Airworthiness Directives; Airbus SAS Airplanes, 67696-67699 [2020-23372]

Download as PDF 67696 Federal Register / Vol. 85, No. 207 / Monday, October 26, 2020 / Proposed Rules 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, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866, 2. Will not affect intrastate aviation in Alaska, and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ Airbus Helicopters Deutschland GmbH: Docket No. FAA–2020–0967; Product Identifier 2018–SW–013–AD. (d) Compliance DEPARTMENT OF TRANSPORTATION You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Within 100 hours time-in-service: (1) Remove the surface coating from the TGB bellcrank attachment arm and using a 5X or higher power magnifying glass, dyepenetrant inspect the TGB arm for a crack and for any dent, nick, and scratch in the area shown in Figure 1 of Airbus Helicopters Alert Service Bulletin (ASB) MBB–BK117 C– 2–65A–008 or ASB MBB–BK117–30A–120, each Revision 0 and dated January 31, 2018, as applicable to your model helicopter. (2) If there is a crack, before further flight, replace the TGB. (3) If there is a dent, a nick, or a scratch, before further flight, remove the surface material up to 0.2 mm using 80-grit abrasive paper and repeat the dye penetrant inspection. If there is a crack or if the damage cannot be removed, before further flight, replace the TGB. (4) If there is no crack and no dent, nick, or scratch, before further flight, finish the surface with 600-grit or finer abrasive paper. (f) Special Flight Permits Special flight permits are prohibited. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (a) Applicability This airworthiness directive (AD) applies to Airbus Helicopters Deutschland GmbH Model MBB–BK117 A–1, MBB–BK117 A–3, MBB–BK117 A–4, MBB–BK117 B–1, MBB– BK117 B–2, MBB–BK117 C–1, and MBB– BK117 C–2 helicopters, certificated in any category. (h) Additional Information (b) Unsafe Condition This AD defines the unsafe condition as a crack in a tail gearbox (TGB) bellcrank attachment arm. This condition could result in disconnection of the bellcrank attachment arm from the TGB and subsequent loss of control of the helicopter. (i) Subject (c) Comments Due Date The FAA must receive comments by December 10, 2020. VerDate Sep<11>2014 17:11 Oct 23, 2020 Jkt 253001 The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD No. 2018–0046, dated February 19, 2018. You may view the EASA AD on the internet at https://www.regulations.gov in the AD Docket. Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor Gearbox. Issued on October 19, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–23446 Filed 10–23–20; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0969; Project Identifier MCAI–2020–00853–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 all Airbus SAS Model A350–941 and –1041 airplanes. This proposed AD was prompted by a report that certain retaining rings could cause damage to frame forks, brackets and edge frames, and their surface protection; subsequent investigation showed that the depth of the frame fork spotfacing on structural parts is inadequate to accommodate the retaining ring. This proposed AD would require repetitive inspections of certain areas of each cargo door for damage and corrective action. This proposed AD would also provide an optional terminating modification, as specified in a European Union Aviation Safety Agency (EASA) AD, which will be incorporated by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by December 10, 2020. 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 https://www.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. For material that will be incorporated by reference (IBR) in this AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@ easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may SUMMARY: E:\FR\FM\26OCP1.SGM 26OCP1 Federal Register / Vol. 85, No. 207 / Monday, October 26, 2020 / Proposed Rules view this IBR 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. It is also available in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0969. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0969; 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, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218; email kathleen.arrigotti@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to participate in this rulemaking by submitting written comments, data, or views about this proposal. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0969; Project Identifier MCAI–2020–00853–T’’ at the beginning of your 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, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, the FAA will consider all comments received by the closing date for comments. The FAA will consider comments filed after the comment period has closed if it is VerDate Sep<11>2014 17:33 Oct 23, 2020 Jkt 253001 possible to do so without incurring expense or delay. The FAA may change this NPRM because of those comments. 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 Kathleen Arrigotti, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218; email kathleen.arrigotti@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. Discussion The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2020–0144, dated June 29, 2020 (‘‘EASA AD 2020–0144’’) (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A350–941 and –1041 airplanes. This proposed AD was prompted by a report that certain retaining rings could cause damage to frame forks, brackets and edge frames, and their surface protection; subsequent investigation showed that the depth of the frame fork spotfacing on structural parts is inadequate to accommodate the retaining ring. The FAA is proposing this AD to address inadequate frame fork spotfacing depth for the retaining rings, which could reduce the structural integrity of the airplane. See the MCAI for additional background information. Related IBR Material Under 1 CFR Part 51 EASA AD 2020–0144 describes procedures for repetitive inspections of the edge frames, brackets, frame forks, and the access cover on the internal side of each cargo door for damage PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 67697 (including cracks and corrosion) and corrective actions. Corrective actions include repair or rework. EASA AD 2020–0144 also describes procedures for an optional modification of each affected cargo door, which terminates the repetitive inspections. 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 and Requirements of This Proposed AD 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 the State of Design Authority, the FAA has been notified of the unsafe condition described in the MCAI referenced above. The FAA is proposing this AD because the FAA evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in EASA AD 2020–0144 described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this AD. Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA initially worked with Airbus and EASA to develop a process to use certain EASA ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has since coordinated with other manufacturers and civil aviation authorities (CAAs) to use this process. As a result, EASA AD 2020–0144 will be incorporated by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2020–0144 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 the EASA AD 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 E:\FR\FM\26OCP1.SGM 26OCP1 67698 Federal Register / Vol. 85, No. 207 / Monday, October 26, 2020 / Proposed Rules will be available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0969 after the FAA final rule is published. not limited to the section titled ‘‘Required Action(s) and Compliance Time(s)’’ in the EASA AD. Service information specified in EASA AD 2020–0144 that is required for compliance with EASA AD 2020–0144 Costs of Compliance The FAA estimates that this proposed AD affects 13 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 24 work-hours × $85 per hour = $2,040 ..................................................................................... $0 $2,040 $26,520 ESTIMATED COSTS FOR OPTIONAL ACTIONS Labor cost Parts cost 9 work-hours × $85 per hour = $765 ...................................................................................................... Up to $8,570 .......... The FAA has received no definitive data on which to base the cost estimates for the on-condition actions specified in this proposed AD. According to the manufacturer, some or all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all known costs in the cost estimate. 