Airworthiness Directives; Bombardier, Inc., Airplanes, 53563-53567 [2018-23031]

Download as PDF 53563 Rules and Regulations Federal Register Vol. 83, No. 206 Wednesday, October 24, 2018 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0160; Product Identifier 2017–NM–139–AD; Amendment 39–19476; AD 2018–22–03] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2016–24– 03, which applied to certain Bombardier, Inc., Model DHC–8–400 series airplanes. AD 2016–24–03 required repetitive detailed inspections of barrel nuts and cradles, a check of the bolt torque of the preload indicating (PLI) washers, and corrective actions if necessary. This AD retains the requirements of AD 2016–24–03 and requires modifying the airplane by installing a sealing disk to a certain location and replacing certain barrel nuts. This AD was prompted by reports of cracked and corroded barrel nuts found at the mid-spar location of the horizontal-stabilizer-to-verticalstabilizer attachment joint, and the issuance of new service information that includes a terminal modification. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 28, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 28, 2018. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 12, 2017 (81 FR 88623, December 8, 2016). amozie on DSK3GDR082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:10 Oct 23, 2018 Jkt 247001 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 Standards 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 http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0160. 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–2018– 0160; 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, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) 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: Aziz Ahmed, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; fax 516–794– 5531; email 9-avs-nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2016–24–03, Amendment 39–18720 (81 FR 88623, December 8, 2016) (‘‘AD 2016–24–03’’). AD 2016–24–03 applied to certain Bombardier, Inc., Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on March 9, 2018 (83 FR 10408). The NPRM was prompted by reports of cracked and corroded barrel nuts found at the midspar location of the horizontalstabilizer-to-vertical-stabilizer attachment joint, and the issuance of PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 new service information that includes a terminal modification. The NPRM proposed to continue to require repetitive detailed inspections of each barrel nut and cradle, a check of the bolt torque of the PLI washers, and corrective action if necessary. The NPRM also proposed to require modifying the airplane by installing a sealing disk to a certain location and replacing certain barrel nuts. We are issuing this AD to address cracked and corroded barrel nuts, which could compromise the structural integrity of the vertical-stabilizer attachment joints and lead to loss of control of the airplane. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2015–13R1, dated June 26, 2017 (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: There has been one in-service report of a cracked and corroded barrel nut, part number (P/N) DSC228–12, found at the mid-spar location of the horizontal stabilizer to vertical stabilizer attachment joint. There have also been two other reports of corroded barrel nuts found at mid-spar locations. Preliminary investigation determined that the cracking is initiated by corrosion. Further investigation confirmed that the corrosion was caused by inadequate cadmium plating on the barrel nuts. Failure of the barrel nuts could compromise the structural integrity of the joint and could lead to loss of control of the aeroplane. The original version of this [Canadian] AD was issued to mandate the initial and repetitive inspections of the barrel nuts [and cradles for cracks and corrosion] at each of the horizontal stabilizer to vertical stabilizer attachment joints. Revision 1 of this [Canadian] AD is issued to terminate the repetitive inspection requirement by requiring the incorporation of a modification to install a sealing disc at the middle spar location of the horizontal stabilizer to vertical stabilizer attachment joint, and the replacement of the DSC228 series barrel nuts with B0203073 series barrel nuts that are more resistant to corrosion. The applicability has been changed to account for the introduction of the modifications in production. 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–2018– 0160. E:\FR\FM\24OCR1.SGM 24OCR1 53564 Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 / Rules and Regulations Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comment received on the NPRM and the FAA’s response. Request To Refer to New Repair Drawing (RD) Horizon Air requested that we revise paragraph (h)(1)(i) of the proposed AD to refer to Bombardier RD 8/4–55–1143, Issue 2, dated May 25, 2015 (we referred to Bombardier RD 8/4–55–1143, Issue 1, dated May 21, 2015, as the appropriate source of service information for the repair specified in paragraph (h)(1)(i) of the proposed AD). Horizon Air noted that Bombardier RD 8/4–55–1143, Issue 2, dated May 25, 2015, adds nominal bore diameters to sheets 1–4. We agree with the commenter’s request. Bombardier RD 8/4–55–1143, Issue 2, dated May 25, 2015, clarifies the bore hole diameters for repair but does not otherwise change the substantive requirements of this AD. No additional work is necessary for airplanes on which Bombardier RD 8/4–55–1143, Issue 1, dated May 21, 2015, has already been done. We have revised paragraph (h)(1)(i) of this AD to include Bombardier RD 8/4–55–1143, Issue 2, dated May 25, 2015, as the appropriate service information for repairing corrosion and damage of the bore of the fitting. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this final rule 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 addressing 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 final rule. Related Service Information Under 1 CFR Part 51 Bombardier has issued the following service information. • Bombardier Alert Service Bulletin A84–55–04, Revision C, dated May 3, 2016. This service information describes procedures for a detailed inspection and repair for cracks and corrosion of the barrel nuts and cradles; a bolt preload check of the PLI washers and applicable corrective actions; a detailed inspection and repair for corrosion and damage of the bore of the fitting; and replacement of the barrel nuts. • Bombardier Service Bulletin 84–55– 06, dated January 31, 2017. This service information describes procedures for installing an aluminum sealing disk at the mid-spar location of the vertical stabilizer. • Bombardier Service Bulletin 84–55– 08, Revision A, dated August 2, 2017. This service information describes procedures for an inspection for part number and damage of the barrel nuts at the horizontal-stabilizer-to-verticalstabilizer attachment joints, and replacement of discrepant parts. • Bombardier Repair Drawing (RD) 8/ 4–55–1143, Issue 2, dated May 25, 2015. This service information describes procedures for repairing corrosion and damage of the fitting bore. 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 54 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Cost per product Parts cost Cost on U.S. operators Action Labor cost Inspections (retained actions from AD 2016– 24–03). Sealing disk installation (new action) ............. Replacement of DSC228 series barrel nuts (new action). 8 work-hours × $85 per hour = $680 ............. $0 $680 $36,720 4 work-hours × $85 per hour = $340 ............. 2 work-hours × $85 per hour = $170 ............. 781 2,236 1,121 2,406 60,534 129,924 We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement (retained action from AD 2016–24–03) amozie on DSK3GDR082PROD with RULES We have received no definitive data that would enable us to provide cost estimates for the other on-condition actions specified in this AD. 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: VerDate Sep<11>2014 16:10 Oct 23, 2018 Jkt 247001 2 work-hours × $85 per hour = $170 ........................... 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 PO 00000 Parts cost Frm 00002 Fmt 4700 Sfmt 4700 $8,881 Cost per product $9,051 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. E:\FR\FM\24OCR1.SGM 24OCR1 Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 / Rules and Regulations In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. 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. [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2016–24–03, Amendment 39–18720 (81 FR 88623, December 8, 2016), and adding the following new AD: amozie on DSK3GDR082PROD with RULES ■ 2018–22–03 Bombardier, Inc.: Amendment 39–19476; Docket No. FAA–2018–0160; Product Identifier 2017–NM–139–AD. (a) Effective Date This AD is effective November 28, 2018. VerDate Sep<11>2014 16:10 Oct 23, 2018 This AD replaces AD 2016–24–03, Amendment 39–18720 (81 FR 88623, December 8, 2016) (‘‘AD 2016–24–03’’). (c) Applicability This AD applies to Bombardier, Inc., Model DHC–8–400, –401 and –402 airplanes, certificated in any category, serial numbers 4001 and subsequent. (d) Subject Regulatory Findings § 39.13 (b) Affected ADs Jkt 247001 Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Reason This AD was prompted by reports of cracked and corroded barrel nuts found at the mid-spar location of the horizontal-stabilizerto-vertical-stabilizer attachment joint, and the issuance of new service information that includes a terminal modification. We are issuing this AD to address cracked and corroded barrel nuts, which could compromise the structural integrity of the vertical-stabilizer attachment joints and lead to loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Detailed Inspection of Barrel Nuts for Cracks and Corrosion, With No Changes This paragraph restates the requirements of paragraphs (g)(1) and (g)(2) of AD 2016–24– 03, with no changes. (1) For airplanes that have accumulated 5,400 flight hours or more, or have been in service 32 months or more since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness, as of January 12, 2017 (the effective date of AD 2016–24–03): Within 600 flight hours or 4 months, whichever occurs first after January 12, 2017, do a detailed visual inspection for signs of cracks and corrosion of the barrel nut and cradle, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–55–04, Revision C, dated May 3, 2016. (2) For airplanes that have less than 5,400 flight hours, and have been in-service for less than 32 months since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness, as of January 12, 2017: Before the accumulation of 6,000 total flight hours or 36 months since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness, whichever occurs first, do a detailed visual inspection of the barrel nut for signs of cracks and corrosion of the barrel nut and cradle, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–55–04, Revision C, dated May 3, 2016. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 53565 (h) Retained Corrective Actions, Detailed Inspection, and Repetitive Inspections, With New Service Information, Reference to Terminating Action, and Reference to Corrective Actions This paragraph restates the requirements of paragraph (h) of AD 2016–24–03, with new service information and terminating action. Depending on the findings of any inspection required by paragraphs (g) and (j) of this AD, do the applicable actions in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of this paragraph. (1) If any barrel nut or cradle is found cracked or broken, before further flight, replace the barrel nut and associated hardware, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017. (i) Concurrently with the replacement of any barrel nut, do a detailed inspection for corrosion and damage of the bore of the fitting, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017, and, before further flight, repair all corrosion and damage, in accordance with Bombardier Repair Drawing (RD) 8/4–55–1143, Issue 1, dated May 21, 2015; or Bombardier RD 8/4– 55–1143, Issue 2, dated May 25, 2015. If the bore of the fitting cannot be repaired in accordance with Bombardier RD 8/4–55– 1143, Issue 1, dated May 21, 2015; or Bombardier RD 8/4–55–1143, Issue 2, dated May 25, 2015; accomplish corrective actions in accordance with