Airworthiness Directives; The Boeing Company Airplanes, 10855-10859 [2017-03112]

Download as PDF 10855 Rules and Regulations Federal Register Vol. 82, No. 31 Thursday, February 16, 2017 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF AGRICULTURE Animal and Plant Health Inspection Service 7 CFR Part 331 9 CFR Part 121 [Docket No. APHIS–2014–0095] RIN 0579–AE08 Agricultural Bioterrorism Protection Act of 2002; Biennial Review and Republication of the Select Agent and Toxin List; Amendments to the Select Agent and Toxin Regulations; Delay of Effective Date Authority: 7 U.S.C. 8401; 7 CFR 2.22, 2.80, and 371.3. Animal and Plant Health Inspection Service, USDA. ACTION: Final rule; delay of effective date. AGENCY: On January 19, 2017, we published a final rule amending the select agent and toxin regulations in several ways, including the addition of provisions to address the inactivation of select agents, provisions addressing biocontainment and biosafety, and clarification of regulatory language concerning security, training, incident response, and records. In this document, we are delaying the effective date of that final rule. DATES: The effective date of the final rule published on January 19, 2017 (82 FR 6197), is delayed until March 21, 2017. FOR FURTHER INFORMATION CONTACT: Mr. Stephen O’Neill, Chief, Regulatory Analysis and Development, PPD, APHIS, 4700 River Road Unit 118, Riverdale, MD 20737–1234; (301) 851– 3175. SUPPLEMENTARY INFORMATION: On January 19, 2017, the Animal and Plant Health Inspection Service (APHIS) published a final rule (82 FR 6197– 6210) to amend the select agent and jstallworth on DSK7TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 11:26 Feb 15, 2017 Jkt 241001 toxin regulations in several ways, including the addition of provisions to address the inactivation of select agents, provisions addressing biocontainment and biosafety, and clarification of regulatory language concerning security, training, incident response, and records. In this document, we are delaying the effective date until March 21, 2017, in accordance with guidance issued January 20, 2017, intended to provide the new Administration an adequate opportunity to review new and pending regulations. To the extent that 5 U.S.C. 553(b)(A) applies to this action, it is exempt from notice and comment for good cause and the reasons cited above. APHIS finds that notice and solicitation of comment regarding the brief extension of the effective date for the final regulation are impracticable, unnecessary, or contrary to the public interest pursuant to 5 U.S.C. 553(b)(B). APHIS also believes that affected entities need to be informed as soon as possible of the extension and its length in order to plan and adjust their implementation process accordingly. Done in Washington, DC, this 10th day of February 2017. Michael C. Gregoire, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. 2017–03125 Filed 2–15–17; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6430; Directorate Identifier 2015–NM–176–AD; Amendment 39–18781; AD 2017–02–02] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2005–13– 30, for all The Boeing Company Model 737–100, –200, and –200C series SUMMARY: PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 airplanes. AD 2005–13–30 required repetitive inspections to detect discrepancies of certain fuselage skin panels located just aft of the wheel well, and repair if necessary. This new AD adds new fuselage skin inspections for cracking, inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin is subject to widespread fatigue damage (WFD), and reports of cracks at the chem-milled steps in the fuselage skin. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 23, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 23, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6430. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6430; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 E:\FR\FM\16FER1.SGM 16FER1 10856 Federal Register / Vol. 82, No. 31 / Thursday, February 16, 2017 / Rules and Regulations New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5264; fax: 562–627– 5210; email: jennifer.tsakoumakis@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2005–13–30, Amendment 39–14167 (70 FR 36829, June 27, 2005) (‘‘AD 2005–13–30’’). AD 2005–13–30 applied to all Boeing Model 737–100, –200, and –200C series airplanes. The NPRM published in the Federal Register on May 11, 2016 (81 FR 29202) (‘‘the NPRM’’). The NPRM was prompted by an evaluation by the DAH indicating that the fuselage skin is subject to WFD, and reports of cracks at the chem-milled steps in the fuselage skin. The NPRM proposed to require fuselage skin inspections for cracking, inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels, which could cause rapid decompression of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. jstallworth on DSK7TPTVN1PROD with RULES Request To Revise Compliance Time Boeing requested that we revise paragraph (i)(4) of the proposed AD to specify that the exception to the service information is for airplanes on which an operator has a record that a skin panel was replaced with a production skin panel ‘‘before’’ 59,000 total flight cycles, instead of ‘‘at or before’’ 59,000 total flight cycles, because of limit of validity (LOV) issues. Boeing also requested that we revise the condition statement regarding the time the skin panel was replaced in paragraph (m) of the proposed AD from ‘‘after’’ 59,000 total flight cycles to ‘‘at or after’’ 59,000 total flight cycles; and in paragraphs (m)(1) and (m)(2) of the proposed AD from ‘‘at or before’’ to ‘‘before.’’ Boeing explained that if a skin panel is replaced at or after VerDate Sep<11>2014 11:26 Feb 15, 2017 Jkt 241001 59,000 total flight cycles, no additional safety inspections would be needed due to the LOV. Boeing stated that upon reaching the LOV the airplane will be retired domestically and no longer supported by Boeing. Boeing also requested that we revise the compliance time for the skin panel replacement in paragraph (i)(4) of the proposed AD to a time approved by the FAA through the alternative method of compliance (AMOC) process instead of the time specified in the service information. Boeing stated that since a Boeing Commercial Airplanes Organization Designation Authorization (ODA) representative cannot approve extensions to the compliance times required by an AD, the AMOC approval would have to come from the FAA. We partially agree with Boeing’s requests. We agree to change the identification of the affected airplanes as requested by Boeing in paragraphs (i)(4), (m), (m)(1), and (m)(2) of this AD. These changes will address the LOV issues expressed by Boeing. We do not agree with changing the compliance time from the applicable time for the next inspection as specified in the service information. We have determined that this is an appropriate compliance time and provides an acceptable level of safety. It also provides operators with sufficient information for maintenance planning purposes. Request To Revise Instructions for Skin Panel Replacement Boeing requested that we revise paragraph (m) of the proposed AD, which specifies replacing the applicable skin panels and doing all applicable related investigative and corrective actions, with replacing the skin panels in accordance with Part 8 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737– 53–1065, Revision 3, dated June 30, 2015 (‘‘SASB 737–53–1065, R3’’). We agree with replacing the skin panels in accordance with Part 8 of the Accomplishment Instructions of SASB 737–53–1065, R3. Part 8 of the Accomplishment Instructions of SASB 737–53–1065, R3 adequately specifies the required actions. We have revised paragraph (m) of this AD accordingly. Request To Add Service Information Paragraph Part References Boeing requested that we revise paragraphs (j)(1)(ii), (j)(2)(ii), and (k) of the proposed AD by adding the service information paragraph part references. Boeing stated that paragraph (h) of the proposed AD includes the part reference. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 We do not agree with Boeing’s requests. Paragraph (h) of this AD, in part, specifies the specific service information paragraph reference for doing repairs that are terminating action for the repetitive inspections at the repaired locations only. We determined that this reference is needed for clarity. We do not agree that the other references are needed for clarity. We have not changed this AD in this regard. Request To Clarify Post-modification Airworthiness Limitation Inspections Boeing requested that we revise paragraph (l) of the proposed AD to specify that table 6 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737–53–1065, R3 is for post-modification airworthiness limitation inspections at the modified locations. Boeing explained that since airworthiness limitation inspections are required by maintenance and operational rules, it is unnecessary to mandate them in this AD. We agree with Boeing’s request. We have revised paragraph (l) of this AD accordingly. Request To Revise the NPRM To Address Certain Repaired Areas For airplanes subject to the requirements of paragraph (h) of the proposed AD, Boeing requested that we add a paragraph that specifies that inspections are not required in areas that are spanned by an FAA-approved repair that has met certain conditions. Boeing submitted specific conditions. Boeing stated that its request is to address elimination of inspections for repairs that have been accomplished for damage other than chem-mill cracking. We do not agree with Boeing’s request. Paragraph (h) of this AD specifies to do the applicable inspections and related investigative and corrective actions specified in the Accomplishment Instructions of SASB 737–53–1065, R3. This service information already contains the criteria Boeing proposed. Therefore, the criteria do not need to be repeated in this AD. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and E:\FR\FM\16FER1.SGM 16FER1 Federal Register / Vol. 82, No. 31 / Thursday, February 16, 2017 / Rules and Regulations • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed SASB 737–53–1065, R3. The service information describes procedures for inspection and repair of the fuselage skin panels between body station (BS) 727 and BS 1016, and between stringers S–14 and S–25; and also describes procedures for skin panel replacement. This service information is 10857 reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 9 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection [actions retained from AD 2005–13–30]. Inspection [new action] ............................. Up to 88 work-hours × $85 per hour = $7,480 per inspection cycle. Up to 1,914 work-hours × $85 per hour = $162,690 per inspection cycle. $0 Skin panel replacement [new action] ........ 688 work-hours × $85 per hour = $58,480 96,000 We estimate the following costs to do any necessary repairs that will be Parts cost 0 required based on the results of the inspection. We have no way of Cost on U.S. operators Cost per product Up to $7,480 per inspection cycle. Up to $162,690 per inspection cycle. $154,480 ................. Up to $67,320 per inspection cycle. Up to $1,464,210 per inspection cycle. $1,390,320. determining the number of aircraft that might need these repairs: ON-CONDITION COSTS Action Labor cost Time-limited repair ............................................................ Permanent repair .............................................................. Permanent repair inspection ............................................. 