Airworthiness Directives; Airbus SAS Airplanes, 67545-67547 [2022-24310]

Download as PDF Federal Register / Vol. 87, No. 216 / Wednesday, November 9, 2022 / Rules and Regulations (b) Affected ADs None. (c) Applicability This AD applies to Airbus Canada Limited Partnership Model BD–500–1A10 and BD– 500–1A11 airplanes, certificated in any category, as identified in Transport Canada Civil Aviation (TCCA) AD CF–2021–50, dated December 21, 2021 (TCCA AD CF– 2021–50). (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Unsafe Condition This AD was prompted by reports that the engine feed pressure switches were installed with no secondary locking mechanism and can become loose and cause a fuel leak. The FAA is issuing this AD to address the absence of a secondary locking feature (lockwire) on the fuel pressure switches, which may allow them to become loose and allow fuel to leak in the affected areas, creating a fire hazard. (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, TCCA AD CF–2021–50. khammond on DSKJM1Z7X2PROD with RULES (h) Exception to TCCA AD CF–2021–50 (1) Where TCCA AD CF–2021–50 refers to hours air time, this AD requires using flight hours. (2) Where TCCA AD CF–2021–50 refers to its effective date, or 14 July 2021, the effective date of TCCA AD CF–2021–21, this AD requires using the effective date of this AD. (i) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300. 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, New York ACO Branch, FAA; or TCCA; or Airbus Canada Limited VerDate Sep<11>2014 16:01 Nov 08, 2022 Jkt 259001 Partnership’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (j) Additional Information For more information about this AD, contact Joseph Catanzaro, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7366; email 9-avs-nyacocos@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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) Transport Canada Civil Aviation (TCCA) AD CF–2021–50, dated December 21, 2021. (ii) [Reserved] (3) For TCCA AD CF–2021–50, contact TCCA, Transport Canada National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario K1A 0N5, Canada; telephone 888– 663–3639; email AD-CN@tc.gc.ca; website tc.canada.ca/en/aviation. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on September 28, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–24311 Filed 11–8–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–0986; Project Identifier MCAI–2021–01440–T; Amendment 39–22201; AD 2022–21–02] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2000–20– SUMMARY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 67545 15, which applied to certain Airbus SAS Model A300 and A300–600 series airplanes. AD 2000–20–15 required a high frequency eddy current (HFEC) inspection to detect cracking of the rear fittings of fuselage frame FR40 at stringer 27, and repetitive inspections or repair, as applicable. In lieu of accomplishing the repetitive inspections, AD 2000–20–15 provided a modification that would allow the inspection to be deferred for a certain period of time. This AD was prompted by cracking of the rear fittings of fuselage frame FR40 at stringer 27, and a determination that reduced compliance times are necessary. This AD removes airplanes from the applicability, and continues to require the actions in AD 2000–20–15, but at reduced compliance times, 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 December 14, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 14, 2022. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2022–0986; 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 mandatory continuing airworthiness information (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. Material Incorporated by Reference: • For material incorporated by reference in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; website easa.europa.eu. You may find this IBR material on the EASA website at 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. It is also available in the AD docket at regulations.gov under Docket No. FAA– 2022–0986. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, Large E:\FR\FM\09NOR1.SGM 09NOR1 67546 Federal Register / Vol. 87, No. 216 / Wednesday, November 9, 2022 / Rules and Regulations Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3225; email dan.rodina@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2000–20–15, Amendment 39–11926 (65 FR 60349, October 11, 2000) (AD 2000–20–15). AD 2000–20–15 applied to certain Airbus SAS Model A300 and A300–600 series airplanes. AD 2000–20–15 required a HFEC inspection to detect cracking of the rear fittings of fuselage frame FR40 at stringer 27, and repetitive inspections or repair, as applicable. In lieu of accomplishing the repetitive inspections, AD 2000–20–15 provides a modification that would allow the inspection to be deferred for a certain period of time. The FAA issued AD 2000–20–15 to address fatigue cracking of the rear fittings of fuselage frame FR40 at stringer 27, which could result in reduced structural integrity of the airplane. The NPRM published in the Federal Register on August 2, 2022 (87 FR 47144). The NPRM was prompted by EASA AD 2021–0288, dated December 21, 2021, issued by the European Union Aviation Safety Agency (referred to after this as the MCAI). The MCAI states that cracking of the rear fittings of fuselage frame FR40 at stringer 27 was found, and a determination made that reduced compliance times are necessary. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2022–0986. In the NPRM, the FAA proposed to continue to require the actions in AD 2000–20–15, but at reduced compliance times, as specified in EASA AD 2021– 0288, dated December 21, 2021. The NPRM also proposed to remove airplanes from the applicability, as specified in EASA AD 2021–0288. The FAA is issuing this AD to address the unsafe condition on these products. Discussion of Final Airworthiness Directive Comments The FAA received comments from the Air Line Pilots Association, International (ALPA), and FedEx Express, who supported the NPRM without change. Conclusion 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 reviewed the relevant data, considered the comment[s] received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on this product. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 EASA AD 2021–0288 specifies procedures for repetitive inspections of the rear fittings of fuselage frame FR40 at stringer 27 for cracking, and repair of any cracking. 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 67 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Inspection ............ 6 work-hours × $85 per hour = $510 ........................ The FAA estimates the following costs to do any necessary repair based Cost per product Parts cost $0 on the results of any required inspection. The FAA has no way of Cost on U.S. operators $510 $34,170, per inspection cycle. determining the number of aircraft that might need this repair: ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Parts cost Cost per product 31 work-hours × $85 per hour = $2,635 ................................................................................................................. $132 $2,767 khammond on DSKJM1Z7X2PROD with RULES 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 VerDate Sep<11>2014 16:01 Nov 08, 2022 Jkt 259001 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 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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 E:\FR\FM\09NOR1.SGM 09NOR1 Federal Register / Vol. 87, No. 216 / Wednesday, November 9, 2022 / Rules and Regulations (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: a. Removing Airworthiness Directive AD 2000–20–15, Amendment 39–11926 (65 FR 60349, October 11, 2000) (AD 2000–20–15); and ■ b. Adding the following new airworthiness directive: ■ ■ 2022–21–02 Airbus SAS: Amendment 39– 22201; Docket No. FAA–2022–0986; Project Identifier MCAI–2021–01440–T. (a) Effective Date This airworthiness directive (AD) is effective December 14, 2022. (b) Affected ADs This AD replaces AD 2000–20–15, Amendment 39–11926 (65 FR 60349, October 11, 2000) (AD 2000–20–15). (c) Applicability This AD applies to Airbus SAS airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as specified in European Union Aviation Safety Agency (EASA) AD 2021–0288, dated December 21, 2021 (EASA AD 2021–0288). (1) Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (2) Model A300 B4–603 and B4–622 airplanes. (3) Model A300 B4–605R and B4–622R airplanes. (4) Model A300 F4–605R airplanes. khammond on DSKJM1Z7X2PROD with RULES (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by cracking of the rear fittings of fuselage frame FR40 at stringer 27, and a determination that reduced compliance times are necessary. The FAA is issuing this AD to address fatigue cracking of the rear fittings of fuselage frame FR40 at stringer 27, which could result in reduced structural integrity of the airplane. VerDate Sep<11>2014 16:01 Nov 08, 2022 Jkt 259001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2021– 0288. (h) Exceptions to EASA AD 2021–0288 (1) Where paragraph (1) of EASA AD 2021– 0288 specifies, for certain conditions, using the compliance time and repetitive intervals ‘‘in the applicable SB,’’ and where ‘‘the applicable SB’’ specifies that the ‘‘1st inspection will be done within [a specified number of flight cycles] after receipt of the Service Bulletin,’’ this AD requires compliance within the specified number of flight cycles after the effective date of this AD. (2) Where EASA AD 2021–0288 refers to its effective date, this AD requires using the effective date of this AD. (3) The ‘‘Remarks’’ section of EASA AD 2021–0288 does not apply to this AD. (i) No Reporting Requirement Although the service information referenced in EASA AD 2021–0288 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Additional 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 (k) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. (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. (k) Additional Information For more information about this AD, contact Dan Rodina, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3225; email dan.rodina@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 67547 (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. (3) The following service information was approved for IBR on December 14, 2022. (i) European Union Aviation Safety Agency (EASA) AD 2021–0288, dated December 21, 2021. (ii) [Reserved] (4) For EASA AD 2021–0288, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; website easa.europa.eu. You may find this EASA AD on the EASA website at ad.easa.europa.eu. (5) 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. (6) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on September 28, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–24310 Filed 11–8–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2022–0243; Airspace Docket No. 22–AGL–5] RIN 2120–AA66 Amendment of VOR Federal Airways V–26 and V–63; Establishment of Area Navigation (RNAV) Route T–464; and Revocation of the Wausau, WI, Low Altitude Reporting Point; in the Vicinity of Wausau, WI Federal Aviation Administration (FAA), DOT. ACTION: Final rule; correction. AGENCY: This action corrects a final rule published by the FAA in the Federal Register on October 31, 2022, that amends VHF Omnidirectional Range (VOR) Federal airways V–26 and V–63; establishes Area Navigation (RNAV) route T–464; and revokes the Wausau, WI, Low Altitude Reporting Point in the vicinity of Wausau, WI. In the new RNAV route T–464, the final rule identified the TONOC, WI, route SUMMARY: E:\FR\FM\09NOR1.SGM 09NOR1