the procedures specified in paragraph (q)(2) of this AD. As of the effective date of this AD, use Bombardier RD 8/4–55–1143, Issue 2, dated May 25, 2015, for the repair required by this paragraph. (ii) Within 600 flight hours or 4 months, whichever occurs first, after the replacement of a cracked barrel nut, replace the remaining barrel nuts and their associated hardware at the horizontal-stabilizer-to-vertical-stabilizer attachment joints, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017. (2) If any corrosion is found on any barrel nut on the front or rear-spar joints, before further flight, replace the barrel nut in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017, or accomplish corrective actions in accordance with the procedures specified in paragraph (q)(2) of this AD. (3) If any corrosion above level 1, as defined in Bombardier Alert Service Bulletin A84–55–04, Revision C, dated May 3, 2016, is found on a barrel nut at the mid-spar joint, before further flight, replace the barrel nut and accomplish corrective actions in accordance with the procedures specified in paragraph (q)(2) of this AD. (4) If all corrosion found is at level 1 or below, as defined in Bombardier Alert Service Bulletin A84–55–04, Revision C, E:\FR\FM\24OCR1.SGM 24OCR1 53566 Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 / Rules and Regulations dated May 3, 2016, on a barrel nut at the midspar joint, repeat the inspection specified in paragraph (g) of this AD at intervals not to exceed 600 flight hours or 4 months, whichever occurs first, until completion of the actions required by paragraph (k) of this AD. (i) Retained Preload Indicating (PLI) Washer Check, With New Terminating Action This paragraph restates the requirements of paragraph (i) of AD 2016–24–03, with new terminating action. For airplanes with PLI washers installed at the front and rear-spar joints, before further flight after accomplishing any inspection required by paragraph (g) of this AD and all applicable corrective actions required by paragraph (h) of this AD, check the bolt preload, and do all applicable corrective actions, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–55–04, Revision C, dated May 3, 2016. Do all applicable corrective actions before further flight. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of this paragraph. (j) Retained Repetitive Inspection Interval, With New Terminating Action This paragraph restates the requirements of paragraph (j) of AD 2016–24–03, with new terminating action. Repeat the inspection and preload check required by paragraphs (g) and (i) of this AD at intervals not to exceed 3,600 flight hours or 18 months, whichever occurs first, except as provided by paragraph (k) of this AD. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of this paragraph. (k) Retained Optional Barrel Nut Replacement, With New Service Information This paragraph restates the provisions of paragraph (k) of AD 2016–24–03, with new service information. Inspection and replacement of all barrel nuts at the horizontal-stabilizer-to-vertical-stabilizer attachment joints, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017, extends the next inspection required by paragraph (j) of this AD to within 6,000 flight hours or 36 months, whichever occurs first, after accomplishing the replacement. amozie on DSK3GDR082PROD with RULES (l) New Requirement of This AD: Sealing Disk Installation Within 8,000 flight hours or 48 months, whichever occurs first, after the effective date of this AD, install a sealing disk at the midspar location of the vertical stabilizer in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–06, dated January 31, 2017. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of paragraphs (h), (i), and (j) of this AD. VerDate Sep<11>2014 16:10 Oct 23, 2018 Jkt 247001 (m) New Requirement of This AD: Replacement of DSC228 Series Barrel Nuts For Bombardier, Inc., Model DHC–8–400, –401 and –402 airplanes, serial numbers 4001 through 4524 inclusive: Within 8,000 flight hours or 48 months, whichever occurs first, after the effective date of this AD, replace all DSC228 series barrel nuts at the horizontal-stabilizer-to-vertical-stabilizer attachment joints with B0203073 series barrel nuts in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of paragraphs (h), (i), and (j) of this AD. (n) Parts Installation Prohibition After modification of an airplane as required by paragraphs (l) and (m) of this AD, no person may install a DSC228 series barrel nut at the horizontal-stabilizer-to-verticalstabilizer attachment joint on the modified airplane. (o) Terminating Actions for Paragraphs (h), (i), and (j) of This AD Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of paragraphs (h), (i), and (j) of this AD. (p) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g)(1), (g)(2), (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), (h)(3), (h)(4), (i), and (k) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (p)(1)(i) through (p)(1)(iii) of this AD. (i) Bombardier Alert Service Bulletin A84– 55–04, dated May 21, 2015, which is not incorporated by reference in this AD. (ii) Bombardier Alert Service Bulletin A84– 55–04, Revision A, dated June 2, 2015, which is not incorporated by reference in this AD. (iii) Bombardier Alert Service Bulletin A84–55–04, Revision B, dated July 30, 2015, which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraphs (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), and (k) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (p)(2)(i) and (p)(2)(ii) of this AD. (i) Bombardier Service Bulletin 84–55–08, dated January 27, 2017, which is not incorporated by reference in this AD. (ii) Bombardier Alert Service Bulletin A84– 55–04, Revision C, dated May 3, 2016, which was incorporated by reference in AD 2016– 24–03. (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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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 2016–24–03 are approved as AMOCs for the corresponding provisions of 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 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. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2015–13R1, dated June 26, 2017, 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–2018–0160. (2) For more information about this AD, contact Aziz Ahmed, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; 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)(5) and (s)(6) 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. (3) The following service information was approved for IBR on November 28, 2018. (i) Bombardier Repair Drawing (RD) 8/4– 55–1143, Issue 2, dated May 25, 2015. (ii) Bombardier Service Bulletin 84–55–06, dated January 31, 2017. (iii) Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017. (4) The following service information was approved for IBR on January 12, 2017 (81 FR 88623, December 8, 2016). (i) Bombardier Alert Service Bulletin A84– 55–04, Revision C, dated May 3, 2016. (ii) Reserved. (5) 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. E:\FR\FM\24OCR1.SGM 24OCR1 Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 / Rules and Regulations (6) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on October 12, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–23031 Filed 10–23–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 SUPPLEMENTARY INFORMATION: [Docket No. FAA–2018–0189; Product Identifier 2017–CE–022–AD; Amendment 39–19460; AD 2018–21–02] Discussion RIN 2120–AA64 Airworthiness Directives; Viking Air Limited Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Viking Air Limited Model DHC–3 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as pitting corrosion on the shank of the wing strut attach bolts. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective November 28, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 28, 2018. ADDRESSES: You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0189; or in person at Docket Operations, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. amozie on DSK3GDR082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:10 Oct 23, 2018 Jkt 247001 For service information identified in this AD, contact Viking Air Limited Technical Support, 1959 De Havilland Way, Sidney, British Columbia, Canada, V8L 5V5; telephone: (North America) (800) 663–8444; fax: (250) 656–0673; email: technical.support@vikingair.com; internet: http://www.vikingair.com/ support/service-bulletins. You may view this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the internet at http:// www.regulations.gov by searching for Docket No. FAA–2018–0189. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 287–7329; fax: (516) 794–5531; email: aziz.ahmed@ faa.gov. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to Viking Air Limited Model DHC–3 airplanes. The NPRM was published in the Federal Register on March 13, 2018 (83 FR 10809). The NPRM proposed to correct an unsafe condition for the specified products and was based on MCAI originated by an aviation authority of another country. The MCAI states: Pitting corrosion has been found on the shank of the following part number wing strut attach bolts: C3W114–3, C3W129–3 and C3W128–3. These bolts are manufactured using a standard AN12 bolt. Metallurgical evaluation concluded that pitting corrosion was present on the affected AN12 bolts prior to forming of the bolt head and threads. The pitting and un-plated voids could cause a surface condition that may have a detrimental effect on fatigue and corrosion resistance, leading to bolt failure and consequent failure of the wing. Viking has not been able to confirm the affected batch numbers or specific manufacture date range. New wing strut bolts manufactured after 21 March 2016 are inspected for pitting during manufacturing and issued new P/Ns C3W114–5, C3W129– 5 and C3W128–5 under MOD 3/1010. The MCAI can be found in the AD docket on the internet at: https:// www.regulations.gov/document ?D=FAA-2018-0189-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 53567 received on the proposal and the FAA’s response to each comment. Request To Issue SAIB Instead of an AD Christopher Campbell requested that we withdraw the AD and issue a special airworthiness information bulletin (SAIB) instead. The commenter stated this AD is unnecessary and redundant since the manufacturer has already addressed this issue with a mandatory service bulletin and all affected bolts should now be removed. The commenter stated the affected bolts are 3/4-inch diameter bolts and only the surface cadmium plating is compromised, not the strength of the bolt. The commenter also disagreed with the manufacturer that the compromised cadmium plating would cause accelerated corrosion because the bolts are treated with anti-corrosion grease on installation. The commenter further stated an AD is unnecessary because the defect would be obvious to any installing mechanic. Lastly, the commenter stated that the proposed AD does little to further enhance safety but adds unwelcome recordkeeping and cost for owners. We do not agree. We concur with Transport Canada’s finding of an unsafe condition, as explained in Transport Canada AD No. CF–2017–11, dated March 23, 2017. An SAIB would not be an appropriate solution. An SAIB contains information and recommended actions that are voluntary and not regulatory. Moreover, an SAIB is issued only for airworthiness concerns that do not rise to the level of an unsafe condition. Similarly, while an operator may incorporate the procedures described in a manufacturer’s service bulletin into its maintenance program, not all operators are required to do so. For the corrective actions in a service bulletin to become mandatory and to correct the unsafe condition, the FAA must issue an AD. Based on the manufacturer’s metallurgical evaluation, the pitting corrosion was present on the affected AN 12 bolts prior to forming of the bolt head and thread. Corrosion pitting was found on airplanes when doing the inspections per Transport Canada’s AD CF–2017–11. Specifically, the pitting was discovered on the bolt shanks of both wing strut fitting to wing spar lug bolts. Relying on an assumption that the corrosion will be obvious at the time of bolts installation, as suggested by the commenter, is not a reliable method to correct an unsafe condition. We have not changed this AD based on this comment. E:\FR\FM\24OCR1.SGM 24OCR1

