31092 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 

(g)(1) through (4) of this AD, except not 

paragraphs (g)(4)(i), (g)(4)(ii)(A) through (C), 

or (g)(4)(iii) of this AD if you completed the 

Accomplishment Instructions, Part I of Bell 

ASB 505–19–12, 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 (j)(1) 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. 

(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 817–222– 

5110; email matthew.fuller@faa.gov. 

(2) Bell Alert Service Bulletin 505–19–12, 

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 (k)(3) and (4) of this AD. 

(3) The subject of this AD is addressed in 

Transport Canada AD CF–2019–35, dated 

October 2, 2019. You may view the Transport 

Canada AD at https://www.regulations.gov in 

Docket No. FAA–2021–0185. 

(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. 552(a) 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 505–19–12, 

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 l’Avenir, Mirabel, 

Quebec J7J1R4; telephone 450–437–2862 or 

800–363–8023; fax 450–433–0272; or at 

https://www.bellcustomer.com. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. 

(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. 2021–12229 Filed 6–10–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0445; Project 

Identifier AD–2021–00268–E; Amendment 

39–21588; AD 2021–12–01] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Alliance Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–25– 

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 2019–25–13 

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. 

DATES: 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. 

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) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 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) 565–0140; 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. FAA–2021– 

0445. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0445; 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) 238–7236; fax: (781) 238– 

7199; email: Stephen.L.Elwin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued AD 2019–25–13, 

Amendment 39–21011 (84 FR 71770, 

December 30, 2019), (AD 2019–25–13), 

for all EA GP7270 and GP7277 model 

turbofan engines with a certain LPC 1ststage fan blade installed. AD 2019–25– 

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 2019–25–13 

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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Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations 31093 

manufacturer determined the fan blades 

experienced cracks that originated on 

the internal surface of the convex airfoil 

and propagated to the point of failure. 

The cracks originated in a microtexture 

area that can result in a low-cycle 

fatigue debit that may allow a crack to 

initiate and propagate to failure. The 

FAA issued AD 2019–25–13 to prevent 

failure of the fan blade. 

Actions Since AD 2019–25–13 Was 

Issued 

Since the FAA issued AD 2019–25– 

13, the manufacturer performed analysis 

of a fractured LPC 1st-stage fan blade 

and determined the fracture resulted 

from a fatigue crack. The manufacturer 

determined that repetitive ultrasonic 

inspection for cracks on the LPC 1ststage fan blade convex airfoil is 

necessary to decrease the risk of fracture 

event. As a result of this analysis, the 

manufacturer published EA Alert 

Service Bulletin (SB) EAGP7–A72–444, 

dated November 18, 2020. This service 

information specifies lower initial 

inspection thresholds for performing 

ultrasonic inspections of affected LPC 

1st-stage fan blades and contains 

procedures for performing repetitive 

ultrasonic inspections of affected LPC 

1st-stage fan blades. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

FAA’s Determination 

The FAA is issuing this AD because 

the agency determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed EA Alert SB 

EAGP7–A72–444, dated November 18, 

2020. The Alert SB describes the 

inspection thresholds and procedures 

for performing an ultrasonic inspection 

of the LPC 1st-stage fan blades. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in ADDRESSES. 

AD Requirements 

This AD requires initial and repetitive 

ultrasonic inspections of the affected 

LPC 1st-stage fan blades and 

replacement of any LPC 1st-stage fan 

blade that fails the inspection. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) authorizes agencies 

to dispense with notice and comment 

procedures for rules when the agency, 

for ‘‘good cause,’’ finds that those 

procedures are ‘‘impracticable, 

unnecessary, or contrary to the public 

interest.’’ Under this section, an agency, 

upon finding good cause, may issue a 

final rule without providing notice and 

seeking comment prior to issuance. 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

The FAA has found the risk to the 

flying public justifies waiving notice 

and comment prior to adoption of this 

rule because no domestic operators use 

this product. It is unlikely that the FAA 

will receive any adverse comments or 

useful information about this AD from 

any U.S. operator. Accordingly, notice 

and opportunity for prior public 

comment are unnecessary, pursuant to 5 

U.S.C. 553(b)(3)(B). In addition, for the 

foregoing reason, the FAA finds that 

good cause exists pursuant to 5 U.S.C. 

553(d) for making this amendment 

effective in less than 30 days. 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2021–0445 

and Project Identifier AD–2021–00268– 

E’’ 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 final rule 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 final rule. 

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 AD 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 AD, 

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 AD. Submissions containing CBI 

should be sent to Stephen Elwin, 

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. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (RFA) do not apply when 

an agency finds good cause pursuant to 

5 U.S.C. 553 to adopt a rule without 

prior notice and comment. Because FAA 

has determined that it has good cause to 

adopt this rule without prior notice and 

comment, RFA analysis is not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 0 engines installed on airplanes 

of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Perform ultrasonic inspection for one set of 1st—stage 

LPC blades.

8 work-hours × $85 per hour = $680 $0 $680 $0 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the inspection. The agency has 

no way of determining the number of 


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31094 Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations 

aircraft that might need these 

replacements. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace 1st-stage LPC fan blade ................................ 4 work-hours × $85 per hour = $340 ........................... $190,000 $190,340 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s 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 Agency’s 

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 

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, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

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 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

2019–25–13, Amendment 39–21011 (84 

FR 71770, December 30, 2019); and 

■ b. Adding the following new 

airworthiness directive: 

2021–12–01 Engine Alliance: Amendment 

39–21588; Docket No. FAA–2021–0445; 

Project Identifier AD–2021–00268–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 28, 2021. 

