Airworthiness Directives; Safran Helicopter Engines, S.A. (Type Certificate Previously Held by Turbomeca, S.A.) Turboshaft Engines, 79438-79440 [2020-27053]

Download as PDF jbell on DSKJLSW7X2PROD with PROPOSALS 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. 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. (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. 14 CFR Part 39 (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 VerDate Sep<11>2014 16:26 Dec 09, 2020 Jkt 253001 (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 [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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 SUMMARY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 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. E:\FR\FM\10DEP1.SGM 10DEP1 Federal Register / Vol. 85, No. 238 / Thursday, December 10, 2020 / Proposed Rules 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, 79439 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 Inspect resistance values of the torque conformation box. 1 work-hour × $85 per hour = $85 ................. The FAA estimates the following costs to do any necessary replacement that would be required based on the Cost per product Parts cost results of the proposed inspections. The agency has no way of determining the $0 $85 Cost on U.S. operators $21,845 number of aircraft that might need this replacement: jbell on DSKJLSW7X2PROD with PROPOSALS ON-CONDITION COSTS Action Labor cost Replace the torque conformation box .......................... 1 work-hour × $85 per hour = $85 ............................... 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. VerDate Sep<11>2014 16:26 Dec 09, 2020 Jkt 253001 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 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Parts cost $1,841 Cost per product $1,926 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 E:\FR\FM\10DEP1.SGM 10DEP1 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. (c) Applicability Regulatory Findings 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. 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: jbell on DSKJLSW7X2PROD with PROPOSALS ■ 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. VerDate Sep<11>2014 16:26 Dec 09, 2020 Jkt 253001 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 (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. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 (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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus SAS Model A330–200 SUMMARY: E:\FR\FM\10DEP1.SGM 10DEP1

Agencies

[Federal Register Volume 85, Number 238 (Thursday, December 10, 2020)]
[Proposed Rules]
[Pages 79438-79440]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-27053]


-----------------------------------------------------------------------

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: [email protected].

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.

[[Page 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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspect resistance values of the        1 work-hour x $85 per                 $0             $85         $21,845
 torque conformation box.                hour = $85.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace the torque conformation box...........  1 work-hour x $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

[[Page 79440]]

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

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 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: 
[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.

(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: [email protected].
    (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
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