Airworthiness Directive · Amendment 39-19483 · Fuel
The Boeing Company Airplanes
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.
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.
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.
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.
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.
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.
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.
(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) 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.
