Federal Register / Vol. 86, No. 35 / Wednesday, February 24, 2021 / Rules and Regulations 11113 

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. 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 Dassault Aviation’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

For more information about this AD, 

contact Tom Rodriguez, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; phone and fax: 

206–231–3226; email: tom.rodriguez@

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. 

(3) The following service information was 

approved for IBR on March 31, 2021. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0127, dated June 4, 2020. 

(ii) [Reserved] 

(4) For EASA AD 2020–0127, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +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. 

(5) 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–2020–0977. 

(6) 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 January 28, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03601 Filed 2–23–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0371; Project 

Identifier AD–2019–00124–E; Amendment 

39–21405; AD 2021–03–02] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) CF6– 

80C2A1, CF6–80C2A2, CF6–80C2A3, 

CF6–80C2A5, CF6–80C2A5F, CF6– 

80C2A8, CF6–80C2B1, CF6–80C2B1F, 

CF6–80C2B2, CF6–80C2B2F, CF6– 

80C2B4, CF6–80C2B4F, CF6–80C2B5F, 

CF6–80C2B6, CF6–80C2B6F, CF6– 

80C2B6FA, CF6–80C2B7F, CF6– 

80C2B8F, and CF6–80C2D1F model 

turbofan engines. This AD was 

prompted by reports of incidents that 

resulted in a significant fuel loss during 

flight and an in-flight shutdown (IFSD) 

of the engine. This AD requires initial 

and repetitive shim checks of the 

hydromechanical unit/main engine 

control (HMU/MEC) idler adapter on the 

accessory gearbox (AGB) assembly and, 

depending on the results of the shim 

check, possible replacement of the 

inserts on the HMU/MEC idler adapter. 

As a terminating action, this AD 

requires a protrusion check and a pullout test, and the replacement of inserts 

on the HMU/MEC idler adapter that fail 

either test. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective March 31, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 31, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, 1 Neumann 

Way, Cincinnati, OH 45215; phone: 

(513) 552–3272; email: 

aviation.fleetsupport@ge.com. You may 

view this service information at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (781) 238– 

7759. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0371. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0371; 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: 

Kevin M. Clark, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7088; fax: (781) 238– 

7199; email: kevin.m.clark@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain GE CF6–80C2A1, CF6– 

80C2A2, CF6–80C2A3, CF6–80C2A5, 

CF6–80C2A5F, CF6–80C2A8, CF6– 

80C2B1, CF6–80C2B1F, CF6–80C2B2, 

CF6–80C2B2F, CF6–80C2B4, CF6– 

80C2B4F, CF6–80C2B5F, CF6–80C2B6, 

CF6–80C2B6F, CF6–80C2B6FA, CF6– 

80C2B7F, CF6–80C2B8F, and CF6– 

80C2D1F model turbofan engines. The 

NPRM published in the Federal 

Register on April 10, 2020 (85 FR 

20211). The NPRM was prompted by 

reports of incidents that resulted in a 

significant fuel loss during flight and an 

IFSD of the engine. The incidents 

resulted from inserts on the HMU/MEC 

idler adapter on the AGB assembly 

pulling out of the housing. An 

investigation by the manufacturer 

discovered improperly cut threads on 

the inserts and erroneous instructions in 

the maintenance manual, which 

contributed to poor thread engagement. 

In the NPRM, the FAA proposed to 

require initial and repetitive shim 

checks of the HMU/MEC idler adapter 

on the AGB assembly and, depending 

on the results of the shim check, 

possible replacement of the inserts on 

the HMU/MEC idler adapter. As a 

terminating action to the repetitive shim 


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11114 Federal Register / Vol. 86, No. 35 / Wednesday, February 24, 2021 / Rules and Regulations 

checks, the NPRM proposed to require 

a protrusion check and a pull-out test, 

and the replacement of inserts on the 

HMU/MEC idler adapter that fail either 

test. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive Comments 

The FAA received comments from 

four commenters. The commenters were 

All Nippon Airways (ANA), Delta Air 

Lines, Inc. (DAL), FedEx Express 

(FedEx), and Japan Airlines (JAL). All 

commenters requested changes, some of 

which resulted in changes to this AD. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Update the Applicability 

DAL requested that paragraph (c), 

Applicability, of this AD be updated to 

align with the effectivity in GE CF6– 

80C2 Service Bulletin (SB) 72–1577 

R01, dated August 16, 2019 (GE CF6– 

80C2 SB 72–1577 R01), which includes 

the part numbers (P/Ns) of the affected 

HMU/MEC idler adapters. 

