[Federal Register Volume 87, Number 143 (Wednesday, July 27, 2022)]
[Rules and Regulations]
[Pages 45013-45015]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-16060]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0457; Project Identifier MCAI-2022-00263-T; 
Amendment 39-22125; AD 2022-15-05]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) 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. This AD was prompted 
by a report that cracks were found on the web horizontal flange and 
inner cap on a certain frame (FR), left-hand (LH) and right-hand (RH) 
sides, at a certain stringer (STGR). This AD requires repetitive high 
frequency eddy current (HFEC) inspections for cracks on the web 
horizontal flange and inner cap, and applicable corrective actions, 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 31, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 31, 
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 www.regulations.gov by searching for and locating Docket No. 
FAA-2022-0457.

Examining the AD Docket

    You may examine the AD docket at www.regulations.gov by searching 
for and locating Docket No. FAA-2022-0457; 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: Dan Rodina, Aerospace Engineer, Large 
Aircraft Section, International Validation Branch, FAA, 2200 South 
216th Street, Des Moines, WA 98198; telephone 206-231-3225; email 
[email protected].

SUPPLEMENTARY INFORMATION: 

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2022-0030, dated February 25, 2022 
(EASA AD 2022-0030) (also referred to as the MCAI), to correct an 
unsafe condition for certain Airbus SAS Model A318-111, A318-112, A318-
121, A318-122, A319-111, A319-112, A319-113, A319-114, A319-115, A319-
131, A319-132, A319-133, A320-211, A320-212, A320-214, A320-215, A320-
216, A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-
211, A321-212, A321-213, A321-231, and A321-232 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 FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain Airbus SAS 
Model A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, A319-
113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-211, A320-
212, A320-214, A320-216, A320-231, A320-232, A320-233, A321-111, A321-
112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 
airplanes. The NPRM published in the Federal Register on April 14, 2022 
(87 FR 22156). The NPRM was prompted by a report that during the 
inspection for the door stop fitting holes at FR 66 and FR 68 required 
by EASA AD 2016-0238, dated December 2, 2016; corrected January 4, 2017 
(which corresponds to FAA AD 2018-03-12, Amendment 39-19185 (83 FR 
5906, February 12, 2018)); cracks were found on the web

[[Page 45014]]

horizontal flange and inner cap on FR 68, LH and RH sides, at STGR 22. 
The NPRM proposed to require repetitive HFEC inspections for cracks on 
the web horizontal flange and inner cap on FR 68, LH and RH sides, at 
STGR 22, and applicable corrective actions (e.g., repairs), as 
specified in EASA AD 2022-0030.
    The FAA is issuing this AD to address the cracks on the web 
horizontal flange and inner cap on FR 68, LH and RH sides, at STGR 22, 
which could result in reduced structural integrity of the fuselage. See 
the MCAI for additional background information.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from United Airlines, who supported the 
NPRM without change.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety requires adopting this AD as 
proposed. Except for minor editorial changes, and any other changes 
described previously, 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 2022-0030 specifies procedures for repetitive HFEC 
inspections for cracks at the web horizontal flange and inner cap on FR 
68, LH and RH sides, at STGR 22, and applicable corrective actions 
(e.g., repairs).
    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.

Costs of Compliance

    The FAA estimates that this AD affects 1,585 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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                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
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28 work-hours x $85 per hour = $2,380........................              $0           $2,380       $3,772,300
----------------------------------------------------------------------------------------------------------------

    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 
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 adding the following new airworthiness 
directive:

2022-15-05 Airbus SAS: Amendment 39-22125; Docket No. FAA-2022-0457; 
Project Identifier MCAI-2022-00263-T.

(a) Effective Date

    This airworthiness directive (AD) is effective August 31, 2022.

(b) Affected ADs

    None.

 (c) Applicability

    This AD applies to Airbus SAS airplanes specified in paragraphs 
(c)(1) through (4) of this AD, certificated in any category, as 
identified in European Union Aviation Safety Agency (EASA) AD 2022-
0030, dated February 25, 2022 (EASA AD 2022-0030).
    (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 cracks were found on the 
web horizontal flange and inner cap on frame (FR) 68, left-hand (LH) 
and right-hand (RH) sides, at stringer (STGR) 22. The FAA is issuing 
this AD to address the cracks on the web horizontal flange and inner 
cap on FR 68, LH and RH sides, at STGR 22, which could result in 
reduced structural integrity of the fuselage.

(f) Compliance

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

[[Page 45015]]

(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 2022-0030.

(h) Exceptions to EASA AD 2022-0030

    (1) Where EASA AD 2022-0030 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2022-0030 does not apply 
to this AD.
    (3) Where paragraph (2) of EASA AD 2022-0030 specifies 
``Accomplishment on an aeroplane of (repetitive) maintenance 
instructions, issued and approved by Airbus,'' for this AD, those 
instructions must have been 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.
    (4) Where paragraph (3) of EASA AD 2022-0030 specifies if 
``discrepancies and/or cracks are detected, before next flight, 
contact Airbus for approved corrective action(s) instructions and, 
within the compliance time specified therein, accomplish those 
instructions accordingly,'' for this AD, if cracks are detected, the 
cracks 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 (4) of EASA AD 2022-0030 specifies ``the 
instructions provided by Airbus,'' for this AD, those instructions 
must be 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.

(i) 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 of the 
certification office, send it to the attention of the person 
identified in paragraph (j) of this AD. Information may be emailed 
to: [email protected]. 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, 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.
    (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) Related Information

    For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, Large Aircraft Section, International Validation 
Branch, FAA, 2200 South 216th Street, 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 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 2022-0030, 
dated February 25, 2022.
    (ii) [Reserved]
    (3) For EASA AD 2022-0030, 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: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 8, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-16060 Filed 7-26-22; 8:45 am]
BILLING CODE 4910-13-P


