Airworthiness Directives; Airbus Helicopters, 11413-11415 [2021-03662]

Download as PDF Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations (i) Subject Joint Aircraft Service Component (JASC) Code: 7120, Engine Mount Section. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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. (i) Leonardo Helicopters Alert Service Bulletin No. 139–593, Revision A, dated June 14, 2019. (ii) [Reserved] (3) For service information identified in this AD, contact Leonardo S.p.a. Helicopters, Emanuele Bufano, Head of Airworthiness, Viale G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone +39–0331– 225074; fax +39–0331–229046; or at https:// www.leonardocompany.com/en/home. (4) You may view this service information 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on January 27, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–03660 Filed 2–24–21; 8:45 am] BILLING CODE 4910–13–P spindle bolts and the inner ring and needle bearings of each flapping hinge, corrective actions if necessary, and repetitive replacements of affected flapping hinge components, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. Replacement of all affected flapping hinge components on each flapping hinge is terminating action for the repetitive inspections. This AD also expands the applicability. This AD was prompted by a report of a damaged flapping hinge on a T/R blade. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 1, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 1, 2021. ADDRESSES: For material incorporated by reference (IBR) in this AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@ easa.europa.eu; internet www.easa.europa.eu. You may find this material 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. It is also available in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0983. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0983; 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, any comments received, and other information. The address for Docket Operations is 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: Daniel Moore, Aviation Safety Engineer, Denver ACO Branch, Compliance & Airworthiness Division, FAA, 26805 E 68th Ave., Denver, CO 80249; telephone 303–342–1095; email daniel.e.moore@ faa.gov. 14 CFR Part 39 [Docket No. FAA–2020–0983; Project Identifier MCAI–2020–00542–R; Amendment 39–21404; AD 2021–03–01] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2018–05– 09, which applied to all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. AD 2018–05–09 required inspecting the tail rotor (T/R) flapping hinge link (hinge) and reporting the results. This AD requires repetitive inspections of the SUMMARY: VerDate Sep<11>2014 16:18 Feb 24, 2021 Jkt 253001 SUPPLEMENTARY INFORMATION: PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 11413 Discussion The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2020–0086, dated April 14, 2020 (EASA AD 2020–0086) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and SA330J helicopters. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2018–05–09, Amendment 39–19218 (83 FR 10360, March 9, 2018) (AD 2018–05–09). AD 2018–05–09 applied to all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. The NPRM published in the Federal Register on November 4, 2020 (85 FR 70087). The NPRM was prompted by report of a damaged flapping hinge on a T/R blade. The NPRM proposed to require repetitive inspections of the spindle bolts and the inner ring and needle bearings of each flapping hinge, corrective actions if necessary, and repetitive replacements of affected flapping hinge components, as specified in an EASA AD. Replacement of all affected flapping hinge components on each flapping hinge is terminating action for the repetitive inspections. The NPRM also proposed to expand the applicability. The FAA is issuing this AD to address failure of a T/R flapping hinge. This condition could result in unbalance of the T/R, detachment of the T/R gearbox and hub, and subsequent loss of control of the helicopter. See the MCAI for additional background information. Comments The FAA gave the public the opportunity to participate in developing this final rule. The FAA received no comments on the NPRM or on the determination of the cost to the public. Conclusion The FAA reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. E:\FR\FM\25FER1.SGM 25FER1 11414 Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations actions include replacement of any affected component with a serviceable part. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Related Service Information Under 1 CFR Part 51 EASA AD 2020–0086 describes procedures for repetitive replacement of the flapping hinge components and repetitive inspections of the spindle bolts, inner ring, and needle bearings of each flapping hinge, and corrective action. The inspection procedures include repetitive inspections of the spindle bolts for cracking; repetitive inspections of the inner ring for spalling, brinelling, and cracking; and repetitive inspections of the needle bearings for spalling. The corrective Differences Between This AD and the MCAI Although the service information referenced in EASA AD 2020–0086 specifies to return affected parts and submit a form to the manufacturer, this AD does not include those requirements. Where paragraph (1) of EASA AD 2020–0086 refers to a compliance time of ‘‘within 25 flight hours or during the next scheduled 50 FH inspection, whichever occurs later . . . ,’’ for the initial replacement, this AD requires completion within 25 hours time-inservice after the effective date of this AD. Costs of Compliance The FAA estimates that this AD affects 26 helicopters of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 8 work-hours × $85 per hour = $680 .......................................................................................... $11,630 $12,310 $320,060 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 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 VerDate Sep<11>2014 16:18 Feb 24, 2021 Jkt 253001 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 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. [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2018–05–09, Amendment 39–19218 (83 FR 10360, March 9, 2018), and adding the following new AD: ■ 2021–03–01 Airbus Helicopters: Amendment 39–21404; Docket No. FAA–2020–0983; Project Identifier