83 FR 53563 - Airworthiness Directives; Bombardier, Inc., Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 206 (October 24, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 206 (October 24, 2018)
| Page Range | 53563-53567 | |
| FR Document | 2018-23031 |
[Federal Register Volume 83, Number 206 (Wednesday, October 24, 2018)] [Rules and Regulations] [Pages 53563-53567] From the Federal Register Online [www.thefederalregister.org] [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
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Rules and Regulations Federal Register
Vol. 83, No. 206
Wednesday, October 24, 2018
This section of the FEDERAL REGISTER ADDRESSES: For service information new service information that includes a
contains regulatory documents having general identified in this final rule, contact terminal modification. The NPRM
applicability and legal effect, most of which Bombardier, Inc., Q-Series Technical proposed to continue to require
are keyed to and codified in the Code of Help Desk, 123 Garratt Boulevard, repetitive detailed inspections of each
Federal Regulations, which is published under Toronto, Ontario M3K 1Y5, Canada; barrel nut and cradle, a check of the bolt
50 titles pursuant to 44 U.S.C. 1510.
telephone 416–375–4000; fax 416–375– torque of the PLI washers, and
The Code of Federal Regulations is sold by 4539; email thd.qseries@ corrective action if necessary. The
the Superintendent of Documents. aero.bombardier.com; internet http:// NPRM also proposed to require
www.bombardier.com. You may view modifying the airplane by installing a
this referenced service information at sealing disk to a certain location and
DEPARTMENT OF TRANSPORTATION the FAA, Transport Standards Branch, replacing certain barrel nuts. We are
2200 South 216th St., Des Moines, WA. issuing this AD to address cracked and
Federal Aviation Administration For information on the availability of corroded barrel nuts, which could
this material at the FAA, call 206–231– compromise the structural integrity of
14 CFR Part 39 3195. It is also available on the internet the vertical-stabilizer attachment joints
[Docket No. FAA–2018–0160; Product at http://www.regulations.gov by and lead to loss of control of the
Identifier 2017–NM–139–AD; Amendment searching for and locating Docket No. airplane.
39–19476; AD 2018–22–03] FAA–2018–0160. Transport Canada Civil Aviation
(TCCA), which is the aviation authority
RIN 2120–AA64 Examining the AD Docket for Canada, has issued Canadian AD
Airworthiness Directives; Bombardier, You may examine the AD docket on CF–2015–13R1, dated June 26, 2017
Inc., Airplanes the internet at http:// (referred to after this as the Mandatory
www.regulations.gov by searching for Continuing Airworthiness Information,
AGENCY: Federal Aviation and locating Docket No. FAA–2018– or ‘‘the MCAI’’), to correct an unsafe
Administration (FAA), Department of 0160; or in person at Docket Operations condition for certain Bombardier, Inc.,
Transportation (DOT). between 9 a.m. and 5 p.m., Monday Model DHC–8–400 series airplanes. The
ACTION: Final rule. through Friday, except Federal holidays. MCAI states:
The AD docket contains this final rule, There has been one in-service report of a
SUMMARY: We are superseding the regulatory evaluation, any cracked and corroded barrel nut, part number
Airworthiness Directive (AD) 2016–24– comments received, and other (P/N) DSC228–12, found at the mid-spar
03, which applied to certain information. The address for Docket location of the horizontal stabilizer to vertical
Bombardier, Inc., Model DHC–8–400 Operations (phone: 800–647–5527) is stabilizer attachment joint. There have also
series airplanes. AD 2016–24–03 U.S. Department of Transportation, been two other reports of corroded barrel
required repetitive detailed inspections Docket Operations, M–30, West nuts found at mid-spar locations.
of barrel nuts and cradles, a check of the Preliminary investigation determined that
Building Ground Floor, Room W12–140,
the cracking is initiated by corrosion. Further
bolt torque of the preload indicating 1200 New Jersey Avenue SE, investigation confirmed that the corrosion
(PLI) washers, and corrective actions if Washington, DC 20590. was caused by inadequate cadmium plating
necessary. This AD retains the FOR FURTHER INFORMATION CONTACT: Aziz on the barrel nuts. Failure of the barrel nuts
requirements of AD 2016–24–03 and Ahmed, Aerospace Engineer, Airframe could compromise the structural integrity of
requires modifying the airplane by and Propulsion Section, FAA, New York the joint and could lead to loss of control of
installing a sealing disk to a certain ACO Branch, 1600 Stewart Avenue, the aeroplane.
