AD 2013-08-23 Airworthiness Directives; The Boeing Company Airplanes

This AD 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; certificated in any category.

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

As of 60 months after the effective date of this AD, 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 Aircraft Certification Office (ACO), FAA, and those design features are installed on the airplane to meet the criteria specified in 14 CFR Section 25.981(a) and (d), at amendment level 25-125. For airplanes on which Boeing-installed auxiliary fuel tanks are removed, the actions specified in this AD are not required. (1) For all airplanes: Each electrically powered alternate current (AC) fuel pump installed in any fuel tank that normally empties during flight—such as 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 flight crew: 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 flight crew 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 flight crew 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 flight crew manual pump shutoff procedures in the Limitations Section of the AFMS must be submitted to the Los Angeles ACO, FAA, for approval. (3) For airplanes with a 3-person flight crew: 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 provide an indication to the flight crew 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 AD was prompted by fuel system reviews 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.

Accomplishment of the requirements of this AD terminates certain requirements of AD 2002-13-10, Amendment 39-12798 (67 FR 45053, July 8, 2002), and AD 2011-11-05, Amendment 39-16704 (76 FR 31462, June 1, 2011).