Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 56680-56684 [2019-23076]

Download as PDF 56680 Federal Register / Vol. 84, No. 205 / Wednesday, October 23, 2019 / Rules and Regulations 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–19–02 The Boeing Company: Amendment 39–19738; Docket No. FAA– 2019–0524; Product Identifier 2019–NM– 081–AD. (a) Effective Date This AD is effective November 27, 2019. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747–400 and 747–400F series airplanes, certificated in any category, as identified in Boeing Alert Requirements Bulletin 747–53A2900 RB, dated April 11, 2019. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation that determined fatigue cracks could develop in the underwing longerons. The FAA is issuing this AD to address cracks in the underwing longerons, which could result in fuel leakage into the pressurized fuselage and increase the risk of a fire, and to address cracks in the adjacent fuselage skin, which could result in rapid decompression. Either condition could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Except as specified by paragraph (h) of this AD: At the applicable times specified in the ‘‘Compliance’’ paragraph of Boeing Alert Requirements Bulletin 747–53A2900 RB, dated April 11, 2019, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 747–53A2900 RB, dated April 11, 2019. Note 1 to paragraph (g): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 747–53A2900, dated April 11, 2019, which is referred to in Boeing Alert Requirements Bulletin 747–53A2900 RB, dated April 11, 2019. (h) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where Boeing Alert Requirements Bulletin VerDate Sep<11>2014 16:04 Oct 22, 2019 Jkt 250001 747–53A2900 RB, dated April 11, 2019, uses the phrase ‘‘the original issue date of Requirements Bulletin 747–53A2900 RB,’’ this AD requires using ‘‘the effective date of this AD.’’ (2) Where Boeing Alert Requirements Bulletin 747–53A2900 RB, dated April 11, 2019, specifies contacting Boeing for repair instructions: This AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (j) Related Information For more information about this AD, contact Eric Lin, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3523; email: eric.lin@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Requirements Bulletin 747–53A2900 RB, dated April 11, 2019. (ii) [Reserved] (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; phone: 562–797–1717; internet: https:// www.myboeingfleet.com. (4) 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. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on September 19, 2019. Suzanne Masterson, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–23074 Filed 10–22–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0493; Product Identifier 2019–NM–043–AD; Amendment 39–19762; AD 2019–20–09] RIN 2120–AA64 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2011–18– 15, which applied to certain De Havilland Aircraft of Canada Limited Model DHC–8–400 series airplanes. AD 2011–18–15 required initial and repetitive torque checks of the bolt preload; detailed inspection of the barrel nuts and cradle for cracking, pitting, and corrosion if the bolt preload is correct; and replacement of certain hardware if necessary. This AD continues to require those actions. This AD also requires new inspections and replacement of certain hardware, which would terminate the repetitive torque checks and inspections; and removes airplanes from the applicability. This AD was prompted by in-service reports of cracked barrel nuts found at the front spar locations of the wing-to-fuselage attachment joints, and a loose washer in the barrel nut assembly. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 27, 2019. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 27, 2019. SUMMARY: E:\FR\FM\23OCR1.SGM 23OCR1 Federal Register / Vol. 84, No. 205 / Wednesday, October 23, 2019 / Rules and Regulations For service information identified in this final rule, contact De Havilland Aircraft of Canada Ltd., QSeries Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 416–375–4000; fax: 416–375–4539; email: thd@ dehavilland.com; internet: https:// dehavilland.com. You may view this referenced service information at the FAA, 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–2019– 0493. 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–2019– 0493; 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 is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 516–228–7330; fax: 516– 794–5531; email: 9-avs-nyaco-cos@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2011–24R1, dated January 21, 2019 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain De Havilland Aircraft of Canada Limited Model DHC– 8–400 series airplanes. 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–2019– 0493. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–18–15, Amendment 39–16797 (76 FR 54093, August 31, 2011) (‘‘AD 2011–18–15’’). AD 2011–18–15 applied to certain De Havilland Aircraft of Canada Limited Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on July 9, 2019 (84 FR 32664). The NPRM was prompted by in-service reports of cracked barrel nuts found at the front spar locations of the wing-tofuselage attachment joints, and a loose washer in the barrel nut assembly. The NPRM proposed to continue to require initial and repetitive torque checks of the bolt preload; detailed inspection of the barrel nuts and cradle for cracking, pitting, and corrosion if the bolt preload is correct; and replacement of hardware if necessary. The NPRM also proposed to require new inspections and replacement of certain hardware, which would terminate the repetitive torque checks and inspections; and remove airplanes from the applicability. We are issuing this AD to address cracked barrel nuts and a loose washer in the barrel nut assembly, which could result in failure of the barrel nuts, compromising the structural integrity of the wing-to-fuselage attachments, and possible separation of the wing from the airplane during flight. See the MCAI for additional background information. Comments The FAA gave the public the opportunity to participate in developing this final rule. The FAA received no comments on the NPRM or on the determination of the cost to the public. Explanation of Changes Made to This Final Rule The FAA has revised this final rule to identify the legal name of the manufacturer as published in the most recent type certificate data sheet (TCDS) for the affected airplane models. The FAA has revised paragraph (n) of this AD to refer to De Havilland Aircraft 56681 of Canada Limited (the current TCDS holder) as the appropriate contact for the referenced repair drawing. Conclusion The FAA reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, with the changes described previously and minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. The FAA 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. • Service Bulletin A84–57–25, Revision A, dated July 16, 2018. This service information describes procedures for initial and repetitive torque checks of the bolt preload, detailed inspection of the barrel nuts and cradle for cracking, pitting, and corrosion if the bolt preload is correct, and replacement of hardware if necessary. • Service Bulletin 84–57–26, Revision C, dated July 16, 2018. This service information describes procedures for a visual inspection of the saddle washer and retainer for any damage (cracks) and corrosion, and replacement of the existing wing front spar barrel nuts, bolts, and preload indicating washers. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance The FAA estimates that this AD affects 54 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Retained actions from AD 2011–18–15 ......... New actions .................................................... 15 work-hours × $85 per hour = $1,275 ........ 15 work-hours × $85 per hour = $1,275 ........ VerDate Sep<11>2014 16:04 Oct 22, 2019 Jkt 250001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Parts cost $10,492 10,492 E:\FR\FM\23OCR1.SGM 23OCR1 Cost per product $11,767 11,767 Cost on U.S. operators $635,418 635,418 56682 Federal Register / Vol. 84, No. 205 / Wednesday, October 23, 2019 / Rules and Regulations The FAA has received no definitive data that would enable us to provide cost estimates for the on-condition repairs specified in this AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Authority for This Rulemaking Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. 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 The FAA determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. VerDate Sep<11>2014 16:04 Oct 22, 2019 Jkt 250001 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–18–15, Amendment 39–16797 (76 FR 54093, August 31, 2011), and adding the following new AD: ■ 2019–20–09 De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.): Amendment 39–19762; Docket No. FAA–2019–0493; Product Identifier 2019–NM–043–AD. (a) Effective Date This AD is effective November 27, 2019. (b) Affected ADs This AD replaces AD 2011–18–15, Amendment 39–16797 (76 FR 54093, August 31, 2011) (‘‘AD 2011–18–15’’). (c) Applicability This AD applies to De Havilland Aircraft of Canada Limited Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers 4001 through 4437 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by in-service reports of cracked barrel nuts found at the front spar locations of the wing-to-fuselage attachment joints, and a loose washer in the barrel nut assembly. The FAA is issuing this AD to address cracked barrel nuts and a loose washer in the barrel nut assembly, which could result in failure of the barrel nuts, compromising the structural integrity of the wing-to-fuselage attachments, and possible separation of the wing from the airplane during flight. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Initial and Repetitive Checks and Inspections, With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2011–18–15, with PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 revised service information. At the applicable time specified in paragraph (g)(1) or (2) of this AD: Do a torque check to determine if the bolt preload is correct, and if the preload is correct, before further flight, do a detailed inspection of each barrel nut and cradle for cracking, pitting or corrosion, in accordance with paragraph 3.B., part A, of the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57–25, dated July 20, 2011; or Bombardier Service Bulletin A84–57–25, Revision A, dated July 16, 2018. After the effective date of this AD, only Bombardier Service Bulletin A84–57–25, Revision A, dated July 16, 2018, may be used. Repeat the torque check and, as applicable, the inspection thereafter at intervals not to exceed 2,000 flight hours or 12 months, whichever occurs