[Federal Register Volume 89, Number 57 (Friday, March 22, 2024)]
[Rules and Regulations]
[Pages 20303-20306]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-06080]



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 Rules and Regulations
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  Federal Register / Vol. 89, No. 57 / Friday, March 22, 2024 / Rules 
and Regulations  

[[Page 20303]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-0760; Project Identifier AD-2024-00175-E; 
Amendment 39-22714; AD 2024-06-09]
RIN 2120-AA64


Airworthiness Directives; CFM International, S.A. Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain CFM International, S.A. (CFM) Model CFM56-2, CFM56-3, CFM56-5, 
CFM56-5B, CFM56-5C, and CFM56-7B engines. This AD was prompted by a 
report of electrical arcing on certain life-limited critical parts. 
This AD requires replacing certain compressor discharge pressure (CDP) 
seals, high-pressure compressor (HPC) stage 3 disks, and high-pressure 
turbine (HPT) rear shafts. This AD also prohibits installation of 
certain CDP seals, HPC stage 3 disks, and HPT rear shafts on any 
engine, and prohibits installation of any engine with certain CDP 
seals, HPC stage 3 disks, and HPT rear shafts installed on any 
airplane. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective March 25, 2024.
    The FAA must receive comments on this 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-2024-0760; 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, any comments received, and other 
information. The street address for Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer, 
FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238-
7241; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``FAA-2024-0760; Project Identifier AD-2024-00175-
E'' at the beginning of your comments. The most helpful comments 
reference a specific portion of the final rule, 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 this 
final rule 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 final rule.

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 (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this AD 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 AD, 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 AD. Submissions containing CBI should be sent to Sungmo 
Cho, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des 
Moines, WA 98198. Any commentary that the FAA receives which is not 
specifically designated as CBI will be placed in the public docket for 
this rulemaking.

Background

    On March 7, 2024, the FAA received a report of electrical arcing on 
certain life-limited critical parts for CFM Model CFM56-2, CFM56-3, 
CFM56-5, CFM56-5B, CFM56-5C, and CFM56-7B engines. A maintenance 
facility reported evidence of electrical arcing and identified the root 
cause as the use of a certain induction heater during maintenance, 
which resulted in unintended electrical arcing to those parts. The 
manufacturer determined that certain CDP seals, HPC stage 3 disks, and 
HPT rear shafts were subject to the same induction heater during 
maintenance and may also have electrical arcing damage. This condition, 
if not addressed, could result in premature fracture of certain CDP 
seals, HPC stage 3 disks, and HPT rear shafts, with consequent 
uncontained part release, damage to the engine, damage to the airplane, 
and loss of the airplane. The FAA is issuing this AD to address the 
unsafe condition on these products.

FAA's Determination

    The FAA is issuing this AD because the agency has determined the 
unsafe condition described previously is likely to exist or develop in 
other products of the same type design.

AD Requirements

    This AD requires replacing certain CDP seals, HPC stage 3 disks, 
and HPT rear shafts. This AD also prohibits installation of certain CDP 
seals, HPC stage 3 disks, and HPT rear shafts on any engine, and 
prohibits installation of any engine with certain CDP seals, HPC

[[Page 20304]]

stage 3 disks, and HPT rear shafts installed on any airplane.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies forgoing notice and comment prior to adoption of this rule 
due to maintenance anomalies that could result in premature fracture of 
certain life-limited critical parts, with consequent uncontained part 
release, damage to the engine, damage to the airplane, and loss of the 
airplane. The compliance time for replacement of these parts is before 
further flight after the effective date of this AD. The longer these 
parts remain in service, the higher the probability of failure. 
Accordingly, notice and opportunity for prior public comment are 
impracticable and contrary to the public interest pursuant to 5 U.S.C. 
553(b)(3)(B).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forgo notice and 
comment.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 3 engines installed on 
airplanes of U.S. registry. The FAA estimates that three engines 
installed on airplanes of U.S. registry require replacement of the CDP 
seal. The FAA estimates that two engines installed on airplanes of U.S. 
registry require replacement of the HPC stage 3 disk and HPT rear 
shaft.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replace CDP seal......................  8 work-hours x $85 per          $131,200        $131,880        $395,640
                                         hour = $680.
Replace HPC stage 3 disk..............  8 work-hours x $85 per            95,930          96,610         193,220
                                         hour = $680.
Replace HPT rear shaft................  8 work-hours x $85 per           187,900         188,580         377,160
                                         hour = $680.
----------------------------------------------------------------------------------------------------------------

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, and
    (2) Will not affect intrastate aviation in Alaska.

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:

2024-06-09 CFM International, S.A.: Amendment 39-22714; Docket No. 
FAA-2024-0760; Project Identifier AD-2024-00175-E.

