Airworthiness Directive · Amendment 39-15838 · Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP Series Airplanes
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP Series Airplanes
Superseded. A later AD replaced this one: AD 2013-23-15. Comply with the one in force.
This AD applies to Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747-53A2682, dated May 8, 2008.
We are adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747- 200F, 747-300, 747-400, 747SR, and 747SP series airplanes. This AD requires inspecting for skin cracks at the shear tie end fastener locations of the fuselage frames, and repairing cracks if necessary. This AD results from a wide-spread fatigue damage assessment of Model 747 airplanes. We are issuing this AD to detect and correct cracks in the fuselage skin that can propagate and grow, resulting in a loss of structural integrity and a sudden decompression of the airplane during flight.
Comply with this AD within the compliance times specified, unless already done.
Except as provided by paragraphs (g) and (h) of this AD: At the applicable compliance times specified in paragraph 1.E. of Boeing Alert Service Bulletin 747-53A2682, dated May 8, 2008 (“the service bulletin”), do an external detailed inspection or external high frequency eddy current inspection for skin cracks at the shear tie end fastener locations of the fuselage frames, and repair any skin cracks before further flight, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of the service bulletin. Repeat the applicable inspection thereafter at the applicable interval specified in paragraph 1.E. of the service bulletin.
Where paragraph 1.E. of Boeing Alert Service Bulletin 747-53A2682, dated May 8, 2008, specifies counting the compliance time from “* * * the date on this service bulletin,” this AD requires counting the compliance time from the effective date of this AD.
(h) If any crack is found in a structural repair manual skin repair during any inspection required by paragraph (f) of this AD, and Boeing Alert Service Bulletin 747-53A2682, dated May 8, 2008, specifies to contact Boeing for repair: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
