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-88 Airplanes, 6578-6582 [E8-1813]

Download as PDF 6578 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations and Van Buren Counties, TN, to include the entirety of each county. Comments on the interim rule were required to be received on or before December 24, 2007. We did not receive any comments. Therefore, for the reasons given in the interim rule, we are adopting the interim rule as a final rule. This action also affirms the information contained in the interim rule regarding Executive Order 12866 and the Regulatory Flexibility Act, Executive Orders 12372 and 12988, and the Paperwork Reduction Act. Further, for this action, the Office of Management and Budget has waived its review under Executive Order 12866. List of Subjects in 7 CFR Part 301 Agricultural commodities, Plant diseases and pests, Quarantine, Reporting and recordkeeping requirements, Transportation. PART 301—DOMESTIC QUARANTINE NOTICES Accordingly, we are adopting as a final rule, without change, the interim rule that amended 7 CFR part 301 and that was published at 72 FR 60533– 60537 on October 25, 2007. I Done in Washington, DC, this 30th day of January 2008. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. E8–2048 Filed 2–4–08; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–29061; Directorate Identifier 2006–NM–243–AD; Amendment 39–15362; AD 2008–03–12] RIN 2120–AA64 rmajette on PROD1PC64 with RULES 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–88 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: VerDate Aug<31>2005 15:28 Feb 04, 2008 Jkt 214001 SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas airplanes. The existing AD currently requires an initial general visual or dye penetrant inspection, repetitive dye penetrant inspections, and replacement, as necessary, of the rudder pedal bracket. The existing AD also currently requires, for certain airplanes, replacing the rudder pedal bracket assemblies with new, improved parts, which would terminate the repetitive inspections. For certain airplanes, this new AD requires initial inspection at a reduced threshold, removes an inspection option, and lengthens the repetitive inspection intervals. This AD results from reports of failures of the captain’s rudder pedal brackets before reaching the initial inspection threshold identified in the existing AD. 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. DATES: This AD becomes effective March 11, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 11, 2008. On May 16, 2006 (71 FR 18201, April 11, 2006), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800– 0024). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5324; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2006–07–25, amendment 39–14552 (71 FR 18201, April 11, 2006). The existing AD applies to certain McDonnell Douglas airplanes. That NPRM was published in the Federal Register on August 31, 2007 (72 FR 50284). That NPRM proposed to retain the requirements of AD 2006–07–25. That NPRM also, for certain airplanes, proposed to reduce certain initial inspection thresholds, remove an inspection option, and lengthen certain repetitive inspection intervals. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Request To Clarify Repetitive Inspections Air Transport Association (ATA), on behalf of its member American Airlines, requests that we clarify paragraphs (h) and (l) of the NPRM. These paragraphs specify repetitive inspections to continue based on the part number of the replaced rudder pedal bracket assemblies in accordance with paragraph (g) or (k) of the NPRM. The commenters state that the referenced rudder pedal bracket assemblies should be clarified to indicate that repetitive inspections apply only to rudder pedal bracket assemblies that are of the same part number as the ones inspected. We agree with the request for the reasons stated. The intent of the replacement in paragraphs (h) and (l) of the NPRM is to replace the rudder pedal bracket assemblies with a part that has the same part number as the part inspected. Therefore, we have revised paragraph (h) and (l) of the AD to replace the words ‘‘new part’’ with ‘‘same part number as the one inspected.’’ Request To Clarify Inspection Criteria in Paragraph (j) of the NPRM ATA, on behalf of its member ASTAR Air Cargo, requests that we clarify the inspection criteria in paragraph (j) of the NPRM. The commenters note that paragraph (j) of the NPRM specifies a special detailed inspection in accordance with McDonnell Douglas E:\FR\FM\05FER1.SGM 05FER1 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations DC–8 Alert Service Bulletin A27–273, Revision 1, dated May 16, 1989; or Revision 5, dated February 18, 1993. The commenters point out that the service bulletins do not have any inspection criteria listed. We agree with the commenters that the paragraph needs clarification. The intent of paragraph (j) of the AD is to specify a general visual inspection and penetrant inspection for Category 2 airplanes in accordance with McDonnell Douglas DC–8 Alert Service Bulletin A27–273, Revision 1. Revision 1 of that service bulletin contains the inspection criteria. The intent of paragraph (j) was to specify a special detailed inspection for Category 4 airplanes in accordance with Boeing Alert Service Bulletin DC9– 27A307, Revision 7, dated August 29, 2006. Revision 7 of that service bulletin contains the inspection criteria. We have revised paragraph (j) of the AD