Airworthiness Directive · Amendment 39-16805 · Wings
The Boeing Company Airplanes
This AD applies to all The Boeing Company Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-61, DC-8-62, DC-8-63, DC-8-61F, DC-8-62F, DC-8-63F, DC-8-71, DC-8-72, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8- 33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-50 series airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-60 series airplanes; Model DC-8-60F series airplanes; Model DC-8-70 series airplanes; and Model DC-8-70F series airplanes. This AD requires repetitive high frequency eddy current or repetitive low frequency eddy current inspections for cracks on the area around certain fasteners of the access opening doubler on the left and right wing center spar lower cap, and repair, if necessary. This AD was prompted by reports that cracks in the center spar lower cap and, in some cases, the web of the spar, have been found at stations Xrs = 168.00, Xrs = 251.00, and Xrs = 358.00. We are issuing this AD to detect and correct cracks in the area around certain fasteners of the access opening doubler on the left and right wing center spar lower cap, which could compromise the structural integrity of the wing structure.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Before the accumulation of 20,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, do a high frequency eddy current (HFEC) or low frequency eddy current (LFEC) inspection for cracks on the area around certain fasteners of the access opening doubler on the left and right wing center spar lower cap, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC8-57A103, dated May 5, 2010. If no crack is found, repeat the inspection thereafter at the applicable interval specified in paragraph 1.E., “Compliance” of Boeing Alert Service Bulletin DC8-57A103, dated May 5, 2010.
If any crack is found during any inspection required by paragraph (g) of this AD, do the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
(1) Before further flight, repair the crack in accordance with Boeing Alert Service Bulletin DC8-57A103, dated May 5, 2010.
(2) Within 6,000 flight cycles after doing the most recent HFEC inspection, or within 1,750 flight cycles after doing the most recent LFEC inspection; as applicable; do the inspection specified in paragraph (g) of this AD of the non-repaired area, and repeat the inspection of the non-repaired area thereafter at the applicable time in paragraph 1.E. “Compliance,” of Boeing Alert Service Bulletin DC8-57A103, dated May 5, 2010.
(3) Within the applicable times specified in paragraph 1.E. “Compliance,” of Boeing Alert Service Bulletin DC8-57A103, dated May 5, 2010, do the inspections of the repaired area, using the inspection defined in Method 101 of Section 57-10-06, “Lower Center Space Cap Flanges (FWD & AFT) from STA Xrs = 100 to 290,” or Methods 101 and 104 of Section 57-10-16, “Lower Center Space Cap Flanges (FWD & AFT) from STA Xrs = 100 to 290,” of the McDonnell Douglas DC-8 Supplemental Inspection Document (SID), Report L26-011, Volume II, Revision 8, dated January 2005, as applicable. Repeat the inspection thereafter at the applicable intervals specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin DC8-57A103, dated May 5, 2010. If any crack is found, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(i) The inspections required by paragraph (h)(3) of this AD constitute compliance with paragraph (j) of AD 2008-25-05 for the repaired area. All requirements of AD 2008-25-05 that are not specifically referenced in this paragraph remain fully applicable and require compliance.
