DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-0016; Project Identifier MCAI-2022-00416-R]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Airbus Helicopters Model EC120B, EC130B4, and EC130T2
helicopters. This proposed AD was prompted by a report of corrosion
detected on certain part-numbered landing gear assemblies. This
proposed AD would require, for helicopters with certain part-numbered
landing gear assemblies installed, visually inspecting for cracks and
corrosion; borescope inspecting; and if required, removing corrosion,
measuring thickness, interpreting results of the measurements, applying
chemical conversion coating and primer, and removing affected parts
(landing gear assembly) and affected part sub-assemblies (front or rear
crossbeam or left-hand or right-hand skid assembly) from service and
replacing with airworthy parts. This proposed AD would allow an
affected part or affected part sub-assembly to be installed on a
helicopter if certain actions in this proposed AD are accomplished. 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 March 6,
2023.

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 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 between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-0016; 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, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For service information identified in this NPRM, contact
Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
www.airbus.com/helicopters/services/technical-support.html.
You may view this 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 at
regulations.gov under Docket No. FAA-2023-0016.

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 ADDRESSES. Include ``Docket No. FAA-2023-0016; Project Identifier
MCAI-2022-00416-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.

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
Stephanie Sunderbruch, Aerospace Engineer, Safety Risk Management
Section, Systems Policy Branch, Policy & Innovation Division, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-4659;
email Stephanie.L.Sunderbruch@faa.gov. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.

Background

The European Union Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union, has issued
EASA AD 2022-0053, dated March 23, 2022 (EASA AD 2022-0053), to correct
an unsafe condition for Airbus Helicopters Model EC 120 B, EC 130 B4,
and EC 130 T2 helicopters, all serial numbers. EASA advises an
occurrence was reported of corrosion found on a landing gear assembly
of a Model EC 130 helicopter. EASA further advises that other
helicopter models are affected by the same unsafe condition due to
design similarity. This condition, if not addressed, could result in
the landing gear collapsing, damage to the helicopter, and injury to
occupants.
Accordingly, EASA AD 2022-0053 requires, for helicopters with
certain part-numbered landing gear assemblies installed, a one-time
visual inspection of the external areas of the landing gear tubes for
corrosion and cracks, and a borescope inspection of the internal sides
of the landing gear tubes for corrosion (including, but not limited to,
leafing and exfoliant corrosion) and cracks. EASA AD 2022-0053 also
requires contacting Airbus Helicopters for approved corrective action
if any crack, or leafing or exfoliant corrosion, is found or if the
remaining thickness of affected part sub-assemblies do not meet
specified acceptability criteria during any of the inspections. EASA AD
2022-0053 allows replacing the affected part sub-assembly in lieu of
contacting Airbus Helicopters for approved corrective action. EASA AD
2022-0053 also requires reporting inspection results to Airbus
Helicopters within 30 days after the inspection or within 30 days after
the effective date of EASA AD 2022-0053, whichever occurs later.
Additionally, EASA AD 2022-0053 allows credit for certain
inspections and corrective actions if those actions were done before
the effective date of EASA AD 2022-0053, and allows an affected part or
affected part sub-assembly to be installed on a helicopter if certain
requirements of EASA AD 2022-0053 are met. EASA considers its AD an
interim action and states that further AD action may follow.

FAA's Determination

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 is proposing this AD
after evaluating all known relevant information and determining that
the unsafe condition described previously is likely to exist or develop
on other helicopters of these same type designs.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB)
No. EC120-32A014 (EC120-32A014 Rev 1), for Model EC120B helicopters and
Airbus Helicopters ASB No. EC130-32A013 (EC130-32A013 Rev 1), for Model
EC130B4 and EC130T2 helicopters, both Revision 1, and both dated
October 17, 2022. This service information includes Detail A Figure 3
(EC120-32A014 Rev 1) and Detail A Figure 4 (EC130-32A013 Rev 1), which
identify the areas and zones to be inspected for cracks and corrosion
(including, but not limited to leafing and exfoliant corrosion). This
service information also includes Table 3, which identifies the minimum
material thickness permitted after corrosion is removed. Additionally,
this service information specifies procedures for visually inspecting
the external areas and borescope inspecting the internal areas of the
landing gear tubes, removing corrosion, measuring thickness,
interpreting results of the measurements, and applying a chemical
conversion coating and primer.
This service information 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.