to clarify the requirements. Request To Clarify Compliance Time in Paragraph (j)(1) of the NPRM ATA, on behalf of its member ASTAR Air Cargo, also notes that paragraph (j)(1) of the NPRM specifies a compliance time of within 40,000 total landings or 30 days after the effective date of the AD, whichever occurs later. The commenters state that paragraph (j)(1) should refer instead to 40,000 total landings on the installed part. We agree with the commenters. McDonnell Douglas DC–8 Alert Service Bulletin A27–273, Revision 1, and Revision 5, specify a compliance time based on the accumulation of 40,000 total landings on the bracket assembly. We have revised paragraph (j)(1) of the AD to specify that the compliance time is 40,000 total landings on the installed part. 6579 Conclusion We have carefully reviewed the available data, including the comments that have been received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 1,840 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. The replacements are applicable only to 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– 88 airplanes. ESTIMATED COSTS Average labor rate per hour Work hours Action Parts 3 $80 None ...... 5 80 None ...... $240, per inspection cycle. $400, per inspection cycle. 9 80 $9,466 .... $10,186 ................ Authority for This Rulemaking rmajette on PROD1PC64 with RULES General visual inspection (required by AD 2006–07–25). Dye penetrant (special detailed) inspection (required by AD 2006–07– 25). Replacements (required by AD 2006– 07–25). Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under VerDate Aug<31>2005 15:28 Feb 04, 2008 Jkt 214001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00003 Number of U.S.registered airplanes Fleet cost 250 .............. $60,000, per inspection cycle. 946 .............. $378,400, per inspection cycle. up to 946 ..... up to $9,635,956. Cost per airplane Fmt 4700 Sfmt 4700 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14552 (71 FR 18201, April 11, 2006) and by adding the following new airworthiness directive (AD): I 2008–03–12 McDonnell Douglas: Amendment 39–15362. Docket No. FAA–2007–29061; Directorate Identifier 2006–NM–243–AD. Effective Date (a) This AD becomes effective March 11, 2008. E:\FR\FM\05FER1.SGM 05FER1 6580 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations Affected ADs Applicability (c) This AD applies to the airplanes identified in Table 1 of this AD, certificated in any category. (b) This AD supersedes AD 2006–07–25. 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; Model DC–8–71F, DC–8–72F, and DC–8–73F airplanes. 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. McDonnell Douglas DC–8 Alert Service Bulletin A27–273, Revision 5, dated February 18, 1993. Unsafe Condition Service Information and Airplane Categories (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD. The term ‘‘airplane category,’’ as used in this AD, means the category identified in Table 2 of this AD. (d) This AD results from reports of failures of the captain’s rudder pedal brackets before reaching the initial inspection threshold identified in AD 2006–07–25. 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. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Boeing Alert Service Bulletin DC9–27A307, Revision 7, dated August 29, 2006. TABLE 2.—SERVICE INFORMATION AND AIRPLANE CATEGORIES Called airplane category— For Model— (1) 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. (2) DC–8–71F, DC–8–72F, and DC–8–73F airplanes ................................... (3) 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. (4) 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. Requirements of AD 2006–07–25 rmajette on PROD1PC64 with RULES Initial Inspection Threshold (g) For airplane categories 1, 3, and 4, 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, amendment 39–6245, which was superseded by AD 2006–07–25), whichever occurs later: Perform either a general visual inspection, dye penetrant inspection, or special detailed inspection (eddy current with dye penetrant or just dye penetrant), as applicable, for cracking of the captain’s and first officer’s rudder pedal bracket, part numbers (P/N) 5616067 and 5616068, respectively, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in Table 2 of this AD. After the effective date of this AD, only the special detailed inspection specified in Boeing Alert Service Bulletin DC9–27A307, Revision 7, VerDate Aug<31>2005 15:28 Feb 04, 2008 Jkt 214001 1 2 3 Use— McDonnell Douglas DC–8 Alert Service Bulletin A27–273, Revision 1, dated May 16, 1989; or Revision 5, dated February 18, 1993. McDonnell Douglas DC–9 Alert Service Bulletin A27–307, Revision 1, dated May 16, 1989; or Boeing Alert Service Bulletin DC9–27A307, Revision 7, dated August 29, 2006, after the effective date of this AD, only Revision 7 may be used. 4 dated August 29, 2006, may be used for airplanes identified in Revision 7. For airplane category 4: Do the inspection required by this paragraph until the inspection required by paragraph (j) of this AD is accomplished. 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.’’ PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 (1) If an initial general visual inspection is accomplished, and no crack is 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. For airplane categories 3 and 4, repeat at this interval until the inspection required by paragraph (k) of this AD is accomplished. (2) If an initial dye penetrant inspection is accomplished, and no crack is found, accomplish repetitive dye penetrant inspections at intervals not to exceed 12 months or 2,500 landings, whichever occurs earlier. For airplane categories 3 and 4, repeat at this interval until the inspection required by paragraph (k) of this AD is accomplished. (3) If an initial special detailed inspection is accomplished after the effective date of this AD, and no crack is found, repeat the E:\FR\FM\05FER1.SGM 05FER1 6581 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations inspection in accordance with paragraph (k) of this AD. Corrective Action (h) Except as provided by paragraph (l) of this AD: If any crack is detected during any inspection required by paragraph (g) or (j) of this AD, before further flight, remove and replace the rudder pedal bracket assembly in accordance with the service bulletin. Prior to the accumulation of 40,000 total landings after replacement with a part that has the same number as the part inspected, resume the repetitive inspections in accordance with paragraph (g) or (k) of this AD, as applicable. Doing the action required by paragraph (l) of this AD terminates the requirements of this paragraph for airplane category 4. Terminating Action for Certain Airplanes (i) For airplane categories 3 and 4: Do the actions in paragraphs (i)(1) and (i)(2) of this AD in accordance with the Accomplishment Instructions of the applicable service bulletin specified in Table 2 of this AD. (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 May 16, 2006, 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 (g), (h), (j), (k), and (l) 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 May 16, 2006, 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 (g), (h), (j), (k), and (l) of this AD. New Requirements of This AD Revised Initial Inspection at Reduced Threshold for Certain Airplanes (j) For airplane categories 2 and 4, at the applicable time specified in paragraph (j)(1), (j)(2) or (j)(3) of this AD: Do a general visual and penetrant inspection (for airplane category 2), and a special detailed inspection (for airplane category 4), as applicable, to detect cracking of the captain’s and first officer’s rudder pedal bracket, part numbers (P/N) 5616067 and 5616068, respectively, in accordance with the applicable service bulletin specified in Table 2 of this AD. Procedures for the dye penetrant inspection for airplane category 2 are contained only in the Accomplishment Instructions of McDonnell Douglas DC–8 Alert Service Bulletin A27–273, Revision 1, dated May 16, 1989. Procedures for the special detailed inspection are contained in Boeing Alert Service Bulletin DC9–27A307, Revision 7, dated August 29, 2006. Doing the applicable inspection required by this paragraph terminates the inspection requirements of paragraphs (g) and (h) of this AD for airplane category 4. (1) For category 2 airplanes: Before the accumulation of 40,000 total landings on the installed part, or within 30 days after the effective date of this AD, whichever occurs later. (2) For category 4 airplanes that have accumulated fewer than 25,000 total landings as of the effective date of this AD: Before the accumulation of 25,000 total landings, or within 3,000 landings after the effective date of this AD, whichever occurs later. (3) For category 4 airplanes that have accumulated 25,000 or more total landings as of the effective date of this AD, do the next inspection at the applicable time in paragraph (j)(3)(i) or (j)(3)(ii) of this AD. (i) For category 4 airplanes on which the corrective action specified in paragraph (h) of this AD has not been accomplished, do the inspection within 3,000 landings after the effective date of this AD. (ii) For category 4 airplanes on which the corrective action required by paragraph (h) of this AD has been accomplished, do the inspection at the earlier of the following: The next repetitive interval required by paragraph (h) of this AD; 40,000 total landings after doing the corrective action required by paragraph (h) of this AD; or 3,000 landings after the effective date of this AD. paragraph (g) or (j) of this AD thereafter at intervals not to exceed 3,000 landings. Doing the first repetitive inspection required by this paragraph terminates the repetitive inspection requirements of paragraph (g) of this AD for airplane categories 3 and 4. Repetitive Inspections at Revised Interval for Certain Airplanes (k) For airplane categories 3 and 4: Repeat the special detailed inspection required by (n) You must use the service information listed in Table 3 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Corrective Action Including Reduced Inspection Threshold for Certain Airplanes (l) For airplane category 4: If any crack is detected during any inspection required by paragraph (g), (j), or (k) of this AD: Before further flight, remove and replace the rudder pedal bracket assembly with a part that has the same part number as the one inspected, in accordance with the applicable service bulletin specified in Table 2 of this AD. Before the accumulation of 25,000 total landings after replacement, resume the repetitive inspections in accordance with paragraph (k) of this AD. Doing the action in this paragraph terminates the requirements of paragraph (h) of this AD for airplane category 4. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) AMOCs, approved previously in accordance with AD 2006–07–25, amendment 39–14552; and AD 89–14–02, amendment 39–6245; are approved as AMOCs for the corresponding requirements of this AD. Material Incorporated by Reference TABLE 3.