24 work-hours × $85 per hour = $2,040 .......................... 43 work-hours × $85 per hour = $3,655 .......................... 7 work-hours × $85 per hour = $595 ............................... 1 We (1) (1) (1) Cost per product 1 $2,040 1 3,655 1 595 have received no definitive data that will enable us to provide parts cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking jstallworth on DSK7TPTVN1PROD with RULES Parts cost 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 VerDate Sep<11>2014 11:26 Feb 15, 2017 Jkt 241001 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. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 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) 2005–13–30, Amendment 39–14167 (70 FR 36829, June 27, 2005), and adding the following new AD: ■ 2017–02–02 The Boeing Company: Amendment 39–18781; Docket No. FAA–2016–6430; Directorate Identifier 2015–NM–176–AD. (a) Effective Date This AD is effective March 23, 2017. (b) Affected ADs This AD replaces AD 2005–13–30, Amendment 39–14167 (70 FR 36829, June 27, 2005) (‘‘AD 2005–13–30’’). E:\FR\FM\16FER1.SGM 16FER1 10858 Federal Register / Vol. 82, No. 31 / Thursday, February 16, 2017 / Rules and Regulations (c) Applicability This AD applies to all The Boeing Company Model 737–100, –200, and –200C series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder indicating that the fuselage skin is subject to widespread fatigue damage, and reports of cracks at the chem-milled steps in the fuselage skin. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels, which could cause rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions for Group 1 Airplanes For Group 1 airplanes identified in Boeing Special Attention Service Bulletin 737–53– 1065, Revision 3, dated June 30, 2015 (‘‘SASB 737–53–1065, R3’’): Within 120 days after the effective date of this AD, accomplish actions to correct the unsafe condition (e.g., inspections, repairs, modifications, and related investigative and corrective actions) using a method approved in accordance with the procedures specified in paragraph (o) of this AD. jstallworth on DSK7TPTVN1PROD with RULES (h) Inspections, Related Investigative and Corrective Actions Except for Group 1 airplanes identified in SASB 737–53–1065, R3: At the applicable times specified in tables 1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737–53–1065, R3, except as required by paragraphs (i)(1) and (i)(2) of this AD, do the applicable inspections to detect cracks in the fuselage skin panels; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 737–53–1065, R3, except as required by paragraphs (i)(3) and (i)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified in SASB 737–53–1065, R3. Accomplishment of a repair in accordance with ‘‘Part 3: Repair’’ of the Accomplishment Instructions of SASB 737– 53–1065, R3, except as required by paragraph (i)(3) of this AD, is terminating action for the repetitive inspections required by this paragraph at the repaired locations only. (i) Exceptions to SASB 737–53–1065, R3 (1) Where SASB 737–53–1065, R3 specifies compliance times ‘‘after the Revision 3 date of this service bulletin,’’ this AD requires compliance within the specified compliance times after the effective date of this AD. (2) The Condition column of paragraph 1.E., ‘‘Compliance,’’ of SASB 737–53–1065, R3 refers to airplanes in certain configurations as of the ‘‘issue date of Revision 3 of this service bulletin.’’ However, this AD applies to airplanes in the specified VerDate Sep<11>2014 11:26 Feb 15, 2017 Jkt 241001 configurations ‘‘as of the effective date of this AD.’’ (3) Where SASB 737–53–1065, R3 specifies contacting Boeing for repair instructions or work instructions, before further flight, repair or perform the work instructions using a method approved in accordance with the procedures specified in paragraph (o) of this AD, except as required by paragraph (i)(4) of this AD. (4) For airplanes on which an operator has a record that a skin panel was replaced with a production skin panel before 59,000 total flight cycles: At the applicable time for the next inspection as specified in tables 1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737–53–1065, R3, except as provided by paragraphs (i)(1) and (i)(2) of this AD, perform inspections and applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (o) of this AD. the Accomplishment Instructions of SASB 737–53–1065, R3, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified in SASB 737–53–1065, R3. (ii) Make the time limited repair permanent; and do all applicable related investigative and corrective actions; in accordance the Accomplishment Instructions of SASB 737–53–1065, R3, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Accomplishing the permanent repair required by this paragraph terminates the inspections required by paragraph (j)(2)(i) of this AD for the permanently repaired area only. (j) Actions for Airplanes With a Time Limited Repair Installed Except for Group 1 airplanes identified in SASB 737–53–1065, R3: Do the applicable actions required by paragraphs (j)(1) and (j)(2) of this AD. (1) For airplanes with a time limited repair installed as specified in Boeing Special Attention Service Bulletin 737–53–1065, Revision 2, dated April 19, 2001: At the applicable times specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737– 53–1065, R3, except as provided by paragraphs (i)(1) and (i)(2) of this AD, do the actions specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD. (i) Do the applicable inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 737–53–1065, R3, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified in SASB 737–53–1065, R3. (ii) Make the time limited repair