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Federal Register / Vol. 86, No. 122 / Tuesday, June 29, 2021 / Proposed Rules
34167

ESTIMATED COSTS
Action
Labor cost
Replace HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate pro-rated part cost.

300 work-hours $85 per hour =
$25,500.

Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs 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 Agencys 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 The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
1 Is not a significant regulatory action under Executive Order 12866, 2 Would not affect intrastate aviation in Alaska, and 3 Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

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Parts cost
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:

Pratt & Whitney: Docket No. FAA2021
0515; Project Identifier AD2021
00191E.
a Comments Due Date The FAA must receive comments on this airworthiness directive AD by August 13, 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 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
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$86,252

Cost per product $111,752

Cost on U.S.
operators $9,834,176

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, 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,
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