Federal Register / Vol. 87, No. 12 / Wednesday, January 19, 2022 / Rules and Regulations 2699 

Note 1 to paragraph (h): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Multi Operator 

Message MOM–MOM–22–0001–01B, dated 

January 3, 2022, and Boeing Flight Crew 

Operations Manual Bulletin TBC–119, 

‘‘Radio Altimeter Anomalies due to 5G CBand Wireless Broadband Interference in the 

United States,’’ dated January 5, 2022. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the manager of the 

certification office, send it to the attention of 

the person identified in paragraph (j)(1) of 

this AD. Information may be emailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(3) AMOCs approved for AD 2021–23–12, 

Amendment 39–21810 (86 FR 69984, 

December 9, 2021) providing relief for 

specific radio altimeter installations are 

approved as AMOCs for the provisions of this 

AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Dean Thompson, Senior Aerospace 

Engineer, Systems and Equipment Section, 

FAA, Seattle ACO Branch, 2200 South 216th 

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

206–231–3165; email: dean.r.thompson@

faa.gov. 

(2) For service information identified in 

this AD that is not incorporated by reference, 

contact Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 110– 

SK57, Seal Beach, CA 90740–5600; telephone 

562–797–1717; internet https://

www.myboeingfleet.com. 

(k) Material Incorporated by Reference 

None. 

Issued on January 13, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–01030 Filed 1–14–22; 2:00 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0793; Project 

Identifier MCAI–2021–00372–E; Amendment 

39–21885; AD 2021–26–26] 

RIN 2120–AA64 

Airworthiness Directives; Safran 

Helicopter Engines, S.A. (Type 

Certificate Previously Held by 

Turbomeca S.A.) Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2005–12– 

08 for certain Safran Helicopter Engines, 

S.A. (Safran Helicopter Engines) Arrius 

2B1, 2B1A, 2B1A–1, and 2B2 model 

turboshaft engines. AD 2005–12–08 

required replacing the software in the 

engine electronic control unit (EECU). 

This AD was prompted by a report of 

simultaneous loss of automatic control 

on both engines installed on an Airbus 

Helicopters Deutschland (formerly 

Eurocopter Deutschland) EC135 

helicopter during flight. This AD 

requires replacement of the EECU or 

upgrade of the EECU software for 

engines with a certain EECU part 

number (P/N) installed. This AD also 

prohibits installation of an affected 

EECU onto any engine. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 23, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 23, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of June 29, 2005 (70 FR 

34334, June 14, 2005). 

ADDRESSES: For service information 

identified in this final rule, contact 

Safran Helicopter Engines, S.A., Avenue 

du 1er Mai, 40220 Tarnos, France; 

phone: +33 (0) 5 59 74 45 00. You may 

view this service information at the 

Airworthiness Products Section, 


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2700 Federal Register / Vol. 87, No. 12 / Wednesday, January 19, 2022 / Rules and Regulations 

Operational Safety Branch, FAA, 1200 

District Avenue, Burlington, MA 01803. 

For information on the availability of 

this material at the FAA, call (817) 222– 

5110. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0793. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0793; 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, the mandatory continuing 

airworthiness information (MCAI), any 

comments received, and other 

information. The address for Docket 

Operations is Document Operations, 

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: 

Wego Wang, Aviation Safety Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

(781) 238–7134; fax: (781) 238–7199; 

email: wego.wang@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–12–08, 

Amendment 39–14124 (70 FR 34334, 

June 14, 2005), (AD 2005–12–08). AD 

2005–12–08 applied to all Safran 

Helicopter Engines (Type Certificate 

previously held by Turbomeca S.A.) 

Arrius 2 B1, 2 B1A, 2 B1A–1, and 2 B2 

model turboshaft engines. These engines 

are installed on, but not limited to, 

Eurocopter Deutschland GmbH EC 

135T1 and EC 135 T2 helicopters. The 

NPRM published in the Federal 

Register on September 20, 2021 (86 FR 

52106). The NPRM was prompted by a 

report of simultaneous loss of automatic 

control on both engines installed on an 

Airbus Helicopters Deutschland 

(formerly Eurocopter Deutschland) 

EC135 helicopter during flight. In 

addition, the manufacturer more 

recently determined that certain EECUs 

identified in AD 2005–12–08 are not 

subject to the unsafe condition. In the 

NPRM, the FAA proposed to require 

replacement of the EECU or upgrade of 

the EECU software for engines with a 

certain EECU P/N installed. In the 

NPRM, the FAA also proposed to 

prohibit installation of an affected EECU 

onto any engine. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

The European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

AD 2021–0088, dated March 24, 2021. 

