Airworthiness Directives; Bombardier, Inc. Airplanes, 89367-89371 [2016-28597]

Download as PDF Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations agency to take corrective action. OPM may suspend or revoke a delegation agreement established under 5 U.S.C. 1104(a)(2) at any time if it determines that the agency is not adhering to the provisions of the agreement. OPM may suspend or withdraw any authority granted under this chapter to an agency, including any authority granted by delegation agreement, when OPM finds that the agency has not complied with qualification standards OPM has issued, instructions OPM has published, or the regulations in this chapter of the regulation. OPM also may suspend or withdraw these authorities when it determines that doing so is in the interest of the civil service for any other reason. ■ 3. Subpart C is revised to read as follows: Subpart C—Employee Surveys Sec. 250.301 Definitions. 250.302 Survey requirements. 250.303 Availability of results. Subpart C—Employee Surveys Authority: 5 U.S.C. 105; 5 U.S.C. 7101 note; Public Law 108–136 § 250.301 Definitions. Agency means an Executive agency, as defined in 5 U.S.C. 105. § 250.302 89367 Survey requirements. (a) Each executive agency must conduct an annual survey of its employees to assess topics outlined in the National Defense Authorization Act for Fiscal Year 2004, Public Law 108– 136, sec. 1128, codified at 5 U.S.C. 7101. (1) Each executive agency may include additional survey questions unique to the agency in addition to the employee survey questions prescribed by OPM under paragraph (a)(2) of this section. (2) The 16 prescribed survey questions are listed in the following table: (i) Leadership and Management practices that contribute to agency performance My work unit has the job-relevant skills necessary to accomplish organizational goals. Managers communicate the goals of the organization. I believe the results of this survey will be used to make my agency a better place to work. (ii) Employee Satisfaction with— (A) .............................. (B) .............................. (C) .............................. (D) .............................. (E) .............................. mstockstill on DSK3G9T082PROD with RULES § 250.303 Leadership Policies and Practices: How satisfied are you with your involvement in decisions that affect your work? How satisfied are you with the information you receive from management on what is going on in your organization? Considering everything, how satisfied are you with your organization? Work Environment: The people I work with cooperate to get the job done. My workload is reasonable. Considering everything, how satisfied are you with your job? I can disclose a suspected violation of any law, rule or regulation without fear of reprisal. Rewards and Recognition: In my work unit, differences in performance are recognized in a meaningful way. How satisfied are you with the recognition you receive for doing a good job? Opportunities for professional development and growth: I am given a real opportunity to improve my skills in my organization. My talents are used well in the workplace. Opportunity to contribute to achieving organizational mission: I know how my work relates to the agency’s goals. I recommend my organization as a good place to work. Availability of results. (a) Each agency will make the results of its annual survey available to the public and post the results on its Web site unless the agency head determines that doing so would jeopardize or negatively impact national security. The posted survey results will include the following: (1) The agency’s evaluation of its survey results; (2) How the survey was conducted; (3) Description of the employee sample, unless all employees are surveyed; (4) The survey questions and response choices with the prescribed questions identified; (5) The number of employees surveyed and number of employees who completed the survey; and VerDate Sep<11>2014 16:18 Dec 09, 2016 Jkt 241001 (6) The number of respondents for each survey question and each response choice. (b) Data must be collected by December 31 of each calendar year. Each agency must post the beginning and ending dates of its employee survey and either the survey results described in paragraph (a) of this section, or a statement noting the decision not to post, no later than 120 days after the agency completes survey administration. OPM may extend this date under unusual circumstances. [FR Doc. 2016–29600 Filed 12–9–16; 8:45 am] BILLING CODE 6325–39–P PO 00000 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8178; Directorate Identifier 2015–NM–197–AD; Amendment 39–18721; AD 2016–24–04] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400 series airplanes. This AD was prompted SUMMARY: Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\12DER1.SGM 12DER1 89368 Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations by a determination by the manufacturer that shims might not have been installed between certain longerons and longeron joint fittings. This AD requires various repetitive and detailed visual inspections of the affected areas and corrective actions if necessary. This AD also provides terminating action for certain repetitive inspections. We are issuing this AD to address the unsafe condition on these products. This AD is effective January 17, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 17, 2017. DATES: 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– 8178. ADDRESSES: 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– 8178; 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. 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. mstockstill on DSK3G9T082PROD with RULES FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: VerDate Sep<11>2014 16:18 Dec 09, 2016 Jkt 241001 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–8–400 series airplanes. The NPRM published in the Federal Register on July 15, 2016 (81 FR 45995) (‘‘the NPRM’’). The NPRM was prompted by a determination by the manufacturer that shims might not have been installed between certain longerons and longeron joint fittings. The NPRM proposed to require repetitive inspections of the external surface of the fuselage skin panel for loose or working fasteners, and corrective action if necessary; a detailed visual inspection of the longeron joint fittings for the existence of shims and, if necessary, repetitive inspections of the longeron and the longeron joint fittings for any cracking, and corrective action if necessary. We are issuing this AD to detect and correct missing shims between the longerons and longeron joint fittings, which could result in a gapping condition and lead to stress corrosion cracking of the longeron joint fittings, and could adversely affect the structural integrity of the wing-tofuselage attachment joints. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2015–22, dated August 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model DHC–8–400 series airplanes. The MCAI states: The aeroplane manufacturer has determined that shims may not have been installed between the longerons and longeron joint fittings at fuselage station X373–380, stringers 7 on the left and right hand side, on certain aeroplanes. The missing shims could result in a gapping condition and could lead to stress corrosion cracking of the longeron joint fittings. Failure of the longeron joint fitting could compromise the structural integrity of the wing-to-fuselage attachment joint. This [Canadian] AD mandates inspections in the area of the longeron joint fittings. Corrective actions include replacing any loose or working fasteners (fasteners that show signs of wear, fatigue, or corrosion), repairing any structural damage, and replacing any cracked longeron or longeron with an amplitude of 50% or more of the calibration signal. 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– 8178. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Incorporate Revised Service Information Horizon Air requested that we incorporate Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016. We agree with the commenter’s request to incorporate the revised service information because Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016, is the latest revision. We have changed all service bulletin references in this final rule to Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016. Request To Provide Credit for Previous Actions Horizon Air requested that we add a paragraph addressing credit for previous actions. We agree. Since we have incorporated revised service information in this final rule, we agree to provide credit for required tasks performed before the effective date of this AD using Bombardier Service Bulletin 84–53–65, dated February 27, 2015. We have added a new paragraph (n) to this AD to provide credit for previous actions and redesignated subsequent paragraphs accordingly. Additional Changes to NPRM We have reformatted paragraph (l) in this AD to clarify the requirements. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016. The service information describes procedures for E:\FR\FM\12DER1.SGM 12DER1 Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations inspections of the external surface of the fuselage skin panel for loose or working fasteners; a detailed visual inspection of the longeron joint fittings for the existence of shims; high frequency eddy current inspections of the longeron and the longeron joint fittings for any cracking; and replacement of longeron fittings, shims, and 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. Costs of Compliance We estimate that this AD affects 76 airplanes of U.S. registry. We also estimate that it will take about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $12,920, or $170 per product. In addition, we estimate that any necessary follow-on actions will take about 3 work-hours for the inspection for missing shims, 9 work-hours for the replacement of longeron fittings and shims, and 1 work-hour for a reporting requirement; and would require parts costing $3,222; for a cost of up to $4,327 per product. We have no way of determining the number of aircraft that might need these actions. We have received no definitive data that will enable us to provide cost estimates for repair of loose or working fasteners or structural damage specified in this AD. mstockstill on DSK3G9T082PROD with RULES Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. VerDate Sep<11>2014 16:18 Dec 09, 2016 Jkt 241001 Authority for This Rulemaking § 39.13 Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. 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. 89369 ■ Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2016–24–04 Bombardier, Inc: Amendment 39–18721; Docket No. FAA–2016–8178; Directorate Identifier 2015–NM–197–AD. (a) Effective Date This AD is effective January 17, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers 4156 through 4453 inclusive, 4456, and 4457. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a determination by the manufacturer that shims might not have been installed between certain longerons and longeron joint fittings. We are issuing this AD to detect and correct missing shims between the longerons and longeron joint fittings, which could result in a gapping condition and lead to stress corrosion cracking of the longeron joint fittings, and could adversely affect the structural integrity of the wing-to-fuselage attachment joints. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of the External Surface of the Fuselage Skin Panels At the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, do a detailed visual inspection of the external surface of the fuselage skin panel for loose or working fasteners (fasteners that show signs of wear, fatigue, or corrosion) and structural damage, in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016. (1) For airplanes that have accumulated less than 10,000 total flight hours, or less than 5 years in service since new, as of the effective date of this AD: Prior to accumulating 12,000 total flight hours or 6 years in service since new, whichever occurs first. (2) For airplanes that have accumulated 10,000 total flight hours or more, or 5 years or more in service since new, as of the effective date of this AD: Within 2,000 flight hours or 12 months after the effective date of this AD, whichever occurs first. (h) Corrective Actions If any loose or working fastener or any structural damage is found during any inspection required by this AD: 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 E:\FR\FM\12DER1.SGM 12DER1 89370 Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations Bombardier, Inc.’s TCCA Design Approval Organization (DAO); and thereafter do the inspections required by paragraph (i) of this AD. Accomplishment of a repair in accordance with a method approved by the Manager, New York ACO, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO terminates the repetitive inspections required by paragraph (i) of this AD for the repaired area only. (i) Repetitive Detailed Visual Inspections Repeat the detailed visual inspection required by the introductory text to paragraph (g) of this AD at intervals not to exceed 12 months or 2,000 flight cycles, whichever occurs first after accomplishment of the most recent inspection, until the actions required by the introductory text to paragraph (j) of this AD are done. (j) Inspection for Missing Shims At the time specified in paragraph (j)(1) or (j)(2) of this AD, as applicable, do a detailed visual inspection of the longeron joint fittings for the existence of shims, in accordance with paragraph 3.C. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016. (1) For airplanes that have accumulated less than 10,000 total flight hours, or less than 5 years in service since new, as of the effective date of this AD: Prior to accumulating 18,000 total flight hours or 9 years in service since new, whichever occurs first. (2) For airplanes that have accumulated 10,000 total flight hours or more, or 5 years or more in service since new, as of the effective date of this AD: Within 8,000 flight hours or 4 years after the effective date of this AD, whichever occurs first; but not to exceed 30,000 total flight hours or 144 months in service since new, whichever occurs first. mstockstill on DSK3G9T082PROD with RULES (k) Airplanes With Installed Shims: No Further Action Required If the inspection required by the introductory text to paragraph (j) of this AD reveals that shims are installed in the longeron joint fittings, no further action is required by this AD. (l) Airplanes With Missing Shims: High Frequency Eddy Current (HFEC) Inspections and Corrective Actions If the inspection required by the introductory text to paragraph (j) of this AD reveals that any shim is missing from the longeron joint fittings: Before further flight, do a high frequency eddy current (HFEC) inspection of the longeron and the longeron joint fittings for any cracking, in accordance with paragraph 3.D. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016. (1) If any crack is found, or if any indication with an amplitude of 50% or more of the calibration signal is found, do the actions specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD. (i) Before further flight: Replace the longeron joint fittings, in accordance with paragraph 3.E. of the Accomplishment Instructions of Bombardier Service Bulletin VerDate Sep<11>2014 16:18 Dec 09, 2016 Jkt 241001 84–53–65, Revision A, dated February 22, 2016. (ii) At the applicable time specified in paragraph (l)(1)(ii)(A) or (l)(1)(ii)(B) of this AD: Report the inspection results to 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. (A) If the inspection was done on or after the effective date of this AD: Report within 30 days after that inspection. (B) If the inspection was done before the effective date of this AD: Report within 30 days after the effective date of this AD. (2) If no crack or indication with an amplitude of 50% or more of the calibration signal is found: Repeat the HFEC inspection required by the introductory text to paragraph (l) of this AD at intervals not to exceed 12,000 flight hours or 6 years, whichever occurs first after accomplishment of the most recent HFEC inspection, in accordance with paragraph 3.D. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016. (m) Terminating Action for Repetitive HFEC Inspections Replacement of the longeron joint fittings, in accordance with paragraph 3.E. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–65, Revision A, dated February 22, 2016, constitutes terminating action for the repetitive HFEC inspections required by paragraph (l)(2) of this AD. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g), (i), (j), (k), (l), and (m) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–53–65, dated February 27, 2015. (o) 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, FAA; or TCCA; or Bombardier, Inc.’s TCCA PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2015–22, dated August 3, 2015, 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– 2016–8178. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD. (q) 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 84–53–65, Revision A, dated February 22, 2016. (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 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. E:\FR\FM\12DER1.SGM 12DER1 Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations Issued in Renton, Washington, on November 17, 2016. Phil Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. 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– 5598. [FR Doc. 2016–28597 Filed 12–9–16; 8:45 am] 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– 5598; 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 (phone: 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: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6432; fax: 425– 917–6590; email: Bill.Ashforth@faa.gov. SUPPLEMENTARY INFORMATION: BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5598; Directorate Identifier 2016–NM–001–AD; Amendment 39–18735; AD 2016–25–09] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2012–22– 02 for certain The Boeing Company Model 747–400, –400D, and –400F series airplanes. AD 2012–22–02 required measuring the web at station (STA) 320 and, depending on findings, various inspections for cracks and missing fasteners, web and fastener replacement, and related investigative and corrective actions if necessary. This new AD requires, for certain airplanes, replacement of the web, including related investigative and corrective actions if necessary. This AD was prompted by a determination that there were no inspection or repair procedures included in AD 2012–22–02 for airplanes with a certain crown frame web thickness. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 17, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 17, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766–5680; Internet: https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, mstockstill on DSK3G9T082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:18 Dec 09, 2016 Jkt 241001 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012–22–02, Amendment 39–17238 (77 FR 69739, November 21, 2012) (‘‘AD 2012–22– 02’’). AD 2012–22–02 applied to certain The Boeing Company Model 747–400, –400D, and –400F series airplanes. The NPRM published in the Federal Register on April 28, 2016 (81 FR 25357) (‘‘the NPRM’’). The NPRM was prompted by a determination that there were no inspection or repair procedures included in AD 2012–22–02 for airplanes with a STA 320 crown frame web thickness less than 0.078 inch, or greater than or equal to 0.084 inch and less than or equal to 0.135 inch. The NPRM proposed to continue to require certain actions required by AD 2012– 22–02. The NPRM also proposed to require, for certain airplanes, replacement of the web, including related investigative and corrective actions if necessary. We are issuing this AD to prevent complete fracture of the crown frame assembly, and consequent damage to the skin. Such damage could result in in-flight decompression of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 89371 following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM United Airlines stated that it concurs with the NPRM. Request To Remove Redundant Requirements Boeing requested we change paragraph (i) of the proposed AD to remove redundant language. Boeing requested we remove the second half of the paragraph and subparagraphs (i)(1) and (i)(2) of the proposed AD because they include redundant requirements. Boeing also noted that the redundant requirements include an exception that does not apply to table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2784, Revision 2, dated August 20, 2015. We agree to revise paragraph (i) of this AD for the reasons provided by Boeing. We have revised paragraph (i) of this AD accordingly. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously, and 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747–53A2784, Revision 2, dated August 20, 2015. The service information describes procedures for various inspections for cracks and missing fasteners, web and fastener replacement, and related investigative and corrective actions, if necessary. 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 29 airplanes. We estimate the following costs to comply with this AD: E:\FR\FM\12DER1.SGM 12DER1