The FAA agrees. The FAA confirmed 

with the manufacturer that only the P/ 

Ns of the HMU/MEC idler adapter listed 

in GE CF6–80C2 SB 72–1577 R01 are 

affected. The FAA updated the 

applicability of this AD to include the 

P/Ns of the affected HMU/MEC idler 

adapter. The number of engines affected 

by this AD is unchanged from the 

NPRM. 

Request To Update Terminating Action 

DAL requested that paragraph (h), 

Terminating Action, of this AD also 

terminate the initial shim check of the 

HMU/MEC idler adapter inserts 

required by paragraph (g)(1) of this AD. 

DAL reasoned that since the NPRM 

proposed to allow for terminating the 

repetitive shim checks of the HMU/MEC 

idler adapter inserts, that this AD 

should add a terminating action for the 

initial shim check of the HMU/MEC 

idler adapter inserts if the action was 

performed within 1,200 flight hours 

(FHs) after the effective date of this AD. 

The FAA agrees. The FAA updated 

paragraph (h) of this AD to terminate the 

actions required by paragraph (g) of this 

AD. 

Request To Remove the Shim Check 

DAL requested that the FAA remove 

the shim check of the HMU/MEC idler 

adapter inserts in paragraph (g)(3)(ii) of 

the NPRM. DAL reasoned that 

performing this shim check is not 

necessary because the (g)(3)(ii) shim 

check is already required by paragraph 

(g)(3)(i) of this AD. Additionally, DAL 

stated that referencing paragraph (g)(1) 

of this AD to perform the shim check 

may confuse operators as paragraph 

(g)(1) of this AD includes the 

requirement to perform the shim check 

within 1,200 FHs after the effective date 

of this AD. Therefore, DAL suggested 

that paragraph (g)(3)(ii) of this AD 

should only address the requirement to 

perform the terminating action if the 

shim check fails. 

The FAA partially agrees. The FAA 

disagrees that paragraph (g)(3)(ii) of this 

AD should only address the requirement 

to perform the terminating action if the 

shim check of the HMU/MEC idler 

adapter inserts fails. After retorque of 

the bolts at each bolt location that failed 

the shim check, operators must perform 

the shim check again. If that shim check 

fails, then the terminating action is 

required. The FAA agrees that 

referencing paragraph (g)(1) of this AD 

may confuse operators whether to 

perform the shim check after the aircraft 

operated for some time or within 1,200 

FHs after the effective date of this AD. 

The FAA updated paragraph (g)(3)(ii) of 

this AD to reference the service 

information when performing the shim 

check rather than paragraph (g)(1) of 

this AD. 

Request To Update Credit for Previous 

Actions 

ANA, DAL, FedEx, and JAL requested 

updates to paragraph (i), Credit for 

Previous Actions, of this AD. ANA 

requested adding credit for the 

repetitive shim checks of the HMU/MEC 

idler adapter inserts and terminating 

action. DAL and FedEx requested credit 

for the terminating action. JAL 

requested credit for the repetitive shim 

checks of the HMU/MEC idler adapter 

inserts, retorque of the bolts that failed 

the shim check, and the terminating 

action. The commenters reasoned that 

GE CF6–80C2 SB 72–1577 R00, dated 

October 31, 2018 (GE CF6–80C2 SB 72– 

1577 R00), instructs the operator to 

perform the same tasks required by GE 

CF6–80C2 SB 72–1577 R01. Therefore, 

credit should be allowed for initial and 

repetitive shim checks of the HMU/MEC 

idler adapter inserts and the terminating 

action. 

The FAA agrees. The FAA reviewed 

GE CF6–80C2 SB 72–1577 R00, and 

determined that the instructions are 

consistent with GE CF6–80C2 SB 72– 

1577 R01. The FAA updated this AD to 

allow credit for the initial and repetitive 

shim checks of the HMU/MEC idler 

adapter inserts, retorque of the bolts that 

failed the shim check, and the 

terminating action, if performed before 

the effective date of this AD using GE 

CF6–80C2 SB 72–1577 R00. 

