Airworthiness Directives; Bombardier, Inc. Airplanes, 79381-79384 [2016-25009]

Download as PDF 79381 Rules and Regulations Federal Register Vol. 81, No. 219 Monday, November 14, 2016 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5593; Directorate Identifier 2015–NM–184–AD; Amendment 39–18687; AD 2016–21–06] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2015–02– 23, for certain Bombardier, Inc. Model CL–600–1A11 (CL–600), CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601– 3A and CL–601–3R Variants) airplanes. AD 2015–02–23 required repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners if necessary. This new AD also requires replacement of the fasteners, which terminates the requirements of this AD. This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane. DATES: This AD is effective December 19, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 18, 2015 (80 FR 5670, February 3, 2015). ADDRESSES: For service information identified in this final rule, contact ˆ Bombardier, Inc., 400 Cote-Vertu Road Lhorne on DSK30JT082PROD with RULES SUMMARY: VerDate Sep<11>2014 15:02 Nov 10, 2016 Jkt 241001 ´ West, Dorval, Quebec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone: 1– 866–538–1247 or direct-dial telephone: 1–514–855–2999; fax 514–855–7401; email: ac.yul@aero.bombardier.com; Internet: https://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. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5593. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5593; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone: 800–647– 5527) is 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 20590. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE– 171, 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 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2015–02–23, Amendment 39–18092 (80 FR 5670, February 3, 2015) (‘‘AD 2015–02–23’’). AD 2015–02–23 applied to certain Bombardier, Inc. Model CL–600–1A11 (CL–600), CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A and CL– 601–3R Variants) airplanes. AD 2015– 02–23 corresponded to Canadian Emergency AD CF–2013–39R2, dated December 12, 2014 (referred to after this as the Mandatory Continuing PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Airworthiness Information, or ‘‘the MCAI’’). The MCAI was issued by Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada. The preamble to AD 2015–02–23 explained that we considered the requirements interim action and were considering further rulemaking. We have now determined that further rulemaking is indeed necessary and that, instead of continuing repetitive inspections, for airplanes which have any incorrectly oriented fastener, and no fractured or missing fastener, replacement of all forward and aft fasteners, regardless of condition or orientation, is necessary. This AD follows from that determination. The NPRM published in the Federal Register on April 20, 2016 (81 FR 23202). The NPRM was prompted by reports of incorrectly oriented fasteners. The NPRM proposed to continue to require repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners if necessary. The NPRM also proposed to require replacement of the fasteners, which would terminate the requirements of this AD. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. E:\FR\FM\14NOR1.SGM 14NOR1 79382 Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations Related Service Information Under 1 CFR Part 51 Bombardier has issued Alert Service Bulletins A600–0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013; and A601–0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. The service information describes procedures for repetitive inspections of the fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of fasteners. These documents are distinct since they apply to different airplane models. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 120 airplanes of U.S. registry. The actions required by AD 2015–02– 23, and retained in this AD, take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2015–02–23 is $85 per product. We also estimate that it would take about 59 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. We have received no definitive data that would enable us to provide cost estimates for the parts cost. Based on these figures, we estimate the cost of this AD on U.S. operators to be $601,800, or $5,015 per product. In addition, we estimate that any necessary follow-on actions will take about 58 work-hours and require parts costing $753, for a cost of $5,683 per product. We have no way of determining the number of aircraft that might need this action. 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 available costs in our cost estimate. 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 that 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); 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. Lhorne on DSK30JT082PROD with RULES Authority for This Rulemaking § 39.13 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. ■ VerDate Sep<11>2014 15:02 Nov 10, 2016 Jkt 241001 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–02–23, Amendment 39–18092 (80 FR 5670, February 3, 2015), and adding the following new AD: 2016–21–06 Bombardier, Inc.: Amendment 39–18687; Docket No. FAA–2016–5593; Directorate Identifier 2015–NM–184–AD. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 (a) Effective Date This AD is effective December 19, 2016. (b) Affected ADs This AD replaces AD 2015–02–23, Amendment 39–18092 (80 FR 5670, February 3, 2015) (‘‘AD 2015–02–23’’). This AD affects AD 2014–03–17, Amendment 39–17754 (79 FR 9389, February 19, 2014) (‘‘AD 2014–03– 17’’). (c) Applicability This AD applies to the Bombardier, Inc. airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Bombardier, Inc. Model CL–600–1A11 (CL–600) airplanes, having serial numbers (S/ Ns) 1004 through 1085 inclusive. (2) Bombardier, Inc. Model CL–600–2A12 (CL–601) airplanes, having S/Ns 3001 through 3066 inclusive. (3) Bombardier, Inc. Model CL–600–2B16 (CL–601–3A and CL–601–3R Variants) airplanes, having S/Ns 5001 through 5194 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection on Airplanes Not Previously Inspected, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2015–02–23, with no changes. For airplanes that