[Federal Register Volume 87, Number 135 (Friday, July 15, 2022)]
[Rules and Regulations]
[Pages 42315-42318]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-15189]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0468; Project Identifier MCAI-2021-01243-T; 
Amendment 39-22115; AD 2022-14-10]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-13-
08, which applied 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 2018-13-08 required repetitive inspections for cracking of the 
radius of the front spar vertical stringers and the horizontal floor 
beam on frame (FR) 36, repetitive inspections for cracking of the 
fastener holes of the front spar vertical stringers on FR 36, and 
repair if necessary, and, for certain airplanes, a potential 
terminating action modification of the center wing box area. This AD 
was prompted by a determination that additional airplanes are subject 
to the unsafe condition. This AD revises the applicability by adding 
airplanes and retains the requirements of AD 2018-13-08; 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 August 19, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 19, 
2022.

ADDRESSES: For material incorporated by reference (IBR) in this AD, 
contact 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 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 https://www.regulations.gov by searching for and locating 
Docket No. FAA-2022-0468.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0468; 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.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
Large Aircraft Section, International Validation Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198; phone 206-231-3229; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2021-0241, dated November 8, 2021 
(EASA AD 2021-0241) (also referred to as the MCAI), to correct an 
unsafe condition 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, -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 AD 
therefore does not include those airplanes in the applicability.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2018-13-08,

[[Page 42316]]

Amendment 39-19320 (83 FR 33809, July 18, 2018) (AD 2018-13-08). AD 
2018-13-08 applied 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. 
The NPRM published in the Federal Register on April 22, 2022 (87 FR 
24081). The NPRM was prompted by a report that, during a center 
fuselage certification full-scale fatigue test, cracks were found on 
the front spar vertical stringer at a certain frame. The NPRM was also 
prompted by a determination that Model A321 airplanes that have 
incorporated modification 160021 are also subject to the unsafe 
condition. The NPRM proposed to revise the applicability by adding 
airplanes and retain the requirements of AD 2018-13-08, as specified in 
EASA AD 2021-0241.
    The FAA is issuing this AD to address fatigue cracking of the front 
spar vertical stringers on the wings, which, if not corrected, could 
result in the reduced structural integrity of the airplane. See the 
MCAI for additional background information.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from United Airlines who supported the 
NPRM without change.

Conclusion

    The FAA reviewed the relevant data, considered the comment 
received, and determined that air safety requires adopting this AD as 
proposed. 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. Accordingly, the FAA is issuing this AD to 
address the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    EASA AD 2021-0241 describes procedures for repetitive special 
detailed inspections for cracking of the radius of the front spar 
vertical stringers, horizontal floor beam radius and fastener holes of 
the front spear vertical stringers on frame 36. EASA AD 2021-0241 
further describes procedures for repetitive high frequency eddy current 
(HFEC) inspections for cracking of the horizontal floor beam, 
repetitive HFEC inspections for cracking of the fastener holes of the 
front spar vertical stringers on FR 36, repetitive rototest inspections 
of the fastener holes of the spar vertical stringers, and repair. EASA 
AD 2021-0241 also describes procedures for the modification of the 
center wing box area. The modification is required for airplanes in 
configuration 1, 2 or 3; and for airplanes in configuration 5, 6, or 7, 
the modification is optional and is a terminating action for the 
repetitive inspections when done within a specified time frame. The 
modification includes related investigative and corrective actions. 
Related investigative actions include an HFEC inspection on the radius 
of the rib flanges, a rototest inspection of the fastener holes, 
detailed and HFEC inspections for cracking on the cut edges, detailed 
and rototest inspections on all open fastener holes, and an inspection 
to determine if secondary structure brackets are installed. Corrective 
actions include reworking the secondary structure bracket and repair. 
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 1,549 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                                          Estimated Costs for Required Actions
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               Action                      Labor cost                  Parts cost                  Cost per product            Cost on U.S. operators
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Retained actions from AD 2018-03-08  Up to 273 work-hours x  $87,500......................  Up to $110,705...............  Up to $1,107,050 for certain
                                      $85 per hour =                                                                        airplanes.*
                                      $23,205.
New inspections....................  25 work-hours x $85     $100.........................  $2,225.......................  $3,446,525.
                                      per hour = $2,125.
New modification (5 airplanes).....  Up to 403 work-hours x  Up to $316,900...............  Up to $351,1555..............  Up to $1,755,775.
                                      $85 per hour =
                                      $34,255.
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* This estimate is based on the determination in AD 2018-13-08 that only 10 airplanes of U.S. registry needed to accomplish all required actions,
  including the modification; other airplanes were only required to accomplish the terminating actions.


