Airworthiness directives › 2017-22-12
AD 2017-22-12 Airworthiness Directives; The Boeing Company Airplanes
Models named: 757-200, -200PF, -200CB 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 757-200, -200PF, and -200CB series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01518SE [ http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38b606833bbd98b386257faa00602538/$FILE/ST01518SE.pdf ] does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE 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
At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 757-57-0066, Revision 1, dated June 7, 2016 (“Boeing SASB 757-57-0066 R1”), except as specified in paragraph (j)(1) of this AD: Inspect each trailing edge slat wedge of the leading edge slats in accordance with Appendixes A, B, C, and D of Boeing SASB 757-57-0066 R1, as applicable, or review the airplane maintenance records, to determine whether the slat wedge is a type A or a type B. If a maintenance records review cannot conclusively determine a slat wedge is a type B, it must be assumed to be a type A slat wedge, or a physical inspection must be done as specified in this paragraph. If a physical inspection cannot determine if a slat wedge is a type A or type B slat wedge, it must be assumed to be a type A slat wedge, or approval of an alternative method of compliance (AMOC) may be requested in accordance with the procedures specified in paragraph (n) of this AD.
Unsafe condition
This AD was prompted by reports of slats disbonding on airplanes on which the terminating actions of AD 2005-07-08 had been performed. We have also received reports of slats disbonding on airplanes outside of the applicability of AD 90-23-06, AD 91-22-51, and AD 2005-07-08, which also addressed slat disbonding. We are issuing this AD to prevent delamination of the trailing edge slat wedges of the leading edge slats. This delamination could cause loss of pieces of the trailing edge slat wedge assemblies during flight, reduction of the maneuver and stall margins, and consequent reduced controllability of the airplane.
Affected ADs
This AD affects AD 90-23-06, Amendment 39-6794 (55 FR 46499, November 5, 1990) (“AD 90-23-06”); AD 91-22-51, Amendment 39-8129 (57 FR 781, January 9, 1992) (“AD 91-22-51”); and AD 2005-07-08, Amendment 39-14032 (70 FR 16403, March 31, 2005) (“AD 2005-07-08”).
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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