Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes, 55785-55788 [2011-22277]

Download as PDF Federal Register / Vol. 76, No. 175 / Friday, September 9, 2011 / Rules and Regulations and –200 IGW airplanes: Within 3,000 flight hours after the effective date of this AD, replace the shear pins having part number (P/ N) 190–15178–003 and P/N 190–15181–003 in the rear outboard and inboard shear pin assembly in the right- and left-hand pylons, with new shear pins having P/N 190–15178– 005 and P/N 190–15181–005, respectively, in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 190–54–0010, dated May 19, 2010. (h) For Model ERJ 190–100 ECJ airplanes: Within 3,000 flight hours or within 12 months after the effective date of this AD, whichever occurs first, replace the shear pins having P/N 190–15178–003 and P/N 190– 15181–003, in the rear outboard and inboard shear pin assembly in the right- and left-hand pylons, with new shear pins having P/N 190– 15178–005 and P/N 190–15181–005, respectively, in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 190LIN–54–0001, dated June 21, 2010. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: The MCAI allows credit for previous installation of internal shear pins in accordance with EMBRAER 190 Aircraft Maintenance Manual Task 54–50–00–400, Revision 19, dated July 15, 2010. This AD does not allow credit for this task; however, under the provisions of paragraph (i) of this AD, we will consider requests for an alternative method of compliance. mstockstill on DSK4VPTVN1PROD with RULES Other FAA AD Provisions (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Cindy Ashforth, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2768; fax (425) 227–1149. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. VerDate Mar<15>2010 16:30 Sep 08, 2011 Jkt 223001 Related Information ˆ (j) Refer to MCAI Agencia Nacional de Aviacao Civil (ANAC) Airworthiness ¸˜ Directive 2010–08–02, dated September 20, 2010; and EMBRAER Service Bulletins 190– 54–0010, dated May 19, 2010, and 190LIN– 54–0001, dated June 21, 2010; for related information. Material Incorporated by Reference (k) You must use EMBRAER Service Bulletin 190–54–0010, dated May 19, 2010; or EMBRAER Service Bulletin 190LIN–54– 0001, dated June 21, 2010; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro ˜ Faria Lima, 2170—Putim—12227–901 Sao Jose dos Campos—SP—BRASIL; telephone +55 12 3927–5852 or +55 12 3309–0732; fax +55 12 3927–7546; e-mail distrib@embraer.com.br; Internet http:// www.flyembraer.com. (3) You may review copies of the 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on August 19, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–22028 Filed 9–8–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0471; Directorate Identifier 2010–NM–219–AD; Amendment 39–16800; AD 2011–18–18] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Model DHC–8–400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 55785 We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: Several operators have reported pitch oscillations and/or elevator asymmetry caution lights illumination when flying with the autopilot engaged. Investigations revealed that loose rivets in the torque tube assemblies caused relative motion between the crank arms and torque tubes. Loose rivets could result in excessive wear and subsequent significant backlash in the driving crank arms. This condition, if left uncorrected, will progressively get worse and degrade the controllability of the aeroplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 14, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 14, 2011. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Stephen Kowalski, 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– 7327; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on May 12, 2011 (76 FR 27617). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Several operators have reported pitch oscillations and/or elevator asymmetry caution lights illumination when flying with the autopilot engaged. Investigations revealed that loose rivets in the torque tube assemblies caused relative motion between the crank arms and torque tubes. Loose rivets could result in excessive wear and subsequent significant backlash in the driving crank arms. This condition, if left E:\FR\FM\09SER1.SGM 09SER1 55786 Federal Register / Vol. 76, No. 175 / Friday, September 9, 2011 / Rules and Regulations uncorrected, will progressively get worse and degrade the controllability of the aeroplane. Required actions include doing an inspection for the part number of the left and right elevator torque tube assemblies and, if necessary, replacing the elevator torque tube assembly or replacing the elevator torque tube rivets, and re-identifying the assemblies. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (76 FR 27617, May 12, 2011) or on the determination of the cost to the public. Revised Service Information Bombardier Service Bulletin 84–27– 50, Revision ‘D,’ dated September 22, 2010, has been issued for clarification, but adds no new actions. We have updated the references in paragraphs (g), (h), (i), and (m) of this AD to include Bombardier Service Bulletin 84–27–50, Revision ‘D,’ dated September 22, 2010. We have also updated Table 1 of this AD to allow credit for Bombardier Service Bulletin 84–27–50, Revision ‘C,’ dated July 26, 2010. Conclusion We reviewed the relevant data, and determined that air safety and the public interest require adopting the AD with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 66 products of U.S. registry. We also estimate the following costs to comply with this AD. ESTIMATED COSTS Cost per product Action Labor cost Parts cost Inspection .................. 2 × $85 per hour = $170 .......................... None ......................................................... We estimate the following costs to do any necessary replacements that would be required based on the results of the required inspection. We have no way of $170 Cost on U.S. operators $11,220 determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replace left torque tube ............................................... Replace right torque tube ............................................. 15 work-hours × $85 per hour = $1,275 ...................... 15 work-hours × $85 per hour = $1,275 ...................... mstockstill on DSK4VPTVN1PROD with RULES 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. VerDate Mar<15>2010 16:30 Sep 08, 2011 Jkt 223001 Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ’’significant regulatory action’’ under Executive Order 12866; 2. Is not a ’’significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Parts cost $4,354 5,913 Cost per product $5,629 7,188 Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: E:\FR\FM\09SER1.SGM 09SER1 55787 Federal Register / Vol. 76, No. 175 / Friday, September 9, 2011 / Rules and Regulations PART 39—AIRWORTHINESS DIRECTIVES driving crank arms. This condition, if left uncorrected, will progressively get worse and degrade the controllability of the aeroplane. 1. The authority citation for part 39 continues to read as follows: 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. ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2011–18–18 Bombardier, Inc.: Amendment 39–16800. Docket No. FAA–2011–0471; Directorate Identifier 2010–NM–219–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 14, 2011. Affected ADs (b) None. Applicability (c) This AD applies to Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes; certificated in any category; serial numbers 4001 through 4305 inclusive. Subject (d) Air Transport Association (ATA) of America Code 27: Flight controls. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Several operators have reported pitch oscillations and/or elevator asymmetry caution lights illumination when flying with the autopilot engaged. Investigations revealed that loose rivets in the torque tube assemblies caused relative motion between the crank arms and torque tubes. Loose rivets could result in excessive wear and subsequent significant backlash in the Inspection for Part Number (g) At the applicable times identified in paragraphs (g)(1) and (g)(2) of this AD, do an inspection to determine the part numbers of the left and right elevator torque tubes, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–50, Revision ‘D,’ dated September 22, 2010. A review of airplane maintenance records is acceptable in lieu of this inspection if the part numbers of the left and right elevator torque tubes can be conclusively determined from that review. (1) For airplanes that have accumulated 8,000 or more total flight hours as of the effective date of this AD: Within 2,000 flight hours after the effective date of this AD. (2) For airplanes that have accumulated less than 8,000 total flight hours as of the effective date of this AD: Within 6,000 flight hours after the effective date of this AD, but before the accumulation of 10,000 total flight hours. Corrective Actions (h) If, as a result of the inspection required by paragraph (g) of this AD, any left elevator torque tube has part number (P/N) 82760709– 009, at the applicable time in paragraph (g)(1) or (g)(2) of this AD, do the actions in paragraph (h)(1) or (h)(2) of this AD. (1) Replace the elevator torque tube with a new elevator torque tube having P/N 82760709–011, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–50, Revision ‘D,’ dated September 22, 2010. (2) Replace the rivets in each elevator torque tube assembly with Hi Lite pins having P/N B0206001AG8 and collars having P/N HST1070CY, and re-identify the elevator torque tube assembly having P/N 