(a) Effective Date

    This airworthiness directive (AD) is effective March 25, 2024.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the following CFM International, S.A. Model 
engines:
    (1) CFM56-2, CFM56-2A, CFM56-2B, CFM56-3, CFM56-3B, and CFM56-3C 
engines;
    (2) CFM56-5, CFM56-5-A1/F, CFM56-5A3, CFM56-5A4, CFM56-5A4/F, 
CFM56-5A5, and CFM56-5A5/F engines;
    (3) CFM56-5B1, CFM56-5B1/2P, CFM56-5B1/3, CFM56-5B1/P, CFM56-
5B2, CFM56-5B2/2P, CFM56-5B2/3, CFM56-5B2/P, CFM56-5B3/2P, CFM56-
5B3/2P1, CFM56-5B3/3, CFM56-5B3/3B1, CFM56-5B3/P, CFM56-5B3/P1, 
CFM56-5B4, CFM56-5B4/2P, CFM56-5B4/2P1, CFM56-5B4/3, CFM56-5B4/3B1, 
CFM56-5B4/P, CFM56-5B4/P1, CFM56-5B5, CFM56-5B5/3, CFM56-5B5/P, 
CFM56-5B6, CFM56-5B6/2P, CFM56-5B6/3, CFM56-5B6/P, CFM56-5B7, CFM56-
5B7/3, CFM56-5B7/P, CFM56-5B8/3, CFM56-5B8/P, CFM56-5B9/2P, CFM56-
5B9/3, and CFM56-5B9/P engines;
    (4) CFM56-5C2, CFM56-5C2/4, CFM56-5C2/F, CFM56-5C2/F4, CFM56-
5C2/G, CFM56-5C2/G4, CFM56-5C2/P, CFM56-5C3/F, CFM56-5C3/F4, CFM56-
5C3/G, CFM56-5C3/G4, CFM56-5C3/P, CFM56-

[[Page 20305]]

5C4, CFM56-5C4/1, CFM56-5C4/1P, and CFM56-5C4/P engines; and
    (5) CFM56-7B20, CFM56-7B20/2, CFM56-7B20/3, CFM56-7B20E, CFM56-
7B22, CFM56-7B22/2, CFM56-7B22/3, CFM56-7B22/3B1, CFM56-7B22/B1, 
CFM56-7B22E, CFM56-7B22E/B1, CFM56-7B24, CFM56-7B24/2, CFM56-7B24/3, 
CFM56-7B24/3B1, CFM56-7B24/B1, CFM56-7B24E, CFM56-7B24E/B1, CFM56-
7B26, CFM56-7B26/2, CFM56-7B26/3, CFM56-7B26/3B1, CFM56-7B26/3B2, 
CFM56-7B26/3B2F, CFM56-7B26/3F, CFM56-7B26/B1, CFM56-7B26/B2, CFM56-
7B26E, CFM56-7B26E/B1, CFM56-7B26E/B2, CFM56-7B26E/B2F, CFM56-7B26E/
F, CFM56-7B27, CFM56-7B27/2, CFM56-7B27/3, CFM56-7B27/3B1, CFM56-
7B27/3B1F, CFM56-7B27/3B3, CFM56-7B27/3F, CFM56-7B27/B1, CFM56-7B27/
B3, CFM56-7B27A, CFM56-7B27A/3, CFM56-7B27AE, CFM56-7B27E, CFM56-
7B27E/B1, CFM56-7B27E/B1F, and CFM56-7B27E/B3 engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7200, Engine 
(Turbine/Turboprop).

(e) Unsafe Condition

    This AD was prompted by a report of evidence of electrical 
arcing on certain life-limited critical parts. The FAA is issuing 
this AD to prevent premature fracture of certain compressor 
discharge pressure (CDP) seals, high-pressure compressor (HPC) stage 
3 disks, and high-pressure turbine (HPT) rear shafts. The unsafe 
condition, if not addressed, could lead to uncontained part release, 
damage to the engine, damage to the airplane, and loss of the 
airplane.

(f) Compliance

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

(g) Required Actions

    Before further flight after the effective date of this AD, 
remove from service each CDP seal, HPC stage 3 disk, and HPT rear 
shaft having a part number (P/N) and serial number (S/N) specified 
in Table 1 to paragraph (g) of this AD and replace with a part 
eligible for installation.

