July 14, 2020 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 35177-35181 [2020-12379]

Download as PDF Federal Register / Vol. 85, No. 111 / Tuesday, June 9, 2020 / Rules and Regulations (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2019–29, dated August 12, 2019, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–1076. (2) For more information about this AD, contact Darren Gassetto, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228– 7323; fax 516–794–5531; email 9-avs-nyacocos@faa.gov. (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 Challenger 300 Airplane Flight Manual, Publication No. CSP 100–1, Revision 56, dated July 8, 2019. (ii) Bombardier Challenger 350 Airplane Flight Manual, Publication No. CH 350 AFM, Revision 22, dated July 8, 2019. (3) For service information identified in this AD, contact Bombardier, Inc., 200 CoˆteVertu Road West, Dorval, Que´bec H4S 2A3, Canada; North America toll-free telephone 1– 866–538–1247 or direct-dial telephone 1– 514–855–2999; email ac.yul@ aero.bombardier.com; internet https:// www.bombardier.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (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, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on May 28, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–12374 Filed 6–8–20; 8:45 am] BILLING CODE 4910–13–P (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference VerDate Sep<11>2014 22:41 Jun 08, 2020 Jkt 250001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0099; Product Identifier 2019–NM–169–AD; Amendment 39–19917; AD 2020–11–13] RIN 2120–AA64 July 14, 2020 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2010–23– 04, which applied to all De Havilland Aircraft of Canada Limited Model DHC– 8–400 series airplanes. AD 2010–23–04 required repetitive detailed inspections of the nacelle attachment fittings for cracks, a conductivity inspection of the nacelle attachment fittings, and replacement if necessary. This AD continues to require these inspections and replacement if necessary, removes a certain inspection requirement for certain airplanes, and adds a new requirement to replace the rear spar fitting and nacelle attaching structure with a new nacelle attachment fitting. This AD was prompted by a determination that it is necessary to do a replacement with new nacelle attachment fittings. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 14, 2020. The Director of the Federal Register approved the incorporation by reference SUMMARY: E:\FR\FM\09JNR1.SGM 09JNR1 ER09JN20.000</GPH> jbell on DSKJLSW7X2PROD with RULES (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, 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 certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, New York ACO Branch, 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. 35177 35178 Federal Register / Vol. 85, No. 111 / Tuesday, June 9, 2020 / Rules and Regulations of certain publications listed in this AD as of July 14, 2020. ADDRESSES: For service information identified in this final rule, contact De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email thd@ dehavilland.com; internet https:// dehavilland.com. You may view this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0099. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0099; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The address for Docket Operations is 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: Andrea Jimenez, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7330; fax 516–794–5531; email 9-avs-nyaco-cos@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2010–30R2, dated July 30, 2019, (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all De Havilland Aircraft of Canada Limited (Type Certificate previously held by Bombardier, Inc.) Model DHC–8–400, –401, and –402 airplanes. You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0099. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2010–23–04, Amendment 39–16493 (75 FR 68174, November 5, 2010) (‘‘AD 2010–23–04’’). AD 2010–23–04 applied to all De Havilland Aircraft of Canada Limited Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on March 12, 2020 (85 FR 14423). The NPRM was prompted by reports of cracked nacelle attachment fittings, which a preliminary investigation determined to be caused by stress corrosion, and a determination that it is necessary to install new nacelle attachment fittings in order to address the unsafe condition. The NPRM proposed to continue to require repetitive detailed inspections of the nacelle attachment fittings for cracks, a conductivity inspection of the nacelle attachment fittings, and replacement if necessary. The NPRM also proposed to remove a certain inspection requirement for certain airplanes, and add a new requirement to replace the rear spar fitting and nacelle attaching structure with a new nacelle attachment fitting. The FAA is issuing this AD to address reports of cracked nacelle attachment fittings, which, if not detected and corrected, could compromise the structural integrity of the nacelle attachment fitting and possibly result in collapse of the landing gear. See the MCAI for additional background information. editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing 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 The FAA gave the public the opportunity to participate in developing this final rule. The FAA received no comments on the NPRM or on the determination of the cost to the public. Bombardier, Inc. has issued Service Bulletin 84–54–14, Revision K, dated August 7, 2018. This service bulletin describes procedures for a conductivity inspection of the nacelle attachment fittings, repetitive detailed inspections of the nacelle