Airworthiness directives › 2023-13-05
AD 2023-13-05 Airworthiness Directives; The Boeing Company Airplanes
Models named: 737-600, -700, -700C, -800, -900, -900ER series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(1) This AD applies to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST00830SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a “change in product” alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Except as specified by paragraph (h) of this AD: At the applicable times specified in the “Compliance” paragraph of Boeing Special Attention Requirements Bulletin 737-53-1399 RB, Revision 1, dated March 14, 2023, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Special Attention Requirements Bulletin 737-53-1399 RB, Revision 1, dated March 14, 2023. Note 1 to paragraph (g): Guidance for accomplishing the actions required by this AD can be found in Boeing Special Attention Service Bulletin 737-53-1399 RB, Revision 1, dated March 14, 2023, which is referred to in Boeing Special Attention Requirements Bulletin 737-53-1399 RB, Revision 1, dated March 14, 2023.
Unsafe condition
This AD was prompted by a report indicating fuselage skin lap splice cracking was found between stations (STA) 767 and STA 787, just below S-14R fuselage skin lap splice, where a lower skin panel buckle intersected the upper skin of the lap splice. Cracking was also found just below S-14R between STA 747 and STA 767. The FAA is issuing this AD to address cracks, skin buckles, wrinkles, and bulges at fuselage longitudinal lap splice areas at S-4, S-14 and S-24. This condition, if not addressed, could result in cracks in fatigue-critical baseline structure and the inability of a principal structural element to sustain limit loads, which could adversely affect the structural integrity of the airplane.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1