—ALL MATERIAL INCORPORATED BY REFERENCE Revision level Service Bulletin rmajette on PROD1PC64 with RULES McDonnell Douglas DC–8 Alert Service Bulletin A27–273 ............................................................................. McDonnell Douglas DC–8 Alert Service Bulletin A27–273 ............................................................................. McDonnell Douglas DC–9 Alert Service Bulletin A27–307 ............................................................................. Boeing Alert Service bulletin DC9-27A307 ..................................................................................................... (1) The Director of the Federal Register approved the incorporation by reference of McDonnell Douglas DC–8 Alert Service Bulletin A27–273, Revision 5, dated February 18, 1993; and Boeing Alert Service Bulletin DC9–27A307, Revision 7, dated August 29, 2006; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. VerDate Aug<31>2005 15:28 Feb 04, 2008 Jkt 214001 (2) On May 16, 2006 (71 FR 18201, April 11, 2006), the Director of the Federal Register approved the incorporation by reference of McDonnell Douglas DC–8 Alert Service Bulletin A27–273, Revision 1, dated May 16, 1989; and McDonnell Douglas DC–9 Alert Service Bulletin A27–307, Revision 1, dated May 16, 1989. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Date 1 5 1 7 May 16, 1989. February 18, 1993. May 16, 1989. August 29, 2006. (3) 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 FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; E:\FR\FM\05FER1.SGM 05FER1 6582 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 24, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–1813 Filed 2–4–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28956; Directorate Identifier 2007–CE–068–AD; Amendment 39–15360; AD 2008–03–10] RIN 2120–AA64 Airworthiness Directives; Cessna Aircraft Company Models 525, 525A, and 525B Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 525, 525A, and 525B airplanes. This AD requires you to inspect the lower wing skin structure, forward wing spar, lower fuselage skin, fairings, and the external fairing frames for corrosion; repair any damage found; apply a corrosion inhibitive sealant to the fuselage fairings before reinstalling; and disable the cockpit mounted pilot relief tube. This AD results from leaking of the cockpit mounted pilot relief tube, which caused corrosion of the airplane structure. We are issuing this AD to detect and correct any damage from corrosion of the airplane structure. Corrosion of the airplane structure could cause structural degradation and lead to structural failure of the airplane with consequent loss of control. DATES: This AD becomes effective on March 11, 2008. On March 11, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: For service information identified in this AD, contact Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, Kansas 67277; telephone: 1–800–835– 4090; fax: 1–800–517–8500. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at https:// www.regulations.gov. The docket number is FAA–2007–28956; Directorate Identifier 2007–CE–068–AD. FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer,1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4155; fax: (316) 946–4107. SUPPLEMENTARY INFORMATION: include an AD that would apply to certain Cessna Models 525, 525A, and 525B airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on October 26, 2007 (72 FR 60790). The NPRM proposed to require you to inspect the lower wing skin structure, forward wing spar, lower fuselage skin, fairings, and the external fairing frames for corrosion; repair any damage found; apply a corrosion inhibitive sealant to the fuselage fairings before reinstalling; and disable the cockpit mounted pilot relief tube. Discussion On October 22, 2007, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to We estimate that this AD affects 261 airplanes in the U.S. registry. We estimate the following costs to do the inspection: Comments We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 80 work-hours × $80 per hour = $6,400 ................................................... Not applicable .................................. $6,400 $1,670,400 We have no way of determining the number of airplanes that may need repair or further inspection based on the results of the inspection, or the costs associated with such repair or inspection. We estimate the following costs to disable the cockpit mounted pilot relief tube: Parts cost Total cost per airplane Total cost on U.S. operators .5 work-hour × $80 per hour = $40 ........................................................... rmajette on PROD1PC64 with RULES Labor cost Not applicable .................................. $40 $10,440 Cessna will provide warranty credit to the extent specified in Cessna Citation Service Bulletin SB525–53–20, dated April 30, 2007; Cessna Citation Service Bulletin SB525A–53–01, dated April 30, 2007; Cessna Citation Service Bulletin SB525B–53–01, dated April 30, 2007; Cessna Citation Alert Service Letter VerDate Aug<31>2005 15:28 Feb 04, 2008 Jkt 214001 ASL525–53–04, Revision 2, dated August 19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 25, 2007; and Cessna Citation Alert Service Letter ASL525B–53–02, Revision 2, dated July 25, 2007. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more E:\FR\FM\05FER1.SGM 05FER1