EASA AD 2021–0088 was revised by 

EASA AD 2021–0088R1, dated July 26, 

2021 (referred to after this as ‘‘the 

MCAI’’), to address the unsafe condition 

on these products. The MCAI states: 

An occurrence was reported of 

simultaneous loss of automatic control in 

flight of both ARRIUS 2B1 engines on an 

EC135 T1 helicopter. Loss of automatic 

control would result, for each engine, from a 

difference between the position datum of the 

fuel metering valve and its measured 

position. 

This condition, if not corrected, could lead 

to increased work for flight crew during 

certain flight phases, possibly resulting in 

reduced control of the helicopter. 

To address this potential unsafe condition, 

Turbomeca developed mod TU80C, TU81C, 

TU82C and TU90C to improve the DECU 

software for ARRIUS 2B1 engines without 

overspeed option, ARRIUS 2B1 engines with 

overspeed option, ARRIUS 2B1A and 

ARRIUS 2B2 engines, and DGAC France 

issued AD F–2004–017 (later revised) to 

require engine modification. 

Since that [DGAC France] AD was issued, 

it was determined that a DECU having a P/ 

N which corresponds to Turbomeca mod 

TU80C, TU81C, TU82C, TU90C or later 

software is not affected by the software 

modification requirement. DGAC France AD 

F–2004–017R1 did not specifically identify 

any affected DECU P/N(s). 

For the reason described above, this 

[EASA] AD retains the requirements of DGAC 

France AD F–2004–017R1 (EASA approval 

2004–1618), which is superseded, and limits 

the required actions to engines with an 

affected DECU P/N installed. This [EASA] 

AD also prohibits (re)installation of affected 

DECU on any engine. 

This [EASA] AD is revised to provide 

clarification on affected and serviceable 

DECU. 

You may obtain further information 

by examining the MCAI in the AD 

docket at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0793. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

one individual commenter. The 

commenter supported the NPRM 

without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require 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 Turbomeca 

Mandatory Service Bulletin (MSB) No. 

319 73 2080, Revision 1, dated February 

13, 2004; Turbomeca MSB No. 319 73 

2081, Revision 1, dated February 13, 

2004; Turbomeca MSB No. 319 73 2082, 

Revision 1, dated February 13, 2004, 

Version C, dated July 31, 2008, and 

Version D, dated June 6, 2011; and 

Turbomeca MSB No. 319 73 2090, 

Original Issue, dated February 13, 2004. 

This service information specifies 

procedures for upgrading the EECU by 

either replacing the EECU or by 

uploading the software to the EECU. 

These documents are distinct since they 

apply to different engine models in 

different configurations. The Director of 

the Federal Register previously 

approved Turbomeca MSB No. 319 73 

2080, Revision 1, dated February 13, 

2004; Turbomeca MSB No. 319 73 2081, 

Revision 1, dated February 13, 2004; 

Turbomeca MSB No. 319 73 2082, 

Revision 1, dated February 13, 2004; 

and Turbomeca MSB No. 319 73 2090, 

Original Issue, dated February 13, 2004 

for incorporation by reference on June 

29, 2005 (70 FR 34334, June 14, 2005). 

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 221 engines installed on 

helicopters of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replace the EECU .......................................... 1 work-hour × $85 per hour = $85 ................. $35,000 $35,085 $7,753,785 


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ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Upgrade the EECU software .......................... 2 work-hours × $85 per hour = $170 ............. 0 170 37,570 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (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 

2005–12–08, Amendment 39–14124 (70 

FR 34334, June 14, 2005); and 

■ b. Adding the following new 

airworthiness directive: 

2021–26–26 Safran Helicopter Engines, 

S.A. (Type Certificate previously held by 

Turbomeca S.A.): Amendment 39– 

21885; Docket No. FAA–2021–0793; 

Project Identifier MCAI–2021–00372–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 23, 2022. 

(b) Affected ADs 

This AD replaces AD 2005–12–08, 

Amendment 39–14124 (70 FR 34334, June 

14, 2005). 

(c) Applicability 

This AD applies to Safran Helicopter 

Engines, S.A. (Type Certificate previously 

held by Turbomeca S.A.) Arrius 2B1, Arrius 

2B1A, (including those that embody 

modification (mod) TU45C, identified as 

Arrius 2B1A_1) and Arrius 2B2 model 

turboshaft engines with an installed engine 

electronic control unit (EECU) having part 

number (P/N) 70EMF01080 or 

70EMF01090—for Arrius 2B1 model 

turboshaft engines without overspeed 

protection option (TU 19C); P/N 

70EMF01100 or P/N 70EMF01120—for 

Arrius 2B1 model turboshaft engines with 

overspeed protection option (TU 67C or TU 

23C); P/N 70EMH01000 or 70EMH01010—for 

Arrius 2B1A model turboshaft engines; or P/ 

N 70EMM01000—for Arrius 2B2 model 

turboshaft engines. 

