This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

29483 

Vol. 86, No. 104 

Wednesday, June 2, 2021 

DEPARTMENT OF THE TREASURY 

2 CFR Part 1000 

Uniform Administrative Requirements, 

Cost Principles, and Audit 

Requirements for Federal Awards; 

Technical Amendment 

AGENCY: Department of the Treasury. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: This technical amendment 

makes nonsubstantive corrections in the 

Department’s conforming regulations 

under the Uniform Administrative 

Requirements, Cost Principles, and 

Audit Requirements for Federal Awards. 

DATES: Effective June 2, 2021. 

FOR FURTHER INFORMATION CONTACT: 

Blossom Butcher-Sumner, Attorney 

Advisor (Banking & Finance), Office of 

the General Counsel, 202–622–0451. 

SUPPLEMENTARY INFORMATION: On 

January 27, 2016 (81 FR 4573), the 

Department adopted as a final rule the 

Office of Management and Budget’s 

(OMB) regulations for all Federal awardmaking agencies, the Uniform 

Administrative Requirements, Cost 

Principles, and Audit Requirements for 

Federal Awards (Uniform Guidance), 

with minor deviations to make the 

Uniform Guidance consistent with 

existing Department policy. Treasury’s 

regulations are codified at 2 CFR part 

1000. 

On August 13, 2020 (85 FR 49506), 

OMB adopted revisions to the Uniform 

Guidance. Among other things, in the 

final rule, OMB redesignated 2 CFR 

200.336 as 2 CFR 200.337. This change 

results in an incorrect section 

numeration and cross-reference in the 

Department’s regulations that is 

corrected in this technical amendment. 

List of Subjects in 2 CFR Part 1000 

Accounting, Administrative practice 

and procedure, Auditing, Audit 

requirements, Cost principles, 

Cooperative agreements, Grant 

programs, Reporting and recordkeeping 

requirements. 

Accordingly, the Treasury Department 

amends 2 CFR part 1000 as follows: 

Title 2—Grants and Agreements 

Chapter X—Department of Treasury 

PART 1000—UNIFORM 

ADMINISTRATIVE REQUIREMENTS, 

COST PRINCIPLES, AND AUDIT 

REQUIREMENTS FOR FEDERAL 

AWARDS 

■ 1. The authority citation for part 1000 

continues to read as follows: 

Authority: 5 U.S.C. 301; 31 U.S.C. 301; 2 

CFR part 200. 

§ 1000.336 [Redesignated as § 1000.337] 

■ 2. Redesignate § 1000.336 as 

§ 1000.337 and revise it to read as 

follows: 

§ 1000.337 Access to records. 

The right of access under 2 CFR 

200.337 shall not extend to client 

information held by attorneys or 

federally authorized tax practitioners 

under the Low Income Taxpayer Clinic 

program. 

Blossom Butcher-Sumner, 

Attorney Advisor (Banking & Finance). 

[FR Doc. 2021–11574 Filed 6–1–21; 8:45 am] 

BILLING CODE 4810–AK–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0135; Project 

Identifier MCAI–2020–01044–R; Amendment 

39–21554; AD 2021–10–21] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–07– 

07 for various Airbus Helicopters 

Deutschland GmbH (Airbus Helicopters) 

Model MBB–BK117 and Model BO–105 

helicopters. AD 2019–07–07 required 

removing certain part numbered 

swashplate bellows (bellows) from 

service, cleaning and inspecting certain 

parts, and depending on the inspection 

results removing certain parts from 

service, applying torque, and 

repetitively inspecting the swashplate 

assembly (swashplate). This AD retains 

certain requirements of AD 2019–07–07, 

expands the installation prohibition, 

adds additional inspections, and 

updates the applicable service 

information. The FAA is issuing this AD 

to address an unsafe condition on these 

products. 

DATES: This AD is effective July 7, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 7, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at https:// 

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 

this service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. For more information on the 

availability of this material at the FAA, 

call (817) 222–5110. It is also available 

on the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0135. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov in Docket No. 

