Airworthiness Directives; The Boeing Company Airplanes, 20229-20234 [2013-07209]

Download as PDF Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations 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. (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) All AMOCs approved for AD 2004–21– 08 (69 FR 62396, October 26, 2004) are approved for this AD. DEPARTMENT OF TRANSPORTATION (l) Related Information SUMMARY: For more information about this AD, contact Gary Park, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946–4123; fax: (316) 946–4107; email: gary.park@faa.gov. (m) Material Incorporated by Reference wreier-aviles on DSK5TPTVN1PROD with RULES (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) Cessna Aircraft Company Single Engine Service Bulletin SEB04–1, Revision 1, dated October 3, 2012. (ii) Reserved. (3) For Cessna Aircraft Company service information identified in this AD, contact Cessna Aircraft Company, Customer service, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517–5800; fax: (316) 517–7271; email: customercare@cessna.textron.com; Internet: http://www.cessnasupport.com. (4) You may view this service information at FAA,, Small Airplane Directorate, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (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 Kansas City, Missouri, on March 14, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–06589 Filed 4–3–13; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 14:43 Apr 03, 2013 Jkt 229001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0994; Directorate Identifier 2012–NM–119–AD; Amendment 39–17402; AD 2013–06–05] 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 all The Boeing Company Model 737– 600, –700, –700C, –800, –900, and –900ER series airplanes. That AD currently requires repetitive inspections of the aft attach lugs of the elevator tab control mechanisms, and replacement of any discrepant elevator tab control mechanism. This new AD requires replacing the left and right elevator tab control mechanisms with elevator tab control mechanisms that have the modified attach lugs, which would terminate the existing requirements. This AD was prompted by reports of failure of the aft attach lugs on the elevator tab control mechanisms, which resulted in severe elevator vibration; and reports of gaps in elevator tab control mechanisms and analysis indicating that additional elevator tab control mechanisms might have bearings that will come loose. We are issuing this AD to prevent discrepancies in the aft attach lugs of the elevator tab control mechanism, which could result in severe elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and aircraft control. DATES: This AD is effective May 9, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 9, 2013. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of September 9, 2010 (75 FR 52242, August 25, 2010). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of April 29, 2010 (75 FR 21499, April 26, 2010). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 20229 MC 2H–65, Seattle, WA 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, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; 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: Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6490; fax: 425–917– 6590; email: kelly.mcguckin@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). (That AD superseded AD 2010–09–05, Amendment 39–16270 (75 FR 21499, April 26, 2010).) That AD applies to the specified products. The NPRM published in the Federal Register on September 20, 2012 (77 FR 58330). That NPRM proposed to continue to require repetitive inspections of the aft attach lugs of the elevator tab control mechanisms, and replacement of any discrepant elevator tab control mechanism. That NPRM also proposed to require replacing the left and right elevator tab control mechanisms with elevator tab control mechanisms that have modified attach lugs, which would terminate the existing requirements. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 58330, September 20, 2012) and the FAA’s response to each comment. Aviation E:\FR\FM\04APR1.SGM 04APR1 20230 Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations wreier-aviles on DSK5TPTVN1PROD with RULES Partners Boeing stated that the installation of winglets per supplemental type certificate (STC) ST00830SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/ rgstc.nsf/0/ 408e012e008616a7862578880060456c/ $FILE/ST00830SE.pdf) does not affect the accomplishment of the manufacturer’s service instructions. United Airlines stated that it agrees with the proposal. Request To Remove Parts Installation Prohibition Boeing requested that we remove paragraph (v) (‘‘New Parts Installation Prohibition’’) from the NPRM (77 FR 58330, September 20, 2012). Boeing stated that we should allow installation of mechanisms having part number (P/ N) 251A2430–13, –14, –15, –16, –17, or –18 within the compliance time specified in the NPRM, and allow continued operations under the provisions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010; and AD 2010–17– 19, Amendment 39–16413 (75 FR 52242, August 25, 2010). Likewise, Boeing requested that we allow installation of mechanisms having P/N 251A2430–101, –102, –103, –104, –105, or –106 within the compliance time specified in the NPRM, and allow continued operations under the provisions of Boeing Alert Service Bulletin 737–27A1299, dated July 1, 2011; and Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012; which are approved as alternative methods of compliance (AMOCs) to AD 2010–17–19. The commenter stated that paragraph (v) of the NPRM (which would prohibit installing those parts as of the effective date of the AD) would reduce operator flexibility by prematurely forcing incorporation of Boeing Service Bulletin 737–27–1300, dated April 16, 2012, before the end of the 60-month compliance period. The commenter added that this also would prevent incorporation of Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012, which Boeing plans to recommend that operators incorporate by April 2013 if they cannot complete terminating action by that date. We partially agree with the request. We agree to allow operators the continued flexibility of using the noted mechanisms in accordance with the provisions of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010), or AMOCs specified in Boeing Alert Service Bulletin 737– 27A1299, dated July 1, 2011, and Boeing VerDate Mar<15>2010 14:43 Apr 03, 2013 Jkt 229001 Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012, before the replacement specified in paragraph (u) of this AD. That replacement is required for airplanes with line numbers 1 through 3909 inclusive. This will provide flexibility and still maintain an adequate level of safety. We disagree, however, with deleting paragraph (v) of this AD. The referenced mechanisms have contributed to a known unsafe condition and must not be used as a spare after the incorporation of paragraph (u) of this AD (which requires replacement of these mechanisms). We have changed paragraph (v) in this final rule to limit the prohibition against installing the referenced parts to a time after the requirements of paragraph (u) have been accomplished for airplanes with line numbers 1 through 3909 inclusive. For airplanes with line numbers 3910 and subsequent, mechanisms with modified aft attach lugs have been installed in production; for these airplanes, the parts referenced in paragraph (v) of this AD are prohibited from installation as of the effective date of this AD. Request To Remove Compliance Time Restriction Request To Revise Identity of Referenced Mechanisms Boeing requested that we revise paragraph (t) of the NPRM (77 FR 58330, September 20, 2012) to limit the affected mechanisms to mechanism P/Ns ‘‘251A2430–13, –14, –15, –16, –17, or –18.’’ Boeing stated that this paragraph should not apply to P/N 251A2430–23 and –24 mechanisms, because their installation is terminating action for the NPRM. The commenter added that paragraph (t) of the NPRM also does not apply to the –101, –102, –103, –104, –105, or –106 mechanism, which have a minimum proposed repetitive inspection requirement of 800 flight hours (not 300 flight hours). We do not agree to incorporate the requested changes in the final rule. Paragraph (t) of the AD restates the requirements of paragraph (t) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). The replacement required by paragraph (u) of this new AD terminates the requirements of AD 2010–17–19, including paragraph (t). The FAA approved an AMOC to AD 2010–17–19 for Boeing Alert Service Bulletin 737– 27A1299, dated July 1, 2011; and Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012; for the requirements of paragraph (t) for the –101, –102, –103, –104, –105, and –106 mechanisms; as specified in paragraph (x)(4) of this AD, that AMOC still applies. We have not changed the final rule regarding this issue. Request To Revise Cost Estimate PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Boeing requested that we revise the NPRM (77 FR 58330, September 20, 2012) to delete ‘‘and until the effective date of this new AD’’ from the second sentence of paragraph (t) of the proposed AD. The commenter stated that operators should be allowed to install P/N 251A2430–13, –14, –15, –16, –17, or –18 mechanisms within the compliance period specified in the NPRM and continue operations under the provisions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010; and AD 2010–17– 19, Amendment 39–16413 (75 FR 52242, August 25, 2010). We agree with the request and have revised paragraph (t) accordingly in this final rule. We are also clarifying the requirements of paragraph (t) in this final rule for line numbers 3910 and subsequent, which are produced with part numbers that terminate the requirements of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). Delta requested that we revise the estimated costs in the NPRM (77 FR 58330, September 20, 2012). Delta stated that the cost information provided in the NPRM does not reflect the most current information available in Boeing Service Bulletin 737–27–1300 Information Notice (IN) 01, dated April 19, 2012, which gives a total of 16 task hours for each installed mechanism (32 hours per airplane) and 10 hours for each modified component (20 hours per airplane). We agree, and have revised the cost estimate accordingly in this final rule. Request To Extend Compliance Time for Related AMOC Delta, American, and Boeing requested that we revise the NPRM (77 FR 58330, September 20, 2012) to extend the compliance time for the AMOC associated with AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). American and Delta stated that we should allow that AMOC to remain valid until the accomplishment of the actions specified in paragraph (u) of the NPRM to allow the fullest benefit of the clip installation. Boeing stated that paragraph (v) of the NPRM conflicts with paragraph (x)(3) of the NPRM regarding the AMOC. Delta stated that Boeing Alert Service Bulletin 737– 27A1299, Revision 1, dated April 16, 2012, notes that the AMOC was intended as interim action and has an E:\FR\FM\04APR1.SGM 04APR1 Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations expiration date of June 30, 2016; Delta concluded that AMOC approval would therefore expire before the 60-month compliance time specified in the NPRM for the replacement in paragraph (u) of the NPRM. We agree with the