                                    Table 1 to Paragraph (g)--Affected Parts
----------------------------------------------------------------------------------------------------------------
                                       CDP seal                HPC stage 3 disk             HPT rear shaft
  Engine S/N    Engine model -----------------------------------------------------------------------------------
                                   S/N           P/N           S/N           P/N           S/N           P/N
----------------------------------------------------------------------------------------------------------------
779879         CFM56-5B       GFF5HR7H      2116M25P01    XAEH4524      1590M59P01    TMT3SB56      1864M90P05
575151         CFM56-5B       GFF5J2R0      1523M35P01    XAEW3896      1590M59P01    TMTA6584      1864M90P04
643313         CFM56-5B       GFF5LL3P      2116M25P01    XAE6377U      2116M23P01    TMT1RJ6T      1864M90P04
643308         CFM56-5B       GFF5LL5R      2116M25P01    XAE6416U      2116M23P01    TMT1T7KF      1864M90P04
643443         CFM56-5B       GFF5LN9K      2116M25P01    XAE6576U      2116M23P01    TMT1UCL8      1864M90P04
643384         CFM56-5B       GFF5LN29      2116M25P01    XAE6749U      2116M23P01    TMT1UDJN      1864M90P04
643383         CFM56-5B       GFF5LN7C      2116M25P01    XAE6883U      2116M23P01    TMT1UTL2      1864M90P04
960147         CFM56-7B       GFF5LC8G      2116M25P01    XAE6329U      2116M23P01    TMT1LPT5      1864M90P04
890800         CFM56-7B       GFF5GL4T      2116M25P01    XAEY9605      2116M23P01    TMTA3602      1864M90P04
960113         CFM56-7B       GFF5LLHK      2116M25P01    XAE6496U      2116M23P01    TMT1RJ6P      1864M90P04
960105         CFM56-7B       GFF5KTW1      2116M25P01    XAE6196U      2116M23P01    TMT1PM2N      1864M90P04
803767         CFM56-7B       GFF5LLJE      2116M25P01    XAE6497U      2116M23P01    TMT1PRR6      1864M90P04
962116         CFM56-7B       GFF5LM2F      2116M25P01    XAE6482U      2116M23P01    TMT1PRR4      1864M90P04
960999         CFM56-7B       GFF5LLK6      2116M25P01    XAE6502U      2116M23P01    TMT1PN56      1864M90P04
961787         CFM56-7B       GFF5LL4A      2116M25P01    XAE7292U      2116M23P01    TMT1U29H      1864M90P04
962504         CFM56-7B       GFF5LLH4      2116M25P01    XAE7324U      2116M23P01    TMT1LPJ6      1864M90P04
962491         CFM56-7B       GFF5LPKJ      2116M25P01    XAE7116U      2116M23P01    TMT1RJ6E      1864M90P04
575348         CFM56-5B       GFF5LH68      2116M25P01    XAE6017U      2116M23P01    TMT1NLFE      1864M90P04
575243         CFM56-5B       GFF5KN5K      2116M25P01    XAE5290U      2116M23P01    TMT1JHJ7      1864M90P04
577604         CFM56-5B       GFF5L936      2116M25P01    XAE4312U      2116M23P01    TMT1JKK8      1864M90P04
577255         CFM56-5B       GFF5ECKK      1523M35P01    XAEG0763      1590M59P01    TMT1M7UD      1864M90P04
645551         CFM56-5B       GFF5LH4H      2116M25P01    XAE5738U      2116M23P01    TMT1NLF0      1864M90P04
779544         CFM56-5B       GFF5ELT0      1523M35P01    XAEW3361      1590M59P01    TMT3SD14      1864M90P05
575840         CFM56-5B       GFF5J4R8      1523M35P01    N/A           N/A           TMTD4155      1864M90P04
960395         CFM56-7B       GFF5G2WC      2116M25P01    XAEV5927      2116M23P01    TMTA1872      1864M90P04
575806         CFM56-5B       GFF5LLHT      2116M25P01    XAEW3261      1590M59P01    TMTD1698      1864M90P04
699126         CFM56-5B       GFF5DNJG      2116M25P01    XAER4768      2116M23P01    TMTA5963      1864M90P04
699277         CFM56-5B       GFF5GWRJ      2116M25P01    XAEBS962      2116M23P01    TMT4E107      1864M90P04
697355         CFM56-5B       GFF59NHM      1523M35P01    GWN04DF4      1590M59P01    TMT3SA87      1864M90P05
577182         CFM56-5B       GFF5DG9W      1523M35P01    XAEH5166      1590M59P01    TMT3S111      1864M90P05
779990         CFM56-5B       GFF5K300      2116M25P01    N/A           N/A           N/A           N/A
697483         CFM56-5B       GFF5LGT2      2116M25P01    XAE5993U      2116M23P01    TMT1MMNL      1864M90P04
577181         CFM56-5B       GFF5J4DH      2116M25P01    XAEGD205      2116M23P01    TMTD1836      1864M90P04
569701         CFM56-5B       GFF5HTFW      2116M25P01    XAEDU465      2116M23P01    TMTA8863      1864M90P04
569702         CFM56-5B       GFF5HTWC      2116M25P01    XAECR455      2116M23P01    TMT1H3E3      1864M90P04
802219         CFM56-7B       GFF5LH8R      2116M25P01    XAE6050U      2116M23P01    TMT1MHCE      1864M90P04
643567         CFM56-5B       GFF5LMWK      2116M25P01    XAE6981U      2116M23P01    TMT1U28M      1864M90P04
573567         CFM56-5B       GFF5JARC      2116M25P01    N/A           N/A           N/A           N/A
643851         CFM56-5B       GFF5LN01      2116M25P01    XAE6899U      2116M23P01    TMT1U0J7      1864M90P04
699992         CFM56-5B       N/A           N/A           XAEHP389      2116M23P01    N/A           N/A
645978         CFM56-5B       GFF5KN5N      2116M25P01    XAE5574U      2116M23P01    TMT1JKJJ      1864M90P04
643446         CFM56-5B       GFF5L8K8      2116M25P01    XAE5761U      2116M23P01    TMT1M7UJ      1864M90P04
643447         CFM56-5B       GFF5L9PN      2116M25P01    XAE5757U      2116M23P01    TMT1MGNL      1864M90P04
699642         CFM56-5B       GFF5L9PR      2116M25P01    XAE6316U      2116M23P01    TMT1MNA8      1864M90P04
643470         CFM56-5B       GFF5LKEP      2116M25P01    XAE6406U      2116M23P01    TMT1RJ7P      1864M90P04
699283         CFM56-5B       GFF5L9P9      2116M25P01    XAE5741U      2116M23P01    TMT1JNTP      1864M90P04
643730         CFM56-5B       GFF5LL3W      2116M25P01    XAE6507U      2116M23P01    TMT1PN4H      1864M90P04
699279         CFM56-5B       GFF5LE8P      2116M25P01    XAE6282U      2116M23P01    TMT1L01A      1864M90P04
699644         CFM56-5B       GFF5LE41      2116M25P01    XAE6311U      2116M23P01    TMT1PG4N      1864M90P04
643479         CFM56-5B       GFF5LFDA      2116M25P01    XAE6892U      2116M23P01    TMT1JLU6      1864M90P04
643635         CFM56-5B       GFF5LN4R      2116M25P01    XAE6811U      2116M23P01    TMT1U0HR      1864M90P04
643633         CFM56-5B       GFF5LMJ9      2116M25P01    XAE6568U      2116M23P01    TMT1JKFH      1864M90P04

