Airworthiness Directives; The Boeing Company Airplanes, 11140-11144 [2017-02661]

Download as PDF 11140 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations still be done as specified, and the airplane can be put back in an airworthy condition. (i) Related Information For more information about this AD, contact Myra Kuck, Aerospace Engineer, Cabin Safety/Mechanical & Environmental Systems branch, ANM–150L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: 562–627– 5316; fax: 562–627–5210; email: myra.j.kuck@faa.gov. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 757– 27A0154, dated July 22, 2016. (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 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. (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 23, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03030 Filed 2–17–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6664; Directorate Identifier 2015–NM–177–AD; Amendment 39–18795; AD 2017–03–04] rmajette on DSK2TPTVN1PROD with RULES RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: VerDate Sep<11>2014 14:42 Feb 17, 2017 Jkt 241001 We are superseding Airworthiness Directive (AD) 2012–16– 07 for certain The Boeing Company Model 737–500 series airplanes. AD 2012–16–07 required inspections of the fuselage skin at the chem-milled steps, and repair if necessary. This new AD adds new inspections, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. This AD was prompted by evaluation by the design approval holder (DAH) that indicates that the fuselage skin is subject to widespread fatigue damage (WFD), and reports of cracking in certain areas of the fuselage skin. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 28, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 28, 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– 6664. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.govby searching for and locating Docket No. FAA–2016– 6664; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 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 2012–16–07, Amendment 39–17154 (77 FR 48423, August 14, 2012) (‘‘AD 2012–16–07’’). AD 2012–16–07 applied to certain The Boeing Company Model 737–500 series airplanes. The NPRM published in the Federal Register on May 13, 2016 (81 FR 29813) (‘‘the NPRM’’). The NPRM was prompted by evaluation by the DAH that indicates 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 continue to require inspections of the fuselage skin at the chem-milled steps, and repair if necessary. The NPRM also proposed to add new fuselage skin inspections for cracking, inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, permanent repairs of timelimited repairs, related investigative and corrective actions if necessary, and skin panel replacement. We are issuing this AD to detect and correct cracking on the aft lower lobe fuselage skins, which could result in rapid decompression of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Remove Time-Limited Repair Exception From Paragraph (g) of the Proposed AD Boeing requested that we remove the paragraph (h)(5) exception specified in paragraph (g) of the proposed AD. Boeing stated that paragraph (h)(5) of the proposed AD refers to structure with time-limited repairs and is not applicable to paragraph (g) of the proposed AD, which deals with actions on unrepaired structure. We agree with Boeing’s request to remove the paragraph (h)(5) reference in paragraph (g) of this AD for the reason provided by Boeing. We have revised paragraph (g) of this AD accordingly. Request To Revise Proposed Compliance Time and Method of Compliance Boeing requested that we revise paragraphs (h)(4), (k)(1), and (k)(2) of the proposed AD to specify that the skin E:\FR\FM\21FER1.SGM 21FER1 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations rmajette on DSK2TPTVN1PROD with RULES panel replacement condition is ‘‘before’’ 53,000 total flight cycles, not ‘‘at or before’’ 53,000 total flight cycles; ‘‘and at or after’’ 53,000 total flight cycles, not ‘‘before’’ for the terminating action in paragraph (k) of the proposed AD. Boeing explained if a skin panel is replaced at 53,000 total flight cycles, no additional safety inspections would be needed due to the limit of validity (LOV). Boeing also requested that we revise the compliance time for skin panel replacement in paragraph (h)(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 asserted that a reset of the compliance times is necessary if the panel is replaced before 53,000 total flight cycles. Since a Boeing authorized representative may not approve extensions of compliance times, Boeing pointed out that the AMOC approval for a reset of the compliance times from total flight cycles to flight cycles from when the panel is replaced would have to come from the FAA. We partially agree with Boeing’s requests. We agree to revise the compliance time condition to ‘‘before 53,000 total flight cycles’’ in paragraphs (h)(4), (k)(1), and (k)(2) of this AD; and to ‘‘at or after 53,000 total flight cycles’’ in paragraph (k) of this AD for the terminating action to address Boeing’s LOV concerns. We also acknowledge the request to change the compliance time in paragraph (h)(4) of this AD from the applicable time for the next inspection as specified in the service information to a time approved by the FAA. However, we have determined that a change to this AD is not necessary. Operators may always request approval for alternative compliance times using a method approved in accordance with the procedures specified in paragraph (m) of this AD. The compliance time in paragraph (h)(4) of this AD is an appropriate compliance time and provides an acceptable level of safety. It should also provide operators with sufficient information for maintenance planning purposes and allow the inspections to be done during scheduled maintenance intervals for most affected operators. Request To Provide Specific Service Information References Boeing requested that we revise paragraphs (i)(1) and (i)(2) of the proposed AD to provide reference to the specific part of the service information. Boeing stated that paragraph (g) of the proposed AD includes specific service VerDate Sep<11>2014 14:42 Feb 17, 2017 Jkt 241001 information part references, so this change would make paragraph (i) consistent with the formatting of paragraph (g) of the proposed AD. We do not agree with Boeing’s requests. Paragraph (g) 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 (j) of the proposed AD to specify that table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 737–53– 1315, Revision 1, dated June 30, 2015 (‘‘SASB 737–53–1315 R1’’), is for postmodification 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 (j) of this AD to clarify that the post-modification inspections are airworthiness limitations that are required by maintenance and operational rules; therefore, these inspections are not required by this AD. Request To Revise Corrective Actions in Paragraph (k) of the Proposed AD Boeing requested that we revise paragraph (k) of the proposed AD, which specifies replacing the applicable skin panels and doing all applicable related investigative and corrective actions. Boeing requested that we remove the phrases ‘‘do all applicable related investigative and corrective actions,’’ in accordance with the Accomplishment Instructions of SASB 737–53–1315 R1 and ‘‘do all applicable related investigative and corrective actions before further flight.’’ Boeing suggested replacing these phrases with in accordance with ‘‘Part 2: Skin Panel Replacement of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–53–1315, Revision 1, dated June 30, 2015,’’ to be similar to the wording in other NPRMs. We disagree with the request to refer to ‘‘Part 2’’ of SASB 737–53–1315 R1. We do not agree that the reference is needed for clarity. We also do not agree with removing the phrase ‘‘all applicable related investigative and PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 11141 corrective actions’’ because that phrase indicates there are on-condition actions. The skin panel replacement includes a conditional action that specifies reinstalling a certain lap joint modification. The sentence ‘‘do all applicable related investigative and corrective actions before further flight’’ is included to reinforce the compliance time for the on-condition actions. We have not changed this AD in regard to these requests. Request To Revise the NPRM To Address Certain Repaired Areas For airplanes subject to the requirements of paragraph (g) 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 (g) of this AD specifies to do the applicable inspections and related investigative and corrective actions specified in the Accomplishment Instructions of SASB 737–53–1315 R1. This service information already contains the criteria Boeing proposed. Therefore, this criteria does not need to be repeated in this AD. We have not changed this AD in this regard. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the Supplemental Type Certificate (STC) ST01219SE does not affect the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as (c)(1) and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to accomplish the actions required by this final rule. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. 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: E:\FR\FM\21FER1.SGM 21FER1 11142 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed SASB 737–53–1315 R1. The service information describes procedures for inspection and repair of the fuselage skin panels between station 727 and station 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 33 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspections (actions retained from AD 2012–16-07). Inspections (new action) ......................... 23 work-hours × $85 per hour = $1,955 per inspection cycle. Up to 1,515 work-hours × $85 per hour = $128,775 per inspection cycle. 688 work-hours × $85 per hour = $58,480. Skin panel replacement (new action) ..... We estimate the following costs to do any necessary repairs that would be Parts cost $0 0 96,000 required based on the results of the inspection. We have no way of Cost on U.S. operators Cost per product $1,955 per inspection cycle. Up to $128,775 per inspection cycle. $154,480 ............... $64,515 per inspection cycle. Up to $4,249,575 per inspection cycle. $5,097,840. 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. ................................. 31 work-hours × $85 per hour = $2,635. ................................. 4 work-hours × $85 per hour = $340 per inspection cycle ...... 1 We Cost per product (1 ) (1 ) ( 1) $2,040. 2,635. 340 per inspection cycle. have received no definitive data that would enable us to provide parts cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. rmajette on DSK2TPTVN1PROD with RULES Parts cost 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, VerDate Sep<11>2014 17:04 Feb 17, 2017 Jkt 241001 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. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2012–16–07, Amendment 39–17154 (77 FR 48423, August 14, 2012), and adding the following new AD: ■ 2017–03–04 The Boeing Company: Amendment 39–18795; Docket No. FAA–2016–6664; Directorate Identifier 2015–NM–177–AD. (a) Effective Date This AD is effective March 28, 2017. (b) Affected ADs List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. This AD replaces AD 2012–16–07, Amendment 39–17154 (77 FR 48423, August 14, 2012) (‘‘AD 2012–16–07’’). Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (1) This AD applies to all The Boeing Company Model 737–500 series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa. gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb 30045557a/$FILE/ST01219SE.pdf) PART 39—AIRWORTHINESS DIRECTIVES (c) Applicability 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\21FER1.SGM 21FER1 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) that indicates 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 detect and correct cracking on the aft lower lobe fuselage skins, which could result in rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. rmajette on DSK2TPTVN1PROD with RULES (g) Inspections, Related Investigative and Corrective Actions At the applicable times specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 737–53– 1315, Revision 1, dated June 30, 2015 (‘‘SASB 737–53–1315 R1’’), except as required by paragraphs (h)(1) and (h)(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– 53–1315 R1, except as required by paragraphs (h)(3) and (h)(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 SASB 737–53–1315 R1. Accomplishment of a repair in accordance with ‘‘Part 3: Repair’’ of the Accomplishment Instructions of SASB 737– 53–1315 R1, except as required by paragraph (h)(3) of this AD, is terminating action for the repetitive inspections required by this paragraph at the repaired locations only. (h) Exceptions to SASB 737–53–1315 R1 (1) Where SASB 737–53–1315 R1, specifies compliance times ‘‘after the Revision 1 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 table 1 of Paragraph 1.E., ‘‘Compliance,’’ of SASB 737– 53–1315 R1, refers to airplanes in certain configurations as of the ‘‘issue date of Revision 1 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 737–53–1315 R1, 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 (m) of this AD, except as required by paragraph (h)(4) of this AD. VerDate Sep<11>2014 17:04 Feb 17, 2017 Jkt 241001 (4) For airplanes on which an operator has a record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles: At the applicable time for the next inspection as specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ SASB 737– 53–1315 R1, except as provided by paragraphs (h)(1) and (h)(2) of this AD: Perform inspections and applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (5) The Condition column of table 2 of Paragraph 1.E., ‘‘Compliance,’’ of SASB 737– 53–1315 R1, refers to airplanes in certain configurations as of the ‘‘issue date of Revision 1 of this service bulletin.’’ However, this AD applies to airplanes in the specified configurations regardless of when the time limited repair is installed. (i) Actions for Airplanes With a Time Limited Repair Installed For airplanes with a time limited repair installed as specified in Boeing Special Attention Service Bulletin 737–53–1315, dated July 29, 2011; or SASB 737–53–1315 R1: At the applicable times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737–53–1315 R1, except as provided by paragraphs (h)(1) and (h)(5) of this AD, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD. (1) 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 737–53–1315 R1, except as required by paragraph (h)(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 SASB 737–53–1315 R1. (2) Make the time limited repair permanent and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of SASB 737– 53–1315 R1, except as required by paragraph (h)(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 (i)(1) of this AD for the permanently repaired area only. (j) AD Provisions for Part 26 Supplemental Inspections Table 3 of paragraph 1.E., ‘‘Compliance,’’ of SASB 737–53–1315 R1, 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. (k) Skin Panel Replacement At the later of the times specified in paragraphs (k)(1) and (k)(2) of this AD: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 11143 Replace the applicable skin panels, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of SASB 737– 53–1315 R1. Do all applicable related investigative and corrective actions before further flight. Doing the skin panel replacement required by this paragraph terminates the inspection requirements of paragraph (g) of this AD for that skin panel only, provided the skin panel replacement was done with a production skin panel at or after 53,000 total flight cycles. (1) Before 60,000 total flight cycles, but not before 53,000 total flight cycles. (2) Within 6,000 flight cycles after the effective date of this AD, but not before 53,000 total flight cycles. (l) Credit for Previous Actions This paragraph provides credit for the zone 1 actions required by paragraph (g) of this AD, as described in SASB 737–53–1315 R1, if the zone 1, 2, and 3 actions, as described in Boeing Special Attention Service Bulletin 737–53–1315, dated July 29, 2011, were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 737–53–1315, dated July 29, 2011, except as required by paragraph (h)(4) of this AD. Boeing Special Attention Bulletin 737– 53–1315, dated July 29, 2011, was incorporated by reference in AD 2012–16–07. (m) 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 (n)(1) 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 2012–16–07 are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (n) Related Information (1) For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification E:\FR\FM\21FER1.SGM 21FER1 11144 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5264; fax: 562–627–5210; email: jennifer.tsakoumakis@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) 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 737–53–1315, Revision 1, 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/ibrlocations.html. Issued in Renton, Washington, on January 31, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–02661 Filed 2–17–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9190; Directorate Identifier 2016–NM–087–AD; Amendment 39–18797; AD 2017–04–02] RIN 2120–AA64 rmajette on DSK2TPTVN1PROD with RULES Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2014–23– 06 for certain Bombardier, Inc. Model SUMMARY: VerDate Sep<11>2014 17:04 Feb 17, 2017 Jkt 241001 CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. AD 2014–23–06 required modifying the main landing gear (MLG) by installing a new bracket on the left and right lower aft-wing planks. This new AD requires modification of the MLG with an improved design. This AD was prompted by a report indicating that inboard and outboard hydraulic lines of the brakes were found connected to the incorrect ports on the swivel assembly of the MLG. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 28, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 28, 2017. ADDRESSES: For service information identified in this final rule, contact ˆ Bombardier, Inc., 400 Cote-Vertu Road ´ West, Dorval, Quebec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone 1– 866–538–1247 or direct-dial telephone 1–514–855–2999; fax 514–855–7401; email ac.yul@aero.bombardier.com; Internet http://www.bombardier.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– 9190. 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– 9190; 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 (telephone 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Fabio Buttitta, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7303; fax 516–794–5531. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2014–23–06, Amendment 39–18022 (79 FR 69037, November 20, 2014) (‘‘AD 2014–23– 06’’). AD 2014–23–06 applied to certain Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. The NPRM published in the Federal Register on October 24, 2016 (81 FR 73042). The NPRM was prompted by a report indicating that inboard and outboard hydraulic lines of the brakes were found connected to the incorrect ports on the swivel assembly of the MLG. The NPRM proposed to require modification of the MLG with an improved design. We are issuing this AD to prevent incorrect installation of the brake hydraulic lines, which could cause the brakes and the anti-skid system to operate incorrectly, and result in catastrophic failure of the airplane during a high-speed rejected takeoff. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–10R1, dated May 4, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model CL– 600–2B19 (Regional Jet Series 100 & 440) airplanes. The MCAI states: Cases of inboard and outboard hydraulic brake lines connected to the incorrect port of the swivel assembly on the main landing gear were found in service. Cross-connected brake hydraulic lines can cause the brakes and/or the anti-skid system to operate incorrectly. During a high speed rejected take-off, inability for the brakes to operate correctly could be catastrophic. The original issue of this [Canadian] AD mandated the modification to prevent inadvertent crossconnection of the inboard and outboard hydraulic brake lines. Following the initial release of this [Canadian] AD, operators reported that the modifications required by Bombardier Service Bulletin (SB) 601R–32–110 Rev. NC., dated 19 December 2013, still have a potential for incorrect connection. Subsequently, the SB has been revised to introduce a modified design and this [Canadian] AD revision is issued to mandate the incorporation of the modified design. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9190. E:\FR\FM\21FER1.SGM 21FER1