Agencies

[Federal Register Volume 73, Number 24 (Tuesday, February 5, 2008)]
[Rules and Regulations]
[Pages 6578-6582]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-1813]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29061; Directorate Identifier 2006-NM-243-AD; 
Amendment 39-15362; AD 2008-03-12]
RIN 2120-AA64


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-88 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain McDonnell Douglas airplanes. The 
existing AD currently requires an initial general visual or dye 
penetrant inspection, repetitive dye penetrant inspections, and 
replacement, as necessary, of the rudder pedal bracket. The existing AD 
also currently requires, for certain airplanes, replacing the rudder 
pedal bracket assemblies with new, improved parts, which would 
terminate the repetitive inspections. For certain airplanes, this new 
AD requires initial inspection at a reduced threshold, removes an 
inspection option, and lengthens the repetitive inspection intervals. 
This AD results from reports of failures of the captain's rudder pedal 
brackets before reaching the initial inspection threshold identified in 
the existing AD. 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.

DATES: This AD becomes effective March 11, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 11, 
2008.
    On May 16, 2006 (71 FR 18201, April 11, 2006), the Director of the 
Federal Register approved the incorporation by reference of certain 
other publications listed in the AD.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024).

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5324; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-07-25, amendment 
39-14552 (71 FR 18201, April 11, 2006). The existing AD applies to 
certain McDonnell Douglas airplanes. That NPRM was published in the 
Federal Register on August 31, 2007 (72 FR 50284). That NPRM proposed 
to retain the requirements of AD 2006-07-25. That NPRM also, for 
certain airplanes, proposed to reduce certain initial inspection 
thresholds, remove an inspection option, and lengthen certain 
repetitive inspection intervals.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Clarify Repetitive Inspections

    Air Transport Association (ATA), on behalf of its member American 
Airlines, requests that we clarify paragraphs (h) and (l) of the NPRM. 
These paragraphs specify repetitive inspections to continue based on 
the part number of the replaced rudder pedal bracket assemblies in 
accordance with paragraph (g) or (k) of the NPRM. The commenters state 
that the referenced rudder pedal bracket assemblies should be clarified 
to indicate that repetitive inspections apply only to rudder pedal 
bracket assemblies that are of the same part number as the ones 
inspected.
    We agree with the request for the reasons stated. The intent of the 
replacement in paragraphs (h) and (l) of the NPRM is to replace the 
rudder pedal bracket assemblies with a part that has the same part 
number as the part inspected. Therefore, we have revised paragraph (h) 
and (l) of the AD to replace the words ``new part'' with ``same part 
number as the one inspected.''

Request To Clarify Inspection Criteria in Paragraph (j) of the NPRM

    ATA, on behalf of its member ASTAR Air Cargo, requests that we 
clarify the inspection criteria in paragraph (j) of the NPRM. The 
commenters note that paragraph (j) of the NPRM specifies a special 
detailed inspection in accordance with McDonnell Douglas

[[Page 6579]]

DC-8 Alert Service Bulletin A27-273, Revision 1, dated May 16, 1989; or 
Revision 5, dated February 18, 1993. The commenters point out that the 
service bulletins do not have any inspection criteria listed.
    We agree with the commenters that the paragraph needs 
clarification. The intent of paragraph (j) of the AD is to specify a 
general visual inspection and penetrant inspection for Category 2 
airplanes in accordance with McDonnell Douglas DC-8 Alert Service 
Bulletin A27-273, Revision 1. Revision 1 of that service bulletin 
contains the inspection criteria. The intent of paragraph (j) was to 
specify a special detailed inspection for Category 4 airplanes in 
accordance with Boeing Alert Service Bulletin DC9-27A307, Revision 7, 
dated August 29, 2006. Revision 7 of that service bulletin contains the 
inspection criteria. We have revised paragraph (j) of the AD to clarify 
the requirements.

