Airworthiness Directives; The Boeing Company Airplanes, 26778-26781 [2019-11925]

Download as PDF 26778 Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329–4090; email: mike.kiesov@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must instead be accomplished using a method approved by the Manager, Small Airplane Standards Branch, FAA; or the Civil Aviation Authority of New Zealand (CAA). (h) Related Information Refer to CAA MCAI AD No. DCA/750XL/ 19A, dated April 26, 2018, for related information. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2018–0842. Pacific Aerospace Limited, Airport Road, Hamilton, Private Bag 3027, Hamilton 3240, New Zealand; telephone: +64 7 843 6144; facsimile: +64 7 843 6134; email: pacific@aerospace.co.nz; Internet: www.aerospace.co.nz. You may review copies of the referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on May 29, 2019. Melvin J. Johnson, Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2019–11751 Filed 6–7–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0326; Product Identifier 2018–NM–166–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). khammond on DSKBBV9HB2PROD with PROPOSALS AGENCY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This AD was prompted by significant changes made to the airworthiness limitations (AWLs) related to fuel tank ignition prevention and the nitrogen generation system. SUMMARY: VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 This AD would require revising the existing maintenance or inspection program, as applicable, to include new or revised AWLs. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 25, 2019. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; phone: 562–797–1717; internet: https:// www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0326; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jeffrey Rothman, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206– 231–3558; email: jeffrey.rothman@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 section. Include ‘‘Docket No. FAA– 2019–0326; Product Identifier 2018– NM–166–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a final rule titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, that rule included Amendment 21–78, which established Special Federal Aviation Regulation No. 88 (‘‘SFAR 88’’) at 14 CFR part 21. Subsequently, SFAR 88 was amended by Amendment 21–82 (67 FR 57490, September 10, 2002; corrected at 67 FR 70809, November 26, 2002) and Amendment 21–83 (67 FR 72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to change ‘‘21–82’’ to ‘‘21–83’’). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the final rule published on May 7, 2001, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. E:\FR\FM\10JNP1.SGM 10JNP1 Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with another latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this proposed AD are necessary to address the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We have determined that accomplishing the revision required by paragraph (g) of this proposed AD would terminate the following requirements for that airplane. • All requirements of AD 2008–10–09 R1, Amendment 39–16148 (74 FR 69264, December 31, 2009). • The revision required by paragraph (l) of AD 2011–12–09, Amendment 39– 16716 (76 FR 33988, June 10, 2011). • The revision required by paragraph (h) of AD 2013–13–15, Amendment 39– 17503 (78 FR 42415, July 16, 2013). • The revision required by paragraph (j) of AD 2013–25–05, Amendment 39– 17701 (78 FR 78701, December 27, 2013). • The revisions required by paragraphs (l) and (n) of AD 2016–18– 16, Amendment 39–18647 (81 FR 65864, September 26, 2016). • The revision required by paragraph (h) of AD 2017–17–09, Amendment 39– 18999 (82 FR 40477, August 25, 2017). khammond on DSKBBV9HB2PROD with PROPOSALS Related Service Information Under 1 CFR Part 51 We reviewed Boeing 737–100/200/ 200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6– 38278–CMR, dated March 2019. This service information describes airworthiness limitations that include Airworthiness Limitation Instructions (ALI) and Critical Design Configuration Control Limitations (CDCCL) tasks related to fuel tank ignition prevention and the nitrogen generation system. This service information is reasonably available because the interested parties have access to it through their normal VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require revising the existing maintenance or inspection program, as applicable, to incorporate new or revised AWLs. This proposed AD would require revisions to certain operator maintenance documents to include new actions (e.g., inspections) and CDCCLs. Compliance with these actions and CDCCLs is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator may not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (k) of this proposed AD. Differences Between This Proposed AD and the Service Information Paragraph (g) of this proposed AD would require operators to revise their maintenance or inspection program by incorporating, amongst other tasks, AWL No. 28–AWL–05, ‘‘Wire Separation Requirements for New Wiring Installed in Proximity to Wiring that Goes Into the Fuel Tanks,’’ in Boeing 737–100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6–38278–CMR, dated March 2019. Paragraph (h) of this proposed AD would allow certain changes to be made to the wire type and sleeving requirements specified in AWL No. 28– AWL–05 as an option. Costs of Compliance We estimate that this proposed AD affects 381 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: We have determined that revising the existing maintenance or inspection program takes an average of 90 workhours per operator, although we recognize that this number may vary from operator to operator. In the past, we have estimated that this action takes 1 work-hour per airplane. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), we have determined PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 26779 that a per-operator estimate is more accurate than a per-airplane estimate. Therefore, we estimate the total cost per operator to be $7,650 (90 work-hours x $85 per work-hour). 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the 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 E:\FR\FM\10JNP1.SGM 10JNP1 26780 Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2019–0326; Product Identifier 2018– NM–166–AD. (a) Comments Due Date We must receive comments by July 25, 2019. (b) Affected ADs This AD affects the ADs specified in paragraphs (b)(1) through (b)(6) of this AD. (1) AD 2008–10–09 R1, Amendment 39– 16148 (74 FR 69264, December 31, 2009) (‘‘AD 2008–10–09 R1’’). (2) AD 2011–12–09, Amendment 39–16716 (76 FR 33988, June 10, 2011) (‘‘AD 2011–12– 09’’). (3) AD 2013–13–15, Amendment 39–17503 (78 FR 42415, July 16, 2013) (‘‘AD 2013–13– 15’’). (4) AD 2013–25–05, Amendment 39–17701 (78 FR 78701, December 27, 2013) (‘‘AD 2013–25–05’’). (5) AD 2016–18–16, Amendment 39–18647 (81 FR 65864, September 26, 2016) (‘‘AD 2016–18–16’’). (6) AD 2017–17–09, Amendment 39–18999 (82 FR 40477, August 25, 2017) (‘‘AD 2017– 17–09’’). khammond on DSKBBV9HB2PROD with PROPOSALS (c) Applicability This AD applies to all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel; 47, Nitrogen Generation System. (e) Unsafe Condition This AD was prompted by a determination that new or revised airworthiness limitations (AWLs) are necessary. We are issuing this AD to address the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Maintenance or Inspection Program Revision (1) For The Boeing Company Model 737– 100, –200, and –200C series airplanes: Within 60 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the information specified in Section C, including Subsections C.1, C.2, and C.3 of Boeing 737–100/200/200C/300/ 400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6–38278–CMR, dated March 2019, except as provided in paragraph (h) of this AD. The initial compliance time for the airworthiness limitation instructions (ALI) tasks are within the applicable compliance times specified in paragraphs (g)(1)(i) through (g)(1)(x) of this AD. (i) For AWL No. 28–AWL–01, ‘‘External Wires Over Center Fuel Tank’’: Within 120 months after the most recent inspection was performed as specified in AWL No. 28– AWL–01, or within 12 months after the effective date of this AD if no initial inspection has been performed. (ii) For AWL No. 28–AWL–03, ‘‘Fuel Quantity Indicating System (FQIS)—Out Tank Wiring Lightning Shield to Ground Termination’’: Within 120 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1178, or within 120 months after the most recent inspection was performed as specified in AWL No. 28–AWL–03, whichever is later. (iii) For AWL No. 28–AWL–21, ‘‘Center Tank Fuel Boost Pump Automatic Shutoff System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1228, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–21, whichever is later. (iv) For AWL No. 28–AWL–22, ‘‘Auxiliary Tank Fuel Boost Pump Automatic Shutoff System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1228, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–22, whichever is later. (v) For AWL No. 28–AWL–23, ‘‘OverCurrent and Arcing Protection Electrical Design Features Operation—Boost Pump Ground Fault Interrupter (GFI)’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737– 28A1212, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–23, whichever is later. (vi) For AWL No. 28–AWL–24, ‘‘Center Tank Fuel Boost Pump Power Failed On Protection System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1227, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–24, whichever is later. (vii) For AWL No. 28–AWL–25, ‘‘Auxiliary Fuel Tank Boost Pump Power Failed On Protection System’’: Within 12 months after PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 accomplishment of the actions specified in Boeing Service Bulletin 737–28A1227, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–25, whichever is later. (viii) For AWL No. 28–AWL–29, ‘‘AC Fuel Boost Pump Installation’’: Within 72 months after the most recent inspection was performed as specified in AWL No. 28– AWL–29, or within 12 months after the effective date of this AD if no inspection has been performed in the last 72 months. (ix) For AWL No. 47–AWL–04, ‘‘Nitrogen Generation System (NGS)—Thermal Switch’’: Within 22,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1005; within 22,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1008; or within 22,500 flight hours after the most recent inspection was performed as specified in AWL No. 47– AWL–04; whichever is latest. (x) For AWL No. 47–AWL–05, ‘‘Nitrogen Generation System (NGS)—Nitrogen Enriched Air (NEA) Distribution Ducting Integrity’’: Within 14,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1005; within 14,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1008; or within 14,500 flight hours after the most recent inspection was performed as specified in AWL No. 47– AWL–05; whichever is latest. (2) For The Boeing Company Model 737– 300, –400, and –500 series airplanes: Within 60 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the information specified in Section C, including Subsections C.1, C.2, and C.3 of Boeing 737– 100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6– 38278–CMR, dated March 2019; except as provided in paragraph (h) of this AD. The initial compliance time for the ALI tasks are within the applicable compliance times specified in paragraphs (g)(2)(i) through (g)(2)(xi) of this AD. (i) For AWL No. 28–AWL–01, ‘‘External Wires Over Center Fuel Tank’’: Within 120 months after the most recent inspection was performed as specified in AWL No. 28– AWL–01, or within 12 months after the effective date of this AD if no initial inspection has been performed. (ii) For AWL No. 28–AWL–03, ‘‘Fuel Quantity Indicating System (FQIS)—Out Tank Wiring Lightning Shield to Ground