85506 Federal Register / Vol. 85, No. 249 / Tuesday, December 29, 2020 / Rules and Regulations 

(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: 

■ a. Removing Airworthiness Directive 

(AD) 2016–07–14, Amendment 39– 

18459 (81 FR 21244, April 11, 2016), 

and 

■ b. Adding the following new AD: 

2020–26–15 Airbus SAS: Amendment 39– 

21370; Docket No. FAA–2020–0858; 

Project Identifier MCAI–2020–00949–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 2, 2021. 

(b) Affected ADs 

This AD replaces AD 2016–07–14, 

Amendment 39–18459 (81 FR 21244, April 

11, 2016) (AD 2016–07–14). 

(c) Applicability 

This AD applies to Airbus SAS airplanes 

specified in paragraphs (c)(1) through (3) of 

this AD, certificated in any category, as 

identified in European Union Aviation Safety 

Agency (EASA) AD 2020–0153, dated July 

10, 2020 (EASA AD 2020–0153). 

(1) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(2) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(3) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by fatigue testing 

that determined that fatigue damage could 

appear on clips, shear webs, and angles at 

certain rear fuselage sections and certain 

frames. The FAA is issuing this AD to 

address fatigue damage on the clips, shear 

webs, and angles, which could affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2020–0153. 

(h) Exceptions to EASA AD 2020–0153 

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

0153 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 Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3223; email Sanjay.Ralhan@

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 2020–0153, dated July 10, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0153, 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–2020–0858. 

(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: http://www.archives.gov/ 

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

Issued on December 11, 2020. 

Lance T. Gant, Director, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2020–28858 Filed 12–28–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0781; Product 

Identifier 2018–CE–045–AD; Amendment 

39–21369; AD 2020–26–14] 

RIN 2120–AA64 

Airworthiness Directives; Mitsubishi 

Heavy Industries, Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 75–16–20, 

which applied to all Mitsubishi Heavy 

Industries, Ltd., Model MU–2B, MU– 

2B–10, MU–2B–15, MU–2B–20, MU– 

2B–25, MU–2B–26, MU–2B–30, MU– 

2B–35, and MU–2B–36 airplanes. AD 

75–16–20 required repetitive 

inspections of the propeller pitch 

control (PPC) lever for security and 

proper rigging. This AD requires 


KHAMMOND on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 85, No. 249 / Tuesday, December 29, 2020 / Rules and Regulations 85507 

modification and repetitive inspections 

of the PPC lever linkage. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 2, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 2, 2021. 

ADDRESSES: For Mitsubishi service 

information identified in this final rule, 

contact Mitsubishi Heavy Industries 

America, Inc., c/o Turbine Aircraft 

Services, Inc., 4550 Jimmy Doolittle 

Drive, Addison, Texas 75001; phone: 

(972) 248–3108, ext. 209; fax: (972) 248– 

3321; website: https://mu-2aircraft.com. 

For Honeywell service information 

identified in this final AD, contact 

Honeywell International Inc., 111 S 34th 

Street, Phoenix, Arizona 85034–2802; 

phone: 855–808–6500; email: 

AeroTechSupport@honeywell.com; 

website: https://

aerospace.honeywell.com/en/services/ 

maintenance-and-monitoring. You may 

view this service information at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329– 

4148. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0781. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0781; 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: John 

Turner, Aviation Safety Engineer, Fort 

Worth ACO Branch, FAA, 10101 

Hillwood Parkway, Fort Worth, Texas 

76177; phone: (817) 222–4508; fax: (817) 

222–5245; email: johh.r.turner@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 75–16–20, 

Amendment 39–2294 (40 FR 31751, July 

29, 1975) (AD 75–16–20). AD 75–16–20 

applied to all Mitsubishi Heavy 

Industries, Ltd. (Mitsubishi) Models 

MU–2B, MU–2B–10, MU–2B–15, MU– 

2B–20, MU–2B–25, MU–2B–26, MU– 

2B–30, MU–2B–35, and MU–2B–36 

airplanes. The NPRM published in the 

Federal Register on August 25, 2020 (85 

FR 52281). The NPRM was prompted by 

reports of the PPC lever linkages 

disconnecting at the engine and 

Mitsubishi developing a secondary 

retention feature to secure the PPC. The 

NPRM was also prompted by Mitsubishi 

type certificating additional airplanes 

that are subject to the unsafe condition. 

