[Federal Register Volume 89, Number 32 (Thursday, February 15, 2024)]
[Rules and Regulations]
[Pages 11720-11722]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-03080]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-2136; Project Identifier MCAI-2023-00759-T; 
Amendment 39-22659; AD 2024-01-08]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-16-
11, which applied to certain Airbus SAS Model A300 F4-605R and FR-622R 
airplanes. AD 2019-16-11 required repetitive high frequency eddy 
current (HFEC) inspections of the aft lower deck cargo door (LDCD) 
frame forks; a one-time check of the LDCD clearances; a one-time 
detailed visual inspection of hooks, eccentric bushes, and x-stops; and 
corrective actions if necessary. This AD was prompted by a 
determination that the threshold for the (repetitive) HFEC inspection 
needs to be corrected, and the LDCD frame forks modified. This AD 
continues to require the actions in AD 2019-16-11, requires correcting 
the HFEC inspection threshold and modifying the LDCD frame forks, and 
prohibits the installation of affected LDCDs under certain conditions; 
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 21, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 21, 
2024.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2023-2136; 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:
    <bullet> For EASA material identified in this final rule, contact 
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email <a href="/cdn-cgi/l/email-protection#1a5b5e695a7f7b697b347f6f68756a7b347f6f"><span class="__cf_email__" data-cfemail="88c9ccfbc8ede9fbe9a6edfdfae7f8e9a6edfd">[email protected]</span></a>; website easa.europa.eu. You may 
find this material on the EASA website ad.easa.europa.eu.
    <bullet> You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th Street, 
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-2023-2136.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-
231-3225; email <a href="/cdn-cgi/l/email-protection#ddb9bcb3f3afb2b9b4b3bc9dbbbcbcf3bab2ab"><span class="__cf_email__" data-cfemail="096d6867277b666d606768496f6868276e667f">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

[[Page 11721]]

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2019-16-11, Amendment 39-19714 (84 FR 
45061, August 28, 2019) (AD 2019-16-11). AD 2019-16-11 applied to 
certain Airbus SAS Model A300 F4-605R and F4-622R airplanes. AD 2019-
16-11 required repetitive HFEC inspections of the aft LDCD frame forks; 
a one-time check of the LDCD clearances; a one-time detailed visual 
inspection of hooks, eccentric bushes, and x-stops; and corrective 
actions if necessary. The FAA issued AD 2019-16-11 to address cracked 
or ruptured aft LDCD frames, which could allow loads to be transferred 
to the remaining structural elements. This condition could lead to the 
rupture of one or more vertical aft LDCD frames, which could result in 
reduced structural integrity of the aft LDCD.
    The NPRM published in the Federal Register on October 31, 2023 (88 
FR 74369). The NPRM was prompted by AD 2023-0117, dated June 13, 2023, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union (EASA AD 2023-0117) (also referred to as the MCAI). 
The MCAI states that based on more detailed stress analyses, it has 
been determined that the threshold for the (repetitive) HFEC inspection 
could be extended from 12,500 flight hours to 26,455 flight hours for 
those affected parts installed on an LDCD that has been modified or 
replaced. It was also determined that an incorrect HFEC inspection 
threshold had been defined for the affected parts that have not been 
modified or replaced. Additional widespread fatigue damage analysis 
determined that all frame forks of affected LDCDs are susceptible to 
crack development, which compromises the structural integrity of the 
LDCD and therefore of the airplane.
    In the NPRM, the FAA proposed to continue to require the actions in 
AD 2019-16-11 and require correcting the HFEC inspection threshold, 
modifying the LDCD frame forks, and prohibit the installation of 
affected LDCDs under certain conditions, as specified in EASA AD 2023-
0117. The FAA is issuing this AD to address the unsafe condition on 
these products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2023-2136.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from FedEx Express and the Air Line 
Pilots Association, International (ALPA), 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 
comments 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 2023-0117 specifies procedures for repetitive HFEC 
inspections for cracks of the aft LDCD frame forks; a one-time check of 
the LDCD clearances; a one-time detailed visual inspection for signs of 
wear on the hooks, eccentric bushes, and x-stops; and corrective 
actions if necessary. In addition, EASA AD 2023-0117 specifies 
procedures for modifying frame forks that have not been reinforced. 
EASA AD 2023-0117 also prohibits the installation of affected LDCDs 
under certain conditions.
    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 58 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2019-16-  15 work-hours x $85              $0  $1,275.............  $73,950.
 11.                                per hour = $1,275.
New actions......................  Up to 38 work-hours             850  Up to $4,080.......  Up to $236,640.
                                    x $85 per hour =
                                    $3,230.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for certain on-condition repairs specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    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.