Agencies

[Federal Register Volume 83, Number 206 (Wednesday, October 24, 2018)]
[Rules and Regulations]
[Pages 53563-53567]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-23031]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 / 
Rules and Regulations

[[Page 53563]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0160; Product Identifier 2017-NM-139-AD; Amendment 
39-19476; AD 2018-22-03]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2016-24-03, 
which applied to certain Bombardier, Inc., Model DHC-8-400 series 
airplanes. AD 2016-24-03 required repetitive detailed inspections of 
barrel nuts and cradles, a check of the bolt torque of the preload 
indicating (PLI) washers, and corrective actions if necessary. This AD 
retains the requirements of AD 2016-24-03 and requires modifying the 
airplane by installing a sealing disk to a certain location and 
replacing certain barrel nuts. This AD was prompted by reports of 
cracked and corroded barrel nuts found at the mid-spar location of the 
horizontal-stabilizer-to-vertical-stabilizer attachment joint, and the 
issuance of new service information that includes a terminal 
modification. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective November 28, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 28, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
12, 2017 (81 FR 88623, December 8, 2016).

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 [email protected]; internet 
http://www.bombardier.com. You may view this referenced service 
information at the FAA, Transport Standards 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 http://www.regulations.gov by searching for and locating 
Docket No. FAA-2018-0160.

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-2018-
0160; 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, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) 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: Aziz Ahmed, Aerospace Engineer, 
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart 
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-
794-5531; email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2016-24-03, Amendment 39-18720 (81 FR 88623, 
December 8, 2016) (``AD 2016-24-03''). AD 2016-24-03 applied to certain 
Bombardier, Inc., Model DHC-8-400 series airplanes. The NPRM published 
in the Federal Register on March 9, 2018 (83 FR 10408). The NPRM was 
prompted by reports of cracked and corroded barrel nuts found at the 
mid-spar location of the horizontal-stabilizer-to-vertical-stabilizer 
attachment joint, and the issuance of new service information that 
includes a terminal modification. The NPRM proposed to continue to 
require repetitive detailed inspections of each barrel nut and cradle, 
a check of the bolt torque of the PLI washers, and corrective action if 
necessary. The NPRM also proposed to require modifying the airplane by 
installing a sealing disk to a certain location and replacing certain 
barrel nuts. We are issuing this AD to address cracked and corroded 
barrel nuts, which could compromise the structural integrity of the 
vertical-stabilizer attachment joints and lead to loss of control of 
the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2015-13R1, dated June 
26, 2017 (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:

    There has been one in-service report of a cracked and corroded 
barrel nut, part number (P/N) DSC228-12, found at the mid-spar 
location of the horizontal stabilizer to vertical stabilizer 
attachment joint. There have also been two other reports of corroded 
barrel nuts found at mid-spar locations.
    Preliminary investigation determined that the cracking is 
initiated by corrosion. Further investigation confirmed that the 
corrosion was caused by inadequate cadmium plating on the barrel 
nuts. Failure of the barrel nuts could compromise the structural 
integrity of the joint and could lead to loss of control of the 
aeroplane.
    The original version of this [Canadian] AD was issued to mandate 
the initial and repetitive inspections of the barrel nuts [and 
cradles for cracks and corrosion] at each of the horizontal 
stabilizer to vertical stabilizer attachment joints.
    Revision 1 of this [Canadian] AD is issued to terminate the 
repetitive inspection requirement by requiring the incorporation of 
a modification to install a sealing disc at the middle spar location 
of the horizontal stabilizer to vertical stabilizer attachment 
joint, and the replacement of the DSC228 series barrel nuts with 
B0203073 series barrel nuts that are more resistant to corrosion. 
The applicability has been changed to account for the introduction 
of the modifications in production.

    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-2018-
0160.