first. (1) For airplanes that have accumulated 1,900 or more total flight hours as of September 15, 2011 (the effective date of AD 2011–18–15), or for which it has been 12 months or more since the date of issuance of the original Canadian airworthiness certificate or the date of issuance of the original Canadian export certificate of airworthiness as of September 15, 2011: Within 100 flight hours or 10 days after September 15, 2011, whichever occurs first. (2) For airplanes that have accumulated less than 1,900 total flight hours as of September 15, 2011 (the effective date of AD 2011–18–15), and for which it has been less than 12 months since the date of issuance of the original Canadian airworthiness certificate or the date of issuance of the original Canadian export certificate of airworthiness as of September 15, 2011: Prior to the accumulation of 2,000 total flight hours or within 12 months since the date of issuance of the original Canadian standard airworthiness certificate or the date of issuance of the original Canadian export certificate of airworthiness, whichever occurs first. (h) Retained Corrective Actions for Incorrect Bolt Preload, With Revised Service Information This paragraph restates the requirements of paragraph (h) of AD 2011–18–15, with revised service information. If any bolt preload is found to be incorrect (i.e., the ring can be rotated during any torque check required by paragraph (g) of this AD), before further flight, replace all hardware at that location (except the saddle washer and retainer) in accordance with paragraph 3.B., part B, of the Accomplishment Instructions of Bombardier Alert Service Bulletin A84– 57–25, dated July 20, 2011; or paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–57–26, Revision C, dated July 16, 2018. After the effective date of this AD, only Bombardier Service Bulletin 84–57–26, Revision C, dated July 16, 2018, may be used. (i) Retained Corrective Actions for Barrel Nut/Cradle Discrepancies, With Revised Service Information This paragraph restates the requirements of paragraph (i) of AD 2011–18–15, with revised service information. If any crack, pitting, or corrosion of the barrel nut or cradle is found E:\FR\FM\23OCR1.SGM 23OCR1 Federal Register / Vol. 84, No. 205 / Wednesday, October 23, 2019 / Rules and Regulations during any inspection required by paragraph (g) of this AD, before further flight, replace all hardware at that location (except the saddle washer and retainer) in accordance with paragraph 3.B., part B, of the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57–25, dated July 20, 2011; or paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–57–26, Revision C, dated July 16, 2018. After the effective date of this AD, only Bombardier Service Bulletin 84– 57–26, Revision C, dated July 16, 2018, may be used. (j) New Requirement of This AD: Replacement and Visual Inspection Within 12,000 flight hours or 72 months after the effective date of this AD, whichever occurs first: Do a visual inspection of the saddle washer and retainer for any damage (cracks) or corrosion; and replace the wing front spar barrel nuts, bolts, and preload indicating washers; in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–57–26, Revision C, dated July 16, 2018. (k) New Corrective Actions for Damage (Cracks) or Corrosion If any damage (cracks) or corrosion is found during any inspection required by paragraph (j) of this AD: Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (p)(2) of this AD. (l) New Provision of This AD: Terminating Actions for Repetitive Torque Checks and Detailed Inspections Accomplishment of the applicable actions required by paragraphs (j) and (k) of this AD, at all four barrel nut locations, terminates the repetitive torque checks and detailed inspections of paragraph (g) of this AD. (m) Parts Installation Prohibition As of the effective date of this AD, no person may install, on any airplane, a barrel nut having part number DSC228–16. (n) Retained Special Flight Permit Provisions, With Revised Compliance Language This paragraph restates the requirements of paragraph (k) of AD 2011–18–15, with revised compliance language. Special flight permits, as described in 14 CFR 21.197 and 21.199, may be issued to operate the airplane to a location where the requirements of this AD can be accomplished, but concurrence by the Manager, New York ACO Branch, FAA, is required before issuance of the special flight permit. Before using any approved special flight permits, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office (FSDO). Operators must request a repair drawing from Bombardier, Inc., or De Havilland Aircraft of Canada Limited, which provides recommendations for a one-time special flight permit. After the effective date of this AD, only De Havilland Aircraft of Canada Limited may provide the repair drawing. The repair drawing will be applicable to the VerDate Sep<11>2014 16:04 Oct 22, 2019 Jkt 250001 operator’s aircraft serial number only. Special flight permits may be permitted provided that the conditions specified in paragraphs (n)(1) through (5) of this AD are met. (1) Only one barrel nut out of four is cracked, one cradle is cracked, or one washer is loose; all other strut (wing front spar) bolt locations must be free of damage. (2) The airplane must operate with reduced airspeed not to exceed 180 KIAS (knots indicated air speed). No passengers and no cargo are onboard. (3) The