Rule2024-06080
Airworthiness Directives; CFM International, S.A. Engines
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
March 22, 2024
Effective
March 25, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 89 Issue 57 (Friday, March 22, 2024)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-06080]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
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having general applicability and legal effect, most of which are keyed
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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:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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 <a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#added8c3cac0c283c983cec5c2edcbcccc83cac2db"><span class="__cf_email__" data-cfemail="c9babca7aea4a6e7ade7aaa1a689afa8a8e7aea6bf">[email protected]</span></a>.
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
<a href="http://regulations.gov">regulations.gov</a>, 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: <a href="/cdn-cgi/l/email-protection#62232c274f23264f232f2d21220403034c050d14"><span class="__cf_email__" data-cfemail="53121d167e12177e121e1c10133532327d343c25">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#86f5f3e8e1ebe9a8e2a8e5eee9c6e0e7e7a8e1e9f0"><span class="__cf_email__" data-cfemail="691a1c070e0406470d470a0106290f0808470e061f">[email protected]</span></a>.
(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
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on March 22, 2024.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.