Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 38065-38069 [2011-16365]

Download as PDF Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules Related Information (i) Refer to MCAI Civil Aviation Authority of Israel (CAAI) Airworthiness Directive 57– 10–06–18, dated July 27, 2010; and Gulfstream Service Bulletin 200–51–366, dated March 30, 2010, including Appendix A: Israel Aircraft Industries Document IS951400E, Radiographic Inspection of SelfLocking Nut P/N MS21042L3, Revision A, dated January 25, 2010; for related information. Issued in Renton, Washington, on June 21, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–16314 Filed 6–28–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0648; Directorate Identifier 2010–NM–276–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. 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: SUMMARY: Seven cases of on-ground hydraulic accumulator screw cap/end cap failure have been experienced on CL–600–2B19 aeroplanes, resulting in the loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. * * * srobinson on DSK4SPTVN1PROD with PROPOSALS * * * * * A detailed analysis of the calculated line of trajectory of a failed screw cap/end cap for each of the accumulators has been conducted, resulting in the identification of several areas where systems and/or structural components could potentially be damaged. Although all of the failures to date have occurred on the ground, an in-flight failure affecting such components could potentially have an adverse effect on the controllability of the aeroplane. * * * VerDate Mar<15>2010 * * 16:52 Jun 28, 2011 Jkt 223001 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 15, 2011. 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; 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: Christopher Alfano, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7340; 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 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 38065 section. Include ‘‘Docket No. FAA–2011–0648; Directorate Identifier 2010–NM–276–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 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. ADDRESSES Discussion On October 7, 2010, we issued AD 2010–22–02, Amendment 39–16481 (75 FR 64636, October 20, 2010). That AD required actions intended to address an unsafe condition on Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. Since we issued AD 2010–22–02, we have determined that further rulemaking is necessary. While AD 2010–22–02 did not require the removal of the hydraulic system No. 3 accumulator, or replacement of the hydraulic system No. 1, inboard brake, and outboard brake accumulators, as specified in Part IV and Part VII of the Canadian Airworthiness Directive CF– 2010–24, dated August 3, 2010, this NPRM proposes to require those actions. Also, for airplanes on which Bombardier Service Bulletin 601R–29– 035, dated May 11, 2010, is done and reducer having part number MS21916D8–6 installed, this NPRM proposes to require replacing the reducer with a new reducer. We have coordinated with Transport Canada Civil Aviation (TCCA) on this issue. Relevant Service Information Bombardier has issued Service Bulletin 601R–29–035, Revision A; and Service Bulletin 601R–32–107, Revision B; both dated December 8, 2010. The actions described in this service information as outlined in the ‘‘Discussion’’ section above, are intended to correct the unsafe condition identified in the MCAI. Change to Existing AD This proposed AD would retain all requirements of AD 2010–22–02. Since AD 2010–22–02 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: E:\FR\FM\29JNP1.SGM 29JNP1 38066 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules Requirement in AD 2010–22–02 paragraph paragraph paragraph paragraph paragraph paragraph paragraph paragraph paragraph (j) (k) (l) (m) (n) (o) (p) (q) (r) Corresponding requirement in this proposed AD paragraph paragraph paragraph paragraph paragraph paragraph paragraph paragraph paragraph (o) (j) (k) (p) (l) (m) (r) (n) (s) 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. srobinson on DSK4SPTVN1PROD with PROPOSALS Differences Between This 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 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 605 products of U.S. registry. The actions that are required by AD 2010–22–02 and retained in this proposed AD take about 19 work-hours per product, at an average labor rate of $85 per work hour. Based on these figures, the estimated cost of the currently required actions is $1,615 per product. We estimate that it would take about 14 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is VerDate Mar<15>2010 16:52 Jun 28, 2011 Jkt 223001 $85 per work-hour. Required parts would cost about $3,054 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $2,567,620, or $4,244 per product. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Authority for This Rulemaking REVISED PARAGRAPH IDENTIFIERS 1. The authority citation for part 39 continues to read as follows: 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. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–16481 (75 FR 64636, October 20, 2010) and adding the following new AD: Bombardier, Inc.: Docket No. FAA–2011– 0648; Directorate Identifier 2010–NM– 276–AD. Comments Due Date (a) We must receive comments by August 15, 2011. Affected ADs (b) This AD supersedes AD 2010–22–02, Amendment 39–16481. Applicability (c) This AD applies to Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers 7003 and subsequent. Subject (d) Air Transport Association (ATA) of America Code 29 and 32: Hydraulic Power and Landing Gear, respectively. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Seven cases of on-ground hydraulic accumulator screw cap/end cap failure have been experienced on CL–600–2B19 aeroplanes, resulting in the loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. * * * * * * * * A detailed analysis of the calculated line of trajectory of a failed screw cap/end cap for each of the accumulators has been conducted, resulting in the identification of several areas where systems and/or structural components could potentially be damaged. Although all of the failures to date have occurred on the ground, an in-flight failure affecting such components could potentially have an adverse effect on the controllability of the aeroplane. * * * * * Compliance (f) You are responsible for having the actions required by this AD performed within E:\FR\FM\29JNP1.SGM 29JNP1 38067 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules the compliance times specified, unless the actions have already been done. Deactivation of the Hydraulic System No. 3 Accumulator Restatement of Requirements of AD 2010– 22–02, With Revised Service Information (h) Within 250 flight cycles after November 4, 2010, deactivate the hydraulic system No. 3 accumulator, in accordance with Part A of the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R– 29–031, Revision A, dated March 26, 2009. Doing the removal of the hydraulic system No. 3 accumulator in paragraph (o) of this AD is an alternate method of compliance with the requirements of this paragraph. The actions in this paragraph apply to all accumulators in hydraulic system No. 3. Airplane Flight Manual (AFM) Revision (g) Within 30 days after November 4, 2010 (the effective date of AD 2010–22–02), revise the Limitations section, Normal Procedures section, and Abnormal Procedures section of the AFM by incorporating Canadair Regional Jet Temporary Revision (TR) RJ/186–1, dated August 24, 2010, into the applicable section of Canadair Regional Jet AFM, CSP A–012. Thereafter, except as provided by paragraph (t) of this AD, no alternative actions specified in Canadair Regional Jet TR RJ/186–1, dated August 24, 2010, may be approved. Note 1: The actions required by paragraph (g) of this AD may be done by inserting a copy of Canadair Regional Jet TR RJ/186–1, dated August 24, 2010, into the applicable section of the Canadair Regional Jet AFM, CSP A–012. When this TR has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and this TR removed, provided that the relevant information in the general revision is identical to that in Canadair Regional Jet TR RJ/186–1, dated August 24, 2010. Removal of the Hydraulic System No. 2 Accumulator (i) Within 500 flight cycles after November 4, 2010, remove the hydraulic system No. 2 accumulator, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–29–032, Revision A, dated January 26, 2010. The actions in this paragraph apply to all accumulators in hydraulic system No. 2. Initial and Repetitive Ultrasonic Inspection of Hydraulic System No. 1, Inboard Brake, and Outboard Brake Accumulators (j) For hydraulic system No. 1, inboard brake, and outboard brake accumulators having P/N 601R75138–1 (08–60163–001 or 08–60163–002): At the applicable compliance times specified in paragraph (l) of this AD, do the inspections required by paragraphs (j)(1) and (j)(2) of this AD. Repeat the inspections for each accumulator having P/N 601R75138–1 (08–60163–001 or 08– 60163–002) thereafter at intervals not to exceed 500 flight cycles until the replacement specified in this paragraph is done or the replacement specified in paragraph (p) of this AD is done. If any crack is found, before further flight, replace the accumulator with a new accumulator having P/N 601R75138–1 (08–60163–001 or 08– 60163–002) and having the letter ‘‘T’’ after the serial number on the identification plate, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in table 1 or table 2 of this AD. (1) Do an ultrasonic inspection for cracks on each accumulator, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin identified in table 1 of this AD. TABLE 1—BOMBARDIER SERVICE INFORMATION FOR ACCUMULATOR INSPECTION Accumulator Document Revision Date Hydraulic System No. 1 ................. Bombardier Alert Service Bulletin A601R–29–029, including Appendix A, dated October 18, 2007. Bombardier Alert Service Bulletin A601R–32–103, including Appendix A, Revision A, dated October 18, 2007. B ............ May 11, 2010. D ............ May 11, 2010. Inboard and Outboard Brake ......... (2) Do an ultrasonic inspection for cracks on the screw cap, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in table 2 of this AD. TABLE 2—BOMBARDIER SERVICE INFORMATION FOR SCREW CAP INSPECTION Accumulator Document Revision Date Hydraulic System No. 1 ................. Bombardier Service Bulletin 601R–29–033, including Appendix A, dated May 5, 2009. Bombardier Service Bulletin 601R–32–106, including Appendix A ....... A ............ May 11, 2010. A ............ May 11, 2010. srobinson on DSK4SPTVN1PROD with PROPOSALS Inboard and Outboard Brake ......... (k) For hydraulic system No. 1, inboard brake, and outboard brake accumulators having P/N 601R75138–1 (08–60163–001 or 08–60163–002): Do the inspections specified in paragraph (j) of this AD at the applicable time in paragraph (k)(1), (k)(2), and (k)(3) of this AD. (1) For any accumulator not having the letter ‘‘T’’ after the serial number on the identification plate and with more than 4,500 flight cycles on the accumulator as of November 4, 2010: Inspect within 500 flight cycles after November 4, 2010. (2) For any accumulator not having the letter ‘‘T’’ after the serial number on the identification plate and with 4,500 flight cycles or less on the accumulator as of November 4, 2010: Inspect prior to the accumulation of 5,000 flight cycles on the accumulator. VerDate Mar<15>2010 16:52 Jun 28, 2011 Jkt 223001 (3) If it is not possible to determine the flight cycles accumulated for any accumulator not having the letter ‘‘T’’ after the serial number on the identification plate: Inspect within 500 flight cycles after November 4, 2010. Note 2: For any accumulator having P/N 601R75138–1 (08–60163–001 or 08–60163– 002) and the letter ‘‘T’’ after the serial number on the identification plate, or if the accumulator P/N is not listed in paragraph (j) of this AD, the inspection specified in paragraph (j) of this AD is not required. Credit for Actions Accomplished in Accordance With Previous Service Information (l) Deactivating the hydraulic system No. 3 accumulator before November 4, 2010, in accordance with Part A of the PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–29–031, dated December 23, 2008, is acceptable for compliance with the requirements of paragraph (h) of this AD. (m) Removing the hydraulic system No. 2 accumulator in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–29–032, dated November 12, 2009, before November 4, 2010, is acceptable for compliance with the requirements of paragraph (i) of this AD. (n) An ultrasonic inspection for cracks done before November 4, 2010, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin identified in table 3 of this AD, or the Accomplishment Instructions of the applicable service bulletin identified in table 4 of this AD, is acceptable for compliance E:\FR\FM\29JNP1.SGM 29JNP1 38068 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules with the corresponding ultrasonic inspection required by paragraph (j) of this AD. TABLE 3—BOMBARDIER CREDIT SERVICE INFORMATION FOR ACCUMULATOR INSPECTION Document Bombardier Bombardier Bombardier Bombardier Bombardier Bombardier Alert Alert Alert Alert Alert Alert Service Service Service Service Service Service Bulletin Bulletin Bulletin Bulletin Bulletin Bulletin Revision A601R–29–029 A601R–29–029 A601R–32–103 A601R–32–103 A601R–32–103 A601R–32–103 .............................................. .............................................. .............................................. .............................................. .............................................. .............................................. Date Original .................................................. A ............................................................ Original .................................................. A ............................................................ B ............................................................ C ........................................................... October 18, 2007. November 12, 2009. November 21, 2006. March 7, 2007. October 18, 2007. February 26, 2009. TABLE 4—BOMBARDIER CREDIT SERVICE INFORMATION FOR SCREW CAP INSPECTION Document Revision Bombardier Service Bulletin 601R–29–033 ......................................................... Bombardier Service Bulletin 601R–32–106 ......................................................... Original .................................................. Original .................................................. New Requirements of This AD action in this paragraph terminates the requirements of paragraph (h) of this AD. Removal of the Hydraulic System No. 3 Accumulator (o) Within 1,000 flight cycles after the effective date of this AD, remove the hydraulic system No. 3 accumulator, in accordance with Part B of the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–29–031, Revision A, dated March 26, 2009. Doing the Replacement of the Hydraulic System No. 1, Inboard Brake, and Outboard Brake Accumulators (p) Within 4,000 flight cycles or 24 months after the effective date of this AD, whichever occurs first, replace any hydraulic system No. 1, inboard brake, or outboard brake accumulator having P/N 601R75138–1 (08– 60163–001 or 08–60163–002), with a new Date May 5, 2009. May 5, 2009. accumulator having P/N 601R75139–1 (11093–4), in accordance with the Accomplishment Instructions of the applicable service bulletin identified in table 5 of this AD. Doing the action in this paragraph terminates the requirement for the inspections in paragraph (j) of this AD for that accumulator. As of the effective date of this AD, use only Bombardier Service Bulletin 601R–29–035, Revision A; or 601R– 32–107, Revision B; both dated December 8, 2010; as applicable. TABLE 5—BOMBARDIER SERVICE INFORMATION FOR ACCUMULATOR REPLACEMENT Accumulator Hydraulic System No. 1 ........ Hydraulic System No. 1 ........ Inboard and Outboard Brake Inboard and Outboard Brake Document Bombardier Bombardier Bombardier Bombardier Service Service Service Service srobinson on DSK4SPTVN1PROD with PROPOSALS Action for Airplanes on Which Bombardier Service Bulletin 601R–29–035, Dated May 11, 2010 Is Done and Reducer Having P/N MS21916D8–6 Is Installed (q) For airplanes on which Bombardier Service Bulletin 601R–29–035, dated May 11, 2010, is done, and reducer having P/N MS21916D8–6 is installed: Within 1,200 flight cycles or 8 months after the effective date of this AD, replace the reducer of the hydraulic system No. 1 with a new reducer in accordance with Part B of Bombardier Service Bulletin 601R–29–035, Revision A, dated December 8, 2010. Credit for Actions Accomplished in Accordance With Previous Service Information (r) Removing the hydraulic system No. 3 accumulator in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin A601R–29–031, dated December 23, 2008, before November 4, 2010, is acceptable for compliance with the requirements of paragraph (o) of this AD. (s) Replacing any hydraulic system No. 1, inboard brake, or outboard brake accumulator before November 4, 2010, in accordance with the Accomplishment Instructions of VerDate Mar<15>2010 16:52 Jun 28, 2011 Jkt 223001 Bulletin Bulletin Bulletin Bulletin Revision 601R–29–035 601R–29–035 601R–32–107 601R–32–107 ....................... ....................... ....................... ....................... Original ................................ A .......................................... A .......................................... B .......................................... Bombardier Service Bulletin 601R–32–107, dated May 11, 2010, is acceptable for compliance with the corresponding requirements of paragraph (p) of this AD. FAA AD Differences Note 3: This AD differs from the MCAI and/or service information as follows: The actions specified in Canadian Airworthiness Directive CF–2010–24, dated August 3, 2010, apply only to Tactair accumulators. The actions required by paragraphs (h), (i), and (o) of this AD apply to all accumulators in the positions specified in paragraphs (h), (i), and (o) of this AD. Note 4: While Canadian Airworthiness Directive CF–2010–24, dated August 3, 2010, does not require replacement of the reducer of the hydraulic system No. 1 with a new reducer, paragraph (q) of this AD does. Other FAA AD Provisions (t) 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 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Date May 11, 2010. December 8, 2010. June 17, 2010. December 8, 2010. 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, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding 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. Related Information (u) Refer to MCAI Canadian Airworthiness Directive CF–2010–24, dated August 3, 2010; Canadair Regional Jet Temporary Revision RJ/186–1, dated August 24, 2010 to the Canadair Regional Jet Airplane Flight E:\FR\FM\29JNP1.SGM 29JNP1 38069 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules Manual, CSP A–012; and the service bulletins listed in table 6 of this AD; for related information. TABLE 6—RELATED SERVICE INFORMATION Document Bombardier Bombardier Bombardier Bombardier Bombardier Bombardier Bombardier Bombardier Alert Service Bulletin A601R–29–029 .............................................. Alert Service Bulletin A601R–29–031 .............................................. Alert Service Bulletin A601R–32–103 .............................................. Service Bulletin 601R–29–032 ......................................................... Service Bulletin 601R–29–033 ......................................................... Service Bulletin 601R–29–035 ......................................................... Service Bulletin 601R–32–106 ......................................................... Service Bulletin 601R–32–107 ......................................................... Issued in Renton, Washington, on June 16, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–16365 Filed 6–28–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0647; Directorate Identifier 2010–NM–193–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model C4–605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) and A310 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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: SUMMARY: srobinson on DSK4SPTVN1PROD with PROPOSALS Revision Surface defects were visually detected on the rudder of an Airbus A319 and an A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were the result of de-bonding between the skin and honeycomb core. Such reworks were also performed on some rudders fitted on A310 and A300–600 aeroplanes. An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder VerDate Mar<15>2010 16:52 Jun 28, 2011 Jkt 223001 B ............................................................ A ............................................................ D ........................................................... A ............................................................ A ............................................................ A ............................................................ A ............................................................ B ............................................................ leads to degradation of the handling qualities and reduces the controllability of the aeroplane. * * * * * 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 15, 2011. 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 Airbus SAS– EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail account.airworth-eas@airbus.com; Internet https://www.airbus.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 PO 00000 Frm 00011 Fmt 4702 Date Sfmt 4702 May 11, 2010. March 26, 2009. May 11, 2010. January 26, 2010. May 11, 2010. December 8, 2010. May 11, 2010. December 8, 2010. 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. 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–2011–0647; Directorate Identifier 2010–NM–193–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 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 European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0144, dated July 16, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Surface defects were visually detected on the rudder of an Airbus A319 and an A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation E:\FR\FM\29JNP1.SGM 29JNP1

