Federal Register / Vol. 88, No. 180 / Tuesday, September 19, 2023 / Rules and Regulations 64365 

Benjamin W. McDonough, 

Senior Deputy Comptroller and Chief 

Counsel. 

[FR Doc. 2023–20187 Filed 9–18–23; 8:45 am] 

BILLING CODE 4810–33–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1221; Project 

Identifier MCAI–2023–00070–T; Amendment 

39–22543; AD 2023–18–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–06– 

10, which applied 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 

2020–06–10 required repetitive 

inspections for cracking of the vertical 

stiffeners of the left- and right-hand 

sides of the window frames and 

corrective actions if necessary. Since the 

FAA issued AD 2020–06–10, it was 

determined that certain compliance 

times need to be reduced. This AD 


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64366 Federal Register / Vol. 88, No. 180 / Tuesday, September 19, 2023 / Rules and Regulations 

retains the requirements of AD 2020– 

06–10, with amended compliance times, 

as specified in a European Union 

Aviation Safety Agency (EASA) AD, 

which is proposed for incorporation by 

reference (IBR). The FAA is issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective October 24, 

2023. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 24, 2023. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1221; 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. 

Material Incorporated by Reference: 

• For the EASA AD incorporated by 

reference in this AD, contact EASA, 

Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 

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

website easa.europa.eu. You may find 

this material on the EASA website at 

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 

regulations.gov under Docket No. FAA– 

2023–1221. 

FOR FURTHER INFORMATION CONTACT: 

Timothy Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone 206–231–3667; email 

Timothy.P.Dowling@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–06–10, 

Amendment 39–19879 (85 FR 17490, 

March 30, 2020) (AD 2020–06–10). AD 

2020–06–10 applied 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 2020–06–10 required repetitive 

inspections for cracking of the vertical 

stiffeners of the left- and right-hand 

sides of the window frames and 

corrective actions if necessary, as 

specified in EASA AD 2019–0173, dated 

July 18, 2019 (EASA AD 2019–0173). 

The FAA issued AD 2020–06–10 to 

address cracking of the vertical 

stiffeners of the left- and right-hand 

sides of the window frames, which 

could affect the structural integrity of 

the airplane. 

The NPRM published in the Federal 

Register on June 27, 2023 (88 FR 41518). 

The NPRM was prompted by AD 2023– 

0009, dated January 16, 2023, issued by 

EASA (EASA AD 2023–0009) (also 

referred to as the MCAI), which 

superseded EASA AD 2019–0173. Since 

EASA AD 2019–0173 was issued, it was 

determined that certain compliance 

times need to be reduced, based on 

further analysis. The MCAI states that, 

during an inspection, cracking was 

found on the frame of the right-hand 

side sliding window in the flight deck. 

This condition, if not corrected, could 

lead to reduced structural integrity of 

the airplane. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2023–1221. 

In the NPRM, the FAA proposed to 

retain the requirements of AD 2020–06– 

10, with amended compliance times, as 

specified in EASA AD 2023–0009. The 

FAA is issuing this AD to address 

cracking of the vertical stiffeners of the 

left- and right-hand sides of the window 

frames, which could affect the structural 

integrity of the airplane. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

one commenter, United Airlines, who 

supported the NPRM without change. 

Conclusion 

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 this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI referenced above. The FAA 

reviewed the relevant data and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on this 

product. 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. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2023–0009 specifies 

procedures for repetitive inspections for 

cracking of the vertical stiffeners of the 

left- and right-hand sides of the window 

frame and corrective actions if 

necessary. Corrective actions include 

modification, rework, and repair. 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 1,525 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 2020– 

06–10.

11 work-hours × $85 per hour = 

$935.

$0 $935 $1,425,875 per inspection cycle. 

* Table does not include estimated costs for reporting. 

The FAA estimates that it would take 

about 1 work-hour per product to 

comply with the reporting requirement 

in this AD. The average labor rate is $85 

per hour. Based on these figures, The 

FAA estimates the cost of reporting the 

inspection results on U.S. operators to 

be $129,625, or $85 per product. 

The FAA estimates the following 

costs to do any necessary on-condition 

modifications that would be required 

based on the results of any required 


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Federal Register / Vol. 88, No. 180 / Tuesday, September 19, 2023 / Rules and Regulations 64367 

actions. The FAA has no way of 

determining the number of aircraft that 

might need this on-condition 

modification: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

5 work-hours × $85 per hour = $425 ...................................................................................................................... (*) * $425 

* The FAA has received no definitive data on which to base the parts cost estimates for the on-condition modification specified in this AD. 

The FAA has received no definitive 

data that would enable the agency to 

provide cost estimates for the other oncondition actions specified in this AD. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a currently valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to take 

approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, and completing and 

reviewing the collection of information. 