requests, for the reasons provided by the commenters. We have changed paragraph (x)(4) in this final rule to extend the expiration of the referenced AMOCs. Request To Clarify Reporting Requirement Delta requested that we revise the NPRM (77 FR 58330, September 20, 2012) to clarify the required methods and requirements for reporting completion of the retrofit. Delta noted that paragraph (u) of the NPRM specifies to replace the elevator tab control mechanism in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–27–1300, dated April 16, 2012. Delta stated that the last step of those instructions specifies reporting retrofit completions to Boeing using the service request application on MyBoeingFleet.com. Delta noted that the NPRM does not specifically identify any requirement to report the tab mechanism retrofit completions. We agree to clarify the reporting requirements: Although Boeing Service Bulletin 737–27–1300, dated April 16, 2012, specifies submitting a report, there is no new reporting requirement to report completion of the replacement required by paragraph (u) of this AD. We have changed paragraph (u) in this final rule to state that there is no reporting requirement as part of the replacement. Request To Revise Applicability American requested that we revise paragraph (c) (‘‘Applicability’’) of the NPRM (77 FR 58330, September 20, 2012) to match the applicability of paragraph (u) (mechanism replacement) of the NPRM (which applied to line numbers 1 through 3909 inclusive). American stated that Boeing Alert Service Bulletin 737–27A1297, Revision 2, dated April 16, 2012; and Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012; have been revised to limit the effectivity of this issue. We disagree with the request to revise the applicability. The applicability of this final rule includes the effectivity of those service bulletins. But the applicability of this AD extends to all Model 737–600, -700, -700C, -800, -900, and -900ER series airplanes to account for spares that might also be installed on those airplanes, as specified in paragraph (v) (‘‘New Parts Installation Prohibition’’) in this final rule. We have not revised the final rule further regarding this issue. Explanation of Change Made to This AD We have added paragraph (x)(3) in this final rule to specify that an AMOC 20231 that provides an acceptable level of safety may be used for any repair required by this AD if that repair is approved by the Boeing Commercial Airplanes Organizational Designation Authorization (ODA) that has been authorized by the Manager of the Seattle Aircraft Certification Office to make those findings. 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 and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (77 FR 58330, September 20, 2012) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 58330, September 20, 2012). We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD affects 1,096 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Retained actions ................................ 7 work-hours × $85 per hour = $595 per inspection cycle. 32 work-hours × $85 per hour = $2,720. 52 work-hours × $85 per hour = $4,420. $0 ..................................................... $595 per inspection cycle. $58,5791 $1,140 (installation kit) ..... $62,439 per airplane. $5,858 (for the modification) $1,140 (installation kit) $2,145 (tooling2). $13,563 per airplane. Mechanism replacement (one option for terminating action). Mechanism modification and replacement (one option for terminating action). Cost per product 1 This is the estimated cost for both a left and right mechanism. Boeing is planning a seed/exchange program so operators are not forced to purchase a new mechanism. 2 Per the Boeing service information, tooling is available from Boeing for $90 per day. wreier-aviles on DSK5TPTVN1PROD with RULES 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 VerDate Mar<15>2010 14:43 Apr 03, 2013 Jkt 229001 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 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), E:\FR\FM\04APR1.SGM 04APR1 20232 Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010), and adding the following new AD: ■ 2013–06–05 The Boeing Company: Amendment 39–17402; Docket No. FAA–2012–0994; Directorate Identifier 2012–NM–119–AD. (a) Effective Date This AD is effective May 9, 2013. (b) Affected ADs This AD supersedes AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). (c) Applicability This AD applies to all The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes, certificated in any category. wreier-aviles on DSK5TPTVN1PROD with RULES (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by reports of failure of the aft attach lugs on the elevator tab control mechanisms, which resulted in severe elevator vibration. This AD also results from reports of gaps in elevator tab control mechanisms and analysis that additional elevator tab control mechanisms might have bearings that will come loose. We are issuing this AD to prevent discrepancies in the aft attach lugs of the elevator tab control mechanism, which could result in severe elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and aircraft control. VerDate Mar<15>2010 14:43 Apr 03, 2013 Jkt 229001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections for Group 1 Airplanes This paragraph restates the requirements of paragraph (g) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 1 airplanes, as identified in Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010: Except as required by paragraph (h) of this AD, within 12 days after April 29, 2010 (the effective date of AD 2010–09–05, Amendment 39–16270 (75 FR 21499, April 26, 2010)), do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator tab control mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. Repeat the inspection thereafter at intervals not to exceed 300 flight hours. Doing the replacement specified in paragraph (l) of this AD before September 9, 2010 (the effective date of AD 2010–17–19), terminates the requirements of this paragraph. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph. (h) Retained Extended Twin Operations (ETOPS) Flight Provisions This paragraph restates the requirements of paragraph (h) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 1 airplanes as identified in Boeing Alert Service Bulletin 737– 27A1297, dated April 16, 2010: Beginning 7 days after April 29, 2010 (the effective date of AD 2010–09–05, Amendment 39–21499 (75 FR 21499, April 26, 2010)), no person may operate an airplane on an ETOPS flight unless the initial inspection required by paragraph (g) of this AD has been accomplished. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph. (i) Retained One-Time Inspection for Group 2, Configuration 1, Airplanes This paragraph restates the requirements of paragraph (i) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 2, Configuration 1, airplanes as identified in Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010: Within 30 days after April 29, 2010 (the effective date of AD 2010–09–05, Amendment 39– 16270 (75 FR 21499, April 26, 2010)), do a one-time detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator tab control mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph. (j) Corrective Actions for Paragraphs (g), (i), and (k) of This AD This paragraph restates the requirements of paragraph (j) of AD 2010–17–19, Amendment PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 39–16413 (75 FR 52242, August 25, 2010). If, during any inspection required by paragraph (g), (i), or (k) of this AD, any discrepancy is found, before further flight, replace the elevator tab control mechanism by doing the actions specified in paragraphs (j)(1) and (j)(2) of this AD. (1) Do a detailed inspection for discrepancies of the replacement elevator tab control mechanism; and, if no discrepancy is found, install the replacement elevator tab control mechanism; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. If any discrepancy is found, then that elevator tab control mechanism cannot be installed and the actions specified in this paragraph must be done before further flight on another replacement elevator tab control mechanism. (2) Re-inspect the installed elevator tab control mechanism using the inspection procedure specified in paragraph (i) of this AD. (k) Retained Repetitive Inspections for Certain Group 2, Configuration 1, Airplanes This paragraph restates the requirements of paragraph (k) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 2, Configuration 1, airplanes as identified in Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010, on which the elevator tab control mechanism is replaced with a mechanism other than a new, Boeing-built mechanism: Within 300 flight hours after doing the replacement, do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator tab control mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. Repeat the inspection thereafter at intervals not to exceed 300 flight hours. Doing the replacement specified in paragraph (l) of this AD before September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)), is terminating action for this paragraph. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph. (l) Terminating Action Credit for Paragraphs (g), (i), and (k) of This AD This paragraph restates the requirements of paragraph (l) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). Replacing an elevator tab control mechanism with a new, Boeing-built mechanism before September 9, 2010 (the effective date of AD 2010–17–19), as specified in paragraphs (l)(1) and (l)(2) of this AD, terminates the inspections required by paragraphs (g), (i), and (k) of this AD. Replacement of the elevator tab control mechanism on or after September 9, 2010 (the effective date of AD 2010–17–19), does not terminate the inspections required by paragraphs (g), (i), and (k) of this AD. Note 1 to paragraph (l) of this AD: Additional guidance can be found in paragraphs 3.B.7.b.(1)(a)(1) and 3.B.7.b.