In the NPRM, the FAA proposed to 

require installation of the secondary 

retention feature, repetitive inspections 

of the PPC lever linkage, and reporting 

inspection results to the FAA. 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety requires 

adoption of the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes, this AD is adopted as proposed 

in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Mitsubishi has issued MU–2 Service 

Recommendation No. 049/76–002, 

dated June 29, 2018, and MU–2 Service 

Recommendation No. 080, dated June 

29, 2018. This service information 

specifies procedures for installing a PPC 

lever secondary retention feature to 

secure the PPC lever. These documents 

are distinct since they apply to different 

airplane models and configurations. 

Mitsubishi has also issued MU–2 

Service Bulletin No. 106/76–004, dated 

February 24, 2016, and MU–2 Service 

Bulletin No. 244, dated December 25, 

2015. This service information specifies 

procedures for replacing the PPC lever 

clamping bolt. These documents are 

distinct since they apply to different 

airplane models and configurations. 

Honeywell International Inc. has 

issued Service Bulletin TPE331–72– 

2190, Revision 0, dated December 21, 

2011. The procedures in this service 

information include instructions for 

incorporating a threaded hole in the 

splined end of the shouldered shaft of 

the PPC assembly and re-identifying the 

shouldered shaft part number. The 

threaded hole is used to accommodate 

a secondary retention method to secure 

the PPC lever. 

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 ADDRESSES. 

Costs of Compliance 

The FAA estimates that this AD 

affects 260 airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD. The 

average labor rate is $85 per work hour. 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Modification ......................... 2 work-hours × $85 per hour = $170 $2 $172 ................................... $44,720. 

Repetitive inspections ......... 1 work-hour × $85 per hour = $85 

per inspection cycle.

0 $85 per inspection cycle .... $22,100 per inspection cycle. 

The FAA estimates the following 

costs to do any necessary on-condition 

actions for the incorporation of the 

threaded hole and reporting 

requirement. The FAA has no way of 

determining the number of aircraft that 

might need these on-condition actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Incorporation of threaded hole ...................................... 4 work-hours × $85 per hour = $340 .......................... $1,000 $1,340 


KHAMMOND on DSKJM1Z7X2PROD with RULES
85508 Federal Register / Vol. 85, No. 249 / Tuesday, December 29, 2020 / Rules and Regulations 

ON-CONDITION COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

Reporting ....................................................................... 1 work-hour × $85 per hour = $85 .............................. 0 85 

If the PPC lever detaches, the 

necessary corrective actions could vary 

significantly from airplane to airplane. 

The FAA has received no definitive data 

that would enable estimating the cost to 

install the PPC lever on each airplane or 

the number of airplanes that may 

require this action. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a currently valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to be 

approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, completing and reviewing 

the collection of information. All 

responses to this collection of 

information are mandatory. Send 

comments regarding this burden 

estimate or any other aspect of this 

collection of information, including 

suggestions for reducing this burden to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701, General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

The FAA has determined that this AD 

will not have federalism implications 

under Executive Order 13132. This AD 

will not have a substantial direct effect 

on the States, on the relationship 

between the national government and 

the States, or on the distribution of 

power and responsibilities among the 

various levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

75–16–20, Amendment 39–2294 (40 FR 

31751, July 29, 1975); and 

■ b. Adding the following new 

airworthiness directive: 

2020–26–14 Mitsubishi Heavy Industries, 

Ltd.: Amendment 39–21369; Docket No. 

FAA–2020–0781; Product Identifier 

2018–CE–045–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 2, 2021. 

(b) Affected ADs 

This AD replaces AD 75–16–20, 

Amendment 39–2294 (40 FR 31751, July 29, 

1975) (AD 75–16–20). 

