Airworthiness Directive · Amendment 39-15171 · Boeing Model 747-100, -200B, -200C, and -200F Series Airplanes
Boeing Model 747-100, -200B, -200C, and -200F Series Airplanes
This AD applies to Boeing Model 747-100, -200B, -200C, and -200F series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747-53A2673, dated February 8, 2007.
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, -200B, -200C, and -200F series airplanes. This AD requires performing repetitive inspections for cracks in the fuselage skin at the cutout of the bulk cargo door light, and corrective actions if necessary. This AD also provides terminating action for airplanes with a certain type of damage. This AD results from a report of a 2-inch crack through the fuselage skin and internal bonded doubler at the cutout of the bulk cargo door light. We are issuing this AD to detect and correct cracks in the fuselage skin at the cutout of the bulk cargo door light, which could result in reduced structural integrity of the fuselage at the bulk cargo door and consequent rapid decompression of the fuselage.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Before the accumulation of 20,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever is later: Perform a high frequency eddy current (HFEC) inspection for cracks in the fuselage skin at the cutout of the bulk cargo door light, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2673, dated February 8, 2007. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles.
(1) If no crack is found: Repeat the inspection required by paragraph (f) of this AD at the time specified.
(2) If any crack is found that is 2.0 inches or less in length from the edge of the light cutout forward lower corner: Before further flight, do all the corrective actions (including an additional HFEC inspection for cracks) in accordance with Part 2 of the Accomplishment Instructions of the service bulletin. Accomplishing the actions specified in Part 2 of the service bulletin ends the repetitive inspections required by paragraph (f) of this AD.
(3) If any crack is found during the inspection required by paragraph (f) of this AD that is more than 2.0 inches in total length from the edge of the light cutout forward lower corner, or is at a location other than the light cutout forward lower corner: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (g)(2) of this AD.
