60402 Federal Register / Vol. 88, No. 169 / Friday, September 1, 2023 / Proposed Rules 

TABLE 1 TO § 217.406—SHORT-TERM WHOLESALE FUNDING COMPONENTS AND WEIGHTS

Component of short-term wholesale funding 

Remaining 

maturity of 30 

days of less or 

no maturity 

(percent) 

Remaining 

maturity of 31 

to 90 days 

(percent) 

Remaining 

maturity of 91 

to 179 days 

(percent) 

Remaining 

maturity of 180 

to 364 days 

(percent) 

Category 1 ............................................................................... 25 10 0 0 

(1) Secured funding transaction secured by a level 1 liquid asset; 

(2) Unsecured wholesale funding where the customer or 

counterparty is not a financial sector entity or a consolidated subsidiary thereof; 

(3) Brokered deposits and sweep deposits provided by a 

retail customer or counterparty; and 

(4) Short positions where the borrowed asset does not 

qualify as either a level 1 liquid asset or level 2A liquid asset. 

Category 2 ............................................................................... 50 25 10 0 

(1) Secured funding transaction secured by a level 2A 

liquid asset; and 

(2) Covered asset exchanges involving the future exchange of a Level 1 liquid asset for a Level 2A liquid 

asset. 

Category 3 ............................................................................... 75 50 25 10 

(1) Secured funding transaction secured by a level 2B 

liquid asset; 

(2) Covered asset exchanges (other than those described in Category 2); and 

(3) Unsecured wholesale funding (other than unsecured 

wholesale funding described in Category 1). 

Category 4 ............................................................................... 100 75 50 25 

Any other component of short-term wholesale funding. 

By order of the Board of Governors of the 

Federal Reserve System. 

Ann E. Misback, 

Secretary of the Board. 

[FR Doc. 2023–16896 Filed 8–31–23; 8:45 am] 

BILLING CODE 6210–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1720; Project 

Identifier MCAI–2023–00003–R] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

Airbus Helicopters Model SA–365C1, 

SA–365C2, and SA–365N helicopters. 

This proposed AD was prompted by 

reports of damaged control rod dual 

bearings (dual bearings) that are 

installed on the tail rotor gearbox (TGB). 

This proposed AD would require 

repetitively inspecting the TGB 

magnetic plug for particles, analyzing 

any particles collected, taking corrective 

actions if necessary, and reporting 

certain information. Finally, this 

proposed AD would allow 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 proposed for 

incorporation by reference. 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 October 16, 

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 above 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–2023–1720; 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 NPRM, the EASA AD, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

Material Incorporated by Reference: 

• For EASA material that is proposed 

for incorporation by reference in this 

NPRM, 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 at 

ad.easa.europa.eu. 

• You may view this material at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. The EASA material 

is also available at regulations.gov under 

Docket No. FAA–2023–1720. 

Other Related Service Information: 

For Airbus Helicopters 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 

airbus.com/en/products-services/ 

helicopters/hcare-services/airbusworld. 


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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: 

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–2023–1720; Project Identifier 

MCAI–2023–00003–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 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. Any 

commentary that the FAA receives that 

is not specifically designated as CBI will 

be placed in the public docket for this 

rulemaking. 

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 for Airbus Helicopters 

Model SA 365 C1, SA 365 C2, SA 365 

C3, and SA 365 N helicopters, all 

manufacturer serial numbers. 

This proposed AD was prompted by 

reports of damaged dual bearings that 

are installed on the TGB. The FAA is 

proposing 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. 

You may examine EASA AD 2023– 

0001 in the AD docket at regulations.gov 

under Docket No. FAA–2023–1720. 

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. 

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 determining that 

the unsafe condition described 

previously is likely to exist or develop 

on other helicopters of the same type 

design. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

accomplishing the actions specified in 

EASA AD 2023–0001, described 

previously, as incorporated by 

reference, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD and 

discussed under ‘‘Differences Between 

this Proposed AD and the EASA AD.’’ 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA developed a process to 

use some civil aviation authority (CAA) 

ADs as the primary source of 

information for compliance with 

requirements for corresponding FAA 

ADs. The FAA has been coordinating 

this process with manufacturers and 

CAAs. As a result, the FAA proposes to 

incorporate EASA AD 2023–0001 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2023–0001 

AD in its entirety through that 

incorporation, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

Using common terms that are the same 


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as the heading of a particular section in 

EASA AD 2023–0001 does not mean 

that operators need comply only with 

that section. For example, where the AD 

requirement refers to ‘‘all required 

actions and compliance times,’’ 

compliance with this AD requirement is 

not limited to the section titled 

‘‘Required Action(s) and Compliance 

Time(s)’’ in EASA AD 2023–0001. 