attachment fittings for cracks, and replacement of the fitting. Bombardier, Inc. has also issued Service Bulletin 84–54–16, Revision D, dated August 7, 2018. This service information describes procedures for replacing the rear spar nacelle attachment fitting and associated structure with a new nacelle attachment fitting, part number (P/N) 8Z9305. The replacement includes applicable related investigative and corrective actions. The related investigative actions include an inspection of the internal bore and external surface of the main landing gear yoke pins, the drag strut pins, and the stabilizer brace pins for signs of corrosion and damage; and an inspection of the inner bore and outer surface of the coat hangar pins for signs of corrosion and damage. The corrective actions include repair, rework, or replacement. Bombardier, Inc. has also issued Modification Summary Package IS4Q5400012, Revision B, dated July 11, 2012. This service information describes procedures for applying a fay sealant gasket to the rear spar access fitting access panel. 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. Conclusion Costs of Compliance The FAA reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor The FAA estimates that this AD affects 54 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: Comments jbell on DSKJLSW7X2PROD with RULES ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Parts cost Cost per product Retained actions from AD 2010– 23–04. New actions ................................. 3 work-hours × $85 per hour = $255. 320 work-hours × $85 per hour = $27,200. $0 ............................... $255 ........................... $13,770. Up to $104,739 .......... Up to $131,939 .......... Up to $7,124,706. VerDate Sep<11>2014 22:41 Jun 08, 2020 Jkt 250001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\09JNR1.SGM 09JNR1 Cost on U.S. operators Federal Register / Vol. 85, No. 111 / Tuesday, June 9, 2020 / Rules and Regulations 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. The FAA is 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 The FAA 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) Will not affect intrastate aviation in Alaska, and (3) 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: jbell on DSKJLSW7X2PROD with RULES ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2010–23–04, Amendment 39–16493 (75 ■ VerDate Sep<11>2014 22:41 Jun 08, 2020 Jkt 250001 FR 68174, November 5, 2010), and adding the following new AD: 2020–11–13 De Havilland Aircraft of Canada Limited (Type Certificate previously held by Bombardier, Inc.): Amendment 39–19917; Docket No. FAA–2020–0099; Product Identifier 2019–NM–169–AD. (a) Effective Date This AD is effective July 14, 2020. (b) Affected ADs This AD replaces AD 2010–23–04, Amendment 39–16493 (75 FR 68174, November 5, 2010) (‘‘AD 2010–23–04’’). (c) Applicability This AD applies to De Havilland Aircraft of Canada Limited (Type Certificate previously held by Bombardier, Inc.) Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers 4001 and subsequent. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/pylons. (e) Reason This AD was prompted by reports of cracked nacelle attachment fittings, which a preliminary investigation determined to be caused by stress corrosion. The FAA is issuing this AD to address this condition, which, if not detected and corrected, could compromise the structural integrity of the nacelle attachment fitting and possibly result in collapse of the landing gear. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Detailed and Conductivity Inspections and Replacement, With Revised Service Information and Revised Replacement Instructions This paragraph restates the requirements of paragraph (g) of AD 2010–23–04, with revised service information and revised replacement instructions. For airplanes having serial numbers 4001 through 4304 inclusive, 4314, and 4315: Within 100 flight hours after November 22, 2010 (the effective date of AD 2010–23–04), do a detailed inspection for cracking, and a conductivity inspection on each of the 4 nacelle attachment fittings, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018. Repeat the detailed inspection at intervals not to exceed 300 flight hours, except as provided by paragraph (i) of this AD. Accomplishing the replacement specified in paragraph (g)(1)(ii) or (g)(2)(ii)(B) of this AD terminates the inspections required by this paragraph. (1) If any nacelle attachment fitting is found cracked, before further flight, do the action specified in paragraph (g)(1)(i) or (ii) of this AD. As of the effective date of this AD, only the action specified in paragraph (g)(1)(ii) of this AD may be done. (i) Replace the fitting with a new fitting in accordance with paragraph (2) of Part A of PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 35179 the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018. (ii) Replace the rear spar nacelle attachment fitting and associated structure with a new nacelle attachment fitting, part number (P/N) 8Z9305, and do all applicable related investigative and corrective actions, in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–16 Revision D, dated August 7, 2018. Do all applicable related investigative and corrective actions before further flight. (2) If the conductivity of any test points on any fitting is found to be greater than 45.0 percent International Annealed Copper Standard (IACS) or if the conductivity of any test points on any fitting is found to be less than 38.0 percent IACS, do the actions required by paragraphs (g)(2)(i) and (ii) of this AD. (i) Within 24 hours after accomplishing the conductivity inspection specified in paragraph (g) of this AD, do a detailed inspection of the nacelle