(c) Applicability 

This AD applies to all Mitsubishi Heavy 

Industries, Ltd. (Mitsubishi) Models MU–2B, 

MU–2B–10, MU–2B–15, MU–2B–20, MU– 

2B–25, MU–2B–26, MU–2B–26A, MU–2B– 

30, MU–2B–35, MU–2B–36, MU–2B–36A, 

MU–2B–40, and MU–2B–60 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 61: Propellers. 

(e) Reason 

This AD was prompted by propeller pitch 

control (PPC) lever linkages disconnecting at 

the engine. The FAA is issuing this AD to 

address the PPC lever linkage from 

disconnecting at the engine, which could 

lead to the inability to control the propeller 

pitch with the power lever in the cockpit and 

consequent loss of control of the engine 

power settings. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

(1) For all airplanes except Model MU–2B 

and MU–2B–10 airplanes: Within 100 hours 

time-in-service (TIS) after the effective date 

of this AD or within 12 months after the 

effective date of this AD, whichever occurs 

first, modify the PPC lever linkage as 

specified in paragraphs (g)(1)(i) through (iii) 

of this AD, as applicable. 

(i) Replace the PPC lever clamping bolt in 

accordance with the Accomplishment 

Instructions, section 2, of Mitsubishi MU–2 

Service Bulletin No. 106/76–004, dated 

February 24, 2016, or Mitsubishi MU–2 

Service Bulletin No. 244, dated December 25, 

2015, as applicable to your model airplane. 

(ii) For airplanes without a threaded hole 

in the splined end of the shouldered shaft of 

the PPC assembly, incorporate a threaded 

hole in accordance with the Accomplishment 

Instructions, paragraph 3.C.(3)(d)2, of 

Honeywell International Inc. Service Bulletin 

TPE331–72–2190, Revision 0, dated 

December 21, 2011. 

(iii) Install a secondary retention feature in 

the threaded end of the PPC input shaft in 

accordance with the Accomplishment 

Instructions, section 2, of Mitsubishi MU–2 

Service Recommendation No. 049/76–002, 

dated June 29, 2018, or Mitsubishi MU–2 

Service Recommendation No. 080, dated June 

29, 2018, as applicable to your model 

airplane. 

(2) For Model MU–2B and MU–2B–10 

airplanes: Within 100 hours TIS after the 

effective date of this AD or within 12 months 

after the effective date of this AD, whichever 


KHAMMOND on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 85, No. 249 / Tuesday, December 29, 2020 / Rules and Regulations 85509 

occurs first, replace the PPC lever clamping 

bolt and install a secondary retention feature 

in the threaded end of the PPC input shaft 

using a method approved by the Manager of 

the Fort Worth ACO Branch, FAA. The 

Manager’s approval letter must specifically 

refer to this AD. 

(h) Repetitive Inspections and Reporting 

Within 100 hours TIS after replacing the 

bolt and installing a secondary retention 

feature as required by paragraph (g) of this 

AD and thereafter at intervals not to exceed 

100 hours TIS, inspect the security of the 

PPC lever by pulling the PPC lever upward 

by hand to ensure it does not detach from the 

PPC input shaft. If the PPC lever detaches, do 

the following. 

(1) Before further flight, install the PPC 

lever using a method approved by the 

Manager of the Fort Worth ACO Branch, 

FAA. The Manager’s approval letter must 

specifically refer to this AD. 

(2) Within 30 days after the PPC lever 

detachment or within 30 days after the 

effective date of this AD, whichever occurs 

later, report the results of the inspection, 

including airplane model and serial number, 

to the FAA representative identified in 

paragraph (l)(2) of this AD. 

(i) Special Flight Permit 

(1) Special flight permits may be issued for 

the purpose of operating the airplane to a 

location where the requirements of paragraph 

(g) of this AD can be performed with the 

following limitations: Flights must not carry 

passengers, must operate in daytime visual 

meteorological conditions only, and must not 

operate in areas of known turbulence. 

(2) Special flight permits may be issued for 

the purpose of operating the airplane to a 

location where the requirements of paragraph 

(h) of this AD may be performed without 

limitations. 