permanent; and do all applicable related investigative and corrective actions; in accordance the Accomplishment Instructions of SASB 737–53–1065, R3, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Accomplishing the permanent repair required by this paragraph terminates the inspections required by paragraph (j)(1)(i) of this AD for the permanently repaired area only. (2) For airplanes with a time limited repair installed as specified in SASB 737–53–1065, R3: At the applicable times specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737–53–1065, R3, do the actions specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. (i) Do the applicable inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers; and do all applicable related investigative and corrective actions; in accordance with (l) Post-Modification Inspections Table 6 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737–53–1065, R3 specifies postmodification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an alternative method of compliance. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 (k) Modification of Certain Permanent Repairs Except for Group 1 airplanes identified in SASB 737–53–1065, R3: For airplanes with an existing time limited repair that was made permanent as specified in Boeing Special Attention Service Bulletin 737–53–1065, Revision 2, dated April 19, 2001, at the applicable times specified in table 5 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737– 53–1065, R3, except as required by paragraph (i)(1) of this AD, modify the existing permanent repair; and do all applicable related investigative and corrective actions; in accordance the Accomplishment Instructions of SASB 737–53–1065, R3, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. (m) Skin Panel Replacement Except for Group 1 airplanes identified in SASB 737–53–1065, R3: At the later of the times specified in paragraphs (m)(1) and (m)(2) of this AD, replace the applicable skin panels, in accordance with the Part 8 of the Accomplishment Instructions of SASB 737– 53–1065, R3. Doing the skin panel replacement required by this paragraph terminates the inspection requirements of paragraph (h) of this AD for that skin panel only, provided the skin panel was replaced with a production skin panel at or after 59,000 total flight cycles. (1) Before 60,000 total flight cycles, but not before 59,000 total flight cycles. (2) Within 6,000 flight cycles after the effective date of this AD, but not before 59,000 total flight cycles. E:\FR\FM\16FER1.SGM 16FER1 Federal Register / Vol. 82, No. 31 / Thursday, February 16, 2017 / Rules and Regulations (n) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 737–53–1065, Revision 2, dated April 19, 2001, which was incorporated by reference in AD 2005–13–30. (o) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (p) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously for AD 2005–13–30, are approved as AMOCs for the corresponding provisions of paragraph (h) of this AD. jstallworth on DSK7TPTVN1PROD with RULES (p) Related Information For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5264; fax: 562–627–5210; email: jennifer.tsakoumakis@faa.gov. (q) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Special Attention Service Bulletin 737–53–1065, Revision 3, dated June 30, 2015. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797– 1717; Internet https:// www.myboeingfleet.com. VerDate Sep<11>2014 11:26 Feb 15, 2017 Jkt 241001 (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 11, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03112 Filed 2–15–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–7003; Directorate Identifier 2016–CE–015–AD; Amendment 39–18766; AD 2016–26–08] RIN 2120–AA64 Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; correction. AGENCY: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to all PILATUS AIRCRAFT LTD. Models PC–12, PC–12/45, PC–12/ 47, and PC–12/47E airplanes. The second reference to the main landing gear (MLG) in paragraph (f)(6) is incorrect. This document corrects that error. In all other respects, the original document remains the same; however we are publishing the entire rule in the Federal Register. DATES: This final rule is effective February 16, 2017. The effective date of AD 2016–26–08 remains February 9, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 9, 2017 (82 FR 1172, January 5, 2017). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 7003; 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 SUMMARY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 10859 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: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: Airworthiness Directive 2016–26–08, Amendment 39–18766 (82 FR 1172, January 5, 2017), requires incorporating new revisions into the Limitations section, Chapter 4, of the FAA-approved maintenance program (e.g., maintenance manual). The limitations were revised to include repetitive inspections of the main landing gear (MLG) attachment bolts. As published, in paragraph (f)(6) there is a typographical error to the second reference of the MLG. The published reference is MLB and it is should be MLG. Although no other part of the preamble or regulatory information has been corrected, we are publishing the entire rule in the Federal Register. The effective date of this AD remains February 9, 2017. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Correction 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 [Corrected] 2. The FAA amends § 39.13 by removing 39–18005 (79 FR 67343, November 13, 2014) and adding the following new AD: ■ 2016–26–08 PILATUS AIRCRAFT LTD.: Amendment 39–18766; Docket No. FAA–2016–7003; Directorate Identifier 2016–CE–015–AD. E:\FR\FM\16FER1.SGM 16FER1