Agencies

[Federal Register Volume 87, Number 216 (Wednesday, November 9, 2022)]
[Rules and Regulations]
[Pages 67545-67547]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-24310]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0986; Project Identifier MCAI-2021-01440-T; 
Amendment 39-22201; AD 2022-21-02]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2000-20-
15, which applied to certain Airbus SAS Model A300 and A300-600 series 
airplanes. AD 2000-20-15 required a high frequency eddy current (HFEC) 
inspection to detect cracking of the rear fittings of fuselage frame 
FR40 at stringer 27, and repetitive inspections or repair, as 
applicable. In lieu of accomplishing the repetitive inspections, AD 
2000-20-15 provided a modification that would allow the inspection to 
be deferred for a certain period of time. This AD was prompted by 
cracking of the rear fittings of fuselage frame FR40 at stringer 27, 
and a determination that reduced compliance times are necessary. This 
AD removes airplanes from the applicability, and continues to require 
the actions in AD 2000-20-15, but at reduced compliance times, 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 December 14, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 14, 
2022.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2022-0986; 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 mandatory continuing airworthiness 
information (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.
    Material Incorporated by Reference:
     For material incorporated by reference 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 IBR material on the EASA website at 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. It is also available in the AD docket at 
regulations.gov under Docket No. FAA-2022-0986.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, Large

[[Page 67546]]

Aircraft Section, FAA, International Validation Branch, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2000-20-15, Amendment 39-11926 (65 FR 
60349, October 11, 2000) (AD 2000-20-15). AD 2000-20-15 applied to 
certain Airbus SAS Model A300 and A300-600 series airplanes. AD 2000-
20-15 required a HFEC inspection to detect cracking of the rear 
fittings of fuselage frame FR40 at stringer 27, and repetitive 
inspections or repair, as applicable. In lieu of accomplishing the 
repetitive inspections, AD 2000-20-15 provides a modification that 
would allow the inspection to be deferred for a certain period of time. 
The FAA issued AD 2000-20-15 to address fatigue cracking of the rear 
fittings of fuselage frame FR40 at stringer 27, which could result in 
reduced structural integrity of the airplane.
    The NPRM published in the Federal Register on August 2, 2022 (87 FR 
47144). The NPRM was prompted by EASA AD 2021-0288, dated December 21, 
2021, issued by the European Union Aviation Safety Agency (referred to 
after this as the MCAI). The MCAI states that cracking of the rear 
fittings of fuselage frame FR40 at stringer 27 was found, and a 
determination made that reduced compliance times are necessary.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2022-0986.
    In the NPRM, the FAA proposed to continue to require the actions in 
AD 2000-20-15, but at reduced compliance times, as specified in EASA AD 
2021-0288, dated December 21, 2021. The NPRM also proposed to remove 
airplanes from the applicability, as specified in EASA AD 2021-0288. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from the Air Line Pilots Association, 
International (ALPA), and FedEx Express, who supported the NPRM without 
change.