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 VerDate Sep<11>2014 17:11 Oct 23, 2020 Jkt 253001 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) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus SAS: Docket No. FAA–2020–0969; Project Identifier MCAI–2020–00853–T. (a) Comments Due Date The FAA must receive comments by December 10, 2020. (b) Affected ADs None. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 Cost per product Up to $9,335. (c) Applicability This AD applies to all Airbus SAS Model A350–941 and –1041 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report that certain retaining rings could cause damage to frame forks, brackets and edge frames, and their surface protection; subsequent investigation showed that the depth of the frame fork spotfacing on structural parts is inadequate to accommodate the retaining ring. The FAA is issuing this AD to address inadequate frame fork spotfacing depth for the retaining rings, which could reduce the 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, European Union Aviation Safety Agency (EASA) AD 2020–0144, dated June 29, 2020 (‘‘EASA AD 2020–0144’’). (h) Exceptions to EASA AD 2020–0144 (1) Where EASA AD 2020–0144 refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2020–0144 does not apply to this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, 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 E:\FR\FM\26OCP1.SGM 26OCP1 Federal Register / Vol. 85, No. 207 / Monday, October 26, 2020 / Proposed Rules Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (j)(2) of this AD. Information may be emailed to: 9-AVS-AIR730-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, Large Aircraft Section, 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): For any service information referenced in EASA AD 2020–0144 that contains RC procedures and tests: Except as required by paragraph (i)(2) of this AD, RC 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) Related Information (1) For information about EASA AD 2020– 0144, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@ easa.europa.eu; Internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. 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. This material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0969. (2) For more information about this AD, contact Kathleen Arrigotti, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218; email kathleen.arrigotti@faa.gov. Issued on October 16, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–23372 Filed 10–23–20; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 17:11 Oct 23, 2020 Jkt 253001 DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Part 292 [Docket Nos. RM21–2–000 and RM20–20– 000] Fuel Cell Thermal Energy Output; Bloom Energy Corporation Federal Energy Regulatory Commission, Department of Energy. ACTION: Notice of proposed rulemaking. AGENCY: In this Notice of Proposed Rulemaking, the Federal Energy Regulatory Commission proposes to amend the definition of useful thermal energy output in its regulations implementing the Public Utility Regulatory Policies Act of 1978 to recognize the technical evolution of cogeneration. SUMMARY: DATES: Comments are due November 25, 2020. Comments, identified by docket number, may be filed electronically at http://www.ferc.gov in acceptable native applications and print-to-PDF, but not in scanned or picture format. For those unable to file electronically, comments may be filed by mail or hand-delivery to: Federal Energy Regulatory Commission, Secretary of the Commission, 888 First Street NE, Washington, DC 20426. The Comment Procedures Section of this document contains more detailed filing procedures. FOR FURTHER INFORMATION CONTACT: Lawrence R. Greenfield (Legal Information), Office of the General Counsel, Federal Energy Regulatory Commission, 888 First Street NE, Washington, DC 20426, (202) 502– 6415, lawrence.greenfield@ferc.gov Helen Shepherd (Technical Information), Office of Energy Market Regulation, Federal Energy Regulatory Commission, 888 First Street NE, Washington, DC 20426, (202) 502– 6176, helen.shepherd@ferc.gov Thomas Dautel (Technical Information), Office of Energy Policy and Innovation, Federal Energy Regulatory Commission, 888 First Street NE, Washington, DC 20426, (202) 502– 6196, thomas.dautel@ferc.gov SUPPLEMENTARY INFORMATION: ADDRESSES: I. Introduction 1. In this Notice of Proposed Rulemaking (NOPR), the Federal Energy Regulatory Commission (Commission) proposes to revise its regulations PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 67699 (PURPA Regulations) 1 implementing sections 201 and 210 of the Public Utility Regulatory Policies Act of 1978 (PURPA) 2 in light of the development of Solid Oxide Fuel Cell systems with integrated natural gas reformation equipment as a technical evolution of cogeneration and in response to a petition for rulemaking submitted by Bloom Energy Corporation (Bloom Energy) asking the Commission to take such action given such development. 2. PURPA was enacted in 1978 as part of a package of legislative proposals intended to reduce the country’s dependence on oil and natural gas, which at the time were in short supply and subject to dramatic price increases.3 PURPA sets forth a framework to encourage the development of cogeneration facilities that make more efficient use of the heat produced both from fossil fuels used in the production of electricity by using that heat for, e.g., industrial purposes, and also from fossil fuels used for, e.g., industrial purposes by using that heat for the production of electricity. As relevant here, as required by PURPA, a cogeneration facility is a qualifying facility (QF) if the Commission determines that the QF meets certain requirements.4 3. In enacting PURPA, Congress could not, and did not, predict specific technological developments that would occur in future years, but instead recognized the Commission’s discretion by directing the Commission to ‘‘from time to time thereafter revise[ ] such rules as it determines necessary to encourage cogeneration.’’ 5 Although in 1978 the predominant form of cogeneration was a more traditional combined heat and power, Congress did not limit the definition of qualifying cogeneration facilities to the particular technologies then in existence. Instead, Congress defined a cogeneration facility in a more open-ended manner, as a facility that produces: (1) Electric energy; and (2) steam or forms of useful energy, such as heat, which are used for industrial, commercial, heating or cooling purpose.6 Congress thus left it for the Commission to determine the types of facilities that would qualify as cogeneration facilities under the statute. 4. Due to innovation and development in the last decade, Solid Oxide Fuel Cell 1 18 CFR part 292. U.S.C. 796, 824a–3. 3 Qualifying Facility Rates and Requirements Implementation Issues Under the Public Utility Regulatory Policies Act of 1978, Order No. 872, 85 FR 54,638 (Sept. 2, 2020), 172 FERC ¶ 61,041, at P 47 (2020). 4 16 U.S.C. 796(18); 18 CFR 292.203(b), 292.205. 5 16 U.S.C. 824a–3(a). 6 16 U.S.C. 796(18)(A). 2 16 E:\FR\FM\26OCP1.SGM 26OCP1

