Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes; Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) Airplanes; Model CL-600-2D15 (Regional Jet Series 705) Airplanes; and Model CL-600-2D24 (Regional Jet Series 900) Airplanes, 34657-34661 [2010-14769]

Download as PDF Federal Register / Vol. 75, No. 117 / Friday, June 18, 2010 / Proposed Rules period to allow additional time for the preparation of their comments. DOE has determined that a brief extension of the public comment period is appropriate to allow stakeholders additional time to submit comments to DOE for consideration as the proposed rule is developed. DOE will consider any comments received by July 9, 2010 and deems any comments received between publication of the Federal Register notice and July 9, 2010 to be timely submitted. Further Information on Submitting Comments Under 10 CFR 1004.11, any person submitting information that he or she believes to be confidential and exempt by law from public disclosure should submit two copies: one copy of the document including all the information believed to be confidential, and one copy of the document with the information believed to be confidential deleted. DOE will make its own determination about the confidential status of the information and treat it according to its determination. Factors of interest to DOE when evaluating requests to treat submitted information as confidential include (1) a description of the items, (2) whether and why such items are customarily treated as confidential within the industry, (3) whether the information is generally known by or available from other sources, (4) whether the information has previously been made available to others without obligation concerning its confidentiality, (5) an explanation of the competitive injury to the submitting person which would result from public disclosure, (6) when such information might lose its confidential character due to the passage of time, and (7) why disclosure of the information would be contrary to the public interest. Issued in Washington, DC, on June 11, 2010. Cathy Zoi, Assistant Secretary, Energy Efficiency and Renewable Energy. hsrobinson on DSK69SOYB1PROD with PROPOSALS-1 [FR Doc. 2010–14755 Filed 6–17–10; 8:45 am] BILLING CODE 6450–01–P VerDate Mar<15>2010 17:12 Jun 17, 2010 Jkt 220001 DEPARTMENT OF ENERGY 10 CFR Parts 433 and 435 [Docket No. EE–RM/STD–02–112] RIN 1904–AC13 Energy Efficiency and Sustainable Design Standards for New Federal Buildings AGENCY: Office of Energy Efficiency and Renewable Energy, Department of Energy. ACTION: Proposed rulemaking; extension of comment period. SUMMARY: The U.S. Department of Energy (DOE) published a document in the Federal Register on May 28, 2010, concerning a public meeting and availability of the notice of proposed rulemaking (NOPR) regarding the application of sustainable design principals with respect to the siting, design, and construction of new Federal buildings. This notice extends the comment period to August 12, 2010. DATES: DOE will hold a public meeting in Washington, DC, on Wednesday, July 28, 2010, beginning at 9 a.m. DOE must receive requests to speak at the meeting before 4 p.m., Wednesday, July 14, 2010. DOE must receive a signed original and an electronic copy of statements to be given at the public meeting before 4 p.m., Wednesday, July 21, 2010. Written comments on the NOPR are welcome, especially following the public meeting, and should be submitted by Thursday, August 12, 2010. ADDRESSES: The public meeting will be held at the U.S. Department of Energy, Forrestal Building, Room 8E–089, 1000 Independence Avenue, SW., Washington, DC 20585–0121. To attend the public meeting, please notify Ms. Brenda Edwards at (202) 586–2945. Please note that foreign nationals participating in the public meeting are subject to advance security screening procedures, requiring a 30-day advance notice. If you are a foreign national and wish to participate in the public meeting, please inform DOE as soon as possible by contacting Ms. Brenda Edwards at (202) 586–2945 so that the necessary procedures can be completed. FOR FURTHER INFORMATION CONTACT: Cyrus Nasseri, U.S. Department of Energy, Office of Energy Efficiency and Renewable Energy, Federal Energy Management Program, EE–2L, 1000 Independence Avenue, SW., Washington, DC 20585–0121, (202) 586– 9138, e-mail: Cyrus.Nasseri@ee.doe.gov, or Ami Grace-Tardy, U.S. Department of Energy, Office of the General Counsel, PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 34657 Forrestal Building, GC–71, 1000 Independence Avenue, SW., Washington, DC 20585, (202) 586–5709, e-mail: Ami.Grace-Tardy@hq.doe.gov. SUPPLEMENTARY INFORMATION: DOE published a document in the Federal Register on May 28, 2010 (75 FR 29933), concerning a public meeting and availability of the NOPR regarding the application of sustainable design principals with respect to the siting, design, and construction of new Federal buildings. This document extends the comment period by 15 days to August 12, 2010. The purpose of the July 28, 2010, public meeting is to discuss the NOPR regarding the application of sustainable design principals with respect to the siting, design, and construction of new Federal buildings. For additional information regarding the NOPR and the public meeting, including detailed instructions for the submission of comments and access to the docket to read background documents or comments received, please refer to the May 28, 2010 notice (75 FR 29933). The Department welcomes all interested parties, regardless of whether they participate in the public meeting, to submit written comments regarding matters addressed in the NOPR, as well as any other related issues, by August 12, 2010. Issued in Washington, DC on June 11, 2010. Cathy Zoi, Assistant Secretary, Energy Efficiency