Conclusion

    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 reviewed the relevant data, considered the 
comment[s] received, and determined that air safety requires adopting 
this AD as proposed. Accordingly, the FAA is issuing this AD to address 
the unsafe condition on this product. Except for minor editorial 
changes, this AD is adopted as proposed in the NPRM. None of the 
changes will increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    EASA AD 2021-0288 specifies procedures for repetitive inspections 
of the rear fittings of fuselage frame FR40 at stringer 27 for 
cracking, and repair of any cracking. 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 67 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                            Cost per
            Action                     Labor cost          Parts cost        product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection....................  6 work-hours x $85 per               $0            $510  $34,170, per inspection
                                 hour = $510.                                             cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repair 
based on the results of any required inspection. The FAA has no way of 
determining the number of aircraft that might need this repair:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
31 work-hours x $85 per hour = $2,635.            $132           $2,767
------------------------------------------------------------------------

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

[[Page 67547]]

    (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

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:
0
a. Removing Airworthiness Directive AD 2000-20-15, Amendment 39-11926 
(65 FR 60349, October 11, 2000) (AD 2000-20-15); and
0
b. Adding the following new airworthiness directive:

2022-21-02 Airbus SAS: Amendment 39-22201; Docket No. FAA-2022-0986; 
Project Identifier MCAI-2021-01440-T.

(a) Effective Date

    This airworthiness directive (AD) is effective December 14, 
2022.

(b) Affected ADs

    This AD replaces AD 2000-20-15, Amendment 39-11926 (65 FR 60349, 
October 11, 2000) (AD 2000-20-15).

(c) Applicability

    This AD applies to Airbus SAS airplanes identified in paragraphs 
(c)(1) through (4) of this AD, certificated in any category, as 
specified in European Union Aviation Safety Agency (EASA) AD 2021-
0288, dated December 21, 2021 (EASA AD 2021-0288).
    (1) Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 
airplanes.
    (2) Model A300 B4-603 and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R airplanes.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by cracking of the rear fittings of 
fuselage frame FR40 at stringer 27, and a determination that reduced 
compliance times are necessary. The FAA is issuing this AD to 
address fatigue cracking of the rear fittings of fuselage frame FR40 
at stringer 27, which could result in 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 paragraphs (h) and (i) of this AD: Comply 
with all required actions and compliance times specified in, and in 
accordance with, EASA AD 2021-0288.

(h) Exceptions to EASA AD 2021-0288

    (1) Where paragraph (1) of EASA AD 2021-0288 specifies, for 
certain conditions, using the compliance time and repetitive 
intervals ``in the applicable SB,'' and where ``the applicable SB'' 
specifies that the ``1st inspection will be done within [a specified 
number of flight cycles] after receipt of the Service Bulletin,'' 
this AD requires compliance within the specified number of flight 
cycles after the effective date of this AD.
    (2) Where EASA AD 2021-0288 refers to its effective date, this 
AD requires using the effective date of this AD.
    (3) The ``Remarks'' section of EASA AD 2021-0288 does not apply 
to this AD.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2021-0288 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(j) Additional 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 (k) of this 
AD. Information may be emailed to: [email protected].
    (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.

(k) Additional Information

    For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, Large Aircraft Section, FAA, International 
Validation Branch, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3225; email [email protected].

(l) 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.
    (3) The following service information was approved for IBR on 
December 14, 2022.
    (i) European Union Aviation Safety Agency (EASA) AD 2021-0288, 
dated December 21, 2021.
    (ii) [Reserved]
    (4) For EASA AD 2021-0288, 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.
    (5) 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.
    (6) You may view this material that is incorporated by reference 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, email 
[email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on September 28, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-24310 Filed 11-8-22; 8:45 am]
BILLING CODE 4910-13-P
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