) and (h) of this AD. If any crack is found, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (2) For Groups 17 and 18 airplanes identified in Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013: At the applicable time specified in table 6 or table 7, as applicable, of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, do a tension tie and frame modification (replacement of tension ties and VerDate Sep<11>2014 14:57 Nov 10, 2014 Jkt 235001 frame structure), in accordance with Part 5 or Part 6, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013. Accomplishment of these modifications terminates the repetitive inspections required by paragraph (g) of this AD. (k) New Repetitive Post-Modification Detailed Inspections of Unmodified Areas; Repetitive Post-Modification HFEC Inspections of Modified and Unmodified Areas (1) For Groups 1 through 16 airplanes identified in Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013: At the applicable time specified in table 2 or table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, do a detailed inspection for cracking in the unmodified areas of the tension ties, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Repeat the detailed inspection thereafter at the applicable time specified in table 2 or table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013. (2) For Groups 1 through 16 airplanes identified in Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013: At the applicable time specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, do eddy current inspections for cracking in all areas of the tension ties (modified and unmodified), in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Repeat the eddy current inspections thereafter at the time specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013. (3) For Groups 1 through 16, Configuration 2, airplanes identified in Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013: At the applicable time specified in table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, except as provided by paragraph (l)(1) of this AD, do surface HFEC inspections for cracking in the unmodified tension tie center sections, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. If no cracking is found, no further action is required until the repetitive inspections required by paragraphs (k)(1) and (k)(2) begin. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 67051 (4) For Groups 17 and 18 airplanes identified in Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013: At the applicable time specified in table 6 or table 7 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, do detailed and HFEC inspections of the modified tension tie and frame structure for cracking, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2502, Revision 1, dated June 17, 2010. Except as required by paragraph (l)(4) of this AD, if any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Repeat the detailed and HFEC inspections thereafter at the times specified in table 6 or table 7, as applicable, of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013. (l) Service Information Clarifications and Exceptions (1) Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, specifies a compliance time ‘‘after the revision 3 date of this service bulletin,’’ this AD requires compliance within the specified time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, specifies to contact Boeing for repair instructions, this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (3) Boeing Alert Service Bulletin 747– 53A2605, Revision 3, dated July 10, 2013, refers to Section 51–10–02 of the Boeing 747– 400F Structural Repair Manual (SRM) and Section 51–10–01 of the Boeing 747–100/ 200/300 SRM as additional sources of guidance for removing small cracks and fatigue damage material from the existing holes in the unmodified center section of the tension tie channels. Where those SRM sections state that ‘‘zero-timing must only be used where specifically permitted in an SRM chapter-section-repair,’’ this AD allows the zero-timing procedures specified in those SRM sections. (4) Where Boeing Alert Service Bulletin 747–53A2605, Revision 3, dated July 10, 2013, specifies to contact Boeing for repair instructions, this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (m) Credit for Previous Actions (1) This paragraph restates the credit provided in paragraph (m) of AD 2012–13– 08, Amendment 39–17110 (77 FR 40481, July 10, 2012). This paragraph provides credit for the actions required by paragraphs (j)(1) and(k)(1) of this AD, if those actions were performed before August 14, 2012 (the effective date of AD 2012–13–08) using Boeing Alert Service Bulletin 747–53A2605, dated December 8, 2009, which was incorporated by reference in AD 2012–13–08. (2) For Groups 1 through 16 airplanes identified in Boeing Alert Service Bulletin E:\FR\FM\12NOR1.SGM 12NOR1 67052 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 747–53A2605, Revision 3, dated July 10, 2013: This paragraph provides credit for the actions required by paragraphs (j)(1) and (k)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747– 53A2605, Revision 2, dated December 9, 2011, which is not incorporated by reference in this AD. (n) 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 (o)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. (4) AMOCs approved for inspections required by AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012) are approved as AMOCs for the corresponding inspection provisions of paragraphs (g), (h), and (i) of this AD. (5) AMOCs approved for AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012) that granted modification deviations are approved as AMOCs for the corresponding modification required by paragraph (j)(1) of this AD. wreier-aviles on DSK5TPTVN1PROD with RULES (o) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 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 (p)(6) and (p)(7) of this AD. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on December 17, 2014. VerDate Sep<11>2014 14:57 Nov 10, 2014 Jkt 235001 (i) Boeing Alert Service Bulletin 747– 53A2605, Revision 3, dated July 10, 2013. (ii) Reserved. (4) The following service information was approved for IBR on August 14, 2012 (77 FR 40481, July 10, 2012). (i) Boeing Alert Service Bulletin 747– 53A2502, Revision 1, dated June 17, 2010. (ii) Reserved. (5) The following service information was approved for IBR on February 16, 2006 (71 FR 1947, January 12, 2006). (i) Boeing Special Attention Service Bulletin 747–53–2502, dated April 21, 2005. (ii) Reserved. (6) 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. (7) 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. (8) 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 October 28, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–26536 Filed 11–10–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0430; Directorate Identifier 2014–NM–083–AD; Amendment 39–18014; AD 2014–22–09] 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 all the Boeing Company Model 767 airplanes. This AD was prompted by a report of a rotary actuator for the trailing edge (TE) flap that had slipped relative to its mating reaction ring, which is attached to the flap support rib. This AD requires repetitive inspections for corrosion of the fixed ring gear and reaction ring splines of the rotary actuator assembly SUMMARY: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 for each support position, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct flap rotary actuator gear disengagement from its mating reaction ring. This disengagement with flaps extended could cause an uncommanded roll due to flap blowback, overload, or flap departure from the airplane, which could compromise safe flight and landing of the airplane. DATES: This AD is effective December 17, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 17, 2014. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0430; 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: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6487; fax: 425–917–6590; email: Allen.Rauschendorfer@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 all The Boeing Company Model 767 airplanes. The NPRM published in E:\FR\FM\12NOR1.SGM 12NOR1

