[Federal Register Volume 88, Number 12 (Thursday, January 19, 2023)]
[Proposed Rules]
[Pages 3330-3334]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-00886]


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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

[[Page 3331]]

(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 [email protected]. 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

[[Page 3332]]

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.

[[Page 3333]]

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

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:

Airbus Helicopters: Docket No. FAA-2023-0016; Project Identifier 
MCAI-2022-00416-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by March 6, 2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Helicopters Model EC120B, EC130B4, 
and EC130T2 helicopters certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 3213, Main Landing 
Gear Strut, Axle, Truck.

(e) Unsafe Condition

    This AD was prompted by a report of corrosion detected on 
certain part-numbered landing gear assemblies. The FAA is issuing 
this AD to detect corrosion and cracks on the landing gear tubes. 
The unsafe condition, if not addressed, could result in the landing 
gear collapsing, damage to the helicopter, and injury to occupants.

(f) Compliance

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

(g) Required Actions

    (1) Within 13 months after the effective date of this AD, for 
Model EC120B helicopters with landing gear assembly part number (P/
N) C321A2106102, P/N C321A2501101, P/N C321A2501102, P/N 
C321A2601051AA, P/N C321A2601051CA, or P/N C321A2601052 installed, 
and for Model EC130B4 and EC130T2 helicopters with landing gear 
assembly P/N 350A41-0077-0201, P/N 350A41-0080-1102, P/N 350A41-
0080-1103, P/N 350A41-0081-0201, P/N 350A41-0082-0101, or P/N 
350A41-0082-0102 installed, except those having a date of first 
installation on a helicopter of February 16, 2022 or later; and for 
helicopters with a landing gear assembly having a P/N specified in 
this paragraph, with an unknown installation date, do the following:
    (i) Remove the landing gear fairing from the rear crossbeam and 
clean the external areas of each of the landing gear tubes item a, 
item c, item d, and item e, including Zones B1, B2, C1, C2, D, E, F, 
and M as depicted in Detail A, Figure 3, and Details B and C, Figure 
4 of Airbus Helicopters Alert Service Bulletin (ASB) No. EC120-
32A014 (ASB EC120-32A014 Rev 1), or as depicted in Detail A, Figure 
4, and Details B and C, Figure 5 of Airbus Helicopters ASB No. 
EC130-32A013 (ASB EC130-32A013 Rev 1), both Revision 1, and both 
dated October 17, 2022, as applicable to your model helicopter.
    (ii) Visually inspect the external areas of each of the landing 
gear tubes item a, item c, item d, and item e, including Zones B1, 
B2, C1, C2, D, E, F, and M for corrosion (including, but not limited 
to leafing and exfoliant corrosion) and cracks.
    (A) If any crack or leafing or exfoliant corrosion is detected, 
before further flight, remove the affected part from service and 
replace it with an airworthy part.
    (B) If any corrosion is detected in Zone C1, C2, or E, other 
than leafing or exfoliant corrosion, before further flight, 
disassemble the landing gear and using a non-metal abrasive pad, 
remove all corrosion from all zones.
    (C) If any corrosion is detected in only Zone B1, B2, D, F, or 
M, other than leafing or exfoliant corrosion, before further flight, 
using a non-metal abrasive pad, remove all corrosion from all zones.
    (iii) Borescope inspect the internal side of each of the landing 
gear tubes item a, item c, item d, and item e, including Zones B1, 
B2, C1, C2, D, E, F, and M for corrosion (including, but not limited 
to leafing and exfoliant corrosion) and cracks.
    (A) If any crack, leafing corrosion, or exfoliant corrosion is 
detected, before further flight, remove the affected part from 
service and replace it with an airworthy part. (B) If any corrosion 
is detected in Zone C1, C2, or E, other than leafing or exfoliant 
corrosion before further flight, disassemble the landing gear and 
