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Federal Register / Vol. 86, No. 128 / Thursday, July 8, 2021 / Rules and Regulations 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 has determined that this AD
will not have federalism implications under Executive Order 13132. This AD
will 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 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:
a. Removing Airworthiness Directive AD 20192111, Amendment 3919777
84 FR 57813, October 29, 2019; and AD 20200702, Amendment 3921106
85 FR 17742, March 31, 2020; and b. Adding the following new airworthiness directive:

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20211406 Pratt & Whitney: Amendment 3921633; Docket No. FAA20210191;
Project Identifier AD202001492E.
a Effective Date This airworthiness directive AD is effective August 12, 2021.
b Affected ADs This AD replaces AD 20192111, Amendment 3919777 84 FR 57813, October 29, 2019; and AD 20200702, Amendment 3921106 85 FR 17742, March 31, 2020.

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c Applicability This AD applies to Pratt & Whitney PW
PW1519G, PW1521G, PW1521G3, PW1521GA, PW1524G, PW1524G3, PW1525G, PW1525G3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923GA model turbofan engines.
d Subject Joint Aircraft System Component JASC
Code 7230, Turbine Engine Compressor Section.
e Unsafe Condition This AD was prompted by reports of inflight shutdowns due to failure of the lowpressure compressor LPC rotor 1 R1 and by subsequent findings of cracked LPC R1s during inspection. The FAA is issuing this AD to prevent failure of the LPC R1. The unsafe condition, if not addressed, could result in uncontained release of the LPC R1, damage to the engine, damage to the airplane, and loss of control of the airplane.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Required Actions 1 Except for those model turbofan engines identified in paragraph g2 of this AD, perform a borescope inspection BSI of the LPC R1 for damage and cracks as follows:
i For engines that have accumulated fewer than 300 flight cycles since new CSN, perform a BSI within 50 flight cycles FCs from September 26, 2019 the effective date of AD 20191911, or before further flight, whichever occurs later.
ii For engines that have accumulated fewer than 300 FCs since installation of V2.11.7 or V2.11.8 electronic engine control EEC full authority digital electronic control FADEC software, perform a BSI within 50
FCs from October 29, 2019 the effective date of AD 20192111, or before further flight, whichever occurs later.
iii Thereafter, at intervals not to exceed 50 FCs until the engine accumulates 300
flight CSN or accumulates 300 FCs since the installation of V2.11.7 or V2.11.8 EEC FADEC
software, whichever occurs later, repeat the BSI for damage and cracks.
iv Perform the BSI required by paragraphs g1i through iii of this AD at the following LPC R1 locations:
A The blade tip;
B The leading edge;
C The leading edge fillet to rotor platform radius; and D The airfoil convex side root fillet to rotor platform radius.
2 For any affected PW model turbofan engine installed as a zero time spare, except for PW1519G, PW1521GA, PW1919G, and PW1922G model turbofan engines, within 15 FCs from the effective date of this AD, and thereafter at intervals not to exceed 15 FCs until the engine accumulates 300
flight CSN, perform a BSI of the LPC R1 for damage and cracks at the locations in paragraph g1iv of this AD.
3 Based on the results of the BSIs required by paragraphs g1 and 2 of this
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AD, before further flight, remove and replace the LPC R1 if:
i There is damage on an LPC R1 that exceeds serviceable limits; or ii Any crack in the LPC R1 exists.
Note 1 to paragraph g3: Guidance on determining the serviceable limits in paragraph g3 of this AD can be found in PW Service Bulletin SB PW1000GA72
00012500A930AD, Issue No. 002, dated October 24, 2019, and PW SB PW1000GA
7200007500B930AD, Issue No. 003, dated October 24, 2019.
4 For PW PW1519G, PW1521G, PW1521G3, PW1521GA, PW1524G, PW1524G3, PW1525G, and PW1525G3
model turbofan engines, within 120 days from the effective date of this AD, remove the EEC FADEC software if the version is earlier than EEC FADEC software version V2.11.10.4
and install EEC FADEC software that is eligible for installation.
5 For PW PW1919G, PW1921G, PW1922G, PW1923G, and PW1923GA
model turbofan engines, within 120 days of the effective date of this AD, remove the EEC
FADEC software if the version is earlier than EEC FADEC software version V9.5.6.7 and install EEC FADEC software that is eligible for installation.
6 For PW PW1519G, PW1521G, PW1521G3, PW1521GA, PW1524G, PW1524G3, PW1525G, and PW1525G3
model turbofan engines with EEC FADEC
software version V2.11.10.4 or later installed, within 15 FCs after receipt of Onboard Maintenance Message fault code 7100F0029
or 7100F0030, perform a BSI of the LPC R1
for damage and cracks at the locations in paragraph g1iv of this AD if the fault code is displayed on the Active Failure Messages and meets the following criteria:
i N1 Exceedance is above 95.2%;
ii N1 Exceedance occurred above 29,100
feet; and iii N1 Exceedance occurs for a duration of 40 seconds 15 seconds of cockpit display or more during any flight.
Note 2 to paragraph g6: Guidance on determining the N1 Exceedance duration can be found in PW Section PW1000GA7200
0002A0B5AA of PW Engine Maintenance Manual EMM, Issue No. 016, dated January 15, 2021.
Note 3 to paragraph g6: Guidance on performing the BSI can be found in PW
Section PW1000GA72310000A312A
D of PW EMM, Issue No. 016, dated January 11, 2021.
7 As the result of the BSI of the LPC R1
required by paragraph g6 of this AD, before further flight, remove and replace the LPC R1 if:
i There is damage on an LPC R1 that exceeds serviceable limits; or ii Any crack in the LPC R1 exists.
h Terminating Actions 1 For PW1519G, PW1521G, PW1521G3, PW1521GA, PW1524G, PW1524G3, PW1525G, and PW1525G3 model turbofan engines, the installation of EEC FADEC
software required by paragraph g4 of this AD terminates the repetitive BSI
requirements of paragraphs g1 and 2 of this AD.

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