79438 Federal Register / Vol. 85, No. 238 / Thursday, December 10, 2020 / Proposed Rules 

(h) Exceptions to EASA AD 2019–0139 

(1) Where EASA AD 2019–0139 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where EASA AD 2019–0139 refers to 

September 5, 2018 (the effective date of 

EASA AD 2018–0186, dated August 29, 

2018), this AD requires using the effective 

date of this AD. 

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

2019–0139 does not apply to this AD. 

(4) Where EASA AD 2019–0139 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(5) Paragraphs (3) and (4) of EASA AD 

2019–0139 refer to ‘‘discrepancies.’’ For this 

AD, discrepancies include corrosion, fretting, 

wear, cracking, bolt play, and bolt tightening 

torque. 

(6) Although the service information 

referenced in EASA AD 2019–0139 specifies 

to discard certain parts, this AD does not 

include that requirement. 

(7) Where EASA AD 2019–0139 specifies 

to contact the manufacturer for repair 

instructions, repair using a method approved 

by the Manager, Rotorcraft Standards Branch, 

FAA. For a repair method to be approved by 

the Manager, Rotorcraft Standards Branch, as 

required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

(8) Paragraph (5) of EASA AD 2019–0139 

specifies to report inspection results to 

Airbus Helicopters within a certain 

compliance time. For this AD, report 

inspection results at the applicable time 

specified in paragraph (h)(8)(i) or (ii) of this 

AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Rotorcraft Standards Branch, 

FAA, may approve AMOCs for this AD. Send 

your proposal to: Manager, Rotorcraft 

Standards Branch, FAA, 10101 Hillwood 

Pkwy, Fort Worth, TX 76177; phone: 817– 

222–5110; email: 9-ASW-FTW-AMOCRequests@faa.gov. 

(j) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 1 hour per 

response, including the time for reviewing 

instructions, searching existing data sources, 

gathering and maintaining the data needed, 

and completing and reviewing the collection 

of information. All responses to this 

collection of information are mandatory as 

required by this AD. Send comments 

regarding this burden estimate or any other 

aspect of this collection of information, 

including suggestions for reducing this 

burden to Information Collection Clearance 

Officer, Federal Aviation Administration, 

10101 Hillwood Parkway, Fort Worth, TX 

76177–1524. 

(k) Related Information 

(1) For EASA AD 2019–0139, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 89990 

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. 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. This 

material may be found in the AD docket on 

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

by searching for and locating Docket No. 

FAA–2020–1114. 

(2) For more information about this AD, 

contact Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, FAA, 470 

L’Enfant Plaza SW, Washington, DC 20024; 

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

faa.gov. 

Issued on December 2, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–26965 Filed 12–9–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1118; Project 

Identifier MCAI–2020–00516–E] 

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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Safran Helicopter Engines, S.A. Arriel 

2C, 2C1, 2S1, and 2S2 model turboshaft 

engines. This proposed AD was 

prompted by investigations by the 

manufacturer following level 1 failures 

in flight (minor anomalies) and level 2 

failures on the ground (minor failures), 

where cracks were found on the 

soldered joints of torque conformation 

boxes. This proposed AD would require 

performing initial and repetitive 

inspections of the resistance values of 

the torque conformation box and, 

depending on the results of the 

inspections, replacement of the torque 

conformation box. The FAA is 

proposing this AD to address the unsafe 

condition on these products. 

DATES: The FAA must receive comments 

on this proposed AD by January 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 service information identified in 

this NPRM, contact Safran Helicopter 

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

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

45 11. You may view this service 

information at the 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 (781) 238–7759. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–1118; 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 

NPRM, the mandatory continuing 

airworthiness information (MCAI), any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

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: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 


jbell on DSKJLSW7X2PROD with PROPOSALS
Federal Register / Vol. 85, No. 238 / Thursday, December 10, 2020 / Proposed Rules 79439 

FAA–2020–1118; Project Identifier 

MCAI–2020–00516–E’’ at the beginning 

of your comments. The most helpful 

comments reference a specific portion of 

the proposal, 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 proposal 

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 NPRM. 

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 NPRM 

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 NPRM, 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 

NPRM. Submissions containing CBI 

should be sent to Wego Wang, Aviation 

Safety Engineer, ECO Branch, FAA, 

1200 District Avenue, Burlington, MA 

01803. Any commentary that the FAA 

receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

The European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

AD 2019–0110, dated May 21, 2019 

(referred to after this as ‘‘the MCAI’’), to 

address the unsafe condition on these 

products. The MCAI states: 

It was reported that, during investigations 

following level 1 failures in flight (minor 

anomalies) and level 2 failures on the ground 

(minor failures), cracks were found on the 

soldered joints of certain torque 

conformation boxes. Although no events in 

operation were reported of One Engine 

Inoperative (OEI) ratings maximum power 

unavailability, the failure mode analysis for 

these boxes demonstrated that such event 

could not be excluded. This condition, if not 

detected and corrected, could lead to engine 

in-flight shut-down, possibly resulting in 

reduced control of the helicopter. 