                  Estimated Costs for Optional Actions
------------------------------------------------------------------------
         Labor cost                Parts cost         Cost per product
------------------------------------------------------------------------
Up to 409 work-hours x $85    Up to $66,050.......  Up to $100,815.
 per hour = $34,765.
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    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition actions 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

[[Page 42317]]

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.

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) 2018-13-08, Amendment 39-
19320; (83 FR 33809, July 18, 2018); and
0
b. Adding the following new AD:

2022-14-10 Airbus SAS: Amendment 39-22115; Docket No. FAA-2022-0468; 
Project Identifier MCAI-2021-01243-T.

(a) Effective Date

    This airworthiness directive (AD) is effective August 19, 2022.

(b) Affected ADs

    This AD replaces AD 2018-13-08, Amendment 39-19320 (83 FR 33809, 
July 18, 2018) (AD 2018-13-08).

(c) Applicability

    This AD applies to the 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 2021-0241, dated November 8, 2021 (EASA AD 2021-0241).
    (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 57, Wings.

(e) Reason

    This AD was prompted by a report that, during a center fuselage 
certification full-scale fatigue test, cracks were found on the 
front spar vertical stringer at a certain frame. This AD was also 
prompted by a determination that Model A321 airplanes that have 
incorporated modification 160021 are also subject to the unsafe 
condition. The FAA is issuing this AD to address fatigue cracking of 
the front spar vertical stringers on the wings, which, if not 
corrected, could result in the 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 paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2021-0241.

(h) Exceptions to EASA AD 2021-0241

    (1) Where EASA AD 2021-0241 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2021-0241 does not apply 
to this AD.
    (3) Where paragraph (3) of EASA AD 2021-0241 specifies actions 
for airplanes repaired ``in accordance with instructions approved by 
EASA or approved under Airbus DOA,'' for this AD use ``using a 
method approved by the Manager, Large Aircraft Section, 
International Validation Branch, FAA; or EASA; or Airbus SAS's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.''
    (4) Where paragraph (4) of EASA AD 2021-0241 specifies to 
``contact Airbus for approved corrective action instructions and 
accomplish those instructions accordingly'' if cracks are detected, 
for this AD if any cracking is detected, the cracking must be 
repaired before further flight using a method approved by the 
Manager, Large Aircraft Section, International Validation Branch, 
FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (5) Where paragraph (8) of EASA AD 2021-0241 specifies actions 
for airplanes inspected by additional instructions ``approved before 
the effective date of this AD by Airbus DOA,'' for this AD use 
``approved before the effective date of this AD by the Manager, 
Large Aircraft Section, International Validation Branch, FAA; or 
EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature.''

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2021-0241 
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, 
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].
    (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 2018-13-08 are approved as 
AMOCs for the corresponding provisions of EASA AD 2021-0241 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, 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 (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) Related Information

    For more information about this AD, contact Vladimir Ulyanov, 
Aerospace Engineer, Large Aircraft Section, International Validation 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone 206-
231-3229; 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.
    (i) European Union Aviation Safety Agency (EASA) AD 2021-0241, 
dated November 8, 2021.

[[Page 42318]]

    (ii) [Reserved]
    (3) For EASA AD 2021-0241, contact 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.
    (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 June 29, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-15189 Filed 7-14-22; 8:45 am]
BILLING CODE 4910-13-P