Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 73785-73788 [E8-28365]

Download as PDF Federal Register / Vol. 73, No. 234 / Thursday, December 4, 2008 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2008–24–13 Pratt & Whitney: Amendment 39–15757. Docket No. FAA–2008–0589; Directorate Identifier 2008–NE–17–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 8, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Pratt & Whitney (P&W) PW4052, PW4056, PW4060, PW4062, PW4152, PW4156A, PW4158, PW4460, and PW4462 turbofan engines. These engines are installed on, but not limited to, Airbus A300– 600 and A310–300, and Boeing 747–400, Boeing 767–200, 767–300, and MD–11 series airplanes. Unsafe Condition (d) This AD results from a report of an uncommanded engine in-flight shutdown due to defective electronic engine control (EEC) pulse width modulator (PWM) microcircuits. We are issuing this AD to prevent uncommanded in-flight engine shutdowns which could result in loss of thrust and prevent continued safe flight or landing. 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. erowe on PROD1PC64 with RULES Onetime Visual Inspection and Reporting Requirements (f) Within 600 operating hours after the effective date of this AD: (1) Perform a onetime visual inspection of the EEC–131 model EECs to identify, categorize, and mark them as a Group 1, Group 2, Group 3, or Group 4 EEC. (2) Use paragraphs 1 through 7 in the Accomplishment Instructions of P&W Alert Service Bulletin No. PW4ENG A73–214, Revision 2, dated May 23, 2008, to inspect, categorize, and mark the EECs. (3) Within 30 calendar days of completing paragraph (f)(1) of this AD, report all inspection findings to Kevin Dickert, Engine Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803. (4) The Office of Management and Budget (OMB) has approved the reporting requirements and assigned OMB control number 2120–0056. Replacement of Group 1 EECs (g) Replace Group 1 EECs with a serviceable EEC before reaching 2,000 cyclesin-service (CIS) after the effective date of this AD, but not later than one year from the effective date of this AD. Replacement of Groups 2, 3, and 4 EECs (h) Replace the following groups of EECs with a serviceable EEC, or any EEC that does VerDate Aug<31>2005 15:50 Dec 03, 2008 Jkt 217001 not violate the EEC installation procedure as provided by paragraphs (k), (l), and (m) of this AD, as follows: (1) Group 2 EECs, before reaching 5,000 CIS after the effective date of this AD, but not later than 21⁄2 years after the effective date of this AD. (2) Group 3 EECs, before reaching 13,000 CIS after the effective date of this AD, but not later than 61⁄2 years after the effective date of this AD. (3) There are no scheduled replacement requirements for Group 4 EECs. Definition of Serviceable EECs (i) A serviceable EEC is an EEC that does not violate the EEC installation procedure as provided by paragraphs (k), (l), and (m) of this AD, or a Group 4 EEC. (j) Information on obtaining a serviceable EEC can be found in P&W SB No. PW4ENG 73–216, dated April 8, 2008. To obtain this SB, see paragraph (q) of this AD for P&W contact information. EEC Installation Prohibition (k) Do not install any Group 1 EEC after 1 year from the effective date of this AD or any Group 1 EEC that has accumulated an additional 2,000 CIS from the effective date of this AD. (l) Do not install any Group 2 EEC after 21⁄2 years from the effective date of this AD or any Group 2 EEC that has accumulated an additional 5,000 CIS from the effective date of this AD. (m) Do not install any Group 3 EEC after 61⁄2 years from the effective date of this AD or any Group 3 EEC that has accumulated an additional 13,000 CIS from the effective date of this AD. Previous Credit (n) Inspecting, categorizing, and marking of EECs before the effective date of this AD performed using the Accomplishment Instructions of P&W Alert SB No. PW4ENG A73–214 original issue or Revision 1, satisfy the requirements of paragraph (f)(1) of this AD. Alternative Methods of Compliance (o) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (p) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference (q) You must use the service information specified in Pratt & Whitney Alert Service Bulletin No. PW4ENG A73–214, Revision 2, dated May 23, 2008, to inspect, categorize, and mark the EECs. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Pratt & Whitney, 400 Main PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 73785 St., East Hartford, CT 06108; telephone (860) 565–8770; fax (860) 565–4503, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on November 21, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–28270 Filed 12–3–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1258; Directorate Identifier 2008–NM–142–AD; Amendment 39–15758; AD 2008–24–14] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) 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: Cracks on the main landing gear trunnion fitting web have been discovered during fatigue testing. Failure of the main landing gear trunnion fitting web could compromise the structural integrity of the trunnion fitting and result in a main landing gear collapse. * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective December 19, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 19, 2008. We must receive comments on this AD by January 5, 2009. ADDRESSES: You may send comments by any of the following methods: E:\FR\FM\04DER1.SGM 04DER1 73786 Federal Register / Vol. 73, No. 234 / Thursday, December 4, 2008 / Rules and Regulations • Federal eRulemaking Portal: Go to https://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 W12–40, 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 https:// 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 aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2008–21, dated June 12, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: erowe on PROD1PC64 with RULES Cracks on the main landing gear trunnion fitting web have been discovered during fatigue testing. Failure of the main landing gear trunnion fitting web could compromise the structural integrity of the trunnion fitting and result in a main landing gear collapse. A Temporary Revision has been made to the Bombardier CL–600–2B19 Maintenance Requirements Manual, Appendix B, ‘‘Airworthiness Limitations’’ to ensure that fatigue cracking of the trunnion fitting web is detected and corrected. The corrective action is revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new structural inspection requirements. You may obtain further information by examining the MCAI in the AD docket. VerDate Aug<31>2005 15:50 Dec 03, 2008 Jkt 217001 Relevant Service Information Bombardier has issued Temporary Revision 2B–2136, dated May 1, 2008, to the Bombardier CL–600–2B19 Maintenance Requirements Manual, Part 2, Appendix B—Airworthiness Limitations. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 if the actions specified in the service information are not accomplished at the specified threshold, cracking in the main landing gear trunnion fitting web could go undetected. 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. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 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–2008–1258; Directorate Identifier 2008–NM–142– 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 https:// 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 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 E:\FR\FM\04DER1.SGM 04DER1 Federal Register / Vol. 73, No. 234 / Thursday, December 4, 2008 / Rules and Regulations 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 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] Effective Date (a) This airworthiness directive (AD) becomes effective December 19, 2008. Affected ADs (b) None. Applicability (c) This AD applies to all Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (g)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. The FAA has provided guidance for this determination in Advisory Circular (AC) 25– 1529–1A. 2. The FAA amends § 39.13 by adding the following new AD: 2008–24–14 Bombardier, Inc. (Formerly Canadair): Amendment 39–15758. Docket No. FAA–2008–1258; Directorate Identifier 2008–NM–142–AD. Subject (d) Air Transport Association (ATA) of America Code 32: Landing Gear. Reason (e) The mandatory continuing airworthiness information (MCAI) states: ■ 73787 Cracks on the main landing gear trunnion fitting web have been discovered during fatigue testing. Failure of the main landing gear trunnion fitting web could compromise the structural integrity of the trunnion fitting and result in a main landing gear collapse. A Temporary Revision has been made to the Bombardier CL–600–2B19 Maintenance Requirements Manual, Appendix B, ‘‘Airworthiness Limitations’’ to ensure that fatigue cracking of the trunnion fitting web is detected and corrected. The corrective action is revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new structural inspection requirements. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 30 days after the effective date of this AD, revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate the Airworthiness Limitation (AWL) No. 57– 21–161, as identified in Bombardier Temporary Revision 2B–2136, dated May 1, 2008, to the Bombardier CL–600–2B19 Maintenance Requirements Manual, Part 2, Appendix B—Airworthiness Limitations. The initial compliance time for the task starts from the applicable time specified in Table 1 or Table 2 of this AD, as applicable. Repeat the inspection thereafter at the applicable interval specified in Bombardier Temporary Revision 2B–2136, dated May 1, 2008. TABLE 1—PRE-MODSUM TC601R15827 AIRPLANES If the airplane has accumulated (as of the effective date of this AD)— Then phase in the initial inspection— 23,500 total flight cycles or fewer ................................ 23,501 to 25,000 total flight cycles .............................. Prior to the accumulation of 25,000 total flight cycles. Prior to the accumulation of 26,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever occurs first. Prior to the accumulation of 26,500 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs first. Within 500 flight cycles after the effective date of this AD. 25,001 to 26,000 total flight cycles .............................. 26,001 or more total flight cycles ................................ TABLE 2—POST-MODSUM TC601R15827 AIRPLANES If the airplane has accumulated (as of the effective date of this AD)— Then phase in the initial inspection— 15,667 total flight cycles or fewer ................................ 15,668 to 16,667 total flight cycles .............................. Prior to the accumulation of 16,667 total flight cycles. Prior to the accumulation of 17,333 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs first. Prior to the accumulation of 17,666 total flight cycles, or within 666 flight cycles after the effective date of this AD, whichever occurs first. Within 333 flight cycles after the effective date of this AD. 16,668 to 17,333 total flight cycles .............................. erowe on PROD1PC64 with RULES 17,334 or more total flight cycles ................................ (2) After accomplishing the actions specified in paragraph (f)(1) of this AD, no alternative inspections or inspection intervals may be used unless the inspection or inspection interval is approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (g)(1) of this AD. VerDate Aug<31>2005 15:50 Dec 03, 2008 Jkt 217001 FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 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 E:\FR\FM\04DER1.SGM 04DER1 73788 Federal Register / Vol. 73, No. 234 / Thursday, December 4, 2008 / Rules and Regulations 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 FAAapproved 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: 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), are not allowed. Related Information (h) Refer to MCAI Canadian Airworthiness Directive CF–2008–21, dated June 12, 2008; and Bombardier Temporary Revision 2B– 2136, dated May 1, 2008, to the Bombardier CL–600–2B19 Maintenance Requirements Manual, Part 2, Appendix B—Airworthiness Limitations; for related information. Material Incorporated by Reference erowe on PROD1PC64 with RULES (i) You must use Bombardier Temporary Revision 2B–2136, dated May 1, 2008, to the Bombardier CL–600–2B19 Maintenance Requirements Manual, Part 2, Appendix B— Airworthiness Limitations Section, 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 https:// 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: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 19, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–28365 Filed 12–3–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:50 Dec 03, 2008 Jkt 217001 DEPARTMENT OF THE TREASURY Office of Foreign Assets Control 31 CFR Part 560 Iranian Transactions Regulations Office of Foreign Assets Control, Treasury. ACTION: Final rule. AGENCY: SUMMARY: The Department of the Treasury’s Office of Foreign Assets Control (‘‘OFAC’’) is amending the Iranian Transactions Regulations to expand the scope of Appendix A to Part 560 to include non-financial as well as financial institutions determined to be owned or controlled by the Government of Iran, and to add to the appendix three non-financial institutions that have been determined to be owned or controlled by the Government of Iran: The National Iranian Oil Company (a.k.a. NIOC), Naftiran Intertrade Company Ltd (a.k.a. NICO), and Naftiran Intertrade Co. (NICO) Sarl. DATES: Effective Date: December 3, 2008. FOR FURTHER INFORMATION CONTACT: Assistant Director for Compliance, Outreach & Implementation, tel.: 202/ 622–2490, Assistant Director for Licensing, tel.: 202/622–2480, Assistant Director for Policy, tel.: 202/622–4855, Office of Foreign Assets Control, or Chief Counsel (Foreign Assets Control), tel.: 202/622–2410, Office of the General Counsel, Department of the Treasury, Washington, DC 20220 (not toll free numbers). SUPPLEMENTARY INFORMATION: Electronic and Facsimile Availability This document and additional information concerning OFAC are available from OFAC’s Web site (https:// www.treas.gov/ofac) or via facsimile through a 24-hour fax-on demand service, tel.: 202/622–0077. Background The Iranian Transactions Regulations, 31 CFR part 560 (the ‘‘ITR’’), implement a series of Executive orders that began with Executive Order 12613, which was issued on October 29, 1987, pursuant to authorities including the International Security and Development Cooperation Act of 1985 (22 U.S.C. 2349aa–9). In that Order, after finding, inter alia, that the Government of Iran was actively supporting terrorism as an instrument of state policy, the President prohibited the importation of Iranian-origin goods and services. Subsequently, in Executive Order 12957, issued on March 15, 1995, under the authority of, inter alia, the International Emergency PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Economic Powers Act (50 U.S.C. 1701– 1706) (‘‘IEEPA’’), the President declared a national emergency with respect to the actions and policies of the Government of Iran, including its support for international terrorism, its efforts to undermine the Middle East peace process, and its efforts to acquire weapons of mass destruction and the means to deliver them. To deal with that threat, Executive Order 12957 imposed prohibitions on certain transactions with respect to the development of Iranian petroleum resources. On May 6, 1995, to further respond to this threat, the President issued Executive Order 12959, which imposed comprehensive trade and financial sanctions on Iran. Finally, on August 19, 1997, the President issued Executive Order 13059 consolidating and clarifying the previous orders. The ITR implement these Executive orders and prohibit various transactions, including, among others, transactions with the Government of Iran, a term defined in § 560.304 to include any entity owned or controlled by the Government of Iran, which is a term that is itself defined in § 560.313 of the ITR. Since its initial publication in 1999, Appendix A to Part 560 has listed financial institutions that OFAC determined to be entities owned or controlled by the Government of Iran, within the meaning of §§ 560.304 and 560.313 of the ITR. This appendix is intended to assist U.S. persons in complying with the ITR. OFAC is expanding the scope of appendix A to include all categories of entities, not just financial institutions. This change will allow OFAC to give notice when it determines that any entity is owned or controlled by the Government of Iran. OFAC is expanding the scope of appendix A today in order to add the National Iranian Oil Company (a.k.a. NIOC), Naftiran Intertrade Company Ltd (a.k.a. NICO), and Naftiran Intertrade Co. (NICO) Sarl to the appendix as entities that are owned or controlled by the Government of Iran within the meaning of §§ 560.304 and 560.313 of the ITR. The ITR prohibit most transactions with any entity, wherever located, that is owned or controlled by the Government of Iran. It is important to note that Appendix A to Part 560 is not a comprehensive list of entities owned or controlled by the Government of Iran. Even if an entity is not listed in appendix A, if it is owned or controlled by the Government of Iran, U.S. persons are prohibited from engaging in transactions with that entity, in any of its locations worldwide, to the same extent that U.S. persons are prohibited from engaging in transactions E:\FR\FM\04DER1.SGM 04DER1

