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-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; and Model DC-8-71F, DC-8-72F, and DC-8-73F Airplanes, 78936-78939 [E8-29233]

Download as PDF 78936 Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0123; Directorate Identifier 2007–NM–056–AD; Amendment 39–15763; AD 2008–25–05] 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–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; and Model DC–8–71F, DC–8–72F, and DC–8–73F Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. approval was predicated. We are issuing this AD to detect and correct fatigue cracking that could compromise the structural integrity of these airplanes. DATES: This AD becomes effective January 28, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of January 28, 2009. On February 26, 1993 (58 FR 5576, January 22, 1993), the Director of the Federal Register approved the incorporation by reference of certain other publications. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. Examining the AD Docket SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to all McDonnell Douglas Model DC–8 airplanes. That AD currently requires, among other things, revision of an existing program of structural inspections. This new AD requires implementation of a revised program of structural inspections of baseline structure to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer’s original fatigue design life goal. This new AD also reduces the inspection threshold for certain principal structural elements. This AD results from a significant number of these airplanes approaching or exceeding the design service goal on which the initial type certification You may examine the AD docket on the Internet at http:// 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: Dara Albouyeh, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5222; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 93–01–15, amendment 39–8469 (58 FR 5576, January 22, 1993). The existing AD applies to all McDonnell Douglas Model DC–8 airplanes. That supplemental NPRM was published in the Federal Register on August 29, 2008 (73 FR 50906). That supplemental NPRM proposed to continue to require, among other things, revision of an existing program of structural inspections. That supplemental NPRM also proposed to require implementation of a revised program of structural inspections of baseline structure to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer’s original fatigue design life goal. That supplemental NPRM also proposed to reduce the inspection threshold for certain principal structural elements. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM 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. Costs of Compliance There are about 194 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. ESTIMATED COSTS Average labor rate per hour Revision of maintenance inspection program (required by AD 93–01–15. Revision of maintenance program and inspections (new actions). pwalker on PROD1PC71 with RULES Work hours 544 per operator (17 U.S. operators). $80 $43,520, per operator ......... 131 $739,840 250 per operator (17 U.S. operators). 80 $20,000 ............................... 131 340,000 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Aug<31>2005 19:28 Dec 23, 2008 Jkt 217001 Cost per operator Number of U.S.registered airplanes Action rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Fleet cost detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, E:\FR\FM\24DER1.SGM 24DER1 Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–8469 (58 FR 5576, January 22, 1993) and by adding the following new airworthiness directive (AD): pwalker on PROD1PC71 with RULES ■ 2008–25–05 McDonnell Douglas: Amendment 39–15763. Docket No. VerDate Aug<31>2005 19:28 Dec 23, 2008 Jkt 217001 FAA–2008–0123; Directorate Identifier 2007–NM–056–AD. Effective Date (a) This AD becomes effective January 28, 2009. Affected ADs (b) This AD supersedes AD 93–01–15. Applicability (c) This AD applies to all McDonnell Douglas airplanes identified in Table 1 of this AD, certificated in any category. TABLE 1—APPLICABILITY 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. (2) DC–8–51, DC–8–52, DC–8–53, and DC– 8–55 airplanes. (3) DC–8F–54 and DC–8F–55 airplanes. (4) DC–8–61, DC–8–62, and DC–8–63 airplanes. (5) DC–8–61F, DC–8–62F, and DC–8–63F airplanes. (6) DC–8–71, DC–8–72, and DC–8–73 airplanes. (7) DC–8–71F, DC–8–72F, and DC–8–73F airplanes. Unsafe Condition (d) This AD results from a significant number of these airplanes approaching or exceeding the design service goal on which the initial type certification approval was predicated. We are issuing this AD to detect and correct fatigue cracking that could compromise the structural integrity of these airplanes. 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. Certain Requirements of AD 93–01–15 Revise the FAA-Approved Maintenance Inspection Program (f) Within 6 months after February 26, 1993 (the effective date of AD 93–01–15), incorporate a revision of the FAA-approved maintenance inspection program that provides no less than the required inspection of the Principal Structural Elements (PSEs) defined in sections 2 and 3 of Volume I of McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Revision 3, dated March 1991, in accordance with section 2 of Volume III–91, dated April 1991, of that document. The nondestructive inspection techniques set forth in sections 2 and 3 of Volume II, Revision 5, dated March 1991, of that SID provide acceptable methods for accomplishing the inspections required by this AD. All inspection results, negative or positive, must be reported to McDonnell Douglas, in accordance with the instructions of section 2 of Volume III–91 of the SID. Information collection requirements contained in this PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 78937 regulation have been approved by the OMB under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120–0056. Corrective Action (g) Cracked structure detected during the inspections required by paragraph (f) of this AD must be repaired before further flight, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. New Requirements of This AD Revision of the Maintenance Inspection Program (h) Within 12 months after the effective date of this AD, incorporate a revision of the FAA-approved maintenance inspection program that provides for inspection(s) of the PSEs, in accordance with Boeing Report No. L26–011, ‘‘DC–8 All Series Supplemental Inspection Document (SID),’’ Volume I, Revision 7, dated March 2008. Incorporation of this revision ends the requirements of paragraphs (f) and (g) of this AD. Non-Destructive Inspections (NDIs) (i) For all PSEs listed in Section 2 of Boeing Report No. L26–011, ‘‘DC–8 All Series Supplemental Inspection Document (SID),’’ Volume I, Revision 7, dated March 2008, perform an NDI for fatigue cracking of each PSE, in accordance with the NDI procedures specified in Section 2 of McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume II, Revision 8, dated January 2005, at the times specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable. (1) For airplanes that have less than three quarters of the fatigue life threshold (3⁄4NTH) as of the effective date of this AD: Perform the NDI for fatigue cracking at the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. After reaching the threshold (NTH), repeat the inspection for that PSE at intervals not to exceed DNDI/2. (i) Perform an initial NDI no earlier than one-half of the threshold (1⁄2NTH) but before reaching three-quarters of the threshold (3⁄4NTH), or within 60 months after the effective date of this AD, whichever occurs later. (ii) Repeat the NDI no earlier than 3⁄4NTH but before reaching the threshold (NTH), or within 18 months after the inspection required by paragraph (i)(1)(i) of this AD, whichever occurs later. Note 1: The DC–8 SID and this AD refer to the repetitive inspection interval as DNDI/2. However, the headings of the tables in section 4 of Volume I, Revision 7, dated March 2008, of the DC–8 SID refer to the repetitive inspection interval of NDI/2. The values listed under NDI/2 in the tables in section 4 of Volume I, Revision 7, dated March 2008, of the DC–8 SID are the repetitive inspection intervals, DNDI/2. (2) For airplanes that have reached or exceeded three-quarters of the fatigue life threshold (3⁄4NTH), but less than the threshold (NTH), as of the effective date of this AD: Perform an NDI before reaching the threshold E:\FR\FM\24DER1.SGM 24DER1 78938 Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations (NTH), or within 18 months after the effective date of this AD, whichever occurs later. Thereafter, after passing the threshold (NTH), repeat the inspection for that PSE at intervals not to exceed DNDI/2. (3) For airplanes that have reached or exceeded the fatigue life threshold (NTH) as of the effective date of this AD: Perform an NDI within 18 months after the effective date of this AD. Thereafter, repeat the inspection for that PSE at intervals not to exceed DNDI/2. Discrepant Findings (j) If any discrepancy (e.g., differences on the airplane from the NDI reference standard, such as PSEs that cannot be inspected as specified in McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume II, Revision 8, dated January 2005, or do not match rework, repair, or modification descriptions in Boeing Report No. L26–011, ‘‘DC–8 All Series Supplemental Inspection Document (SID),’’ Volume I, Revision 7, dated March 2008) is detected during any inspection required by paragraph (i) of this AD, do the action specified in paragraph (j)(1) or (j)(2) of this AD, as applicable. (1) If a discrepancy is detected during any inspection done before 3⁄4NTH or NTH: The area of the PSE affected by the discrepancy must be inspected before NTH or within 18 months after the discovery of the discrepancy, whichever occurs later, in accordance with a method approved by the Manager, Los Angeles ACO. (2) If a discrepancy is detected during any inspection done after NTH: The area of the PSE affected by the discrepancy must be inspected before the accumulation of an additional DNDI/2 or within 18 months after the discovery of the discrepancy, whichever occurs later, in accordance with a method approved by the Manager, Los Angeles ACO. Reporting Requirements (k) All negative or positive findings of the inspections done in accordance with paragraph (i) of this AD must be reported to Boeing at the times specified in, and in accordance with, the instructions contained in section 4 of Boeing Report No. L26–011, ‘‘DC–8 All Series Supplemental Inspection Document (SID),’’ Volume I, Revision 7, dated March 2008. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120–0056. Corrective Actions (l) Any cracked structure of a PSE detected during any inspection required by paragraph (i) of this AD must be repaired before further flight using a method approved in accordance with the procedures specified in paragraph (p) of this AD. Accomplish the actions described in paragraphs (l)(1), (l)(2), and (l)(3) of this AD, at the times specified. (1) Within 18 months after repair, do a damage tolerance assessment (DTA) that defines the threshold for inspection of the repair and submit the assessment for approval. (2) Before reaching 75 percent of the repair threshold as determined in paragraph (l)(1) of this AD, submit the inspection methods and repetitive inspection intervals for the repair for approval. (3) Before the repair threshold, as determined in paragraph (l)(1) of this AD, incorporate the inspection method and repetitive inspection intervals into the FAAapproved structural maintenance or inspection program for the airplane. Note 2: For the purposes of this AD, we anticipate that submissions of the DTA of the repair, if acceptable, should be approved within 6 months after submission. Note 3: FAA Order 8110.54, ‘‘Instructions for Continued Airworthiness, Responsibilities, Requirements, and Contents’’ dated July 1, 2005, provides additional guidance about the approval of repairs to PSEs. Inspection for Transferred Airplanes (m) Before any airplane that has exceeded the fatigue life threshold (NTH) can be added to an air carrier’s operations specifications, a program for the accomplishment of the inspections required by this AD must be established as specified in paragraph (m)(1) or (m)(2) of this AD, as applicable. (1) For airplanes that have been inspected in accordance with this AD: The inspection of each PSE must be done by the new operator in accordance with the previous operator’s schedule and inspection method, or the new operator’s schedule and inspection method, at whichever time would result in the earlier accomplishment date for that PSE inspection. The compliance time for accomplishing this inspection must be measured from the last inspection done by the previous operator. After each inspection has been done once, each subsequent inspection must be done in accordance with the new operator’s schedule and inspection method. (2) For airplanes that have not been inspected in accordance with this AD: The inspection of each PSE required by this AD must be done either before adding the airplane to the air carrier’s operations specification, or in accordance with a schedule and an inspection method approved by the Manager, Los Angeles ACO. After each inspection has been done once, each subsequent inspection must be done in accordance with the new operator’s schedule. Acceptable for Compliance (n) McDonnell Douglas Report No. MDC 91K0262, ‘‘DC–8 Aging Aircraft Repair Assessment Program Document,’’ Revision 1, dated October 2000, provides inspection/ replacement programs for certain repairs to the fuselage pressure shell. Accomplishing these repairs and inspection/replacement programs before the effective date of this AD is considered acceptable for compliance with the requirements of paragraphs (g) and (l) of this AD for repairs subject to that document. (o) Actions done before the effective date of this AD in accordance with Boeing Report No. L26–011, ‘‘DC–8 All Series Supplemental Inspection Document (SID),’’ Volume I, Revision 6, dated July 2005, are acceptable for compliance with the corresponding requirements of this AD. Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, Los Angeles ACO, FAA, ATTN: Dara Albouyeh, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5222; fax (562) 627–5210; has the authority to approve AMOCs for this AD, if requested using 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) 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) AMOCs approved previously in accordance with AD 93–01–15 are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (q) You must use the service information identified in Table 2 of this AD to perform the actions that are required by this AD, as applicable, unless the AD specifies otherwise. pwalker on PROD1PC71 with RULES TABLE 2—MATERIAL INCORPORATED BY REFERENCE Service information Revision level Boeing Report No. L26–011, ‘‘DC–8 All Series Supplemental Inspection Document (SID),’’ Volume I .......... McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume I ...... McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume II ..... 