Source: https://regulations.justia.com/regulations/fedreg/2019/12/30/2019-28072.html
Timestamp: 2020-07-14 14:35:16
Document Index: 223049627

Matched Legal Cases: ['art 39', 'art 39', 'art 51', 'art 39', 'art 39', 'ART 39', 'art 39', '§ 39', '§ 39', 'art 39', 'art 51', 'art 39', 'art 39']

Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 71785-71788 [2019-28072] :: Federal Aviation Administration :: Department Of Transportation :: Regulation Tracker :: Justia
Justia Regulation Tracker Department Of Transportation Federal Aviation Administration Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 71785-71788 [2019-28072]
Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 71785-71788 [2019-28072]
Download as PDF Federal Register / Vol. 84, No. 249 / Monday, December 30, 2019 / Rules and Regulations internet: www.easa.europa.eu. You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. (4) You may view this material 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. This material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0674. (5) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@ nara.gov, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Issued in Des Moines, Washington, on December 9, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–28067 Filed 12–27–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0675; Product Identifier 2019–NM–068–AD; Amendment 39–19815; AD 2019–24–12] 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 adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC–8–401 and –402 airplanes. This AD was prompted by a report that certain fuselages were delivered with nonconforming keel tension fittings and stringer end fittings. This AD requires a detailed visual inspection of stringer end fittings and keel fittings for loose or working fasteners, signs of wear, and corrosion, and repair if necessary; and a general visual inspection of the keel tension fitting and stringer end fittings, as applicable, and repairs and replacement of the keel and stringer end fittings if necessary. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 3, 2020. The Director of the Federal Register approved the incorporation by reference khammond on DSKJM1Z7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:33 Dec 27, 2019 Jkt 250001 of certain publications listed in this AD as of February 3, 2020. ADDRESSES: For Bombardier, Inc., or De Havilland Aircraft of Canada Limited service information identified in this final rule, contact De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 416–375–4000; fax: 416–375– 4539; email: thd@dehavilland.com; internet: https://dehavilland.com. 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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0675. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0675; 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–2019–06, dated February 18, 2019 (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain De Havilland Aircraft of Canada Limited Model DHC– 8–401 and –402 airplanes. You may examine the MCAI in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0675. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would PO 00000 Frm 00051 Fmt 4700 Sfmt 4700 71785 apply to certain Bombardier, Inc., Model DHC–8–401 and –402 airplanes. The NPRM published in the Federal Register on September 9, 2019 (84 FR 47170). The NPRM was prompted by a report that certain fuselages were delivered with non-conforming keel tension fittings and stringer end fittings. The NPRM proposed to require a detailed visual inspection of stringer end fittings and keel fittings for loose or working fasteners, signs of wear, and corrosion, and repair if necessary; and a general visual inspection of the keel tension fitting and stringer end fittings, as applicable, and repairs and replacement of the keel and stringer end fittings if necessary. The FAA is issuing this AD to address non-conforming keel tension fittings and stringer end fittings, which could lead to premature cracking and corrosion in several locations and compromise the structural integrity of the fuselage joints. See the MCAI for additional background information. Comments The FAA gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Update the Design Approval Holder (DAH) for the Affected Airplanes Horizon Air requested that the FAA update the DAH for the affected airplanes. Horizon Air pointed out that De Havilland Aircraft of Canada Limited is now the DAH for the Model DHC–8– 401 and –402 airplanes. The FAA agrees with the commenter for the reasons provided and has updated this final rule accordingly. Request To Include Revised Service Information and Credit for Previous Revision Horizon Air requested that the FAA update the final rule to include revised service information. Horizon Air mentioned that De Havilland Aircraft of Canada Limited has issued Service Bulletin 84–53–75, Revision A, dated August 2, 2019. Horizon