Agencies

[Federal Register Volume 76, Number 125 (Wednesday, June 29, 2011)]
[Proposed Rules]
[Pages 38065-38069]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-16365]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0648; Directorate Identifier 2010-NM-276-AD]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19
(Regional Jet Series 100 & 440) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. 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:

Seven cases of on-ground hydraulic accumulator screw cap/end cap
failure have been experienced on CL-600-2B19 aeroplanes, resulting
in the loss of the associated hydraulic system and high-energy
impact damage to adjacent systems and structure. * * *
* * * * *
A detailed analysis of the calculated line of trajectory of a
failed screw cap/end cap for each of the accumulators has been
conducted, resulting in the identification of several areas where
systems and/or structural components could potentially be damaged.
Although all of the failures to date have occurred on the ground, an
in-flight failure affecting such components could potentially have
an adverse effect on the controllability of the aeroplane.
* * * * *
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 15, 2011.

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 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. 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: Christopher Alfano, Aerospace
Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New
York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite
410, Westbury, New York 11590; telephone (516) 228-7340; 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-2011-0648;
Directorate Identifier 2010-NM-276-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 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

On October 7, 2010, we issued AD 2010-22-02, Amendment 39-16481 (75
FR 64636, October 20, 2010). That AD required actions intended to
address an unsafe condition on Bombardier, Inc. Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes.
Since we issued AD 2010-22-02, we have determined that further
rulemaking is necessary. While AD 2010-22-02 did not require the
removal of the hydraulic system No. 3 accumulator, or replacement of
the hydraulic system No. 1, inboard brake, and outboard brake
accumulators, as specified in Part IV and Part VII of the Canadian
Airworthiness Directive CF-2010-24, dated August 3, 2010, this NPRM
proposes to require those actions. Also, for airplanes on which
Bombardier Service Bulletin 601R-29-035, dated May 11, 2010, is done
and reducer having part number MS21916D8-6 installed, this NPRM
proposes to require replacing the reducer with a new reducer. We have
coordinated with Transport Canada Civil Aviation (TCCA) on this issue.

Relevant Service Information

Bombardier has issued Service Bulletin 601R-29-035, Revision A; and
Service Bulletin 601R-32-107, Revision B; both dated December 8, 2010.
The actions described in this service information as outlined in the
``Discussion'' section above, are intended to correct the unsafe
condition identified in the MCAI.

Change to Existing AD

This proposed AD would retain all requirements of AD 2010-22-02.
Since AD 2010-22-02 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:

[[Page 38066]]

Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2010-22-02 proposed AD
------------------------------------------------------------------------
paragraph (j) paragraph (o)
paragraph (k) paragraph (j)
paragraph (l) paragraph (k)
paragraph (m) paragraph (p)
paragraph (n) paragraph (l)
paragraph (o) paragraph (m)
paragraph (p) paragraph (r)
paragraph (q) paragraph (n)
paragraph (r) paragraph (s)
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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
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 605 products of U.S. registry.
The actions that are required by AD 2010-22-02 and retained in this
proposed AD take about 19 work-hours per product, at an average labor
rate of $85 per work hour. Based on these figures, the estimated cost
of the currently required actions is $1,615 per product.
We estimate that it would take about 14 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $3,054
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these costs. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of the proposed AD
on U.S. operators to be $2,567,620, or $4,244 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 removing Amendment 39-16481 (75 FR
64636, October 20, 2010) and adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2011-0648; Directorate Identifier
2010-NM-276-AD.

