[Federal Register Volume 87, Number 88 (Friday, May 6, 2022)]
[Proposed Rules]
[Pages 27032-27035]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-08909]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0503; Project Identifier MCAI-2021-01244-T]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2018-03-12, 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, -231, -232, and -233 airplanes; 
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. AD 2018-03-12 requires repetitive rototest inspections for 
cracking of the fastener holes in certain door stop fittings, and 
repair if necessary. Since the FAA issued AD 2018-03-12, new analysis 
by the manufacturer resulted in optimized compliance times for the 
inspections. This proposed AD would require repetitive rototest 
inspections for cracking of the fastener holes in certain door stop 
fittings at revised compliance times, and corrective actions if 
necessary, as specified in a European Union Aviation Safety Agency 
(EASA) AD, which is proposed for incorporation by reference. 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 June 21, 
2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For material that will be 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#0544417645606476642b6070776a75642b6070"><span class="__cf_email__" data-cfemail="fcbdb88fbc999d8f9dd299898e938c9dd29989">[email protected]</span></a>; 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 IBR 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 on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0503.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2022-
0503; 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, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
Large Aircraft Section, International Validation Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198; telephone 206-231-3229; email 
<a href="/cdn-cgi/l/email-protection#b8ced4d9dcd1d5d1ca96cdd4c1d9d6d7cef8ded9d996dfd7ce"><span class="__cf_email__" data-cfemail="bbcdd7dadfd2d6d2c995ced7c2dad5d4cdfbdddada95dcd4cd">[email protected]</span></a>.

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-2022-0503; Project Identifier 
MCAI-2021-01244-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 
the 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 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposed AD.

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

[[Page 27033]]

NPRM. Submissions containing CBI should be sent to Vladimir Ulyanov, 
Aerospace Engineer, Large Aircraft Section, International Validation 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 206-
231-3229; email <a href="/cdn-cgi/l/email-protection#3f49535e5b5652564d114a53465e5150497f595e5e11585049"><span class="__cf_email__" data-cfemail="97e1fbf6f3fefafee5b9e2fbeef6f9f8e1d7f1f6f6b9f0f8e1">[email protected]</span></a>. Any commentary that the FAA 
receives which is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Discussion

    The FAA issued AD 2018-03-12, Amendment 39-19185 (83 FR 5906, 
February 12, 2018) (AD 2018-03-12), 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, -231, -232, 
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes. AD 2018-03-12 requires repetitive rototest 
inspections for cracking of the fastener holes in certain door stop 
fittings, and repair if necessary. The FAA issued AD 2018-03-12 to 
address cracking at the door stop fitting holes of fuselage frame (FR) 
66 and FR68. Such cracking could result in reduced structural integrity 
of the airplane due to the failure of structural components.

Actions Since AD 2018-03-12 Was Issued

    Since the FAA issued AD 2018-03-12, Airbus has revised the 
compliance times to accomplish the rototest inspections based on 
reports from operators and new analysis.
    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2021-0242, dated November 8, 2021 
(EASA AD 2021-0242) (also referred to as the Mandatory Continuing 
Airworthiness Information, or 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. EASA AD 
2021-0242 supersedes EASA AD 2016-0238 (which corresponds to FAA AD 
2018-03-12). 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.
    This proposed AD was prompted by reports of fatigue damage in the 
structure for the door stop fittings on certain fuselage frames. The 
FAA is proposing this AD to address cracking at the door stop fitting 
holes of fuselage FR66 and FR68 which could result in reduced 
structural integrity of the airplane. See the MCAI for additional 
background information.

Model A320-216 Airplanes

    The Airbus SAS Model A320-216 was U.S. type certificated on 
December 19, 2016. Before that date, any EASA ADs that affected Model 
A320-216 airplanes were included in the U.S. type certificate as part 
of the Required Airworthiness Actions List (RAAL). One or more Model 
A320-216 airplanes have subsequently been placed on the U.S. Register, 
and will now be included in FAA AD actions. For Model A320-216 
airplanes, the requirements that correspond to AD 2018-03-12 were 
mandated by the MCAI via the RAAL. Although that RAAL requirement is 
still in effect, for continuity and clarity the FAA has identified 
Model A320-216 airplanes in paragraph (c) of this proposed AD; the MCAI 
that is specified in paragraph (g) in this proposed AD includes 
retained requirements, which would therefore apply to those airplanes.

