Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 50239 

(g) Required Actions 

(1) Within 25 hours time-in-service after 

the effective date of this AD, replace relay 

panel assembly P/N SLS–075–002–107 with 

relay panel assembly P/N SLS–075–002–109 

by following the Accomplishment 

Instructions, paragraphs 1.a. through 3, of 

Bell Helicopter Alert Service Bulletin 505– 

17–04, dated December 6, 2017. 

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

not install relay panel assembly P/N SLS– 

075–002–107 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 Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 L’Enfant 

Plaza N SW, Washington, DC 20024; 

telephone (202) 267–9167; email hal.jensen@

faa.gov. 

(2) The subject of this AD is addressed in 

Transport Canada AD CF–2017–36, dated 

December 15, 2017. You may view the 

Transport Canada AD at https://

www.regulations.gov in Docket No. FAA– 

2021–0377. 

(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) Bell Helicopter Alert Service Bulletin 

505–17–04, dated December 6, 2017. 

(ii) [Reserved] 

(3) For Bell Helicopter service information 

identified in this AD, contact Bell Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4, Canada; telephone 

(450) 437–2862 or (800) 363–8023; fax (450) 

433–0272; email productsupport@

bellflight.com; or at https://

www.bellflight.com/support/contact-support. 

(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: fr.inspection@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on July 27, 2021. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–19251 Filed 9–7–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0607; Project 

Identifier MCAI–2020–01249–R; Amendment 

39–21666; AD 2021–16–04] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Leonardo S.p.a. Model AB412 and 

AB412 EP helicopters. This AD was 

prompted by a report of the failure of 

both inverters in-flight, leading to an 

autopilot disconnection. This AD 

requires a one-time inspection of the 

clearance between a certain protective 

grommet installed in the emergency bus 

interlock compartment and the cable 

assemblies passing through it, and 

depending on the finding, applicable 

corrective actions, 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 becomes effective 

September 23, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 23, 2021. 

The FAA must receive comments on 

this AD by October 25, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For EASA material incorporated by 

reference (IBR) in this AD, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

internet www.easa.europa.eu. You may 

find this IBR material on the EASA 

website at https://ad.easa.europa.eu. 

You may view the EASA 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 the EASA material at the 

FAA, call (817) 222–5110. The EASA 

material is also available at https://

www.regulations.gov by searching for 

and locating Docket FAA–2021–0607. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0607; 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 EASA AD, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

FOR FURTHER INFORMATION CONTACT: 

Jacob Fitch, Aerospace Engineer, COS 

Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–4130; email 

jacob.fitch@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0192, dated September 4, 2020 

(EASA AD 2020–0192) (also referred to 

as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for Leonardo S.p.a. (formerly 

AgustaWestland S.p.A., Agusta S.p.A., 

and Costruzioni Aeronautiche Giovanni 

Agusta) Model AB412 and AB412 EP 

helicopters, all serial numbers. 

This AD was prompted by a report of 

the failure of both inverters in-flight, 

leading to an autopilot disconnection. 

Subsequent inspection identified 


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50240 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 

chafing of a wire in the alternating 

current (AC) power system cable 

assembly, due to a protective grommet 

incorrectly installed in the emergency 

bus interlock compartment. Insufficient 

clearance between a protective grommet 

and the cable assemblies that pass 

through it could result in chafing of the 

cable assemblies. The FAA is issuing 

this AD to address incorrect installation 

of a protective grommet in the 

emergency bus interlock compartment 

and chafed wiring in the AC power 

system cable assembly. Chafed wiring in 

the AC power system cable assembly, if 

not addressed, could lead to a short in 

the AC power system, resulting in 

autopilot failure, possibly the loss of 

other avionics systems, increased pilot 

workload, and reduced control of the 

helicopter. 

Related IBR Material Under 1 CFR Part 

51 

EASA AD 2020–0192 specifies 

procedures for a one-time inspection of 

the clearance between a protective 

grommet installed in the emergency bus 

interlock compartment and the cable 

assemblies passing through it, and 

corrective actions. The corrective 

actions include replacing the existing 

grommet with a new grommet, 

inspecting the cable assemblies for 

damage (including chafing) and 

replacing affected cable assemblies, and 

reworking the bulkhead in the 

emergency bus interlock compartment. 

The rework of the bulkhead includes 

removing paint and primer, reworking 

the lightening hole, deburring the hole, 

applying chemical film protection, and 

priming all bare metal surfaces. 

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. 

FAA’s Determination 

These products have been approved 

by the aviation authority of another 

country, and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the State 

of Design Authority, the FAA has been 

notified of the unsafe condition 

described in the MCAI referenced 

above. The FAA is issuing this AD after 

evaluating all pertinent information and 

determining that the unsafe condition 

exists and is likely to exist or develop 

on other products of these same type 

designs. 

