Airworthiness Directives; The Boeing Company Airplanes, 55610-55614 [2018-23822]

Download as PDF 55610 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0510; Product Identifier 2017–NM–115–AD; Amendment 39–19483; AD 2018–22–10] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2016–04– 16, which applied 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 required adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. This AD continues to require adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. This AD also provides optional terminating action for certain requirements. This AD was prompted by a fuel system review conducted by the manufacturer. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective December 12, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 12, 2018. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of April 15, 2016 (81 FR 12806, March 11, 2016). ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone: 562–797–1717; internet: https://www.myboeingfleet.com. You may view this 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 https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0510. amozie on DSK3GDR082PROD with RULES DATES: VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 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–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 final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is Docket Operations, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2016–04–16, Amendment 39–18410 (81 FR 12806, March 11, 2016) (‘‘AD 2016–04–16’’). AD 2016–04–16 applied 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. The NPRM published in the Federal Register on June 14, 2018 (83 FR 27718). The NPRM was prompted by a fuel system review conducted by the manufacturer and a determination that accomplishing new service information in conjunction with certain service information specified in AD 2016–04– 16 would terminate certain actions in related ADs. The NPRM proposed to continue to require adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. The NPRM also proposed to provide optional terminating action for certain requirements. 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. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Support for the NPRM FedEx Express (FedEx) and Air Line Pilots Association, International (ALPA) provided their concurrence with the NPRM. FedEx also pointed out that the NPRM affects 39 Model MD–10 airplanes and 57 Model MD–11 airplanes in the FedEx fleet. Request To Clarify the Terminating Action Specified in Paragraph (k) of the Proposed AD Boeing requested that we clarify the terminating action specified in paragraph (k) of the proposed AD. Boeing agreed that the repetitive inspections and tests may be terminated upon installation of the new connector design per the Boeing service bulletins cited in paragraph (k) of the proposed AD (Boeing Service Bulletin DC10–28– 264, dated May 15, 2015; and Boeing Service Bulletin MD11–28–146, dated May 15, 2015). Boeing noted that those service bulletins were approved by the Manager, Los Angeles ACO Branch. Boeing added that those service bulletins also specify an additional condition for the terminating actions: the fault current detectors cited in paragraphs (h)(1)(ii) and (h)(2)(ii) of the proposed AD must also be installed before the repetitive actions are terminated. Boeing recommended that paragraph (k) of the proposed AD be revised to clarify that the fault current detectors must be installed per paragraphs (h)(1)(ii) and (h)(2)(ii) of the proposed AD in order to accomplish the terminating action per the Boeing service bulletins cited in paragraph (k) of the proposed AD. We agree with the commenter’s request. Paragraph F., ‘‘Approval,’’ of Boeing Service Bulletin DC10–28–264, dated May 15, 2015; and Boeing Service Bulletin MD11–28–146, dated May 15, 2015, specifies that the actions in those service bulletins as well as the service bulletins specified in paragraphs (h)(1)(ii) and (h)(2)(ii) of this AD terminate the actions required by paragraph (a) of AD 2002–13–10, Amendment 39–12798 (67 FR 45053, July 8, 2002) (‘‘AD 2002–13–10’’), paragraph (a) of AD 2003–07–14, Amendment 39–13110 (68 FR 17544, April 10, 2003) (‘‘AD 2003–07–14’’), and paragraph (j) of AD 2011–11–05, Amendment 39–16704 (76 FR 31462, June 1, 2011) (‘‘AD 2011–11–05’’). We have revised paragraph (k) of this AD accordingly. Request To Withdraw the NPRM United Parcel Service (UPS) requested that we withdraw the NPRM. UPS pointed out that the NPRM includes no E:\FR\FM\07NOR1.SGM 07NOR1 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations new requirements or information. UPS indicated that no new requirements or actions would create an undue burden on operators because existing internal paperwork and records must then be revised to provide proof of compliance. We acknowledge the commenter’s concerns; however, we disagree with the request to withdraw the NPRM. AD 2003–07–14 was affected by AD 2016– 04–16 but was inadvertently left out of AD 2016–04–16. This AD corrects that oversight and includes AD 2003–07–14 as an affected AD. Additionally, this AD provides new optional terminating actions that affect AD 2003–07–14 as well as AD 2002–13–10 and AD 2011– 11–05. Request To Include Updated Service Information UPS requested that we revise the NPRM to include a later revision of Boeing Trijet Special Compliance Item Report MDC–02K1003. UPS pointed out that the new fuel pump housing assembly that is created by installation of the new connectors was not added until Revision N of Boeing Trijet Special Compliance Item Report MDC–02K1003. Additionally, UPS mentioned that Revision R of Boeing Trijet Special Compliance Item Report MDC–02K1003 was in the approval process at the time the comment was submitted. We agree with the request to include the latest published version of Boeing Trijet Special Compliance Item Report MDC–02K1003. We referred to Boeing Trijet Special Compliance Item Report MDC–02K1003, Revision M, including Appendices A through D, dated July 25, 2014, as an appropriate source of service information in the NPRM. Revision R of Boeing Trijet Special Compliance Item Report MDC–02K1003, including Appendices A through D, dated May 9, 2018, includes new part numbers for Critical Design Configuration Control Limitation (CDCCL) 28–2 and updates certain special compliance items to include additional procedures for airplanes with a certain configuration. We have added paragraph (l) to this AD to include Revision R of Boeing Trijet Special Compliance Item Report MDC– 02K1003, including Appendices B through D, dated May 9, 2018, as an optional revision to paragraph (h)(3) of this AD, and we have redesignated subsequent paragraphs accordingly. We are considering further rulemaking to require revising the maintenance or inspection program to include Revision R of Boeing Trijet Special Compliance Item Report MDC–02K1003, including Appendices B through D, dated May 9, 2018. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed 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. 