Termination’’: Within 120 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1175; within 120 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1183; within 120 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1186; or within 120 months after the most recent inspection was performed as specified in AWL No. 28–AWL–03; whichever is latest. (iii) For AWL No. 28–AWL–20, ‘‘Center Tank Fuel Boost Pump Automatic Shutoff System’’: Within 12 months after accomplishment of the actions specified in E:\FR\FM\10JNP1.SGM 10JNP1 khammond on DSKBBV9HB2PROD with PROPOSALS Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules Boeing Service Bulletin 737–28A1216, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–20, whichever is later. (iv) For AWL No. 28–AWL–21, ‘‘Auxiliary Tank Fuel Boost Pump Automatic Shutoff System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1216, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–21, whichever is later. (v) For AWL No. 28–AWL–22, ‘‘OverCurrent and Arcing Protection Electrical Design Features Operation—Boost Pump Ground Fault Interrupter (GFI)’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737– 28A1212, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–22, whichever is later. (vi) For AWL No. 28–AWL–23, ‘‘Center Tank Fuel Boost Pump Power Failed On Protection System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1227, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–23, whichever is later. (vii) For AWL No. 28–AWL–24, ‘‘Auxiliary Fuel Tank Boost Pump Power Failed On Protection System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1227, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–24, whichever is later. (viii) For AWL No. 28–AWL–27, ‘‘AC Fuel Boost Pump Installation’’: Within 72 months after the most recent inspection was performed as specified in AWL No. 28– AWL–27, or within 12 months after the effective date of this AD if no inspection has been performed in the last 72 months. (ix) For AWL No. 28–AWL–31, ‘‘Cushion Clamps and Teflon Sleeving Installed on Outof-Tank Wire Bundles Installed on Brackets that are Mounted Directly on the Fuel Tanks’’: Within 144 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1228. (x) For AWL No. 47–AWL–04, ‘‘Nitrogen Generation System (NGS)—Thermal Switch’’: Within 22,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1005; within 22,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1008; or within 22,500 flight hours after the most recent inspection was performed as specified in AWL No. 47– AWL–04; whichever is latest. (xi) For AWL No. 47–AWL–05, ‘‘Nitrogen Generation System (NGS)—Nitrogen Enriched Air (NEA) Distribution Ducting Integrity’’: Within 14,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1005; within 14,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1008; or within 14,500 flight hours after the most recent inspection was performed as specified in AWL No. 47– AWL–05; whichever is latest. VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 (h) Additional Acceptable Wire Types and Sleeving As an option, when accomplishing the actions required by paragraph (g) of this AD, the changes specified in paragraphs (h)(1) and (h)(2) of this AD are acceptable. (1) Where AWL No. 28–AWL–05 identifies wire types BMS 13–48, BMS 13–58, and BMS 13–60, the following wire types are acceptable: MIL–W–22759/16, SAE AS22759/16 (M22759/16), MIL–W–22759/32, SAE AS22759/32 (M22759/32), MIL–W– 22759/34, SAE AS22759/34 (M22759/34), MIL–W–22759/41, SAE AS22759/41 (M22759/41), MIL–W–22759/86, SAE AS22759/86 (M22759/86), MIL–W–22759/87, SAE AS22759/87 (M22759/87), MIL–W– 22759/92, and SAE AS22759/92 (M22759/ 92); and MIL–C–27500 and NEMA WC 27500 cables constructed from these military or SAE specification wire types, as applicable. (2) Where AWL No. 28–AWL–05 identifies TFE–2X Standard wall for wire sleeving, the following sleeving materials are acceptable: Roundit 2000NX and Varglas Type HO, HP, or HM. (i) No Alternative Actions, Intervals, or Critical Design Configuration Control Limitations (CDCCLs) After the existing maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals, and CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k) of this AD. (j) Terminating Actions for Certain AD Requirements Accomplishment of the revision required by paragraph (g) of this AD terminates the requirements specified in paragraphs (j)(1) through (j)(6) of this AD for that airplane: (1) All requirements of AD 2008–10–09 R1. (2) The revision required by paragraph (l) of AD 2011–12–09. (3) The revision required by paragraph (h) of AD 2013–13–15. (4) The revision required by paragraph (j) of AD 2013–25–05. (5) The revisions required by paragraphs (l) and (n) of AD 2016–18–16. (6) The revision required by paragraph (h) of AD 2017–17–09. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9ANM-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. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 26781 (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 Branch, FAA, 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. (l) Related Information (1) For more information about this AD, contact Jeffrey Rothman, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3558; email: jeffrey.rothman@faa.gov. (2) For information about AMOCs, contact Serj Harutunian, Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5254; fax: 562–627–5210; email: serj.harutunian@faa.gov. (3) For 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; phone: 562–797–1717; internet: https:// www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on May 20, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–11925 Filed 6–7–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0402; Product Identifier 2019–NM–008–AD] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2005–17– 14, which applies to all Airbus SAS Model A300 series airplanes; Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– SUMMARY: E:\FR\FM\10JNP1.SGM 10JNP1

