40934 Federal Register / Vol. 86, No. 144 / Friday, July 30, 2021 / Rules and Regulations 

that the update of the hydraulic monitoring 

system be accomplished using the method of 

compliance specified in paragraphs (h)(1)(i) 

through (iv) of this AD, as applicable. 

(i) For Model A350–941 airplanes 

identified in Airbus Service Bulletin A350– 

29–P025 (MOD 114531 and MOD 114075): 

The modification must be done in 

accordance with paragraphs 3.C., 3.D., and 

3.E. of the Accomplishment Instructions of 

Airbus Service Bulletin A350–29–P025, 

dated August 10, 2020. 

(ii) For Model A350–941 airplanes 

identified in Airbus Service Bulletin A350– 

29–P027 (MOD 114533 and MOD 114075): 

The modification must be done in 

accordance with paragraphs 3.C., 3.D., and 

3.E. of the Accomplishment Instructions of 

Airbus Service Bulletin A350–29–P027, 

dated November 24, 2020. 

(iii) For Model A350–941 airplanes 

identified in Airbus Service Bulletin A350– 

29–P029 (MOD 114535 and MOD 114075): 

The modification must be done in 

accordance with paragraphs 3.C., 3.D., and 

3.E. of the Accomplishment Instructions of 

Airbus Service Bulletin A350–29–P029, 

dated December 16, 2020. 

(iv) For Model A350–941 airplanes not 

identified in paragraphs (h)(1)(i) through (iii) 

of this AD, and without MOD 114073 and 

114075 installed in production: The 

modification must be done 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. 

(2) Where EASA AD 2020–0268 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) The requirements specified in 

paragraphs (1) and (2) of EASA AD 2020– 

0268 do not apply to this AD. 

(4) Paragraph (3) of EASA AD 2020–0268 

specifies revising ‘‘the approved AMP’’ 

within 12 months after its effective date, but 

this AD requires revising the existing 

maintenance or inspection program, as 

applicable, within 90 days after the effective 

date of this AD. 

(5) The initial compliance time for doing 

the tasks specified in paragraph (3) of EASA 

AD 2020–0268 is at the applicable 

‘‘thresholds’’ as incorporated by the 

requirements of paragraph (3) of EASA AD 

2020–0268, or within 90 days after the 

effective date of this AD, whichever occurs 

later. 

(6) The provisions specified in paragraphs 

(4) and (5) of EASA AD 2020–0268 do not 

apply to this AD. 

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

2020–0268 does not apply to this AD. 

(i) Provisions for Alternative Actions, 

Intervals, and Critical Design Configuration 

Control Limitations (CDCCLs) 

After the existing maintenance or 

inspection program has been revised as 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and CDCCLs are allowed unless 

they are approved as specified in the 

provisions of the ‘‘Ref. Publications’’ section 

of EASA AD 2020–0268. 

(j) 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 local Flight Standards 

District 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. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by 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 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; 

Kathleen.Arrigotti@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 2020–0268, dated December 4, 

2020. 

(ii) Airbus Service Bulletin A350–29–P025, 

dated August 10, 2020. 

(iii) Airbus Service Bulletin A350–29– 

P027, dated November 24, 2020. 

(iv) Airbus Service Bulletin A350–29– 

P029, dated December 16, 2020. 

(3) For EASA AD 2020–0268, 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. For Airbus SAS service 

information identified in this AD, contact 

Airbus SAS, Airworthiness Office—EAL, 

Rond-Point Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; telephone +33 5 61 

93 36 96; fax +33 5 61 93 45 80; email 

continued-airworthiness.a350@airbus.com; 

internet http://www.airbus.com. 

(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–2021–0193. 

(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 May 21, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–16241 Filed 7–29–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0303; Project 

Identifier MCAI–2020–01367–T; Amendment 

39–21611; AD 2021–13–06] 

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 certain 

Airbus SAS Model A350–941 and –1041 

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 two 

European Union Aviation Safety Agency 

(EASA) ADs, which are incorporated by 

reference. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 


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Federal Register / Vol. 86, No. 144 / Friday, July 30, 2021 / Rules and Regulations 40935 

DATES: This AD is effective September 3, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 3, 2021. 

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 IBR 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 on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0303. 

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–2021– 

0303; 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: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2020–0211, 

dated October 5, 2020 (EASA AD 2020– 

0211); and EASA AD 2021–0026, dated 

January 20, 2021 (EASA AD 2021– 

0026); (also referred to as the Mandatory 

Continuing Airworthiness Information, 

or the MCAI) to correct an unsafe 

condition for all Airbus SAS Model 

A350–941 and –1041 airplanes. EASA 

AD 2021–0026 refers to Airbus A350 

Airworthiness Limitations Section 

(ALS) Part 4, Variation 5.1, dated July 

22, 2020. Airplanes with an original 

airworthiness certificate or original 

export certificate of airworthiness 

issued after July 22, 2020, must comply 

with the airworthiness limitations 

specified as part of the approved type 

design and referenced on the type 

certificate data sheet; this AD therefore 

does not include those airplanes in the 

applicability. 