location and replacing certain barrel The original version of this [Canadian] AD
Suite 410, Westbury, NY 11590; was issued to mandate the initial and
nuts. This AD was prompted by reports telephone 516–228–7329; fax 516–794– repetitive inspections of the barrel nuts [and
of cracked and corroded barrel nuts 5531; email 9-avs-nyaco-cos@faa.gov. cradles for cracks and corrosion] at each of
found at the mid-spar location of the SUPPLEMENTARY INFORMATION: the horizontal stabilizer to vertical stabilizer
horizontal-stabilizer-to-vertical- attachment joints.
stabilizer attachment joint, and the Discussion Revision 1 of this [Canadian] AD is issued
issuance of new service information that We issued a notice of proposed to terminate the repetitive inspection
includes a terminal modification. We rulemaking (NPRM) to amend 14 CFR requirement by requiring the incorporation of
are issuing this AD to address the unsafe a modification to install a sealing disc at the
part 39 to supersede AD 2016–24–03, middle spar location of the horizontal
condition on these products. Amendment 39–18720 (81 FR 88623, stabilizer to vertical stabilizer attachment
DATES: This AD is effective November December 8, 2016) (‘‘AD 2016–24–03’’). joint, and the replacement of the DSC228
28, 2018. AD 2016–24–03 applied to certain series barrel nuts with B0203073 series barrel
The Director of the Federal Register Bombardier, Inc., Model DHC–8–400 nuts that are more resistant to corrosion. The
approved the incorporation by reference series airplanes. The NPRM published applicability has been changed to account for
of certain publications listed in this AD in the Federal Register on March 9, the introduction of the modifications in
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as of November 28, 2018. 2018 (83 FR 10408). The NPRM was production.
The Director of the Federal Register prompted by reports of cracked and You may examine the MCAI in the
approved the incorporation by reference corroded barrel nuts found at the mid- AD docket on the internet at http://
of certain other publications listed in spar location of the horizontal- www.regulations.gov by searching for
this AD as of January 12, 2017 (81 FR stabilizer-to-vertical-stabilizer and locating Docket No. FAA–2018–
88623, December 8, 2016). attachment joint, and the issuance of 0160.
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![Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 / Rules and Regulations 53565
In accordance with that order, issuance (b) Affected ADs (h) Retained Corrective Actions, Detailed
of ADs is normally a function of the This AD replaces AD 2016–24–03, Inspection, and Repetitive Inspections, With
Compliance and Airworthiness Amendment 39–18720 (81 FR 88623, New Service Information, Reference to
Division, but during this transition December 8, 2016) (‘‘AD 2016–24–03’’). Terminating Action, and Reference to
Corrective Actions
period, the Executive Director has (c) Applicability
delegated the authority to issue ADs This paragraph restates the requirements of
This AD applies to Bombardier, Inc., paragraph (h) of AD 2016–24–03, with new
applicable to transport category
Model DHC–8–400, –401 and –402 airplanes, service information and terminating action.
airplanes and associated appliances to Depending on the findings of any inspection
certificated in any category, serial numbers
the Director of the System Oversight 4001 and subsequent. required by paragraphs (g) and (j) of this AD,
Division. do the applicable actions in paragraphs
(d) Subject (h)(1), (h)(2), (h)(3), and (h)(4) of this AD.
Regulatory Findings Accomplishment of the actions required by
Air Transport Association (ATA) of
We determined that this AD will not America Code 55, Stabilizers. paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of
have federalism implications under (e) Reason this paragraph.