FAA–2021–0135; 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 

AD, the European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD, any service 

information that is incorporated by 

reference, any comments received, and 

other information. The street 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: Matt 

Fuller, AD Program Manager, 

Operational Safety Branch, 

Airworthiness Products Section, 

General Aviation & Rotorcraft Unit, 


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29484 Federal Register / Vol. 86, No. 104 / Wednesday, June 2, 2021 / Rules and Regulations 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

5110; email Matthew.Fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–07–07, 

Amendment 39–19618 (84 FR 16394, 

April 19, 2019) (AD 2019–07–07). AD 

2019–07–07 applied to Airbus 

Helicopters Model BO–105A, BO–105C, 

BO–105S, BO105LS A–3, MBB–BK 

117A–1, MBB–BK 117A–3, MBB–BK 

117A–4, MBB–BK 117B–1, MBB–BK 

117B–2, MBB–BK 117C–1, MBB–BK 

117C–2, and MBB–BK 117D–2 

helicopters. The NPRM published in the 

Federal Register on March 10, 2021 (86 

FR 13665). The NPRM proposed to 

require, within 50 hours time-in-service, 

removing the affected bellows from the 

swashplate, cleaning and inspecting the 

support tube for scratches, and 

depending on the inspection results 

reworking the cylindrical area. The 

NPRM proposed to require inspecting 

the clamp for corrosion, damage, and 

incorrect installation, and depending on 

the inspection results, removing the 

clamp from service or reinstalling the 

clamp correctly and applying a torque. 

The NPRM also proposed to require 

inspecting each ball bearing for 

corrosion, and depending on the 

inspection results, removing each ball 

bearing from service. The NPRM 

proposed to require inspecting the 

deflection ring for foreign objects by 

removing the lockwire, screws, and the 

outer deflection ring and removing any 

foreign objects. 

Additionally, the NPRM proposed to 

require, within 400 hours TIS, 

inspecting the swashplate for foreign 

objects and excessive bearing rolling 

friction. Finally, the NPRM proposed to 

prohibit installing a bellows P/N 105– 

10113.05, P/N 4619305044, P/N 

4638305043, or P/N B623M20X2240, or 

a gearbox with a bellows P/N 105– 

10113.05, P/N 4619305044, or P/N 

4638305043 on any helicopter. 

EASA AD 2016–0142, dated July 19, 

2016, which was revised to EASA AD 

2016–0142R1, dated April 12, 2018, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Model MBB–BK117 A–1, 

MBB–BK117 A–3, MBB–BK117 A–4, 

MBB–BK117 B–1, MBB–BK117 B–2, 

MBB–BK117 C–1, MBB–BK117 C–2, 

and MBB–BK117 C–2e helicopters, all 

serial numbers (S/Ns), and Model 

BO105 A, BO105 C, BO105 D, BO105 S, 

and BO105 LS A–3 helicopters, all 

variants, all S/Ns. EASA advises of 

several reports of a lower clamp found 

missing from the bellows and damaging 

the swashplate bearing ring before 

becoming detached. EASA states that an 

investigation showed that overtorqueing can damage the clamp, which 

may have caused the clamp to become 

loose and detach. EASA further advises 

that this condition, if not addressed, 

could result a detached clamp, which 

could damage the swashplate and pitch 

link or strike the tail rotor, resulting in 

loss of control of the helicopter. 

Accordingly, EASA AD 2016–0142R1 

requires removing the bellows, and 

performing modifications, inspections, 

and corrective actions in accordance 

with the applicable service information 

for your helicopter. EASA AD 2016– 

0142R1 also prohibits the installation of 

certain part-numbered bellows or any 

gearbox with certain part-numbered 

bellows on any helicopter. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or the determination of the 

costs. 