Air also requested that the FAA give credit for accomplishment of the required actions prior to the effective date of this AD using Bombardier Service Bulletin 84– 53–75, dated August 29, 2018. The FAA agrees with the commenter for the reasons provided and has updated this final rule to refer to De Havilland Aircraft of Canada Limited Service Bulletin 84–53–75, Revision A, dated August 2, 2019. The FAA has determined that no additional work is E:\FR\FM\30DER1.SGM 30DER1 71786 Federal Register / Vol. 84, No. 249 / Monday, December 30, 2019 / Rules and Regulations required for airplanes on which the actions specified in Bombardier Service Bulletin 84–53–75, dated August 29, 2018, have already been done. The FAA has added paragraph (k) to this AD to provide credit for accomplishment of the required actions prior to the effective date of this AD using Bombardier Service Bulletin 84–53–75, dated August 29, 2018. • 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. Conclusion Related Service Information Under 1 CFR Part 51 The FAA reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes: De Havilland Aircraft of Canada Limited has issued the following service information. • Bombardier Service Bulletin 84–53– 74, dated August 29, 2018. This service information describes procedures for a general visual inspection of the keel and stringer end fittings, repair, and replacement of the keel and stringer end fittings. • Service Bulletin 84–53–75, Revision A, dated August 2, 2019. This service information describes procedures for a detailed visual inspection of stringer end fittings and keel fittings, in the passenger compartment at stations X373.15 and X428.50, for loose or working fasteners, signs of wear, and corrosion. 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 1 airplane of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 33 work-hours × $85 per hour = $2,805 ..................................................................................... $0 $2,805 $2,805 Labor cost Parts cost Cost per product 46 work-hours × $85 per hour = $3,910 ................................................................................................................. $54,649 $58,559 The FAA has received no definitive data that would enable the agency to provide cost estimates for the on- condition replacements specified in this AD. khammond on DSKJM1Z7X2PROD with RULES ESTIMATED COSTS OF ON-CONDITION REPLACEMENTS 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 VerDate Sep<11>2014 16:33 Dec 27, 2019 Jkt 250001 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 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: PO 00000 Frm 00052 Fmt 4700 Sfmt 4700 (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\30DER1.SGM 30DER1 Federal Register / Vol. 84, No. 249 / Monday, December 30, 2019 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–24–12 De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.): Amendment 39–19815; Docket No. FAA–2019–0675; Product Identifier 2019–NM–068–AD. (a) Effective Date This AD is effective February 3, 2020. (b) Affected ADs None. (c) Applicability This AD applies to De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC–8–401 and –402 airplanes, certificated in any category, serial numbers 4327, 4330, 4337, 4342, 4350, 4352, 4362, 4367, 4372, 4375, 4376, 4378, 4383, 4384, 4385, 4388, 4391, 4392, 4396, and 4397. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report that certain fuselages were delivered with nonconforming keel tension fittings and stringer end fittings. The FAA is issuing this AD to address non-conforming keel tension fittings and stringer end fittings which could lead to premature cracking and corrosion in several locations and compromise the structural integrity of the fuselage joints. (f) Compliance Comply with this AD within the compliance times specified, unless already done. khammond on DSKJM1Z7X2PROD with RULES (g) Detailed Visual Inspection of the Stringer End Fittings and Keel Fittings and Repair Within 8,000 flight hours or 5 years after the effective date of this AD, whichever occurs first: Do a detailed visual inspection of the stringer end fittings and keel fittings at fuselage stations X373.15 and X428.50 for loose and working fasteners, signs of wear, and corrosion in accordance with paragraph 3.B. of the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 84–53–75, Revision A, dated August 2, 2019. If any loose or working fasteners, signs of wear, or corrosion are found during any inspection required by this paragraph, before further flight, repair 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. Doing the actions specified in Bombardier Service Bulletin 84– 53–66 does not constitute compliance with the actions specified in this paragraph. VerDate Sep<11>2014 16:33 Dec 27, 2019 Jkt 250001 (h) General Visual Inspection, Repair, and Replacement of the Stringer End Fittings and Keel Fittings Except