86816 Federal Register / Vol. 88, No. 240 / Friday, December 15, 2023 / Rules and Regulations 

(7) Title 29 CFR, part 1926, ‘‘Safety 

and Health Regulations for 

Construction,’’ except for 29 CFR 

1926.1124, ‘‘Beryllium.’’ 

* * * * * 

(9) American Conference of 

Governmental Industrial Hygienists 

(ACGIH®), Threshold Limit Values for 

Chemical Substances and Physical 

Agents and Biological Exposure Indices, 

(2016) (incorporated by reference, see 

§ 851.27), excluding the threshold limit 

values (TLVs®) for beryllium and 

beryllium compounds, when the 

ACGIH® TLVs® are lower (more 

protective) than permissible exposure 

limits in 29 CFR part 1910 for general 

industry, 29 CFR part 1915 for 

shipyards, and/or 29 CFR part 1926 for 

construction. When the ACGIH® TLVs®

are used as exposure limits, contractors 

must comply with the other provisions 

of any applicable expanded health 

standard found in 29 CFR parts 1910, 

1915, and 1926. 

* * * * * 

(b) Nothing in this part relieves 

contractors from the responsibility to 

comply with any additional safety and 

health requirements that are necessary 

to protect the safety and health of 

workers. 

* * * * * 

■ 6. Amend § 851.27 by revising 

paragraph (a) to read as follows: 

§ 851.27 Materials incorporated by 

reference. 

(a) Certain material is incorporated by 

reference into this subpart with the 

approval of the Director of the Federal 

Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. To enforce 

any edition other than that specified in 

this section, the U.S. Department of 

Energy (DOE) must publish a document 

in the Federal Register and the material 

must be available to the public. All 

approved incorporation by reference 

(IBR) material is available for inspection 

at DOE and at the National Archives and 

Records Administration (NARA). 

Contact DOE: the U.S. Department of 

Energy, Office of Environment, Health, 

Safety and Security, Office of Worker 

Safety and Health Policy, Mailstop 

EHSS–11, 1000 Independence Ave. SW, 

Washington, DC 20585; (301) 903–1165. 

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. The material may be obtained 

from the sources in the following 

paragraphs of this section. 

* * * * * 

[FR Doc. 2023–27615 Filed 12–14–23; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1821; Project 

Identifier MCAI–2022–01045–A; Amendment 

39–22601; AD 2023–22–17] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited (Type Certificate Previously 

Held by Bombardier Inc. and de 

Havilland, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Viking Air Limited (type certificate 

previously held by Bombardier Inc. and 

de Havilland, Inc.) (Viking) Model 

DHC–3 airplanes. This AD was 

prompted by a report of cracking in the 

left-hand side (LHS) and right-hand side 

(RHS) lower engine mount pickup 

fittings. This AD requires a one-time 

inspection of the affected parts for 

cracking, deformation, corrosion, 

fretting or wear, paint or surface coating 

damage, and loose, missing, or broken 

fasteners, and applicable corrective 

actions. This AD also requires reporting 

the inspection results. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective January 19, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 19, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1821; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this final rule, the mandatory 

continuing airworthiness information 

(MCAI), 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 service information identified 

in this final rule, contact Viking Air 

Limited Technical Support, 1959 de 

Havilland Way, Sidney, British 

Columbia, Canada, V8L 5V5; phone: 

(800) 663–8444; fax: (403) 295–8888; 

email: dh_technical.support@

vikingair.com; website: vikingair.com/ 

support/service-bulletins. 

• 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. It is also available 

at regulations.gov under Docket No. 

FAA–2023–1821. 

FOR FURTHER INFORMATION CONTACT: 

Yaser Osman, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (917) 348– 

6266; email: avs-nyaco-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Viking Model DHC–3 

airplanes. The NPRM published in the 

Federal Register on September 7, 2023 

(88 FR 61488). The NPRM was 

prompted by AD CF–2022–41, dated 

August 4, 2022 (also referred to as the 

MCAI), issued by Transport Canada, 

which is the aviation authority for 

Canada. The MCAI states that Viking 

received a post inspection report of 

fatigue cracking on the LHS and RHS of 

the lower engine mount pickup fittings 

on a Viking Model DHC–3 airplane. The 

two upper and two lower engine mount 

pickup fittings provide a rigid 

connection between the engine mount 

ring to which the engine is secured, and 

the firewall rear face. The MCAI also 

states that the current inspection 

requirements do not include a direct 

inspection of the lower and upper 

engine mount pickup fittings, and 

consequently, cracks or other damage to 

the engine mount pickup fittings may 

not be detected. Additionally, the MCAI 

states that an investigation determined 

that the upper engine mount pickup 

fittings can also have undetected fatigue 

cracks because they are manufactured 

from the same material as the lower 

engine mount pickup fittings. 

