Airworthiness Directive · Amendment 39-14468 · McDonnell Douglas Model DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F Airplanes
McDonnell Douglas Model DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F Airplanes
This AD applies to McDonnell Douglas Model DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes, certificated in any category; as identified in Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002.
The FAA is adopting a new airworthiness directive (AD) for certain transport category airplanes, identified above. This AD requires repetitive inspections for cracks of the doorjamb corners of the main cabin cargo door, and repair if necessary. This AD also provides an optional preventive modification that extends certain repetitive intervals. This AD results from reports of cracks in the fuselage skin at the corners of the doorjamb for the main cabin cargo door. We are issuing this AD to detect and correct fatigue cracks in the fuselage skin, which could result in rapid decompression of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the applicable time in paragraph (f)(1) or (f)(2) of this AD: Do the applicable inspections for cracking of the doorjamb corners of the main cabin cargo door in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002; the applicable inspections are specified in Table 1 of Paragraph 1.E. “Compliance” of the service bulletin. Except as provided by paragraphs (g) and (h) of this AD, repeat the inspections thereafter at intervals not to exceed the applicable intervals specified in Table 1 of Paragraph 1.E. “Compliance” of the service bulletin.
(1) For airplanes that have been converted from passenger to cargo under Amended Type Certificate Data Sheet 4A25, Notes 25 and 26, and McDonnell Douglas Supplemental Type Certificates SA3749WE and SA3403WE: Within 15,000 flight cycles after the conversion; or within 12 months after the effective date of this AD; whichever occurs later.
(2) For airplanes that have not been converted from passenger to cargo: Before the accumulation of 15,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later.
If any crack is found during any inspection required by this AD, before further flight: Do the applicable action in paragraph (g)(1) or (g)(2) of this AD in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002.
(1) For any corner where all cracks are 2.50 inches or less in length, install an external doubler in accordance with the service bulletin: Before the accumulation of 17,000 flight cycles after the installation, do the next inspection of that corner as specified in paragraph (f) of this AD. Repeat the inspections in paragraph (f) of this AD for that corner thereafter at intervals not to exceed 4,400 flight cycles.
(2) For any corner where any crack is greater than 2.50 inches in length, repair the crack using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
Installing an external doubler on a corner in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002, terminates the repetitive inspection intervals of paragraph (f) of this AD for that corner. Before the accumulation of 17,000 flight cycles after the installation: Do the next inspection of that corner, as specified in paragraph (f) of this AD. Repeat the inspections in paragraph (f) of this AD for that corner thereafter at intervals not to exceed 4,400 flight cycles.
(i) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement.
Actions accomplished before the effective date of this AD in accordance with McDonnell Douglas Service Bulletin C8-53-079, dated January 31, 2001, are acceptable for compliance with the corresponding action in this AD.