have not been inspected as required by paragraph (g) of AD 2014–03–17, as of February 18, 2015 (the effective date of AD 2015–02–23): Within 10 flight cycles after February 18, 2015, or 100 flight cycles after March 6, 2014 (the effective date of AD 2014–03–17), whichever occurs first, do a detailed visual inspection for incorrect orientation and any fractured or missing fastener heads of each inboard flap fastener of the hinge-box forward fitting at wing station (WS) 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1) and (g)(2) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraph (g) of AD 2014–03–17 for the inspected airplane only. (1) For Model CL–600–1A11 (CL–600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600–0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (2) For Model CL–600–2A12 (CL–601) airplanes having S/Ns 3001 through 3066 E:\FR\FM\14NOR1.SGM 14NOR1 Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations inclusive, and Model CL–600–2B16 (CL– 601–3A and CL–601–3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601– 0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. Lhorne on DSK30JT082PROD with RULES (h) Retained Corrective Actions for Paragraph (g) of This AD, With Revised Paragraph (h)(2) of This AD (1) This paragraph restates the requirements of paragraph (h)(1) of AD 2015– 02–23, with no changes. If, during any inspection required by paragraph (g) of this AD, all fasteners are found correctly oriented and not fractured, and no fastener heads are missing (fasteners found intact): No further action is required by this AD. (2) This paragraph restates the requirements of paragraph (h)(2) of AD 2015– 02–23, with revised references to replacement paragraphs. If, during any inspection required by paragraph (g) of this AD, any fastener is found incorrectly oriented but no fasteners are fractured or are missing a fastener head (fasteners found intact), repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 10 flight cycles until the replacements specified in paragraphs (h)(3), (k), or (n) of this AD are accomplished. (3) This paragraph restates the requirements of paragraph (h)(3) of AD 2015– 02–23, with no changes. If, during any inspection required by paragraph (g) of this AD, any fastener is found fractured or has a missing fastener head: Before further flight, remove and replace all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, except as required by paragraph (m) of this AD. After accomplishing the replacements required by this paragraph, no further action is required by this AD. (i) For Model CL–600–1A11 (CL–600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600–0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (ii) For Model CL–600–2A12 (CL–601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL–600–2B16 (CL– 601–3A and CL–601–3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601– 0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (i) Retained Inspection for Airplanes Previously Inspected and Found To Have Incorrectly Oriented Fastener(s), With No Changes This paragraph restates the requirements of paragraph (i) of AD 2015–02–23, with no changes. For airplanes on which an inspection required by paragraph (g) or (j) of AD 2014–03–17, has been done as of the effective date of this AD, and on which any incorrectly oriented fastener was found but VerDate Sep<11>2014 15:02 Nov 10, 2016 Jkt 241001 no fasteners were fractured (fasteners found intact): Except as provided by paragraph (l) of this AD, within 10 flight cycles after February 18, 2015 (the effective date of AD 2015–02–23), or within 100 flight cycles after accomplishing the most recent inspection required by AD 2014–03–17, whichever occurs first, do a detailed visual inspection for any fractured or missing fastener heads of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings. Do the inspection in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (i)(1) and (i)(2) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014–03–17 for the inspected airplane only. (1) For Model CL–600–1A11 (CL–600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600–0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (2) For Model CL–600–2A12 (CL–601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL–600–2B16 (CL– 601–3A and CL–601–3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601– 0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (j) Retained Corrective Actions for Paragraph (i) of This AD, With Revised Reference to Additional, New Requirements (1) This paragraph restates the requirements of paragraph (j)(1) of AD 2015– 02–23, with revised reference to additional, new requirements. If, during any inspection required by paragraph (i) of this AD, no fasteners are found fractured or have missing fastener heads (fasteners are intact), repeat the inspection required by paragraph (i) of this AD thereafter at intervals not to exceed 10 flight cycles until the replacement specified in paragraph (j)(2), (k), or (n) of this AD is accomplished. (2) This paragraph restates the requirements of paragraph (j)(2) of AD 2015– 02–23, with no changes. If, during any inspection required by paragraph (i) of this AD, any fastener is found fractured or has a missing fastener head: Before further flight, remove and replace all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, except as required by paragraph (m) of this AD. After accomplishing the replacements required by this paragraph, no further action is required by this AD. (i) For Model CL–600–1A11 (CL–600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600–0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (ii) For Model CL–600–2A12 (CL–601) airplanes having S/Ns 3001 through 3066 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 79383 inclusive, and Model CL–600–2B16 (CL– 601–3A and CL–601–3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601– 0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (k) Retained Optional Terminating Action for Incorrectly Oriented Fasteners, With No Changes This paragraph restates the provisions of paragraph (k) of AD 2015–02–23, with no changes. Replacement of all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, terminates the requirements of this AD. The replacement must be done