Conclusion 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA of the unsafe condition described 

in its AD. The FAA reviewed the 

relevant data 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 helicopters. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Airbus Helicopters 

Alert Service Bulletin ASB (ASB) 

BO105–40A–107 for Model BO105Cseries, D-series and S-series helicopters; 

ASB BO105 LS–40A–12 for Model BO– 

105LS A–3 helicopters; ASB MBB– 

BK117–40A–115 for Model MBB–BK 

117 A–1, MBB–BK 117 A–3, MBB–BK 

117 A–4, MBB–BK 117 B–1, MBB–BK 

117 B–2, and MBB–BK 117 C–1 

helicopters; and ASB MBB–BK117 

C–2–62A–007 for Model MBB–BK 117 

C–2 helicopters, each Revision 5 and 

dated July 25, 2017. The FAA also 

reviewed Airbus Helicopters ASB MBB– 

BK117 D–2–62A–003, Revision 3, dated 

July 25, 2017, for Model MBB–BK 117 

D–2 helicopters. This service 

information specifies removing the 

bellows and repetitively inspecting the 

swashplate. 

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. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires compliance 

within different time intervals for some 

actions than what this AD requires. The 

EASA AD allows a non-cumulative 

tolerance of 10 percent that may be 

applied to the compliance times, and 

this AD does not. This AD applies to 

Model MBB–BK 117D–2 helicopters 

while the EASA AD does not. The 

EASA AD applies to Model BO–105D 

helicopters, while this AD does not. The 

EASA AD requires reporting corrosion 

to Airbus Helicopters while this AD 

does not. 

Costs of Compliance 

The FAA estimates that this AD 

affects 211 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates that operators may incur 

the following costs in order to comply 

with this AD. 

Inspecting the swashplate assembly 

takes about 3 work-hours for an 

estimated cost of $255 per helicopter 

and $53,805 for the U.S. fleet per 

inspection cycle. 

Repairing a scratched support tube 

takes about 3 work-hours for an 

estimated cost of $255 per helicopter. 

Replacing a corroded or damaged 

clamp takes about 2 work-hours and 

parts cost about $8 for a cost of $178 per 

helicopter. 

Replacing corroded ball bearings takes 

about 4 work-hours and parts cost about 

$3,000 for a cost of $3,340 per 

helicopter. 

Removing foreign objects from the 

outer deflection ring takes about 2 workhours for an estimated cost of $170 per 

helicopter. 

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 


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Federal Register / Vol. 86, No. 104 / Wednesday, June 2, 2021 / Rules and Regulations 29485 

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. 

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) 2019–07–07, Amendment 39– 

19618 (84 FR 16394, April 19, 2019); 

and 

■ b. Adding the following new AD: 

2021–10–21 Airbus Helicopters 

Deutschland GmbH: Amendment 39– 

21554; Docket No. FAA–2021–0135; 

Project Identifier MCAI–2020–01044–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 7, 2021. 

(b) Affected ADs 

This AD replaces AD 2019–07–07, 

Amendment 39–19618 (84 FR 16394, April 

19, 2019) (2019–07–07). 

(c) Applicability 

This AD applies to Airbus Helicopters 

Deutschland GmbH Model BO–105A, BO– 

105C, BO–105S, BO105LS A–3, MBB–BK 

117A–1, MBB–BK 117A–3, MBB–BK 117A– 

4, MBB–BK 117B–1, MBB–BK 117B–2, MBB– 

BK 117C–1, MBB–BK 117C–2, and MBB–BK 

117D–2 helicopters, certificated in any 

category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200, Main Rotor System. 

(e) Unsafe Condition 

This AD was prompted by a lower clamp 

found missing from the swashplate bellows 

(bellows) and damaging the swashplate 

bearing ring before becoming detached. The 

FAA is issuing this AD to prevent a loose 

bellows clamp. The unsafe condition, if not 

addressed, could result in loss of the bellows, 

contact of the bellows with the main rotor 

blades, main rotor mast, and tail rotor, and 

subsequent loss of helicopter control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 50 hours time-in-service (TIS) 

after the effective date of this AD: 

(i) Remove from service bellows part 

number (P/N) 105–10113.05, P/N 

4638305043, P/N 4619305044, or P/N 

B623M20X2240 from the swashplate 

assembly (swashplate). 

(ii) Clean and inspect the support tube for 

scratches as depicted in Detail 11, Figure 6 

of Airbus Helicopters Alert Service Bulletin 

ASB (ASB) BO105–40A–107 (ASB BO105– 

40A–107); or Detail 11, Figure 5 of ASB 

BO105 LS–40A–12 (ASB BO105 LS 40A–12); 

or Detail 11, Figure 5 of ASB MBB–BK117– 

40A–115, (ASB MBB–BK117–40A–115); or 

Detail 11, Figure 5 of ASB MBB–BK117 C– 

2–62A–007 (ASB MBB–BK117 C–2–62A– 

007), each Revision 5 and dated July 25, 

2017; or Detail 11, Figure 5 of ASB MBB– 

BK117 D–2–62A–003, Revision 3, dated July 

25, 2017 (ASB MBB–BK117 D–2–62A–003); 

as applicable to your model helicopter. If 

there are scratches on the support tube, 

before further flight, rework the cylindrical 

area to a max depth of 0.1 mm with a 

polishing cloth #400 or equivalent polishing 

cloth. The reworked area must not exceed 10 

mm in width or 3 cm2 in area, the minimum 

separation between any adjacent reworked 

areas must be 30 mm, and total reworked 

areas must not exceed 10 percent of the 

cylindrical area. 

(iii) Inspect the clamp for corrosion and 

correct installation. 

Note 1 to paragraph (g)(1)(iii): A figure of 

the clamp is depicted in Detail 9, Figure 6 

of ASB BO105–40A–107; or Detail 9, Figure 

5 of ASB BO105 LS–40A–12, ASB MBB– 

BK117–40A–115, or ASB MBB–BK117 C–2– 

62A–007; or Detail 9, Figure 5 of ASB MBB– 

BK117 D–2–62A–003; as applicable to your 

model helicopter. 

(A) If there is corrosion on the clamp, 

before further flight remove the clamp from 

service. 

(B) If the clamp is incorrectly installed, 

before further flight install the clamp 

correctly on the shield as depicted in Detail 

10, Figure 6 of ASB BO105–40A–107; or 

Detail 10, Figure 5 of ASB BO105 LS–40A– 

12, ASB MBB–BK117–40A–115, or ASB 

MBB–BK117 C–2–62A–007; or Detail 10, 

Figure 5 of ASB MBB–BK117 D–2–62A–003; 

as applicable to your model helicopter. 

(C) Apply a torque between 0.5 Nm and 0.7 

Nm to the screw and install lockwire as 

depicted in Detail 8, Figure 6 of ASB BO105– 

40A–107; or Detail 8, Figure 5 of ASB BO105 

LS–40A–12, ASB MBB–BK117–40A–115, or 

ASB MBB–BK117 C–2–62A–007; or Detail 8, 

Figure 5 of ASB MBB–BK117 D–2–62A–003; 

as applicable to your model helicopter. 

(iv) Inspect each ball bearing for corrosion. 

If there is corrosion on any ball bearing, 

before further flight, remove the ball bearing 

from service. 

(v) Inspect the area under the deflection 

ring for foreign objects by removing the lock 

wire, removing the screws, and removing the 

outer deflection ring. If there are any foreign 

objects, remove the foreign objects with a 

lint-free cloth. 

(2) Within 400 hours TIS after the effective 

date of this AD, after complying with the 

actions in paragraph (g)(1) of this AD, and 

thereafter at intervals not to exceed 400 hours 

TIS, inspect the swashplate by following the 

Accomplishment Instructions, paragraph 

3.B.4 of ASB BO105–40A–107; or paragraph 

3.B.3 of ASB BO105 LS–40A–12, ASB MBB– 

BK117–40A–115, ASB MBB–BK117 C–2– 

62A–007, or ASB MBB–BK117 D–2–62A– 

003; as applicable to your model helicopter. 

(3) After May 24, 2019 (the effective date 

of AD 2019–07–07), do not install a bellows 

P/N 105–10113.05, P/N 4619305044, or P/N 

4638305043, or a gearbox with a bellows 

P/N 105–10113.05, P/N 4619305044, or P/N 

4638305043 on any helicopter. 

(4) As of the effective date of this AD, do 

not install a bellows P/N B623M20X2240 on 

any helicopter. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, 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 manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (i)(1) of this AD. 

Information may be emailed to: 9-AVS-AIR730-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. 