attachment fitting for cracking, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018, and repeat thereafter at intervals not to exceed 24 hours. If cracking is found, before further flight, replace the fitting with a new fitting in accordance with the requirements of paragraph (g)(2)(ii) of this AD. Replacement of the fitting terminates the daily detailed inspection requirements of this paragraph. (ii) Except as required by paragraph (g)(2)(i) of this AD: Within 300 flight hours after accomplishing the conductivity inspection specified in paragraph (g) of this AD, do the action specified in paragraph (g)(2)(ii)(A) or (B) of this AD. As of the effective date of this AD, only the action specified in paragraph (g)(2)(ii)(B) of this AD may be done. (A) Replace the fitting with a new fitting in accordance with paragraph (2) of Part A of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018. (B) Replace the rear spar nacelle attachment fitting and associated structure with a new nacelle attachment fitting, P/N 8Z9305, and do all applicable related investigative and corrective actions, in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–16 Revision D, dated August 7, 2018. Do all applicable related investigative and corrective actions before further flight. (h) Retained Inspections and Replacement, With Revised Service Information, Revised Affected Airplanes, and Revised Replacement Instructions This paragraph restates the requirements of paragraph (i) of AD 2010–23–04, with revised service information, revised affected airplanes, and revised replacement instructions. For airplanes having serial numbers 4305 through 4313 inclusive, and 4316 through 4380 inclusive, and airplanes that have replaced nacelle attachment fitting(s) with P/N 854146663: Within 1,200 E:\FR\FM\09JNR1.SGM 09JNR1 Federal Register / Vol. 85, No. 111 / Tuesday, June 9, 2020 / Rules and Regulations flight hours after November 22, 2010 (the effective date of AD 2010–23–04), do a detailed inspection for cracking on each of the 4 nacelle attachment fittings, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018. If any nacelle attachment fitting is found cracked, before further flight, do the action specified in paragraph (h)(1) or (2) of this AD. As of the effective date of this AD, only the action specified in paragraph (h)(2) of this AD may be done. Thereafter, repeat the detailed inspection at intervals not to exceed 300 flight hours, except as provided by paragraph (i) of this AD. Accomplishing the replacement specified in paragraph (h)(2) of this AD terminates the inspections required by this paragraph. (1) Replace the fitting with a new fitting in accordance with paragraph (2) of Part A of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018. (2) Replace the rear spar nacelle attachment fitting and associated structure with a new nacelle attachment fitting, P/N 8Z9305, and do all applicable related investigative and corrective actions, in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–16 Revision D, dated August 7, 2018. Do all applicable related investigative and corrective actions before further flight. (k) Retained Credit for Previous Actions (Inspections), With No Changes corresponding actions required by paragraphs (g) and (h) of this AD. This paragraph restates the credit provided in paragraph (l) of AD 2010–23–04, with no changes. Accomplishment of the inspections required by paragraphs (g) and (h) of this AD before November 22, 2010 (the effective date of AD 2010–23–04) in accordance with any Bombardier service bulletin identified in figure 1 to paragraphs (j) and (k) of this AD is acceptable for compliance with the (l) New Requirements of This AD: Modification of the Rear Spar Fitting and Nacelle Attaching Structure VerDate Sep<11>2014 22:41 Jun 08, 2020 Jkt 250001 (i) Retained Inspection Compliance Time, With Revised Service Information This paragraph restates the requirements of paragraph (j) of AD 2010–23–04, with revised service information. For any fitting that is replaced in accordance with paragraph (3) of Part A of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision J, dated September 17, 2010; or paragraph (2) of Part A of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018, as specified in paragraph (g) For airplanes with nacelle attachment fitting P/N 85414663: Unless already done as specified in paragraph (g)(1)(ii), (g)(2)(ii)(B), or (h)(2) of this AD: Within 8,000 flight hours or 48 months, whichever occurs first, from the effective date of this AD, replace the rear PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 or (h) of this AD: Within 1,200 flight hours after replacing the fitting, do a detailed inspection of that replaced fitting as specified in paragraph (g) or (h) of this AD, and repeat the detailed inspection thereafter at intervals not to exceed 300 flight hours. Accomplishing the replacement specified in paragraph (g)(1)(ii), (g)(2)(ii)(B), or (h)(2) of this AD terminates the inspections required by this paragraph. (j) Retained Credit for Previous Actions (Replacing the Fitting), With Revised Paragraph References This paragraph restates the credit provided in paragraph (k) of AD 2010–23–04, with revised paragraph references. Accomplishing the replacement of the nacelle fittings in accordance with any Bombardier service bulletin identified in figure 1 to paragraphs (j) and (k) of this AD before November 22, 2010 (the effective date of AD 2010–23–04) is also acceptable for compliance with the fitting replacements specified in paragraphs (g)(1)(i), (g)(2)(ii)(A), and (h)(1) of this AD. spar nacelle attachment fitting and associated structure with a new nacelle attachment fitting, P/N 8Z9305, and do all applicable related investigative