Airworthiness Directives; Bombardier, Inc. Airplanes, 64088-64092 [2014-25018]

Download as PDF 64088 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations affected fittings and striker plates, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–52–037, Revision B, dated September 16, 2013. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2014–21–07 Bombardier, Inc.: Amendment 39–18000. Docket No. FAA–2014–0287; Directorate Identifier 2013–NM–247–AD. (a) Effective Date This AD becomes effective December 2, 2014. (b) Affected ADs None. (c) Applicability This AD applies to the Bombardier, Inc. airplanes specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, serial numbers 10303 through 10333 inclusive. (2) Model CL–600–2D24 (Regional Jet Series 900) airplanes, serial numbers 15257 through 15284 inclusive. (3) Model CL–600–2E25 (Regional Jet Series 1000) airplanes, serial numbers 19011 through 19024 inclusive. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report that certain parts of the aft baggage door did not conform to the design specifications and were of degraded strength. We are issuing this AD to prevent cracking and deformations of stop fittings and striker plates, which could result in the opening of the aft baggage bay door and rapid decompression or reduced controllability of the airplane. asabaliauskas on DSK5VPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections of the Aft Baggage Bay Door Stop Fittings and Striker Plates Within 600 flight hours or 6 months after the effective date of this AD, whichever occurs first: Do a detailed visual inspection for cracking and deformations of the stop fittings and striker plates of the aft baggage bay door, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–52–037, Revision B, dated September 16, 2013. Repeat the inspection thereafter at intervals not to exceed 2,000 flight hours or 12 months, whichever occurs first, until the terminating action specified in paragraph (h) of this AD has been accomplished. If a crack or deformation is found on a stop fitting or striker plate, before further flight, replace the VerDate Sep<11>2014 16:44 Oct 27, 2014 Jkt 235001 (h) Terminating Action—Replacement of the Aft Baggage Bay Door Stop Fittings and Striker Plates Within 6,000 flight hours or 36 months, whichever occurs first, after the effective date of this AD: Replace the affected stop fittings and striker plates, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–52–037, Revision B, dated September 16, 2013. Replacement of the affected stop fittings and striker plates of the aft baggage bay door constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD. (i) Other FAA AD Provisions 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, NY 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) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (j) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–37, dated November 28, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0287-0002. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 (i) Bombardier Service Bulletin 670BA–52– 037, Revision B, dated September 16, 2013. (ii) Reserved. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this 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/cfr/ibrlocations.html. Issued in Renton, Washington, on October 13, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–25022 Filed 10–27–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0581; Directorate Identifier 2014–NM–167–AD; Amendment 39–17999; AD 2014–17–51] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2B16 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires inspecting the inboard flap fasteners of the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 to determine the orientation and condition of the fasteners, as applicable, and replacement or repetitive inspections of the fasteners if necessary. This AD also provides for optional terminating action for the requirements of the AD. This AD was prompted by reports of fractured fastener heads on the inboard flap hinge-box forward fitting at WS 76.50 due to incorrect installation. We are issuing this AD to detect and correct SUMMARY: E:\FR\FM\28OCR1.SGM 28OCR1 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations incorrectly oriented or fractured fasteners, which could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane. This AD is effective November 12, 2014 to all persons except those persons to whom it was made immediately effective by Emergency AD 2014–17–51, issued on August 19, 2014, which contained the requirements of this amendment. The Director of the Federal Register approved the incorporation by reference of certain publications identified in this AD as of November 12, 2014. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of March 6, 2014 (79 FR 9389, February 19, 2014). We must receive comments on this AD by December 12, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Bombardier, Inc., 400 ˆ ´ Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. DATES: asabaliauskas on DSK5VPTVN1PROD with RULES Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0581; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory VerDate Sep<11>2014 16:44 Oct 27, 2014 Jkt 235001 evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, Propulsion and Services Branch, ANE–173, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7329; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion On August 19, 2014, we issued Emergency AD 2014–17–51, which requires inspecting the inboard flap fasteners of the hinge-box forward fitting at WS 76.50 and WS 127.25 to determine the orientation and condition of the fasteners, as applicable, and replacement or repetitive inspections of the fasteners if necessary. Emergency AD 2014–17–51 also provides for optional terminating action for the requirements of the AD. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This action was prompted by reports of fractured fastener heads on the inboard flap hinge-box forward fitting at Wing Station (WS) 76.50 due to incorrect installation. This condition, if not corrected, could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Emergency Airworthiness Directive CF– 2014–27, dated August 15, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on certain Model CL–600– 2B16 airplanes. The MCAI states: There have been three in-service reports on 604 Variant aeroplanes of a fractured fastener head on the inboard flap hinge-box forward fitting at Wing Station (WS) 76.50, found during a routine maintenance inspection. Investigation revealed that the installation of these fasteners on the inboard flap hinge-box forward fittings at WS 76.50 and WS 127.25, on both wings, does not conform to the engineering drawings. Incorrect installation may result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could lead to the detachment of the flap hinge box and consequently the detachment of the flap surface. The loss of a flap surface could PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 64089 adversely affect the continued safe operation of the aeroplane. The original issue of AD CF–2013–39 [dated December 6, 2013] [which corresponds to FAA AD 2014–03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014)] mandated a detailed visual inspection (DVI) of each inboard flap hingebox forward fitting, on both wings, and rectification as required. Incorrectly oriented fasteners require repetitive inspections until the terminating action is accomplished. After the issuance of AD CF–2013–39, there has been one reported incident on a 604 Variant aeroplane where four fasteners were found fractured on the same flap hinge-box forward fitting. The investigation determined that the fasteners were incorrectly installed. This [Canadian] AD is issued to reduce the initial and repetitive inspection intervals previously mandated in AD CF–2013–39, and to impose replacement of the incorrectly oriented fasteners within 24 months. The CL–600–1A11, –2A12 and –2B16 (601–3A/– 3R Variant) aeroplanes are addressed through AD CF–2013–39R1 [dated August 15, 2014]. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0581. Relevant Service Information We reviewed the following service information: • Bombardier Alert Service Bulletin A604–57–006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013. • Bombardier Alert Service Bulletin A604–57–006, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013. • Bombardier Alert Service Bulletin A605–57–004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013. • Bombardier Alert Service Bulletin A605–57–004, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. Revision 02 of the service information instructs operators to contact Bombardier for repair procedures for certain configurations; paragraph (k)(2) of this AD addresses this issue. FAA’s Determination and AD Requirements 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 E:\FR\FM\28OCR1.SGM 28OCR1 64090 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Accomplishment of the requirements of this AD constitutes terminating action for the requirements of AD 2014–03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014), for the airplanes identified in paragraph (c) of this AD. FAA AD 2014–03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014), corresponds to Canadian AD CF– 2013–39, dated December 6, 2013. FAA AD 2014–03–17 applies to Bombardier, Inc. Model CL–600–1A11 (CL–600), CL– 600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes. Because of the urgency of this unsafe condition for the CL–604 Variant airplanes, we have determined that it is necessary to issue an emergency AD, only for CL–604 Variant airplanes, to reduce the compliance times for the inspection required by AD 2014–03–17. Therefore this AD applies to all CL– 600–2B16 models in the specified serialnumber range. Explanation of Applicability This AD applies to Bombardier, Inc. Model CL–600–2B16 airplanes with certain serial numbers. The CL–605 is a marketing designation for the Challenger CL–600–2B16, CL–604 Variant, with Modsums 604DX10000, 604DX20000, and 604DX30000 incorporated, beginning with serial numbers 5701 and subsequent. All CL– 604 and CL–605 airplanes are type certified as CL–600–2B16 airplanes. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because incorrect installation of the fasteners attaching the inboard flap hinge-box forward fitting may result in their premature failure, and possible detachment of the flap hinge box and Differences Between This AD and the MCAI/Service Information Canadian Airworthiness Directive CF–2014–27, dated August 15, 2014, specifies to replace all forward and aft fasteners at WS 76.50 and 127.25 within 24 months, if any incorrectly installed fasteners are found. We are considering requiring this replacement, which would terminate the actions required by this AD. However, the planned compliance time for the replacement would allow enough time to provide notice and opportunity for prior public comment on the merits of the replacement. Although the service information identified previously specifies that operators may contact the manufacturer for disposition of certain repair conditions, this AD requires operators to repair those conditions in accordance with a method approved by the FAA, or TCCA, or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). the flap surface, and loss of control of the airplane. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2014–0581 and Directorate Identifier 2014–NM–167–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 285 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection ................................ 1 work-hour × $85 per hour = $85 ......................................... $0 $85 $24,225 We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Labor cost Parts cost Cost per product Fastener replacement ...................... asabaliauskas on DSK5VPTVN1PROD with RULES Action Up to 58 work-hours × $85 per hour = $4,930 ......................................... $0 $4,930 According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we VerDate Sep<11>2014 16:44 Oct 27, 2014 Jkt 235001 have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 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, E:\FR\FM\28OCR1.SGM 28OCR1 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 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. August 19, 2014, which contained the requirements of this amendment. Regulatory Findings 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) 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. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): asabaliauskas on DSK5VPTVN1PROD with RULES ■ 2014–17–51 Bombardier, Inc.: Amendment 39–17999; Docket No. FAA–2014–0581; Directorate Identifier 2014–NM–167–AD. (a) Effective Date This AD is effective November 12, 2014 to all persons except those persons to whom it was made immediately effective by Emergency AD 2014–17–51, issued on VerDate Sep<11>2014 16:44 Oct 27, 2014 Jkt 235001 (b) Affected ADs The requirements of this AD terminate the requirements of AD 2014–03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014), only for the airplanes identified in paragraph (c) of this AD. (c) Applicability This AD applies to Bombardier, Inc. Model CL–600–2B16 airplanes, certificated in any category, serial numbers 5301 through 5665 inclusive, and 5701 through 5920 inclusive. (e) Unsafe Condition This AD was prompted by reports of fractured fastener heads on the inboard flap hinge-box forward fitting at Wing Station (WS) 76.50 due to incorrect installation. