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Federal Register / Vol. 86, No. 108 / Tuesday, June 8, 2021 / Rules and Regulations
3 Will 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 Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

20211115 International Aero Engines AG: Amendment 3921577; Docket No.
FAA20210129; Project Identifier AD
202001597E.
a Effective Date This airworthiness directive AD is effective July 13, 2021.
b Affected ADs None.
c Applicability This AD applies to International Aero Engines AG IAE V2522A5, V2524A5, V2525D5, V2527A5, V2527EA5, V2527MA5, V2528D5, V2530A5, V2531
E5, and V2533A5 model turbofan engines with an installed:
1 High-pressure turbine HPT 1st-stage disk, part number P/N 2A5001, with a serial number S/N listed in Appendix A, Table 1, of IAE Non-Modification Service Bulletin NMSB No. V2500ENG720713, Revision 1, dated January 26, 2021 IAE NMSB V2500
ENG720713, Revision 1 or IAE NMSB No.
V2500E5720015, dated December 15, 2020 IAE NMSB V2500E5720015; and/
or 2 HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE
NMSB V2500ENG720713, Revision 1, or IAE NMSB V2500E5720015.

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d Subject Joint Aircraft System Component JASC
Code 7250, Turbine Section.
e Unsafe Condition This AD was prompted by an analysis performed by the manufacturer after an event involving an uncontained failure of a HPT
1st-stage disk that resulted in high-energy debris penetrating the engine cowling. The FAA is issuing this AD to prevent failure of the HPT 1st-stage disk and HPT 2nd-stage
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disk. The unsafe condition, if not addressed, could result in uncontained HPT disk failure, 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 1 For IAE V2527EA5, V2527MA5, V2528D5, V2530A5, and V2533A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500ENG72
0713, Revision 1, at the next engine shop visit after the effective date of this AD or before the HPT 1st-stage disk has accumulated 3,200 flight cycles FCs since the effective date of this AD, whichever occurs first, perform an ultrasonic inspection USI of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB V2500ENG720713, Revision 1.
Note 1 to paragraph g1: The USI
required by paragraphs g1 through 6 of this AD requires the HPT 1st-stage disk and HPT 2nd-stage disks to be removed from the engine allowing piece-part opportunity inspections. Per the Airworthiness Limitations Section of the manufacturers Instructions for Continued Airworthiness ICAs, the additional inspections are not required unless the part has more than 100
FCs since the last piece-part opportunity inspection, is damaged, or is the cause for the removal of the engine. Engine removal for the purposes of complying with this AD is not cause for removal as stated in the ALS.
2 For IAE V2527EA5, V2527MA5, V2528D5, V2530A5, and V2533A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500ENG72
0713, Revision 1, at the next engine shop visit after the effective date of this AD or before the HPT 2nd-stage disk has accumulated 3,200 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB V2500ENG72
0713, Revision 1.
3 For IAE V2522A5, V2524A5, V2525
D5, and V2527A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500ENG720713, Revision 1, at the next HPT rotor and stator assembly HPT module removal or before the HPT 1st-stage disk has accumulated 6,700
FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB V2500ENG720713, Revision 1.
4 For IAE V2522A5, V2524A5, V2525
D5, and V2527A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500ENG720713, Revision 1, at the next HPT module removal or before the HPT 2nd-stage disk has
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accumulated 6,700 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB V2500ENG72
0713, Revision 1.
5 For IAE V2531E5 model turbofan engines with an HPT 1st-stage disk, P/N
2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500E5720015, at the next engine shop visit or before the HPT
1st-stage disk has accumulated 3,200 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 1ststage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB
V2500E5720015.
6 For IAE V2531E5 model turbofan engines with an HPT 2nd-stage disk, P/N
2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500E5720015, at the next engine shop visit or before the HPT
2nd-stage disk has accumulated 3,200 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 2ndstage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB
V2500E5720015.
7 If, during the USI required by paragraphs g1 through 6 of this AD, a HPT 1st-stage disk or HPT 2nd-stage disk does not pass the inspection as specified in the Accomplishment Instructions, paragraph 8., of IAE NMSB V2500ENG720713, Revision 1, or IAE NMSB V2500E572
0015, as applicable, before further flight, remove the HPT 1st-stage disk or 2nd-stage disk, as applicable, from service and replace with a part eligible for installation.
h Definition 1 For the purpose of this AD, an engine shop visit is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, HP, except for the following situations, which do not constitute an engine shop visit.
i Separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance.
ii Engine removal for the purpose of performing field maintenance activities at a maintenance facility in lieu of performing them on-wing.
2 For the purpose for this AD, a part eligible for installation is:
i An HPT 1st-stage disk or HPT 2nd-stage disk listed in Appendix A, Tables 1 and 2, of IAE NMSB V2500ENG720713, Revision 1, or Appendix A, Tables 1 and 2, of IAE NMSB V2500E5720015, that passed the USI required by paragraphs g1
through 6 of this AD; or ii An HPT 1st-stage disk or HPT 2nd-stage disk that is not listed in Appendix A, Tables 1 and 2, of IAE NMSB V2500ENG720713, Revision 1, or Appendix A, Tables 1 and 2, of IAE NMSB V2500E5720015.
i Alternative Methods of Compliance AMOCs 1 The Manager, ECO 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,
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