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Federal Register / Vol. 86, No. 181 / Wednesday, September 22, 2021 / Rules and Regulations
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, 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:

20212001 Pratt & Whitney: Amendment 3921739; Docket No. FAA20210515;
Project Identifier AD202100191E.
a Effective Date This airworthiness directive AD is effective October 27, 2021.
b Affected ADs None.
c Applicability This AD applies to Pratt & Whitney PW1519G, PW1521G, PW1521G3, PW1521GA, PW1524G, PW1524G3, PW1525G, PW1525G3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923GA model turbofan engines with a high-pressure turbine HPT 1st-stage hub, part number P/N 30G5701, or an HPT rotor 1st-stage blade retaining plate, P/N 30G1692, installed.
d Subject Joint Aircraft System Component JASC
Code 7250, Turbine Section.
e Unsafe Condition This AD was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate fail to meet the published life-cycle limits for each part. The FAA is issuing this AD to prevent failure of the HPT 1st-stage hub or HPT rotor 1st-stage blade retaining plate. The unsafe condition, if not addressed, could result in the release
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of the HPT 1st-stage hub or HPT rotor 1ststage blade retaining plate, damage to the engine, and damage to the aircraft.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Required Actions 1 For PW1519G, PW1521G, PW1521G3, PW1521GA, PW1524G, and PW1524G3
model turbofan engines:
i For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with 3,000 cycles since new CSN or fewer on the effective date of this AD, before the affected part exceeds 4,700
CSN, remove the affected part, as applicable, and replace with a part eligible for installation.
ii For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with greater than 3,000 CSN
but fewer than 4,960 CSN on the effective date of the AD, at the next engine shop visit after accumulating 4,700 CSN or before the affected part exceeds 5,260 CSN, whichever occurs first, remove the affected part, as applicable, and replace with a part eligible for installation.
iii For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with 4,960 CSN or greater on the effective date of the AD, at the next engine shop visit or within 300 cycles after the effective date of this AD, whichever occurs first, remove the affected part, as applicable, and replace with a part eligible for installation.
2 For PW1919G and PW1921G model turbofan engines:
i For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with 3,000 CSN or fewer on the effective date of this AD, before the affected part exceeds 4,700 CSN, remove the affected part, as applicable, and replace with a part eligible for installation.
ii For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with greater than 3,000 CSN
but fewer than 4,700 CSN on the effective date of the AD, at the next engine shop visit after the affected part accumulates 4,700 CSN
or before the affected part exceeds 5,000
CSN, whichever occurs first, remove the affected part, as applicable, and replace with a part eligible for installation.
iii For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with 4,700 CSN or greater on the effective date of the AD, at the next engine shop visit or within 300 cycles after the effective date of this AD, whichever occurs first, remove the affected part, as applicable, and replace with a part eligible for installation.
3 For PW1525G and PW1525G3 model turbofan engines:
i Before the affected HPT 1st-stage hub and affected HPT rotor 1st-stage blade retaining plate exceeds 2,800 CSN, respectively, or within 300 cycles after the effective date of this AD, whichever occurs later, remove the affected part, as applicable,
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and replace with a part eligible for installation.
ii Reserved 4 For PW1922G, PW1923G, and PW1923GA model turbofan engines:
i Before the affected HPT 1st-stage hub and affected HPT rotor 1st-stage blade retaining plate exceeds 3,000 CSN, respectively, or within 300 cycles after the effective date of this AD, whichever occurs later, remove the affected part, as applicable, and replace with a part eligible for installation.
ii Reserved 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 case flanges, except for the following, which do not constitute an engine shop visit:
i Separation of engine flanges solely for the purposes of transportation without subsequent maintenance does not constitute an engine shop visit.
ii Separation of engine flanges solely for the purpose of replacing the fan without subsequent maintenance does not constitute an engine shop visit.
2 For the purpose of this AD, a part eligible for installation is:
i For PW1519G, PW1521G, PW1521G3, PW1521GA, PW1524G, PW1524G3, PW1919G, and PW1921G model turbofan engines:
A Any HPT 1st-stage hub with P/N
30G5701 with 4,700 CSN or fewer, or with a P/N not listed in this AD.
B Any HPT rotor 1st-stage blade retaining plate with P/N 30G1692 with 4,700 CSN or fewer, or with a P/N not listed in this AD.
ii For PW1525G and PW1525G3 model turbofan engines:
A Any HPT 1st-stage hub with P/N
30G5701 with 2,800 CSN or fewer, or with a P/N not listed in this AD.
B Any HPT rotor 1st-stage blade retaining plate with P/N 30G1692 with 2,800 CSN or fewer, or with a P/N not listed in this AD.
iii For PW1922G, PW1923G, and PW1923GA model turbofan engines:
A Any HPT 1st-stage hub with P/N
30G5701 with 3,000 CSN or fewer, or with a P/N not listed in this AD.
B Any HPT rotor 1st-stage blade retaining plate with P/N 30G1692 with 3,000 CSN or fewer, or with a P/N not listed in this AD.
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, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph j of this AD. You may email your request to: ANE-AD-AMOC@
faa.gov.
2 Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager
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