and Renewable Energy. [FR Doc. 2010–14752 Filed 6–17–10; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0550; Directorate Identifier 2009–NM–124–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes; Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) Airplanes; Model CL–600– 2D15 (Regional Jet Series 705) Airplanes; and Model CL–600–2D24 (Regional Jet Series 900) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). E:\FR\FM\18JNP1.SGM 18JNP1 hsrobinson on DSK69SOYB1PROD with PROPOSALS-1 34658 Federal Register / Vol. 75, No. 117 / Friday, June 18, 2010 / Proposed Rules SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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: Two cases of a crack on a ‘‘dry’’ ADG [air driven generator] (Hamilton Sundstrand part number in the 761339 series), in the aft area of the strut and generator housing assembly, have been reported on CL–600–2B19 aircraft. The same part is also installed on CL–600–2C10, –2D15 and –2D24 aircraft. Investigation determined that the crack was in an area of the strut where the wall thickness of the casting was below specification, due to a manufacturing anomaly in a specific batch of ADGs. Structural failure and departure of the ADG during deployment could possibly result in damage to the aircraft structure. If deployment was activated by a dual engine shutdown, ADG structural failure would also result in loss of hydraulics for the flight controls. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by August 2, 2010. ADDRESSES: You may send comments by any of the following methods: • 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. For service information identified in this proposed AD, contact Bombardier, ˆ Inc., 400 Cote Vertu Road West, Dorval, ´ Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. VerDate Mar<15>2010 17:12 Jun 17, 2010 Jkt 220001 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 proposed 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: Craig Yates, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7355; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0550; Directorate Identifier 2009–NM–124–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We have lengthened the 30-day comment period for proposed ADs that address MCAI originated by aviation authorities of other countries to provide adequate time for interested parties to submit comments. The comment period for these proposed ADs is now typically 45 days, which is consistent with the comment period for domestic transport ADs. 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 proposed AD. Discussion Transport Canada Civil Aviation, which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2009–27, dated June 8, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Two cases of a crack on a ‘‘dry’’ ADG [air driven generator] (Hamilton Sundstrand part number in the 761339 series), in the aft area of the strut and generator housing assembly, have been reported on CL–600–2B19 aircraft. The same part is also installed on CL–600– 2C10, –2D15 and –2D24 aircraft. Investigation determined that the crack was in an area of the strut where the wall thickness of the casting was below specification, due to a manufacturing anomaly in a specific batch of ADGs. Structural failure and departure of the ADG during deployment could possibly result in damage to the aircraft structure. If deployment was activated by a dual engine shutdown, ADG structural failure would also result in loss of hydraulics for the flight controls. This directive gives instructions to check the part number of the installed ADG and, for ADGs with a part number in the 761339 series, the serial numbers of the ADG and strut and generator housing assembly are also to be checked. If these serial numbers are within specified ranges ***, a one-time fluorescent penetrant inspection of the ADG strut is required [and replacement of the ADG if necessary]. Note: For ADGs with serial numbers in the *** specified ranges, subsequent fluorescent penetrant inspections are required after each scheduled in-flight or on-ground functional check of the ADG and also after each unscheduled in-flight ADG deployment. These inspection requirements are not mandated in this directive but are specified in the approved maintenance program. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Bombardier has issued Alert Service Bulletin A601R–24–120, Revision C, dated April 20, 2009; and Alert Service Bulletin A670BA–24–020, Revision C, dated April 20, 2009. 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 Proposed 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 proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in E:\FR\FM\18JNP1.SGM 18JNP1 Federal Register / Vol. 75, No. 117 / Friday, June 18, 2010 / Proposed Rules 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 proposed 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 proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 1,073 products of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $91,205, or $85 per product. hsrobinson on DSK69SOYB1PROD with PROPOSALS-1 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; VerDate Mar<15>2010 17:12 Jun 17, 2010 Jkt 220001 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 proposed 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Bombardier, Inc.: Docket No. FAA–2010– 0550; Directorate Identifier 2009–NM– 124–AD. Comments Due Date (a) We must receive comments by August 2, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers 7305 through 8051 inclusive; Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, serial numbers 10003 through 10260 inclusive; and Model CL–600–2D15 (Regional Jet Series 705) airplanes and Model CL–600–2D24 (Regional Jet Series 900) airplanes, serial numbers 15001 through 15106 inclusive; certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 24: Electrical Power. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Two cases of a crack on a ‘‘dry’’ ADG [air driven generator] (Hamilton Sundstrand part number in the 761339 series), in the aft area of the strut and generator housing assembly, have been reported on CL–600–2B19 aircraft. The same part is also installed on CL–600– 2C10, –2D15 and –2D24 aircraft. Investigation determined that the crack was PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 34659 in an area of the strut where the wall thickness of the casting was below specification, due to a manufacturing anomaly in a specific batch of ADGs. Structural failure and departure of the ADG during deployment could possibly result in damage to the aircraft structure. If deployment was activated by a dual engine shutdown, ADG structural failure would also result in loss of hydraulics for the flight controls. This directive gives instructions to check the part number of the installed ADG and, for ADGs with a part number in the 761339 series, the serial numbers of the ADG and strut and generator housing assembly are also to be checked. If these serial numbers are within specified ranges ***, a one-time fluorescent penetrant inspection of the ADG strut is required [and replacement of the ADG if necessary]. Note: For ADGs with serial numbers in the * * * specified ranges, subsequent fluorescent penetrant inspections are required after each scheduled in-flight or onground functional check of the ADG and also after each unscheduled in-flight ADG deployment. These inspection requirements are not mandated in this directive but are specified in the approved maintenance program. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) Do the following actions. (1) Within 1,000 flight hours after the effective date of this AD or before the first scheduled ADG functional test after the effective date of this AD, whichever occurs first, inspect to determine the part number of the installed ADG. A review of the airplane maintenance records is acceptable in lieu of this inspection if the part number can be conclusively determined from that review. (i) If a Hamilton Sundstrand ADG having part number 1711405 is installed, the strut thickness is within specification and no further action is required by this AD. (ii) If a Hamilton Sundstrand ADG having a part number in the 761339 series is installed, within 1,000 flight hours after the effective date of this AD or before the first scheduled ADG functional test after the effective date of this AD, whichever occurs first, inspect to determine the serial number of the ADG. A review of the airplane maintenance records is acceptable in lieu of this inspection if the serial number can be conclusively determined from that review. (A) If the serial number of the ADG is 2000 or higher, the strut wall thickness is within specification and no further action is required by this AD. (B) If the serial number of the ADG is in the range 0101 through 1999 and symbol ‘‘24–3’’ is marked in the serial number block of the identification plate, the strut wall thickness is within specification, no further action is required by this AD. (C) If the serial number of the ADG is in the range 0101 through 1999 and the symbol E:\FR\FM\18JNP1.SGM 18JNP1 34660 Federal Register / Vol. 75, No. 117 / Friday, June 18, 2010 / Proposed Rules ‘‘24–3’’ is not marked in the serial block of the identification plate, within 1,000 flight hours after the effective date of this AD or before the first scheduled ADG functional test after the effective date of this AD, whichever occurs first, inspect to determine the serial number of the strut and generator housing assembly. A review of the airplane maintenance records is acceptable in lieu of this inspection if the serial number can be conclusively determined from that review. (1) If the serial number of the strut and generator housing assembly is in the range 0001 through 2503, do a fluorescent penetrant inspection in accordance with paragraph (g)(2) of this AD at the times specified in paragraph (g)(2) of this AD. (2) If the serial number of the strut and generator housing assembly is 2504 or higher, the strut wall thickness is within specification and no further action is required by this AD. (3) If the serial number of the strut and generator housing assembly is not inspected or it is not possible to determine the serial number, do a fluorescent penetrant inspection in accordance with paragraph (g)(2) of this AD at the times specified in paragraph (g)(2) of this AD. (2) For ADGs having a strut and generator assembly identified in paragraph (g)(1)(ii)(C)(1) or (g)(1)(ii)(C)(3) of this AD: Within 1,000 flight hours after the effective date of this AD or before the first scheduled ADG functional test after the effective date of this AD, whichever occurs first, do a fluorescent penetrant inspection for cracking of the ADG strut, and if any crack is found, before further flight, replace the ADG with a serviceable ADG, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–24–120, Revision C, dated April 20, 2009 (for Model CL–600–2B19 airplanes); or Bombardier Alert Service Bulletin A670BA–24–020, Revision C, dated April 20, 2009 (for Model CL–600– 2C10, CL–600–2D15, and CL–600–2D24 airplanes). (3) Fluorescent penetrant inspections accomplished before the effective date of this AD in accordance with any applicable service bulletin specified in Table 1 of this AD are considered acceptable for compliance with the corresponding fluorescent penetrant inspection specified in this AD. TABLE 1—CREDIT SERVICE BULLETINS Bombardier, Inc. Model— Service Bulletin— Revision— Dated— CL–600–2B19 airplanes ........................................... CL–600–2B19 airplanes ........................................... CL–600–2B19 airplanes ........................................... CL–600–2C10 airplanes and CL–600–2D24 airplanes. CL–600–2C10 airplanes; and CL–600–2D15 and CL–600–2D24 airplanes. CL–600–2C10 airplanes; and CL–600–2D15 and CL–600–2D24 airplanes. CL–600–2B19 airplanes; CL–600–2C10 airplanes; and CL–600–2D15 and CL–600–2D24 airplanes. CL–600–2B19 airplanes; CL–600–2C10 airplanes; and CL–600–2D15 and CL–600–2D24 airplanes. CL–600–2B19 airplanes; CL–600–2C10 airplanes; and CL–600–2D15 and CL–600–2D24 airplanes. Bombardier, Inc. CL–600–2B19 airplanes; CL– 600–2C10 airplanes; and CL–600–2D15 and CL–600–2D24 airplanes. Bombardier Alert Service Bulletin A601R–24–120 Bombardier Alert Service Bulletin A601R–24–120 Bombardier Alert Service Bulletin A601R–24–120 Bombardier Alert Service Bulletin A670BA–24– 020. Bombardier Alert Service Bulletin A670BA–24– 020. Bombardier Alert Service Bulletin A670BA–24– 020. Hamilton Sundstrand Service Bulletin ERPS10AG–24–3. Hamilton Sundstrand Service Bulletin ERPS10AG–24–3. Hamilton Sundstrand Service Bulletin ERPS10AG–24–3. Hamilton Sundstrand Service Bulletin ERPS10AG–24–3. Original .... A .............. B .............. Original .... April 20, 2005. December 1, 2005. December 7, 2006. April 20, 2005. A .............. May 17, 2005. B .............. December 7, 2006. Original .... April 14, 2005. 1 .............. April 19, 2005. 2 .............. November 14, 2006. 3 ............... March 12, 2009. Note 1: For additional guidance on the ADGs specified in paragraphs (g)(1)(ii)(C)(1)and (g)(1)(ii)(C)(3) of this AD and the repetitive fluorescent penetrant inspections specified as part of the periodic ADG functional check procedure, refer to the applicable tasks identified in Table 2 of this AD. These tasks can be found in Part 2 –Airworthiness Requirements, Appendix A— Certification Maintenance Requirements (CMR) of the Bombardier (Canadair) Regional Jet Maintenance Requirements Manual, and the Bombardier CRJ Series Regional Jet Aircraft Maintenance Manual (AMM). TABLE 2—GUIDANCE FOR THE PERIODIC ADG FUNCTIONAL CHECK PROCEDURE Bombardier, Inc. Model— Task Number (No.)— CL–600–2B19 airplanes ................. CL–600–2C10 airplanes ................. CL–600–2D15 and CL–600–2D24 airplanes. CMR Task No. C24–20–129–01 and AMM Task No: 24–23–01–720–803. CMR Task No. 24–23–00–102 and AMM Task No. 24–23–01–720–802. CMR Task No. 24–23–00–102 and AMM Task No. 24–23–01–720–802. Note 2: For additional guidance on the ADGs specified in paragraph (g)(1)(ii)(C)(1), and the fluorescent penetrant inspection necessary following each future unscheduled in-flight ADG deployment, refer to following task specified in Table 3 of this AD. hsrobinson on DSK69SOYB1PROD with PROPOSALS-1 TABLE 3—GUIDANCE FOR INSPECTION FOLLOWING UNSCHEDULED IN-FLIGHT ADG DEPLOYMENT Bombardier, Inc. Model— AMM Task No.— CL–600–2B19 airplanes, serial numbers 7305 through 8051 inclusive ............................................................................. CL–600–2C10 airplanes, serial numbers 10003 through 10260 inclusive ......................................................................... CL–600–2D15 and CL–600–2D24 airplanes, serial numbers 15001 through 15106 inclusive .......................................... VerDate Mar<15>2010 17:12 Jun 17, 2010 Jkt 220001 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 E:\FR\FM\18JNP1.SGM 18JNP1 05–51–19–210–801 05–51–19–210–801 05–51–19–210–801 Federal Register / Vol. 75, No. 117 / Friday, June 18, 2010 / Proposed Rules Note 3: In Hamilton Sundstrand Service Bulletin ERPS10AG–24–3, the fluorescent penetrant inspection is referred to as a ‘‘Penetrant Check.’’ DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 FAA AD Differences [Docket No. FAA–2010–0549; Directorate Identifier 2010–NM–109–AD] Note 4: This AD differs from the MCAI and/or service information as follows: No differences. RIN 2120–AA64 Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York, 11590; telephone 516–228–7300; fax 516– 794–5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (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 (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. (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. hsrobinson on DSK69SOYB1PROD with PROPOSALS-1 Related Information (i) Refer to MCAI Canadian Airworthiness Directive CF–2009–27, dated June 8, 2009; Bombardier Alert Service Bulletin A601R– 24–120, Revision C, dated April 20, 2009; and Bombardier Alert Service Bulletin A670BA–24–020, Revision C, dated April 20, 2009; for related information. Issued in Renton, Washington, on June 10, 2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–14769 Filed 6–17–10; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 17:12 Jun 17, 2010 Jkt 220001 Airworthiness Directives; McDonnell Douglas Corporation Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–87), and MD–88 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–87), and MD–88 airplanes. This proposed AD would require installing fuel level float and pressure switch inline fuses on the wing forward spars and forward and aft auxiliary fuel tanks, depending on the airplane configuration. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by August 2, 2010. ADDRESSES: You may send comments by any of the following methods: • 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 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 34661 https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone 562–627–5262; fax 562–627– 5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0549; Directorate Identifier 2010–NM–109–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed 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 proposed AD. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport E:\FR\FM\18JNP1.SGM 18JNP1