Executive Order 13132. This AD will (1) If any barrel nut or cradle is found
This AD was prompted by reports of
not have a substantial direct effect on cracked and corroded barrel nuts found at the cracked or broken, before further flight,
the States, on the relationship between mid-spar location of the horizontal-stabilizer- replace the barrel nut and associated
the national government and the States, to-vertical-stabilizer attachment joint, and the hardware, in accordance with paragraph 3.B.,
or on the distribution of power and issuance of new service information that ‘‘Procedure,’’ of the Accomplishment
responsibilities among the various Instructions of Bombardier Service Bulletin
includes a terminal modification. We are
levels of government. 84–55–08, Revision A, dated August 2, 2017.
issuing this AD to address cracked and
(i) Concurrently with the replacement of
For the reasons discussed above, I corroded barrel nuts, which could
any barrel nut, do a detailed inspection for
certify that this AD: compromise the structural integrity of the corrosion and damage of the bore of the
vertical-stabilizer attachment joints and lead fitting, in accordance with paragraph 3.B.,
1. Is not a ‘‘significant regulatory to loss of control of the airplane. ‘‘Procedure,’’ of the Accomplishment
action’’ under Executive Order 12866; Instructions of Bombardier Service Bulletin
(f) Compliance
2. Is not a ‘‘significant rule’’ under the 84–55–08, Revision A, dated August 2, 2017,
DOT Regulatory Policies and Procedures Comply with this AD within the and, before further flight, repair all corrosion
compliance times specified, unless already and damage, in accordance with Bombardier
(44 FR 11034, February 26, 1979);
done. Repair Drawing (RD) 8/4–55–1143, Issue 1,
3. Will not affect intrastate aviation in dated May 21, 2015; or Bombardier RD 8/4–
Alaska; and (g) Retained Detailed Inspection of Barrel
Nuts for Cracks and Corrosion, With No 55–1143, Issue 2, dated May 25, 2015. If the
4. Will not have a significant Changes bore of the fitting cannot be repaired in
economic impact, positive or negative, accordance with Bombardier RD 8/4–55–
This paragraph restates the requirements of 1143, Issue 1, dated May 21, 2015; or
on a substantial number of small entities paragraphs (g)(1) and (g)(2) of AD 2016–24– Bombardier RD 8/4–55–1143, Issue 2, dated
under the criteria of the Regulatory 03, with no changes. May 25, 2015; accomplish corrective actions
Flexibility Act. (1) For airplanes that have accumulated in accordance with the procedures specified
5,400 flight hours or more, or have been in in paragraph (q)(2) of this AD. As of the
List of Subjects in 14 CFR Part 39
service 32 months or more since the date of effective date of this AD, use Bombardier RD
Air transportation, Aircraft, Aviation issuance of the original certificate of 8/4–55–1143, Issue 2, dated May 25, 2015,
airworthiness or the date of issuance of the for the repair required by this paragraph.
safety, Incorporation by reference,
original export certificate of airworthiness, as (ii) Within 600 flight hours or 4 months,
Safety. whichever occurs first, after the replacement
of January 12, 2017 (the effective date of AD
Adoption of the Amendment 2016–24–03): Within 600 flight hours or 4 of a cracked barrel nut, replace the remaining
months, whichever occurs first after January barrel nuts and their associated hardware at
Accordingly, under the authority 12, 2017, do a detailed visual inspection for the horizontal-stabilizer-to-vertical-stabilizer
delegated to me by the Administrator, signs of cracks and corrosion of the barrel nut attachment joints, in accordance with
the FAA amends 14 CFR part 39 as and cradle, in accordance with paragraph paragraph 3.B., ‘‘Procedure,’’ of the
Accomplishment Instructions of Bombardier
follows: 3.B., ‘‘Procedure,’’ of the Accomplishment
Service Bulletin 84–55–08, Revision A, dated
Instructions of Bombardier Alert Service
August 2, 2017.
PART 39—AIRWORTHINESS Bulletin A84–55–04, Revision C, dated May
(2) If any corrosion is found on any barrel
DIRECTIVES 3, 2016. nut on the front or rear-spar joints, before
(2) For airplanes that have less than 5,400 further flight, replace the barrel nut in
■ 1. The authority citation for part 39 flight hours, and have been in-service for less accordance with paragraph 3.B.,
than 32 months since the date of issuance of ‘‘Procedure,’’ of the Accomplishment
continues to read as follows:
the original certificate of airworthiness or the Instructions of Bombardier Service Bulletin
Authority: 49 U.S.C. 106(g), 40113, 44701. date of issuance of the original export 84–55–08, Revision A, dated August 2, 2017,
certificate of airworthiness, as of January 12, or accomplish corrective actions in
§ 39.13 [Amended] 2017: Before the accumulation of 6,000 total accordance with the procedures specified in
flight hours or 36 months since the date of paragraph (q)(2) of this AD.