(1)(a)(2) of the Accomplishment Instructions of Boeing Alert Service Bulletin E:\FR\FM\04APR1.SGM 04APR1 Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations 737–27A1297, dated April 16, 2010, for establishing whether the mechanism is Boeing built. (1) Do a detailed inspection for discrepancies of the new, Boeing-built replacement elevator tab control mechanism; and, if no discrepancy is found, install the replacement elevator tab control mechanism; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. If any discrepancy is found, then that elevator tab control mechanism cannot be installed and the actions specified in this paragraph must be done on another new, Boeing-built replacement elevator tab control mechanism. (2) Re-inspect the installed elevator tab control mechanism using the inspection procedure specified in paragraph (i) of this AD. wreier-aviles on DSK5TPTVN1PROD with RULES (m) Retained Reporting for Paragraphs (g), (i), and (k) of This AD This paragraph restates the requirements of paragraph (m) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For airplanes identified in Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010: At the applicable time specified in paragraph (m)(1) or (m)(2) of this AD, submit a report of any findings (positive and negative) of the first inspection required by paragraphs (g), (i), and (k) of this AD, and any positive findings from the repetitive inspections required by paragraphs (g) and (k) of this AD, to Boeing Commercial Airplanes Group, Attention: Manager, Airline Support, email: rse.boecom@boeing.com. The report must include the inspection results including a description of any discrepancies found, the airplane line number, and the total number of flight cycles and flight hours accumulated on the airplane. (1) If the inspection was done on or after April 29, 2010 (the effective date of AD 2010–09–05, Amendment 39–16270 (75 FR 21499, April 26, 2010)): Submit the report within 10 days after the inspection. (2) If the inspection was done before April 29, 2010 (the effective date of AD 2010–09– 05, Amendment 39–16270 (75 FR 21499, April 26, 2010)): Submit the report within 10 days after April 29, 2010 (the effective date of AD 2010–09–05). (n) Retained Repetitive Inspections This paragraph restates the requirements of paragraph (n) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For airplanes having line numbers 1 through 3909 inclusive: At the applicable time specified in paragraph (n)(1), (n)(2), or (n)(3) of this AD, do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator tab control mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010. For Groups 1 and 2 airplanes identified in Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010, repeat the inspection thereafter at intervals not to exceed 300 flight hours, except as provided by paragraph (t)(2) of this AD. For Group 3 airplanes identified in Boeing Alert Service Bulletin 737– VerDate Mar<15>2010 14:43 Apr 03, 2013 Jkt 229001 27A1297, Revision 1, dated August 2, 2010, repeat the inspection thereafter at intervals not to exceed 1,800 flight hours, except as required by paragraphs (p) and (t)(2) of this AD. Doing the inspection specified in this paragraph terminates the requirements of paragraphs (g), (h), (i), and (k) of this AD. (1) For Group 1 airplanes identified in Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010: Within 300 flight hours after doing an inspection in accordance with Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010, or within 30 days after September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)), whichever occurs later. (2) For Group 2 airplanes identified in Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010: At the later of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of this AD. (i) Before the accumulation of 2,000 total flight cycles or 4,000 total flight hours, whichever occurs first. (ii) Within 14 days after September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)). (3) For Group 3 airplanes identified in Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010: Within 180 days or 1,800 flight hours after September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)), whichever occurs first. (o) Retained Corrective Actions for Paragraphs (n) and (p) of This AD This paragraph restates the requirements of paragraph (o) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). If, during any inspection required by paragraph (n) or (p) of this AD, any discrepancy is found, before further flight, replace the elevator tab control mechanism by doing the actions specified in paragraphs (o)(1) and (o)(2) of this AD. (1) Do a detailed inspection for discrepancies of the replacement elevator tab control mechanism; and, if no discrepancy is found, install the replacement elevator tab control mechanism; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010. If any discrepancy is found, then that elevator tab control mechanism cannot be installed and the actions specified in this paragraph must be done before further flight on another replacement elevator tab control mechanism. (2) Re-inspect the installed elevator tab control mechanism using the inspection procedure specified in paragraph (n) of this AD. (p) Retained Reduced Repetitive Inspection Interval for Group 3 Airplanes This paragraph restates the requirements of paragraph (p) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 3 airplanes as identified in Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010, on which the elevator tab control mechanism is replaced during the actions required by PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 20233 paragraph (o) of this AD: Within 300 flight hours after doing the replacement, do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the replaced elevator tab control mechanism, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010. Repeat the inspection of the replaced elevator tab control mechanism thereafter at intervals not to exceed 300 flight hours, except as provided by paragraph (t)(2) of this AD. (q) Retained Credit for Previous Action This paragraph restates the provisions specified in paragraph (q) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 1 airplanes as identified in Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010: Inspections done in accordance with Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010, are acceptable for compliance with only the initial inspection required by paragraph (n) of this AD. (r) Retained Reporting for Paragraphs (n) and (p) of This AD This paragraph restates the requirements of paragraph (r) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For airplanes having line numbers 1 through 3909 inclusive: At the applicable time specified in paragraph (r)(1) or (r)(2) of this AD, submit a report of any findings (positive and negative) of the first inspection required by paragraphs (n) and (p) of this AD, except for airplanes on which a report required by paragraph (m) of this AD has been submitted, only submit positive findings; and submit a report of any positive findings from the repetitive inspections required by paragraphs (n) and (p) of this AD; to Boeing Commercial Airplanes Group, Attention: Manager, Airline Support, email: rse.boecom@boeing.com. The report must include the inspection results including a description of any discrepancies found, the airplane line number, and the total number of flight cycles and flight hours accumulated on the airplane. (1) If the inspection was done on or after September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)): Submit the report within 10 days after the inspection. (2) If the inspection was done before September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)): Submit the report within 10 days after September 9, 2010 (the effective date of AD 2010–17–19). (s) Retained Provision Regarding Not Returning Parts This paragraph restates the provision specified in paragraph (s) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). Although Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010; and Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010; specify to return the affected elevator tab control mechanism to the manufacturer, this AD does not require the return of the part to the manufacturer. E:\FR\FM\04APR1.SGM 04APR1 20234 Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations (t) Retained Parts Installation Limitations This paragraph restates the requirements of paragraph (t) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010), with revised limitations. As of September 9, 2010 (the effective date of AD 2010–17–19), and until the replacement required by paragraph (u) of this AD for airplanes with line numbers 1 through 3909 inclusive, or until the effective date of this new AD for airplanes with line numbers 3910 and subsequent, as applicable: Comply with the conditions specified in paragraphs (t)(1) and (t)(2) of this AD. (1) No person may install an elevator tab control mechanism, part number (P/N) 251A2430-(), on any airplane, unless the mechanism has been inspected before and after installation using the inspection procedures specified in paragraphs (o)(1) and (o)(2) of this AD, and no discrepancies have been found. (2) An elevator tab control mechanism, P/ N 251A2430-(), may be installed, provided that the inspection specified in paragraph (n) of this AD is done within 300 flight hours after doing the installation, and that the inspection specified in paragraph (n) of this AD is repeated thereafter at intervals not to exceed 300 flight hours. (u) New Replacement For airplanes having line numbers 1 through 3909 inclusive: Within 60 months after the effective date of this AD, replace the left and right elevator tab control mechanisms with elevator tab control mechanisms that have new machined aft attach lugs, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–27–1300, dated April 16, 2012. This replacement terminates the requirements of paragraphs (g) through (t) of this AD. Although Boeing Service Bulletin 737–27–1300, dated April 16, 2012, specifies submitting a report, there is no requirement to report completion of the replacement required by paragraph (u) of this AD. wreier-aviles on DSK5TPTVN1PROD with RULES (v) New Parts Installation Prohibition As of the effective date of this AD, no person may install, on any airplane identified in paragraph (v)(1) or (v)(2) of this AD, an elevator tab control mechanism having P/N 251A2430–13, –14, –15, –16, –17, –18, –101, –102, –103, –104, –105, or –106. (1) Airplanes on which the replacement in paragraph (u) of this AD has been accomplished. (2) Airplanes with line numbers 3910 and subsequent. (w) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per VerDate Mar<15>2010 14:43 Apr 03, 2013 Jkt 229001 response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (x) 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. (4) AMOCs approved for AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010), are approved as AMOCs for the corresponding provisions of this AD. The expiration of the AMOCS to AD 2010–17–19, as specified in the service information identified in paragraphs (x)(4)(i) and (x)(4)(ii) of this AD, is extended to remain valid until accomplishment of the requirements of paragraph (u) of this AD. (i) Boeing Alert Service Bulletin 737– 27A1299, dated July 1, 2011 (which is not incorporated by reference in this AD). (ii) Boeing Alert Service Bulletin 737– 27A1299, Revision 1, dated April 16, 2012 (which is not incorporated by reference in this AD). (y) Related Information For more information about this AD, contact Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6490; fax: 425–917–6590; email: kelly.mcguckin@faa.gov. (z) 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. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (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 May 9, 2013. (i) Boeing Service Bulletin 737–27–1300, dated April 16, 2012. (ii) Reserved. (4) The following service information was approved for IBR on September 9, 2010 (75 FR 52242, August 25, 2010). (i) Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010. (ii) Reserved. (5) The following service information was approved for IBR on April 29, 2010 (75 FR 21499, April 26, 2010). (i) Boeing Alert Service Bulletin 737– 27A1297, dated April 16, 2010. (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, You may review copies of the 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. (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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 20, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–07209 Filed 4–3–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1014; Directorate Identifier 2010–SW–058–AD; Amendment 39–17404; AD 2013–06–07] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model SA–365N1, AS–365N2, and AS 365 N3 SUMMARY: E:\FR\FM\04APR1.SGM 04APR1