and corrective actions, in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–16, Revision D, dated August 7, 2018. Do all applicable related investigative and corrective actions before further flight. E:\FR\FM\09JNR1.SGM 09JNR1 ER09JN20.001</GPH> jbell on DSKJLSW7X2PROD with RULES 35180 Federal Register / Vol. 85, No. 111 / Tuesday, June 9, 2020 / Rules and Regulations (m) New Credit for Previous Actions jbell on DSKJLSW7X2PROD with RULES (1) This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD that are identified in Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–54–14, Revision J, dated September 17, 2010, which was incorporated by reference in AD 2010– 23–04; except as provided by paragraph (p) of this AD. (2) This paragraph provides credit for accomplishing the replacement of the rear spar fitting and nacelle attaching structure required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (m)(2)(i) through (iii) of this AD. (i) Bombardier Service Bulletin 84–54–16, dated April 29, 2011. (ii) Bombardier Service Bulletin 84–54–16, Revision A, dated August 1, 2011. (iii) Bombardier Service Bulletin 84–54–16, Revision C, dated January 31, 2017. (3) This paragraph provides credit for accomplishing the replacement of the rear spar fitting and nacelle attaching structure required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–54–16, Revision B, dated October 6, 2016. Although Bombardier Service Bulletin 84–54–16, Revision B, dated October 6, 2016, incorrectly stated that airworthiness limitations (AWLs) or damage tolerance inspections (DTIs) are not affected, they are affected. Refer to the applicable AWLs for Post/Pre-Modification Summary (ModSum) 4–113697 and Bombardier Service Bulletin 84–54–16 in the existing maintenance requirements manual. (4) This paragraph provides credit for accomplishing the action identified in Bombardier Service Bulletin 84–54–14, Revision K, dated August 7, 2018, that are required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (m)(4)(i) through (iv) of this AD. (i) Bombardier Service Bulletin 84–54–15, dated August 20, 2010. (ii) Bombardier Service Bulletin 84–54–15, Revision A, dated October 25, 2010. (iii) Bombardier Service Bulletin 84–54–15, Revision B, dated February 2, 2017. (iv) Bombardier Service Bulletin 84–54–15, Revision C, dated August 7, 2018. (n) Terminating Action for Certain Actions in Paragraphs (g), (h), and (i) of This AD Accomplishing the modification of the rear spar fitting and nacelle attaching structure required by paragraph (l) of this AD terminates the repetitive inspection required by paragraphs (g), (h), and (i) of this AD for that airplane. (o) Parts Installation Limitations As of the effective date of this AD, no person may install a rear spar nacelle attachment fitting P/N 85414663 on any airplane. VerDate Sep<11>2014 22:41 Jun 08, 2020 Jkt 250001 (p) Credit for Alternative to Certain Credit Actions For airplanes on which Bombardier Service Bulletin 84–54–14, Revision J, dated September 17, 2010, was accomplished before the effective date of this AD: As an alternative to applying sealant to each fitting and access panel as specified in paragraph C.(1) of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–14, Revision J, dated September 17, 2010, the use of the instructions of Bombardier Modification Summary Package IS4Q5400012, Revision B, dated July 11, 2012, to apply sealant is also acceptable if accomplished before the effective date of this AD. (q) Other FAA AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, 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 certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. (i) 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. (ii) AMOCs approved previously for AD 2010–23–04, are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or De Havilland Aircraft of Canada Limited’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2010–30R2, dated July 30, 2019, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0099. (2) For more information about this AD, contact Andrea Jimenez, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7330; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (s)(3) and (4) of this AD. (s) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 35181 (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 84–54–14, Revision K, dated August 7, 2018. (ii) Bombardier Service Bulletin 84–54–16, Revision D, dated August 7, 2018. (iii) Bombardier Modification Summary Package IS4Q5400012, Revision B, dated July 11, 2012. (3) For service information identified in this AD, contact De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416– 375–4000; fax 416–375–4539; email thd@ dehavilland.com; internet https:// dehavilland.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (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, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on May 29, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–12379 Filed 6–8–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE INTERIOR National Park Service 36 CFR Part 13 [NPS–AKRO–27791; PPAKAKROZ5, PPMPRLE1Y.L00000] RIN 1024–AE38 Alaska; Hunting and Trapping in National Preserves National Park Service, Interior. Final rule. AGENCY: ACTION: The National Park Service amends its regulations for sport hunting and trapping in national preserves in Alaska. This rule removes regulatory provisions issued by the National Park Service in 2015 that prohibited certain sport hunting practices otherwise permitted by the State of Alaska. These changes are consistent with Federal law providing for State management of hunting and trapping in Alaska preserves. DATES: This rule is effective July 9, 2020. SUMMARY: E:\FR\FM\09JNR1.SGM 09JNR1