To address this potential unsafe condition, 

SAFRAN Helicopter Engines issued the SB 

[Service Bulletin], to provide instructions for 

repetitive checks of the box resistance values. 

For the reasons described above, this 

[EASA] AD requires repetitive checks of the 

affected part and, depending on findings, 

replacement of the affected part with a 

serviceable part. 

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–2020–1118. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Safran Helicopter 

Engines Mandatory Service Bulletin 

(MSB) No. 292 72 2868, Version A, 

dated December 2018. The MSB 

describes procedures for performing an 

inspection of the resistance values of the 

torque conformation box. 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. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

performing initial and repetitive 

inspections of the resistance values of 

the torque conformation box and, 

depending on the results of the 

inspections, replacement of the torque 

conformation box. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 257 

engines installed on helicopters of U.S. 

registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect resistance values of the torque conformation box.1 work-hour × $85 per hour = $85 ................. $0 $85 $21,845 

The FAA estimates the following 

costs to do any necessary replacement 

that would be required based on the 

results of the proposed inspections. The 

agency has no way of determining the 

number of aircraft that might need this 

replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace the torque conformation box .......................... 1 work-hour × $85 per hour = $85 ............................... $1,841 $1,926 

The FAA has included all known 

costs in its estimate. According to the 

manufacturer, however, some of the 

costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. 

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 


jbell on DSKJLSW7X2PROD with PROPOSALS
79440 Federal Register / Vol. 85, No. 238 / Thursday, December 10, 2020 / Proposed Rules 

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 

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 this 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, 

the FAA proposes to amend 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: 

Safran Helicopter Engines, S.A. (Type 

Certificate previously held by 

Turbomeca, S.A.): Docket No. FAA– 

2020–1118; Project Identifier MCAI– 

2020–00516–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by January 25, 

2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Safran Helicopter 

Engines, S.A. (Type Certificate previously 

held by Turbomeca, S.A.) Arriel 2C, 2C1, 

2S1, and 2S2 model turboshaft engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7712, Engine BMEP/Torque Indicating. 

(e) Unsafe Condition 

This AD was prompted by investigations 

by the manufacturer following level 1 failures 

in flight (minor anomalies) and level 2 

failures on the ground (minor failures), where 

cracks were found on the soldered joints of 

torque conformation boxes. The FAA is 

issuing this AD to prevent failure of the 

torque conformation box. The unsafe 

condition, if not addressed, could result in 

failure of the engine, in-flight shutdown, and 

loss of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For engines with the torque 

conformation box in pre-modification TU 34 

configuration, installed on Arriel 2C and 2C1 

model turboshaft engines; pre-modification 

TU 34 or post-modification TU 188 

configuration, installed on Arriel 2S1 model 

turboshaft engines; or post-modification TU 

188 configuration, installed on Arriel 2S2 

model turboshaft engines: 

(i) Within 600 engine hours (EHs) or 180 

days after the effective date of this AD, 

whichever occurs first, perform an initial 

inspection of the resistance values of the 

torque conformation box. 

Note 1 to paragraph (g)(1)(i): You may 

delay the initial inspection by up to 60 EHs 

to align with other scheduled maintenance 

tasks. 

(ii) Thereafter, perform repetitive 

inspections of the resistance values of the 

torque conformation box before exceeding 

600 EHs since the last inspection of the 

resistance values of the torque conformation 

box. 

(2) Use the Accomplishment Instructions, 

paragraph 2.3.2 or 4.3.2, of Safran Helicopter 

Engines Mandatory Service Bulletin No. 292 

72 2868, Version A, dated December 2018, to 

perform the inspections of the resistance 

values of the torque conformation box 

required by paragraph (g)(1) of this AD. 

(3) If, during any inspection required by 

paragraph (g)(1) of this AD, a non-conforming 

resistance value is found, before further 

flight, remove the torque conformation box 

from service and replace it with a part 

eligible for installation. 

(h) Definition 

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

for installation’’ is a zero hour torque 

conformation box or a torque conformation 

box that has been inspected as required by 

paragraph (g)(1) of this AD. 

(i) 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 Related Information. You may 

email your request to: ANE-AD-AMOC@

faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

(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 2019–0110, dated 

May 21, 2019, for more information. You may 

examine the EASA AD in the AD docket at 

https://www.regulations.gov by searching for 

and locating it in Docket No. FAA–2020– 

1118. 

(3) For service information identified in 

this AD, contact Safran Helicopter Engines, 

S.A., Avenue du 1er Mai, Tarnos, France; 

phone: +33 (0) 5 59 74 45 11. You may view 

this referenced service information at the 

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 (781) 238–7759. 

Issued on December 4, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–27053 Filed 12–9–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1115; Project 

Identifier MCAI–2020–01230–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Airbus SAS Model A330–200 


jbell on DSKJLSW7X2PROD with PROPOSALS