Agencies

[Federal Register Volume 82, Number 31 (Thursday, February 16, 2017)]
[Rules and Regulations]
[Pages 10855-10859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03112]


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

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6430; Directorate Identifier 2015-NM-176-AD; 
Amendment 39-18781; AD 2017-02-02]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2005-13-30, 
for all The Boeing Company Model 737-100, -200, and -200C series 
airplanes. AD 2005-13-30 required repetitive inspections to detect 
discrepancies of certain fuselage skin panels located just aft of the 
wheel well, and repair if necessary. This new AD adds new fuselage skin 
inspections for cracking, inspections to detect missing or loose 
fasteners and any disbonding or cracking of bonded doublers, permanent 
repairs of time-limited repairs, related investigative and corrective 
actions if necessary, and skin panel replacement. This AD was prompted 
by an evaluation by the design approval holder (DAH) indicating that 
the fuselage skin is subject to widespread fatigue damage (WFD), and 
reports of cracks at the chem-milled steps in the fuselage skin. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective March 23, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 23, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6430.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6430; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200

[[Page 10856]]

New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: 
jennifer.tsakoumakis@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2005-13-30, Amendment 39-14167 (70 FR 36829, 
June 27, 2005) (``AD 2005-13-30''). AD 2005-13-30 applied to all Boeing 
Model 737-100, -200, and -200C series airplanes. The NPRM published in 
the Federal Register on May 11, 2016 (81 FR 29202) (``the NPRM''). The 
NPRM was prompted by an evaluation by the DAH indicating that the 
fuselage skin is subject to WFD, and reports of cracks at the chem-
milled steps in the fuselage skin. The NPRM proposed to require 
fuselage skin inspections for cracking, inspections to detect missing 
or loose fasteners and any disbonding or cracking of bonded doublers, 
permanent repairs of time-limited repairs, related investigative and 
corrective actions if necessary, and skin panel replacement. We are 
issuing this AD to detect and correct fatigue cracking of the fuselage 
skin panels, which could cause rapid decompression of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Revise Compliance Time

    Boeing requested that we revise paragraph (i)(4) of the proposed AD 
to specify that the exception to the service information is for 
airplanes on which an operator has a record that a skin panel was 
replaced with a production skin panel ``before'' 59,000 total flight 
cycles, instead of ``at or before'' 59,000 total flight cycles, because 
of limit of validity (LOV) issues. Boeing also requested that we revise 
the condition statement regarding the time the skin panel was replaced 
in paragraph (m) of the proposed AD from ``after'' 59,000 total flight 
cycles to ``at or after'' 59,000 total flight cycles; and in paragraphs 
(m)(1) and (m)(2) of the proposed AD from ``at or before'' to 
``before.'' Boeing explained that if a skin panel is replaced at or 
after 59,000 total flight cycles, no additional safety inspections 
would be needed due to the LOV. Boeing stated that upon reaching the 
LOV the airplane will be retired domestically and no longer supported 
by Boeing.
    Boeing also requested that we revise the compliance time for the 
skin panel replacement in paragraph (i)(4) of the proposed AD to a time 
approved by the FAA through the alternative method of compliance (AMOC) 
process instead of the time specified in the service information. 
Boeing stated that since a Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) representative cannot approve 
extensions to the compliance times required by an AD, the AMOC approval 
would have to come from the FAA.
    We partially agree with Boeing's requests. We agree to change the 
identification of the affected airplanes as requested by Boeing in 
paragraphs (i)(4), (m), (m)(1), and (m)(2) of this AD. These changes 
will address the LOV issues expressed by Boeing. We do not agree with 
changing the compliance time from the applicable time for the next 
inspection as specified in the service information. We have determined 
that this is an appropriate compliance time and provides an acceptable 
level of safety. It also provides operators with sufficient information 
for maintenance planning purposes.