Agencies

[Federal Register Volume 78, Number 65 (Thursday, April 4, 2013)]
[Rules and Regulations]
[Pages 20229-20234]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-07209]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0994; Directorate Identifier 2012-NM-119-AD; 
Amendment 39-17402; AD 2013-06-05]
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 all The Boeing Company Model 737-600, -700, -700C, -800, -900, and 
-900ER series airplanes. That AD currently requires repetitive 
inspections of the aft attach lugs of the elevator tab control 
mechanisms, and replacement of any discrepant elevator tab control 
mechanism. This new AD requires replacing the left and right elevator 
tab control mechanisms with elevator tab control mechanisms that have 
the modified attach lugs, which would terminate the existing 
requirements. This AD was prompted by reports of failure of the aft 
attach lugs on the elevator tab control mechanisms, which resulted in 
severe elevator vibration; and reports of gaps in elevator tab control 
mechanisms and analysis indicating that additional elevator tab control 
mechanisms might have bearings that will come loose. We are issuing 
this AD to prevent discrepancies in the aft attach lugs of the elevator 
tab control mechanism, which could result in severe elevator and tab 
vibration. Consequent structural failure of the elevator or horizontal 
stabilizer could result in loss of structural integrity and aircraft 
control.

DATES: This AD is effective May 9, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 9, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
September 9, 2010 (75 FR 52242, August 25, 2010).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of April 
29, 2010 (75 FR 21499, April 26, 2010).