All responses to this collection of 

information are mandatory. Send 

comments regarding this burden 

estimate or any other aspect of this 

collection of information, including 

suggestions for reducing this burden, to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2020–06–10, Amendment 39– 

19879 (85 FR 17490, March 30, 2020); 

and 

■ b. Adding the following new AD: 

2023–18–02 Airbus SAS: Amendment 39– 

22543; Docket No. FAA–2023–1221; 

Project Identifier MCAI–2023–00070–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 24, 2023. 

(b) Affected ADs 

This AD replaces AD 2020–06–10, 

Amendment 39–19879 (85 FR 17490, March 

30, 2020) (AD 2020–06–10). 

(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 2023– 

0009, dated January 16, 2023 (EASA AD 

2023–0009). 

(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 a report of 

cracking found on the frame of the right-hand 

side sliding window in the flight deck, and 

a determination that certain compliance 

times need to be reduced. The FAA is issuing 

this AD to address cracking of the vertical 

stiffeners of the left- and right-hand sides of 

the window frames, which could affect the 

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 2023–0009. 

(h) Exceptions to EASA AD 2023–0009 

(1) Where EASA AD 2023–0009 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where EASA AD 2023–0009 refers to 

August 1, 2019 (the effective date of EASA 

AD 2019–0173), this AD requires using May 

4, 2020 (the effective date of AD 2020–06– 

10). 

(3) This AD does not adopt the ‘‘Remarks’’ 

section of EASA AD 2023–0009. 

(4) Paragraph (3) of EASA AD 2023–0009 

specifies to report inspection results to 

Airbus within a certain compliance time. For 

this AD, report inspection results (in case of 

findings only) at the applicable time 


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64368 Federal Register / Vol. 88, No. 180 / Tuesday, September 19, 2023 / Rules and Regulations 

specified in paragraph (h)(4)(i) or (ii) of this 

AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(5) Where paragraph (5) of EASA AD 2023– 

0009 specifies credit for certain actions, this 

AD provides credit for using the torque 

values specified in Section 13 of the Airbus 

technical adaptations (TAs) identified in 

paragraphs (h)(5)(i) through (vi) of this AD, 

when installing a certain eccentric referenced 

in ‘‘Airbus SB A320–53–1402 original issue’’ 

or ‘‘Airbus SB A320–53–1403 original issue,’’ 

as specified in the applicable TA, before the 

effective date of this AD. 

(i) Airbus TA 80662272/007/2019, Issue 1, 

dated August 29, 2019. 

(ii) Airbus TA 80662272/008/2019, Issue 1, 

dated August 29, 2019. 

(iii) Airbus TA 80662272/009/2019, Issue 

1, dated August 29, 2019. 

(iv) Airbus TA 80662272/010/2019, Issue 

1, dated August 29, 2019. 

(v) Airbus TA 80696258/006/2019, Issue 1, 

dated October 29, 2019. 

(vi) Airbus TA 80696258/007/2019, Issue 

1, dated October 29, 2019. 

(6) Where Table 1 of EASA AD 2023–0009 

specifies configurations, replace the text 

‘‘post SB’’ with ‘‘post embodiment of SB’’ 

and replace the text ‘‘pre SB’’ with ‘‘pre 

embodiment of SB.’’ 

(i) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, may be issued to 

operate the airplane to a location where the 

requirements of this AD can be 

accomplished, but concurrence by the 

Manager, International Validation Branch, 

FAA, is required before issuance of the 

special flight permit. 

(j) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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 

responsible Flight Standards Office, as 

appropriate. If sending information directly 

to the International Validation Branch, send 

it to the attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-AVS-AIR-730-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 

2020–06–10 are approved as AMOCs for the 

corresponding provisions of EASA AD 2023– 

0009 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, 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 (j)(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. 

(k) Additional Information 

For more information about this AD, 

contact Timothy Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY; telephone 206–231–3667; 

email Timothy.P.Dowling@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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2023–0009, dated January 16, 

2023. 

(ii) [Reserved] 

(3) For EASA AD 2023–0009, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

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

easa.europa.eu. You may find this EASA AD 

on the EASA website at ad.easa.europa.eu. 

(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: 

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

Issued on September 1, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–20174 Filed 9–18–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1076; Project 

Identifier MCAI–2020–01201–A; Amendment 

39–22544; AD 2023–18–03] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited (Type Certificated Previously 

Held by Bombardier Inc. and de 

Havilland, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Viking Air Limited (Viking) (type 

certificate previously held by 

Bombardier Inc. and de Havilland, Inc.) 

Model DHC–3 airplanes. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as corrosion, wear, and 

fatigue-related degradation in aging 

aircraft. This AD requires incorporating 

into the existing maintenance records 

for your airplane the actions and 

associated thresholds and intervals, 

including life limits, specified in a 

supplemental inspection and corrosion 

control manual for Model DHC–3 

airplanes. This AD also requires 

completing all the initial tasks 

identified in this manual and reporting 

corrosion findings to Viking. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 24, 

2023. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 24, 2023. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2020–1076; 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 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. 

Material Incorporated by Reference: 


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