Agencies

[Federal Register Volume 79, Number 218 (Wednesday, November 12, 2014)]
[Rules and Regulations]
[Pages 67048-67052]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26536]

[[Page 67048]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0289; Directorate Identifier 2013-NM-146-AD;
Amendment 39-18016; AD 2014-22-11]
RIN 2120-AA64

Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2012-13-08 for
certain the Boeing Company Model 747-100, 747-100B, 747-200B, 747-200C,
747-200F, 747-400F, 747SR, and 747SP series airplanes, without a
stretched upper deck or stretched upper deck modification. AD 2012-13-
08 required inspections of tension ties and surrounding structure for
cracking, and related investigative and corrective actions if
necessary; modification of tension tie structure or tension tie and
frame structure at specified stations; and post-modification
inspections of some modified and unmodified areas, and repair if
necessary. This new AD adds inspections in unmodified center section
tension ties, and repair if necessary; post-modification inspections of
modified and unmodified areas, and repair if necessary; a new
modification of tension tie and frame structures; and inspections of
tension ties and surrounding structure, and related investigative and
corrective actions if necessary. This new AD reduces an inspection
interval. This AD was prompted by widespread fatigue damage analysis
that resulted in a determination that more inspections are necessary.
We are issuing this AD to prevent tension ties from becoming severed or
disconnected from the frames, which could lead to reduced structural
integrity and sudden decompression of the airplane in flight.

DATES: This AD is effective December 17, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 17,
2014.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of August
14, 2012 (77 FR 40481, July 10, 2012).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 16, 2006 (71 FR 1947, January 12, 2006).