Request To Clarify Compliance Time in Paragraph (j)(1) of the NPRM

    ATA, on behalf of its member ASTAR Air Cargo, also notes that 
paragraph (j)(1) of the NPRM specifies a compliance time of within 
40,000 total landings or 30 days after the effective date of the AD, 
whichever occurs later. The commenters state that paragraph (j)(1) 
should refer instead to 40,000 total landings on the installed part.
    We agree with the commenters. McDonnell Douglas DC-8 Alert Service 
Bulletin A27-273, Revision 1, and Revision 5, specify a compliance time 
based on the accumulation of 40,000 total landings on the bracket 
assembly. We have revised paragraph (j)(1) of the AD to specify that 
the compliance time is 40,000 total landings on the installed part.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 1,840 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD. The replacements are applicable 
only to 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-88 airplanes.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                  Average
                                         Work      labor                                                     Number of U.S.-
               Action                   hours     rate per         Parts            Cost per airplane     registered  airplanes         Fleet cost
                                                    hour
--------------------------------------------------------------------------------------------------------------------------------------------------------
General visual inspection (required           3        $80  None...............  $240, per inspection    250....................  $60,000, per
 by AD 2006-07-25).                                                               cycle.                                           inspection cycle.
Dye penetrant (special detailed)              5         80  None...............  $400, per inspection    946....................  $378,400, per
 inspection (required by AD 2006-07-                                              cycle.                                           inspection cycle.
 25).
Replacements (required by AD 2006-07-         9         80  $9,466.............  $10,186...............  up to 946..............  up to $9,635,956.
 25).
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14552 (71 FR 18201, April 11, 2006) and by adding 
the following new airworthiness directive (AD):

2008-03-12 McDonnell Douglas: Amendment 39-15362. Docket No. FAA-
2007-29061; Directorate Identifier 2006-NM-243-AD.

Effective Date

    (a) This AD becomes effective March 11, 2008.

[[Page 6580]]

Affected ADs

    (b) This AD supersedes AD 2006-07-25.

Applicability

    (c) This AD applies to the airplanes identified 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,   McDonnell Douglas DC-8 Alert
 DC-8-32, DC-8-33, DC-8-41, DC-8-42, and     Service Bulletin A27-273,
 DC-8-43 airplanes; Model DC-8-51, DC-8-     Revision 5, dated February
 52, DC-8-53, and DC-8-55 airplanes; Model   18, 1993.
 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; Model DC-8-71F, DC-8-72F,
 and DC-8-73F airplanes.
Model DC-9-11, DC-9-12, DC-9-13, DC-9-14,   Boeing Alert Service
 DC-9-15, and DC-9-15F airplanes; Model DC-  Bulletin DC9-27A307,
 9-21 airplanes; Model DC-9-31, DC-9-32,     Revision 7, dated August
 DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-  29, 2006.
 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.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of failures of the captain's 
rudder pedal brackets before reaching the initial inspection 
threshold identified in AD 2006-07-25. 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.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Information and Airplane Categories

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the applicable service bulletin 
identified in Table 2 of this AD. The term ``airplane category,'' as 
used in this AD, means the category identified in Table 2 of this 
AD.

          Table 2.--Service Information and Airplane Categories
------------------------------------------------------------------------
                                      Called
           For Model--               airplane              Use--
                                    category--
------------------------------------------------------------------------
(1) DC-8-11, DC-8-12, DC-8-21,                 1  McDonnell Douglas DC-8
 DC-8-31, DC-8-32, DC-8-33, DC-8-                  Alert Service
 41, DC-8-42, and DC-8-43                          Bulletin A27-273,
 airplanes; Model DC-8-51, DC-8-                   Revision 1, dated May
 52, DC-8-53, and DC-8-55                          16, 1989; or Revision
 airplanes; Model DC-8F-54 and                     5, dated February 18,
 DC-8F-55 airplanes; Model DC-8-                   1993.
 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.
(2) DC-8-71F, DC-8-72F, and DC-8-              2
 73F airplanes.
(3) DC-9-11, DC-9-12, DC-9-13,                 3  McDonnell Douglas DC-9
 DC-9-14, DC-9-15, and DC-9-15F                    Alert Service
 airplanes; Model DC-9-21                          Bulletin A27-307,
 airplanes; Model DC-9-31, DC-9-                   Revision 1, dated May
 32, DC-9-32 (VC-9C), DC-9-32F,                    16, 1989; or Boeing
 DC-9-33F, DC-9-34, DC-9-34F,                      Alert Service
 and DC-9-32F (C-9A, C-9B)                         Bulletin DC9-27A307,
 airplanes; Model DC-9-41                          Revision 7, dated
 airplanes; Model DC-9-51                          August 29, 2006,
 airplanes.                                        after the effective
                                                   date of this AD, only
                                                   Revision 7 may be
                                                   used.
(4) DC-9-81 (MD-81), DC-9-82 (MD-              4
 82), DC-9-83 (MD-83), and DC-9-
 87 (MD-87) airplanes; and Model
 MD-88 airplanes.
------------------------------------------------------------------------