MCAI–2020–00542–R. (a) Effective Date This Airworthiness Directive (AD) is effective April 1, 2021. (b) Affected ADs This AD removes AD 2018–05–09, Amendment 39–19218 (83 FR 10360, March 9, 2018) (AD 2018–05–09). (c) Applicability This AD applies to all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and SA330J helicopters, certificated in any category, all manufacturer serial numbers. PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Joint Aircraft System Component (JASC) Codes 6420, Tail Rotor Head; 6720, Tail Rotor Control System. (e) Reason This AD was prompted by a report of a damaged flapping hinge link (hinge) on a tail rotor (T/R) blade. The FAA is issuing this AD to address failure of a T/R flapping hinge. This condition could result in unbalance of the T/R, detachment of the T/R gearbox and hub, and subsequent loss of control of the helicopter. (f) Compliance ■ § 39.13 (d) Subject Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2020–0086, dated April 14, 2020 (EASA AD 2020–0086). (h) Exceptions to EASA AD 2020–0086 (1) Where EASA AD 2020–0086 refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2020–0086 does not apply to this AD. (3) Although the service information referenced in EASA AD 2020–0086 specifies to return affected parts and submit a form to the manufacturer, this AD does not include those requirements. (4) Where paragraph (9) of EASA AD 2020– 0086 refers to ‘‘any discrepancy,’’ for the purposes of this AD, discrepancies include spalling, brinelling, and cracking on the inner ring, and spalling on the bearing needles. (5) Where EASA AD 2020–0086 refers to flight hours (FH), this AD requires using hours time-in-service. E:\FR\FM\25FER1.SGM 25FER1 Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations (6) Where paragraph (1) of EASA AD 2020– 0086 refers to a compliance time of ‘‘within 25 flight hours or during the next scheduled 50 FH inspection, whichever occurs later . . . , ’’ for the initial replacement, this AD requires completion within 25 hours time-inservice after the effective date of this AD. (i) Alternative Methods of Compliance (AMOCs) BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 For more information about this AD, contact Daniel Moore, Aviation Safety Engineer, Denver ACO Branch, Compliance & Airworthiness Division, FAA, 26805 E 68th Ave., Denver, CO 80249; telephone 303–342– 1095; email daniel.e.moore@faa.gov. (k) 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 this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2020–0086, dated April 14, 2020. (ii) [Reserved] (3) For EASA AD 2020–0086, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 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. (4) You may view this service information 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–2020–0983. (5) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@ nara.gov, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Jkt 253001 RIN 2120–AA64 Airworthiness Directives; Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited) Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 429 helicopters. This AD was prompted by the introduction of a new life limit for the centrifugal force bearing (CFB). This AD requires determining the accumulated retirement index number (RIN) and removing each affected CFB from service before it accumulates 8,000 total RIN. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 1, 2021. For service information identified in this final rule, contact Bell Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J 1R4; telephone 450–437–2862 or 800–363– 8023; fax 450–433–0272; or at https:// www.bellcustomer.com. You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. You may view this service information 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. ADDRESSES: Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for PO 00000 Frm 00029 Fmt 4700 and locating Docket No. FAA–2020– 0860; 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, any comments received, and other information. The street address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Matt Fuller, AD Program Manager, Continued Operational Safety Branch, Airworthiness Products Section, General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222– 5110; email matthew.fuller@faa.gov. FOR FURTHER INFORMATION CONTACT: [Docket No. FAA–2020–0860; Product Identifier 2019–SW–005–AD; Amendment 39–21416; AD 2021–03–13] SUMMARY: (j) Related Information 16:18 Feb 24, 2021 [FR Doc. 2021–03662 Filed 2–24–21; 8:45 am] DEPARTMENT OF TRANSPORTATION (1) The Manager, Strategic Policy Rotorcraft Section, 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 Strategic Policy Rotorcraft Section, send it to: Manager, Strategic Policy Rotorcraft Section, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110. Information may be emailed to: 9-ASW-FTW-AMOCRequests@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. VerDate Sep<11>2014 Issued on January 21, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. 11415 Sfmt 4700 SUPPLEMENTARY INFORMATION: Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, issued Transport Canada AD CF–2019–03, dated January 31, 2019 (referred to after this as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for certain Bell Helicopter Textron Canada Limited (now Bell Textron Canada Limited) Model 429 helicopters. TCCA advises that an airworthiness limitations schedule document introduces a new life limit for CFB part number (P/N) 429–310–003– 103, a component that was not previously included. Failure to observe the CFB life limit could result in excessive vibration and loss of control of the helicopter. You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0860. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bell Helicopter Textron Canada Limited (now Bell Textron Canada Limited) Model 429 helicopters. The NPRM published in the Federal Register on October 1, 2020 (85 FR 61879). The NPRM was prompted by the introduction of a new life limit for the CFB. The NPRM proposed to require determining the accumulated RIN and removing each affected CFB from service before it accumulates 8,000 total RIN. The FAA is issuing this AD to address a CFB remaining in service beyond its fatigue life. Failure to observe the CFB life limit could result in excessive vibration and loss of control of the helicopter. See the MCAI for additional background information. E:\FR\FM\25FER1.SGM 25FER1