■ 2. The FAA amends § 39.13 by
issuance of the original certificate of (3) If any corrosion above level 1, as
removing Airworthiness Directive (AD) airworthiness or the date of issuance of the defined in Bombardier Alert Service Bulletin
2016–24–03, Amendment 39–18720 (81 original export certificate of airworthiness, A84–55–04, Revision C, dated May 3, 2016,
FR 88623, December 8, 2016), and whichever occurs first, do a detailed visual is found on a barrel nut at the mid-spar joint,
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adding the following new AD: inspection of the barrel nut for signs of cracks before further flight, replace the barrel nut
2018–22–03 Bombardier, Inc.: Amendment and corrosion of the barrel nut and cradle, in and accomplish corrective actions in
39–19476; Docket No. FAA–2018–0160; accordance with paragraph 3.B., accordance with the procedures specified in
Product Identifier 2017–NM–139–AD. ‘‘Procedure,’’ of the Accomplishment paragraph (q)(2) of this AD.
Instructions of Bombardier Alert Service (4) If all corrosion found is at level 1 or
(a) Effective Date Bulletin A84–55–04, Revision C, dated May below, as defined in Bombardier Alert
This AD is effective November 28, 2018. 3, 2016. Service Bulletin A84–55–04, Revision C,
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![Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 / Rules and Regulations 53567
(6) You may view this service information For service information identified in received on the proposal and the FAA’s
at the FAA, Transport Standards Branch, this AD, contact Viking Air Limited response to each comment.
2200 South 216th St., Des Moines, WA. For Technical Support, 1959 De Havilland
information on the availability of this
Way, Sidney, British Columbia, Canada, Request To Issue SAIB Instead of an AD
material at the FAA, call 206–231–3195.
(7) You may view this service information V8L 5V5; telephone: (North America) Christopher Campbell requested that
that is incorporated by reference at the (800) 663–8444; fax: (250) 656–0673; we withdraw the AD and issue a special
National Archives and Records email: technical.support@vikingair.com; airworthiness information bulletin
Administration (NARA). For information on internet: http://www.vikingair.com/ (SAIB) instead. The commenter stated
the availability of this material at NARA, call support/service-bulletins. You may view
202–741–6030, or go to: http:// this AD is unnecessary and redundant
this referenced service information at
www.archives.gov/federal-register/cfr/ibr- since the manufacturer has already
the FAA, Policy and Innovation
locations.html. addressed this issue with a mandatory
Division, 901 Locust, Kansas City,
Issued in Des Moines, Washington, on service bulletin and all affected bolts
Missouri 64106. For information on the
October 12, 2018. availability of this material at the FAA, should now be removed. The
Michael Kaszycki, call (816) 329–4148. It is also available commenter stated the affected bolts are
Acting Director, System Oversight Division, on the internet at http:// 3/4-inch diameter bolts and only the
Aircraft Certification Service. www.regulations.gov by searching for surface cadmium plating is
[FR Doc. 2018–23031 Filed 10–23–18; 8:45 am] Docket No. FAA–2018–0189. compromised, not the strength of the
BILLING CODE 4910–13–P bolt. The commenter also disagreed
FOR FURTHER INFORMATION CONTACT: Aziz
with the manufacturer that the
Ahmed, Aerospace Engineer, FAA, New
York ACO Branch, 1600 Stewart compromised cadmium plating would
DEPARTMENT OF TRANSPORTATION cause accelerated corrosion because the
Avenue, Suite 410, Westbury, New York
11590; telephone: (516) 287–7329; fax: bolts are treated with anti-corrosion
Federal Aviation Administration grease on installation. The commenter
(516) 794–5531; email: aziz.ahmed@
faa.gov. further stated an AD is unnecessary
14 CFR Part 39
because the defect would be obvious to
[Docket No. FAA–2018–0189; Product SUPPLEMENTARY INFORMATION: any installing mechanic. Lastly, the
Identifier 2017–CE–022–AD; Amendment Discussion commenter stated that the proposed AD
39–19460; AD 2018–21–02] does little to further enhance safety but
We issued a notice of proposed
RIN 2120–AA64 adds unwelcome recordkeeping and
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would cost for owners.