Agencies

[Federal Register Volume 85, Number 207 (Monday, October 26, 2020)]
[Proposed Rules]
[Pages 67696-67699]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-23372]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0969; Project Identifier MCAI-2020-00853-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 A350-941 and -1041 airplanes. This proposed AD 
was prompted by a report that certain retaining rings could cause 
damage to frame forks, brackets and edge frames, and their surface 
protection; subsequent investigation showed that the depth of the frame 
fork spotfacing on structural parts is inadequate to accommodate the 
retaining ring. This proposed AD would require repetitive inspections 
of certain areas of each cargo door for damage and corrective action. 
This proposed AD would also provide an optional terminating 
modification, as specified in a European Union Aviation Safety Agency 
(EASA) AD, which will be incorporated by reference. The FAA is 
proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by December 
10, 2020.

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 https://www.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.
    For material that will be incorporated by reference (IBR) in this 
AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 8999 000; email [email protected]; internet 
www.easa.europa.eu. You may find this IBR material on the EASA website 
at https://ad.easa.europa.eu. You may

[[Page 67697]]

view this IBR 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. It is also available in the AD docket on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2020-0969.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0969; 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, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aerospace 
Engineer, Large Aircraft Section, International Validation Branch, FAA, 
2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-
3218; email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting 
written comments, data, or views about this proposal. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time. Send your 
comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2020-0969; Project Identifier MCAI-2020-00853-T'' at 
the beginning of your 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, as well 
as a report summarizing each substantive public contact with FAA 
personnel concerning this proposed rulemaking. Before acting on this 
proposal, the FAA will consider all comments received by the closing 
date for comments. The FAA will consider comments filed after the 
comment period has closed if it is possible to do so without incurring 
expense or delay. The FAA may change this NPRM because of those 
comments.