[[Page 53564]]

Comments

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

Request To Refer to New Repair Drawing (RD)

    Horizon Air requested that we revise paragraph (h)(1)(i) of the 
proposed AD to refer to Bombardier RD 8/4-55-1143, Issue 2, dated May 
25, 2015 (we referred to Bombardier RD 8/4-55-1143, Issue 1, dated May 
21, 2015, as the appropriate source of service information for the 
repair specified in paragraph (h)(1)(i) of the proposed AD). Horizon 
Air noted that Bombardier RD 8/4-55-1143, Issue 2, dated May 25, 2015, 
adds nominal bore diameters to sheets 1-4.
    We agree with the commenter's request. Bombardier RD 8/4-55-1143, 
Issue 2, dated May 25, 2015, clarifies the bore hole diameters for 
repair but does not otherwise change the substantive requirements of 
this AD. No additional work is necessary for airplanes on which 
Bombardier RD 8/4-55-1143, Issue 1, dated May 21, 2015, has already 
been done. We have revised paragraph (h)(1)(i) of this AD to include 
Bombardier RD 8/4-55-1143, Issue 2, dated May 25, 2015, as the 
appropriate service information for repairing corrosion and damage of 
the bore of the fitting.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this final rule 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 addressing 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 final 
rule.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     Bombardier Alert Service Bulletin A84-55-04, Revision C, 
dated May 3, 2016. This service information describes procedures for a 
detailed inspection and repair for cracks and corrosion of the barrel 
nuts and cradles; a bolt preload check of the PLI washers and 
applicable corrective actions; a detailed inspection and repair for 
corrosion and damage of the bore of the fitting; and replacement of the 
barrel nuts.
     Bombardier Service Bulletin 84-55-06, dated January 31, 
2017. This service information describes procedures for installing an 
aluminum sealing disk at the mid-spar location of the vertical 
stabilizer.
     Bombardier Service Bulletin 84-55-08, Revision A, dated 
August 2, 2017. This service information describes procedures for an 
inspection for part number and damage of the barrel nuts at the 
horizontal-stabilizer-to-vertical-stabilizer attachment joints, and 
replacement of discrepant parts.
     Bombardier Repair Drawing (RD) 8/4-55-1143, Issue 2, dated 
May 25, 2015. This service information describes procedures for 
repairing corrosion and damage of the fitting bore.
    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 54 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions from AD   8 work-hours x $85 per                $0            $680         $36,720
 2016-24-03).                            hour = $680.
Sealing disk installation (new action)  4 work-hours x $85 per               781           1,121          60,534
                                         hour = $340.
Replacement of DSC228 series barrel     2 work-hours x $85 per             2,236           2,406         129,924
 nuts (new action).                      hour = $170.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement (retained action from AD 2016-24-   2 work-hours x $85 per hour =             $8,881          $9,051
 03).                                            $170.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the other on-condition actions specified in this AD.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C.

[[Page 53565]]

In accordance with that order, issuance of ADs is normally a function 
of the Compliance and Airworthiness Division, but during this 
transition period, the Executive Director has delegated the authority 
to issue ADs applicable to transport category airplanes and associated 
appliances to the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2016-24-03, Amendment 39-18720 (81 FR 88623, December 8, 2016), and 
adding the following new AD:

2018-22-03 Bombardier, Inc.: Amendment 39-19476; Docket No. FAA-
2018-0160; Product Identifier 2017-NM-139-AD.

(a) Effective Date

    This AD is effective November 28, 2018.

(b) Affected ADs

    This AD replaces AD 2016-24-03, Amendment 39-18720 (81 FR 88623, 
December 8, 2016) (``AD 2016-24-03'').

(c) Applicability

    This AD applies to 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 55, Stabilizers.

(e) Reason

    This AD was prompted by reports of cracked and corroded barrel 
nuts found at the mid-spar location of the horizontal-stabilizer-to-
vertical-stabilizer attachment joint, and the issuance of new 
service information that includes a terminal modification. We are 
issuing this AD to address cracked and corroded barrel nuts, which 
could compromise the structural integrity of the vertical-stabilizer 
attachment joints and lead to loss of control of the airplane.

(f) Compliance

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

(g) Retained Detailed Inspection of Barrel Nuts for Cracks and 
Corrosion, With No Changes

    This paragraph restates the requirements of paragraphs (g)(1) 
and (g)(2) of AD 2016-24-03, with no changes.
    (1) For airplanes that have accumulated 5,400 flight hours or 
more, or have been in service 32 months or more since the date of 
issuance of the original certificate of airworthiness or the date of 
issuance of the original export certificate of airworthiness, as of 
January 12, 2017 (the effective date of AD 2016-24-03): Within 600 
flight hours or 4 months, whichever occurs first after January 12, 
2017, do a detailed visual inspection for signs of cracks and 
corrosion of the barrel nut and cradle, in accordance with paragraph 
3.B., ``Procedure,'' of the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A84-55-04, Revision C, dated May 
3, 2016.
    (2) For airplanes that have less than 5,400 flight hours, and 
have been in-service for less than 32 months since the date of 
issuance of the original certificate of airworthiness or the date of 
issuance of the original export certificate of airworthiness, as of 
January 12, 2017: Before the accumulation of 6,000 total flight 
hours or 36 months since the date of issuance of the original 
certificate of airworthiness or the date of issuance of the original 
export certificate of airworthiness, whichever occurs first, do a 
detailed visual inspection of the barrel nut for signs of cracks and 
corrosion of the barrel nut and cradle, in accordance with paragraph 
3.B., ``Procedure,'' of the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A84-55-04, Revision C, dated May 
3, 2016.

