AD 2011-23-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Boeing | Company Model 737-300 | Airworthiness Directives; The Boeing Company Model 737-300, -400, and -500 Series Airplanes |
Unsafe Condition
Cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringers S-20 and S-21, on both the left and right sides of the airplane. Such cracking could reduce the structural capability of the frames to sustain limit loads, and result in cracking in the fuselage skin and subsequent rapid depressurization of the airplane.
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Required Actions
Inspect for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringers S-20 and S-21, on both the left and right sides of the airplane. Repair any identified cracking in accordance with an approved method or using data that meet the certification basis of the airplane, approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA).
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Compliance Time
Within 4,500 flight cycles after accomplishment of the most recent Part 2 or Part 4 inspection, with a grace period of 90 days. For certain airplanes with 40,000 or more total flight cycles and solid fuselage skins, the compliance time for Part 2 inspection is extended to 90 days.
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Affected Aircraft
The Boeing Company Model 737-300, -400, and -500 series airplanes.
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Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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