AD 2022-06-12

[Federal Register Volume 87, Number 64 (Monday, April 4, 2022)]
[Rules and Regulations]
[Pages 19376-19378]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-06940]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1176; Project Identifier MCAI-2021-00755-R; 
Amendment 39-21978; AD 2022-06-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Helicopters Model SA330J helicopters. This AD was 
prompted by a review of Model EC225LP helicopter data that revealed 
potential tightening torque loss of the attachment screws of the upper 
deck fittings of the three main gearbox (MGB) suspension bars. Due to 
design similarities, the MGB right-hand (RH) rear fittings and MGB RH 
rear fitting attachment screws on Model SA330J helicopters could also 
be affected. Additional analysis confirmed that the service life limit 
(life limit) (SLL) for these affected MGB RH rear fittings needs to be 
reduced for helicopters on which these affected parts were operated 
concurrently with metallic main rotor blades installed. This AD 
requires determining the damage value and SLL of each affected MGB RH 
rear fitting, replacing each affected MGB RH rear fitting with a new 
part, and replacing the MGB RH rear fitting attachment screws, 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 May 9, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 9, 2022.

ADDRESSES: For EASA material incorporated by reference (IBR) in this 
final rule, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, 
Germany; telephone: +49 221 8999 000; email: <a href="/cdn-cgi/l/email-protection#84c5c0f7c4e1e5f7e5aae1f1f6ebf4e5aae1f1"><span class="__cf_email__" data-cfemail="66272215260307150748031314091607480313">[email&#160;protected]</span></a>; 
internet: www.easa.europa.eu. You may find the EASA material on the 
EASA website at <a href="https://ad.easa.europa.eu">https://ad.easa.europa.eu</a>. 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 at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by 
searching for and locating Docket No. FAA-2021-1176.

Examining the AD Docket

    You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by 
searching for and locating Docket No. FAA-2021-1176; 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, the 
European Union Aviation Safety Agency (EASA) AD, 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, FAA, 950 L'Enfant Plaza SW, Washington, DC 
20024; telephone: (202) 267-9167; email: <a href="/cdn-cgi/l/email-protection#0f676e6321656a617c6a614f696e6e21686079"><span class="__cf_email__" data-cfemail="b9d1d8d597d3dcd7cadcd7f9dfd8d897ded6cf">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2021-0152R1, dated July 20, 2021 
(EASA AD 2021-0152R1), to correct an unsafe condition for Airbus 
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale, Sud 
Aviation) Model SA 330 J helicopters, all serial numbers, which were 
modified in service in accordance with the instructions of Eurocopter 
France Service Bulletin (SB) No. 01.20 (part of which is the in-service 
retrofit Modification (Mod) 07 40043), except those on which each 
affected part (as defined in EASA AD 2021-0152R1) was replaced with a 
new part (not previously installed) during

[[Page 19377]]

embodiment of Eurocopter France SB No. 01.20 in service.
    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 SA330J helicopters. The NPRM published in the Federal 
Register on January 13, 2022 (87 FR 2085). The NPRM was prompted by a 
review of Model EC225LP helicopter in-service data that revealed 
potential tightening torque loss of the attachment screws of the upper 
deck fittings of the three MGB suspension bars. The FAA issued AD 2020-
06-12, Amendment 39-19881 (85 FR 19077, April 6, 2020) to address the 
unsafe condition on Model EC225LP helicopters). Due to design 
similarities, the MGB RH rear fittings and MGB RH rear fitting 
attachment screws on Model SA330J helicopters could also be affected. 
Additional analysis confirmed that the SLL for these affected MGB RH 
rear fittings needs to be reduced for helicopters on which these 
affected parts were operated concurrently with metallic main rotor 
blades (pre-Airbus Helicopters Modification 07 40043) installed. Airbus 
Helicopters Modification 07 40043 introduced the installation of 
composite main rotor blades. The NPRM proposed to require determining 
the damage value and SLL of each affected MGB RH rear fitting, 
replacing each affected MGB RH rear fitting with a new part, and 
replacing the MGB RH rear fitting attachment screws, as specified in 
EASA AD 2021-0152R1.
    The FAA is issuing this AD to address tightening torque loss of the 
attachment screws of the upper deck fittings of the three MGB 
suspension bars. The unsafe condition, if not addressed, could result 
in structural failure of the MGB RH rear fittings and MGB RH rear 
fitting attachment screws, resulting in detachment of the MGB 
suspension bars and consequent loss of control of the helicopter. See 
EASA AD 2021-0152R1 for additional background information.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA reviewed the relevant 
data and determined that air safety requires adopting this AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these helicopters. Except for minor editorial changes, 
this AD is adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    EASA AD 2021-0152R1 requires determining the damage value of each 
affected MGB RH rear fitting by calculating the damage caused during 
the time each affected part was operated concurrently with metallic 
main rotor blades installed on the helicopter, calculating the SLL for 
each affected MGB RH rear fitting, and eventually replacing each 
affected MGB RH rear fitting and the MGB RH rear fitting attachment 
screws with new parts. 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 15 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Determine damage value and SLL........  1 work-hours x $85 per                $0             $85          $1,275
                                         hour = $85.
Replace parts.........................  8 work-hours x $85 per             7,540           8,220         123,300
                                         hour = $680.
----------------------------------------------------------------------------------------------------------------

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:

2022-06-12 Airbus Helicopters: Amendment 39-21978; Docket No.

