AD 2007-07-04 Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F Airplanes

Models named: MD-11, -11F. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all McDonnell Douglas Model MD-11 and -11F 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 (i) 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.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Revision of Airworthiness Limitations Section (f) Except as provided by paragraph (h) of this AD: Within 18 months after the effective date of this AD, revise the Airworthiness Limitations section of the Instructions for Continued Airworthiness, Airworthiness Limitations Instructions (ALI), according to a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. Boeing MD-11 ALI, Report Number MDC-K5225, Revision 11, dated March 2006, is one approved method. (g) Except as provided by paragraph (i) 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 MD-11 ALI Report Number MDC-K5225, Revision 11, dated March 2006. Compliance Times for Inspections (h) Accomplish the initial threshold and repetitive inspection intervals specified in the ALI, as applicable, at the times specified in paragraphs (h)(1) and (h)(2) of this AD. (1) For PSEs 54.52.01.1, 57.21.02.1, and 57.23.01.1: Accomplish the initial inspection within 24 months after accomplishment of the requirements in paragraph (f) of this AD, or within the initial inspection interval specified in the ALI, whichever occurs later. (2) For airplanes on which the initial inspection of PSE 57.21.05.1 has been accomplished as of the effective date of this AD: Repeat the inspection within 24 months after accomplishment of the requirements in paragraph (f) of this AD, or within 3,200 flight cycles after accomplishment of the initial inspection, whichever occurs later. Repeat the inspection thereafter at intervals not to exceed 3,200 flight cycles. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Los Angeles ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by accomplishing the actions of this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (3) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (j) None. Issued in Renton, Washington, on March 19, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-5554 Filed 3-27-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from a revised damage tolerance analysis. We are issuing this AD to detect and correct fatigue cracking of certain principal structural elements (PSEs), which could adversely affect the structural integrity of the airplane.