in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (k)(1) and (k)(2) of this AD, except as provided by paragraph (m) of this AD. Doing the replacements specified in this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014–03–17, only for the airplane on which the replacement was done. (1) For Model CL–600–1A11 (CL–600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600–0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (2) For Model CL–600–2A12 (CL–601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL–600–2B16 (CL– 601–3A and CL–601–3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601– 0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (l) Retained Exception for Previously Replaced Fasteners, With No Changes This paragraph restates the provisions of paragraph (l) of AD 2015–02–23, with no changes. Replacement of all fractured and incorrectly oriented forward and aft fasteners, as specified in paragraph (i) or (k) of AD 2014–03–17, if done before the effective date of this AD, is considered acceptable for compliance with the requirements of this AD. (m) Retained Exception to the Service Information, With No Changes This paragraph restates the requirements of paragraph (m) of AD 2015–02–23, with no changes. Where Bombardier Alert Service Bulletin A600–0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013; and Bombardier Alert Service Bulletin A601– 0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013; specify to contact Bombardier for repair instructions, before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier’s TCCA Design Approval Organization (DAO). E:\FR\FM\14NOR1.SGM 14NOR1 79384 Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations (n) New Requirement of This AD: Terminating Action For airplanes on which any incorrectly oriented fastener, and no fractured or missing fastener, was detected during any inspection required by paragraph (g), (h)(2), (i), and (j)(1) of this AD: Within 24 months after the effective date of this AD, replace all forward and aft fasteners, regardless of condition or orientation, at WS 76.50 and WS 127.25, on affected wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (k)(1) and (k)(2) of this AD, except as provided by paragraph (m) of this AD. Doing the replacements specified in this paragraph terminates the requirements of this AD. Doing the replacements specified in this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014–03–17, only for the airplane on which the replacement was done. Lhorne on DSK30JT082PROD with RULES (o) Credit for Previous Actions This paragraph restates the provisions of paragraph (n) of AD 2015–02–23, with new credit for paragraph (n) of this AD. This paragraph provides credit for actions required by paragraphs (g), (h), (i), and (n) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (o)(1) through (o)(4) of this AD. (1) Bombardier Alert Service Bulletin A600–0763, including Appendixes 1 and 2, dated September 26, 2013, which was previously incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 2014). (2) Bombardier Alert Service Bulletin A600–0763, Revision 01, dated February 26, 2014, including Appendixes 1 and 2, dated September 26, 2013, which is not incorporated by reference in this AD. (3) Bombardier Alert Service Bulletin A601–0627, including Appendixes 1 and 2, dated September 26, 2013, which was previously incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 2014). (4) Bombardier Alert Service Bulletin A601–0627, Revision 01, dated February 26, 2014, including Appendixes 1 and 2, dated September 26, 2013, which is not incorporated by reference in this AD. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York 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 VerDate Sep<11>2014 15:02 Nov 10, 2016 Jkt 241001 flight standards district office/certificate holding district office. (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, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–7527; Directorate Identifier 2015–NM–094–AD; Amendment 39–18686; AD 2016–21–05] RIN 2120–AA64 (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Emergency AD CF–2013–39R2, dated December 12, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–5593. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(4) and (r)(5) of this AD. (r) 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. (3) The following service information was approved for IBR on February 18, 2015 (80 FR 5670, February 3, 2015). (i) Bombardier Alert Service Bulletin A600–0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A601–0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (4) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone: 1– 866–538–1247 or direct-dial telephone: 1– 514–855–2999; fax 514–855–7401; email: ac.yul@aero.bombardier.com; Internet: https://www.bombardier.com. (5) 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. (6) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on October 7, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–25009 Filed 11–10–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. This AD was prompted by a report indicating that the manufacturer discovered locations where the control components and wiring of the left and right engine fuel spar valves do not have adequate physical separation to meet the redundant system separation requirements. This AD requires modifying the wiring, and installing a new relay bracket and new location for the relay on the left and right engine fuel spar valves. This AD also requires an inspection to identify the part number of the motor operated valve (MOV) actuators for the left and right engine fuel spar valves; replacement of specified MOV actuators with new MOV actuators; certain bonding resistance measurements; and applicable corrective actions. We are issuing this AD to prevent loss of control of both the left and right engine fuel spar valves during a single event, such as local wire bundle damage or a wire bundle fire, which could cause both engines to shut down or result in the inability to control an engine fire. DATES: This AD is effective December 19, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 19, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.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. It is also SUMMARY: E:\FR\FM\14NOR1.SGM 14NOR1