Agencies

[Federal Register Volume 81, Number 238 (Monday, December 12, 2016)]
[Rules and Regulations]
[Pages 89367-89371]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28597]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8178; Directorate Identifier 2015-NM-197-AD; 
Amendment 39-18721; AD 2016-24-04]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted

[[Page 89368]]

by a determination by the manufacturer that shims might not have been 
installed between certain longerons and longeron joint fittings. This 
AD requires various repetitive and detailed visual inspections of the 
affected areas and corrective actions if necessary. This AD also 
provides terminating action for certain repetitive inspections. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective January 17, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 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-2016-8178.

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-
8178; 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: 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 by adding an AD that would apply to certain Bombardier, Inc. 
Model DHC-8-400 series airplanes. The NPRM published in the Federal 
Register on July 15, 2016 (81 FR 45995) (``the NPRM''). The NPRM was 
prompted by a determination by the manufacturer that shims might not 
have been installed between certain longerons and longeron joint 
fittings. The NPRM proposed to require repetitive inspections of the 
external surface of the fuselage skin panel for loose or working 
fasteners, and corrective action if necessary; a detailed visual 
inspection of the longeron joint fittings for the existence of shims 
and, if necessary, repetitive inspections of the longeron and the 
longeron joint fittings for any cracking, and corrective action if 
necessary. We are issuing this AD to detect and correct missing shims 
between the longerons and longeron joint fittings, which could result 
in a gapping condition and lead to stress corrosion cracking of the 
longeron joint fittings, and could adversely affect the structural 
integrity of the wing-to-fuselage attachment joints.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2015-22, dated August 3, 2015 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Bombardier, Inc. Model DHC-8-400 series 
airplanes. The MCAI states:

    The aeroplane manufacturer has determined that shims may not 
have been installed between the longerons and longeron joint 
fittings at fuselage station X373-380, stringers 7 on the left and 
right hand side, on certain aeroplanes. The missing shims could 
result in a gapping condition and could lead to stress corrosion 
cracking of the longeron joint fittings.
    Failure of the longeron joint fitting could compromise the 
structural integrity of the wing-to-fuselage attachment joint.
    This [Canadian] AD mandates inspections in the area of the 
longeron joint fittings.

