Airworthiness Directives; The Boeing Company Airplanes, 27718-27721 [2018-12656]

Download as PDF 27718 Proposed Rules Federal Register Vol. 83, No. 115 Thursday, June 14, 2018 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0510; Product Identifier 2017–NM–115–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2016–04– 16, which applies to all The Boeing Company Model DC–10–10, DC–10– 10F, DC–10–15, DC–10–30, DC–10–30F (KC–10A and KDC–10), DC–10–40, DC– 10–40F, MD–10–10F, MD–10–30F, MD– 11, and MD–11F airplanes. AD 2016– 04–16 requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. Since we issued AD 2016–04–16, we have received new service information that would eliminate the need for certain provisions of AD 2016–04–16. This proposed AD would provide optional terminating action for certain requirements. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 30, 2018. 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 http://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 daltland on DSKBBV9HB2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:14 Jun 13, 2018 Jkt 244001 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; telephone: 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. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0510. 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–2018– 0510; 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 in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION 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. 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– 2018–0510; Product Identifier 2017– NM–115–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 http:// PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2016–04–16, Amendment 39–18410 (81 FR 12806, March 11, 2016) (‘‘AD 2016–04–16’’), for all The Boeing Company Model DC–10– 10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC–10A and KDC–10), DC– 10–40, DC–10–40F, MD–10–10F, MD– 10–30F, MD–11, and MD–11F airplanes. AD 2016–04–16 requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. AD 2016–04–16 resulted from a determination that it is necessary to clarify the requirements for the design features and to remove a terminating action for certain inspections. We issued AD 2016–04–16 to reduce 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. Actions Since AD 2016–04–16 Was Issued Since we issued AD 2016–04–16, we have received new service information that would eliminate the need for certain provisions of AD 2016–04–16. Related Service Information Under 1 CFR Part 51 We reviewed the following Boeing service information. • Boeing Alert Service Bulletin DC10–28A253, dated June 5, 2014; and Boeing Alert Service Bulletin MD11– 28A133, dated June 5, 2014. This service information describes procedures for replacing the fuel pump control relays with fault current detectors and changing the fuel tank boost/transfer pump wire termination. These documents are distinct since they apply to different airplane models. • Boeing Service Bulletin DC10–28– 256, dated June 24, 2014; and Boeing Service Bulletin MD11–28–137, dated June 24, 2014. This service information describes procedures for changing the fuel pump control and indication system wiring. These documents are distinct since they apply to different airplane models. • Boeing Trijet Special Compliance Item Report MDC–02K1003, Revision M, E:\FR\FM\14JNP1.SGM 14JNP1 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules including Appendices A through D, dated July 25, 2014, which includes Critical Design Configuration Control Limitations (CDCCLs), Airworthiness Limitation Instructions (ALIs), and short-term extensions in Appendices B, C, and D, respectively. The service information describes fuel ALIs that address ignition sources. • Boeing Service Bulletin DC10–28– 264, dated May 15, 2015, or Boeing Service Bulletin MD11–28–146, dated May 15, 2015. This service information describes procedures for replacement of the fuel pump housing electrical connector, associated wires, fuel tank feed-through components, and installing sealed terminal lugs on the fuel pump wiring, or replacement of the fuel pump housing, associated wires, fuel tank feed-through components, and installing sealed terminal lugs on the fuel pump. These documents are distinct since they apply to different airplane models. 