Airworthiness Directive · Amendment 39-14396 · Boeing Model 737-600, -700, -700C, and -800 Series Airplanes
Boeing Model 737-600, -700, -700C, and -800 Series Airplanes
Superseded. A later AD replaced this one: AD 2007-06-09. Comply with the one in force.
This AD applies to Boeing Model 737-600, -700, -700C, and -800 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin (ASB) 737-53A1222, Revision 2, dated October 20, 2005.
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, and -800 series airplanes. This AD requires replacing the point "D" splice fitting between windows number 1 and 2 with a new splice fitting, performing an eddy current inspection for cracking of the holes in the structure common to the new splice fitting, including doing any related investigative actions; and corrective actions if necessary. This AD results from full-scale fuselage fatigue testing on the splice fitting that failed prior to the design objective on Boeing Model 737-800 series airplanes, and a report of a cracked splice fitting on an operational airplane. We are issuing this AD to prevent cracking of the existing fitting that may result in cracking through the skin and consequent decompression of the flight cabin.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Replace the splice fittings with new splice fittings in accordance with the Accomplishment Instructions of Boeing ASB 737-53A1222, Revision 2, dated October 20, 2005, at the times specified in paragraph (f)(1) or (f)(2) of this AD, as applicable. Before further flight, do any related investigative actions by accomplishing all the applicable actions specified in the Accomplishment Instructions.
(1) For airplanes that have accumulated less than 13,500 total flight cycles as of the effective date of this AD: Replace prior to the accumulation of 13,500 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later.
(2) For airplanes that have accumulated 13,500 or more total flight cycles as of the effective date of this AD: Replace at the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
(i) Prior the accumulation of 18,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs first.
(ii) Within 90 days after the effective date of this AD.
If any cracking is found during any inspection required by this AD, prior to further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, or with a method approved in accordance with the procedures specified in paragraph (i) of this AD.
Replacing the splice fitting before the effective date of this AD in accordance with Boeing Service Bulletin 737-53-1222, dated June 6, 2002; or Boeing ASB 737-53A1222, Revision 1, dated January 30, 2003, is acceptable for compliance with the requirements of paragraph (f) of this AD.