Airworthiness Directives; Viking Air
Limited Airplanes apply to Viking Air Limited Model We do not agree. We concur with
DHC–3 airplanes. The NPRM was Transport Canada’s finding of an unsafe
AGENCY: Federal Aviation published in the Federal Register on condition, as explained in Transport
Administration (FAA), Department of March 13, 2018 (83 FR 10809). The Canada AD No. CF–2017–11, dated
Transportation (DOT). NPRM proposed to correct an unsafe March 23, 2017. An SAIB would not be
ACTION: Final rule. condition for the specified products and an appropriate solution. An SAIB
was based on MCAI originated by an contains information and recommended
SUMMARY: We are adopting a new aviation authority of another country. actions that are voluntary and not
airworthiness directive (AD) for Viking The MCAI states:
Air Limited Model DHC–3 airplanes. regulatory. Moreover, an SAIB is issued
This AD results from mandatory Pitting corrosion has been found on the only for airworthiness concerns that do
continuing airworthiness information shank of the following part number wing not rise to the level of an unsafe
strut attach bolts: C3W114–3, C3W129–3 and condition. Similarly, while an operator
(MCAI) issued by an aviation authority
C3W128–3. These bolts are manufactured may incorporate the procedures
of another country to identify and using a standard AN12 bolt. Metallurgical
correct an unsafe condition on an described in a manufacturer’s service
evaluation concluded that pitting corrosion
aviation product. The MCAI describes was present on the affected AN12 bolts prior
bulletin into its maintenance program,
the unsafe condition as pitting corrosion to forming of the bolt head and threads. The not all operators are required to do so.
on the shank of the wing strut attach pitting and un-plated voids could cause a For the corrective actions in a service
bolts. We are issuing this AD to require surface condition that may have a bulletin to become mandatory and to
actions to address the unsafe condition detrimental effect on fatigue and corrosion correct the unsafe condition, the FAA
on these products. resistance, leading to bolt failure and must issue an AD. Based on the
consequent failure of the wing. manufacturer’s metallurgical evaluation,
DATES: This AD is effective November Viking has not been able to confirm the
28, 2018. the pitting corrosion was present on the
affected batch numbers or specific
The Director of the Federal Register manufacture date range. New wing strut bolts affected AN 12 bolts prior to forming of
approved the incorporation by reference manufactured after 21 March 2016 are the bolt head and thread. Corrosion
of a certain publication listed in the AD inspected for pitting during manufacturing pitting was found on airplanes when
as of November 28, 2018. and issued new P/Ns C3W114–5, C3W129– doing the inspections per Transport
ADDRESSES: You may examine the AD 5 and C3W128–5 under MOD 3/1010. Canada’s AD CF–2017–11. Specifically,
docket on the internet at http:// The MCAI can be found in the AD the pitting was discovered on the bolt
www.regulations.gov by searching for docket on the internet at: https:// shanks of both wing strut fitting to wing
and locating Docket No. FAA–2018– www.regulations.gov/document spar lug bolts. Relying on an assumption
amozie on DSK3GDR082PROD with RULES
0189; or in person at Docket Operations, ?D=FAA-2018-0189-0002. that the corrosion will be obvious at the
U.S. Department of Transportation, time of bolts installation, as suggested
Docket Operations, M–30, West Comments by the commenter, is not a reliable
Building Ground Floor, Room W12–140, We gave the public the opportunity to method to correct an unsafe condition.
1200 New Jersey Avenue SE, participate in developing this AD. The We have not changed this AD based on
Washington, DC 20590. following presents the comments this comment.
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Document Created: 2018-10-24 00:23:57
Document Modified: 2018-10-24 00:23:57
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 28, 2018. | |
| 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] | |
| FR Citation | 83 FR 53563 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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