AD 2006-07-25 Airworthiness Directives; McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-50, -60, -60F, -70, and -70F Series Airplanes; Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-8

Models named: DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the airplanes listed in Table 1 of this AD, certificated in any category. Table 1.—Applicability McDonnell Douglas As identified in- Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-51, DC-8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-63 airplanes; Model DC-8-61F, DC-8-62F, and DC-8-63F airplanes; Model DC-8-71, DC-8-72, and DC-8-73 airplanes McDonnell Douglas DC-8 Alert Service Bulletin A27-273, dated May 16, 1989. Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41 airplanes; Model DC-9-51 airplanes; DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes McDonnell Douglas DC-9 Alert Service Bulletin Model A27-307, Revision 6, dated December 19, 1994.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 89-14-02 (f) Prior to the accumulation of 40,000 total landings or within 30 days after July 5, 1989 (the effective date of AD 89-14-02), whichever occurs later, perform either a general visual inspection or dye penetrant inspection for cracks of the captain's and first officer's rudder pedal bracket, part numbers (P/N) 5616067 and 5616068, respectively, in accordance with McDonnell Douglas DC-8 Alert Service Bulletin A27-273 (for Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-51, DC-8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-63 airplanes; Model DC-8-61F, DC-8-62F, and DC-8-63F airplanes; Model DC-8-71, DC-8-72, and DC-8-73 airplanes), or McDonnell Douglas DC-9 Alert Service Bulletin A27-307 (for Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41 airplanes; Model DC-9-51 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes), both Revision 1, both dated May 16, 1989, as applicable. Note 1: For the purposes of this AD, a general visual inspection is: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.” Note 2: McDonnell Douglas DC-8 Alert Service Bulletin A27-273 and McDonnell Douglas DC-9 Alert Service Bulletin A27-307, both Revision 1, both dated May 16, 1989, are hereinafter referred to as ASB A27-273 and ASB A27-307, respectively. (1) If an initial general visual inspection is accomplished, and no cracks are found, perform a dye penetrant inspection of the rudder pedal bracket assembly within 180 days after the general visual inspection, and thereafter accomplish dye penetrant inspections at intervals not to exceed 12 months or 2,500 landings, whichever occurs earlier. (2) If an initial dye penetrant inspection is accomplished, and no cracks are found, accomplish repetitive dye penetrant inspections at intervals not to exceed 12 months or 2,500 landings, whichever occurs earlier. (g) If cracks are detected, prior to further flight, remove and replace the rudder pedal bracket assembly in accordance with ASB A27-273 or A27-307, as applicable. Prior to the accumulation of 40,000 total landings after replacement with the new part, resume the repetitive inspections in accordance with paragraph (f) in this AD. New Requirements of This AD Terminating Action for Certain Airplanes (h) For McDonnell Douglas Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41 airplanes; Model DC-9-51 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes: Do the actions in paragraphs (h)(1) and (h)(2) of this AD in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Alert Service Bulletin A27-307, Revision 4, dated June 3, 1991; Revision 5, dated February 14, 1992; or Revision 6, dated December 19, 1994. (1) Before the accumulation of 75,000 total landings on the captain's rudder pedal bracket assembly, P/N 5616067-501, or within 60 months after the effective date of this AD, whichever occurs later: Remove the rudder pedal bracket assembly and replace it with new, improved P/N 5962903-501. Accomplishment of the replacement terminates the repetitive inspections of the captain's rudder pedal bracket assembly required by paragraphs (f) and (g) of this AD. (2) Before the accumulation of 75,000 total landings on the first officer's rudder pedal bracket assembly, P/N 5616068-501, or within 60 months after the effective date of this AD, whichever occurs later: Remove the rudder pedal bracket assembly and replace it with new, improved P/N 5962904-501. Accomplishment of the replacement terminates the repetitive inspections of the first officer's rudder pedal bracket assembly required by paragraphs (f) and (g) of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Los Angeles Aircraft Certification Office, 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 14 CFR 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) AMOCs, approved previously in accordance with AD 89-14-02, amendment 39-6245, are approved as AMOCs for the corresponding requirements of this AD. Material Incorporated by Reference (j) You must use the applicable service information identified in Table 2 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 2.—Material Incorporated by Reference Service bulletin Revision level Date McDonnell Douglas DC-8 Alert Service Bulletin A27-273 1 May 16, 1989. McDonnell Douglas DC-9 Alert Service Bulletin A27-307 1 May 16, 1989. McDonnell Douglas DC-9 Alert Service Bulletin A27-307 4 June 3, 1991. McDonnell Douglas DC-9 Alert Service Bulletin A27-307 5 February 14, 1992. McDonnell Douglas DC-9 Alert Service Bulletin A27-307 6 December 19, 1994. McDonnell Douglas Alert Service Bulletin A27-307, Revision 6, dated December 19, 1994, contains the following effective pages:   Page Number Revision level shown on page Date shown on page 1-24 6 December 19, 1994. 25-36 5 February 14, 1992. The Director of the Federal Register approved the incorporation by reference of these documents 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 March 31, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-3380 Filed 4-10-06; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by a report of numerous cracked rudder pedal brackets found during inspections of certain affected airplanes. We are issuing this AD to prevent failure of the rudder pedal bracket assembly, which could result in the loss of rudder and braking control at either the captain's or first officer's position.