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection: Airplanes Not Previously Inspected For airplanes on which the actions required by AD 2014–03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014), have not been done as of the effective date of this AD: Within 10 flight cycles after the effective date of this AD, or within 100 flight cycles after March 6, 2014 (the effective date of AD 2014–03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014)), whichever occurs first: Do a detailed visual inspection of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners are correctly oriented and intact (nonfractured, with intact fastener head). Do the inspection in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604–57–006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605–57– 004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). (1) If all fasteners are found intact and correctly oriented, no further action is required by this AD. (2) If any fastener is found fractured: Before further flight, remove and replace all forward PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 64091 and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604–57–006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605–57– 004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). After replacement of all fasteners as required by paragraph (g)(2) of this AD, no further action is required by this AD. (3) If any incorrectly oriented but intact fastener is found, and no fractured fastener is found, repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 10 flight cycles, until the requirements of paragraph (i)(1) of this AD have been done. (h) Airplanes Previously Inspected, With Incorrectly Oriented Fastener(s) For airplanes on which an inspection required by paragraph (g) or (j) of AD 2014– 03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014), has been done as of the effective date of this AD, and on which any incorrectly oriented fastener, but no fractured fastener, was found: Except as provided by paragraph (i)(3) of this AD, do a detailed visual inspection of all inboard flap fasteners of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners are intact (non-fractured, with intact fastener head). Inspect within 10 flight cycles after the effective date of this AD, or within 100 flight cycles after the most recent inspection done as required by AD 2014–03– 17, whichever occurs first. Inspect in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604–57–006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605–57–004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). (1) If all fasteners are found intact, repeat the inspection thereafter at intervals not to exceed 10 flight cycles, until the requirements of paragraph (i)(1) of this AD have been done. (2) If any fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604–57–006, E:\FR\FM\28OCR1.SGM 28OCR1 64092 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605–57– 004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). After replacement of all fasteners as required by paragraph (h)(2) of this AD, no further action is required by this AD. (i) Terminating Action (1) Replacement of all forward and aft fasteners at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604–57–006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605–57– 004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive); terminates the requirements of this AD. (2) Accomplishment of the applicable requirements of this AD constitutes terminating action for the requirements of AD 2014–03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014), for that airplane only. (3) Replacement, before the effective date of this AD, of all fractured and incorrectly oriented fasteners, as provided by paragraph (i) or (k) of AD 2014–03–17, Amendment 39– 17754 (79 FR 9389, February 19, 2014), is acceptable for compliance with the requirements of this AD. asabaliauskas on DSK5VPTVN1PROD with RULES (j) Special Flight Permit Special flight permits to operate the airplane to a location where the airplane can be repaired in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) are not allowed. (k) Other FAA Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, 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, NY 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 VerDate Sep<11>2014 16:44 Oct 27, 2014 Jkt 235001 flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York Aircraft Certification Office, ANE–170, FAA; or the TCCA; or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. Issued in Renton, Washington, on October 13, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (l) Related Information 14 CFR Part 39 Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Emergency Airworthiness Directive CF– 2014–27, dated August 15, 2014, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2014–0581. [Docket No. FAA–2013–0548; Directorate Identifier 2013–NM–008–AD; Amendment 39–18002; AD 2014–21–08] (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on November 12, 2014. (i) Bombardier Alert Service Bulletin A604–57–006, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A605–57–004, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013. (4) The following service information was approved for IBR on March 6, 2014 (79 FR 9389, February 19, 2014). (i) Bombardier Alert Service Bulletin A604–57–006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A605–57–004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013. (5) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this 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/cfr/ibrlocations.html. PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 [FR Doc. 2014–25018 Filed 10–27–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD–700–1A11 airplanes. This AD was prompted by a report that certain lanyards for the passenger oxygen masks are longer than the specified length, possibly leading to inactive oxygen masks in an emergency. This AD requires replacement of certain oxygen mask lanyards. We are issuing this AD to detect and correct lanyards of incorrect length, which might not activate the flow of oxygen in an emergency, resulting in injury to passengers. SUMMARY: This AD becomes effective December 2, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 2, 2014. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0548 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Bombardier, Inc., 400 ˆ ´ Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., DATES: E:\FR\FM\28OCR1.SGM 28OCR1