55611 • 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, including Appendices A through D, dated July 25, 2014; and Boeing Trijet Special Compliance Item Report MDC– 02K1003, Revision R, including Appendices A through D, dated May 9, 2018; which include CDCCLs, ALIs, and short-term extensions in Appendices B, C, and D, respectively. This service information describes fuel ALIs that address ignition sources. These documents are distinct since Revision R includes additional requirements. • Boeing Service Bulletin DC10–28– 264, dated May 15, 2015, and 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. Costs of Compliance We estimate that this AD affects 341 airplanes of U.S. registry. We estimate the following costs to comply with this AD: amozie on DSK3GDR082PROD with RULES ESTIMATED COSTS FOR REQUIRED ACTIONS Cost on U.S. operators 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 optional 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. VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Parts cost Cost per product Action E:\FR\FM\07NOR1.SGM 07NOR1 55612 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations ESTIMATED COSTS FOR OPTIONAL TERMINATING ACTIONS Labor cost Parts cost Option 1: Replace connectors for Model DC–10 and MD–10 (122 airplanes). Option 1: Replace connectors for Model MD–11 (124 airplanes). 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). 68 work-hours × $85 per hour = $5,780 $54,842 ................... $60,622. 59 work-hours × $85 per hour = $5,015 $67,031 ................... $72,046. Up to 81 work-hours × $85 per hour = $6,885. Up to 77 work-hours × $85 per hour = $6,545. Up to $54,842 ......... Up to $61,727. Up to $67,031 ......... Up to $73,576. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This 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. amozie on DSK3GDR082PROD with RULES Cost per product Action For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2016–04–16, Amendment 39–18410 (81 FR 12806, March 11, 2016), and adding the following new AD: ■ 2018–22–10 The Boeing Company: Amendment 39–19483; Docket No. FAA–2018–0510; Product Identifier 2017–NM–115–AD. Regulatory Findings (a) Effective Date This AD is effective December 12, 2018. We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. (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’’). VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (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 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) 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 (https://rgl.faa.gov/ Regulatory_and_Guidance_Library/rgFAR.nsf /0/339DAEE3E0A6379D862574CF00641951? OpenDocument)). For airplanes on which Boeing-installed auxiliary fuel tanks are E:\FR\FM\07NOR1.SGM 07NOR1 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations amozie on DSK3GDR082PROD with RULES 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), VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 change the fuel pump control and indication system wiring, in accordance with the 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 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 55613 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 (m) 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 For airplanes on which the actions specified in paragraph (h)(1)(ii) or (h)(2)(ii) have been done: 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) New Provision of This AD: Optional Revision (1) In lieu of accomplishing the revision specified in paragraph (h)(3) of this AD: Within the compliance time specified in paragraph (h)(3) of this AD, operators may revise the maintenance or inspection program, as applicable, to incorporate the CDCCLs, ALIs, and short-term extensions specified in Appendices B, C, and D of Boeing Trijet Special Compliance Item Report MDC–02K1003, Revision R, dated May 9, 2018. The initial compliance time for accomplishing the actions specified in the ALIs is at the later of the times specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD. Revising the maintenance or inspection program specified in 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 Special Compliance Item Report MDC–02K1003, Revision R, dated May 9, 2018, except as provided by Appendix D of Boeing Trijet Special Compliance Item Report MDC– 02K1003, Revision R, dated May 9, 2018. (ii) Within 30 days after accomplishing the actions required by paragraph (h)(1) or (h)(2) E:\FR\FM\07NOR1.SGM 07NOR1 55614 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations of this AD, as applicable; or within 30 days after the effective date of this AD; whichever occurs later. (2) If the optional revision specified in paragraph (l)(1) of this AD is accomplished: After the maintenance or inspection program has been revised as provided by paragraph (1)(1) 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 AMOC in accordance with the procedures specified in paragraph (m) of this AD. amozie on DSK3GDR082PROD with RULES (m) 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 (n) of this AD. Information may be emailed to: 9-ANMLAACO-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, 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. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(4)(i) and (m)(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. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on December 12, 2018. (i) Boeing Service Bulletin DC10–28–264, dated May 15, 2015. (ii) Boeing Service Bulletin MD11–28–146, dated May 15, 2015. (iii) Boeing Trijet Special Compliance Item Report MDC–02K1003, Revision R, including Appendices A through D, dated May 9, 2018. (4) The following service information was approved for IBR on April 15, 2016 (81 FR 12806, March 11, 2016). (i) Boeing Alert Service Bulletin DC10– 28A253, dated June 5, 2014. (ii) Boeing Service Bulletin DC10–28–256, dated June 24, 2014. (iii) Boeing Alert Service Bulletin MD11– 28A133, dated June 5, 2014. (iv) Boeing Service Bulletin MD11–28–137, dated June 24, 2014. (v) Boeing Trijet Special Compliance Item Report MDC–02K1003, Revision M, including Appendices A through D, dated July 25, 2014. (5) 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. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on October 24, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–23822 Filed 11–6–18; 8:45 am] BILLING CODE 4910–13–P (n) Related Information 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. VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0404; Product Identifier 2018–NE–15–AD; Amendment 39– 19468; AD 2018–21–10] RIN 2120–AA64 Airworthiness Directives; International Aero Engines (IAE) Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all International Aero Engines (IAE) PW1133G–JM, PW1133GA–JM, PW1130G–JM, PW1127G–JM, PW1127GA–JM, PW1127G1–JM, PW1124G–JM, PW1124G1–JM, and PW1122G–JM turbofan engines. This AD was prompted by reports of in-flight engine shutdowns and aborted take-offs as the result of certain parts affecting the durability of the rear high-pressure compressor (HPC) rotor hub knife edge seal. This AD requires replacing the diffuser case air seal assembly, the highpressure turbine (HPT) 2nd-stage vane assembly, and the HPT 2nd-stage borescope stator vane assembly with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 12, 2018. ADDRESSES: For service information identified in this final rule, contact International Aero Engines, 400 Main Street, East Hartford, CT, 06118; phone: 800–565–0140; email: help24@ pw.utc.com; internet: https:// fleetcare.pw.utc.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238– 7759. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018–0404. SUMMARY: 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–2018– 0404; 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 final rule, the regulatory evaluation, any comments received, and other E:\FR\FM\07NOR1.SGM 07NOR1