Agencies

[Federal Register Volume 75, Number 117 (Friday, June 18, 2010)]
[Proposed Rules]
[Pages 34657-34661]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-14769]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0550; Directorate Identifier 2009-NM-124-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19 
(Regional Jet Series 100 & 440) Airplanes; Model CL-600-2C10 (Regional 
Jet Series 700, 701, & 702) Airplanes; Model CL-600-2D15 (Regional Jet 
Series 705) Airplanes; and Model CL-600-2D24 (Regional Jet Series 900) 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

[[Page 34658]]

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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: Two cases of a crack on a ``dry'' ADG [air driven 
generator] (Hamilton Sundstrand part number in the 761339 series), in 
the aft area of the strut and generator housing assembly, have been 
reported on CL-600-2B19 aircraft. The same part is also installed on 
CL-600-2C10, -2D15 and -2D24 aircraft. Investigation determined that 
the crack was in an area of the strut where the wall thickness of the 
casting was below specification, due to a manufacturing anomaly in a 
specific batch of ADGs. Structural failure and departure of the ADG 
during deployment could possibly result in damage to the aircraft 
structure. If deployment was activated by a dual engine shutdown, ADG 
structural failure would also result in loss of hydraulics for the 
flight controls. The proposed AD would require actions that are 
intended to address the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by August 2, 2010.

ADDRESSES: You may send comments by any of the following methods:
     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.
    For service information identified in this proposed 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. You 
may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221.

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 proposed 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: Craig Yates, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7355; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0550; 
Directorate Identifier 2009-NM-124-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We have lengthened the 30-day comment period for proposed ADs that 
address MCAI originated by aviation authorities of other countries to 
provide adequate time for interested parties to submit comments. The 
comment period for these proposed ADs is now typically 45 days, which 
is consistent with the comment period for domestic transport ADs.
    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 proposed AD.

