Federal Register / Vol. 87, No. 77 / Thursday, April 21, 2022 / Rules and Regulations 23755 

specified in paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Special 

Attention Requirements Bulletin 757–25– 

0315 RB, Revision 1, dated May 20, 2020. 

(j) Parts Installation Limitation 

As of the applicable time specified in 

paragraph (j)(1) or (2) of this AD, no person 

may install on any airplane any PSU, life vest 

panel, or video panel without an updated 

lanyard assembly installed. 

(1) For airplanes that have PSUs, life vest 

panels, or video panels without the updated 

lanyard assemblies installed as of the 

effective date of this AD: After modification 

of the airplane as required by paragraph (g) 

of this AD. 

(2) For airplanes that do not have PSUs, 

life vest panels, or video panels without the 

updated lanyard assemblies installed as of 

the effective date of this AD: As of the 

effective date of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO 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 paragraph (l) of this 

AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by The Boeing Company 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Seattle ACO Branch, FAA, to make 

those findings. To be approved, the repair 

method, modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(l) Related Information 

For more information about this AD, 

contact Tony Koung, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Section, FAA, Seattle ACO Branch, 2200 

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

phone and fax: 206–231–3985; email: 

tony.koung@faa.gov. 

(m) 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) Boeing Special Attention Requirements 

Bulletin 757–25–0315 RB, Revision 2, dated 

March 17, 2021. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

phone: 562–797–1717; internet: https://

www.myboeingfleet.com. 

(4) You may view this service information 

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. 

(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, 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on March 17, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–08493 Filed 4–20–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0091; Project 

Identifier MCAI–2021–01123–T; Amendment 

39–22011; AD 2022–08–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) 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, 

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

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

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

This AD was prompted by reports that, 

during inspections accomplished as 

specified in certain airworthiness 

limitation items (ALIs), cracks were 

detected in the double joggle areas at 

frame (FR) 16 and FR20 in the nose 

forward fuselage. This AD requires 

repetitive special detailed inspections of 

certain areas and applicable oncondition actions, 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 May 26, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 26, 2022. 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

AD, contact EASA, Konrad-AdenauerUfer 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 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 at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0091. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0091; 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, the mandatory continuing 

airworthiness information (MCAI), 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, FAA, 

International Validation Branch, 2200 

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

phone 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 2021–0227, 

dated October 11, 2021 (EASA AD 

2021–0227) (also referred to as 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, 

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

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

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

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 


jspears on DSK121TN23PROD with RULES1
23756 Federal Register / Vol. 87, No. 77 / Thursday, April 21, 2022 / Rules and Regulations 

part 39 by adding an AD that would 

apply 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. The NPRM published in the 

Federal Register on February 8, 2022 

(87 FR 7062). The NPRM was prompted 

by reports that during inspections 

accomplished in accordance with 

certain ALIs, cracks were detected in 

double joggle areas at FR16 and FR20, 

right hand and left hand sides. The 

NPRM proposed to require repetitive 

special detailed inspections of certain 

areas and applicable on-condition 

actions, as specified in EASA AD 2021– 

0227. The NPRM also proposed an 

optional modification of the double 

joggle area, which terminates the 

repetitive inspections. 

The FAA is issuing this AD to address 

cracks in the double joggle areas at FR16 

and FR20 in the nose forward fuselage, 

which, if not detected and corrected, 

could reduce the structural integrity of 

the fuselage. See the MCAI for 

additional background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from the 

Air Line Pilots Association, 

International (ALPA) who supported the 

NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed. Except for minor 

editorial changes, this AD is adopted as 

proposed in the NPRM. None of the 

changes will increase the economic 

burden on any operator. Accordingly, 

the FAA is issuing this AD to address 

the unsafe condition on these products. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2021–0227 specifies 

procedures for repetitive special 

detailed inspections (rototest 

inspections) of double joggle areas at 

FR16 and FR20, right hand and left 

hand sides for cracking, applicable oncondition actions (repair) and an 

optional modification of the double 

joggle area, which terminates the 

repetitive inspections. The modification 

includes a rotating probe inspection of 

certain fastener holes for cracks, a check 

of the fastener holes for a minimum 

diameter, and applicable on-condition 

actions (repair and oversizing holes). 

