Sun, Nov 15, 2020
AD 2020-22-15 Requires An Inspection Of The Overwing Floor Beams
The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-10-10 and DC-10-10F airplanes, Model DC-10-15 airplanes, Model DC-10-30 and DC10-30F (KC-10A and KDC-10) airplanes, Model DC-10-40 and DC-10-40F airplanes, Model MD10-10F and MD-10-30F airplanes, and Model MD-11 and MD-11F airplanes. This AD was prompted by reports of cracked floor beams and floor beam supports in the area of the overwing exit doors located at certain stations (STA). This AD requires an inspection of the overwing floor beams for any repair, repetitive inspections of the overwing floor beams and floor beam supports at certain STA on the left and right sides for any crack, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products. This AD is effective December 18, 2020.
Supplementary Information: The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model DC-10-10 and DC-10-10F airplanes, Model DC-10-15 airplanes, Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes, Model DC-10-40 and DC-10-40F airplanes, Model MD-10-10F and MD-10-30F airplanes, and Model MD-11 and MD-11F airplanes. The NPRM published in the Federal Register on August 25, 2020 (85 FR 52287). The NPRM was prompted by reports of cracked floor beams and floor beam supports in the area of the overwing exit doors located at certain STA. The NPRM proposed to require an inspection of the overwing floor beams for any repair, repetitive inspections of the overwing floor beams and floor beam supports at certain STA on the left and right sides for any crack, and applicable on-condition actions.
The FAA is issuing this AD to address potential undetected overwing floor beam cracks that could grow in length until the floor beam severs, and, if limit load is applied with two adjacent severed floor beams, could adversely affect the structural integrity of the airplane, which could result in the loss of primary control systems and lead to reduced controllability of the airplane.
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