The FAA issued AD 2019–20–01, 

Amendment 39–19754 (84 FR 55495, 

October 17, 2019) (AD 2019–20–01), to 

require, among other things, repetitive 

greasing of certain thrust reverser 

actuators (TRAs). For those TRAs 

identified as batch 02 in EASA AD 

2018–0234R2, dated September 17, 2019 

(which is required by AD 2019–20–01), 

the repetitive greasing task has since 

been incorporated into Airbus A350 

Airworthiness Limitations Section 

(ALS), Part 4, Systems Equipment 

Maintenance Requirements (SEMR), 

Revision 05 Issue 02, dated June 25, 

2020, which is specified in EASA 2020– 

0211. Accomplishing the actions in this 

AD would therefore terminate the 

repetitive greasing of batch 02 TRAs 

required by paragraph (g) of AD 2019– 

20–01. 

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 and –1041 airplanes. The 

NPRM published in the Federal 

Register on April 16, 2021 (86 FR 

20086). 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 

specified in EASA AD 2020–0211 and 

EASA AD 2021–0026. 

The FAA is issuing this AD to address 

hazardous or catastrophic airplane 

system failures. See the MCAI for 

additional background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA has considered 

the comment received. The Air Line 

Pilots Association, International (ALPA) 

stated its support for the NPRM. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. 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. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2020–0211 and EASA AD 

2021–0026 describe new or more 

restrictive airworthiness limitations for 

airplane systems and safe life limits. 

These documents are distinct because 

they apply to different airplane 

configurations. 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 15 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

The FAA has determined that revising 

the existing maintenance or inspection 

program takes an average of 90 workhours per operator, although the agency 

recognizes that this number may vary 

from operator to operator. Since 

operators incorporate maintenance or 

inspection program changes for their 

affected fleet(s), the FAA has 

determined that a per-operator estimate 

is more accurate than a per-airplane 

estimate. Therefore, the agency 

estimates the average total cost per 

operator to be $7,650 (90 work-hours × 

$85 per work-hour). 

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 


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40936 Federal Register / Vol. 86, No. 144 / Friday, July 30, 2021 / Rules and Regulations 

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: 

2021–13–06 Airbus SAS: Amendment 39– 

21611; Docket No. FAA–2021–0303; 

Project Identifier MCAI–2020–01367–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective September 3, 2021. 

(b) Affected ADs 

This AD affects AD 2019–20–01, 

Amendment 39–19754 (84 FR 55495, October 

17, 2019) (AD 2019–20–01). 

(c) Applicability 

This AD applies to Airbus SAS Model 

A350–941 and –1041 airplanes, certificated 

in any category, with an original 

airworthiness certificate or original export 

certificate of airworthiness issued on or 

before July 22, 2020. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a determination 

that new or more restrictive airworthiness 

limitations are necessary. The FAA is issuing 

this AD to address hazardous or catastrophic 

airplane system failures. 

(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, European Union Aviation 

Safety Agency (EASA) AD 2020–0211, dated 

October 5, 2020 (EASA AD 2020–0211); and 

EASA AD 2021–0026, dated January 20, 2021 

(EASA AD 2021–0026). Where EASA AD 

2021–0026 affects the same airworthiness 

limitations (tasks and life limits) as those in 

EASA AD 2020–0211, the airworthiness 

limitations referenced in EASA AD 2021– 

0026 prevail. 

(h) Exceptions to EASA AD 2020–0211 and 

EASA AD 2021–0026 

(1) Where EASA AD 2020–0211 and EASA 

AD 2021–0026 refers to its effective date, this 

AD requires using the effective date of this 

AD. 

(2) The requirements specified in 

paragraphs (1) and (2) of EASA AD 2020– 

0211 and EASA AD 2021–0026 do not apply 

to this AD. 

(3) Paragraph (3) of EASA AD 2020–0211 

and EASA AD 2021–0026 specifies revising 

‘‘the approved AMP [aircraft maintenance 

program]’’ within 12 months after its 

effective date, but this AD requires revising 

the existing maintenance or inspection 

program, as applicable, to incorporate the 

‘‘limitations, tasks and associated thresholds 

and intervals’’ specified in paragraph (3) of 

EASA AD 2020–0211 and EASA AD 2021– 

0026 within 90 days after the effective date 

of this AD. 