Explanation of Retained Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2018-03-12, this proposed AD would retain all of the 
requirements of AD 2018-03-12. Those requirements are referenced in 
EASA AD 2021-0242, which, in turn, is referenced in paragraph (g) of 
this proposed AD.

Related Service Information Under 1 CFR Part 51

    EASA AD 2021-0242 describes procedures for rototest inspections for 
cracking of the fastener holes in the airframe structure for the door 
stop fittings installation in FR66 and FR68, and corrective actions. 
Corrective actions include repair or modification of fastener holes at 
door stop locations.
    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 and Requirements of This Proposed AD

    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, 
the FAA has been notified of the unsafe condition described in the MCAI 
referenced above. The FAA is proposing this AD because the FAA 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2021-0242 described previously, as incorporated by 
reference, 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 2021-0242 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2021-0242 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 2021-0242 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 2021-
0242. Service information required by EASA AD 2021-0242 for compliance 
will be available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2022-0503 after the FAA final rule is 
published.

Costs of Compliance

    The FAA estimates that this proposed AD affects 1,084 airplanes of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

[[Page 27034]]



                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
            Action                Labor cost      Parts cost       Cost per  product     Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Inspections..................  Up to 25 work-               $0  Up to $2,125..........  Up to $2,303,500.
                                hours x $85
                                per hour =
                                $2,125.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition modifications 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 modifications:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
Up to 27 work-hours x $85 per hour =              $610           $2,905
 $2,295...............................
------------------------------------------------------------------------

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

    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) 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 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) 2018-03-12, Amendment 39-19185 
(83 FR 5906, February 12, 2018); and
0
b. Adding the following new AD:

Airbus SAS: Docket No. FAA-2022-0503; Project Identifier MCAI-2021-
01244-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by June 21, 2022

(b) Affected ADs

    This AD replaces AD 2018-03-12, Amendment 39-19185 (83 FR 5906, 
February 12, 2018) (AD 2018-03-12).

(c) Applicability

    This AD applies to Airbus SAS Model 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 2021-0242, dated November 8, 2021 (EASA AD 2021-0242).
    (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) Reason

    This AD was prompted by reports of fatigue damage in the 
structure for the door stop fittings on certain fuselage frames, and 
new analysis by the manufacturer, which resulted in optimized 
compliance times for the inspections. The FAA is issuing this AD to 
address cracking at the door stop fitting holes of fuselage frame 
(FR) 66 and FR68, which could result in 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 2021-0242.

(h) Exceptions to EASA AD 2021-0242

    (1) Where EASA AD 2021-0242 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2021-0242 does not apply 
to this AD.
    (3) Where paragraph (3) of EASA AD 2021-0242 specifies if any 
crack is found during any inspection to ``contact Airbus for 
approved instructions for corrective actions and accomplish those 
instructions accordingly,'' this AD requires if any cracking is 
found, 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 
Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (4) Where paragraphs (2), (3), (5), and (5.1) of EASA AD 2021-
0242 specify limits or actions in ``the applicable SRM'' or ``the

[[Page 27035]]

SRM,'' for purposes of this AD, replace those phrases with the 
following phrase: ``the applicable SRM as specified in the 
instructions of the inspection SB.''

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2021-0242 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(j) Other FAA 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)(2) of 
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#172e3a5641443a565e453a2024273a565a58545771767639707861"><span class="__cf_email__" data-cfemail="f1c8dcb0a7a2dcb0b8a3dcc6c2c1dcb0bcbeb2b1979090df969e87">[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 2018-03-12 are approved as 
AMOCs for the corresponding provisions of EASA AD 2021-0242 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): For any service information 
referenced in EASA AD 2021-0242 that contains RC procedures and 
tests: Except as required by paragraph (j)(2) of this AD, RC 
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

    (1) For information about EASA AD 2021-0242 contact EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email <a href="/cdn-cgi/l/email-protection#cf8e8bbc8faaaebcaee1aababda0bfaee1aaba"><span class="__cf_email__" data-cfemail="3170754271545042501f5444435e41501f5444">[email protected]</span></a>; internet www.easa.europa.eu. You 
may find this EASA AD 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. This material may be 
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2022-0503.
    (2) 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; 
telephone 206-231-3229; email <a href="/cdn-cgi/l/email-protection#97e1fbf6f3fefafee5b9e2fbeef6f9f8e1d7f1f6f6b9f0f8e1"><span class="__cf_email__" data-cfemail="7c0a101d181511150e520910051d12130a3c1a1d1d521b130a">[email protected]</span></a>.

    Issued on April 21, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-08909 Filed 5-5-22; 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>