Corrective actions include replacing any loose or working fasteners 
(fasteners that show signs of wear, fatigue, or corrosion), repairing 
any structural damage, and replacing any cracked longeron or longeron 
with an amplitude of 50% or more of the calibration signal. 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-
8178.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Incorporate Revised Service Information

    Horizon Air requested that we incorporate Bombardier Service 
Bulletin 84-53-65, Revision A, dated February 22, 2016.
    We agree with the commenter's request to incorporate the revised 
service information because Bombardier Service Bulletin 84-53-65, 
Revision A, dated February 22, 2016, is the latest revision. We have 
changed all service bulletin references in this final rule to 
Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 
2016.

Request To Provide Credit for Previous Actions

    Horizon Air requested that we add a paragraph addressing credit for 
previous actions.
    We agree. Since we have incorporated revised service information in 
this final rule, we agree to provide credit for required tasks 
performed before the effective date of this AD using Bombardier Service 
Bulletin 84-53-65, dated February 27, 2015. We have added a new 
paragraph (n) to this AD to provide credit for previous actions and 
redesignated subsequent paragraphs accordingly.

Additional Changes to NPRM

    We have reformatted paragraph (l) in this AD to clarify the 
requirements.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    We reviewed Bombardier Service Bulletin 84-53-65, Revision A, dated 
February 22, 2016. The service information describes procedures for

[[Page 89369]]

inspections of the external surface of the fuselage skin panel for 
loose or working fasteners; a detailed visual inspection of the 
longeron joint fittings for the existence of shims; high frequency eddy 
current inspections of the longeron and the longeron joint fittings for 
any cracking; and replacement of longeron fittings, shims, and 
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.

Costs of Compliance

    We estimate that this AD affects 76 airplanes of U.S. registry.
    We also estimate that it will take about 2 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $12,920, or $170 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 3 work-hours for the inspection for missing shims, 9 work-
hours for the replacement of longeron fittings and shims, and 1 work-
hour for a reporting requirement; and would require parts costing 
$3,222; for a cost of up to $4,327 per product. We have no way of 
determining the number of aircraft that might need these actions. We 
have received no definitive data that will enable us to provide cost 
estimates for repair of loose or working fasteners or structural damage 
specified in this AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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):

2016-24-04 Bombardier, Inc: Amendment 39-18721; Docket No. FAA-2016-
8178; Directorate Identifier 2015-NM-197-AD.

(a) Effective Date

    This AD is effective January 17, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers 4156 
through 4453 inclusive, 4456, and 4457.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a determination by the manufacturer that 
shims might not have been installed between certain longerons and 
longeron joint fittings. We are issuing this AD to detect and 
correct missing shims between the longerons and longeron joint 
fittings, which could result in a gapping condition and lead to 
stress corrosion cracking of the longeron joint fittings, and could 
adversely affect the structural integrity of the wing-to-fuselage 
attachment joints.

(f) Compliance

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

(g) Inspection of the External Surface of the Fuselage Skin Panels

    At the time specified in paragraph (g)(1) or (g)(2) of this AD, 
as applicable, do a detailed visual inspection of the external 
surface of the fuselage skin panel for loose or working fasteners 
(fasteners that show signs of wear, fatigue, or corrosion) and 
structural damage, in accordance with paragraph 3.B. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, 
Revision A, dated February 22, 2016.
    (1) For airplanes that have accumulated less than 10,000 total 
flight hours, or less than 5 years in service since new, as of the 
effective date of this AD: Prior to accumulating 12,000 total flight 
hours or 6 years in service since new, whichever occurs first.
    (2) For airplanes that have accumulated 10,000 total flight 
hours or more, or 5 years or more in service since new, as of the 
effective date of this AD: Within 2,000 flight hours or 12 months 
after the effective date of this AD, whichever occurs first.