Cracking of any of the engine mount 

pickup fittings can result in failure of 

the fitting, leading to a loose connection 

of the engine mount ring, which 

provides main support for the engine at 

the firewall. This condition, if not 

addressed, could, in the case of cracking 

of any of the engine mount pickup 

fittings, result in failure of the fitting, 

leading to a loose connection of the 

engine mount ring and consequent 

reduced control of the airplane. To 

address the unsafe condition, the MCAI 

requires a one-time inspection of the 

affected parts and applicable corrective 


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Federal Register / Vol. 88, No. 240 / Friday, December 15, 2023 / Rules and Regulations 86817 

action. The MCAI also requires 

reporting the inspection results to 

Viking. 

In the NPRM, the FAA proposed to 

require a one-time inspection of the 

affected parts for cracking, deformation, 

corrosion, fretting or wear, paint or 

surface coating damage, and loose, 

missing, or broken fasteners, and 

applicable corrective actions. 

Additionally, in the NPRM, the FAA 

proposed to require reporting the 

inspection results. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2023–1821. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

These products have been approved 

by the aviation authority of another 

country and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with this 

State of Design Authority, it has notified 

the FAA of the unsafe condition 

described in the MCAI referenced 

above. 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 

products. This AD is adopted as 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Part 1 of Viking 

PSM 1–3–3, DHC–3 Otter Repair 

Manual, dated August 1, 1963. This 

service information specifies procedures 

for determining the damage 

classification and repair limits of any 

structural damage found on an engine 

mount pickup fitting and determining if 

an affected engine mount pickup fitting 

can be repaired or if it should be 

replaced. Although the watermarked 

words ‘‘Uncontrolled for Reference 

Only’’ appear on the title page and each 

page of the table of contents of this 

document, and the watermarked word 

‘‘Uncontrolled’’ appears on each page of 

Part 1 of this document, this is the 

current version. 

The FAA also reviewed Part 1 of 

Viking PSM 1–3–5, DHC–3 Otter 

Supplemental Inspection and Corrosion 

Control Manual, Revision IR, dated 

December 21, 2017 (Viking PSM 1–3–5, 

Revision IR). This service information 

specifies procedures for repairing any 

damaged paint or surface coating of an 

engine mount pickup fitting. 

In addition, the FAA reviewed Viking 

Service Bulletin V3/0012, Revision NC, 

dated January 20, 2022. This service 

information specifies procedures for 

inspecting the upper and lower LHS and 

RHS engine mount pickup fittings, 

reporting the inspection results, and 

performing corrective actions. The 

corrective actions include replacing any 

loose, missing, or broken fastener; and 

replacing any cracked or deformed 

engine mount pickup fitting with a new 

or serviceable part. 

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 ADDRESSES. 

Differences Between This AD and the 

MCAI 

The MCAI requires contacting Viking 

for approval of proposed repair 

instructions if any corrosion, wear, or 

fretting damage to any engine mount 

pickup fitting is found and this AD does 

not. This AD requires contacting either 

the Manager, International Validation 

Branch, FAA; Transport Canada; or 

Viking’s Transport Canada Design 

Approval Organization (DAO). If 

approved by the DAO, the approval 

must include the DAO-authorized 

signature. 

Where Part 1 of Viking PSM 1–3–5, 

Revision IR, specifies contacting Viking 

if the alloy and condition of an affected 

engine mount pickup fitting cannot be 

identified, this AD requires contacting 

the Manager, International Validation 

Branch, FAA; Transport Canada; or 

Viking’s Transport Canada DAO for 

instructions. If approved by the DAO, 

the approval must include the DAOauthorized signature. 

Interim Action 

The FAA considers that this AD is an 

interim action. If final action is later 

identified, the FAA might consider 

further rulemaking. 

Costs of Compliance 

The FAA estimates that this AD 

affects 65 airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Detailed visual inspection of the engine 

mount pickup fitting.

