Airworthiness Directive · Amendment 39-15070 · McDonnell Douglas Model 717-200 Airplanes
McDonnell Douglas Model 717-200 Airplanes
Superseded. A later AD replaced this one: AD 2017-01-03. Comply with the one in force.
This AD applies to all McDonnell Douglas Model 717-200 airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to incorporate new inspections for fatigue cracking of principal structural elements (PSEs). Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to incorporate the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25-1529-1.
The FAA is superseding an existing airworthiness directive (AD), which applies to all McDonnell Douglas Model 717-200 airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new removal limits for certain components of the flap system and to reduce the interval of inspections for fatigue cracking of certain principal structural elements (PSEs). This new AD requires revising the ALS of the Instructions for Continued Airworthiness to incorporate reduced initial inspection and repeat inspection intervals for certain PSEs. This AD results from a revised damage tolerance analysis. We are issuing this AD to detect and correct fatigue cracking of certain PSEs, which could adversely affect the structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 180 days after September 23, 2003 (the effective date of AD 2003-17-01), revise the Airworthiness Limitations Section of the Instructions for Continued Airworthiness, Airworthiness Limitations Instructions (ALI), in accordance with Boeing Report No. MDC-96K9063, Revision 3, dated August 2002.
(g) Except as provided by paragraph (j) of this AD: After the actions specified in paragraph (f) of this AD have been done, no alternative inspection intervals or replacement times may be approved for the PSEs and safe-life limited parts specified in Boeing Report No. MDC-96K9063, Revision 3, dated August 2002.
Within 180 days after the effective date of this AD: Revise the Airworthiness Limitations Section of the Instructions for Continued Airworthiness, ALI, in accordance with Boeing 717-200 ALI, Report MDC-96K9063, Revision 5, dated February 2006.
(i) Except as provided by paragraph (j) of this AD: After the actions specified in paragraph (h) of this AD have been done, no alternative inspection intervals or replacement times may be approved for the PSEs and safe-life limited parts specified in Boeing 717-200 ALI, Report MDC-96K9063, Revision 5, dated February 2006.