82760709– 009, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–50, Revision ‘D,’ dated September 22, 2010. (i) If, as a result of the inspection required by paragraph (g) of this AD, any right elevator torque tube has P/N 82760757–009, at the applicable time in paragraph (g)(1) or (g)(2) of this AD, do the actions in paragraph (i)(1) or (i)(2) of this AD. (1) Replace the elevator torque tube with a new elevator torque tube having P/N 82760757–011, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–50, Revision ‘D,’ dated September 22, 2010. (2) Replace the rivets in each elevator torque tube assembly with Hi Lite pins having P/N B0206001AG8 and collars having P/N HST1070CY, and re-identify the elevator torque tube assembly having P/N 82760757– 009, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–50, Revision ‘D,’ dated September 22, 2010. Credit for Actions Accomplished in Accordance With Previous Service Information (j) Actions done before the effective date of this AD, in accordance with the service bulletins listed in table 1 of this AD, are considered acceptable for compliance with the corresponding action specified in this AD. TABLE 1—CREDIT SERVICE BULLETINS Service Bulletin Bombardier Bombardier Bombardier Bombardier Service Service Service Service Bulletin Bulletin Bulletin Bulletin 84–27–50 84–27–50 84–27–50 84–27–50 .............................................................................. .............................................................................. .............................................................................. .............................................................................. Parts Installation (k) As of the effective date of this AD, no person may install on any airplane an elevator torque tube assembly having P/N 82760709–009 or 82760757–009. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. mstockstill on DSK4VPTVN1PROD with RULES Other FAA AD Provisions (l) 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. In accordance with 14 CFR VerDate Mar<15>2010 16:30 Sep 08, 2011 Revision Jkt 223001 Original ............................................. A ....................................................... B ....................................................... C ...................................................... 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it 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 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Date March 3, 2010. April 28, 2010. May 19, 2010. July 26, 2010. (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. Related Information (m) Refer to MCAI Canadian Airworthiness Directive CF–2010–27, dated August 20, 2010; and Bombardier Service Bulletin 84– 27–50, Revision ‘D,’ dated September 22, 2010; for related information. Material Incorporated by Reference (n) You must use Bombardier Service Bulletin 84–27–50, Revision ‘D,’ dated September 22, 2010, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. E:\FR\FM\09SER1.SGM 09SER1 55788 Federal Register / Vol. 76, No. 175 / Friday, September 9, 2011 / Rules and Regulations (2) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; e-mail thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. (3) You may review copies of the 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ibr_ locations.html. Issued in Renton, Washington, on August 23, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–22277 Filed 9–8–11; 8:45 am] BILLING CODE 4910–13–P SECURITIES AND EXCHANGE COMMISSION 17 CFR Parts 239, 249, 269 and 274 [Release Nos. 33–9256; 34–65244; 39–2478; IC–29780] Amendments To Include New Applicant Types on Form ID Securities and Exchange Commission. ACTION: Final rule amendments. AGENCY: The Securities and Exchange Commission (‘‘Commission’’) is amending Form ID to include additional applicant types in order to facilitate processing of the form. Form ID is the application for access codes to file on the Commission’s Electronic Data Gathering, Analysis, and Retrieval (‘‘EDGAR’’) system. The purpose of introducing these new applicant types is to improve the Commission’s internal procedures for processing filings, including by routing Form ID filings to the appropriate internal office or division. SUMMARY: DATES: Effective Date: September 9, mstockstill on DSK4VPTVN1PROD with RULES 2011. FOR FURTHER INFORMATION CONTACT: Catherine Moore, Senior Special Counsel or Andrew Bernstein, AttorneyAdviser, Office of Clearance and Settlement, Division of Trading and Markets, Securities and Exchange Commission, 100 F Street, NE., VerDate Mar<15>2010 16:30 Sep 08, 2011 Jkt 223001 Washington, DC 20549, at (202) 551– 5710. SUPPLEMENTARY INFORMATION: I. Background Form ID is filed by registrants, third party filers, or any of their respective agents, to whom the Commission previously has not assigned a Central Index Key (‘‘CIK’’) code, to request access codes in order to file in electronic format through EDGAR. EDGAR access codes include the CIK code, the CIK Confirmation Code (‘‘CCC’’), Password (‘‘PW’’), and Password Modification Authorization Code (‘‘PMAC’’).1 Currently, Form ID does not differentiate applicants by specific type and simply lists as possible applicant types ‘‘filer,’’ ‘‘filing agent,’’ ‘‘training agent,’’ ‘‘transfer agent,’’ and ‘‘individual.’’ However, the number and type of persons that use EDGAR for submitting filings has increased since Form ID was first adopted by the Commission and may increase further following the adoption of various rules under the Dodd-Frank Wall Street Reform and Consumer Protection Act (‘‘Dodd-Frank Act’’).2 Accordingly, the Commission is amending Form ID to list specific persons as applicant types on the form in order to allow the form to be assigned for processing within the Commission based on the type of applicant. The new applicant types include persons that currently file on EDGAR but who are not separately listed on Form ID, persons that currently file forms with the Commission in paper but who may be required to file on EDGAR in the future, and persons who will be required to meet certain new filing obligations under the Securities Exchange Act of 1934 (‘‘Exchange Act’’), including provisions added by the Dodd-Frank Act. The amendments to Form ID also include corresponding definitions for each new applicant type.3 New applicants should select only one entity type when completing and submitting Form ID.4 If an applicant 1 See EDGAR Filing Manual (Volume I) General Information (Section 2.4, Accessing EDGAR). 2 The Dodd-Frank Wall Street Reform and Consumer Protection Act, Public Law 111–203, 124 Stat. 1376 (2010). 3 The definitions included in Form ID are to facilitate the correct selection of ‘‘applicant type’’ by a particular filer and are not intended to amend or otherwise change any provision of the federal securities laws or the regulations promulgated thereunder. 4 For purposes of Form ID, the term ‘‘person’’ includes either an individual or entity. If the applicant is also an ‘‘individual’’ as defined in the current Form ID, then the applicant must apply as both an ‘‘individual’’ as well as another appropriate applicant type that properly characterizes it. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 qualifies as more than one of the applicant types listed on the form, it should select the applicant type related to the first filing it plans to submit on EDGAR. The access codes the applicant retrieves after Form ID is approved may be used to submit filings on EDGAR for any entity type (other than transfer agent) provided that such filing complies with all other applicable rules and regulations.5 Persons that have previously filed Form ID applications with the Commission are not required to re-file Form ID as a result of these amendments. As more fully described below, the following applicant types and applicable definitions are being added to Form ID: Investment Company, Business Development Company or Insurance Company Separate Account, Institutional Investment Manager (Form 13F Filer), Non-Investment Company Applicant under the Investment Company Act of 1940, Large Trader, Clearing Agency, Municipal Advisor, Municipal Securities Dealer, Nationally Recognized Statistical Rating Organization, Security-Based Swap Data Repository, Security-Based Swap Dealer and Major Security-Based Swap Participant, and Security-Based Swap Execution Facility. Investment Company, Business Development Company or Insurance Company Separate Account, Institutional Investment Manager (Form 13F Filer), and Non-Investment Company Applicant Under the Investment Company Act of 1940 Currently, a person that may fall within the applicant type of ‘‘Investment Company, Business Development Company or Insurance Company Separate Account,’’ ‘‘Institutional Investment Manager (Form 13F Filer),’’ or ‘‘Non-Investment Company Applicant under the Investment Company Act of 1940’’ may make submissions on EDGAR in electronic format without referencing the appropriate applicant type on Form ID. As such, the Commission is adding these specific applicant types to Form ID in order to facilitate processing of the form as filed by such persons. The applicant type of ‘‘Investment Company, Business Development Company or Insurance Company Separate Account’’ being added to Form ID includes persons that meet the definition of ‘‘investment company’’ in Section 3 of 5 Persons that are transfer agents must apply for a separate set of access codes even if they already submit filings on EDGAR in another capacity. See Securities Exchange Act Release No. 54865 (December 4, 2006), 71 FR 74698 (December 12, 2006) (File No. S7–14–06). E:\FR\FM\09SER1.SGM 09SER1