Service information referenced in EASA 

AD 2023–0001 for compliance will be 

available at regulations.gov under 

Docket No. FAA–2023–1720 after the 

FAA final rule is published. 

Differences Between This Proposed AD 

and the EASA AD 

EASA AD 2023–0001 applies to 

Airbus Helicopters Model SA 365 C3 

helicopters, whereas this proposed AD 

would not because that model is not 

FAA type-certificated. 

This proposed AD would clarify that 

Model SA–365N helicopters with an 

affected dual bearing installed that has 

an unknown total number of hours timein-service accumulated on the dual 

bearing would be subject to certain 

requirements in this proposed 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 

proposed 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 proposed 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 proposed AD would 

require 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. 

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 proposed AD would 

require 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’ 

Design Organization Approval. 

Service information referenced in 

EASA AD 20223–0001 permits a pilot to 

perform a magnetic plug check, whereas 

this proposed AD would not. 

Service information referenced in 

EASA AD 2023–0001 specifies sending 

compliance forms, certain parts, and 

particles to the manufacturer, whereas 

this proposed AD would require 

reporting certain information but would 

not require sending any parts or 

particles to the manufacturer. 

Interim Action 

The FAA considers this proposed AD 

would be an interim action. If final 

action is later identified, the FAA might 

consider further rulemaking then. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 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 proposed AD. 

Inspecting the magnetic plug of the 

TGB for particles would take about 1 

work-hour for an estimated cost of $85 

per inspection and up to $85 for the 

U.S. fleet, per inspection cycle. 

Inspecting a dual bearing would take 

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 would take 

about 1 additional work-hour following 

the inspection and parts would cost 

about $6,678 for an estimated cost of 

$6,763 per dual bearing replacement. 

If required, analyzing collected 

particles would take about 1 work-hour 

for an estimated cost of $85 per 

helicopter. If required, a metallurgical 

analysis would take about 1 work-hour 

for an estimated cost of $85 per 

instance. 

If required, replacing an O-ring would 

take about 1 work-hour and parts would 

cost about $100 for an estimated cost of 

$185 per O-ring. 

If required, replacing a TGB would 

take about 8 work-hours and parts 

would 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 would take about 1 

work-hour 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 current 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. 


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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 above, 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

Airbus Helicopters: Docket No. FAA–2023– 

1720; Project Identifier MCAI–2023– 

00003–R. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by October 16, 

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, 

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 being 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 


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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, 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 at 

ad.easa.europa.eu. 

(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 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 

fr.inspection@nara.gov, or go to: 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on August 23, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–18612 Filed 8–31–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1812; Project 

Identifier MCAI–2023–00726–A] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Diamond Aircraft Industries Inc. Model 

DA 62 airplanes. This proposed AD was 

prompted by reports of baggage nets 

installed with defective buckles, which 

may result in failure of the baggage net 

to restrain the baggage or cargo, which 

could lead to injury to the occupants in 

the case of an emergency landing. This 

proposed AD would require identifying 

and replacing the affected part. The 

FAA is proposing this AD to address the 

unsafe condition on these products. 

DATES: The FAA must receive comments 

on this NPRM by October 16, 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 above 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–2023–1812; 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 Diamond Aircraft 

Industries Inc., Att: Thit Tun, 1560 

Crumlin Road, London, N5V 1S2, 

Canada; phone: (519) 457–4000; email: 

t.tun@diamondaircraft.com; website: 

diamondaircraft.com. 

• You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 901 Locust, Kansas City, MO 

64106. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. 

FOR FURTHER INFORMATION CONTACT: 

Chirayu Gupta, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 

(516) 228–7300; email: 

chirayu.a.gupta@faa.gov. 

SUPPLEMENTARY INFORMATION: 


lotter on DSK11XQN23PROD with PROPOSALS1