Requirements of This AD 

This AD requires accomplishing the 

actions specified in EASA AD 2020– 

0192, described previously, as 

incorporated by reference, except for 

any differences identified as exceptions 

in the regulatory text of this AD. 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA initially worked with 

Airbus and EASA to develop a process 

to use certain EASA ADs as the primary 

source of information for compliance 

with requirements for corresponding 

FAA ADs. The FAA has since 

coordinated with other manufacturers 

and civil aviation authorities (CAAs) to 

use this process. As a result, EASA AD 

2020–0192 is incorporated by reference 

in this FAA final rule. This AD 

therefore, requires compliance with 

EASA AD 2020–0192 in its entirety, 

through that incorporation, except for 

any differences identified as exceptions 

in the regulatory text of this AD. Using 

common terms that are the same as the 

heading of a particular section in the 

EASA AD does not mean that operators 

need comply only with that section. For 

example, where the AD requirement 

refers to ‘‘all required actions and 

compliance times,’’ compliance with 

this AD requirement is not limited to 

the section titled ‘‘Required Action(s) 

and Compliance Time(s)’’ in the EASA 

AD. Service information specified in 

EASA AD 2020–0192 that is required for 

compliance with EASA AD 2020–0192 

is available on the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0607. 

FAA’s Justification and Determination 

of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) authorizes agencies 

to dispense with notice and comment 

procedures for rules when the agency, 

for ‘‘good cause’’ finds that those 

procedures are ‘‘impracticable, 

unnecessary, or contrary to the public 

interest.’’ Under this section, an agency, 

upon finding good cause, may issue a 

final rule without providing notice and 

seeking comment prior to issuance. 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

There are currently no domestic 

operators of these products. Therefore, 

the FAA finds that notice and 

opportunity for prior public comment 

are unnecessary pursuant to 5 U.S.C. 

553(b)(3)(B). In addition, for the 

foregoing reason, the FAA finds that 

good cause exists pursuant to 5 U.S.C. 

553(d) for making this amendment 

effective in less than 30 days. 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2021–0607; Project Identifier MCAI– 

2020–01249–R’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the AD, 

explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this AD because of 

those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this AD. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this AD contain 

commercial or financial information 

that is customarily treated as private, 

that you actually treat as private, and 

that is relevant or responsive to this AD, 

it is important that you clearly designate 

the submitted comments as CBI. Please 

mark each page of your submission 

containing CBI as ‘‘PROPIN.’’ The FAA 

will treat such marked submissions as 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Jacob Fitch, Aerospace 

Engineer, COS Program Management 

Section, Operational Safety Branch, 

Compliance & Airworthiness Division, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

4130; email jacob.fitch@faa.gov. Any 

commentary that the FAA receives that 

is not specifically designated as CBI will 

be placed in the public docket for this 

rulemaking. 

Regulatory Flexibility Act (RFA) 

The requirements of the RFA do not 

apply when an agency finds good cause 

pursuant to 5 U.S.C. 553 to adopt a rule 

without prior notice and comment. 

Because the FAA has determined that it 


jbell on DSKJLSW7X2PROD with RULES
Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 50241 

has good cause to adopt this rule 

without notice and comment, RFA 

analysis is not required. 

Costs of Compliance 

There are no costs of compliance with 

this AD because there are no helicopters 

with this type certificate on the U.S. 

Registry. 

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 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 this regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

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: 

2021–16–04 Leonardo S.p.a.: Amendment 

39–21666; Docket No. FAA–2021–0607; 

Project Identifier MCAI–2020–01249–R. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 23, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Leonardo S.p.a. 

Model AB412 and AB412 EP helicopters, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2400, Electrical Power System. 

(e) Unsafe Condition 

This AD was prompted by a report of the 

failure of both inverters in-flight, leading to 

an autopilot disconnection. Subsequent 

inspection identified chafing of a wire in the 

alternating current (AC) power system cable 

assembly, due to a protective grommet 

incorrectly installed in the emergency bus 

interlock compartment. Insufficient clearance 

between a protective grommet and the cable 

assemblies that pass through it could result 

in damage (including chafing) to the cable 

assemblies. The FAA is issuing this AD to 

address incorrect installation of a protective 

grommet in the emergency bus interlock 

compartment and chafed wiring in the AC 

power system cable assembly. Chafed wiring 

in the AC power system cable assembly, if 

not addressed, could lead to a short in the 

AC power system, resulting in autopilot 

failure, possibly the loss of other avionics 

systems, increased pilot workload, and 

reduced 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 2020–0192, dated 

September 4, 2020 (EASA AD 2020–0192). 

(h) Exceptions to EASA AD 2020–0192 

(1) Where EASA AD 2020–0192 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where the service information 

referenced in EASA AD 2020–0192 specifies 

to discard a certain part, this AD requires 

removing that part from service. 

(3) Where the service information 

referenced in EASA AD 2020–0192 specifies 

to replace a certain part, this AD requires 

removing that part from service. 

(4) Where EASA AD 2020–0192 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

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

2020–0192 does not apply to this AD. 

(6) Where paragraph (2) of EASA AD 2020– 

0192 refers to ‘‘any discrepancy’’ for this AD, 

discrepancies include inadequate clearance 

between the protective grommet and AC 

power system cable assembly and damaged 

(chafed) AC power system cable assemblies. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2020–0192 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are prohibited. 

(k) 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 (l) 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. 

(l) Related Information 

For more information about this AD, 

contact Jacob Fitch, Aerospace Engineer, COS 

Program Management Section, Operational 

Safety Branch, Compliance & Airworthiness 

Division, FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222–4130; 

email jacob.fitch@faa.gov. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0192, dated September 4, 

2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0192, 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 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 


jbell on DSKJLSW7X2PROD with RULES
50242 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 

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

by searching for and locating Docket No. 

FAA 2021–0607. 

(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 July 21, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–19248 Filed 9–7–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0380; Project 

Identifier MCAI–2020–01683–R; Amendment 

39–21672; AD 2021–16–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Helicopters Deutschland GmbH 

Model EC135P1, EC135P2, EC135P2+, 

EC135P3, EC135T1, EC135T2, 

EC135T2+, and EC135T3 helicopters. 

This AD was prompted by a report that 

geometrical non-conformities were 

found in the root section of the tail rotor 

blade (TRB). This AD requires a onetime inspection (dimensional check) of 

the TRB for conformity and, depending 

on the findings, replacement of certain 

affected parts, as specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which is incorporated by 

reference. This AD also prohibits 

rework, repair, or modification of 

affected parts in the affected area of the 

TRB assembly root. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective October 13, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 13, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, 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 

IBR 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– 

0380. 

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– 

0380; 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: 

Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 1600 

Stewart Ave., Mail Stop: Room 410, 

Westbury, NY 11590; telephone 516– 

228–7330; email andrea.jimenez@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0282, dated December 17, 2020 

(EASA AD 2020–0282) (also referred to 

as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for Airbus Helicopters Deutschland 

GmbH Model EC135 P1, EC135 P2, 

EC135 P2+, EC135 P3, EC135 T1, EC135 

T2, EC135 T2+, EC135 T3, EC635 P2+, 

EC635 P3, EC635 T1, EC635 T2+, and 

EC635 T3 helicopters, all variants, all 

serial numbers. Model EC635 P2+, 

EC635 P3, EC635 T1, EC635 T2+, and 

EC635 T3 helicopters are not 

certificated by the FAA and are not 

included on the U.S. type certificate 

data sheet, except where the U.S. type 

certificate data sheet explains that the 

Model EC635T2+ helicopter having 

serial number 0858 was converted from 

Model EC635T2+ to Model EC135T2+. 

This AD, therefore, does not include 

Model EC635 P2+, EC635 P3, EC635 T1, 

EC635 T2+, and EC635 T3 helicopters in 

the applicability. 

Furthermore, although EASA AD 

2020–0282 applies to all Model EC135 

P1, EC135 P2, EC135 P2+, EC135 P3, 

EC135 T1, EC135 T2, EC135 T2+, and 

EC135 T3 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 

Deutschland GmbH Model EC135P1, 

EC135P2, EC135P2+, EC135P3, 

EC135T1, EC135T2, EC135T2+, and 

EC135T3 helicopters. The NPRM 

published in the Federal Register on 

June 1, 2021 (86 FR 29216). The NPRM 

was prompted by a report that during an 

investigation related to an accident on 

an Airbus Helicopters Model EC130B4 

helicopter, geometrical nonconformities were observed in the TRB 

root section. EASA issued AD 2020– 

0187, dated August 21, 2020, to address 

this issue on Model EC130B4 and 

EC130T2 helicopters and the FAA 

issued corresponding AD 2021–10–25, 

Amendment 39–21558 (86 FR 29176, 

June 1, 2021). The Airbus Helicopters 

Deutschland GmbH Model EC135P1, 

EC135P2, EC135P2+, EC135P3, 

EC135T1, EC135T2, EC135T2+, and 

EC135T3 helicopters have a similar 

design and production requirements to 

the affected Model EC130B4 helicopter, 

and an inspection of the affected parts 

detected geometrical non-conformities 

in some instances. The NPRM proposed 

to require a one-time inspection 

(dimensional check) of the TRB for 

conformity and, depending on the 

findings, replacement of certain affected 

parts, as specified in EASA AD 2020– 

0282. The NPRM also proposed to 

prohibit rework, repair, or modification 

of affected parts in the affected area of 

the TRB assembly root. 

The FAA is issuing this AD to address 

geometrical non-conformities in the 

TRB root section, which could lead to 

crack initiation and consequent blade 

failure, resulting in loss of control of the 

helicopter. See the MCAI for additional 

background information. 

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. 


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