Airworthiness Directives; Bombardier Model BD-700-1A10 and BD-700-1A11 Airplanes, 72316-72320 [E8-28103]

Download as PDF 72316 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. DEPARTMENT OF TRANSPORTATION The effective date of AD 2008– 20–05 remains October 27, 2008. Related Information (h) Refer to MCAI European Aviation Safety Agency AD No.: 2007–0027, dated February 5, 2007, for related information. repetitively inspecting the tailboom attachment fittings, installing inspection holes and attachment bolt washers, modifying both access covers, and replacing broken attachment bolts. This document corrects the AD number that is incorrectly listed as 2008–20–08 on page 60104 of the AD. RIN 2120–AA64 DATES: Material Incorporated by Reference (i) You must use Vulcanair S.p.A. Service Bulletin No. 120 Rev. 1, dated June 7, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Vulcanair S.p.A, Via G. Pascoli, 7, Casoria (Naples), 80026 Italy; telephone: +39 081 5918111; fax: +39 081 5918172; e-mail: info@vulcanair.com; Internet: http://www.vulcanair.com. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Kansas City, Missouri, on November 19, 2008. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–27916 Filed 11–26–08; 8:45 am] BILLING CODE 4910–13–P Eric Schrieber, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627–5348, fax (562) 627–5210. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Discussion: On September 25, 2008, we issued AD 2008–20–05 to amend 14 CFR part 39 to include an AD that applies to MDHI Model 600N helicopters. That AD requires modifying the fuselage aft section, repetitively inspecting the tailboom attachment fittings, installing inspection holes and attachment bolt washers, modifying both access covers, and replacing broken attachment bolts. As published, AD 2008–20–05 contains an incorrect AD number (2008– 20–08) in the regulatory text on page 60104 of the AD. The correct AD number is 2008–20–05. No other part of the regulatory information has been changed; therefore, the AD is not republished in the Federal Register. Correction of Publication DEPARTMENT OF TRANSPORTATION [Docket No. FAA–2008–0835; Directorate Identifier 2008–SW–34–AD; Amendment 39– 15684; AD 2008–20–05] Accordingly, the publication on October 10, 2008 of Amendment 39– 15684, AD 2008–20–05, Docket No. FAA–2008–0835, Directorate Identifier 2008–SW–34–AD (73 FR 60102), which is the subject of FR Doc. E8–23540, is corrected as follows: RIN 2120–AA64 § 39.13 Airworthiness Directives; MD Helicopters, Inc. Model 600N Helicopters On page 60104, in the second column, in the paragraph under § 39.13 [Amended], change ‘‘2008–20–08’’ to read ‘‘2008–20–05’’. Federal Aviation Administration 14 CFR Part 39 Federal Aviation Administration, DOT. ACTION: Final rule; correction. dwashington3 on PROD1PC60 with RULES AGENCY: SUMMARY: This document corrects airworthiness directive (AD) 2008–20– 05 which was published on October 10, 2008 (73 FR 60102) and applies to MD Helicopters, Inc. (MDHI) Model 600N helicopters. AD 2008–20–05 requires modifying the fuselage aft section, VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 [Corrected] Issued in Fort Worth, Texas, on November 14, 2008. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–28108 Filed 11–26–08; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1238; Directorate Identifier 2008–NM–181–AD; Amendment 39–15753; AD 2008–24–12] Airworthiness Directives; Bombardier Model BD–700–1A10 and BD–700– 1A11 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During scheduled maintenance inspection, a bolt which connects the PCU (power control unit) to the elevator surface was found fractured in the assembly. Further inspection of the assembly revealed that the bearing on the PCU rod end had seized, which resulted in damage to the attachment fitting bushing and fracture of the bolt. Inspection of other in-service airplanes revealed two more seized PCU attachment joints. However, except seizure, no fractured bolt was found on these airplanes. Failure of the bolts in both PCUs on one side could result in disconnection of the elevator control surface which would lead to flutter and loss of the aircraft. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective December 15, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 15, 2008. We must receive comments on this AD by December 29, 2008. ADDRESSES: You may send comments by any of the following methods: • 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. E:\FR\FM\28NOR1.SGM 28NOR1 72317 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office 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 street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Pong K. Lee, Aerospace Engineer, Airframe and Propulsion Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7324; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Discussion Transport Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada, has issued Canadian Emergency Airworthiness Directive CF–2008–31, dated October 9, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During scheduled maintenance inspection, a bolt which connects the PCU (power control unit) to the elevator surface was found fractured in the assembly. Further inspection of the assembly revealed that the bearing on the PCU rod end had seized, which resulted in damage to the attachment fitting bushing and fracture of the bolt. Inspection of other in-service airplanes revealed two more seized PCU attachment joints. However, except seizure, no fractured bolt was found on these airplanes. Failure of the bolts in both PCUs on one side could result in disconnection of the elevator control surface which would lead to flutter and loss of the aircraft. This Airworthiness Directive (AD) is issued to mandate the inspection and lubrication of all part number (P/N) GT411– 3800–5 and GT411–3800–7 PCU attachment joints. The required actions include inspections for damage and seizure (including signs of seizure) of the PCU attachment joints, an inspection for damage (including wear damage, fretting, corrosion, galling, scoring, fretting wear, and parts that do not meet inspection requirements) of the PCU attachment joint components, and applicable corrective actions. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Bombardier has issued the service information in the following table. The actions described in the service information are intended to correct the unsafe condition identified in the MCAI. SERVICE BULLETINS Service Bulletin Bombardier Bombardier Bombardier Bombardier Alert Service Bulletin A700–1A11–27–024 ......................................... Alert Service Bulletin A700–27–066 .................................................... Service Bulletin 700–1A11–27–025 .................................................... Service Bulletin 700–27–067 ............................................................... FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. dwashington3 on PROD1PC60 with RULES Revision level Differences Between the AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 01 ........................................................... 01 ........................................................... Original ................................................... Original ................................................... We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the AD. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because failure of the bolts in both PCUs on one side of the airplane could cause disconnection of the elevator control surface which could result in flutter and consequent loss of the airplane. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Date October October October October 3, 3, 9, 9, 2008. 2008. 2008. 2008. invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2008–1238; Directorate Identifier 2008–NM–181– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. 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\28NOR1.SGM 28NOR1 72318 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations 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. 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 Regulatory Findings We 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 this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2008–24–12 Bombardier: Amendment 39– 15753. Docket No. FAA–2008–1238; Directorate Identifier 2008–NM–181–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 15, 2008. Affected ADs (b) None. During scheduled maintenance inspection, a bolt which connects the PCU (power control unit) to the elevator surface was found fractured in the assembly. Further inspection of the assembly revealed that the bearing on the PCU rod end had seized, which resulted in damage to the attachment fitting bushing and fracture of the bolt. Inspection of other in-service airplanes revealed two more seized PCU attachment joints. However, except seizure, no fractured bolt was found on these airplanes. Failure of the bolts in both PCUs on one side could result in disconnection of the elevator control surface which would lead to flutter and loss of the aircraft. This Airworthiness Directive (AD) is issued to mandate the inspection and lubrication of all part number (P/N) GT411– 3800–5 and GT411–3800–7 PCU attachment joints. The required actions include inspections for damage and seizure (including signs of seizure) of the PCU attachment joints, an