(h) Corrective Actions

    If any loose or working fastener or any structural damage is 
found during any inspection required by this AD: 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

[[Page 89370]]

Bombardier, Inc.'s TCCA Design Approval Organization (DAO); and 
thereafter do the inspections required by paragraph (i) of this AD. 
Accomplishment of a repair in accordance with a method approved by 
the Manager, New York ACO, FAA; or TCCA; or Bombardier, Inc.'s TCCA 
DAO terminates the repetitive inspections required by paragraph (i) 
of this AD for the repaired area only.

(i) Repetitive Detailed Visual Inspections

    Repeat the detailed visual inspection required by the 
introductory text to paragraph (g) of this AD at intervals not to 
exceed 12 months or 2,000 flight cycles, whichever occurs first 
after accomplishment of the most recent inspection, until the 
actions required by the introductory text to paragraph (j) of this 
AD are done.

(j) Inspection for Missing Shims

    At the time specified in paragraph (j)(1) or (j)(2) of this AD, 
as applicable, do a detailed visual inspection of the longeron joint 
fittings for the existence of shims, in accordance with paragraph 
3.C. of the Accomplishment Instructions of Bombardier Service 
Bulletin 84-53-65, Revision A, dated February 22, 2016.
    (1) For airplanes that have accumulated less than 10,000 total 
flight hours, or less than 5 years in service since new, as of the 
effective date of this AD: Prior to accumulating 18,000 total flight 
hours or 9 years in service since new, whichever occurs first.
    (2) For airplanes that have accumulated 10,000 total flight 
hours or more, or 5 years or more in service since new, as of the 
effective date of this AD: Within 8,000 flight hours or 4 years 
after the effective date of this AD, whichever occurs first; but not 
to exceed 30,000 total flight hours or 144 months in service since 
new, whichever occurs first.

(k) Airplanes With Installed Shims: No Further Action Required

    If the inspection required by the introductory text to paragraph 
(j) of this AD reveals that shims are installed in the longeron 
joint fittings, no further action is required by this AD.

(l) Airplanes With Missing Shims: High Frequency Eddy Current (HFEC) 
Inspections and Corrective Actions

    If the inspection required by the introductory text to paragraph 
(j) of this AD reveals that any shim is missing from the longeron 
joint fittings: Before further flight, do a high frequency eddy 
current (HFEC) inspection of the longeron and the longeron joint 
fittings for any cracking, in accordance with paragraph 3.D. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, 
Revision A, dated February 22, 2016.
    (1) If any crack is found, or if any indication with an 
amplitude of 50% or more of the calibration signal is found, do the 
actions specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD.
    (i) Before further flight: Replace the longeron joint fittings, 
in accordance with paragraph 3.E. of the Accomplishment Instructions 
of Bombardier Service Bulletin 84-53-65, Revision A, dated February 
22, 2016.
    (ii) At the applicable time specified in paragraph (l)(1)(ii)(A) 
or (l)(1)(ii)(B) of this AD: Report the inspection results to 
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.
    (A) If the inspection was done on or after the effective date of 
this AD: Report within 30 days after that inspection.
    (B) If the inspection was done before the effective date of this 
AD: Report within 30 days after the effective date of this AD.
    (2) If no crack or indication with an amplitude of 50% or more 
of the calibration signal is found: Repeat the HFEC inspection 
required by the introductory text to paragraph (l) of this AD at 
intervals not to exceed 12,000 flight hours or 6 years, whichever 
occurs first after accomplishment of the most recent HFEC 
inspection, in accordance with paragraph 3.D. of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-53-65, Revision A, 
dated February 22, 2016.

(m) Terminating Action for Repetitive HFEC Inspections

    Replacement of the longeron joint fittings, in accordance with 
paragraph 3.E. of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-53-65, Revision A, dated February 22, 2016, 
constitutes terminating action for the repetitive HFEC inspections 
required by paragraph (l)(2) of this AD.

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (i), (j), (k), (l), and (m) of this AD, if those 
actions were performed before the effective date of this AD using 
Bombardier Service Bulletin 84-53-65, dated February 27, 2015.

(o) 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, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved 
by the DAO, the approval must include the DAO-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2015-22, dated August 3, 
2015, 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-2016-8178.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(3) and (q)(4) of this AD.

(q) 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 84-53-65, Revision A, dated 
February 22, 2016.
    (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 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.


[[Page 89371]]


    Issued in Renton, Washington, on November 17, 2016.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-28597 Filed 12-9-16; 8:45 am]
 BILLING CODE 4910-13-P