Comments Due Date

(a) We must receive comments by August 15, 2011.

Affected ADs

(b) This AD supersedes AD 2010-22-02, Amendment 39-16481.

Applicability

(c) This AD applies to Bombardier, Inc. Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes, certificated in any
category, serial numbers 7003 and subsequent.

Subject

(d) Air Transport Association (ATA) of America Code 29 and 32:
Hydraulic Power and Landing Gear, respectively.

Reason

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

Compliance

(f) You are responsible for having the actions required by this
AD performed within

[[Page 38067]]

the compliance times specified, unless the actions have already been
done.

Restatement of Requirements of AD 2010-22-02, With Revised Service
Information

Airplane Flight Manual (AFM) Revision

(g) Within 30 days after November 4, 2010 (the effective date of
AD 2010-22-02), revise the Limitations section, Normal Procedures
section, and Abnormal Procedures section of the AFM by incorporating
Canadair Regional Jet Temporary Revision (TR) RJ/186-1, dated August
24, 2010, into the applicable section of Canadair Regional Jet AFM,
CSP A-012. Thereafter, except as provided by paragraph (t) of this
AD, no alternative actions specified in Canadair Regional Jet TR RJ/
186-1, dated August 24, 2010, may be approved.

Note 1: The actions required by paragraph (g) of this AD may be
done by inserting a copy of Canadair Regional Jet TR RJ/186-1, dated
August 24, 2010, into the applicable section of the Canadair
Regional Jet AFM, CSP A-012. When this TR has been included in the
general revisions of the AFM, the general revisions may be inserted
into the AFM, and this TR removed, provided that the relevant
information in the general revision is identical to that in Canadair
Regional Jet TR RJ/186-1, dated August 24, 2010.

Deactivation of the Hydraulic System No. 3 Accumulator

(h) Within 250 flight cycles after November 4, 2010, deactivate
the hydraulic system No. 3 accumulator, in accordance with Part A of
the Accomplishment Instructions of Bombardier Alert Service Bulletin
A601R-29-031, Revision A, dated March 26, 2009. Doing the removal of
the hydraulic system No. 3 accumulator in paragraph (o) of this AD
is an alternate method of compliance with the requirements of this
paragraph. The actions in this paragraph apply to all accumulators
in hydraulic system No. 3.

Removal of the Hydraulic System No. 2 Accumulator

(i) Within 500 flight cycles after November 4, 2010, remove the
hydraulic system No. 2 accumulator, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 601R-29-
032, Revision A, dated January 26, 2010. The actions in this
paragraph apply to all accumulators in hydraulic system No. 2.

Initial and Repetitive Ultrasonic Inspection of Hydraulic System No. 1,
Inboard Brake, and Outboard Brake Accumulators

(j) For hydraulic system No. 1, inboard brake, and outboard
brake accumulators having P/N 601R75138-1 (08-60163-001 or 08-60163-
002): At the applicable compliance times specified in paragraph (l)
of this AD, do the inspections required by paragraphs (j)(1) and
(j)(2) of this AD. Repeat the inspections for each accumulator
having P/N 601R75138-1 (08-60163-001 or 08-60163-002) thereafter at
intervals not to exceed 500 flight cycles until the replacement
specified in this paragraph is done or the replacement specified in
paragraph (p) of this AD is done. If any crack is found, before
further flight, replace the accumulator with a new accumulator
having P/N 601R75138-1 (08-60163-001 or 08-60163-002) and having the
letter ``T'' after the serial number on the identification plate, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in table 1 or table 2 of this AD.
(1) Do an ultrasonic inspection for cracks on each accumulator,
in accordance with Part B of the Accomplishment Instructions of the
applicable service bulletin identified in table 1 of this AD.

Table 1--Bombardier Service Information for Accumulator Inspection
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Accumulator Document Revision Date
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Hydraulic System No. 1........... Bombardier Alert Service B................ May 11, 2010.
Bulletin A601R-29-029,
including Appendix A,
dated October 18, 2007.
Inboard and Outboard Brake....... Bombardier Alert Service D................ May 11, 2010.
Bulletin A601R-32-103,
including Appendix A,
Revision A, dated
October 18, 2007.
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(2) Do an ultrasonic inspection for cracks on the screw cap, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in table 2 of this AD.