2 work-hours × $85 per hour = $170 ............. $0 $170 $11,050 

Report results of inspection ............................ 1 work-hour × $85 per hour = $85 ................. 0 85 5,525 

The FAA estimates the following 

costs to do any necessary actions that 

would be required based on the results 

of the inspection. The agency has no 

way of determining the number of 

aircraft that might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replace engine mount pickup fitting.4 work-hours × $85 per hour = 

$340 (per engine mount pickup 

fitting).

Up to $692 per engine mount 

pickup fitting.

Up to $1,032 per engine mount 

pickup fitting. 

Replace the fastener with a new 

fastener.

1 work-hour × $85 per hour = $85 Negligible ...................................... $85. 

Perform a detailed visual inspection of the fastener hole.1 work-hour × $85 per hour = $85 $0 .................................................. $85. 


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86818 Federal Register / Vol. 88, No. 240 / Friday, December 15, 2023 / Rules and Regulations 

Any repair that may be needed as a 

result of the detailed visual inspection 

of the engine mount pickup fitting could 

vary significantly from airplane to 

airplane. The FAA has no data to 

determine the costs to accomplish the 

repair or the number of airplanes that 

may require repair. 

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: 

2023–22–17 Viking Air Limited (Type 

Certificate Previously Held by 

Bombardier Inc. and de Havilland, Inc.): 

Amendment 39–22601; Docket No. 

FAA–2023–1821; Project Identifier 

MCAI–2022–01045–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 19, 2024. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Viking Air Limited 

(type certificate previously held by 

Bombardier Inc. and de Havilland, Inc.) 

Model DHC–3 airplanes, all serial numbers, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7120, Engine Mount Section. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracking in the left-hand side (LHS) and 

right-hand side (RHS) lower engine mount 

pickup fittings. The FAA is issuing this AD 

to address cracking in the LHS and RHS 

lower engine mount pickup fittings. The 

unsafe condition, if not addressed, could, in 

the case of cracking of any of the engine 

mount pickup fittings, result in failure of the 

fitting, leading to a loose connection of the 

engine mount ring, which provides main 

support for the engine at the firewall, and 

consequent reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 6 months after the effective date 

of this AD, do a detailed visual inspection of 

the lower engine mount pickup fittings part 

numbers (P/Ns) C3FS46–7 and C3FS46–8 

and the upper engine mount pickup fittings 

P/Ns C3FS42–5 and C3FS42–6 for cracking, 

deformation (altered form or shape), 

corrosion, fretting or wear, paint or surface 

coating damage (loose, delaminating, flaking, 

peeling, chipping of the coating or paint, 

exposed bare metal, or corroded), and loose, 

missing, or broken fasteners, in accordance 

with Part A, steps 1 through 8, of the 

Accomplishment Instructions in Viking 

Service Bulletin V3/0012, Revision NC, dated 

January 20, 2022 (Viking SB V3/0012). 

(2) If any crack or deformation (altered 

form or shape) of any engine mount pickup 

fitting is found during the detailed visual 

inspection required by paragraph (g)(1) of 

this AD, before further flight, replace the 

fitting with a new or serviceable part, in 

accordance with Part A, step 10, of the 

Accomplishment Instructions in Viking SB 

V3/0012. For purposes of this AD, ‘‘new’’ 

means zero hours time-in-service. 

(3) If any paint or surface coating of the 

engine mount pickup fitting is found 

damaged (loose, delaminating, flaking, 

peeling, chipping of the coating or paint, 

exposed bare metal, or corroded) during the 

detailed visual inspection required by 

paragraph (g)(1) of this AD, before further 

flight, repair the fitting in accordance with 

Part 1 of Viking PSM 1–3–5, DHC–3 Otter 

Supplemental Inspection and Corrosion 

Control Manual, Revision IR, dated December 

21, 2017 (Viking PSM 1–3–5, Revision IR), 

and Part A, step 12, of the Accomplishment 

Instructions in Viking SB V3/0012. Where 

Part 1 of Viking PSM 1–3–5, Revision IR, 

specifies contacting Viking if the alloy and 

condition of an affected engine mount pickup 

fitting cannot be identified, this AD requires 

contacting the Manager, International 

Validation Branch, FAA; Transport Canada; 

or Viking’s Transport Canada Design 

Approval Organization (DAO) for 

instructions. 

