89 FR 57 pgs. 20303-20306 - Airworthiness Directives; CFM International, S.A. Engines
Type: RULEVolume: 89Number: 57Pages: 20303 - 20306
Pages: 20303, 20304, 20305, 20306Docket number: [Docket No. FAA–2024–0760; Project Identifier AD–2024–00175–E; Amendment 39–22714; AD 2024–06–09]
FR document: [FR Doc. 2024–06080 Filed 3–19–24; 11:15 am]
Agency: Transportation Department
Sub Agency: Federal Aviation Administration
Official PDF Version: PDF Version
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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: sungmo.d.cho@faa.gov .
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
[top] 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
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:
| Action | Labor cost | Parts cost | Cost per product | Cost on U.S. operators |
|---|---|---|---|---|
| Replace CDP seal | 8 work-hours × $85 per hour = $680 | $131,200 | $131,880 | $395,640 |
| Replace HPC stage 3 disk | 8 work-hours × $85 per hour = $680 | 95,930 | 96,610 | 193,220 |
| Replace HPT rear shaft | 8 work-hours × $85 per hour = $680 | 187,900 | 188,580 | 377,160 |
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
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:
2024-06-09 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;
[top] (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-
(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.
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| Engine S/N | Engine model | CDP seal | S/N | P/N | HPC stage 3 disk | S/N | P/N | HPT rear shaft | 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 | |||
| 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: ANE-AD-AMOC@faa.gov.
(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: sungmo.d.cho@faa.gov.
(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]
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