airplane must not operate in known or forecast turbulence, other than light turbulence. (4) The airplane descent rate on landing flare-out is not to exceed 5 feet per second. (5) Heavy braking or hard turning of the airplane upon landing is to be avoided if possible. (o) Credit for Previous Actions (1) This paragraph restates the provisions of paragraph (j) of AD 2011–18–15, with revised formatting and updated service information. This paragraph provides credit for torque checks, initial inspections, and replacements required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (o)(1)(i) through (v) of this AD, which is not incorporated by reference in this AD. The repetitive torque checks, and as applicable, the inspections required by paragraph (g) of this AD must be continued at the time specified. (i) Bombardier Alert Service Bulletin A84– 57–19, dated February 1, 2008. (ii) Bombardier Alert Service Bulletin A84– 57–19, Revision A, dated February 6, 2008. (iii) Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008. (iv) Bombardier Alert Service Bulletin A84–57–19, Revision C, dated August 20, 2008. (v) Bombardier Alert Service Bulletin A84– 57–19, Revision D, dated August 12, 2011. (2) This paragraph provides credit for the actions required by paragraphs (h) through (k) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (o)(2)(i) through (iii) of this AD. This service information is not incorporated by reference in this AD. (i) Bombardier Service Bulletin 84–57–26, dated March 21, 2013. (ii) Bombardier Service Bulletin 84–57–26, Revision A, dated July 18, 2014. (iii) Bombardier Service Bulletin 84–57–26, Revision B, dated February 26, 2015. (3) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (o)(3)(i) and (ii) of this AD. (i) Bombardier Alert Service Bulletin A84– 57–25, dated July 20, 2011, which was incorporated by reference in AD 2011–18–15. (ii) Bombardier Service Bulletin A84–57– 25, Revision A, dated July 16, 2018, which is incorporated by reference in this AD. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 56683 (p) 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; phone: 516– 228–7300; fax: 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain 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 De Havilland Aircraft of Canada Limited’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (3) AMOCs approved previously for AD 2011–18–15 are approved as AMOCs for the corresponding provisions of this AD. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2011–24R1, dated January 21, 2019, 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–2019–0493. (2) For more information about this AD, contact Andrea Jimenez, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 516– 228–7330; fax: 516–794–5531; email: 9-avsnyaco-cos@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(4) and (5) of this AD. (r) 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 27, 2019. (i) Bombardier Service Bulletin A84–57– 25, Revision A, dated July 16, 2018. (ii) Bombardier Service Bulletin 84–57–26, Revision C, dated July 16, 2018. (4) For service information identified in this AD, contact De Havilland Aircraft of Canada Ltd., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 416–375–4000; fax: E:\FR\FM\23OCR1.SGM 23OCR1 56684 Federal Register / Vol. 84, No. 205 / Wednesday, October 23, 2019 / Rules and Regulations 416–375–4539; email: thd@dehavilland.com; internet: https://dehavilland.com. (5) 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. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on October 7, 2019. Michael Kaszycki, Acting Manager, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–23076 Filed 10–22–19; 8:45 am] BILLING CODE 4910–13–P CONSUMER PRODUCT SAFETY COMMISSION 16 CFR Parts 1220 and 1221 [Docket No. CPSC–2019–0025] Revisions to Safety Standards for NonFull-Size Baby Cribs and Play Yards Consumer Product Safety Commission. ACTION: Direct final rule. AGENCY: The U.S. Consumer Product Safety Commission (CPSC) previously published consumer product safety standards for non-full-size baby cribs (NFS cribs) and play yards under section 104 of the Consumer Product Safety Improvement Act of 2008 (CPSIA). The standards incorporated by reference the ASTM voluntary standard for NFS cribs and play yards, with modifications. ASTM recently revised the voluntary standard for NFS cribs and play yards. The CPSIA provides a process for when a voluntary standards organization updates a standard that the Commission incorporated by reference in a section 104 rule. Consistent with that process, this direct final rule revises the mandatory standards for NFS cribs and play yards to incorporate by reference the updated version of the ASTM standard. DATES: The rule is effective on January 20, 2020, unless CPSC receives a significant adverse comment by November 22, 2019. If CPSC receives such a comment, it will publish a notice in the Federal Register, withdrawing this direct final rule before its effective date. The incorporation by reference of the publication listed in this rule is approved by the Director of the Federal Register as of January 20, 2020. SUMMARY: VerDate Sep<11>2014 16:04 Oct 22, 2019 Jkt 250001 You may submit comments, identified by Docket No. CPSC–2019– 0025, by any of the following methods: Electronic Submissions: Submit electronic comments to the Federal eRulemaking Portal at: www.regulations.gov. Follow the instructions