(j) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 1 hour per 

response, including the time for reviewing 

instructions, searching existing data sources, 

gathering and maintaining the data needed, 

and completing and reviewing the collection 

of information. All responses to this 

collection of information are mandatory as 

required by this AD; the nature and extent of 

confidentiality to be provided, if any. Send 

comments regarding this burden estimate or 

any other aspect of this collection of 

information, including suggestions for 

reducing this burden to: Information 

Collection Clearance Officer, Federal 

Aviation Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Fort Worth ACO 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 Fort Worth ACO 

Branch, send it to the attention of the person 

identified in paragraph (l)(2) of this AD. 

(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 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Japan 

Civil Aviation Bureau (JCAB) AD No. TCD– 

8678–2016, dated February 5, 2016, for 

related information. This MCAI may be 

found in the AD docket at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–0781. 

(2) For more information about this AD, 

contact John Turner, Aviation Safety 

Engineer, Fort Worth ACO Branch, FAA, 

10101 Hillwood Parkway, Fort Worth, Texas 

76177; phone: (817) 222–4508; fax: (817) 

222–5245; email: johh.r.turner@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) Honeywell International Inc. Service 

Bulletin TPE331–72–2190, Revision 0, dated 

December 21, 2011. 

(ii) Mitsubishi MU–2 Service Bulletin No. 

244, dated December 25, 2015. 

(iii) Mitsubishi MU–2 Service Bulletin No. 

106/76–004, dated February 24, 2016. 

(iv) Mitsubishi MU–2 Service 

Recommendation No. 049/76–002, dated 

June 29, 2018. 

(v) Mitsubishi MU–2 Service 

Recommendation No. 080, dated June 29, 

2018. 

(3) For Mitsubishi service information 

identified in this AD, contact Mitsubishi 

Heavy Industries America, Inc., c/o Turbine 

Aircraft Services, Inc., 4550 Jimmy Doolittle 

Drive, Addison, Texas 75001; phone: (972) 

248–3108, ext. 209; fax: (972) 248–3321; 

website: https://mu-2aircraft.com. 

(4) For Honeywell service information 

identified in this AD, contact Honeywell 

International Inc., 111 S 34th Street, Phoenix, 

Arizona 85034–2802; phone: 855–808–6500; 

email: AeroTechSupport@honeywell.com; 

website: https://aerospace.honeywell.com/ 

en/services/maintenance-and-monitoring. 

(5) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

(6) 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 December 11, 2020. 

Lance T. Gant, Director, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2020–28855 Filed 12–28–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2020–0750; Airspace 

Docket No. 20–ACE–17] 

RIN 2120–AA66 

Amendment of the Class E Airspace; 

Trenton, MO 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends the Class 

E airspace extending upward from 700 

feet above the surface at Trenton 

Municipal Airport, Trenton, MO. This 

action is the result of an airspace review 

caused by the decommissioning of the 

Trenton non-directional beacon (NDB) 

navigation information to the 

instrument procedures at this airport. 

The geographic coordinates of the 

airport are also being updated to 

coincide with the FAA’s aeronautical 

database. Airspace redesign is necessary 

for the safety and management of 

instrument flight rules (IFR) operations 

at this airport. 

DATES: Effective 0901 UTC, February 25, 

2021. Director of the Federal Register 

approves this incorporation by reference 

action under Title 1 Code of Federal 

Regulations part 51, subject to the 

annual revision of FAA Order 7400.11 

and publication of conforming 

amendments. 

ADDRESSES: FAA Order 7400.11E, 

Airspace Designations and Reporting 

Points, and subsequent amendments can 

be viewed online at https://

www.faa.gov/air_traffic/publications/. 

For further information, you can contact 

the Airspace Policy Group, Federal 

Aviation Administration, 800 

Independence Avenue SW, Washington, 

DC 20591; telephone: (202) 267–8783. 

The Order is also available for 

inspection at the National Archives and 


KHAMMOND on DSKJM1Z7X2PROD with RULES