inspection for damage (including wear damage, fretting, corrosion, galling, scoring, fretting wear, and parts that do not meet inspection requirements) of the PCU attachment joint components, and applicable corrective actions. Actions and Compliance Applicability (c) This AD applies to Bombardier Model BD–700–1A10 and BD–700–1A11 airplanes, certificated in any category, serial numbers (S/Ns) 9002 through 9222 inclusive; equipped with elevator power control units (PCUs) having part number (P/N) GT411– 3800–5 or GT411–3800–7. Subject (d) Air Transport Association (ATA) of America Code 27: Flight controls. Reason (e) The mandatory continued airworthiness information (MCAI) states: (f) Unless already done: For airplanes on which elevator PCUs with P/N GT411–3800– 5 or P/N GT411–3800–7, S/N 0615 and lower, are installed, excluding P/N GT411– 3800–7 PCUs having a serial number listed in Table 1 of this AD, and excluding P/N GT411–3800–7 PCUs on which less than 1,000 flight hours have accumulated on the PCUs as of the effective date of this AD, do the actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD. Note 1: Units listed in Table 1 of this AD have been lubricated by the vendor and the inspections required by paragraphs (f)(1), (f)(2), (f)(3), and (f)(4) of this AD are not required for those units. TABLE 1—SERIAL NUMBERS dwashington3 on PROD1PC60 with RULES 0030 0031 0033 0041 0046 0060 0062 0066 0081 0083 0087 0092 0097 0101 0105 0108 0109 0110 0111 0119 0130 0138 0141 0145 0156 0161 0163 0164 0165 0171 0173 0174 0178 0179 0181 0183 (1) Within 10 flight cycles or 50 flight hours after the effective date of this AD, whichever occurs first: Inspect for damage and wear and lubricate the PCU attachment joints in accordance with Bombardier Alert Service Bulletin A700–1A11–27–024, Revision 01, dated October 3, 2008; or Bombardier Alert Service Bulletin A700–27– VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 0188 0190 0191 0197 0198 0199 0202 0205 0206 0208 0210 0214 0218 0222 0223 0240 0262 0265 0281 0296 0301 0310 0323 0365 066, Revision 01, dated October 3, 2008; as applicable. (2) Within 90 days or 200 flight hours after performing the actions required by paragraph (f)(1) of this AD, whichever occurs first: Repeat the inspection and lubrication of the PCU attachment joints in accordance with Bombardier Alert Service Bulletin A700– PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 0369 0406 0407 0408 0413 0420 0427 0429 0430 0431 0433 0435 0438 0453 0491 0495 0504 0506 0513 0533 0536 0586 1A11–27–024, Revision 01, dated October 3, 2008; or Bombardier Alert Service Bulletin A700–27–066, Revision 01, dated October 3, 2008; as applicable. (3) Within 45 days or 100 flight hours after performing the actions required by paragraph (f)(2) of this AD, whichever occurs first: Repeat the inspection and lubrication of the E:\FR\FM\28NOR1.SGM 28NOR1 72319 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations PCU attachment joints in accordance with Bombardier Alert Service Bulletin A700– 1A11–27–024, Revision 01, dated October 3, 2008; or Bombardier Alert Service Bulletin A700–27–066, Revision 01, dated October 3, 2008; as applicable. Repeat the inspection thereafter at intervals not to exceed 45 days or 100 flight hours, whichever occurs first, until paragraph (f)(4) of this AD is accomplished. (4) Completion of a disassembly with an inspection for damage, applicable corrective actions, and lubrication of the PCU attachment joint components in accordance with Bombardier Service Bulletin 700–1A11– 27–025, dated October 9, 2008; or Bombardier Service Bulletin 700–27–067, dated October 9, 2008; as applicable; constitutes terminating action for the inspections required by paragraphs (f)(1), (f)(2), and (f)(3) of this AD. (5) Unless already done, if any damage or seizure is found during any inspection required by paragraphs (f)(1), (f)(2), (f)(3), and (f)(4) of this AD, before further flight, replace the affected part in accordance with Bombardier Service Bulletin 700–1A11–27– 025, dated October 9, 2008, or Bombardier Service Bulletin 700–27–067, dated October 9, 2008, as applicable. (6) Actions done before the effective date of this AD in accordance with the Bombardier Alert Service Bulletins A700– 1A11–27–024 and A700–27–066, both dated October 2, 2008, are acceptable for compliance with the corresponding requirements of this AD. (7) Unless already done, submit a report to Bombardier of all findings found during any inspection required by this AD, in accordance with the applicable service bulletin listed in Table 2 of this AD. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 14 days after the inspection. (ii) If the inspection was done before the effective date of this AD: Submit the report within 14 days after the effective date of this AD. TABLE 2—SERVICE BULLETINS FOR REPORTS Service Bulletin Bombardier Bombardier Bombardier Bombardier Revision level Alert Service Bulletin; A700–1A11–27–024 ........................................ Alert Service Bulletin; A700–27–066 ................................................... Service Bulletin; 700–1A11–27–025 ................................................... Service Bulletin; 700–27–067 .............................................................. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: (1) This AD does not mandate the terminating action specified in paragraph A.4. of the MCAI; it is included as an optional terminating action in paragraph (f)(4) of this AD. The planned compliance times for that action would allow enough time to provide notice and opportunity for prior public comment on the merits of those actions. Therefore, we are considering further rulemaking to require the terminating action on all affected airplanes. (2) Paragraph A.3. of the MCAI requires a one-time inspection; however, since we have changed the terminating action in paragraph A.4. of the MCAI to an optional action, paragraph (f)(3) of this AD requires repeating the inspections until the terminating action is performed. (3) This AD does not require the inspection and lubrication of PCUs specified in Paragraph B. of the MCAI. The planned compliance times for those actions would allow enough time to provide notice and opportunity for prior public comment on the merits of those actions. Therefore, we are considering further rulemaking to address this issue. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft 01 ........................................................... 01 ........................................................... Original ................................................... Original ................................................... Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Pong K. Lee, Aerospace Engineer, Airframe and Propulsion Branch, ANE–171, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7324; fax (516) 794–5531. 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. (4) Special Flight Permits: As described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), special flight permits are not allowed. Date October October October October 3, 3, 9, 9, 2008. 2008. 2008. 2008. Related Information (h) Refer to Mandatory Continuing Airworthiness Information (MCAI) Transport Canada Civil Aviation Emergency Airworthiness Directive CF–2008–31, dated October 9, 2008, and the service information specified in Table 2 of this AD, for related information. Material Incorporated by Reference (i) You must use the service information specified in Table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; e-mail thd.crj@aero.bombardier.com; Internet http:// www.bombardier.com. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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: http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. TABLE 3—MATERIAL INCORPORATED BY REFERENCE dwashington3 on PROD1PC60 with RULES Service Bulletin Bombardier Bombardier Bombardier Bombardier Revision level Alert Service Bulletin A700–1A11–27–024 ......................................... Alert Service Bulletin A700–27–066 .................................................... Service Bulletin 700–1A11–27–025 .................................................... Service Bulletin 700–27–067 ............................................................... VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 01 ........................................................... 01 ........................................................... Original ................................................... Original ................................................... E:\FR\FM\28NOR1.SGM 28NOR1 Date October October October October 3, 3, 9, 9, 2008. 2008. 2008. 2008. 72320 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations Issued in Renton, Washington, on November 16, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–28103 Filed 11–26–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration by reference of Boeing Service Bulletin 737–25–1404, dated May 25, 2000 on August 28, 2001 (66 FR 38361, July 24, 2001). For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207; telephone (206) 544–9990; fax (206) 766–5682; e-mail DDCS@boeing.com; Internet https:// www.myboeingfleet.com. ADDRESSES: 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2008–0176; Directorate Identifier 2007–NM–228–AD; Amendment 39–15748; AD 2008–24–08] 