Federal Register / Vol. 86, No. 127 / Wednesday, July 7, 2021 / Rules and Regulations 35601 

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: 

2021–13–05 Airbus Helicopters 

Deutschland GmbH: Amendment 39– 

21610; Docket No. FAA–2019–0293; 

Product Identifier 2017–SW–052–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 11, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Deutschland GmbH Model EC135P1, 

EC135P2, EC135P2+, EC135P3, EC135T1, 

EC135T2, EC135T2+, and EC135T3 

helicopters with serial number (S/N) up to 

and including 1254 (except S/N 1235), 

certificated in any category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, Tail Rotor Control System. 

(e) Unsafe Condition 

This AD defines the unsafe condition as 

interference between the tail rotor (T/R) 

control bearing connection close-tolerance 

bolt and the helicopter structure, which 

could lead to blockage of the pedal 

controlling the T/R thrust. This condition 

could result in loss of T/R control, prompting 

a forced landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 360 hours time-in-service, modify 

the T/R control by installing a Teflon washer 

and perform a functional test of the 

modification in accordance with the 

Accomplishment Instructions, paragraphs 

3.B.2 through 3.B.4.2., of Airbus Helicopters 

Alert Service Bulletin ASB EC135–67A–031, 

Revision 0, dated March 30, 2017. If, during 

the functional test, the clearance between the 

end of the close-tolerance bolt, castellated 

nut, and the lower stringer is less than 1.0 

mm, repair in accordance with FAAapproved procedures. 

(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 David Hatfield, Aviation Safety 

Engineer, Aircraft Systems Section, 

Technical Innovation Policy Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone 817–222–5110; email 

david.hatfield@faa.gov. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD 2017–0147, dated August 10, 

2017. You may view the EASA AD at https:// 

www.regulations.gov in Docket No. FAA– 

2019–0293. 

(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 EC135–67A–031, Revision 0, 

dated March 30, 2017. 

(ii) [Reserved] 

(3) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, 2701 North 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/ 

ibr-locations.html. 

Issued on June 10, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–14343 Filed 7–6–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0333; Project 

Identifier MCAI–2020–00252–R; Amendment 

39–21609; AD 2021–13–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Helicopters Model AS332C, 

AS332C1, AS332L, and AS332L1 

helicopters. This AD was prompted by 

a report of a yaw control failure that was 

the result of the disconnection of the tail 

rotor hub (TRH) pitch control rod from 

the tail rotor servo-control, which 

resulted from a seized TRH bearing. The 

TRH bearing had grease dissolving after 

contamination by leaked hydraulic fluid 

from the tail rotor servo-control that 

came through the TRH assembly boot. 

This AD requires repetitive inspections 

for hydraulic leaks, corrective actions if 

necessary, and an optional modification 

which constitutes terminating action, as 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 11, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 11, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 


khammond on DSKJM1Z7X2PROD with RULES
35602 Federal Register / Vol. 86, No. 127 / Wednesday, July 7, 2021 / Rules and Regulations 

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 

material on the EASA website at https:// 

ad.easa.europa.eu. You may view this 

material 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. It is also 

available in the AD docket on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0333. 

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– 

0333; 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: Hal 

Jensen, Aerospace Engineer, Operational 

Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 

L’Enfant Plaza N SW, Washington, DC 

20024; phone: (202) 267–9167; email: 

hal.jensen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0021, dated February 6, 2020 

(EASA AD 2020–0021) (also referred to 

as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for all Airbus Helicopters Model 

AS332C, AS332C1, AS332L, and 

AS332L1 helicopters. Although EASA 

AD 2020–0021 applies to all Model 

AS332C, AS332C1, AS332L, and 

AS332L1 helicopters, this AD applies to 

helicopters with an affected part 

installed instead. 

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 Helicopters 

Model AS332C, AS332C1, AS332L, and 

AS332L1 helicopters. The NPRM 

published in the Federal Register on 

April 22, 2021 (86 FR 21238). The 

NPRM was prompted by a report of a 

yaw control failure that was the result 

of the disconnection of the TRH pitch 

control rod from the tail rotor servocontrol, which resulted from a seized 

TRH bearing. The TRH bearing had 

grease dissolving after contamination by 

leaked hydraulic fluid from the tail rotor 

servo-control that came through the 

TRH assembly boot. The NPRM 

proposed to require repetitive 

inspections for hydraulic leaks, 

corrective actions if necessary, and an 

optional modification which constitutes 

terminating action, as specified in an 

EASA AD. 

The FAA is issuing this AD to address 

seized TRH bearings, which could 

reduce the effectiveness of the pitch 

control of the tail rotor system, possibly 

resulting in reduced yaw control of the 

helicopter. See the MCAI for additional 

background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

The FAA reviewed the relevant data 

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 2020–0021 describes 

procedures for repetitive inspections for 

hydraulic leaks, corrective actions if 

necessary (i.e., replacement of the pitch 

control rod bearing of the affected TRH 

assembly), and an optional modification 

(i.e., installation of a TRH assembly 

having certain part numbers) which 

constitutes terminating action. 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 10 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

1 work-hour × $85 per hour = $85 per inspection cycle .......... $0 $85 per inspection cycle ......... $850 per inspection cycle. 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of helicopters that might need 

these on-condition actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

6 work-hours × $85 per hour = $510 ...................................................................................................................... $509 $1,019 


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Federal Register / Vol. 86, No. 127 / Wednesday, July 7, 2021 / Rules and Regulations 35603 

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: 

2021–13–04 Airbus Helicopters: 

Amendment 39–21609; Docket No. 

FAA–2021–0333; Project Identifier 

MCAI–2020–00252–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 11, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model AS332C, AS332C1, AS332L, and 

AS332L1 helicopters, certificated in any 

category, with a tail rotor hub (TRH) 

assembly, having part number (P/N) 332A33– 

0001–05 or P/N 332A33–0001–06, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 6420, Tail rotor head. 

(e) Reason 

This AD was prompted by a report of a yaw 

control failure that was the result of a 

disconnection of the TRH pitch control rod 

from the tail rotor servo-control, which 

resulted from a seized TRH bearing. The TRH 

bearing had grease dissolving after 

contamination by leaked hydraulic fluid from 

the tail rotor servo-control that came through 

the TRH assembly boot. The FAA is issuing 

this AD to address seized TRH bearings, 

which could reduce the effectiveness of the 

pitch control of the tail rotor system, possibly 

resulting in reduced yaw control of the 

helicopter. 

(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 2020–0021, dated 

February 6, 2020 (EASA AD 2020–0021). 

(h) Exceptions to EASA AD 2020–0021 

(1) Where EASA AD 2020–0021 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

2020–0021 does not apply to this AD. 

(3) Where EASA AD 2020–0021 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(4) Where paragraph (1) of EASA AD 2020– 

0021 requires doing inspections ‘‘in 

accordance with the instructions of the ASB 

[alert service bulletin],’’ this AD requires 

accomplishing a visual inspection for any 

hydraulic fluid leak at the TRH boot. 

(5) Where EASA AD 2020–0021 refers to 

February 28, 2004 (the effective date of 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) AD F–2004–031, dated February 18, 

2004), this AD requires using the effective 

date of this AD. 

(i) 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 (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 L’Enfant 

Plaza N SW, Washington, DC 20024; phone: 

(202) 267–9167; email: hal.jensen@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 2020–0021, dated February 6, 

2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0021, 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 

material on the EASA website at https://

ad.easa.europa.eu. You may find this EASA 

AD on the EASA website at https://

ad.easa.europa.eu. 

(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. 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–2021–0333. 

(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. 2021–14340 Filed 7–6–21; 8:45 am] 

BILLING CODE 4910–13–P 


khammond on DSKJM1Z7X2PROD with RULES