Airworthiness Directives; Airbus Helicopters

[Federal Register Volume 86, Number 47 (Friday, March 12, 2021)]
[Rules and Regulations]
[Pages 13989-13992]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05145]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1132; Project Identifier MCAI-2020-01386-R; 
Amendment 39-21452; AD 2021-05-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-15-
02, which applied to certain Airbus Helicopters Model AS350B, AS350B1, 
AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N, 
and AS355NP helicopters. AD 2018-15-02 required repetitively inspecting 
the tail rotor (TR) pitch rod for a damaged elastomeric ball joint, and 
corrective action if necessary. This AD continues to require the 
repetitive inspections and allows the repetitive inspection interval to 
be extended under certain conditions, as specified in a European Union 
Aviation Safety Agency (EASA) AD, which is incorporated by reference. 
This AD was prompted by a report of several cases of damaged TR pitch 
rod ball joints. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective April 16, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 16, 
2021.

ADDRESSES: For material incorporated by reference (IBR) in this AD, 
contact the EASA, Konrad-Adenauer-Ufer 3,

[[Page 13990]]

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-2020-1132.

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-
1132; 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: Katherine Venegas, Aviation Safety 
Engineer, Cabin Safety, Mechanical and Environmental Systems Section, 
Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 
90712-4137; phone: 562-627-5353; fax: 562-627-5210; 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 2017-0020R1, dated May 22, 2019 
(EASA AD 2017-0020R1) (also referred to as the Mandatory Continuing 
Airworthiness Information, or the MCAI), to correct an unsafe condition 
for certain Airbus Helicopters Model AS350B, AS350BA, AS350BB, AS350B1, 
AS350B2, AS350B3, AS355E, AS355F, AS355F1, AS355F2, AS355N and AS355NP 
helicopters. Model AS350BB helicopters are not certificated by the FAA 
and are not included on the U.S. type certificate data sheet; this AD 
therefore does not include those helicopters in the applicability.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2018-15-02, Amendment 39-19334 (83 FR 
34029, July 19, 2018) (AD 2018-15-02). AD 2018-15-02 applied to certain 
Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, 
AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. The 
NPRM published in the Federal Register on December 16, 2020 (85 FR 
81427). The NPRM was prompted by a report of several cases of damaged 
TR pitch rod ball joints. The NPRM proposed to continue to require the 
repetitive inspections of the TR pitch rod for a damaged elastomeric 
ball joint, as specified in an EASA AD. The NPRM also proposed to allow 
the repetitive inspection intervals specified in AD 2018-15-02 to be 
extended to correspond with the intervals for the inspection of the TR 
pitch rod specified in the airworthiness limitation section of the 
applicable helicopter maintenance manual, as specified in an EASA AD. 
The FAA is issuing this AD to address damage to the elastomeric ball 
joint on the TR pitch change rod. This condition could result in 
failure of the TR pitch change rod and subsequent loss of control of 
the helicopter.

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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
    <bullet> 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 2017-0020R1 describes procedures for repetitively 
inspecting the TR pitch rod for a damaged (debonding, extrusion, or 
cracking) elastomeric ball joint and corrective action. The corrective 
action includes replacing an affected TR pitch rod with a serviceable 
TR pitch rod. 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 955 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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                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
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Retained actions from AD 2018-15-02...  0.5 work-hour x $85 per               $0          $42.50      $40,587.50
                                         hour = $42.50.
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    This new AD adds no new costs to affected operators.
    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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1 work-hour x $85 per hour = $85......          $3,358           $3,443
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[[Page 13991]]

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:
0
a. removing Airworthiness Directive (AD) 2018-15-02, Amendment 39-19334 
(83 FR 34029, July 19, 2018); and
0
b. adding the following new AD:

2021-05-09 Airbus Helicopters: Amendment 39-21452; Docket No. FAA-
2020-1132; Project Identifier MCAI-2020-01386-R.

(a) Effective Date

    This airworthiness directive (AD) is effective April 16, 2021.

(b) Affected ADs

    This AD replaces AD 2018-15-02, Amendment 39-19334 (83 FR 34029, 
July 19, 2018) (AD 2018-15-02).

(c) Applicability

    This AD applies to Airbus Helicopters Model AS350B, AS350B1, 
AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N, 
and AS355NP helicopters, certificated in any category, as identified 
in European Union Aviation Safety Agency (EASA) AD 2017-0020R1, 
dated May 22, 2019 (EASA AD 2017-0020R1).

(d) Subject

    Joint Aircraft System Component (JASC) Code 6720, Tail Rotor 
Control System.

(e) Reason

    This AD was prompted by a report of several cases of damaged 
tail rotor (TR) pitch rod ball joints. The FAA is issuing this AD to 
address damage to the elastomeric ball joint on the TR pitch change 
rod. This condition could result in failure of the TR pitch change 
rod and subsequent loss of control of the helicopter.

(f) Compliance

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

(g) New Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2017-0020R1.

(h) Exceptions to EASA AD 2017-0020R1

    (1) Where EASA AD 2017-0020R1 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2017-0020R1 refers to February 9, 2017 (the 
effective date of EASA AD 2017-0020-E, dated February 9, 2017), this 
AD requires using August 3, 2018 (the effective date of AD 2018-15-
02).
    (3) The ``Remarks'' section of EASA AD 2017-0020R1 does not 
apply to this AD.
    (4) Although the service information referenced in EASA AD 2017-
0020R1 specifies to discard certain parts, this AD does not include 
that requirement.
    (5) Where EASA AD 2017-0020R1 refers to flight hours (FH), this 
AD requires using hours time-in-service (TIS).
    (6) Where paragraph (1) of EASA AD 2017-0020R1 specifies an 
initial compliance time of ``Before exceeding 50 FH [flight hours] 
since the last inspection per ALS [airworthiness limitations] 
chapter 04-20-00, or within 10 FH or 7 days, whichever occurs 
first,'' for this AD, the initial compliance time is within 10 hours 
TIS.
    (7) For the inspections specified in paragraph (1) of EASA AD 
2017-0020R1: Accomplishing the actions specified in paragraphs 
(h)(7)(i) and (ii) of this AD before the effective date of this AD 
are acceptable for compliance with the inspections specified in in 
paragraph (1) of EASA AD 2017-0020R1. On or after the effective date 
of this AD, comply with the inspections as specified in paragraph 
(1) of EASA AD 2017-0020R1.
    (i) Manually induce a flapping movement in the TR blade until 
the pitch change rod rotates a minimum of 10 degrees.
    (ii) Inspect both faces of the blade side of the ball joint 
elastomer for debonding, extrusion, and cracks.
    (8) Although the service information referenced in EASA AD 2017-
0020R1 permits certain actions to be performed by a mechanical 
engineering technician or pilot, this AD requires that the actions 
be performed by a qualified mechanic.

(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 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 Katherine Venegas, 
Aviation Safety Engineer, Cabin Safety, Mechanical and Environmental 
Systems Section, Los Angeles ACO Branch, FAA, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5353; fax: 562-
627-5210; 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 2017-0020R1, 
dated May 22, 2019.
    (ii) [Reserved]
    (3) For EASA AD 2017-0020R1, 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.

[[Page 13992]]

    (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-
2020-1132.
    (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 February 19, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-05145 Filed 3-11-21; 8:45 am]
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