Airworthiness Directives; Safran Helicopter Engines, S.A. (Type Certificate Previously Held by Turbomeca S.A.) Turboshaft Engines, 2699-2702 [2022-00891]

Download as PDF 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. jspears on DSK121TN23PROD with RULES1 (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: 9ANM-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. VerDate Sep<11>2014 16:00 Jan 18, 2022 Jkt 256001 (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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2005–12– SUMMARY: PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 2699 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, E:\FR\FM\19JAR1.SGM 19JAR1 ER19JA22.081</GPH> Federal Register / Vol. 87, No. 12 / Wednesday, January 19, 2022 / Rules and Regulations 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. jspears on DSK121TN23PROD with RULES1 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: 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 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. Costs of Compliance 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. 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: 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. ESTIMATED COSTS Action Labor cost Replace the EECU .......................................... 1 work-hour × $85 per hour = $85 ................. VerDate Sep<11>2014 16:00 Jan 18, 2022 Jkt 256001 PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Parts cost $35,000 E:\FR\FM\19JAR1.SGM 19JAR1 Cost per product $35,085 Cost on U.S. operators $7,753,785 Federal Register / Vol. 87, No. 12 / Wednesday, January 19, 2022 / Rules and Regulations 2701 ESTIMATED COSTS—Continued Action Labor cost Upgrade the EECU software .......................... 2 work-hours × $85 per hour = $170 ............. 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. jspears on DSK121TN23PROD with RULES1 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 16:00 Jan 18, 2022 Jkt 256001 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 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/ Frm 00029 Fmt 4700 0 170 Cost on U.S. operators 37,570 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 [Amended] ■ ■ PO 00000 Cost per product Parts cost Sfmt 4700 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 E:\FR\FM\19JAR1.SGM 19JAR1 Federal Register / Vol. 87, No. 12 / Wednesday, January 19, 2022 / Rules and Regulations 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 jspears on DSK121TN23PROD with RULES1 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) VerDate Sep<11>2014 16:00 Jan 18, 2022 Jkt 256001 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. PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 (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) ■ E:\FR\FM\19JAR1.SGM 19JAR1 ER19JA22.076</GPH> 2702

Agencies

[Federal Register Volume 87, Number 12 (Wednesday, January 19, 2022)]
[Rules and Regulations]
[Pages 2699-2702]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-00891]


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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.

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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,

[[Page 2700]]

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: [email protected].

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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replace the EECU......................  1 work-hour x $85 per            $35,000         $35,085      $7,753,785
                                         hour = $85.

[[Page 2701]]

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

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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2005-12-08, Amendment 39-14124 (70 
FR 34334, June 14, 2005); and
0
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.
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[[Page 2702]]

[GRAPHIC] [TIFF OMITTED] TR19JA22.076

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(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: [email protected].
    (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: [email protected].
    (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: 
[email protected], 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

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