Agencies

[Federal Register Volume 83, Number 216 (Wednesday, November 7, 2018)]
[Rules and Regulations]
[Pages 55610-55614]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-23822]



[[Page 55610]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0510; Product Identifier 2017-NM-115-AD; Amendment 
39-19483; AD 2018-22-10]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2016-04-16, 
which applied 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 
required adding design features to detect electrical faults and to 
detect a pump running in an empty fuel tank. This AD continues to 
require adding design features to detect electrical faults and to 
detect a pump running in an empty fuel tank. This AD also provides 
optional terminating action for certain requirements. This AD was 
prompted by a fuel system review conducted by the manufacturer. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective December 12, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 12, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of April 
15, 2016 (81 FR 12806, March 11, 2016).

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone: 562-797-1717; internet: https://www.myboeingfleet.com. You may view this 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 https://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 https://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 final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is Docket Operations, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: 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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2016-04-16, Amendment 39-18410 (81 FR 12806, 
March 11, 2016) (``AD 2016-04-16''). AD 2016-04-16 applied 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. The NPRM published in the Federal Register on 
June 14, 2018 (83 FR 27718). The NPRM was prompted by a fuel system 
review conducted by the manufacturer and a determination that 
accomplishing new service information in conjunction with certain 
service information specified in AD 2016-04-16 would terminate certain 
actions in related ADs. The NPRM proposed to continue to require adding 
design features to detect electrical faults and to detect a pump 
running in an empty fuel tank. The NPRM also proposed to provide 
optional terminating action for certain requirements. 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.

