Airworthiness Directives; Airbus Helicopters, 35814-35816 [2020-12029]

Download as PDF 35814 Federal Register / Vol. 85, No. 114 / Friday, June 12, 2020 / Proposed Rules 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. Talon IIB outer combustion chamber assembly, P/N 51J500 or P/N 51J381, installed. 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) 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. (e) Unsafe Condition This AD was prompted by reports of damaged or failed 3rd stage LPT duct segments on PW engines with the Talon IIB outer combustion chamber assembly configuration installed. The FAA is issuing this AD to prevent failure of the 3rd stage LPT duct segments. The unsafe condition, if not addressed, could result in uncontained release of LPT blades and vanes, damage to the engine, and damage to the airplane. 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 (AD): ■ Pratt & Whitney Division: Docket No. FAA– 2020–0542; Project Identifier AD–2020– 00582–E. (a) Comments Due Date The FAA must receive comments by July 27, 2020. jbell on DSKJLSW7X2PROD with PROPOSALS (b) Affected ADs None. (c) Applicability This AD applies to all Pratt & Whitney Division (PW) PW4164, PW4164–1D, PW4168, PW4168–1D, PW4168A, PW4168A– 1D, and PW4170 model turbofan engines that have 3rd stage low-pressure turbine (LPT) duct segments, part number (P/N) 50N434–01 or P/N 50N450–01 installed, and have the VerDate Sep<11>2014 16:40 Jun 11, 2020 Jkt 250001 (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Action At every engine shop visit after the effective date of this AD, remove from service the 3rd stage LPT duct segments, P/N 50N434–01 and P/N 50N450–01, and replace them with parts with zero flight cycles. (h) Terminating Action Removal of the 3rd stage LPT duct segments, P/N 50N434–01 and P/N 50N450– 01, and their replacement with parts having P/Ns other than P/N 50N434–01 and P/N 50N450–01, constitutes terminating action for the repetitive replacement required by paragraph (g) of this AD. (i) Definition For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges (lettered flanges). The separation of engine flanges solely for the purpose of transportation without subsequent engine maintenance does not constitute an engine shop visit. (j) 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 (k) of this AD. 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. (k) Related Information For more information about this AD, contact Carol Nguyen, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 7655; fax: 781–238–7199; email: carol.nguyen@faa.gov. Issued on June 5, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–12626 Filed 6–11–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0463; Product Identifier 2013–SW–041–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to remove Airworthiness Directive (AD) 2015–17– 01, which applies to certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2015–17–01 requires certain inspections of each tail rotor pitch horn assembly (pitch horn) for a crack, replacement of a cracked pitch horn, and a repetitive visual inspection of certain pitch horns. AD 2015–17–01 is no longer necessary because the cause of the unsafe condition has been removed from all affected helicopter models. Accordingly, the FAA proposes to remove AD 2015– 17–01. DATES: The FAA must receive comments on this proposed AD by July 27, 2020. 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. You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, SUMMARY: E:\FR\FM\12JNP1.SGM 12JNP1 Federal Register / Vol. 85, No. 114 / Friday, June 12, 2020 / Proposed Rules 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0463; 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 proposal, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: jbell on DSKJLSW7X2PROD with PROPOSALS 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 the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0463; Product Identifier 2013–SW–041–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM because of those comments. The FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact received about this NPRM. Discussion The FAA issued AD 2015–17–01, Amendment 39–18234 (80 FR 50554, August 20, 2015) (‘‘AD 2015–17–01’’), for certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2015–17–01 requires certain inspections of each pitch horn for a crack, repetitive visual inspections of certain pitch horns for a crack, replacing a cracked pitch horn before further flight, and before installing any pitch horn having part number 350A121368 with more than 0 hours time-in-service, dye-penetrant inspecting it for a crack. AD 2015–17– VerDate Sep<11>2014 16:40 Jun 11, 2020 Jkt 250001 01 was prompted by a report of a crack in the yoke of a pitch horn and is intended to detect a crack in the pitch horn to prevent failure of the pitch horn, loss of the anti-torque function, and subsequent loss of control of the helicopter. The FAA issued AD 2015– 17–01 to detect a crack in the pitch horn to prevent failure of the pitch horn, loss of the anti-torque function, and subsequent loss of control of the helicopter. Actions Since AD 2015–17–01 Was Issued Since issuing AD 2015–17–01, the FAA has determined that the chin weights installed per Airbus Modification 07 5601 (that caused the pitch horn to crack) can only be installed on Model AS350B3 helicopters. The FAA had previously issued AD 2014–05–10, Amendment 39–17783 (79 FR 17408, March 28, 2014), which requires Model AS350B3 helicopters to remove the chin weights. The FAA has determined that with the chin weights removed, the unsafe condition no longer exists on Model AS350 and AS355 helicopters. FAA’s Conclusions Upon further consideration, the FAA has determined that AD 2015–17–01 is no longer necessary. Accordingly, this proposed AD would remove AD 2015– 17–01. Removal of AD 2015–17–01 would not preclude the FAA from issuing another related action or commit the FAA to any course of action in the future. Related Costs of Compliance This proposed AD would add no cost. This proposed AD would remove AD 2015–17–01 from 14 CFR part 39; therefore, operators would no longer be required to show compliance with that AD. 