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 review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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: Kelly McGuckin, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6490; fax: 425-917-6590; email: 
kelly.mcguckin@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2010-17-19, Amendment 39-16413 (75 FR 52242, 
August 25, 2010). (That AD superseded AD 2010-09-05, Amendment 39-16270 
(75 FR 21499, April 26, 2010).) That AD applies to the specified 
products. The NPRM published in the Federal Register on September 20, 
2012 (77 FR 58330). That NPRM proposed to continue to require 
repetitive inspections of the aft attach lugs of the elevator tab 
control mechanisms, and replacement of any discrepant elevator tab 
control mechanism. That NPRM also proposed to require replacing the 
left and right elevator tab control mechanisms with elevator tab 
control mechanisms that have modified attach lugs, which would 
terminate the existing requirements.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 58330, September 20, 2012) and the FAA's response to each 
comment. Aviation

[[Page 20230]]

Partners Boeing stated that the installation of winglets per 
supplemental type certificate (STC) ST00830SE (http://rgl.faa.gov/
Regulatory--and--Guidance--Library/rgstc.nsf/0/
408e012e008616a7862578880060456c/$FILE/ST00830SE.pdf) does not affect 
the accomplishment of the manufacturer's service instructions. United 
Airlines stated that it agrees with the proposal.

Request To Remove Parts Installation Prohibition

    Boeing requested that we remove paragraph (v) (``New Parts 
Installation Prohibition'') from the NPRM (77 FR 58330, September 20, 
2012). Boeing stated that we should allow installation of mechanisms 
having part number (P/N) 251A2430-13, -14, -15, -16, -17, or -18 within 
the compliance time specified in the NPRM, and allow continued 
operations under the provisions of Boeing Alert Service Bulletin 737-
27A1297, Revision 1, dated August 2, 2010; and AD 2010-17-19, Amendment 
39-16413 (75 FR 52242, August 25, 2010). Likewise, Boeing requested 
that we allow installation of mechanisms having P/N 251A2430-101, -102, 
-103, -104, -105, or -106 within the compliance time specified in the 
NPRM, and allow continued operations under the provisions of Boeing 
Alert Service Bulletin 737-27A1299, dated July 1, 2011; and Boeing 
Alert Service Bulletin 737-27A1299, Revision 1, dated April 16, 2012; 
which are approved as alternative methods of compliance (AMOCs) to AD 
2010-17-19. The commenter stated that paragraph (v) of the NPRM (which 
would prohibit installing those parts as of the effective date of the 
AD) would reduce operator flexibility by prematurely forcing 
incorporation of Boeing Service Bulletin 737-27-1300, dated April 16, 
2012, before the end of the 60-month compliance period. The commenter 
added that this also would prevent incorporation of Boeing Alert 
Service Bulletin 737-27A1299, Revision 1, dated April 16, 2012, which 
Boeing plans to recommend that operators incorporate by April 2013 if 
they cannot complete terminating action by that date.
    We partially agree with the request. We agree to allow operators 
the continued flexibility of using the noted mechanisms in accordance 
with the provisions of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, 
August 25, 2010), or AMOCs specified in Boeing Alert Service Bulletin 
737-27A1299, dated July 1, 2011, and Boeing Alert Service Bulletin 737-
27A1299, Revision 1, dated April 16, 2012, before the replacement 
specified in paragraph (u) of this AD. That replacement is required for 
airplanes with line numbers 1 through 3909 inclusive. This will provide 
flexibility and still maintain an adequate level of safety. We 
disagree, however, with deleting paragraph (v) of this AD. The 
referenced mechanisms have contributed to a known unsafe condition and 
must not be used as a spare after the incorporation of paragraph (u) of 
this AD (which requires replacement of these mechanisms). We have 
changed paragraph (v) in this final rule to limit the prohibition 
against installing the referenced parts to a time after the 
requirements of paragraph (u) have been accomplished for airplanes with 
line numbers 1 through 3909 inclusive. For airplanes with line numbers 
3910 and subsequent, mechanisms with modified aft attach lugs have been 
installed in production; for these airplanes, the parts referenced in 
paragraph (v) of this AD are prohibited from installation as of the 
effective date of this AD.

Request To Revise Identity of Referenced Mechanisms

    Boeing requested that we revise paragraph (t) of the NPRM (77 FR 
58330, September 20, 2012) to limit the affected mechanisms to 
mechanism P/Ns ``251A2430-13, -14, -15, -16, -17, or -18.'' Boeing 
stated that this paragraph should not apply to P/N 251A2430-23 and -24 
mechanisms, because their installation is terminating action for the 
NPRM. The commenter added that paragraph (t) of the NPRM also does not 
apply to the -101, -102, -103, -104, -105, or -106 mechanism, which 
have a minimum proposed repetitive inspection requirement of 800 flight 
hours (not 300 flight hours).
    We do not agree to incorporate the requested changes in the final 
rule. Paragraph (t) of the AD restates the requirements of paragraph 
(t) of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 
2010). The replacement required by paragraph (u) of this new AD 
terminates the requirements of AD 2010-17-19, including paragraph (t). 
The FAA approved an AMOC to AD 2010-17-19 for Boeing Alert Service 
Bulletin 737-27A1299, dated July 1, 2011; and Boeing Alert Service 
Bulletin 737-27A1299, Revision 1, dated April 16, 2012; for the 
requirements of paragraph (t) for the -101, -102, -103, -104, -105, and 
-106 mechanisms; as specified in paragraph (x)(4) of this AD, that AMOC 
still applies. We have not changed the final rule regarding this issue.

Request To Remove Compliance Time Restriction

    Boeing requested that we revise the NPRM (77 FR 58330, September 
20, 2012) to delete ``and until the effective date of this new AD'' 
from the second sentence of paragraph (t) of the proposed AD. The 
commenter stated that operators should be allowed to install P/N 
251A2430-13, -14, -15, -16, -17, or -18 mechanisms within the 
compliance period specified in the NPRM and continue operations under 
the provisions of Boeing Alert Service Bulletin 737-27A1297, Revision 
1, dated August 2, 2010; and AD 2010-17-19, Amendment 39-16413 (75 FR 
52242, August 25, 2010).
    We agree with the request and have revised paragraph (t) 
accordingly in this final rule. We are also clarifying the requirements 
of paragraph (t) in this final rule for line numbers 3910 and 
subsequent, which are produced with part numbers that terminate the 
requirements of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 
25, 2010).

Request To Revise Cost Estimate

    Delta requested that we revise the estimated costs in the NPRM (77 
FR 58330, September 20, 2012). Delta stated that the cost information 
provided in the NPRM does not reflect the most current information 
available in Boeing Service Bulletin 737-27-1300 Information Notice 
(IN) 01, dated April 19, 2012, which gives a total of 16 task hours for 
each installed mechanism (32 hours per airplane) and 10 hours for each 
modified component (20 hours per airplane).
    We agree, and have revised the cost estimate accordingly in this 
final rule.

Request To Extend Compliance Time for Related AMOC

    Delta, American, and Boeing requested that we revise the NPRM (77 
FR 58330, September 20, 2012) to extend the compliance time for the 
AMOC associated with AD 2010-17-19, Amendment 39-16413 (75 FR 52242, 
August 25, 2010). American and Delta stated that we should allow that 
AMOC to remain valid until the accomplishment of the actions specified 
in paragraph (u) of the NPRM to allow the fullest benefit of the clip 
installation. Boeing stated that paragraph (v) of the NPRM conflicts 
with paragraph (x)(3) of the NPRM regarding the AMOC. Delta stated that 
Boeing Alert Service Bulletin 737-27A1299, Revision 1, dated April 16, 
2012, notes that the AMOC was intended as interim action and has an

[[Page 20231]]

expiration date of June 30, 2016; Delta concluded that AMOC approval 
would therefore expire before the 60-month compliance time specified in 
the NPRM for the replacement in paragraph (u) of the NPRM.
    We agree with the requests, for the reasons provided by the 
commenters. We have changed paragraph (x)(4) in this final rule to 
extend the expiration of the referenced AMOCs.

