Airworthiness Directive · Amendment 39-18415 · 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 superseding Airworthiness Directive (AD) 2008-26-07 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. AD 2008-26-07 required repetitive inspections of the lower skin and stringers at certain stations, and corrective actions if necessary. This new AD continues to require the actions specified in AD 2008-26-07 and also requires an eddy current high frequency (ETHF) inspection for cracks of the fastener open holes common to the lower skins, stringers, and splice fittings at a certain station; installation of external doublers and fasteners and repetitive eddy current low frequency (ETLF) inspections around the fasteners for any crack; and corrective actions if necessary. This AD was prompted by certain mandated programs intended to support the airplane reaching its limit of validity of the engineering data that support the established structural maintenance program. We are issuing this AD to detect and correct cracks in the lower skins, stringers, and fastener holes of the splice fittings, which could result in the loss of structural integrity of the airplane.
This paragraph restates the requirements of paragraph (f) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), with no changes. At the times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, except as provided by paragraph (h) of this AD, do the applicable inspections for fatigue cracking of the lower skin and stringers at stations Xw = 408 and Xw = −408, and do all applicable corrective actions, by accomplishing all applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008. Do all corrective actions before further flight. Thereafter, repeat the inspections at the applicable intervals specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, until paragraph (j) of this AD is done.
This paragraph restates the exception specified in paragraph (g) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), with no changes. Where Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, specifies a compliance time “after the date on this service bulletin,” this AD requires compliance within the specified compliance time after January 28, 2009 (the effective date of AD 2008-26-07).
This paragraph restates the exception specified in paragraph (h) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), with no changes. If any cracking is found during any inspection required by paragraph (g) of this AD, and Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(1) For Groups 1-3, Configuration 1 airplanes identified in Boeing Service Bulletin DC8-57-104, dated August 18, 2014: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin DC8-57-104, dated August 18, 2014, except as required in paragraph (l) of this AD, do an inspection for any cracking of the lower skins, stringers, and splice fittings, and do all applicable corrective actions, using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(2) For Groups 1-3, Configuration 2 airplanes identified in Boeing Service Bulletin DC8-57-104, dated August 18, 2014: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin DC8-57-104, dated August 18, 2014, except as required in paragraph (l) of this AD, do an eddy current high frequency (ETHF) inspection for any cracking of the fastener open holes common to the lower skins, stringers, and splice fittings at station Xw = 408 and Xw = −408 from stringer 51 to stringer 65, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-57-104, dated August 18, 2014. If any cracking is found, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
If no crack is found during the inspection required by paragraph (j)(2) of this AD: At the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin DC8-57-104, dated August 18, 2014, install external doublers and fasteners, and do an external doubler ETLF inspection around the fasteners for any cracking, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-57-104, dated August 18, 2014. Repeat the external ETLF inspection at the applicable intervals specified in 1.E., “Compliance,” of Boeing Service Bulletin DC8-57-104, dated August 18, 2014. If any cracking is found during any ETLF inspection required by this paragraph, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
Where Boeing Service Bulletin DC8-57-104, dated August 18, 2014, specifies a compliance time “after the original issue date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
