80556 Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations 

(i) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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 

responsible Flight Standards 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: 9-AVS-AIR-730-AMOC@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the responsible Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, International Validation 

Branch, FAA; or EASA; or Deutsche Aircraft 

GmbH’s EASA Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(j) Additional Information 

For more information about this AD, 

contact Todd Thompson, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 206– 

231–3228; email todd.thompson@faa.gov. 

(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 2023–0081, dated April 18, 2023. 

(ii) [Reserved] 

(3) For EASA AD 2023–0081, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email: ADs@easa.europa.eu; website: 

easa.europa.eu. You may find this EASA AD 

on the EASA website: ad.easa.europa.eu. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 216th 

Street, Des Moines, WA. For information on 

the availability of this material at the FAA, 

call 206–231–3195. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit www.archives.gov/federal-register/cfr/ 

ibr-locations or email fr.inspection@nara.gov. 

Issued on October 30, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–25504 Filed 11–17–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1720; Project 

Identifier MCAI–2023–00003–R; Amendment 

39–22598; AD 2023–22–14] 

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 Airbus 

Helicopters Model SA–365C1, SA– 

365C2, and SA–365N helicopters. This 

AD was prompted by reports of 

damaged control rod dual bearings (dual 

bearings) that are installed on the tail 

rotor gearbox (TGB). This AD requires 

repetitively inspecting the TGB 

magnetic plug for particles, analyzing 

any particles collected, taking corrective 

actions if necessary, and reporting 

certain information. Finally, this AD 

allows an affected dual bearing to be 

installed on a helicopter if certain 

actions are accomplished, 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 December 

26, 2023. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 26, 2023. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1720; 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. 

Material Incorporated by Reference: 

• For EASA material identified in this 

final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; internet 

easa.europa.eu. You may find the EASA 

material on the EASA website 

ad.easa.europa.eu. 

• You may view this material at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Parkway, 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–2023–1720. 

Other Related Service Information: 

For Airbus Helicopters service 

information identified in this AD, 

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 

airbus.com/en/products-services/ 

helicopters/hcare-services/airbusworld. 

You may also view this service 

information at the FAA contact 

information under Material 

Incorporated by Reference above. 

FOR FURTHER INFORMATION CONTACT: 

Kevin Kung, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone (781) 

238–7244; email 9-AVS-AIR-BACOCOS@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued a series of EASA ADs 

with the most recent being EASA AD 

2023–0001, dated January 4, 2023 

(EASA AD 2023–0001), to correct an 

unsafe condition on Airbus Helicopters 

Model SA 365 C1, SA 365 C2, SA 365 

C3, and SA 365 N helicopters, all 

manufacturer serial numbers. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Airbus Helicopters Model SA– 

365C1, SA–365C2, and SA–365N 

helicopters. The NPRM published in the 

Federal Register on September 1, 2023 

(88 FR 60402). The NPRM was 

prompted by reports of damaged dual 

bearings that are installed on the TGB. 

The NPRM proposed to require 

repetitively inspecting the TGB 

magnetic plug for particles, analyzing 

any particles collected, taking corrective 

actions if necessary, and reporting 

certain information. The NPRM also 

proposed to allow installing an affected 

dual bearing on a helicopter if certain 

actions are accomplished, as specified 

in EASA AD 2023–0001. 

The FAA is issuing this AD to inspect 

for particles in the TGB magnetic plug. 

The unsafe condition, if not addressed, 

could result in loss of yaw control and 

subsequent loss of control of the 

helicopter. See EASA AD 2023–0001 for 

additional background information. 


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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 clarifying the conditions that could 

exist after performing a metallurgical 

analysis in paragraph (h)(17) of this AD 

and minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2023–0001 requires 

continuing close monitoring for certain 

helicopters and analyzing any particles 

collected during required inspections, 

repetitively inspecting the magnetic 

plug of the TGB for particles, and 

corrective actions. Corrective actions 

include replacing or repairing an 

affected TGB; sending certain 

information and affected parts to the 

manufacturer; accomplishing a 

metallurgical analysis; and replacing an 

affected dual bearing and other affected 

parts. 

Additionally, EASA AD 2023–0001 

requires for certain helicopters with an 

affected dual bearing installed, 

performing a one-time inspection of the 

dual bearing. 

EASA AD 2023–0001 allows a dual 

bearing part number (P/N) 360A33– 

4052–00 installed on a control rod of a 

TGB P/N 365A33–4000–00, 365A33– 

4000–01, 365A33–4000–02, or 365A33– 

5000–00 to be installed on an aircraft, if 

certain requirements are met. 

