Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 58061-58064 [2024-15657]

Download as PDF Federal Register / Vol. 89, No. 137 / Wednesday, July 17, 2024 / Rules and Regulations (i) Retained Repetitive Lubrications, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2021–25–12, with no changes. For airplanes with pivot pin retention bolt P/N NAS6204–14D installed on the NLG assembly: Within 30 days or 400 flight cycles, whichever occurs first after January 5, 2022 (the effective date of AD 2021–25–12), and thereafter at intervals not exceeding 400 flight cycles, lubricate the trailing arm of the NLG, including doing a general visual inspection of the NLG pivot pin mechanism for discrepancies (i.e., bolt P/ N NAS602–14D is missing or has damage (e.g., stress corrosion or stress corrosion cracking)) and, as applicable, replacing the bolt before further flight, in accordance with paragraph 3.B. of the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 84–32–167, dated August 12, 2021. (j) Retained Modification, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2022–11–11, with no changes. For any airplane having an NLG shock strut assembly, P/N 47100–XX (where XX represents any number), that has special bolt P/N 47205–1 or 47205–3: Within 1,600 flight cycles or 9 months after July 8, 2022 (the effective date of AD 2022–11–11), whichever occurs first, modify the NLG shock strut assembly, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 84–32–161, Revision B, dated March 31, 2021, including UTC Aerospace Systems Service Bulletin 47100–32–145, Revision 3, dated March 26, 2021. Note 1 to paragraph (j): After installing pivot pin retention bolt part number NAS6204–14D, paragraphs (g), (h), and (i) of this AD apply to pivot pin retention bolt part number NAS6204–14D. ddrumheller on DSK120RN23PROD with RULES1 (k) New Replacement Within 8,000 flight hours or 48 months, whichever occurs first, after the effective date of this AD, remove pivot pin linkage components and replace pivot pin P/N 47127–1 or P/N 47127–3 and tow fitting assembly P/N 47160–1 with pivot pin P/N 47127–5 and tow fitting assembly P/N 47160–3, in accordance with Section 3.B. of the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 84–32–173, dated November 15, 2022, including Collins Aerospace Service Bulletin 47100–32–153, dated November 10, 2022. Accomplishing the replacement required by this paragraph terminates the requirements of paragraphs (g), (h), (i), and (j) of this AD. (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before July 8, 2022 (the effective date of AD 2022–11–11), using De Havilland Aircraft of Canada Limited Service Bulletin 84–32–161, dated April 7, 2020, including UTC Aerospace Systems Service Bulletin 47100–32–145, dated April 3, 2020; or De Havilland Aircraft of Canada VerDate Sep<11>2014 16:06 Jul 16, 2024 Jkt 262001 Limited Service Bulletin 84–32–161, Revision A, dated January 27, 2021, including UTC Aerospace Systems Service Bulletin 47100–32–145, Revision 2, dated January 4, 2021. (m) Parts Installation Prohibition As of the effective date of this AD, no person may install pivot pin P/N 47127–1 or P/N 47127–3 as a replacement part for pivot pin P/N 47127–5 on De Havilland Aircraft of Canada Limited Model DHC–8–401 and DHC–8–402 airplanes. (n) Additional AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, International Validation 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the International Validation Branch, mail it to the address identified in paragraph (o)(2) of this AD. Information may be emailed to: 9-AVS-NYACO-COS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or Transport Canada; or De Havilland Aircraft of Canada Limited’s Transport Canada Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (o) Additional Information (1) For more information about this AD, contact Deep Gaurav, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 518– 228–7300; email 9-avs-nyaco-cos@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the address specified in paragraph (p)(6) of this AD. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following material was approved for IBR on August 21, 2024. (i) De Havilland Aircraft of Canada Limited Service Bulletin 84–32–173, dated November 15, 2022, including Collins Aerospace Service Bulletin 47100–32–153, dated November 10, 2022. Note 2 to paragraph (p)(3)(i): De Havilland issued De Havilland Aircraft of Canada Limited Service Bulletin 84–32–173, dated November 15, 2022, with Collins Aerospace Service Bulletin 47100–32–153, dated November 10, 2022, attached as one PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 58061 ‘‘merged’’ file for the convenience of affected operators. (ii) [Reserved] (4) The following material was approved for IBR on July 8, 2022 (87 FR 33627, June 3, 2022). (i) De Havilland Aircraft of Canada Limited Service Bulletin 84–32–161, Revision B, dated March 31, 2021, including UTC Aerospace Systems Service Bulletin 47100– 32–145, Revision 3, dated March 26, 2021. Note 3 to paragraph (p)(4)(i): De Havilland issued De Havilland Service Bulletin 84–32– 161, Revision B, dated March 31, 2021, with UTC Aerospace Systems Service Bulletin 47100–32–145, Revision 3, dated March 26, 2021, attached as one ‘‘merged’’ file for the convenience of affected operators. (ii) [Reserved] (5) The