Agencies

[Federal Register Volume 82, Number 33 (Tuesday, February 21, 2017)]
[Rules and Regulations]
[Pages 11140-11144]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-02661]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6664; Directorate Identifier 2015-NM-177-AD; 
Amendment 39-18795; AD 2017-03-04]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2012-16-07 for 
certain The Boeing Company Model 737-500 series airplanes. AD 2012-16-
07 required inspections of the fuselage skin at the chem-milled steps, 
and repair if necessary. This new AD adds new inspections, permanent 
repairs of time-limited repairs, related investigative and corrective 
actions if necessary, and skin panel replacement. This AD was prompted 
by evaluation by the design approval holder (DAH) that indicates that 
the fuselage skin is subject to widespread fatigue damage (WFD), and 
reports of cracking in certain areas of the fuselage skin. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective March 28, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 28, 
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-
6664.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2016-
6664; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: 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 2012-16-07, Amendment 39-17154 (77 FR 48423, 
August 14, 2012) (``AD 2012-16-07''). AD 2012-16-07 applied to certain 
The Boeing Company Model 737-500 series airplanes. The NPRM published 
in the Federal Register on May 13, 2016 (81 FR 29813) (``the NPRM''). 
The NPRM was prompted by evaluation by the DAH that indicates 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 continue to 
require inspections of the fuselage skin at the chem-milled steps, and 
repair if necessary. The NPRM also proposed to add 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. We are issuing this 
AD to detect and correct cracking on the aft lower lobe fuselage skins, 
which could result in rapid decompression of the airplane.