Agencies

[Federal Register Volume 79, Number 208 (Tuesday, October 28, 2014)]
[Rules and Regulations]
[Pages 64088-64092]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-25018]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0581; Directorate Identifier 2014-NM-167-AD; 
Amendment 39-17999; AD 2014-17-51]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model CL-600-2B16 airplanes. This emergency AD was 
sent previously to all known U.S. owners and operators of these 
airplanes. This AD requires inspecting the inboard flap fasteners of 
the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 
to determine the orientation and condition of the fasteners, as 
applicable, and replacement or repetitive inspections of the fasteners 
if necessary. This AD also provides for optional terminating action for 
the requirements of the AD. This AD was prompted by reports of 
fractured fastener heads on the inboard flap hinge-box forward fitting 
at WS 76.50 due to incorrect installation. We are issuing this AD to 
detect and correct

[[Page 64089]]

incorrectly oriented or fractured fasteners, which could result in 
premature failure of the fasteners attaching the inboard flap hinge-box 
forward fitting. Failure of the fasteners could lead to the detachment 
of the flap hinge box and the flap surface, and consequent loss of 
control of the airplane.

DATES: This AD is effective November 12, 2014 to all persons except 
those persons to whom it was made immediately effective by Emergency AD 
2014-17-51, issued on August 19, 2014, which contained the requirements 
of this amendment.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications identified in this AD as of November 
12, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of March 
6, 2014 (79 FR 9389, February 19, 2014).
    We must receive comments on this AD by December 12, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Bombardier, 
Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, 
Canada; telephone 514-855-5000; fax 514-855-7401; email 
thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. You 
may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0581; or in person at the Docket Operations Office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations Office 
(phone: 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, 
Propulsion and Services Branch, ANE-173, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone 516-228-7329; fax 516-794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    On August 19, 2014, we issued Emergency AD 2014-17-51, which 
requires inspecting the inboard flap fasteners of the hinge-box forward 
fitting at WS 76.50 and WS 127.25 to determine the orientation and 
condition of the fasteners, as applicable, and replacement or 
repetitive inspections of the fasteners if necessary. Emergency AD 
2014-17-51 also provides for optional terminating action for the 
requirements of the AD. This emergency AD was sent previously to all 
known U.S. owners and operators of these airplanes. This action was 
prompted by reports of fractured fastener heads on the inboard flap 
hinge-box forward fitting at Wing Station (WS) 76.50 due to incorrect 
installation. This condition, if not corrected, could result in 
premature failure of the fasteners attaching the inboard flap hinge-box 
forward fitting. Failure of the fasteners could lead to the detachment 
of the flap hinge box and the flap surface, and consequent loss of 
control of the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Emergency Airworthiness 
Directive CF-2014-27, dated August 15, 2014 (referred to after this as 
the Mandatory Continuing Airworthiness Information, or ``the MCAI''), 
to correct an unsafe condition on certain Model CL-600-2B16 airplanes. 
The MCAI states:

