Airworthiness Directives; Airbus SAS Airplanes, 10772-10775 [2021-03568]

Download as PDF 10772 Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–04–07 Piper Aircraft, Inc.: Amendment 39–21428; Docket No. FAA–2020–0830; Project Identifier 2020–CE–002–AD. (a) Effective Date This airworthiness directive (AD) is effective March 30, 2021. (b) Affected ADs None. (c) Applicability (c) This AD applies to the following Piper Aircraft, Inc., airplanes, certificated in any category: (1) Model PA–46–350P (Malibu Mirage) airplanes, serial numbers (S/Ns) 4622041, 4636041, 4636142, 4636143, 4636313, 4636341, and 4636379; (2) Model PA–46–500TP (Malibu Meridian) airplanes, S/Ns 4697141, 4697161, 4697086, and 4697020; and (3) Models PA–46–350P (Malibu Mirage), PA–46R–350T (Malibu Matrix), and PA–46– 500TP (Malibu Meridian) airplanes, all serial numbers, if the left wing has been replaced with a serviceable (more than zero hours time-in-service) wing. (d) Subject Joint Aircraft System Component (JASC) 3700, VACUUM SYSTEM. (e) Unsafe Condition This AD was prompted by nonconforming stall warning heat control systems, utilizing a left wing assembly without the proper stall warning modification design. Without the proper stall warning heat control modification kit during flights into icing VerDate Sep<11>2014 21:28 Feb 22, 2021 Jkt 253001 conditions with the landing gear down, ice can form on the stall vane, which may result in failure of the stall warning system. The FAA is issuing this AD to identify and correct nonconforming stall warning heat control systems. The unsafe condition, if not addressed, could result in the pilot being unaware of an approaching stall situation. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions (1) Within 100 hours time-in-service (TIS) after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, inspect the configuration of stall warning heat control system and, if required, install stall warning heat control modification kit part number (P/N) 8452–002 before further flight in accordance with steps 2 and 3 of the Instructions in Piper Aircraft, Inc., Service Letter No. 1261, dated July 19, 2019. (2) As of the effective date of this AD, do not install a wing on any Model PA–46–350P (Malibu Mirage), PA–46R–350T (Malibu Matrix), or PA–46–500TP (Malibu Meridian) airplane unless you have determined that the wing has the correct stall warning heat control system as required by paragraph (g)(1) of this AD. (h) Special Flight Permit A special flight permit may be issued to operate the airplane to a location where the requirements of this AD can be accomplished provided flight into known icing conditions is prohibited. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta ACO 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 certification office, send it to the attention of the person identified in paragraph (j)(1) of this AD. (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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by a Piper Aircraft, Inc. Organization Designation Authorization (ODA) that has been authorized by the Manager, Atlanta ACO Branch to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required PO 00000 Frm 00070 Fmt 4700 Sfmt 4700 for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information For more information about this AD, contact John Lee, Aviation Safety Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474–5568; email: john.lee@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 the AD specifies otherwise. (i) Piper Service Letter No. 1261, dated July 19, 2019. (ii) [Reserved] (3) For Piper Aircraft, Inc. service information identified in this AD, contact Piper Aircraft Inc., 2926 Piper Drive, Vero Beach, FL 32960; phone: 772–299–2686; email: customerservice@piper.com; website: https://www.piper.com/. (4) You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on February 4, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–03499 Filed 2–22–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0969; Project Identifier MCAI–2020–00853–T; Amendment 39–21393; AD 2021–02–10] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: E:\FR\FM\23FER1.SGM 23FER1 Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations ACTION: Final rule. The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350–941 and –1041 airplanes. 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. This AD requires repetitive inspections of certain areas of each cargo door for damage and corrective action. This AD also provides an optional terminating modification, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 30, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 30, 2021. ADDRESSES: For material 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 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. SUMMARY: Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for 10773 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. See the MCAI for additional background information. 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 final rule, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. 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 The FAA gave the public the opportunity to participate in developing this final rule. The FAA received no comments on the NPRM or on the determination of the cost to the public. Conclusion The FAA reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. 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. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus SAS Model A350– 941 and –1041 airplanes. The NPRM published in the Federal Register on October 26, 2020 (85 FR 67696). The NPRM 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 NPRM proposed to require repetitive inspections of certain areas of each cargo door for damage and corrective action. The NPRM also proposed to provide an optional terminating modification, as specified in an EASA AD. Related Service Information 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. Costs of Compliance The FAA estimates that this AD affects 13 airplanes of U.S. registry. The FAA estimates the following costs to comply with this 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 ..... VerDate Sep<11>2014 21:28 Feb 22, 2021 Jkt 253001 PO 00000 Frm 00071 Fmt 4700 Sfmt 4700 E:\FR\FM\23FER1.SGM 23FER1 Cost per product Up to $9,335. 10774 Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations The FAA has received no definitive data on which to base the cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. The FAA does not control warranty coverage for affected operators. 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 This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, VerDate Sep<11>2014 21:28 Feb 22, 2021 Jkt 253001 the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–02–10 Airbus SAS: Amendment 39– 21393; Docket No. FAA–2020–0969; Project Identifier MCAI–2020–00853–T. (a) Effective Date This airworthiness directive (AD) is effective March 30, 2021. (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 PO 00000 Frm 00072 Fmt 4700 Sfmt 4700 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 Large Aircraft Section, 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-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): 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) Related Information 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. (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 2020–0144, dated June 29, 2020. (ii) [Reserved] (3) For EASA AD 2020–0144, 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 EASA AD on the EASA website at https:// 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. This material may be found E:\FR\FM\23FER1.SGM 23FER1 Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020–0969. (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 fedreg.legal@ nara.gov, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Issued on January 12, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–03568 Filed 2–22–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0818; Project Identifier MCAI–2020–00987–A; Amendment 39–21381; AD 2021–01–05] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC– 24 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as electrical harness installations on PC–24 airplanes that are not in compliance with the approved design. This unsafe condition could lead to wire chafing and potential arcing or failure of wires having the incorrect length, possibly resulting in loss of system redundancy, or generation of smoke and smell, or loss of power plant fire protection function. This AD requires modifying the electrical harness installation. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 30, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 30, 2021. ADDRESSES: For service information identified in this final rule, contact Pilatus Aircraft Ltd., CH–6371, Stans, Switzerland; phone: +41 848 24 7 365; email: techsupport.ch@pilatusSUMMARY: VerDate Sep<11>2014 21:28 Feb 22, 2021 Jkt 253001 aircraft.com; website: http:// www.pilatus-aircraft.com/. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0818. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0818; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the MCAI, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aviation Safety Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; phone: (816) 329–4059; fax: (816) 329– 4090; email: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain serial-numbered Pilatus Model PC–24 airplanes. The NPRM published in the Federal Register on September 17, 2020 (85 FR 58002). The NPRM was prompted by MCAI originated by the European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. EASA has issued EASA AD No. 2020–0158, dated July 16, 2020 (referred to after this as ‘‘the MCAI’’), to address the unsafe condition on these products. The MCAI states: During production, electrical harness installations on some PC–24 aeroplanes were found not to comply with the approved design. This condition, if not corrected, could lead to wire chafing and potential arcing, or to failure of wires having the incorrect length, possibly resulting in loss of system redundancy, or generation of smoke and smell, or loss of power plant fire protection function. To address this potential unsafe condition, Pilatus issued the [service bulletin] SB, PO 00000 Frm 00073 Fmt 4700 Sfmt 4700 10775 providing instructions to improve the electrical harness installations in the nose bay, cockpit, fuselage, wing fairing and rear fuselage areas. For the reason described above, this [EASA] AD requires modification of the electrical harness installations. The incorrect length wires are too short in length and do not have appropriate slack, which could lead to wires being pulled loose from the terminals during flight or ground operation. Generation of smell refers to the smell from electrical arcing. You may examine the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0818. In the NPRM, the FAA proposed to require modifying the electrical harness installation. The FAA is issuing this AD to address the unsafe condition on these products. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the costs. Conclusion This product has been approved by the aviation authority of another country and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI and service information referenced above. The FAA reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. This AD is adopted as proposed in the NPRM. Related Service Information Under 1 CFR Part 51 The FAA reviewed Pilatus PC–24 Service Bulletin No. 91–001, dated April 7, 2020. The service information specifies procedures necessary to improve the electrical harness installation in the nose bay, cockpit, avionics rack, fuselage, wing fairing, and rear fuselage. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance The FAA estimates that this AD will affect 36 products of U.S. registry. The FAA also estimates that it will take 20 E:\FR\FM\23FER1.SGM 23FER1