(h) Retained Corrective Actions, Detailed Inspection, and Repetitive 
Inspections, With New Service Information, Reference to Terminating 
Action, and Reference to Corrective Actions

    This paragraph restates the requirements of paragraph (h) of AD 
2016-24-03, with new service information and terminating action. 
Depending on the findings of any inspection required by paragraphs 
(g) and (j) of this AD, do the applicable actions in paragraphs 
(h)(1), (h)(2), (h)(3), and (h)(4) of this AD. Accomplishment of the 
actions required by paragraphs (l) and (m) of this AD, as 
applicable, terminates the requirements of this paragraph.
    (1) If any barrel nut or cradle is found cracked or broken, 
before further flight, replace the barrel nut and associated 
hardware, in accordance with paragraph 3.B., ``Procedure,'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-55-08, 
Revision A, dated August 2, 2017.
    (i) Concurrently with the replacement of any barrel nut, do a 
detailed inspection for corrosion and damage of the bore of the 
fitting, in accordance with paragraph 3.B., ``Procedure,'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-55-08, 
Revision A, dated August 2, 2017, and, before further flight, repair 
all corrosion and damage, in accordance with Bombardier Repair 
Drawing (RD) 8/4-55-1143, Issue 1, dated May 21, 2015; or Bombardier 
RD 8/4-55-1143, Issue 2, dated May 25, 2015. If the bore of the 
fitting cannot be repaired in accordance with Bombardier RD 8/4-55-
1143, Issue 1, dated May 21, 2015; or Bombardier RD 8/4-55-1143, 
Issue 2, dated May 25, 2015; accomplish corrective actions in 
accordance with the procedures specified in paragraph (q)(2) of this 
AD. As of the effective date of this AD, use Bombardier RD 8/4-55-
1143, Issue 2, dated May 25, 2015, for the repair required by this 
paragraph.
    (ii) Within 600 flight hours or 4 months, whichever occurs 
first, after the replacement of a cracked barrel nut, replace the 
remaining barrel nuts and their associated hardware at the 
horizontal-stabilizer-to-vertical-stabilizer attachment joints, in 
accordance with paragraph 3.B., ``Procedure,'' of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-55-08, Revision A, 
dated August 2, 2017.
    (2) If any corrosion is found on any barrel nut on the front or 
rear-spar joints, before further flight, replace the barrel nut in 
accordance with paragraph 3.B., ``Procedure,'' of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-55-08, Revision A, 
dated August 2, 2017, or accomplish corrective actions in accordance 
with the procedures specified in paragraph (q)(2) of this AD.
    (3) If any corrosion above level 1, as defined in Bombardier 
Alert Service Bulletin A84-55-04, Revision C, dated May 3, 2016, is 
found on a barrel nut at the mid-spar joint, before further flight, 
replace the barrel nut and accomplish corrective actions in 
accordance with the procedures specified in paragraph (q)(2) of this 
AD.
    (4) If all corrosion found is at level 1 or below, as defined in 
Bombardier Alert Service Bulletin A84-55-04, Revision C,

[[Page 53566]]

dated May 3, 2016, on a barrel nut at the mid-spar joint, repeat the 
inspection specified in paragraph (g) of this AD at intervals not to 
exceed 600 flight hours or 4 months, whichever occurs first, until 
completion of the actions required by paragraph (k) of this AD.

(i) Retained Preload Indicating (PLI) Washer Check, With New 
Terminating Action

    This paragraph restates the requirements of paragraph (i) of AD 
2016-24-03, with new terminating action. For airplanes with PLI 
washers installed at the front and rear-spar joints, before further 
flight after accomplishing any inspection required by paragraph (g) 
of this AD and all applicable corrective actions required by 
paragraph (h) of this AD, check the bolt preload, and do all 
applicable corrective actions, in accordance with paragraph 3.B., 
``Procedure,'' of the Accomplishment Instructions of Bombardier 
Alert Service Bulletin A84-55-04, Revision C, dated May 3, 2016. Do 
all applicable corrective actions before further flight. 
Accomplishment of the actions required by paragraphs (l) and (m) of 
this AD, as applicable, terminates the requirements of this 
paragraph.

(j) Retained Repetitive Inspection Interval, With New Terminating 
Action

    This paragraph restates the requirements of paragraph (j) of AD 
2016-24-03, with new terminating action. Repeat the inspection and 
preload check required by paragraphs (g) and (i) of this AD at 
intervals not to exceed 3,600 flight hours or 18 months, whichever 
occurs first, except as provided by paragraph (k) of this AD. 
Accomplishment of the actions required by paragraphs (l) and (m) of 
this AD, as applicable, terminates the requirements of this 
paragraph.