Agencies

[Federal Register Volume 76, Number 175 (Friday, September 9, 2011)]
[Rules and Regulations]
[Pages 55785-55788]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-22277]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0471; Directorate Identifier 2010-NM-219-AD; 
Amendment 39-16800; AD 2011-18-18]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series 
Airplanes

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

ACTION: Final rule.

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

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

    Several operators have reported pitch oscillations and/or 
elevator asymmetry caution lights illumination when flying with the 
autopilot engaged. Investigations revealed that loose rivets in the 
torque tube assemblies caused relative motion between the crank arms 
and torque tubes.
    Loose rivets could result in excessive wear and subsequent 
significant backlash in the driving crank arms. This condition, if 
left uncorrected, will progressively get worse and degrade the 
controllability of the aeroplane.

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective October 14, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 14, 
2011.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Stephen Kowalski, 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) 228-7327; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on May 12, 2011 (76 FR 
27617). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Several operators have reported pitch oscillations and/or 
elevator asymmetry caution lights illumination when flying with the 
autopilot engaged. Investigations revealed that loose rivets in the 
torque tube assemblies caused relative motion between the crank arms 
and torque tubes.
    Loose rivets could result in excessive wear and subsequent 
significant backlash in the driving crank arms. This condition, if 
left

[[Page 55786]]

uncorrected, will progressively get worse and degrade the 
controllability of the aeroplane.

Required actions include doing an inspection for the part number of the 
left and right elevator torque tube assemblies and, if necessary, 
replacing the elevator torque tube assembly or replacing the elevator 
torque tube rivets, and re-identifying the assemblies. You may obtain 
further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (76 FR 27617, May 12, 
2011) or on the determination of the cost to the public.

Revised Service Information

    Bombardier Service Bulletin 84-27-50, Revision `D,' dated September 
22, 2010, has been issued for clarification, but adds no new actions. 
We have updated the references in paragraphs (g), (h), (i), and (m) of 
this AD to include Bombardier Service Bulletin 84-27-50, Revision `D,' 
dated September 22, 2010. We have also updated Table 1 of this AD to 
allow credit for Bombardier Service Bulletin 84-27-50, Revision `C,' 
dated July 26, 2010.

Conclusion

    We reviewed the relevant data, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 66 products of U.S. registry. 
We also estimate the following costs to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
             Action                     Labor cost              Parts cost            product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  2 x $85 per hour = $170  None..................            $170         $11,220
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the required inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace left torque tube......................  15 work-hours x $85 per hour =            $4,354          $5,629
                                                 $1,275.
Replace right torque tube.....................  15 work-hours x $85 per hour =             5,913           7,188
                                                 $1,275.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ''significant regulatory action'' under Executive Order 
12866;
    2. Is not a ''significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

[[Page 55787]]

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2011-18-18 Bombardier, Inc.: Amendment 39-16800. Docket No. FAA-
2011-0471; Directorate Identifier 2010-NM-219-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
14, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401, 
and -402 airplanes; certificated in any category; serial numbers 
4001 through 4305 inclusive.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Several operators have reported pitch oscillations and/or 
elevator asymmetry caution lights illumination when flying with the 
autopilot engaged. Investigations revealed that loose rivets in the 
torque tube assemblies caused relative motion between the crank arms 
and torque tubes.
    Loose rivets could result in excessive wear and subsequent 
significant backlash in the driving crank arms. This condition, if 
left uncorrected, will progressively get worse and degrade the 
controllability of the aeroplane.