Agencies

[Federal Register Volume 85, Number 111 (Tuesday, June 9, 2020)]
[Rules and Regulations]
[Pages 35177-35181]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-12379]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0099; Product Identifier 2019-NM-169-AD; Amendment 
39-19917; AD 2020-11-13]
RIN 2120-AA64


July 14, 2020 Airworthiness Directives; De Havilland Aircraft of 
Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) 
Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2010-23-
04, which applied to all De Havilland Aircraft of Canada Limited Model 
DHC-8-400 series airplanes. AD 2010-23-04 required repetitive detailed 
inspections of the nacelle attachment fittings for cracks, a 
conductivity inspection of the nacelle attachment fittings, and 
replacement if necessary. This AD continues to require these 
inspections and replacement if necessary, removes a certain inspection 
requirement for certain airplanes, and adds a new requirement to 
replace the rear spar fitting and nacelle attaching structure with a 
new nacelle attachment fitting. This AD was prompted by a determination 
that it is necessary to do a replacement with new nacelle attachment 
fittings. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective July 14, 2020.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 35178]]

of certain publications listed in this AD as of July 14, 2020.

ADDRESSES: For service information identified in this final rule, 
contact De Havilland Aircraft of Canada Limited, Q-Series Technical 
Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; 
telephone 416-375-4000; fax 416-375-4539; email [email protected]; 
internet https://dehavilland.com. You may view this referenced service 
information at the FAA, Airworthiness Products Section, Operational 
Safety Branch, 2200 South 216th St., Des Moines, WA. For information on 
the availability of this material at the FAA, call 206-231-3195. It is 
also available on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0099.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0099; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, any comments received, and other information. The 
address for Docket Operations is 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: Andrea Jimenez, Aerospace Engineer, 
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart 
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7330; fax 516-
794-5531; email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2010-30R2, dated July 
30, 2019, (also referred to as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for all 
De Havilland Aircraft of Canada Limited (Type Certificate previously 
held by Bombardier, Inc.) Model DHC-8-400, -401, and -402 airplanes. 
You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0099.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2010-23-04, Amendment 39-16493 (75 FR 
68174, November 5, 2010) (``AD 2010-23-04''). AD 2010-23-04 applied to 
all De Havilland Aircraft of Canada Limited Model DHC-8-400 series 
airplanes. The NPRM published in the Federal Register on March 12, 2020 
(85 FR 14423). The NPRM was prompted by reports of cracked nacelle 
attachment fittings, which a preliminary investigation determined to be 
caused by stress corrosion, and a determination that it is necessary to 
install new nacelle attachment fittings in order to address the unsafe 
condition. The NPRM proposed to continue to require repetitive detailed 
inspections of the nacelle attachment fittings for cracks, a 
conductivity inspection of the nacelle attachment fittings, and 
replacement if necessary. The NPRM also proposed to remove a certain 
inspection requirement for certain airplanes, and add a new requirement 
to replace the rear spar fitting and nacelle attaching structure with a 
new nacelle attachment fitting. The FAA is issuing this AD to address 
reports of cracked nacelle attachment fittings, which, if not detected 
and corrected, could compromise the structural integrity of the nacelle 
attachment fitting and possibly result in collapse of the landing gear. 
See the MCAI for additional background information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
except for minor editorial changes. The FAA has determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing 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

    Bombardier, Inc. has issued Service Bulletin 84-54-14, Revision K, 
dated August 7, 2018. This service bulletin describes procedures for a 
conductivity inspection of the nacelle attachment fittings, repetitive 
detailed inspections of the nacelle attachment fittings for cracks, and 
replacement of the fitting.
    Bombardier, Inc. has also issued Service Bulletin 84-54-16, 
Revision D, dated August 7, 2018. This service information describes 
procedures for replacing the rear spar nacelle attachment fitting and 
associated structure with a new nacelle attachment fitting, part number 
(P/N) 8Z9305. The replacement includes applicable related investigative 
and corrective actions. The related investigative actions include an 
inspection of the internal bore and external surface of the main 
landing gear yoke pins, the drag strut pins, and the stabilizer brace 
pins for signs of corrosion and damage; and an inspection of the inner 
bore and outer surface of the coat hangar pins for signs of corrosion 
and damage. The corrective actions include repair, rework, or 
replacement.
    Bombardier, Inc. has also issued Modification Summary Package 
IS4Q5400012, Revision B, dated July 11, 2012. This service information 
describes procedures for applying a fay sealant gasket to the rear spar 
access fitting access panel.
    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

