Rule2022-15189
Airworthiness Directives; Airbus SAS Airplanes
Primary source
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Published
July 15, 2022
Effective
August 19, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 87 Issue 135 (Friday, July 15, 2022)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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 <a href="/cdn-cgi/l/email-protection#c78683b487a2a6b4a6e9a2b2b5a8b7a6e9a2b2"><span class="__cf_email__" data-cfemail="94d5d0e7d4f1f5e7f5baf1e1e6fbe4f5baf1e1">[email protected]</span></a>; internet
www.easa.europa.eu. You may find this IBR material on the EASA website
at <a href="https://ad.easa.europa.eu">https://ad.easa.europa.eu</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating
Docket No. FAA-2022-0468.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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
<a href="/cdn-cgi/l/email-protection#ceb8a2afaaa7a3a7bce0bba2b7afa0a1b88ea8afafe0a9a1b8"><span class="__cf_email__" data-cfemail="aadcc6cbcec3c7c3d884dfc6d3cbc4c5dceacccbcb84cdc5dc">[email protected]</span></a>.
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
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Labor cost Parts cost Cost per product
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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: <a href="/cdn-cgi/l/email-protection#a89185e9fefb85e9e1fa859f9b9885e9e5e7ebe8cec9c986cfc7de"><span class="__cf_email__" data-cfemail="ac9581edfaff81ede5fe819b9f9c81ede1e3efeccacdcd82cbc3da">[email protected]</span></a>.
(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 <a href="/cdn-cgi/l/email-protection#57213b36333e3a3e2579223b2e363938211731363679303821"><span class="__cf_email__" data-cfemail="f6809a97929f9b9f84d8839a8f97989980b6909797d8919980">[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 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
<a href="/cdn-cgi/l/email-protection#b5f4f1c6f5d0d4c6d49bd0c0c7dac5d49bd0c0"><span class="__cf_email__" data-cfemail="a2e3e6d1e2c7c3d1c38cc7d7d0cdd2c38cc7d7">[email protected]</span></a>; internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at <a href="https://ad.easa.europa.eu">https://ad.easa.europa.eu</a>.
(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
<a href="/cdn-cgi/l/email-protection#1a7c68347374696a7f796e7375745a747b687b347d756c"><span class="__cf_email__" data-cfemail="6402164a0d0a17140107100d0b0a240a0516054a030b12">[email protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
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
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