Request To Clarify Reporting Requirement

    Delta requested that we revise the NPRM (77 FR 58330, September 20, 
2012) to clarify the required methods and requirements for reporting 
completion of the retrofit. Delta noted that paragraph (u) of the NPRM 
specifies to replace the elevator tab control mechanism in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 737-27-
1300, dated April 16, 2012. Delta stated that the last step of those 
instructions specifies reporting retrofit completions to Boeing using 
the service request application on MyBoeingFleet.com. Delta noted that 
the NPRM does not specifically identify any requirement to report the 
tab mechanism retrofit completions.
    We agree to clarify the reporting requirements: Although Boeing 
Service Bulletin 737-27-1300, dated April 16, 2012, specifies 
submitting a report, there is no new reporting requirement to report 
completion of the replacement required by paragraph (u) of this AD. We 
have changed paragraph (u) in this final rule to state that there is no 
reporting requirement as part of the replacement.

Request To Revise Applicability

    American requested that we revise paragraph (c) (``Applicability'') 
of the NPRM (77 FR 58330, September 20, 2012) to match the 
applicability of paragraph (u) (mechanism replacement) of the NPRM 
(which applied to line numbers 1 through 3909 inclusive). American 
stated that Boeing Alert Service Bulletin 737-27A1297, Revision 2, 
dated April 16, 2012; and Boeing Alert Service Bulletin 737-27A1299, 
Revision 1, dated April 16, 2012; have been revised to limit the 
effectivity of this issue.
    We disagree with the request to revise the applicability. The 
applicability of this final rule includes the effectivity of those 
service bulletins. But the applicability of this AD extends to all 
Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes to 
account for spares that might also be installed on those airplanes, as 
specified in paragraph (v) (``New Parts Installation Prohibition'') in 
this final rule. We have not revised the final rule further regarding 
this issue.

Explanation of Change Made to This AD

    We have added paragraph (x)(3) in this final rule to specify that 
an AMOC that provides an acceptable level of safety may be used for any 
repair required by this AD if that repair is approved by the Boeing 
Commercial Airplanes Organizational Designation Authorization (ODA) 
that has been authorized by the Manager of the Seattle Aircraft 
Certification Office to make those findings.

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 and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 58330, September 20, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 58330, September 20, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 1,096 airplanes of U.S. registry. 
We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
            Action                    Labor cost             Parts cost                Cost per product
----------------------------------------------------------------------------------------------------------------
Retained actions..............  7 work-hours x $85     $0...................  $595 per inspection cycle.
                                 per hour = $595 per
                                 inspection cycle.
Mechanism replacement (one      32 work-hours x $85    $58,579\1\ $1,140      $62,439 per airplane.
 option for terminating          per hour = $2,720.     (installation kit).
 action).
Mechanism modification and      52 work-hours x $85    $5,858 (for the        $13,563 per airplane.
 replacement (one option for     per hour = $4,420.     modification) $1,140
 terminating action).                                   (installation kit)
                                                        $2,145 (tooling\2\).
----------------------------------------------------------------------------------------------------------------
\1\ This is the estimated cost for both a left and right mechanism. Boeing is planning a seed/exchange program
  so operators are not forced to purchase a new mechanism.
\2\ Per the Boeing service information, tooling is available from Boeing for $90 per day.

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),

[[Page 20232]]

    (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) 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010), and 
adding the following new AD:

2013-06-05 The Boeing Company: Amendment 39-17402; Docket No. FAA-
2012-0994; Directorate Identifier 2012-NM-119-AD.

(a) Effective Date

    This AD is effective May 9, 2013.

(b) Affected ADs

    This AD supersedes AD 2010-17-19, Amendment 39-16413 (75 FR 
52242, August 25, 2010).

(c) Applicability

    This AD applies to all The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any 
category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

    This AD was prompted by reports of failure of the aft attach 
lugs on the elevator tab control mechanisms, which resulted in 
severe elevator vibration. This AD also results from reports of gaps 
in elevator tab control mechanisms and analysis that additional 
elevator tab control mechanisms might have bearings that will come 
loose. We are issuing this AD to prevent discrepancies in the aft 
attach lugs of the elevator tab control mechanism, which could 
result in severe elevator and tab vibration. Consequent structural 
failure of the elevator or horizontal stabilizer could result in 
loss of structural integrity and aircraft control.

(f) Compliance

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

(g) Retained Repetitive Inspections for Group 1 Airplanes

    This paragraph restates the requirements of paragraph (g) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For 
Group 1 airplanes, as identified in Boeing Alert Service Bulletin 
737-27A1297, dated April 16, 2010: Except as required by paragraph 
(h) of this AD, within 12 days after April 29, 2010 (the effective 
date of AD 2010-09-05, Amendment 39-16270 (75 FR 21499, April 26, 
2010)), do a detailed inspection for discrepancies of the inboard 
and outboard aft attach lugs of the left and right elevator tab 
control mechanisms, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-27A1297, dated 
April 16, 2010. Repeat the inspection thereafter at intervals not to 
exceed 300 flight hours. Doing the replacement specified in 
paragraph (l) of this AD before September 9, 2010 (the effective 
date of AD 2010-17-19), terminates the requirements of this 
paragraph. Doing the inspection required by paragraph (n) of this AD 
terminates the requirements of this paragraph.

(h) Retained Extended Twin Operations (ETOPS) Flight Provisions

    This paragraph restates the requirements of paragraph (h) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For 
Group 1 airplanes as identified in Boeing Alert Service Bulletin 
737-27A1297, dated April 16, 2010: Beginning 7 days after April 29, 
2010 (the effective date of AD 2010-09-05, Amendment 39-21499 (75 FR 
21499, April 26, 2010)), no person may operate an airplane on an 
ETOPS flight unless the initial inspection required by paragraph (g) 
of this AD has been accomplished. Doing the inspection required by 
paragraph (n) of this AD terminates the requirements of this 
paragraph.

(i) Retained One-Time Inspection for Group 2, Configuration 1, 
Airplanes

    This paragraph restates the requirements of paragraph (i) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For 
Group 2, Configuration 1, airplanes as identified in Boeing Alert 
Service Bulletin 737-27A1297, dated April 16, 2010: Within 30 days 
after April 29, 2010 (the effective date of AD 2010-09-05, Amendment 
39-16270 (75 FR 21499, April 26, 2010)), do a one-time detailed 
inspection for discrepancies of the inboard and outboard aft attach 
lugs of the left and right elevator tab control mechanisms, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-27A1297, dated April 16, 2010. Doing the 
inspection required by paragraph (n) of this AD terminates the 
requirements of this paragraph.