    The FAA estimates that this AD affects 54 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2010-23- 3 work-hours x $85  $0................  $255..............  $13,770.
 04.                               per hour = $255.
New actions.....................  320 work-hours x    Up to $104,739....  Up to $131,939....  Up to $7,124,706.
                                   $85 per hour =
                                   $27,200.
----------------------------------------------------------------------------------------------------------------


[[Page 35179]]

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.
    The FAA is 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

    The FAA 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) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2010-23-04, Amendment 39-16493 (75 FR 68174, November 5, 2010), and 
adding the following new AD:

2020-11-13 De Havilland Aircraft of Canada Limited (Type Certificate 
previously held by Bombardier, Inc.): Amendment 39-19917; Docket No. 
FAA-2020-0099; Product Identifier 2019-NM-169-AD.

(a) Effective Date

    This AD is effective July 14, 2020.

(b) Affected ADs

    This AD replaces AD 2010-23-04, Amendment 39-16493 (75 FR 68174, 
November 5, 2010) (``AD 2010-23-04'').

(c) Applicability

    This AD applies to De Havilland Aircraft of Canada Limited (Type 
Certificate previously held by Bombardier, Inc.) Model DHC-8-400, -
401, and -402 airplanes, certificated in any category, serial 
numbers 4001 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Reason

    This AD was prompted by reports of cracked nacelle attachment 
fittings, which a preliminary investigation determined to be caused 
by stress corrosion. The FAA is issuing this AD to address this 
condition, which, if not detected and corrected, could compromise 
the structural integrity of the nacelle attachment fitting and 
possibly result in collapse of the landing gear.

(f) Compliance

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

(g) Retained Detailed and Conductivity Inspections and Replacement, 
With Revised Service Information and Revised Replacement Instructions

    This paragraph restates the requirements of paragraph (g) of AD 
2010-23-04, with revised service information and revised replacement 
instructions. For airplanes having serial numbers 4001 through 4304 
inclusive, 4314, and 4315: Within 100 flight hours after November 
22, 2010 (the effective date of AD 2010-23-04), do a detailed 
inspection for cracking, and a conductivity inspection on each of 
the 4 nacelle attachment fittings, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, 
Revision K, dated August 7, 2018. Repeat the detailed inspection at 
intervals not to exceed 300 flight hours, except as provided by 
paragraph (i) of this AD. Accomplishing the replacement specified in 
paragraph (g)(1)(ii) or (g)(2)(ii)(B) of this AD terminates the 
inspections required by this paragraph.
    (1) If any nacelle attachment fitting is found cracked, before 
further flight, do the action specified in paragraph (g)(1)(i) or 
(ii) of this AD. As of the effective date of this AD, only the 
action specified in paragraph (g)(1)(ii) of this AD may be done.
    (i) Replace the fitting with a new fitting in accordance with 
paragraph (2) of Part A of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 
2018.
    (ii) Replace the rear spar nacelle attachment fitting and 
associated structure with a new nacelle attachment fitting, part 
number (P/N) 8Z9305, and do all applicable related investigative and 
corrective actions, in accordance with Part B of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-16 Revision D, 
dated August 7, 2018. Do all applicable related investigative and 
corrective actions before further flight.
    (2) If the conductivity of any test points on any fitting is 
found to be greater than 45.0 percent International Annealed Copper 
Standard (IACS) or if the conductivity of any test points on any 
fitting is found to be less than 38.0 percent IACS, do the actions 
required by paragraphs (g)(2)(i) and (ii) of this AD.
    (i) Within 24 hours after accomplishing the conductivity 
inspection specified in paragraph (g) of this AD, do a detailed 
inspection of the nacelle attachment fitting for cracking, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 84-54-14, Revision K, dated August 7, 2018, and 
repeat thereafter at intervals not to exceed 24 hours. If cracking 
is found, before further flight, replace the fitting with a new 
fitting in accordance with the requirements of paragraph (g)(2)(ii) 
of this AD. Replacement of the fitting terminates the daily detailed 
inspection requirements of this paragraph.
    (ii) Except as required by paragraph (g)(2)(i) of this AD: 
Within 300 flight hours after accomplishing the conductivity 
inspection specified in paragraph (g) of this AD, do the action 
specified in paragraph (g)(2)(ii)(A) or (B) of this AD. As of the 
effective date of this AD, only the action specified in paragraph 
(g)(2)(ii)(B) of this AD may be done.
    (A) Replace the fitting with a new fitting in accordance with 
paragraph (2) of Part A of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 
2018.
    (B) Replace the rear spar nacelle attachment fitting and 
associated structure with a new nacelle attachment fitting, P/N 
8Z9305, and do all applicable related investigative and corrective 
actions, in accordance with Part B of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-16 Revision D, 
dated August 7, 2018. Do all applicable related investigative and 
corrective actions before further flight.