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 35815 This regulation is within the scope of that authority. 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) 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. 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 removing Airworthiness Directive (AD) 2015–17–01, Amendment 39–18234 (80 FR 50554, August 20, 2015), and adding the following new AD: ■ Airbus Helicopters: Docket No. FAA–2020– 0463; Product Identifier 2013–SW–041– AD. (a) Comments Due Date The FAA must receive comments on this AD action by July 27, 2020. (b) Affected ADs This AD replaces AD 2015–17–01, Amendment 39–18234 (80 FR 50554, August 20, 2015). (c) Applicability This AD applies to Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with tail rotor hub pitch horn (pitch horn) assembly, part number (P/N) 350A121368.01, E:\FR\FM\12JNP1.SGM 12JNP1 35816 Federal Register / Vol. 85, No. 114 / Friday, June 12, 2020 / Proposed Rules 350A121368.02, 350A121368.03, or 350A121368.04, with a pitch horn, P/N 350A121368.XX, where XX stands for a twodigit dash number, installed, certificated in any category. The pitch horn may be marked with either the pitch horn assembly P/N or pitch horn P/N. (d) Related Information For more information about this AD, contact Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email matthew.fuller@faa.gov. Issued on May 29, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–12029 Filed 6–11–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2020–0592; Project Identifier AD–2020–00251–E] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan 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 General Electric Company (GE) GEnx– 1B64/P2, GEnx–1B67/P2, GEnx–1B70/ 75/P2, GEnx–1B70/P2, GEnx–1B70C/P2, GEnx–1B74/75/P2, GEnx–1B76/P2, GEnx–1B76A/P2, and GEnx–2B67/P model turbofan engines with a certain a high-pressure turbine (HPT) rotor stage 2 disk installed. This proposed AD was prompted by a report of the potential for undetected subsurface anomalies formed during the manufacturing process that could result in uncontained failure of the HPT rotor stage 2 disk. This proposed AD would require an immersion ultrasonic inspection (USI) of the HPT rotor stage 2 disk and, depending on the results of the inspection, replacement of the HPT rotor stage 2 disk with a part eligible for installation. 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 July 27, 2020. ADDRESSES: You may send comments, using the procedures found in 14 CFR jbell on DSKJLSW7X2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:40 Jun 11, 2020 Jkt 250001 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 General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: aviation.fleetsupport@ge.com. 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. You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0592; 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, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Mehdi Lamnyi, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7743; fax: 781–238–7199; email: Mehdi.Lamnyi@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 the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0592; Project Identifier AD–2020–00251–E’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM because of those comments. Except for Confidential Business Information as described in the PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 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 FAA will also post a report summarizing each substantive verbal contact received about this NPRM. Confidential Business Information 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 Mehdi Lamnyi, Aerospace 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. Discussion The FAA received a report of the potential for undetected subsurface anomalies formed during the manufacturing process that could result in uncontained failure of the HPT rotor stage 2 disk. During an investigation by GE into melt-related material anomalies, a subsurface anomaly was found in an early production HPT rotor stage 2 disk. This type of subsurface anomaly has the potential to cause the failure of the HPT rotor stage 2 disk. In response, GE published service information that introduces inspections to prevent failure of the HPT rotor stage 2 disk. This condition, if not addressed, could result in uncontained HPT rotor stage 2 disk release, damage to the engine, and damage to the airplane. Related Service Information Under 1 CFR Part 51 The FAA reviewed GE GEnx–1B Service Bulletin (SB) 72–0463 R01, dated January 6, 2020, and GE GEnx–2B SB 72–0402 R01, dated January 8, 2020. The service information describes procedures for performing an immersion E:\FR\FM\12JNP1.SGM 12JNP1