(b) Affected ADs 

This AD replaces AD 2019–25–13, 

Amendment 39–21011 (84 FR 71770, 

December 30, 2019). 

(c) Applicability 

This AD applies to Engine Alliance (EA) 

GP7270 and GP7277 model turbofan engines 

with low-pressure compressor (LPC) 1st-stage 

fan blades, part number (P/N) 5700531, 

5702931, 5702931CL1, or 5702931CL2, 

installed. 

(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 

in-flight shutdown of an engine due to the 

fracture of multiple LPC 1st-stage fan blades. 

The FAA is issuing this AD to prevent failure 

of the LPC 1st-stage fan blades. The unsafe 

condition, if not addressed, could result in 

uncontained fan blade release, damage to the 

engine, and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within the compliance time specified 

in Table 1 to paragraph (g)(1) of this AD, 

perform an ultrasonic inspection of the LPC 

1st-stage fan blades using the 

Accomplishment Instructions, ‘‘For Fan 

Blades Installed In An Engine,’’ paragraph 1, 

or ‘‘For Fan Blades Not Installed In An 

Engine,’’ paragraph 1, as applicable, of EA 

Alert Service Bulletin (SB) EAGP7–A72–444, 

dated November 18, 2020. 


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Table 1 to Paragraph (g)(l) 

Fan Blade Flie:ht Cvcles Compliance Time 

Fewer than 2,250 flight cycles since new Before exceeding 2,500 flight CSN. 

(CSN) on the effective date of this AD. 

2,250 flight CSN or greater as of the Before exceeding 250 flight cycles from 

effective date of this AD, but fewer than the effective date of this AD. 

3,250 CSN on January 14, 2020 (the 

effective date of AD 2019-25-13). 

3,250 flight CSN or greater on January Within 250 flight cycles since January 14, 

14, 2020. 2020 or before further flight, whichever 

occurs later. 
Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations 31095 

(2) Thereafter, at intervals not to exceed 

800 flight cycles since last inspection, 

perform an ultrasonic inspection of the LPC 

1st-stage fan blades using the 

Accomplishment Instructions, ‘‘For Fan 

Blades Installed In An Engine,’’ paragraph 1, 

or ‘‘For Fan Blades Not Installed In An 

Engine,’’ paragraph 1, as applicable, of EA 

Alert SB EAGP7–A72–444, dated November 

18, 2020. 

(3) If an ultrasonic inspection of an LPC 

1st-stage fan blade results in a rejectable 

ultrasonic indication, remove the LPC 1ststage fan blade from service and replace with 

a part eligible for installation before further 

flight. 

Note 1 to paragraph (g)(3): Guidance on 

determining a rejectable ultrasonic indication 

can be found in GP7000 1st Stage LPC Rotor 

(Fan) Blade Assembly Airfoil Ultrasonic 

Inspection for Cracks (Fan Blade Installed or 

Uninstalled), NDIP–1205, Revision C, dated 

September 15, 2020. 

(h) Credit for Previous Actions 

You may take credit for the ultrasonic 

inspection required by paragraph (g)(1) of 

this AD if you performed the inspection 

before the effective date of this AD using 

GP7000 1st Stage LPC Rotor (Fan) Blade 

Assembly Airfoil Ultrasonic Inspection for 

Cracks (Fan Blade installed or uninstalled), 

NDIP–1205, Revision B, dated September 27, 

2019, or an earlier version. 

(i) No Reporting Requirement 

The reporting requirements contained 

within NDIP–1205 are not required by this 

AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 certification office, 

send it to the attention of the person 

identified in Related Information. 

Information may be emailed to: ANE-ADAMOC@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. 

(k) Related Information 

For more information about this AD, 

contact Stephen Elwin, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7236; fax: (781) 238–7199; email: 

Stephen.L.Elwin@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) 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) Engine Alliance (EA) Alert Service 

Bulletin EAGP7–A72–444, dated November 

18, 2020. 

(ii) [Reserved] 

(3) For EA service information identified in 

this AD, contact Engine Alliance, 411 Silver 

Lane, East Hartford, CT 06118; phone: (800) 

565–0140; email: help24@pw.utc.com; 

website: www.engineallianceportal.com. 

(4) You may view this service information 

at 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. 

(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 25, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12302 Filed 6–10–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0140; Project 

Identifier MCAI–2020–01531–T; Amendment 

39–21582; AD 2021–11–20] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus SAS Model A330–200, A330– 

300, A340–200, A340–300, A340–500, 

and A340–600 series airplanes. This AD 

was prompted by reports that, for 

certain lower deck mobile crew rest 

(LDMCR) units, the connection of a 

certain halon outlet tube to the outlet of 

a certain fire extinguisher bottle may be 

incorrect. This AD requires replacing 

each affected halon outlet tube with a 

flexible hose, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective July 16, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 16, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

internet www.easa.europa.eu. You may 

find this IBR material on the EASA 

website at https://ad.easa.europa.eu. 

You may view this IBR material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0140. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0140; 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 address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3229; email 

vladimir.ulyanov@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2020–0255, 

dated November 13, 2020 (EASA AD 

2020–0255) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for certain Airbus SAS 

Model A330–201, –202, –203, –223, 

–243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes; 

and Model A340–211, –212, –213, –311, 

–312, –313, –541, –542, –642, and –643 

airplanes. Model A340–542 and A340– 

643 airplanes are not certificated by the 

FAA and are not included on the U.S. 

type certificate data sheet; this AD 

therefore does not include those 

airplanes in the applicability. 


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