Airworthiness Directives; Bombardier, Inc., Airplanes, 17537-17540 [2017-06963]

Download as PDF Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations Maintenance Manual, Revision 23, dated June 20, 2013. (4) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, of section 26, Fuel Boost Pumps, of chapter 28, Fuel, of the Gulfstream G500 Maintenance Manual, Revision 23, dated June 20, 2013. (5) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, in table 20, 500 Flight Hours Scheduled Inspection Table, in section 05–20–00, of chapter 05, Time Limits/ Maintenance Checks, of the Gulfstream G550 Maintenance Manual, Revision 23, dated June 20, 2013. (6) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, of section 26, Fuel Boost Pumps, of chapter 28, Fuel, of the Gulfstream G550 Maintenance Manual, Revision 23, dated June 20, 2013. (7) Table 12, Certification Maintenance Requirements (CMR), in section 05–10–10, Airworthiness Limitations, of chapter 05, Time Limits/Maintenance Checks, of the Gulfstream V Maintenance Manual, Revision 43, dated February 15, 2015. (8) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, of section 28–26–01, Fuel Boost Pumps—Inspection/Check, of chapter 28, Fuel, of the Gulfstream V Maintenance Manual, Revision 43, dated February 15, 2015. (9) Table 12, Certification Maintenance Requirements (CMR), in section 05–10–10, Airworthiness Limitations, of chapter 05, Time Limits/Maintenance Checks, of the Gulfstream G500 Maintenance Manual, Revision 24, dated February 15, 2015. (10) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, of section 28–26–01, Fuel Boost Pumps—Inspection/Check, of chapter 28, Fuel, of the Gulfstream G500 Maintenance Manual, Revision 24, dated February 15, 2015. (11) Table 12, Certification Maintenance Requirements (CMR), in section 05–10–10, Airworthiness Limitations, of chapter 05, Time Limits/Maintenance Checks, of the Gulfstream G550 Maintenance Manual, Revision 24, dated February 15, 2015. (12) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, of section 28–26–01, Fuel Boost Pumps—Inspection/Check, of chapter 28, Fuel, of the Gulfstream G550 Maintenance Manual, Revision 24, dated February 15, 2015. pmangrum on DSK3GDR082PROD with RULES (l) No Alternative Actions or Intervals After accomplishing the revision required by paragraph (i) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance in accordance with the procedures specified in paragraph (n) of this AD. (m) Parts Installation Prohibition As of January 7, 2014 (the effective date of AD 2013–22–19), no person may install a fuel boost pump having Gulfstream P/N 1159SCP500–5 on any airplane. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if VerDate Sep<11>2014 15:14 Apr 11, 2017 Jkt 241001 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 manager of the ACO, send it to the attention of the person identified in paragraph (o)(1) of this AD. (2) 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. (3) AMOCs approved for AD 2013–22–19, are approved as AMOCs for the corresponding provisions of this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (n)(4)(i) and (n)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (o) Related Information (1) For more information about this AD, contact Ky Phan, Aerospace Engineer, Propulsion and Services Branch, ACE–118A, FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474– 5536; fax: 404–474–5606; email: ky.phan@ faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(5) and (p)(6) of this AD. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on May 17, 2017. (i) Gulfstream G500 Customer Bulletin 122, dated April 11, 2012. (ii) Gulfstream V Maintenance Manual, Revision 44, dated June 15, 2016: (A) Table 12, Certification Maintenance Requirements (CMR), in section 05–10–10, Airworthiness Limitations, of chapter 05, Time Limits/Maintenance Checks. (B) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, of section 28–26–01, Fuel Boost Pumps—Inspection/Check, of chapter 28, Fuel. (iii) Gulfstream G500 Maintenance Manual, Revision 25, dated June 15, 2016: (A) Table 12, Certification Maintenance Requirements (CMR), in section 05–10–10, Airworthiness Limitations, of chapter 05, Time Limits/Maintenance Checks. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 17537 (B) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, of Section 28–26–01, Fuel Boost Pumps—Inspection/Check, of chapter 28, Fuel. (iv) Gulfstream G550 Maintenance Manual, Revision 25, dated June 15, 2016: (A) Table 12, Certification Maintenance Requirements (CMR), in section 05–10–10, Airworthiness Limitations, of chapter 05, Time Limits/Maintenance Checks. (B) Task 28–26–01, Fuel Boost Pumps— Fuel Leak Check, of section 28–26–01, Fuel Boost Pumps—Inspection/Check, of chapter 28, Fuel. (4) The following service information was approved for IBR on January 7, 2014 (78 FR 72554, December 3, 2013). (i) Gulfstream G550 Customer Bulletin 122, dated April 11, 2012. (ii) Gulfstream V Customer Bulletin 197, dated April 11, 2012. (iii) General Electric Service Bulletin 31760–28–100, dated February 15, 2011. (iv) Triumph Service Bulletin SB–TAGV/ GVSP–28–JG0162, dated August 30, 2011. (5) For Gulfstream, Triumph Aerostructures, and General Electric Aviation service information identified in this AD, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone 800– 810–4853; fax 912 965–3520; email pubs@ gulfstream.com; Internet http:// www.gulfstream.com/product_support/ technical_pubs/pubs/index.htm. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 31, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–06962 Filed 4–11–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9299; Directorate Identifier 2016–NM–119–AD; Amendment 39–18851; AD 2017–08–02] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: E:\FR\FM\12APR1.SGM 12APR1 17538 ACTION: Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations Final rule. We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC–8–102, –103, and –106 airplanes; and Model DHC–8–200 and DHC–8–300 series airplanes. This AD was prompted by reports of incorrect installation of the auto-ignition system due to crossed wires at one of the splices in the autorelight system. This AD requires inspecting the auto-ignition system for correct wiring, and doing corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective May 17, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 17, 2017. ADDRESSES: For service information identified in this final rule, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375– 4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9299. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9299; 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 street 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: Norman Perenson, Aerospace Engineer, Propulsion and Services Branch, ANE– 173, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7337; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc., Model DHC–8–102, –103, and –106 airplanes; and Model DHC–8–200 and DHC–8–300 series airplanes. The NPRM published in the Federal Register on October 26, 2016 (81 FR 74360) (‘‘the NPRM’’). The NPRM was prompted by reports of incorrect installation of the autoignition system due to crossed wires at one of the splices in the auto-relight system. The NPRM proposed to require inspecting the auto-ignition system for correct wiring, and doing corrective actions if necessary. We are issuing this AD to detect and correct incorrect wiring of the auto-ignition system, which could result in inability to restart the engine in flight and consequent reduced controllability of the airplane. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–36, dated November 19, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., Model DHC–8–102, –103, and –106 airplanes; and Model DHC–8–200 and DHC–8–300 series airplanes. The MCAI states: There have been reports of incorrect installation of the auto-ignition system introduced by MS [ModSum] 8Q100813 of SB [Service Bulletin] 8–74–02, where wires crossed at one of the splices in the autorelight system. The incorrect wire installation may result in the inability to achieve an inflight engine relight when the ignition switch is selected in the AUTO position. Bombardier has issued SB 8–74–05 to introduce an inspection to check for correct wiring connection and rectification as required. This [Canadian] AD mandates incorporation of Bombardier SB 8–74–05. Corrective actions include reconnecting any incorrect wiring of the auto-ignition system and performing a functional test. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–9299. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. The Air Line Pilots Association, International (ALPA) supported the NPRM. Conclusion We reviewed the relevant data, considered the comment received, 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. Related Service Information Under 1 CFR Part 51 We reviewed Bombardier Service Bulletin 8–74–05, Revision B, dated April 14, 2014. This service information describes procedures for inspecting the auto-ignition system for correct wiring, and doing corrective actions that include rewiring if needed, followed by a functional test of the auto-ignition system. 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 88 airplanes of U.S. registry. We estimate the following costs to comply with this AD: pmangrum on DSK3GDR082PROD with RULES ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection ........................................................ 1 work-hour × $85 per hour = $85 ................. $0 $85 $7,480 VerDate Sep<11>2014 16:44 Apr 11, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\12APR1.SGM 12APR1 Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations In addition, we estimate that any necessary corrective actions will take about 2 work-hours, for a cost of $170 per product. We have no way of determining the number of aircraft that might need these actions. Authority for This Rulemaking 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. pmangrum on DSK3GDR082PROD with RULES List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: VerDate Sep<11>2014 15:14 Apr 11, 2017 Jkt 241001 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 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. 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. Adoption of the Amendment PART 39—AIRWORTHINESS DIRECTIVES [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2017–08–02 Bombardier, Inc.: Amendment 39–18851; FAA–2016–9299; Directorate Identifier 2016–NM–119–AD. (a) Effective Date This AD is effective May 17, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc., airplanes identified in paragraphs (c) (1), (c) (2), and (c) (3) of this AD, certificated in any category, serial numbers 003 through 672 inclusive, on which Bombardier ModSum 8Q100813 or Bombardier Service Bulletin 8– 74–02 is incorporated. (1) Model DHC–8–102, –103, and –106 airplanes. (2) Model DHC–8–201 and –202 airplanes. (3) Model DHC–8–301, –311, and –315 airplanes. (d) Subject Air Transport Association (ATA) of America Code 74, Ignition. (e) Reason This AD was prompted by reports of incorrect installation of the auto-ignition system due to crossed wires at one of the splices in the auto-relight system. We are issuing this AD to detect and correct incorrect wiring of the auto-ignition system, which could result in inability to restart the engine in flight and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Actions Within 2,000 flight hours or 12 months after the effective date of this AD, whichever occurs first: Inspect the auto-ignition system for correct wiring and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–74–05, Revision B, dated April 14, 2014. All applicable corrective actions must be done before further flight. (h) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–74–05, dated July 12, 2013; or Revision A, dated January 27, 2014. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 17539 (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the New York ACO, send it to the attention of the person identified in paragraph (j) (2) of this AD. 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 Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–36, dated November 19, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–9299. (2) For more information about this AD, contact the Program Manager, Continuing Operational Safety, New York ACO, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k) (3) and (k) (4) of this AD. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 8–74–05, Revision B, dated April 14, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the E:\FR\FM\12APR1.SGM 12APR1 17540 Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 31, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–06963 Filed 4–11–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6897; Directorate Identifier 2015–NM–187–AD; Amendment 39–18853; AD 2017–08–04] 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) 2015–03– 01, for all Bombardier, Inc. Model CL– 600–2B19 (Regional Jet Series 100 & 440) airplanes. AD 2015–03–01 required installing additional attaching hardware on the left and right engine fan cowl access panels and the nacelle attaching structures. This new AD requires weight and balance data to be included in the Weight and Balance Manual for certain modified airplanes. This new AD also requires the weight and balance data to be used in order to calculate the center of gravity for affected airplanes. This AD was prompted by updates to the weight and balance data needed to calculate the center of gravity for affected airplanes. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective May 17, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 17, 2017. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of March 17, 2015 (80 FR 7298, February 10, 2015). ADDRESSES: For service information identified in this final rule, contact ˆ Bombardier, Inc., 400 Cote Vertu Road ´ West, Dorval, Quebec H4S 1Y9, Canada; pmangrum on DSK3GDR082PROD with RULES SUMMARY: VerDate Sep<11>2014 15:14 Apr 11, 2017 Jkt 241001 telephone 514–855–5000; fax 514–855– 7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6897. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6897; 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 2015–03–01, Amendment 39–18097 (80 FR 7298, February 10, 2015) (‘‘AD 2015–03–01’’). AD 2015–03–01 applied to all Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. The NPRM published in the Federal Register on June 8, 2016 (81 FR 36813). The NPRM was prompted by updates to the weight and balance data needed to calculate the center of gravity for affected airplanes. The NPRM proposed to continue to require installing additional attaching hardware on the left and right engine fan cowl access panels and the nacelle attaching structures. The NPRM also proposed to require weight and balance data to be included in the Weight and Balance Manual and applicable logbooks for certain modified airplanes. We are PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 issuing this AD to prevent damage to the fuselage and flight control surfaces from dislodged engine fan cowl access panels, and prevent incorrect weight and balance calculations. Incorrect weight and balance calculations may shift the center of gravity beyond approved design parameters and affect in-flight control, which could endanger passengers and crew. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–20R1, dated August 12, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Bombardier, Inc. Model CL–600– 2B19 (Regional Jet Series 100 & 440) airplanes. The MCAI states: There have been a number of engine fan cowl panel dislodgement incidents reported on the Bombardier CL–600–2B19 aeroplane fleet. The dislodged panels may cause damage to the fuselage and flight control surfaces of the aeroplane. Also, the debris from a dislodged panel may result in runway contamination and has the potential of causing injury on the ground. Although the majority of the subject panel dislodgements were reported on the first or second flight after an engine maintenance task was performed that required removal and reinstallation of the subject panels, the frequency of the dislodgements indicates that the existing attachment design is prone to human (maintenance) error. In order to mitigate the potential safety hazard of the subject panel dislodgement, Bombardier had issued Service Bulletin (SB) 601R–71–034 to install additional fasteners for the attachment of the engine fan cowl panels to the nacelle’s structure. Compliance of the above SB was mandated by the original issue of [Canadian] AD CF–2014–20 dated 9 July 2014 [which corresponded to FAA AD 2015–03–01]. Bombardier has now revised the SB 601R– 71–034 (to Revision C) requiring weight and balance data to be included in the Weight and Balance manual for aeroplanes modified per the subject SB. This revised [Canadian] AD is issued to mandate compliance with SB 601R–71–034, Rev C. Required actions also include the retained actions of modifying the engine fan cowl access panel. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6897. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA’s response. E:\FR\FM\12APR1.SGM 12APR1