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 these same type designs. Proposed AD Requirements This proposed AD would retain all requirements of AD 2016–04–16. Specifically, this proposed AD would retain the repetitive inspections for proper operation of the fuel pump, and applicable corrective actions. This proposed AD would also eliminate the need for the provisions in paragraph (j) of this proposed AD by providing optional terminating action for the requirements of paragraph (a) of AD 2002–13–10, Amendment 39–12798 (67 FR 45053, July 8, 2002); paragraph (a) of AD 2003–07–14, Amendment 39– 13110 (68 FR 17544, April 10, 2003); and paragraph (j) of AD 2011–11–05, Amendment 39–16704 (76 FR 31462, June 1, 2011). This proposed AD specifies to revise certain operator maintenance documents to include new actions (e.g., 27719 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 (l) of this proposed AD. The request should include a description of changes to the required actions and CDCCLs that will ensure the continued operational safety of the airplane. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0510. Costs of Compliance We estimate that this proposed AD affects 341 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Cost per product Parts cost Cost on U.S. operators Action Labor cost Installing design features using a method approved by the FAA (retained actions from AD 2016–04–16). Installing design features using service information (retained actions from AD 2016– 04–16). 152 work-hours × $85 per hour = $12,920 .... $137,500 $150,420 $51,293,220 98 work-hours × $85 per hour = $8,330 ........ 109,000 117,330 40,009,530 Inspection for proper operation (new proposed action). Up to 130 work-hours × $85 per hour = $11,050 per inspection cycle. 0 Up to $11,050 per inspection cycle. ESTIMATED COSTS FOR OPTIONAL TERMINATING ACTIONS Action Labor cost Option 1: Replace connectors for Model DC–10 and MD–10 (122 airplanes). Option 1: Replace connectors for Model MD–11 (124 airplanes) ......... daltland on DSKBBV9HB2PROD with PROPOSALS Option 2: Replace fuel pump housings for Model DC–10 and MD–10 (122 airplanes). Option 2: Replace fuel pump housings for Model MD–11 (124 airplanes). We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed 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 VerDate Sep<11>2014 16:14 Jun 13, 2018 Jkt 244001 68 work-hours × $85 $5,780. 59 work-hours × $85 $5,015. Up to 81 work-hours hour = $6,885. Up to 77 work-hours hour = $6,545. 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Parts cost Cost per product per hour = $54,842 ............ $60,622. per hour = $67,031 ............ $72,046. × $85 per Up to $54,842 .. Up to $61,727. × $85 per Up to $67,031 .. Up to $73,576. 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. E:\FR\FM\14JNP1.SGM 14JNP1 27720 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 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 have 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 that the 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 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. daltland on DSKBBV9HB2PROD with PROPOSALS § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2016–04–16, Amendment 39–18410 (81 FR 12806, March 11, 2016), and adding the following new AD: ■ The Boeing Company: Docket No. FAA– 2018–0510; Product Identifier 2017– NM–115–AD. VerDate Sep<11>2014 16:14 Jun 13, 2018 Jkt 244001 (a) Comments Due Date The FAA must receive comments on this AD action by July 30, 2018. (b) Affected ADs (1) This AD replaces AD 2016–04–16, Amendment 39–18410 (81 FR 12806, March 11, 2016) (‘‘AD 2016–04–16’’). (2) This AD affects AD 2002–13–10, Amendment 39–12798 (67 FR 45053, July 8, 2002) (‘‘AD 2002–13–10’’). (3) This AD affects AD 2003–07–14, Amendment 39–13110 (68 FR 17544, April 10, 2003) (‘‘AD 2003–07–14’’). (4) This AD affects AD 2008–06–21 R1, Amendment 39–16100 (74 FR 61504, November 25, 2009) (‘‘AD 2008–06–21 R1’’). (5) This AD affects AD 2011–11–05, Amendment 39–16704 (76 FR 31462, June 1, 2011) (‘‘AD 2011–11–05’’). (c) Applicability This AD applies to all The Boeing Company airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Model DC–10–10, DC–10–10F, DC–10– 15, DC–10–30, DC–10–30F (KC–10A and KDC–10), DC–10–40, and DC–10–40F airplanes. (2) Model MD–10–10F, MD–10–30F, MD– 11, and MD–11F airplanes. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Unsafe Condition This AD was prompted by a fuel system review conducted by the manufacturer. We are issuing this AD to reduce 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) Restatement of Paragraph (g) of AD 2016– 04–16, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2016–04–16, with no changes. Except as provided by paragraph (h) of this AD: As of 48 months after April 15, 2016 (the effective date of AD 2016–04–16), no person may operate any airplane affected by this AD unless an amended type certificate or supplemental type certificate that incorporates the design features and requirements described in paragraphs (g)(1) through (g)(4) of this AD has been approved by the Manager, Los Angeles ACO Branch, FAA, and those design features are installed on the airplane to meet the criteria specified in section 25.981(a) and (d) of the Federal Aviation Regulations (14 CFR 25.981(a) and (d), at Amendment 25–125 (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/ rgFAR.nsf/0/339DAEE3E0A6379D86257 4CF00641951?OpenDocument)). For airplanes on which Boeing-installed auxiliary fuel tanks are removed, the actions specified in this AD for the auxiliary fuel tanks are not required. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 (1) For all airplanes: Each electrically powered alternating current (AC) fuel pump installed in any fuel tank that normally empties during flight and each pump that is partially covered by a lowering fuel level— such as main tanks, center wing tanks, auxiliary fuel tanks installed by the airplane manufacturer, and tail tanks—must have a protective device installed to detect electrical faults that can cause arcing and burn through of the fuel pump housing and pump electrical connector. The same device must shut off the pump by automatically removing electrical power from the pump when such faults are detected. When a fuel pump is shut off resulting from detection of an electrical fault, the device must stay latched off, until the fault is cleared through maintenance action and the pump is verified safe for operation. (2) For airplanes with a 2-person flightcrew: Additional design features, if not originally installed by the airplane manufacturer, must be installed to meet 3 criteria: To detect a running fuel pump in a tank that is normally emptied during flight, to provide an indication to the flightcrew that the tank is empty, and to automatically shut off that fuel pump. The prospective pump indication and shutoff system must automatically shut off each pump in case the flightcrew does not shut off a pump running dry in an empty tank within 60 seconds after each fuel tank is emptied. An airplane flight manual supplement (AFMS) that includes flightcrew manual pump shutoff procedures in the Limitations section of the AFMS must be submitted to the Los Angeles ACO Branch, FAA, for approval. (3) For airplanes with a 3-person flightcrew: Additional design features, if not originally installed by the airplane manufacturer, must be installed to detect when a fuel pump in a tank that is normally emptied during flight is running in an empty fuel tank, and to provide an indication to the flightcrew that the tank is empty. The flight engineer must manually shut off each pump running dry in an empty tank within 60 seconds after the tank is emptied. The AFMS Limitations section must be revised to specify that this pump shutoff must be done by the flight engineer. (4) For all airplanes with tanks that normally empty during flight: Separate means must be provided to detect and shut off a pump that was previously commanded to be shut off automatically or manually but remained running in an empty tank during flight. (h) Restatement of Paragraph (h) of AD 2016–04–16, With No Changes This paragraph restates the provisions of paragraph (h) of AD 2016–04–16, with no changes. In lieu of doing the requirements of paragraph (g) of this AD, do the applicable actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) For MD–11 and MD–11F airplanes: Do the actions specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. (i) As of 48 months after April 15, 2016 (the effective date of AD 2016–04–16), change the fuel pump control and indication system wiring, in accordance with the E:\FR\FM\14JNP1.SGM 14JNP1 daltland on DSKBBV9HB2PROD with PROPOSALS Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules Accomplishment Instructions of Boeing Service Bulletin MD11–28–137, dated June 24, 2014. (ii) Prior to or concurrently with accomplishing the actions specified in paragraph (h)(1)(i) of this AD: Replace the fuel pump control relays with fault current detectors, and change the fuel tank boost/ transfer pump wire termination, in accordance with Accomplishment Instructions of Boeing Alert Service Bulletin MD11–28A133, dated June 5, 2014. (2) For Model DC–10–10, DC–10–10F, DC– 10–15, DC–10–30, DC–10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD–10– 10F, and MD–10–30F airplanes: Do the actions specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) As of 48 months after April 15, 