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. 

Other Related Service Information 

The FAA reviewed Airbus Helicopters 

Alert Service Bulletin (ASB) No. 

AS365–05.00.83 and Airbus Helicopters 

ASB No. SA365–05.35, both Revision 0, 

and both dated February 7, 2022. This 

service information specifies procedures 

to inspect the magnetic plug of the TGB 

for particles; analyze and define the 

particles collected; replace an affected 

TGB and an affected dual bearing; 

perform a metallurgical analysis; and 

report certain information to the 

manufacturer. 

The FAA also reviewed Airbus 

Helicopters ASB No. AS365–65.00.20 

Revision 0, dated November 23, 2022. 

This service information specifies 

procedures for a one-time inspection of 

a certain dual bearing and replacement 

of the dual bearing if any particles are 

found. 

Additionally, the FAA reviewed 

Airbus Standard Practices Manual, 20– 

08–01–601, Periodical monitoring of 

lubricating oil checking elements, dated 

July 7, 2020. This service information 

specifies procedures for analyzing 

collected particles. 

Interim Action 

The FAA considers this AD to be an 

interim action. If final action is later 

identified, the FAA might consider 

further rulemaking then. 

Differences Between This AD and the 

EASA AD 

EASA AD 2023–0001 applies to 

Airbus Helicopters Model SA 365 C3 

helicopters, whereas this AD does not 

because that model is not FAA typecertificated. 

This AD clarifies that Model SA– 

365N helicopters with an affected dual 

bearing installed that has an unknown 

total number of hours time-in-service 

accumulated on the dual bearing are 

subject to certain requirements in this 

AD, whereas EASA AD 2023–0001 is 

unclear about those parts with an 

accumulated usage that cannot be 

determined. 

EASA AD 2023–0001 does not clarify 

what is considered an anomaly 

regarding the chip detector and conical 

housing chip detector; whereas, for this 

AD, an anomaly may be indicated by the 

magnetic component of the TGB chip 

detector or the conical housing chip 

detector not being magnetized. EASA 

AD 2023–0001 also does not clarify 

what is considered good condition 

regarding the chip detector or conical 

housing chip detector; whereas, for this 

AD, good condition for the chip detector 

is indicated when there are no signs of 

wear on the locking systems (including 

wear on the bayonets and slotted tubes) 

and good condition for the conical 

housing chip detector is when the 

conical housing chip detector is 

magnetized. 

Where EASA AD 2023–0001 describes 

a doubt concerning the physical 

characteristics of any collected particles, 

this AD requires performing a 

metallurgical analysis. If there is any 

doubt remaining after performing the 

metallurgical analysis, EASA AD 2023– 

0001 requires contacting Airbus, 

whereas this AD requires removing an 

affected TGB from service and replacing 

it with an airworthy part, or repairing 

the TGB in accordance with a method 

approved by the FAA, EASA, or Airbus 

Helicopters’ Design Organizational 

Approval (DOA) if the type, size, or 

classification of any collected particle 

cannot be determined after performing a 

metallurgical analysis. 

If any particles (including abrasiontype particles) are found on the 

magnetic plug during any inspection 

that are outside the limits, EASA AD 

2023–0001 requires replacing each 

affected dual bearing with a serviceable 

dual bearing, and replacing the TGB, 

whereas this AD requires removing each 

affected dual bearing and replacing with 

a serviceable dual bearing, or removing 

the TGB from service and replacing it 

with an airworthy TGB, or repairing the 

TGB in accordance with a method 

approved by the FAA, EASA, or Airbus 

Helicopters’ DOA. 

Service information referenced in 

EASA AD 2023–0001 permits a pilot to 

perform a magnetic plug check, whereas 

this AD does not. 

Service information referenced in 

EASA AD 2023–0001 specifies sending 

compliance forms, certain parts, and 

particles to the manufacturer, whereas 

this AD requires reporting certain 

information but does not require 

sending any parts or particles to the 

manufacturer. 

Costs of Compliance 

The FAA estimates that this AD 

affects 1 helicopter 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. 

Inspecting the magnetic plug of the 

TGB for particles takes about 1 workhour for an estimated cost of $85 per 

inspection and up to $85 for the U.S. 

fleet, per inspection cycle. 

Inspecting a dual bearing takes about 

16 work-hours for an estimated cost of 

$1,360 per inspection and up to $1,360 

for the U.S. fleet. If required, replacing 

a dual bearing takes about 1 additional 

work-hour following the inspection and 

parts cost about $6,678 for an estimated 

cost of $6,763 per dual bearing 

replacement. 