    There have been three in-service reports on 604 Variant 
aeroplanes of a fractured fastener head on the inboard flap hinge-
box forward fitting at Wing Station (WS) 76.50, found during a 
routine maintenance inspection. Investigation revealed that the 
installation of these fasteners on the inboard flap hinge-box 
forward fittings at WS 76.50 and WS 127.25, on both wings, does not 
conform to the engineering drawings. Incorrect installation may 
result in premature failure of the fasteners attaching the inboard 
flap hinge-box forward fitting. Failure of the fasteners could lead 
to the detachment of the flap hinge box and consequently the 
detachment of the flap surface. The loss of a flap surface could 
adversely affect the continued safe operation of the aeroplane.
    The original issue of AD CF-2013-39 [dated December 6, 2013] 
[which corresponds to FAA AD 2014-03-17, Amendment 39-17754 (79 FR 
9389, February 19, 2014)] mandated a detailed visual inspection 
(DVI) of each inboard flap hinge-box forward fitting, on both wings, 
and rectification as required. Incorrectly oriented fasteners 
require repetitive inspections until the terminating action is 
accomplished.
    After the issuance of AD CF-2013-39, there has been one reported 
incident on a 604 Variant aeroplane where four fasteners were found 
fractured on the same flap hinge-box forward fitting. The 
investigation determined that the fasteners were incorrectly 
installed.
    This [Canadian] AD is issued to reduce the initial and 
repetitive inspection intervals previously mandated in AD CF-2013-
39, and to impose replacement of the incorrectly oriented fasteners 
within 24 months. The CL-600-1A11, -2A12 and -2B16 (601-3A/-3R 
Variant) aeroplanes are addressed through AD CF-2013-39R1 [dated 
August 15, 2014].

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2014-0581.

Relevant Service Information

    We reviewed the following service information:
     Bombardier Alert Service Bulletin A604-57-006, Revision 
01, dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013.
     Bombardier Alert Service Bulletin A604-57-006, Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
     Bombardier Alert Service Bulletin A605-57-004, Revision 
01, dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013.
     Bombardier Alert Service Bulletin A605-57-004, Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.
    Revision 02 of the service information instructs operators to 
contact Bombardier for repair procedures for certain configurations; 
paragraph (k)(2) of this AD addresses this issue.

FAA's Determination and AD Requirements

    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

[[Page 64090]]

MCAI and service information referenced above. We are issuing this AD 
because we evaluated all pertinent information and determined the 
unsafe condition exists and is likely to exist or develop on other 
products of the same type design.
    Accomplishment of the requirements of this AD constitutes 
terminating action for the requirements of AD 2014-03-17, Amendment 39-
17754 (79 FR 9389, February 19, 2014), for the airplanes identified in 
paragraph (c) of this AD.
    FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 
2014), corresponds to Canadian AD CF-2013-39, dated December 6, 2013. 
FAA AD 2014-03-17 applies to Bombardier, Inc. Model CL-600-1A11 (CL-
600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and 
CL-604 Variants) airplanes. Because of the urgency of this unsafe 
condition for the CL-604 Variant airplanes, we have determined that it 
is necessary to issue an emergency AD, only for CL-604 Variant 
airplanes, to reduce the compliance times for the inspection required 
by AD 2014-03-17.

Explanation of Applicability

    This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes 
with certain serial numbers. The CL-605 is a marketing designation for 
the Challenger CL-600-2B16, CL-604 Variant, with Modsums 604DX10000, 
604DX20000, and 604DX30000 incorporated, beginning with serial numbers 
5701 and subsequent. All CL-604 and CL-605 airplanes are type certified 
as CL-600-2B16 airplanes. Therefore this AD applies to all CL-600-2B16 
models in the specified serial-number range.

