Airworthiness Directive · Amendment 39-18015 · Fuselage
The Boeing Company Airplanes
This AD applies to The Boeing Company airplanes identified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, as identified in Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated September 18, 2013.
(1) The Boeing Company Model DC-8-55 airplanes.
(2) The Boeing Company Model DC-8F-54 and DC-8F-55 airplanes.
(3) The Boeing Company Model DC-8-61, DC-8-62, and DC-8-63 airplanes.
(4) The Boeing Company Model DC-8-61F, DC-8-62F, and DC-8-63F airplanes.
(5) The Boeing Company Model DC-8-71, DC-8-72, and DC-8-73 airplanes.
(6) The Boeing Company Model DC-8-71F, DC-8-72F, and DC-8-73F airplanes.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-8-55, 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 was prompted by multiple reports of cracking of the upper aft skin panel of the fuselage. An evaluation by the design approval holder (DAH) indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage (WFD). This AD requires removing any previously installed local repairs; installing a full-length improvement modification with or without finger doublers, or a full- length repair with or without finger doublers, as applicable; and doing repetitive inspections for cracking of the doublers, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane.
Before the accumulation of 45,400 total flight cycles, or within 72 months after the effective date of this AD, whichever occurs later: Remove any previously installed local repairs and install a full-length improvement modification with or without finger doublers, or a full-length repair with or without finger doublers, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated September 18, 2013. Installation of the full-length improvement modification or full-length repair, in accordance with paragraph (i) of AD 2008-06-23, Amendment 39-15435 (73 FR 14378, March 18, 2008), is a method of compliance with the requirements of this paragraph. Installation of a local repair as specified in paragraph (i) of AD 2008-06-23, does not comply with the requirements of this paragraph.
After accomplishing the actions required by paragraph (g) of this AD, at the applicable time and intervals specified in paragraph (h)(1) or (h)(2) of this AD: Do an external visual inspection or low frequency eddy current (LFEC) inspection for cracking along all four edges of each external doubler, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated September 18, 2013. Repeat the inspections thereafter at the applicable time and interval specified in paragraphs (h)(1) and (h)(2) of this AD. Accomplishment of the applicable repetitive inspection specified in paragraph (j)(1) or (j)(2)(ii) of AD 2008-06-23, Amendment 39-15435 (73 FR 14378, March 18, 2008), is a method of compliance with the applicable inspection requirements of this paragraph.
(1) For repair or modification with finger doublers: Within 30,000 flight cycles after doing the actions specified in paragraph (g) of this AD, do an external visual inspection. Repeat the external visual inspection thereafter at intervals not to exceed 5,000 flight cycles.
(2) For repair or modification without finger doublers: Within 15,000 flight cycles after doing the actions specified in paragraph (g) of this AD, do a LFEC inspection. Repeat the LFEC inspection thereafter at intervals not to exceed 10,000 flight cycles.
If any cracking is found during any inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