7 ....................... 3 ....................... 8 ....................... VerDate Aug<31>2005 19:28 Dec 23, 2008 Jkt 217001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\24DER1.SGM 24DER1 Date March 2008. March 1991. January 2005. Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations 78939 TABLE 2—MATERIAL INCORPORATED BY REFERENCE—Continued Service information Revision level McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume III–91 Original ............. Boeing Report No. L26–011, ‘‘DC–8 All Series Supplemental Inspection Document (SID),’’ Volume I, Revision 7, dated March 2008, contains the following effective pages: Pages Revision List of Effective Pages, Pages A through C. Date 7 March 2008. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume II, Revision 8, dated January 2005, contains the following effective pages: Pages Revision pwalker on PROD1PC71 with RULES List of Effective Pages, Pages A through L. 8 March 2008. 19:28 Dec 23, 2008 Jkt 217001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1328; Directorate Identifier 2008–CE–066–AD; Amendment 39–15776; AD 2008–26–10] Date RIN 2120–AA64 (1) The Director of the Federal Register approved the incorporation by reference of Boeing Report No. L26–011, ‘‘DC–8 All Series Supplemental Inspection Document (SID),’’ Volume I, Revision 7, dated March 2008; and McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume II, Revision 8, dated January 2005; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On February 26, 1993 (58 FR 5576, January 22, 1993), the Director of the Federal Register approved the incorporation by reference of McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume I, Revision 3, dated March 1991; and McDonnell Douglas Report No. L26–011, ‘‘DC–8 Supplemental Inspection Document (SID),’’ Volume III–91, dated April 1991. (3) Contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766– 5683; e-mail dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. (4) You may review copies of the service information that is incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (5) You may also review copies of the service information 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: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. VerDate Aug<31>2005 Issued in Renton, Washington, on November 26, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–29233 Filed 12–23–08; 8:45 am] Airworthiness Directives; Cessna Aircraft Company 172, 175, 177, 180, 182, 185, 188, 206, 207, 208, 210, 303, 336, and 337 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) 172, 175, 177, 180, 182, 185, 188, 206, 207, 208, 210, 303, 336, and 337 series airplanes. This AD requires you to inspect the alternate static air source selector valve to assure that the part number identification placard does not obstruct the alternate static air source selector valve port. If the part number identification placard obstructs the port, this AD also requires you to remove the placard, assure that the port is unobstructed, and report to the FAA if obstruction is found. This AD results from reports of airplanes found with alternate static air source selector valve port obstruction caused by improper installation of the part number identification placard. The actions specified by this AD are intended to prevent erroneous indications from the altimeter, airspeed, and vertical speed indicators, which could cause the pilot to react to incorrect flight information and possibly result in loss of control. DATES: This AD becomes effective on January 5, 2009. On January 5, 2009, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 Date April 1991. We must receive any comments on this AD by February 23, 2009. ADDRESSES: Use one of the following addresses to comment on this AD. • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. To get the service information identified in this AD, contact Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277; telephone: (800) 423–7762 or (316) 517–6056; Internet: http://www.cessna.com. To view the comments to this AD, go to http://www.regulations.gov. The docket number is FAA–2008–1328; Directorate Identifier 2008–CE–066–AD. FOR FURTHER INFORMATION CONTACT: Ann Johnson, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: 316–946– 4105; fax: 316–946–4107; e-mail address: ann.johnson@faa.gov. SUPPLEMENTARY INFORMATION: Discussion Reports of improper installation of the part number (P/N) identification placard on P/N 2013142–18 alternate static air source selector valves prompted us to issue AD 98–01–01, Amendment 39– 10286 (63 FR 3455, January 23, 1998), which applies to certain Cessna Aircraft Company (Cessna) Models 172R and 182S airplanes, and AD 2008–10–02, Amendment 39–155508 (73 FR 24168, May 2, 2008), which applies to certain Cessna 172, 175, 180, 182, 185, 206, 207, 208, 210, and 303 series airplanes. These ADs require inspecting the alternate static air source selector valve to determine if the P/N identification placard obstructs the alternate static air source selector valve port and removing E:\FR\FM\24DER1.SGM 24DER1