Comments

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

Request To Remove Time-Limited Repair Exception From Paragraph (g) of 
the Proposed AD

    Boeing requested that we remove the paragraph (h)(5) exception 
specified in paragraph (g) of the proposed AD. Boeing stated that 
paragraph (h)(5) of the proposed AD refers to structure with time-
limited repairs and is not applicable to paragraph (g) of the proposed 
AD, which deals with actions on unrepaired structure.
    We agree with Boeing's request to remove the paragraph (h)(5) 
reference in paragraph (g) of this AD for the reason provided by 
Boeing. We have revised paragraph (g) of this AD accordingly.

Request To Revise Proposed Compliance Time and Method of Compliance

    Boeing requested that we revise paragraphs (h)(4), (k)(1), and 
(k)(2) of the proposed AD to specify that the skin

[[Page 11141]]

panel replacement condition is ``before'' 53,000 total flight cycles, 
not ``at or before'' 53,000 total flight cycles; ``and at or after'' 
53,000 total flight cycles, not ``before'' for the terminating action 
in paragraph (k) of the proposed AD. Boeing explained if a skin panel 
is replaced at 53,000 total flight cycles, no additional safety 
inspections would be needed due to the limit of validity (LOV).
    Boeing also requested that we revise the compliance time for skin 
panel replacement in paragraph (h)(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 asserted that a reset of the compliance times is necessary if 
the panel is replaced before 53,000 total flight cycles. Since a Boeing 
authorized representative may not approve extensions of compliance 
times, Boeing pointed out that the AMOC approval for a reset of the 
compliance times from total flight cycles to flight cycles from when 
the panel is replaced would have to come from the FAA.
    We partially agree with Boeing's requests. We agree to revise the 
compliance time condition to ``before 53,000 total flight cycles'' in 
paragraphs (h)(4), (k)(1), and (k)(2) of this AD; and to ``at or after 
53,000 total flight cycles'' in paragraph (k) of this AD for the 
terminating action to address Boeing's LOV concerns.
    We also acknowledge the request to change the compliance time in 
paragraph (h)(4) of this AD from the applicable time for the next 
inspection as specified in the service information to a time approved 
by the FAA. However, we have determined that a change to this AD is not 
necessary. Operators may always request approval for alternative 
compliance times using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD. The compliance time 
in paragraph (h)(4) of this AD is an appropriate compliance time and 
provides an acceptable level of safety. It should also provide 
operators with sufficient information for maintenance planning purposes 
and allow the inspections to be done during scheduled maintenance 
intervals for most affected operators.

Request To Provide Specific Service Information References

    Boeing requested that we revise paragraphs (i)(1) and (i)(2) of the 
proposed AD to provide reference to the specific part of the service 
information. Boeing stated that paragraph (g) of the proposed AD 
includes specific service information part references, so this change 
would make paragraph (i) consistent with the formatting of paragraph 
(g) of the proposed AD.
    We do not agree with Boeing's requests. Paragraph (g) 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 (j) of the proposed AD to 
specify that table 3 of paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 737-53-1315, Revision 1, dated June 
30, 2015 (``SASB 737-53-1315 R1''), 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 (j) of 
this AD to clarify that the post-modification inspections are 
airworthiness limitations that are required by maintenance and 
operational rules; therefore, these inspections are not required by 
this AD.

