Federal Register / Vol. 88, No. 168 / Thursday, August 31, 2023 / Proposed Rules 60157 

3CS–E, Amendment 6—Aircraft cybersecurity. 

TABLE 7—MODIFICATIONS APPLICABLE TO ASTM F3198–18 ‘‘STANDARD SPECIFICATION FOR LIGHT SPORT AIRCRAFT

MANUFACTURER’S CONTINUED OPERATIONAL SAFETY (COS) PROGRAM’’ 

Requirement: 

Include all sections of ASTM F3198–18 except: 

• Section 1 and all subsections 

• Section 5.2 and all subsections 

• Section 5.3 and all subsections 

• Section 6.1.1.3 

• Section 6.1.1.4 

• Section 7.7 and all subsections 

• Section 8.1.2.1 

• Section 8.2 and all subsections 

• Section 10 

Change section 4.1 to: ‘‘The purpose of this specification is to establish, by the manufacturer, a method by which unsafe conditions and service 

difficulty issues are reported, evaluated, and corrected. The type certificate holder is responsible to report failures, malfunctions or defects to 

the FAA as outlined in § 21.3.’’ 

Replace ‘‘manufacturer’’ with ‘‘type certificate holder’’ throughout section 7. 

TABLE 8—FAA VALIDATION OF EASA STATE OF DESIGN RECIPROCATING AIRCRAFT ENGINES

[In addition to the EASA CS–E, amendment 6 requirements,3 the following requirements from 14 CFR part 33, amendment 33–34 also apply.] 

Subject 14 CFR part 33 

Instructions for Continued Airworthiness (ICA) ........................................ Section 33.4, appendices A33.1(b), A33.2, A33.3(b) and (c), and 

A33.4(a)(2). 

Engine ratings and operating limitations including reciprocating engine 

limits.

Sections 33.7(b)(6) and (b)(8). 

Durability (Propeller blade pitch control systems) .................................... Section 33.19(b). 

Turbine, compressor, fan, and turbosupercharger rotor overspeed ........ Section 33.27. 

Turbocharger rotors .................................................................................. Section 33.34. 

Lubrication system .................................................................................... Sections 33.39(a) and (c). 

Vibration test ............................................................................................. Sections 33.43(a) and (c). 

Endurance test ......................................................................................... Section 33.49(d). 

Issued in Kansas City, Missouri, on 24 

August, 2023. 

Patrick R. Mullen, 

Manager, Technical Policy Branch, Policy and 

Standards Division, Aircraft Certification 

Service. 

[FR Doc. 2023–18679 Filed 8–30–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1723; Project 

Identifier MCAI–2023–00457–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

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 

Airbus SAS Model A330–200 Freighter 

series airplanes. This proposed AD was 

prompted by a widespread fatigue 

damage (WFD) evaluation on Airbus 

SAS Model A330–200 Freighter series 

airplanes, which found that the 

circumferential joint at Frame 58 (near 

the rear fuselage) is susceptible to WFD. 

This proposed AD would require a 

modification to reinforce the 

circumferential joints at Frame 58 and, 

if necessary, corrective action, as 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

proposed for incorporation by reference 

(IBR). 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–2023–1723; 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 material that is proposed for 

IBR in this AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; website 

easa.europa.eu. You may find this 

material on the EASA website at 


ddrumheller on DSK120RN23PROD with PROPOSALS1
60158 Federal Register / Vol. 88, No. 168 / Thursday, August 31, 2023 / Proposed Rules 

ad.easa.europa.eu. It is also available at 

regulations.gov under Docket No. FAA– 

2023–1723. 

• You may view this material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dowling, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone: 206– 

231–3667; email: timothy.p.dowling@

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–2023–1723; Project Identifier 

MCAI–2023–00457–T’’ 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 Tim Dowling, 

Aviation Safety Engineer, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone: 206–231–3667; 

email: timothy.p.dowling@faa.gov. Any 

commentary that the FAA receives 

which is not specifically designated as 

CBI will be placed in the public docket 

for this rulemaking. 

Background 

Fatigue damage can occur locally, in 

small areas or structural design details, 

or globally, in widespread areas. 

Multiple-site damage is widespread 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Widespread damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-site 

damage and multiple-element damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane. This 

condition is known as WFD. It is 

associated with general degradation of 

large areas of structure with similar 

structural details and stress levels. As 

an airplane ages, WFD will likely occur, 

and will certainly occur if the airplane 

is operated long enough without any 

intervention. 

An FAA final rule (‘‘Aging Airplane 

Program: Widespread Fatigue Damage;’’ 

75 FR 69746, November 15, 2010) 

became effective on January 14, 2011, 

and amended 14 CFR parts 25, 26, 121, 

and 129 (commonly known as the WFD 

rule). The WFD rule requires certain 

actions to prevent structural failure due 

to WFD throughout the operational life 

of certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. Design 

approval holders (DAHs) of existing and 

future airplanes subject to the WFD rule 

are required to establish a limit of 

validity (LOV) of the engineering data 

that support the structural maintenance 

program. Operators affected by the WFD 

rule may not fly an airplane beyond its 

LOV, unless an extended LOV is 

approved. 