Agencies

[Federal Register Volume 82, Number 69 (Wednesday, April 12, 2017)]
[Rules and Regulations]
[Pages 17537-17540]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06963]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9299; Directorate Identifier 2016-NM-119-AD; 
Amendment 39-18851; AD 2017-08-02]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

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

[[Page 17538]]


ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes; and Model 
DHC-8-200 and DHC-8-300 series airplanes. This AD was prompted by 
reports of incorrect installation of the auto-ignition system due to 
crossed wires at one of the splices in the auto-relight system. This AD 
requires inspecting the auto-ignition system for correct wiring, and 
doing corrective actions if necessary. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective May 17, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 17, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221. It is also available on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-9299.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9299; 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 street 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: Norman Perenson, Aerospace Engineer, 
Propulsion and Services Branch, ANE-173, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7337; fax 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Bombardier, Inc., 
Model DHC-8-102, -103, and -106 airplanes; and Model DHC-8-200 and DHC-
8-300 series airplanes. The NPRM published in the Federal Register on 
October 26, 2016 (81 FR 74360) (``the NPRM''). The NPRM was prompted by 
reports of incorrect installation of the auto-ignition system due to 
crossed wires at one of the splices in the auto-relight system. The 
NPRM proposed to require inspecting the auto-ignition system for 
correct wiring, and doing corrective actions if necessary. We are 
issuing this AD to detect and correct incorrect wiring of the auto-
ignition system, which could result in inability to restart the engine 
in flight and consequent reduced controllability of the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-36, dated November 19, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Bombardier, Inc., Model DHC-8-
102, -103, and -106 airplanes; and Model DHC-8-200 and DHC-8-300 series 
airplanes. The MCAI states:

