[Federal Register Volume 89, Number 57 (Friday, March 22, 2024)]
[Proposed Rules]
[Pages 20367-20370]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-05963]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-0756; Project Identifier MCAI-2023-00549-T]
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.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2021-25-12 and AD 2022-11-11, which apply to certain De Havilland 
Aircraft of Canada Limited Model DHC-8-401 and -402 airplanes. AD 2021-
25-12 requires repetitive lubrications of the trailing arm of the nose 
landing gear (NLG). AD 2021-25-12 also requires revising the existing 
maintenance or inspection program to include new and revised 
airworthiness limitations. AD 2022-11-11 requires a modification to the 
NLG shock strut assembly. Since the FAA issued AD 2021-25-12 and AD 
2022-11-11, it has been determined that the pivot pin and tow fitting 
assembly of the NLG must be replaced. This proposed AD would continue 
to require the actions specified in AD 2021-25-12 and AD 2022-11-11 and 
would require replacement of the pivot pin and tow fitting assembly 
with a new, improved pivot pin and tow fitting assembly and prohibit 
the installation of affected parts. The FAA is proposing this AD to 
address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by May 6, 
2024.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to regulations.gov. Follow 
the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-0756; 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 NPRM, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For service information identified in this NPRM, 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 dehavilland.com">thd@dehavilland.com; website dehavilland.com.
     You may view this service information 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.

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: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2024-0756; Project Identifier 
MCAI-2023-00549-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act

[[Page 20368]]

(FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your 
comments responsive to this NPRM contain commercial or financial 
information that is customarily treated as private, that you actually 
treat as private, and that is relevant or responsive to this NPRM, it 
is important that you clearly designate the submitted comments as CBI. 
Please mark each page of your submission containing CBI as ``PROPIN.'' 
The FAA will treat such marked submissions as confidential under the 
FOIA, and they will not be placed in the public docket of this NPRM. 
Submissions containing CBI should be sent to Deep Gaurav, Aviation 
Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 518-228-7300; email [email protected]. Any 
commentary that the FAA receives which is not specifically designated 
as CBI will be placed in the public docket for this rulemaking.

Background

    The FAA issued AD 2021-25-12, Amendment 39-21856 (86 FR 72174, 
December 21, 2021) (AD 2021-25-12); and AD 2022-11-11, Amendment 39-
22061 (87 FR 33627, June 3, 2022) (AD 2022-11-11), for certain 
DeHavilland Aircraft of Canada Limited Model DHC-8-401 and -402 
airplanes. AD 2021-25-12 and AD 2022-11-11 were prompted by an MCAI 
originated by Transport Canada, which is the aviation authority for 
Canada. Transport Canada issued AD CF-2009-29R4, dated October 1, 2021 
(Transport Canada AD CF-2009-29R4), to correct an unsafe condition.
    AD 2021-25-12 requires repetitive lubrications of the trailing arm 
of the NLG. AD 2021-25-12 also requires revising the existing 
maintenance or inspection program to include new and revised 
airworthiness limitations (life limits for certain bolts). AD 2022-11-
11 requires modification to the NLG shock strut assembly. The FAA 
issued AD 2021-25-12 and AD 2022-11-11 to address failure of the pivot 
pin retention bolt, which could result in a loss of directional control 
or loss of an NLG tire during takeoff or landing, which could lead to 
runway excursions.

Actions Since AD 2021-25-12 and AD 2022-11-11 Were Issued

    Since the FAA issued AD 2021-25-12 and AD 2022-11-11, Transport 
Canada superseded AD CF-2009-29R4, and issued Transport Canada AD CF-
2023-22, dated March 30, 2023 (Transport Canada AD CF-2023-22) 
(referred to after this as the MCAI), to correct an unsafe condition on 
certain DeHavilland Aircraft of Canada Limited Model DHC-8-401 and -402 
airplanes. The MCAI states that it requires the removal of pivot pin 
part number (P/N) 47127-1 or P/N 47127-3 and tow fitting assembly P/N 
47160-1, and their replacement with pivot pin P/N 47127-5 and tow 
fitting assembly P/N 47160-3, as terminating action to the requirements 
of AD CF-2009-29R4. The pivot pin P/N 47127-5 is now attached directly 
to the new tow fitting lug and no longer requires the use of a 
retention bolt. Transport Canada AD CF-2023-22 also prohibits the 
installation of certain parts. This proposed AD would also remove 
airplanes from the applicability of AD 2021-25-12 and AD 2022-11-11. 
The FAA is proposing 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-2024-0756.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed 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. This 
service information specifies procedures for replacing the pivot pin 
retention mechanism and tow fitting assembly with a new, improved pivot 
pin and tow fitting assembly, which consists of removing pivot pin 
linkage components and replacing 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.
    This proposed AD would also require 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, which the Director of the Federal Register 
approved for incorporation by reference as of July 8, 2022 (87 FR 
33627, June 3, 2022).
    This proposed AD would also require De Havilland Aircraft of Canada 
Limited Service Bulletin 84-32-167, dated August 12, 2021; and De 
Havilland Aircraft of Canada Limited Temporary Revision ALI-0223, dated 
October 15, 2020, which the Director of the Federal Register approved 
for incorporation by reference as of January 5, 2022 (86 FR 72174, 
December 21, 2021).
    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.

FAA's Determination

    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 
and service information referenced above. The FAA is issuing this NPRM 
after determining that unsafe condition described previously is likely 
to exist or develop on other products of the same type design.