Agencies

[Federal Register Volume 84, Number 111 (Monday, June 10, 2019)]
[Proposed Rules]
[Pages 26778-26781]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11925]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0326; Product Identifier 2018-NM-166-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This AD was prompted by significant changes made to 
the airworthiness limitations (AWLs) related to fuel tank ignition 
prevention and the nitrogen generation system. This AD would require 
revising the existing maintenance or inspection program, as applicable, 
to include new or revised AWLs. We are proposing this AD to address the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 25, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; phone: 
562-797-1717; internet: https://www.myboeingfleet.com. You may view 
this service information at the FAA, Transport Standards Branch, 2200 
South 216th St., Des Moines, WA. For information on the availability of 
this material at the FAA, call 206-231-3195.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0326; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jeffrey Rothman, Aerospace Engineer, 
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des 
Moines, WA 98198; phone and fax: 206-231-3558; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2019-0326; 
Product Identifier 2018-NM-166-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a final 
rule titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, that rule 
included Amendment 21-78, which established Special Federal Aviation 
Regulation No. 88 (``SFAR 88'') at 14 CFR part 21. Subsequently, SFAR 
88 was amended by Amendment 21-82 (67 FR 57490, September 10, 2002; 
corrected at 67 FR 70809, November 26, 2002) and Amendment 21-83 (67 FR 
72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to 
change ``21-82'' to ``21-83'').
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the final rule published on 
May 7, 2001, we intended to adopt airworthiness directives to mandate 
any changes found necessary to address unsafe conditions identified as 
a result of these reviews.

