Airworthiness Directives; Airbus SAS Airplanes, 79477-79480 [2024-22180]

Download as PDF Federal Register / Vol. 89, No. 189 / Monday, September 30, 2024 / Proposed Rules check analysis—Aluminum PPM allowable; of Austro MSB–E4–039/3, before further flight, replace the pistons, piston rings, conrods assembly, and crankcase, or replace the engine core in accordance with paragraph 2., Technical Details, Engine core replacement; or Pistons, piston rings, crankcase and conrod assy replacement; as applicable, of Austro MSB–E4–039/3. (5) For Group 3 and Group 4 engines, within the applicable compliance times specified in Table 3 to paragraph (g)(5) of this 79477 AD, replace the pistons, piston rings, and con-rods assembly, or replace the engine core in accordance with paragraph 2., Technical Details, Engine core replacement; or Pistons, piston rings and con-rod assy replacement, as applicable, of Austro MSB–E4–039/3. TABLE 3 TO PARAGRAPH (g)(5)—REPLACEMENT FOR GROUP 3 AND 4 ENGINES Engine group Compliance time Group 3 engines that do not have an ESN identified in Table 2 to paragraph (g)(1) of this AD. Before exceeding 900 FHs since new, or within 15 FHs after December 11, 2023 (the effective date of AD 2023–20–03), whichever occurs later. Before exceeding 900 FHs since new, or within 15 FHs after the effective date of this AD, whichever occurs later Before exceeding 1,000 FHs since new, or within 25 FHs after December 11, 2023 (the effective date of AD 2023–20–03), whichever occurs later. Before exceeding 1,000 FHs since new, or within 25 FHs after the effective date of this AD, whichever occurs later. Group 3 engines that have an ESN identified in Table 2 to paragraph (g)(1) of this AD. Group 4 engines that do not have an ESN identified in Table 2 to paragraph (g)(1) of this AD. Group 4 engines that have an ESN identified in Table 2 to paragraph (g)(1) of this AD. Note 1 to paragraph (g)(5): FHs since new indicated in Table 3 to paragraph (g)(5) of this AD are FHs accumulated by the engine since first installation on an airplane or since last overhaul as of December 11, 2023 (the effective date of AD 2023–20–03) for Group 3 and 4 engines that do not have an ESN identified in Table 2 to paragraph (g)(1) of this AD, or as of the effective date of this AD for Group 3 and 4 engines that have an ESN identified in Table 2 to paragraph (g)(1) of this AD. (h) Terminating Action (1) Replacement of the pistons, piston rings, con-rods assembly, and crankcase, or replacement of the engine core, as specified in paragraph (g)(4) of this AD, constitutes terminating action for the repetitive oil analysis required by paragraph (g)(2) of this AD. (2) Replacement of the pistons, piston rings, and con-rods assembly, or replacement of the engine core, as specified in paragraph (g)(5) of this AD, constitutes terminating action for the repetitive oil analysis required by paragraph (g)(2) of this AD. ddrumheller on DSK120RN23PROD with PROPOSALS1 (i) Definitions For the purpose of this AD: (1) Group 1 engines are engines having an ESN listed in Table 1 of No. MSB–E4–039/ 3. (2) Group 2 engines are engines having an ESN listed in Table 2 of No. MSB–E4–039/ 3. (3) Group 3 engines are engines having an ESN listed in Table 3 of No. MSB–E4–039/ 3. (4) Group 4 engines are engines having an ESN listed in Table 4 of No. MSB–E4–039/ 3. (j) Credit for Previous Actions (1) You may take credit for the actions required by paragraph (g)(1), (4), or (5) of this AD, if you performed those actions before December 11, 2023 (the effective date of AD 2023–20–03) using Austro Engine GmbH Mandatory Service Bulletin No. MSB–E4– 039/0, dated October 24, 2022. (2) You may take credit for the actions required by paragraph (g)(1), (4), or (5) of this VerDate Sep<11>2014 16:41 Sep 27, 2024 Jkt 262001 AD if you performed those actions before the effective date of this AD using Austro Engine GmbH Mandatory Service Bulletin No. MSB– E4–039/2, Revision 2, dated July 26, 2023. (k) No Return of Parts/Reporting Requirement Although the service information specifies returning certain parts and submitting certain information to the manufacturer, this AD does not include those requirements. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (m)(1) of this AD and email to AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (i) Austro Engine GmbH Mandatory Service Bulletin No. MSB–E4–039/3, Revision 3, dated November 22, 2023. (ii) [Reserved] (3) For Austro Engine GmbH material identified in this AD, contact Austro Engine GmbH, Rudolf-Diesel-Strasse 11, A–2700 Weiner Neustadt, Austria; phone: +43 2622 23000; website: austroengine.at. (4) You may view this material at FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. 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 September 23, 2024. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–22064 Filed 9–27–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION (m) Additional Information (1) For more information about this AD, contact Morton Lee, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (860) 386– 1791; email: morton.y.lee@faa.gov. (2) Material identified in this AD that is not incorporated by reference is available at the address specified in paragraph (n)(3) of this AD. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless the AD specifies otherwise. PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2320; Project Identifier MCAI–2024–00268–T] 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 SUMMARY: E:\FR\FM\30SEP1.SGM 30SEP1 ddrumheller on DSK120RN23PROD with PROPOSALS1 79478 Federal Register / Vol. 89, No. 189 / Monday, September 30, 2024 / Proposed Rules certain Airbus SAS Model A350–941 and –1041 airplanes. This proposed AD was prompted by an updated stress analysis on the forward (FWD) cargo door and its attachment piano hinges that revealed a risk of cracking and crack propagation on piano hinges 2 and 3, originating from opening-closing fatigue cycles of the FWD cargo door. This proposed AD would require an inspection of the affected parts, and applicable corrective actions, 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 November 14, 2024. 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–2024–2320; 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 EASA material identified in this proposed 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 ad.easa.europa.eu. It is also available at regulations.gov under Docket No. FAA– 2024–2320. • 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: Dat Le, Aviation Safety Engineer, FAA, 1600 VerDate Sep<11>2014 16:41 Sep 27, 2024 Jkt 262001 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; email dat.v.le@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 the ADDRESSES section. Include ‘‘Docket No. FAA–2024–2320; Project Identifier MCAI–2024–00268–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 Dat Le, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; email dat.v.le@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 EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2024–0129, dated July 5, 2024 (also referred to as PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 the MCAI), to correct an unsafe condition for certain Airbus SAS Model A350–941 and –1041 airplanes. The MCAI states an update of the stress analysis resulted in a new definition of interface load distribution between the FWD cargo door and the associated fuselage piano hinges. Further investigation revealed a risk of cracking and crack propagation on the affected parts, originating from opening-closing fatigue cycles of the FWD cargo door. Under this condition, door operation could cause damage to the FWD cargo door surrounding structure. The FAA is proposing this AD to address damage to the FWD cargo door surrounding structure, which could reduce the structural integrity of the airplane. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2024–2320. Material Incorporated by Reference Under 1 CFR Part 51 EASA AD 2024–0129 specifies procedures for performing a detailed inspection for cracks and damage (including dents, discoloration, punctures, nicks, and scratches) of the FWD cargo door piano hinges 2 and 3, and obtaining and following instructions for repair of cracks and damage. EASA AD 2024–0129 also specifies procedures for checking the condition and integrity of the temporary protection system (TPS) layer, if installed, removing any damaged TPS layer, and applying a new layer if the TPS layer was damaged, removed, or cleaned. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. 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. Proposed AD Requirements in This NPRM This proposed AD would require accomplishing the actions specified in EASA AD 2024–0129 described previously, except for any differences E:\FR\FM\30SEP1.SGM 30SEP1 Federal Register / Vol. 89, No. 189 / Monday, September 30, 2024 / Proposed Rules 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 2024–0129 by reference in the FAA final rule. This proposed AD would, therefore, requires compliance with EASA AD 2024–0129 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 2024–0129 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 79479 not limited to the section titled ‘‘Required Action(s) and Compliance Time(s)’’ in EASA AD 2024–0129. Material required by EASA AD 2024– 0129 for compliance will be available at regulations.gov under Docket No. FAA– 2024–2320 after the FAA final rule is published. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 28 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 1 work-hour × $85 per hour = $85 ................. $0 $85 $2,380 Action Inspection (cargo door piano hinges) and TPS layer check. 