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

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.govby searching for and locating Docket No. FAA-2014-
0289; 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, Seattle Aircraft Certification Office (ACO),
FAA, 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 2012-13-08, Amendment 39-17110 (77 FR 40481,
July 10, 2012). AD 2012-13-08 applied to certain The Boeing Company
Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR,
and 747SP series airplanes, without a stretched upper deck or stretched
upper deck modification. The NPRM published in the Federal Register on
May 29, 2014 (79 FR 30756). The NPRM was prompted by a widespread
fatigue damage analysis conducted by Boeing that resulted in a
determination that additional inspections are needed. The NPRM proposed
to continue to require repetitive inspections of tension ties and
surrounding structure for cracking, additional inspections for certain
airplanes, and related investigative and corrective actions if
necessary. The NPRM also proposed to continue to require modification
of tension tie structure or tension tie and frame structure at
specified stations, a post-modification inspection of any modified area
for cracking, repetitive inspections for cracking in the unmodified
areas of the tension tie structure and frame structure at certain
stations, and repair if necessary. The NPRM proposed to add, for
certain airplanes, surface HFEC inspections for cracking in unmodified
center section tension ties, and repair if necessary; repetitive post-
modification eddy current inspections for cracking of modified and
unmodified areas, and repair if necessary; a new modification
(replacement) of tension tie and frame structures; and repetitive
inspections of tension ties and surrounding structure for cracking, and
related investigative and corrective actions if necessary. The NPRM
also proposed to reduce an inspection interval. We are issuing this AD
to prevent tension ties from becoming severed or disconnected from the
frames, which could lead to reduced structural integrity and sudden
decompression of the airplane in flight.

Comments

We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. Boeing stated that it
concurred with the contents of the NPRM (79 FR 30756, May 29, 2014).

Conclusion

We reviewed the relevant data, considered the comments received,
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 (79 FR 30756, May 29, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 30756, May 29, 2014).

Costs of Compliance

We estimate that this AD affects 86 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

[[Page 67049]]

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained from AD 8 work-hours per $0................ Between $5,440 and Between $467,840
2012-13-08, Amendment 39-17110 tension tie $8,160 per and $701,760, per
(77 FR 40481, July 10, 2012)). location, between inspection cycle. inspection cycle.
8 and 12 tension
tie locations per
airplane,
depending on
airplane
configuration x
$85 per hour =
between $5,440
and $8,160.
One-time inspection for Group 2 6 work-hours x $85 None.............. $510.............. $43,860.
airplanes, (retained from AD per hour = $510.
2012-13-08, Amendment 39-17110
(77 FR 40481, July 10, 2012)).
Modification (retained from AD Between 24 and 130 Between $18,657 Between $20,697 Between $1,779,942
2012-13-08, Amendment 39-17110 work-hours, and $658,423. and $669,473. and $57,574,678.
(77 FR 40481, July 10, 2012)). depending on
station location
x $85 per hour =
between $2,040
and 11,050.
Inspection for unmodified area 2 work-hours per None.............. Between $1,360 and Between $116,960
(retained from AD 2012-13-08, tension tie $2,040, per and $175,440.
Amendment 39-17110 (77 FR location, between inspection cycle.
40481, July 10, 2012)). 8 and 12 tension
tie locations per
airplane,
depending on
airplane
configuration x
$85 per hour =
between $1,360
and $2,040.
Inspection for modified area 2 work-hours per None.............. Between $1,360 and Between $116,960
(retained from AD 2012-13-08, tension tie $2,040. and $175,440.
Amendment 39-17110 (77 FR location, between
40481, July 10, 2012)). 8 and 12 tension
tie locations per
airplane,
depending on
airplane
configuration x
$85 per hour =
between $1,360
and $2,040.
Modification (new action; 1 U.S. Up to 387 work- Up to $658,423.... Up to $691,318.... Up to $691,318.
-registered airplane). hours, depending
on station
location x $85
per hour = up to
$32,895.
Post-modification eddy current 18 work-hours x None.............. $1,530 for each $131,580 for each
inspection of all areas (new $85 per hour = tension tie, per tension tie, per
action). $1,530 for each inspection cycle. inspection cycle.
tension tie.
Surface high frequency eddy Up to 120 work- None.............. Up to $10,200..... Up to $877,200.
current inspection of hours, depending
unmodified tension tie center on airplane
sections (new action). configuration x
$85 per hour = Up
to $10,200.
----------------------------------------------------------------------------------------------------------------

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

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

[[Page 67050]]

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)
2012-13-08, Amendment 39-17110 (77 FR 40481, July 10, 2012), and adding
the following new AD:

2014-22-11 The Boeing Company: Amendment 39-18016; Docket No. FAA-
2014-0289; Directorate Identifier 2013-NM-146-AD.