Request To Revise Instructions for Skin Panel Replacement

    Boeing requested that we revise paragraph (m) of the proposed AD, 
which specifies replacing the applicable skin panels and doing all 
applicable related investigative and corrective actions, with replacing 
the skin panels in accordance with Part 8 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 737-53-1065, 
Revision 3, dated June 30, 2015 (``SASB 737-53-1065, R3'').
    We agree with replacing the skin panels in accordance with Part 8 
of the Accomplishment Instructions of SASB 737-53-1065, R3. Part 8 of 
the Accomplishment Instructions of SASB 737-53-1065, R3 adequately 
specifies the required actions. We have revised paragraph (m) of this 
AD accordingly.

Request To Add Service Information Paragraph Part References

    Boeing requested that we revise paragraphs (j)(1)(ii), (j)(2)(ii), 
and (k) of the proposed AD by adding the service information paragraph 
part references. Boeing stated that paragraph (h) of the proposed AD 
includes the part reference.
    We do not agree with Boeing's requests. Paragraph (h) of this AD, 
in part, specifies the specific service information paragraph reference 
for doing repairs that are terminating action for the repetitive 
inspections at the repaired locations only. We determined that this 
reference is needed for clarity. We do not agree that the other 
references are needed for clarity. We have not changed this AD in this 
regard.

Request To Clarify Post-modification Airworthiness Limitation 
Inspections

    Boeing requested that we revise paragraph (l) of the proposed AD to 
specify that table 6 of paragraph 1.E., ``Compliance,'' of SASB 737-53-
1065, R3 is for post-modification airworthiness limitation inspections 
at the modified locations. Boeing explained that since airworthiness 
limitation inspections are required by maintenance and operational 
rules, it is unnecessary to mandate them in this AD.
    We agree with Boeing's request. We have revised paragraph (l) of 
this AD accordingly.

Request To Revise the NPRM To Address Certain Repaired Areas

    For airplanes subject to the requirements of paragraph (h) of the 
proposed AD, Boeing requested that we add a paragraph that specifies 
that inspections are not required in areas that are spanned by an FAA-
approved repair that has met certain conditions. Boeing submitted 
specific conditions. Boeing stated that its request is to address 
elimination of inspections for repairs that have been accomplished for 
damage other than chem-mill cracking.
    We do not agree with Boeing's request. Paragraph (h) of this AD 
specifies to do the applicable inspections and related investigative 
and corrective actions specified in the Accomplishment Instructions of 
SASB 737-53-1065, R3. This service information already contains the 
criteria Boeing proposed. Therefore, the criteria do not need to be 
repeated in this AD. We have not changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously, and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and

[[Page 10857]]

     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed SASB 737-53-1065, R3. The service information describes 
procedures for inspection and repair of the fuselage skin panels 
between body station (BS) 727 and BS 1016, and between stringers S-14 
and S-25; and also describes procedures for skin panel replacement. 
This service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 9 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                               Parts                             Cost on U.S.
              Action                      Labor cost            cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection [actions retained from  Up to 88 work-hours x            $0  Up to $7,480 per     Up to $67,320 per
 AD 2005-13-30].                    $85 per hour = $7,480                inspection cycle.    inspection cycle.
                                    per inspection cycle.
Inspection [new action]..........  Up to 1,914 work-hours x          0  Up to $162,690 per   Up to $1,464,210
                                    $85 per hour = $162,690              inspection cycle.    per inspection
                                    per inspection cycle.                                     cycle.
Skin panel replacement [new        688 work-hours x $85 per     96,000  $154,480...........  $1,390,320.
 action].                           hour = $58,480.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Parts       Cost per
                    Action                                    Labor cost                  cost        product
----------------------------------------------------------------------------------------------------------------
Time-limited repair...........................  24 work-hours x $85 per hour = $2,040      (\1\)      \1\ $2,040
Permanent repair..............................  43 work-hours x $85 per hour = $3,655      (\1\)       \1\ 3,655
Permanent repair inspection...................  7 work-hours x $85 per hour = $595...      (\1\)         \1\ 595
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that will enable us to provide parts cost estimates for the on-condition
  actions specified in this AD.