Agencies

[Federal Register Volume 85, Number 114 (Friday, June 12, 2020)]
[Proposed Rules]
[Pages 35814-35816]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-12029]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0463; Product Identifier 2013-SW-041-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to remove Airworthiness Directive (AD) 2015-
17-01, which applies to certain Airbus Helicopters Model AS350B, 
AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, 
AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2015-17-
01 requires certain inspections of each tail rotor pitch horn assembly 
(pitch horn) for a crack, replacement of a cracked pitch horn, and a 
repetitive visual inspection of certain pitch horns. AD 2015-17-01 is 
no longer necessary because the cause of the unsafe condition has been 
removed from all affected helicopter models. Accordingly, the FAA 
proposes to remove AD 2015-17-01.

DATES: The FAA must receive comments on this proposed AD by July 27, 
2020.

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.
    You may view this service information at the FAA, Office of the 
Regional Counsel, Southwest Region,

[[Page 35815]]

10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0463; 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 proposal, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; 
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 the ADDRESSES section. Include ``Docket No. FAA-2020-0463; 
Product Identifier 2013-SW-041-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Discussion

    The FAA issued AD 2015-17-01, Amendment 39-18234 (80 FR 50554, 
August 20, 2015) (``AD 2015-17-01''), for certain Airbus Helicopters 
Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, 
AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP 
helicopters. AD 2015-17-01 requires certain inspections of each pitch 
horn for a crack, repetitive visual inspections of certain pitch horns 
for a crack, replacing a cracked pitch horn before further flight, and 
before installing any pitch horn having part number 350A121368 with 
more than 0 hours time-in-service, dye-penetrant inspecting it for a 
crack. AD 2015-17-01 was prompted by a report of a crack in the yoke of 
a pitch horn and is intended to detect a crack in the pitch horn to 
prevent failure of the pitch horn, loss of the anti-torque function, 
and subsequent loss of control of the helicopter. The FAA issued AD 
2015-17-01 to detect a crack in the pitch horn to prevent failure of 
the pitch horn, loss of the anti-torque function, and subsequent loss 
of control of the helicopter.

Actions Since AD 2015-17-01 Was Issued

    Since issuing AD 2015-17-01, the FAA has determined that the chin 
weights installed per Airbus Modification 07 5601 (that caused the 
pitch horn to crack) can only be installed on Model AS350B3 
helicopters. The FAA had previously issued AD 2014-05-10, Amendment 39-
17783 (79 FR 17408, March 28, 2014), which requires Model AS350B3 
helicopters to remove the chin weights. The FAA has determined that 
with the chin weights removed, the unsafe condition no longer exists on 
Model AS350 and AS355 helicopters.

FAA's Conclusions

    Upon further consideration, the FAA has determined that AD 2015-17-
01 is no longer necessary. Accordingly, this proposed AD would remove 
AD 2015-17-01. Removal of AD 2015-17-01 would not preclude the FAA from 
issuing another related action or commit the FAA to any course of 
action in the future.

Related Costs of Compliance

    This proposed AD would add no cost. This proposed AD would remove 
AD 2015-17-01 from 14 CFR part 39; therefore, operators would no longer 
be required to show compliance with that AD.

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.

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) 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.

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 removing Airworthiness Directive (AD) 
2015-17-01, Amendment 39-18234 (80 FR 50554, August 20, 2015), and 
adding the following new AD:

Airbus Helicopters: Docket No. FAA-2020-0463; Product Identifier 
2013-SW-041-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by July 27, 
2020.

(b) Affected ADs

    This AD replaces AD 2015-17-01, Amendment 39-18234 (80 FR 50554, 
August 20, 2015).

(c) Applicability

    This AD applies to Airbus Helicopters Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, 
AS355F1, AS355F2, AS355N, and AS355NP helicopters with tail rotor 
hub pitch horn (pitch horn) assembly, part number (P/N) 
350A121368.01,

[[Page 35816]]

350A121368.02, 350A121368.03, or 350A121368.04, with a pitch horn, 
P/N 350A121368.XX, where XX stands for a two-digit dash number, 
installed, certificated in any category. The pitch horn may be 
marked with either the pitch horn assembly P/N or pitch horn P/N.

(d) Related Information

    For more information about this AD, contact Matt Fuller, Senior 
Aviation Safety Engineer, Safety Management Section, Rotorcraft 
Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone 817-222-5110; email [email protected].

    Issued on May 29, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-12029 Filed 6-11-20; 8:45 am]
BILLING CODE 4910-13-P