Airworthiness Directive · Amendment 39-15236 · McDonnell Douglas Model DC-8-53, DC-8-55, DC-8F-54, and DC-8F-55 Airplanes; and Model DC-8-60, DC-8-60F, DC-8-70, and DC-8-70F Series Airplanes
McDonnell Douglas Model DC-8-53, DC-8-55, DC-8F-54, and DC-8F-55 Airplanes; and Model DC-8-60, DC-8-60F, DC-8-70, and DC-8-70F Series Airplanes
This AD applies to McDonnell Douglas Model DC-8-53, DC-8-55, DC-8-61, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-71, DC-8-71F, DC-8-72, DC-8-72F, DC-8-73, DC-8-73F, DC-8F-54, and DC-8F-55 airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin DC8-53A081, dated November 14, 2006.
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas airplanes, identified above. This AD requires a one-time inspection to determine the configuration of the airplane. This AD also requires repetitive inspections for cracking of the tee or angle doubler, and corrective actions if necessary. This AD results from a report indicating that numerous operators have found cracks on the tee. We are issuing this AD to detect and correct stress corrosion cracking of the tee or angle doubler installed on the flat aft pressure bulkhead. Cracking in this area could continue to progress and damage the adjacent structure, which could result in loss of structural integrity 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.
For all airplanes: Within 24 months after the effective date of this AD, inspect the left and right sides of the flat aft pressure bulkhead to determine if a repair has been installed. As noted in Boeing Alert Service Bulletin DC8-53A081, dated November 14, 2006, Configuration 1 applies to airplanes with no repairs installed; Configuration 2 applies to airplanes with repairs installed in accordance with DC-8 Structural Repair Manual (SRM) 53-2-5, Figure 9; and Configuration 3 applies to airplanes with repairs that are not installed in accordance with DC-8 SRM 53-2-5, Figure 9. A review of airplane maintenance records is acceptable in lieu of this inspection if the applicable installation can be conclusively determined from that review.
(1) For airplanes determined to be either Configuration 1 or Configuration 2: Within 24 months after the effective date of this AD, do the applicable inspection for cracking of the tee or angle doubler, and do all applicable corrective actions before further flight, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin DC8-53A081, dated November 14, 2006. Repeat the applicable inspection thereafter at the applicable interval specified in Paragraph 1.E, “Compliance,” of Boeing Alert Service Bulletin DC8-53A081, dated November 14, 2006. Where the service bulletin specifies to do the pressure test, that action is not required by this AD.
(2) For airplanes determined to be Configuration 1 airplanes: A review of the airplane maintenance records to determine if the tee was previously inspected using one of the three inspection methods specified in the DC-8 Supplemental Inspection Document (SID) L26-011, Volume II, 53-10-18, and to determine that no crack was found, is acceptable to determine the type of inspection and corresponding repetitive interval if the inspection type and crack finding can be conclusively determined from that review.
(3) For airplanes determined to be Configuration 3 airplanes: Within 24 months after the effective date of this AD, repair the previous installation. Where Boeing Alert Service Bulletin DC8-53A081, dated November 14, 2006, specifies to contact Boeing for instructions, repair using a method approved in accordance with the procedures specified in paragraph (g) of this AD.