2016 (the effective date of AD 2016–04–16), change the fuel pump control and indication system wiring, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–28–256, dated June 24, 2014. (ii) Prior to or concurrently with accomplishing the actions specified in paragraph (h)(2)(i) of this AD: Replace the fuel pump control relays with fault current detectors, and change the fuel tank boost/ transfer pump wire termination, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10–28A253, dated June 5, 2014. (3) For all airplanes: Within 30 days after accomplishing the actions required by paragraph (h)(1) or (h)(2) of this AD, or within 30 days after April 15, 2016 (the effective date of AD 2016–04–16), whichever occurs later, revise the maintenance or inspection program, as applicable, to incorporate the Critical Design Configuration Control Limitations (CDCCLs), Airworthiness Limitation Instructions (ALIs), and shortterm extensions specified in Appendices B, C, and D of Boeing Trijet Special Compliance Item (SCI) Report MDC–02K1003, Revision M, dated July 25, 2014. The initial compliance time for accomplishing the actions specified in the ALIs is at the later of the times specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. Revising the maintenance or inspection program required by this paragraph terminates the requirements in paragraphs (g) and (h) of AD 2008–06–21 R1. (i) At the applicable time specified in Appendix C of Boeing Trijet SCI Report MDC–02K1003, Revision M, dated July 25, 2014, except as provided by Appendix D of Boeing Trijet SCI Report MDC–02K1003, Revision M, dated July 25, 2014. (ii) Within 30 days after accomplishing the actions required by paragraph (h)(1) or (h)(2) of this AD, as applicable; or within 30 days after April 15, 2016 (the effective date of AD 2016–04–16); whichever occurs later. (i) Restatement of Paragraph (i) of AD 2016– 04–16, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2016–04–16, with no changes. If the option in paragraph (h)(3) of this AD is accomplished: After the maintenance or inspection program has been revised as provided by paragraph (h)(3) of VerDate Sep<11>2014 16:14 Jun 13, 2018 Jkt 244001 this AD, no alternative actions (e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals, or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (l) of this AD. (j) Restatement of Paragraph (j) of AD 2016– 04–16, With Additional AD Reference and Clarification of Provisions This paragraph restates the provisions of paragraph (j) of AD 2016–04–16, with an additional AD reference and clarification of the provisions. Accomplishment of the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as applicable, extends the 18-month interval for the repetitive inspections and tests required by paragraph (a) of AD 2002–13–10; the 18-month interval for the repetitive inspections required by paragraph (a) of AD 2003–07–14; and the 18month interval for the repetitive inspections required by paragraph (j) of AD 2011–11–05; to 24-month intervals for pumps affected by those ADs, regardless if the pump is installed in a tank that normally empties, provided the remaining actions required by those three ADs have been accomplished. (k) New Provision of This AD: Optional Terminating Action Replacing the electrical connectors or fuel pump housing in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–28–264, dated May 15, 2015; or Boeing Service Bulletin MD11– 28–146, dated May 15, 2015, as applicable; terminates the repetitive inspections and tests required by paragraph (a) of AD 2002– 13–10, paragraph (a) of AD 2003–07–14, and paragraph (j) of AD 2011–11–05. (l) 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 (m)(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 Branch, 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) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 27721 paragraphs (l)(4)(i) and (l)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (m) Related Information (1) For more information about this AD, 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. (2) 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; telephone: 562–797–1717; internet: https:// www.myboeingfleet.com. You may view this referenced 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 June 6, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–12656 Filed 6–13–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0511; Product Identifier 2017–NM–145–AD] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model 4101 airplanes. This proposed AD was prompted by a determination that SUMMARY: E:\FR\FM\14JNP1.SGM 14JNP1