for submitting comments provided on the website. To ensure timely processing of comments, please submit all electronic comments through www.regulations.gov, rather than by email to CPSC. Written Submissions: Submit written comments by mail, hand delivery, or courier to: U.S. Consumer Product Safety Commission, Division of the Secretariat, Room 820, 4330 East West Highway, Bethesda, MD 20814; telephone (301) 504–7923. Instructions: All submissions must include the agency name and docket number for this notice. CPSC may post all comments, without change, including any personal identifiers, contact information, or other personal information provided, to: http:// www.regulations.gov. Do not submit confidential business information, trade secret information, or other sensitive or protected information that you do not want to be available to the public. If furnished at all, submit such information by mail, hand delivery, or courier. Docket: For access to the docket to read background documents or comments, go to: http:// www.regulations.gov, and insert the docket number, CPSC–2019–0025, into the ‘‘Search’’ box, and follow the prompts. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Justin Jirgl, Compliance Officer, U.S. Consumer Product Safety Commission, 4330 East West Highway, Bethesda, MD 20814; email: jjirgl@cpsc.gov. SUPPLEMENTARY INFORMATION: A. Background and Statutory Authority 1. Initial Mandatory Standards for Durable Infant or Toddler Products Section 104 of the CPSIA (Pub. L. 110–314, 122 Stat. 3016) requires the Commission to assess the effectiveness of voluntary standards for durable infant or toddler products 1 and adopt mandatory standards for these products. 15 U.S.C. 2056a(b)(1). The mandatory standard must be ‘‘substantially the same as’’ the voluntary standard, or may be ‘‘more stringent than’’ the voluntary standard, if the Commission determines that more stringent requirements would 1 The statute lists NFS cribs and play yards as durable infant or toddler products. 15 U.S.C. 2056a(f)(2). PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 further reduce the risk of injury associated with the product. Id. Under this authority, the Commission adopted mandatory standards for NFS cribs and play yards in 16 CFR parts 1220 and 1221, respectively. The Commission defines NFS cribs and play yards in 16 CFR 1220.1(c). In general, a NFS crib is ‘‘a bed that is designed to provide sleeping accommodations for an infant’’ that meets specified dimensions.2 A play yard is a framed enclosure that includes a floor and mesh or fabric sides in which children sleep or play.3 The Commission’s mandatory standards incorporated by reference ASTM F406, Standard Consumer Safety Specification for Non-Full-Size Baby Cribs/Play Yards (ASTM F406), which is the voluntary standard for NFS cribs and play yards. The Commission issued separate rules for NFS cribs and play yards, although they are covered by the same voluntary standard, because section 104(c) of the CPSIA includes unique provisions for rules regarding cribs (both full-size and NFS cribs), applying initial crib standards to more parties than are ordinarily subject to section 104 rules.4 15 U.S.C. 2056a(c)(1), (2). 2 16 CFR 1220.1(c)(1) defines a NFS crib as ‘‘a bed that is: (i) Designed to provide sleeping accommodations for an infant; (ii) Intended for use in or around the home, for travel, in a child care facility, in a family child care home, in a place of public accommodation affecting commerce and other purposes; (iii) Has an interior length dimension either greater than 139.7 cm (55 in.) or smaller than 126.3 cm (493⁄4 in.), or, an interior width dimension either greater than 77.7 cm (305⁄8 in.) or smaller than 64.3 cm (253⁄8 in.), or both . . . (v) Does not include mesh/net/screen cribs, nonrigidly constructed baby cribs, cradles (both rocker and pendulum types), car beds, baby baskets, and bassinets (also known as junior cribs).’’ It further states that NFS cribs include, but are not limited to, portable cribs, crib pens, specialty cribs, undersize cribs, and oversize cribs, which the regulation also defines. 3 16 CFR 1220.1(c)(2) defines a play yard as ‘‘a framed enclosure that includes a floor and has mesh or fabric sided panels primarily intended to provide a play or sleeping environment for children. It may fold for storage or travel.’’ 4 Section 104(c) of the CPSIA requires more parties to comply with standards for cribs that the Commission adopts under section 104(b) than other durable infant or toddler product standards. Specifically, section 104(c) prohibits the following parties from manufacturing, selling, contracting to sell or resell, leasing, subletting, offering, providing for use, or otherwise placing in the stream of commerce a crib that is not in compliance with a standard promulgated under section 104(b): ‘‘any person that—(A) manufactures, distributes in commerce, or contracts to sell cribs; (B) based on the person’s occupation, holds itself out as having knowledge of skill peculiar to cribs, including child care facilities and family child care homes; (C) is in the business of contracting to sell or resell, lease, sublet, or otherwise place cribs in the stream of commerce; or (D) owns or operates a place of accommodation affecting commerce (as defined in section 4 of the Federal Fire Prevention and Control Act of 1974 (15 U.S.C. 2203) applied without regard E:\FR\FM\23OCR1.SGM 23OCR1