Request To Revise Corrective Actions in Paragraph (k) of the Proposed 
AD

    Boeing requested that we revise paragraph (k) of the proposed AD, 
which specifies replacing the applicable skin panels and doing all 
applicable related investigative and corrective actions. Boeing 
requested that we remove the phrases ``do all applicable related 
investigative and corrective actions,'' in accordance with the 
Accomplishment Instructions of SASB 737-53-1315 R1 and ``do all 
applicable related investigative and corrective actions before further 
flight.'' Boeing suggested replacing these phrases with in accordance 
with ``Part 2: Skin Panel Replacement of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 737-53-1315, 
Revision 1, dated June 30, 2015,'' to be similar to the wording in 
other NPRMs.
    We disagree with the request to refer to ``Part 2'' of SASB 737-53-
1315 R1. We do not agree that the reference is needed for clarity. We 
also do not agree with removing the phrase ``all applicable related 
investigative and corrective actions'' because that phrase indicates 
there are on-condition actions. The skin panel replacement includes a 
conditional action that specifies reinstalling a certain lap joint 
modification. The sentence ``do all applicable related investigative 
and corrective actions before further flight'' is included to reinforce 
the compliance time for the on-condition actions. We have not changed 
this AD in regard to these requests.

Request To Revise the NPRM To Address Certain Repaired Areas

    For airplanes subject to the requirements of paragraph (g) 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 (g) of this AD 
specifies to do the applicable inspections and related investigative 
and corrective actions specified in the Accomplishment Instructions of 
SASB 737-53-1315 R1. This service information already contains the 
criteria Boeing proposed. Therefore, this criteria does not need to be 
repeated in this AD. We have not changed this AD in this regard.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that accomplishing the Supplemental 
Type Certificate (STC) ST01219SE does not affect the actions specified 
in the NPRM.
    We concur with the commenter. We have redesignated paragraph (c) of 
the proposed AD as (c)(1) and added paragraph (c)(2) to this AD to 
state that installation of STC ST01219SE does not affect the ability to 
accomplish the actions required by this final rule. Therefore, for 
airplanes on which STC ST01219SE is installed, a ``change in product'' 
alternative method of compliance (AMOC) approval request is not 
necessary to comply with the requirements of 14 CFR 39.17.

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:

[[Page 11142]]

     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed SASB 737-53-1315 R1. The service information describes 
procedures for inspection and repair of the fuselage skin panels 
between station 727 and station 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 33 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
----------------------------------------------------------------------------------------------------------------
Inspections (actions retained      23 work-hours x $85 per          $0  $1,955 per           $64,515 per
 from AD 2012-16[dash]07).          hour = $1,955 per                    inspection cycle.    inspection cycle.
                                    inspection cycle.
Inspections (new action).........  Up to 1,515 work-hours x          0  Up to $128,775 per   Up to $4,249,575
                                    $85 per hour = $128,775              inspection cycle.    per inspection
                                    per inspection cycle.                                     cycle.
Skin panel replacement (new        688 work-hours x $85 per     96,000  $154,480...........  $5,097,840.
 action).                           hour = $58,480.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                            Labor cost              Parts cost        Cost per product
----------------------------------------------------------------------------------------------------------------
Time-limited repair...................  24 work-hours x $85 per hour =           (\1\)  $2,040.
                                         $2,040..
Permanent repair......................  31 work-hours x $85 per hour =           (\1\)  2,635.
                                         $2,635..
Permanent repair inspection...........  4 work-hours x $85 per hour =            (\1\)  340 per inspection
                                         $340 per inspection cycle.                      cycle.
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide parts cost estimates for the on-
  condition actions specified in this AD.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2012-16-07, Amendment 39-17154 (77 FR 48423, August 14, 2012), and 
adding the following new AD:

2017-03-04 The Boeing Company: Amendment 39-18795; Docket No. FAA-
2016-6664; Directorate Identifier 2015-NM-177-AD.

(a) Effective Date

    This AD is effective March 28, 2017.

(b) Affected ADs

    This AD replaces AD 2012-16-07, Amendment 39-17154 (77 FR 48423, 
August 14, 2012) (``AD 2012-16-07'').

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 737-500 
series airplanes, certificated in any category.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf)

[[Page 11143]]

does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01219SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) that indicates 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 detect 
and correct cracking on the aft lower lobe fuselage skins, which 
could result in rapid decompression of the airplane.

