Federal Register / Vol. 87, No. 78 / Friday, April 22, 2022 / Proposed Rules 24081 

Service Bulletin 429–19–47, dated August 28, 

2019. 

(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 Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Suite 410, Westbury, NY 11590; 

telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

(2) For service information identified in 

this AD, contact Bell Textron Canada 

Limited, 12,800 Rue de l’Avenir, Mirabel, 

Quebec J7J 1R4, Canada; telephone 1–450– 

437–2862 or 1–800–363–8023; fax 1–450– 

433–0272; email productsupport@

bellflight.com; or at https://

www.bellflight.com/support/contact-support. 

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. 

(3) The subject of this AD is addressed in 

Transport Canada AD CF–2021–15, dated 

April 14, 2021. You may view the Transport 

Canada AD on the internet at https://

www.regulations.gov in Docket No. FAA– 

2021–1074. 

Issued on April 15, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–08561 Filed 4–21–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0468; Project 

Identifier MCAI–2021–01243–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2018–13–08 which applies to certain 

Airbus SAS Model A318 series 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–216, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

AD 2018–13–08 requires repetitive 

inspections for cracking of the radius of 

the front spar vertical stringers and the 

horizontal floor beam on frame (FR) 36, 

repetitive inspections for cracking of the 

fastener holes of the front spar vertical 

stringers on FR 36, and repair if 

necessary, and, for certain airplanes, a 

potential terminating action 

modification of the center wing box 

area. Since the FAA issued AD 2018– 

13–08, Airbus has determined that 

additional airplanes are subject to the 

unsafe condition. This proposed AD 

would revise the applicability by adding 

airplanes and retain the requirements of 

AD 2018–13–08, as specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which is proposed for 

incorporation by reference. 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 6, 2022. 

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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For material that will be 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–2022– 

0468. 

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–2022– 

0468; 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. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

phone 206–231–3229; email 

vladimir.ulyanov@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. 

FAA–2022–0468; Project Identifier 

MCAI–2021–01243–T’’ 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 the 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:// 


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24082 Federal Register / Vol. 87, No. 78 / Friday, April 22, 2022 / Proposed Rules 

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this proposed 

AD. 

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 

NPRM. Submissions containing CBI 

should be sent to Vladimir Ulyanov, 

Aerospace Engineer, Large Aircraft 

Section, International Validation 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; phone 206–231– 

3229; email vladimir.ulyanov@faa.gov. 

Any commentary that the FAA receives 

which is not specifically designated as 

CBI will be placed in the public docket 

for this rulemaking. 

Discussion 

The FAA issued AD 2018–13–08, 

Amendment 39–19320 (83 FR 33809, 

July 18, 2018) (AD 2018–13–08) which 

applies to certain Airbus SAS Model 

A318 series airplanes; Model A319–111, 

–112, –113, –114, –115, –131, –132, and

–133 airplanes; Model A320–211, –212,

–214, –216, –231, –232, and –233

airplanes; and Model A321–111, –112,

–131, –211, –212, –213, –231, and –232

airplanes. AD 2018–13–08 requires

repetitive inspections for cracking of the

radius of the front spar vertical stringers

and the horizontal floor beam on FR 36,

repetitive inspections for cracking of the

fastener holes of the front spar vertical

stringers on FR 36, and repair if

necessary, and, for certain airplanes, a

potential terminating action

modification of the center wing box

area. The FAA issued AD 2018–13–08 to

address fatigue cracking of the front spar

vertical stringers on the wings, which

could result in the reduced structural

integrity of the airplane.

Actions Since AD 2018–13–08 Was 

Issued 

Since the FAA issued AD 2018–13– 

08, Airbus has determined that Model 

A321 airplanes that have incorporated 

modification 160021 (structural 

reinforcement for Airbus SAS Model 

A321 airplanes sharklet installation) are 

also subject to the identified unsafe 

condition. In addition, Airbus 

determined that, for airplanes in 

configuration 5, 6, or 7, an optional 

modification of the center wing box 

after accumulating a certain number of 

total flight cycles and total flight hours 

terminates the repetitive inspections. 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0241, 

dated November 8, 2021 (EASA AD 

2021–0241) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for certain Airbus SAS 

Model A318 series airplanes; Model 

A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model

A320–211, –212, –214, –215, –216,

–231, –232, and –233 airplanes; and

Model A321–111, –112, –131, –211,

–212, –213, –231, and –232 airplanes.

EASA AD 2021–0241 supersedes EASA

AD 2017–0099, dated June 8, 2017

(which corresponds to FAA AD 2018–

13–08). Model A320–215 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.