[[Page 26779]]

    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: Single failures, single failures in 
combination with another latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this proposed AD 
are necessary to address the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    We have determined that accomplishing the revision required by 
paragraph (g) of this proposed AD would terminate the following 
requirements for that airplane.
     All requirements of AD 2008-10-09 R1, Amendment 39-16148 
(74 FR 69264, December 31, 2009).
     The revision required by paragraph (l) of AD 2011-12-09, 
Amendment 39-16716 (76 FR 33988, June 10, 2011).
     The revision required by paragraph (h) of AD 2013-13-15, 
Amendment 39-17503 (78 FR 42415, July 16, 2013).
     The revision required by paragraph (j) of AD 2013-25-05, 
Amendment 39-17701 (78 FR 78701, December 27, 2013).
     The revisions required by paragraphs (l) and (n) of AD 
2016-18-16, Amendment 39-18647 (81 FR 65864, September 26, 2016).
     The revision required by paragraph (h) of AD 2017-17-09, 
Amendment 39-18999 (82 FR 40477, August 25, 2017).

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing 737-100/200/200C/300/400/500 Airworthiness 
Limitations (AWLs) and Certification Maintenance Requirements (CMRs), 
D6-38278-CMR, dated March 2019. This service information describes 
airworthiness limitations that include Airworthiness Limitation 
Instructions (ALI) and Critical Design Configuration Control 
Limitations (CDCCL) tasks related to fuel tank ignition prevention and 
the nitrogen generation system. 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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require revising the existing maintenance or 
inspection program, as applicable, to incorporate new or revised AWLs.
    This proposed AD would require revisions to certain operator 
maintenance documents to include new actions (e.g., inspections) and 
CDCCLs. Compliance with these actions and CDCCLs is required by 14 CFR 
91.403(c). For airplanes that have been previously modified, altered, 
or repaired in the areas addressed by this proposed AD, the operator 
may not be able to accomplish the actions described in the revisions. 
In this situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according to 
paragraph (k) of this proposed AD.

Differences Between This Proposed AD and the Service Information

    Paragraph (g) of this proposed AD would require operators to revise 
their maintenance or inspection program by incorporating, amongst other 
tasks, AWL No. 28-AWL-05, ``Wire Separation Requirements for New Wiring 
Installed in Proximity to Wiring that Goes Into the Fuel Tanks,'' in 
Boeing 737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) 
and Certification Maintenance Requirements (CMRs), D6-38278-CMR, dated 
March 2019. Paragraph (h) of this proposed AD would allow certain 
changes to be made to the wire type and sleeving requirements specified 
in AWL No. 28-AWL-05 as an option.

Costs of Compliance

    We estimate that this proposed AD affects 381 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:
    We have determined that revising the existing maintenance or 
inspection program takes an average of 90 work-hours per operator, 
although we recognize that this number may vary from operator to 
operator. In the past, we have estimated that this action takes 1 work-
hour per airplane. Since operators incorporate maintenance or 
inspection program changes for their affected fleet(s), we have 
determined that a per-operator estimate is more accurate than a per-
airplane estimate. Therefore, we estimate the total cost per operator 
to be $7,650 (90 work-hours x $85 per work-hour).

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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes and associated appliances to the 
Director of the System Oversight Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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

[[Page 26780]]

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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2019-0326; Product Identifier 
2018-NM-166-AD.

(a) Comments Due Date

    We must receive comments by July 25, 2019.

(b) Affected ADs

    This AD affects the ADs specified in paragraphs (b)(1) through 
(b)(6) of this AD.
    (1) AD 2008-10-09 R1, Amendment 39-16148 (74 FR 69264, December 
31, 2009) (``AD 2008-10-09 R1'').
    (2) AD 2011-12-09, Amendment 39-16716 (76 FR 33988, June 10, 
2011) (``AD 2011-12-09'').
    (3) AD 2013-13-15, Amendment 39-17503 (78 FR 42415, July 16, 
2013) (``AD 2013-13-15'').
    (4) AD 2013-25-05, Amendment 39-17701 (78 FR 78701, December 27, 
2013) (``AD 2013-25-05'').
    (5) AD 2016-18-16, Amendment 39-18647 (81 FR 65864, September 
26, 2016) (``AD 2016-18-16'').
    (6) AD 2017-17-09, Amendment 39-18999 (82 FR 40477, August 25, 
2017) (``AD 2017-17-09'').

(c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel; 47, 
Nitrogen Generation System.

