Airworthiness Directives; Bombardier, Inc. Airplanes, 23202-23206 [2016-08960]

Download as PDF 23202 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules (2) Replace the current electrical cable with the new standard one in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–92–1052, dated December 5, 2007. During the replacement, ensure that the anti-chafing protection specified in Airbus Service Bulletin A320– 92–1049, as required by paragraph (h)(1) of this AD, remains in place. (i) Additional Modification For airplanes on which the installation specified in Airbus Service Bulletin A320– 24–1062, Revision 05, dated June 27, 2002, has been done: Within 60 months after the effective date of this AD, install insulators and cable ties, in accordance with ‘‘Modification—Additional Work (Introduced at Revision No. 06)’’ of the Accomplishment Instructions of Airbus Service Bulletin A320– 24–1062, Revision 07, dated November 28, 2011. Lhorne on DSK5TPTVN1PROD with PROPOSALS (j) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–24–1062, Revision 06, dated June 26, 2007, which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–92–1049, dated July 23, 2007, which is not incorporated by reference in this AD. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0198, dated September 5, 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–2016–5591. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. 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. Issued in Renton, Washington, on April 4, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–08953 Filed 4–19–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5593; Directorate Identifier 2015–NM–184–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede 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 currently requires 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 preamble to AD 2015–02–23 explains that we consider the requirements interim action and are considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and that replacement of the fasteners is necessary. This proposed AD would require terminating action to replace the fasteners on the inboard flap SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 hinge-box forward fittings on both wings. We are proposing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in detachment of the flap hingebox and the flap surface, and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by June 6, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Bombardier, Inc., ˆ 400 Cote-Vertu Road West, Dorval, ´ Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You may 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 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; fax 516–794–5531. SUPPLEMENTARY INFORMATION: E:\FR\FM\20APP1.SGM 20APP1 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–5593; Directorate Identifier 2015–NM–184–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Lhorne on DSK5TPTVN1PROD with PROPOSALS Discussion On January 20, 2015, we issued AD 2015–02–23, Amendment 39–18092 (80 FR 5670, February 3, 2015) (‘‘AD 2015– 02–23’’). AD 2015–02–23 requires actions intended to address an unsafe condition on 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 corresponds to Canadian Emergency Airworthiness Directive 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 explains that we consider the requirements interim action and are considering further rulemaking. We have now determined that further rulemaking is indeed necessary and that, instead of continuing repetitive inspections, replacement of the incorrectly oriented fasteners is necessary. This proposed AD follows from that determination. This proposed AD would require terminating action to replace the fasteners on the inboard flap hinge-box forward fittings on affected wings. The repetitive inspections can only detect if a fastener head has fractured and sheared off. For incorrectly oriented fasteners, it is not possible to detect whether a crack has already initiated and propagated. The fastener fracture speed is unpredictable due to the variability in the quality of the hole preparation prior to fastener installation and whether there was any VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 misalignment in the installation of the fasteners. The failure of two fasteners could result in the loss of the flap attachment, causing flap asymmetry and consequent reduced controllability of the airplane. We are proposing this AD to detect and correct 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. Related Service Information Under 1 CFR Part 51 Bombardier has issued Alert Service Bulletins A600–0763, Revision 02, dated December 9, 2014, including Appendices 1 and 2, dated September 26, 2013; and A601–0627, Revision 02, dated December 9, 2014, including Appendices 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. 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. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type designs. Clarification of Intent of the MCAI Paragraph C. of Canadian Emergency AD CF–2013–39R2, dated December 12, 2014, specifies to do the replacement on ‘‘both’’ wings. We have clarified with TCCA that the intent of paragraph C. of Canadian Emergency AD CF–2013– 39R2, dated December 12, 2014, is that for airplanes on which any incorrectly oriented fastener, and no fractured or missing fastener, was detected, the replacement only needs to be done on the affected wing on which incorrectly oriented fasteners were found but none were found to be fractured. The replacement of all forward and aft fasteners, regardless of condition or orientation, at wing station (WS) 76.50 PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 23203 and WS 127.25, on the affected wings, constitutes terminating action. Fasteners that have cracks or fractures were already addressed by the requirements of AD 2015–02–13, which is restated in this proposed AD. Costs of Compliance We estimate that this proposed AD affects 120 airplanes of U.S. registry. The actions required by AD 2015–02– 23, and retained in this proposed AD, take about 1 work-hour per product, at an average labor rate of $85 per workhour. 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 proposed 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 proposed 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 proposed 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. E:\FR\FM\20APP1.SGM 20APP1 23204 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 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. (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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (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 Appendices 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 Appendices 1 and 2, dated September 26, 2013. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–02–23, Amendment 39–18092 (80 FR 5670, February 3, 2015), and adding the following new AD: ■ Bombardier, Inc.: Docket No. FAA–2016– 5593; Directorate Identifier 2015–NM– 184–AD. Lhorne on DSK5TPTVN1PROD with PROPOSALS (a) Comments Due Date We must receive comments by June 6, 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. VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 (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 detect and correct 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. (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 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 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 paragraph (h)(3), (k), or (n) of this AD is 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 Appendices 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 Appendices 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 E:\FR\FM\20APP1.SGM 20APP1 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules Lhorne on DSK5TPTVN1PROD with PROPOSALS 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 Appendices 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 Appendices 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 Appendices 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 Appendices 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 VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 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 Appendices 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 Appendices 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 Appendices 1 and 2, dated September 26, 2013; and Bombardier Alert Service Bulletin A601– 0627, Revision 02, dated December 9, 2014, including Appendices 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). (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 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 23205 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 Appendices 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 Appendices 1 and 2, dated September 26, 2013, which is not incorporated by reference in this AD. (3) Bombardier Alert Service Bulletin A601–0627, including Appendices 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 Appendices 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. 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 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 Airworthiness Directive CF– 2013–39R2, dated December 12, 2014, for related information. This MCAI may be E:\FR\FM\20APP1.SGM 20APP1 23206 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–5593. (2) 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 https:// www.bombardier.com. 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. Issued in Renton, Washington, on April 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–08960 Filed 4–19–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5464; Directorate Identifier 2015–NM–097–AD] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2011–10– 01, for all Dassault Aviation Model FALCON 7X airplanes. AD 2011–10–01 currently requires repetitive functional tests of the ram air turbine (RAT) heater and repair if necessary. Since we issued AD 2011–10–01, we received a revision of an airworthiness limitations items (ALI) document, which introduces new and more restrictive maintenance requirements and airworthiness limitations for airplane structures and systems. This proposed AD would require revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. We are proposing this AD to prevent reduced structural integrity and reduced control of these airplanes due to the failure of system components. DATES: We must receive comments on this proposed AD by June 6, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. Lhorne on DSK5TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone: 201–440–6700; Internet: https://www.dassaultfalcon.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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5464; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–5464; Directorate Identifier 2015–NM–097–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On April 20, 2011, we issued AD 2011–10–01, Amendment 39–16682 (76 FR 25535, May 5, 2011). AD 2011–10– 01 requires actions intended to address an unsafe condition on all Dassault Aviation Model FALCON 7X airplanes. Since we issued AD 2011–10–01, we received a revision of an ALI document, Chapter 5–40–00, Airworthiness Limitations, DGT 107838, Revision 4, dated February 2, 2015, of the Dassault Falcon 7X Maintenance Manual, which introduces new and more restrictive maintenance requirements and airworthiness limitations. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive AD 2015–0095, dated May 29, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Dassault Aviation FALCON 7X airplanes. The MCAI states: The airworthiness limitations and maintenance requirements for the FALCON 7X type design are included in Dassault Aviation FALCON 7X Aircraft Maintenance Manual (AMM) chapter 5–40 and are approved by EASA. To ensure accomplishment of the maintenance tasks, and implementation of the airworthiness limitations, as specified in Dassault Aviation FALCON 7X AMM chapter 5–40 original issue, including temporary revision (TR) TR– 01, EASA issued AD 2008–0221 [https:// ad.easa.europa.eu/ad/2008-0221]. Since that [EASA] AD was issued, Dassault Aviation issued revision 4 of the FALCON 7X AMM chapter 5–40, which introduces new and more restrictive maintenance requirements and/or airworthiness limitations. Dassault Aviation AMM chapter 5–40 revision 4 contains, among others, the following changes: —Fatigue and Damage tolerance airworthiness limitations, —Miscellaneous Certification Maintenance Requirements and Airworthiness Limitation Items, —Periodic restoration of the DC generators (this action was required by EASA AD 2009–0254) [https://ad.easa.europa.eu/ad/ 2009-0254], —Functional test of the Ram Air Turbine heater (this action was required by EASA AD 2010–0033) [https://ad.easa.europa.eu/ ad/2010-0233] [which corresponds to FAA AD 2011–10–01, Amendment 39–16682 (76 FR 25535, May 5, 2011)], E:\FR\FM\20APP1.SGM 20APP1

Agencies

[Federal Register Volume 81, Number 76 (Wednesday, April 20, 2016)]
[Proposed Rules]
[Pages 23202-23206]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08960]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede 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 currently requires 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 preamble to AD 2015-02-23 explains that we consider the 
requirements interim action and are considering further rulemaking. We 
now have determined that further rulemaking is indeed necessary, and 
that replacement of the fasteners is necessary. This proposed AD would 
require terminating action to replace the fasteners on the inboard flap 
hinge-box forward fittings on both wings. We are proposing this AD to 
detect and correct 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: We must receive comments on this proposed AD by June 6, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 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.