Agencies

[Federal Register Volume 73, Number 248 (Wednesday, December 24, 2008)]
[Rules and Regulations]
[Pages 78936-78939]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-29233]



[[Page 78936]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0123; Directorate Identifier 2007-NM-056-AD; 
Amendment 39-15763; AD 2008-25-05]
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-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; and Model DC-8-71F, DC-8-72F, 
and DC-8-73F Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all McDonnell Douglas Model DC-8 airplanes. That 
AD currently requires, among other things, revision of an existing 
program of structural inspections. This new AD requires implementation 
of a revised program of structural inspections of baseline structure to 
detect and correct fatigue cracking in order to ensure the continued 
airworthiness of these airplanes as they approach the manufacturer's 
original fatigue design life goal. This new AD also reduces the 
inspection threshold for certain principal structural elements. This AD 
results from a significant number of these airplanes approaching or 
exceeding the design service goal on which the initial type 
certification approval was predicated. We are issuing this AD to detect 
and correct fatigue cracking that could compromise the structural 
integrity of these airplanes.

DATES: This AD becomes effective January 28, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of January 28, 
2009.
    On February 26, 1993 (58 FR 5576, January 22, 1993), the Director 
of the Federal Register approved the incorporation by reference of 
certain other publications.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
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: Dara Albouyeh, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5222; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a supplemental notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that supersedes AD 93-01-15, 
amendment 39-8469 (58 FR 5576, January 22, 1993). The existing AD 
applies to all McDonnell Douglas Model DC-8 airplanes. That 
supplemental NPRM was published in the Federal Register on August 29, 
2008 (73 FR 50906). That supplemental NPRM proposed to continue to 
require, among other things, revision of an existing program of 
structural inspections. That supplemental NPRM also proposed to require 
implementation of a revised program of structural inspections of 
baseline structure to detect and correct fatigue cracking in order to 
ensure the continued airworthiness of these airplanes as they approach 
the manufacturer's original fatigue design life goal. That supplemental 
NPRM also proposed to reduce the inspection threshold for certain 
principal structural elements.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM 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.

Costs of Compliance

    There are about 194 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.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number of
                                                         Average                           U.S.-
             Action                    Work hours       labor rate   Cost per operator   registered   Fleet cost
                                                         per hour                        airplanes
----------------------------------------------------------------------------------------------------------------
Revision of maintenance           544 per operator             $80  $43,520, per                131     $739,840
 inspection program (required by   (17 U.S.                          operator.
 AD 93-01-15.                      operators).
Revision of maintenance program   250 per operator              80  $20,000...........          131      340,000
 and inspections (new actions).    (17 U.S.
                                   operators).
----------------------------------------------------------------------------------------------------------------

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,

[[Page 78937]]

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 39-8469 (58 FR 5576, January 22, 1993) and by adding 
the following new airworthiness directive (AD):

2008-25-05 McDonnell Douglas: Amendment 39-15763. Docket No. FAA-
2008-0123; Directorate Identifier 2007-NM-056-AD.

Effective Date

    (a) This AD becomes effective January 28, 2009.

Affected ADs

    (b) This AD supersedes AD 93-01-15.

Applicability

    (c) This AD applies to all McDonnell Douglas airplanes 
identified in Table 1 of this AD, certificated in any category.

                         Table 1--Applicability
------------------------------------------------------------------------
                                  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.
(2) DC-8-51, DC-8-52, DC-8-53, and DC-8-55 airplanes.
(3) DC-8F-54 and DC-8F-55 airplanes.
(4) DC-8-61, DC-8-62, and DC-8-63 airplanes.
(5) DC-8-61F, DC-8-62F, and DC-8-63F airplanes.
(6) DC-8-71, DC-8-72, and DC-8-73 airplanes.
(7) DC-8-71F, DC-8-72F, and DC-8-73F airplanes.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a significant number of these airplanes 
approaching or exceeding the design service goal on which the 
initial type certification approval was predicated. We are issuing 
this AD to detect and correct fatigue cracking that could compromise 
the structural integrity of these airplanes.

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.