[[Page 11722]]

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 2019-16-11, Amendment 39-19714 (84 
FR 45061, August 28, 2019); and
0
b. Adding the following new Airworthiness Directive:

2024-01-08 Airbus SAS: Amendment 39-22659; Docket No. FAA-2023-2136; 
Project Identifier MCAI-2023-00759-T.

(a) Effective Date

    This airworthiness directive (AD) is effective March 21, 2024.

(b) Affected ADs

    This AD replaces AD 2019-16-11, Amendment 39-19714 (84 FR 45061, 
August 28, 2019) (AD 2019-16-11).

(c) Applicability

    This AD applies to Airbus SAS Model A300 F4-605R and F4-622R 
airplanes, certificated in any category, as identified in European 
Union Aviation Safety Agency (EASA) AD 2023-0117, dated June 13, 
2023 (EASA AD 2023-0117).

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of two adjacent frame forks 
that were found cracked on the aft lower deck cargo door (LDCD) of 
two airplanes during scheduled maintenance, and a determination that 
certain compliance times need to be revised. The FAA is also issuing 
this AD to address the susceptibility of the frame forks of affected 
LDCDs to develop cracks, which could lead to additional rupture of 
one or more LDCD frame forks, compromising the structural integrity 
of the LDCD and therefore of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2023-0117.

(h) Exceptions to EASA AD 2023-0117

    (1) Where EASA AD 2023-0117 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where Table 2 of EASA AD 2023-0117 refers to the effective 
date of EASA AD 2015-0152R1, dated May 23, 2017, this AD requires 
using November 5, 2018 (the effective date of AD 2018-20-06, 
Amendment 39-19440 (83 FR 49265, October 1, 2018)).
    (3) Where Table 2 of EASA AD 2023-0117 refers to the effective 
date of EASA AD 2015-0152, dated July 24, 2015, this AD requires 
using January 26, 2017 (the effective date of AD 2016-25-03, 
Amendment 39-18729 (81 FR 93801, December 22, 2016)).
    (4) Where paragraph (6) of EASA AD 2023-0117 uses the phrase 
``before next flight, contact Airbus for approved corrective action 
instructions, and within the compliance time specified therein, 
accomplish those instructions accordingly,'' this AD requires 
replacing those words with ``repair cracking before further flight 
using a method approved by the Manager, International Validation 
Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization 
Approval (DOA). If approved by the DOA, the approval must include 
the DOA-authorized signature.''
    (5) This AD does not adopt the ``Remarks'' section of EASA AD 
2023-0117.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2023-0117 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(j) Additional AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Validation Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or responsible Flight Standards Office, as 
appropriate. If sending information directly to the International 
Validation Branch, send it to the attention of the person identified 
in paragraph (k) of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#caf3e78b9c99e78b8398e7fdf9fae78b8785898aacababe4ada5bc"><span class="__cf_email__" data-cfemail="764f5b3720255b373f245b4145465b373b39353610171758111900">[email protected]</span></a>. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the responsible Flight Standards Office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (h)(4) and (j)(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.

(k) Additional Information

    For more information about this AD, contact Dan Rodina, Aviation 
Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 206-231-3225; email <a href="/cdn-cgi/l/email-protection#9cf8fdf2b2eef3f8f5f2fddcfafdfdb2fbf3ea"><span class="__cf_email__" data-cfemail="5d393c33732f323934333c1d3b3c3c733a322b">[email protected]</span></a>.

(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.
    (i) European Union Aviation Safety Agency (EASA) AD 2023-0117, 
dated June 13, 2023.
    (ii) [Reserved]
    (3) For EASA AD 2023-0117, contact EASA, Konrad-Adenauer-Ufer 3, 
50668 Cologne, Germany; telephone +49 221 8999 000; email 
<a href="/cdn-cgi/l/email-protection#92d3d6e1d2f7f3e1f3bcf7e7e0fde2f3bcf7e7"><span class="__cf_email__" data-cfemail="dd9c99ae9db8bcaebcf3b8a8afb2adbcf3b8a8">[email protected]</span></a>; website easa.europa.eu. You may find this EASA 
AD on the EASA website ad.easa.europa.eu.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 2200 
South 216th Street, Des Moines, WA. For information on the 
availability of this material at the FAA, call 206-231-3195.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations, or email <a href="/cdn-cgi/l/email-protection#2d4b5f0344435e5d484e594442436d434c5f4c034a425b"><span class="__cf_email__" data-cfemail="b7d1c599ded9c4c7d2d4c3ded8d9f7d9d6c5d699d0d8c1">[email protected]</span></a>.

    Issued on January 9, 2024.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2024-03080 Filed 2-14-24; 8:45 am]
BILLING CODE 4910-13-P


</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>