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 
Kathleen Arrigotti, Aerospace Engineer, Large Aircraft Section, 
International Validation Branch, FAA, 2200 South 216th St., Des Moines, 
WA 98198; telephone and fax 206-231-3218; 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.

Discussion

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2020-0144, dated June 29, 2020 
(``EASA AD 2020-0144'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Airbus SAS Model A350-941 and -1041 airplanes.
    This proposed AD was prompted by a report that certain retaining 
rings could cause damage to frame forks, brackets and edge frames, and 
their surface protection; subsequent investigation showed that the 
depth of the frame fork spotfacing on structural parts is inadequate to 
accommodate the retaining ring. The FAA is proposing this AD to address 
inadequate frame fork spotfacing depth for the retaining rings, which 
could reduce the structural integrity of the airplane. See the MCAI for 
additional background information.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2020-0144 describes procedures for repetitive inspections 
of the edge frames, brackets, frame forks, and the access cover on the 
internal side of each cargo door for damage (including cracks and 
corrosion) and corrective actions. Corrective actions include repair or 
rework. EASA AD 2020-0144 also describes procedures for an optional 
modification of each affected cargo door, which terminates the 
repetitive inspections. 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 and Requirements of This Proposed AD

    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 the State of Design Authority, 
the FAA has been notified of the unsafe condition described in the MCAI 
referenced above. The FAA is proposing this AD because the FAA 
evaluated all the relevant information and determined the unsafe 
condition described previously is likely to exist or develop in other 
products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2020-0144 described previously, as incorporated by 
reference, except for any differences identified as exceptions in the 
regulatory text of this AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA initially worked with Airbus and EASA to develop a 
process to use certain EASA ADs as the primary source of information 
for compliance with requirements for corresponding FAA ADs. The FAA has 
since coordinated with other manufacturers and civil aviation 
authorities (CAAs) to use this process. As a result, EASA AD 2020-0144 
will be incorporated by reference in the FAA final rule. This proposed 
AD would, therefore, require compliance with EASA AD 2020-0144 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 the EASA AD 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

[[Page 67698]]

not limited to the section titled ``Required Action(s) and Compliance 
Time(s)'' in the EASA AD. Service information specified in EASA AD 
2020-0144 that is required for compliance with EASA AD 2020-0144 will 
be available on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0969 after the FAA final 
rule is published.

Costs of Compliance

    The FAA estimates that this proposed AD affects 13 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
----------------------------------------------------------------------------------------------------------------
24 work-hours x $85 per hour = $2,040........................              $0           $2,040          $26,520
----------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
               Labor cost                             Parts cost                       Cost per product
----------------------------------------------------------------------------------------------------------------
9 work-hours x $85 per hour = $765.....  Up to $8,570.......................  Up to $9,335.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition actions specified in this proposed AD.
    According to the manufacturer, some or all of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected individuals. The FAA does not control warranty 
coverage for affected individuals. As a result, the FAA has included 
all known costs in the cost estimate.

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) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The 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 (AD):

Airbus SAS: Docket No. FAA-2020-0969; Project Identifier MCAI-2020-
00853-T.

(a) Comments Due Date

    The FAA must receive comments by December 10, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A350-941 and -1041 
airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report that certain retaining rings 
could cause damage to frame forks, brackets and edge frames, and 
their surface protection; subsequent investigation showed that the 
depth of the frame fork spotfacing on structural parts is inadequate 
to accommodate the retaining ring. The FAA is issuing this AD to 
address inadequate frame fork spotfacing depth for the retaining 
rings, which could reduce the 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, European Union Aviation Safety Agency (EASA) AD 
2020-0144, dated June 29, 2020 (``EASA AD 2020-0144'').

(h) Exceptions to EASA AD 2020-0144

    (1) Where EASA AD 2020-0144 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2020-0144 does not apply 
to this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Large Aircraft Section, 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

[[Page 67699]]

Standards Office, as appropriate. If sending information directly to 
the Large Aircraft Section, International Validation Branch, send it 
to the attention of the person identified in paragraph (j)(2) 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, Large Aircraft 
Section, 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): For any service information 
referenced in EASA AD 2020-0144 that contains RC procedures and 
tests: Except as required by paragraph (i)(2) of this AD, RC 
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) Related Information

    (1) For information about EASA AD 2020-0144, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email [email protected]; Internet www.easa.europa.eu. You 
may find this EASA AD on the EASA website at https://ad.easa.europa.eu. 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. This material may be 
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2020-0969.
    (2) For more information about this AD, contact Kathleen 
Arrigotti, Aerospace Engineer, Large Aircraft Section, International 
Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3218; email [email protected].

    Issued on October 16, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.

[FR Doc. 2020-23372 Filed 10-23-20; 8:45 am]
BILLING CODE 4910-13-P