Comments

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

Support for the NPRM

    FedEx Express (FedEx) and Air Line Pilots Association, 
International (ALPA) provided their concurrence with the NPRM. FedEx 
also pointed out that the NPRM affects 39 Model MD-10 airplanes and 57 
Model MD-11 airplanes in the FedEx fleet.

Request To Clarify the Terminating Action Specified in Paragraph (k) of 
the Proposed AD

    Boeing requested that we clarify the terminating action specified 
in paragraph (k) of the proposed AD. Boeing agreed that the repetitive 
inspections and tests may be terminated upon installation of the new 
connector design per the Boeing service bulletins cited in paragraph 
(k) of the proposed AD (Boeing Service Bulletin DC10-28-264, dated May 
15, 2015; and Boeing Service Bulletin MD11-28-146, dated May 15, 2015). 
Boeing noted that those service bulletins were approved by the Manager, 
Los Angeles ACO Branch. Boeing added that those service bulletins also 
specify an additional condition for the terminating actions: the fault 
current detectors cited in paragraphs (h)(1)(ii) and (h)(2)(ii) of the 
proposed AD must also be installed before the repetitive actions are 
terminated. Boeing recommended that paragraph (k) of the proposed AD be 
revised to clarify that the fault current detectors must be installed 
per paragraphs (h)(1)(ii) and (h)(2)(ii) of the proposed AD in order to 
accomplish the terminating action per the Boeing service bulletins 
cited in paragraph (k) of the proposed AD.
    We agree with the commenter's request. Paragraph F., ``Approval,'' 
of Boeing Service Bulletin DC10-28-264, dated May 15, 2015; and Boeing 
Service Bulletin MD11-28-146, dated May 15, 2015, specifies that the 
actions in those service bulletins as well as the service bulletins 
specified in paragraphs (h)(1)(ii) and (h)(2)(ii) of this AD terminate 
the actions required by paragraph (a) of AD 2002-13-10, Amendment 39-
12798 (67 FR 45053, July 8, 2002) (``AD 2002-13-10''), paragraph (a) of 
AD 2003-07-14, Amendment 39-13110 (68 FR 17544, April 10, 2003) (``AD 
2003-07-14''), and paragraph (j) of AD 2011-11-05, Amendment 39-16704 
(76 FR 31462, June 1, 2011) (``AD 2011-11-05''). We have revised 
paragraph (k) of this AD accordingly.

Request To Withdraw the NPRM

    United Parcel Service (UPS) requested that we withdraw the NPRM. 
UPS pointed out that the NPRM includes no

[[Page 55611]]

new requirements or information. UPS indicated that no new requirements 
or actions would create an undue burden on operators because existing 
internal paperwork and records must then be revised to provide proof of 
compliance.
    We acknowledge the commenter's concerns; however, we disagree with 
the request to withdraw the NPRM. AD 2003-07-14 was affected by AD 
2016-04-16 but was inadvertently left out of AD 2016-04-16. This AD 
corrects that oversight and includes AD 2003-07-14 as an affected AD. 
Additionally, this AD provides new optional terminating actions that 
affect AD 2003-07-14 as well as AD 2002-13-10 and AD 2011-11-05.

Request To Include Updated Service Information

    UPS requested that we revise the NPRM to include a later revision 
of Boeing Trijet Special Compliance Item Report MDC-02K1003. UPS 
pointed out that the new fuel pump housing assembly that is created by 
installation of the new connectors was not added until Revision N of 
Boeing Trijet Special Compliance Item Report MDC-02K1003. Additionally, 
UPS mentioned that Revision R of Boeing Trijet Special Compliance Item 
Report MDC-02K1003 was in the approval process at the time the comment 
was submitted.
    We agree with the request to include the latest published version 
of Boeing Trijet Special Compliance Item Report MDC-02K1003. We 
referred to Boeing Trijet Special Compliance Item Report MDC-02K1003, 
Revision M, including Appendices A through D, dated July 25, 2014, as 
an appropriate source of service information in the NPRM. Revision R of 
Boeing Trijet Special Compliance Item Report MDC-02K1003, including 
Appendices A through D, dated May 9, 2018, includes new part numbers 
for Critical Design Configuration Control Limitation (CDCCL) 28-2 and 
updates certain special compliance items to include additional 
procedures for airplanes with a certain configuration. We have added 
paragraph (l) to this AD to include Revision R of Boeing Trijet Special 
Compliance Item Report MDC-02K1003, including Appendices B through D, 
dated May 9, 2018, as an optional revision to paragraph (h)(3) of this 
AD, and we have redesignated subsequent paragraphs accordingly. We are 
considering further rulemaking to require revising the maintenance or 
inspection program to include Revision R of Boeing Trijet Special 
Compliance Item Report MDC-02K1003, including Appendices B through D, 
dated May 9, 2018.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously, and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed 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, including Appendices A through D, dated July 25, 2014; and 
Boeing Trijet Special Compliance Item Report MDC-02K1003, Revision R, 
including Appendices A through D, dated May 9, 2018; which include 
CDCCLs, ALIs, and short-term extensions in Appendices B, C, and D, 
respectively. This service information describes fuel ALIs that address 
ignition sources. These documents are distinct since Revision R 
includes additional requirements.
     Boeing Service Bulletin DC10-28-264, dated May 15, 2015, 
and 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.