for airplanes identified in paragraph (i) of this AD: Before accumulating 40,000 total flight cycles or within 12 months after the effective date of this AD, whichever occurs later, do the inspections specified in paragraphs (h)(1) and (2) of this AD. (1) Do a general visual inspection of the keel tension fittings at fuselage stations X373.15 and X428.50 for non-conformance conditions (oversize, elongated, and off angle conditions) in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–74, dated August 29, 2018. If any non-conformance condition is found, before further flight, replace the keel tension fittings at fuselage stations X373.15 and X428.50, including doing all applicable repairs, in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–74, dated August 29, 2018; except where Bombardier Service Bulletin 84–53– 74, dated August 29, 2018, specifies to contact Bombardier, before further flight, repair using a method approved by the Manager, New York ACO Branch, FAA; or TCCA; or De Havilland Aircraft of Canada Limited’s TCCA DAO. If approved by the DAO, the approval must include the DAOauthorized signature. (2) Do a general visual inspection of the stringer end fittings at fuselage stations X373.15 and X428.50 for non-conformance conditions (i.e., excessive depth Hi-Lite fastener hole chamfers and installation too close to the fillet radius), in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–74, dated August 29, 2018. If any nonconformance condition is found, before further flight, replace the stringer end fittings at fuselage stations X373.15 and X428.50, including doing all applicable repairs and an eddy current or fluorescent dye penetrant inspection for cracks of all blended areas and fasteners, in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–74, dated August 29, 2018; except where Bombardier Service Bulletin 84–53–74, dated August 29, 2018, specifies to contact Bombardier, before further flight, repair using a method approved by the Manager, New York ACO Branch, FAA; or TCCA; or De Havilland Aircraft of Canada Limited’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (i) Rework for Airplanes That Have Accomplished Bombardier Service Bulletin 84–53–69 Prior to the Effective Date of This AD For airplanes on which the actions specified in Bombardier Service Bulletin 84– 53–69 have been accomplished prior to the effective date of this AD: Before accumulating 40,000 total flight cycles or within 12 months after the effective date of this AD, whichever occurs later, do a general visual inspection of the stringer end fittings at fuselage stations X373.15 and X428.50 for non-conformance conditions (i.e., excessive depth Hi-Lite fastener hole chamfers and PO 00000 Frm 00053 Fmt 4700 Sfmt 4700 71787 installation too close to the fillet radius) in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–74, dated August 29, 2018. If any non-conformance condition is found, before further flight, replace the stringer end fittings at fuselage stations X373.15 and X428.50, including doing all applicable repairs and an eddy current or fluorescent dye penetrant inspection for cracks of all blended areas and fasteners, in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84–53–74, dated August 29, 2018; except where Bombardier Service Bulletin 84–53–74, dated August 29, 2018, specifies to contact Bombardier, before further flight, repair using a method approved by the Manager, New York ACO Branch, FAA; or TCCA; or De Havilland Aircraft of Canada Limited’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (j) Corrective Action for Eddy Current and Fluorescent Dye Penetrant Inspections If, during any eddy current or fluorescent dye penetrant inspection required by paragraph (h)(2) or (i) of this AD, any cracking is found, before further flight, repair using a method approved by the Manager, New York ACO Branch, FAA; or TCCA; or De Havilland Aircraft of Canada Limited’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–53–75, dated August 29, 2018. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 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 TCCA; or De Havilland Aircraft of Canada Limited’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. E:\FR\FM\30DER1.SGM 30DER1 71788 Federal Register / Vol. 84, No. 249 / Monday, December 30, 2019 / Rules and Regulations (m) Related Information DEPARTMENT OF TRANSPORTATION (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2019–06, dated February 18, 2019, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0675. (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 (n)(3) and (4) of this AD. (n) Material Incorporated by Reference khammond on DSKJM1Z7X2PROD with RULES [FR Doc. 2019–28072 Filed 12–27–19; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:33 Dec 27, 2019 Jkt 250001 14 CFR Part 39 [Docket No. FAA–2019–0481; Product Identifier 2019–NM–058–AD; Amendment 39–21002; AD 2019–24–13] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes, Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This AD was prompted by a report that during a maintenance check, cracks were found in a stiffener of a certain lateral window frame. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of a stiffener of a certain lateral window frame, and applicable related investigative and corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 3, 2020. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 3, 2020. ADDRESSES: For the material incorporated by reference (IBR) in this AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material 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 in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0481. SUMMARY: (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 84–53–74, dated August 29, 2018. (ii) De Havilland Aircraft of Canada Limited Service Bulletin 84–53–75, Revision A, dated August 2, 2019. (3) For Bombardier, Inc., or De Havilland Aircraft of Canada Limited service information identified in this AD, contact De Havilland Aircraft of Canada Limited, 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. (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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on November 27, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. Federal Aviation Administration PO 00000 Frm 00054 Fmt 4700 Sfmt 4700 Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0481; 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: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. SUPPLEMENTARY INFORMATION: Discussion The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2019–0067R1, dated September 11, 2019 (‘‘EASA AD 2019–0067R1’’) (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A318 series airplanes, Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –215, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. Model A320–215 airplanes are not on the U.S. Register; this AD therefore does not include those airplanes in the applicability. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus SAS Model A318 series airplanes, Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The NPRM published in the Federal Register on June 24, 2019 (84 FR 29426). The NPRM was prompted by a report that during a maintenance check, cracks were found in a stiffener of a certain lateral window frame. The NPRM proposed to require repetitive HFEC inspections for cracking of a stiffener of a certain lateral window frame, and applicable related investigative and corrective actions. The FAA is issuing this AD to address cracking of the horizontal upper E:\FR\FM\30DER1.SGM 30DER1
[Pages 71785-71788]
[FR Doc No: 2019-28072]
[Docket No. FAA-2019-0675; Product Identifier 2019-NM-068-AD; Amendment
39-19815; AD 2019-24-12]
certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and -
402 airplanes. This AD was prompted by a report that certain fuselages
were delivered with nonconforming keel tension fittings and stringer
end fittings. This AD requires a detailed visual inspection of stringer
end fittings and keel fittings for loose or working fasteners, signs of
wear, and corrosion, and repair if necessary; and a general visual
inspection of the keel tension fitting and stringer end fittings, as
applicable, and repairs and replacement of the keel and stringer end
fittings if necessary. The FAA is issuing this AD to address the unsafe
reference of certain publications listed in this AD as of February 3,
ADDRESSES: For Bombardier, Inc., or De Havilland Aircraft of Canada
Limited service information identified in this final rule, contact De
Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 416-375-
4000; fax: 416-375-4539; email: [email protected]; internet: https://dehavilland.com. You may view this service information at the FAA,
0675; or in person at Docket Operations between 9 a.m. and 5 p.m.,
authority for Canada, has issued Canadian AD CF-2019-06, dated February
18, 2019 (also referred to as the Mandatory Continuing Airworthiness
402 airplanes. You may examine the MCAI in the AD docket on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0675.
CFR part 39 by adding an AD that would apply to certain Bombardier,
Inc., Model DHC-8-401 and -402 airplanes. The NPRM published in the
Federal Register on September 9, 2019 (84 FR 47170). The NPRM was
prompted by a report that certain fuselages were delivered with non-
conforming keel tension fittings and stringer end fittings. The NPRM
proposed to require a detailed visual inspection of stringer end
fittings and keel fittings for loose or working fasteners, signs of
fittings if necessary. The FAA is issuing this AD to address non-
conforming keel tension fittings and stringer end fittings, which could
lead to premature cracking and corrosion in several locations and
compromise the structural integrity of the fuselage joints. See the
MCAI for additional background information.