This proposed AD was prompted by 

a report that, during a center fuselage 

certification full-scale fatigue test, 

cracks were found on the front spar 

vertical stringer at a certain frame. This 

proposed AD was also prompted by a 

determination that Model A321 

airplanes that have incorporated 

modification 160021 are also subject to 

the unsafe condition. The FAA is 

proposing this AD to address fatigue 

cracking of the front spar vertical 

stringers on the wings, which, if not 

corrected, could result in the reduced 

structural integrity of the airplane. See 

the MCAI for additional background 

information. 

Model A320–216 Airplanes 

The Airbus SAS Model A320–216 was 

U.S. type certificated on December 19, 

2016. Before that date, any EASA ADs 

that affected Model A320–216 airplanes 

were included in the U.S. type 

certificate as part of the Required 

Airworthiness Actions List (RAAL). One 

or more Model A320–216 airplanes have 

subsequently been placed on the U.S. 

Register, and will now be included in 

FAA AD actions. For Model A320–216 

airplanes, the requirements that 

correspond to AD 2018–13–08 were 

mandated by the MCAI via the RAAL. 

Although that RAAL requirement is still 

in effect, for continuity and clarity the 

FAA has identified Model A320–216 

airplanes in paragraph (c) of this 

proposed AD; the MCAI that is specified 

in paragraph (g) in this proposed AD 

includes retained requirements, which 

would therefore apply to those 

airplanes. 

Explanation of Retained Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2018–13–08, this proposed AD would 

retain all of the requirements of AD 

2018–13–08. Those requirements are 

referenced in EASA AD 2021–0241, 

which, in turn, is referenced in 

paragraph (g) of this proposed AD. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2021–0241 describes 

procedures for repetitive special 

detailed inspections for cracking of the 

radius of the front spar vertical 

stringers, horizontal floor beam radius 

and fastener holes of the front spear 

vertical stringers on frame 36. EASA AD 

2021–0241 further describes procedures 

for repetitive high frequency eddy 

current (HFEC) for cracking of the 

horizontal floor beam, repetitive HFEC 

inspections for cracking of the fastener 

holes of the front spar vertical stringers 

on FR 36, repetitive rototest inspections 

of the fastener holes of the spar vertical 

stringers, and repair. EASA AD 2021– 

0241 also describes procedures for the 

modification of the center wing box 

area. The modification is required for 

airplanes in configuration 1, 2 or 3; and 

for airplanes in configuration 5, 6, or 7, 

the modification is optional and is a 

terminating action for the repetitive 

inspections when done within a 

specified time frame. The modification 

includes related investigative and 

corrective actions. Related investigative 

actions include an HFEC inspection on 

the radius of the rib flanges, a rototest 

inspection of the fastener holes, detailed 

and HFEC inspections for cracking on 

the cut edges, detailed and rototest 

inspections on all open fastener holes, 

and an inspection to determine if 

secondary structure brackets are 

installed. Corrective actions include 

reworking the secondary structure 

bracket and repair. This material is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 


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Federal Register / Vol. 87, No. 78 / Friday, April 22, 2022 / Proposed Rules 24083 

or by the means identified in the 

ADDRESSES section. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the State 

of Design Authority, the FAA has been 

notified of the unsafe condition 

described in the MCAI referenced 

above. The FAA is proposing this AD 

because the FAA evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

EASA AD 2021–0241 described 

previously, as incorporated by 

reference, except for any differences 

identified as exceptions in the 

regulatory text of this AD. 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA developed a process to 

use some civil aviation authority (CAA) 

ADs as the primary source of 

information for compliance with 

requirements for corresponding FAA 

ADs. The FAA has been coordinating 

this process with manufacturers and 

CAAs. As a result, the FAA proposes to 

incorporate EASA AD 2021–0241 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2021–0241 

in its entirety through that 

incorporation, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

Using common terms that are the same 

as the heading of a particular section in 

EASA AD 2021–0241 does not mean 

that operators need comply only with 

that section. For example, where the AD 

requirement refers to ‘‘all required 

actions and compliance times,’’ 

compliance with this AD requirement is 

not limited to the section titled 

‘‘Required Action(s) and Compliance 

Time(s)’’ in EASA AD 2021–0241. 

Service information required by EASA 

AD2021–0241 for compliance will be 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0468 after the FAA final 

rule is published. 

Costs of Compliance 

The FAA estimates that this proposed 

AD affects 1,549 airplanes of U.S. 

registry. The FAA estimates the 

following costs to comply with this 

proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Retained actions from AD 

2018–03–08.

Up to 273 work-hours × $85 per hour = 

$23,205.

$87,500 ................ Up to $110,705 .... Up to $1,107,050 for certain airplanes.* 

New proposed inspections 25 work-hours × $85 per hour = $2,125 .. $100 ..................... $2,225 .................. $3,446,525. 

