Federal Register / Vol. 87, No. 135 / Friday, July 15, 2022 / Rules and Regulations 42315 

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 Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) TCCA AD 

CF–2021–30, dated September 7, 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–2022–0470. 

(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. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(4) and (5) of this AD. 

(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 this AD specifies otherwise. 

(i) Bombardier Service Bulletin 700–35– 

5004, Revision 02, dated August 27, 2021. 

(ii) Bombardier Service Bulletin 700–35– 

5502, dated August 27, 2021. 

(iii) Bombardier Service Bulletin 700–35– 

6004, Revision 05, dated August 27, 2021. 

(iv) Bombardier Service Bulletin 700–35– 

6502, dated August 27, 2021. 

(3) For service information identified in 

this AD, contact Bombardier Business 

Aircraft Customer Response Center, 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–2999; email 

ac.yul@aero.bombardier.com; internet 

https://www.bombardier.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, 

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

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

ibr-locations.html. 

Issued on June 27, 2022. 

Christina Underwood, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–15190 Filed 7–14–22; 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; Amendment 

39–22115; AD 2022–14–10] 

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) 2018–13– 

08, 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 

2018–13–08 required 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. This AD was prompted by a 

determination that additional airplanes 

are subject to the unsafe condition. This 

AD revises the applicability by adding 

airplanes and retains the requirements 

of AD 2018–13–08; 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 August 19, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 19, 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 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0468. 

Examining the AD Docket 

You may examine the AD docket 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 

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, International 

Validation Branch, FAA, 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 2021–0241, 

dated November 8, 2021 (EASA AD 

2021–0241) (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, 

–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 2018–13–08, 


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42316 Federal Register / Vol. 87, No. 135 / Friday, July 15, 2022 / Rules and Regulations 

Amendment 39–19320 (83 FR 33809, 

July 18, 2018) (AD 2018–13–08). AD 

2018–13–08 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. 

The NPRM published in the Federal 

Register on April 22, 2022 (87 FR 

24081). The NPRM 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. The 

NPRM was also prompted by a 

determination that Model A321 

airplanes that have incorporated 

modification 160021 are also subject to 

the unsafe condition. The NPRM 

proposed to revise the applicability by 

adding airplanes and retain the 

requirements of AD 2018–13–08, as 

specified in EASA AD 2021–0241. 

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. See 

the MCAI for additional background 

information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

United Airlines who supported the 

NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment 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 2021–0241 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) inspections 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 or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

affects 1,549 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 2018–03–08 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 inspections ..................................... 25 work-hours × $85 per hour = $2,125 $100 .................... $2,225 ................. $3,446,525. 

New 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 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 


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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) 2018–13–08, Amendment 39– 

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

■ b. Adding the following new AD: 

2022–14–10 Airbus SAS: Amendment 39– 

22115; Docket No. FAA–2022–0468; 

Project Identifier MCAI–2021–01243–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 19, 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) 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 (k) 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): 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) Related Information 

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. 

(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 2021–0241, dated November 8, 

2021. 


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(ii) [Reserved] 

(3) For 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. 

(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 June 29, 2022. 

Christina Underwood, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–15189 Filed 7–14–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0505; Project 

Identifier MCAI–2021–01289–T; Amendment 

39–22111; AD 2022–14–06] 

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 all 

Airbus SAS Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). This AD 

was prompted by a determination that 

new or more restrictive airworthiness 

limitations are necessary. This AD 

requires revising the existing 

maintenance or inspection program, as 

applicable, to incorporate new or more 

restrictive airworthiness limitations, 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 August 19, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 19, 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 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0505. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0505; 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: Dan 

Rodina, Aerospace Engineer, Large 

Aircraft Section, FAA, International 

Validation Branch, 2200 South 216th 

St., Des Moines, WA 98198; phone: 

206–231–3225; email: dan.rodina@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0258, 

dated November 17, 2021 (EASA AD 

2021–0258) (also referred to as the 

MCAI), to correct an unsafe condition 

for all Airbus SAS Model A300–600 

series airplanes. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus SAS Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes). The 

NPRM published in the Federal 

Register on May 6, 2022 (87 FR 27029). 

The NPRM was prompted by a 

determination that new or more 

restrictive airworthiness limitations are 

necessary. The NPRM proposed to 

require revising the existing 

maintenance or inspection program, as 

applicable, to incorporate new or more 

restrictive airworthiness limitations, as 

specified in EASA AD 2021–0258. 

The FAA is issuing this AD to prevent 

reduced structural integrity of the 

airplane. See the MCAI for additional 

background information. 

EASA previously issued EASA AD 

2019–0090, dated April 26, 2019 (EASA 

AD 2019–0090), requiring the actions 

described in the Airbus A300–600 

Airworthiness Limitations Section 

(ALS), Part 2, ‘‘Damage Tolerant 

Airworthiness Limitation Items (DT– 

ALI),’’ Revision 03, dated December 14, 

2018, which also includes the limit of 

validity (LOV) for the Model A300–600 

airplanes. EASA AD 2019–0090 

corresponds to FAA AD 2019–21–01, 

Amendment 39–19767 (84 FR 56935, 

October 24, 2019) (AD 2019–21–01). 

Since that EASA AD was issued, Airbus 

published the Variation, as defined in 

EASA AD 2021–0258, which reduces 

the LOV for Model A300–600 airplanes, 

reflecting the engineering data that 

supports the structural maintenance 

program and that corresponds to the 

period of time during which it is 

demonstrated that Widespread Fatigue 

Damage will not occur. EASA AD 2021– 

0258 does not supersede EASA AD 

2019–0090, but does specify that it 

invalidates the LOV as specified in the 

Airbus A300–600 ALS, Part 2. 

Therefore, this AD would replace the 

LOVs specified in Airbus A300–600 

Airworthiness Limitations Section 

(ALS), Part 2, ‘‘Damage Tolerant 

Airworthiness Limitation Items (DT– 

ALI),’’ Revision 03, dated December 14, 

2018, as required by FAA AD 2019–21– 

01. 

For the reason described above, this 

AD requires compliance with the 

reduced LOV as specified in the 

variation. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from the 

Air Line Pilots Association, 

International (ALPA) and FedEx 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 


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