Agencies

[Federal Register Volume 84, Number 205 (Wednesday, October 23, 2019)]
[Rules and Regulations]
[Pages 56680-56684]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-23076]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0493; Product Identifier 2019-NM-043-AD; Amendment 
39-19762; AD 2019-20-09]
RIN 2120-AA64


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

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2011-18-
15, which applied to certain De Havilland Aircraft of Canada Limited 
Model DHC-8-400 series airplanes. AD 2011-18-15 required initial and 
repetitive torque checks of the bolt preload; detailed inspection of 
the barrel nuts and cradle for cracking, pitting, and corrosion if the 
bolt preload is correct; and replacement of certain hardware if 
necessary. This AD continues to require those actions. This AD also 
requires new inspections and replacement of certain hardware, which 
would terminate the repetitive torque checks and inspections; and 
removes airplanes from the applicability. This AD was prompted by in-
service reports of cracked barrel nuts found at the front spar 
locations of the wing-to-fuselage attachment joints, and a loose washer 
in the barrel nut assembly. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective November 27, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 27, 
2019.

[[Page 56681]]


ADDRESSES: For service information identified in this final rule, 
contact De Havilland Aircraft of Canada Ltd., Q-Series Technical Help 
Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 
416-375-4000; fax: 416-375-4539; email: [email protected]; internet: 
https://dehavilland.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-2019-0493.

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-2019-
0493; 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 is U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, 
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart 
Avenue, Suite 410, Westbury, NY 11590; phone: 516-228-7330; fax: 516-
794-5531; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2011-24R1, dated 
January 21, 2019 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain De Havilland Aircraft of Canada Limited Model 
DHC-8-400 series airplanes. 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-2019-0493.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2011-18-15, Amendment 39-16797 (76 FR 
54093, August 31, 2011) (``AD 2011-18-15''). AD 2011-18-15 applied to 
certain De Havilland Aircraft of Canada Limited Model DHC-8-400 series 
airplanes. The NPRM published in the Federal Register on July 9, 2019 
(84 FR 32664). The NPRM was prompted by in-service reports of cracked 
barrel nuts found at the front spar locations of the wing-to-fuselage 
attachment joints, and a loose washer in the barrel nut assembly. The 
NPRM proposed to continue to require initial and repetitive torque 
checks of the bolt preload; detailed inspection of the barrel nuts and 
cradle for cracking, pitting, and corrosion if the bolt preload is 
correct; and replacement of hardware if necessary. The NPRM also 
proposed to require new inspections and replacement of certain 
hardware, which would terminate the repetitive torque checks and 
inspections; and remove airplanes from the applicability. We are 
issuing this AD to address cracked barrel nuts and a loose washer in 
the barrel nut assembly, which could result in failure of the barrel 
nuts, compromising the structural integrity of the wing-to-fuselage 
attachments, and possible separation of the wing from the airplane 
during flight. See the MCAI for additional background information.

Comments

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

Explanation of Changes Made to This Final Rule

    The FAA has revised this final rule to identify the legal name of 
the manufacturer as published in the most recent type certificate data 
sheet (TCDS) for the affected airplane models.
    The FAA has revised paragraph (n) of this AD to refer to De 
Havilland Aircraft of Canada Limited (the current TCDS holder) as the 
appropriate contact for the referenced repair drawing.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
with the changes described previously and minor editorial changes. The 
FAA has determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    The FAA 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.
     Service Bulletin A84-57-25, Revision A, dated July 16, 
2018. This service information describes procedures for initial and 
repetitive torque checks of the bolt preload, detailed inspection of 
the barrel nuts and cradle for cracking, pitting, and corrosion if the 
bolt preload is correct, and replacement of hardware if necessary.
     Service Bulletin 84-57-26, Revision C, dated July 16, 
2018. This service information describes procedures for a visual 
inspection of the saddle washer and retainer for any damage (cracks) 
and corrosion, and replacement of the existing wing front spar barrel 
nuts, bolts, and preload indicating washers.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

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

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2011-18-15...  15 work-hours x $85 per          $10,492         $11,767        $635,418
                                         hour = $1,275.
New actions...........................  15 work-hours x $85 per           10,492          11,767         635,418
                                         hour = $1,275.
----------------------------------------------------------------------------------------------------------------


[[Page 56682]]

    The FAA has received no definitive data that would enable us to 
provide cost estimates for the on-condition repairs 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.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. 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

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-18-15, Amendment 39-16797 (76 FR 54093, August 31, 2011), and 
adding the following new AD:

2019-20-09 De Havilland Aircraft of Canada Limited (Type Certificate 
Previously Held by Bombardier, Inc.): Amendment 39-19762; Docket No. 
FAA-2019-0493; Product Identifier 2019-NM-043-AD.

(a) Effective Date

    This AD is effective November 27, 2019.

(b) Affected ADs

    This AD replaces AD 2011-18-15, Amendment 39-16797 (76 FR 54093, 
August 31, 2011) (``AD 2011-18-15'').

(c) Applicability

    This AD applies to De Havilland Aircraft of Canada Limited Model 
DHC-8-400, -401, and -402 airplanes, certificated in any category, 
serial numbers 4001 through 4437 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by in-service reports of cracked barrel 
nuts found at the front spar locations of the wing-to-fuselage 
attachment joints, and a loose washer in the barrel nut assembly. 
The FAA is issuing this AD to address cracked barrel nuts and a 
loose washer in the barrel nut assembly, which could result in 
failure of the barrel nuts, compromising the structural integrity of 
the wing-to-fuselage attachments, and possible separation of the 
wing from the airplane during flight.