Note 1 to paragraph (c): Turbomeca 

Mandatory Service Bulletin (MSB) No. 319 

73 2082, Version D, dated June 6, 2011, 

references Arrius 2B1A_1 model turboshaft 

engines. Arrius 2B1A model turboshaft 

engines with mod TU 45C applied are 

identified as Arrius 2B1A_1 on the engine 

identification plate. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7600, Engine Controls. 

(e) Unsafe Condition 

This AD was prompted by a report of 

simultaneous loss of automatic control on 

both engines installed on an Airbus 

Helicopters Deutschland (formerly 

Eurocopter Deutschland) EC135 helicopter 

during flight. The FAA is issuing this AD to 

prevent simultaneous loss of automatic 

control of both engines. The unsafe 

condition, if not addressed, could result in 

failure of the engines and loss of control of 

the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For engines with an EECU having P/N 

70EMF01090, 70EMF01100, 70EMF01120, 

70EMH01010, or 70EMM01000, within 90 

days after June 29, 2005 (the effective date of 

AD 2005–12–08), or before further flight, 

whichever occurs later, upload the EECU 

software on both engines of the helicopter 

simultaneously using paragraph 2, 

Instructions to be incorporated, of the 

applicable Turbomeca MSB listed in Table 1 

to paragraph (g) of this AD, or replace the 

affected EECU with a part eligible for 

installation. 

(2) For engines with an EECU having P/N 

70EMF01080 or 70EMH01000, within 90 

days after June 29, 2005 (the effective date of 

AD 2005–12–08), or before further flight, 

whichever occurs later, replace the affected 

EECU with a part eligible for installation. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install onto any engine any EECU having a 

P/N identified in paragraph (c) of this AD. 

(i) Definition 

For the purpose of this AD, a ‘‘part eligible 

for installation’’ is an EECU having a P/N that 

is not identified in paragraph (c) of this AD. 

(j) No Reporting Requirements 

The reporting requirements specified in 

Turbomeca MSB No. 319 73 2080, Revision 

1, dated February 13, 2004; Turbomeca MSB 

No. 319 73 2081, Revision 1, dated February 

13, 2004; Turbomeca MSB No. 319 73 2082, 

Revision 1, dated February 13, 2004, Version 

C, dated July 31, 2008, and Version D, dated 

June 6, 2011; and Turbomeca MSB No. 319 

73 2090, Original Issue, dated February 13, 

2004, are not required by this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to the attention of the person 

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

Information may be emailed to: ANE-ADAMOC@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 

(1) For more information about this AD, 

contact Wego Wang, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7134; fax: (781) 238–7199; email: 

wego.wang@faa.gov. 

(2) Refer to European Union Aviation 

Safety Agency (EASA) AD 2021–0088R1, 

dated July 26, 2021, for more information. 

You may examine the EASA AD in the AD 

docket at https://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2021–0793. 

(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. 

(3) The following service information was 

approved for IBR on February 23, 2022. 

(i) Turbomeca Mandatory Service Bulletin 

(MSB) No. 319 73 2082, Version C, dated July 

31, 2008. 

(ii) Turbomeca MSB No. 319 73 2082, 

Version D, dated June 6, 2011. 

(4) The following service information was 

approved for IBR on June 29, 2005 (70 FR 

34334, June 14, 2005). 

(i) Turbomeca MSB No. 319 73 2080, 

Revision 1, dated February 13, 2004. 

(ii) Turbomeca MSB No. 319 73 2081, 

Revision 1, dated February 13, 2004. 

(iii) Turbomeca MSB No. 319 73 2082, 

Revision 1, dated February 13, 2004. 

(iv) Turbomeca MSB No. 319 73 2090, 

Original Issue, dated February 13, 2004. 

(5) For Turbomeca service information 

identified in this AD, contact Safran 

Helicopter Engines, S.A., Avenue du 1er Mai, 

40220 Tarnos, France; phone: +33 (0) 5 59 74 

45 00. 

(6) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

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

(7) You may view this service information 

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 December 17, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–00891 Filed 1–18–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 12 

[Docket No. RM20–9–000; Order No. 880] 

Safety of Water Power Projects and 

Project Works 

Correction 

In rule document 2021–27736, 

appearing on pages 1490–1520, in the 

issue of Tuesday, January 11, 2022, 

make the following changes: 

§ 12.4 [Corrected]. 

■ 1. On page 1514, in the first column, 

under amendatory instruction number 

3, instruction ‘‘3c’’ currently reads, 

‘‘Adding paragraphs (b)(2)(iii)(C) and 

(D);’’ should read, ‘‘Revising paragraphs 

(c)(1), (c)(2) introductory text, and (c)(3); 

and’’ 

■ 2. On page 1514, in the first column, 

under amendatory instruction number 

3, instruction ‘‘3d’’ currently reads, 

‘‘Revising paragraphs (c)(1), (c)(2) 


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