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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7329; fax 516-794-5531.

SUPPLEMENTARY INFORMATION:

[[Page 23203]]

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-5593; 
Directorate Identifier 2015-NM-184-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On January 20, 2015, we issued AD 2015-02-23, Amendment 39-18092 
(80 FR 5670, February 3, 2015) (``AD 2015-02-23''). AD 2015-02-23 
requires actions intended to address an unsafe condition on 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 corresponds to Canadian Emergency Airworthiness Directive 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 explains that we consider the 
requirements interim action and are considering further rulemaking. We 
have now determined that further rulemaking is indeed necessary and 
that, instead of continuing repetitive inspections, replacement of the 
incorrectly oriented fasteners is necessary. This proposed AD follows 
from that determination. This proposed AD would require terminating 
action to replace the fasteners on the inboard flap hinge-box forward 
fittings on affected wings.
    The repetitive inspections can only detect if a fastener head has 
fractured and sheared off. For incorrectly oriented fasteners, it is 
not possible to detect whether a crack has already initiated and 
propagated. The fastener fracture speed is unpredictable due to the 
variability in the quality of the hole preparation prior to fastener 
installation and whether there was any misalignment in the installation 
of the fasteners. The failure of two fasteners could result in the loss 
of the flap attachment, causing flap asymmetry and consequent reduced 
controllability of the airplane.
    We are proposing this AD to detect and correct 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.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Alert Service Bulletins A600-0763, Revision 
02, dated December 9, 2014, including Appendices 1 and 2, dated 
September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014, 
including Appendices 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. 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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type designs.

Clarification of Intent of the MCAI

    Paragraph C. of Canadian Emergency AD CF-2013-39R2, dated December 
12, 2014, specifies to do the replacement on ``both'' wings. We have 
clarified with TCCA that the intent of paragraph C. of Canadian 
Emergency AD CF-2013-39R2, dated December 12, 2014, is that for 
airplanes on which any incorrectly oriented fastener, and no fractured 
or missing fastener, was detected, the replacement only needs to be 
done on the affected wing on which incorrectly oriented fasteners were 
found but none were found to be fractured.
    The replacement of all forward and aft fasteners, regardless of 
condition or orientation, at wing station (WS) 76.50 and WS 127.25, on 
the affected wings, constitutes terminating action. Fasteners that have 
cracks or fractures were already addressed by the requirements of AD 
2015-02-13, which is restated in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 120 airplanes of U.S. 
registry.
    The actions required by AD 2015-02-23, and retained in this 
proposed 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 proposed 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 proposed 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 proposed 
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.

[[Page 23204]]

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    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.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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:

Bombardier, Inc.: Docket No. FAA-2016-5593; Directorate Identifier 
2015-NM-184-AD.

(a) Comments Due Date

    We must receive comments by June 6, 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 detect and correct 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 Appendices 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 Appendices 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 paragraph (h)(3), (k), or (n) of this AD 
is 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 Appendices 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 Appendices 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

[[Page 23205]]

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 Appendices 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 Appendices 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 Appendices 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 Appendices 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 Appendices 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 Appendices 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 Appendices 
1 and 2, dated September 26, 2013; and Bombardier Alert Service 
Bulletin A601-0627, Revision 02, dated December 9, 2014, including 
Appendices 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).

(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 
Appendices 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 Appendices 1 and 2, dated 
September 26, 2013, which is not incorporated by reference in this 
AD.
    (3) Bombardier Alert Service Bulletin A601-0627, including 
Appendices 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 Appendices 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. 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 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 Airworthiness Directive CF-2013-39R2, 
dated December 12, 2014, for related information. This MCAI may be

[[Page 23206]]

found in the AD docket on the Internet at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2016-5593.
    (2) 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 https://www.bombardier.com. 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.

    Issued in Renton, Washington, on April 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08960 Filed 4-19-16; 8:45 am]
 BILLING CODE 4910-13-P
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