following material was approved for IBR on January 5, 2022 (86 FR 72174, December 21, 2021). (i) De Havilland Aircraft of Canada Limited Service Bulletin 84–32–167, dated August 12, 2021. (ii) De Havilland Aircraft of Canada Limited Temporary Revision ALI–0223, dated October 15, 2020. (6) For De Havilland material identified in this AD, contact De Havilland Aircraft of Canada Limited, Dash 8 Series Customer Response Centre, 5800 Explorer Drive, Mississauga, Ontario, L4W 5K9, Canada; telephone North America (toll-free): 855– 310–1013, Direct: 647–277–5820; email thd@ dehavilland.com; website dehavilland.com. (7) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (8) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locations, or email fr.inspection@ nara.gov. Issued on July 10, 2024. James D. Foltz, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–15656 Filed 7–16–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1885; Project Identifier MCAI–2022–01484–T; Amendment 39–22770; AD 2024–12–06] RIN 2120–AA64 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\17JYR1.SGM 17JYR1 58062 ACTION: Federal Register / Vol. 89, No. 137 / Wednesday, July 17, 2024 / Rules and Regulations Final rule. 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 reports of moisture in the wing-to-fuselage joint, between the mating front spar and rear spar frame segments. This AD requires a visual inspection of the fuselage front and rear spar frames, an ultrasonic test if applicable, other specified actions, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 21, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 21, 2024. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–1885; 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 mandatory continuing airworthiness information (MCAI), 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. Material Incorporated by Reference: • For De Havilland Aircraft material incorporated by reference in this AD, contact De Havilland Aircraft of Canada Limited, Dash 8 Series Customer Response Centre, 5800 Explorer Drive, Mississauga, Ontario, L4W 5K9, Canada; telephone 855–310–1013 or 647–277– 5820; email thd@dehavilland.com; website dehavilland.com. • You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at regulations.gov under Docket No. FAA–2023–1885. FOR FURTHER INFORMATION CONTACT: Deep Gaurav, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7300; email deep.gaurav@faa.gov. SUPPLEMENTARY INFORMATION: ddrumheller on DSK120RN23PROD with RULES1 SUMMARY: VerDate Sep<11>2014 16:06 Jul 16, 2024 Jkt 262001 Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain De Havilland Aircraft of Canada Limited Model DHC–8–401 and –402 airplanes. The NPRM published in the Federal Register on September 25, 2023 (88 FR 65635). The NPRM was prompted by AD CF–2022–63, dated November 17, 2022, issued by Transport Canada, which is the aviation authority for Canada (referred to after this as the MCAI). The MCAI states several reports of moisture have been found in the wing-to-fuselage joint, between the mating front spar and rear spar frame segments. This condition, if not corrected, could lead to corrosion and structural degradation of the wing-tofuselage joint and possible wing separation from the airplane. In the NPRM, the FAA proposed to require a visual inspection of the fuselage front and rear spar frames, an ultrasonic test if applicable, other specified actions, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–1885. of compliance with this AD under the provisions of paragraph (i)(1) of this AD. In light of the critical nature of the identified unsafe condition (i.e., corrosion and structural degradation of the wing-to-fuselage joint), the FAA does not consider it warranted to delay the issuance of this final rule until the revised service information is published. The FAA has not changed this AD in this regard. Discussion of Final Airworthiness Directive The FAA reviewed De Havilland Aircraft of Canada Limited Service Bulletin 84–53–81, Revision A, dated August 23, 2022. This material specifies procedures for a general visual inspection of the fuselage front and rear spar frames (including around the frame bolts) for signs of moisture (i.e., stains and streaks). If signs of moisture ingress are noted in the affected structure because of this inspection, then an ultrasonic test and other specified actions will be required, which includes installing a sealant plug, refinishing the frame edge sealing, and removing the existing frame recess sealant between the frame and struts in the cabin. This material 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. Comments The FAA received a comment from De Havilland. The following presents the comment received on the NPRM and the FAA’s response. Request To Update the Service Information De Havilland stated that to allow some operators to accomplish the AD, an update is necessary to the work instructions in De Havilland Aircraft of Canada Limited Service Bulletin 84–53– 81, Revision A, dated August 23, 2022. The service bulletin is in the process of being revised to allow operators an alternative means of accessing the front spar joint via the forward fairing rib on certain airplanes. To allow operators to use later revisions of the referenced document (issued after publication of the AD), either the FAA must revise the AD to reference specific later revisions, or operators may request approval to use later revisions as an alternative method PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Conclusion This product has been approved by the aviation authority of another country and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data, considered the comments received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on this product. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Material Incorporated by Reference Under 1 CFR Part 51 Costs of Compliance The FAA estimates that this AD affects 41 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E:\FR\FM\17JYR1.SGM 17JYR1 Federal Register / Vol. 89, No. 137 / Wednesday, July 17, 2024 / Rules and Regulations 58063 ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 16 work-hours × $85 per hour = $1,360 ..................................................................................... $3,134 $4,494 $184,254 The FAA has received no definitive data on which to base the cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. 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. ddrumheller on DSK120RN23PROD with RULES1 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: (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. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: VerDate Sep<11>2014 16:06 Jul 16, 2024 Jkt 262001 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: ■ 2024–12–06 De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.): Amendment 39–22770; Docket No. FAA–2023–1885; Project Identifier MCAI–2022–01484–T. (a) Effective Date This airworthiness directive (AD) is effective August 21, 2024. (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, having serial numbers 4001 and 4003 through 4624 inclusive. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of moisture in the wing-to-fuselage joint, between the mating front spar and rear spar frame segments. The FAA is issuing this AD to address potential corrosion and structural degradation of the wing-to-fuselage joint. The unsafe condition, if not addressed, could result in wing separation from the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Action At the applicable compliance times specified in paragraph (g)(1) or (2) of this AD, in accordance with Section 3.B., of the Accomplishment Instructions of De Havilland Aircraft of Canada Service Bulletin 84–53–81, Revision A, dated August 23, 2022, complete a general visual inspection of the fuselage spar frames and around the frame bolts for signs of moisture ingress (i.e., stains and streaks), accomplish other specified actions, and if necessary, perform an ultrasonic test. Do all applicable ultrasonic tests before further flight. If, PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 during any ultrasonic test, any corrosion or structural degradation is found, before further flight, repair using a method approved by the Manager, International Validation Branch, FAA; or Transport Canada; or De Havilland Aircraft of Canada Limited’s Transport Canada Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (1) For airplanes that, as of the effective date of this AD, have accumulated less than 32,000 total flight cycles: before accumulating 40,000 total flight cycles. (2) For airplanes that, as of the effective date of this AD, have accumulated 32,000 or more total flight cycles: within 8,000 flight hours or 48 months, whichever occurs first after the effective date of this AD. (h) 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 De Havilland Aircraft of Canada Limited Service Bulletin 84–53– 81, dated May 27, 2022. (i) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Validation 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager, International Validation Branch, mail it to the address identified in paragraph (j) of this AD or email to 9-AVSAIR-730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or Transport Canada; or De Havilland Aircraft of Canada Limited’s Transport Canada DAO. If approved by the DAO, the approval must include the DAOauthorized signature. (j) Additional Information For more information about this AD, contact Deep Gaurav, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7300; email deep.gaurav@faa.gov. E:\FR\FM\17JYR1.SGM 17JYR1 58064 Federal Register / Vol. 89, No. 137 / Wednesday, July 17, 2024 / Rules and Regulations (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) De Havilland Aircraft of Canada Limited Service Bulletin 84–53–81, Revision A, dated August 23, 2022. (ii) [Reserved] (3) For De Havilland Aircraft material incorporated by reference in this AD, contact De Havilland Aircraft of Canada Limited, Dash 8 Series Customer Response Centre, 5800 Explorer Drive, Mississauga, Ontario, L4W 5K9, Canada; telephone 855–310–1013 or 647–277–5820; email thd@ dehavilland.com; website dehavilland.com. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locationsoremailfr.inspection@nara.gov. Issued on July 10, 2024. James D. Foltz, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–15657 Filed 7–16–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 165 [Docket Number USCG–2024–0254] RIN 1625–AA87 Security Zones; 2024 Republican National Convention; Lake Michigan, Milwaukee Harbor, Kinnickinnic River, Menomonee River and Milwaukee River, Milwaukee, WI Coast Guard, DHS. Temporary final rule. AGENCY: ACTION: The Coast Guard is establishing temporary security zones and a safety zone for navigable waters within Lake Michigan, Milwaukee Harbor, Kinnickinnic River, Menomonee River, and Milwaukee River during the 2024 Republican National Convention. These actions are necessary to protect convention delegates, official parties, dignitaries, the public and surrounding waterways from terrorist acts, sabotage or other ddrumheller on DSK120RN23PROD with RULES1 SUMMARY: VerDate Sep<11>2014 16:06 Jul 16, 2024 Jkt 262001 subversive acts, accidents, or other causes of a similar nature. Entry of vessels or persons into these zones is prohibited unless specifically authorized by the Captain of the Port Sector Lake Michigan or designated representative. This rule is effective from 8 a.m. on July 13, 2024, to 3 a.m. on July 19, 2024. All Security Zones will be enforced as needed with actual notice. ADDRESSES: To view documents mentioned in this preamble as being available in the docket, go to https:// www.regulations.gov, type USCG–2024– 0254 in the search box and click ‘‘Search.’’ Next, in the Document Type column, select ‘‘Supporting & Related Material.’’ DATES: If you have questions about this proposed rulemaking, call or email Chief Petty Officer Aaron Sunstrom, Sector Lake Michigan Waterways Management Division, U.S. Coast Guard; telephone 770–527–3964, email Aaron.R.Sunstrom@uscg.mil. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: I. Table of Abbreviations CFR Code of Federal Regulations DHS Department of Homeland Security FR Federal Register NPRM Notice of proposed rulemaking § Section U.S.C. United States Code II. Background Information and Regulatory History The Coast Guard is issuing this temporary rule under authority in 5 U.S.C. 553(b)(B). This statutory provision authorizes an agency to issue a rule without prior notice and opportunity to comment when the agency for good cause finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ The Coast Guard finds that good cause exists for not publishing a notice of proposed rulemaking (NPRM) with respect to this rule due to it being impracticable and contrary to the public interest. Due to the sensitive security issues related to the Republican National Convention, providing a public notice and comment period would be contrary to the security zone’s intended objective of protecting VIPs and the public because we cannot share the sensitive security information details prior to the rule being published. Also, under 5 U.S.C. 553(d)(3), the Coast Guard finds that good cause exists for making this rule effective less than 30 days after publication in the Federal Register. Delaying the effective date by first publishing an NPRM and holding a PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 comment period would be contrary to the rule’s objectives of ensuring safety of life on the navigable waters and protection of the Republican National Convention and accompanying highranking government officials. III. Legal Authority and Need for Rule The Coast Guard may issue security zone regulations under authority in 46 U.S.C. 70051 and 70124. The Captain of the Port, Sector Lake Michigan has determined that these temporary security zones are necessary to provide for the security of the Republican National Convention and the accompanying high-ranking government officials, and to protect against sabotage or terrorist attacks to human life, vessels, mariners, and waterfront venues at or near this event. Additionally, the Coast Guard believes that, given the nature of the First Amendment activity expected and likely type of vessels used by individuals desiring to express their First Amendment rights—namely kayaks and other small vessels—a safety zone designating a voluntary First Amendment Area is necessary to ensure the safety of those vessels and persons who chose to express their views safely and without interference from, or interfering with, other maritime traffic. IV. Discussion of the Rule The Republican National Convention will take place in Milwaukee, WI from July 13, 2024, until July 19, 2024. The Secretary of the Department of Homeland Security has designated the 2024 Republican National Convention as a National Special Security Event (NSSE). NSSE’s are significant events, which, due to their political, economic, social, or religious significance, may render them particularly attractive targets of terrorism or other criminal activity. The Federal government provides support, assistance, and resources to state and local governments to ensure public safety and security during NSSE’s. During this NSSE many high-ranking government officials will be arriving in Milwaukee, WI. The Coast Guard is establishing several security zones and a safety zone in portions of Lake Michigan, Milwaukee Harbor, Kinnickinnic River, Menomonee River, and Milwaukee River in Milwaukee, WI. Voluntary First Amendment Safety Zone 1 includes all waters of Lake Michigan within Milwaukee Harbor north of Discovery World. The area is enclosed by a line connecting the following points: starting at 43 02.62′ N, 087 52.83′ W, then west to 43 02.62′ N, 087 53.21′ W, then southwest to 43 E:\FR\FM\17JYR1.SGM 17JYR1