Certain Requirements of AD 93-01-15

Revise the FAA-Approved Maintenance Inspection Program

    (f) Within 6 months after February 26, 1993 (the effective date 
of AD 93-01-15), incorporate a revision of the FAA-approved 
maintenance inspection program that provides no less than the 
required inspection of the Principal Structural Elements (PSEs) 
defined in sections 2 and 3 of Volume I of McDonnell Douglas Report 
No. L26-011, ``DC-8 Supplemental Inspection Document (SID),'' 
Revision 3, dated March 1991, in accordance with section 2 of Volume 
III-91, dated April 1991, of that document. The non-destructive 
inspection techniques set forth in sections 2 and 3 of Volume II, 
Revision 5, dated March 1991, of that SID provide acceptable methods 
for accomplishing the inspections required by this AD. All 
inspection results, negative or positive, must be reported to 
McDonnell Douglas, in accordance with the instructions of section 2 
of Volume III-91 of the SID. Information collection requirements 
contained in this regulation have been approved by the OMB under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.

Corrective Action

    (g) Cracked structure detected during the inspections required 
by paragraph (f) of this AD must be repaired before further flight, 
in accordance with a method approved by the Manager, Los Angeles 
Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate.

New Requirements of This AD

Revision of the Maintenance Inspection Program

    (h) Within 12 months after the effective date of this AD, 
incorporate a revision of the FAA-approved maintenance inspection 
program that provides for inspection(s) of the PSEs, in accordance 
with Boeing Report No. L26-011, ``DC-8 All Series Supplemental 
Inspection Document (SID),'' Volume I, Revision 7, dated March 2008. 
Incorporation of this revision ends the requirements of paragraphs 
(f) and (g) of this AD.

Non-Destructive Inspections (NDIs)

    (i) For all PSEs listed in Section 2 of Boeing Report No. L26-
011, ``DC-8 All Series Supplemental Inspection Document (SID),'' 
Volume I, Revision 7, dated March 2008, perform an NDI for fatigue 
cracking of each PSE, in accordance with the NDI procedures 
specified in Section 2 of McDonnell Douglas Report No. L26-011, 
``DC-8 Supplemental Inspection Document (SID),'' Volume II, Revision 
8, dated January 2005, at the times specified in paragraph (i)(1), 
(i)(2), or (i)(3) of this AD, as applicable.
    (1) For airplanes that have less than three quarters of the 
fatigue life threshold (\3/4\NTH) as of the effective 
date of this AD: Perform the NDI for fatigue cracking at the times 
specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. After 
reaching the threshold (NTH), repeat the inspection for 
that PSE at intervals not to exceed [Delta]NDI/2.
    (i) Perform an initial NDI no earlier than one-half of the 
threshold (\1/2\NTH) but before reaching three-quarters 
of the threshold (\3/4\NTH), or within 60 months after 
the effective date of this AD, whichever occurs later.
    (ii) Repeat the NDI no earlier than \3/4\NTH but 
before reaching the threshold (NTH), or within 18 months 
after the inspection required by paragraph (i)(1)(i) of this AD, 
whichever occurs later.

    Note 1: The DC-8 SID and this AD refer to the repetitive 
inspection interval as [Delta]NDI/2. However, the headings of the 
tables in section 4 of Volume I, Revision 7, dated March 2008, of 
the DC-8 SID refer to the repetitive inspection interval of NDI/2. 
The values listed under NDI/2 in the tables in section 4 of Volume 
I, Revision 7, dated March 2008, of the DC-8 SID are the repetitive 
inspection intervals, [Delta]NDI/2.

    (2) For airplanes that have reached or exceeded three-quarters 
of the fatigue life threshold (\3/4\NTH), but less than 
the threshold (NTH), as of the effective date of this AD: 
Perform an NDI before reaching the threshold

[[Page 78938]]

(NTH), or within 18 months after the effective date of 
this AD, whichever occurs later. Thereafter, after passing the 
threshold (NTH), repeat the inspection for that PSE at 
intervals not to exceed [Delta]NDI/2.
    (3) For airplanes that have reached or exceeded the fatigue life 
threshold (NTH) as of the effective date of this AD: 
Perform an NDI within 18 months after the effective date of this AD. 
Thereafter, repeat the inspection for that PSE at intervals not to 
exceed [Delta]NDI/2.

Discrepant Findings

    (j) If any discrepancy (e.g., differences on the airplane from 
the NDI reference standard, such as PSEs that cannot be inspected as 
specified in McDonnell Douglas Report No. L26-011, ``DC-8 
Supplemental Inspection Document (SID),'' Volume II, Revision 8, 
dated January 2005, or do not match rework, repair, or modification 
descriptions in Boeing Report No. L26-011, ``DC-8 All Series 
Supplemental Inspection Document (SID),'' Volume I, Revision 7, 
dated March 2008) is detected during any inspection required by 
paragraph (i) of this AD, do the action specified in paragraph 
(j)(1) or (j)(2) of this AD, as applicable.
    (1) If a discrepancy is detected during any inspection done 
before \3/4\NTH or NTH: The area of the PSE 
affected by the discrepancy must be inspected before NTH 
or within 18 months after the discovery of the discrepancy, 
whichever occurs later, in accordance with a method approved by the 
Manager, Los Angeles ACO.
    (2) If a discrepancy is detected during any inspection done 
after NTH: The area of the PSE affected by the 
discrepancy must be inspected before the accumulation of an 
additional [Delta]NDI/2 or within 18 months after the discovery of 
the discrepancy, whichever occurs later, in accordance with a method 
approved by the Manager, Los Angeles ACO.

Reporting Requirements

    (k) All negative or positive findings of the inspections done in 
accordance with paragraph (i) of this AD must be reported to Boeing 
at the times specified in, and in accordance with, the instructions 
contained in section 4 of Boeing Report No. L26-011, ``DC-8 All 
Series Supplemental Inspection Document (SID),'' Volume I, Revision 
7, dated March 2008. Information collection requirements contained 
in this regulation have been approved by the Office of Management 
and Budget (OMB) under the provisions of the Paperwork Reduction Act 
of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control 
Number 2120-0056.

Corrective Actions

    (l) Any cracked structure of a PSE detected during any 
inspection required by paragraph (i) of this AD must be repaired 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (p) of this AD. Accomplish the 
actions described in paragraphs (l)(1), (l)(2), and (l)(3) of this 
AD, at the times specified.
    (1) Within 18 months after repair, do a damage tolerance 
assessment (DTA) that defines the threshold for inspection of the 
repair and submit the assessment for approval.
    (2) Before reaching 75 percent of the repair threshold as 
determined in paragraph (l)(1) of this AD, submit the inspection 
methods and repetitive inspection intervals for the repair for 
approval.
    (3) Before the repair threshold, as determined in paragraph 
(l)(1) of this AD, incorporate the inspection method and repetitive 
inspection intervals into the FAA-approved structural maintenance or 
inspection program for the airplane.

    Note 2: For the purposes of this AD, we anticipate that 
submissions of the DTA of the repair, if acceptable, should be 
approved within 6 months after submission.


    Note 3: FAA Order 8110.54, ``Instructions for Continued 
Airworthiness, Responsibilities, Requirements, and Contents'' dated 
July 1, 2005, provides additional guidance about the approval of 
repairs to PSEs.

Inspection for Transferred Airplanes

    (m) Before any airplane that has exceeded the fatigue life 
threshold (NTH) can be added to an air carrier's 
operations specifications, a program for the accomplishment of the 
inspections required by this AD must be established as specified in 
paragraph (m)(1) or (m)(2) of this AD, as applicable.
    (1) For airplanes that have been inspected in accordance with 
this AD: The inspection of each PSE must be done by the new operator 
in accordance with the previous operator's schedule and inspection 
method, or the new operator's schedule and inspection method, at 
whichever time would result in the earlier accomplishment date for 
that PSE inspection. The compliance time for accomplishing this 
inspection must be measured from the last inspection done by the 
previous operator. After each inspection has been done once, each 
subsequent inspection must be done in accordance with the new 
operator's schedule and inspection method.
    (2) For airplanes that have not been inspected in accordance 
with this AD: The inspection of each PSE required by this AD must be 
done either before adding the airplane to the air carrier's 
operations specification, or in accordance with a schedule and an 
inspection method approved by the Manager, Los Angeles ACO. After 
each inspection has been done once, each subsequent inspection must 
be done in accordance with the new operator's schedule.