Request for an Alternate Marking Area 

ANA requested that the FAA approve 

an alternate marking area to show 

compliance with performing the 

terminating action of this AD. ANA 

stated that the marking areas indicated 

in GE CF6–80C2 SB 72–1577 R01, are 

difficult to access because many 

components are installed to AGB 

assembly. 

The FAA disagrees with approving an 

alternate marking area. The 

manufacturer provided two possible 

marking areas in GE CF6–80C2 SB 72– 

1577 R01, and confirmed the suitability 

of the areas. 

Request To Not Mandate the Marking 

Requirement 

DAL requested that the FAA not 

mandate the provision in GE CF6–80C2 

SB 72–1577 R01 to mark the HMU/MEC 

idler adapter to show compliance with 

the terminating actions of this AD. DAL 

reasoned that the NPRM did not 

propose to apply to all engines and 

therefore should not be required. 

The FAA disagrees. Marking the 

HMU/MEC idler adapter identifies if the 

terminating action of this AD has been 

completed. As noted in a previous 

comment response, the FAA revised the 

applicability of this AD to limit 

applicability to affected engines with 

certain HMU/MEC idler adapter P/Ns 

installed. Operators who determine that 

their engines are not applicable to this 

AD do not need to perform the 

terminating action or mark the HMU/ 

MEC idler adapter. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes and any other changes 

described previously, 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 

The FAA reviewed GE CF6–80C2 SB 

72–1577 R01, dated August 16, 2019. 

The SB describes procedures for 

performing shim checks of the HMU/ 

MEC idler adapter and for replacing the 

HMU/MEC idler adapter inserts. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 


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Federal Register / Vol. 86, No. 35 / Wednesday, February 24, 2021 / Rules and Regulations 11115 

course of business or by the means 

identified in ADDRESSES. 

Costs of Compliance 

The FAA estimates that this AD 

affects 555 engines installed on 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Shim check ..................................................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $47,175 

Protrusion check/pull-out test ......................... 4 work-hours × $85 per hour = $340 ............. 0 340 188,700 

The FAA estimates the following 

costs to do any necessary replacements 

that are required based on the results of 

the shim check. The agency has no way 

of determining the number of aircraft 

that might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace HMU/MEC idler adapter insert ....................... 4 work-hours × $85 per hour = $340 ........................... $50 $390 

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 adding 

the following new airworthiness 

directive: 

2021–03–02 General Electric Company: 

Amendment 39–21405; Docket No. 

FAA–2020–0371; Project Identifier AD– 

2019–00124–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 31, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CF6–80C2A1, CF6–80C2A2, 

CF6–80C2A3, CF6–80C2A5, CF6–80C2A5F, 

CF6–80C2A8, CF6–80C2B1, CF6–80C2B1F, 

CF6–80C2B2, CF6–80C2B2F, CF6–80C2B4, 

CF6–80C2B4F, CF6–80C2B5F, CF6–80C2B6, 

CF6–80C2B6F, CF6–80C2B6FA, CF6– 

80C2B7F, CF6–80C2B8F, and CF6–80C2D1F 

model turbofan engines that underwent an 

engine shop visit before November 1, 2018, 

and with accessory gearbox (AGB) adapter 

hydromechanical unit (HMU)/main engine 

control (MEC) idler adapter with part number 

(P/N) 9395M78G01, P/N 9395M78G02, P/N 

9395M78G04, P/N 9395M78G05, P/N 

9395M78G08, or P/N 9395M78G10, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7321, Fuel Control/Turbine Engines. 

(e) Unsafe Condition 

This AD was prompted by failure of the 

HMU/MEC on the AGB assembly. The FAA 

is issuing this AD to prevent failure of the 

HMU/MEC. The unsafe condition, if not 

addressed, could result in engine fire and 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Perform a shim check of the HMU/MEC 

idler adapter inserts using paragraph 3.B.(1) 

of GE CF6–80C2 Service Bulletin (SB) 72– 

1577 R01, dated August 16, 2019 (the SB), 

within 1,200 flight hours (FHs) after the 

effective date of this AD. 

