Federal Register / Vol. 85, No. 250 / Wednesday, December 30, 2020 / Rules and Regulations 86459 

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: 

2020–26–18 Airbus SAS: Amendment 39– 

21373; Docket No. FAA–2020–1135; 

Project Identifier MCAI–2020–01363–T. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 14, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A330–243, –343, and –941 airplanes, 

certificated in any category, as identified in 

European Union Aviation Safety Agency 

(EASA) AD 2020–0209, dated October 5, 

2020 (EASA AD 2020–0209). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that 

during an inspection of the wing/fuselage 

fillet interface, evidence of black stains and 

white oxidation was found on several areas 

of the fillet fairing adjustable rods due to 

surface corrosion. The FAA is issuing this 

AD to address surface corrosion, which could 

lead to rod failures and consequent fillet 

fairing detachment, and possibly result in 

damage to the tailplane and reduced control 

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 2020–0209. 

(h) Exception to EASA AD 2020–0209 

The ‘‘Remarks’’ section of EASA AD 2020– 

0209 does not apply to this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, International Validation Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. In accordance with 

14 CFR 39.19, send your request to your 

principal inspector or responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (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 Vladimir Ulyanov, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

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

telephone and fax: 206–231–3229; email 

vladimir.ulyanov@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 2020–0209, dated October 5, 

2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0209, contact the 

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. This material may be found 

in the AD docket on the internet at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–1135. 

(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 fedreg.legal@

nara.gov, or go to: https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on December 14, 2020. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2020–28859 Filed 12–29–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0681; Product 

Identifier 2020–NM–089–AD; Amendment 

39–21376; AD 2020–26–21] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus SAS Model A350–941 airplanes. 

This AD was prompted by a report that 

during the assembly of a certain section 

of the fuselage, the gaps found on selfaligning nuts for eight fasteners were 

out of tolerance. This AD requires a 

rotating probe test of all fastener holes 

located in the affected area for any 

discrepancies, an eddy current 

inspection of the surrounding flange for 

any discrepancies, a detailed inspection 

of certain frames for any discrepancies, 

and corrective actions if necessary, 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 February 3, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 3, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

the EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; telephone +49 

221 8999 000; email ADs@

easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

IBR material on the EASA website at 

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

view this IBR material at the FAA, 

86460 Federal Register / Vol. 85, No. 250 / Wednesday, December 30, 2020 / Rules and Regulations 

Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0681. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0681; 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, 

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: 

Kathleen Arrigotti, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3218; email 

Kathleen.Arrigotti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0109, dated May 15, 2020 (EASA 

AD 2020–0109) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for certain Airbus SAS 

Model A350–941 airplanes. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus SAS Model 

A350–941 airplanes. The NPRM 

published in the Federal Register on 

August 4, 2020 (85 FR 47122). The 

NPRM was prompted by a report that 

during the assembly of the section 19 

skin to frame (FR) 98 joint of the 

fuselage, the gaps found on self-aligning 

nuts for eight fasteners were out of 

tolerance. The NPRM proposed to 

require a rotating probe test of all 

fastener holes located in the affected 

area for any discrepancies, an eddy 

current inspection of the surrounding 

flange for any discrepancies, a detailed 

inspection of certain frames for any 

discrepancies, and corrective actions if 

necessary, as specified in an EASA AD. 

The FAA is issuing this AD to address 

gaps that are out of tolerance, which 

could reduce the fatigue and damage 

tolerance properties of the affected area, 

and possibly affect the structural 

integrity of the rear cone of the fuselage. 

See the MCAI for additional background 

information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The following presents 

the comments received on the NPRM 

and the FAA’s response to each 

comment. 

Request To Revise the Proposed 

Applicability 

Delta Air Lines, Inc. (DAL) requested 

that the FAA revise the applicability in 

the NPRM. DAL stated that the 

applicability should reflect the 

effectivity specified in Airbus Service 

Bulletin A350–53–P057, dated February 

21, 2020, and not what is specified in 

the NPRM and in EASA AD 2020–0109. 

DAL also stated that the NPRM and 

EASA AD 2020–0109 would require 

operators the unnecessary burden of 

reviewing records and updating 

associated paperwork to ensure and 

prove that the proper modification 

status is embodied on all airplanes, 

including on any Model A350 airplanes 

delivered in the future, despite the 

embodiment of the applicable 

modification in production. DAL 

commented that Airbus Service Bulletin 

A350–53–P057, dated February 21, 

2020, specifies specific manufacturer 

serial numbers and describes which 

airplanes will have the modification 

embodied in production (manufacturer 

serial number 0307 and subsequent). 