    There have been reports of incorrect installation of the auto-
ignition system introduced by MS [ModSum] 8Q100813 of SB [Service 
Bulletin] 8-74-02, where wires crossed at one of the splices in the 
auto-relight system. The incorrect wire installation may result in 
the inability to achieve an in-flight engine relight when the 
ignition switch is selected in the AUTO position.
    Bombardier has issued SB 8-74-05 to introduce an inspection to 
check for correct wiring connection and rectification as required. 
This [Canadian] AD mandates incorporation of Bombardier SB 8-74-05.

    Corrective actions include reconnecting any incorrect wiring of the 
auto-ignition system and performing a functional test. You may examine 
the MCAI in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2016-9299.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The Air Line Pilots 
Association, International (ALPA) supported the NPRM.

Conclusion

    We reviewed the relevant data, considered the comment received, 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.

Related Service Information Under 1 CFR Part 51

    We reviewed Bombardier Service Bulletin 8-74-05, Revision B, dated 
April 14, 2014. This service information describes procedures for 
inspecting the auto-ignition system for correct wiring, and doing 
corrective actions that include rewiring if needed, followed by a 
functional test of the auto-ignition system. 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 88 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection..........................  1 work-hour x $85 per                $0              $85           $7,480
                                       hour = $85.
----------------------------------------------------------------------------------------------------------------


[[Page 17539]]

    In addition, we estimate that any necessary corrective actions will 
take about 2 work-hours, for a cost of $170 per product. We have no way 
of determining the number of aircraft that might need these actions.

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 adding the following new airworthiness 
directive (AD):

2017-08-02 Bombardier, Inc.: Amendment 39-18851; FAA-2016-9299; 
Directorate Identifier 2016-NM-119-AD.

(a) Effective Date

    This AD is effective May 17, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc., airplanes identified in 
paragraphs (c) (1), (c) (2), and (c) (3) of this AD, certificated in 
any category, serial numbers 003 through 672 inclusive, on which 
Bombardier ModSum 8Q100813 or Bombardier Service Bulletin 8-74-02 is 
incorporated.
    (1) Model DHC-8-102, -103, and -106 airplanes.
    (2) Model DHC-8-201 and -202 airplanes.
    (3) Model DHC-8-301, -311, and -315 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 74, Ignition.

(e) Reason

    This AD was prompted by reports of incorrect installation of the 
auto-ignition system due to crossed wires at one of the splices in 
the auto-relight system. We are issuing this AD to detect and 
correct incorrect wiring of the auto-ignition system, which could 
result in inability to restart the engine in flight and consequent 
reduced controllability of the airplane.

(f) Compliance

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

(g) Inspection and Corrective Actions

    Within 2,000 flight hours or 12 months after the effective date 
of this AD, whichever occurs first: Inspect the auto-ignition system 
for correct wiring and do all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-74-05, Revision B, dated April 14, 2014. All 
applicable corrective actions must be done before further flight.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Bombardier Service Bulletin 8-74-05, 
dated July 12, 2013; or Revision A, dated January 27, 2014.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), ANE-170, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the New York ACO, send it to the 
attention of the person identified in paragraph (j) (2) of this AD. 
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 Transport Canada Civil Aviation (TCCA); or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2013-36, dated November 
19, 2013, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-9299.
    (2) For more information about this AD, contact the Program 
Manager, Continuing Operational Safety, New York ACO, FAA, 1600 
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7300; fax 516-794-5531.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k) (3) and (k) (4) of this AD.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Bombardier Service Bulletin 8-74-05, Revision B, dated April 
14, 2014.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the

[[Page 17540]]

National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 31, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-06963 Filed 4-11-17; 8:45 am]
 BILLING CODE 4910-13-P