Agencies

[Federal Register Volume 81, Number 219 (Monday, November 14, 2016)]
[Rules and Regulations]
[Pages 79381-79384]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-25009]



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Rules and Regulations
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having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

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Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / 
Rules and Regulations

[[Page 79381]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-AD; 
Amendment 39-18687; AD 2016-21-06]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-02-23, 
for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 
(CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes. 
AD 2015-02-23 required repetitive inspections for fractured or 
incorrectly oriented fasteners on the inboard flap hinge-box forward 
fittings on both wings, and replacement of all fasteners if necessary. 
This new AD also requires replacement of the fasteners, which 
terminates the requirements of this AD. This AD was prompted by reports 
of incorrectly oriented fasteners. We are issuing this AD to prevent 
incorrectly oriented or fractured fasteners, which could result in 
detachment of the flap hinge-box and the flap surface, and consequent 
reduced controllability of the airplane.

DATES: This AD is effective December 19, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 18, 
2015 (80 FR 5670, February 3, 2015).

ADDRESSES: For service information identified in this final rule, 
contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; Widebody Customer Response Center North 
America toll-free telephone: 1-866-538-1247 or direct-dial telephone: 
1-514-855-2999; fax 514-855-7401; email: ac.yul@aero.bombardier.com; 
Internet: https://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. It is also available on 
the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-5593.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5593; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone: 800-
647-5527) is 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 20590.

FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, 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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2015-02-23, Amendment 39-18092 (80 FR 5670, 
February 3, 2015) (``AD 2015-02-23''). AD 2015-02-23 applied to certain 
Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and 
CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes. AD 2015-02-23 
corresponded to Canadian Emergency AD CF-2013-39R2, dated December 12, 
2014 (referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''). The MCAI was issued by Transport Canada 
Civil Aviation (TCCA), which is the aviation authority for Canada.
    The preamble to AD 2015-02-23 explained that we considered the 
requirements interim action and were considering further rulemaking. We 
have now determined that further rulemaking is indeed necessary and 
that, instead of continuing repetitive inspections, for airplanes which 
have any incorrectly oriented fastener, and no fractured or missing 
fastener, replacement of all forward and aft fasteners, regardless of 
condition or orientation, is necessary. This AD follows from that 
determination.
    The NPRM published in the Federal Register on April 20, 2016 (81 FR 
23202). The NPRM was prompted by reports of incorrectly oriented 
fasteners. The NPRM proposed to continue to require repetitive 
inspections for fractured or incorrectly oriented fasteners on the 
inboard flap hinge-box forward fittings on both wings, and replacement 
of all fasteners if necessary. The NPRM also proposed to require 
replacement of the fasteners, which would terminate the requirements of 
this AD. We are issuing this AD to prevent incorrectly oriented or 
fractured fasteners, which could result in detachment of the flap 
hinge-box and the flap surface, and consequent reduced controllability 
of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