Agencies

[Federal Register Volume 83, Number 115 (Thursday, June 14, 2018)]
[Proposed Rules]
[Pages 27718-27721]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-12656]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / 
Proposed Rules

[[Page 27718]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0510; Product Identifier 2017-NM-115-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-04-
16, which applies to all The Boeing Company Model DC-10-10, DC-10-10F, 
DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, 
MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. AD 2016-04-16 
requires adding design features to detect electrical faults and to 
detect a pump running in an empty fuel tank. Since we issued AD 2016-
04-16, we have received new service information that would eliminate 
the need for certain provisions of AD 2016-04-16. This proposed AD 
would provide optional terminating action for certain requirements. We 
are proposing this AD to address the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by July 30, 2018.

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 http://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; 
telephone: 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. It is also 
available on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2018-0510.

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-2018-
0510; 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 in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION 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].

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-2018-0510; 
Product Identifier 2017-NM-115-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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 2016-04-16, Amendment 39-18410 (81 FR 12806, March 11, 
2016) (``AD 2016-04-16''), for all The Boeing Company Model DC-10-10, 
DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, 
DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. AD 2016-
04-16 requires adding design features to detect electrical faults and 
to detect a pump running in an empty fuel tank. AD 2016-04-16 resulted 
from a determination that it is necessary to clarify the requirements 
for the design features and to remove a terminating action for certain 
inspections. We issued AD 2016-04-16 to reduce 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.

Actions Since AD 2016-04-16 Was Issued

    Since we issued AD 2016-04-16, we have received new service 
information that would eliminate the need for certain provisions of AD 
2016-04-16.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Boeing service information.
     Boeing Alert Service Bulletin DC10-28A253, dated June 5, 
2014; and Boeing Alert Service Bulletin MD11-28A133, dated June 5, 
2014. This service information describes procedures for replacing the 
fuel pump control relays with fault current detectors and changing the 
fuel tank boost/transfer pump wire termination. These documents are 
distinct since they apply to different airplane models.
     Boeing Service Bulletin DC10-28-256, dated June 24, 2014; 
and Boeing Service Bulletin MD11-28-137, dated June 24, 2014. This 
service information describes procedures for changing the fuel pump 
control and indication system wiring. These documents are distinct 
since they apply to different airplane models.
     Boeing Trijet Special Compliance Item Report MDC-02K1003, 
Revision M,

[[Page 27719]]

including Appendices A through D, dated July 25, 2014, which includes 
Critical Design Configuration Control Limitations (CDCCLs), 
Airworthiness Limitation Instructions (ALIs), and short-term extensions 
in Appendices B, C, and D, respectively. The service information 
describes fuel ALIs that address ignition sources.
     Boeing Service Bulletin DC10-28-264, dated May 15, 2015, 
or Boeing Service Bulletin MD11-28-146, dated May 15, 2015. This 
service information describes procedures for replacement of the fuel 
pump housing electrical connector, associated wires, fuel tank feed-
through components, and installing sealed terminal lugs on the fuel 
pump wiring, or replacement of the fuel pump housing, associated wires, 
fuel tank feed-through components, and installing sealed terminal lugs 
on the fuel pump. These documents are distinct since they apply to 
different airplane models.
    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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2016-04-16. 
Specifically, this proposed AD would retain the repetitive inspections 
for proper operation of the fuel pump, and applicable corrective 
actions.
    This proposed AD would also eliminate the need for the provisions 
in paragraph (j) of this proposed AD by providing optional terminating 
action for the requirements of paragraph (a) of AD 2002-13-10, 
Amendment 39-12798 (67 FR 45053, July 8, 2002); paragraph (a) of AD 
2003-07-14, Amendment 39-13110 (68 FR 17544, April 10, 2003); and 
paragraph (j) of AD 2011-11-05, Amendment 39-16704 (76 FR 31462, June 
1, 2011).
    This proposed AD specifies to revise 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 (l) of this proposed AD. The request should include a 
description of changes to the required actions and CDCCLs that will 
ensure the continued operational safety of the airplane. For 
information on the procedures and compliance times, see this service 
information at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2018-0510.