(f) Compliance

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

(g) Retained Initial and Repetitive Checks and Inspections, With 
Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2011-18-15, with revised service information. At the applicable time 
specified in paragraph (g)(1) or (2) of this AD: Do a torque check 
to determine if the bolt preload is correct, and if the preload is 
correct, before further flight, do a detailed inspection of each 
barrel nut and cradle for cracking, pitting or corrosion, in 
accordance with paragraph 3.B., part A, of the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A84-57-25, dated 
July 20, 2011; or Bombardier Service Bulletin A84-57-25, Revision A, 
dated July 16, 2018. After the effective date of this AD, only 
Bombardier Service Bulletin A84-57-25, Revision A, dated July 16, 
2018, may be used. Repeat the torque check and, as applicable, the 
inspection thereafter at intervals not to exceed 2,000 flight hours 
or 12 months, whichever occurs first.
    (1) For airplanes that have accumulated 1,900 or more total 
flight hours as of September 15, 2011 (the effective date of AD 
2011-18-15), or for which it has been 12 months or more since the 
date of issuance of the original Canadian airworthiness certificate 
or the date of issuance of the original Canadian export certificate 
of airworthiness as of September 15, 2011: Within 100 flight hours 
or 10 days after September 15, 2011, whichever occurs first.
    (2) For airplanes that have accumulated less than 1,900 total 
flight hours as of September 15, 2011 (the effective date of AD 
2011-18-15), and for which it has been less than 12 months since the 
date of issuance of the original Canadian airworthiness certificate 
or the date of issuance of the original Canadian export certificate 
of airworthiness as of September 15, 2011: Prior to the accumulation 
of 2,000 total flight hours or within 12 months since the date of 
issuance of the original Canadian standard airworthiness certificate 
or the date of issuance of the original Canadian export certificate 
of airworthiness, whichever occurs first.

(h) Retained Corrective Actions for Incorrect Bolt Preload, With 
Revised Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2011-18-15, with revised service information. If any bolt preload is 
found to be incorrect (i.e., the ring can be rotated during any 
torque check required by paragraph (g) of this AD), before further 
flight, replace all hardware at that location (except the saddle 
washer and retainer) in accordance with paragraph 3.B., part B, of 
the Accomplishment Instructions of Bombardier Alert Service Bulletin 
A84-57-25, dated July 20, 2011; or paragraph 3.B. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-57-26, 
Revision C, dated July 16, 2018. After the effective date of this 
AD, only Bombardier Service Bulletin 84-57-26, Revision C, dated 
July 16, 2018, may be used.

(i) Retained Corrective Actions for Barrel Nut/Cradle Discrepancies, 
With Revised Service Information

    This paragraph restates the requirements of paragraph (i) of AD 
2011-18-15, with revised service information. If any crack, pitting, 
or corrosion of the barrel nut or cradle is found

[[Page 56683]]

during any inspection required by paragraph (g) of this AD, before 
further flight, replace all hardware at that location (except the 
saddle washer and retainer) in accordance with paragraph 3.B., part 
B, of the Accomplishment Instructions of Bombardier Alert Service 
Bulletin A84-57-25, dated July 20, 2011; or paragraph 3.B. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-57-26, 
Revision C, dated July 16, 2018. After the effective date of this 
AD, only Bombardier Service Bulletin 84-57-26, Revision C, dated 
July 16, 2018, may be used.

(j) New Requirement of This AD: Replacement and Visual Inspection

    Within 12,000 flight hours or 72 months after the effective date 
of this AD, whichever occurs first: Do a visual inspection of the 
saddle washer and retainer for any damage (cracks) or corrosion; and 
replace the wing front spar barrel nuts, bolts, and preload 
indicating washers; in accordance with paragraph 3.B. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-57-26, 
Revision C, dated July 16, 2018.

(k) New Corrective Actions for Damage (Cracks) or Corrosion

    If any damage (cracks) or corrosion is found during any 
inspection required by paragraph (j) of this AD: Before further 
flight, accomplish corrective actions in accordance with the 
procedures specified in paragraph (p)(2) of this AD.

(l) New Provision of This AD: Terminating Actions for Repetitive Torque 
Checks and Detailed Inspections

    Accomplishment of the applicable actions required by paragraphs 
(j) and (k) of this AD, at all four barrel nut locations, terminates 
the repetitive torque checks and detailed inspections of paragraph 
(g) of this AD.

(m) Parts Installation Prohibition

    As of the effective date of this AD, no person may install, on 
any airplane, a barrel nut having part number DSC228-16.