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.

Inspection for Part Number

    (g) At the applicable times identified in paragraphs (g)(1) and 
(g)(2) of this AD, do an inspection to determine the part numbers of 
the left and right elevator torque tubes, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-50, 
Revision `D,' dated September 22, 2010. A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
part numbers of the left and right elevator torque tubes can be 
conclusively determined from that review.
    (1) For airplanes that have accumulated 8,000 or more total 
flight hours as of the effective date of this AD: Within 2,000 
flight hours after the effective date of this AD.
    (2) For airplanes that have accumulated less than 8,000 total 
flight hours as of the effective date of this AD: Within 6,000 
flight hours after the effective date of this AD, but before the 
accumulation of 10,000 total flight hours.

Corrective Actions

    (h) If, as a result of the inspection required by paragraph (g) 
of this AD, any left elevator torque tube has part number (P/N) 
82760709-009, at the applicable time in paragraph (g)(1) or (g)(2) 
of this AD, do the actions in paragraph (h)(1) or (h)(2) of this AD.
    (1) Replace the elevator torque tube with a new elevator torque 
tube having P/N 82760709-011, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-27-50, Revision `D,' 
dated September 22, 2010.
    (2) Replace the rivets in each elevator torque tube assembly 
with Hi Lite pins having P/N B0206001AG8 and collars having P/N 
HST1070CY, and re-identify the elevator torque tube assembly having 
P/N 82760709-009, in accordance with the Accomplishment Instructions 
of Bombardier Service Bulletin 84-27-50, Revision `D,' dated 
September 22, 2010.
    (i) If, as a result of the inspection required by paragraph (g) 
of this AD, any right elevator torque tube has P/N 82760757-009, at 
the applicable time in paragraph (g)(1) or (g)(2) of this AD, do the 
actions in paragraph (i)(1) or (i)(2) of this AD.
    (1) Replace the elevator torque tube with a new elevator torque 
tube having P/N 82760757-011, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-27-50, Revision `D,' 
dated September 22, 2010.
    (2) Replace the rivets in each elevator torque tube assembly 
with Hi Lite pins having P/N B0206001AG8 and collars having P/N 
HST1070CY, and re-identify the elevator torque tube assembly having 
P/N 82760757-009, in accordance with the Accomplishment Instructions 
of Bombardier Service Bulletin 84-27-50, Revision `D,' dated 
September 22, 2010.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (j) Actions done before the effective date of this AD, in 
accordance with the service bulletins listed in table 1 of this AD, 
are considered acceptable for compliance with the corresponding 
action specified in this AD.

                    Table 1--Credit Service Bulletins
------------------------------------------------------------------------
       Service Bulletin              Revision               Date
------------------------------------------------------------------------
Bombardier Service Bulletin 84- Original.........  March 3, 2010.
 27-50.
Bombardier Service Bulletin 84- A................  April 28, 2010.
 27-50.
Bombardier Service Bulletin 84- B................  May 19, 2010.
 27-50.
Bombardier Service Bulletin 84- C................  July 26, 2010.
 27-50.
------------------------------------------------------------------------

Parts Installation

    (k) As of the effective date of this AD, no person may install 
on any airplane an elevator torque tube assembly having P/N 
82760709-009 or 82760757-009.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (l) 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. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the ACO, send it 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

    (m) Refer to MCAI Canadian Airworthiness Directive CF-2010-27, 
dated August 20, 2010; and Bombardier Service Bulletin 84-27-50, 
Revision `D,' dated September 22, 2010; for related information.

Material Incorporated by Reference

    (n) You must use Bombardier Service Bulletin 84-27-50, Revision 
`D,' dated September 22, 2010, to do the actions required by this 
AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.

[[Page 55788]]

    (2) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; e-mail thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.com.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on August 23, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-22277 Filed 9-8-11; 8:45 am]
BILLING CODE 4910-13-P