The FAA disagrees with the request. 

The applicability of this AD (and EASA 

AD 2020–0109) excludes any airplanes 

on which the modification has been 

embodied, whether during or after 

production. EASA, as the State of 

Design Authority for Airbus products, 

has determined that this applicability is 

appropriate because it includes any 

airplanes on which the modification 

was not embodied, while excluding 

those on which the modification has 

been embodied. The FAA agrees with 

this decision because it ensures the 

unsafe condition is addressed on all 

applicable airplanes. The FAA has not 

changed the AD in this regard. 

Request To Include Exception To 

Provide Correct Reference for Installing 

New Fasteners 

DAL requested that the NPRM be 

revised to address a discrepancy in a 

manual reference for installing the new 

fasteners. DAL noted that Airbus 

Service Bulletin A350–53–P057, dated 

February 21, 2020, specifies Airbus task 

A350–A–53–XX–P057–01001–720A–A 

and task A350–A–53–XX–P057–02001– 

720A–A for instructions to install the 

new fasteners, and that the actions in 

those tasks are considered Required for 

Compliance (RC). DAL asserted that the 

instructions in those tasks should refer 

to the Airbus A350 Aircraft 

Maintenance Manual (AMM) procedure 

rather than the aircraft structural repair 

(ASR) manual. DAL pointed out that 

there is no existing ASR manual with 

chapter A350–A–20–51–50–01ZZZ– 

25BZ–A; however, the AMM reference 

for standard mechanical torques is 

maintenance procedure chapter A350– 

A–20–51–50–01ZZZ–25BZ–A. DAL 

stated that Airbus has confirmed in 

Airbus Technical Request Dossier 

80808465 that the correct reference is to 

the AMM. DAL further requested that, if 

this discrepancy is not addressed in the 

AD, it will require that a global 

alternative method of compliance 

(AMOC) be requested by Airbus. 

The FAA agrees that the correct 

document should be referenced for the 

reasons provided above. The FAA has 

added paragraph (h)(3) in this AD to 

clarify that, where Airbus Service 

Bulletin A350–53–P057, dated February 

21, 2020, specifies Airbus task A350–A– 

53–XX–P057–01001–720A–A and task 

A350–A–53–XX–P057–02001–720A–A, 

for instructions for installing the new 

fasteners, and those instructions specify 

to refer to ‘‘Ref. ASR A350–A–20–51– 

01ZZZ–25BZ–A,’’ for the purposes of 

this AD, the correct reference is ‘‘Ref. 

AMM Maintenance Procedure A350–A– 

20–51–01ZZZ–25BZ–A.’’ 

Request To Provide Clarification on the 

Use of Substitute Fasteners 

DAL requested that the FAA provide 

clarification regarding the use of 

substitute fasteners. DAL stated that task 

A350–A–53–XX–P057–01001–720A–A 

and task A350–A–53–XX–P057–02001– 

720A–A, specified in Airbus Service 

Bulletin A350–53–P057, dated February 

21, 2020, provide instructions to install 

new fasteners. DAL also stated that 

standard notes within these allow for 

the use of washers or approved 

substitute fasteners should the installed 

fasteners not be sufficient per the 

standards provided in the ASR manual. 

DAL questioned whether, since Airbus 

Service Bulletin A350–53–P057, dated 

February 21, 2020, provides the specific 

fasteners to use to address the issue in 

the NPRM, an AMOC will be required 

for the use of substitute fasteners 

despite these notes. 

The FAA agrees to provide 

clarification. An AMOC is not needed 

for the use of washers or approved 

Federal Register / Vol. 85, No. 250 / Wednesday, December 30, 2020 / Rules and Regulations 86461 

substitute fasteners should the installed 

fasteners not be sufficient. The FAA has 

not changed this AD in this regard. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the change described 

previously and minor editorial changes. 

The FAA has determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

The FAA also determined that this 

change will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2020–0109 describes 

procedures for a rotating probe test of all 

fastener holes located in the affected 

area for any discrepancies (i.e., cracking 

or damage), an eddy current inspection 

of the surrounding flange for any 

discrepancies, a detailed inspection of 

FR 97 to FR 99 for any discrepancies, 

and corrective actions if necessary. 