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. RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–600, –700, –700C, –800 and –900 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737–600, –700, –700C, –800 and –900 series airplanes. This AD requires an inspection of the escape slides for the forward and aft entry and service doors to determine the part number and service bulletin number stenciled on the escape slide girt, and modification of the escape slide assemblies. This AD also requires concurrent modification of the escape slide latch assemblies; concurrent inspection of the escape slides to determine the part number and service bulletin number stenciled on the escape slide girts, and replacement of the trigger housing on the regulator valve with an improved trigger housing if necessary; and concurrent replacement of the rod in the pilot valve regulator with a new, improved rod; as applicable. This AD results from reports that certain escape slides did not automatically inflate when deployed or after the manual inflation cable was pulled. We are issuing this AD to prevent failure of an escape slide to inflate when deployed, which could result in the slide being unusable during an emergency evacuation and consequent injury to passengers or crewmembers. This AD is effective January 2, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 2, 2009. The Director of the Federal Register previously approved the incorporation dwashington3 on PROD1PC60 with RULES DATES: VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 FOR FURTHER INFORMATION CONTACT: Robert K. Hettman, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6457, fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Boeing Model 737–600, –700, –700C, –800 and –900 series airplanes. That NPRM was published in the Federal Register on February 15, 2008 (73 FR 8833). That NPRM proposed to require an inspection of the escape slides for the forward and aft entry and service doors to determine the part number and service bulletin number stenciled on the escape slide girt, and modification of the escape slide assemblies. That NPRM also proposed to require concurrent modification of the escape slide latch assemblies; concurrent inspection of the escape slides to determine the part number and service bulletin number stenciled on the escape slide girts, and replacement of the trigger housing on the regulator valve with an improved trigger housing if necessary; and concurrent replacement of the rod in the pilot valve PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 regulator with a new, improved rod; as applicable. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received from the three commenters. Support for the NPRM Boeing concurs with the contents of the proposed rule. Requests To Refer to Additional Goodrich Service Bulletin Goodrich, and Air Transport Association (ATA) on behalf of one of its members, American Airlines (AA), request that Boeing revise Boeing Service Bulletin 737–25–1491, dated April 23, 2007 (cited in the NPRM as the appropriate source of service information for accomplishing certain actions specified in the NPRM), to include a reference to Goodrich Service Bulletin 5A3307–25–339, Revision 2, dated March 31, 2004, as an alternative method of compliance (AMOC) to BFGoodrich Service Bulletin 25–308, dated January 21, 2000 (cited in the NPRM as a source of service information for accomplishing certain other actions specified in the NPRM). ATA and AA note that this service bulletin modifies the applicable slide to the latest standard offered by Goodrich. AA and Goodrich suggest that if Boeing Service Bulletin 737–25–1491, dated April 23, 2007, is not revised, the AD should state that it does not apply to Goodrich part number (P/N) 5A3307–5 slides and that Goodrich Service Bulletin 5A3307–25– 339, Revision 2, dated March 31, 2004, be identified as an AMOC for the slide portion of the AD. We disagree with the request to revise the AD to refer to Goodrich Service Bulletin 5A3307–25–339, Revision 2, dated March 31, 2004. There are significant differences in the actions between BFGoodrich Service Bulletin 25–308, dated January 21, 2000 and Goodrich Service Bulletin 5A3307–25– 339, Revision 2, dated March 31, 2004. Therefore, any request to use the procedures in Goodrich Service Bulletin 5A3307–25–339 is best handled through the AMOC process. Under the provisions of paragraph (k) of the AD, we will consider requests for approval of an AMOC if sufficient data are submitted to substantiate that the change would provide an acceptable level of safety. We have not changed the AD in this regard. Request To Revise Unsafe Condition Goodrich notes that paragraph (g)(1) of the NPRM addresses an unsafe E:\FR\FM\28NOR1.SGM 28NOR1