Discussion

    Transport Canada Civil Aviation, which is the aviation authority 
for Canada, has issued Canadian Airworthiness Directive CF-2009-27, 
dated June 8, 2009 (referred to after this as ``the MCAI''), to correct 
an unsafe condition for the specified products. The MCAI states:

    Two cases of a crack on a ``dry'' ADG [air driven generator] 
(Hamilton Sundstrand part number in the 761339 series), in the aft 
area of the strut and generator housing assembly, have been reported 
on CL-600-2B19 aircraft. The same part is also installed on CL-600-
2C10, -2D15 and -2D24 aircraft. Investigation determined that the 
crack was in an area of the strut where the wall thickness of the 
casting was below specification, due to a manufacturing anomaly in a 
specific batch of ADGs. Structural failure and departure of the ADG 
during deployment could possibly result in damage to the aircraft 
structure. If deployment was activated by a dual engine shutdown, 
ADG structural failure would also result in loss of hydraulics for 
the flight controls.
    This directive gives instructions to check the part number of 
the installed ADG and, for ADGs with a part number in the 761339 
series, the serial numbers of the ADG and strut and generator 
housing assembly are also to be checked. If these serial numbers are 
within specified ranges ***, a one-time fluorescent penetrant 
inspection of the ADG strut is required [and replacement of the ADG 
if necessary].
    Note: For ADGs with serial numbers in the *** specified ranges, 
subsequent fluorescent penetrant inspections are required after each 
scheduled in-flight or on-ground functional check of the ADG and 
also after each unscheduled in-flight ADG deployment. These 
inspection requirements are not mandated in this directive but are 
specified in the approved maintenance program.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bombardier has issued Alert Service Bulletin A601R-24-120, Revision 
C, dated April 20, 2009; and Alert Service Bulletin A670BA-24-020, 
Revision C, dated April 20, 2009. 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 Proposed 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 proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in

[[Page 34659]]

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 proposed 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 proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 1,073 products of U.S. registry. We also estimate 
that it would take about 1 work-hour per product to comply with the 
basic requirements of this proposed AD. The average labor rate is $85 
per work-hour. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $91,205, or $85 per product.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

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

Bombardier, Inc.: Docket No. FAA-2010-0550; Directorate Identifier 
2009-NM-124-AD.

Comments Due Date

    (a) We must receive comments by August 2, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier, Inc. Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes, serial numbers 7305 
through 8051 inclusive; Model CL-600-2C10 (Regional Jet Series 700, 
701, & 702) airplanes, serial numbers 10003 through 10260 inclusive; 
and Model CL-600-2D15 (Regional Jet Series 705) airplanes and Model 
CL-600-2D24 (Regional Jet Series 900) airplanes, serial numbers 
15001 through 15106 inclusive; certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 24: 
Electrical Power.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Two cases of a crack on a ``dry'' ADG [air driven generator] 
(Hamilton Sundstrand part number in the 761339 series), in the aft 
area of the strut and generator housing assembly, have been reported 
on CL-600-2B19 aircraft. The same part is also installed on CL-600-
2C10, -2D15 and -2D24 aircraft. Investigation determined that the 
crack was in an area of the strut where the wall thickness of the 
casting was below specification, due to a manufacturing anomaly in a 
specific batch of ADGs. Structural failure and departure of the ADG 
during deployment could possibly result in damage to the aircraft 
structure. If deployment was activated by a dual engine shutdown, 
ADG structural failure would also result in loss of hydraulics for 
the flight controls.
    This directive gives instructions to check the part number of 
the installed ADG and, for ADGs with a part number in the 761339 
series, the serial numbers of the ADG and strut and generator 
housing assembly are also to be checked. If these serial numbers are 
within specified ranges ***, a one-time fluorescent penetrant 
inspection of the ADG strut is required [and replacement of the ADG 
if necessary].


    Note: For ADGs with serial numbers in the * * * specified 
ranges, subsequent fluorescent penetrant inspections are required 
after each scheduled in-flight or on-ground functional check of the 
ADG and also after each unscheduled in-flight ADG deployment. These 
inspection requirements are not mandated in this directive but are 
specified in the approved maintenance program.