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 ddrumheller on DSK120RN23PROD with PROPOSALS1 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. (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. (c) Applicability This AD applies to Airbus SAS Model A350–941 and –1041 airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2024–0129, dated July 5, 2024 (EASA AD 2024–0129). List of Subjects in 14 CFR Part 39 (e) Unsafe Condition This AD was prompted by an updated stress analysis on the forward (FWD) cargo door and its attachment piano hinges that revealed a risk of cracking and crack propagation on piano hinges 2 and 3, originating from opening-closing fatigue cycles of the FWD cargo door. The FAA is issuing this AD to address potential failure of the piano hinges due to cracking. The unsafe condition, if not addressed, could result in damage to the FWD cargo door surrounding structure and consequent reduced structural integrity of the airplane. 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. Regulatory Findings § 39.13 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: ■ VerDate Sep<11>2014 16:41 Sep 27, 2024 Jkt 262001 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: Airbus SAS: Docket No. FAA–2024–2320; Project Identifier MCAI–2024–00268–T. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by November 14, 2024. (b) Affected ADs None. PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (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, EASA AD 2024–0129. (h) Exceptions to EASA AD 2024–0129 (1) Where EASA AD 2024–0129 refers to ‘‘16 May 2024 [the effective date of EASA AD 2024–0098],’’ this AD requires using the effective date of this AD. (2) Where paragraph (2) of EASA AD 2024– 0129 specifies ‘‘if, during the DET as required by paragraph (1) of this AD, any crack or damage is detected, before next flight, contact Airbus for approved instructions and, within the compliance time specified therein, E:\FR\FM\30SEP1.SGM 30SEP1 79480 Federal Register / Vol. 89, No. 189 / Monday, September 30, 2024 / Proposed Rules accomplish those instructions accordingly,’’ this AD requires replacing that text with ‘‘if any crack or damage is detected, the crack or damage 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.’’ (3) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2024–0129. ddrumheller on DSK120RN23PROD with PROPOSALS1 (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 manager of the International Validation Branch, mail it to the address identified in paragraph (j) of this AD. Information may be emailed to: 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 paragraphs (h)(2) and (i)(2) of this AD, if any material referenced in EASA AD 2024–0129 contains paragraphs that are labeled as RC, the instructions in RC paragraphs, including subparagraphs under an RC paragraph, must be done to comply with this AD; any paragraphs, including subparagraphs under those paragraphs, that are not identified as RC are recommended. The instructions in paragraphs, including subparagraphs under those paragraphs, 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 instructions identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to instructions identified as RC require approval of an AMOC. (j) Additional Information For more information about this AD, contact Dat Le, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228– 7300; email dat.v.le@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. VerDate Sep<11>2014 16:41 Sep 27, 2024 Jkt 262001 (2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2024–0129, dated July 5, 2024. (ii) [Reserved] (3) For EASA AD 2024–0129 identified in this AD, contact EASA, Konrad-AdenauerUfer 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 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 September 23, 2024. Peter A. White, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024–22180 Filed 9–27–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2322; Project Identifier MCAI–2024–00065–Q] RIN 2120–AA64 Airworthiness Directives; THOMMEN AIRCRAFT EQUIPMENT AG Digital Air Data Computers Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain THOMMEN AIRCRAFT EQUIPMENT AG (THOMMEN) AC32 Digital Air Data Computers. This proposed AD results from occurrences of AC32 Digital Air Data Computers (ADCs) that stop functioning below certain temperatures. This proposed AD would require replacing an affected AC32 Digital ADC with a serviceable part. The FAA is proposing this AD to address the unsafe condition on these products. SUMMARY: The FAA must receive comments on this NPRM by November 14, 2024. ADDRESSES: You may send comments, using the procedures found in 14 CFR DATES: PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 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–2024–2322; 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 THOMMEN AIRCRAFT EQUIPMENT material identified in this proposed AD, contact THOMMEN AIRCRAFT EQUIPMENT AG, Hofackerstrasse 48, 4132 Muttenz, Switzerland; phone: +41 (0) 61 965 22 22; email: sales@thommen.aero; website: thommen.aero. • You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (817) 222–5110. FOR FURTHER INFORMATION CONTACT: William Reisenauer, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (516) 228–7301; email: 9-AVS-AIRBACO-COS@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–2024–2322; Project Identifier MCAI–2024–00065–Q’’ 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 E:\FR\FM\30SEP1.SGM 30SEP1