(a) Effective Date

This AD is effective December 17, 2014.

(b) Affected ADs

This AD replaces AD 2012-13-08, Amendment 39-17110 (77 FR 40481,
July 10, 2012).

This AD applies to The Boeing Company Model 747-100, 747-100B,
747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP series
airplanes, certificated in any category, as identified in Boeing
Alert Service Bulletin 747-53A2502, Revision 1, dated June 17, 2010.

(d) Subject

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

(e) Unsafe Condition

This AD was prompted by an analysis by the manufacturer
indicating that tension ties are susceptible to widespread fatigue
damage. The actions were developed to support the airplane's limit
of validity of the engineering data that support the established
structural maintenance program. We are issuing this AD to prevent
tension ties from becoming severed or disconnected from the frames,
which could lead to reduced structural integrity and sudden
decompression of the airplane in flight.

(f) Compliance

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

(g) Retained Actions for Group 1 and Groups 3 Through 6 Airplanes

This paragraph restates the requirements of paragraph (g) of AD
2012-13-08, Amendment 39-17110 (77 FR 40481, July 10, 2012). For
Group 1, and Groups 3 through 6 airplanes identified in Boeing
Special Attention Service Bulletin 747-53-2502, dated April 21,
2005: At the applicable time in paragraph (g)(1) or (g)(2) of this
AD, do detailed and high frequency eddy current (HFEC) inspections
for cracking of each affected tension tie and of the surrounding
structure. If any cracking is found: Before further flight, do all
applicable corrective and related investigative actions. Do all
actions in accordance with the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747-53-2502, dated April 21,
2005; or Boeing Alert Service Bulletin 747-53A2502, Revision 1,
dated June 17, 2010. Where Boeing Special Attention Service Bulletin
747-53-2502, dated April 21, 2005; or Boeing Alert Service Bulletin
747-53A2502, Revision 1, dated June 17, 2010; specifies to contact
Boeing for repair instructions: Before further flight, repair the
area using a method approved in accordance with the procedures
specified in paragraph (n) of this AD. As of August 14, 2012 (the
effective date of AD 2012-13-08), only Boeing Alert Service Bulletin
747-53A2502, Revision 1, dated June 17, 2010, may be used to
accomplish the actions required in this paragraph.
(1) For airplanes identified in Boeing Special Attention Service
Bulletin 747-53-2502, dated April 21, 2005, as Groups 1, 3, and 6
airplanes: Do the first inspections before the accumulation of
20,000 total flight cycles, or within 1,000 flight cycles after
February 16, 2006 (the effective date of AD 2006-01-07, Amendment
39-14446 (71 FR 1947, January 12, 2006)), whichever occurs later;
and repeat the inspections thereafter at intervals not to exceed
4,000 flight cycles until the modification required by paragraph (j)
of this AD is accomplished.
(2) For airplanes identified in Boeing Special Attention Service
Bulletin 747-53-2502, dated April 21, 2005, as Groups 4 and 5
airplanes: Do the first inspections before the accumulation of
17,000 total flight cycles, or within 1,000 flight cycles after
February 16, 2006 (the effective date of AD 2006-01-07, Amendment
39-14446 (71 FR 1947, January 12, 2006)), whichever occurs later;
and repeat the inspections thereafter at intervals not to exceed
3,000 flight cycles until the modification required by paragraph (j)
of this AD is accomplished.