Compliance

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

Actions

    (g) Do the following actions.
    (1) Within 1,000 flight hours after the effective date of this 
AD or before the first scheduled ADG functional test after the 
effective date of this AD, whichever occurs first, inspect to 
determine the part number of the installed ADG. A review of the 
airplane maintenance records is acceptable in lieu of this 
inspection if the part number can be conclusively determined from 
that review.
    (i) If a Hamilton Sundstrand ADG having part number 1711405 is 
installed, the strut thickness is within specification and no 
further action is required by this AD.
    (ii) If a Hamilton Sundstrand ADG having a part number in the 
761339 series is installed, within 1,000 flight hours after the 
effective date of this AD or before the first scheduled ADG 
functional test after the effective date of this AD, whichever 
occurs first, inspect to determine the serial number of the ADG. A 
review of the airplane maintenance records is acceptable in lieu of 
this inspection if the serial number can be conclusively determined 
from that review.
    (A) If the serial number of the ADG is 2000 or higher, the strut 
wall thickness is within specification and no further action is 
required by this AD.
    (B) If the serial number of the ADG is in the range 0101 through 
1999 and symbol ``24-3'' is marked in the serial number block of the 
identification plate, the strut wall thickness is within 
specification, no further action is required by this AD.
    (C) If the serial number of the ADG is in the range 0101 through 
1999 and the symbol

[[Page 34660]]

``24-3'' is not marked in the serial block of the identification 
plate, within 1,000 flight hours after the effective date of this AD 
or before the first scheduled ADG functional test after the 
effective date of this AD, whichever occurs first, inspect to 
determine the serial number of the strut and generator housing 
assembly. A review of the airplane maintenance records is acceptable 
in lieu of this inspection if the serial number can be conclusively 
determined from that review.
    (1) If the serial number of the strut and generator housing 
assembly is in the range 0001 through 2503, do a fluorescent 
penetrant inspection in accordance with paragraph (g)(2) of this AD 
at the times specified in paragraph (g)(2) of this AD.
    (2) If the serial number of the strut and generator housing 
assembly is 2504 or higher, the strut wall thickness is within 
specification and no further action is required by this AD.
    (3) If the serial number of the strut and generator housing 
assembly is not inspected or it is not possible to determine the 
serial number, do a fluorescent penetrant inspection in accordance 
with paragraph (g)(2) of this AD at the times specified in paragraph 
(g)(2) of this AD.
    (2) For ADGs having a strut and generator assembly identified in 
paragraph (g)(1)(ii)(C)(1) or (g)(1)(ii)(C)(3) of this AD: Within 
1,000 flight hours after the effective date of this AD or before the 
first scheduled ADG functional test after the effective date of this 
AD, whichever occurs first, do a fluorescent penetrant inspection 
for cracking of the ADG strut, and if any crack is found, before 
further flight, replace the ADG with a serviceable ADG, in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A601R-24-120, Revision C, dated April 20, 2009 (for 
Model CL-600-2B19 airplanes); or Bombardier Alert Service Bulletin 
A670BA-24-020, Revision C, dated April 20, 2009 (for Model CL-600-
2C10, CL-600-2D15, and CL-600-2D24 airplanes).
    (3) Fluorescent penetrant inspections accomplished before the 
effective date of this AD in accordance with any applicable service 
bulletin specified in Table 1 of this AD are considered acceptable 
for compliance with the corresponding fluorescent penetrant 
inspection specified in this AD.

                                        Table 1--Credit Service Bulletins
----------------------------------------------------------------------------------------------------------------
      Bombardier, Inc. Model--             Service Bulletin--            Revision--               Dated--
----------------------------------------------------------------------------------------------------------------
CL-600-2B19 airplanes...............  Bombardier Alert Service      Original............  April 20, 2005.
                                       Bulletin A601R-24-120.
CL-600-2B19 airplanes...............  Bombardier Alert Service      A...................  December 1, 2005.
                                       Bulletin A601R-24-120.
CL-600-2B19 airplanes...............  Bombardier Alert Service      B...................  December 7, 2006.
                                       Bulletin A601R-24-120.
CL-600-2C10 airplanes and CL-600-     Bombardier Alert Service      Original............  April 20, 2005.
 2D24 airplanes.                       Bulletin A670BA-24-020.
CL-600-2C10 airplanes; and CL-600-    Bombardier Alert Service      A...................  May 17, 2005.
 2D15 and CL-600-2D24 airplanes.       Bulletin A670BA-24-020.
CL-600-2C10 airplanes; and CL-600-    Bombardier Alert Service      B...................  December 7, 2006.
 2D15 and CL-600-2D24 airplanes.       Bulletin A670BA-24-020.
CL-600-2B19 airplanes; CL-600-2C10    Hamilton Sundstrand Service   Original............  April 14, 2005.
 airplanes; and CL-600-2D15 and CL-    Bulletin ERPS10AG-24-3.
 600-2D24 airplanes.
CL-600-2B19 airplanes; CL-600-2C10    Hamilton Sundstrand Service   1...................  April 19, 2005.
 airplanes; and CL-600-2D15 and CL-    Bulletin ERPS10AG-24-3.
 600-2D24 airplanes.
CL-600-2B19 airplanes; CL-600-2C10    Hamilton Sundstrand Service   2...................  November 14, 2006.
 airplanes; and CL-600-2D15 and CL-    Bulletin ERPS10AG-24-3.
 600-2D24 airplanes.
Bombardier, Inc. CL-600-2B19          Hamilton Sundstrand Service   3...................  March 12, 2009.
 airplanes; CL-600-2C10 airplanes;     Bulletin ERPS10AG-24-3.
 and CL-600-2D15 and CL-600-2D24
 airplanes.
----------------------------------------------------------------------------------------------------------------