[[Page 20306]]

 
699867         CFM56-5B       GFF5LN9E      2116M25P01    XAE6932U      2116M23P01    TMT1UNLM      1864M90P04
643267         CFM56-5B       GFF5MH2       2116M25P01    XAE7182U      2116M23P01    TMT1U296      1864M90P04
779533         CFM56-5B       GFF5J6MH      2116M25P01    XAEGD645      2116M23P01    TMTD2505      1864M90P04
643444         CFM56-5B       GFF5LN7D      2116M25P01    N/A           N/A           TMT1U9RJ      1864M90P04
699887         CFM56-5B       GFF5LKGP      2116M25P01    XAE6818U      2116M23P01    TMT1U0HU      1864M90P04
----------------------------------------------------------------------------------------------------------------


    Note 1 to paragraph (g): Table 1 to paragraph (g) of this AD 
includes, for information only, the engine serial numbers (engine S/
N) and engine models on which the affected parts were installed.

(h) Installation Prohibition

    (1) After the effective date of this AD, do not install any CDP 
seal, HPC stage 3 disk, or HPT rear shaft having a P/N and S/N 
specified in Table 1 to paragraph (g) of this AD on any engine.
    (2) After the effective date of this AD, do not install any 
engine having a CDP seal, HPC stage 3 disk, or HPT rear shaft having 
a P/N and S/N specified in Table 1 to paragraph (g) of this AD 
installed on any airplane.

(i) Definition

    For the purposes of this AD, a part eligible for installation is 
any CDP seal, HPC stage 3 disk, or HPT rear shaft that does not have 
a P/N and S/N specified in Table 1 to paragraph (g) of this AD.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, AIR-520 Continued Operational Safety 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 AIR-520 Continued 
Operational Safety Branch, send it to the attention of the person 
identified in paragraph (k) of this AD and email to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(k) Additional Information

    For more information about this AD, contact Sungmo Cho, Aviation 
Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; 
phone: (781) 238-7241; email: [email protected].

(l) Material Incorporated by Reference

    None.

    Issued on March 18, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-06080 Filed 3-19-24; 11:15 am]
BILLING CODE 4910-13-P