(j) Corrective Actions for Paragraphs (g), (i), and (k) of This AD

    This paragraph restates the requirements of paragraph (j) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). If, 
during any inspection required by paragraph (g), (i), or (k) of this 
AD, any discrepancy is found, before further flight, replace the 
elevator tab control mechanism by doing the actions specified in 
paragraphs (j)(1) and (j)(2) of this AD.
    (1) Do a detailed inspection for discrepancies of the 
replacement elevator tab control mechanism; and, if no discrepancy 
is found, install the replacement elevator tab control mechanism; in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-27A1297, dated April 16, 2010. If any 
discrepancy is found, then that elevator tab control mechanism 
cannot be installed and the actions specified in this paragraph must 
be done before further flight on another replacement elevator tab 
control mechanism.
    (2) Re-inspect the installed elevator tab control mechanism 
using the inspection procedure specified in paragraph (i) of this 
AD.

(k) Retained Repetitive Inspections for Certain Group 2, Configuration 
1, Airplanes

    This paragraph restates the requirements of paragraph (k) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For 
Group 2, Configuration 1, airplanes as identified in Boeing Alert 
Service Bulletin 737-27A1297, dated April 16, 2010, on which the 
elevator tab control mechanism is replaced with a mechanism other 
than a new, Boeing-built mechanism: Within 300 flight hours after 
doing the replacement, do a detailed inspection for discrepancies of 
the inboard and outboard aft attach lugs of the left and right 
elevator tab control mechanisms, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
27A1297, dated April 16, 2010. Repeat the inspection thereafter at 
intervals not to exceed 300 flight hours. Doing the replacement 
specified in paragraph (l) of this AD before September 9, 2010 (the 
effective date of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, 
August 25, 2010)), is terminating action for this paragraph. Doing 
the inspection required by paragraph (n) of this AD terminates the 
requirements of this paragraph.

(l) Terminating Action Credit for Paragraphs (g), (i), and (k) of This 
AD

    This paragraph restates the requirements of paragraph (l) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). 
Replacing an elevator tab control mechanism with a new, Boeing-built 
mechanism before September 9, 2010 (the effective date of AD 2010-
17-19), as specified in paragraphs (l)(1) and (l)(2) of this AD, 
terminates the inspections required by paragraphs (g), (i), and (k) 
of this AD. Replacement of the elevator tab control mechanism on or 
after September 9, 2010 (the effective date of AD 2010-17-19), does 
not terminate the inspections required by paragraphs (g), (i), and 
(k) of this AD.

    Note 1 to paragraph (l) of this AD:  Additional guidance can be 
found in paragraphs 3.B.7.b.(1)(a)(1) and 3.B.7.b.(1)(a)(2) of the 
Accomplishment Instructions of Boeing Alert Service Bulletin

[[Page 20233]]

737-27A1297, dated April 16, 2010, for establishing whether the 
mechanism is Boeing built.

    (1) Do a detailed inspection for discrepancies of the new, 
Boeing-built replacement elevator tab control mechanism; and, if no 
discrepancy is found, install the replacement elevator tab control 
mechanism; in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010. If 
any discrepancy is found, then that elevator tab control mechanism 
cannot be installed and the actions specified in this paragraph must 
be done on another new, Boeing-built replacement elevator tab 
control mechanism.
    (2) Re-inspect the installed elevator tab control mechanism 
using the inspection procedure specified in paragraph (i) of this 
AD.

(m) Retained Reporting for Paragraphs (g), (i), and (k) of This AD

    This paragraph restates the requirements of paragraph (m) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For 
airplanes identified in Boeing Alert Service Bulletin 737-27A1297, 
dated April 16, 2010: At the applicable time specified in paragraph 
(m)(1) or (m)(2) of this AD, submit a report of any findings 
(positive and negative) of the first inspection required by 
paragraphs (g), (i), and (k) of this AD, and any positive findings 
from the repetitive inspections required by paragraphs (g) and (k) 
of this AD, to Boeing Commercial Airplanes Group, Attention: 
Manager, Airline Support, email: rse.boecom@boeing.com. The report 
must include the inspection results including a description of any 
discrepancies found, the airplane line number, and the total number 
of flight cycles and flight hours accumulated on the airplane.
    (1) If the inspection was done on or after April 29, 2010 (the 
effective date of AD 2010-09-05, Amendment 39-16270 (75 FR 21499, 
April 26, 2010)): Submit the report within 10 days after the 
inspection.
    (2) If the inspection was done before April 29, 2010 (the 
effective date of AD 2010-09-05, Amendment 39-16270 (75 FR 21499, 
April 26, 2010)): Submit the report within 10 days after April 29, 
2010 (the effective date of AD 2010-09-05).

(n) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (n) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For 
airplanes having line numbers 1 through 3909 inclusive: At the 
applicable time specified in paragraph (n)(1), (n)(2), or (n)(3) of 
this AD, do a detailed inspection for discrepancies of the inboard 
and outboard aft attach lugs of the left and right elevator tab 
control mechanisms, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-27A1297, Revision 
1, dated August 2, 2010. For Groups 1 and 2 airplanes identified in 
Boeing Alert Service Bulletin 737-27A1297, Revision 1, dated August 
2, 2010, repeat the inspection thereafter at intervals not to exceed 
300 flight hours, except as provided by paragraph (t)(2) of this AD. 
For Group 3 airplanes identified in Boeing Alert Service Bulletin 
737-27A1297, Revision 1, dated August 2, 2010, repeat the inspection 
thereafter at intervals not to exceed 1,800 flight hours, except as 
required by paragraphs (p) and (t)(2) of this AD. Doing the 
inspection specified in this paragraph terminates the requirements 
of paragraphs (g), (h), (i), and (k) of this AD.
    (1) For Group 1 airplanes identified in Boeing Alert Service 
Bulletin 737-27A1297, Revision 1, dated August 2, 2010: Within 300 
flight hours after doing an inspection in accordance with Boeing 
Alert Service Bulletin 737-27A1297, dated April 16, 2010, or within 
30 days after September 9, 2010 (the effective date of AD 2010-17-
19, Amendment 39-16413 (75 FR 52242, August 25, 2010)), whichever 
occurs later.
    (2) For Group 2 airplanes identified in Boeing Alert Service 
Bulletin 737-27A1297, Revision 1, dated August 2, 2010: At the later 
of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of 
this AD.
    (i) Before the accumulation of 2,000 total flight cycles or 
4,000 total flight hours, whichever occurs first.
    (ii) Within 14 days after September 9, 2010 (the effective date 
of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 
2010)).
    (3) For Group 3 airplanes identified in Boeing Alert Service 
Bulletin 737-27A1297, Revision 1, dated August 2, 2010: Within 180 
days or 1,800 flight hours after September 9, 2010 (the effective 
date of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 
2010)), whichever occurs first.