    Note 1: For additional guidance on the ADGs specified in 
paragraphs (g)(1)(ii)(C)(1)and (g)(1)(ii)(C)(3) of this AD and the 
repetitive fluorescent penetrant inspections specified as part of 
the periodic ADG functional check procedure, refer to the applicable 
tasks identified in Table 2 of this AD. These tasks can be found in 
Part 2 -Airworthiness Requirements, Appendix A--Certification 
Maintenance Requirements (CMR) of the Bombardier (Canadair) Regional 
Jet Maintenance Requirements Manual, and the Bombardier CRJ Series 
Regional Jet Aircraft Maintenance Manual (AMM).


    Table 2--Guidance for the Periodic ADG Functional Check Procedure
------------------------------------------------------------------------
     Bombardier, Inc. Model--                Task Number (No.)--
------------------------------------------------------------------------
CL-600-2B19 airplanes.............  CMR Task No. C24-20-129-01 and AMM
                                     Task No: 24-23-01-720-803.
CL-600-2C10 airplanes.............  CMR Task No. 24-23-00-102 and AMM
                                     Task No. 24-23-01-720-802.
CL-600-2D15 and CL-600-2D24         CMR Task No. 24-23-00-102 and AMM
 airplanes.                          Task No. 24-23-01-720-802.
------------------------------------------------------------------------


    Note 2:  For additional guidance on the ADGs specified in 
paragraph (g)(1)(ii)(C)(1), and the fluorescent penetrant inspection 
necessary following each future unscheduled in-flight ADG 
deployment, refer to following task specified in Table 3 of this AD.


  Table 3--Guidance for Inspection Following Unscheduled In-Flight ADG
                               Deployment
------------------------------------------------------------------------
            Bombardier, Inc. Model--                  AMM Task No.--
------------------------------------------------------------------------
CL-600-2B19 airplanes, serial numbers 7305              05-51-19-210-801
 through 8051 inclusive........................
CL-600-2C10 airplanes, serial numbers 10003             05-51-19-210-801
 through 10260 inclusive.......................
CL-600-2D15 and CL-600-2D24 airplanes, serial           05-51-19-210-801
 numbers 15001 through 15106 inclusive.........
------------------------------------------------------------------------



[[Page 34661]]

    Note 3: In Hamilton Sundstrand Service Bulletin ERPS10AG-24-3, 
the fluorescent penetrant inspection is referred to as a ``Penetrant 
Check.''

FAA AD Differences

    Note 4:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), ANE-170, 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: Program 
Manager, Continuing Operational Safety, FAA, New York ACO, 1600 
Stewart Avenue, Suite 410, Westbury, New York, 11590; telephone 516-
228-7300; fax 516-794-5531. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your principal 
maintenance inspector (PMI) or principal avionics inspector (PAI), 
as appropriate, or lacking a principal inspector, your local Flight 
Standards District Office. The AMOC approval letter must 
specifically reference this AD.
    (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 (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.
    (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

    (i) Refer to MCAI Canadian Airworthiness Directive CF-2009-27, 
dated June 8, 2009; Bombardier Alert Service Bulletin A601R-24-120, 
Revision C, dated April 20, 2009; and Bombardier Alert Service 
Bulletin A670BA-24-020, Revision C, dated April 20, 2009; for 
related information.

    Issued in Renton, Washington, on June 10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-14769 Filed 6-17-10; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.