(e) Unsafe Condition

    This AD was prompted by a determination that new or revised 
airworthiness limitations (AWLs) are necessary. We are issuing this 
AD to address the potential of ignition sources inside fuel tanks, 
which, in combination with flammable fuel vapors, could result in 
fuel tank explosions and consequent loss of the airplane.

(f) Compliance

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

(g) Maintenance or Inspection Program Revision

    (1) For The Boeing Company Model 737-100, -200, and -200C series 
airplanes: Within 60 days after the effective date of this AD, 
revise the existing maintenance or inspection program, as 
applicable, to incorporate the information specified in Section C, 
including Subsections C.1, C.2, and C.3 of Boeing 737-100/200/200C/
300/400/500 Airworthiness Limitations (AWLs) and Certification 
Maintenance Requirements (CMRs), D6-38278-CMR, dated March 2019, 
except as provided in paragraph (h) of this AD. The initial 
compliance time for the airworthiness limitation instructions (ALI) 
tasks are within the applicable compliance times specified in 
paragraphs (g)(1)(i) through (g)(1)(x) of this AD.
    (i) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel 
Tank'': Within 120 months after the most recent inspection was 
performed as specified in AWL No. 28-AWL-01, or within 12 months 
after the effective date of this AD if no initial inspection has 
been performed.
    (ii) For AWL No. 28-AWL-03, ``Fuel Quantity Indicating System 
(FQIS)--Out Tank Wiring Lightning Shield to Ground Termination'': 
Within 120 months after accomplishment of the actions specified in 
Boeing Service Bulletin 737-28A1178, or within 120 months after the 
most recent inspection was performed as specified in AWL No. 28-AWL-
03, whichever is later.
    (iii) For AWL No. 28-AWL-21, ``Center Tank Fuel Boost Pump 
Automatic Shutoff System'': Within 12 months after accomplishment of 
the actions specified in Boeing Service Bulletin 737-28A1228, or 
within 12 months after the most recent inspection was performed as 
specified in AWL No. 28-AWL-21, whichever is later.
    (iv) For AWL No. 28-AWL-22, ``Auxiliary Tank Fuel Boost Pump 
Automatic Shutoff System'': Within 12 months after accomplishment of 
the actions specified in Boeing Service Bulletin 737-28A1228, or 
within 12 months after the most recent inspection was performed as 
specified in AWL No. 28-AWL-22, whichever is later.
    (v) For AWL No. 28-AWL-23, ``Over-Current and Arcing Protection 
Electrical Design Features Operation--Boost Pump Ground Fault 
Interrupter (GFI)'': Within 12 months after accomplishment of the 
actions specified in Boeing Service Bulletin 737-28A1212, or within 
12 months after the most recent inspection was performed as 
specified in AWL No. 28-AWL-23, whichever is later.
    (vi) For AWL No. 28-AWL-24, ``Center Tank Fuel Boost Pump Power 
Failed On Protection System'': Within 12 months after accomplishment 
of the actions specified in Boeing Service Bulletin 737-28A1227, or 
within 12 months after the most recent inspection was performed as 
specified in AWL No. 28-AWL-24, whichever is later.
    (vii) For AWL No. 28-AWL-25, ``Auxiliary Fuel Tank Boost Pump 
Power Failed On Protection System'': Within 12 months after 
accomplishment of the actions specified in Boeing Service Bulletin 
737-28A1227, or within 12 months after the most recent inspection 
was performed as specified in AWL No. 28-AWL-25, whichever is later.
    (viii) For AWL No. 28-AWL-29, ``AC Fuel Boost Pump 
Installation'': Within 72 months after the most recent inspection 
was performed as specified in AWL No. 28-AWL-29, or within 12 months 
after the effective date of this AD if no inspection has been 
performed in the last 72 months.
    (ix) For AWL No. 47-AWL-04, ``Nitrogen Generation System (NGS)--
Thermal Switch'': Within 22,500 flight hours after accomplishment of 
the actions specified in Boeing Service Bulletin 737-47-1005; within 
22,500 flight hours after accomplishment of the actions specified in 
Boeing Service Bulletin 737-47-1008; or within 22,500 flight hours 
after the most recent inspection was performed as specified in AWL 
No. 47-AWL-04; whichever is latest.
    (x) For AWL No. 47-AWL-05, ``Nitrogen Generation System (NGS)--
Nitrogen Enriched Air (NEA) Distribution Ducting Integrity'': Within 
14,500 flight hours after accomplishment of the actions specified in 
Boeing Service Bulletin 737-47-1005; within 14,500 flight hours 
after accomplishment of the actions specified in Boeing Service 
Bulletin 737-47-1008; or within 14,500 flight hours after the most 
recent inspection was performed as specified in AWL No. 47-AWL-05; 
whichever is latest.
    (2) For The Boeing Company Model 737-300, -400, and -500 series 
airplanes: Within 60 days after the effective date of this AD, 
revise the existing maintenance or inspection program, as 
applicable, to incorporate the information specified in Section C, 
including Subsections C.1, C.2, and C.3 of Boeing 737-100/200/200C/
300/400/500 Airworthiness Limitations (AWLs) and Certification 
Maintenance Requirements (CMRs), D6-38278-CMR, dated March 2019; 
except as provided in paragraph (h) of this AD. The initial 
compliance time for the ALI tasks are within the applicable 
compliance times specified in paragraphs (g)(2)(i) through 
(g)(2)(xi) of this AD.
    (i) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel 
Tank'': Within 120 months after the most recent inspection was 
performed as specified in AWL No. 28-AWL-01, or within 12 months 
after the effective date of this AD if no initial inspection has 
been performed.
    (ii) For AWL No. 28-AWL-03, ``Fuel Quantity Indicating System 
(FQIS)--Out Tank Wiring Lightning Shield to Ground Termination'': 
Within 120 months after accomplishment of the actions specified in 
Boeing Service Bulletin 737-28A1175; within 120 months after 
accomplishment of the actions specified in Boeing Service Bulletin 
737-28A1183; within 120 months after accomplishment of the actions 
specified in Boeing Service Bulletin 737-28A1186; or within 120 
months after the most recent inspection was performed as specified 
in AWL No. 28-AWL-03; whichever is latest.
    (iii) For AWL No. 28-AWL-20, ``Center Tank Fuel Boost Pump 
Automatic Shutoff System'': Within 12 months after accomplishment of 
the actions specified in

