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Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations
iii If there is a gap that is more than 0.020
inch 0.508 mm, before further flight, remove the nut, washer, and bolt from service and repair or replace the truss assembly clevis lower lug in accordance with FAA-approved procedures.
h Credit for Previous Actions You may take credit for the first instance of the actions that are required by paragraphs g1 through 4 of this AD, except not paragraphs g4i, g4iiA through C, or g4iii of this AD if you completed the Accomplishment Instructions, Part I of Bell ASB 5051912, dated June 27, 2019, before the effective date of this AD.
i Alternative Methods of Compliance AMOCs 1 The Manager, International Validation 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 International Validation Branch, send it to the attention of the person identified in paragraph j1 of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
2 Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/
certificate holding district office.

jbell on DSKJLSW7X2PROD with RULES

j Related Information 1 For more information about this AD, contact Matt Fuller, AD Program Manager, General Aviation & Rotorcraft Unit, Airworthiness Products Section, Operational Safety Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817222
5110; email matthew.fuller@faa.gov.
2 Bell Alert Service Bulletin 5051912, dated June 27, 2019, which is not incorporated by reference, contains additional information about the subject of this AD. This service information is available at the contact information specified in paragraphs k3 and 4 of this AD.
3 The subject of this AD is addressed in Transport Canada AD CF201935, dated October 2, 2019. You may view the Transport Canada AD at https www.regulations.gov in Docket No. FAA20210185.
k Material Incorporated by Reference 1 The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552a and 1 CFR
part 51.
2 You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.
i Bell Alert Service Bulletin 5051912, Revision A, dated July 11, 2019.
ii Reserved 3 For service information identified in this AD, contact Bell Textron Canada Limited, 12,800 Rue de lAvenir, Mirabel, Quebec J7J1R4; telephone 4504372862 or 8003638023; fax 4504330272; or at https www.bellcustomer.com.

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4 You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 8172225110.
5 You may view this service information that is incorporated by reference at the National Archives and Records Administration NARA. For information on the availability of this material at NARA, email: fedreg.legal@nara.gov, or go to:
https www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on May 20, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202112229 Filed 61021; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210445; Project Identifier AD202100268E; Amendment 3921588; AD 20211201
RIN 2120AA64

Airworthiness Directives; Engine Alliance Turbofan Engines
Examining the AD Docket
Federal Aviation Administration FAA, DOT.
ACTION: Final rule; request for comments.
AGENCY:

The FAA is superseding Airworthiness Directive AD 201925
13, which applied to all Engine Alliance EA GP7270 and GP7277 model turbofan engines with a certain lowpressure compressor LPC 1st-stage fan blade installed. AD 20192513
required an ultrasonic inspection of the affected LPC 1st-stage fan blades and replacement of any affected LPC 1ststage fan blade that fails the inspection.
This AD lowers the initial inspection threshold and requires repetitive ultrasonic inspections on affected LPC
1st-stage fan blades. This AD was prompted by a report of an in-flight shutdown IFSD of an engine due to the fracture of multiple LPC 1st-stage fan blades. The FAA is issuing this AD to address the unsafe condition on these products.

SUMMARY:

This AD is effective June 28, 2021.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD
as of June 28, 2021.
The FAA must receive any comments on this AD by July 26, 2021.

DATES:

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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, M
30, 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 final rule, contact Engine Alliance, 411 Silver Lane, East Hartford, CT
06118; phone: 800 5650140; email:
help24@pw.utc.com; website:
www.engineallianceportal.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 781 238
7759. It is also available at https
www.regulations.gov by searching for and locating Docket No. FAA2021
0445.

ADDRESSES:

You may examine the AD docket at https www.regulations.gov by searching for and locating Docket No.
FAA20210445; 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 final rule, any comments received, and other information. The street address for Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Stephen Elwin, Aviation Safety Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: 781 2387236; fax: 781 238
7199; email: Stephen.L.Elwin@faa.gov.
SUPPLEMENTARY INFORMATION:
Background The FAA issued AD 20192513, Amendment 3921011 84 FR 71770, December 30, 2019, AD 20192513, for all EA GP7270 and GP7277 model turbofan engines with a certain LPC 1ststage fan blade installed. AD 201925
13 required an ultrasonic inspection of the affected LPC 1st-stage fan blades and replacement of any affected fan blades that fail the inspection. AD 20192513
resulted from a report of an IFSD of an engine due to the fracture of multiple LPC 1st-stage fan blades. After an analysis of these fractures, the
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