(2) Thereafter, perform a repetitive shim 

check of the HMU/MEC idler adapter inserts 

using paragraph 3.B.(1) of the SB within 

every 1,200 FHs since the last shim check. 

(3) If any HMU/MEC idler adapter insert 

fails the shim check required by paragraph 

(g)(1) or (2) of this AD, perform the following 

before further flight: 

(i) Retorque the bolts at each bolt location 

that failed the shim check using paragraph 

3.B.(1)(c) of the SB. 

(ii) Perform the shim check again using 

paragraph 3.B.(1)(b) of the SB. If the shim 

check fails, perform the terminating action 

required by paragraph (h) of this AD. 


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11116 Federal Register / Vol. 86, No. 35 / Wednesday, February 24, 2021 / Rules and Regulations 

(h) Terminating Action 

As a terminating action to the requirements 

of paragraph (g) of this AD, perform the 

following: 

(1) Do a protrusion check at all eight bolt 

locations using paragraph 3.C.(3) of the SB. 

(2) Do a pull-out test at all eight bolt 

locations using paragraph 3.C.(4) of the SB. 

(3) If the inserts on the HMU/MEC idler 

adapter fail the protrusion check or pull-out 

test required by paragraph (h)(1) or (2) of this 

AD, replace the inserts using paragraph 

3.C.(5) of the SB. After replacement of the 

inserts is accomplished, the requirements of 

this AD have been met and no further action 

is required. 

(4) If the inserts on the HMU/MEC idler 

adapter pass both the protrusion check and 

the pull-out test required by paragraphs (h)(1) 

and (2) of this AD, the requirements of this 

AD have been met and no further action is 

required. 

(i) Credit for Previous Actions 

(1) You may take credit for any shim check 

of the HMU/MEC idler adapter required by 

paragraph (g) of this AD if you performed this 

shim check before the effective date of this 

AD using GE CF6–80C2 SB 72–1577 R00, 

dated October 31, 2018. 

(2) You may take credit for the terminating 

action required by paragraph (h) of this AD 

if you performed this action before the 

effective date of this AD using GE CF6–80C2 

SB 72–1577 R00, dated October 31, 2018. 

(j) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

case flanges, except separation of engine 

flanges solely for the purposes of 

transportation of the engine without 

subsequent maintenance, which does not 

constitute an engine shop visit. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 manager of the certification office, 

send it to the attention of the person 

identified in Related Information. You may 

email your request to: ANE-AD-AMOC@

faa.gov. 

(2) 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. 

(l) Related Information 

For more information about this AD, 

contact Kevin M. Clark, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7088; fax: (781) 238–7199; email: 

kevin.m.clark@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 the AD specifies otherwise. 

(i) General Electric Company (GE) CF6– 

80C2 Service Bulletin 72–1577 R01, dated 

August 16, 2019. 

(ii) [Reserved] 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

1 Neumann Way, Cincinnati, OH 45215; 

phone: (513) 552–3272; email: 

aviation.fleetsupport@ge.com. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (781) 238–7759. 

(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: fedreg.legal@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on January 21, 2021. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–03606 Filed 2–23–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0980; Product 

Identifier 2020–NM–094–AD; Amendment 

39–21414; AD 2021–03–11] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–02– 

21, which applied to all Dassault 

Aviation Model FALCON 2000 

airplanes. AD 2020–02–21 required 

revising the existing maintenance or 

inspection program, as applicable, to 

incorporate new or more restrictive 

airworthiness limitations. 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. This AD was 

prompted by a determination that new 

or more restrictive airworthiness 

limitations are necessary. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective March 31, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 31, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of March 18, 2020 (85 FR 

7860, February 12, 2020). 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

AD, contact the 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 this 

IBR material on the EASA website at 

https://ad.easa.europa.eu. For Dassault 

Aviation service information identified 

in this final rule, contact Dassault 

Falcon Jet Corporation, Teterboro 

Airport, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; internet https://

www.dassaultfalcon.com. 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–2020– 

0980. 

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– 

0980; 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: Tom 

Rodriguez, Aerospace Engineer, Large 

Aircraft Section, International 

Validation Branch, FAA, 2200 South 


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