Corrective actions include replacing all 

fasteners located in the affected area 

with new bolts and self-aligning nuts, 

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 13 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 

1 work-hour × $85 per hour = $85 .............................................................................................. $0 $85 $1,105 

The FAA estimates the following 

costs to do any necessary on-condition 

replacements that would be required 

based on the results of any required 

actions. The FAA has no way of 

determining the number of aircraft that 

might need these replacements: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS * 

Labor cost Parts cost Cost per 

product 

6 work-hours × $85 per hour = $510 ...................................................................................................................... $70 $580 

* The FAA has received no definitive data that would enable providing cost estimates for the on-condition repairs specified in this AD. 

According to the manufacturer, some 

or all of the costs of this AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. The FAA does not control 

warranty coverage for affected operators. 

As a result, the FAA has included all 

known costs in the cost estimate. 

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. 

Adoption of 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: 

2020–26–21 Airbus SAS: Amendment 39– 

21376; Docket No. FAA–2020–0681; 

Product Identifier 2020–NM–089–AD. 

(a) Effective Date 

This AD is effective February 3, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A350–941 airplanes, certificated in any 

category, as identified in European Union 

Aviation Safety Agency (EASA) AD 2020– 

86462 Federal Register / Vol. 85, No. 250 / Wednesday, December 30, 2020 / Rules and Regulations 

0109, dated May 15, 2020 (EASA AD 2020– 

0109). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that 

during the assembly of the section 19 skin to 

frame (FR) 98 joint of the fuselage, the gaps 

found on self-aligning nuts for eight fasteners 

were out of tolerance. The FAA is issuing 

this AD to address gaps that are out of 

tolerance, which could reduce the fatigue 

and damage tolerance properties of the 

affected area, and possibly affect the 

structural integrity of the rear cone 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 2020–0109. 

(h) Exceptions to EASA AD 2020–0109 

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

2020–0109 does not apply to this AD. 

(2) Where paragraph (2) of EASA AD 2020– 

0109 specifies actions if ‘‘any discrepancy is 

detected, as defined in the SB,’’ for this AD 

a discrepancy is defined as any crack or 

damage. 

(3) Where Airbus Service Bulletin A350– 

53–P057, dated February 21, 2020 

(referenced in EASA AD 2020–0109), 

specifies Airbus task A350–A–53–XX–P057– 

01001–720A–A and task A350–A–53–XX– 

P057–02001–720A–A, for instructions for 

installing the new fasteners, and those 

instructions specify to refer to ‘‘ASR A350– 

A–20–51–01ZZZ–25BZ–A,’’ for the purposes 

of this AD, the correct reference is ‘‘AMM 

Maintenance Procedure A350–A–20–51– 

01ZZZ–25BZ–A.’’ 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, International Validation Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. In accordance with 

14 CFR 39.19, send your request to your 

principal inspector or responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (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 paragraphs (h)(2) and (3) and 

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 Kathleen Arrigotti, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

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

telephone and fax 206–231–3218; email 

Kathleen.Arrigotti@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 2020–0109, dated May 15, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0109, contact the 

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. This material may be found 

in the AD docket on the internet at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–0681. 

(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 fedreg.legal@

nara.gov, or go to: https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on December 17, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–28861 Filed 12–29–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0683; Project 

Identifier MCAI–2020–01134–T; Amendment 

39–21375; AD 2020–26–20] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Canada Limited Partnership (Type 

Certificate Previously Held by C Series 

Aircraft Limited Partnership (CSALP); 

Bombardier, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Canada Limited Partnership 

Model BD–500–1A10 and BD–500– 

1A11 airplanes. This AD was prompted 

by a report that during installation on 

the final assembly line, a foreign object 

damage (FOD) protective end cap was 

not removed from an extraction duct of 

the crew oxygen system. The protective 

end cap must be removed to prevent a 

build-up of oxygen under the flight deck 

floor, which is a fire risk. This AD 

requires inspecting the air extraction 

duct installation to determine if a 

protective end cap is installed, and 

removing any protective end cap found. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective February 3, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 3, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Canada Limited Partnership, 

13100 Henri-Fabre Boulevard, Mirabel, 

Que ́bec, J7N 3C6, Canada; telephone 

450–476–7676; email a220_crc@

abc.airbus; internet https://

a220world.airbus.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. 

It is also available on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0683. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://