Proposed AD Requirements in This NPRM

This proposed AD would require, for helicopters with certain part-
numbered landing gear assemblies installed, removing and cleaning
certain parts and visually inspecting the external areas of the landing
gear tubes for cracks and corrosion (including, but not limited to,
leafing and exfoliant corrosion). If any crack, leafing corrosion, or
exfoliant corrosion is detected, this proposed AD would require
removing certain parts from service and replacing with airworthy parts.
If any corrosion other than leafing or exfoliant corrosion is detected,
this proposed AD would require removing the corrosion.
This proposed AD would also require borescope inspecting the
internal side of the landing gear tubes for cracks and corrosion
(including, but not limited to, leafing and exfoliant corrosion). If
any crack, leafing corrosion, or exfoliant corrosion is detected, this
proposed AD would require removing any affected part from service and
replacing it with an airworthy part. If any corrosion other than
leafing or exfoliant corrosion is detected, this proposed AD would
require removing the corrosion.
If any corrosion other than leafing or exfoliant corrosion is
detected during any of the inspections required by this proposed AD,
this proposed AD would require removing all corrosion and measuring the
remaining thickness of the landing gear tubes. This proposed AD would
require interpreting the results of the measurements and if the
remaining thickness does not meet the permitted criteria as specified,
this proposed AD would require removing each affected sub-assembly from
service and replacing it with an airworthy part. If the remaining
thickness meets the permitted criteria as specified, this proposed AD
would require applying a chemical conversion coating and a double layer
of primer.
Additionally, this proposed AD would allow an affected part or
affected part sub-assembly to be installed on a helicopter, if certain
requirements of this proposed AD have been accomplished.

Differences Between This Proposed AD and EASA AD 2022-0053

EASA AD 2022-0053 requires, for certain helicopters, the initial
inspections to be completed within certain compliance times specified
in Table 1 of EASA AD 2022-0053, whereas this proposed AD would require
the initial inspections to be completed within 13 months after the
effective date of this proposed AD. EASA AD 2022-0053 requires
contacting Airbus Helicopters for repair instructions if any cracks,
leafing corrosion, or exfoliant corrosion are found, or if the residual
thickness of an affected part sub-assembly does not meet certain
criteria, whereas this proposed AD would require removing the affected
part or part sub-assembly from service instead. EASA AD 2022-0053
allows credit for certain inspections and corrective actions if these
requirements were accomplished in accordance with previously issued
service information, whereas this proposed AD would not allow credit
for the inspections and corrective actions if previously issued service
information was used. EASA AD 2022-0053 requires reporting the
inspection results to Airbus Helicopters, whereas this proposed AD
would not require reporting.

Interim Action

The FAA considers this proposed AD would be an interim action. Once
final action has been identified, the FAA might consider further
rulemaking.

Costs of Compliance

The FAA estimates that this AD, if adopted as proposed, would
affect 353 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 proposed AD.
Removing and cleaning parts, and visually inspecting the external
surface of each landing gear tube for cracks and corrosion would take
about 2 work-hours for an estimated cost of $170 per inspection, up to
$680 per helicopter (4 landing gear tubes per helicopter), and up to
$240,040 for the U.S. fleet.
Borescope inspecting the internal side of each landing gear tube
for cracks and corrosion (including, but not limited to, leafing and
exfoliant corrosion) would take about 1 work-hour for an estimated cost
of $85 per inspection, up to $340 per helicopter (4 landing gear tubes
per helicopter), and up to $120,020 for the U.S. fleet.
If required, applying a chemical conversion coating and a double
layer of primer would take about 2 work-hours and parts would cost a
minimal amount for an estimated cost of $170 per helicopter and up to
$60,010 for the U.S. fleet.
If required, disassembling certain zones and removing corrosion
would take about 1 work hour for an estimated cost of $85 per
helicopter.
If required, measuring the thickness of the internal side of each
landing gear tube and interpreting the results would take up to 1 work-
hour for an estimated cost of $85 per helicopter.
If required, replacing a landing gear assembly would take about 2
work-hours and parts would cost up to $106,612 for an estimated cost of
up to $106,782 per replacement.
If required, replacing a front crossbeam would take about 1 work-
hour and parts would cost up to $9,081 for an estimated cost of up to
$9,166 per replacement.
If required, replacing a rear crossbeam would take about 1 work-
hour and parts would cost up to $11,639 for an estimated cost of up to
$11,724 per replacement.
If required, replacing a right-hand or left-hand skid assembly
would take about 1 work-hour and parts would cost up to $21,447 for an
estimated cost of up to $21,532 per skid assembly replacement.

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

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, I certify this proposed regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: