Federal Register / Vol. 87, No. 65 / Tuesday, April 5, 2022 / Rules and Regulations 19619 

which could cause the main landing gear 

emergency release cable to malfunction. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 48 months or 8,000 flight hours, 

whichever occurs first, from the effective 

date of this AD: Remove the affected V-band 

coupling and check valve seals, do a visual 

inspection for damage to the coupling covers 

and surrounding area, and replace the 

coupling and seals with a redesigned 

assembly, in accordance with the 

Accomplishment Instructions, paragraph 

3.B., of de Havilland Service Bulletin 84–36– 

06, dated December 15, 2020. 

(1) If any damage to a coupling cover is 

found, replace the coupling cover before 

further flight in accordance with the 

Accomplishment Instructions of de 

Havilland Service Bulletin 84–36–06, dated 

December 15, 2020. 

(2) If any damage to the surrounding area 

is found, before further flight, accomplish 

corrective actions in accordance with the 

procedures specified in paragraph (i)(2) of 

this AD. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a V-band coupling, part 

number (P/N) DSC361–250, or check valve 

seal, P/N MS35769–71, in the center wing 

front spar area of any airplane. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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 

responsible Flight Standards Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300. 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, New York ACO Branch, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or De Havilland Aircraft of Canada 

Limited’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) TCCA AD 

CF–2021–11, dated March 29, 2021, for 

related information. This MCAI may be 

found in the AD docket on the internet at 

https://www.regulations.gov by searching for 

and locating Docket No. FAA–2021–1068. 

(2) For more information about this AD, 

contact Elizabeth Dowling, Aerospace 

Engineer, Mechanical Systems and 

Administrative Services Section, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; email 9-avs-nyaco-cos@

faa.gov. 

(k) 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 this AD specifies otherwise. 

(i) De Havilland Aircraft of Canada Limited 

Service Bulletin 84–36–06, dated December 

15, 2020. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact De Havilland Aircraft of 

Canada Limited, Q-Series Technical Help 

Desk, 123 Garratt Boulevard, Toronto, 

Ontario M3K 1Y5, Canada; telephone 416– 

375–4000; fax 416–375–4539; email thd@

dehavilland.com; internet https://

dehavilland.com. 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. 

(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, 

email fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on March 10, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–07083 Filed 4–4–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1063; Project 

Identifier MCAI–2021–00826–T; Amendment 

39–21987; AD 2022–06–21] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2018–09– 

09, which applied to certain Airbus 

Model A318 and A319 series airplanes; 

all Model A320–211, –212, –214, –216, 

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

Model A321–111, –112, –131, –211, 

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

AD 2018–09–09 required modifying the 

holes of the upper cleat to upper 

stringer attachments at certain areas of 

the left- and right-hand wings. Since the 

FAA issued AD 2018–09–09, additional 

affected configurations were identified 

and, for certain airplanes, it was 

determined that additional modification 

work and revised compliance times are 

necessary. This AD retains the 

requirements of AD 2018–09–09 and 

adds airplanes, requires different 

compliance times for certain airplane 

configurations, and, for certain 

airplanes, requires additional 

modifications or reduces compliance 

times, 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 10, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 10, 2022. 

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 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 


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19620 Federal Register / Vol. 87, No. 65 / Tuesday, April 5, 2022 / Rules and Regulations 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1063. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1063; 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: 

Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, FAA, 

International Validation Branch, 2200 

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

telephone 206–231–3223; email 

sanjay.ralhan@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0167, 

dated July 14, 2021 (EASA AD 2021– 

0167) (also referred to as the MCAI), to 

correct an unsafe condition for certain 

Airbus SAS Model A318–111, –112, 

–121, and –122 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. 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. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2018–09–09, 

Amendment 39–19266 (83 FR 19925, 

May 7, 2018; corrected May 15, 2018 (83 

FR 22354)) (AD 2018–09–09). AD 2018– 

09–09 applied to certain Airbus Model 

A318 and A319 series airplanes; all 

Model A320–211, –212, –214, –216, 

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

Model A321–111, –112, –131, –211, 

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

The NPRM published in the Federal 

Register on December 21, 2021 (86 FR 

72195). The NPRM was prompted by a 

report indicating that additional affected 

configurations were identified to be 

subject to widespread fatigue damage 

and, for certain airplanes, it was 

determined that additional modification 

work (such as, for certain 

configurations, oversizing certain 

additional holes, replacing a certain 

fastener with a corrosion-resistant 

fastener, or cleat refit and sealant 

procedure) or revised compliance times 

are necessary. The NPRM proposed to 

retain the requirements of AD 2018–09– 

09 and add airplanes, require different 

compliance times for certain airplane 

configurations, and, for certain 

airplanes, require additional 

modifications or reduce compliance 

times, as specified in EASA AD 2021– 

0167. 

The FAA is issuing this AD to prevent 

fatigue cracking in the stringer 

attachment holes of the wings, which 

could result in reduced structural 

integrity of the wings. See the MCAI for 

additional background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

two commenters, Air Line Pilots 

Association, International (ALPA), and 

United Airlines, who supported the 

NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 

adopting this AD 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 2021–0167 specifies 

procedures for modifying the stringer 

attachments at rib 2 through rib 7 of the 

left- and right-hand wings. The 

modification includes oversizing the 

holes, doing an eddy current inspection 

of the affected holes for damage, and 

repairing damage. EASA AD 2021–0167 

also specifies additional work for 

airplanes on which the modification 

actions were accomplished using certain 

service information. 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 

affects 1,446 airplanes of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Retained actions from AD 2018–09–09 125 work-hours × $85 per hour = $10,625 $26,260 $36,885 $41,901,360 (1,136 airplanes). 

New actions ........................................... 125 work-hours × $85 per hour = $10,625 1,520 12,145 $17,561,670. 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions or the 

additional work for certain previously 

modified airplanes, as 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. 


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Federal Register / Vol. 87, No. 65 / Tuesday, April 5, 2022 / Rules and Regulations 19621 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2018–09–09, Amendment 39– 

19266 (83 FR 19925, May 7, 2018; 

corrected May 15, 2018 (83 FR 22354)); 

and 

■ b. Adding the following new AD: 

2022–06–21 Airbus SAS: Amendment 39– 

21987; Docket No. FAA–2021–1063; 

Project Identifier MCAI–2021–00826–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 10, 2022. 

(b) Affected ADs 

This AD replaces AD 2018–09–09, 

Amendment 39–19266 (83 FR 19925, May 7, 

2018; corrected May 15, 2018 (83 FR 22354)). 

(c) Applicability 

This AD applies to 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 2021–0167, dated July 

14, 2021 (EASA AD 2021–0167). 

(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 

additional affected configurations were 

identified to be subject to widespread fatigue 

damage at certain stringer attachments and, 

for certain airplanes, it was determined that 

additional modification work is necessary. 

The FAA is issuing this AD to prevent fatigue 

cracking in the stringer attachment holes of 

the wings, which could result in reduced 

structural integrity of the wings. 

(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 2021–0167. 

(h) Exceptions to EASA AD 2021–0167 

(1) Where EASA AD 2021–0167 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

2021–0167 does not apply to this AD. 

(i) 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 (j) 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 Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i)(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. 

(j) Related Information 

For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, FAA, International 

Validation Branch, 2200 South 216th St., Des 

Moines, WA 98198; telephone 206–231– 

3223; email sanjay.ralhan@faa.gov. 

(k) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2021–0167, dated July 14, 2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0167, 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 March 10, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–07085 Filed 4–4–22; 8:45 am] 

BILLING CODE 4910–13–P 


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