AD 2006-03-04 Airworthiness Directives; McDonnell Douglas Model DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F Airplanes

Models named: DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, DC-8-71. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to McDonnell Douglas Model DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes, certificated in any category; as identified in Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections (f) At the applicable time in paragraph (f)(1) or (f)(2) of this AD: Do the applicable inspections for cracking of the doorjamb corners of the main cabin cargo door in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002; the applicable inspections are specified in Table 1 of Paragraph 1.E. “Compliance” of the service bulletin. Except as provided by paragraphs (g) and (h) of this AD, repeat the inspections thereafter at intervals not to exceed the applicable intervals specified in Table 1 of Paragraph 1.E. “Compliance” of the service bulletin. (1) For airplanes that have been converted from passenger to cargo under Amended Type Certificate Data Sheet 4A25, Notes 25 and 26, and McDonnell Douglas Supplemental Type Certificates SA3749WE and SA3403WE: Within 15,000 flight cycles after the conversion; or within 12 months after the effective date of this AD; whichever occurs later. (2) For airplanes that have not been converted from passenger to cargo: Before the accumulation of 15,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later. Corrective Actions and New Repetitive Intervals (g) If any crack is found during any inspection required by this AD, before further flight: Do the applicable action in paragraph (g)(1) or (g)(2) of this AD in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002. (1) For any corner where all cracks are 2.50 inches or less in length, install an external doubler in accordance with the service bulletin: Before the accumulation of 17,000 flight cycles after the installation, do the next inspection of that corner as specified in paragraph (f) of this AD. Repeat the inspections in paragraph (f) of this AD for that corner thereafter at intervals not to exceed 4,400 flight cycles. (2) For any corner where any crack is greater than 2.50 inches in length, repair the crack using a method approved in accordance with the procedures specified in paragraph (k) of this AD. Optional Preventive Modification (h) Installing an external doubler on a corner in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002, terminates the repetitive inspection intervals of paragraph (f) of this AD for that corner. Before the accumulation of 17,000 flight cycles after the installation: Do the next inspection of that corner, as specified in paragraph (f) of this AD. Repeat the inspections in paragraph (f) of this AD for that corner thereafter at intervals not to exceed 4,400 flight cycles. No Reporting Required (i) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Actions Accomplished In Accordance With Previous Issue of Service Bulletin (j) Actions accomplished before the effective date of this AD in accordance with McDonnell Douglas Service Bulletin C8-53-079, dated January 31, 2001, are acceptable for compliance with the corresponding action in this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by 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 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. (4) Inspections required by this AD of specified areas of Principal Structural Element (PSE) 53.08.044 are acceptable for compliance with the applicable requirements of paragraphs (a) and (b) of AD 93-01-15, amendment 39-8469 (58 FR 5576, January 22, 1993). The remaining areas of the affected PSEs must be inspected and repaired as applicable, in accordance with AD 93-01-15. Material Incorporated by Reference (l) You must use Boeing Service Bulletin DC8-53-079, Revision 01, dated June 26, 2002, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on January 24, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-987 Filed 2-3-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracks in the fuselage skin at the corners of the doorjamb for the main cabin cargo door. We are issuing this AD to detect and correct fatigue cracks in the fuselage skin, which could result in rapid decompression of the airplane.