Acceptable for Compliance

    (n) McDonnell Douglas Report No. MDC 91K0262, ``DC-8 Aging 
Aircraft Repair Assessment Program Document,'' Revision 1, dated 
October 2000, provides inspection/replacement programs for certain 
repairs to the fuselage pressure shell. Accomplishing these repairs 
and inspection/replacement programs before the effective date of 
this AD is considered acceptable for compliance with the 
requirements of paragraphs (g) and (l) of this AD for repairs 
subject to that document.
    (o) Actions done before the effective date of this AD in 
accordance with Boeing Report No. L26-011, ``DC-8 All Series 
Supplemental Inspection Document (SID),'' Volume I, Revision 6, 
dated July 2005, are acceptable for compliance with the 
corresponding requirements of this AD.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Los Angeles ACO, FAA, ATTN: Dara Albouyeh, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
California 90712-4137; telephone (562) 627-5222; fax (562) 627-5210; 
has the authority to approve AMOCs for this AD, if requested using 
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) 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) AMOCs approved previously in accordance with AD 93-01-15 are 
approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (q) You must use the service information identified in Table 2 
of this AD to perform the actions that are required by this AD, as 
applicable, unless the AD specifies otherwise.

               Table 2--Material Incorporated by Reference
------------------------------------------------------------------------
     Service information         Revision level             Date
------------------------------------------------------------------------
Boeing Report No. L26-011,    7...................  March 2008.
 ``DC-8 All Series
 Supplemental Inspection
 Document (SID),'' Volume I.
McDonnell Douglas Report No.  3...................  March 1991.
 L26-011, ``DC-8
 Supplemental Inspection
 Document (SID),'' Volume I.
McDonnell Douglas Report No.  8...................  January 2005.
 L26-011, ``DC-8
 Supplemental Inspection
 Document (SID),'' Volume II.

[[Page 78939]]

 
McDonnell Douglas Report No.  Original............  April 1991.
 L26-011, ``DC-8
 Supplemental Inspection
 Document (SID),'' Volume
 III-91.
------------------------------------------------------------------------

    Boeing Report No. L26-011, ``DC-8 All Series Supplemental 
Inspection Document (SID),'' Volume I, Revision 7, dated March 2008, 
contains the following effective pages:

------------------------------------------------------------------------
                Pages                   Revision           Date
------------------------------------------------------------------------
List of Effective Pages, Pages A               7  March 2008.
 through C.
------------------------------------------------------------------------

    McDonnell Douglas Report No. L26-011, ``DC-8 Supplemental 
Inspection Document (SID),'' Volume II, Revision 8, dated January 
2005, contains the following effective pages:

------------------------------------------------------------------------
                Pages                   Revision           Date
------------------------------------------------------------------------
List of Effective Pages, Pages A               8  March 2008.
 through L.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of Boeing Report No. L26-011, ``DC-8 All 
Series Supplemental Inspection Document (SID),'' Volume I, Revision 
7, dated March 2008; and McDonnell Douglas Report No. L26-011, ``DC-
8 Supplemental Inspection Document (SID),'' Volume II, Revision 8, 
dated January 2005; in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) On February 26, 1993 (58 FR 5576, January 22, 1993), the 
Director of the Federal Register approved the incorporation by 
reference of McDonnell Douglas Report No. L26-011, ``DC-8 
Supplemental Inspection Document (SID),'' Volume I, Revision 3, 
dated March 1991; and McDonnell Douglas Report No. L26-011, ``DC-8 
Supplemental Inspection Document (SID),'' Volume III-91, dated April 
1991.
    (3) Contact Boeing Commercial Airplanes, Attention: Data & 
Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long 
Beach, California 90846-0001; telephone 206-544-5000, extension 2; 
fax 206-766-5683; e-mail dse.boecom@boeing.com; Internet https://
www.myboeingfleet.com.
    (4) You may review copies of the service information that is 
incorporated by reference at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221 or 425-227-1152.
    (5) You may also review copies of the service information 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: http://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.

    Issued in Renton, Washington, on November 26, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-29233 Filed 12-23-08; 8:45 am]
BILLING CODE 4910-13-P