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Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules
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 that the 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.
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:
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 20110702, Amendment 3916639
76 FR 16526, March 24, 2011; and b. Adding the following new airworthiness directive:

lotter on DSK11XQN23PROD with PROPOSALS1

Pratt & Whitney: Docket No. FAA2021
0661; Project Identifier AD202001349
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a Comments Due Date The FAA must receive comments on this airworthiness directive AD action by October 12, 2021.
b Affected ADs This AD replaces AD 20110702, Amendment 3916639 76 FR 16526, March 24, 2011.
c Applicability This AD applies to Pratt & Whitney P&W
JT8D209, JT8D217, JT8D217A, JT8D
217C, and JT8D219 model turbofan engines.
d Subject Joint Aircraft System Component JASC
Code 7230, Turbine Engine Compressor Section.
e Unsafe Condition This AD was prompted by a report of an MD82 airplane, equipped with a JT8D217C
model turbofan engine, experiencing an engine surge that resulted in the fracture of the low-pressure turbine LPT blade and uncontained release of the LPT blade. Five prior uncontained LPT blade failures were also reported on affected model turbofan engines. The FAA is issuing this AD to prevent LPT blade fracture and uncontained release of the LPT blade. The unsafe condition, if not addressed, could result in uncontained engine debris, 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 JT8D209, JT8D217, and JT8D
217A model turbofan engines, within the compliance times specified in the Accomplishment Instructions, Part 1: JT8D
209, 217, 217A Engines Part 1, paragraph 1.A., of P&W Alert Service Bulletin No. JT8D
A6224, Revision No. 7, dated August 26, 2019 the ASB, perform an initial torque inspection for shroud notch wear of the 3rdstage LPT blades using the procedures in Part 1, paragraph 1, of the ASB.
i Thereafter, within the applicable reinspection interval specified in Table 1
Reinspection Interval for all 3rd Stage Blades, of the ASB, repeat the torque inspection for shroud notch wear required by paragraph g1 of this AD.
ii If the results of the torque inspection required by paragraphs g1 or g1i of this AD meet the criteria for engine removal specified in Table 1Reinspection Interval for all 3rd Stage Blades, of the ASB, perform piece-part inspections in accordance with the Instructions for Continued Airworthiness ICA on all 3rd-stage LPT blades before exceeding 20 hours time-in-service TIS
since the last torque inspection.
2 For JT8D209, JT8D217, and JT8D
217A model turbofan engines, within the compliance times specified in Table A or Table B, of the ASB, as applicable, perform an initial torque inspection for shroud notch wear of the 4th-stage LPT blades using the procedures in Part 1, paragraph 1, of the ASB. Wherever the ASB refers to Revision
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7 Release Date and At SB Release Date, use the effective date of this AD.
i For engines in which the last inspection prior to the effective date of this AD had a torque inspection result of less than 15 LB
IN on any 4th-stage LPT blade, perform piece-part inspections in accordance with the ICA on all 3rd-stage and 4th-stage LPT blades within 20 hours TIS after the effective date of this AD.
ii Thereafter, within the applicable reinspection interval specified in Table 2
Reinspection Interval for all 4th Stage Blades, of the ASB, repeat the torque inspection for shroud notch wear required by paragraph g2 of this AD.
iii If the results of the torque inspection required by paragraphs g2 or g2ii of this AD meet the criteria for engine removal specified in Table 2Reinspection Interval for all 4th Stage Blades, of the ASB, perform piece-part inspections in accordance with the ICA on all 3rd-stage and 4th-stage LPT blades before exceeding 20 hours TIS since the last torque inspection.
3 For JT8D217C and JT8D219 model turbofan engines, within the compliance times specified in Table A or Table B, of the ASB, as applicable, perform an initial torque inspection for shroud notch wear of the 4thstage LPT blades using the procedures in the Accomplishment Instructions, Part 2: JT8D
217C, 219 Engines Part 2, paragraph 1, of the ASB. Wherever the ASB refers to Revision 7 Release Date and At SB
Release Date, use the effective date of this AD.
i For engines in which the last inspection prior to the effective date of this AD had a torque inspection result of less than 15 LB
IN on any 4th-stage LPT blade, perform piece-part inspections in accordance with the ICA on all 3rd-stage and 4th-stage LPT blades within 20 hours TIS after the effective date of this AD.
ii Thereafter, within the reinspection interval specified in Table 3-Reinspection Interval for all 4th Stage Blades, of the ASB, repeat the torque inspection for shroud notch wear required by paragraph g3 of this AD.
iii If the results of the torque inspection required by paragraph g3 and g3ii of this AD meet the criteria for engine removal specified in Table 3Reinspection Interval for all 4th Stage Blades, of the ASB, perform piece-part inspections in accordance with the ICA on all 3rd-stage and 4th-stage LPT blades before exceeding 20 hours TIS since the last torque inspection.
4 At the first engine shop visit after January 1, 2023, or prior to accumulating 5,000 TIS on the 3rd-stage and 4th-stage LPT
blades, whichever occurs later, but not to exceed 6 years after the effective date of the AD, replace the 3rd-stage and 4th-stage LPT
blades with parts eligible for installation.
5 Thereafter, prior to accumulating 5,000
hours TIS on the 3rd-stage and 4th-stage LPT
blades since their last replacement, replace the 3rd-stage and 4th-stage LPT blades with parts eligible for installation.
6 After every replacement of the 3rd-stage or 4th-stage LPT blades, perform initial and repetitive torque inspections of the 3rd-stage or 4th-stage LPT blades using, as applicable, the accomplishment instructions and
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