(h) Retained Inspections and Replacement, With Revised Service 
Information, Revised Affected Airplanes, and Revised Replacement 
Instructions

    This paragraph restates the requirements of paragraph (i) of AD 
2010-23-04, with revised service information, revised affected 
airplanes, and revised replacement instructions. For airplanes 
having serial numbers 4305 through 4313 inclusive, and 4316 through 
4380 inclusive, and airplanes that have replaced nacelle attachment 
fitting(s) with P/N 854146663: Within 1,200

[[Page 35180]]

flight hours after November 22, 2010 (the effective date of AD 2010-
23-04), do a detailed inspection for cracking on each of the 4 
nacelle attachment fittings, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-14, Revision K, 
dated August 7, 2018. If any nacelle attachment fitting is found 
cracked, before further flight, do the action specified in paragraph 
(h)(1) or (2) of this AD. As of the effective date of this AD, only 
the action specified in paragraph (h)(2) of this AD may be done. 
Thereafter, repeat the detailed inspection at intervals not to 
exceed 300 flight hours, except as provided by paragraph (i) of this 
AD. Accomplishing the replacement specified in paragraph (h)(2) of 
this AD terminates the inspections required by this paragraph.
    (1) Replace the fitting with a new fitting in accordance with 
paragraph (2) of Part A of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 
2018.
    (2) Replace the rear spar nacelle attachment fitting and 
associated structure with a new nacelle attachment fitting, P/N 
8Z9305, and do all applicable related investigative and corrective 
actions, in accordance with Part B of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-16 Revision D, 
dated August 7, 2018. Do all applicable related investigative and 
corrective actions before further flight.

(i) Retained Inspection Compliance Time, With Revised Service 
Information

    This paragraph restates the requirements of paragraph (j) of AD 
2010-23-04, with revised service information. For any fitting that 
is replaced in accordance with paragraph (3) of Part A of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, 
Revision J, dated September 17, 2010; or paragraph (2) of Part A of 
the Accomplishment Instructions of Bombardier Service Bulletin 84-
54-14, Revision K, dated August 7, 2018, as specified in paragraph 
(g) or (h) of this AD: Within 1,200 flight hours after replacing the 
fitting, do a detailed inspection of that replaced fitting as 
specified in paragraph (g) or (h) of this AD, and repeat the 
detailed inspection thereafter at intervals not to exceed 300 flight 
hours. Accomplishing the replacement specified in paragraph 
(g)(1)(ii), (g)(2)(ii)(B), or (h)(2) of this AD terminates the 
inspections required by this paragraph.

(j) Retained Credit for Previous Actions (Replacing the Fitting), With 
Revised Paragraph References

    This paragraph restates the credit provided in paragraph (k) of 
AD 2010-23-04, with revised paragraph references. Accomplishing the 
replacement of the nacelle fittings in accordance with any 
Bombardier service bulletin identified in figure 1 to paragraphs (j) 
and (k) of this AD before November 22, 2010 (the effective date of 
AD 2010-23-04) is also acceptable for compliance with the fitting 
replacements specified in paragraphs (g)(1)(i), (g)(2)(ii)(A), and 
(h)(1) of this AD.
[GRAPHIC] [TIFF OMITTED] TR09JN20.001

(k) Retained Credit for Previous Actions (Inspections), With No Changes

    This paragraph restates the credit provided in paragraph (l) of 
AD 2010-23-04, with no changes. Accomplishment of the inspections 
required by paragraphs (g) and (h) of this AD before November 22, 
2010 (the effective date of AD 2010-23-04) in accordance with any 
Bombardier service bulletin identified in figure 1 to paragraphs (j) 
and (k) of this AD is acceptable for compliance with the 
corresponding actions required by paragraphs (g) and (h) of this AD.

(l) New Requirements of This AD: Modification of the Rear Spar Fitting 
and Nacelle Attaching Structure

    For airplanes with nacelle attachment fitting P/N 85414663: 
Unless already done as specified in paragraph (g)(1)(ii), 
(g)(2)(ii)(B), or (h)(2) of this AD: Within 8,000 flight hours or 48 
months, whichever occurs first, from the effective date of this AD, 
replace the rear spar nacelle attachment fitting and associated 
structure with a new nacelle attachment fitting, P/N 8Z9305, and do 
all applicable related investigative and corrective actions, in 
accordance with Part B of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-16, Revision D, dated August 7, 
2018. Do all applicable related investigative and corrective actions 
before further flight.