Agencies

[Federal Register Volume 86, Number 34 (Tuesday, February 23, 2021)]
[Rules and Regulations]
[Pages 10772-10775]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-03568]


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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; 
Amendment 39-21393; AD 2021-02-10]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

[[Page 10773]]


ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A350-941 and -1041 airplanes. 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. This AD requires repetitive inspections of certain 
areas of each cargo door for damage and corrective action. This AD also 
provides an optional terminating modification, as specified in a 
European Union Aviation Safety Agency (EASA) AD, which is incorporated 
by reference. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective March 30, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 30, 
2021.

ADDRESSES: For material 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 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 final rule, any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

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:

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.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Airbus SAS Model 
A350-941 and -1041 airplanes. The NPRM published in the Federal 
Register on October 26, 2020 (85 FR 67696). The NPRM 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 
NPRM proposed to require repetitive inspections of certain areas of 
each cargo door for damage and corrective action. The NPRM also 
proposed to provide an optional terminating modification, as specified 
in an EASA AD.
    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. See the MCAI for additional 
background information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
except for minor editorial changes. The FAA has determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information 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.

Costs of Compliance

    The FAA estimates that this AD affects 13 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this 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   Up to $8,570........  Up to $9,335.
 = $765.
------------------------------------------------------------------------


[[Page 10774]]

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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:

2021-02-10 Airbus SAS: Amendment 39-21393; Docket No. FAA-2020-0969; 
Project Identifier MCAI-2020-00853-T.

(a) Effective Date

    This airworthiness directive (AD) is effective March 30, 2021.

(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 
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) 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): 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) Related Information

    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].

(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 2020-0144, 
dated June 29, 2020.
    (ii) [Reserved]
    (3) For 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.
    (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. This material may be found

[[Page 10775]]

in the AD docket on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0969.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on January 12, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-03568 Filed 2-22-21; 8:45 am]
BILLING CODE 4910-13-P