Agencies

[Federal Register Volume 89, Number 137 (Wednesday, July 17, 2024)]
[Rules and Regulations]
[Pages 58061-58064]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-15657]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1885; Project Identifier MCAI-2022-01484-T; 
Amendment 39-22770; AD 2024-12-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 58062]]


ACTION: Final rule.

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

SUMMARY: 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 reports of moisture in the wing-
to-fuselage joint, between the mating front spar and rear spar frame 
segments. This AD requires a visual inspection of the fuselage front 
and rear spar frames, an ultrasonic test if applicable, other specified 
actions, and repair if necessary. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective August 21, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 21, 
2024.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2023-1885; 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 mandatory continuing airworthiness 
information (MCAI), 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.
    Material Incorporated by Reference:
     For De Havilland Aircraft material incorporated by 
reference in this AD, contact De Havilland Aircraft of Canada Limited, 
Dash 8 Series Customer Response Centre, 5800 Explorer Drive, 
Mississauga, Ontario, L4W 5K9, Canada; telephone 855-310-1013 or 647-
277-5820; email dehavilland.com">thd@dehavilland.com; website dehavilland.com.
     You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th Street, 
Des Moines, WA. For information on the availability of this material at 
the FAA, call 206-231-3195. It is also available at regulations.gov 
under Docket No. FAA-2023-1885.

FOR FURTHER INFORMATION CONTACT: Deep Gaurav, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-
228-7300; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain De Havilland 
Aircraft of Canada Limited Model DHC-8-401 and -402 airplanes. The NPRM 
published in the Federal Register on September 25, 2023 (88 FR 65635). 
The NPRM was prompted by AD CF-2022-63, dated November 17, 2022, issued 
by Transport Canada, which is the aviation authority for Canada 
(referred to after this as the MCAI). The MCAI states several reports 
of moisture have been found in the wing-to-fuselage joint, between the 
mating front spar and rear spar frame segments. This condition, if not 
corrected, could lead to corrosion and structural degradation of the 
wing-to-fuselage joint and possible wing separation from the airplane.
    In the NPRM, the FAA proposed to require a visual inspection of the 
fuselage front and rear spar frames, an ultrasonic test if applicable, 
other specified actions, and repair if necessary. The FAA is issuing 
this AD to address the unsafe condition on these products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2023-1885.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from De Havilland. The following 
presents the comment received on the NPRM and the FAA's response.

Request To Update the Service Information

    De Havilland stated that to allow some operators to accomplish the 
AD, an update is necessary to the work instructions in De Havilland 
Aircraft of Canada Limited Service Bulletin 84-53-81, Revision A, dated 
August 23, 2022. The service bulletin is in the process of being 
revised to allow operators an alternative means of accessing the front 
spar joint via the forward fairing rib on certain airplanes.
    To allow operators to use later revisions of the referenced 
document (issued after publication of the AD), either the FAA must 
revise the AD to reference specific later revisions, or operators may 
request approval to use later revisions as an alternative method of 
compliance with this AD under the provisions of paragraph (i)(1) of 
this AD.
    In light of the critical nature of the identified unsafe condition 
(i.e., corrosion and structural degradation of the wing-to-fuselage 
joint), the FAA does not consider it warranted to delay the issuance of 
this final rule until the revised service information is published. The 
FAA has not changed this AD in this regard.