(4) The initial compliance time for doing 

the tasks specified in paragraph (3) of EASA 

AD 2020–0211 and EASA AD 2021–0026 is 

at the applicable ‘‘thresholds’’ as 

incorporated by the requirements of 

paragraph (3) of EASA AD 2020–0211 and 

EASA AD 2021–0026, or within 90 days after 

the effective date of this AD, whichever 

occurs later. 

(5) The provisions specified in paragraphs 

(4) and (5) of EASA AD 2020–0211 do not 

apply to this AD. 

(6) The provisions specified in paragraph 

(4) of EASA AD 2021–0026 do not apply to 

this AD. 

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

2020–0211 and EASA AD 2021–0026 does 

not apply to this AD. 

(i) Provisions for Alternative Actions and 

Intervals 

After the existing maintenance or 

inspection program has been revised as 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections) and 

intervals are allowed unless they are 

approved as specified in the provisions of the 

‘‘Ref. Publications’’ section of EASA AD 

2020–0211 or EASA AD 2021–0026. 

(j) Terminating Action for Certain 

Requirements of AD 2019–20–01 

Accomplishing the actions required by this 

AD terminates the repetitive greasing task for 

batch 02 group of affected thrust reverser 

actuators required by paragraph (g) of AD 

2019–20–01. 

(k) 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 (l) of this AD. 

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

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA 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 (k)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

For more information about this AD, 

contact 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. 

(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) European Union Aviation Safety Agency 

(EASA) AD 2020–0211, dated October 5, 

2020. 


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(ii) European Union Aviation Safety 

Agency (EASA) AD 2021–0026, dated 

January 20, 2021. 

(3) For EASA AD 2020–0211 and EASA AD 

2021–0026, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; 

telephone +49 221 8999 000; email ADs@

easa.europa.eu; internet 

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

EASA ADs 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–2021–0303. 

(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 June 10, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–16245 Filed 7–29–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0264; Project 

Identifier MCAI–2020–01416–T; Amendment 

39–21616; AD 2021–13–11] 

RIN 2120–AA64 

Airworthiness Directives; MHI RJ 

Aviation ULC (Type Certificate 

Previously Held by 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 

MHI RJ Aviation ULC Model CL–600– 

2D15 (Regional Jet Series 705) and CL– 

600–2D24 (Regional Jet Series 900) 

airplanes. This AD was prompted by a 

report that the lower aft outboard 

supporting structure of galley 2 does not 

meet certification requirements for all 

flight and/or emergency landing loads. 

This AD requires modifying the floor 

structure between certain fuselage 

stations. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective September 3, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 3, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact MHI 

RJ Aviation ULC, 12655 Henri-Fabre 

Blvd., Mirabel, Que ́bec J7N 1E1 Canada; 

Widebody Customer Response Center 

North America toll-free telephone +1– 

844–272–2720 or direct-dial telephone 

+1–514–855–8500; fax +1–514–855– 

8501; email thd.crj@mhirj.com; internet 

https://mhirj.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–2021–0264. 

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–2021– 

0264; 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: 

Antariksh Shetty, Aerospace Engineer, 

Airframe and Propulsion Section, FAA, 

New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7300; fax 

516–794–5531; email 9-avs-nyaco-cos@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued TCCA AD CF– 

2020–40, dated October 15, 2020 (also 

referred to as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for certain MHI RJ Aviation ULC Model 

CL–600–2D15 (Regional Jet Series 705) 

and CL–600–2D24 (Regional Jet Series 

900) airplanes. You may examine the 

MCAI in the AD docket on the internet 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0264. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain MHI RJ Aviation ULC 

Model CL–600–2D15 (Regional Jet 

Series 705) and CL–600–2D24 (Regional 

Jet Series 900) airplanes. The NPRM 

published in the Federal Register on 

April 7, 2021 (86 FR 17998). The NPRM 

was prompted by a report that the lower 

aft outboard supporting structure of 

galley 2 does not meet certification 

requirements for all flight and/or 

emergency landing loads. The NPRM 

proposed to require modifying the floor 

structure between certain fuselage 

stations. The FAA is issuing this AD to 

address the insufficient structural safety 

margin of galley 2 in case of hard 

landing or severe turbulence. This 

condition, if not corrected, could result 

in injury to the occupants and could 

limit access to the exit door during 

emergencies if the galley is displaced or 

fails structurally. See the MCAI for 

additional background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA has considered 

the comment received. The Air Line 

Pilots Association, International 

(ALPA), indicated its support for the 

NPRM. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. 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. 

Related Service Information Under 1 

CFR Part 51 

MHI RJ has issued MHI RJ Service 

Bulletin 670BA–53–060, Revision A, 

dated September 17, 2020. This service 

information describes procedures for 

modifying the floor structure between 

fuselage station (FS) 379.00 and FS 

394.00 at right buttock line (RBL) 37.75. 

This service information 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. 


lotter on DSK11XQN23PROD with RULES1