Airworthiness Directives; The Boeing Company Airplanes, 60891-60896 [2012-24412]

Download as PDF Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) Terminating Action Replacing the STA 908 upper butt strap and doing all applicable related investigative and corrective actions, in accordance with Part 4, Part 5, and Part 6, of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–53– 1313, dated November 3, 2011, except as provided by paragraph (i)(2) of this AD, terminates the inspections and chemical spot test required by this AD. (k) 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. pmangrum on DSK3VPTVN1PROD with RULES (l) Related Information For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917–6447; fax: (425) 917–6590; email: wayne.lockett@faa.gov. (m) 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 Special Attention Service Bulletin 737–53–1313, dated November 3, 2011. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. VerDate Mar<15>2010 15:07 Oct 04, 2012 Jkt 229001 (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. Issued in Renton, Washington, on September 21, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–24280 Filed 10–4–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0492; Directorate Identifier 2010–NM–126–AD; Amendment 39–17209; AD 2012–20–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 747 airplanes. That AD currently requires repetitive visual inspections around the bushings of the wing landing gear (WLG) beam outboard end fittings for corrosion, and rework if necessary; and ultrasonic inspections for cracks of the outboard end fittings of the WLG support beams, and rework if necessary. This new AD adds airplanes and adds repetitive inspections of the outboard end fitting of the left and right WLG support beams for cracks and corrosion, and corrective actions if necessary. This AD was prompted by new reports of corrosion damage to the end fittings of the WLG support beams, and one report of subsequent cracking in the end fittings. We are issuing this AD to detect and correct corrosion and subsequent cracking in the outboard end fittings, which could result in separation of the fitting and damage to adjacent flight control cables and hydraulic systems and consequent reduced controllability of the airplane. DATES: This AD is effective November 9, 2012. SUMMARY: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 60891 The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 9, 2012. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1, fax 206–766–5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; 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. FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6432; fax: (425) 917–6590; email: bill.ashforth@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 89–15–07, Amendment 39–6267 (54 FR 30009, July 18, 1989). That AD applies to the specified products. The NPRM published in the Federal Register on May 31, 2012 (77 FR 32064). That NPRM proposed to continue to require repetitive visual inspections around the bushings of the wing landing gear (WLG) beam outboard end fittings for corrosion, and rework if necessary; and ultrasonic inspections for cracks of the outboard end fittings of the WLG support beams, and rework if necessary. That NPRM also proposed to add airplanes and repetitive inspections of the outboard end fitting of the left and right WLG support beams for cracks and E:\FR\FM\05OCR1.SGM 05OCR1 60892 Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations corrosion, and corrective actions if necessary. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 32064, May 31, 2012) and the FAA’s response to each comment. Request To Change Certain Language in Paragraph (s) of the NPRM (77 FR 32064, May 31, 2012) Boeing asked that the following sentence be added to paragraph (s) of the NPRM (77 FR 32064, May 31, 2012): ‘‘After accomplishing the repair or change in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, do the applicable actions required by paragraph (r) of this AD.’’ Boeing stated that the follow-on inspections are required after accomplishing the repair or replacement in Part 7. Boeing added that paragraph (q) of the NPRM contains a similar requirement for Groups 1 through 5 airplanes. We partially agree with the commenter. We agree that the language specified in paragraphs (q) and (s) of the NPRM (77 FR 32064, May 31, 2012) is inconsistent. However, we do not agree to include the additional sentence in paragraph (s) of this final rule because it would continue to restate redundant information, and may further confuse operators. Therefore, we have removed ‘‘* * * do the applicable actions required by paragraph (p) of this AD,’’ as was specified in paragraph (q) of the NPRM, in order to provide consistency between those related paragraphs. Request To Include Certain Part Numbers (P/Ns) in the NPRM (77 FR 32064, May 31, 2012) Qantas Airways (QAN) asked that the NPRM (77 FR 32064, May 31, 2012) be reviewed to accurately capture all approved part numbers for end fitting replacements. QAN stated that, for its Model 747–400 Configuration 6 airplanes, Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, specifies that if a replacement spare end fitting is required, an end fitting assembly having P/N 112U1701– 1 is to be used for that replacement. QAN noted that the parts page inventory list from the original equipment manufacturer (OEM) shows that P/N 112U1701–1 is no longer available and has been replaced with P/N 112U2701– 7. QAN also noted that P/N 65B14473– 23 and P/N 65B14473–24 are no longer available and have been replaced by P/ N 65B14473–33 and P/N 65B14473–34, respectively. QAN added that these replacement parts are not identified in the referenced service information. QAN also stated that, if any of the replacement parts are used, it will be forced to request an alternative method of compliance (AMOC) from the OEM to approve the use of an alternate part in order to comply with the AD requirements. We acknowledge the commenter’s concerns. However, as specified in the NPRM (77 FR 32064, May 31, 2012), since issuance of AD 89–15–07, Amendment 39–6267 (54 FR 30009, July 18, 1989), corrosion occurred again at the lug bore and bushing interface because moisture continued to develop in that area due to exposure of the end fittings to environmental conditions. Subsequently, cracks occurred at the corroded areas of the end fittings; therefore, the unsafe condition specified in the existing AD has not been corrected. We find that issuing this AD without further delay is necessary to adequately address the identified unsafe condition. Operators may submit a request for approval of the replacement part numbers (P/Ns) through an AMOC, as specified in paragraph (u) of the AD. We have not changed the AD in this regard. Request To Change Certain Paragraph Identifiers in the NPRM (77 FR 32064, May 31, 2012) Boeing and Atlas Air asked that the paragraph identifier in the last sentence in paragraph (l) of the NPRM (77 FR 32064, May 31, 2012) be changed from paragraph (j) to paragraph (p). Boeing and Atlas Air stated that paragraph (j) of the NPRM would not be applicable since it applies to inspections of the end fittings prior to accomplishing the repair or replacement in Part 7 of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. Atlas Air added that paragraph (p) of the NPRM defines the procedures for follow-on end fitting inspections on which the repair or replacement specified in Part 7 has been done. Boeing, Atlas Air, and UPS asked that the paragraph identifier in the last sentence in paragraph (n) of the NPRM (77 FR 32064, May 31, 2012) be changed from paragraph (m) to paragraph (r). Boeing, Atlas Air, and UPS stated that paragraph (m) of the NPRM applies to inspections of the end fittings prior to accomplishing the repair or replacement in Part 7 of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. Atlas Air added that paragraph (r) of the NPRM defines the procedures for follow-on end fitting inspections on which the repair or replacement specified in Part 7 has been done. We agree with the commenters for the reasons provided. We have changed the paragraph identifiers in paragraphs (l) and (n) of this AD accordingly. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Explanation of Change to Costs of Compliance Since issuance of AD 89–15–07, Amendment 39–6267 (54 FR 30009, July 18, 1989), we have increased the labor rate used in the Costs of Compliance from $40 per work-hour to $85 per work-hour. The Costs of Compliance information, below, reflects this increase in the specified labor rate. Costs of Compliance We estimate that this AD affects 173 airplanes of U.S. registry. We estimate the following costs to comply with this AD: pmangrum on DSK3VPTVN1PROD with RULES ESTIMATED COSTS Action Labor cost Inspections [retained actions from existing AD 89–15–07, Amendment 39-6267 (54 FR 30009, July 18, 1989)]. 10 work-hours × $85 per hour = $850 per inspection cycle. VerDate Mar<15>2010 15:07 Oct 04, 2012 Jkt 229001 PO 00000 Parts cost Frm 00010 Cost per product $0 Fmt 4700 Sfmt 4700 $850 per inspection cycle ...... E:\FR\FM\05OCR1.SGM 05OCR1 Cost on U.S. operators $147,050 per inspection cycle. Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 60893 ESTIMATED COSTS—Continued Action Inspections [new action] ......... Labor cost Parts cost Up to 67 work-hours × $85 per hour = $5,695 per inspection cycle, depending on configuration. We estimate the following costs to do any necessary repairs/replacements that Cost per product $0 Cost on U.S. operators Up to $5,695 per inspection cycle, depending on configuration. would be required based on the results of the inspection. We have no way of Up to $985,235 per inspection cycle, depending on configuration. determining the number of aircraft that might need these repairs/replacements: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Repair or replacement ................... Up to 71 work-hours × $85 per hour = $6,035, depending on configuration. Up to $26,436, depending on configuration. Up to $32,471, depending on configuration. 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. pmangrum on DSK3VPTVN1PROD with RULES Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities VerDate Mar<15>2010 15:07 Oct 04, 2012 Jkt 229001 under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 89–15–07, Amendment 39–6267 (54 FR 30009, July 18, 1989), and adding the following new AD: ■ 2012–20–03 The Boeing Company: Amendment 39–17209; Docket No. FAA–2012–0492; Directorate Identifier 2010–NM–126–AD. (a) Effective Date This airworthiness directive (AD) is effective November 9, 2012. (b) Affected ADs This AD supersedes AD 89–15–07, Amendment 39–6267 (54 FR 30009, July 18, 1989). (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by new reports of corrosion damage to the end fittings of the wing landing gear (WLG) support beams, and one report of subsequent cracking in the end fittings. We are issuing this AD to detect and correct corrosion and subsequent cracking in the outboard end fittings, which could result in separation of the fitting and damage to adjacent flight control cables and hydraulic systems and consequent reduced controllability of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Retained Repetitive Inspections With Revised Compliance Times This paragraph restates the requirements of paragraphs A., B., C., and D., of AD 89–15– 07, Amendment 39–6267 (54 FR 30009, July 18, 1989) with revised compliance times. For airplanes identified in Boeing Service Bulletin 747–57–2244, Revision 1, dated July 28, 1988: Prior to the accumulation of 30,000 flight hours or 8 years in service, whichever occurs first; or within the next 14 months after August 22, 1989 (the effective date of AD 89–15–07); whichever occurs later; visually inspect around the fitting lug bushings at the WLG beam outboard end fittings for corrosion, and ultrasonically inspect the WLG beam outboard end fittings for cracks, in accordance with Boeing Service Bulletin 747–57–2244, Revision 1, dated July 28, 1988. Accomplishing the initial inspections required by paragraph (j) of this AD terminates the inspections required by this paragraph. (1) If no cracking or corrosion is found, repeat the inspections at intervals not to exceed 18 months until paragraph (j) of this AD has been accomplished. (2) If cracking is found, prior to further flight, remove the WLG beam outboard E:\FR\FM\05OCR1.SGM 05OCR1 60894 Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations fitting, and rework, in accordance with Boeing Service Bulletin 747–57–2244, Revision 1, dated July 28, 1988. (3) If only corrosion is found, within the next 12 months, rework in accordance with Boeing Service Bulletin 747–57–2244, Revision 1, dated July 28, 1988. The ultrasonic inspections for cracks required by paragraph (g) of this AD must be accomplished at intervals not to exceed 6 months until the rework is accomplished. For any corrosion that is found after the effective date of this AD, the rework must be done before further flight. (h) Retained Terminating Action This paragraph restates the requirements of paragraph E., of AD 89–15–07, Amendment 39–6267 (54 FR 30009, July 18, 1989). Terminating action for the inspections required by paragraph (g) of this AD consists of rework of the WLG beam outboard fittings, in accordance with Boeing Service Bulletin 747–57–2244, Revision 1, dated July 28, 1988. (i) New Compliance Times for This AD For all the actions identified in paragraphs (j) through (t) of this AD, do the actions at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. Where paragraph 1.E., ‘‘Compliance’’ of this service bulletin specifies a compliance time relative to the original issue date of the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. pmangrum on DSK3VPTVN1PROD with RULES (j) New Repetitive Inspections for Groups 1 Through 5 Airplanes For Groups 1 through 3 airplanes, Configurations 1 and 2; and Groups 4 and 5 airplanes: Do detailed and ultrasonic inspections of the end fittings for cracks and corrosion, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (k) New Inspections for No Crack or Corrosion Findings for Groups 1 Through 5 Airplanes If no crack or corrosion is found during any inspection required by paragraph (j) of this AD, do either of the actions required by paragraph (k)(1) or (k)(2) of this AD. (1) Repeat the detailed and ultrasonic inspections of the end fittings for cracks and corrosion, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (2) Do a detailed inspection of the