Agencies

[Federal Register Volume 89, Number 189 (Monday, September 30, 2024)]
[Proposed Rules]
[Pages 79477-79480]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-22180]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2320; Project Identifier MCAI-2024-00268-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

[[Page 79478]]

certain Airbus SAS Model A350-941 and -1041 airplanes. This proposed AD 
was prompted by an updated stress analysis on the forward (FWD) cargo 
door and its attachment piano hinges that revealed a risk of cracking 
and crack propagation on piano hinges 2 and 3, originating from 
opening-closing fatigue cycles of the FWD cargo door. This proposed AD 
would require an inspection of the affected parts, and applicable 
corrective actions, 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 November 
14, 2024.

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-2024-2320; 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 EASA material identified in this proposed 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 ad.easa.europa.eu. It is also 
available at regulations.gov under Docket No. FAA-2024-2320.
     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: Dat Le, Aviation Safety Engineer, FAA, 
1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7300; 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 the ADDRESSES section. Include ``Docket No. FAA-2024-2320; 
Project Identifier MCAI-2024-00268-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 Dat 
Le, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7300; 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

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2024-0129, dated July 5, 2024 (also 
referred to as the MCAI), to correct an unsafe condition for certain 
Airbus SAS Model A350-941 and -1041 airplanes. The MCAI states an 
update of the stress analysis resulted in a new definition of interface 
load distribution between the FWD cargo door and the associated 
fuselage piano hinges. Further investigation revealed a risk of 
cracking and crack propagation on the affected parts, originating from 
opening-closing fatigue cycles of the FWD cargo door. Under this 
condition, door operation could cause damage to the FWD cargo door 
surrounding structure.
    The FAA is proposing this AD to address damage to the FWD cargo 
door surrounding structure, which could reduce the structural integrity 
of the airplane.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2024-2320.

Material Incorporated by Reference Under 1 CFR Part 51

    EASA AD 2024-0129 specifies procedures for performing a detailed 
inspection for cracks and damage (including dents, discoloration, 
punctures, nicks, and scratches) of the FWD cargo door piano hinges 2 
and 3, and obtaining and following instructions for repair of cracks 
and damage. EASA AD 2024-0129 also specifies procedures for checking 
the condition and integrity of the temporary protection system (TPS) 
layer, if installed, removing any damaged TPS layer, and applying a new 
layer if the TPS layer was damaged, removed, or cleaned.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

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.

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2024-0129 described previously, except for any differences

[[Page 79479]]

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 2024-0129 by reference in the FAA 
final rule. This proposed AD would, therefore, requires compliance with 
EASA AD 2024-0129 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 2024-0129 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 2024-
0129. Material required by EASA AD 2024-0129 for compliance will be 
available at regulations.gov under Docket No. FAA-2024-2320 after the 
FAA final rule is published.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 28 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.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection (cargo door piano hinges)  1 work-hour x $85 per                $0              $85           $2,380
 and TPS layer check.                  hour = $85.
----------------------------------------------------------------------------------------------------------------

    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-2024-2320; Project Identifier MCAI-2024-
00268-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by November 14, 2024.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A350-941 and -1041 
airplanes, certificated in any category, as identified in European 
Union Aviation Safety Agency (EASA) AD 2024-0129, dated July 5, 2024 
(EASA AD 2024-0129).

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an updated stress analysis on the 
forward (FWD) cargo door and its attachment piano hinges that 
revealed a risk of cracking and crack propagation on piano hinges 2 
and 3, originating from opening-closing fatigue cycles of the FWD 
cargo door. The FAA is issuing this AD to address potential failure 
of the piano hinges due to cracking. The unsafe condition, if not 
addressed, could result in damage to the FWD cargo door surrounding 
structure and consequent reduced structural integrity of the 
airplane.

(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, EASA AD 2024-0129.

(h) Exceptions to EASA AD 2024-0129

    (1) Where EASA AD 2024-0129 refers to ``16 May 2024 [the 
effective date of EASA AD 2024-0098],'' this AD requires using the 
effective date of this AD.
    (2) Where paragraph (2) of EASA AD 2024-0129 specifies ``if, 
during the DET as required by paragraph (1) of this AD, any crack or 
damage is detected, before next flight, contact Airbus for approved 
instructions and, within the compliance time specified therein,

[[Page 79480]]

accomplish those instructions accordingly,'' this AD requires 
replacing that text with ``if any crack or damage is detected, the 
crack or damage 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.''
    (3) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0129.

(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 manager of the 
International Validation Branch, mail it to the address 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 
paragraphs (h)(2) and (i)(2) of this AD, if any material referenced 
in EASA AD 2024-0129 contains paragraphs that are labeled as RC, the 
instructions in RC paragraphs, including subparagraphs under an RC 
paragraph, must be done to comply with this AD; any paragraphs, 
including subparagraphs under those paragraphs, that are not 
identified as RC are recommended. The instructions in paragraphs, 
including subparagraphs under those paragraphs, 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 instructions identified as RC can 
be done and the airplane can be put back in an airworthy condition. 
Any substitutions or changes to instructions identified as RC 
require approval of an AMOC.

(j) Additional Information

    For more information about this AD, contact Dat Le, Aviation 
Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7300; email [email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the material listed in this paragraph 
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless this AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2024-0129, 
dated July 5, 2024.
    (ii) [Reserved]
    (3) For EASA AD 2024-0129 identified 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 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 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 [email protected].

    Issued on September 23, 2024.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2024-22180 Filed 9-27-24; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.