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Federal Register / Vol. 86, No. 179 / Monday, September 20, 2021 / Proposed Rules
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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation:
1 Is not a significant regulatory action under Executive Order 12866, 2 Would not affect intrastate aviation in Alaska, and 3 Would 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 Proposed Amendment Accordingly, under the authority delegated to me by the Administrator,
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the FAA proposes to amend 14 CFR part 39 as follows:
PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
Arrius 2B1A model turboshaft engines; or P/N 70EMM01000for 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.

Safran Helicopter Engines, S.A. Type Certificate previously held by Turbomeca S.A.: Docket No. FAA
20210793; Project Identifier MCAI
202100372E.

e Unsafe Condition This AD was prompted by a report of simultaneous loss of automatic control of both engines of 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.

2. The FAA amends 39.13 by:
a. Removing Airworthiness Directive 20051208, Amendment 3914124 70
FR 34334, June 14, 2005; and b. Adding the following new airworthiness directive:

a Comments Due Date The FAA must receive comments on this airworthiness directive AD by November 4, 2021.
b Affected ADs This AD replaces AD 20051208, Amendment 3914124 70 FR 34334, June 14, 2005 AD 20051208.
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 70EMF01090for Arrius 2B1 model turboshaft engines without overspeed protection option TU 19C; P/N
70EMF01100 or P/N 70EMF01120for Arrius 2B1 model turboshaft engines with overspeed protection option TU 67C or TU
23C; P/N 70EMH01000 or 70EMH01010for
PO 00000

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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 20051208, 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 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 20051208, or before further flight, whichever occurs later, replace the affected EECU with a part eligible for installation.

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