end fittings for fillet seal damage and for cracks and corrosion, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (i) If no fillet seal damage, crack, or corrosion is found: Repeat the inspection required by paragraph (k)(2) of this AD. (ii) If any fillet seal damage is found, but no crack or corrosion is found: Remove the fillet seal, and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 2 of the VerDate Mar<15>2010 15:07 Oct 04, 2012 Jkt 229001 Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (A) If any crack or corrosion is found: Repair or change the end fitting, in accordance with paragraph (l) of this AD. (B) If no crack or corrosion is found: Apply corrosion inhibiting compound on each end fitting, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (1) If no crack or corrosion is found: Apply corrosion inhibiting compound on each end fitting, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, and thereafter repeat the inspections required by paragraph (k)(2)(ii)(B) of this AD. (2) If any crack or corrosion is found: Repair or change the end fitting, in accordance with paragraph (l) of this AD. (l) New Repair for Crack or Corrosion Findings for Groups 1 Through 5 Airplanes If any crack or corrosion is found during any inspection required by paragraph (j) or (k) of this AD: Repair or change the end fitting, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. After accomplishing the repair or change in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, do the applicable actions required by paragraph (p) of this AD. (m) New Repetitive Inspections and Corrective Actions for Group 6 Airplanes For Group 6 airplanes: Do a detailed inspection of the end fittings for fillet seal damage and for cracks and corrosion, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (1) If no fillet seal damage, crack, or corrosion is found: Do the detailed inspection of the end fittings for fillet seal damage and for cracks and corrosion, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (i) If no fillet seal damage, crack, or corrosion is found: Repeat the detailed inspection required by paragraph (m)(1) of this AD. (ii) If any fillet seal damage is found, but no crack or corrosion is found: Remove the fillet seal, and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (A) If any crack or corrosion is found: Repair or change the end fitting, in accordance with paragraph (n) of this AD. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (B) If no crack or corrosion is found: Apply corrosion inhibiting compound on each end fitting, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (1) If any crack or corrosion is found: Repair or change the end fitting, in accordance with paragraph (n) of this AD. (2) If no crack or corrosion is found: Apply corrosion inhibiting compound, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, and thereafter repeat the inspections required by paragraph (m)(1)(ii)(B) of this AD. (2) If any fillet seal damage is found, but no crack or corrosion is found: Remove the fillet seal, and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (i) If any crack or corrosion is found: Repair or change the end fitting, in accordance with paragraph (n) of this AD. (ii) If no crack or corrosion is found: Apply corrosion inhibiting compound on each end fitting, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (A) If any crack or corrosion is found: Repair or change the end fitting, in accordance with paragraph (n) of this AD. (B) If no crack or corrosion is found: Apply corrosion inhibiting compound, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, and thereafter repeat the inspections required by paragraph (m)(2)(ii) of this AD. (n) New Repair for Group 6 Airplanes If any crack or corrosion is found during any inspection required by paragraph (m) of this AD: Repair or change the end fitting, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. After accomplishing the repair or change in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, do the applicable actions required by paragraph (r) of this AD. (o) New Optional Terminating Action for Part 1, Part 2, and Part 3 Inspections In lieu of doing Part 1, Part 2, or Part 3 inspections required by this AD: Repair or change the end fitting, in accordance with Part 7 of the Accomplishment Instructions of E:\FR\FM\05OCR1.SGM 05OCR1 Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations pmangrum on DSK3VPTVN1PROD with RULES Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. After accomplishing the repair or change in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, do the applicable actions required by paragraphs (p) and (r) of this AD. Doing the repair or change terminates the Part 1, 2, or 3 inspections for that part only of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (p) New Follow-On End Fitting Inspection for Groups 1 Through 5 Airplanes For Groups 1 through 5 airplanes on which the repair or change specified in Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, has been done: Do detailed and ultrasonic inspections of the end fittings for cracks and corrosion, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. If no crack or corrosion is found, do the actions required by either paragraph (p)(1) or (p)(2) of this AD. (1) Repeat the detailed and ultrasonic inspections of the end fittings for cracks and corrosion required by paragraph (p) of this AD. (2) Do a detailed inspection of each end fitting for fillet seal damage, cracks, and corrosion, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (i) If no fillet seal damage, crack, or corrosion is found: Repeat the inspection required by paragraph (p)(2) of this AD. (ii) If any fillet seal damage is found, but no crack or corrosion is found: Remove the fillet seal, and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (A) If any crack or corrosion is found: Repair or change the end fitting, as required by paragraph (q) of this AD. (B) If no crack or corrosion is found: Apply corrosion inhibiting compound on each end fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (1) If any crack or corrosion is found: Repair or change the end fitting, as required by paragraph (q) of this AD. (2) If no crack or corrosion is found: Apply corrosion inhibiting compound, in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and repeat the detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 6 of the Accomplishment Instructions of VerDate Mar<15>2010 15:07 Oct 04, 2012 Jkt 229001 Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (q) New Repair for Groups 1 Through 5 Airplanes If any crack or corrosion is found during any inspection required by paragraph (p) of this AD, repair or change the end fitting, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (r) New Follow-On End Fitting Inspection for Group 6 Airplanes For Group 6 airplanes on which the repair or change specified in Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, has been done: Do a detailed inspection of the end fittings for fillet seal damage, cracks, and corrosion, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (1) If no fillet seal damage, crack, or corrosion is found: Do a detailed inspection of each end fitting for fillet seal damage, cracks, and corrosion, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (i) If