Costs of Compliance

    We estimate that this proposed AD affects 341 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Installing design features using a   152 work-hours x $85 per           $137,500        $150,420     $51,293,220
 method approved by the FAA           hour = $12,920.
 (retained actions from AD 2016-04-
 16).
Installing design features using     98 work-hours x $85 per             109,000         117,330      40,009,530
 service information (retained        hour = $8,330.
 actions from AD 2016-04-16).
                                                                 -----------------------------------------------
Inspection for proper operation      Up to 130 work-hours x $85                0   Up to $11,050 per inspection
 (new proposed action).               per hour = $11,050 per                                  cycle.
                                      inspection cycle.
----------------------------------------------------------------------------------------------------------------


                                Estimated Costs for Optional Terminating Actions
----------------------------------------------------------------------------------------------------------------
              Action                      Labor cost               Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Option 1: Replace connectors for    68 work-hours x $85    $54,842...................  $60,622.
 Model DC-10 and MD-10 (122          per hour = $5,780.
 airplanes).
Option 1: Replace connectors for    59 work-hours x $85    $67,031...................  $72,046.
 Model MD-11 (124 airplanes).        per hour = $5,015.
Option 2: Replace fuel pump         Up to 81 work-hours x  Up to $54,842.............  Up to $61,727.
 housings for Model DC-10 and MD-    $85 per hour =
 10 (122 airplanes).                 $6,885.
Option 2: Replace fuel pump         Up to 77 work-hours x  Up to $67,031.............  Up to $73,576.
 housings for Model MD-11 (124       $85 per hour =
 airplanes).                         $6,545.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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.

[[Page 27720]]

    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 have 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 that the 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 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 removing Airworthiness Directive (AD) 
2016-04-16, Amendment 39-18410 (81 FR 12806, March 11, 2016), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2018-0510; Product Identifier 
2017-NM-115-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by July 30, 
2018.

(b) Affected ADs

    (1) This AD replaces AD 2016-04-16, Amendment 39-18410 (81 FR 
12806, March 11, 2016) (``AD 2016-04-16'').
    (2) This AD affects AD 2002-13-10, Amendment 39-12798 (67 FR 
45053, July 8, 2002) (``AD 2002-13-10'').
    (3) This AD affects AD 2003-07-14, Amendment 39-13110 (68 FR 
17544, April 10, 2003) (``AD 2003-07-14'').
    (4) This AD affects AD 2008-06-21 R1, Amendment 39-16100 (74 FR 
61504, November 25, 2009) (``AD 2008-06-21 R1'').
    (5) This AD affects AD 2011-11-05, Amendment 39-16704 (76 FR 
31462, June 1, 2011) (``AD 2011-11-05'').

(c) Applicability

    This AD applies to all The Boeing Company airplanes identified 
in paragraphs (c)(1) and (c)(2) of this AD, certificated in any 
category.
    (1) Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F 
(KC-10A and KDC-10), DC-10-40, and DC-10-40F airplanes.
    (2) Model MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