[[Page 79382]]

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Alert Service Bulletins A600-0763, Revision 
02, dated December 9, 2014, including Appendixes 1 and 2, dated 
September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014, 
including Appendixes 1 and 2, dated September 26, 2013. The service 
information describes procedures for repetitive inspections of the 
fasteners on the inboard flap hinge-box forward fittings on both wings, 
and replacement of fasteners. These documents are distinct since they 
apply to different airplane models. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 120 airplanes of U.S. registry.
    The actions required by AD 2015-02-23, and retained in this AD, 
take about 1 work-hour per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that are required by AD 2015-02-23 is $85 per product.
    We also estimate that it would take about 59 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. We have received no definitive data that 
would enable us to provide cost estimates for the parts cost. Based on 
these figures, we estimate the cost of this AD on U.S. operators to be 
$601,800, or $5,015 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 58 work-hours and require parts costing $753, for a cost of 
$5,683 per product. We have no way of determining the number of 
aircraft that might need this action.
    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 available 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, 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 that 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);
    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 removing Airworthiness Directive (AD) 
2015-02-23, Amendment 39-18092 (80 FR 5670, February 3, 2015), and 
adding the following new AD:

2016-21-06 Bombardier, Inc.: Amendment 39-18687; Docket No. FAA-
2016-5593; Directorate Identifier 2015-NM-184-AD.

(a) Effective Date

    This AD is effective December 19, 2016.

(b) Affected ADs

    This AD replaces AD 2015-02-23, Amendment 39-18092 (80 FR 5670, 
February 3, 2015) (``AD 2015-02-23''). This AD affects AD 2014-03-
17, Amendment 39-17754 (79 FR 9389, February 19, 2014) (``AD 2014-
03-17'').

(c) Applicability

    This AD applies to the Bombardier, Inc. airplanes identified in 
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in 
any category.
    (1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes, 
having serial numbers (S/Ns) 1004 through 1085 inclusive.
    (2) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes, 
having S/Ns 3001 through 3066 inclusive.
    (3) Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-3R 
Variants) airplanes, having S/Ns 5001 through 5194 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of incorrectly oriented 
fasteners. We are issuing this AD to prevent incorrectly oriented or 
fractured fasteners, which could result in detachment of the flap 
hinge-box and the flap surface, and consequent reduced 
controllability of the airplane.

(f) Compliance

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

(g) Retained Inspection on Airplanes Not Previously Inspected, With No 
Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2015-02-23, with no changes. For airplanes that have not been 
inspected as required by paragraph (g) of AD 2014-03-17, as of 
February 18, 2015 (the effective date of AD 2015-02-23): Within 10 
flight cycles after February 18, 2015, or 100 flight cycles after 
March 6, 2014 (the effective date of AD 2014-03-17), whichever 
occurs first, do a detailed visual inspection for incorrect 
orientation and any fractured or missing fastener heads of each 
inboard flap fastener of the hinge-box forward fitting at wing 
station (WS) 76.50 and WS 127.25, on both wings, in accordance with 
the Accomplishment Instructions of the applicable service 
information specified in paragraphs (g)(1) and (g)(2) of this AD. 
Accomplishing the inspection required by this paragraph terminates 
the requirements of paragraph (g) of AD 2014-03-17 for the inspected 
airplane only.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendixes 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066

[[Page 79383]]

inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) 
airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert 
Service Bulletin A601-0627, Revision 02, dated December 9, 2014, 
including Appendixes 1 and 2, dated September 26, 2013.