no fillet seal damage, crack, or corrosion is found: Repeat the inspection required by paragraph (r)(1) of this AD. (ii) If any fillet seal damage is found, but no crack or corrosion is found: Do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (A) If any crack or corrosion is found: Repair or change the end fitting as required by paragraph (s) of this AD. (B) If no crack or corrosion is found: Apply corrosion inhibiting compound on each end fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and repeat the detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (1) If any crack or corrosion is found: Repair or change the end fitting, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (2) If no crack or corrosion is found: Apply corrosion inhibiting compound, in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and repeat the detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (2) If any fillet seal damage is found, but no crack or corrosion is found: Do detailed PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 60895 and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (i) If any crack or corrosion is found: Repair or change the end fitting, as required by paragraph (s) of this AD. (ii) If no crack or corrosion is found: Apply corrosion inhibiting compound on each end fitting, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and do detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (A) If any crack or corrosion is found: Repair or change the end fitting, as required by paragraph (s) of this AD. (B) If no crack or corrosion is found: Apply corrosion inhibiting compound, in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009; and repeat the detailed and HFEC inspections of each end fitting for cracks and corrosion, in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (s) New Repair for Group 6 Airplanes If any crack or corrosion is found during any inspection required by paragraph (r) of this AD, repair or change the end fitting, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. (t) New Optional Action for Part 4, Part 5, and Part 6 Inspections In lieu of doing Part 4, Part 5, or Part 6 inspections required by this AD: Repair or change the end fitting, in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009. After accomplishing the repair or change in accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2331, dated November 12, 2009, do the applicable actions required by paragraphs (p) and (r) of this AD. (u) 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager E:\FR\FM\05OCR1.SGM 05OCR1 60896 Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously in accordance with AD 89–15–07, Amendment 39–6267 (54 FR 30009, July 18, 1989), are approved as AMOCs for the corresponding requirements of this AD. (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: (425) 917–6432; fax: (425) 917– 6590; email: bill.ashforth@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1, fax 206–766– 5680; Internet https:// www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. pmangrum on DSK3VPTVN1PROD with RULES (w) 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– 57A2331, dated November 12, 2009. (ii) Boeing Service Bulletin 747–57–2244, Revision 1, dated July 28, 1988. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. 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. 15:07 Oct 04, 2012 [FR Doc. 2012–24412 Filed 10–4–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 117 [Docket No. USCG–2012–0888] (v) Related Information VerDate Mar<15>2010 Issued in Renton, Washington, on September 26, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. Jkt 229001 Drawbridge Operation Regulation; Delaware River, Between Burlington, NJ and Bristol, PA Coast Guard, DHS. Notice of temporary deviation from regulations. AGENCY: ACTION: The Commander, Fifth Coast Guard District, has issued a temporary deviation from the regulations governing the operation of the Burlington-Bristol Bridge on Route 413, across the Delaware River, at mile 117.8, between Burlington, NJ and Bristol, PA. This deviation restricts the operation of the draw span in order to facilitate the adjustment of the operating lift cables. DATES: This deviation is effective from 7 a.m. on October 30, 2012 to 3 p.m. on November 1, 2012. ADDRESSES: Documents mentioned in this preamble as being available in the docket are part of docket USCG–2012– 0888 and are available online by going to http://www.regulations.gov, inserting USCG–2012–0888 in the ‘‘Keyword’’ box and then clicking ‘‘Search’’. They are also available for inspection or copying at the Docket Management Facility (M–30), U.S. Department of Transportation, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: If you have questions on this rule, call or email Terrance Knowles, Environmental Protection Specialist, Fifth Coast Guard District; telephone 757–398–6587, email Terrance.A.Knowles@uscg.mil. If you have questions on viewing the docket, call Renee V. Wright, Program Manager, Docket Operations, telephone 202–366– 9826. SUPPLEMENTARY INFORMATION: The Burlington County Bridge Commission, who owns and operates this vertical-lift type drawbridge, has requested a temporary deviation from the current SUMMARY: PO 00000 Frm 00014 Fmt 4700 Sfmt 9990 operating regulations set out in 33 CFR 117.5 and 117.716(b) to facilitate the adjustment of the operational lift cables. The Burlington-Bristol Bridge on Route 413, at mile 117.8, across the Delaware River, between Burlington NJ and Bristol PA, has a vertical clearance in the closed position to vessels of 62 feet above mean high water. Under the regular operating schedule the bridge opens on signal as required by 33 CFR 117.5 and the opening of a bridge may not be delayed more than five minutes for a highway bridge, after the signal to open is given as required by 33 CFR 117.716(b). Under this temporary deviation, the Burlington-Bristol Bridge will be closed to navigation and unable to open on signal each day from 7 a.m. until 3 p.m. on October 30, 2012 and November 1, 2012. Vessels that can pass under the bridge without a drawbridge opening may do so at all times. There are no alternate routes for vessels transiting this section of the Delaware River. There are approximately four to six vessels per week from four facilities whose vertical clearance surpasses the closed bridge position, requiring an opening of the draw span. The Coast Guard has coordinated this replacement work with the Mariners’ Advisory Committee for the Bay & River Delaware, and will inform the other users of the waterway through our Local and Broadcast Notices to Mariners of the closure periods for the bridge so that vessels can arrange their transits to minimize any impact caused by the temporary deviation. The bridge will not be able to open in an emergency during lift cable tension adjustments. In accordance with 33 CFR 117.35(e), the drawbridge must return to its regular operating schedule immediately at the end of the designated time period. This deviation from the operating regulations is authorized under 33 CFR 117.35. Dated: September 25, 2012. Waverly W. Gregory, Jr., Bridge Program Manager, Fifth Coast Guard District. [FR Doc. 2012–24598 Filed 10–4–12; 8:45 am] BILLING CODE 9110–04–P E:\FR\FM\05OCR1.SGM 05OCR1

