Airworthiness Directive · Amendment 39-17198 · Fuselage
The Boeing Company Airplanes
This AD applies to 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, and DC-10-40F airplanes, and Model MD-10-10F and MD-10-30F airplanes that have been converted from Model DC-10 series airplanes; certificated in any category; as identified in paragraphs (c)(1) and (c)(2) of this AD, as applicable.
(1) Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 2011 (for airplanes with extended wing-to-fuselage fillets).
(2) Boeing Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011 (for airplanes with conventional wing-to-fuselage fillets).
We are superseding an existing airworthiness directive (AD) for certain 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, and MD-10-30F airplanes. That AD currently requires installing or replacing with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane; and for certain airplanes, repositioning or replacing two bonding straps, doing a bonding-resistance check and an inspection to determine correct installation of certain bonding straps, and applicable corrective actions. This new AD adds airplanes to the applicability and, depending on the airplane configuration, requires installing new braided bonding straps, inspecting to determine if a certain strap is installed and replacing with or installing a braided bonding strap if necessary, measuring the electrical resistance of the bonding straps, verifying that brackets have an acceptable fillet seal, and doing corrective actions if necessary. This AD was prompted by fuel system reviews conducted by the manufacturer, and our determination that additional actions are necessary to address the identified unsafe condition. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a severe lightning strike, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
This paragraph restates the installation or replacement requirements of paragraph (g) of AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009), with new service information. For airplanes with manufacturer's fuselage numbers identified in the applicable service bulletin listed in paragraph (g)(1) of this AD: Within 7,500 flight hours or 60 months after September 7, 2006 (the effective date of AD 2006-16-03, Amendment 39-14703 (71 FR 43962, August 3, 2006)), whichever occurs earlier: Install or replace with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. After February 4, 2010 (the effective date of AD 2009-26-17), use the applicable service bulletin identified in paragraph (g)(2) or (g)(3) of this AD. After the effective date of this AD, use only the applicable service bulletin identified in paragraph (g)(3) of this AD to do the actions required by this paragraph.
(1) McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 4, dated October 7, 1992 (for airplanes with extended wing-to-fuselage fillets); or McDonnell Douglas DC-10 Service Bulletin 53-111, Revision 3, dated August 24, 1992 (for airplanes with conventional wing-to-fuselage fillets).
(2) Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009 (for airplanes with extended wing-to-fuselage fillets); or Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009 (for airplanes with conventional wing-to-fuselage fillets).
(3) Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 2011 (for airplanes with extended wing-to-fuselage fillets); or Boeing Service Bulletin
DC10-53-111, Revision 7, dated March 16, 2011 (for airplanes with conventional wing-to-fuselage fillets).
This paragraph restates the installation or replacement requirements of paragraph (h) of AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009), with new service information. For airplanes with fuselage numbers identified in the applicable service bulletin listed in paragraph (g)(2) of this AD that are not also identified in the applicable service bulletin listed in paragraph (g)(1) of this AD, except for airplanes identified in paragraph (i) or (j) of this AD: Within 7,500 flight hours or 60 months, whichever occurs first after February 4, 2010 (the effective date of AD 2009-26-17), install or replace with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane. Do the actions in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(2) or (g)(3) of this AD. After the effective date of this AD, use only the applicable service bulletin identified in paragraph (g)(3) of this AD to do the actions required by this paragraph.
This paragraph restates the strap repositioning requirements of paragraph (i) of AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009), with new service information. For Group 1-4, Configuration 3 airplanes, as identified in Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009: Within 7,500 flight hours or 60 months after February 4, 2010 (the effective date of AD 2009-26-17), whichever occurs first, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD.
(1) Remove two braided bonding straps and install two longer braided bonding straps between the metallic frame of the fillet and the wing leading edge ribs, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009; or Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 2011. After the effective date of this AD, use only Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 2011, to do the actions required by this paragraph.
(2) Measure the resistance of the previously installed bonding straps and, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009; or Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 2011. After the effective date of this AD, use only Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 2011, to do the actions required by this paragraph.
This paragraph restates the inspection requirements of paragraph (j) of AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009), with new service information. For Group 1-2, Configuration 2 airplanes, as identified in Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009: Within 7,500 flight hours or 60 months after February 4, 2010 (the effective date of AD 2009-26-17), whichever occurs first, do the actions specified in paragraphs (j)(1) and (j)(2) of this AD.
(1) Do a general visual inspection to verify correct installation of the braided bonding straps (one left-hand wing and one right-hand wing) as shown in Sheet 7 in Figure 3 of Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009, or Boeing Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011; and, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009, or Boeing Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011. After the effective date of this AD, use only Boeing Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011, to do the actions required by this paragraph.
(2) Measure the resistance of the previously installed bonding straps and, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009; or Boeing Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011. After the effective date of this AD, use only Boeing Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011, to do the actions required by this paragraph.