(h) Retained Corrective Actions for Paragraph (g) of This AD, With 
Revised Paragraph (h)(2) of This AD

    (1) This paragraph restates the requirements of paragraph (h)(1) 
of AD 2015-02-23, with no changes. If, during any inspection 
required by paragraph (g) of this AD, all fasteners are found 
correctly oriented and not fractured, and no fastener heads are 
missing (fasteners found intact): No further action is required by 
this AD.
    (2) This paragraph restates the requirements of paragraph (h)(2) 
of AD 2015-02-23, with revised references to replacement paragraphs. 
If, during any inspection required by paragraph (g) of this AD, any 
fastener is found incorrectly oriented but no fasteners are 
fractured or are missing a fastener head (fasteners found intact), 
repeat the inspection required by paragraph (g) of this AD 
thereafter at intervals not to exceed 10 flight cycles until the 
replacements specified in paragraphs (h)(3), (k), or (n) of this AD 
are accomplished.
    (3) This paragraph restates the requirements of paragraph (h)(3) 
of AD 2015-02-23, with no changes. If, during any inspection 
required by paragraph (g) of this AD, any fastener is found 
fractured or has a missing fastener head: Before further flight, 
remove and replace all forward and aft fasteners (regardless of 
orientation or condition) at WS 76.50 and WS 127.25, on both wings, 
in accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraphs (h)(3)(i) and (h)(3)(ii) 
of this AD, except as required by paragraph (m) of this AD. After 
accomplishing the replacements required by this paragraph, no 
further action is required by this AD.
    (i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendixes 1 and 2, 
dated September 26, 2013.
    (ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendixes 1 and 2, dated September 26, 
2013.

(i) Retained Inspection for Airplanes Previously Inspected and Found To 
Have Incorrectly Oriented Fastener(s), With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2015-02-23, with no changes. For airplanes on which an inspection 
required by paragraph (g) or (j) of AD 2014-03-17, has been done as 
of the effective date of this AD, and on which any incorrectly 
oriented fastener was found but no fasteners were fractured 
(fasteners found intact): Except as provided by paragraph (l) of 
this AD, within 10 flight cycles after February 18, 2015 (the 
effective date of AD 2015-02-23), or within 100 flight cycles after 
accomplishing the most recent inspection required by AD 2014-03-17, 
whichever occurs first, do a detailed visual inspection for any 
fractured or missing fastener heads of each inboard flap fastener of 
the hinge-box forward fitting at WS 76.50 and WS 127.25, on both 
wings. Do the inspection in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraphs (i)(1) and (i)(2) of this AD. Accomplishing the 
inspection required by this paragraph terminates the requirements of 
paragraphs (g) and (j) of AD 2014-03-17 for the inspected airplane 
only.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendixes 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendixes 1 and 2, dated September 26, 
2013.

(j) Retained Corrective Actions for Paragraph (i) of This AD, With 
Revised Reference to Additional, New Requirements

    (1) This paragraph restates the requirements of paragraph (j)(1) 
of AD 2015-02-23, with revised reference to additional, new 
requirements. If, during any inspection required by paragraph (i) of 
this AD, no fasteners are found fractured or have missing fastener 
heads (fasteners are intact), repeat the inspection required by 
paragraph (i) of this AD thereafter at intervals not to exceed 10 
flight cycles until the replacement specified in paragraph (j)(2), 
(k), or (n) of this AD is accomplished.
    (2) This paragraph restates the requirements of paragraph (j)(2) 
of AD 2015-02-23, with no changes. If, during any inspection 
required by paragraph (i) of this AD, any fastener is found 
fractured or has a missing fastener head: Before further flight, 
remove and replace all forward and aft fasteners (regardless of 
orientation or condition) at WS 76.50 and WS 127.25, on both wings, 
in accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraphs (j)(2)(i) and (j)(2)(ii) 
of this AD, except as required by paragraph (m) of this AD. After 
accomplishing the replacements required by this paragraph, no 
further action is required by this AD.
    (i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendixes 1 and 2, 
dated September 26, 2013.
    (ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendixes 1 and 2, dated September 26, 
2013.

(k) Retained Optional Terminating Action for Incorrectly Oriented 
Fasteners, With No Changes

    This paragraph restates the provisions of paragraph (k) of AD 
2015-02-23, with no changes. Replacement of all forward and aft 
fasteners (regardless of orientation or condition) at WS 76.50 and 
WS 127.25, on both wings, terminates the requirements of this AD. 
The replacement must be done in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraphs (k)(1) and (k)(2) of this AD, except as provided by 
paragraph (m) of this AD. Doing the replacements specified in this 
paragraph terminates the requirements of paragraphs (g) and (j) of 
AD 2014-03-17, only for the airplane on which the replacement was 
done.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendixes 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendixes 1 and 2, dated September 26, 
2013.

