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Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Rules and Regulations 1 Is not a significant regulatory action under Executive Order 12866, 2 Will not affect intrastate aviation in Alaska, and 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:

20211107 General Electric Company:
Amendment 3921569; Docket No.
FAA20200850; Project Identifier AD
202000288E.
a Effective Date This airworthiness directive AD is effective July 30, 2021.

b Affected ADs
33497

d Subject
None.
c Applicability This AD applies to:
1 General Electric Company GE GEnx 1B64, GEnx1B64/P1, GEnx1B64/P2, GEnx 1B67, GEnx1B67/P1, GEnx1B67/P2, GEnx 1B70, GEnx1B70/75/P1, GEnx1B70/75/P2, GEnx1B70/P1, GEnx1B70/P2, GEnx 1B70C/P1, GEnx1B70C/P2, GEnx1B74/75/
P1, GEnx1B74/75/P2, GEnx1B76/P2, GEnx1B76A/P2 model turbofan engines with stages 610 compressor rotor spools in the high-pressure compressor HPC
assembly with the following part numbers P/N installed:
i P/N 2357M30G01, P/N 2357M30G02, P/N 2439M35G01, P/N 2439M35G02, or P/N
2445M40G02, all serial numbers S/Ns;
ii P/N 2610M90G01 with the S/Ns listed in paragraph 4., APPENDIXA, Table 1 of the GE GEnx1B Service Bulletin SB 72
0472 R02, dated November 5, 2020 GEnx1B
SB 720472; and iii P/N 2628M56G01 with the S/Ns listed in paragraph 4., APPENDIXA, Table 2 or Table 3 of GEnx1B SB 720472.
2 GEnx2B67, GEnx2B67/P, GEnx 2B67B model turbofan engines with the following stages 610 compressor rotor spools P/Ns installed:
i P/N 2357M30G02, P/N 2439M35G02, or P/N 2445M40G02, all S/Ns;
ii P/N 2340M36G01 with S/Ns listed in paragraph 4., APPENDIXA, Table 1 of GE
GEnx2B SB 720415 R02, dated November 5, 2020 GEnx2B SB 720415; and iii P/N 2628M56G01 with S/Ns listed in paragraph 4., APPENDIXA, Table 2 or Table 3 of GEnx2B SB 720415.

Joint Aircraft System Component JASC
Code 7230, Turbine Engine Compressor Section.
e Unsafe Condition This AD was prompted by a finding during an inspection that two stages 610
compressor rotor spools were damaged at similar locations. In addition, the manufacturer reported that certain stages 6
10 compressor rotor spool webs did not undergo a required fluorescent penetrant inspection FPI during production. The FAA
is issuing this AD to prevent failure of the compressor rotor spool. The unsafe condition, if not addressed, could result in uncontained release of debris, damage to the engine, and damage to the airplane.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Required Actions 1 For all affected GEnx1B and GEnx2B
model turbofan engines, before exceeding the compliance time in Table 1 to paragraph g1 of this AD, perform a borescope inspection BSI or eddy current inspection ECI of the stage 6, stage 7, and stage 8 webs, web transitions, and bore faces of the stages 610 compressor rotor spool in accordance with the Accomplishment Instructions, paragraph 3, of GEnx1B SB 720472 for GEnx1B models or the Accomplishment Instructions, paragraph 3, of GEnx2B SB 72
0415 for GEnx2B models.

TABLE 1 TO PARAGRAPH g1
Cycles Since New CSN accumulated on the stages 610 compressor rotor spool
Compliance time
Less than 6,400 CSN

Next engine shop visit or before the stages 610 compressor rotor spool accumulates 6,500
CSN, whichever occurs first after the effective date of this AD.
Within 100 flight cycles after the effective date of this AD.

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6,400 CSN or greater

i For GEnx1B model turbofan engines, except those identified in paragraph 4, APPENDIXA, Table 3 of SB 720472, if, before the effective date of this AD, the engines have undergone inspections of the aft web of stage 6, stage 7, and stage 8 of the stages 610 compressor rotor spool using both GE GEnx1B SB 720448 R00, dated July 29, 2019, and GE GEnx1B SB 720460
R00, dated October 30, 2019, regardless of the CSN accumulated on the stages 610
compressor rotor spool, perform the inspection required by paragraph g1 of this AD no later than the next engine shop visit after the effective date of this AD.
ii For GEnx2B model turbofan engines, except those identified in paragraph 4., APPENDIXA, Table 3 of SB 720415, if, before the effective date of this AD, the engines have undergone inspections of the aft web of stage 6, stage 7, and stage 8 of the stages 610 compressor rotor spool using
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both GE GEnx2B SB 72385 R02, dated July 29, 2019, and GE GEnx2B SB 720398 R00, dated October 30, 2019, regardless of the CSN
accumulated on the stages 610 compressor rotor spool, perform the inspection required by paragraph g1 of this AD no later than the next engine shop visit after the effective date of this AD.
2 For all affected GEnx1B and GEnx2B
model turbofan engines, during the inspections required by paragraph g1 of this AD, if a rejectable indication is found, before further flight, remove the stages 610
compressor rotor spool from service and replace it with a part eligible for installation.
h Definitions 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, except that the separation of engine
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flanges solely for the purposes of transportation of the engine without subsequent engine maintenance does not constitute an engine shop visit.
2 For the purpose of this AD, a rejectable indication is:
i A BSI indication that does not meet the BSI serviceable or repairable limits referenced in the Accomplishment Instructions, paragraph 3.A.1a2, of GEnx 1B SB 720472, or paragraph 3.A.1a2 of GEnx2B SB 720415, and the affected part has not undergone a subsequent ECI; or ii A BSI indication that does not meet the BSI serviceable or repairable limits referenced in the Accomplishment Instructions, paragraph 3.A.1a2, of GEnx 1B SB 720472, or paragraph 3.A.1a2 of GEnx2B SB 720415, and the affected part has undergone a subsequent ECI in which the indication did not meet the ECI serviceable or repairable limits referenced in the
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