Airworthiness Directives; Airbus SAS Airplanes, 60157-60160 [2023-18693]

Download as PDF Federal Register / Vol. 88, No. 168 / Thursday, August 31, 2023 / Proposed Rules 60157 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) ........................................ Engine ratings and operating limitations including reciprocating engine limits. Durability (Propeller blade pitch control systems) .................................... Turbine, compressor, fan, and turbosupercharger rotor overspeed ........ Turbocharger rotors .................................................................................. Lubrication system .................................................................................... Vibration test ............................................................................................. Endurance test ......................................................................................... 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] ddrumheller on DSK120RN23PROD with PROPOSALS1 RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all SUMMARY: 3 CS–E, Section 33.4, appendices A33.1(b), A33.2, A33.3(b) and (c), and A33.4(a)(2). Sections 33.7(b)(6) and (b)(8). Section 33.19(b). Section 33.27. Section 33.34. Sections 33.39(a) and (c). Sections 33.43(a) and (c). Section 33.49(d). 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 Amendment 6—Aircraft cybersecurity. VerDate Sep<11>2014 17:26 Aug 30, 2023 Jkt 259001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\31AUP1.SGM 31AUP1 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. ddrumheller on DSK120RN23PROD with PROPOSALS1 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 VerDate Sep<11>2014 17:26 Aug 30, 2023 Jkt 259001 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 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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. E:\FR\FM\31AUP1.SGM 31AUP1 Federal Register / Vol. 88, No. 168 / Thursday, August 31, 2023 / Proposed Rules 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. 60159 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 ddrumheller on DSK120RN23PROD with PROPOSALS1 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 VerDate Sep<11>2014 17:26 Aug 30, 2023 Jkt 259001 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 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. Frm 00008 Fmt 4702 Sfmt 4702 [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 Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PO 00000 § 39.13 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. E:\FR\FM\31AUP1.SGM 31AUP1 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. ddrumheller on DSK120RN23PROD with PROPOSALS1 (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 VerDate Sep<11>2014 17:26 Aug 30, 2023 Jkt 259001 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. DEPARTMENT OF TRANSPORTATION (j) Additional Information Airworthiness Directives; Airbus Canada Limited Partnership (Type Certificate Previously Held by C Series Aircraft Limited Partnership (CSALP); Bombardier, Inc.) Airplanes 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1810; Project Identifier MCAI–2023–00267–T] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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. SUMMARY: 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. ADDRESSES: E:\FR\FM\31AUP1.SGM 31AUP1

Agencies

[Federal Register Volume 88, Number 168 (Thursday, August 31, 2023)]
[Proposed Rules]
[Pages 60157-60160]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-18693]


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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, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email [email protected]; website easa.europa.eu. You may 
find this material on the EASA website at

[[Page 60158]]

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: [email protected].

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: 
[email protected]. Any commentary that the FAA receives which 
is not specifically designated as CBI will be placed in the public 
docket for this rulemaking.

Background

    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.

[[Page 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
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
368 work-hours x $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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

Airbus 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.

[[Page 60160]]

(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: [email protected]. 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: 
[email protected].

(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 
[email protected]; 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 
[email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.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
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