Conclusion

    This product has been approved by the aviation authority of another 
country and is approved for operation in the United States. Pursuant to 
the FAA's bilateral agreement with this State of Design Authority, it 
has notified the FAA of the unsafe condition described in the MCAI 
referenced above. The FAA reviewed the relevant data, considered the 
comments received, and determined that air safety requires adopting 
this AD as proposed. Accordingly, the FAA is issuing this AD to address 
the unsafe condition on this product. Except for minor editorial 
changes, this AD is adopted as proposed in the NPRM. None of the 
changes will increase the economic burden on any operator.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed De Havilland Aircraft of Canada Limited Service 
Bulletin 84-53-81, Revision A, dated August 23, 2022. This material 
specifies procedures for a general visual inspection of the fuselage 
front and rear spar frames (including around the frame bolts) for signs 
of moisture (i.e., stains and streaks). If signs of moisture ingress 
are noted in the affected structure because of this inspection, then an 
ultrasonic test and other specified actions will be required, which 
includes installing a sealant plug, refinishing the frame edge sealing, 
and removing the existing frame recess sealant between the frame and 
struts in the cabin.
    This material 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 41 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

[[Page 58063]]



                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
16 work-hours x $85 per hour = $1,360........................          $3,134           $4,494         $184,254
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    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.

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 adding the following new airworthiness 
directive:

2024-12-06 De Havilland Aircraft of Canada Limited (Type Certificate 
Previously Held by Bombardier, Inc.): Amendment 39-22770; Docket No. 
FAA-2023-1885; Project Identifier MCAI-2022-01484-T.

(a) Effective Date

    This airworthiness directive (AD) is effective August 21, 2024.

(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, having serial numbers 
4001 and 4003 through 4624 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of moisture in the wing-to-
fuselage joint, between the mating front spar and rear spar frame 
segments. The FAA is issuing this AD to address potential corrosion 
and structural degradation of the wing-to-fuselage joint. The unsafe 
condition, if not addressed, could result in wing separation from 
the airplane.

(f) Compliance

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

(g) Inspection and Corrective Action

    At the applicable compliance times specified in paragraph (g)(1) 
or (2) of this AD, in accordance with Section 3.B., of the 
Accomplishment Instructions of De Havilland Aircraft of Canada 
Service Bulletin 84-53-81, Revision A, dated August 23, 2022, 
complete a general visual inspection of the fuselage spar frames and 
around the frame bolts for signs of moisture ingress (i.e., stains 
and streaks), accomplish other specified actions, and if necessary, 
perform an ultrasonic test. Do all applicable ultrasonic tests 
before further flight. If, during any ultrasonic test, any corrosion 
or structural degradation is found, before further flight, repair 
using a method approved by the Manager, International Validation 
Branch, FAA; or Transport Canada; or De Havilland Aircraft of Canada 
Limited's Transport Canada Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.
    (1) For airplanes that, as of the effective date of this AD, 
have accumulated less than 32,000 total flight cycles: before 
accumulating 40,000 total flight cycles.
    (2) For airplanes that, as of the effective date of this AD, 
have accumulated 32,000 or more total flight cycles: within 8,000 
flight hours or 48 months, whichever occurs first after the 
effective date of this AD.

(h) 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 De Havilland Aircraft of Canada Limited 
Service Bulletin 84-53-81, dated May 27, 2022.

(i) Additional AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Validation 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 responsible Flight Standards Office, as 
appropriate. If sending information directly to the manager, 
International Validation Branch, mail it to the address identified 
in paragraph (j) of this AD or email to [email protected]. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
responsible Flight Standards Office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Validation Branch, FAA; or Transport Canada; or De Havilland 
Aircraft of Canada Limited's Transport Canada DAO. If approved by 
the DAO, the approval must include the DAO-authorized signature.

(j) Additional Information

    For more information about this AD, contact Deep Gaurav, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7300; email 
[email protected].

[[Page 58064]]

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the material listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless this AD specifies otherwise.
    (i) De Havilland Aircraft of Canada Limited Service Bulletin 84-
53-81, Revision A, dated August 23, 2022.
    (ii) [Reserved]
    (3) For De Havilland Aircraft material incorporated by reference 
in this AD, contact De Havilland Aircraft of Canada Limited, Dash 8 
Series Customer Response Centre, 5800 Explorer Drive, Mississauga, 
Ontario, L4W 5K9, Canada; telephone 855-310-1013 or 647-277-5820; 
email dehavilland.com">thd@dehavilland.com; website dehavilland.com.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th 
Street, Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/[email protected]">www.archives.gov/federal-register/cfr/[email protected].

    Issued on July 10, 2024.
James D. Foltz,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-15657 Filed 7-16-24; 8:45 am]
BILLING CODE 4910-13-P

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