New proposed modification 

(5 airplanes).

Up to 403 work-hours × $85 per hour = 

$34,255.

Up to $316,900 .... Up to $351,1555 .. Up to $1,755,775. 

* This estimate is based on the determination in AD 2018–13–08 that only 10 airplanes of U.S. registry needed to accomplish all required actions, including the modification; other airplanes were only required to accomplish the terminating actions. 

ESTIMATED COSTS FOR OPTIONAL ACTIONS

Labor cost Parts cost Cost per 

product 

Up to 409 work-hours × $85 per hour = $34,765 ...................................................................................... Up to $66,050 ...... Up to $100,815. 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions specified in 

this proposed AD. 

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 

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 this 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: 


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24084 Federal Register / Vol. 87, No. 78 / Friday, April 22, 2022 / Proposed Rules 

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 

(AD) 2018–13–08, Amendment 39– 

19320; (83 FR 33809, July 18, 2018); and 

■ b. Adding the following new AD: 

Airbus SAS: Docket No. FAA–2022–0468; 

Project Identifier MCAI–2021–01243–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by June 6, 2022. 

(b) Affected ADs 

This AD replaces AD 2018–13–08, 

Amendment 39–19320 (83 FR 33809, July 18, 

2018) (AD 2018–13–08). 

(c) Applicability 

This AD applies to the Airbus SAS 

airplanes identified in paragraphs (c)(1) 

through (4) of this AD, certificated in any 

category, as identified in European Union 

Aviation Safety Agency (EASA) AD 2021– 

0241, dated November 8, 2021 (EASA AD 

2021–0241). 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a report that, 

during a center fuselage certification fullscale fatigue test, cracks were found on the 

front spar vertical stringer at a certain frame. 

This AD was also prompted by a 

determination that Model A321 airplanes 

that have incorporated modification 160021 

are also subject to the unsafe condition. The 

FAA is issuing this AD to address fatigue 

cracking of the front spar vertical stringers on 

the wings, which, if not corrected, could 

result in the reduced structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2021–0241. 

(h) Exceptions to EASA AD 2021–0241 

(1) Where EASA AD 2021–0241 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The ‘‘Remarks’’ section of EASA AD 

2021–0241 does not apply to this AD. 

(3) Where paragraph (3) of EASA AD 2021– 

0241 specifies actions for airplanes repaired 

‘‘in accordance with instructions approved 

by EASA or approved under Airbus DOA,’’ 

for this AD use ‘‘using a method approved by 

the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature.’’ 

(4) Where paragraph (4) of EASA AD 2021– 

0241 specifies to ‘‘contact Airbus for 

approved corrective action instructions and 

accomplish those instructions accordingly’’ if 

cracks are detected, for this AD if any 

cracking is detected, the cracking must be 

repaired before further flight using a method 

approved by the Manager, Large Aircraft 

Section, International Validation Branch, 

FAA; or EASA; or Airbus SAS’s EASA DOA. 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(5) Where paragraph (8) of EASA AD 2021– 

0241 specifies actions for airplanes inspected 

by additional instructions ‘‘approved before 

the effective date of this AD by Airbus DOA,’’ 

for this AD use ‘‘approved before the 

effective date of this AD by the Manager, 

Large Aircraft Section, International 

Validation Branch, FAA; or EASA; or Airbus 

SAS’s EASA DOA. If approved by the DOA, 

the approval must include the DOAauthorized signature.’’ 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0241 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (k)(2) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(ii) AMOCs approved previously for AD 

2018–13–08 are approved as AMOCs for the 

corresponding provisions of EASA AD 2021– 

0241 that are required by paragraph (g) of this 

AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): For any 

service information referenced in EASA AD 

2021–0241 that contains RC procedures and 

tests: Except as required by paragraph (j)(2) 

of this AD, RC procedures and tests must be 

done to comply with this AD; any procedures 

or tests that are not identified as RC are 

recommended. Those procedures and tests 

that are not identified as RC may be deviated 

from using accepted methods in accordance 

with the operator’s maintenance or 

inspection program without obtaining 

approval of an AMOC, provided the 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

(1) For information about EASA AD 2021– 

0241, 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 EASA AD on the EASA website at 

https://ad.easa.europa.eu. You may view this 

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. This 

material may be found in the AD docket on 

the internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0468. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

phone 206–231–3229; email 

vladimir.ulyanov@faa.gov. 

Issued on April 15, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–08585 Filed 4–21–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 100 

[Docket Number USCG–2022–0141] 

RIN 1625–AA08 

Special Local Regulation; Back River, 

Baltimore County, MD 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Coast Guard is proposing 

to establish temporary special local 


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