2024-06-09: Engine (Turbine/Turboprop)

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 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; (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- 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 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: [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