[Federal Register Volume 87, Number 232 (Monday, December 5, 2022)]
[Rules and Regulations]
[Pages 74294-74296]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-26356]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1155; Project Identifier MCAI-2022-00655-T; 
Amendment 39-22243; AD 2022-24-03]
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 all 
Airbus SAS Model A321-251N, A321-251NX, A321-252N, A321-252NX, A321-
253N, and A321-253NX airplanes. This AD was prompted by a stress 
analysis on the engine structure that indicated that the fail-safe lug 
may not be able to sustain, during one inspection interval as currently 
specified in an airworthiness limitations item, the loads deriving from 
the engagement of the secondary load path within that inspection 
interval for the aft engine mount system. This AD requires repetitive 
detailed inspections of the aft engine mount and secondary load path 
clearance fail-safe pin and replacement of the engine if necessary, 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 January 9, 2023.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 9, 
2023.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2022-1155; or in person at Docket Operations between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket

[[Page 74295]]

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.
    Material Incorporated by Reference:
     For material incorporated by reference in this AD, 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.
     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 
regulations.gov under Docket No. FAA-2022-1155.

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

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Airbus SAS Model 
A321-251N, A321-251NX, A321-252N, A321-252NX, A321-253N, and A321-253NX 
airplanes. The NPRM published in the Federal Register on September 12, 
2022 (87 FR 55737). The NPRM was prompted by AD 2022-0089, dated May 
17, 2022, issued by EASA, which is the Technical Agent for the Member 
States of the European Union (referred to after this as the MCAI). The 
MCAI states that the engine fail safe lug may not be able to sustain, 
during one inspection interval as currently specified in airworthiness 
limitation item (ALI) task 712232-01-1, the loads deriving from the 
engagement of the secondary load path. This condition, if not detected 
and corrected, could lead to engine mount rupture, possibly resulting 
in engine loss during flight and loss of control of the airplane.
    In the NPRM, the FAA proposed to require repetitive detailed 
inspections of the aft engine mount and secondary load path clearance 
fail-safe pin and replacement of the engine if necessary, as specified 
in EASA AD 2022-0089. The FAA is issuing this AD to address the unsafe 
condition on these products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2022-1155.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from Air Line Pilots Association, 
International (ALPA) and an anonymous commenter. Both commenters 
supported the NPRM without change.

Conclusion

    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 this State of Design Authority, it 
has notified the FAA of the unsafe condition described in the MCAI 
referenced above. The FAA reviewed the relevant data, considered the 
comments received, and determined that air safety requires adopting 
this AD as proposed. Accordingly, the FAA is issuing this AD to address 
the unsafe condition on this product. 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.

Related Service Information Under 1 CFR Part 51

    EASA AD 2022-0089 specifies procedures for repetitive detailed 
inspections (DET) for discrepancies of the aft engine mount and 
secondary load path clearance fail-safe pin for each engine, and 
replacement of any engine with discrepant findings on the secondary 
load path clearance check.
    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 156 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
               Labor cost                   Parts cost         Cost per product         Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 4 work-hours x $85 per hour = $340              $0  Up to $340................  Up to $53,040.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates that it would take 64 work-hours (at $85 per 
work-hour) to replace an engine, if required based on the results of 
any required actions. The FAA has received no definitive data on which 
to base the estimate for the cost of a replacement engine or any 
necessary additional on-condition actions that would be required by 
this AD. The FAA has no way of determining the number of aircraft that 
might need these on-condition actions.

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

[[Page 74296]]

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:

2022-24-03 Airbus SAS: Amendment 39-22243; Docket No. FAA-2022-1155; 
Project Identifier MCAI-2022-00655-T.

(a) Effective Date

    This airworthiness directive (AD) is effective January 9, 2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A321-251N, A321-251NX, 
A321-252N, A321-252NX, A321-253N, and A321-253NX airplanes, 
certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Unsafe Condition

    This AD was prompted by a stress analysis on the engine 
structure that indicated that the fail-safe lug may not be able to 
sustain, during one inspection interval, as currently specified in 
airworthiness limitation item (ALI) task 712232-01-1, the loads 
deriving from the engagement of the secondary load path within that 
inspection interval for the aft engine mount system. The FAA is 
issuing this AD to address potential failure of the LEAP-1A aft 
engine mount waiting fail-safe male lug, which could lead to engine 
mount rupture, possibly resulting in engine loss during flight and 
loss of control 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, European Union Aviation Safety Agency (EASA) AD 
2022-0089, dated May 17, 2022 (EASA AD 2022-0089).

(h) Exceptions to EASA AD 2022-0089

    (1) Where paragraph (3) of EASA AD 2022-0089 specifies 
corrective action if ``discrepancies are detected, as defined in the 
SB,'' for purposes of this AD, discrepancies include a fail-safe pin 
that does not rotate freely, or has damage (dents, scratches, nicks, 
corrosion, or cracks).
    (2) The ``Remarks'' section of EASA AD 2022-0089 does not apply 
to this AD.

(i) Additional AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 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 (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 Design Organization Approval (DOA). If approved by the 
DOA, the approval must include the DOA-authorized signature.

(j) Additional 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 2022-0089, 
dated May 17, 2022.
    (ii) [Reserved]
    (3) For EASA AD 2022-0089, 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 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 November 9, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-26356 Filed 12-2-22; 8:45 am]
BILLING CODE 4910-13-P