using a non-metal abrasive pad, remove all corrosion from all zones.
    (C) If any corrosion is detected in only Zone B1, B2, D, F, or 
M, other than leafing or exfoliant corrosion, before further flight, 
using a non-metal abrasive pad, remove all corrosion from all zones.
    (iv) Before further flight after performing the inspections 
required by paragraphs (g)(1)(ii) and (iii) of this AD, if any 
corrosion was detected during any inspection required by paragraphs 
(g)(1)(ii) and (iii) of this AD other than leafing or exfoliant 
corrosion, using an ultrasonic thickness gauge, measure the 
remaining thickness of the landing gear tubes in the zones where any 
corrosion was removed. Interpret the results of the measurement 
using the criteria specified in Table 3 of ASB EC120-32A014 Rev 1 or 
Table 3 of EC130-32A013 Rev 1, as applicable to your model 
helicopter. If the remaining thickness does not meet the permitted 
criteria as specified, before further flight, remove each affected 
sub-assembly from service and replace it with an airworthy part. If 
the remaining thickness meets the permitted criteria as specified, 
before further flight, accomplish the actions required by paragraph 
(g)(1)(v) of this AD.
    (v) Apply a chemical conversion coating (Alodine 1200) or 
equivalent, and a double layer of chromate Primer P05 and Primer 
P20, or equivalent, below the collar in Zones F and M and to any 
reworked zone.
    (2) For Model EC120B helicopters, as of the effective date of 
this AD, do not install landing gear assembly P/N C321A2106102, P/N 
C321A2501101, P/N C321A2501102, P/N C321A2601051AA, P/N 
C321A2601051CA, or P/N C321A2601052, previously installed with an 
unknown installation date or a date of first installation on a 
helicopter before February 16, 2022; and do not install a front 
crossbeam, rear crossbeam, left-hand (LH) skid assembly, or right-
hand (RH) skid assembly having a P/N identified in Table 2 of ASB 
EC120-32A014 Rev 1, previously installed with an unknown 
installation date, or a date of first installation on a helicopter 
before February 16, 2022, on any helicopter; unless the actions 
required by paragraphs (g)(1)(i) through (v) of this AD, as 
applicable, have been accomplished on the part.
    (3) For Model EC130B4 and EC130T2 helicopters, as of the 
effective date of this AD, do not install landing gear assembly P/N 
350A41-0077-0201, P/N 350A41-0080-1102, P/N 350A41-0080-1103, P/N 
350A41-0081-0201, P/N 350A41-0082-0101, or P/N 350A41-0082-0102, 
previously installed with an unknown installation date or a date of 
first installation on a helicopter before February 16, 2022, and do 
not install a front crossbeam, rear crossbeam, LH skid assembly, or 
RH skid assembly, having a P/N identified in Table 2 of ASB EC130-
32A013 Rev 1 previously installed with an unknown installation date, 
or a date of first installation on a helicopter before February

[[Page 3334]]

16, 2022, on any helicopter, unless the actions required by 
paragraphs (g)(1)(i) through (v) of this AD, as applicable, have 
been accomplished on the part.

(h) 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 (i)(2) 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.

(i) Additional Information

    (1) Refer to European Union Aviation Safety Agency (EASA) AD 
2022-0053, dated March 23, 2022, for related information. This EASA 
AD may be found in the AD docket at regulations.gov under Docket No. 
FAA-2023-0016.
    (2) For more information about this AD, contact 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 [email protected].

(j) 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) Airbus Helicopters Alert Service Bulletin (ASB) No. EC120-
32A014, Revision 1, dated October 17, 2022.
    (ii) Airbus Helicopters ASB No. EC130-32A013, Revision 1, dated 
October 17, 2022.
    (3) For service information identified in this AD, contact 
Airbus Helicopters, 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.
    (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 [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on January 12, 2023.
Gaetano A. Sciortino,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-00886 Filed 1-18-23; 8:45 am]
BILLING CODE 4910-13-P