(4) If any loose, missing, or broken fastener 

is found during the detailed visual inspection 

required by paragraph (g)(1) of this AD, 

before further flight, replace the fastener with 

a new fastener, do a detailed visual 

inspection of the fastener hole to detect 

cracking, corrosion, an elongated bore hole, 

bore surface roughness, or other defects 

(abnormalities when compared to a new 

part), and repair any damage found or replace 

the engine mount pickup fitting with a new 

or serviceable part if damage is beyond 

repairable limits, in accordance with Part 1 


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Federal Register / Vol. 88, No. 240 / Friday, December 15, 2023 / Rules and Regulations 86819 

of Viking PSM 1–3–3 DHC–3 Otter Repair 

Manual, dated August 1, 1963, and Part A, 

step 9, of the Accomplishment Instructions 

in Viking SB V3/0012. 

(5) If any corrosion, wear, or fretting to any 

engine mount pickup fitting is found during 

the detailed visual inspection required by 

paragraph (g)(1) of this AD, before further 

flight, contact the Manager, International 

Validation Branch, FAA; Transport Canada; 

or Viking’s Transport Canada DAO to obtain 

instructions for an approved repair and, 

within the compliance timeframe specified 

therein, do the repair. If approved by the 

DAO, the approval must include the DAOauthorized signature. Alternatively, before 

further flight, replace the engine mount 

pickup fitting with a new or serviceable part 

in accordance with Part A, step 10, of the 

Accomplishment Instructions in Viking SB 

V3/0012. 

(h) Reporting Requirement 

Report the inspection results from the 

detailed visual inspection required by 

paragraph (g)(1) of this AD at the applicable 

time specified in paragraph (h)(1) or (2) of 

this AD in accordance with Part A, step 14, 

of the Accomplishment Instructions in 

Viking SB V3/0012. 

(1) For inspections done on or after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) For inspections done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(i) 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 local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, mail it to the address identified in 

paragraph (j)(2) of this AD or email to: 9- 

AVS-AIR-730-AMOC@faa.gov. If mailing 

information, also submit information by 

email. 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. 

(j) Additional Information 

(1) Refer to Transport Canada AD CF– 

2022–41, dated August 4, 2022, for related 

information. This Transport Canada AD may 

be found in the AD docket at regulations.gov 

under Docket No. FAA–2023–1821. 

(2) For more information about this AD, 

contact Yaser Osman, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (917) 348– 

6266; email: Yaser.M.Osman@faa.gov. 

(k) 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 the AD specifies otherwise. 

(i) Viking PSM 1–3–3, DHC–3 Otter Repair 

Manual, Part 1, dated August 1, 1963. 

Note 1 to paragraph (k)(2)(i): Although the 

document specified in paragraph (k)(2)(i) has 

the watermarked words ‘‘Uncontrolled for 

Reference Only’’ on the title page and each 

page of the table of contents, and the 

watermarked word ‘‘Uncontrolled’’ on each 

page of Part 1, this is a current version of that 

document. 

(ii) Viking PSM 1–3–5, DHC–3 Otter 

Supplemental Inspection and Corrosion 

Control Manual, Revision IR, Part 1, dated 

December 21, 2017. 

(iii) Viking Service Bulletin V3/0012, 

Revision NC, dated January 20, 2022. 

(3) For Viking service information 

identified in this AD, contact Viking Air 

Limited Technical Support, 1959 de 

Havilland Way, Sidney, British Columbia, 

Canada, V8L 5V5; phone: (800) 663–8444; 

fax: (403) 295–8888; email: dh_

technical.support@vikingair.com; website: 

vikingair.com/support/service-bulletins. 

(4) 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. 

(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 November 3, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–27495 Filed 12–14–23; 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; Amendment 

39–22602; AD 2023–22–18] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Diamond Aircraft Industries Inc. Model 

DA 62 airplanes. This 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 AD requires 

identifying and replacing the affected 

part. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective January 19, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 19, 2024. 

ADDRESSES: 

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 final rule, the mandatory 

continuing airworthiness information 

(MCAI), 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 service information identified 

in this final rule, 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. It is also available 

at regulations.gov under Docket No. 

FAA–2023–1812. 

FOR FURTHER INFORMATION CONTACT: 

Fatin Saumik, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (516) 228– 

7350; email: fatin.r.saumik@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Diamond Aircraft Industries 

Inc. Model DA 62 airplanes. The NPRM 

published in the Federal Register on 

September 1, 2023 (88 FR 60406). The 

NPRM was prompted by AD CF–2021– 

24, dated July 21, 2021 (also referred to 

as the MCAI), issued by Transport 

Canada, which is the aviation authority 

for Canada. The MCAI states Diamond 

Aircraft Industries Inc. received reports 

of defective buckles installed on the 

baggage nets on DA 40 NG and DA 62 


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