(e) Unsafe Condition

    This AD was prompted by a fuel system review conducted by the 
manufacturer. We are issuing this AD to reduce 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) Restatement of Paragraph (g) of AD 2016-04-16, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2016-04-16, with no changes. Except as provided by paragraph (h) of 
this AD: As of 48 months after April 15, 2016 (the effective date of 
AD 2016-04-16), no person may operate any airplane affected by this 
AD unless an amended type certificate or supplemental type 
certificate that incorporates the design features and requirements 
described in paragraphs (g)(1) through (g)(4) of this AD has been 
approved by the Manager, Los Angeles ACO Branch, FAA, and those 
design features are installed on the airplane to meet the criteria 
specified in section 25.981(a) and (d) of the Federal Aviation 
Regulations (14 CFR 25.981(a) and (d), at Amendment 25-125 (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgFAR.nsf/0/339DAEE3E0A6379D862574CF00641951?OpenDocument)). For airplanes on 
which Boeing-installed auxiliary fuel tanks are removed, the actions 
specified in this AD for the auxiliary fuel tanks are not required.
    (1) For all airplanes: Each electrically powered alternating 
current (AC) fuel pump installed in any fuel tank that normally 
empties during flight and each pump that is partially covered by a 
lowering fuel level--such as main tanks, center wing tanks, 
auxiliary fuel tanks installed by the airplane manufacturer, and 
tail tanks--must have a protective device installed to detect 
electrical faults that can cause arcing and burn through of the fuel 
pump housing and pump electrical connector. The same device must 
shut off the pump by automatically removing electrical power from 
the pump when such faults are detected. When a fuel pump is shut off 
resulting from detection of an electrical fault, the device must 
stay latched off, until the fault is cleared through maintenance 
action and the pump is verified safe for operation.
    (2) For airplanes with a 2-person flightcrew: Additional design 
features, if not originally installed by the airplane manufacturer, 
must be installed to meet 3 criteria: To detect a running fuel pump 
in a tank that is normally emptied during flight, to provide an 
indication to the flightcrew that the tank is empty, and to 
automatically shut off that fuel pump. The prospective pump 
indication and shutoff system must automatically shut off each pump 
in case the flightcrew does not shut off a pump running dry in an 
empty tank within 60 seconds after each fuel tank is emptied. An 
airplane flight manual supplement (AFMS) that includes flightcrew 
manual pump shutoff procedures in the Limitations section of the 
AFMS must be submitted to the Los Angeles ACO Branch, FAA, for 
approval.
    (3) For airplanes with a 3-person flightcrew: Additional design 
features, if not originally installed by the airplane manufacturer, 
must be installed to detect when a fuel pump in a tank that is 
normally emptied during flight is running in an empty fuel tank, and 
to provide an indication to the flightcrew that the tank is empty. 
The flight engineer must manually shut off each pump running dry in 
an empty tank within 60 seconds after the tank is emptied. The AFMS 
Limitations section must be revised to specify that this pump 
shutoff must be done by the flight engineer.
    (4) For all airplanes with tanks that normally empty during 
flight: Separate means must be provided to detect and shut off a 
pump that was previously commanded to be shut off automatically or 
manually but remained running in an empty tank during flight.

(h) Restatement of Paragraph (h) of AD 2016-04-16, With No Changes

    This paragraph restates the provisions of paragraph (h) of AD 
2016-04-16, with no changes. In lieu of doing the requirements of 
paragraph (g) of this AD, do the applicable actions specified in 
paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
    (1) For MD-11 and MD-11F airplanes: Do the actions specified in 
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
    (i) As of 48 months after April 15, 2016 (the effective date of 
AD 2016-04-16), change the fuel pump control and indication system 
wiring, in accordance with the

[[Page 27721]]