Agencies

[Federal Register Volume 77, Number 194 (Friday, October 5, 2012)]
[Rules and Regulations]
[Pages 60891-60896]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-24412]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0492; Directorate Identifier 2010-NM-126-AD; 
Amendment 39-17209; AD 2012-20-03]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for certain The Boeing Company Model 747 airplanes. That AD currently 
requires repetitive visual inspections around the bushings of the wing 
landing gear (WLG) beam outboard end fittings for corrosion, and rework 
if necessary; and ultrasonic inspections for cracks of the outboard end 
fittings of the WLG support beams, and rework if necessary. This new AD 
adds airplanes and adds repetitive inspections of the outboard end 
fitting of the left and right WLG support beams for cracks and 
corrosion, and corrective actions if necessary. This AD was prompted by 
new reports of corrosion damage to the end fittings of the WLG support 
beams, and one report of subsequent cracking in the end fittings. We 
are issuing this AD to detect and correct corrosion and subsequent 
cracking in the outboard end fittings, which could result in separation 
of the fitting and damage to adjacent flight control cables and 
hydraulic systems and consequent reduced controllability of the 
airplane.

DATES: This AD is effective November 9, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of November 9, 
2012.

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6432; fax: (425) 917-6590; email: bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 89-15-07, Amendment 39-6267 (54 FR 30009, July 
18, 1989). That AD applies to the specified products. The NPRM 
published in the Federal Register on May 31, 2012 (77 FR 32064). That 
NPRM proposed to continue to require repetitive visual inspections 
around the bushings of the wing landing gear (WLG) beam outboard end 
fittings for corrosion, and rework if necessary; and ultrasonic 
inspections for cracks of the outboard end fittings of the WLG support 
beams, and rework if necessary. That NPRM also proposed to add 
airplanes and repetitive inspections of the outboard end fitting of the 
left and right WLG support beams for cracks and

[[Page 60892]]

corrosion, and corrective actions if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 32064, May 31, 2012) and the FAA's response to each comment.

Request To Change Certain Language in Paragraph (s) of the NPRM (77 FR 
32064, May 31, 2012)

    Boeing asked that the following sentence be added to paragraph (s) 
of the NPRM (77 FR 32064, May 31, 2012): ``After accomplishing the 
repair or change in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009, do the applicable actions required by paragraph (r) 
of this AD.'' Boeing stated that the follow-on inspections are required 
after accomplishing the repair or replacement in Part 7. Boeing added 
that paragraph (q) of the NPRM contains a similar requirement for 
Groups 1 through 5 airplanes.
    We partially agree with the commenter. We agree that the language 
specified in paragraphs (q) and (s) of the NPRM (77 FR 32064, May 31, 
2012) is inconsistent. However, we do not agree to include the 
additional sentence in paragraph (s) of this final rule because it 
would continue to restate redundant information, and may further 
confuse operators. Therefore, we have removed ``* * * do the applicable 
actions required by paragraph (p) of this AD,'' as was specified in 
paragraph (q) of the NPRM, in order to provide consistency between 
those related paragraphs.

Request To Include Certain Part Numbers (P/Ns) in the NPRM (77 FR 
32064, May 31, 2012)

    Qantas Airways (QAN) asked that the NPRM (77 FR 32064, May 31, 
2012) be reviewed to accurately capture all approved part numbers for 
end fitting replacements. QAN stated that, for its Model 747-400 
Configuration 6 airplanes, Boeing Alert Service Bulletin 747-57A2331, 
dated November 12, 2009, specifies that if a replacement spare end 
fitting is required, an end fitting assembly having P/N 112U1701-1 is 
to be used for that replacement. QAN noted that the parts page 
inventory list from the original equipment manufacturer (OEM) shows 
that P/N 112U1701-1 is no longer available and has been replaced with 
P/N 112U2701-7. QAN also noted that P/N 65B14473-23 and P/N 65B14473-24 
are no longer available and have been replaced by P/N 65B14473-33 and 
P/N 65B14473-34, respectively. QAN added that these replacement parts 
are not identified in the referenced service information. QAN also 
stated that, if any of the replacement parts are used, it will be 
forced to request an alternative method of compliance (AMOC) from the 
OEM to approve the use of an alternate part in order to comply with the 
AD requirements.
    We acknowledge the commenter's concerns. However, as specified in 
the NPRM (77 FR 32064, May 31, 2012), since issuance of AD 89-15-07, 
Amendment 39-6267 (54 FR 30009, July 18, 1989), corrosion occurred 
again at the lug bore and bushing interface because moisture continued 
to develop in that area due to exposure of the end fittings to 
environmental conditions. Subsequently, cracks occurred at the corroded 
areas of the end fittings; therefore, the unsafe condition specified in 
the existing AD has not been corrected. We find that issuing this AD 
without further delay is necessary to adequately address the identified 
unsafe condition. Operators may submit a request for approval of the 
replacement part numbers (P/Ns) through an AMOC, as specified in 
paragraph (u) of the AD. We have not changed the AD in this regard.

