Document ID: FAA-2023-0165-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2023-02-15T05:00Z

[Federal Register Volume 88, Number 31 (Wednesday, February 15, 2023)]
[Proposed Rules]
[Pages 9776-9779]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-03141]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-0165; Project Identifier MCAI-2022-01003-T]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2019-24-13, which applies to certain Airbus SAS Model A318 series 
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. AD 2019-24-13 requires repetitive high-frequency eddy 
current (HFEC) inspections for cracking of a stiffener of a certain 
lateral window frame, and applicable related investigative and 
corrective actions, as applicable. Since the FAA issued AD 2019-24-13, 
it was determined that certain inspection times need to be revised. 
This proposed AD would retain the requirements of AD 2019-24-13, with 
amended compliance times, as specified in a European Union Aviation 
Safety Agency (EASA) AD, which is proposed for incorporation by 
reference (IBR). The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by April 3, 
2023.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to regulations.gov. Follow 
the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2023-0165; or in person at Docket Operations between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this NPRM, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For EASA material that is proposed for IBR in this NPRM, 
you may contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 8999 000; email [email protected]; website 
easa.europa.eu. You may find this material on the EASA website at 
ad.easa.europa.eu. It is also available at regulations.gov under Docket 
No. FAA-2023-0165.
     You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 2200 South 
216th St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, Large 
Aircraft Section, International Validation Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone 206-231-3225; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2023-0165; Project Identifier 
MCAI-2022-01003-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to Dan 
Rodina, Aerospace Engineer, Large Aircraft Section, International 
Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone 206-231-3225; email [email protected]. Any commentary that 
the FAA receives which is not specifically designated as CBI will be 
placed in the public docket for this rulemaking.

Background

    The FAA issued AD 2019-24-13, Amendment 39-21002 (84 FR 71788, 
December 30, 2019) (AD 2019-24-13), for certain Airbus SAS Model A318 
series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes. AD 2019-24-13 was prompted by an MCAI originated by 
EASA, which is the Technical Agent for the Member States of the 
European Union. EASA issued AD 2019-0067R1, dated September 11, 2019 
(EASA AD 2019-0067R1), to correct an unsafe condition.
    AD 2019-24-13 requires repetitive HFEC inspections for cracking of 
a stiffener of a certain lateral window frame, and rework, repair, or 
replacement of the lateral window frame, as applicable, as specified in 
EASA AD 2019-0067R1. The FAA issued AD 2019-24-13 to address cracking 
of the horizontal upper stiffener of the lateral window frame, which 
could reduce the structural integrity of the fuselage.

[[Page 9777]]

Actions Since AD 2019-24-13 Was Issued

    Since the FAA issued AD 2019-24-13, EASA superseded EASA AD 2019-
0067R1 and issued EASA AD 2022-0151, dated July 26, 2022 (EASA AD 2022-
0151) (also referred to as the MCAI), to correct an unsafe condition on 
certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -
113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, 
-214, -215, -216, -231, -232, and -233 airplanes; and Model A321-111, -
112, -131, -211, -212, -213, -231, and -232 airplanes. Model A320-215 
airplanes are not certificated by the FAA and are not included on the 
U.S. type certificate data sheet; this proposed AD therefore does not 
include those airplanes in the applicability. The MCAI states that 
several occurrences were reported where, during a maintenance check, 
cracks were found in the horizontal upper stiffener of the lateral 
window frame at the frame 4 upper attachment. Since EASA AD 2019-0067R1 
was issued, it was determined that the embodiment of Airbus production 
modification (mod) 161229 does not provide any benefit versus the pre-
mod 161229 configuration, and Airbus issued revised service information 
to remove the credit and higher inspection threshold for post-mod 
161229 airplanes. In addition, based on new calculations, the 
inspection interval was increased. The unsafe condition, if not 
addressed, could reduce the structural integrity of the fuselage.
    The FAA is proposing this AD to address cracking of the horizontal 
upper stiffener of the lateral window frame, which could reduce the 
structural integrity of the fuselage. You may examine the MCAI in the 
AD docket at regulations.gov under Docket No. FAA-2023-0165.

Explanation of Retained Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2019-24-13, this proposed AD would retain the 
requirements of AD 2019-24-13. Those requirements are referenced in 
EASA AD 2022-0151, which, in turn, is referenced in paragraph (g) of 
this proposed AD.

Related Service Information Under 1 CFR Part 51

    EASA AD 2022-0151 specifies procedures for repetitive HFEC 
inspections of the horizontal upper stiffener of the lateral window 
frame on the right-hand (RH) and left-hand (LH) sides for any cracking 
and applicable related investigative and corrective actions. Related 
investigative and corrective actions include repair, replacement, and 
rework. EASA AD 2022-0151 also specifies reporting to Airbus if any 
discrepancies (cracking) are found during the inspections.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

FAA's Determination

    This product has been approved by the aviation authority of another 
country and is approved for operation in the United States. Pursuant to 
the FAA's bilateral agreement with the State of Design Authority, it 
has notified the FAA of the unsafe condition described in the MCAI 
referenced above. The FAA is issuing this NPRM after determining that 
the unsafe condition described previously is likely to exist or develop 
in other products of the same type design.