Request To Update the Design Approval Holder (DAH) for the Affected
Horizon Air requested that the FAA update the DAH for the affected
airplanes. Horizon Air pointed out that De Havilland Aircraft of Canada
Limited is now the DAH for the Model DHC-8-401 and -402 airplanes.
The FAA agrees with the commenter for the reasons provided and has
updated this final rule accordingly.
Request To Include Revised Service Information and Credit for Previous
Horizon Air requested that the FAA update the final rule to include
revised service information. Horizon Air mentioned that De Havilland
Aircraft of Canada Limited has issued Service Bulletin 84-53-75,
Revision A, dated August 2, 2019. Horizon Air also requested that the
FAA give credit for accomplishment of the required actions prior to the
effective date of this AD using Bombardier Service Bulletin 84-53-75,
dated August 29, 2018.
updated this final rule to refer to De Havilland Aircraft of Canada
Limited Service Bulletin 84-53-75, Revision A, dated August 2, 2019.
The FAA has determined that no additional work is
required for airplanes on which the actions specified in Bombardier
Service Bulletin 84-53-75, dated August 29, 2018, have already been
done. The FAA has added paragraph (k) to this AD to provide credit for
accomplishment of the required actions prior to the effective date of
this AD using Bombardier Service Bulletin 84-53-75, dated August 29,
and minor editorial changes. We have determined that these minor
De Havilland Aircraft of Canada Limited has issued the following
Bombardier Service Bulletin 84-53-74, dated August 29,
2018. This service information describes procedures for a general
visual inspection of the keel and stringer end fittings, repair, and
replacement of the keel and stringer end fittings.
Service Bulletin 84-53-75, Revision A, dated August 2,
2019. This service information describes procedures for a detailed
visual inspection of stringer end fittings and keel fittings, in the
passenger compartment at stations X373.15 and X428.50, for loose or
working fasteners, signs of wear, and corrosion.
The FAA estimates that this AD affects 1 airplane of U.S. registry.
33 work-hours x $85 per hour = $2,805........................              $0           $2,805           $2,805
The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition replacements
46 work-hours x $85 per hour = $3,910.         $54,649          $58,559
2019-24-12 De Havilland Aircraft of Canada Limited (Type Certificate
Previously Held by Bombardier, Inc.): Amendment 39-19815; Docket No.
FAA-2019-0675; Product Identifier 2019-NM-068-AD.
Certificate Previously Held by Bombardier, Inc.) Model DHC-8-401 and
-402 airplanes, certificated in any category, serial numbers 4327,
4330, 4337, 4342, 4350, 4352, 4362, 4367, 4372, 4375, 4376, 4378,
4383, 4384, 4385, 4388, 4391, 4392, 4396, and 4397.
This AD was prompted by a report that certain fuselages were
delivered with non-conforming keel tension fittings and stringer end
fittings. The FAA is issuing this AD to address non-conforming keel
tension fittings and stringer end fittings which could lead to
premature cracking and corrosion in several locations and compromise
the structural integrity of the fuselage joints.
(g) Detailed Visual Inspection of the Stringer End Fittings and Keel
Fittings and Repair
Within 8,000 flight hours or 5 years after the effective date of
this AD, whichever occurs first: Do a detailed visual inspection of
the stringer end fittings and keel fittings at fuselage stations
X373.15 and X428.50 for loose and working fasteners, signs of wear,
and corrosion in accordance with paragraph 3.B. of the
If any loose or working fasteners, signs of wear, or corrosion are
further flight, repair 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
include the DAO-authorized signature. Doing the actions specified in
Bombardier Service Bulletin 84-53-66 does not constitute compliance
with the actions specified in this paragraph.