(n) Retained Special Flight Permit Provisions, With Revised Compliance 
Language

    This paragraph restates the requirements of paragraph (k) of AD 
2011-18-15, with revised compliance language. Special flight 
permits, as described in 14 CFR 21.197 and 21.199, may be issued to 
operate the airplane to a location where the requirements of this AD 
can be accomplished, but concurrence by the Manager, New York ACO 
Branch, FAA, is required before issuance of the special flight 
permit. Before using any approved special flight permits, notify 
your principal maintenance inspector (PMI) or principal avionics 
inspector (PAI), as appropriate, or lacking a principal inspector, 
your local Flight Standards District Office (FSDO). Operators must 
request a repair drawing from Bombardier, Inc., or De Havilland 
Aircraft of Canada Limited, which provides recommendations for a 
one-time special flight permit. After the effective date of this AD, 
only De Havilland Aircraft of Canada Limited may provide the repair 
drawing. The repair drawing will be applicable to the operator's 
aircraft serial number only. Special flight permits may be permitted 
provided that the conditions specified in paragraphs (n)(1) through 
(5) of this AD are met.
    (1) Only one barrel nut out of four is cracked, one cradle is 
cracked, or one washer is loose; all other strut (wing front spar) 
bolt locations must be free of damage.
    (2) The airplane must operate with reduced airspeed not to 
exceed 180 KIAS (knots indicated air speed). No passengers and no 
cargo are onboard.
    (3) The airplane must not operate in known or forecast 
turbulence, other than light turbulence.
    (4) The airplane descent rate on landing flare-out is not to 
exceed 5 feet per second.
    (5) Heavy braking or hard turning of the airplane upon landing 
is to be avoided if possible.

(o) Credit for Previous Actions

    (1) This paragraph restates the provisions of paragraph (j) of 
AD 2011-18-15, with revised formatting and updated service 
information. This paragraph provides credit for torque checks, 
initial inspections, and replacements required by paragraphs (g) and 
(h) of this AD, if those actions were performed before the effective 
date of this AD using the service information specified in 
paragraphs (o)(1)(i) through (v) of this AD, which is not 
incorporated by reference in this AD. The repetitive torque checks, 
and as applicable, the inspections required by paragraph (g) of this 
AD must be continued at the time specified.
    (i) Bombardier Alert Service Bulletin A84-57-19, dated February 
1, 2008.
    (ii) Bombardier Alert Service Bulletin A84-57-19, Revision A, 
dated February 6, 2008.
    (iii) Bombardier Alert Service Bulletin A84-57-19, Revision B, 
dated March 6, 2008.
    (iv) Bombardier Alert Service Bulletin A84-57-19, Revision C, 
dated August 20, 2008.
    (v) Bombardier Alert Service Bulletin A84-57-19, Revision D, 
dated August 12, 2011.
    (2) This paragraph provides credit for the actions required by 
paragraphs (h) through (k) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (o)(2)(i) through (iii) of this 
AD. This service information is not incorporated by reference in 
this AD.
    (i) Bombardier Service Bulletin 84-57-26, dated March 21, 2013.
    (ii) Bombardier Service Bulletin 84-57-26, Revision A, dated 
July 18, 2014.
    (iii) Bombardier Service Bulletin 84-57-26, Revision B, dated 
February 26, 2015.
    (3) This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using the service information 
specified in paragraphs (o)(3)(i) and (ii) of this AD.
    (i) Bombardier Alert Service Bulletin A84-57-25, dated July 20, 
2011, which was incorporated by reference in AD 2011-18-15.
    (ii) Bombardier Service Bulletin A84-57-25, Revision A, dated 
July 16, 2018, which is incorporated by reference in this AD.

(p) 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; phone: 516-228-7300; fax: 516-794-5531. Before 
using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain 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 De 
Havilland Aircraft of Canada Limited's TCCA Design Approval 
Organization (DAO). If approved by the DAO, the approval must 
include the DAO-authorized signature.
    (3) AMOCs approved previously for AD 2011-18-15 are approved as 
AMOCs for the corresponding provisions of this AD.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2011-24R1, dated January 21, 2019, 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-2019-0493.
    (2) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: 516-228-7330; fax: 516-794-5531; email: [email protected].
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(4) and (5) of this AD.

(r) 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 27, 2019.
    (i) Bombardier Service Bulletin A84-57-25, Revision A, dated 
July 16, 2018.
    (ii) Bombardier Service Bulletin 84-57-26, Revision C, dated 
July 16, 2018.
    (4) For service information identified in this AD, contact De 
Havilland Aircraft of Canada Ltd., Q-Series Technical Help Desk, 123 
Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 416-375-
4000; fax:

[[Page 56684]]

416-375-4539; email: [email protected]; internet: https://dehavilland.com.
    (5) 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.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email [email protected], or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on October 7, 2019.
Michael Kaszycki,
Acting Manager, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-23076 Filed 10-22-19; 8:45 am]
 BILLING CODE 4910-13-P