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2022-0151 described previously, except for any differences 
identified as exceptions in the regulatory text of this proposed AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2022-0151 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2022-0151 in its entirety through that incorporation, except 
for any differences identified as exceptions in the regulatory text of 
this proposed AD. Using common terms that are the same as the heading 
of a particular section in EASA AD 2022-0151 does not mean that 
operators need comply only with that section. For example, where the AD 
requirement refers to ``all required actions and compliance times,'' 
compliance with this AD requirement is not limited to the section 
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2022-
0151. Service information required by EASA AD 2022-0151 for compliance 
will be available at regulations.gov under Docket No. FAA-2023-0165 
after the FAA final rule is published.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 1,528 airplanes of U.S. registry. The FAA estimates the 
following costs to comply with this proposed AD:

                                      Estimated Costs for Required Actions
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                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2019-24-13...  9 work-hours x $85 per                $0            $765        $987,615
                                         hour = $765.
New proposed actions..................  6 work-hours x $85 per                $0            $510        $779,280
                                         hour = $510.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition rework, replacement, or reporting that would be required 
based on the results of any required actions. The FAA has no way of 
determining the number of aircraft that might need these on-condition 
actions:

[[Page 9778]]

                Estimated Costs of On-Condition Actions *
------------------------------------------------------------------------
                                                             Cost per
            Labor cost                   Parts cost           product
------------------------------------------------------------------------
Up to 543 work-hours x $85 per      Up to $107,370......        $153,525
 hour = $46,155.
------------------------------------------------------------------------
* The FAA has received no definitive data on which to base the cost
  estimates for the on-condition repairs specified in this proposed AD.

    According to the manufacturer, some or all of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected individuals. The FAA does not control warranty 
coverage for affected individuals. As a result, the FAA has included 
all known costs in the cost estimate.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to take 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, and completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Send comments regarding this burden estimate 
or any other aspect of this collection of information, including 
suggestions for reducing this burden, to: Information Collection 
Clearance Officer, Federal Aviation Administration, 10101 Hillwood 
Parkway, Fort Worth, TX 76177-1524.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2019-24-13, Amendment 39-21002 
(84 FR 71788, December 30, 2019); and
0
b. Adding the following new AD:

Airbus SAS: Docket No. FAA-2023-0165; Project Identifier MCAI-2022-
01003-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by April 3, 2023.

(b) Affected ADs

    This AD replaces AD 2019-24-13, Amendment 39-21002 (84 FR 71788, 
December 30, 2019).

(c) Applicability

    This AD applies to Airbus SAS airplanes identified in paragraphs 
(c)(1) through (4) of this AD, certificated in any category, as 
identified in European Union Aviation Safety Agency (EASA) AD 2022-
0151, dated July 26, 2022 (EASA AD 2022-0151).
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report that during a maintenance 
check, cracks were found in the horizontal upper stiffener of the 
lateral window frame at the frame 4 upper attachment, and a 
determination that certain compliance times need to be revised. The 
FAA is issuing this AD to address cracking of the horizontal upper 
stiffener of the lateral window frame. The unsafe condition, if not 
addressed, could reduce the structural integrity of the fuselage.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2022-0151.

(h) Exceptions to EASA AD 2022-0151

    (1) Where EASA AD 2022-0151 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) This AD does not adopt the ``Remarks'' section of EASA AD 
2022-0151.
    (3) Paragraph (7) of EASA AD 2022-0151 specifies to report 
inspection results to Airbus within a certain compliance time. For 
this AD, report inspection results at the applicable time specified 
in paragraph (h)(3)(i) or (ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report

[[Page 9779]]

within 90 days after the effective date of this AD.
    (4) Where EASA AD 2022-0151 specifies to perform corrective 
actions if ``discrepancies are detected, as identified in the 
inspection SB,'' for this AD perform corrective actions if cracking 
is detected.
    (5) Where paragraph (2) of EASA AD 2022-0151 specifies to 
``accomplish the applicable corrective action(s)'' if discrepancies 
are detected, for this AD if any cracking is detected and the 
stiffener has already been reworked, or if any cracking is not 
removed after a third rework of the horizontal upper stiffener, the 
cracking must be repaired before further flight using a method 
approved by the Manager, International Validation Branch, FAA; or 
EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(i) Additional AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Validation Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or responsible Flight Standards Office, as 
appropriate. If sending information directly to the 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].
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the responsible Flight Standards Office.
    (ii) AMOCs approved previously for AD 2019-24-13 are approved as 
AMOCs for the corresponding provisions of EASA AD 2022-0151 that are 
required by paragraph (g) of this AD.
    (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 
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) Additional Information

    For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, Large Aircraft Section, International Validation 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
206-231-3225; 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 2022-0151, 
dated July 26, 2022.
    (ii) [Reserved]
    (3) For EASA AD 2022-0151, contact EASA, Konrad-Adenauer-Ufer 3, 
50668 Cologne, Germany; telephone +49 221 8999 000; email 
[email protected]; website easa.europa.eu. You may find this EASA 
AD on the EASA website at ad.easa.europa.eu.
    (4) You may view this service information 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 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 [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on February 9, 2023.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-03141 Filed 2-14-23; 8:45 am]
BILLING CODE 4910-13-P