Agencies

[Federal Register Volume 73, Number 230 (Friday, November 28, 2008)]
[Rules and Regulations]
[Pages 72316-72320]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-28103]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1238; Directorate Identifier 2008-NM-181-AD; 
Amendment 39-15753; AD 2008-24-12]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model BD-700-1A10 and BD-
700-1A11 Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    During scheduled maintenance inspection, a bolt which connects 
the PCU (power control unit) to the elevator surface was found 
fractured in the assembly. Further inspection of the assembly 
revealed that the bearing on the PCU rod end had seized, which 
resulted in damage to the attachment fitting bushing and fracture of 
the bolt. Inspection of other in-service airplanes revealed two more 
seized PCU attachment joints. However, except seizure, no fractured 
bolt was found on these airplanes. Failure of the bolts in both PCUs 
on one side could result in disconnection of the elevator control 
surface which would lead to flutter and loss of the aircraft.
* * * * *
This AD requires actions that are intended to address the unsafe 
condition described in the MCAI.

DATES: This AD becomes effective December 15, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 15, 
2008.
    We must receive comments on this AD by December 29, 2008.

ADDRESSES: You may send comments by any of the following methods:
     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.

[[Page 72317]]

     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
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 street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Pong K. Lee, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7324; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    Transport Canada Civil Aviation (TCCA), which is the airworthiness 
authority for Canada, has issued Canadian Emergency Airworthiness 
Directive CF-2008-31, dated October 9, 2008 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During scheduled maintenance inspection, a bolt which connects 
the PCU (power control unit) to the elevator surface was found 
fractured in the assembly. Further inspection of the assembly 
revealed that the bearing on the PCU rod end had seized, which 
resulted in damage to the attachment fitting bushing and fracture of 
the bolt. Inspection of other in-service airplanes revealed two more 
seized PCU attachment joints. However, except seizure, no fractured 
bolt was found on these airplanes. Failure of the bolts in both PCUs 
on one side could result in disconnection of the elevator control 
surface which would lead to flutter and loss of the aircraft.
    This Airworthiness Directive (AD) is issued to mandate the 
inspection and lubrication of all part number (P/N) GT411-3800-5 and 
GT411-3800-7 PCU attachment joints.

The required actions include inspections for damage and seizure 
(including signs of seizure) of the PCU attachment joints, an 
inspection for damage (including wear damage, fretting, corrosion, 
galling, scoring, fretting wear, and parts that do not meet inspection 
requirements) of the PCU attachment joint components, and applicable 
corrective actions. You may obtain further information by examining the 
MCAI in the AD docket.

Relevant Service Information

    Bombardier has issued the service information in the following 
table. The actions described in the service information are intended to 
correct the unsafe condition identified in the MCAI.

                            Service Bulletins
------------------------------------------------------------------------
       Service Bulletin         Revision level             Date
------------------------------------------------------------------------
Bombardier Alert Service       01..............  October 3, 2008.
 Bulletin A700-1A11-27-024.
Bombardier Alert Service       01..............  October 3, 2008.
 Bulletin A700-27-066.
Bombardier Service Bulletin    Original........  October 9, 2008.
 700-1A11-27-025.
Bombardier Service Bulletin    Original........  October 9, 2008.
 700-27-067.
------------------------------------------------------------------------

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the AD.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
failure of the bolts in both PCUs on one side of the airplane could 
cause disconnection of the elevator control surface which could result 
in flutter and consequent loss of the airplane. Therefore, we 
determined that notice and opportunity for public comment before 
issuing this AD are impracticable and that good cause exists for making 
this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2008-1238; Directorate 
Identifier 2008-NM-181-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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

[[Page 72318]]

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 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 this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.

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 FAA amends Sec.  39.13 by adding the following new AD:

2008-24-12 Bombardier: Amendment 39-15753. Docket No. FAA-2008-1238; 
Directorate Identifier 2008-NM-181-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
15, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model BD-700-1A10 and BD-700-
1A11 airplanes, certificated in any category, serial numbers (S/Ns) 
9002 through 9222 inclusive; equipped with elevator power control 
units (PCUs) having part number (P/N) GT411-3800-5 or GT411-3800-7.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
controls.