(i) Related Information 

(1) For more information about this AD, 

contact Matt Fuller, AD Program Manager, 

Operational Safety Branch, Airworthiness 

Products Section, General Aviation & 

Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 222– 

5110; email 9-AVS-AIR-730-AMOC@faa.gov. 


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29486 Federal Register / Vol. 86, No. 104 / Wednesday, June 2, 2021 / Rules and Regulations 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD 2016–0142R1, dated April 12, 

2018. You may view the EASA AD on the 

internet at https://www.regulations.gov in 

Docket No. FAA–2021–0135. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Airbus Helicopters Alert Service 

Bulletin ASB (ASB) BO105–40A–107, 

Revision 5, dated July 25, 2017. 

(ii) Airbus Helicopters ASB BO105 LS– 

40A–12, Revision 5, dated July 25, 2017. 

(iii) Airbus Helicopters ASB MBB–BK117– 

40A–115, Revision 5, dated July 25, 2017. 

(iv) Airbus Helicopters ASB MBB–BK117 

C–2–62A–007, Revision 5, dated July 25, 

2017. 

(v) Airbus Helicopters ASB MBB–BK117 

D–2–62A–003, Revision 3, dated July 25, 

2017. 

(3) For service information identified in 

this AD, contact Airbus Helicopters, 2701 N 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at https://

www.airbus.com/helicopters/services/ 

technical-support.html. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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/ibrlocations.html. 

Issued on Issued on May 5, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–11444 Filed 6–1–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0223; Project 

Identifier AD–2020–00539–A; Amendment 

39–21550; AD 2021–10–17] 

RIN 2120–AA64 

Airworthiness Directives; Mooney 

International Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Mooney International Corporation 

(Mooney) Model M20V airplanes. This 

AD was prompted by reports of short 

circuit and arcing of the alternator main 

power cable in the engine compartment. 

This condition, if unaddressed, could 

result in a fire hazard, loss of engine 

thrust control, and reduced control of 

the airplane. This AD requires 

inspecting the alternator main power 

cable and the exhaust crossover tube for 

damage, replacing damaged parts as 

necessary, and installing an additional 

alternator cable clamp. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective July 7, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 7, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Mooney International Corporation, 165 

Al Mooney Road, North Kerrville, TX 

78028; phone: (800) 456–3033; email: 

support@mooney.com. You may view 

this service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 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 2021–0223. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0223; 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: 

Jacob Fitch, Aviation Safety Engineer, 

Fort Worth ACO Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

phone: (817) 222–4130; fax: (817) 222– 

5245; email: jacob.fitch@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 serial-numbered 

Mooney Model M20V airplanes. The 

NPRM published in the Federal 

Register on March 9, 2021 (86 FR 13502; 

corrected March 17, 2021, 86 FR 14554). 

The NPRM was prompted by reports of 

short circuit and arcing of the alternator 

main power cable in the engine 

compartment. Mooney determined the 

alternator main power cable was 

incorrectly positioned with slack in the 

cable and allowed contact between the 

alternator main power cable and 

turbocharger right-hand (RH) exhaust 

crossover tube. In one instance, this 

contact caused arcing of the alternator 

main power cable and created a hole in 

the RH exhaust crossover tube, which 

may result in a fire hazard. A damaged 

crossover tube may also decrease 

effectiveness of the turbochargers and 

cause complete loss of engine power at 

higher altitudes (above 9,000 ft. above 

sea level). In the NPRM, the FAA 

proposed to require inspecting the 

alternator main power cable and the 

exhaust crossover tube and modifying 

the alternator main power cable routing 

by installing an additional alternator 

cable clamp, part number (P/N) 

MS21919WCJ6. This condition, if not 

addressed, could result in an inflight 

fire and loss of engine thrust control, 

which may lead to reduced control of 

the airplane. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive 

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 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. This AD is adopted as 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Mooney 

International Corporation Service 

Bulletin M20–340C, dated February 14, 

2020. The service information specifies 

inspecting the alternator main power 

cable and the exhaust crossover tube for 

damage and replacing damaged parts as 

necessary. The service information also 

contains procedures for modifying the 

alternator main power cable routing by 

installing an additional alternator cable 

clamp, P/N MS21919WCJ6. 


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