(f) Compliance

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

(g) Inspections, Related Investigative and Corrective Actions

    At the applicable times specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-
1315, Revision 1, dated June 30, 2015 (``SASB 737-53-1315 R1''), 
except as required by paragraphs (h)(1) and (h)(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 
737-53-1315 R1, except as required by paragraphs (h)(3) and (h)(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 SASB 737-53-1315 
R1. Accomplishment of a repair in accordance with ``Part 3: Repair'' 
of the Accomplishment Instructions of SASB 737-53-1315 R1, except as 
required by paragraph (h)(3) of this AD, is terminating action for 
the repetitive inspections required by this paragraph at the 
repaired locations only.

(h) Exceptions to SASB 737-53-1315 R1

    (1) Where SASB 737-53-1315 R1, specifies compliance times 
``after the Revision 1 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 table 1 of Paragraph 1.E., 
``Compliance,'' of SASB 737-53-1315 R1, refers to airplanes in 
certain configurations as of the ``issue date of Revision 1 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 737-53-1315 R1, 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 (m) of this 
AD, except as required by paragraph (h)(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 53,000 total 
flight cycles: At the applicable time for the next inspection as 
specified in table 1 of paragraph 1.E., ``Compliance,'' SASB 737-53-
1315 R1, except as provided by paragraphs (h)(1) and (h)(2) of this 
AD: Perform inspections and applicable corrective actions using a 
method approved in accordance with the procedures specified in 
paragraph (m) of this AD.
    (5) The Condition column of table 2 of Paragraph 1.E., 
``Compliance,'' of SASB 737-53-1315 R1, refers to airplanes in 
certain configurations as of the ``issue date of Revision 1 of this 
service bulletin.'' However, this AD applies to airplanes in the 
specified configurations regardless of when the time limited repair 
is installed.

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

    For airplanes with a time limited repair installed as specified 
in Boeing Special Attention Service Bulletin 737-53-1315, dated July 
29, 2011; or SASB 737-53-1315 R1: At the applicable times specified 
in table 2 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1315 
R1, except as provided by paragraphs (h)(1) and (h)(5) of this AD, 
do the actions specified in paragraphs (i)(1) and (i)(2) of this AD.
    (1) 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 737-53-1315 
R1, except as required by paragraph (h)(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 SASB 737-53-1315 R1.
    (2) Make the time limited repair permanent and do all applicable 
related investigative and corrective actions in accordance with the 
Accomplishment Instructions of SASB 737-53-1315 R1, except as 
required by paragraph (h)(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 (i)(1) of this AD 
for the permanently repaired area only.

(j) AD Provisions for Part 26 Supplemental Inspections

    Table 3 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1315 
R1, 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.

(k) Skin Panel Replacement

    At the later of the times specified in paragraphs (k)(1) and 
(k)(2) of this AD: Replace the applicable skin panels, and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of SASB 737-53-1315 
R1. Do all applicable related investigative and corrective actions 
before further flight. Doing the skin panel replacement required by 
this paragraph terminates the inspection requirements of paragraph 
(g) of this AD for that skin panel only, provided the skin panel 
replacement was done with a production skin panel at or after 53,000 
total flight cycles.
    (1) Before 60,000 total flight cycles, but not before 53,000 
total flight cycles.
    (2) Within 6,000 flight cycles after the effective date of this 
AD, but not before 53,000 total flight cycles.

(l) Credit for Previous Actions

    This paragraph provides credit for the zone 1 actions required 
by paragraph (g) of this AD, as described in SASB 737-53-1315 R1, if 
the zone 1, 2, and 3 actions, as described in Boeing Special 
Attention Service Bulletin 737-53-1315, dated July 29, 2011, were 
performed before the effective date of this AD using Boeing Special 
Attention Service Bulletin 737-53-1315, dated July 29, 2011, except 
as required by paragraph (h)(4) of this AD. Boeing Special Attention 
Bulletin 737-53-1315, dated July 29, 2011, was incorporated by 
reference in AD 2012-16-07.

(m) 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 (n)(1) 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 2012-16-07 are approved as 
AMOCs for the corresponding provisions of paragraph (g) of this AD.

(n) Related Information

    (1) For more information about this AD, contact Jennifer 
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles Aircraft Certification

[[Page 11144]]

Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; 
phone: 562-627-5264; fax: 562-627-5210; email: 
jennifer.tsakoumakis@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) 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 737-53-1315, 
Revision 1, 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 31, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-02661 Filed 2-17-17; 8:45 am]
BILLING CODE 4910-13-P