Request To Change Certain Paragraph Identifiers in the NPRM (77 FR 
32064, May 31, 2012)

    Boeing and Atlas Air asked that the paragraph identifier in the 
last sentence in paragraph (l) of the NPRM (77 FR 32064, May 31, 2012) 
be changed from paragraph (j) to paragraph (p). Boeing and Atlas Air 
stated that paragraph (j) of the NPRM would not be applicable since it 
applies to inspections of the end fittings prior to accomplishing the 
repair or replacement in Part 7 of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009. Atlas Air added that paragraph (p) of 
the NPRM defines the procedures for follow-on end fitting inspections 
on which the repair or replacement specified in Part 7 has been done.
    Boeing, Atlas Air, and UPS asked that the paragraph identifier in 
the last sentence in paragraph (n) of the NPRM (77 FR 32064, May 31, 
2012) be changed from paragraph (m) to paragraph (r). Boeing, Atlas 
Air, and UPS stated that paragraph (m) of the NPRM applies to 
inspections of the end fittings prior to accomplishing the repair or 
replacement in Part 7 of Boeing Alert Service Bulletin 747-57A2331, 
dated November 12, 2009. Atlas Air added that paragraph (r) of the NPRM 
defines the procedures for follow-on end fitting inspections on which 
the repair or replacement specified in Part 7 has been done.
    We agree with the commenters for the reasons provided. We have 
changed the paragraph identifiers in paragraphs (l) and (n) of this AD 
accordingly.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We also determined that 
these changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Explanation of Change to Costs of Compliance

    Since issuance of AD 89-15-07, Amendment 39-6267 (54 FR 30009, July 
18, 1989), we have increased the labor rate used in the Costs of 
Compliance from $40 per work-hour to $85 per work-hour. The Costs of 
Compliance information, below, reflects this increase in the specified 
labor rate.

Costs of Compliance

    We estimate that this AD affects 173 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 [retained actions      10 work-hours x $85              $0  $850 per inspection  $147,050 per
 from existing AD 89-15-07,         per hour = $850                      cycle.               inspection cycle.
 Amendment 39[dash]6267 (54 FR      per inspection
 30009, July 18, 1989)].            cycle.

[[Page 60893]]

 
Inspections [new action].........  Up to 67 work-hours              $0  Up to $5,695 per     Up to $985,235 per
                                    x $85 per hour =                     inspection cycle,    inspection cycle,
                                    $5,695 per                           depending on         depending on
                                    inspection cycle,                    configuration.       configuration.
                                    depending on
                                    configuration.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the 
inspection. We have no way of determining the number of aircraft that 
might need these repairs/replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Repair or replacement................  Up to 71 work-hours x    Up to $26,436,           Up to $32,471,
                                        $85 per hour = $6,035,   depending on             depending on
                                        depending on             configuration.           configuration.
                                        configuration.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]


0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
89-15-07, Amendment 39-6267 (54 FR 30009, July 18, 1989), and adding 
the following new AD:

2012-20-03 The Boeing Company: Amendment 39-17209; Docket No. FAA-
2012-0492; Directorate Identifier 2010-NM-126-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective November 9, 2012.

(b) Affected ADs

    This AD supersedes AD 89-15-07, Amendment 39-6267 (54 FR 30009, 
July 18, 1989).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SR, and 747SP series airplanes; certificated in 
any category; as identified in Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by new reports of corrosion damage to the 
end fittings of the wing landing gear (WLG) support beams, and one 
report of subsequent cracking in the end fittings. We are issuing 
this AD to detect and correct corrosion and subsequent cracking in 
the outboard end fittings, which could result in separation of the 
fitting and damage to adjacent flight control cables and hydraulic 
systems and consequent reduced controllability of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Repetitive Inspections With Revised Compliance Times

    This paragraph restates the requirements of paragraphs A., B., 
C., and D., of AD 89-15-07, Amendment 39-6267 (54 FR 30009, July 18, 
1989) with revised compliance times. For airplanes identified in 
Boeing Service Bulletin 747-57-2244, Revision 1, dated July 28, 
1988: Prior to the accumulation of 30,000 flight hours or 8 years in 
service, whichever occurs first; or within the next 14 months after 
August 22, 1989 (the effective date of AD 89-15-07); whichever 
occurs later; visually inspect around the fitting lug bushings at 
the WLG beam outboard end fittings for corrosion, and ultrasonically 
inspect the WLG beam outboard end fittings for cracks, in accordance 
with Boeing Service Bulletin 747-57-2244, Revision 1, dated July 28, 
1988. Accomplishing the initial inspections required by paragraph 
(j) of this AD terminates the inspections required by this 
paragraph.
    (1) If no cracking or corrosion is found, repeat the inspections 
at intervals not to exceed 18 months until paragraph (j) of this AD 
has been accomplished.
    (2) If cracking is found, prior to further flight, remove the 
WLG beam outboard

[[Page 60894]]

fitting, and rework, in accordance with Boeing Service Bulletin 747-
57-2244, Revision 1, dated July 28, 1988.
    (3) If only corrosion is found, within the next 12 months, 
rework in accordance with Boeing Service Bulletin 747-57-2244, 
Revision 1, dated July 28, 1988. The ultrasonic inspections for 
cracks required by paragraph (g) of this AD must be accomplished at 
intervals not to exceed 6 months until the rework is accomplished. 
For any corrosion that is found after the effective date of this AD, 
the rework must be done before further flight.

(h) Retained Terminating Action

    This paragraph restates the requirements of paragraph E., of AD 
89-15-07, Amendment 39-6267 (54 FR 30009, July 18, 1989). 
Terminating action for the inspections required by paragraph (g) of 
this AD consists of rework of the WLG beam outboard fittings, in 
accordance with Boeing Service Bulletin 747-57-2244, Revision 1, 
dated July 28, 1988.

(i) New Compliance Times for This AD

    For all the actions identified in paragraphs (j) through (t) of 
this AD, do the actions at the applicable time specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009. Where paragraph 1.E., 
``Compliance'' of this service bulletin specifies a compliance time 
relative to the original issue date of the service bulletin, this AD 
requires compliance within the specified compliance time after the 
effective date of this AD.

(j) New Repetitive Inspections for Groups 1 Through 5 Airplanes

    For Groups 1 through 3 airplanes, Configurations 1 and 2; and 
Groups 4 and 5 airplanes: Do detailed and ultrasonic inspections of 
the end fittings for cracks and corrosion, in accordance with Part 1 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009.

(k) New Inspections for No Crack or Corrosion Findings for Groups 1 
Through 5 Airplanes

    If no crack or corrosion is found during any inspection required 
by paragraph (j) of this AD, do either of the actions required by 
paragraph (k)(1) or (k)(2) of this AD.
    (1) Repeat the detailed and ultrasonic inspections of the end 
fittings for cracks and corrosion, in accordance with Part 1 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
    (2) Do a detailed inspection of the end fittings for fillet seal 
damage and for cracks and corrosion, in accordance with Part 2 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009.
    (i) If no fillet seal damage, crack, or corrosion is found: 
Repeat the inspection required by paragraph (k)(2) of this AD.
    (ii) If any fillet seal damage is found, but no crack or 
corrosion is found: Remove the fillet seal, and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (A) If any crack or corrosion is found: Repair or change the end 
fitting, in accordance with paragraph (l) of this AD.
    (B) If no crack or corrosion is found: Apply corrosion 
inhibiting compound on each end fitting, in accordance with Part 2 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009; and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (1) If no crack or corrosion is found: Apply corrosion 
inhibiting compound on each end fitting, in accordance with Part 3 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009, and thereafter repeat the 
inspections required by paragraph (k)(2)(ii)(B) of this AD.
    (2) If any crack or corrosion is found: Repair or change the end 
fitting, in accordance with paragraph (l) of this AD.

(l) New Repair for Crack or Corrosion Findings for Groups 1 Through 5 
Airplanes

    If any crack or corrosion is found during any inspection 
required by paragraph (j) or (k) of this AD: Repair or change the 
end fitting, in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009. After accomplishing the repair or change in 
accordance with Part 7 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009, do the 
applicable actions required by paragraph (p) of this AD.

(m) New Repetitive Inspections and Corrective Actions for Group 6 
Airplanes

    For Group 6 airplanes: Do a detailed inspection of the end 
fittings for fillet seal damage and for cracks and corrosion, in 
accordance with Part 1 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (1) If no fillet seal damage, crack, or corrosion is found: Do 
the detailed inspection of the end fittings for fillet seal damage 
and for cracks and corrosion, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
    (i) If no fillet seal damage, crack, or corrosion is found: 
Repeat the detailed inspection required by paragraph (m)(1) of this 
AD.
    (ii) If any fillet seal damage is found, but no crack or 
corrosion is found: Remove the fillet seal, and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (A) If any crack or corrosion is found: Repair or change the end 
fitting, in accordance with paragraph (n) of this AD.
    (B) If no crack or corrosion is found: Apply corrosion 
inhibiting compound on each end fitting, in accordance with Part 2 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009; and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (1) If any crack or corrosion is found: Repair or change the end 
fitting, in accordance with paragraph (n) of this AD.
    (2) If no crack or corrosion is found: Apply corrosion 
inhibiting compound, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009, and thereafter repeat the inspections required by 
paragraph (m)(1)(ii)(B) of this AD.
    (2) If any fillet seal damage is found, but no crack or 
corrosion is found: Remove the fillet seal, and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 1 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (i) If any crack or corrosion is found: Repair or change the end 
fitting, in accordance with paragraph (n) of this AD.
    (ii) If no crack or corrosion is found: Apply corrosion 
inhibiting compound on each end fitting, in accordance with Part 1 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009; and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (A) If any crack or corrosion is found: Repair or change the end 
fitting, in accordance with paragraph (n) of this AD.
    (B) If no crack or corrosion is found: Apply corrosion 
inhibiting compound, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009, and thereafter repeat the inspections required by 
paragraph (m)(2)(ii) of this AD.

(n) New Repair for Group 6 Airplanes

    If any crack or corrosion is found during any inspection 
required by paragraph (m) of this AD: Repair or change the end 
fitting, in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009. After accomplishing the repair or change in 
accordance with Part 7 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009, do the 
applicable actions required by paragraph (r) of this AD.