Agencies

[Federal Register Volume 73, Number 234 (Thursday, December 4, 2008)]
[Rules and Regulations]
[Pages 73785-73788]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-28365]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1258; Directorate Identifier 2008-NM-142-AD; 
Amendment 39-15758; AD 2008-24-14]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) 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:

    Cracks on the main landing gear trunnion fitting web have been 
discovered during fatigue testing. Failure of the main landing gear 
trunnion fitting web could compromise the structural integrity of 
the trunnion fitting and result in a main landing gear collapse. * * 
*

This AD requires actions that are intended to address the unsafe 
condition described in the MCAI.

DATES: This AD becomes effective December 19, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 19, 
2008.
    We must receive comments on this AD by January 5, 2009.

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

[[Page 73786]]

     Federal eRulemaking Portal: Go to https://
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 W12-40, 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 https://
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 aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2008-21, dated June 12, 2008 (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    Cracks on the main landing gear trunnion fitting web have been 
discovered during fatigue testing. Failure of the main landing gear 
trunnion fitting web could compromise the structural integrity of 
the trunnion fitting and result in a main landing gear collapse. A 
Temporary Revision has been made to the Bombardier CL-600-2B19 
Maintenance Requirements Manual, Appendix B, ``Airworthiness 
Limitations'' to ensure that fatigue cracking of the trunnion 
fitting web is detected and corrected.

The corrective action is revising the Airworthiness Limitations Section 
of the Instructions for Continued Airworthiness to incorporate new 
structural inspection requirements. You may obtain further information 
by examining the MCAI in the AD docket.

Relevant Service Information

    Bombardier has issued Temporary Revision 2B-2136, dated May 1, 
2008, to the Bombardier CL-600-2B19 Maintenance Requirements Manual, 
Part 2, Appendix B--Airworthiness Limitations.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

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 if 
the actions specified in the service information are not accomplished 
at the specified threshold, cracking in the main landing gear trunnion 
fitting web could go undetected. 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-2008-1258; Directorate 
Identifier 2008-NM-142-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 https://
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 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

[[Page 73787]]

    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:

2008-24-14 Bombardier, Inc. (Formerly Canadair): Amendment 39-15758. 
Docket No. FAA-2008-1258; Directorate Identifier 2008-NM-142-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
19, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Bombardier Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes, certificated in any 
category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (g)(1) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued operational safety of the airplane. The FAA has 
provided guidance for this determination in Advisory Circular (AC) 
25-1529-1A.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
Gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Cracks on the main landing gear trunnion fitting web have been 
discovered during fatigue testing. Failure of the main landing gear 
trunnion fitting web could compromise the structural integrity of 
the trunnion fitting and result in a main landing gear collapse. A 
Temporary Revision has been made to the Bombardier CL-600-2B19 
Maintenance Requirements Manual, Appendix B, ``Airworthiness 
Limitations'' to ensure that fatigue cracking of the trunnion 
fitting web is detected and corrected.