Requirements of AD 2006-07-25

Initial Inspection Threshold

    (g) For airplane categories 1, 3, and 4, 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, amendment 39-6245, which 
was superseded by AD 2006-07-25), whichever occurs later: Perform 
either a general visual inspection, dye penetrant inspection, or 
special detailed inspection (eddy current with dye penetrant or just 
dye penetrant), as applicable, for cracking of the captain's and 
first officer's rudder pedal bracket, part numbers (P/N) 5616067 and 
5616068, respectively, in accordance with the Accomplishment 
Instructions of the applicable service bulletin specified in Table 2 
of this AD. After the effective date of this AD, only the special 
detailed inspection specified in Boeing Alert Service Bulletin DC9-
27A307, Revision 7, dated August 29, 2006, may be used for airplanes 
identified in Revision 7. For airplane category 4: Do the inspection 
required by this paragraph until the inspection required by 
paragraph (j) of this AD is accomplished.

    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.''

    (1) If an initial general visual inspection is accomplished, and 
no crack is 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. For airplane categories 3 and 4, repeat at this 
interval until the inspection required by paragraph (k) of this AD 
is accomplished.
    (2) If an initial dye penetrant inspection is accomplished, and 
no crack is found, accomplish repetitive dye penetrant inspections 
at intervals not to exceed 12 months or 2,500 landings, whichever 
occurs earlier. For airplane categories 3 and 4, repeat at this 
interval until the inspection required by paragraph (k) of this AD 
is accomplished.
    (3) If an initial special detailed inspection is accomplished 
after the effective date of this AD, and no crack is found, repeat 
the

[[Page 6581]]

inspection in accordance with paragraph (k) of this AD.

Corrective Action

    (h) Except as provided by paragraph (l) of this AD: If any crack 
is detected during any inspection required by paragraph (g) or (j) 
of this AD, before further flight, remove and replace the rudder 
pedal bracket assembly in accordance with the service bulletin. 
Prior to the accumulation of 40,000 total landings after replacement 
with a part that has the same number as the part inspected, resume 
the repetitive inspections in accordance with paragraph (g) or (k) 
of this AD, as applicable. Doing the action required by paragraph 
(l) of this AD terminates the requirements of this paragraph for 
airplane category 4.

Terminating Action for Certain Airplanes

    (i) For airplane categories 3 and 4: Do the actions in 
paragraphs (i)(1) and (i)(2) of this AD in accordance with the 
Accomplishment Instructions of the applicable service bulletin 
specified in Table 2 of this AD.
    (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 May 16, 2006, 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 (g), (h), (j), (k), and (l) 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 May 16, 2006, 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 (g), (h), (j), (k), and (l) of this 
AD.