Agencies

[Federal Register Volume 86, Number 36 (Thursday, February 25, 2021)]
[Rules and Regulations]
[Pages 11413-11415]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-03662]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0983; Project Identifier MCAI-2020-00542-R; 
Amendment 39-21404; AD 2021-03-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-05-
09, which applied to all Airbus Helicopters Model AS332C, AS332C1, 
AS332L, and AS332L1 helicopters. AD 2018-05-09 required inspecting the 
tail rotor (T/R) flapping hinge link (hinge) and reporting the results. 
This AD requires repetitive inspections of the spindle bolts and the 
inner ring and needle bearings of each flapping hinge, corrective 
actions if necessary, and repetitive replacements of affected flapping 
hinge components, as specified in a European Union Aviation Safety 
Agency (EASA) AD, which is incorporated by reference. Replacement of 
all affected flapping hinge components on each flapping hinge is 
terminating action for the repetitive inspections. This AD also expands 
the applicability. This AD was prompted by a report of a damaged 
flapping hinge on a T/R blade. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective April 1, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 1, 
2021.

ADDRESSES: For material incorporated by reference (IBR) in this AD, 
contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 8999 000; email [email protected]; internet 
www.easa.europa.eu. You may find this material 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. It is also available in 
the AD docket on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0983.

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-
0983; 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, any comments received, and other information. The 
address for Docket Operations is 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: Daniel Moore, Aviation Safety 
Engineer, Denver ACO Branch, Compliance & Airworthiness Division, FAA, 
26805 E 68th Ave., Denver, CO 80249; telephone 303-342-1095; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2020-0086, dated April 14, 2020 
(EASA AD 2020-0086) (also referred to as the Mandatory Continuing 
Airworthiness Information, or the MCAI), to correct an unsafe condition 
for all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and 
SA330J helicopters.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2018-05-09, Amendment 39-19218 (83 FR 
10360, March 9, 2018) (AD 2018-05-09). AD 2018-05-09 applied to all 
Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 
helicopters. The NPRM published in the Federal Register on November 4, 
2020 (85 FR 70087). The NPRM was prompted by report of a damaged 
flapping hinge on a T/R blade. The NPRM proposed to require repetitive 
inspections of the spindle bolts and the inner ring and needle bearings 
of each flapping hinge, corrective actions if necessary, and repetitive 
replacements of affected flapping hinge components, as specified in an 
EASA AD. Replacement of all affected flapping hinge components on each 
flapping hinge is terminating action for the repetitive inspections. 
The NPRM also proposed to expand the applicability.
    The FAA is issuing this AD to address failure of a T/R flapping 
hinge. This condition could result in unbalance of the T/R, detachment 
of the T/R gearbox and hub, and subsequent loss of control of the 
helicopter. See the MCAI for additional background information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
except for minor editorial changes. The FAA has determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

[[Page 11414]]

Related Service Information Under 1 CFR Part 51

    EASA AD 2020-0086 describes procedures for repetitive replacement 
of the flapping hinge components and repetitive inspections of the 
spindle bolts, inner ring, and needle bearings of each flapping hinge, 
and corrective action. The inspection procedures include repetitive 
inspections of the spindle bolts for cracking; repetitive inspections 
of the inner ring for spalling, brinelling, and cracking; and 
repetitive inspections of the needle bearings for spalling. The 
corrective actions include replacement of any affected component with a 
serviceable part. This material is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Differences Between This AD and the MCAI

    Although the service information referenced in EASA AD 2020-0086 
specifies to return affected parts and submit a form to the 
manufacturer, this AD does not include those requirements.
    Where paragraph (1) of EASA AD 2020-0086 refers to a compliance 
time of ``within 25 flight hours or during the next scheduled 50 FH 
inspection, whichever occurs later . . . ,'' for the initial 
replacement, this AD requires completion within 25 hours time-in-
service after the effective date of this AD.

Costs of Compliance

    The FAA estimates that this AD affects 26 helicopters of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
8 work-hours x $85 per hour = $680...........................         $11,630          $12,310         $320,060
----------------------------------------------------------------------------------------------------------------

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

    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 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) 
2018-05-09, Amendment 39-19218 (83 FR 10360, March 9, 2018), and adding 
the following new AD:

2021-03-01 Airbus Helicopters: Amendment 39-21404; Docket No. FAA-
2020-0983; Project Identifier MCAI-2020-00542-R.

(a) Effective Date

    This Airworthiness Directive (AD) is effective April 1, 2021.

(b) Affected ADs

    This AD removes AD 2018-05-09, Amendment 39-19218 (83 FR 10360, 
March 9, 2018) (AD 2018-05-09).

(c) Applicability

    This AD applies to all Airbus Helicopters Model AS332C, AS332C1, 
AS332L, AS332L1, and SA330J helicopters, certificated in any 
category, all manufacturer serial numbers.

(d) Subject

    Joint Aircraft System Component (JASC) Codes 6420, Tail Rotor 
Head; 6720, Tail Rotor Control System.

(e) Reason

    This AD was prompted by a report of a damaged flapping hinge 
link (hinge) on a tail rotor (T/R) blade. The FAA is issuing this AD 
to address failure of a T/R flapping hinge. This condition could 
result in unbalance of the T/R, detachment of the T/R gearbox and 
hub, and subsequent loss of control of the helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, European Union Aviation Safety Agency (EASA) AD 
2020-0086, dated April 14, 2020 (EASA AD 2020-0086).

(h) Exceptions to EASA AD 2020-0086

    (1) Where EASA AD 2020-0086 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2020-0086 does not apply 
to this AD.
    (3) Although the service information referenced in EASA AD 2020-
0086 specifies to return affected parts and submit a form to the 
manufacturer, this AD does not include those requirements.
    (4) Where paragraph (9) of EASA AD 2020-0086 refers to ``any 
discrepancy,'' for the purposes of this AD, discrepancies include 
spalling, brinelling, and cracking on the inner ring, and spalling 
on the bearing needles.
    (5) Where EASA AD 2020-0086 refers to flight hours (FH), this AD 
requires using hours time-in-service.

[[Page 11415]]

    (6) Where paragraph (1) of EASA AD 2020-0086 refers to a 
compliance time of ``within 25 flight hours or during the next 
scheduled 50 FH inspection, whichever occurs later . . . , '' for 
the initial replacement, this AD requires completion within 25 hours 
time-in-service after the effective date of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Strategic Policy Rotorcraft Section, 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 Strategic Policy Rotorcraft Section, 
send it to: Manager, Strategic Policy Rotorcraft Section, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110. 
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.

(j) Related Information

    For more information about this AD, contact Daniel Moore, 
Aviation Safety Engineer, Denver ACO Branch, Compliance & 
Airworthiness Division, FAA, 26805 E 68th Ave., Denver, CO 80249; 
telephone 303-342-1095; email [email protected].

(k) 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 this AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2020-0086, 
dated April 14, 2020.
    (ii) [Reserved]
    (3) For EASA AD 2020-0086, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email 
[email protected]; internet www.easa.europa.eu. You may find this 
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) You may view this service information 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-
2020-0983.
    (5) You may view this material that is incorporated by reference 
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 January 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-03662 Filed 2-24-21; 8:45 am]
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