(h) General Visual Inspection, Repair, and Replacement of the Stringer
End Fittings and Keel Fittings
Except for airplanes identified in paragraph (i) of this AD:
Before accumulating 40,000 total flight cycles or within 12 months
after the effective date of this AD, whichever occurs later, do the
inspections specified in paragraphs (h)(1) and (2) of this AD.
(1) Do a general visual inspection of the keel tension fittings
at fuselage stations X373.15 and X428.50 for non-conformance
conditions (oversize, elongated, and off angle conditions) in
accordance with paragraph 3.B. of the Accomplishment Instructions of
Bombardier Service Bulletin 84-53-74, dated August 29, 2018. If any
non-conformance condition is found, before further flight, replace
the keel tension fittings at fuselage stations X373.15 and X428.50,
including doing all applicable repairs, in accordance with paragraph
3.B. of the Accomplishment Instructions of Bombardier Service
Bulletin 84-53-74, dated August 29, 2018; except where Bombardier
Service Bulletin 84-53-74, dated August 29, 2018, specifies to
contact Bombardier, before further flight, repair using a method
approved by the Manager, New York ACO Branch, FAA; or TCCA; or De
Havilland Aircraft of Canada Limited's TCCA DAO. If approved by the
(2) Do a general visual inspection of the stringer end fittings
conditions (i.e., excessive depth Hi-Lite fastener hole chamfers and
installation too close to the fillet radius), in accordance with
paragraph 3.B. of the Accomplishment Instructions of Bombardier
Service Bulletin 84-53-74, dated August 29, 2018. If any non-
conformance condition is found, before further flight, replace the
stringer end fittings at fuselage stations X373.15 and X428.50,
including doing all applicable repairs and an eddy current or
fluorescent dye penetrant inspection for cracks of all blended areas
and fasteners, in accordance with paragraph 3.B. of the
Accomplishment Instructions of Bombardier Service Bulletin 84-53-74,
dated August 29, 2018; except where Bombardier Service Bulletin 84-
53-74, dated August 29, 2018, specifies to contact Bombardier,
before further flight, repair using a method approved by the
Manager, New York ACO Branch, FAA; or TCCA; or De Havilland Aircraft
of Canada Limited's TCCA DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(i) Rework for Airplanes That Have Accomplished Bombardier Service
Bulletin 84-53-69 Prior to the Effective Date of This AD
For airplanes on which the actions specified in Bombardier
Service Bulletin 84-53-69 have been accomplished prior to the
effective date of this AD: Before accumulating 40,000 total flight
cycles or within 12 months after the effective date of this AD,
whichever occurs later, do a general visual inspection of the
stringer end fittings at fuselage stations X373.15 and X428.50 for
non-conformance conditions (i.e., excessive depth Hi-Lite fastener
hole chamfers and installation too close to the fillet radius) in
the stringer end fittings at fuselage stations X373.15 and X428.50,
(j) Corrective Action for Eddy Current and Fluorescent Dye Penetrant
If, during any eddy current or fluorescent dye penetrant
inspection required by paragraph (h)(2) or (i) of this AD, any
cracking is found, before further flight, repair using a method
(g) of this AD, if those actions were performed before the effective
date of this AD using Bombardier Service Bulletin 84-53-75, dated
Branch, FAA; or TCCA; or De Havilland Aircraft of Canada Limited's
TCCA DAO. If approved by the DAO, the approval must include the DAO-
(MCAI) Canadian AD CF-2019-06, dated February 18, 2019, for related
No. FAA-2019-0675.
paragraphs (n)(3) and (4) of this AD.
(i) Bombardier Service Bulletin 84-53-74, dated August 29, 2018.
(ii) De Havilland Aircraft of Canada Limited Service Bulletin
84-53-75, Revision A, dated August 2, 2019.
(3) For Bombardier, Inc., or De Havilland Aircraft of Canada
Limited service information identified in this AD, contact De
[FR Doc. 2019-28072 Filed 12-27-19; 8:45 am]