Airworthiness Directive · Amendment 39-11518 · McDonnell Douglas Model DC-8 Series Airplanes
McDonnell Douglas Model DC-8 Series Airplanes
Model DC-8 series airplanes, as listed in McDonnell Douglas Service Bulletin DC8-57-100, Revision 01, dated August 26, 1998; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires detailed visual and eddy current inspections of the lower wing skin at the 3 outboard fasteners of the stringer 64 end fitting to detect cracks; and corrective actions, if necessary. This amendment is prompted by reports of fatigue cracks found in the lower wing skin initiating from the outboard fasteners of the stringer 64 end fitting. The actions specified by this AD are intended to prevent such fatigue cracking, which could reduce structural integrity and loss of fail-safe capability of the airplane.
To prevent fatigue cracking of the lower wing skin, which could reduce structural integrity and loss of fail-safe capability of the airplane, accomplish the following:
Note 2: This AD will affect Principal Structural Elements (PSE) 57.08.037, 57.08.038, 57.08.021, and 57.08.022 of the DC-8 Supplemental Inspection Document (SID).
(a) Within 24 months after the effective date of this AD, perform detailed visual and eddy current inspections to detect cracks in the lower wing skin fastener holes in the area surrounding 3 outboard fasteners of the stringer 64 end fitting, in accordance with McDonnell Douglas Service Bulletin DC8-57-100, Revision 01, dated August 26, 1998.
Note 3: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
(1) If any crack is detected in the skin fastener holes and it is less than 3.1 inches long, prior to further flight, repair in accordance with the service bulletin. Within 14,100 landings after accomplishment of the repair, inspect the lower wing skin to detect cracks, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.
(2) If any crack is detected in the skin fastener holes and it is greater than or equal to 3.1 inches long, prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles ACO.
(3) If no crack is found, within 24 months after the effective date of this AD, accomplish the preventative modification (including stress or split sleeve coining the three fastener holes in the skin, and installing new pins), in accordance with the service bulletin. Accomplishment of this action constitutes terminating action for the requirements of this AD.
Note 4: This AD does not terminate the inspection requirements for PSE's 57.08.037, 57.08.038, 57.08.021, and 57.08.022 of the DC-8 SID in accordance with AD 93-01-15, amendment 39-6330.