New Requirements of This AD

Revised Initial Inspection at Reduced Threshold for Certain Airplanes

    (j) For airplane categories 2 and 4, at the applicable time 
specified in paragraph (j)(1), (j)(2) or (j)(3) of this AD: Do a 
general visual and penetrant inspection (for airplane category 2), 
and a special detailed inspection (for airplane category 4), as 
applicable, to detect cracking of the captain's and first officer's 
rudder pedal bracket, part numbers (P/N) 5616067 and 5616068, 
respectively, in accordance with the applicable service bulletin 
specified in Table 2 of this AD. Procedures for the dye penetrant 
inspection for airplane category 2 are contained only in the 
Accomplishment Instructions of McDonnell Douglas DC-8 Alert Service 
Bulletin A27-273, Revision 1, dated May 16, 1989. Procedures for the 
special detailed inspection are contained in Boeing Alert Service 
Bulletin DC9-27A307, Revision 7, dated August 29, 2006. Doing the 
applicable inspection required by this paragraph terminates the 
inspection requirements of paragraphs (g) and (h) of this AD for 
airplane category 4.
    (1) For category 2 airplanes: Before the accumulation of 40,000 
total landings on the installed part, or within 30 days after the 
effective date of this AD, whichever occurs later.
    (2) For category 4 airplanes that have accumulated fewer than 
25,000 total landings as of the effective date of this AD: Before 
the accumulation of 25,000 total landings, or within 3,000 landings 
after the effective date of this AD, whichever occurs later.
    (3) For category 4 airplanes that have accumulated 25,000 or 
more total landings as of the effective date of this AD, do the next 
inspection at the applicable time in paragraph (j)(3)(i) or 
(j)(3)(ii) of this AD.
    (i) For category 4 airplanes on which the corrective action 
specified in paragraph (h) of this AD has not been accomplished, do 
the inspection within 3,000 landings after the effective date of 
this AD.
    (ii) For category 4 airplanes on which the corrective action 
required by paragraph (h) of this AD has been accomplished, do the 
inspection at the earlier of the following: The next repetitive 
interval required by paragraph (h) of this AD; 40,000 total landings 
after doing the corrective action required by paragraph (h) of this 
AD; or 3,000 landings after the effective date of this AD.

Repetitive Inspections at Revised Interval for Certain Airplanes

    (k) For airplane categories 3 and 4: Repeat the special detailed 
inspection required by paragraph (g) or (j) of this AD thereafter at 
intervals not to exceed 3,000 landings. Doing the first repetitive 
inspection required by this paragraph terminates the repetitive 
inspection requirements of paragraph (g) of this AD for airplane 
categories 3 and 4.

Corrective Action Including Reduced Inspection Threshold for Certain 
Airplanes

    (l) For airplane category 4: If any crack is detected during any 
inspection required by paragraph (g), (j), or (k) of this AD: Before 
further flight, remove and replace the rudder pedal bracket assembly 
with a part that has the same part number as the one inspected, in 
accordance with the applicable service bulletin specified in Table 2 
of this AD. Before the accumulation of 25,000 total landings after 
replacement, resume the repetitive inspections in accordance with 
paragraph (k) of this AD. Doing the action in this paragraph 
terminates the requirements of paragraph (h) of this AD for airplane 
category 4.

Alternative Methods of Compliance (AMOCs)

     (m)(1) The Manager, Los Angeles Aircraft Certification Office, 
Transport Airplane Directorate, FAA, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) AMOCs, approved previously in accordance with AD 2006-07-25, 
amendment 39-14552; and AD 89-14-02, amendment 39-6245; are approved 
as AMOCs for the corresponding requirements of this AD.

Material Incorporated by Reference

    (n) You must use the service information listed in Table 3 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

             Table 3.--All Material Incorporated by Reference
------------------------------------------------------------------------
                                  Revision
        Service Bulletin           level                 Date
------------------------------------------------------------------------
 McDonnell Douglas DC-8 Alert             1  May 16, 1989.
 Service Bulletin A27-273.
 McDonnell Douglas DC-8 Alert             5  February 18, 1993.
 Service Bulletin A27-273.
 McDonnell Douglas DC-9 Alert             1  May 16, 1989.
 Service Bulletin A27-307.
 Boeing Alert Service bulletin            7  August 29, 2006.
 DC9-27A307.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of McDonnell Douglas DC-8 Alert Service 
Bulletin A27-273, Revision 5, dated February 18, 1993; and Boeing 
Alert Service Bulletin DC9-27A307, Revision 7, dated August 29, 
2006; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On May 16, 2006 (71 FR 18201, April 11, 2006), the Director 
of the Federal Register approved the incorporation by reference of 
McDonnell Douglas DC-8 Alert Service Bulletin A27-273, Revision 1, 
dated May 16, 1989; and McDonnell Douglas DC-9 Alert Service 
Bulletin A27-307, Revision 1, dated May 16, 1989.
    (3) 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 FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington;

[[Page 6582]]

or at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal-register/cfr/
ibr-locations.html.

    Issued in Renton, Washington, on January 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-1813 Filed 2-4-08; 8:45 am]
BILLING CODE 4910-13-P