[[Page 19378]]

FAA-2021-1176; Project Identifier MCAI-2021-00755-R.

(a) Effective Date

    This airworthiness directive (AD) is effective May 9, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Model SA330J helicopters, 
certificated in any category, as identified in European Union 
Aviation Safety Agency (EASA) AD 2021-0152R1, dated July 20, 2021 
(EASA AD 2021-0152R1).

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor 
Drive System.

(e) Unsafe Condition

    This AD was prompted by a review of Airbus Helicopters Model 
EC225LP helicopter data that revealed potential tightening torque 
loss of the attachment screws of the upper deck fittings of the 
three main gearbox (MGB) suspension bars. Due to design 
similarities, the MGB right-hand (RH) rear fittings and MGB RH rear 
fitting attachment screws on Model SA330J helicopters could also be 
affected. Additional analysis confirmed that the service life limit 
(life limit) (SLL) for the affected MGB RH rear fittings needs to be 
reduced for helicopters on which these affected parts were operated 
concurrently with metallic main rotor blades installed. The FAA is 
issuing this AD to address tightening torque loss of the attachment 
screws of the upper deck fittings of the three MGB suspension bars. 
The unsafe condition, if not addressed, could result in structural 
failure of the MGB RH rear fittings and MGB RH rear fitting 
attachment screws, resulting in detachment of the MGB suspension 
bars and consequent 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, EASA AD 2021-0152R1.

(h) Exceptions to EASA AD 2021-0152R1

    (1) Where EASA AD 2021-0152R1 requires compliance in terms of 
flight hours, this AD requires using hours time-in-service.
    (2) Where EASA AD 2021-0152R1 refers to July 9, 2021 (the 
effective date of EASA AD 2021-0152R1, dated June 25, 2021), this AD 
requires using the effective date of this AD.
    (3) Where the service information referenced in EASA AD 2021-
0152R1 specifies discarding parts, this AD requires removing those 
parts from service.
    (4) Although the service information referenced in EASA AD 2021-
0152R1 specifies that ``The work must be performed on the helicopter 
by the operator.'' this AD does not require that the operator 
perform the work.
    (5) This AD does not mandate compliance with the ``Remarks'' 
section of EASA AD 2021-0152R1.
    (6) The preliminary steps specified in paragraph 3.B.1. of the 
service information referenced in EASA AD 2021-0152R1 are not 
required for compliance with this AD.
    (7) Although the service information referenced in EASA AD 2021-
0152R1 specifies contacting Airbus Helicopters if the time since new 
(TSN) is unknown at the retrofit date, this AD requires determining 
the damage value and the SLL of each affected part but does not 
require contacting Airbus Helicopters if the TSN is unknown at the 
retrofit date.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2021-
0152R1 specifies to submit certain information to the manufacturer, 
this AD does not include that requirement.

(j) 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 (k) of 
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#bc8591fdeaef91fdf5ee918b8f8c91fdf1f3fffcdadddd92dbd3ca"><span class="__cf_email__" data-cfemail="e7decaa6b1b4caa6aeb5cad0d4d7caa6aaa8a4a7818686c9808891">[email&#160;protected]</span></a>.
    (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 Hal Jensen, 
Aerospace Engineer, Operational Safety Branch, FAA, 950 L'Enfant 
Plaza SW, Washington, DC 20024; telephone: (202) 267-9167; email: 
<a href="/cdn-cgi/l/email-protection#e68e878ac88c8388958388a6808787c8818990"><span class="__cf_email__" data-cfemail="b4dcd5d89aded1dac7d1daf4d2d5d59ad3dbc2">[email&#160;protected]</span></a>.

(l) 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 this AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2021-0152R1, 
dated July 20, 2021.
    (ii) [Reserved].
    (3) For EASA AD 2021-0152R1, contact EASA, Konrad-Adenauer-Ufer 
3, 50668 Cologne, Germany; telephone: +49 221 8999 000; email: 
<a href="/cdn-cgi/l/email-protection#6021241320050113014e0515120f10014e0515"><span class="__cf_email__" data-cfemail="2465605764414557450a4151564b54450a4151">[email&#160;protected]</span></a>; internet: www.easa.europa.eu. You may find the 
EASA material on the EASA website at <a href="https://ad.easa.europa.eu">https://ad.easa.europa.eu</a>.
    (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 at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2021-1176.
    (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 
<a href="/cdn-cgi/l/email-protection#096f7b2760677a796c6a7d6066674967687b68276e667f"><span class="__cf_email__" data-cfemail="b6d0c498dfd8c5c6d3d5c2dfd9d8f6d8d7c4d798d1d9c0">[email&#160;protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued on March 10, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2022-06940 Filed 4-1-22; 8:45 am]
BILLING CODE 4910-13-P