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:
    During scheduled maintenance inspection, a bolt which connects 
the PCU (power control unit) to the elevator surface was found 
fractured in the assembly. Further inspection of the assembly 
revealed that the bearing on the PCU rod end had seized, which 
resulted in damage to the attachment fitting bushing and fracture of 
the bolt. Inspection of other in-service airplanes revealed two more 
seized PCU attachment joints. However, except seizure, no fractured 
bolt was found on these airplanes. Failure of the bolts in both PCUs 
on one side could result in disconnection of the elevator control 
surface which would lead to flutter and loss of the aircraft.
    This Airworthiness Directive (AD) is issued to mandate the 
inspection and lubrication of all part number (P/N) GT411-3800-5 and 
GT411-3800-7 PCU attachment joints.

The required actions include inspections for damage and seizure 
(including signs of seizure) of the PCU attachment joints, an 
inspection for damage (including wear damage, fretting, corrosion, 
galling, scoring, fretting wear, and parts that do not meet 
inspection requirements) of the PCU attachment joint components, and 
applicable corrective actions.

Actions and Compliance

    (f) Unless already done: For airplanes on which elevator PCUs 
with P/N GT411-3800-5 or P/N GT411-3800-7, S/N 0615 and lower, are 
installed, excluding P/N GT411-3800-7 PCUs having a serial number 
listed in Table 1 of this AD, and excluding P/N GT411-3800-7 PCUs on 
which less than 1,000 flight hours have accumulated on the PCUs as 
of the effective date of this AD, do the actions specified in 
paragraphs (f)(1), (f)(2), and (f)(3) of this AD.

    Note 1: Units listed in Table 1 of this AD have been lubricated 
by the vendor and the inspections required by paragraphs (f)(1), 
(f)(2), (f)(3), and (f)(4) of this AD are not required for those 
units.


                         Table 1--Serial Numbers
------------------------------------------------------------------------
 
------------------------------------------------------------------------
    0030       0097       0156       0188      0218      0369      0438
    0031       0101       0161       0190      0222      0406      0453
    0033       0105       0163       0191      0223      0407      0491
    0041       0108       0164       0197      0240      0408      0495
    0046       0109       0165       0198      0262      0413      0504
    0060       0110       0171       0199      0265      0420      0506
    0062       0111       0173       0202      0281      0427      0513
    0066       0119       0174       0205      0296      0429      0533
    0081       0130       0178       0206      0301      0430      0536
    0083       0138       0179       0208      0310      0431      0586
    0087       0141       0181       0210      0323      0433
    0092       0145       0183       0214      0365      0435
------------------------------------------------------------------------

    (1) Within 10 flight cycles or 50 flight hours after the 
effective date of this AD, whichever occurs first: Inspect for 
damage and wear and lubricate the PCU attachment joints in 
accordance with Bombardier Alert Service Bulletin A700-1A11-27-024, 
Revision 01, dated October 3, 2008; or Bombardier Alert Service 
Bulletin A700-27-066, Revision 01, dated October 3, 2008; as 
applicable.
    (2) Within 90 days or 200 flight hours after performing the 
actions required by paragraph (f)(1) of this AD, whichever occurs 
first: Repeat the inspection and lubrication of the PCU attachment 
joints in accordance with Bombardier Alert Service Bulletin A700-
1A11-27-024, Revision 01, dated October 3, 2008; or Bombardier Alert 
Service Bulletin A700-27-066, Revision 01, dated October 3, 2008; as 
applicable.
    (3) Within 45 days or 100 flight hours after performing the 
actions required by paragraph (f)(2) of this AD, whichever occurs 
first: Repeat the inspection and lubrication of the

[[Page 72319]]