The WFD rule does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2023–0053, 

dated March 14, 2023 (EASA AD 2023– 

0053) (also referred to as the MCAI), to 

correct an unsafe condition for all 

Airbus SAS Model A330–223F and 

–243F airplanes. The MCAI states that 

within the scope of WFD evaluations on 

Model A330–200 Freighter series 

airplanes, it was determined that the 

circumferential joint at Frame 58 (near 

rear fuselage) is susceptible to WFD. 

WFD, if not corrected, may lead to crack 

initiation and undetected propagation, 

which could affect the structural 

integrity of the airplane. 

The FAA is proposing 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–2023–1723. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2023–0053 specifies 

procedures for a modification (including 

rotating probe inspections for 

discrepancies and measurement of the 

maximum hole diameter at any point in 

the fastener hole bores on the 

circumferential joints) to reinforce the 

circumferential joints at Frame 58 and, 

if any discrepancies (cracking) are 

found, corrective action (contacting the 

manufacturer for instructions and 

accomplishing those instructions). 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 

ADDRESSES. 

FAA’s Determination 

This product has been approved by 

the aviation authority of another 

country and is 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 

is issuing this NPRM after determining 

that the unsafe condition described 

previously is likely to exist or develop 

in other products of the same type 

design. 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 88, No. 168 / Thursday, August 31, 2023 / Proposed Rules 60159 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

accomplishing the actions specified in 

EASA AD 2023–0053 described 

previously, except for any differences 

identified as exceptions in the 

regulatory text of this proposed 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 2023–0053 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2023–0053 

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 

as the heading of a particular section in 

EASA AD 2023–0053 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 2023–0053. 

Service information required by EASA 

AD 2023–0053 for compliance will be 

available at regulations.gov under 

Docket No. FAA–2023–1723 after the 

FAA final rule is published. 

Explanation of Compliance Time 

The compliance time for the 

replacement specified in this proposed 

AD for addressing WFD was established 

to ensure that certain structure is 

replaced before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. The FAA will not grant any 

extensions of the compliance time to 

complete any AD-mandated service 

bulletin related to WFD without 

extensive new data that would 

substantiate and clearly warrant such an 

extension. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 6 

airplanes of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

368 work-hours × $85 per hour = $31,280 ................................................................................. $7,700 $38,980 $233,880 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions specified in 

this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

The FAA determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed 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 SAS: Docket No. FAA–2023–1723; 

Project Identifier MCAI–2023–00457–T. 

(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 all Airbus SAS Model 

A330–223F and –243F airplanes, certificated 

in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a widespread 

fatigue damage (WFD) evaluation on Model 

A330–200 Freighter series airplanes, which 

found that the circumferential joint at Frame 

58 (near the rear fuselage) is susceptible to 

WFD. The FAA is issuing this AD to address 

WFD in the affected area. The unsafe 

condition, if not corrected, may lead to crack 

initiation and undetected propagation, which 

could affect the structural integrity of the 

airplane. 


ddrumheller on DSK120RN23PROD with PROPOSALS1
60160 Federal Register / Vol. 88, No. 168 / Thursday, August 31, 2023 / Proposed Rules 

(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 2023–0053, dated 

March 14, 2023 (EASA AD 2023–0053). 

(h) Exceptions to EASA AD 2023–0053 

(1) Where EASA AD 2023–0053 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

section of EASA AD 2023–0053. 

(3) Where paragraph (2) of EASA AD 2023– 

0053 specifies ‘‘if, during the 

accomplishment of any inspection, which is 

part of the modification as required by 

paragraph (1) of this AD, any discrepancy, as 

identified in the SB, is detected, before next 

flight, contact Airbus for approved 

instructions and accomplish those 

instructions accordingly,’’ this AD requires 

replacing those words with ‘‘if, during the 

accomplishment of any inspection, which is 

part of the modification as required by 

paragraph (1) of this AD, any cracking is 

detected, the cracking must be repaired 

before further flight using a method approved 

by the Manager, International Validation 

Branch, FAA; or EASA; or Airbus SAS’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature.’’ 

(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 Airbus SAS’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Additional Information 

For more information about this AD, 

contact Tim Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone: 206– 

231–3667; email: timothy.p.dowling@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 2023–0053, dated March 14, 

2023. 

(ii) [Reserved] 

(3) For EASA AD 2023–0053, 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 at ad.easa.europa.eu. 

(4) You may view this material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(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 24, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–18693 Filed 8–30–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1810; Project 

Identifier MCAI–2023–00267–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Canada Limited Partnership (Type 

Certificate Previously Held by C Series 

Aircraft Limited Partnership (CSALP); 

Bombardier, 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 

certain Airbus Canada Limited 

Partnership Model BD–500–1A11 

airplanes. This proposed AD was 

prompted by a manufacturing issue with 

an electrical connector that may prevent 

the connector from self-locking. This 

proposed AD would require removing 

the affected connector, installing a new 

connector, and testing the emergency 

power supply units (EPSUs), as 

specified in a Transport Canada AD, 

which is proposed for incorporation by 

reference (IBR). 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–2023–1810; 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. 


ddrumheller on DSK120RN23PROD with PROPOSALS1