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Federal Register / Vol. 86, No. 122 / Tuesday, June 29, 2021 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210515; Project Identifier AD202100191E
RIN 2120AA64

Airworthiness Directives; Pratt &
Whitney Turbofan Engines Federal Aviation Administration FAA, DOT.
ACTION: Notice of proposed rulemaking NPRM.
AGENCY:

The FAA proposes to adopt a new airworthiness directive AD for all Pratt & Whitney PW1500G and PW1900G series turbofan engines with a certain high-pressure turbine HPT 1ststage hub or HPT rotor 1st-stage blade retaining plate installed. This proposed AD was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1ststage blade retaining plate fail to meet the published life-cycle limits for each part. This proposed AD would require removal and replacement of the HPT
1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to reaching certain cycle limits. The FAA is proposing this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by June 29, 2021.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202 4932251.
Mail: U.S. Department of Transportation, Docket Operations, M30, West Building Ground Floor, Room W12140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Pratt & Whitney, 400 Main Street, East Hartford, CT
06118; phone: 800 5650140; fax: 860
5655442; email: help24@pw.utc.com;
website: https fleetcare.pw.utc.com.
You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA
01803. For information on the availability of this material at the FAA, call 781 2387759.

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Examining the AD Docket You may examine the AD docket at https www.regulations.gov by searching for and locating Docket No.
FAA20210515; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, any comments received, and other information. The street address for Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Mark Taylor, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
781 2387229; fax: 781 2387199;
email: Mark.Taylor@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include Docket No.
FAA20210515; Project Identifier AD
202100191E at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments.
Except for Confidential Business Information CBI as described in the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to https
www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM.
Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner.
Under the Freedom of Information Act FOIA 5 U.S.C. 552, CBI is exempt from public disclosure. If your comments responsive to this NPRM
contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI
as PROPIN. The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this
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NPRM. Submissions containing CBI
should be sent to Mark Taylor, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA
01803. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking.
Background The FAA received a report from the manufacturer, who determined after recalculating life limits using a thermal match model and other life-calculation methodology updates, the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate failed to meet the published life-cycle limits for each part.
This condition, if not addressed, could result in the release of the HPT 1st-stage hub or HPT rotor 1st-stage blade retaining plate, damage to the engine, and damage to the aircraft.
FAAs Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design.
Related Service Information The FAA reviewed Pratt & Whitney Service Bulletin SB PW1000GA72
00011500B930AD, Issue No. 001, dated April 26, 2021, and Pratt &
Whitney SB PW1000GA72000168
00A930AD, Issue No. 001, dated April 26, 2021. These SBs describe procedures for removing and replacing the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate.
Proposed AD Requirements in This NPRM
This proposed AD would require removal and replacement of the HPT
1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to reaching certain cycle limits.
Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 88
engines installed on airplanes of U.S.
registry. The FAA estimates that in most cases the affected HPT 1st-stage hub and the affected HPT 1st-stage blade retaining plate will both be replaced during the same disassembly of the engine. This cost estimate therefore reflects the cost of replacing both parts during the same engine disassembly.
The FAA estimates the following costs to comply with this proposed AD:

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