Airworthiness directives › 2016-11-04
AD 2016-11-04 Airworthiness Directives; The Boeing Company Airplanes
Models named: 737-300, -400, -500 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 737-300, -400, and -500 series airplanes; certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE 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
This paragraph restates the requirements of paragraph (g) of AD 2011-23-05, with references to terminating actions. At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, except as required by paragraphs (k)(1), (k)(2), and (k)(4) of this AD: Do a high frequency eddy current (HFEC) surface or HFEC hole/edge inspection for any cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement between stringer (S) S-20 and S-21, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011. Accomplishment of the applicable inspections required by paragraphs (m) and (n) of this AD terminates the inspections required by this paragraph. Accomplishment of the modification required by paragraph (p) of this AD terminates the inspections required by this paragraph for the modified area only.
Unsafe condition
This AD was prompted by an evaluation by the design approval holder (DAH) that indicates the fuselage frames and frame reinforcements are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the fuselage frames and frame reinforcements, which could result in reduced structural integrity of the airplane.
Affected ADs
This AD replaces AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011) (“AD 2011-23-05”).
Read the original on the Federal Register →
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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