(o) New Optional Terminating Action for Part 1, Part 2, and Part 3 
Inspections

    In lieu of doing Part 1, Part 2, or Part 3 inspections required 
by this AD: Repair or change the end fitting, in accordance with 
Part 7 of the Accomplishment Instructions of

[[Page 60895]]

Boeing Alert Service Bulletin 747-57A2331, dated November 12, 2009. 
After accomplishing the repair or change in accordance with Part 7 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009, do the applicable actions 
required by paragraphs (p) and (r) of this AD. Doing the repair or 
change terminates the Part 1, 2, or 3 inspections for that part only 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009.

(p) New Follow-On End Fitting Inspection for Groups 1 Through 5 
Airplanes

    For Groups 1 through 5 airplanes on which the repair or change 
specified in Part 7 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009, has 
been done: Do detailed and ultrasonic inspections of the end 
fittings for cracks and corrosion, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009. If no crack or corrosion is found, 
do the actions required by either paragraph (p)(1) or (p)(2) of this 
AD.
    (1) Repeat the detailed and ultrasonic inspections of the end 
fittings for cracks and corrosion required by paragraph (p) of this 
AD.
    (2) Do a detailed inspection of each end fitting for fillet seal 
damage, cracks, and corrosion, in accordance with Part 5 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
    (i) If no fillet seal damage, crack, or corrosion is found: 
Repeat the inspection required by paragraph (p)(2) of this AD.
    (ii) If any fillet seal damage is found, but no crack or 
corrosion is found: Remove the fillet seal, and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 5 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (A) If any crack or corrosion is found: Repair or change the end 
fitting, as required by paragraph (q) of this AD.
    (B) If no crack or corrosion is found: Apply corrosion 
inhibiting compound on each end fitting, in accordance with Part 5 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009; and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 6 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (1) If any crack or corrosion is found: Repair or change the end 
fitting, as required by paragraph (q) of this AD.
    (2) If no crack or corrosion is found: Apply corrosion 
inhibiting compound, in accordance with Part 6 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009; and repeat the detailed and HFEC inspections of 
each end fitting for cracks and corrosion, in accordance with Part 6 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009.

(q) New Repair for Groups 1 Through 5 Airplanes

    If any crack or corrosion is found during any inspection 
required by paragraph (p) of this AD, repair or change the end 
fitting, in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009.

(r) New Follow-On End Fitting Inspection for Group 6 Airplanes

    For Group 6 airplanes on which the repair or change specified in 
Part 7 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2331, dated November 12, 2009, has been done: Do a 
detailed inspection of the end fittings for fillet seal damage, 
cracks, and corrosion, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
    (1) If no fillet seal damage, crack, or corrosion is found: Do a 
detailed inspection of each end fitting for fillet seal damage, 
cracks, and corrosion, in accordance with Part 5 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
    (i) If no fillet seal damage, crack, or corrosion is found: 
Repeat the inspection required by paragraph (r)(1) of this AD.
    (ii) If any fillet seal damage is found, but no crack or 
corrosion is found: Do detailed and HFEC inspections of each end 
fitting for cracks and corrosion, in accordance with Part 5 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
    (A) If any crack or corrosion is found: Repair or change the end 
fitting as required by paragraph (s) of this AD.
    (B) If no crack or corrosion is found: Apply corrosion 
inhibiting compound on each end fitting, in accordance with Part 5 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009; and repeat the detailed and 
HFEC inspections of each end fitting for cracks and corrosion, in 
accordance with Part 6 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (1) If any crack or corrosion is found: Repair or change the end 
fitting, in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009.
    (2) If no crack or corrosion is found: Apply corrosion 
inhibiting compound, in accordance with Part 6 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009; and repeat the detailed and HFEC inspections of 
each end fitting for cracks and corrosion, in accordance with Part 6 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009.
    (2) If any fillet seal damage is found, but no crack or 
corrosion is found: Do detailed and HFEC inspections of each end 
fitting for cracks and corrosion, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
    (i) If any crack or corrosion is found: Repair or change the end 
fitting, as required by paragraph (s) of this AD.
    (ii) If no crack or corrosion is found: Apply corrosion 
inhibiting compound on each end fitting, in accordance with Part 4 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009; and do detailed and HFEC 
inspections of each end fitting for cracks and corrosion, in 
accordance with Part 6 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
    (A) If any crack or corrosion is found: Repair or change the end 
fitting, as required by paragraph (s) of this AD.
    (B) If no crack or corrosion is found: Apply corrosion 
inhibiting compound, in accordance with Part 6 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009; and repeat the detailed and HFEC inspections of 
each end fitting for cracks and corrosion, in accordance with Part 6 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2331, dated November 12, 2009.

(s) New Repair for Group 6 Airplanes

    If any crack or corrosion is found during any inspection 
required by paragraph (r) of this AD, repair or change the end 
fitting, in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009.

(t) New Optional Action for Part 4, Part 5, and Part 6 Inspections

    In lieu of doing Part 4, Part 5, or Part 6 inspections required 
by this AD: Repair or change the end fitting, in accordance with 
Part 7 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2331, dated November 12, 2009. After accomplishing 
the repair or change in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated 
November 12, 2009, do the applicable actions required by paragraphs 
(p) and (r) of this AD.

(u) 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 the Related Information 
section 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

[[Page 60896]]

of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously in accordance with AD 89-15-07, 
Amendment 39-6267 (54 FR 30009, July 18, 1989), are approved as 
AMOCs for the corresponding requirements of this AD.

(v) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: (425) 917-6432; fax: (425) 917-6590; email: 
bill.ashforth@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1, fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

(w) 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 747-57A2331, dated November 
12, 2009.
    (ii) Boeing Service Bulletin 747-57-2244, Revision 1, dated July 
28, 1988.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. 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 September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-24412 Filed 10-4-12; 8:45 am]
BILLING CODE 4910-13-P