If required, analyzing collected 

particles takes about 1 work-hour for an 

estimated cost of $85 per helicopter. If 

required, a metallurgical analysis takes 

about 1 work-hour for an estimated cost 

of $85 per instance. 


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If required, replacing an O-ring takes 

about 1 work-hour and parts cost about 

$100 for an estimated cost of $185 per 

O-ring. 

If required, replacing a TGB takes 

about 8 work-hours and parts cost about 

$155,302 for an estimated cost of 

$155,982 per replacement. 

The FAA has received no definitive 

data for the repair cost of a TGB. 

If required, reporting information to 

the manufacturer takes about 1 workhour for an estimated cost of $85 per 

instance. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a currently valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to take 

approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, and completing and 

reviewing the collection of information. 

All responses to this collection of 

information are mandatory. Send 

comments regarding this burden 

estimate or any other aspect of this 

collection of information, including 

suggestions for reducing this burden to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2023–22–14 Airbus Helicopters: 

Amendment 39–22598; Docket No. 

FAA–2023–1720; Project Identifier 

MCAI–2023–00003–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective December 26, 2023. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model SA–365C1, SA–365C2, and SA–365N 

helicopters, certificated in any category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520, Tail rotor gearbox. 

(e) Unsafe Condition 

This AD was prompted by reports of 

damaged control rod dual bearings (dual 

bearings) installed on the tail rotor gearbox 

(TGB). The FAA is issuing this AD to inspect 

for particles in the TGB magnetic plug. The 

unsafe condition, if not addressed, could 

result in loss of yaw control and subsequent 

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, European Union Aviation 

Safety Agency (EASA) AD 2023–0001, dated 

January 4, 2023 (EASA AD 2023–0001). 

(h) Exceptions to EASA AD 2023–0001 

(1) Where EASA AD 2023–0001 requires 

compliance in terms of flight hours, this AD 

requires using hours time-in-service. 

(2) Where EASA AD 2023–0001 refers to 

the effective dates specified in paragraphs 

(h)(2)(i) and (ii) of this AD, this AD requires 

using the effective date of this AD. 

(i) March 21, 2022 (the effective date of 

EASA AD 2022–0038, dated March 7, 2022). 

(ii) The effective date of EASA AD 2023– 

0001. 

(3) Where EASA AD 2023–0001 defines 

Groups, for Group 2, replace the text ‘‘SA 365 

N helicopters with an affected part installed 

that has accumulated 500 flight hours (FH) or 

more since first installation on a helicopter,’’ 

with ‘‘SA–365N helicopters with an affected 

part installed that has accumulated 500 or 

more total hours time-in-service on the 

affected part or the total hours time-inservice on the affected part cannot be 

determined.’’ 

(4) Where the service information 

referenced in EASA AD 2023–0001 permits 

a pilot to perform a check of the magnetic 

plug, this AD requires that action be 

performed by a person authorized under 14 

CFR 43.3. 

(5) Where Note 1 of EASA AD 2023–0001 

specifies, ‘‘Helicopters that were under close 

monitoring on March 21 2022 (the effective 

date of EASA AD 2022–0038) must continue 

the close monitoring procedure up to the first 

inspection accomplished in accordance with 

the instructions of ASB 1;’’ for this AD, 

replace that text with, ‘‘Helicopters that are 

under close monitoring as of the effective 

date of this AD must continue close 

monitoring until the first instance of the 

requirements in paragraph (1) of EASA AD 

2023–0001 are completed.’’ 

(6) Where EASA AD 2023–0001 requires 

replacing the TGB and the service 

information referenced in EASA AD 2023– 

0001 specifies replacing the TGB, for this AD, 

before further flight, remove the TGB from 

service and replace it with an airworthy part, 

or repair the TGB in accordance with a 

method approved by the Manager, Europe 

Middle East & Africa Section, International 

Validation Branch, FAA; EASA; or Airbus 

Helicopters’ Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(7) Where paragraphs (5) and (6) of EASA 

AD 2023–0001 require replacing an affected 

part, as defined in EASA AD 2023–0001, 


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with a serviceable part, as defined in EASA 

AD 2023–0001; for this AD, remove the 

affected part, as defined in EASA AD 2023– 

0001, from service and replace it with a 

serviceable part, as defined in EASA AD 

2023–0001. 

(8) Where paragraph (5) of EASA AD 2023– 

0001 does not specify a compliance time; for 

this AD, the compliance time for those 

actions is before further flight. 

