[Federal Register Volume 86, Number 127 (Wednesday, July 7, 2021)]
[Rules and Regulations]
[Pages 35601-35603]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-14340]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0333; Project Identifier MCAI-2020-00252-R; 
Amendment 39-21609; AD 2021-13-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 
helicopters. This AD was prompted by a report of a yaw control failure 
that was the result of the disconnection of the tail rotor hub (TRH) 
pitch control rod from the tail rotor servo-control, which resulted 
from a seized TRH bearing. The TRH bearing had grease dissolving after 
contamination by leaked hydraulic fluid from the tail rotor servo-
control that came through the TRH assembly boot. This AD requires 
repetitive inspections for hydraulic leaks, corrective actions if 
necessary, and an optional modification which constitutes terminating 
action, as specified in a European Union Aviation Safety Agency (EASA) 
AD, which is incorporated by reference. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective August 11, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 11, 
2021.

ADDRESSES: For material incorporated by reference (IBR) in this AD, 
contact

[[Page 35602]]

the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +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-2021-0333.

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-2021-
0333; 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: Hal Jensen, Aerospace Engineer, 
Operational Safety Branch, Compliance & Airworthiness Division, FAA, 
950 L'Enfant Plaza N SW, Washington, DC 20024; phone: (202) 267-9167; 
email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2020-0021, dated February 6, 2020 
(EASA AD 2020-0021) (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, and AS332L1 
helicopters. Although EASA AD 2020-0021 applies to all Model AS332C, 
AS332C1, AS332L, and AS332L1 helicopters, this AD applies to 
helicopters with an affected part installed instead.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain Airbus 
Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. The 
NPRM published in the Federal Register on April 22, 2021 (86 FR 21238). 
The NPRM was prompted by a report of a yaw control failure that was the 
result of the disconnection of the TRH pitch control rod from the tail 
rotor servo-control, which resulted from a seized TRH bearing. The TRH 
bearing had grease dissolving after contamination by leaked hydraulic 
fluid from the tail rotor servo-control that came through the TRH 
assembly boot. The NPRM proposed to require repetitive inspections for 
hydraulic leaks, corrective actions if necessary, and an optional 
modification which constitutes terminating action, as specified in an 
EASA AD.
    The FAA is issuing this AD to address seized TRH bearings, which 
could reduce the effectiveness of the pitch control of the tail rotor 
system, possibly resulting in reduced yaw control of the helicopter. 
See the MCAI for additional background information.

Discussion of Final Airworthiness Directive

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.

Related Service Information Under 1 CFR Part 51

    EASA AD 2020-0021 describes procedures for repetitive inspections 
for hydraulic leaks, corrective actions if necessary (i.e., replacement 
of the pitch control rod bearing of the affected TRH assembly), and an 
optional modification (i.e., installation of a TRH assembly having 
certain part numbers) which constitutes terminating action. 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.

Costs of Compliance

    The FAA estimates that this AD affects 10 helicopters of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
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               Labor cost                   Parts cost         Cost per product         Cost on U.S. operators
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1 work-hour x $85 per hour = $85 per                  $0  $85 per inspection cycle..  $850 per inspection cycle.
 inspection cycle.
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    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
helicopters that might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
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                                                             Cost per
              Labor cost                   Parts cost        product
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6 work-hours x $85 per hour = $510....            $509           $1,019
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[[Page 35603]]

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.

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 adding the following new airworthiness 
directive:

2021-13-04 Airbus Helicopters: Amendment 39-21609; Docket No. FAA-
2021-0333; Project Identifier MCAI-2020-00252-R.

(a) Effective Date

    This airworthiness directive (AD) is effective August 11, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Model AS332C, AS332C1, 
AS332L, and AS332L1 helicopters, certificated in any category, with 
a tail rotor hub (TRH) assembly, having part number (P/N) 332A33-
0001-05 or P/N 332A33-0001-06, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6420, Tail rotor 
head.

(e) Reason

    This AD was prompted by a report of a yaw control failure that 
was the result of a disconnection of the TRH pitch control rod from 
the tail rotor servo-control, which resulted from a seized TRH 
bearing. The TRH bearing had grease dissolving after contamination 
by leaked hydraulic fluid from the tail rotor servo-control that 
came through the TRH assembly boot. The FAA is issuing this AD to 
address seized TRH bearings, which could reduce the effectiveness of 
the pitch control of the tail rotor system, possibly resulting in 
reduced yaw 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 
2020-0021, dated February 6, 2020 (EASA AD 2020-0021).

(h) Exceptions to EASA AD 2020-0021

    (1) Where EASA AD 2020-0021 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2020-0021 does not apply 
to this AD.
    (3) Where EASA AD 2020-0021 refers to flight hours (FH), this AD 
requires using hours time-in-service.
    (4) Where paragraph (1) of EASA AD 2020-0021 requires doing 
inspections ``in accordance with the instructions of the ASB [alert 
service bulletin],'' this AD requires accomplishing a visual 
inspection for any hydraulic fluid leak at the TRH boot.
    (5) Where EASA AD 2020-0021 refers to February 28, 2004 (the 
effective date of Direction G[eacute]n[eacute]rale de l'Aviation 
Civile (DGAC) AD F-2004-031, dated February 18, 2004), this AD 
requires using the effective date of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation 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 International Validation Branch, send 
it to the attention of the person identified in paragraph (j) of 
this AD. 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 Hal Jensen, 
Aerospace Engineer, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC 
20024; phone: (202) 267-9167; 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 2020-0021, 
dated February 6, 2020.
    (ii) [Reserved]
    (3) For EASA AD 2020-0021, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; phone: +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 
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-
2021-0333.
    (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 June 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-14340 Filed 7-6-21; 8:45 am]
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