Airworthiness Directive · Amendment 39-14990 · Boeing Model 737-600, -700, -700C, and -800 Series Airplanes
Boeing Model 737-600, -700, -700C, and -800 Series Airplanes
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 3, dated January 3, 2007.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 737-600, -700, -700C, and - 800 series airplanes. That AD currently 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 performing corrective actions if necessary. This new AD adds repetitive inspections for cracking of the skin just below each splice fitting, and related 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, which may result in cracking through the skin and consequent decompression of the flight deck.
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, or Revision 3, dated January 3, 2007, 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 fewer than 13,500 total flight cycles as December 21, 2005 (the effective date of AD 2005-25-03): Replace prior to the accumulation of 13,500 total flight cycles, or within 1,000 flight cycles after December 21, 2005, whichever occurs later.
(2) For airplanes that have accumulated 13,500 or more total flight cycles as of December 21, 2005: Replace at the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
(i) Prior to the accumulation of 18,000 total flight cycles, or within 1,000 flight cycles after December 21, 2005, whichever occurs first.
(ii) Within 90 days after December 21, 2005.
Within 24,000 flight cycles after accomplishing the actions specified in paragraph (f) of this AD, perform an external detailed inspection of the skin just below each splice fitting, in accordance with the Accomplishment Instructions of Boeing ASB 737-53A1222, Revision 3, dated January 3, 2007. Thereafter, repeat the external detailed inspections at intervals not to exceed 24,000 flight cycles.
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 (j) of this AD.
(i) Replacing the splice fitting and any related investigative actions before December 21, 2005 (the effective date of AD 2005-25-03), 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. An inspection done before the effective date of this AD in accordance with Boeing ASB 737-53A1222, Revision 2, dated October 20, 2005, is acceptable for compliance with the requirements of paragraph (g) of this AD.