PCU attachment joints in accordance with Bombardier Alert Service 
Bulletin A700-1A11-27-024, Revision 01, dated October 3, 2008; or 
Bombardier Alert Service Bulletin A700-27-066, Revision 01, dated 
October 3, 2008; as applicable. Repeat the inspection thereafter at 
intervals not to exceed 45 days or 100 flight hours, whichever 
occurs first, until paragraph (f)(4) of this AD is accomplished.
    (4) Completion of a disassembly with an inspection for damage, 
applicable corrective actions, and lubrication of the PCU attachment 
joint components in accordance with Bombardier Service Bulletin 700-
1A11-27-025, dated October 9, 2008; or Bombardier Service Bulletin 
700-27-067, dated October 9, 2008; as applicable; constitutes 
terminating action for the inspections required by paragraphs 
(f)(1), (f)(2), and (f)(3) of this AD.
    (5) Unless already done, if any damage or seizure is found 
during any inspection required by paragraphs (f)(1), (f)(2), (f)(3), 
and (f)(4) of this AD, before further flight, replace the affected 
part in accordance with Bombardier Service Bulletin 700-1A11-27-025, 
dated October 9, 2008, or Bombardier Service Bulletin 700-27-067, 
dated October 9, 2008, as applicable.
    (6) Actions done before the effective date of this AD in 
accordance with the Bombardier Alert Service Bulletins A700-1A11-27-
024 and A700-27-066, both dated October 2, 2008, are acceptable for 
compliance with the corresponding requirements of this AD.
    (7) Unless already done, submit a report to Bombardier of all 
findings found during any inspection required by this AD, in 
accordance with the applicable service bulletin listed in Table 2 of 
this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 14 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 14 days after the effective date 
of this AD.

                 Table 2--Service Bulletins for Reports
------------------------------------------------------------------------
       Service Bulletin         Revision level             Date
------------------------------------------------------------------------
Bombardier Alert Service       01..............  October 3, 2008.
 Bulletin; A700-1A11-27-024.
Bombardier Alert Service       01..............  October 3, 2008.
 Bulletin; A700-27-066.
Bombardier Service Bulletin;   Original........  October 9, 2008.
 700-1A11-27-025.
Bombardier Service Bulletin;   Original........  October 9, 2008.
 700-27-067.
------------------------------------------------------------------------

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows:
    (1) This AD does not mandate the terminating action specified in 
paragraph A.4. of the MCAI; it is included as an optional 
terminating action in paragraph (f)(4) of this AD. The planned 
compliance times for that action would allow enough time to provide 
notice and opportunity for prior public comment on the merits of 
those actions. Therefore, we are considering further rulemaking to 
require the terminating action on all affected airplanes.
    (2) Paragraph A.3. of the MCAI requires a one-time inspection; 
however, since we have changed the terminating action in paragraph 
A.4. of the MCAI to an optional action, paragraph (f)(3) of this AD 
requires repeating the inspections until the terminating action is 
performed.
    (3) This AD does not require the inspection and lubrication of 
PCUs specified in Paragraph B. of the MCAI. The planned compliance 
times for those actions would allow enough time to provide notice 
and opportunity for prior public comment on the merits of those 
actions. Therefore, we are considering further rulemaking to address 
this issue.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. Send information to ATTN: Pong K. Lee, Aerospace 
Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York 
ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; 
telephone (516) 228-7324; fax (516) 794-5531. 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.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.
    (4) Special Flight Permits: As described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), special flight permits are not allowed.

Related Information

    (h) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Transport Canada Civil Aviation Emergency Airworthiness 
Directive CF-2008-31, dated October 9, 2008, and the service 
information specified in Table 2 of this AD, for related 
information.

Material Incorporated by Reference

    (i) You must use the service information specified in Table 3 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; e-mail thd.crj@aero.bombardier.com; Internet http://
www.bombardier.com.
    (3) You may review copies at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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: http://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.

               Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
       Service Bulletin         Revision level             Date
------------------------------------------------------------------------
Bombardier Alert Service       01..............  October 3, 2008.
 Bulletin A700-1A11-27-024.
Bombardier Alert Service       01..............  October 3, 2008.
 Bulletin A700-27-066.
Bombardier Service Bulletin    Original........  October 9, 2008.
 700-1A11-27-025.
Bombardier Service Bulletin    Original........  October 9, 2008.
 700-27-067.
------------------------------------------------------------------------



[[Page 72320]]

    Issued in Renton, Washington, on November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E8-28103 Filed 11-26-08; 8:45 am]
BILLING CODE 4910-13-P