(l) Retained Exception for Previously Replaced Fasteners, With No 
Changes

    This paragraph restates the provisions of paragraph (l) of AD 
2015-02-23, with no changes. Replacement of all fractured and 
incorrectly oriented forward and aft fasteners, as specified in 
paragraph (i) or (k) of AD 2014-03-17, if done before the effective 
date of this AD, is considered acceptable for compliance with the 
requirements of this AD.

(m) Retained Exception to the Service Information, With No Changes

    This paragraph restates the requirements of paragraph (m) of AD 
2015-02-23, with no changes. Where Bombardier Alert Service Bulletin 
A600-0763, Revision 02, dated December 9, 2014, including Appendixes 
1 and 2, dated September 26, 2013; and Bombardier Alert Service 
Bulletin A601-0627, Revision 02, dated December 9, 2014, including 
Appendixes 1 and 2, dated September 26, 2013; specify to contact 
Bombardier for repair instructions, before further flight, repair 
using a method approved by the Manager, New York Aircraft 
Certification Office (ACO), FAA; or Transport Canada Civil Aviation 
(TCCA); or Bombardier's TCCA Design Approval Organization (DAO).

[[Page 79384]]

(n) New Requirement of This AD: Terminating Action

    For airplanes on which any incorrectly oriented fastener, and no 
fractured or missing fastener, was detected during any inspection 
required by paragraph (g), (h)(2), (i), and (j)(1) of this AD: 
Within 24 months after the effective date of this AD, replace all 
forward and aft fasteners, regardless of condition or orientation, 
at WS 76.50 and WS 127.25, on affected wings, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraphs (k)(1) and (k)(2) of this AD, except as 
provided by paragraph (m) of this AD. Doing the replacements 
specified in this paragraph terminates the requirements of this AD. 
Doing the replacements specified in this paragraph terminates the 
requirements of paragraphs (g) and (j) of AD 2014-03-17, only for 
the airplane on which the replacement was done.

(o) Credit for Previous Actions

    This paragraph restates the provisions of paragraph (n) of AD 
2015-02-23, with new credit for paragraph (n) of this AD. This 
paragraph provides credit for actions required by paragraphs (g), 
(h), (i), and (n) of this AD, if those actions were performed before 
the effective date of this AD using the applicable service 
information identified in paragraphs (o)(1) through (o)(4) of this 
AD.
    (1) Bombardier Alert Service Bulletin A600-0763, including 
Appendixes 1 and 2, dated September 26, 2013, which was previously 
incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 
2014).
    (2) Bombardier Alert Service Bulletin A600-0763, Revision 01, 
dated February 26, 2014, including Appendixes 1 and 2, dated 
September 26, 2013, which is not incorporated by reference in this 
AD.
    (3) Bombardier Alert Service Bulletin A601-0627, including 
Appendixes 1 and 2, dated September 26, 2013, which was previously 
incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 
2014).
    (4) Bombardier Alert Service Bulletin A601-0627, Revision 01, 
dated February 26, 2014, including Appendixes 1 and 2, dated 
September 26, 2013, which is not incorporated by reference in this 
AD.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York 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.
    (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, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved 
by the DAO, the approval must include the DAO-authorized signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Emergency AD CF-2013-39R2, dated December 12, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-5593.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(4) and (r)(5) of this AD.

(r) 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.
    (3) The following service information was approved for IBR on 
February 18, 2015 (80 FR 5670, February 3, 2015).
    (i) Bombardier Alert Service Bulletin A600-0763, Revision 02, 
dated December 9, 2014, including Appendixes 1 and 2, dated 
September 26, 2013.
    (ii) Bombardier Alert Service Bulletin A601-0627, Revision 02, 
dated December 9, 2014, including Appendixes 1 and 2, dated 
September 26, 2013.
    (4) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; Widebody Customer Response Center 
North America toll-free telephone: 1-866-538-1247 or direct-dial 
telephone: 1-514-855-2999; fax 514-855-7401; email: 
ac.yul@aero.bombardier.com; Internet: https://www.bombardier.com.
    (5) 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.
    (6) 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 7, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25009 Filed 11-10-16; 8:45 am]
 BILLING CODE 4910-13-P

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