Differences Between This AD and the MCAI/Service Information

    Canadian Airworthiness Directive CF-2014-27, dated August 15, 2014, 
specifies to replace all forward and aft fasteners at WS 76.50 and 
127.25 within 24 months, if any incorrectly installed fasteners are 
found. We are considering requiring this replacement, which would 
terminate the actions required by this AD. However, the planned 
compliance time for the replacement would allow enough time to provide 
notice and opportunity for prior public comment on the merits of the 
replacement.
    Although the service information identified previously specifies 
that operators may contact the manufacturer for disposition of certain 
repair conditions, this AD requires operators to repair those 
conditions in accordance with a method approved by the FAA, or TCCA, or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO).

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
incorrect installation of the fasteners attaching the inboard flap 
hinge-box forward fitting may result in their premature failure, and 
possible detachment of the flap hinge box and the flap surface, and 
loss of control of the airplane. Therefore, we find that notice and 
opportunity for prior public comment are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2014-0581 and 
Directorate Identifier 2014-NM-167-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 285 airplanes of U.S. registry. We 
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........................  1 work-hour x $85 per                  $0              $85          $24,225
                                     hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the 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
----------------------------------------------------------------------------------------------------------------
Fastener replacement......................  Up to 58 work-hours x $85 per hour              $0           $4,930
                                             = $4,930.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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,

[[Page 64091]]

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

    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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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 airworthiness 
directive (AD):

2014-17-51 Bombardier, Inc.: Amendment 39-17999; Docket No. FAA-
2014-0581; Directorate Identifier 2014-NM-167-AD.

(a) Effective Date

    This AD is effective November 12, 2014 to all persons except 
those persons to whom it was made immediately effective by Emergency 
AD 2014-17-51, issued on August 19, 2014, which contained the 
requirements of this amendment.

(b) Affected ADs

    The requirements of this AD terminate the requirements of AD 
2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), only 
for the airplanes identified in paragraph (c) of this AD.

(c) Applicability

    This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes, 
certificated in any category, serial numbers 5301 through 5665 
inclusive, and 5701 through 5920 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of fractured fastener heads on 
the inboard flap hinge-box forward fitting at Wing Station (WS) 
76.50 due to incorrect installation. We are issuing this AD to 
detect and correct incorrectly oriented or fractured fasteners, 
which could result in premature failure of the fasteners attaching 
the inboard flap hinge-box forward fitting. Failure of the fasteners 
could lead to the detachment of the flap hinge box and the flap 
surface, and consequent loss of control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection: Airplanes Not Previously Inspected

    For airplanes on which the actions required by AD 2014-03-17, 
Amendment 39-17754 (79 FR 9389, February 19, 2014), have not been 
done as of the effective date of this AD: Within 10 flight cycles 
after the effective date of this AD, or within 100 flight cycles 
after March 6, 2014 (the effective date of AD 2014-03-17, Amendment 
39-17754 (79 FR 9389, February 19, 2014)), whichever occurs first: 
Do a detailed visual inspection of each inboard flap fastener of the 
hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, 
to determine if the fasteners are correctly oriented and intact 
(non-fractured, with intact fastener head). Do the inspection in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, 
including Appendices 1 and 2, dated September 26, 2013, or Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013 (for serial numbers 5301 through 5665 inclusive); 
or Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated 
September 26, 2013, including Appendices 1 and 2, dated September 
26, 2013, or Revision 02, dated January 22, 2014, including 
Appendices 1 and 2, dated September 26, 2013 (for serial numbers 
5701 through 5920 inclusive).
    (1) If all fasteners are found intact and correctly oriented, no 
further action is required by this AD.
    (2) If any fastener is found fractured: Before further flight, 
remove and replace all forward and aft fasteners at WS 76.50 and WS 
127.25, regardless of condition or orientation, on both wings, in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, 
including Appendices 1 and 2, dated September 26, 2013, or Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013 (for serial numbers 5301 through 5665 inclusive); 
or Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated 
September 26, 2013, including Appendices 1 and 2, dated September 
26, 2013, or Revision 02, dated January 22, 2014, including 
Appendices 1 and 2, dated September 26, 2013 (for serial numbers 
5701 through 5920 inclusive). After replacement of all fasteners as 
required by paragraph (g)(2) of this AD, no further action is 
required by this AD.
    (3) If any incorrectly oriented but intact fastener is found, 
and no fractured fastener is found, repeat the inspection required 
by paragraph (g) of this AD thereafter at intervals not to exceed 10 
flight cycles, until the requirements of paragraph (i)(1) of this AD 
have been done.