[[Page 26781]]

Boeing Service Bulletin 737-28A1216, or within 12 months after the 
most recent inspection was performed as specified in AWL No. 28-AWL-
20, whichever is later.
    (iv) For AWL No. 28-AWL-21, ``Auxiliary Tank Fuel Boost Pump 
Automatic Shutoff System'': Within 12 months after accomplishment of 
the actions specified in Boeing Service Bulletin 737-28A1216, or 
within 12 months after the most recent inspection was performed as 
specified in AWL No. 28-AWL-21, whichever is later.
    (v) For AWL No. 28-AWL-22, ``Over-Current and Arcing Protection 
Electrical Design Features Operation--Boost Pump Ground Fault 
Interrupter (GFI)'': Within 12 months after accomplishment of the 
actions specified in Boeing Service Bulletin 737-28A1212, or within 
12 months after the most recent inspection was performed as 
specified in AWL No. 28-AWL-22, whichever is later.
    (vi) For AWL No. 28-AWL-23, ``Center Tank Fuel Boost Pump Power 
Failed On Protection System'': Within 12 months after accomplishment 
of the actions specified in Boeing Service Bulletin 737-28A1227, or 
within 12 months after the most recent inspection was performed as 
specified in AWL No. 28-AWL-23, whichever is later.
    (vii) For AWL No. 28-AWL-24, ``Auxiliary Fuel Tank Boost Pump 
Power Failed On Protection System'': Within 12 months after 
accomplishment of the actions specified in Boeing Service Bulletin 
737-28A1227, or within 12 months after the most recent inspection 
was performed as specified in AWL No. 28-AWL-24, whichever is later.
    (viii) For AWL No. 28-AWL-27, ``AC Fuel Boost Pump 
Installation'': Within 72 months after the most recent inspection 
was performed as specified in AWL No. 28-AWL-27, or within 12 months 
after the effective date of this AD if no inspection has been 
performed in the last 72 months.
    (ix) For AWL No. 28-AWL-31, ``Cushion Clamps and Teflon Sleeving 
Installed on Out-of-Tank Wire Bundles Installed on Brackets that are 
Mounted Directly on the Fuel Tanks'': Within 144 months after 
accomplishment of the actions specified in Boeing Service Bulletin 
737-28A1228.
    (x) For AWL No. 47-AWL-04, ``Nitrogen Generation System (NGS)--
Thermal Switch'': Within 22,500 flight hours after accomplishment of 
the actions specified in Boeing Service Bulletin 737-47-1005; within 
22,500 flight hours after accomplishment of the actions specified in 
Boeing Service Bulletin 737-47-1008; or within 22,500 flight hours 
after the most recent inspection was performed as specified in AWL 
No. 47-AWL-04; whichever is latest.
    (xi) For AWL No. 47-AWL-05, ``Nitrogen Generation System (NGS)--
Nitrogen Enriched Air (NEA) Distribution Ducting Integrity'': Within 
14,500 flight hours after accomplishment of the actions specified in 
Boeing Service Bulletin 737-47-1005; within 14,500 flight hours 
after accomplishment of the actions specified in Boeing Service 
Bulletin 737-47-1008; or within 14,500 flight hours after the most 
recent inspection was performed as specified in AWL No. 47-AWL-05; 
whichever is latest.