Table 2--Bombardier Service Information for Screw Cap Inspection
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Accumulator Document Revision Date
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Hydraulic System No. 1........... Bombardier Service A................ May 11, 2010.
Bulletin 601R-29-033,
including Appendix A,
dated May 5, 2009.
Inboard and Outboard Brake....... Bombardier Service A................ May 11, 2010.
Bulletin 601R-32-106,
including Appendix A.
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(k) For hydraulic system No. 1, inboard brake, and outboard
brake accumulators having P/N 601R75138-1 (08-60163-001 or 08-60163-
002): Do the inspections specified in paragraph (j) of this AD at
the applicable time in paragraph (k)(1), (k)(2), and (k)(3) of this
AD.
(1) For any accumulator not having the letter ``T'' after the
serial number on the identification plate and with more than 4,500
flight cycles on the accumulator as of November 4, 2010: Inspect
within 500 flight cycles after November 4, 2010.
(2) For any accumulator not having the letter ``T'' after the
serial number on the identification plate and with 4,500 flight
cycles or less on the accumulator as of November 4, 2010: Inspect
prior to the accumulation of 5,000 flight cycles on the accumulator.
(3) If it is not possible to determine the flight cycles
accumulated for any accumulator not having the letter ``T'' after
the serial number on the identification plate: Inspect within 500
flight cycles after November 4, 2010.

Note 2: For any accumulator having P/N 601R75138-1 (08-60163-
001 or 08-60163-002) and the letter ``T'' after the serial number on
the identification plate, or if the accumulator P/N is not listed in
paragraph (j) of this AD, the inspection specified in paragraph (j)
of this AD is not required.

Credit for Actions Accomplished in Accordance With Previous Service
Information

(l) Deactivating the hydraulic system No. 3 accumulator before
November 4, 2010, in accordance with Part A of the Accomplishment
Instructions of Bombardier Alert Service Bulletin A601R-29-031,
dated December 23, 2008, is acceptable for compliance with the
requirements of paragraph (h) of this AD.
(m) Removing the hydraulic system No. 2 accumulator in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 601R-29-032, dated November 12, 2009, before
November 4, 2010, is acceptable for compliance with the requirements
of paragraph (i) of this AD.
(n) An ultrasonic inspection for cracks done before November 4,
2010, in accordance with Part B of the Accomplishment Instructions
of the applicable service bulletin identified in table 3 of this AD,
or the Accomplishment Instructions of the applicable service
bulletin identified in table 4 of this AD, is acceptable for
compliance

[[Page 38068]]

with the corresponding ultrasonic inspection required by paragraph
(j) of this AD.

Table 3--Bombardier Credit Service Information for Accumulator Inspection
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Document Revision Date
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Bombardier Alert Service Bulletin A601R- Original.................... October 18, 2007.
29-029.
Bombardier Alert Service Bulletin A601R- A........................... November 12, 2009.
29-029.
Bombardier Alert Service Bulletin A601R- Original.................... November 21, 2006.
32-103.
Bombardier Alert Service Bulletin A601R- A........................... March 7, 2007.
32-103.
Bombardier Alert Service Bulletin A601R- B........................... October 18, 2007.
32-103.
Bombardier Alert Service Bulletin A601R- C........................... February 26, 2009.
32-103.
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Table 4--Bombardier Credit Service Information for Screw Cap Inspection
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Document Revision Date
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Bombardier Service Bulletin 601R-29-033.. Original.................... May 5, 2009.
Bombardier Service Bulletin 601R-32-106.. Original.................... May 5, 2009.
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New Requirements of This AD

Removal of the Hydraulic System No. 3 Accumulator

(o) Within 1,000 flight cycles after the effective date of this
AD, remove the hydraulic system No. 3 accumulator, in accordance
with Part B of the Accomplishment Instructions of Bombardier Alert
Service Bulletin A601R-29-031, Revision A, dated March 26, 2009.
Doing the action in this paragraph terminates the requirements of
paragraph (h) of this AD.