This material is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

would affect 1,549 airplanes of U.S. 

registry. The FAA estimates the 

following costs to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Up to 55 work-hours × $85 per hour = $4,675 ..................................................... $0 ........................ Up to $4,675 .......... Up to $7,241,575. 

ESTIMATED COSTS FOR OPTIONAL ACTIONS

Labor cost Parts cost Cost per 

product 

60 work-hours × $85 per hour = $5,100 ................................................................................................................. $1,624 $6,724 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition repairs specified in 

this 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 

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, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will 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 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 adding 

the following new airworthiness 

directive: 


jspears on DSK121TN23PROD with RULES1
Federal Register / Vol. 87, No. 77 / Thursday, April 21, 2022 / Rules and Regulations 23757 

2022–08–08 Airbus SAS: Amendment 39– 

22011; Docket No. FAA–2022–0091; 

Project Identifier MCAI–2021–01123–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 26, 2022. 

(b) Affected ADs 

This AD affects AD 2020–20–05, 

Amendment 39–21261 (85 FR 65197, October 

15, 2020) (AD 2020–20–05). 

(c) Applicability 

This AD applies to Airbus SAS Model 

airplanes specified in paragraphs (c)(1) 

through (4) of this AD, certificated in any 

category, as identified in European Union 

Aviation Safety Agency (EASA) AD 2021– 

0227, dated October 11, 2021 (EASA AD 

2021–0227). 

(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 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports that, 

during inspections accomplished as specified 

in certain airworthiness limitation items 

(ALIs), cracks were detected in the double 

joggle areas at frame (FR) 16 and FR20 in the 

nose forward fuselage. The FAA is issuing 

this AD to address cracks in these areas, 

which, if not detected and corrected, could 

reduce the structural integrity of the fuselage. 

(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 2021–0227. 

(h) Exceptions to EASA AD 2021–0227 

(1) Where EASA AD 2021–0227 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

2021–0227 does not apply to this AD. 

(3) Where paragraph (2) of EASA AD 2021– 

0227 specifies to ‘‘contact Airbus for 

approved repair instructions and, within the 

compliance time specified therein, 

accomplish those instructions accordingly’’ if 

any cracks are detected, for this AD if any 

cracking is detected, the cracking must be 

repaired before further flight using a method 

approved by Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(4) Where paragraphs (3) and (4) of EASA 

AD 2021–0227 specify ‘‘Airbus approved 

repair instructions,’’ or ‘‘post-repair 

inspection instructions approved by Airbus,’’ 

for this AD, to be acceptable for credit, the 

repair instructions must be approved by 

Airbus SAS’s EASA DOA. If approved by the 

DOA, the approval must include the DOA 

authorized signature. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0227 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Terminating Action for Certain 

Requirements in AD 2020–20–05 

Accomplishing the initial inspections 

required by this AD terminates ALI Tasks 

531153–02–1, 531153–02–2, 531155–02–1 

and 531155–02–2, as required by paragraph 

(i) of AD 2020–20–05 only for the airplanes 

identified in paragraph (c) of this AD. 

(k) Additional 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 (l) of this AD. 

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

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(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 DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraphs (h)(3), (i), and 

(k)(2) of this AD, if any service information 

contains procedures or tests that are 

identified as RC, those 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. 

(l) Related Information 

For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, Large Aircraft Section, FAA, 

International Validation Branch, 2200 South 

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

206–231–3229; email vladimir.ulyanov@

faa.gov. 

(m) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2021–0227, dated October 11, 

2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0227, 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. 

(4) 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. 

(5) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on April 4, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–08494 Filed 4–20–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 31426; Amdt. No. 565] 

IFR Altitudes; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts 

miscellaneous amendments to the 

required IFR (instrument flight rules) 

altitudes and changeover points for 

certain Federal airways, jet routes, or 

direct routes for which a minimum or 

maximum en route authorized IFR 

altitude is prescribed. This regulatory 

action is needed because of changes 

occurring in the National Airspace 

System. These changes are designed to 

provide for the safe and efficient use of 


jspears on DSK121TN23PROD with RULES1