Accomplishment Instructions of Boeing Service Bulletin MD11-28-137, 
dated June 24, 2014.
    (ii) Prior to or concurrently with accomplishing the actions 
specified in paragraph (h)(1)(i) of this AD: Replace the fuel pump 
control relays with fault current detectors, and change the fuel 
tank boost/transfer pump wire termination, in accordance with 
Accomplishment Instructions of Boeing Alert Service Bulletin MD11-
28A133, dated June 5, 2014.
    (2) For Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F 
(KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F 
airplanes: Do the actions specified in paragraphs (h)(2)(i) and 
(h)(2)(ii) of this AD.
    (i) As of 48 months after April 15, 2016 (the effective date of 
AD 2016-04-16), change the fuel pump control and indication system 
wiring, in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin DC10-28-256, dated June 24, 2014.
    (ii) Prior to or concurrently with accomplishing the actions 
specified in paragraph (h)(2)(i) of this AD: Replace the fuel pump 
control relays with fault current detectors, and change the fuel 
tank boost/transfer pump wire termination, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC10-
28A253, dated June 5, 2014.
    (3) For all airplanes: Within 30 days after accomplishing the 
actions required by paragraph (h)(1) or (h)(2) of this AD, or within 
30 days after April 15, 2016 (the effective date of AD 2016-04-16), 
whichever occurs later, revise the maintenance or inspection 
program, as applicable, to incorporate the Critical Design 
Configuration Control Limitations (CDCCLs), Airworthiness Limitation 
Instructions (ALIs), and short-term extensions specified in 
Appendices B, C, and D of Boeing Trijet Special Compliance Item 
(SCI) Report MDC-02K1003, Revision M, dated July 25, 2014. The 
initial compliance time for accomplishing the actions specified in 
the ALIs is at the later of the times specified in paragraphs 
(h)(3)(i) and (h)(3)(ii) of this AD. Revising the maintenance or 
inspection program required by this paragraph terminates the 
requirements in paragraphs (g) and (h) of AD 2008-06-21 R1.
    (i) At the applicable time specified in Appendix C of Boeing 
Trijet SCI Report MDC-02K1003, Revision M, dated July 25, 2014, 
except as provided by Appendix D of Boeing Trijet SCI Report MDC-
02K1003, Revision M, dated July 25, 2014.
    (ii) Within 30 days after accomplishing the actions required by 
paragraph (h)(1) or (h)(2) of this AD, as applicable; or within 30 
days after April 15, 2016 (the effective date of AD 2016-04-16); 
whichever occurs later.

(i) Restatement of Paragraph (i) of AD 2016-04-16, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2016-04-16, with no changes. If the option in paragraph (h)(3) of 
this AD is accomplished: After the maintenance or inspection program 
has been revised as provided by paragraph (h)(3) of this AD, no 
alternative actions (e.g., inspections), intervals, or CDCCLs may be 
used unless the actions, intervals, or CDCCLs are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (l) of this AD.

(j) Restatement of Paragraph (j) of AD 2016-04-16, With Additional AD 
Reference and Clarification of Provisions

    This paragraph restates the provisions of paragraph (j) of AD 
2016-04-16, with an additional AD reference and clarification of the 
provisions. Accomplishment of the actions specified in paragraphs 
(h)(1), (h)(2), and (h)(3) of this AD, as applicable, extends the 
18-month interval for the repetitive inspections and tests required 
by paragraph (a) of AD 2002-13-10; the 18-month interval for the 
repetitive inspections required by paragraph (a) of AD 2003-07-14; 
and the 18-month interval for the repetitive inspections required by 
paragraph (j) of AD 2011-11-05; to 24-month intervals for pumps 
affected by those ADs, regardless if the pump is installed in a tank 
that normally empties, provided the remaining actions required by 
those three ADs have been accomplished.

(k) New Provision of This AD: Optional Terminating Action

    Replacing the electrical connectors or fuel pump housing in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin DC10-28-264, dated May 15, 2015; or Boeing Service Bulletin 
MD11-28-146, dated May 15, 2015, as applicable; terminates the 
repetitive inspections and tests required by paragraph (a) of AD 
2002-13-10, paragraph (a) of AD 2003-07-14, and paragraph (j) of AD 
2011-11-05.

(l) 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 (m)(1) 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, 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) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(l)(4)(i) and (l)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(m) Related Information

    (1) For more information about this AD, 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].
    (2) 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; telephone: 562-797-1717; internet: https://www.myboeingfleet.com. You may view this referenced 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 June 6, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-12656 Filed 6-13-18; 8:45 am]
 BILLING CODE 4910-13-P