(9) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies to do the 

actions identified in paragraphs (h)(9)(i) and 

(ii) of this AD, this AD does not include those 

requirements. 

(i) Comply with paragraph 2.D., except this 

AD requires reporting information, including 

the information in Appendix 4. of the service 

information, in accordance with paragraph 

(h)(18) of this AD. 

(ii) Send parts and particles to Airbus 

Helicopters. 

(10) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies replacing the 

chip detector or conical housing chip 

detector if there is an anomaly; for this AD, 

an anomaly may be indicated by the 

magnetic component of the TGB chip 

detector or the conical housing chip detector 

not being magnetized. If there is an anomaly, 

this AD requires before further flight, 

removing from service the TGB chip detector 

or the conical housing chip detector, as 

applicable to your model helicopter. 

(11) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies making sure 

that the chip detector or conical housing chip 

detector is in good condition; for this AD, 

good condition for the chip detector is 

indicated when there are no signs of wear on 

the locking systems (including wear on the 

bayonets and slotted tubes). If there are any 

signs of wear on the locking systems, this AD 

requires, before further flight, removing the 

TGB chip detector from service. Good 

condition for the conical housing chip 

detector is when the conical housing chip 

detector is magnetized. If the conical housing 

chip detector is not magnetized, this AD 

requires, before further flight, removing the 

conical housing chip detector from service. 

(12) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies replacing the 

O-rings if necessary; this AD requires, before 

further flight, removing any affected O-ring 

from service and replacing it with an 

airworthy O-ring. 

(13) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies removing an 

affected TGB, returning it to an approved 

workshop, including sending all the particles 

found in the affected part; this AD requires, 

before further flight, removing an affected 

TGB from service and replacing it with an 

airworthy part, or repairing the TGB in 

accordance with a method approved by the 

Manager, Europe Middle East & Africa 

Section, International Validation Branch, 

FAA; EASA; or Airbus Helicopters’ DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. You 

are not required to send the particles found 

in the TGB to Airbus Helicopters or send an 

affected TGB to an approved workshop. 

(14) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies to use tooling, 

this AD allows the use of equivalent tooling. 

(15) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies discarding 

certain parts, this AD requires removing 

those parts from service. 

(16) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies performing a 

metallurgical analysis of particles if there is 

a doubt concerning the type, size, or 

classification of any collected particle, this 

AD requires, before further flight, performing 

a metallurgical analysis if the type, size, or 

classification of any collected particle cannot 

be determined. 

(17) Where the service information 

(including any work card) referenced in 

EASA AD 2023–0001 specifies if there is any 

doubt remaining (pertaining to particle 

classification) after performing a 

metallurgical analysis, contact Airbus, this 

AD requires, if the type, size, or classification 

of any collected particle cannot be 

determined after performing a metallurgical 

analysis, before further flight, removing an 

affected TGB from service and replacing it 

with an airworthy part, or repairing the TGB 

in accordance with a method approved by 

the Manager, Europe Middle East & Africa 

Section, International Validation Branch, 

FAA; EASA; or Airbus Helicopters’ DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(18) Where the service information 

referenced in EASA AD 2023–0001 requires 

reporting inspection results, including 

Appendix 4.A., to Airbus Helicopters, if any 

M50 particles are found, this AD requires 

reporting those inspection results along with 

a detailed description of any information and 

findings, and if possible, provide photos, at 

the applicable time in paragraph (h)(18)(i) or 

(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 10 days after accomplishing the 

metallurgical analysis. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 10 days after the effective date of this 

AD. 

(19) This AD does not adopt the ‘‘Remarks’’ 

section of EASA AD 2023–0001. 

(i) Special Flight Permits 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199, 

provided no passengers are onboard. 

(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: 9-AVS-AIR730-AMOC@faa.gov. 

(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 Kevin Kung, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone (781) 

238–7244; email 9-AVS-AIR-BACO-COS@

faa.gov. 

(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 2023–0001, dated January 4, 

2023. 

(ii) [Reserved] 

(3) For EASA AD 2023–0001, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

easa.europa.eu. You may find the EASA 

material on the EASA website 

ad.easa.europa.eu. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Parkway, 

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 material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit www.archives.gov/federal-register/cfr/ 

ibr-locations or email fr.inspection@nara.gov. 

Issued on October 30, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–25556 Filed 11–17–23; 8:45 am] 

BILLING CODE 4910–13–P 


ddrumheller on DSK120RN23PROD with RULES1