(h) Retained Inspections for Group 2 Airplanes

This paragraph restates the requirements of paragraph (h) of AD
2012-13-08, Amendment 39-17110 (77 FR 40481, July 10, 2012). For
Group 2 airplanes identified in Boeing Alert Service Bulletin 747
53A2502, Revision 1, dated June 17, 2010: At the applicable times
specified in paragraphs (h)(1) and (h)(2) of this AD, do detailed
and HFEC inspections for cracking of each affected tension tie and
of the surrounding structure, in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-53-
2502, dated April 21, 2005; or Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010. If any cracking is found:
Before further flight, do all applicable corrective and related
investigative actions. Do all actions in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2502, dated April 21, 2005; or Boeing Alert Service
Bulletin 747-53A2502, Revision 1, dated June 17, 2010. Where Boeing
Special Attention Service Bulletin 747-53-2502, dated April 21,
2005; or Boeing Alert Service Bulletin 747-53A2502, Revision 1,
dated June 17, 2010; specify to contact Boeing for repair
instructions: Before further flight, repair the area using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD. As of August 14, 2012 (the effective date of AD
2012-13-08, Amendment 39-17110 (77 FR 40481, July 10, 2012)), only
Boeing Alert Service Bulletin 747-53A2502, Revision 1, dated June
17, 2010, may be used to accomplish the actions required by this
paragraph. Repeat the inspections thereafter at intervals not to
exceed 3,000 flight cycles until the modification required by
paragraph (j) of this AD is accomplished.
(1) For stations (STA) 780 through 940: Before the accumulation
of 17,000 total flight cycles, or within 1,000 flight cycles after
February 16, 2006 (the effective date of AD 2006-01-07, Amendment
39-14446 (71 FR 1947, January 12, 2006)), whichever occurs later.
(2) For STA 720, 740, and 760: At the earlier of the times
specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD.
(i) Before the accumulation of 17,000 total flight cycles, or
within 1,000 flight cycles after February 16, 2006 (the effective
date of AD 2006-01-07, Amendment 39-14446 (71 FR 1947, January 12,
2006)), whichever occurs later.
(ii) Before the accumulation of 8,000 total flight cycles, or
within 1,000 flight cycles after August 14, 2012 (the effective date
of AD 2012-13-08, Amendment 39-17110 (77 FR 40481, July 10, 2012)),
whichever occurs later.

(i) Retained One-Time Inspection for Group 2 Airplanes

This paragraph restates the requirements of paragraph (i) of AD
2012-13-08, Amendment 39-17110 (77 FR 40481, July 10, 2012). For
airplanes identified in Boeing Alert Service Bulletin 747-53A2502,
Revision 1, dated June 17, 2010, as Group 2 airplanes: Before the
accumulation of 8,000 total flight cycles, or within 1,000 flight
cycles after August 14, 2012 (the effective date of AD 2012-13-08),
whichever occurs later, do a general visual inspection for correct
configuration, as identified in Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010, of each affected tension
tie and of the surrounding structure, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010.
(1) If all tension ties match the correct configurations
specified in the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2502, Revision 1, dated June 17, 2010, no further
work is required by this paragraph.
(2) If any incorrect configuration is found, before further
flight, do detailed and open fastener-hole HFEC inspections for
cracking in the tension tie and frame, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010.

[[Page 67051]]

(i) If no crack is found during the inspections required by
paragraph (i)(2) of this AD: Before further flight, install the
correct configuration for the tension ties at locations where the
incorrect configuration was found, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010; except where Boeing Alert
Service Bulletin 747-53A2502, Revision 1, dated June 17, 2010,
specifies to contact Boeing for installation instructions, use a
method approved in accordance with the procedures specified in
paragraph (n) of this AD.
(ii) If any crack is found during the inspections required by
paragraph (i)(2) of this AD, before further flight, do the actions
specified in paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
(A) Repair the crack in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2502, Revision
1, dated June 17, 2010; except where Boeing Alert Service Bulletin
747-53A2502, Revision 1, dated June 17, 2010, specifies to contact
Boeing for appropriate action, before further flight, repair the
crack using a method approved in accordance with the procedures
specified in paragraph (n) of this AD.
(B) Install the correct configuration for the tension ties at
locations where the incorrect configuration was found, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2502, Revision 1, dated June 17, 2010; except where
Boeing Alert Service Bulletin 747-53A2502, Revision 1, dated June
17, 2010, specifies to contact Boeing for installation instructions,
use a method approved in accordance with the procedures specified in
paragraph (n) of this AD.

(j) New Tension Tie and Frame Modification and Inspections

(1) For Groups 1 through 16, Configuration 1, airplanes
identified in Boeing Alert Service Bulletin 747-53A2605, Revision 3,
dated July 10, 2013: At the applicable compliance time specified in
table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2605, Revision 3, dated July 10, 2013, except as
required by paragraph (l)(1) of this AD, do tension tie and frame
modifications, in accordance with Part 1, and surface HFEC
inspections for cracks, in accordance with Part 4, of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2605, Revision 3, dated July 10, 2013. Accomplishment of these
modifications terminates the repetitive inspections required by
paragraphs (g) and (h) of this AD. If any crack is found, before
further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (n) of this
AD.
(2) For Groups 17 and 18 airplanes identified in Boeing Alert
Service Bulletin 747-53A2605, Revision 3, dated July 10, 2013: At
the applicable time specified in table 6 or table 7, as applicable,
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2605, Revision 3, dated July 10, 2013, do a tension tie and
frame modification (replacement of tension ties and frame
structure), in accordance with Part 5 or Part 6, as applicable, of
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-53A2605, Revision 3, dated July 10, 2013. Accomplishment of
these modifications terminates the repetitive inspections required
by paragraph (g) of this AD.

(k) New Repetitive Post-Modification Detailed Inspections of Unmodified
Areas; Repetitive Post-Modification HFEC Inspections of Modified and
Unmodified Areas

(1) For Groups 1 through 16 airplanes identified in Boeing Alert
Service Bulletin 747-53A2605, Revision 3, dated July 10, 2013: At
the applicable time specified in table 2 or table 3 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2605,
Revision 3, dated July 10, 2013, do a detailed inspection for
cracking in the unmodified areas of the tension ties, in accordance
with Part 2 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2605, Revision 3, dated July 10, 2013. If
any cracking is found, before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD. Repeat the detailed inspection thereafter at the
applicable time specified in table 2 or table 3 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2605,
Revision 3, dated July 10, 2013.
(2) For Groups 1 through 16 airplanes identified in Boeing Alert
Service Bulletin 747-53A2605, Revision 3, dated July 10, 2013: At
the applicable time specified in table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2605,
Revision 3, dated July 10, 2013, do eddy current inspections for
cracking in all areas of the tension ties (modified and unmodified),
in accordance with Part 3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2605, Revision 3, dated July
10, 2013. If any cracking is found, before further flight, repair
using a method approved in accordance with the procedures specified
in paragraph (n) of this AD. Repeat the eddy current inspections
thereafter at the time specified in table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2605,
Revision 3, dated July 10, 2013.
(3) For Groups 1 through 16, Configuration 2, airplanes
identified in Boeing Alert Service Bulletin 747-53A2605, Revision 3,
dated July 10, 2013: At the applicable time specified in table 5 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2605, Revision 3, dated July 10, 2013, except as provided by
paragraph (l)(1) of this AD, do surface HFEC inspections for
cracking in the unmodified tension tie center sections, in
accordance with Part 4 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2605, Revision 3, dated July 10, 2013.
If any cracking is found, before further flight, repair using a
method approved in accordance with the procedures specified in
paragraph (n) of this AD. If no cracking is found, no further action
is required until the repetitive inspections required by paragraphs
(k)(1) and (k)(2) begin.
(4) For Groups 17 and 18 airplanes identified in Boeing Alert
Service Bulletin 747-53A2605, Revision 3, dated July 10, 2013: At
the applicable time specified in table 6 or table 7 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2605,
Revision 3, dated July 10, 2013, do detailed and HFEC inspections of
the modified tension tie and frame structure for cracking, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2502, Revision 1, dated June 17, 2010.
Except as required by paragraph (l)(4) of this AD, if any cracking
is found, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (n) of this
AD. Repeat the detailed and HFEC inspections thereafter at the times
specified in table 6 or table 7, as applicable, of Boeing Alert
Service Bulletin 747-53A2605, Revision 3, dated July 10, 2013.

(l) Service Information Clarifications and Exceptions

(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2605, Revision 3, dated July 10, 2013,
specifies a compliance time ``after the revision 3 date of this
service bulletin,'' this AD requires compliance within the specified
time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2605, Revision 3,
dated July 10, 2013, specifies to contact Boeing for repair
instructions, this AD requires repair before further flight using a
method approved in accordance with the procedures specified in
paragraph (n) of this AD.
(3) Boeing Alert Service Bulletin 747-53A2605, Revision 3, dated
July 10, 2013, refers to Section 51-10-02 of the Boeing 747-400F
Structural Repair Manual (SRM) and Section 51-10-01 of the Boeing
747-100/200/300 SRM as additional sources of guidance for removing
small cracks and fatigue damage material from the existing holes in
the unmodified center section of the tension tie channels. Where
those SRM sections state that ``zero-timing must only be used where
specifically permitted in an SRM chapter-section-repair,'' this AD
allows the zero-timing procedures specified in those SRM sections.
(4) Where Boeing Alert Service Bulletin 747-53A2605, Revision 3,
dated July 10, 2013, specifies to contact Boeing for repair
instructions, this AD requires repair before further flight using a
method approved in accordance with the procedures specified in
paragraph (n) of this AD.

(m) Credit for Previous Actions

(1) This paragraph restates the credit provided in paragraph (m)
of AD 2012-13-08, Amendment 39-17110 (77 FR 40481, July 10, 2012).
This paragraph provides credit for the actions required by
paragraphs (j)(1) and(k)(1) of this AD, if those actions were
performed before August 14, 2012 (the effective date of AD 2012-13-
08) using Boeing Alert Service Bulletin 747-53A2605, dated December
8, 2009, which was incorporated by reference in AD 2012-13-08.
(2) For Groups 1 through 16 airplanes identified in Boeing Alert
Service Bulletin

[[Page 67052]]

747-53A2605, Revision 3, dated July 10, 2013: This paragraph
provides credit for the actions required by paragraphs (j)(1) and
(k)(1) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2605, Revision 2, dated December 9, 2011, which is not
incorporated by reference in this AD.

(n) 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 (o)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane.
(4) AMOCs approved for inspections required by AD 2012-13-08,
Amendment 39-17110 (77 FR 40481, July 10, 2012) are approved as
AMOCs for the corresponding inspection provisions of paragraphs (g),
(h), and (i) of this AD.
(5) AMOCs approved for AD 2012-13-08, Amendment 39-17110 (77 FR
40481, July 10, 2012) that granted modification deviations are
approved as AMOCs for the corresponding modification required by
paragraph (j)(1) of this AD.

(o) Related Information

(1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft
Certification Office (ACO), FAA, 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 (p)(6) and (p)(7) of this AD.

(p) Material Incorporated by Reference

(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
December 17, 2014.
(i) Boeing Alert Service Bulletin 747-53A2605, Revision 3, dated
July 10, 2013.
(ii) Reserved.
(4) The following service information was approved for IBR on
August 14, 2012 (77 FR 40481, July 10, 2012).
(i) Boeing Alert Service Bulletin 747-53A2502, Revision 1, dated
June 17, 2010.
(ii) Reserved.
(5) The following service information was approved for IBR on
February 16, 2006 (71 FR 1947, January 12, 2006).
(i) Boeing Special Attention Service Bulletin 747-53-2502, dated
April 21, 2005.
(ii) Reserved.
(6) 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.
(7) 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.
(8) 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 October 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-26536 Filed 11-10-14; 8:45 am]
BILLING CODE 4910-13-P

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