Proposed AD Requirements in This NPRM

    This proposed AD would continue to require the actions specified in 
AD 2021-25-12 and AD 2022-11-11 and would also require accomplishing 
the actions specified in the service information described previously. 
This proposed AD would also prohibit the installation of affected 
parts.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 41 airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
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                                                                                     Cost per      Cost on U.S.
              Action                      Labor cost             Parts cost           product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD            1 work-hour x $85 per  Negligible...........             $85          $3,485
 2021[dash]25[dash]12 *.             hour = $85.
Retained actions from AD 2022-11-   4 work-hours x $85     $8...................             348          14,268
 11.                                 per hour = $340.
New proposed actions..............  4 work-hours x $85     $25,804..............          26,144       1,071,904
                                     per hour = $340.
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* Table does not include estimated costs for revising the maintenance or inspection program.


[[Page 20369]]

    The FAA has determined that revising the maintenance or inspection 
program takes an average of 90 work-hours per operator, although the 
FAA recognizes that this number may vary from operator to operator. In 
the past, the FAA has estimated that this action takes 1 work-hour per 
airplane. Since operators incorporate maintenance or inspection program 
changes for their affected fleet(s), the FAA has determined that a per-
operator estimate is more accurate than a per-airplane estimate. 
Therefore, the FAA estimates the total cost per operator to be $7,650 
(90 work-hours x $85 per work-hour).
    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
aircraft that might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
           Labor cost                 Parts cost       Cost per product
------------------------------------------------------------------------
2 work-hours x $85 per hour =                    $8                $178
 $170...........................
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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

    The FAA has determined that this proposed AD would not have 
federalism implications under Executive Order 13132. This proposed AD 
would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:
0
a. Removing Airworthiness Directive (AD) 2021-25-12, Amendment 39-21856 
(86 FR 72174, December 21, 2021); and AD 2022-11-11, Amendment 39-22061 
(87 FR 33627, June 3, 2022); and
0
b. Adding the following new AD:

DeHavilland Aircraft of Canada (Type Certificate Previously Held by 
Bombardier, Inc.): Docket No. FAA-2024-0756; Project Identifier 
MCAI-2023-00549-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by May 6, 2024.

(b) Affected ADs

    This AD replaces AD 2021-25-12, Amendment 39-21856 (86 FR 72174, 
December 21, 2021) (AD 2021-25-12); and AD 2022-11-11, Amendment 39-
22061 (87 FR 33627, June 3, 2022) (AD 2022-11-11).

(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 4633 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports of a certain bolt at the pivot 
pin link being found missing or having stress corrosion cracking and 
a determination that the pivot pin and tow fitting assembly of the 
nose landing gear (NLG) must be replaced. The FAA is issuing this AD 
to address failure of the pivot pin retention bolt. The unsafe 
condition, if not addressed, could result in a loss of directional 
control or loss of an NLG tire during takeoff or landing, which 
could lead to runway excursions.

(f) Compliance

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

(g) Retained Maintenance or Inspection Program Revision, With No 
Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2021-25-12, with no changes. For airplanes with pivot pin retention 
bolt part number (P/N) NAS6204-14D installed on the NLG assembly: 
Within 30 days after January 5, 2022 (the effective date of AD 2021-
25-12), or within 30 days after installation of pivot pin retention 
bolt part number P/N NAS6204-14D, whichever occurs later, revise the 
existing maintenance or inspection program, as applicable, to 
incorporate the information for Structures Safe Life Task 32-21-01-
701 and Task 32-21-01-702, as specified in De Havilland Aircraft of 
Canada Limited Temporary Revision ALI-0223, dated October 15, 2020. 
The initial compliance time for doing the tasks is at the applicable 
time specified in De Havilland Aircraft of Canada Limited Temporary 
Revision ALI-0223, dated October 15, 2020, or within 30 days after 
January 5, 2022, whichever occurs later; except, if replacement of 
bolt P/N NAS6204-14D was performed before January 5, 2022, as 
specified in De Havilland Aircraft of Canada Service Bulletin 84-32-
161, the initial compliance time for Task 32-21-01-702 (bolt P/N 
NAS6204-14D replacement) is within 3 months after January 5, 2022, 
or within 800 flight cycles after performing the replacement, 
whichever occurs later.

(h) Retained No Alternative Actions or Intervals, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2021-25-12, with no changes. After the existing maintenance or 
inspection program has been revised as required by paragraph (g) of 
this AD, no alternative actions (e.g., replacements) or intervals 
may be used unless the actions and intervals are approved as an 
alternative method of compliance (AMOC) in

[[Page 20370]]

accordance with the procedures specified in paragraph (n)(1) of this 
AD.

(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, part number (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 applies to pivot pin retention bolt part number NAS6204-14D.

(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 30, 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 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) of this AD. Information may be emailed to: 9-AVS-
[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 Design Approval 
Organization (DAO). If approved by the DAO, the approval must 
include the DAO-authorized signature.

(o) Additional Information

    (1) Refer to Transport Canada AD CF-2023-22, dated March 30, 
2023, for related information. This Transport Canada AD may be found 
in the AD docket at regulations.gov under Docket No. FAA-2024-0756.
    (2) 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 [email protected].

 (p) 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 
[DATE 35 DAYS AFTER PUBLICATION OF THE FINAL RULE].
    (i) De Havilland Aircraft of Canada 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 
Service Bulletin 84-32-173, dated November 15, 2022, with Collins 
Aerospace Service Bulletin 47100-32-153, dated November 10, 2022, 
attached as one ``merged'' file for the convenience of affected 
operators.
    (ii) [Reserved]
    (4) The following service information 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 service information 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 service information 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 dehavilland.com">thd@dehavilland.com; website dehavilland.com.
    (7) You may view this service information 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 [email protected].

    Issued on March 15, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-05963 Filed 3-21-24; 8:45 am]
BILLING CODE 4910-13-P