Replacement of the Hydraulic System No. 1, Inboard Brake, and Outboard
Brake Accumulators

(p) Within 4,000 flight cycles or 24 months after the effective
date of this AD, whichever occurs first, replace any hydraulic
system No. 1, inboard brake, or outboard brake accumulator having P/
N 601R75138-1 (08-60163-001 or 08-60163-002), with a new accumulator
having P/N 601R75139-1 (11093-4), in accordance with the
Accomplishment Instructions of the applicable service bulletin
identified in table 5 of this AD. Doing the action in this paragraph
terminates the requirement for the inspections in paragraph (j) of
this AD for that accumulator. As of the effective date of this AD,
use only Bombardier Service Bulletin 601R-29-035, Revision A; or
601R-32-107, Revision B; both dated December 8, 2010; as applicable.

Table 5--Bombardier Service Information for Accumulator Replacement
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Accumulator Document Revision Date
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Hydraulic System No. 1........... Bombardier Service Original........... May 11, 2010.
Bulletin 601R-29-035.
Hydraulic System No. 1........... Bombardier Service A.................. December 8, 2010.
Bulletin 601R-29-035.
Inboard and Outboard Brake....... Bombardier Service A.................. June 17, 2010.
Bulletin 601R-32-107.
Inboard and Outboard Brake....... Bombardier Service B.................. December 8, 2010.
Bulletin 601R-32-107.
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Action for Airplanes on Which Bombardier Service Bulletin 601R-29-035,
Dated May 11, 2010 Is Done and Reducer Having P/N MS21916D8-6 Is
Installed

(q) For airplanes on which Bombardier Service Bulletin 601R-29-
035, dated May 11, 2010, is done, and reducer having P/N MS21916D8-6
is installed: Within 1,200 flight cycles or 8 months after the
effective date of this AD, replace the reducer of the hydraulic
system No. 1 with a new reducer in accordance with Part B of
Bombardier Service Bulletin 601R-29-035, Revision A, dated December
8, 2010.

Credit for Actions Accomplished in Accordance With Previous Service
Information

(r) Removing the hydraulic system No. 3 accumulator in
accordance with Part B of the Accomplishment Instructions of
Bombardier Service Bulletin A601R-29-031, dated December 23, 2008,
before November 4, 2010, is acceptable for compliance with the
requirements of paragraph (o) of this AD.
(s) Replacing any hydraulic system No. 1, inboard brake, or
outboard brake accumulator before November 4, 2010, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
601R-32-107, dated May 11, 2010, is acceptable for compliance with
the corresponding requirements of paragraph (p) of this AD.

FAA AD Differences

Note 3: This AD differs from the MCAI and/or service
information as follows: The actions specified in Canadian
Airworthiness Directive CF-2010-24, dated August 3, 2010, apply only
to Tactair accumulators. The actions required by paragraphs (h),
(i), and (o) of this AD apply to all accumulators in the positions
specified in paragraphs (h), (i), and (o) of this AD.

Note 4: While Canadian Airworthiness Directive CF-2010-24,
dated August 3, 2010, does not require replacement of the reducer of
the hydraulic system No. 1 with a new reducer, paragraph (q) of this
AD does.

Other FAA AD Provisions

(t) 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, notify
your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding 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.

Related Information

(u) Refer to MCAI Canadian Airworthiness Directive CF-2010-24,
dated August 3, 2010; Canadair Regional Jet Temporary Revision RJ/
186-1, dated August 24, 2010 to the Canadair Regional Jet Airplane
Flight

[[Page 38069]]

Manual, CSP A-012; and the service bulletins listed in table 6 of
this AD; for related information.

Table 6--Related Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Bombardier Alert Service Bulletin A601R- B........................... May 11, 2010.
29-029.
Bombardier Alert Service Bulletin A601R- A........................... March 26, 2009.
29-031.
Bombardier Alert Service Bulletin A601R- D........................... May 11, 2010.
32-103.
Bombardier Service Bulletin 601R-29-032.. A........................... January 26, 2010.
Bombardier Service Bulletin 601R-29-033.. A........................... May 11, 2010.
Bombardier Service Bulletin 601R-29-035.. A........................... December 8, 2010.
Bombardier Service Bulletin 601R-32-106.. A........................... May 11, 2010.
Bombardier Service Bulletin 601R-32-107.. B........................... December 8, 2010.
----------------------------------------------------------------------------------------------------------------

Issued in Renton, Washington, on June 16, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-16365 Filed 6-28-11; 8:45 am]
BILLING CODE 4910-13-P

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