(h) Airplanes Previously Inspected, With Incorrectly Oriented 
Fastener(s)

    For airplanes on which an inspection required by paragraph (g) 
or (j) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 
19, 2014), has been done as of the effective date of this AD, and on 
which any incorrectly oriented fastener, but no fractured fastener, 
was found: Except as provided by paragraph (i)(3) of this AD, do a 
detailed visual inspection of all inboard flap fasteners of the 
hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, 
to determine if the fasteners are intact (non-fractured, with intact 
fastener head). Inspect within 10 flight cycles after the effective 
date of this AD, or within 100 flight cycles after the most recent 
inspection done as required by AD 2014-03-17, whichever occurs 
first. Inspect in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated 
September 26, 2013, including Appendices 1 and 2, dated September 
26, 2013, or Revision 02, dated January 22, 2014, including 
Appendices 1 and 2, dated September 26, 2013 (for serial numbers 
5301 through 5665 inclusive); or Bombardier Alert Service Bulletin 
A605-57-004, Revision 01, dated September 26, 2013, including 
Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated 
January 22, 2014, including Appendices 1 and 2, dated September 26, 
2013 (for serial numbers 5701 through 5920 inclusive).
    (1) If all fasteners are found intact, repeat the inspection 
thereafter at intervals not to exceed 10 flight cycles, until the 
requirements of paragraph (i)(1) of this AD have been done.
    (2) If any fastener is found fractured: Before further flight, 
remove and replace all forward and aft fasteners at WS 76.50 and WS 
127.25, regardless of condition or orientation, on both wings, in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A604-57-006,

[[Page 64092]]

Revision 01, dated September 26, 2013, including Appendices 1 and 2, 
dated September 26, 2013, or Revision 02, dated January 22, 2014, 
including Appendices 1 and 2, dated September 26, 2013 (for serial 
numbers 5301 through 5665 inclusive); or Bombardier Alert Service 
Bulletin A605-57-004, Revision 01, dated September 26, 2013, 
including Appendices 1 and 2, dated September 26, 2013, or Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013 (for serial numbers 5701 through 5920 inclusive). 
After replacement of all fasteners as required by paragraph (h)(2) 
of this AD, no further action is required by this AD.

(i) Terminating Action

    (1) Replacement of all forward and aft fasteners at WS 76.50 and 
WS 127.25, on both wings, in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A604-57-006, 
Revision 01, dated September 26, 2013, including Appendices 1 and 2, 
dated September 26, 2013, or Revision 02, dated January 22, 2014, 
including Appendices 1 and 2, dated September 26, 2013 (for serial 
numbers 5301 through 5665 inclusive); or Bombardier Alert Service 
Bulletin A605-57-004, Revision 01, dated September 26, 2013, 
including Appendices 1 and 2, dated September 26, 2013, or Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013 (for serial numbers 5701 through 5920 inclusive); 
terminates the requirements of this AD.
    (2) Accomplishment of the applicable requirements of this AD 
constitutes terminating action for the requirements of AD 2014-03-
17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for that 
airplane only.
    (3) Replacement, before the effective date of this AD, of all 
fractured and incorrectly oriented fasteners, as provided by 
paragraph (i) or (k) of AD 2014-03-17, Amendment 39-17754 (79 FR 
9389, February 19, 2014), is acceptable for compliance with the 
requirements of this AD.

(j) Special Flight Permit

    Special flight permits to operate the airplane to a location 
where the airplane can be repaired in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) are not allowed.

(k) Other FAA Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, 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, 
NY 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, New York 
Aircraft Certification Office, ANE-170, FAA; or the TCCA; or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
Canadian Emergency Airworthiness Directive CF-2014-27, dated August 
15, 2014, for related information. You may examine the MCAI on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2014-0581.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 12, 2014.
    (i) Bombardier Alert Service Bulletin A604-57-006, Revision 02, 
dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 02, 
dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    (4) The following service information was approved for IBR on 
March 6, 2014 (79 FR 9389, February 19, 2014).
    (i) Bombardier Alert Service Bulletin A604-57-006, Revision 01, 
dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013.
    (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 01, 
dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013.
    (5) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.com.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 13, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-25018 Filed 10-27-14; 8:45 am]
BILLING CODE 4910-13-P