(h) Additional Acceptable Wire Types and Sleeving

    As an option, when accomplishing the actions required by 
paragraph (g) of this AD, the changes specified in paragraphs (h)(1) 
and (h)(2) of this AD are acceptable.
    (1) Where AWL No. 28-AWL-05 identifies wire types BMS 13-48, BMS 
13-58, and BMS 13-60, the following wire types are acceptable: MIL-
W-22759/16, SAE AS22759/16 (M22759/16), MIL-W-22759/32, SAE AS22759/
32 (M22759/32), MIL-W-22759/34, SAE AS22759/34 (M22759/34), MIL-W-
22759/41, SAE AS22759/41 (M22759/41), MIL-W-22759/86, SAE AS22759/86 
(M22759/86), MIL-W-22759/87, SAE AS22759/87 (M22759/87), MIL-W-
22759/92, and SAE AS22759/92 (M22759/92); and MIL-C-27500 and NEMA 
WC 27500 cables constructed from these military or SAE specification 
wire types, as applicable.
    (2) Where AWL No. 28-AWL-05 identifies TFE-2X Standard wall for 
wire sleeving, the following sleeving materials are acceptable: 
Roundit 2000NX and Varglas Type HO, HP, or HM.

(i) No Alternative Actions, Intervals, or Critical Design Configuration 
Control Limitations (CDCCLs)

    After the existing maintenance or inspection program has been 
revised as required by paragraph (g) of this AD, no alternative 
actions (e.g., inspections), intervals, or CDCCLs may be used unless 
the actions, intervals, and CDCCLs are approved as an alternative 
method of compliance (AMOC) in accordance with the procedures 
specified in paragraph (k) of this AD.

(j) Terminating Actions for Certain AD Requirements

    Accomplishment of the revision required by paragraph (g) of this 
AD terminates the requirements specified in paragraphs (j)(1) 
through (j)(6) of this AD for that airplane:
    (1) All requirements of AD 2008-10-09 R1.
    (2) The revision required by paragraph (l) of AD 2011-12-09.
    (3) The revision required by paragraph (h) of AD 2013-13-15.
    (4) The revision required by paragraph (j) of AD 2013-25-05.
    (5) The revisions required by paragraphs (l) and (n) of AD 2016-
18-16.
    (6) The revision required by paragraph (h) of AD 2017-17-09.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of 
the person identified in paragraph (l)(2) of this AD. Information 
may be emailed to: [email protected].
    (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 Branch, FAA, 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.

(l) Related Information

    (1) For more information about this AD, contact Jeffrey Rothman, 
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3558; email: [email protected].
    (2) For information about AMOCs, contact Serj Harutunian, 
Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5254; fax: 562-627-5210; email: [email protected].
    (3) For 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; phone: 562-797-1717; internet: https://www.myboeingfleet.com. 
You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.

    Issued in Des Moines, Washington, on May 20, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-11925 Filed 6-7-19; 8:45 am]
 BILLING CODE 4910-13-P