The corrective action is revising the Airworthiness Limitations 
Section of the Instructions for Continued Airworthiness to 
incorporate new structural inspection requirements.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 30 days after the effective date of this AD, revise 
the Airworthiness Limitations Section (ALS) of the Instructions for 
Continued Airworthiness to incorporate the Airworthiness Limitation 
(AWL) No. 57-21-161, as identified in Bombardier Temporary Revision 
2B-2136, dated May 1, 2008, to the Bombardier CL-600-2B19 
Maintenance Requirements Manual, Part 2, Appendix B--Airworthiness 
Limitations. The initial compliance time for the task starts from 
the applicable time specified in Table 1 or Table 2 of this AD, as 
applicable. Repeat the inspection thereafter at the applicable 
interval specified in Bombardier Temporary Revision 2B-2136, dated 
May 1, 2008.

                Table 1--Pre-Modsum TC601R15827 Airplanes
------------------------------------------------------------------------
 If the airplane has accumulated (as       Then phase in the initial
 of the effective date of this AD)--              inspection--
------------------------------------------------------------------------
23,500 total flight cycles or fewer..  Prior to the accumulation of
                                        25,000 total flight cycles.
23,501 to 25,000 total flight cycles.  Prior to the accumulation of
                                        26,000 total flight cycles, or
                                        within 1,500 flight cycles after
                                        the effective date of this AD,
                                        whichever occurs first.
25,001 to 26,000 total flight cycles.  Prior to the accumulation of
                                        26,500 total flight cycles, or
                                        within 1,000 flight cycles after
                                        the effective date of this AD,
                                        whichever occurs first.
26,001 or more total flight cycles...  Within 500 flight cycles after
                                        the effective date of this AD.
------------------------------------------------------------------------


               Table 2--Post-Modsum TC601R15827 Airplanes
------------------------------------------------------------------------
 If the airplane has accumulated (as       Then phase in the initial
 of the effective date of this AD)--              inspection--
------------------------------------------------------------------------
15,667 total flight cycles or fewer..  Prior to the accumulation of
                                        16,667 total flight cycles.
15,668 to 16,667 total flight cycles.  Prior to the accumulation of
                                        17,333 total flight cycles, or
                                        within 1,000 flight cycles after
                                        the effective date of this AD,
                                        whichever occurs first.
16,668 to 17,333 total flight cycles.  Prior to the accumulation of
                                        17,666 total flight cycles, or
                                        within 666 flight cycles after
                                        the effective date of this AD,
                                        whichever occurs first.
17,334 or more total flight cycles...  Within 333 flight cycles after
                                        the effective date of this AD.
------------------------------------------------------------------------

    (2) After accomplishing the actions specified in paragraph 
(f)(1) of this AD, no alternative inspections or inspection 
intervals may be used unless the inspection or inspection interval 
is approved as an alternative method of compliance (AMOC) in 
accordance with the procedures specified in paragraph (g)(1) of this 
AD.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: No differences.

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

[[Page 73788]]

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: 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), are not allowed.

Related Information

    (h) Refer to MCAI Canadian Airworthiness Directive CF-2008-21, 
dated June 12, 2008; and Bombardier Temporary Revision 2B-2136, 
dated May 1, 2008, to the Bombardier CL-600-2B19 Maintenance 
Requirements Manual, Part 2, Appendix B--Airworthiness Limitations; 
for related information.

Material Incorporated by Reference

    (i) You must use Bombardier Temporary Revision 2B-2136, dated 
May 1, 2008, to the Bombardier CL-600-2B19 Maintenance Requirements 
Manual, Part 2, Appendix B--Airworthiness Limitations Section, 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 https://
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: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on November 19, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E8-28365 Filed 12-3-08; 8:45 am]
BILLING CODE 4910-13-P
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