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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) 
2005-13-30, Amendment 39-14167 (70 FR 36829, June 27, 2005), and adding 
the following new AD:

2017-02-02 The Boeing Company: Amendment 39-18781; Docket No. FAA-
2016-6430; Directorate Identifier 2015-NM-176-AD.

(a) Effective Date

    This AD is effective March 23, 2017.

(b) Affected ADs

    This AD replaces AD 2005-13-30, Amendment 39-14167 (70 FR 36829, 
June 27, 2005) (``AD 2005-13-30'').

[[Page 10858]]

(c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, 
and -200C series airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder indicating that the fuselage skin is subject to widespread 
fatigue damage, and reports of cracks at the chem-milled steps in 
the fuselage skin. We are issuing this AD to detect and correct 
fatigue cracking of the fuselage skin panels, which could cause 
rapid decompression of the airplane.

(f) Compliance

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

(g) Actions for Group 1 Airplanes

    For Group 1 airplanes identified in Boeing Special Attention 
Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015 
(``SASB 737-53-1065, R3''): Within 120 days after the effective date 
of this AD, accomplish actions to correct the unsafe condition 
(e.g., inspections, repairs, modifications, and related 
investigative and corrective actions) using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.

(h) Inspections, Related Investigative and Corrective Actions

    Except for Group 1 airplanes identified in SASB 737-53-1065, R3: 
At the applicable times specified in tables 1 and 2 of paragraph 
1.E., ``Compliance,'' of SASB 737-53-1065, R3, except as required by 
paragraphs (i)(1) and (i)(2) of this AD, do the applicable 
inspections to detect cracks in the fuselage skin panels; and do all 
applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of SASB 737-53-1065, 
R3, except as required by paragraphs (i)(3) and (i)(4) of this AD. 
Do all applicable related investigative and corrective actions 
before further flight. Repeat the applicable inspections thereafter 
at the applicable intervals specified in SASB 737-53-1065, R3. 
Accomplishment of a repair in accordance with ``Part 3: Repair'' of 
the Accomplishment Instructions of SASB 737-53-1065, R3, except as 
required by paragraph (i)(3) of this AD, is terminating action for 
the repetitive inspections required by this paragraph at the 
repaired locations only.

(i) Exceptions to SASB 737-53-1065, R3

    (1) Where SASB 737-53-1065, R3 specifies compliance times 
``after the Revision 3 date of this service bulletin,'' this AD 
requires compliance within the specified compliance times after the 
effective date of this AD.
    (2) The Condition column of paragraph 1.E., ``Compliance,'' of 
SASB 737-53-1065, R3 refers to airplanes in certain configurations 
as of the ``issue date of Revision 3 of this service bulletin.'' 
However, this AD applies to airplanes in the specified 
configurations ``as of the effective date of this AD.''
    (3) Where SASB 737-53-1065, R3 specifies contacting Boeing for 
repair instructions or work instructions, before further flight, 
repair or perform the work instructions using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD, except as required by paragraph (i)(4) of this AD.
    (4) For airplanes on which an operator has a record that a skin 
panel was replaced with a production skin panel before 59,000 total 
flight cycles: At the applicable time for the next inspection as 
specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of 
SASB 737-53-1065, R3, except as provided by paragraphs (i)(1) and 
(i)(2) of this AD, perform inspections and applicable corrective 
actions using a method approved in accordance with the procedures 
specified in paragraph (o) of this AD.