(k) Retained Optional Barrel Nut Replacement, With New Service 
Information

    This paragraph restates the provisions of paragraph (k) of AD 
2016-24-03, with new service information. Inspection and replacement 
of all barrel nuts at the horizontal-stabilizer-to-vertical-
stabilizer attachment joints, in accordance with paragraph 3.B., 
``Procedure,'' of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-55-08, Revision A, dated August 2, 2017, extends 
the next inspection required by paragraph (j) of this AD to within 
6,000 flight hours or 36 months, whichever occurs first, after 
accomplishing the replacement.

(l) New Requirement of This AD: Sealing Disk Installation

    Within 8,000 flight hours or 48 months, whichever occurs first, 
after the effective date of this AD, install a sealing disk at the 
mid-spar location of the vertical stabilizer in accordance with 
paragraph 3.B., ``Procedure,'' of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-55-06, dated January 31, 2017. 
Accomplishment of the actions required by paragraphs (l) and (m) of 
this AD, as applicable, terminates the requirements of paragraphs 
(h), (i), and (j) of this AD.

(m) New Requirement of This AD: Replacement of DSC228 Series Barrel 
Nuts

    For Bombardier, Inc., Model DHC-8-400, -401 and -402 airplanes, 
serial numbers 4001 through 4524 inclusive: Within 8,000 flight 
hours or 48 months, whichever occurs first, after the effective date 
of this AD, replace all DSC228 series barrel nuts at the horizontal-
stabilizer-to-vertical-stabilizer attachment joints with B0203073 
series barrel nuts in accordance with paragraph 3.B., ``Procedure,'' 
of the Accomplishment Instructions of Bombardier Service Bulletin 
84-55-08, Revision A, dated August 2, 2017. Accomplishment of the 
actions required by paragraphs (l) and (m) of this AD, as 
applicable, terminates the requirements of paragraphs (h), (i), and 
(j) of this AD.

(n) Parts Installation Prohibition

    After modification of an airplane as required by paragraphs (l) 
and (m) of this AD, no person may install a DSC228 series barrel nut 
at the horizontal-stabilizer-to-vertical-stabilizer attachment joint 
on the modified airplane.

(o) Terminating Actions for Paragraphs (h), (i), and (j) of This AD

    Accomplishment of the actions required by paragraphs (l) and (m) 
of this AD, as applicable, terminates the requirements of paragraphs 
(h), (i), and (j) of this AD.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g)(1), (g)(2), (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), 
(h)(3), (h)(4), (i), and (k) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information identified in paragraphs (p)(1)(i) through (p)(1)(iii) 
of this AD.
    (i) Bombardier Alert Service Bulletin A84-55-04, dated May 21, 
2015, which is not incorporated by reference in this AD.
    (ii) Bombardier Alert Service Bulletin A84-55-04, Revision A, 
dated June 2, 2015, which is not incorporated by reference in this 
AD.
    (iii) Bombardier Alert Service Bulletin A84-55-04, Revision B, 
dated July 30, 2015, which is not incorporated by reference in this 
AD.
    (2) This paragraph provides credit for actions required by 
paragraphs (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), and (k) of this 
AD, if those actions were performed before the effective date of 
this AD using the service information identified in paragraphs 
(p)(2)(i) and (p)(2)(ii) of this AD.
    (i) Bombardier Service Bulletin 84-55-08, dated January 27, 
2017, which is not incorporated by reference in this AD.
    (ii) Bombardier Alert Service Bulletin A84-55-04, Revision C, 
dated May 3, 2016, which was incorporated by reference in AD 2016-
24-03.

(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 2016-24-03 are approved as 
AMOCs for the corresponding provisions of 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 
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.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2015-13R1, dated June 26, 2017, 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-2018-0160.
    (2) For more information about this AD, contact Aziz Ahmed, 
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 516-228-7329; 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)(5) and (s)(6) 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.
    (3) The following service information was approved for IBR on 
November 28, 2018.
    (i) Bombardier Repair Drawing (RD) 8/4-55-1143, Issue 2, dated 
May 25, 2015.
    (ii) Bombardier Service Bulletin 84-55-06, dated January 31, 
2017.
    (iii) Bombardier Service Bulletin 84-55-08, Revision A, dated 
August 2, 2017.
    (4) The following service information was approved for IBR on 
January 12, 2017 (81 FR 88623, December 8, 2016).
    (i) Bombardier Alert Service Bulletin A84-55-04, Revision C, 
dated May 3, 2016.
    (ii) Reserved.
    (5) 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 [email protected]; internet 
http://www.bombardier.com.

[[Page 53567]]

    (6) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on October 12, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-23031 Filed 10-23-18; 8:45 am]
BILLING CODE 4910-13-P