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Airworthiness directives › 2013-09-02

AD 2013-09-02 Airworthiness Directives; The Boeing Company Airplanes

Superseded. This directive was replaced by AD 2018-18-13. Work to the current one.
2013-06-13
2013-05-09
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Airframe
2018-18-13

Models named: 737-100, -200, -200C, -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 737-100, -200, -200C, -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/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se ) 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 inspections required by paragraph (a) of AD 2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000), with added references to a terminating action. For Model 737-100, -200, and -200C series airplanes on which the left- or right-hand inboard flap tracks of the wing outboard flap have a part number (P/N) listed in paragraphs (g)(4)(i) through (g)(4)(x) of this AD: Do a detailed visual inspection to detect damage (corrosion, cracking) of the aft end of the left- and right-hand inboard flap tracks of the wing outboard flap, per Boeing All Operator Message (AOM) M-7200-00-01854, dated July 27, 2000, at the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,200 flight cycles. Accomplishing the requirements of paragraph (p) of this AD terminates the requirements of this paragraph. (1) Within 30 days after January 2, 2001 (the effective date of AD 2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000)). (2) Within 1,200 flight cycles after the last documented inspection or overhaul of the aft end of each flap track. (3) Before the accumulation of 15,000 total flight cycles. (4) Boeing flap tracks subject to this AD are identified in paragraphs (g)(4)(i) through (g)(4)(x) of this AD. (i) P/N 65-46428-9. (ii) P/N 65-46428-15. (iii) P/N 65-46428-17. (iv) P/N 65-46428-19. (v) P/N 65-46428-21. (vi) P/N 65-46428-23. (vii) P/N 65-46428-25. (viii) P/N 65-46428-27. (ix) P/N 65-46428-33. (x) P/N 65-46428-35.

Unsafe condition

This AD was prompted by reports that the work sequence and procedures used during installation of replacement tracks installed in accordance with AD 2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000); or AD 2002-05-07, Amendment 39-12675 (67 FR 11891, March 18, 2002); could cause loose or cracked tracks. We are issuing this AD to detect and correct cracking and damage in the flap track, which could cause loss of the outboard trailing edge flap and consequent reduced controllability of the airplane.

Affected ADs

This AD supersedes ADs 2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000); and 2002-05-07, Amendment 39-12675 (67 FR 11891, March 18, 2002).

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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