[[Page 35181]]

(m) New Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD that are identified in Bombardier 
Service Bulletin 84-54-14, Revision K, dated August 7, 2018, if 
those actions were performed before the effective date of this AD 
using Bombardier Service Bulletin 84-54-14, Revision J, dated 
September 17, 2010, which was incorporated by reference in AD 2010-
23-04; except as provided by paragraph (p) of this AD.
    (2) This paragraph provides credit for accomplishing the 
replacement of the rear spar fitting and nacelle attaching structure 
required by paragraph (l) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (m)(2)(i) through (iii) of this 
AD.
    (i) Bombardier Service Bulletin 84-54-16, dated April 29, 2011.
    (ii) Bombardier Service Bulletin 84-54-16, Revision A, dated 
August 1, 2011.
    (iii) Bombardier Service Bulletin 84-54-16, Revision C, dated 
January 31, 2017.
    (3) This paragraph provides credit for accomplishing the 
replacement of the rear spar fitting and nacelle attaching structure 
required by paragraph (l) of this AD, if those actions were 
performed before the effective date of this AD using Bombardier 
Service Bulletin 84-54-16, Revision B, dated October 6, 2016. 
Although Bombardier Service
    Bulletin 84-54-16, Revision B, dated October 6, 2016, 
incorrectly stated that airworthiness limitations (AWLs) or damage 
tolerance inspections (DTIs) are not affected, they are affected. 
Refer to the applicable AWLs for Post/Pre-Modification Summary 
(ModSum) 4-113697 and Bombardier Service Bulletin 84-54-16 in the 
existing maintenance requirements manual.
    (4) This paragraph provides credit for accomplishing the action 
identified in Bombardier Service Bulletin 84-54-14, Revision K, 
dated August 7, 2018, that are required by paragraphs (g) and (h) of 
this AD, if those actions were performed before the effective date 
of this AD using the service information specified in paragraphs 
(m)(4)(i) through (iv) of this AD.
    (i) Bombardier Service Bulletin 84-54-15, dated August 20, 2010.
    (ii) Bombardier Service Bulletin 84-54-15, Revision A, dated 
October 25, 2010. (iii) Bombardier Service Bulletin 84-54-15, 
Revision B, dated February 2, 2017. (iv) Bombardier Service Bulletin 
84-54-15, Revision C, dated August 7, 2018.

(n) Terminating Action for Certain Actions in Paragraphs (g), (h), and 
(i) of This AD

    Accomplishing the modification of the rear spar fitting and 
nacelle attaching structure required by paragraph (l) of this AD 
terminates the repetitive inspection required by paragraphs (g), 
(h), and (i) of this AD for that airplane.

(o) Parts Installation Limitations

    As of the effective date of this AD, no person may install a 
rear spar nacelle attachment fitting P/N 85414663 on any airplane.

(p) Credit for Alternative to Certain Credit Actions

    For airplanes on which Bombardier Service Bulletin 84-54-14, 
Revision J, dated September 17, 2010, was accomplished before the 
effective date of this AD: As an alternative to applying sealant to 
each fitting and access panel as specified in paragraph C.(1) of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, 
Revision J, dated September 17, 2010, the use of the instructions of 
Bombardier Modification Summary Package IS4Q5400012, Revision B, 
dated July 11, 2012, to apply sealant is also acceptable if 
accomplished before the effective date of this AD.

(q) Other FAA AD Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO Branch, 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 certification 
office, send it to ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531.
    (i) 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.
    (ii) AMOCs approved previously for AD 2010-23-04, are approved 
as AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, New York ACO 
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or De 
Havilland Aircraft of Canada Limited's TCCA Design Approval 
Organization (DAO). If approved by the DAO, the approval must 
include the DAO-authorized signature.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2010-30R2, dated July 30, 2019, for related 
information. This MCAI may be found in the AD docket on the internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2020-0099.
    (2) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 516-228-7330; fax 516-794-5531; email [email protected].
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (s)(3) and (4) of this AD.

(s) 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 84-54-14, Revision K, dated 
August 7, 2018.
    (ii) Bombardier Service Bulletin 84-54-16, Revision D, dated 
August 7, 2018.
    (iii) Bombardier Modification Summary Package IS4Q5400012, 
Revision B, dated July 11, 2012.
    (3) For service information identified in this AD, contact De 
Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 
123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 
416-375-4000; fax 416-375-4539; email [email protected]; internet 
https://dehavilland.com.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 2200 
South 216th St., Des Moines, WA. For information on the availability 
of this material at the FAA, call 206-231-3195.
    (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, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on May 29, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-12379 Filed 6-8-20; 8:45 am]
 BILLING CODE 4910-13-P