Costs of Compliance

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

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     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 (retained    hour = $12,920.
 actions from AD 2016[dash]04[dash]16).
Installing design features using        98 work-hours x $85 per          109,000         117,330     40,009,530.
 service information (retained           hour = $8,330.
 optional actions from AD
 2016[dash]04[dash]16).
----------------------------------------------------------------------------------------------------------------


[[Page 55612]]


                                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   Up to $54,842................  Up to $61,727.
 housings for Model DC-10 and MD-   x $85 per hour =
 10 (122 airplanes).                $6,885.
Option 2: Replace fuel pump        Up to 77 work-hours   Up to $67,031................  Up to $73,576.
 housings for Model MD-11 (124      x $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 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.
    This 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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2016-04-16, Amendment 39-18410 (81 FR 12806, March 11, 2016), and 
adding the following new AD:

2018-22-10 The Boeing Company: Amendment 39-19483; Docket No. FAA-
2018-0510; Product Identifier 2017-NM-115-AD.

(a) Effective Date

    This AD is effective December 12, 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 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) 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 (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgFAR.nsf/0/339DAEE3E0A6379D862574CF00641951?OpenDocument)). For airplanes on 
which Boeing-installed auxiliary fuel tanks are

[[Page 55613]]

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 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 (m) 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

    For airplanes on which the actions specified in paragraph 
(h)(1)(ii) or (h)(2)(ii) have been done: 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) New Provision of This AD: Optional Revision

    (1) In lieu of accomplishing the revision specified in paragraph 
(h)(3) of this AD: Within the compliance time specified in paragraph 
(h)(3) of this AD, operators may revise the maintenance or 
inspection program, as applicable, to incorporate the CDCCLs, ALIs, 
and short-term extensions specified in Appendices B, C, and D of 
Boeing Trijet Special Compliance Item Report MDC-02K1003, Revision 
R, dated May 9, 2018. The initial compliance time for accomplishing 
the actions specified in the ALIs is at the later of the times 
specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD. 
Revising the maintenance or inspection program specified in 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 Special Compliance Item Report MDC-02K1003, Revision R, dated 
May 9, 2018, except as provided by Appendix D of Boeing Trijet 
Special Compliance Item Report MDC-02K1003, Revision R, dated May 9, 
2018.
    (ii) Within 30 days after accomplishing the actions required by 
paragraph (h)(1) or (h)(2)

[[Page 55614]]

of this AD, as applicable; or within 30 days after the effective 
date of this AD; whichever occurs later.
    (2) If the optional revision specified in paragraph (l)(1) of 
this AD is accomplished: After the maintenance or inspection program 
has been revised as provided by paragraph (1)(1) 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 
AMOC in accordance with the procedures specified in paragraph (m) of 
this AD.

(m) 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 (n) 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.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(m)(4)(i) and (m)(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.

(n) Related Information

    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].

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
December 12, 2018.
    (i) Boeing Service Bulletin DC10-28-264, dated May 15, 2015.
    (ii) Boeing Service Bulletin MD11-28-146, dated May 15, 2015.
    (iii) Boeing Trijet Special Compliance Item Report MDC-02K1003, 
Revision R, including Appendices A through D, dated May 9, 2018.
    (4) The following service information was approved for IBR on 
April 15, 2016 (81 FR 12806, March 11, 2016).
    (i) Boeing Alert Service Bulletin DC10-28A253, dated June 5, 
2014.
    (ii) Boeing Service Bulletin DC10-28-256, dated June 24, 2014.
    (iii) Boeing Alert Service Bulletin MD11-28A133, dated June 5, 
2014.
    (iv) Boeing Service Bulletin MD11-28-137, dated June 24, 2014.
    (v) Boeing Trijet Special Compliance Item Report MDC-02K1003, 
Revision M, including Appendices A through D, dated July 25, 2014.
    (5) 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.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on October 24, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-23822 Filed 11-6-18; 8:45 am]
 BILLING CODE 4910-13-P

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