(o) Retained Corrective Actions for Paragraphs (n) and (p) of This AD

    This paragraph restates the requirements of paragraph (o) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). If, 
during any inspection required by paragraph (n) or (p) of this AD, 
any discrepancy is found, before further flight, replace the 
elevator tab control mechanism by doing the actions specified in 
paragraphs (o)(1) and (o)(2) of this AD.
    (1) Do a detailed inspection for discrepancies of the 
replacement elevator tab control mechanism; and, if no discrepancy 
is found, install the replacement elevator tab control mechanism; in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-27A1297, Revision 1, dated August 2, 2010. If 
any discrepancy is found, then that elevator tab control mechanism 
cannot be installed and the actions specified in this paragraph must 
be done before further flight on another replacement elevator tab 
control mechanism.
    (2) Re-inspect the installed elevator tab control mechanism 
using the inspection procedure specified in paragraph (n) of this 
AD.

(p) Retained Reduced Repetitive Inspection Interval for Group 3 
Airplanes

    This paragraph restates the requirements of paragraph (p) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For 
Group 3 airplanes as identified in Boeing Alert Service Bulletin 
737-27A1297, Revision 1, dated August 2, 2010, on which the elevator 
tab control mechanism is replaced during the actions required by 
paragraph (o) of this AD: Within 300 flight hours after doing the 
replacement, do a detailed inspection for discrepancies of the 
inboard and outboard aft attach lugs of the replaced elevator tab 
control mechanism, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-27A1297, Revision 
1, dated August 2, 2010. Repeat the inspection of the replaced 
elevator tab control mechanism thereafter at intervals not to exceed 
300 flight hours, except as provided by paragraph (t)(2) of this AD.

(q) Retained Credit for Previous Action

    This paragraph restates the provisions specified in paragraph 
(q) of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 
2010). For Group 1 airplanes as identified in Boeing Alert Service 
Bulletin 737-27A1297, Revision 1, dated August 2, 2010: Inspections 
done in accordance with Boeing Alert Service Bulletin 737-27A1297, 
dated April 16, 2010, are acceptable for compliance with only the 
initial inspection required by paragraph (n) of this AD.

(r) Retained Reporting for Paragraphs (n) and (p) of This AD

    This paragraph restates the requirements of paragraph (r) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For 
airplanes having line numbers 1 through 3909 inclusive: At the 
applicable time specified in paragraph (r)(1) or (r)(2) of this AD, 
submit a report of any findings (positive and negative) of the first 
inspection required by paragraphs (n) and (p) of this AD, except for 
airplanes on which a report required by paragraph (m) of this AD has 
been submitted, only submit positive findings; and submit a report 
of any positive findings from the repetitive inspections required by 
paragraphs (n) and (p) of this AD; to Boeing Commercial Airplanes 
Group, Attention: Manager, Airline Support, email: 
rse.boecom@boeing.com. The report must include the inspection 
results including a description of any discrepancies found, the 
airplane line number, and the total number of flight cycles and 
flight hours accumulated on the airplane.
    (1) If the inspection was done on or after September 9, 2010 
(the effective date of AD 2010-17-19, Amendment 39-16413 (75 FR 
52242, August 25, 2010)): Submit the report within 10 days after the 
inspection.
    (2) If the inspection was done before September 9, 2010 (the 
effective date of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, 
August 25, 2010)): Submit the report within 10 days after September 
9, 2010 (the effective date of AD 2010-17-19).

(s) Retained Provision Regarding Not Returning Parts

    This paragraph restates the provision specified in paragraph (s) 
of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). 
Although Boeing Alert Service Bulletin 737-27A1297, dated April 16, 
2010; and Boeing Alert Service Bulletin 737-27A1297, Revision 1, 
dated August 2, 2010; specify to return the affected elevator tab 
control mechanism to the manufacturer, this AD does not require the 
return of the part to the manufacturer.

[[Page 20234]]

(t) Retained Parts Installation Limitations

    This paragraph restates the requirements of paragraph (t) of AD 
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010), with 
revised limitations. As of September 9, 2010 (the effective date of 
AD 2010-17-19), and until the replacement required by paragraph (u) 
of this AD for airplanes with line numbers 1 through 3909 inclusive, 
or until the effective date of this new AD for airplanes with line 
numbers 3910 and subsequent, as applicable: Comply with the 
conditions specified in paragraphs (t)(1) and (t)(2) of this AD.
    (1) No person may install an elevator tab control mechanism, 
part number (P/N) 251A2430-(), on any airplane, unless the mechanism 
has been inspected before and after installation using the 
inspection procedures specified in paragraphs (o)(1) and (o)(2) of 
this AD, and no discrepancies have been found.
    (2) An elevator tab control mechanism, P/N 251A2430-(), may be 
installed, provided that the inspection specified in paragraph (n) 
of this AD is done within 300 flight hours after doing the 
installation, and that the inspection specified in paragraph (n) of 
this AD is repeated thereafter at intervals not to exceed 300 flight 
hours.

(u) New Replacement

    For airplanes having line numbers 1 through 3909 inclusive: 
Within 60 months after the effective date of this AD, replace the 
left and right elevator tab control mechanisms with elevator tab 
control mechanisms that have new machined aft attach lugs, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-27-1300, dated April 16, 2012. This replacement 
terminates the requirements of paragraphs (g) through (t) of this 
AD. Although Boeing Service Bulletin 737-27-1300, dated April 16, 
2012, specifies submitting a report, there is no requirement to 
report completion of the replacement required by paragraph (u) of 
this AD.

(v) New Parts Installation Prohibition

    As of the effective date of this AD, no person may install, on 
any airplane identified in paragraph (v)(1) or (v)(2) of this AD, an 
elevator tab control mechanism having P/N 251A2430-13, -14, -15, -
16, -17, -18, -101, -102, -103, -104, -105, or -106.
    (1) Airplanes on which the replacement in paragraph (u) of this 
AD has been accomplished.
    (2) Airplanes with line numbers 3910 and subsequent.

(w) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(x) 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 
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 for AD 2010-17-19, Amendment 39-16413 (75 FR 
52242, August 25, 2010), are approved as AMOCs for the corresponding 
provisions of this AD. The expiration of the AMOCS to AD 2010-17-19, 
as specified in the service information identified in paragraphs 
(x)(4)(i) and (x)(4)(ii) of this AD, is extended to remain valid 
until accomplishment of the requirements of paragraph (u) of this 
AD.
    (i) Boeing Alert Service Bulletin 737-27A1299, dated July 1, 
2011 (which is not incorporated by reference in this AD).
    (ii) Boeing Alert Service Bulletin 737-27A1299, Revision 1, 
dated April 16, 2012 (which is not incorporated by reference in this 
AD).

(y) Related Information

    For more information about this AD, contact Kelly McGuckin, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, Washington 98057-3356; phone: 425-917-6490; fax: 425-917-
6590; email: kelly.mcguckin@faa.gov.

(z) 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 
May 9, 2013.
    (i) Boeing Service Bulletin 737-27-1300, dated April 16, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
September 9, 2010 (75 FR 52242, August 25, 2010).
    (i) Boeing Alert Service Bulletin 737-27A1297, Revision 1, dated 
August 2, 2010.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
April 29, 2010 (75 FR 21499, April 26, 2010).
    (i) Boeing Alert Service Bulletin 737-27A1297, dated April 16, 
2010.
    (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, You may review 
copies of the 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.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on March 20, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-07209 Filed 4-3-13; 8:45 am]
BILLING CODE 4910-13-P