(j) Actions for Airplanes With a Time Limited Repair Installed

    Except for Group 1 airplanes identified in SASB 737-53-1065, R3: 
Do the applicable actions required by paragraphs (j)(1) and (j)(2) 
of this AD.
    (1) For airplanes with a time limited repair installed as 
specified in Boeing Special Attention Service Bulletin 737-53-1065, 
Revision 2, dated April 19, 2001: At the applicable times specified 
in table 3 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1065, 
R3, except as provided by paragraphs (i)(1) and (i)(2) of this AD, 
do the actions specified in paragraphs (j)(1)(i) and (j)(1)(ii) of 
this AD.
    (i) Do the applicable inspections to detect missing or loose 
fasteners and any disbonding or cracking of bonded doublers; and do 
all applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of SASB 737-53-1065, 
R3, except as required by paragraph (i)(3) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight. Repeat the applicable inspections thereafter at the 
applicable intervals specified in SASB 737-53-1065, R3.
    (ii) Make the time limited repair permanent; and do all 
applicable related investigative and corrective actions; in 
accordance the Accomplishment Instructions of SASB 737-53-1065, R3, 
except as required by paragraph (i)(3) of this AD. Do all applicable 
related investigative and corrective actions before further flight. 
Accomplishing the permanent repair required by this paragraph 
terminates the inspections required by paragraph (j)(1)(i) of this 
AD for the permanently repaired area only.
    (2) For airplanes with a time limited repair installed as 
specified in SASB 737-53-1065, R3: At the applicable times specified 
in table 4 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1065, 
R3, do the actions specified in paragraphs (j)(2)(i) and (j)(2)(ii) 
of this AD.
    (i) Do the applicable inspections to detect missing or loose 
fasteners and any disbonding or cracking of bonded doublers; and do 
all applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of SASB 737-53-1065, 
R3, except as required by paragraph (i)(3) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight. Repeat the applicable inspections thereafter at the 
applicable intervals specified in SASB 737-53-1065, R3.
    (ii) Make the time limited repair permanent; and do all 
applicable related investigative and corrective actions; in 
accordance the Accomplishment Instructions of SASB 737-53-1065, R3, 
except as required by paragraph (i)(3) of this AD. Do all applicable 
related investigative and corrective actions before further flight. 
Accomplishing the permanent repair required by this paragraph 
terminates the inspections required by paragraph (j)(2)(i) of this 
AD for the permanently repaired area only.

(k) Modification of Certain Permanent Repairs

    Except for Group 1 airplanes identified in SASB 737-53-1065, R3: 
For airplanes with an existing time limited repair that was made 
permanent as specified in Boeing Special Attention Service Bulletin 
737-53-1065, Revision 2, dated April 19, 2001, at the applicable 
times specified in table 5 of paragraph 1.E., ``Compliance,'' of 
SASB 737-53-1065, R3, except as required by paragraph (i)(1) of this 
AD, modify the existing permanent repair; and do all applicable 
related investigative and corrective actions; in accordance the 
Accomplishment Instructions of SASB 737-53-1065, R3, except as 
required by paragraph (i)(3) of this AD. Do all applicable related 
investigative and corrective actions before further flight.

(l) Post-Modification Inspections

    Table 6 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1065, 
R3 specifies post-modification airworthiness limitation inspections 
in compliance with 14 CFR 25.571(a)(3) at the modified locations, 
which support compliance with 14 CFR 121.1109(c)(2) or 
129.109(b)(2). As airworthiness limitations, these inspections are 
required by maintenance and operational rules. It is therefore 
unnecessary to mandate them in this AD. Deviations from these 
inspections require FAA approval, but do not require an alternative 
method of compliance.

(m) Skin Panel Replacement

    Except for Group 1 airplanes identified in SASB 737-53-1065, R3: 
At the later of the times specified in paragraphs (m)(1) and (m)(2) 
of this AD, replace the applicable skin panels, in accordance with 
the Part 8 of the Accomplishment Instructions of SASB 737-53-1065, 
R3. Doing the skin panel replacement required by this paragraph 
terminates the inspection requirements of paragraph (h) of this AD 
for that skin panel only, provided the skin panel was replaced with 
a production skin panel at or after 59,000 total flight cycles.
    (1) Before 60,000 total flight cycles, but not before 59,000 
total flight cycles.
    (2) Within 6,000 flight cycles after the effective date of this 
AD, but not before 59,000 total flight cycles.

[[Page 10859]]

(n) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Special Attention Service 
Bulletin 737-53-1065, Revision 2, dated April 19, 2001, which was 
incorporated by reference in AD 2005-13-30.

(o) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (p) of this AD. 
Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Los Angeles ACO, to make those findings. To be approved, 
the repair method, modification deviation, or alteration deviation 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.
    (4) AMOCs approved previously for AD 2005-13-30, are approved as 
AMOCs for the corresponding provisions of paragraph (h) of this AD.

(p) Related Information

    For more information about this AD, contact Jennifer 
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; 
phone: 562-627-5264; fax: 562-627-5210; email: 
jennifer.tsakoumakis@faa.gov.

(q) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Special Attention Service Bulletin 737-53-1065, 
Revision 3, dated June 30, 2015.
    (ii) Reserved.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 11, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-03112 Filed 2-15-17; 8:45 am]
 BILLING CODE 4910-13-P